WO/1995/032896 | AEROSPACE TRANSPORT SYSTEM |
WO/2009/068488 | SPACECRAFT AFTERBODY DEVICE |
WO/2021/058356 | DEVICE TRANSPORT BY AIR |
US20140260930A1 | 2014-09-18 | |||
US20180362191A1 | 2018-12-20 | |||
US5097743A | 1992-03-24 |
CLAIMS What is claimed is: 1. A system comprising: a pre‐launch system comprising; a launch tube having a launch tube entry and a launch tube exit; a ram accelerator system comprising: a first section having a first end and a second end, wherein the first end is proximate to the launch tube exit; a second section having a third end and a fourth end, wherein the third end is proximate to the second end; a first fill stage having a fifth end and a sixth end, wherein the fifth end is proximate to the second end and the sixth end is proximate to the third end; a first valve between the fifth end and the second end; and a second valve between the sixth end and the third end; a gas control system; and a control system in communication with the pre‐launch system and the ram accelerator system, the control system to: operate the first valve and the second valve to close; operate the gas control system to fill the first fill stage with a first gas; operate the first valve to open; operate the second valve to open; and initiate operation of the pre‐launch system to launch a projectile. 2. The system of claim 1 wherein the control system operates the first valve and the second valve to open and operates the pre‐launch system such that as the projectile enters the first section, the first gas moves past the projectile, resulting in a relative velocity of the first gas with respect to the projectile that is a sum of a projectile velocity and a gas velocity. 3. The system of claim 1 or claim 2 wherein the control system operates the first valve and the second valve to open and operates the pre‐launch system such that as the projectile enters the second section, the first gas moves in a same direction as the projectile, resulting in a relative velocity of the first gas with respect to the projectile that is a difference of a projectile velocity and a gas velocity. 4. The system of any of claims 1‐3, further comprising an exit diaphragm proximate to an exit of a section of the ram accelerator system to a surrounding environment, wherein the exit diaphragm is penetrated by the projectile. 5. The system of any of claims 1‐4, wherein the first section is evacuated before initiation of the pre‐ launch system to launch the projectile. 6. The system of any of claims 1‐5, wherein the first section contains the first gas before initiation of the pre‐launch system to launch the projectile. 7. The system of any of claims 1‐6, wherein one or more of the first section or the second section are at a specified temperature before initiation of the pre‐launch system. 8. The system of any of claims 1‐7, wherein the first gas is at a specified temperature before initiation of the pre‐launch system. 9. The system of any of claims 1‐8, the ram accelerator system comprising at least one baffle tube section comprising a plurality of baffles. 10. The system of any of claims 1‐9, the ram accelerator system comprising a plurality of baffles and a plurality of rails, wherein the plurality of rails are mechanically engaged to the plurality of baffles and the rails constrain movement of the projectile within the ram accelerator system. 11. The system of any of claims 1‐10, the pre‐launch system further comprising: the gas control system to provide pressurized gas to the launch tube; a third valve proximate to the launch tube entry, wherein the third valve is operable to provide an opening with a time‐variable cross‐sectional area between the gas control system and the launch tube; and the control system to: operate the third valve to provide: a first specified mass flow of launch gas through the third valve and into the launch tube at a first time, and a second specified mass flow of launch gas through the third valve and into the launch tube at a second time. 12. The system of any of claims 1‐11, the projectile comprising a space vehicle. 13. A method comprising: pressurizing, with a first gas, a first volume associated with a portion of a ram accelerator; releasing the first gas into a second volume, wherein the first gas in the second volume moves towards a projectile in the ram accelerator; and performing ram combustion of the first gas proximate to the projectile based on a relative velocity between the first gas and the projectile. 14. The method of claim 13, further comprising: evacuating the second volume before releasing the first gas into the second volume. 15. The method of claim 13 or claim 14, further comprising: accelerating, in a launch tube, the projectile to a first velocity; and passing the projectile into the second volume, wherein the releasing of the first gas is controlled such that the projectile enters the second volume and encounters an oncoming portion of the first gas. |
low‐pressure “evacuated” section in the launch tube between the breech and the start of the first ram accelerator stage allows the projectile to encounter low air resistance, reducing pressure and momentum lo sses against the projectile which allows the start gun to achieve the minimum initial velocity of the projectile necessary for successful ram accelerator operation. [0020] Traditional systems have also relied upon fixed frangible diaphragms to separate and pressurize gases in different stages. This has resu lted in time‐intensive operations to change out the diaphragm between uses, and has resulted in fouling of the ram accelerator with debris from these diaphragms. Replacement, cleaning, and other operations to make r eady are time consuming, costly, and may be impracti cal in situations where at least part of the ram accele rator is inaccessible. For example, if the ram acc elerator is constructed underground, access to a fouled portion m ay be limited. [0021] Described in this disclosure are systems and techniques for dynamic operation of a system comprising the pre‐launcher section and multiple ram accelerator sections. These techniques allow for c ontrol over the velocity of the projectile and control over a relative velocity of gas past the projectile. In one implementation, controlled pressurization and release o f gas at particular times and in a particular sequence results in the projectile entering the ram accelerato r system when the gas is rushing towards the projec tile. The initial velocity is attained by a combination of the projectile velocity plus the relative motion of the gas in the opposite direction. In another implementation, controlled pressurization and release may enable ram acceleration to start with the projectile at zero ve locity. [0022] The systems and techniques in this disclosure reduce or eliminate the need for the use of diaphragms or other consumable components. This redu ces the overall cost, increases launch frequency, and eliminates the need to mitigate fouling of the interior of the ram accelerator due to debris from those consumable components. For example, the system descr ibed may utilize valves that are operable to open a nd close. This provides a substantial operational and safety benefit: in addition to being reusable, the s ystem may be operated such that all valves are open before th e projectile begins moving. This eliminates the ris k of the projectile inadvertently striking a valve that is not fully opened, providing a crucial safety advantage. [0023] In some implementations an exit diaphragm may separat e an exit of the ram accelerator from the surrounding environment. In this implementation, the projectile exits the ram accelerator by penetrat ing the exit diaphragm. As the exit diaphragm is at t he end of the ram accelerator, debris from the exit diaphragm is shed outward, avoiding fouling of the ram acceler ator. [0024] Also described in this disclosure are techniques for further controlling the relative velocity between the projectile and the surrounding gas. As described above, one implementation lowers the veloci ty requirements of the projectile upon exit from the pre‐launch system by using a relative motion of the gas towards the projectile, reaching the initial velocity for ram combustion to begin. Propagation of the g as may also be controlled to facilitate transition between d ifferent gas mixtures and further improve efficiency and may also smooth out acceleration. For example, a portion of the ram accelerator may be operated to produce a relative velocity of the gas in the same direction as the projectile, reducing the relative velocity of the projectile with respect to the surrounding gas. While still a bove the initial velocity, the relative velocity is lowered resulting in improved efficiency.
[0025] In some implementations hydrostatic pressure at an ex it end of a ram accelerator or drift tube stage may be used to limit movement of materials be tween the interior of the ram accelerator and the e xterior environment. For example, at least a portion of th e pressurized gas that is released towards the proje ctile to produce the relative motion mentioned above may also be released towards an exit end of the ram acceler ator, producing pressure on materials such as contaminants, water, and so forth that are at least partially wi thin the exit end of the ram accelerator. This pressure wou ld displace the materials from the exit tube before the arrival of the projectile. In some implementations the dist ribution of pressurized gas within the ram accelerato r may be asymmetrical. For example, one or more of a la rger pressure or mass of pressurized gas may be dis pensed towards the projectile than toward the exit end, or vice versa. [0026] In some implementations, gases having different densit ies may be used to provide a density gradient inside the ram accelerator tube exit or drift tube. For example, the temperature of the gases, or composition may be controlled to provide a desired d ensity gradient. This gradient may be used to modi fy the rate of change of acceleration, or “jerk”, as th e projectile transitions to high‐speed exit into a denser surrounding atmosphere. This manages acceleration experienced by the projectile and associated payload. [0027] Other implementations are also discussed herein. Dif ferent aspects of the implementations described herein may be used in different combination s. [0028] The dynamic ram accelerator also enables a rapid lau nch cadence. The projectiles and the fuel mixture used during ram acceleration may be reloaded relatively quickly. Reusable valves may remove the need for consumable diaphragms within the ram accelerator. The operation of the dynamic ram accelerator is inherently safe in that all reusable valves may be opened before the initiation of the ram acceleration, ensuring the projectile is unobstructed from exiting. [0029] By using the system and techniques described in this disclosure, a dynamic ram accelerator may be used to launch a projectile at lower or zer o initial velocity, and provide a smoother accelerati on over time and lower transient accelerations compared to a conventional ram accelerator. As a result, more se nsitive payloads may be included in the projectile. For ex ample, human passengers, delicate mechanisms, and so forth may be included in the projectile. As a result, i t is now feasible to launch such payloads on a sub orbital or orbital trajectory. For example, the dynamic ram accelerator may be used to launch a projectile comprising a c rewed space vehicle on a suborbital trajectory. A boost or “kick” rocket attached to the space vehicle, or rendezvoused with the space vehicle after launch, may then be us ed to place the space vehicle into orbit. DETAILED DESCRIPTION [0030] FIG. 1 is an illustrative system 100 comprising a dynamic ram accelerator 102. In some implementations, the dynamic ram accelerator 102 is p laced above, or having at least a portion located w ithin, a geologic material or body of water. In other im plementations, the dynamic ram accelerator 102 may be a free‐ flying structure, such as in space. The dynamic ra m accelerator 102 has a body 108. The body 108 m ay comprise one or more materials such as steel, carbon fiber, ceramics, and so forth.
[0031] The dynamic ram accelerator 102 includes a pre‐laun ch system 110. The pre‐launch system 110 may include one or more of a gas gun, electromagnetic launcher, solid explosive charge, liquid explosive charge, backpressure system, and so forth. The pre‐launch system 110 may comprise a launch tube 116. A projectile 118 may be placed within the launch tube 116 before launch. During operation, the pre‐laun ch system 110 may operate to accelerate a projectile 118 into the launch tube 116 of a ram acceleration system 1 24. In some implementations, at least a portion of the launch tube 116 within the pre‐launch system 110 may be evacuated to maintain a vacuum prior to launch. [0032] In one example depicted here the pre‐launch system 110 comprises a detonation ga s gun, including an igniter 112 coupled to a chamber 114. The chamber 114 may be configured to contain one or more combustible, explosive, or detonable materials which, when triggered by the igniter 112, generate an energ etic reaction. The gases may include pressurized air, or inert gases. In the gas gun implementation depict ed, the chamber 114 is coupled to a launch tube 116 within which the projectile 118 is placed. In some imple mentations, the projectile 118 may include or be adjacent to an obturator 120 configured to seal, at least temporar ily, the chamber 114 from the launch tube 116. The obturator 120 may be attached, integrated but frangible, or separate from but in‐contact with the projectile 11 8. One or more blast vents 122 may provide releas e of the reaction byproducts. In some implementations the lau nch tube 116 may be smooth, rifled, include one or more guide rails or other guide features, and so forth. The projectile 118 may include one or more features that engage the guide rails. [0033] The launch tube 116, or portions thereof, may be ma intained at a pressure which is lower than that of standard atmosphere. For example, portions of the launch tube 116 such as those in the pre‐launch system 110 may be evacuated to a pressure of less than 25 torr. [0034] The pre‐launch system 110 is configured to initiate a ram effect with the projectile 118 in conjunction with a relative velocity differential of one or more combustible gases flowing past the proje ctile 118. The ram effect results in compression of one or more combustible gases by interaction with surfaces of the projectile 118 and subsequent combustion proximate to a back (aft) side of the projectile 118. This co mpression results in heating of the one or more combustible gases, triggering or sustaining ignition. The ignited gases combusting in an exothermic reaction impart an impuls e on the projectile 118 which is accelerated down t he launch tube 116. In some implementations ignition m ay be assisted or initiated using a pyrotechnic igni ter. The pyrotechnic igniter may either be affixed to or a p ortion of the projectile 118, or may be arranged wi thin the launch tube 116. [0035] The pre‐launch system 110 may use an electromagnetic, solid explosive charge, liquid explosive charge, stored compressed gases, and so for th to propel the projectile 118 from rest along the launch tube 116 to achieve the initial ram velocity. [0036] In some implementations the one or more combustible gases may move past a stationary projectile 118, producing the ram effect in an initi ally stationary projectile 118. For example, the co mbustible gas mixture under high pressure may be exhausted pas t the projectile 118 as it rests within the launch tube 116. This relative velocity difference achieves the ram ve locity from a zero velocity projectile 118, and the ram effect of combustion begins and pushes the projectile 118 d own the launch tube 116. Hybrid systems may also be
used, in which the projectile 118 is moved using the pre‐launch system 110 and relative velocity of gas flowing towards the projectile 118 simultaneously. [0037] The projectile 118 passes along the launch tube 116 from the pre‐launch system 110 into a ram acceleration system 124 comprising one or more s ections 190. Each section 190 may be bounded by s ection separator mechanisms 126. The section separator mechanism 126 provides a barr ier to movement of gases between sections 190 which allows for the tailoring of the acceleration profile of the projectile 118 as it transits through the ram accelerator system 124. For ease o f discussion and not as a limitation, the section s eparator mechanism 126 may be referred to as a “valve”. In some implementations the valve may be reusable, such as with a ball valve, clamshell valve, gate valve, and so forth. In other implementations the valve may comprise a diaphragm or single‐use device. Valves may be mechanical, pneumatic, electrical, magnetic, chemical, pyrotechnical, and so forth. [0038] The section separator mechanisms 126 may include valves such as ball valves, diaphragms, gravity gradient, liquids, or other structures or materials configured to maintain the different mixtures of combustible gas 128 substantially within their respect ive sections 190. [0039] A gas 128 may be admitted into a respective section via one or more gas inlet valves 130 associated with the particular section 190. Each of the different sections 190 may have a dif ferent gas 128, mixture of gas 128, gas 128 at different temperature s, and so forth. [0040] The gas 128 may include one or more combustible gas es, combustible materials in suspension within the gas, diluents, and so forth. The one o r more combustible gases may include an oxidizer or an oxidizing agent. For example, the gas 128 may include hydrog en and oxygen gas in a ratio of 2:1 and may inclu de an inert gas such as nitrogen, carbon dioxide, or helium. In other examples, the gas 128 may comprise methan e and oxygen, methane and ambient air, propane and oxygen, and so forth. Other combustible gas 128 mixtures may be diluted with non‐combustible gases such as silan e and carbon dioxide. In some implementations a ga s and a solid may be used. For example, the gas 128 may comprise a gaseous o xidizer with suspended fuel particles such as jet‐A or diesel, a gaseous fuel with susp ended oxidizer particles, and so forth. [0041] The gas 128 may be provided by extraction from ambient atmosphere, electrolysis of a material such as water, from a solid or liquid gas generator using solid materials which react chemicall y to release a combustible gas, from a previously stored gas or liquid, and so forth. [0042] The mixture of gas 128 used may be the same or ma y differ between the sections 190. These differences include chemical composition, pressure, tem perature, and so forth. For example, the density o f the gas 128 in each of the sections 190(1)‐(4) may de crease along the launch tube 116, such that the sec tion 190(1) holds the gas 128 at a higher pressure than the se ction 190(4). In another example, the gas 128(1) i n the section 190(1) may comprise oxygen and propane while the gas 128(3) may comprise oxygen and hydrogen. [0043] In this illustration four sections 190(1)‐(4) are d epicted, as maintained by five section separator mechanisms 126(1)‐(5). When ready for operation, s ome of the sections 190 may be selectively filled w ith gas 128, while others are evacuated. While four sections 190(1)‐(4) are depicted, in other implementations, different numbers of sections 190, section separator mechanisms 126, and so forth may be used. The sys tem
100 may also include additional components not dep icted in FIG. 1, such as reservoirs. Reservoirs ar e discussed in more detail with regard to FIG. 5. [0044] One or more sensors 132 may be configured at one o r more positions along the dynamic ram accelerator 102. These sensors may include pressure sensors, chemical sensors, density sensors, fatigue s ensors, strain gauges, velocity sensors, accelerometers, proxim ity sensors, and so forth. [0045] The dynamic ram accelerator 102 is configured to eject the projectile 118 from an exit or ejection end. In some implementations the exit may be closed by a section separator mechanism 126 that is reusable, such as a ball valve that is opened befor e passage of the projectile 118, or a consumable di aphragm that is broken before or penetrated by the projectile 118 which exits the system and emerges into the surrounding environment at supersonic or hypersonic ve locity. [0046] During normal operation, the dynamic ram accelerator 102 may accelerate the projectile 118 to a hypervelocity. As used in this disclosure, hypervelocity includes velocities greater than or equal to two kilometers per second upon ejection or exit from the dynamic ram accelerator 102. [0047] In other implementations, the projectile may accelerate to a non‐hypervelocity. Non‐ hypervelocity includes velocities below two kilometers per second. Hypervelocity and non‐hypervelocity ma y also be characterized based on interaction of the pr ojectile 118 with the surrounding material. For exa mple, given a relative velocity between the gas 128 and t he projectile 118 the projectile 118 operates at hyp ervelocity with ram combustion while the absolute velocity of t he projectile 118 with respect to the stationary pre ssure tube 160 is non‐hypervelocity. The pressure tube 160 comprises a structure that maintains the ram com bustion reaction and resulting stresses. [0048] For ease of discussion, and not necessarily as a li mitation unless otherwise indicated, as shown in this figure “upstream” refers to a direction along a longitudinal axis of the dynamic ram acceler ator 102 away from the exit of the dynamic ram accelerator 102 while “downstream” refers to a direction along this axis towards the exit of the dynamic ram accelerator 102. [0049] A gas control system 150 comprises one or more of valves, sensors, metering devices, gas mixing devices, and other equipment to dispense gas to one or more sections 190 for operation. In some implementations the gas control system 150 may includ e one or more of heating or refrigeration equipment to heat or cool the gas 128 to a specified temperature . The gas control system 150 is in communication with a control system 144. The gas control system 150 is connected via one or more passages, such as pipes, to supply tanks 152 or other sources of requisite gases for o peration. The gas control system 150 is also conne cted via one or more passages, such as pipes, to gas inlet valves 130(1), …, (N). In some circumstances the gas control system 150 may perform additional functions, such as evacuating a section 190 to a reduced pressure, rem oving gas 128 from the dynamic ram accelerator 102 followi ng an abort, and so forth. [0050] A control system 144 may be coupled to one or more of the dynamic ram accelerator 102, the gas control system 150, and so forth. The control system 144 may comprise one or more processors, mem ory, interfaces, and so forth which are configured to fac ilitate operation of the dynamic ram accelerator 102. The control system 144 may couple to the one or more s ection separator mechanisms 126, the gas inlet valves 130, and the sensors 132 to coordinate the configuration of the dynamic ram accelerator 102 for launch of the
projectile 118. For example, responsive to a control input specifying a desired trajectory at exit and gi ven a specified mass and shape of the projectile 118, the control system 144 may operate the gas control syst em 150 to fill a particular mixture of gas 128 into one o r more sections 190. [0051] During operation the control system 144 operates the gas control system 150 to selectively pressurize one or more portions of the dynamic ram accelerator 102. For example, one or more sections 190 that are downstream of the projectile 118 before lau nch may be pressurized. During the launch sequence one or more of the section separator mechanisms 126 are opened, permitting at least a portion of the gas 1 28 in that pressurized section 190 to be released and flow towards the projectile 118. This results in a re lative velocity difference between the projectile 118 and the onrushi ng gas 128. As a result, ram combustion may be i nitiated and maintained with the projectile 118 at a much lo wer velocity measured with respect to a stationary o bject, such as the pressure tube 160. Various aspects of this dynamic flow operation are discussed with respe ct to the following figures. In some implementations, the syst em 100 may be operated in a zero velocity start in which the projectile 118 remains stationary while the onrus hing gas 128 produces the start conditions for the desired ram combustion. [0052] Other mechanisms may be present which are not depict ed here. For example, an ejection system may be configured to divert or otherwise remo ve the projectile 118 from the dynamic ram accelerat or 102 in the event of an off‐nominal condition. In another example, an injection system may be configu red to add one or more materials into the wake of the projecti les 118. These materials may be used to clean the launch tube 116, remove debris, and so forth. [0053] FIG. 2 illustrates at 200 some portions of a dynami c ram accelerator 102, according to some implementations. A baffle tube section 202 comprises a plurality of baffles 206. In some implementations baffles 206 may be fabricated from a solid block of suitable material, such as steel. Monolithic segme nts (one or more baffles 206) are stacked together forming th e sequence of baffles 206. A variable baffle may be used for low‐speed start operations such as described he rein. [0054] A baffle tube section with rails 220 is also shown. In some implementations one or more rails 222 may be mounted proximate to or within the baffl es 206. The rails 220 may be used to maintain al ignment of the projectile 118 during passage through the dyn amic ram accelerator 102. [0055] In a first implementation 248 a pre‐launch system 110 may comprise a baffle tube section 202. For example, a zero velocity start system may utiliz e a baffle tube section 202 in conjunction with the relative velocity between the stationary projectile 118 and th e oncoming gas 128. Downstream of the baffle tube section 202 may be a smooth bore ram accelerator section 25 0. The smooth bore ram accelerator section 250 may omit the baffles 206. In some implementations, the smooth bore ram accele rator section 250 may include one or more rails 222. [0056] In a second implementation 258 the dynamic ram accel erator 102 may comprise a pre‐launch system 110 that includes a smooth bore launch tube 116. Downstream of the smooth bore launch tube 116 the dynamic ram accelerator 102 may comprise a smooth bo re ram accelerator section 250. Downstream of a fi rst smooth bore ram accelerator section 250(1) is a baff le tube section 252. Downstream of the baffle tube section 252 may be a second smooth bore ram accelerator sec tion 250(2).
[0057] Some implementations of components and construction of the baffle tube section with rails 220 are discussed in more detail with regard to FIG S. 7‐8. [0058] FIG. 3 illustrates at 300 an enlarged view of a po rtion of a dynamic ram accelerator 102 and the relative velocity between gas flow and projectile 118 at various portions, according to some implementations. For ease of illustration other elem ents of the system 100 have been omitted. A porti on of the dynamic ram accelerator 102 comprises a baffle t ube section 252. [0059] In this figure, the system is shown after pressuriza tion with gas 128 of fill stages 362(1) and 362(2), and subsequent opening of the section separat or mechanisms 126. When filled, the pressure within the fill stages 362 may exceed the pressure in the imme diately adjacent sections 190. When the section sep arator mechanism 126 between the fill stage 362 and the adjacent section 190 is opened, the pressurized gas 128 moves into the adjacent section 190 due to a pressu re gradient. Movement of the gas 128 is depicted by velocity of gas v g 350. In this illustration, the velocity of gas 350 is away from the initially pressurized fill stages 362 and towards the respective ends. As a result, a first portion of gas 128 is moving upstream while a seco nd portion of gas 128 is moving downstream. [0060] Also shown in this figure is the projectile 118 hav ing a non‐zero velocity of projectile vp 352. For example, the pre‐launch system 110 may have imparted some motion on the projectile 118 before en try into the ram acceleration system 124. [0061] By coordinating the pressurization and release of the fill stages 362, a relative velocity between the projectile 118 and the gas 128 may be created, resulting in a ram combustion effect. This occurs while the velocity of the projectile 118, with respect to a f ixed reference frame such as the pressure tube 160, is relatively low or zero. [0062] At different locations with respect to the dynamic r am accelerator 102 this movement of the gas 128 resulting from the pressure gradient produces different relative velocities. These relative veloc ities may be tailored to optimize ram combustion by the projectile 118 during passage through the ram acceleration system 124. For example, at time t=0 before the p rojectile 118 reaches the fill stage 362(1) that is proximate to the pre‐launch system 110, the projectile 118 encou nters onrushing gas 128. The resulting relative vel ocity of the gas 128 with respect to the projectile 118 is the velocity of gas v g1 350(1) summed with the velocity of the projectile v p 352. As a result, ram combustion begins soone r, reducing the necessary overall length of the typi cal non‐dynamic ram accelerator 102, requirements for th e pre‐launch system 110 (if any), reduction in tra nsient accelerations, and so forth, compared to traditional non‐dynamic ram accelerator operations. [0063] Continuing the example, at time t=1, the projectile 118 (not shown) has moved farther downstream, past the first fill stage 362(1) and the region, and begins to encounter the velocity of ga s 350(2) that is downstream. As a result, the resulting rel ative velocity of the gas 128 with respect to the projectile 118 is the difference between the velocity of gas v g2 350(2) and the velocity of the projectile v p 352. In some implementations this decrease in relative velocity dur ing later passage through the dynamic ram accelerator 102 is advantageous, as it maintains the projectile 118 at a relative velocity with respect to the gas 128 that provides improved ram combustion, improving overall efficiency.
[0064] The various mathematical signs of the operations described may be varied based on the coordinate system used and associated signs indicative of direction. For example, a downstream velocity may be deemed positive while an upstream velocity is neg ative. [0065] Various implementations of pressurization of fill stages 362 and release of the gases 128 contained therein may be utilized to facilitate vario us operations. Some implementations are discussed with regards to FIGS. 4‐6. [0066] FIGS. 4‐6 depict simplified schematics of a portion of the system 100 for ease of illustration in depicting a sequence of events, and not necessarily as a limitation. Times are depicted from t = 0 t o t = 5. These time labels are for description purposes and not by way of limitation. The actual duration of time between individual time labels may differ. For example, the duration of the interval between t=0 and t=1 may differ from the duration of the interval between time t=4 and t =5. [0067] Shading in these figures is provided to differentiate various elements, and is not necessarily indicative of other physical parameters, such as pres sure. [0068] Unless otherwise specified, the section separator mech anisms 126 are depicted as gate valves for clarity of illustration and not necessarily as a limitation. [0069] In some implementations, fill stages 362 may be pres surized, while sections 190 that are not used as fill stages 362 may be evacuated. [0070] The quantity and relative arrangement of section separator mechanisms 126 are for illustration only. In other implementations the system 100 may utilize greater or lesser numbers of section separator mechanisms 126. [0071] A projectile 118 is shown proximate to a first section separator mechanism 126 that may separate the ram acceleration system 124 from the pr e‐launch system 110. [0072] FIG. 4 illustrates at 400 a first implementation of operation of a dynamic ram accelerator system 100. In this implementation, the dynamic ram accelerator 102 incorporates one or more baffle tube sections 202 (not shown). [0073] At t=0 a first fill stage 362(1) comprising a porti on of the dynamic ram accelerator 102 that is bounded by section separator mechanisms 126(2) and 12 6(3), that are closed, is pressurized with gas 128(2 ). [0074] A second fill stage 362(2) comprising a portion of the dynamic ram accelerator 102 that is bounded by section separator mechanisms 126(3) and 12 6(4), that are closed, is pressurized with gas 128(3 ). [0075] A first section 190(1) bounded by section separator mechanisms 126(1) and 126(2), that are closed, may be evacuated. [0076] A fourth section 190(4) bounded by section separator mechanisms 126(4) and 126(5), that are closed, may be evacuated. The chamber 114 (or othe r launch mechanism) is pressurized or otherwise prime d for launch. The first section 190(1) is separated from the chamber 114 by a closed first section separator mechanism 126(1). In some implementations the fourth section 190(4) may omit baffles 206. [0077] The composition, pressure, temperature, or other param eters of the respective gas 128(2) or 128(3) may be the same or may differ.
[0078] At t=1 the section separator mechanism 126(3) is opened. If a pressure gradient exists between the first fill section 362(1) and the second fill section 362(2), one or more of the gas 128(2 ) or 128(3) may begin moving. [0079] At t=2 the section separator mechanism 126(2) is ope ned. A first pressure differential between one or more of the first fill section 362(1) or th e second fill section 362(2) relative to the first section 190(1) results in upstream movement of the gas 128 towards the projectile 118. [0080] At t=3 the section separator mechanism 126(4) is opened. A second pressure differential between one or more of the first fill section 362(1 ) or the second fill section 362(2) relative to the fourth section 190(4) results in downstream movement of the gas 128 towards the exit. Meanwhile, a portion of the ga s 128 continues upstream towards the projectile 118. [0081] At t=4 the section separator mechanism 126(5) is opened, exposing the ram acceleration system 124 to the exterior environment. In other i mplementations, the section separator mechanism 126(5) may comprise a diaphragm or other element that is l eft in place and is opened before, or penetrated by , passage of the projectile 118. Portions of the gas 128 continue to proceed moving upstream and downstream, respectively. [0082] The section separator mechanism 126(1) is opened, and the pre‐launch system 110 is activated, moving the projectile 118 towards the onru shing upstream gas 128. [0083] At t=5 the projectile 118 encounters the onrushing upstream gas 128, producing a relative velocity that is a sum of the first velocity of ga s 350(1) and the velocity of the projectile 352. With this relative velocity, ram combustion may begin or be sustained. In some implementations, an initiator may be used to initiate ram combustion. For example, the projectile 118 may include a pyrotechnic flare that serves as an ignition source or controlled, timed, triggered in‐tube fixed location(s) ignition (spark, pyros, and so forth) sources may initiate ram accelerator start at even l ower velocities than traditional or dynamic ram accel erator without these secondary energetic ignition sources. [0084] With ram combustion initiated, the projectile 118 accelerates downstream and exits the dynamic ram accelerator 102. [0085] FIG. 5 illustrates at 500 a second implementation of operation of a dynamic ram accelerator system 100 with one or more additional gas reservoir s 550. The system 100 may include one or more re servoirs 550 that serve to provide additional buffering capaci ty of the gas 128, provide a controlled egress of gases 128 from the pressure tube 160, or other functions. Th e reservoir(s) 550 may store some quantity of gas 1 28 at a particular pressure for use during operation of the ram acceleration system 124, and have passageways siz ed to provide a desired flow rate of the gas 128 therein to the pressure tube 160. In some implementations the reservoir 550 may comprise one or more of the suppl y tanks 152. [0086] A combustible gas pushed by an inert that by the time the projectile passes the reservoir entrance, since the gases are inert, it won't induce a detonation or an unstart condition stopping ram combustion, since it will have naturally stopped combusting and is drifting or coasting in the inerts. In the implementation depicted, a reservoir 550 is fitted to the pressure tube 160 in section 190(4), proximate to the
exit. In this implementation, the dynamic ram ac celerator 102 may incorporate one or more baffle tub e sections 202 (not shown). [0087] In some implementations one or more of the pressure tube 160, or the reservoir 550 may be smooth bore, baffled or otherwise shaped, and comprise a valve 126 to control the exit gas velocity. The reservoir 550 may store one or more gases with grad ient or separate gases and fuel injection, as the g as enters the section 190, creating upstream flowing gas 128. [0088] At t=0 a first fill stage 362(1) comprising a porti on of the dynamic ram accelerator 102 that is bounded by section separator mechanisms 126(2) and 12 6(3), that are closed, is pressurized with gas 128(2 ). [0089] A second fill stage 362(2) comprising a portion of the dynamic ram accelerator 102 that is bounded by section separator mechanisms 126(3) and 126(5), that are closed, and the reservoir 550 is pressurized with gas 128(5). A section separator me chanism 126(6) between the reservoir 550 and the sec ond fill stage 362(2) is open. [0090] In this implementation the section separator mechanism 126(4) may be omitted or remain in the open state. [0091] A first section 190(1) bounded by section separator mechanisms 126(1) and 126(2), that are closed, may be evacuated. [0092] The chamber 114 (or other launch mechanism) is press urized or otherwise primed for launch. The first section 190(1) is separated from the chamb er 114 by a closed first section separator mechanism 126(1). [0093] The composition, pressure, temperature, or other param eters of the respective gas 128(2) or 128(5) may be the same or may differ. [0094] At t=1 an additional gas 128(6) is introduced into the reservoir 550. [0095] At t=2 the section separator mechanisms 126(2) and 126(3) are opened. A first pressure differential between one or more of the first fill section 362(1) or the second fill section 362(2) rel ative to the first section 190(1) results in upstream movement of the gas 128 towards the projectile 118. [0096] At t=3 the additional gas 128(6) continues to be in troduced into the reservoir 550. As a result, the gas 128(6) is proximate to the exit while a portion of the ga s 128(5) is pushed upstream. Meanwhile, a portion of the gas 128 continues upstream towards th e projectile 118. [0097] The section separator mechanism 126(1) is opened, and the pre‐launch system 110 is activated, moving the projectile 118 towards the onru shing upstream gas 128. [0098] At t=4 the projectile 118 encounters the onrushing upstream gas 128, producing a relative velocity that is a sum of the first velocity of ga s 350(1) and the velocity of the projectile 352. With this relative velocity, ram combustion may begin or be sustained. [0099] At t=5 the section separator mechanism 126(6) is clo sed and the section separator mechanism 126(5) is opened to allow passage of the projectile 118 to exit the dynamic ram accelerator 102. With the section separator mechanism 126(5) open, a portion of the gas 128 may move downstream, into the ambient environment, respectively. [00100] In other implementations, the section separator mechan ism 126(5) may comprise a diaphragm or other element that is left in place and is open ed before, or penetrated by, passage of the projecti le 118.
[00101] FIG. 6 illustrates at 600 a third implementation of operation of a dynamic ram accelerator system 100 with a moveable cap or moveable diaphragm 640 or variable mass and material type to tailor acceleration and relative gas velocity and a reserv oir 550. In the implementation depicted, a reservoi r 550 is fitted to the pressure tube 160 proximate to the ex it. In this implementation, the dynamic ram acceler ator 102 may incorporate one or more baffle tube sections 202 (not shown). [00102] At t=0 the reservoir 550 is pressurized with gas 12 8. The reservoir 550 is separated from the pressure tube 160 by section separator mechanism 126( 6) that is closed. [00103] In this implementation the section separator mechanism s 126(2)‐(4) may be omitted or remain in the open state. [00104] A first section 190(1) is bounded by section separator mechanisms 126(1) and 126(5) and 126(6), that are closed. The first section 190(1) may be evacuated. [00105] Placed within the first section 190(1) is a moveable diaphragm 640. The moveable diaphragm 640 may comprise an assembly that restricts or preve nts flow of gas 128 past itself but is able to mo ve upstream along the dynamic ram accelerator 102. For example, the moveable diaphragm 640 may have a profile that is the same as, or similar to, the projectile 118. [00106] The chamber 114 (or other launch mechanism) is press urized or otherwise primed for launch. The first section 190(1) is separated from the chamb er 114 by a closed first section separator mechanism 126(1). [00107] At t=1 the section separator mechanism 126(1) is ope ned, and the pre‐launch system 110 is activated, moving the projectile 118 downstream, towar ds the exit. [00108] At t=2 the section separator mechanism 126(6) is ope ned. A first pressure differential between the reservoir 550 relative to the first section 190( 1) results in gas 128 and the moveable diaphragm 64 0 being displaced upstream, towards the oncoming projectile 11 8. [00109] At t=3 the gas 128 and the moveable diaphragm 640 continue moving upstream, and the projectile 118 continues moving downstream towards the exit. [00110] At t=4 the projectile 118 enters a baffle tube section 252 and encounters the onrushing moveable diaphragm 640 and gas 128. The moveable d iaphragm 640 is penetrated by the projectile 118, or the moveable diaphragm 640 may be destroyed before encountering the projectile 118. With the encounter between the projectile 118 and the onrushing gas 128 producing the relative velocity, ram combustion star ts. [00111] At t=5 the section separator mechanism 126(5) is ope ned to allow passage of the projectile 118 to exit the dynamic ram accelerator 102. With the section separator mechanism 126(5) open, a porti on of the gas 128 may move downstream, into the ambient e nvironment, respectively. In some implementations, th e section separator mechanism 126(6) is closed before p assage of the projectile 118. [00112] In other implementations, the section separator mechan ism 126(5) may comprise a diaphragm or other element that is left in place and is open ed before, or penetrated by, passage of the projecti le 118. ADDITIONAL DESCRIPTION OF IMPLEMENTATIONS
FIRST IMPLEMENTATION [00113] A first implementation utilizes an evacuated launch tube 116. A first section of the ram acceleration system 124 is evacuated to a low pressu re, while a second section “fill stage” is fille d above desired operational pressure. A closed valve maintains the gas in the fill stage 362 until opened. The fill stage 362 acts as a gas supply that flows upstream into the evacua ted section of the ram acceleration system 124 secti on once the valve is opened. The timing of the opening of the breech valve or other pre‐launch system eleme nt and the valve of the fill stage 362 may be synchronized or sequenced with the timing of the start of projectile 118 movement to optimize velocity and position of the projectile 118 as it comes into contact with the ram acceleration system 124 gases 128 at a pressure that is efficient for ram acceleration system 124 combus tion. The upstream flowing gases 128 meet with the downstr eam projectile 118 in the ram acceleration system 12 4 to provide a relative velocity for combustion start and operation. For long ram acceleration system 124 sections this method is particularly efficient because the pro jectile 118 may remain stationary until the fill sta ge valve (and other valves in some implementation) are fully open due to the time of gas transit through the ram accelerator sections downstream of the projectile. [00114] The use of two fill stages 362 provides different sections of gas 128 to move in different (opposite) relative velocities. As a result, as the projectile 118 enters the gases 128 released from the first fill stage 362, the relative velocity between the projecti le 118 and the oncoming (upstream) gases 128 is inc reased. This allows the projectile 118 to achieve initial velocity at a lower absolute velocity with respect to the ram acceleration system 124 structure. In comparison, as the projectile 118 travels downstream, it encounters the downstream gases 128 released from the second fill stage 362. These gases 128 are travelling in the same direction as the projectile 118, reducing the relativ e velocity. While still above the initial velocity, this reduction in relative velocity maintains the projectile 118 wit hin a desired range of thrust coefficients. (See C . Knowlen, et al, “Dynamic ram acceleration system 124 as an Impulsive Space Launcher: Assessment of Technical R isks”, FIG. 6.) This may also facilitate the use of th e same gas mixture 128 between adjacent sections. For example, the projectile 118 may first encounter a first gas mixture 128 from the first fill stage 362, and then encounter the same first gas mixture 128 in the second fill stage 362, while maintaining the desired thrust coeff icient. The projectile 118 may then move into a third section u sing a second gas mixture 128 having an upstream ve locity, a fourth section using the second gas mixture 128 h aving a downstream velocity, and so forth. [00115] The pre‐launch system 110 may include a breech val ve that is operable to provide an opening with a time‐variable cross‐sectional area or stage d injections between the launch gas system and the launch tube 116. This allows for a variable flow rate of gases 128 from the pre‐launch system 110 into the ram acceleration system 124 and allowing controlled accele ration of the projectile 118. [00116] The first implementation may omit the use of any internal consumable elements, such as diaphragms. In one implementation an exit diaphragm or exit valve may be used to permit the projectile 118 to pass into the surrounding environment. SECOND IMPLEMENTATION
[00117] A second implementation is a variation of the first implementation, where a valve in the ram acceleration system 124 is open or opens and allows the ram acceleration system 124 sections and the la unch tube 116 to equalize in pressure. The ram accelera tion system 124 and launch tube 116 are filled to a target pressure below the intended operational pressure of t he ram acceleration system 124. The start gun or other element of the pre‐launch system 110 pushes the pr ojectile 118 while the projectile 118 pushes the ups tream gases 128 ahead of the projectile 118. The upstream gases 128 are at a substantial, but significantly lower pressure than the breech and launch tube 116, allowing projectile 118 acceleration and high velocity. An optional active or passive vent system at the launch tube 116 to ram section interface may vent out th e gases 128 being pushed by the projectile 118. As the pr ojectile 118 enters the ram acceleration system 124 stage, an area change occurs. For example, the launch tube 1 16 has a smaller inner diameter than the ram accele ration system 124. This transition in cross‐sectional are a results in a decrease in the pressure of the gas es 128 being pushed by the projectile 118. Additionally, the relative velocity between the gas 128 and the projectile 118 produces the initial velocity. As a result of the local pressure decrease resulting from the change in cross sectional area, the launch tube 116 gases 128 are p rovided with a volume into which to expand and slow ‐down, thus enabling a ram effect start for combustion. I n a system having a relatively short overall length, this may reduce the opening velocity requirement of or elimina te all‐together the need for the upstream ram valv e. [00118] In some implementations the launch tube 116 may be filled with a different gas 128 than the ram section, for example air instead of methane‐air , to prevent any unintended initiation of combustion ahead of the projectile 118. For example, unintended combustion ahead of the pro jectile 118 may result from gas blow‐by around the projectile 118, projectile 118 n ose shock heating while transiting the launch tube 1 16, and so forth. Such unintended combustion could substanti ally slow the projectile 118 down with high combusti on pressures and/or interfere with ram acceleration syste m 124 combustion. THIRD IMPLEMENTATION [00119] A third implementation utilizes a partial, or no, evacuation of the launch tube 116 and the pressure of the gun launch is used similar to a two‐stage light gas gun in which the projectile 118 is used to increase the pressure of the gas 128 (fluid) ahead of the projectile 118. The ram acceleration system 124 geometry (volume) is well‐defined ahead of the proj ectile 118 and Press1*Vol1 = P2*Vol2 ideal gas law as a first approximation to the pressurization, shows the velocit y of the projectile 118 still accelerating to a suf ficient velocity for ram acceleration operations. This imple mentation avoids the use of any evacuation requiremen ts on the launch tube 116, and eliminates the requirement for segmentation between the launch tube 116 and ram acceleration system 124 stage, thus simplifying c onstruction and operations. This implementation may be used in combination with other implementations to accommodate zero velocity or lower velocity start requirements. [00120] FIGS. 7‐8 depict implementations of a baffle tube section with rails 220, according to some implementations. [00121] FIG. 7 depicts at 700 two views of a first impleme ntation of the baffle tube section with rails 220. At 702 a first view depicts a baffle tube s ection with rails 220 in assembled form, as well as examples of an
unassembled rail 222 and unassembled baffles 206, with the pressure tube 160 and other elements omitte d for ease of illustration, and not necessarily as a limit ation. Depicted are four rails 222 and a plurality of baffles 206. Each rail 222 may include one or more engagement features, such as slo ts or notches. Each baffle 206 may include one or more engagement features, such as slo ts, notches, tabs, and so forth. In this implement ation the baffle 206 comprises slots disposed along the outer circumference of the baffle 206. When assembled, th e rails 222 may be joined, by at least the mechanical engag ement features, to the baffles 206. In this implem entation the rail notches and baffle notches are interfaced with the rail 222 inserting from the outer diameter of the baffle 206, which may produce intermittent, discontinu ous rail contact with the projectile 118 while incre asing the interference drag with projectile passage. This arrangement may improve overall cost efficiency and the reduced contact area of the rail‐projectile interfac e may be minimized to reduce rail drag between the projectile 118 and the rail 222. [00122] In some implementations, contact between the projectil e 118 and the rail 222 may introduce additional drag during projectile passage. The contact area of the rail 222 to projectile interface may be minimized to further reduce this projectile to rail drag. For example, the profile or portion of the rail that comes into contact with the projectile may be rounded, gro oved, knife‐edged, and so forth. In some implemen tations a lubricant may be applied to the rails 222 prior to projectile passage. [00123] At 750 a view of the completed assembly is shown, with the engagement features providing mechanical engagement between the rails 222 and the baffles 206. Additional forms of engagement may als o be utilized, such as welding, wedges, fasteners, and so forth to join the baffles 206 to the rails 222. During passage, a gap may be present between the projectile 118 and the inner diameter of the baffles 206. [00124] FIG. 8 depicts at 800 two views of a second implementation of the baffle tube section with rails 220. At 802 a first view depicts a baffle tube section with rails 220 in assembled form, examples of an unassembled rail 222 and unassembled baffles 206, and the pressure tube 160, with other elements omitted for ease of illustration, and not necessarily as a limit ation. Depicted are four rails 222 and a plurality of baffles 206. Each rail 222 may include one or more engagement fe atures, such as slots, notches, tabs, and so forth. Each baffle 206 may include one or more engagement featur es, such as slots or notches. In this implementati on the baffle 206 comprises slots disposed along the inner circumference of the baffle 206. When assembled, th e rails 222 may be joined, by at least the mechanical engag ement features, to the baffles 206. In this implem entation the rail notches and baffle notches are interfaced w ith the rail 222 being inserted from the inside dia meter of the baffle 206. This arrangement provides continuous rail contact with the projectile 118 without the intermittent notches depicted with regard to the arrangement of FIG. 7. In some implementations, this continuous contact may introduce additional drag betwe en the rail and projectile during projectile passage. The contact area of the rail to projectile interface may be minimized to further reduce this projectile to rail drag. For example, the profile or portion of the rail that co mes into contact with the projectile may be rounded, grooved, knife‐edged, and so forth. In some implementations a lubricant may be applied to the rails 222 prior to projectile 118 passage. [00125] At 850 a view of the completed assembly is shown, with the engagement features providing mechanical engagement between the rails 222 and the baffles 206. Additional forms of engagement may als o
be utilized, such as welding, wedges, fasteners, and so forth to join the baffles 206 to the rails 222. During passage, a gap may be present between the projectile 118 and the inner diameter of the baffles 206. IMPLEMENTATIONS OF RAM ACCELERATION SYSTEM CONSTRUCTION [00126] A baffle tube section 202 ram acceleration system 12 4 (BTRA) utilizes a series of baffles 206 within the ram acceleration system 124. In some im plementations baffles 206 may be fabricated from a s olid block of suitable material, such as steel. Monolith ic segments (one or more baffles 206) are stacked t ogether forming the sequence of baffles 206 with a rail 222 system and inner (minor) diameter of the bore that are the same and constant with the outer tube. A variable baffle 206 may be used for low‐speed start operat ions such as described herein. [00127] One consideration with the use of baffles 206 is th e proximity of the projectile 118 to the minor diameter of the baffle 206. A non‐zero correct s pacing is optimal for allowing the gases 128 and co mbustion processes to react against the projectile 118 to ram accelerate, while the shoulder‐to‐shoulder spacing of the projectile 118 and the baffle 206 and the gap creat e temporary high‐pressure zones. [00128] The constant separation of the gap between the projectile 118 and the baffle 206 may be provided in some implementations by the rail 222 inn er dimension which may be manufactured continuous and subcaliber to the baffle 206 minor diameter. The r ail 222 provides smooth passage for the projectile 1 18 transit, provides gap separation between the projectile 118 and the baffle 206, preventing significant canting or “balloting” of the angle of the projectile 118 while in the BTRA section. This is advantageous, as undesired canting could result in an unintended collision betwe en the projectile 118 and the baffles 206 or other portions of the ram acceleration system 124. By using the implementation described herein, the rail 222 provides the separation as well as a continuous structural load t ransmission path from the baffle 206 to baffle 206 volumes resulting from combustion and other effects back to the outer pressure tube 160 interface of the ram acceleration system 124. [00129] This allows the ram acceleration system 124 to be c onstructed such that the outer diameter may be varied to allow for larger area ratio for lower speed start and smaller area ratios for higher speed operations. This simplifies construction, such as tu nnel boring to provide a path for the ram accelerat ion system 124. [00130] The path of the ram acceleration system 124 may com bine one or more curves in one or more planes. For example, the ram acceleration system 12 4 installed on Earth may describe a path that takes into consideration Coriolis force. [00131] A combination of interlocking features may allow the diameter, thickness, and spacing of the baffles 206 to be tailored. This allows the volume of combustion at any point within the ram accelera tion system 124 to be controlled. [00132] The ram acceleration system 124 may include other features. For example, the ram acceleration system 124 may include one or more vent s. In some implementations reverse circulation may be
provided to vent around a baffle 206 and towards the projectile 118. The rails 222 may protrude pa st the baffle 206, allowing gas‐projectile 118 gap while preventin g canting. [00133] In some implementations python or labyrinth seals may be used between different portions of the system. For example, python seals or other seals may be used to seal between baffle tube sect ion 202 sections. [00134] One or more fastening techniques may be used to aff ix a rail 222 to a baffle 206. For example, pins, bolts, wedges, welds, adhesive, mechanical inter face, threaded fasteners, and so forth. [00135] A locking wedge on or near the outer (major) diamet er of the baffle 206 structurally locks the baffle 206 to the rail 222. Allowing the rail 222 to take a pinned (or fixed, etc.) bending load of the unsupported notched section of the baffle 206. The lower section of the baffle 206 is retained by a locking interface and notch in the rail 222, fully pin‐supported by the inner diameter section of the rail 222. The rail 222 section with notches is assembled from the outside diameter to the inside. Tie rods may be used to connect baffles 206, assisting with beam loads. In some implementations the transport tubes may also be load bearing. This allows in manufacturing the bore dimensions to be easily ma intained using a calibrated rod to set the distance between rails 222 during, welding, for example of the baffle s 206 to the rails 222. This allows the rail 222 dimensions to be precisely managed. The baffles 206 (or sweepers) may be connected with one or more rails 222 that a ssemble self‐aligning from the inside out (as Fig 8) or o utside (Fig 7). The rails 222 and the baffles 206 may be slotted to fit puzzle‐like together to share the structural loading and an inner rod will set the rail 222 spacing precisely during assembly and possibly welding/adhesion is required. Locking structure with tack welding may be sufficient to handle pressure loads on baffles 206. The rails 222 will provide that subcaliber stand‐ off to prevent the projectile from striking the edge of the baffle 206. The baffle 206 is a means by which the rel ative velocity may be controlled, and may also be used to manage drag and alignment of the projectile 118 relative to the baffle 206. [00136] In some implementations a venting path may be provid ed from the pre‐filled launch tube 116 around the baffles 206 as the projectile 118 approac hes. As discussed above, the area change of the b affle 206 compared to the launch tube 116 assists in expansion and lowering of pressure ahead of the projectile 118 compared to a full caliber launch tube 116. [00137] A “T” (“tee”) of ram gases and inert gases may be injected at an angle to the ram acceleration system 124 section, allowing continuous back‐filling of ram acceleration system 124 gases 128 while thos e gases 128 push towards the low pressure section (launch tube 116) and evacuated ram acceleration system 124 sections. As a result of the angle, the projectile 118 is allowed to transit past the injection tube. The gases 128 may be sequenced to prevent any undesirable combustion or detonation d uring projectile 118 transit. This “parallel” gas source acts like a shock tube sou rce keeping the ram acceleration system 124 section filled to the right pressure and velocity of the gases 128. [00138] Features such as rail 222 to inner‐tube diameter s pacing, diameter, or in case of baffle tube section 202 ram acceleration system 124, baffle 206 angles and spacing and geometry can be optimized to match the desired gas velocity, and relative velocity gas pressure required to optimize the flow field is matc hed to best ram acceleration system 124 performance for ram accel eration system 124 masses and geometries (nose angles ,
length, center of gravity (CG)), shock induction f eatures (protuberances), and on‐board propellants (so lid fuels or oxidizers on the board as function of radius and length, etc.) [00139] In some implementations, the notches of the rail 222 and the baffle 206 may be arranged opposite one another, allowing the rail 222 to be i nserted from the inner diameter. Loading supports m ay be inverted where structural pinned supports of the baff le 206 form the rail 222 from the notch directly a nd the pins, bolts, or wedges are inserted at the interior location. This allows adjustment of the rail 222 concentricity and gap, by using a long calibrated oversized projec tile 118 cylinder to set the alignment of the rails 222 during assembly and attachment. This approach allows for s mooth rail 222, continuous between rail 222, likely offering lower intermittent drag and scalloping between rail 222 sections, as well as providing direct reaction of the larger span simple load supports interacting between baffle 206 and rail 222. For example, the larger the span, the higher the load. Likewise, the shorter the inner span, the lower the load on the pins, if used. In some implementations a pin may be avoided all together by using a joint at the bottom (smaller diameter area of the notch) and using a tack weld at the outer perimeter to support the baffle 206 with the rail 222. [00140] As shown in the figures, the inner rail 222 may be relatively smooth. The rails 222 keep the projectile 118 from canting, while the gap between t he inner rail 222 and the inner diameter of the ba ffle 206 allows the shockwave effects desired for ram accelera tion combustion. [00141] In some implementations, the gap between the pressure tube 160 and the baffle 206 and/or rail 222 may be filled with a solder/weld alloy, or temperature or pressure activated adhesive. This a llows for simple assembly of the rail 222 and pressurize conta ct assembly and welding and fusing of the rail 222 and or baffle 206 section to the inner wall of the pressur e tube 160. The temperature or pressure change of a long over‐caliber projectile 118 as an alignment tool ca n swell at a higher rate than the steel tube and rail 222 for example, or rails 222 and or baffle 206 could have different coefficients of thermal expansion (CTE) for cing the high‐pressure contact and better bonding for metal or composite adhesion of the rail 222 and baffle 20 6 to the tube walls. This allows for long sections of baffle 206 to be manufactured quickly and cheaply. In some situations, manufacture may occur in‐situ. [00142] The baffles 206 or rails 222 themselves may be fibe r or steel (rebar) reinforced and then cast by section to final form to create the baffle 206 and rail 222 section with the metal, composite, and so forth. The portions comprising a rail 222 and/or baffle 206 may involve critical geometry as they come into co ntact or are near the projectile 118 during transit. In com parison other elements are less critical during manuf acture, such as the inner diameter of the pressure tube 160 . [00143] The pressure tube 160 may comprise fiber reinforced material. [00144] The valves described herein may comprise re‐usable valves that are operable to transition between a closed and an open state. In some imple mentations the valves may include a flapper, ball, g ate, dual clam shell, and other valve types. In other implem entations the valve may comprise a diaphragm or sing le‐use device. Valves may be mechanically, pneumatically, electrical ly, magnetically, chemically, or pyrotechnically operated. [00145] In some implementations the valves may provide a var iable cross‐sectional area over time, to provide for controlled mass flow per unit time.
[00146] In some implementations, passages, pipes, or other fe atures may be included in one or more of the pressure tube 160, the baffles 206, or other structures to allow for transport of gases 128 to their respective sections. DISCUSSION OF DYNAMIC RAM ACCELERATION SYSTEM [00147] In some implementations, the following components of the ram acceleration system 124 may be present. In some implementations, one or more o f these components may be omitted, or other componen ts used to provide the same or similar functionality. [00148] A breech which provides gas chemical energy for movement of a projectile 118 may start motion. Motion may result from pressure of a cold gas or combustion of a gas that is initiated via spark, heat, compression, and so forth. Other systems may be us ed. [00149] A breech throat is the interface between the breech and launch tube 116. The breech throat holds an obturator 120 and a projectile 118 prior t o a start gun launch event. In some implementation s, plastic separators or cups may be used. The interface may be bolted or bolted‐thread‐compressed mylar thin diaphragms. [00150] A launch tube 116 may be evacuated between the bree ch and a first ram section. [00151] An obturator 120 may be connected to the base of t he projectile 118. Transmitting the breech pressure load to push the projectile 118 up to ram speeds. The obturator 120 also provides a gas dyn amic start function at point of contact with the ram gases 128 . The obturator 120 may include a sealing mechanis m. [00152] A projectile 118 may be either a finned projectile 118, for instance, with a shoulder diameter sub‐caliber to the launch tube 116 diameter with fin spacing allowing for ram gas passage and compression around the ram projectile 118 body or an axisymmetri c projectile 118 flying through the baffle tube sect ion 202 or spacers with no fin allowing for ram gas passage and compression around the ram projectile 118 body through the baffles 206. [00153] An entrance diaphragm or cap preventing gases to ent er launch tube 116 via pressure retaining may burst at impact or upstream timing. This may be omitted in one or more of the implementations de scribed herein. [00154] Initial stages or sections 1, 2, …, N of the ram acceleration system 124 may use gases 128, such as a mixture of one or more of fuel, oxidizer, or diluent premixed at pressure to affect ram accelerat ion. [00155] Stage separators prevent stage gases 128 from mixing during fill. The stage separators may comprise ball valves, plastic separators, or cups. The stage separators may be bolted or thread‐comp ressed mylar thin diaphragms. These may comprise a permane nt valve that is actuated or replaceable diaphragms that are burst actively with, for example a pyro initiati on, gas initiated, or simply a passive piercing impa ct. [00156] An exit diaphragm or end cap may prevent ram accele ration system 124 gases at pressure from exiting, prevent outside atmosphere from entering, and allow projectile 118 passage. For example, plastic separators or caps may be used. The diaphragms may be bolted or thread‐compressed mylar thin diaphrag ms. [00157] The ram start velocity relative velocity (initial vel ocity) between the projectile 118 and the ram acceleration system 124 gas may be 1100 m/s for Nit rogen (diluent) based fuel/oxidizer, or may be lower, such
as 550 m/s for baffle tube section 202 ram accel eration systems 124. The diluent gas (N2, Co2, etc .) is used to manage sound speed and provide a fluid medium for ram jet compression during projectile 118 in ram acceleration system 124 start and operation while the pre‐mixed fuel and oxidizer provide the energy so urce for start and sustained combustion. [00158] For example: a 2.2 Ch4 + 9.5 Air molar ratio has very predictable start performance at 1100 m/s for small projectiles (100 gram approximate mass) . In a research setting, a high performance cold gas gun such as high pressure helium is used to push projec tiles to Mach 2.5 (relative to the ram dases downst ream of the launch tube 116 barrel.) Due to sound speed o f helium at medium to high pressures (6000 psi) in a 38 mm (1.5”) tube instance is sufficient to bring this p rojectile 118 to even higher velocities than 1100 m/ s without the need for an intermediate ram acceleration system 124 stage to move from 1100 m/s to 1500 m/s for entry into other ram acceleration system 124 configurations. [00159] Helium gas operations are well known but have seriou s drawbacks. The cost of helium gas itself is expensive and specialized equipment is requ ired to pump from nominal tank pressures from indust rial suppliers (2000 psi) up to 6000 psi are also expensive from a capital standpoint as well as slow from an operational standpoint. The use of hydrogen, also w ith a favorable sound speed has lower cost operation s for the gas itself, but also requires expensive complex pumping systems to similar pressure and due to the ease of flammability of the hydrogen gas, presents difficulty. Additionally the use of other types of specialty gas guns such as two stage gas guns with pre‐heating of ga ses also provides similar if not higher levels of c omplexity and costs to have sufficient performance to bring various projectiles 118 up to velocity to produce ram acce leration. Some of the beneficial values of light gas guns is that there is no requirement for a combustion mechanism (spark plug, etc.), no heat buildup or combustion pr oducts to coat and/or contaminate the launch tube 11 6 and breech, as well as the low temperature operations of the gas from the breech to the launch tube 116 w ith low temperature, there is very little potential for erosi on of the interface between the breech and the laun ch tube 116 called the throat, nor erosion of the launch tube 116 itself. However, this simplicity of operation comes with complexity and cost as discussed above in the gas 128 and pressurization operations, but it also c omes with complexity of release of the gases to initiate movem ent of the projectile 118. In some implementations one or more fixed diaphragm stages are manually placed and mechanically sandwiched (both, threaded, etc.) where the breech is filled to full pressure and the diaphragm(s) are broken in sequence to allow the rush of high pressure gas 128 to provide a high force and thus high acceleration to activate movement behind the ram acceleration system 124 projectile 118 (and obturator 120). This sequence may be started by a mechanical release of breaking mechanism on the diaphragms, or the pressure exceeding the strength of the diaphragms is enough to break the diaphragm and begin projectile 118 acceleration. Placement and replacement of this method may be expensive and time consuming. Automat ing the process with diaphragm caps or plugs replaci ng the sandwiched diaphragms that mechanically repetitivel y seats, seals, and releases reliably at high pressu res (6000 psi) is possible, but due to the high pressur e requirements this process requires significant desig n strength and high tolerances to work repetitively. [00160] Other methods of start guns such as combustion gas guns (CGG) or combustion light gas guns (CLGG) operate to create mass driver motion with com bustion of some or all of the gas 128 in the tube behind
the projectile 118. The heat and pressure create d from the combustion (such as stoichiometric methane + pure oxygen or stoich methane‐air) are ignited and then move the projectile 118 (and the gas 128) down the tube providing velocity for ram acceleration. The value of combustion gas guns as the ram acceleration syste m 124 start gun as the sole means of creation of start v elocity for ram acceleration system 124 projectiles 1 18 is at first glance a simpler and more elegant method for a star t gun. The combustion gas gun allows for low fill pressure of the propellant gases 128 (fuel, oxidizer, and dil uent or inert) while there is substantially less gas mass required and fill pressure approximately an order of magnitude compared with cold gas and light gas start guns. There are problems associated with combustion guns as start guns such as the rapid temperature and pressure increases of the gases 128 at ignition create high pressure and temperature loading on the breech, launc h tube 116, and filling equipment (lines, valves, etc.), as well as high pressure and temperature spikes on the ram acceleration system 124 projectile 118 and the obtura tor 120. A 20‐50X pressure spike multiple over f ill pressure may be experienced on the upstream end of the breec h and on the base of the obturator 120 attached to the projectile 118. For example, a 500 psi fill of Ox ygen + methane in stoichiometric conditions may have pressure spikes up to 70,000 psi. The pressure spike agains t the areas that obturate the projectile 118 to get up to speed for light mass projectiles (100 grams and 38mm diame ter) may produce extreme forces and thus acceleration s on the structure. The projectile 118 and obturator 120 may experience 10,000’s to 100,000’s of “G ’s” multiples of earth gravity of 9.81 m/s^2, thus large destructi ve loads are pressing on the projectile 118 and any payload encapsulated (electronics, satellite, passengers, etc.) This then requires significant structural capability in the breech as well as heavier and more structurally capable obturators 120 and projectiles 118. The heavier structures in turn require more mass and thus more start gun propellant and pressure to get up to ramming velocities of 850 m/s to 1100 m/s. One additional issue that also affects the reliability, repeatabilit y, cost, and timing of operations is the throat erosion (breech t o launch tube 116) and launch tube 116 erosion due to high temperature gases 128 created in the combustion event . [00161] Rather than using solid gas generator materials such as black powder, gun powder, ANFO, etc., in one implementation, to use low cost gaseous combu stion propellants such as methane, hydrogen, oxygen, air (21% ox, 78% nitrogen etc.) for ease of handlin g, safety, and ease of evacuation and cycle time of propellants. Also, it is preferable, but not required for the co mbustion gun system to consume all of the propellant s leaving no additional fuel or oxidizer after combustion, thus the goal is stoichiometric mixtures that leave noth ing but CO2, H2O, and trace amounts of CO, etc., and any i nert gases (such as nitrogen, etc.). [00162] A key differentiator between operability of guns and the ram acceleration system 124 is that in guns, a significant portion of the hot combustion propellants reach the speed of the projectile 118. With the above specified gaseous propellants comes higher tempe ratures than typical powder guns. A powder gun may have a gas temperature of 1600 degrees Kelvin compar ed to 3000 degrees Kelvin or higher for Stoich Meth ane‐ Pure Oxygen for instance for a combustion gun. Wit h that gas mass, gas temperature, and the gases mov ing at high velocities (1000 m/s or more) it creates a pot entially high erosive flow causing wear and change o f diameter of the breech, launch tube 116 (barrel), and the th roat. In some cases the throat joining the breech and the launch tube 116 is a neck down where there is sign ificant chamberage between the breech diameter (larger ) and the launch tube 116 diameter and the throat con verges the flow from a large diameter to the projec tile 118
diameter. This change in area also influences si gnificant further temperature and pressure loading on the throat. Additionally, the throat is where the projectile 118 and obturator 120 sit statically prior to combustion and in the case of a gas‐filled breech, the obturator 120 ‐projectile 118 unit may provide the sealing mechan ism during the breech filling process. This has been done wit h bridgeman seals, o‐rings, and a variety of other mechanisms such as shear and locking mechanisms. The throat may see a high pressure differential and temperature differential between breech and launch tube 116. Th e highest heat flux and any changes in geometry, jo ints, etc. under supersonic or hypersonic flow may also se t up shock waves and other combustion related intera ction where those protuberances are exposed to the hot, hi gh speed erosive gases of combustion and get extreme ly hot to the point of melting, diameter widening, pitt ing, or other damage to the throat. [00163] The throat is the preferred location to have at least minor geometry changes to afford automation interfaces for obturator 120‐projectile 118 placement , and sealing and release mechanisms. For instance, a minor throat neck down (17‐15 degree t hroat contraction) to a slightly smaller diameter tha n the breech (say a 45mm breech to a 38 mm launch tube 116), offer an excellent location to lock in a proj ectile 118 with an o‐ring and a shearing mechanism to hold a nd seal the obturator 120‐projectile 118 while the breech is filled with propellant that will then be ignited aft er filling, and the projectile 118 shear lock is br oken or released allowing movement of the projectile 118 in a repetit ive fill and fire mechanism of the gun. [00164] In order to afford low‐cost, highly reliable components in the operations of the ram acceleration system 124 this start gun system should likely be more reliable by operating in conditions that are similar to those experienced in powder guns, meaning lower pressures and temperatures. Powder guns may be operated through many cycles without significant degra dation of performance of the breech, throat, and bar rel. Most guns have a brass shell that does absorb some of the heat of breech combustion and the interfaces from breech to barrel (launch tube 116) are minimal, near ly mono‐bore. The obvious drawback of powder guns is having the adverse safety issue of pre‐mixed oxidiz er and fuel and extra mass for brass casing. Lowe r velocity performance is one of the key drawbacks to operating with either powder guns or low performance combusti on gas guns. The sound speed is typically lower (Air/ Methane, etc.) and pressures are lower, thus the l oads on the obturator 120‐projectile 118 are also lower, but ul timately the final velocity at exit is also lower t han may be theoretically gained with such guns as helium or hyd rogen light gas guns or stoichiometric combustion gas guns. This means that in order to achieve start velocities consistent with ram acceleration system 124 operations additional efforts may be used on the ram accelerati on system 124 to initiate start at lower velocity. Such efforts may include mechanisms such as on‐board ignitors be tween the obturator 120 and the projectile 118, or use of s baffle tube section 202 ram acceleration system 12 4 allowing for higher energy propellants to start at lower entrance velocities, and so forth. The simplicity o f a spark ignition and simple low cost propellants for a start gun are very appealing for ram acceleration system 1 24 operations. [00165] In one implementation a start gun for a ram acceleration system 124 is a low‐cost air or nitrogen cold gas gun or a low temperature combustion gas gun with powder‐gun reliability (defined by gas temp and velocity), with relative velocity of the pr ojectile 118 with the gases 128 approaching 550‐110 0 m/s for ram acceleration system 124 start.
[00166] The cold gas gun start gun (nitrogen gun, or air g un) mechanism is extremely low cost with today’s air compressor technology in capital cost a nd operations, but is fundamentally limited by sound speed of the gas. In practice, operating a gun at 2‐2 .5X the gas speed of sound expanding the gas to mo ve the projectile 118 is about the maximum reasonably attainable. A speed of 1‐1.2X speed of sound is very low cost and easy to achieve. [00167] Cold heavy gas guns, similar to their hydrogen/helium gas gun counterparts offer very simple, predictable gas handling and modes shock pressure loa ding on the breech as well as the obturator 120‐p rojectile 118 system. Air or nitrogen based systems are rela tively simple, low cost and may provide low shock l oading on the obturator 120‐projectile 118 system, allowing fo r low‐cost operations for shock intolerant payloads such as satellites and human space capsules. [00168] Hot steam catapults and other mechanisms with high s ound speed and low‐cost operations such as aircraft carries are also options with added complexity over simple gas guns and combustion guns . Other methods may be used to improve the launch capability of the system including a sabot that provides as larger area through a larger diameter and then release of the sabot is accomplished at the end of the launch tube 116. [00169] The ram acceleration system 124 is also sound speed dependent. A nitrogen diluent mixture may be used to modify sound speed resulting in star t velocities of approximately 1100 m/s. Using CO2 based diluent mixtures having CO2 + methane + oxygen with a lower sound speed have allowed reliable ram acceleration system 124 start operations at 820 – 850 m/s. For ram acceleration system 124 start it is critical to have the relative velocity of the projectile 118 moving from the launch tube 116 into the pre‐mixed ram acceleration system 124 gases 128 to be of sufficien t velocity to create the compression needed for auto ignition of the fuel‐oxidizer mixture in the CO2 or nitrogen (diluent) based gas mixture 128 and the setup of thermal choked normal shock operations, allows self‐synchroni zed combustion of the propellants on the base of th e projectile 118. [00170] What is presented in this disclosure are systems, te chniques, and methods of relative velocity of the obturator 120‐projectile 118 to the oncoming ram acceleration system 124 gases 128. A timed r elease of projectile 118 motion and a cap/valve is presented to lower required start gun performance among other advantages in cost, cycle time, and ram acceleration system 124 operations. [00171] What is presented in this disclosure is a method for managing the relative motion between the projectile 118 and the ram acceleration system 1 24 (smooth bore, rail 222ed, baffle tube 202, spacer , and so forth) gas 128, and the movement, timing, and sp eed of the ram acceleration system 124 gas 128 towa rds the projectile 118 while the projectile 118 is accel erating towards the flowing gases 128. The mechanis m used may include hinged valves, gate valves, ball valves, etc. The gases 128 and the flow pattern (velocity and pressure) of the gases 128 that move in the ram ac celeration system 124, especially gases 128 in the b affle tube section 202 ram acceleration system 124 may move and velocities (and pressure) of the gases 128 may be modified (faster, slower) towards the projectile 118, based on the gas constituents, initial pressures, temperatures, and internal flow path and interaction with the open systems (valves, etc.). [00172] For the example shown, there is a section of the r am acceleration system 124 tube (baffle tube section 202 in this case), that has one or more se ctions filled at a pressure with ram acceleration sy stem 124
gases 128 that are higher than the desired ram a cceleration system 124 operation pressure intended for the projectile 118 passage. A projectile 118 is positio ned upstream of a ram acceleration system 124 tube, start gun gases 128 (cold gas or hot or combustible gases) ar e held behind the projectile 118 ready to push the projectile 118 down stream. The launch tube 116 and unfilled ram acceleration system 124 section upstream of the hinged flapper valve separating the filled ram section are at a low pressure (vacuum, etc.) to provide low gas‐ aerodynamic resistance to the flight so the projectil e 118 moves towards the expected oncoming gases 128. The first stage through n ram inner stages may be fille d with gases 128 such as combustible oxidizer and f uel mixtures for the ram acceleration system 124 and a different level of diluent (N2, Co2, etc.) to tailor the soun d speed expected by the passage of the projectile 118 to ke ep it in optimal range for the ram acceleration sys tem 124 (Mach 2‐ Mach 5) within the gas 128. One or mo re ball valves may be used to fill different stages and opened (slowly or high speed) to allow passage of the proj ectile 118. Prior to ram acceleration, these pre‐ filled stages are essentially a staged gas‐spring ready to expand out of this central section to fill the evacuated or low pressure unfilled ram sections. [00173] Before initiation of movement of the projectile 118 towards the ram acceleration system 124 stage, the upstream hinged flapper valve is opened a nd the “gas spring” begins its release to fill the upstream section of the ram acceleration system 124 where the higher pressure gases 128 from the filled section begin to expand towards the lower pressure ram section and to wards the launch tube 116 upstream. In a smooth b ore ram acceleration system 124 this expansion would look like a shock tube expansion with gases 128 moving quickly upstream towards the projectile 118 and may move at speeds up to 2‐3X the speed of sound wit h no significant mass to push, however with valve actuatio n, mass, and inertia of the hinged flapper valve, a nd spacer or baffles 206 (with intention of gas routing featur es like a silencer) the gases 128 may take a more tortuous internal flow path slowing the average gas speed (an d core gas in baffle tube section 202 central zone) towards the projectile 118. This provides tailoring of the velocity of the gases 128. The multi‐part gas (N2 , O2, methane, etc.) could have mixing promoted due to flow of the gas 128 through the tortuous geometry of the baffl e tube section 202 ram acceleration system 124 or rail 222 tube for example. Passages in the baffles 206 may be designed to allow gas reverse flow during the expansion before combustion as well as combustion wave propagation etc. [00174] At a specific time the projectile 118 begins its ac celeration down the (evacuated) launch tube 116 and towards the ram acceleration system 124 sect ion with an increasing velocity Vp. The gases 128 in the ram acceleration system 124 section meet the projecti le 118 at a location defined by gas Velocity (Vg2) at a pressure defined by expansion of the gas 128 (ideal gas for example: P1V1=P2V2) defined by the volume t he gas 128 has expanded into. The relative velocity vector (Vp – Vg2) provides the required velocity to ini tiate a shock wave compression in the correct geometry configuration (baffle tube section 202 area ratio is larger for lower speed start, for example) for the pressure and chemi stry required for ram acceleration system 124 start and sustained combustion. The baffles 206 and timing ma y provide for the initial entrance velocity of the projectile 118 into a partially evacuated section and the gas 128 behind the projectile 118 (and obturator 120 if necessary) allowing the start‐gun gases 128 to expand (and sl ow down) lessening the inert gas pressure effect on the ram
acceleration system 124 start process. In some i mplementations the ram acceleration system 124 may op erate in a ventless mode. [00175] The projectile 118 at the point of contact with the oncoming gases 128 from the valve may have an on‐board pyrotechnic that has been initiate d, is initiated upon acceleration (at start or slow down of the oncoming gases 128), or externally triggered. Something similar to a continuous flare, an explosi ve or a spark, may be used for its heat and chemistry or c atalytic effect to further make the activation energy lower for ease of combustion and further lower the required re lative velocity of the projectile 118 and ram accele ration system 124 gases 128. [00176] As the projectile 118 accelerates in the ram acceleration system 124, it passes by the valve that allows for full passage of the projectile 118 and continued operation in the expanding gas field i n the ram acceleration system 124. The projectile 118 passes the separator ball valve which allows repetitive mult i‐stage fill operation, separating between ram fill 1 and 2 and n stages that use sound speed modification with diluents as described above. The downstream valve may be ti med and actively controlled (or may simply be diaphr agm‐ active or passive) that the ram projectile 118 passe s through while it continues to accelerate. [00177] The system geometry (total ram length, baffle 206 an gles, shapes, fluid connection between rails 222, baffles 206, spacers, etc.) presented defi nes the required fill pressures of the middle sectio n of the ram acceleration system 124 that provides the source gas 128 for the ram acceleration event. The projectile 118 will fly into a moving gas field and will accelerate and continue to fly at a changing relative velocity du e to its own acceleration based on ram combustion as well as flyi ng into an expanding and then possibly retreating ga s field. [00178] The retreating gas field may be timed in such a wa y with the down stream valve(s) actuate to provide a similar function of sound speed modificatio n that the diluent provides, keeping the relative ve locity in the optimum mach number range for efficient operation s without having to modify the diluent for sound sp eed purposes only. [00179] Additionally, the gases 128 downstream of the downstr eam valve or upstream of the upstream valve may be a low pressure evacuated region or a tailored gas mixture and pressure that provides an i nertia of gas that is to be moved so it properly damps the speed of the expanding gas 128 within the filled in ner section of the tube. [00180] For short‐length, high acceleration ram acceleration systems 124, the timing of the valves and associated movement of the gases 128 in the ram acc eleration system 124 and movement of the projectile 118 is controlled. In one implementation, the system 100 may have the upstream valve open or nearly open to guarantee free passage of the projectile 118 before the projectile 118 is released. [00181] Those having ordinary skill in the art will readily recognize that certain steps or operations illustrated in the figures above can be eliminated, combined, su bdivided, executed in parallel, or taken in an alternate order. Moreover, the methods described above may be implemented as one or more software programs for a computer system and are encoded in a computer‐readable storage medium as instructions executable on one or more processors. Separate inst ances of these programs can be executed on or distr ibuted across separate computer systems.
[00182] Although certain steps have been described as being performed by certain devices, processes, or entities, this need not be the case and a varie ty of alternative implementations will be understood by those having ordinary skill in the art. [00183] Additionally, those having ordinary skill in the art readily recognize that the techniques described above can be utilized in a variety of devices, environments, and situations . Although the present disclosure is written with respect to specific implementations, various changes and modifications may be suggested to one skilled in the art and it is inte nded that the present disclosure encompass such chang es and modifications that fall within the scope of the appe nded claims. ILLUSTRATIVE ADVANTAGES [00184] The systems and techniques described herein provide a variety of possible advantages. These include, but are not limited to the following: [00185] Lower velocity requirements for the pre‐launch syste m 110, such as the start gun. This allows simple air gas guns and also provides for low accel eration operations suitable for sensitive payloads. [00186] Reduction or removal of one or more frangible diaphr agms, reducing cost to re‐cycle, speeding up cycle time, and avoiding frangible materials conta minating the ram acceleration system 124. [00187] Reduction or removal of ram accelerator fuel on‐boa rd the projectile 118, improving the safety characteristics. [00188] Avoiding the complications and safety issues with det onation of pre‐mixed fuel and oxidizer in the tube. Use of the techniques described herein l owers structural requirements on the baffle tube se ction 202 that would take an unstart pressure 10‐50 X the f ill pressure (making the tube expensive and thick) w ith a runway detonation which may occur during operation. [00189] Ability to quench the combustion if we want to stop the acceleration or throttle to tailor the acceleration profile or even capture the projectile 1 18 in the tube after a certain test section of com bustion. [00190] Compatible with use of a solid fuel ram acceleration system 124 or a liquid or gaseous fluid injection from the nose or sidewalls to assist with structural skin cooling as well. [00191] Some implementations allow omission of an ignitor on the obturator 120 or projectile 118. [00192] Allows use of a near constant acceleration pre‐laun ch system 110, such as a start gun. Allows use of a variable area cold gas gun or multi‐orif ice gas gun which allows for a tailored acceleration profile for sensitive payloads to start velocity. With lower ve locity requirements on the projectile 118, this simpl ifies the system from a cost and injection complexity perspecti ve, decreasing cycle time between launches and making the system safer for occupants and payloads. [00193] The National Aeronautics and Space Administration (NAS A) and other agencies specify human‐ rated systems to have an acceleration that is less than approximately 20 G. By using the techniques d escribed herein, accelerations of less than 20 G may be main tained while providing the projectile 118 with exit velocities of 1750 m/s. Depending on implementation, the launch tube 116 may have a length of 1 km and the ram acceleration system 124 may have a length of 8 km. An example of a typical ram acceleration system 1 24 N2 diluent based propellant (air‐ methane) is described below.
[00194] Because the physical size (length and overall volume) of the system that is suitable for sensitive payloads, timing is on the order of many seconds fo r the propagation of the gas wave from the ram fil l section expanding towards the projectile 118. As a result, it is possible to ensure all valves are open befor e initiating movement of the projectile 118, improving safety to the payload. [00195] The propagation speed of the gas 128 may also be controlled by maintaining a specified temperature of one or more sections of the launch tube 116, ram acceleration system 124, or the gas 128 therein. For example, one or more of the first se ction or the second section of the ram acceleration system 124 may be heated or cooled to a specified temperature before initiation of the pre‐launch system 110. C ontinuing the example, one or more of the baffles 206, pressu re tube 160, rails 222, and so forth may include thermal transfer devices. In another example, the first fil l gas 128 may be heated or cooled to a specified temperature before initiation of the pre‐launch system 110. [00196] In another implementation the spacing between baffles 206 may be varied to provide relatively large increases in volume, producing a tem perature drop upon a gas 128 entering that volume. [00197] The system 100 may maintain conditions that are read y for flight “takeoff” with gas expansion and even provided large valves or diversion channels just after the projectile 118 that are open or rel eased after all safety conditions are met for movement of the p rojectile 118. The shorter high G‐load systems fo r industrial uses may use pyro‐initiated events or CLGG (combust ion light gas guns) to trigger the movement of the projectile 118 and perform synchronized timing of the projectile 118 movement with the upstream and (optional downstream) ram acceleration system 124 valves. In one implementation, it is possible for high speed va lves to release a thin moveable diaphragm 640 of some mass to retain the gas shock train instead of it being an open wave. APPLICATIONS [00198] Further applications of the systems and techniques de scribed herein may be used to move projectiles for other use cases. This may include using projectiles for geotechnical drilling, mining, a nd so forth. For example, a projectile 118 may be launched towards a material to interact with the material. In one implementation, during construction, completed portions of the ram acceleration system 124 may be used to launch projectiles against a working face to aid in the excavation of a tunnel within which to continue constructions of the ram acceleration system 124. [00199] In some implementations, the system may be used to launch projectiles to provide transport of materials within those projectiles, such as for t errestrial transport of materials, for launching mater ials into orbital or suborbital trajectories, conveying passenger s, and so forth. In other implementations, the sys tem may be used to direct projectiles at high velocity to impact on a working face, such as for drilling, tunnel boring, excavation, material fracturing, and so forth. COMPUTER PROGRAM LISTING [00200] This disclosure includes a computer program listing. The computer program listing is expressed in the GNU Octave language as promulgated at gnu.org/software/octave. The computer program listing contains material which is subject to copyrig ht protection. The copyright owner has no objection to the facsimile reproduction by anyone of the patent docume nt or the patent disclosure, as it appears in the Patent and Trademark Office patent file or records, or rela ted international filings, but otherwise reserves all copyright rights whatsoever. Copyright 2022 Mark Russell. Al l Rights Reserved. %
(L_lt +L_ram) 2*D_proj] %diamter profile of LT + Ram for projectile passage computation .. %max g allowable drives max Pbreech mass_proj=1.5 %mass of projectile kg time_proj_start=0.0 timex_proj(1)=time_proj_start; %maxG_proj=500; %Pmax_breech=maxG_proj*mass_proj*2.205/(pi*((D_lt)^2)/4); Pmax_breech=4200 maxG_proj=Pmax_breech*(pi*((D_lt)^2)/4)/(mass_proj*2.205) mass_cap=.040 %mass of ram cap kg time_ramcap_start=0.05 timex_cap(1)=time_ramcap_start; %Ideal Gas Rspec= R/M R=8.31446261815324; % J(Deg K mol) Univ gas constant %Source Fuel (propane) Air % Propellant Mix C3H8 + Air(79%N2 + 21%O2) c3H8 + 5O2 + (.79/.21)*5N2 = 3CO2 + 4H2O + 18.8N2 % 3*12+8*1 + 5*2*16 + 18.8*2*16 x_fuel_s=3 x_ox_s=5 x_dil_s=18.8 A_source=pi*((D_source*.0254)^2)/4; Vol_source(1)=A_source*L_source; Vol_source_liters=Vol_source(1)*1000 %fixed source voume..could however be a piston moving in 2gas, intensfier mode or 2stgae gas gun mode T_source(1)=300 P_source(1)=1500*6894.76 %psi to Pa n_fuel_s=x_fuel_s/(x_fuel_s + x_ox_s+x_dil_s ) %partial P contribution of fuel Mol_fuel_s=3*12+8*1 %Molecular wt Fuel n_ox_s=x_ox_s/(x_fuel_s + x_ox_s +x_dil_s ) %partial P contribution of ox Mol_ox_s=2*16 %Mol wt of Oxidizer (Oxygen) n_dil_s=x_dil_s/(x_fuel_s + x_ox_s +x_dil_s )%partial P contribution of diluent Mol_dil_s=2*14 %Mol wt of Diluent Mol_source = n_fuel_s*Mol_fuel_s+ n_ox_s*Mol_ox_s + n_dil_s*Mol_dil_s %Mol wt of source R_source=R/(Mol_source/1000) %J/Deg-kg gamma_s=1.3444 %specific heat ratio mass_source=Mol_source*P_source(1)*Vol_source(1)/(R*T_source (1)) %mass of gas in grams a_sound_source=sqrt(gamma_s*R_source*T_source(1)) % Breech Fuel Air % we can use fuel air mixture and ignite with spark, or leave it cold gas *Air, Helium, etc) % Propellant Mix C3H8 + Air(79%N2 + 21%O2) c3H8 + 5O2 + (.79/.21)*5N2 = 3CO2 + 4H2O + 18.8N2 % 3*12+8*1 + 5*2*16 + 18.8*2*16 x_fuel_b=3 x_ox_b=5 x_dil_b=18.8 A_breech=pi*((D_breech*.0254)^2)/4; Vol_breech(1)=A_breech*L_breech; %this was corrected on 2/14/2022 There was an error using the L_source for L_breech Vol_breech_liters=Vol_breech(1)*1000 T_breech(1)=300 P_breech(1)=Pmax_breech*6894.76 %psi to Pa n_fuel_b=x_fuel_b/(x_fuel_b + x_ox_b + x_dil_b ) %partial P contribution of fuel Mol_fuel_b=3*12+8*1 %Molecular wt Fuel - propane n_ox_b=x_ox_b/(x_fuel_b + x_ox_b +x_dil_b ) %partial P contribution of ox Mol_ox_b=2*16 %Mol wt of Oxidizer (Oxygen) n_dil_b=x_dil_b/(x_fuel_b + x_ox_b +x_dil_b )%partial P contribution of diluent Mol_dil_b=2*14 %Mol wt of Diluent Mol_breech = n_fuel_b*Mol_fuel_b+ n_ox_b*Mol_ox_b + n_dil_b*Mol_dil_b %Mol wt of source R_breech=R/(Mol_breech/1000) %J/Deg-kg gamma_b=1.3444 %specific heat ratio mass_breech=Mol_breech*P_breech(1)*Vol_breech(1)/(R*T_breech (1)) %mass of gas in grams a_sound_breech=sqrt(gamma_b*R_breech*T_breech(1)) % Low pressure Launch Tube and attached Ram Tube (if not separated) % Launch Tube couldhve remnants of Fuel Air mixture.. but likely just low pressure air % Propellant Mix C3H8 + Air(79%N2 + 21%O2) c3H8 + 5O2 + (.79/.21)*5N2 = 3CO2 + 4H2O + 18.8N2 % 3*12+8*1 + 5*2*16 + 18.8*2*16 x_fuel_lt=3 x_ox_lt=5 x_dil_lt=18.8 A_lt=pi*((D_lt*.0254)^2)/4; Vol_lt(1)=A_lt*L_lt; Vol_lt_liters=Vol_lt(1)*1000 T_lt(1)=300 P_lt(1)=.0*6894.76 %psi to Pa Low pressure launch tube (evacuated) n_fuel_lt=x_fuel_lt/(x_fuel_lt + x_ox_lt + x_dil_lt ) %partial P contribution of fuel Mol_fuel_lt=3*12+8*1 %Molecular wt Fuel - propane n_ox_lt=x_ox_lt/(x_fuel_lt + x_ox_lt + x_dil_lt ) %partial P contribution of ox Mol_ox_lt=2*16 %Mol wt of Oxidizer (Oxygen) n_dil_lt=x_dil_lt/(x_fuel_lt + x_ox_lt + x_dil_lt )%partial P contribution of diluent Mol_dil_lt=2*14 %Mol wt of Diluent Mol_lt = n_fuel_lt*Mol_fuel_lt+ n_ox_lt*Mol_ox_lt + n_dil_lt*Mol_dil_lt %Mol wt of source R_lt=R/(Mol_lt/1000) %J/Deg-kg gamma_lt=1.4 %specific heat ratio mass_lt=Mol_lt*P_lt(1)*Vol_lt(1)/(R*T_lt(1)) %mass of gas in grams a_sound_lt=sqrt(gamma_lt*R_lt*T_lt(1)) % movement of Ram Cap Vel_cap(1)=0; %initial Velocity Force_cap(1)=0; accel_cap(1)=0; vel_chk_cap(1)=0; deltat(1)=0; dist_chk(1)=0; %numX_ramcap=100+1; %discretize the locations on the ram accelerator for Xpositional movement tracking of ram cap %deltaX_ramcap=(L_ram+1*L_lt)/numX_ramcap %ficticiously we send the cap nX length of LT to generate a trailing velocity profile from
deltaX_ramcap=1.5 % meters n_LT=8 % This is the number of multiples of the Lauch Tube length to propogate backwards to get a velocity profile behind the gas motion behind shock front (ram cap) movement numX_ramcap = ceil((L_ram+n_LT*L_lt)/deltaX_ramcap)+1 % you may need to make the downrange of LT multiples(nLT) longer to accomodate a fast cap and a slow projectile from timing out. Need flow feld behind as if no refectionwave (we can accoodate reflection from breech end later) deltaX_proj_ram=deltaX_ramcap; %ram start otherwise we lose the velocity profile on the time lookup after cap reaches the start of LT.. due to sonic conditions the end of cap velocity profile will be unaffected for a substatially long LT (and the cap is likelu essentially destroyed anyway at projectile contact x_pos_ramcap(1)=0 D_ram(1)=interp1(D_ram_out(:,1),D_ram_out(:,2),(L_lt+L_ram-x _pos_ramcap(1))) %table lookup interpoloation of diam vs ram length A_ram(1)=pi*((D_ram(1)*.0254)^2)/4; Vel_ram(1)=0; Vol_ram(1)=0; %initial volume of ram accel section is zero % movement of Projectile Vel_proj(1)=0 %initial Velocity of projectile Force_proj(1)=0; accel_proj(1)=0; vel_chk_proj(1)=0; deltat_proj(1)=0; %numX_proj=100+1; %discretize the locations on the ram accelerator for X positional movement tracking of ram cap %deltaX_proj=(L_lt + L_ram)/numX_proj deltaX_proj=deltaX_ramcap; numX_proj=ceil((L_lt + L_ram)/deltaX_proj)+1 x_pos_proj(1)=0 %location of projectile start.. zero in thei case is the breech to LT interface D_proj_pass(1)=interp1(D_lt_ram(:,1),D_lt_ram(:,2),x_pos_pro j(1)) %table lookup interpoloation of diam of projectile passge through LT and Ram volumes A_proj_pass(1)=pi*((D_proj_pass(1)*.0254)^2)/4; Vel_proj(1)=0;
Vol_lt_aft(1)=0; %Volume of lt behind projectile Vol_br_lt(1)=Vol_breech; %initial volume behind projectile (in LT) Vol_ram_source(1)=Vol_source(1) Vol_br_lt(1)=Vol_breech(1) num_tsteps_ramcap=numX_ramcap %below we compute a timestep for each position of the ramcap n_nrgy_cap=1000 %Energy reduction factor for cap... amount of energy into gas movement. Compute the accelerator of the gas mass of projectile (1/(1+{1/n}) n_nrgy_proj=1000 %Energy reduction factor for projectile... amount of energy into gas movement. Compute the accelerator of the gas mass of projectile (1/(1+{1/n}) %ratio of mass of gass / mass of projectile mg_mp_proj = mass_breech/(mass_proj*1000) mg_mp_cap = mass_source/(mass_cap*1000) % = 2*I50 /(1+I50/I47 )*$B26*$B33 /(1-$B32) * $B7^(2*(1-$B$32)) % = 2*I50 /(1+I50/I47 )*$B26*$B33 /(1-$B32)* $B7^(2*(1-$B$32)) I50=mg_mp_proj; I47=n_nrgy_proj; B26=R_breech; B33=T_breech(1); B32=gamma_b; B7=L_breech; C2_proj_check= 2*I50 /(1+I50/I47 )*B26*B33 /(1- B32)* B7^(2*(1-B32)) C2_proj = 2*mg_mp_proj /(1+mg_mp_proj/n_nrgy_proj)*R_breech*T_breech(1)/(1- gamma_b)*L_breech^(2*(1-gamma_b)) C2_cap = 2*mg_mp_cap /(1+mg_mp_cap/ n_nrgy_cap)*R_source*T_source(1)/(1- gamma_s)*L_source^(2*(1-gamma_s)) Pratio_cap_aft(1) = 1.0; a_factor_Pr=0; for i=2:numX_ramcap if x_pos_ramcap(i-1)> (L_ram+L_lt) %confirm postion sent cap past the ram stage and into launch tube, cap_PAST_LAUNCHTUBE = x_pos_ramcap(i-1) ; time_cap_PAST_LAUNCHTUBE=timex_cap(i-1) ; endif
x_pos_ramcap(i)=x_pos_ramcap(i-1)+deltaX_ramcap; %movementofprojectile..zero for endcap is exit of ramstage1n-1 if (L_lt+L_ram -x_pos_ramcap(i)) >= 0 D_ram(i)=interp1(D_ram_out(:,1),D_ram_out(:,2),(L_lt+L_ram -x_pos_ramcap(i))); % lookup Diam of Ram and Lt section as seen by Ram cap from Ram cap movment else D_ram(i) = D_ram_out(1,2); % for convenience and to avoid a div by zero voume calc, set Diam of ram even is not in real section of ram. endif % gotta fix the problem where the x_pos_ramcap exceeds the call out of ram diamter... I don;t think it matters since we only lookup while projectile is in ram tube... but I'll set it to last known diam to be safe. A_ram(i)=pi*((D_ram(i)*.0254)^2)/4; Vol_ram(i)=Vol_ram(i-1)+A_ram(i)*deltaX_ramcap; %volume of ram section growing...filledbysourcebehindramcapmovement-pressure communicationwithsource Vol_ram_source(i)=Vol_ram(i)+Vol_source(1); %volofexpandingRamsectionpushing the ramcap towards projectile T_source(i) = T_source(1)*(Vol_source(1)/Vol_ram_source(i))^(gamma_s-1); % temp of gas expansion in expanding breech chamber P_source(i)=P_source(1)*Vol_source(1)*T_source(i)/(Vol_ram_s ource(i)*T_source(1)); %P1V1T2=P2V2T1 %P2=P1V1T2/(V2*T1) Ideal gas law %P(i)=P_i*Vol_c*T(i)/(Vol(i)*Ti); %Pressure gas in breech chamber upstream of projectile...pushing projectile to velocity of interest %x_LT_downstream(i)=Lt-x_pos(i); %distance of remaining LT before exit (or entry into ram stage 1) %Vol_LT_downstream(i)=A*x_LT_downstream(i) + Vol_ram; %T_downstream(i) = T_downstream(1)*(Vol_LT_downstream(1)/Vol_LT_downstream(i))^ (gamma1-1); %P_downstream(i)=P_downstream(1)*Vol_LT_downstream(1)*T_down stream(i)/(Vol_LT_downs tream(i)*T_downstream(1)); %Lx_c(i)=x_pos(i)+L_c; A1=2*(mass_source/1000)/mass_cap; B1=R_source*T_source(1)/(1-gamma_s); C1=L_source^(gamma_s-1); D1=(L_source+x_pos_ramcap(i))^(1-gamma_s); E1=(L_source)^(1-gamma_s);
%=SQRT(I$51*((1+$B53)^(1-$B$32)-1))/$B$34 U_ao_cap(i)=sqrt(C2_cap*((1+x_pos_ramcap(i)/L_source)^(1-gam ma_s)- 1))/a_sound_source; Vel_cap_carlucci(i)=sqrt(A1*B1*C1*(D1-E1)); Vel_cap(i)=U_ao_cap(i)*a_sound_source; deltat(i)=deltaX_ramcap/(.5*(abs(Vel_cap(i)+Vel_cap(i-1)))); %doublecheckthis 16- 1-2022 timex_cap(i)=timex_cap(i-1)+deltat(i); % Pratio_cap_aft(i) =(1-(gamma_s-1)/2*Vel_cap(i)/a_sound_source)^(2*gamma_s/(gam ma_s- 1)); a_factor_Pr(i)=-log(Pratio_cap_aft(i))/x_pos_ramcap(i); %Nat log computation for decrease as function of length %V1=a*t+Vo (eq 1) %D1=.5*a*t^2+Vo*t+Do (eq 2) % eqn 1 -> %a=(V1-Vo)/t %into eqn 2 % D1=.5*((V1-Vo)/t)*t^2 + Vo*t +Do % simplifies to D1=.5(V1-Vo)*t+Vo*t +Do % D1-Do = t*(.5V1 + .5Vo) % solve for t % t=(D1-Do)/(.5*V1 + .5*Vo) % %V2-V1=(D2-D1)/(T2-T1) end % mapping the velocity behind the projectile % % i is the x-location % j is the index for time Vel_matrix(1:num_tsteps_ramcap+1,1:numX_ramcap+1)=0; Vel_mat_row_col=size(Vel_matrix); Press_matrix(1:num_tsteps_ramcap+1,1:numX_ramcap+1)=0; Vel_mat_frm_Pmat(1:num_tsteps_ramcap+1,1:numX_ramcap+1)=0; Temp_matrix(1:num_tsteps_ramcap+1,1:numX_ramcap+1)=0;
% for i=1:numX_ramcap % for j=1:num_tsteps_ramcap % X_gas_behind_cap(1,i+1) = L_lt + L_ram - x_pos_ramcap(i) ; %location of cap leading edge relative to projectile strt (zero) % X_gas_behind_cap(j+1,1) = timex_cap(j); %timestep associated with position of cap leading edge % Time_gas_behind_cap(j,1) = timex_cap(j); % if X_gas_behind_cap(j,i) > % Vel_gas_behind_cap(j+1,i+1) = Vel_cap(i); % end % end Vel_matrix(1,2:numX_ramcap+1)=L_ram+L_lt-x_pos_ramcap(:)'; for j=1:numX_ramcap Vel_matrix(j+1,1) = timex_cap(j); %j is effectively time (at each position) k is location (effectively) for k=1:numX_ramcap if k>j Press_matrix(j+1,k+1)=0; Vel_matrix(j+1,k+1)=0; Temp_matrix(j+1,k+1)=0; else Press_matrix(j+1,k+1) = P_source(1)*exp(- x_pos_ramcap(k)*a_factor_Pr(j)); Vel_mat_frm_Pmat(j+1,k+1) = 2*a_sound_source/(gamma_s-1)*(1- (Press_matrix(j+1,k+1)/Press_matrix(j+1,2))^((gamma_s-1)/2/g amma_s)) ; % =2*$Z$50/($Z$48-1)*(1-(AE56/AE$53)^(($Z$48-1)/2/$Z$48)) Vel_matrix(j+1,k+1) = Vel_cap(j)*(x_pos_ramcap(k)+L_source)/(x_pos_ramcap(j)+L_sou rce); % assume (rough approx) linear velocity profile of gas behind cap at each location.. full velocity at cap, zero velocity at source end (ram end) % P1*V1/T1 = P2*V1/T2 % T2 =((P2*V1)/(P1*V1))*T1 ? Temp_matrix(j+1,k+1) = T_source(1)*(L_source/(L_source+x_pos_ramcap(k)))^(gamma_s-1 ); %placeholder estimate of temp behind cap at postion and time endif
end end Press_matrix(:,1)=Vel_matrix(:,1); Press_matrix(1,:)=Vel_matrix(1,:); Vel_mat_frm_Pmat(:,1)=Vel_matrix(:,1); Vel_mat_frm_Pmat(1,:)=Vel_matrix(1,:); Temp_matrix(:,1)=Vel_matrix(:,1); Temp_matrix(1,:)=Vel_matrix(1,:); %Vel_matrix(2:Vel_mat_row_col(1),1) = timex_cap(:) % mat_Xincr=size(X_gas_behind_cap); eliminate % mat_Vel_incr=size(Vel_gas_behind_cap); eliminate % X_cap_time_matrix = X_gas_behind_cap num_tsteps_proj=numX_proj %below we compute a timestep for each position of the ramcap % now compute movement of the projectile clear i for i=2:numX_proj if x_pos_proj(i-1) < (L_lt+L_ram) x_pos_proj(i)=x_pos_proj(i-1)+deltaX_proj; %movement of projectile.. zero for BReech to LT interface .. end is exit of ramstage1n-1 D_proj_pass(i)=interp1(D_lt_ram(:,1),D_lt_ram(:,2),x_pos_pro j(i)); %lookup area change for projectile.. pressure drop computation behnd projectile with variable volume as it should fly into ram stage before cap contact A_proj_pass(i)=pi*((D_proj_pass(i)*.0254)^2)/4; Vol_lt_aft(i)=Vol_lt_aft(i-1)+A_proj_pass(i)*deltaX_proj; %volume of ram section growing...filled by source behind ram cap movement- pressure communication with sourc Vol_br_lt(i)=Vol_lt_aft(i)+Vol_breech(1); %vol of expanding LT section from breech pushing the projectile T_breech(i) = T_breech(1)*(Vol_breech(1)/Vol_br_lt(i))^(gamma_b-1); % temp of gas expansion in expanding breech chamber P_breech(i)=P_breech(1)*Vol_breech(1)*T_breech(i)/(Vol_br_lt (i)*T_breech(1)); %ideal gas %P1V1T2=P2V2T1
%P2=P1V1T2/(V2*T1) Ideal gas law %P(i)=P_i*Vol_c*T(i)/(Vol(i)*Ti); %Pressure gas in breech chamber upstream of projectile...pushing projectile to velocity of interest %x_LT_downstream(i)=Lt-x_pos(i); %distance of remaining LT before exit (or entry into ram stage 1) %Vol_LT_downstream(i)=A*x_LT_downstream(i) + Vol_ram; %T_downstream(i) = T_downstream(1)*(Vol_LT_downstream(1)/Vol_LT_downstream(i))^ (gamma1-1); %P_downstream(i)=P_downstream(1)*Vol_LT_downstream(1)*T_down stream(i)/(Vol_LT_downs tream(i)*T_downstream(1)); %Lx_c(i)=x_pos(i)+L_c; A1_proj=2*(mass_breech/1000)/mass_proj; B1_proj=R_breech*T_breech(1)/(1-gamma_b); C1_proj=L_breech^(gamma_b-1); D1_proj=(L_breech+x_pos_proj(i))^(1-gamma_b); E1_proj=(L_breech)^(1-gamma_b); U_ao_proj(i)=sqrt(C2_proj*((1+x_pos_proj(i)/L_breech)^(1-gam ma_b)- 1))/a_sound_breech; Vel_proj(i)=U_ao_proj(i)*a_sound_breech; Vel_proj_carlucci(i)=sqrt(A1_proj*B1_proj*C1_proj*(D1_proj-E 1_proj)); deltat_proj(i)=deltaX_proj/(.5*(abs(Vel_proj(i)+Vel_proj(i-1 )))); %double check this timex_proj(i)=timex_proj(i-1)+deltat_proj(i); I51=C2_proj; %fixed part of Carlucci modified. B54=x_pos_proj(i)/L_breech; %ratioofthe loction of projectilerelativeto LT length B34=a_sound_breech; U_ao_proj_chk(i)=sqrt(I51*((1+B54)^(1-B32)-1))/B34 endif end Vel_mat_row_col=size(Vel_mat_frm_Pmat); timex_ram_out=timex_proj(1)% setthe time watchbecasue the slowprojectile is outrun many times over by the cap speed... and we still need a Velocity field behind the cap for each timestep
impact=0; %index for first time of cap toprojectile impact impact_k_index=0; ram_proj_x_loc=x_pos_proj(1); k=0 while timex_ram_out <= max(timex_cap) % while ram_proj_x_loc<=(L_lt+L_ram) k=k+1 flagchk=1 pos_cap_chk(k) = interp1(timex_cap(:),L_ram+L_lt- x_pos_ramcap(:),timex_proj(k)); %postion of cap (rel to projectile if impact<1 %set the ram position and times equal to non-ram projectile timex_ram(k)=timex_proj(k); x_pos_proj_ram(k)=x_pos_proj(k); ram_proj_x_loc = x_pos_proj_ram(k); Vel_proj_ram(k)=Vel_proj(k); % Same velocities just prior to impact % if x_pos_proj_ram(k)>=(L_ram+L_lt-x_pos_ramcap(k)) %then cap location is less than projectile locations the cap has passed the projectile (or vice versa) time to compute relative Vel if x_pos_proj_ram(k)>= pos_cap_chk(k) impact=1+impact; if impact = 1 timex_ram(k-1) = timex_proj(k) impact_k_index=k % define moment of impact index % timex_ram(k) = timex_proj(k); % x_pos_proj_ram(k)=x_pos_proj(k); % Vel_proj_ram(k)=Vel_proj(k); % Same velocities just prior to impact % Vel_gas(k) =0; % RelVel_proj_gas(k) = Vel_proj(k)+Vel_gas(k); % technially the relative velocity is just the projectile velocity, but it is imaterial since we don't have contact crossing (passage) between source gases(RamCap) and Projectile
% RelVel_proj_gas(k)=.00001; % Set Relative vel as Non-real for non-Rel Vel areas (Cap and projetile haven't yet impacted) % Rel_Mach(k) = .00001 ; % fix Mach as Non-real for non-Rel Vel areas (Cap and projetile haven't yet impacted) % Density_source(k)= .0001; % fix density as Non-real for non- Rel Vel areas (Cap and projetile haven't yet impacted) % F_PA(k)=0; % accel_proj_ram(k)=0.; % deltat_proj_ram(k) = deltat_proj(k); % RelVel_proj_ram_gas(k)=0.0; endif endif endif if impact >= 1 if timex_ram(k-1)>= min(timex_cap) if timex_ram(k-1)<= max(timex_cap) % ensuring we have overlapping times for projectile and cap to lookup impact=impact+1 k timex_proj(k) timex_ram(k-1) pos_cap(k) = interp1(timex_cap(:),L_ram+L_lt- x_pos_ramcap(:),timex_proj(k)); %postion of cap (rel to projectile start[zero])at any time of projectile (lookup table) pos_proj(k) = interp1(timex_proj(:),x_pos_proj(:),timex_proj(k)); %position of projectile at any time of projectile (lookup) indx_time_gas_closest = lookup(timex_cap(:),timex_proj(k)); % find index of time for gas field at a given projectile time indx_pos_in_gas_field_closest = lookup(Vel_matrix(1,2:Vel_mat_row_col(2)),x_pos_proj(k)); %location of index of gas field for given projectile location Vel_gas(k)=Vel_matrix(indx_time_gas_closest+1,indx_pos_in_ga s_field_closest+1); RelVel_proj_gas(k) = Vel_proj(k)+Vel_gas(k); %grab the last velocity known of projectile and use it to set the ram rel vel... then used to compte ram acel down below. with small timesteps should work fine
x_pos_proj_ram(k)=x_pos_proj(k); %perform same above ops for the ram accelerator indx_time_gas_closest_ram = lookup(timex_cap(:),timex_ram(k-1)); %find index of time for gas field at a given projectile time indx_pos_in_gas_field_closest_ram = lookup(Vel_matrix(1,2:Vel_mat_row_col(2)),x_pos_proj_ram(k)) ; % location of index of gas field for given projectile location Vel_gas_ram(k)= Vel_gas(k); % jut to get things checkedout 3- 29-2022) % Vel_gas_ram(k)=Vel_mat_frm_Pmat(indx_time_gas_closest_ram+1, indx_pos_in_gas_field_c losest_ram+1); Temp_behind_cap(k)=Temp_matrix(indx_time_gas_closest_ram+1,i ndx_pos_in_gas_field_cl osest_ram+1); % RelVel_proj_ram_gas(k) = Vel_proj_ram(k-1)+Vel_gas_ram(k); a_spd_snd_gas_source(k)=sqrt(gamma_s*R_source*Temp_behind_ca p(k)); % again for simplicity assume Temp and P are instanteous, therefre speed of sound in the gas feild is constant... this is an approximation which will be update vs. postion, time, velocity, colume and pressure in next rev a_spd_snd_gas_source_ram(k)=sqrt(gamma_s*R_source*Temp_behin d_cap(k)); % again for simplicity assume Temp and P are instanteous, therefre speed of sound in the gas feild is constant... this is an approximation which will be update vs. postion, time, velocity, colume and pressure in next rev Rel_Mach(k) = RelVel_proj_gas(k) / a_spd_snd_gas_source(k); %coasting projectile (no drag assumption) Rel_Mach_ram(k) = RelVel_proj_ram_gas(k) / a_spd_snd_gas_source_ram(k); %Rel Mach of Ramming projectile Density_source(k) = (P_source(indx_pos_in_gas_field_closest))/(R_source*T_source (indx_pos_in_gas_field_ closest)); Density_source_ram(k) = (P_source(indx_pos_in_gas_field_closest_ram))/(R_source*T_so urce(indx_pos_in_gas_fi eld_closest_ram));
F_PA(k) = (-0.1286*(Rel_Mach_ram(k)^4)) + (2.086*(Rel_Mach_ram(k)^3)) - (12.455*Rel_Mach_ram(k)^2) + (30.826*Rel_Mach_ram(k)) - 22.258 ; F_proj_ram(k) = F_PA(k)*(P_source(indx_pos_in_gas_field_closest_ram))*(A_lt) ; %Compute Net Force on Ram projectile accel_proj_ram(k) = F_proj_ram(k)/mass_proj; Vel_proj_ram(k) = sqrt((2*deltaX_proj_ram*mean([accel_proj_ram(k-1) accel_proj_ram(k)]))+ (Vel_proj_ram(k-1)^2)) ; % for a given deltax compute the velocity fro that segment under avg acceleration field between points deltat_proj_ram(k) = deltaX_proj_ram /(.5*(abs(Vel_proj_ram(k)+Vel_proj_ram(k-1)))); %new Feb 152022 timex_ram(k)=timex_ram(k-1)+deltat_proj_ram(k) timex_ram_out=timex_ram(k) % if impact=2 % x_pos_proj_ram(k)=x_pos_proj_ram(k)+Vel_proj_ram(k)*deltat_p roj_ram(k); %this ensures we move forward after 1st impact when using previous position normally to define next location with vel*dt % else x_pos_proj_ram(k)=x_pos_proj_ram(k- 1)+Vel_proj_ram(k)*deltat_proj_ram(k); ram_proj_x_loc = x_pos_proj_ram(k); % end % x1-xo= (1/2)*a*t^2+Vo*t % deltat_proj_ram(i)=deltaX_proj/(.5*(abs(Vel_proj_ram(i)+Vel_ proj_ram(i- 1)))); % distance calc =M6+(O7^2-O6^2)/2/AVERAGE(R6:R7) Xo + (V1^2- Vo^2)/ (2*avg(A0,A1)) % else % Vel_gas(k) =0; % RelVel_proj_gas(k) = Vel_proj(k)+Vel_gas(k); % technially the relative velocity is just the projectile velocity, but it is imaterial since we don't have contact crossing (passage) between source gases(RamCap) and Projectile % RelVel_proj_gas(k)=.00001; % Set Relative vel as Non-real for non- Rel Vel areas (Cap and projetile haven't yet impacted)
% Rel_Mach(k) = .00001 ; % fix Mach as Non-real for non-Rel Vel areas (Cap and projetile haven't yet impacted) % Density_source(k)= 1; % fix density as Non-real for non-Rel Vel areas (Cap and projetile haven't yet impacted) % F_PA(k)=0; else ERROR=100000 % Flag that you need to make your fictitous launch tube longer to have more time steps before projectile runs out of it. time_proj_greater_than_time_cap = 1 endif endif %We are through the post impact calcs endif endwhile % endwhile clf figure(1) subplot (4,1,1) plot(L_lt+L_ram-x_pos_ramcap,T_source,"r-+",x_pos_proj,T_bre ech,"g") xlim([0 ceil(L_lt+L_ram)]) ylim([0350]) xlabel("X position (m) Rel to each start point") ylabel("Temp(Deg K)") legend("Tram-source", "Temp breech") title("Temp Deg K vs. position") subplot(4,1,2) %plot(x_pos_ramcap,P_source/6894.6,"r",dist_chk,P/6894.6,"g" ,x_pos,P_downstream/689 4.6,"b") plot(L_lt+L_ram-x_pos_ramcap,P_source/6894.6,"r-+",x_pos_pro j,P_breech/6894.6,"g") xlim([0 ceil(L_lt+L_ram)]) %ylim([01000]) xlabel("X position (m) Rel to each start point") ylabel("Pressure (psia)") legend("P-ramsource", "P-breech")
title("Pressure .vs. position") subplot(4,1,3) %plot(x_pos_ramcap,Vel_cap,"r",dist_chk,vel_chk,"g") plot(L_lt+L_ram-x_pos_ramcap,Vel_cap,"r-+",x_pos_proj,Vel_pr oj,"g") xlim([0 ceil(L_lt+L_ram)]) %ylim([01200]) xlabel("X position (m) Ref 0 (proj. start position)") ylabel("Velocity (m/s)") legend("x-RamCap", "x-Projectile") title ("Velocity .vs. position") subplot(4,1,4) plot(L_lt+L_ram-x_pos_ramcap,timex_cap,"r-+",x_pos_proj,time x_proj,"g") %plot(L_lt+L_ram-x_pos_ramcap,timex_cap,"r+",x_pos_proj,time x_proj,"g") xlim([0 ceil(L_lt+L_ram)]) %ylim([0 .050]) xlabel("X position (m), Ref 0 (proj. start position)") ylabel("time (sec)") legend("x-RamCap", "x-Projectile") title(" time .vs. position") figure(2) subplot(3,1,1) %plot(x_pos_ramcap,timex_cap,"r",dist_chk,timex_cap,"g") plot(timex_cap,L_lt+L_ram-x_pos_ramcap,"r-+",timex_proj,x_po s_proj,"g") ylim([0 ceil(L_lt+L_ram)]) %xlim([0 .050]) xlabel("time (sec)") ylabel("X position (m) Ref 0 (proj. start position)") legend("x-RamCap", "x-Projectile") title("position .vs time") subplot(3,1,2) lohi_proj=size(x_pos_proj) lohi_RelVel=size(RelVel_proj_gas) lohi_RelVel_ramgas=size(RelVel_proj_ram_gas) indx_print=min([lohi_proj(2) lohi_RelVel(2) lohi_RelVel_ramgas(2)]) %plot(x_pos_ramcap,timex_cap,"r",dist_chk,timex_cap,"g") plot(x_pos_proj,Vel_proj,"g",x_pos_proj(1:indx_print),RelVel _proj_gas(1:indx_print) ,"r",x_pos_proj(1:indx_print),RelVel_proj_ram_gas(1:indx_pri nt),"b") xlim([0 ceil(L_lt+L_ram)]) %ylim([01000]) xlabel("X position (m) Ref 0 (proj. start position)") ylabel("Velocity (m/s)") legend("V-Projectile","relVel proj","RelVel ramming proj" ) title("Velocity .vs. position") Vel_cap_check=diag(Vel_matrix,0); subplot(3,1,3) %for k=2:Vel_mat_row_col(2) plot(Vel_matrix(1,2:Vel_mat_row_col(2)),Vel_cap_check(2:Vel_ mat_row_col(2)),"o",Vel _matrix(1,2:Vel_mat_row_col(2)),Vel_matrix(2,2:Vel_mat_row_c ol(2)),"r",Vel_matrix(1 ,2:Vel_mat_row_col(2)),Vel_matrix(floor(Vel_mat_row_col(1)/2 ),2:Vel_mat_row_col(2)) ,"g",Vel_matrix(1,2:Vel_mat_row_col(2)),Vel_matrix(floor(Vel _mat_row_col(1)*.75),2: Vel_mat_row_col(2)),"b",Vel_matrix(1,2:Vel_mat_row_col(2)),V el_matrix(floor(Vel_mat _row_col(1)*.9),2:Vel_mat_row_col(2)),"y") %hold %end xlabel("X position (m) Ref 0 (proj. start position)") ylabel("Velocity of gas behind Ram Cap (m/s)") title("Velocity .vs. distance profile behind ramcap, at diff times") legend("V-ramcap vel max") %Legend("time =0", num2str(.1)) % pull the velocity .vs. time/distance from the diagonal of Vel_matrix to check figure(3) % Ram accelerator plots subplot(4,1,1) %plot(x_pos_ramcap,timex_cap,"r",dist_chk,timex_cap,"g") plot(timex_cap,L_lt+L_ram- x_pos_ramcap,"r+",timex_proj,x_pos_proj,"g",timex_ram,x_pos_ proj_ram,"b") ylim([0 ceil(L_lt+L_ram)]) %xlim([0 .050]) xlabel("time (sec)") ylabel("X position (m) ") title("position .vs. time") legend("x-ramcap","x-proj gaspush","x-proj ramming") subplot(4,1,2) %plot(x_pos_ramcap,timex_cap,"r",dist_chk,timex_cap,"g")
%plot(x_pos_proj,Vel_proj,"r",x_pos_proj,RelVel_proj_gas, "g",x_pos_proj_ram,RelVel_ proj_ram_gas,"b") plot(x_pos_proj,Vel_proj,"r",x_pos_proj_ram,RelVel_proj_ram_ gas,"b") xlim([0 ceil(L_lt+L_ram)]) %ylim([01000]) xlabel("X position (m) ") ylabel("Velocity (m/s)") title("Velocity Proj & Rel Vel Ramming Proj & RamCap .vs. time") legend("V-proj_gaspush","RelV-proj ramming") %Vel_cap_check=diag(Vel_matrix,0); subplot(4,1,3) plot(x_pos_proj,Vel_proj,"g",x_pos_proj_ram,Vel_proj_ram,"b" ) % time vs. Projectile cruise and projectile ram accelerating xlabel("X position (m) )") ylabel("Velocity (m/s)") title("Velocity .vs. dist Projecile gaspush only and ramming") legend("V-proj gaspush only","V-Proj Ramming") subplot(4,1,4) plot(timex_proj,Vel_proj,"g",timex_ram,Vel_proj_ram,"b") % time vs. Projectile cruise and projectile ram accelerating xlabel("Time(sec) Ref 0 (proj. start)") ylabel("Velocity (m/s)") title("Velocity .vs. time Projectile _gaspush only and ramming") legend("V-proj gaspush only","V-Proj Ramming") figure (4) % Ram Thrust Curves subplot(2,1,1) plot(x_pos_proj_ram,Rel_Mach_ram,"b") xlabel("xpos") ylabel("Rel Mach_proj_ram") title("Relative Mach .vs. position") legend("Mach") subplot(2,1,2) plot(Rel_Mach_ram(3:max(size(Rel_Mach_ram))),F_PA(3:max(size (F_PA))),"ro") xlabel("RelMach_proj_ram") ylabel("F/PA")
title("F/PA non-dim thrust .vs. Rel Mach") legend("F/PA") [00201] Embodiments of the present disclosure can be describe d in view of the following clauses: [00202] (Clause 1) A system comprising: a pre‐launch system comprising; a launch tube having a launch tube entry and a lau nch tube exit; a ram accelerator system comprising: a first section having a first end and a second en d, wherein the first end is proximate to the launch tube exit; a second section having a third end and a fourth e nd, wherein the third end is proximate to the second end; a first fill stage having a fifth end and a sixth end, wherein the fifth end is proximate to the second end and the sixth end is proximate to the t hird end; a first valve between the fifth end and the second end; and a second valve between the sixth end and the third end; a gas control system; and a control system in communication with the pre‐laun ch system and the ram accelerator system, the control system to: operate the first valve and the second valve to clo se; operate the gas control system to fill the first fi ll stage with a first gas; operate the first valve to open; operate the second valve to open; and initiate operation of the pre‐launch system to laun ch a projectile. [00203] (Clause 2) The system of clause 1 wherein the contr ol system operates the first valve and the second valve to open and operates the pre‐launch s ystem such that as the projectile enters the first section, the first gas moves past the projectile, resulting in a relative velocity of the first gas with respect to the projectile that is a sum of a projectile velocity and a gas velocity. [00204] (Clause 3) The system of clause 1 or clause 2 wher ein the control system operates the first valve and the second valve to open and operates the pre‐launch system such that as the projectile ent ers the second section, the first gas moves in a same direc tion as the projectile, resulting in a relative velo city of the first gas with respect to the projectile that is a differ ence of a projectile velocity and a gas velocity. [00205] (Clause 4) The system of any of clauses 1‐3, furt her comprising an exit diaphragm proximate to an exit of a section of the ram accelerator sys tem to a surrounding environment, wherein the exit d iaphragm is penetrated by the projectile. [00206] (Clause 5) The system of any of clauses 1‐4, wherein the first section is evacuated before initiation of the pre‐launch system to launch the projectile. [00207] (Clause 6) The system of any of clauses 1‐5, wher ein the first section contains the first gas before initiation of the pre‐launch system to launc h the projectile.
[00208] (Clause 7) The system of any of clauses 1‐6, wher ein one or more of the first section or the second section are at a specified temperature before initiation of the pre‐launch system. [00209] (Clause 8) The system of any of clauses 1‐7, wher ein the first gas is at a specified temperature before initiation of the pre‐launch system. [00210] (Clause 9) The system of any of clauses 1‐8, the ram accelerator system comprising at least one baffle tube section comprising a plurality of ba ffles. [00211] (Clause 10) The system of any of clauses 1‐9, the ram accelerator system comprising a plurality of baffles and a plurality of rails, wherein the pl urality of rails are mechanically engaged to the plu rality of baffles and the rails constrain movement of the projectile w ithin the ram accelerator system. [00212] (Clause 11) The system of any of clauses 1‐10, the pre‐launch system further comprising: the gas control system to provide pressurized gas to the launch tube; a third valve proximate to the launch tube entry, wherein the third valve is operable to provide an opening with a time‐variable cross‐sectional area between the gas control system and the launch tube; and the control system to: operate the third valve to provide: a first specified mass flow of launch gas through t he third valve and into the launch tube at a first time, and a second specified mass flow of launch gas through the third valve and into the launch tube at a second time. [00213] (Clause 12) The system of any of clauses 1‐11, th e projectile comprising a space vehicle. [00214] (Clause 13) A method comprising: pressurizing, with a first gas, a first volume assoc iated with a portion of a ram accelerator; releasing the first gas into a second volume, wherei n the first gas in the second volume moves towards a projectile in the ram accelerator; and performing ram combustion of the first gas proximate to the projectile based on a relative velocity between the first gas and the projectile. [00215] (Clause 14) The method of clause 13, further compris ing: evacuating the second volume before releasing the fir st gas into the second volume. [00216] (Clause 15) The method of clause 13 or clause 14, further comprising: accelerating, in a launch tube, the projectile to a first velocity; and passing the projectile into the second volume, wherei n the releasing of the first gas is controlled such that the projectile enters the second volume and enc ounters an oncoming portion of the first gas. [00217] (Clause 16) A system comprising: a ram accelerator system comprising: a first section having a first end and a second en d and comprising a plurality of baffles; a second section having a third end and a fourth e nd, wherein the third end is proximate to the second end;
a first fill stage having a fifth end and a sixth end, wherein the fifth end is proximate to the second end and the sixth end is proximate to the t hird end; a first separator mechanism between the fifth end an d the second end; and a second separator mechanism between the sixth end a nd the third end; a gas control system; and a control system in communication with the ram accel erator system, the control system to: operate the gas control system to fill the first fi ll stage with a first gas; and cause release of the first gas from the first fill stage to the first section. [00218] (Clause 17) The system of clause 16, further compris ing: a pre‐launch system in communication with the contr ol system, the pre‐launch system comprising; a launch tube having a launch tube entry and a lau nch tube exit, and the first end is proximate to the launch tube exit, wherein: the launch tube has a first inner diameter; and the first end of the first section has a second in ner diameter, further wherein the second inner diameter is greater than the first inner diameter. [00219] (Clause 18) The system of clause 16 or clause 17, further comprising: a projectile disposed within the ram accelerator syst em; and wherein the control system operates such that as the projectile is proximate to the first end of the f irst section, the first gas moves past the projectile, re sulting in a relative velocity of the first gas wit h respect to the projectile that is a sum of a projectile velocity a nd a gas velocity. [00220] (Clause 19) The system of any of clauses 16‐18, f urther comprising: a projectile disposed within the ram accelerator syst em; and wherein the control system operates such that as the projectile is proximate to the third end of the second section, the first gas moves in a same direc tion as the projectile, resulting in a relative velo city of the first gas with respect to the projectile that is a differ ence of a projectile velocity and a gas velocity. [00221] (Clause 20) The system of any of clauses 16‐19, further comprising an exit diaphragm proximate to an exit of a section of the ram accel erator system to a surrounding environment. [00222] (Clause 21) The system of any of clauses 16‐20, t he ram accelerator system comprising: a first rail comprising a first engagement feature; and a first baffle comprising a second engagement feature, wherein the second engagement features engages the first engagement feature.
Next Patent: SINGLE HAND PAPER TOWEL HOLDER