AN UNMANNED AERIAL VEHICLE

TECHNICAL FIELD

The invention is particularly related to unmanned aerial vehicles whose wings open after being launched and detonate their ammunition when they reach the target.

BACKGROUND

Shape-changing unmanned aerial vehicles have begun to be used in many different areas, especially in defense systems. Shape-changing unmanned aerial vehicles are vehicles whose wings open after launch and that can be launched single or multiple times from the ground, from the air, and even from the shoulder, with launch mechanisms. Unmanned aerial vehicles of this type are often used as suicide drones. Suicide vehicles are aerial vehicles that approach a certain target, detonate the ammunition attached to them, and disintegrate along with the target.

In the said unmanned aerial vehicles, the design and the way of opening the wings are of great importance. Namely; both the wing design and the aircraft body design can change according to the way of opening the said wings. In addition, by minimizing the area covered by the wings in the closed form, the related unmanned aerial vehicles can be used more effectively with much smaller launch mechanisms.

In the article titled “Aerodynamic characteristics of a novel catapult launched morphing tandem-wing unmanned aerial vehicle” by Liang Gao et al., a wing opening mechanism for shape-changing unmanned aerial vehicles is explained (1). Here, the two wings, which are placed on the two shafts provided on the beam placed longitudinally on the aircraft body, are opened with a pivotal movement following launch. In addition, a similar structure is shown in patent applications with publication numbers CN103043214A and EP2475575B1.

In another article titled “A Drone with Insect-Inspired Folding Wings” by L. Dufour et al., another folding wing structure is described (2). In this structure, insect wings were taken as the basis, and accordingly, the wings in question were designed to have multiple parts and to overlap. However, the structure here is extremely complex and has many axes of connection and folding. This situation causes difficulty in production and a decrease in durability.

In Cory Sudduth's master's thesis titled “Design of A Hybrid Rocket / Inflatable Wing UAV”, an unmanned aerial vehicle with wings that are inflatable during the launch was studied (3). Even though a compact structure was provided here with a wing mounting body, the synchronous opening of the wings could not be achieved as stated in the study. This will cause instability, especially at the first launch.

In addition, studies on target detection in suicide-type unmanned aerial vehicles and inflicting damage on the target with maximum efficiency are ongoing. Generally, in this type of system, after target detection is achieved, the unmanned aerial vehicle is launched with a launch mechanism and its wings are opened. After this, with the help of the camera and the auto-pilot system in the unmanned aerial vehicle, the target is reached and the ammunition detonates. In this case, the amount of time it takes to reach the target is more than desired and most of the tracking of the target is provided by the unmanned aerial vehicle.

The orientation of the existing systems to the target is made either by the control operator on the ground according to the camera image on them or with the help of the radar, and the delays and errors that occur here reduce the rate of hitting the target.

As a result, all the above-mentioned problems have made it necessary to make an innovation in the related technical field.

OBJECT OF THE INVENTION

The present invention aims to eliminate the above-mentioned problems and to make a technical innovation in the related field.

The main object of the invention is to provide an unmanned aerial vehicle structure with similar dimensions, different wings, and wing opening mechanisms, which can be controlled more easily in the air and can hit the target at a higher rate. Another object of the invention is to provide the structure of a target tracking and detonation system that can provide more efficient target detection and reach the target more efficiently.

Another object of the invention is to provide the structure of a system that maximizes the volatility efficiency of the unmanned aerial vehicle.

BRIEF DESCRIPTION OF THE INVENTION

In order to achieve all the above-mentioned objectives and the ones that will emerge from the detailed description below, the present invention is an unmanned aerial vehicle arranged to self-destruct near a target, comprising a body, foldable wings that comprise the wing body connected to the body and flaps partially movably connected to the wing body and are opened after launch and the rear wings, and a propeller driven by an engine and ammunition. Accordingly, the present invention is characterized in that when said wings are closed, the wing body is positioned longitudinally with respect to the body, and said flaps are positioned to extend to each other on the upper part of the body at an angle with respect to the wing body and it comprises a wing connection for opening the said foldable wing with a pivotal movement from the point where it is connected to the body, opening the said flaps by rotating with respect to an axis passing through the part where they are connected to the wing body and rotating the wing with respect to a vertical axis passing through the point where it is connected to the body.

Thereby, by arranging the flaps and the wing body to wrap around the body of the unmanned aerial vehicle, the area covered by the wings is minimized and it is possible to position the wings at the center of gravity of the unmanned aerial vehicle.

In a preferred embodiment of the invention, the center of gravity of the unmanned aerial vehicle is arranged between the wings.

In a preferred embodiment of the invention, the said propeller comprises at least two propeller wings that are rotatably connected to a propeller body with respect to the connection axis.

In a preferred embodiment of the invention, each wing comprises more than one flap.

A preferred embodiment of the invention includes at least one spring mechanism that continuously pushes the wings outward from the body.

A preferred embodiment of the invention includes at least two image acquisition elements.

In a preferred embodiment of the invention, one of the said image acquisition elements is configured for quadrant tracking.

A preferred embodiment of the invention includes a LIDAR system.

A preferred embodiment of the invention includes three arc-shaped arms with slots at both ends, one of which is rotatably connected to the other two via slots at their ends.

In a preferred embodiment of the invention, the said wing connection comprises two arms, one of which is rotatably connected to the other two via slots at their ends, which have slots at both ends and formed in the form of an interconnected arc, and another fork-shaped arm connected to one of the said arms and rotatably connected to the body on an axis perpendicular to the axis of the said arms.

In a preferred embodiment of the invention, the said wings are configured to open 90 degrees.

In order to achieve all the above-mentioned objectives and the ones that will emerge from the detailed description below, the present invention is a system for target detection and destruction of an unmanned aerial vehicle arranged to self-destruct near a target. Accordingly, the present invention comprises an unmanned aerial vehicle according to any one of Claims 1-11 or the embodiments given in the detailed description, a launch mechanism to launch said unmanned aerial vehicle, a radar to detect elements in the airspace, an image acquisition element to identify elements detected by the radar, and a processing unit that can communicate with the said launch mechanism, radar, and image acquisition element and process the data received from them.

Thus, in the said system, the tracking and detection systems on the unmanned aerial vehicle are not opened up to a certain point, and accordingly, energy savings are achieved and the unmanned aerial vehicle is kept away for a longer period. In order to achieve all the above-mentioned objectives and the ones that will emerge from the detailed description below, the present invention is a method for target detection and destruction of a system suitable for an unmanned aerial vehicle according to claim 12 and the detailed description, which is arranged for an unmanned aircraft to self- destruct near a target. Accordingly, the present method comprises the steps of detecting an element with radar in the airspace, displaying the said element with an image acquisition element and identifying whether it is a target, if the said element is a target, determining an intersection point that the unmanned aerial vehicle will contact after launch, taking into account the speed and direction of the target, launching said unmanned aerial vehicle towards the intersection with a launch mechanism, turning on a camera provided on the same or a LIDAR provided on the same when it arrives at the intersection of the said unmanned aerial vehicle, bringing the target to the detonation distance of the unmanned aerial vehicle by tracking the target by the camera or LIDAR, and detonation of the ammunition.

In another preferred embodiment of the invention, in case of detecting more than one target, the distance between the targets is determined and if the distance between the targets is less than the radius of destruction of the ammunition, the ammunition between the targets is detonated.

Thereby, the level of destruction is maximized for multiple threats.

BRIEF DESCRIPTION OF THE FIGURES

Figure 1 shows the isometric view of the unmanned aerial vehicle of the invention with the wings closed before launch.

Figure 1 .A shows the detail view of the wing opening spring of Figure 1 . Figure 1.B shows an isometric view of an embodiment of the wing connection mechanism.

Figure 1.C shows the reverse isometric view of Figure 1 .

Figure 1.D shows the isometric view of the propeller.

Figure 2 shows the isometric view of the unmanned aerial vehicle of the invention with the wings open after launch.

Figure 2. A shows the front view of Figure 2.

Figure 2.B shows the detailed view of the open propeller.

Figure 3 shows the isometric view of the unmanned aerial vehicle of the invention with the wings open after launch.

Figure 3. A shows the detail view of the wing connection mechanism of Figure 3.

Figures 3.B, 3.C, and 3.D show the step-by-step opening movement of the wings of the unmanned aerial vehicle given as an isometric view.

Figure 4 shows the representative schematic view of the system.

Figure 5 shows the flow diagram of the method of the invention.

Figure 5. A shows the flow diagram of another embodiment of the method of the invention.

Drawings do not necessarily need to be scaled and details that are not necessary for understanding the present invention may be omitted. Furthermore, elements that are at least substantially identical or have at least substantially identical functions are denoted by the same number. DESCRIPTION OF THE REFERENCE NUMBERS IN THE FIGURES

1. Unmanned aerial vehicle

2. Image acquisition element

3. Radar

4. Processing unit

10. Body

20. Wing

21. Wing body

22. Flap

30. Propeller

31. Propeller wing

32. Propeller body

32a. Engine connection clearance

33. Connection member

40. Ammunition

50. Wing connection

51. Arm

52. Slot

53. Arm connection element

54. Intermediate arm

55. Cover

60. Rear wing

61. Rear vertical wing

62. Rear horizontal wing

63. Wing slot

F. Launch mechanism

S. Spring mechanism

H. Target

R1. First axis

R2. Second axis

R3. Third axis

Ra. Flap opening axis

Rb. Wing opening axis Rc. Wing rotation axis

Rd. First rear wing axis

Re. Second rear wing axis

KN. Intersection point

DETAILED DESCRIPTION OF THE INVENTION

In this detailed description, the unmanned aerial vehicle (1 ) of the invention is described only for a better understanding of the subject and the way to create no limiting effect whatsoever.

The subject of the invention is particularly related to unmanned aerial vehicles (1) whose wings (20) are opened after being launched and which detonate their ammunition (40) when they reach the target.

Referring to Figure 1 ; the unmanned aerial vehicle (1) of the invention is constructed on a longitudinal body (10). There is ammunition (40) connected to the body (10). Said ammunition (40) is preferably placed at the end of the body (10). In addition, a propeller (30) is preferably arranged at the rear of the unmanned aerial vehicle (1 ). The said propeller (30) is associated with an engine (not shown in the figures).

In Figure 1 , the wings (20) of the unmanned aerial vehicle (1) are in the closed position. After launch, the wings (20) move from the position in Figure 1 to the position in Figure 2. Preferably, the unmanned aerial vehicle (1 ) includes two wings (20), and said wings (20) comprise a longitudinal wing body (21 ) and flaps (22) partially movably connected to the wing body (21 ). Two flaps (22) arranged preferably longitudinally are connected to the said wing bodies (21 ).

The said wings (20) are positioned in the closed position, and the wing body (21 ) is longitudinally on the body (10). Here, the flaps (22) are positioned to extend from the upper part of the body (10) and preferably to contact each other. That is, the flaps (22) are positioned at an angle to the wing body (21). Thereby, in the closed position, the two wings (20) are positioned to wrap around the body except for its lower part.

Referring to Figure 1.A; on the said body (10), there is a spring mechanism (S) with one end connected to the body (10) and the other end to the wing body (21). The said spring mechanism (S) is arranged in a constant tendency to push the wings (20) away from the body (10). When the unmanned aerial vehicle (1 ) is launched from the launch mechanism (F), the spring mechanism (S) initiates the opening of the wing (20) by pushing the wings (20).

Referring to Figure 1.B; the wings (20) are connected to the body (10) with a wing connection (50). The said wing connection (50) comprises three arms (51 ) which are rotatably connected, and arm connection elements (53) provided in the form of a shaft together with the shaft slots (52) at the ends of the arms (51). The said arms (51 ) are preferably arranged in connection with the spring, and there are slots (52) at both ends of each, and springs close to the slots (52). The arms (51 ) are connected to one of the other arms (51 ) passing through the said slots (52) at each end, by means of a shaft.

One end of the first arm (51 ) is connected to the body (10) and the other end is connected to a second arm (51 ) via the slot (52). The two arms (51) mentioned here can rotate according to a first axis (R1 ) passing through the center of the slot (52).

A third arm (51 ) is rotatably connected to the second arm (51 ) from the slot (52) at the other end of the second arm (51 ) relative to the second axis (R2) passing through the center of the slot (52). The said third arm (51 ) is connected to the wing body (21).

Referring to Figures 1.C and 1.D; as stated before, the propeller (30) is positioned at the rear of the body (10). As with the wings (20), the propeller (30) stays closed before launch and opens after launch, thereby saving volume. The propeller (30) includes at least two propeller wings (31 ). The said propeller wings (31) are connected to a propeller body (32). The said propeller body (32) includes an engine connection opening (32a) that enables it to be associated with the engine. The engine shaft passes through said engine connection opening (32a) and rotates the propeller wings (31).

The propeller wings (31 ) are connected to the propeller body (32) by a connection element (33) in a rotatable manner. Here, the propeller wings (31 ) rotate according to a third axis (R3) passing through the center of the connection element (33). In the closed position, the propeller wings (31 ) are positioned longitudinally parallel to each other and perpendicular to the propeller body (32). After the launch, the propeller wings (31 ) rotate on the third axis (R3) and come to the position in Figure 2.B.

Referring to Figures 1.C and 2; after the unmanned aerial vehicle (1) is launched from the launch mechanism (F), the flaps (22) rotate according to a flap opening axis (Ra) passing through the junction of the flap (22) and the wing body (21). This rotational movement continues until the flaps (22) and the wing body (21 ) are approximately coplanar as in Figure 2.

Then, the wings (20) are opened by pivoting with respect to a flap opening axis (Rb) perpendicular to or approximately perpendicular to the flap opening axis (Ra). During the opening of the wings (20), the order of the opening movements of the flap (22) and the wing (20) may be changed, or the two movements may take place synchronously.

At the end of the wing (20) and flap (22) opening, the wings (20) are positioned perpendicular to the direction of the aircraft movement, and therefore a third rotational movement is performed, and with this movement, the wing (20) provides the positioning in Figure 2. In this movement, the wing (20) rotates relative to a wing rotation axis (Rc) perpendicular or approximately perpendicular to the flap and wing opening axis (Ra, Rb).

In addition, there is a rear wing (60) at the rear of the body (10), and the said rear wing (60) includes a rear vertical wing (61 ) and two rear horizontal wings (62) perpendicular to the said rear vertical wing (61 ). The said rear vertical and horizontal wings (61 , 62) also include flaps (22). The said rear wing (60) is also arranged in a foldable manner like the wings (20), and here the rear wing (60) is opened after launch.

Referring to Figure 2. A; as can be seen in the figure, the said unmanned aerial vehicle (1 ) is arranged symmetrically about an axis passing vertically through its center, and this arrangement greatly facilitates the movement of the aircraft. In addition, the wings (20) are specially arranged to extend outward from the aircraft's center of gravity.

An alternative wing connection (50) for connecting the wings (20) is shown in Figures 3 and 3. A. Here, the wing connection (50) is constructed on an intermediate arm (54). The intermediate arm (54) is connected to the body (10), especially to a groove provided on the body (10). An arc-shaped arm (51 ) is connected to the intermediate arm (54) relative to the second axis (R2). The said arm (51 ) is connected from the other end to an arm (51 ) formed in the form of an arc from the other end, and this arm (51 ) is directly connected to the wing (20). The other end of this arm is connected to another arm (51 ) provided in the form of a fork, with an arm connection element (53) in the form of a shaft positioned relative to the first axis (R1) passing through the two ends of the fork arm (51). Here, the fork arm (51 ) includes a pair of lugs and the arm connector (53) passes through said lugs.

In the closed position of the wings (20), the arc-shaped arms (51 ) are in the nested position. When the wings (20) start to open relative to the wing rotation axis (Rc) in Figures 3.B and 3.C, the spring arms (51 ) start to rotate relative to the first axis (R1) from their connection points. This rotational movement rotates until the two flaps (20) are fully opened. Here, the fork-shaped arm (51 ) rotates according to the second axis (R2) from the point where it is connected to the intermediate arm (54) in order to rotate the wing (20) according to the wing opening axis (Rb) during or before the rotation of the arc-shaped arms (51 ). When both rotational movements are completed, the wings (20) come to the fully open position in Figure 3.D.

Figure 3-3. D also shows the opening of the rear wing (60). It has been previously mentioned that the rear wing (60) includes a rear vertical wing (61 ) and two rear horizontal wings (62) perpendicular to said rear vertical wing (61 ). Before the unmanned aerial vehicle (1 ) is launched, the said three parts are positioned in such a way that they touch each other surface-to-surface within the longitudinally arranged wing slot (63) provided on the body (10). Following the launch, the rear vertical wing (61 ) and the rear horizontal wings (62) rotate together according to the first rear wing axis (Rd) and come out of the wing slot (63) by contacting the surface. Then, the said rear horizontal wings (62) rotate relative to a second rear wing axis (Re) perpendicular to the first rear wing axis (Rd) and are positioned approximately or exactly perpendicular to the rear vertical wing (61) and the rear wing (60) reaches the full open position in Figure 3.D. Here, the opening direction of the rear wing (60) is provided by a hinged spring provided at the junction of the rear vertical wing (61 ) and the rear horizontal wings (62).

In addition, although not shown in the figures, the said unmanned aerial vehicle (1 ) includes a camera, preferably a camera suitable for a quadrant tracking system, and a laser imaging detection and ranging system, also known as a LIDAR. The LIDAR system is used as an autonomous decision-making mechanism, especially after target (H) detection.

Although not shown in the figures, the unmanned aerial vehicle (1) may also include a parachute system. If the said parachute mission fails, it contributes to the landing of the unmanned aerial vehicle (1) without being damaged.

Referring to Figure 4; the said unmanned aerial vehicle (1 ) is a sub-element of a system used in target (H) detection and destruction.

The said system comprises a launch mechanism (F) to launch the unmanned aerial vehicle (1 ), a radar (3) that will provide presence detection in the airspace where the system will be used, an image acquisition element (2) to identify the type of asset, i.e. whether it is a target (H) when the said radar (3) provides presence detection, and a processing unit (4) that can communicate with the said unmanned aerial vehicle (1 ), launch mechanism (F), image acquisition element (2) and radar (3) and process the data it receives from them.

The image acquisition element (2) is preferably chosen as a camera, in particular an electro-optical camera. In addition, the said processing unit (4) can also be configured to allow the unmanned aerial vehicle (1 ) to be controlled manually.

The said system has been designed for a specific target detection and destruction method. Referring to Figure 5; in the said method, the radar (3) continuously controls the airspace. In the said airspace, when an element is detected, the image acquisition element (2) activates and takes an image to determine whether the said element is a target (H).

If the identification of the said image acquisition element (2) is in the direction of the element (H), an intersection point (KN) is preferably determined by the processing unit (4), taking into account the speed and direction of the target (H) and the speed of the unmanned launch vehicle (1 ). Once the intersection point (KN) is determined, the processing unit (4) ensures that the unmanned aerial vehicle (1 ) is launched towards the intersection point (KN) from the launch mechanism (F).

When the unmanned aerial vehicle (1 ) reaches the intersection point (KN), its cameras work and lock onto the target (H). Here, target (H) tracking can be achieved with the quadrant tracking system. Thereby, energy savings are achieved without using the tracking systems on the unmanned aerial vehicle (1 ) for a certain period.

When the unmanned aerial vehicle (1 ) approaches the target up to a certain threshold distance, its LIDAR system is turned on and the ammunition (40) is detonated by moving to the point that will cause maximum damage to the target.

Referring to Figure 5. A; in an alternative method, the path to be followed in case of more than one target (H) is shown. Here, the operation steps are the same up to the launch of the unmanned aerial vehicle (1 ) to the intersection point (KN). Here, the LIDAR is opened and if the distance between the targets (H) is short in the detonation distance of the ammunition (40), the optimum destruction point between the two targets (H), and more targets (H) depending on the situation, is determined autonomously and the ammunition (40) detonates.

The protection scope of the invention is given in the attached claims, and it cannot be limited to what has been described as an example in this detailed description under any circumstances. It is understood that a person with the skill in the related technique can put forth similar embodiments in the light of what has been described above, without departing from the main theme of the invention. REFERENCES

1. Liang Gao, Ge Li, Hongzhe Jin and Yanhe Zhu. “Aerodynamic characteristics of a novel catapult launched morphing tandem wing unmanned aerial vehicle” ■ February 2017

2. L. Dufour, K. Owen, S. Mintchev and D. Floreano. “A Drone with Insect-Inspired Folding Wings”. IEEE, December 2016

3. CORY SUDDUTH Post Graduate Thesis. “DESIGN OF A HYBRID ROCKET /

INFLATABLE WING UAV”. Oklohoma State University 2012