Title:
COMBUSTION CONTROL METHOD FOR HYBRID ROCKET
Document Type and Number:
Japanese Patent JP2673663
Kind Code:
B2
Abstract:
PURPOSE: To provide a combustion control method, by which speed increasing quantity can be precisely controlled while maintaining features of a solid propellant rocket, for a hybrid rocket.
CONSTITUTION: A liquid propellant tank 10, in which liquid propellant 11 pressurized at a pressure lower than a fuel pressure for a solid propellant rocket 1 is filled, is connected to an igniter 5 provided with a catalyst in a combustion chamber 3 of the solid propellant rocket 1 via an opening/closing valve 13 and a pressure check valve 14, and the liquid propellant 11 is fed to the igniter 5 in the combustion chamber 3 for igniting the solid propellant rocket 1. After supply of the liquid propellant 11 is stopped once by a combustion pressure of the solid propellant rocket 1, the liquid propellant 11 is automatically fed again following a drop of the combustion pressure nearby a finish of combustion of the solid propellant rocket 1, and when the predetermined speed increasing quantity is obtained, the opening/closing valve 13 is closed so as to cut off the supply of the liquid propellant 11 to the combustion chamber 3, and as a result, the speed increasing quantity is precisely controlled.
Inventors:
Atsuta Watanabe
Application Number:
JP12716994A
Publication Date:
November 05, 1997
Filing Date:
May 18, 1994
Export Citation:
Assignee:
Space Development Agency
International Classes:
F02K9/72; F02K9/95; (IPC1-7): F02K9/72; F02K9/95
Domestic Patent References:
| JP361161B1 | ||||
| JP4639166B1 |
Attorney, Agent or Firm:
Kenji Mogami
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