Tail-ignitable solid-fuel rocket motor
A rocket engine and solid fuel technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of difficult ignition and combustion, unstable performance of rocket engines, and difficult ignition, etc., to achieve convenient implementation and structure Simple, stable performance
Active Publication Date: 2016-07-06
AEROSPACE LIFE SUPPORT IND LTD
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Problems solved by technology
The tail ignition can only ignite the solid fuel at the tail of the rocket first, and it is difficult to achieve ignition and combustion, resulting in unstable rocket engine performance, especially for solid rocket engines with low burning rate propellants and high packing density. more difficult to ignite
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Embodiment Construction
[0020] Such as figure 1 The shown embodiment of the solid fuel rocket motor capable of tail ignition of the present invention includes a combustion chamber 4, a nozzle assembly 5 and a solid fuel 3, the nozzle assembly 5 is arranged at the tail end of the combustion chamber 4, and the solid fuel 3 is arranged on the combustion chamber. In the chamber 4; it is characterized in that: the solid fuel rocket engine also includes an ignition box 2, an ignition tool 6 and its firing mechanism 7, the ignition box 2 is arranged at the front end of the solid fuel in the combustion chamber, and the ignition tool 6 is arranged at the nozzle assembly 5 end of . A buffer pad 1 is provided between the front end of the combustion chamber and the ignition box to compensate for changes in the length of the solid fuel 3 due to temperature.
[0021] The present invention is a two-stage ignition mode composed of an igniter 6 installed at the tail of the rocket and an ignition box installed at the...
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The invention relates to a solid fuel rocket motor capable of tail ignition, which comprises a combustion chamber, a nozzle assembly and a solid fuel, the nozzle assembly is arranged at the tail end of the combustion chamber, and the solid fuel is arranged in the combustion chamber; the solid fuel rocket motor It also includes an ignition box, an ignition tool and its firing mechanism. The ignition box is arranged at the front end of the solid fuel in the combustion chamber, and the ignition tool is arranged at the tail end of the nozzle assembly; the solid fuel is a cylinder, and its outer wall and the inner side of the combustion chamber With a gap between the walls, the nozzle combustor end of the nozzle assembly is aligned with the center tube of the solid fuel cartridge. The invention can realize mechanical percussion, ignition at the tail, and can firstly ignite the solid fuel at the head of the rocket, and the rocket engine has stable working performance.
Description
technical field [0001] This invention relates to solid fuel rocket motors. Background technique [0002] Existing solid fuel rocket motors all adopt the head ignition method. This ignition method can first ignite the solid fuel in the rocket head, which is easier to ignite and burn, and the rocket engine has stable working performance. At present, the head ignition method usually uses electric shock. In some cases, the structural characteristics of the product require the use of a mechanical method to fire the rocket, and the direction of the rocket's movement is opposite to the direction of the mechanical force for starting. For this reason, only the tail ignition method is adopted. The tail ignition can only ignite the solid fuel at the tail of the rocket first, and it is difficult to achieve ignition and combustion, resulting in unstable rocket engine performance, especially for solid rocket engines with low burning rate propellants and high packing density. It is more d...
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IPC IPC(8): F02K9/08F02K9/95
Inventor 马金贵赵迎春
Owner AEROSPACE LIFE SUPPORT IND LTD