Thrust-adjustable multistage pulse solid rocket engine

A rocket engine and pulse solid technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of complex structure, difficult dynamic sealing control, and inability to adjust the thrust of pulse solid rocket motor in real time, etc., to achieve structural Simple, easy-to-adjust effects

Active Publication Date: 2019-11-19
北京灵动飞天动力科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The disadvantage of the existing multi-stage pulse solid rocket motor is that the opening modes of the prefabricated holes on the compartment are all passive, that is, taking the two-stage pulse solid rocket motor as an example, charge the charge in the two-stage pulse combustion chamber, and ignite a pulse combustion The high-temperature and high-pressure gas generated after the fuel in the chamber flushes away the blockage on the compartment
At this time, because the size of the ...

Method used

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  • Thrust-adjustable multistage pulse solid rocket engine
  • Thrust-adjustable multistage pulse solid rocket engine

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Embodiment 1

[0020] This embodiment provides a thrust-adjustable multi-stage pulse solid rocket motor. Active holes are added to the compartment of the multi-stage pulse solid rocket motor. The structure is simple, the adjustment and control are convenient, and the multi-stage pulse solid rocket motor can be adjusted according to engineering needs. thrust.

[0021] The multi-stage pulse solid rocket motor includes more than two pulse combustion chambers connected in sequence and a compartment 3 for connecting adjacent pulse combustion chambers. The compartment 3 is connected to two adjacent pulse combustion chambers through a connection card fast 7 , the connection is sealed by an O-ring 8.

[0022] Taking the two-stage pulse solid rocket motor as an example, the adjacent two pulse combustion chambers are the first pulse combustion chamber 4 and the second pulse combustion chamber 1, the first pulse combustion chamber 4 is equipped with a pulse charge 5, and the first pulse combustion cham...

Embodiment 2

[0029] On the basis of Embodiment 1, the blocking cover opening device includes: pin 11, spring 12, pyrotechnics and excitation device, the non-metallic blocking cover 10 outer circumference of the I-shaped through hole facing the second pulse combustion chamber 1 side along the radial direction Open the prefabricated hole, after the pin 11, the spring 12 and the pyrotechnic device are loaded into the prefabricated hole in sequence, the opening of the prefabricated hole is blocked from the outer periphery of the compartment 3, and a via hole is opened at the plugged place, and the excitation device passes through the via hole and connects with the pyrotechnic device. For the connection of the device, the two ends of the spring 12 are respectively in contact with the shoulder of the pin 11 and the pyrotechnic device. Before the pyrotechnic device moves, the spring 12 is in a compressed state, which is used to compress the pyrotechnic device to the blockage of the compartment 3 A...

Embodiment 3

[0031] On the basis of Embodiment 2, the pyrotechnic product is selected as the electric pyrotechnic device 13, and the excitation device is selected as the electric pyrotechnic device 9. Product 13 exploded.

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Abstract

The invention discloses a thrust-adjustable multistage pulse solid rocket engine. The multistage pulse solid rocket engine comprises more than two pulse combustion chambers, explosives arranged in thepulse combustion chambers and compartments used for connecting every two adjacent pulse combustion chambers, wherein more than one T-shaped through hole and more than one I-shaped through hole are formed in each compartment and are used for communicating between every two adjacent pulse combustion chambers; the large ends of the T-shaped through holes face the combustion chamber of the rear end and are provided with plug covers which are in interference fit with the T-shaped through holes, and the plug covers are closed under the high-pressure action of the combustion chamber at the rear endand are opened under the high-pressure action of the combustion chamber at the front end; and the two ends of the I-shaped through holes are correspondingly provided with plug covers which are in interference fit with the interiors of the I-shaped through holes, plug cover opening devices are arranged on the peripheries of the plug covers at the front ends of the I-shaped through holes and are used for punching the plug covers, facing the front end combustion chamber, in the I-shaped through holes, high pressure in the front end combustion chamber is used for opening the plug covers, facing the rear end combustion chamber, of the I-shaped through holes, so that the flow area between the every two adjacent combustion chambers is actively adjustable, and the push force of the multistage pulse solid rocket engine is actively adjusted.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to a thrust-adjustable multistage pulse solid rocket motor. Background technique [0002] At present, as a new way to realize the energy management technology of solid rocket motors, pulsed solid rocket motors are the hotspots of current research. During the working process of the pulsed solid rocket motor, it can effectively control the engine energy output in real time, realize the optimal distribution of engine energy according to the system requirements, orderly control the opening sequence of the multi-stage pulse chamber, and then orderly control the intermittent release of the thrust, more reasonably Distribute the propellant energy, effectively improve the utilization efficiency of the engine energy, increase the range of the missile, and improve its maneuverability and actual combat capability. [0003] The disadvantage of the existing multi-stage pulse solid r...

Claims

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Application Information

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IPC IPC(8): F02K9/08F02K9/32F02K9/95
CPCF02K9/08F02K9/32F02K9/95
Inventor 王君祺郑才浪吴刚
Owner 北京灵动飞天动力科技有限公司
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