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Igniting and starting device of solid rocket engine

A technology for ignition and solid rockets, which is applied in the direction of rocket motor devices, machines/engines, jet propulsion devices, etc. It can solve the problems of deformation of the medicine box, low structural strength, and influence on the structure of the powder charge column, so as to ensure the working time, Effect of reducing deformation and avoiding impact

Active Publication Date: 2014-03-19
BEIJING POWER MACHINERY INST
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Problems solved by technology

However, due to the low structural strength of the plastic medicine box, when the radius of the ring igniter is large, the impact of the electric initiator is easy to damage the medicine box, which is not conducive to the propagation of the electric initiator flame inside the igniter, and affects the work of the igniter performance, making the ignition process of the engine prolong
The single test proves that, in the corresponding part of the electric detonator, the deformation of the medicine box is relatively serious under the impact of the electric detonator, and there is a possibility of affecting the structure of the corresponding part of the charge column.

Method used

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Embodiment Construction

[0017] In order to make the purpose, content, and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0018] Such as figure 2 As shown, the embodiment of the present invention provides an ignition and starting device for a solid rocket motor. The ignition and starting device includes an annular igniter 1, a buffer pad 2, and a charging grain 3, and the charging grain 3 is located at the One side of the ring igniter 1, and a certain distance between the charge column 3 and the ring igniter 1, the buffer pad 2 is two pieces, installed on the ring igniter 1 close to the One side of the charged powder column 3, and respectively located at the two ends of the same diameter on the ring igniter 1 (corresponding to the installation position of the electric detonator), the top surface of the buffer pad 2 and the charged powder...

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Abstract

The invention relates to an igniting and starting device of a solid rocket engine, and belongs to the technical field of solid rocket engines. Through the matching between selected material and the thickness of a buffering cushion arranged on an annular igniter and the distance matching between the top surface of the buffering cushion and a charging grain, deformation of an annular igniter shell under the impact of an electric initiating device is reduced, and the influence on the structure of the charging grain by the annular igniter shell in the process is effectively avoided. Meanwhile, the annular igniter shell can maintain integrity in the working process, and the working performance of the annular igniter is ensured.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to an ignition device for solid rocket motors. Background technique [0002] The solid rocket motor is a power device widely used in weapons and equipment, and the ring igniter, which has flexible installation positions and structural dimensions that can change with the adaptability of the installation site structure, has been widely used in it. [0003] In order to ensure that the structure of the ring igniter of the ignition and starting device of the solid rocket motor does not affect the structure of the powder charge column during the working process, most ring igniters use plastic pill boxes. However, due to the low structural strength of the plastic medicine box, when the radius of the ring igniter is large, the impact of the electric initiator is easy to damage the medicine box, which is not conducive to the propagation of the electric initiator flame inside the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95
Inventor 刘顶新吴华祯苏华何海燕张鹏峰
Owner BEIJING POWER MACHINERY INST
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