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A small inertial ignition device

An ignition device and inertial technology, applied in the field of the separation structure of the payload of a launch vehicle, can solve the problems of weak anti-electromagnetic interference capability, unstable performance of the ignition device, difficult storage, etc. Simple and compact effect

Active Publication Date: 2020-08-07
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The electric control type igniter technology is already mature, and the design is correspondingly simple, but the performance of the electric control type ignition device is unstable, the anti-electromagnetic interference ability is weak, and it is not easy to store

Method used

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Embodiment Construction

[0025] see Figure 1-6 , the present invention relates to a small inertial ignition device, including a rotor mechanism 1 with a built-in ignition system arranged in a casing 5, a clock timing mechanism 2, an overload identification and safety mechanism 3, a seat body 4 with an ignition tube, and a quick reset mechanism 6 The center of the housing 5 is provided with a rotor mechanism 1 with a built-in ignition system, and the rotor mechanism 1 with a built-in ignition system has an ignition mechanism; the front side of the rotor mechanism 1 with a built-in ignition system is provided with an overload identification and safety mechanism 3; the rear of the rotor mechanism 1 with a built-in ignition system The side is provided with a quick reset mechanism 6 and a clock timing mechanism 2 respectively from top to bottom; a seat body 4 with an ignition tube is provided at the bottom of the shell 5, and an ignition tube is built in the seat body 4 with an ignition tube; The spring 7...

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Abstract

The invention discloses a small inertia ignition device. The small inertia ignition device comprises a rotor mechanism of a build-in ignition system, a clock timing mechanism, an overload identification and safety mechanism, a seat body with an ignition tube and a rapid reset mechanism which are arranged in a shell; the rotor mechanism of the build-in ignition system is arranged in the center of the shell; and an ignition mechanism is arranged in the rotor mechanism of the built-in ignition system. When the small inertia ignition device senses that the flight acceleration of a carrier reachesa fixed value, a timer is started, and when the lasting time of the fight acceleration reaches a certain time, a firing pin can reliably unlock and excite a firing assembly to ignite a gas generator;and if the lasting time of the flight acceleration is not longer than a certain time, the inertia ignition device returns to an initial state rapidly in a short time. The small inertia ignition devicehas the advantages of high explosion suppression and anti-electromagnetic interference capability, simple and compact structure, good safety, high response to small overload, long action time and stable performance.

Description

technical field [0001] The invention relates to a small-sized inertial ignition device, which belongs to the field of payload separation structures for launch vehicles. Background technique [0002] The ignition device used to ignite the gas generator is mostly controlled electrically or mechanically. The electric control type igniter technology is already mature, and the design is correspondingly simple, but the performance of the electric control type ignition device is unstable, the anti-electromagnetic interference ability is weak, and it is not easy to store. For the purely mechanical control type ignition device, there are few applications, and only the drag reducer in the Trident series missiles of the United States in the 1970s and 1980s has adopted this purely mechanical ignition device. Contents of the invention [0003] (1) Technical problems to be solved [0004] Aiming at the above-mentioned deficiencies in the prior art, the present invention proposes a sma...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23Q13/00
CPCF23Q13/00
Inventor 张乔飞胡振兴唐科陈楷路志峰张晓晖宋保永陈岱松侯金瑛宋乾强张亮荣晶晶权晓波
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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