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Pulse trigger

A technology of pulse triggering and ignition tube, which is applied to machines/engines, rocket engine devices, jet propulsion devices, etc., can solve the problems of less query results, less verification of large engines, and lack of verification technology, and achieves clear principles and consistency. Good, good craftsmanship

Inactive Publication Date: 2015-04-01
中国航天科工集团第六研究院二一〇所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The pulse-triggered unstable combustion of solid rocket motors has been studied abroad for many years, and the corresponding research theories and analysis methods have been perfected day by day. Especially in China, there is a serious lack of unstable combustion ground verification technology for solid rocket motors
[0003] Secondly, foreign research on pulse triggers is mainly used in the test verification of scaled-down engines, and the verification of large-scale engines is less. Due to technical confidentiality reasons, there are few query results

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Engine pulser trigger pressure curve as Figure 7 shown.

[0041] Pulse trigger outline size: Φ60mm×205.5mm; gas inlet diameter: Φ14mm; trigger dose: 45g; trigger times: 2 times; trigger time engine work: 15s, 17s; trigger pressure: 0.22MPa, 0.28MPa; trigger action time : 2ms.

Embodiment 2

[0043] Engine pulser trigger pressure curve as Figure 8 shown.

[0044] Pulse trigger outline size: Φ60mm×205.5mm; gas inlet diameter: Φ14mm; trigger dose: 65g; trigger times: 1 time; trigger time engine operation: 4.5s; trigger pressure: 2.59MPa; trigger action time: 2.3ms.

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Abstract

The invention provides a pulse trigger. A medicine box is a hollow chamber; a thermal insulating layer covers the internal wall of the chamber; the chamber is full of ignition powder; two ends of the medicine box are respectively connected with an end cap and a connecting chamber assembly; the middle of the end cap is fixedly connected with an ignition tube; the connecting chamber is a through hollow chamber; the thermal insulating layer covers the internal wall of the chamber; a separation plate is arranged and positioned inside the connecting chamber through a supporting ring; the separation plate is provided with a plurality of through holes; a communicating part of the medicine box and the connecting chamber positions a sealing piston assembly through a stepped hole; the sealing piston assembly comprises a sealing piston and a thermal insulating layer; the sealing piston seals the communicating position of the medicine box and the connecting chamber and can be separated under combustion pressure of ignition powder; the medicine box and the connecting chamber are guaranteed to be communicated; the thermal insulating layer covers the sealing piston. The pulse trigger can increase the working pressure strong pulse by 0 to 20% in 0 to 5millisecond short time at any time during working of and engine and saves target range test costs.

Description

technical field [0001] The invention relates to the field of solid rocket motor test verification. Background technique [0002] The pulse trigger is one of the important technologies for the ground verification of pulse-triggered unstable combustion of solid rocket motors. The use of pulse triggers can effectively verify the phenomenon of pulse-triggered unstable combustion of solid rocket motors. The pulse-triggered unstable combustion of solid rocket motors has been studied abroad for many years, and the corresponding research theories and analysis methods have been perfected day by day. Especially in China, there is a serious lack of unstable combustion ground verification technology for solid rocket motors. [0003] Secondly, foreign research on pulse triggers is mainly used in the test verification of scaled engines, and the verification of large engines is less. Due to technical confidentiality reasons, there are few query results. Contents of the invention [000...

Claims

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Application Information

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IPC IPC(8): F02K9/96
Inventor 王小永王栋万东王占利高凤莲申清芳赵海波
Owner 中国航天科工集团第六研究院二一〇所
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