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Residue conductive solid propellant burning rate testing and explosive binding device

A technology of solid propellant and drug binding, applied in jet propulsion device, rocket engine device, machine/engine, etc., can solve problems such as the sensitivity of amplification timer, and achieve the effect of reliable performance, easy implementation and simple structure.

Active Publication Date: 2021-03-19
SHANGHAI AEROSPACE CHEM ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This technology will amplify the sensitivity of the timer by adding a sliding resistance with adjustable resistance, and at the same time put forward higher requirements for the consistency of the drug binding device, the target wire body resistance and the contact resistance of the two, and is not suitable for mass production. test

Method used

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  • Residue conductive solid propellant burning rate testing and explosive binding device
  • Residue conductive solid propellant burning rate testing and explosive binding device
  • Residue conductive solid propellant burning rate testing and explosive binding device

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Embodiment Construction

[0023] The present invention will be described in detail below based on specific embodiments and with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0024] figure 1 , figure 2 A schematic structural diagram of a residue conductive solid propellant burning rate test binding device provided in an embodiment of the present invention, wherein, figure 1 It is a schematic diagram of the front part of the drug binding device, figure 2 It is the rear schematic diagram of the drug binding device.

[0025] The drug binding device for testing the combustion rate of residue conductive solid propellant in the embodiment of the present invention includes:

[0026] The first plug 1, the second plug 6, the third plug 22, the fourth plug 23, the base 4, the medicine strip socket 5, the first transition assembly, the second transition assembly...

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Abstract

The invention discloses a residue conductive solid propellant burning rate testing and explosive binding device. The device comprises a first plug, a second plug, a third plug, a fourth plug, a base,a medicine strip socket, a first transition assembly, a second transition assembly, a third transition assembly, a fourth transition assembly, a first supporting rod nut, a second supporting rod nut,a third supporting rod nut, a fourth supporting rod nut, a first supporting rod, a second supporting rod, a third supporting rod, a fourth supporting rod and a spring piece. The first transition assembly comprises a first transition nut and a second fastening nut, the second transition assembly comprises a second transition nut and a second fastening nut, the third transition assembly comprises athird transition nut and a third fastening nut, and the fourth transition assembly comprises a fourth transition nut and a fourth fastening nut. The device is reliable in performance and simple in structure.

Description

technical field [0001] The invention belongs to the technical field of solid propellant burning rate testing, in particular to a residue conductive solid propellant burning rate testing binder. Background technique [0002] The drug binding device is an important part of the solid propellant static burning rate (target line method) test. Its main function is to fix the propellant rod and pass through the ignition line, the first target line and the second The target line is connected to the control circuit through the drug binding device to realize the ignition of the propellant charge and the timing of the target line, and then calculate the burning rate of the propellant. However, with the development of tactical missile weapon systems in the direction of high performance, integration, intelligence, and actual combat, higher requirements are placed on the performance of solid propellants, so it is imperative to increase the content of ammonium perchlorate and aluminum powd...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/95F02K9/97F02K9/24F02K9/34
CPCF02K9/96F02K9/95F02K9/97F02K9/24F02K9/343
Inventor 樊荣万代红沈肖胤李京修姜洪伟鲍海明邱礼蒋建霞车沈荣吴斌杨佳炜陈峰白玉兰沈坚
Owner SHANGHAI AEROSPACE CHEM ENG INST
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