Formula for reducing high pressure exponent of solid propellant

A solid propellant, high-pressure technology, applied in the direction of ammonium perchlorate composition, etc., can solve the problems such as the negative impact of propellant performance, and achieve the effects of low smoke signal characteristics, scientific proportioning, and good compatibility

Inactive Publication Date: 2017-01-18
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this type of method has a relatively large negative impact on the performance of the propellant, including

Method used

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  • Formula for reducing high pressure exponent of solid propellant
  • Formula for reducing high pressure exponent of solid propellant
  • Formula for reducing high pressure exponent of solid propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] ⑴ Propellant composition (mass percentage)

[0015]

[0016] (2) Propellant performance: Before formula optimization, the pressure index of propellant 11MPa~19MPa is 0.64, after formula optimization, the pressure index of propellant 11MPa~19MPa is 0.46.

Embodiment 2

[0018] ⑴ Propellant composition (mass percentage)

[0019]

[0020] (2) Propellant performance: Before formula optimization, the pressure index of propellant 11MPa~19MPa is 0.62, after formula optimization, the pressure index of propellant 11MPa~19MPa is 0.45.

Embodiment 3

[0022] ⑴ Propellant composition (mass percentage)

[0023]

[0024] (2) Propellant performance: Before formula optimization, the pressure index of propellant 11MPa~19MPa is 0.61, after formula optimization, the pressure index of propellant 11MPa~19MPa is 0.48.

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Abstract

The invention relates to a formula for reducing high pressure exponent of solid propellant and improving the performances of a rocket engine fuel. The formula is characterized in that 20-30% of an adhesive and a plasticizer, 0-15% of an oxidant ammonium perchlorate (AP), 30-45% of nitramine explosive, 10-30% of insensitive high explosive FOX-7 with the granularity of 8-200 [mu]m, 1.0-2.0% of a curing agent and 0.5-2% of a combustion stabilizing agent are added to a solid propellant system. The insensitive high explosive FOX-7 with good dispersibility and component compatibility, the AP, the adhesive and the plasticizer are used to guarantee the signal characteristic and the energy, technology and mechanical performances of the propellant, reduce the high pressure exponent of the propellant and guarantee the working reliability of an engine. The formula has the advantages of scientific formula, convenience in production, obvious effect and stable performances.

Description

technical field [0001] The invention relates to a method for improving the performance of a high-energy low-signature solid propellant in the field of aerospace engines, in particular to a formula for reducing the high-pressure index of the solid propellant. Background technique [0002] High-energy low-signature solid propellants have important application prospects, because the content of aluminum powder (Al powder) in the propellant system is small, or there is no aluminum powder (Al powder), the content of ammonium perchlorate (AP) is small, and the content of nitric acid There are many factors such as amine (HMX or RDX) content, so there is a problem of high pressure index at high pressure, and it seriously affects the reliability of the normal operation of the solid rocket motor. [0003] In the prior art, technical measures such as adding a burning rate regulator to the propellant system to adjust the particle size distribution of the solid filler and the plasticizing...

Claims

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Application Information

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IPC IPC(8): C06B29/22
Inventor 宋琴顾健尹必文吴京汉代志高项丽
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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