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Negative pressure intensity index propellant

A technology of propellant and negative pressure, which can be used in offensive equipment, generation of compressed gas, ammonium perchlorate composition, etc., can solve the problems of poor low temperature performance, low energy performance, narrow operating temperature range, etc. Low, high energy, wide temperature range effects

Active Publication Date: 2019-03-15
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the negative pressure index propellants that have been widely applied and researched are mainly double-base propellants, but their energy performance is low, and the use temperature range is narrow, especially the low temperature performance is poor.

Method used

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  • Negative pressure intensity index propellant
  • Negative pressure intensity index propellant
  • Negative pressure intensity index propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0049] (1) Propellant formula composition (mass percentage %):

[0050]

[0051] (2) Propellant performance:

[0052] Pressure index: -0.09 (3 ~ 9MPa);

[0053] Residue content: 2.1%;

[0054] Combustion temperature: 2087K (6.86MPa);

[0055] Burning rate: r (6.86MPa) = 5.2mm / s;

[0056] Specific impulse: 2131.6N.s / kg

[0057]Low temperature performance: Tg=-60.1°C, maximum elongation ε at -50°C m =45.3%

[0058] Safety performance: Passed seven low-vulnerability tests, hazard level 1.3

Embodiment 2

[0060] (1) Propellant formula composition (mass percentage %):

[0061]

[0062] (2) Propellant performance:

[0063] Pressure index: -1.08 (3 ~ 9MPa);

[0064] Residue content: 2.3%;

[0065] Combustion temperature: 2150K (6.86MPa);

[0066] Burning rate: r (6.86MPa) = 4.8mm / s;

[0067] Specific impulse: 2145.5N.s / kg

[0068] Low temperature performance: Tg = -61.2°C, maximum elongation ε at -50°C m =55.1%

[0069] Safety performance: Passed seven low-vulnerability tests, hazard level 1.3

Embodiment 3

[0071] (1) Propellant formula composition (mass percentage %):

[0072]

[0073]

[0074] (2) Propellant performance:

[0075] Pressure index: -0.61 (3 ~ 9MPa);

[0076] Residue content: 1.9%;

[0077] Combustion temperature: 1938K (6.86MPa);

[0078] Burning rate: r (6.86MPa) = 4.5mm / s;

[0079] Specific impulse: 2029.2N.s / kg

[0080] Low temperature performance: Tg=-60.5°C, maximum elongation ε at -50°C m =50.5%

[0081] Safety performance: Passed seven low-vulnerability tests, hazard level 1.3

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Abstract

The invention relates to a negative pressure intensity index propellant, and belongs to the technical field of solid propellants. The negative pressure intensity index propellant provided by the invention comprises the following components in percent by mass: 6-20% of a blended adhesive, 5-20% of a plasticizer, 55-70% of a main oxidant, 5-20% of an auxiliary oxidant, 0.4-1.0% of a curing agent and0.4-0.7 % of a functional auxiliary agent, wherein the blended adhesive is a mixture of ethylene oxide-tetrahydrofuran copolyether PET and cellulose acetate CA; the cellulose acetate CA accounts for5-10% of the total mass of the adhesive; the plasticizer is a mixture of triethylene glycol dinitrate TEGDN and triacetin GTA; the blended adhesive is the mixture of the ethylene oxide-tetrahydrofurancopolyether PET and the cellulose acetate CA. The propellant has the characteristics of a negative pressure intensity index, low combustion temperature, low residue, high energy, good safety performance, a wide applicable temperature range and the like.

Description

technical field [0001] The invention relates to a propellant with a negative pressure index and belongs to the technical field of solid propellants. Background technique [0002] With the development of missile weapon defense technology, countries around the world are vigorously developing missile interception technology for ballistic missile defense purposes. The kinetic energy interceptor is an interceptor warhead with its own power, self-seeking and relying on its own kinetic energy to kill and destroy the target by collision. The thrust requirements of the attitude control and orbit control systems of kinetic interceptors are quite different, so it is generally inclined to combine the negative pressure index propellant technology with the variable throat surface technology of the swirl valve to control the effective exhaust area of ​​the nozzle throat. In addition, due to the special working conditions of the attitude control power system, the propellant is also require...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B29/22C06B31/28C06B45/10C06D5/06
CPCC06B29/22C06B31/28C06B45/10C06D5/06
Inventor 李伟潘新洲汪越尹欣梅王小英张林唐泉
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY