Press-fit high density fuel-rich propellant and preparation method thereof

A fuel-rich propellant, high-density technology, applied in offensive equipment, explosive processing equipment, compressed gas generation, etc., can solve the problems of poor fuel-rich propellant, short production cycle, low energy consumption, etc., and achieve low cost , short production cycle and low energy consumption

Inactive Publication Date: 2019-01-15
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention provides a press-packed high-density fuel-rich propellant for a solid rocket ramjet. The propellant of the invention does not require a solidification and cross-linking process, has a short p...

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] A press-packed high-density fuel-rich propellant, the formula composition (calculated by mass percentage) is as follows:

[0042] Binder: F 23 Rubber, 3.5%; PTFE, 1.5%;

[0043] Oxidizer: AP, 15%, d 50 298um;

[0044] Oxidant: KP, 15%; d 50 The KP content of 288um is 7%, d 50 The KP content of 120um is 8%;

[0045] Fuel: B powder, 45%; d 50 The B powder content of 30um is 24%, d 50 The B powder content of 5um is 21%;

[0046] Fuel: magnesium powder, 5%, d 50 10um; aluminum powder, 10%, d 50 5um;

[0047] Plasticizer: TA, 1%;

[0048] Desensitizer: Graphite, 0.5%; Paraffin, 1.5%;

[0049] Combustion Catalyst:, Fe 2 o 3 , 1%; Catoxin, 1%.

[0050] The preparation method is:

[0051] (1) Dissolve F23 rubber with ethyl acetate solvent, the weight ratio of F23 rubber to solvent is 1:4, and configure it into glue; weigh the above components according to the proportion;

[0052] (2) Put the glue, polytetrafluoroethylene, desensitizer, accelerator, and combusti...

Embodiment 2

[0057] A press-packed high-density fuel-rich propellant, the formula composition (calculated by mass percentage) is as follows:

[0058] Binder: BAMO-GAP copolymer, 3%;

[0059] Oxidant: KP, 20%, d 50 288um;

[0060] Oxidant: AP, 15%; d 50 AP content of 298um is 7%, d 50 The AP content of 100um is 8%;

[0061] Fuel: B powder, 45%; d 50 The B powder content of 30um is 22%, d 50 The B powder content of 5um is 23%;

[0062] Fuel: magnesium alloy, 10%, d 50 10um; Zr, 3%, d 50 5um;

[0063] Plasticizer: BDNPF / A, 1%;

[0064] Desensitizer: Graphene, 1%; Graphite, 1%;

[0065] Combustion Catalyst: 1%, Octylferrocene.

[0066] The properties of the propellant are as follows:

[0067] The theoretical density is 2.174g / cm 3 , grain (Ф40mm) density is 2.120g / cm 3 , the calorific value is 45.28MJ / kg, the pressure index is 0.42, and the response levels of the fast cook-off test, slow cook-off test and bullet impact test are all burning.

[0068] The preparation method is: ...

Embodiment 3

[0073] A press-packed high-density fuel-rich propellant, the formula composition (calculated by mass percentage) is as follows:

[0074] Binder: BAMO-THF copolymer, 6%;

[0075] Oxidizer: AP, 20%, d 50 298um;

[0076] Oxidant: KP, 25%; d 50 The KP content of 288um is 13%, d 50 The KP content of 120um is 12%;

[0077] Fuel: B powder, 40%; d 50 The B powder content of 30um is 25%, d 50 The B powder content of 5um is 15%;

[0078] Fuel: magnesium alloy, 5%; d 50 10um;

[0079] Plasticizer: BuNENA, 2%;

[0080] Combustion catalyst: octyl ferrocene, 0.5%; cattosine, 0.5%;

[0081] Desensitizing agent: paraffin wax, 0.5%; polyethylene wax, 0.5%;

[0082] The properties of the propellant are as follows:

[0083] The theoretical density is 2.09g / cm 3 , grain column (Ф40mm) density is 2.038g / cm 3 , the calorific value is 46.62MJ / kg, the pressure index is 0.39, and the response levels of the fast cook-off test, slow cook-off test and bullet impact test are all burning.

...

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Abstract

The invention relates to a press-fit high density fuel-rich propellant for solid rocket ramjets and a preparation method thereof. The press-fit high density fuel-rich propellant comprises: 30%-45% ofan oxidant; 45%-60% of fuel; 3%-6% of a binder; 1%-3% of a plasticizer; 1%-3% of a desensitizing agent; and 0.5-2% of a combustion catalyst. The propellant provided by the invention has the characteristics of no need for curing and crosslinking, short production cycle, low cost and low energy consumption, and solves the problem of poor technological performance of existing cast type high solid content (a solid content of greater than 88%) fuel-rich propellants. The propellant provided by the invention has good compressibility, can achieve unidirectional compaction at room temperature, and whenthe specific pressure is lower than 240MPa, the density of the propellant grain (phi 40mm) is 97.5% of the theoretical density. The propellant provided by the invention has high energy and density, the density of the propellant is greater than 2.0g/cm<3>, the calorific value is greater than 45MJ/kg, the primary injection efficiency is more than 96%, and the pressure index is less than 0.55.

Description

technical field [0001] The invention relates to a press-packed high-density fuel-rich propellant for a solid rocket ramjet, belonging to the field of composite propellants. Background technique [0002] Fuel-rich propellants, also known as oxygen-depleted propellants, contain relatively less oxidizer and more metallic combustibles and have high energy characteristics. Oxygen-deficient solid propellant is the power source of solid rocket ramjet, mainly composed of oxidant and fuel. Oxygen-depleted solid propellant can use oxygen in the air, increase the content of high-energy fuel, and reduce the specific gravity of oxidizer, so it has a higher Payload, while reducing the quality of the engine, not only economical but also greatly improved the specific impulse of the engine, prolonging the range of the missile. The excellent performance of the solid ramjet is based on the high-energy characteristics of the oxygen-poor propellant. The higher the energy of the oxygen-poor prop...

Claims

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Application Information

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IPC IPC(8): C06B33/12C06B21/00C06D5/06
CPCC06B21/00C06B33/12C06D5/06
Inventor 熊伟强曹仕瑾王鹏张天福赵新岩李忠友高扬程迪张艳
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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