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A kind of pressure index modifier of solid propellant

A solid propellant and regulator technology, which is applied in the production of compressed gas, offensive equipment, non-explosive/non-thermal agent components, etc. obvious effect

Active Publication Date: 2020-07-21
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Adjusting the AP particle size of the oxidant can reduce the pressure index of the propellant to a certain extent, but at the same time it will greatly increase the burning rate of the propellant; while changing the type of plasticizer will reduce the pressure index while reducing the energy performance of the propellant. a substantial reduction in

Method used

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  • A kind of pressure index modifier of solid propellant
  • A kind of pressure index modifier of solid propellant
  • A kind of pressure index modifier of solid propellant

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0019] PEG / NG / BTTN / HMX propellant blank formulation, Co-free 3 o 4 ·CuO composite metal oxide pressure index regulator, see Table 1 for propellant composition.

[0020] Table 1 PEG / NG / BTTN / HMX propellant blank formula composition

[0021]

[0022] Does not contain Co 3 o 4 The combustion performance of the CuO composite metal oxide pressure index modifier blank propellant formula is as follows:

[0023] 1) Propellant burning rate at standard pressure of 6.86MPa: r 6.86MPa =12.82mm / s

[0024] 2) Under the pressure of 3-12MPa, the pressure exponent of propellant burning rate conforms to r=3.2666p 0.71 , n=0.71

Embodiment 2

[0026] PEG / NG / BTTN / HMX propellant blank formulation, add 0.5% Co 3 o 4 ·CuO composite metal oxide pressure index regulator, see Table 2 for propellant composition.

[0027] Table 2 PEG / NG / BTTN / HMX propellant formulation composition

[0028]

[0029]

[0030] Contains 0.5% Co 3 o 4 The combustion performance of the propellant formula of the CuO composite metal oxide pressure index regulator is as follows:

[0031] 1) Propellant burning rate at standard pressure of 6.86MPa: r 6.86MPa =12.80mm / s

[0032] 2) Under the pressure of 3-12MPa, the pressure exponent of propellant burning rate conforms to r=3.7322p 0.64 , n=0.64

Embodiment 3

[0034] In the blank formula of PEG / NG / BTTN / HMX propellant, add 1.0% Co 3 o 4 ·CuO composite metal oxide pressure index modifier, see Table 3 for propellant composition.

[0035] Table 3 PEG / NG / BTTN / HMX propellant formulation composition

[0036]

[0037] Contains 0.5% Co 3 o 4 The combustion performance of the propellant formula of the CuO composite metal oxide pressure index regulator is as follows:

[0038] 1) Propellant burning rate at standard pressure of 6.86MPa: r 6.86MPa =12.81mm / s

[0039] 2) Under the pressure of 3-12MPa, the pressure exponent of propellant burning rate conforms to r=4.6163p 0.53 , n=0.53

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Abstract

The present invention relates to a pressure index regulator of a solid propellant. In the prior art, the burning rate pressure index of the PEG / nitrate / nitramine system solid propellant is too high. A purpose of the present invention is to solve the problem in the prior art. The invention provides a pressure index regulator of a solid propellant, wherein Co3O4 and CuO are compounded according to a mass ratio of 1:1 to form the pressure index regulator. According to the present invention, based on the PEG / nitrate / nitramine system solid propellant, after 1.0% of the metal oxide composite pressure index regulator is added, the pressure index of the propellant can be minimized to 0.53 from 0.71 while the burning rate basically remains the unchanged state; and with the promotion of the regulator in the PEG / nitrate / nitramine system propellant, the applications of the propellant formula in the tactical missile engine are promoted, and the important military significance is provided.

Description

technical field [0001] The invention relates to a pressure index regulator for solid propellants, in particular to a metal oxide composite pressure index regulator suitable for solid propellants. Background technique [0002] Nitrate plasticized (NEPE) polyether propellant is a representative of contemporary high-energy solid propellants. It not only has the advantages of high energy of modified double-base propellants, but also obtains good mechanical properties due to the introduction of polymer prepolymers as binders. performance. The PEG / nitrate / nitroamine system high-energy solid propellant is currently the highest level of practical solid propellant in NEPE propellants. The United States has used it in various types of missiles such as "Trident" II and "Dwarf". It is used in a variety of new-generation strategic missile weapons, which greatly improves the performance level of strategic weapons. As the current high-energy solid propellant application range gradually e...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06D5/06C06B25/34C06B23/00
CPCC06B23/00C06B25/34C06D5/06
Inventor 宋会彬庞爱民汪越潘新洲尹欣梅唐根张林
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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