A kind of pressure index modifier of solid propellant

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...

Examples

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

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...

Examples

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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