A kind of thermoplastic composite solid propellant and preparation method thereof
A solid propellant and thermoplastic technology, which is applied in the field of thermoplastic composite solid propellants, can solve the problems of thermoplastic propellants such as safety and hidden dangers, and achieve the effect of improving intrinsic safety, improving safety and reducing costs
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Embodiment 1
[0035] (1) Composition of thermoplastic composite solid propellant (mass percentage)
[0036] Binder (EVA420): 11.5%; Oxidizer (Ammonium Perchlorate): 55%; Oxidizer (Hexogen): 10%; Plasticizer (Dioctyl Sebacate): 10.5%; Metal Fuel (Aluminum Powder): 10%; Auxiliary (tris[1,-(2-methylaziridine)]phosphine oxide): 0.4%; Auxiliary (silane coupling agent): 0.5%; Auxiliary (N,N- Diphenyl-p-phenylenediamine): 0.6%; additive (carbon black): 0.4%; additive (ferric oxide): 1.1%.
[0037] The preparation process of the present invention includes: weighing the oxidizing agent, adhesive, plasticizer, metal fuel, and auxiliary agent according to the ratio; putting the adhesive into a vertical mixer to heat and melt, and the melting temperature is 84 ~ 88 ℃;
[0038] Put the rest of the weighed components into a vertical mixer and mix, the mixing temperature is 84~88°C, and the mixing time is 60~110min to make a slurry; the slurry is vacuum sprayed into the mold or poured into the engine, ...
Embodiment 2
[0042] (1) Composition of thermoplastic composite solid propellant (mass percentage)
[0043] Binder (EVA420): 10%; Oxidizer (Ammonium Perchlorate): 58%; Oxidizer (Ammonium Dinitramide): 4%; Plasticizer (Acetyl Triethyl Citrate): 10%; Metal Fuel (aluminum powder): 12%; metal fuel (magnesium powder): 3%; additive (alcohol amine complex): 0.5%; additive (aluminate coupling agent): 0.6%; additive (N, N-diphenyl-p-phenylenediamine): 0.5%; additive (carbon black): 0.5%; additive (catocin): 0.9%.
[0044] The preparation method is the same as in Example 1.
[0045] (2) Properties of thermoplastic composite solid propellants
[0046] Density: 1.62 g / cm 3 ; Combustion temperature: 2538.66°C; Characteristic velocity: 1523.06 m / s; Specific impulse: 2462.69 N*s / kg; Average molecular weight of gas: 24.71 g / mol; Melting point: 82~84°C; 0.56MPa; maximum elongation (25°C): 20.6%; elongation at break (25°C): 26.4%; pressure index (3MPa~9MPa): 0.41.
Embodiment 3
[0048] (1) Composition of thermoplastic composite solid propellant (mass percentage)
[0049] Binder (EVA420): 12%; Oxidizer (Ammonium Perchlorate): 57%; Oxidizer (Octogen): 4%; Plasticizer (Mineral Oil): 10.5%; Metal Fuel (Aluminum Powder): 11%; metal fuel (boron powder): 2%; additive (tris[1,-(2-methylaziridine)]phosphine oxide): 0.5%; additive (aluminate coupling agent): 0.8 %; Auxiliary (N,N-diphenyl-p-phenylenediamine): 0.8%; Auxiliary (carbon black): 0.6%; Auxiliary (ferric oxide): 0.5%; Auxiliary (catocin) : 0.3%.
[0050] The preparation method is the same as in Example 1.
[0051] (2) Properties of thermoplastic composite solid propellants
[0052] Density: 1.57 g / cm 3 ; Combustion temperature: 2041.85°C; Characteristic velocity: 1465.75 m / s; Specific impulse: 2368.85 N*s / kg; Average molecular weight of gas: 23.27 g / mol; Melting point: 80~83°C; 0.61MPa; maximum elongation (25°C): 21.2%; elongation at break (25°C): 28.3%; pressure index (3MPa~9MPa): 0.38.
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