A kind of composite solid propellant and preparation method based on multiscale modified nitramine oxidant
A solid propellant and oxidant technology, which is used in offensive equipment, compressed gas generation, explosives, etc., can solve the problems of sudden increase in high-pressure burning rate, inability to accurately catalyze the burning rate catalyst, and low combustion efficiency of solid propellant, and achieve a solution to the problem. Paradoxical issues, effects of increased production and safety of use
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preparation example Construction
[0043] The preparation process of the embodiment can be divided into the following four steps:
[0044] (1) Preparation of inactivated modified nitramine crystals: Triaminoguanidine hydrochloride TAG (2.5 mmol, 119.2 mg) was dissolved in dimethyl sulfoxide (DMSO, 7.3 mL), and heated to 100° C., stirred for 30 min, then nitramine (RDX / HMX / CL-20, 5 mmol) was added to the solution, stirred for 30 min, and the solution gradually changed from colorless and transparent to pink. The above solution was kept in an oil bath at a temperature of 105°C, and then 2.5 mmol (290.2 μL) of aqueous glyoxal was added. The 2D flexible TAGP material can be generated within 1 hour of cross-linking reaction. Finally, at 1.008mL·min -1 Add the anti-solvent (H 2 O). DMSO and anti-solvent H 2 The volume ratio of O was kept at 1:2. Finally, the precipitated crystals were filtered out and washed with distilled water to obtain inactivated modified nitramine crystals.
[0045] (2) Preparation of dopa...
example 1
[0050] Example 1: A composite solid propellant without burn rate catalyst. The content of ammonium perchlorate (AP) is 57wt%, the content of μ-Al is 18wt%, the content of RDX is 10wt%, the binder is hydroxyl-terminated polybutadiene (HTPB, 11.5wt%), and the plasticizer is Kwai Di Diisooctyl acid (DOS, 2.5 wt %), and isophorone diisocyanate (IPDI, 1 wt %) as the curing agent. The propellant preparation method is as follows:
[0051] (a) Drying treatment of raw materials: place the solid material in an oven at 60°C for 96h;
[0052] (b) Fully mixing the propellant components: Weigh the propellant components of a certain mass according to the formula, and add AP, HTPB, DOS, IPDI, RDX, and micron aluminum powder to the mixer in turn, under the condition of 60 ℃ water bath Stir to make it evenly mixed;
[0053] (c) Vacuum pouring: pour the propellant slurry into the customized mold, and the vacuuming time is more than 12h;
[0054] (d) Curing: The propellant slurry that has bee...
example 2
[0056] Example 2: The propellant formula and preparation steps are the same as in Example 1, and only the RDX in the example 1 is replaced by the deactivated modified qy-RDX;
[0057] qy-RDX is more insensitive than RDX, and no cracks are generated under the action of electron beam ( Figure 9 ). The melting endothermic peak of Example 2 is slightly lower than that of Example 1, which is 204.2 °C, but the endothermic value is reduced; compared with Example 1, the exothermic peak temperature of AP in Example 2 is reduced by 5.6 °C, and the heat of decomposition is increased to 1011.0 J·g -1 , the thermal weight loss of the propellant in the uncontrollable reaction zone of Example 2 increased by 4.42%, and the residual mass of thermal decomposition decreased by 4.52% ( Figure 10 ). The burning rate of the propellant in Example 2 was increased to 3.37 mm s at 0.5 MPa -1 , the burning rate pressure index n is 0.314 ( Figure 11). qy-RDX can only improve its own reactivity, ...
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