A kind of anti-high overload composite propellant and preparation method thereof

A propellant and oxidant technology, applied in offensive equipment, explosives processing equipment, explosives, etc., can solve the problem that composite propellants cannot meet the needs of use, and achieve the effect of improving anti-overload performance, ensuring work safety, and reducing the degree of deformation.

Active Publication Date: 2020-09-22
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the existing composite propellant cannot meet the use requirements, and provide a high overload resistant composite propellant and its preparation method

Method used

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  • A kind of anti-high overload composite propellant and preparation method thereof
  • A kind of anti-high overload composite propellant and preparation method thereof
  • A kind of anti-high overload composite propellant and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] The formula of this embodiment: HTPB, mass content is 8%; Ammonium perchlorate, mass content is 60%; RDXG, mass content is 18%; Aluminum powder, mass content is 6%; Diisocyanate , with a mass content of 3%; triethanolamine; with a mass content of 2%, and dibutyl phthalate, with a mass content of 3%. The composition of raw materials is as follows: HTPB 192.4g, ammonium perchlorate 1443g, RDX 432.9g, aluminum powder 144.3g, diisocyanate 72.15g, triethanolamine 48.1g, dibutyl phthalate 72.15g.

[0031] The preparation method is as follows:

[0032] Step 1, weighing and obtaining corresponding raw materials;

[0033] Step 2: Mix the above raw materials, stir evenly, and stir at a temperature of 50°C to 60°C to obtain a propellant slurry;

[0034] Step 3. Vacuum pouring: pour the propellant slurry into the medicine mold or the engine casing, and the pouring time is not less than 80 minutes;

[0035] Step 4. Curing: heat and cure the mold or the engine housing containing t...

Embodiment 2

[0041] The formula of this embodiment: HTPB, mass content is 8.5%; Ammonium perchlorate, mass content is 57%; Octogen, mass content is 15%; Aluminum powder, mass content is 16.5%; Diisocyanate Esters, with a mass content of 1%; triethanolamine, with a mass content of 1%, and dioctyl adipate, with a mass content of 1%. The composition of raw materials is as follows: HTPB 205.5g, ammonium perchlorate 1376.5g, Octogen 362.5g, aluminum powder 398.5g, diisocyanate 24g, triethanolamine 24g, dioctyl adipate 24g.

[0042] The preparation method is the same as in Example 1.

[0043] The propellant grain obtained in this example has a maximum axial strain of about 0.23 and a maximum strain rate of about 3s under a high overload of 12000g -1 . The maximum radial displacement of a point on the outer diameter of the bottom end surface is about 0.27mm, and the propellant grain obtained in this embodiment is capable of resisting a high overload of 12000g.

Embodiment 3

[0045] The formula of this embodiment: HTPB, mass content is 8%; Ammonium perchlorate, mass content is 54.5%; RDX, mass content is 19%; Aluminum powder, mass content is 10%; Diisocyanate , with a mass content of 4%; triethanolamine; with a mass content of 2%, and dioctyl sebacate, with a mass content of 2.5%. The composition of raw materials is as follows: HTPB 192g, perchloric acid 1308.5g, RDX 456.2g, aluminum powder 240g, diisocyanate 96g, triethanolamine 48g, dioctyl sebacate 60g.

[0046] The preparation method is the same as in Example 1.

[0047] The propellant grain obtained in this example has a maximum axial strain of about 0.22 and a maximum strain rate of about 4s under a high overload of 12000g -1 . The maximum radial displacement of a point on the outer diameter of the bottom end surface is about 0.3 mm, and the propellant grain obtained in this embodiment is capable of resisting a high overload of 12000 g.

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Abstract

The invention relates to a composite propellant with high overload resistance and a preparation method thereof, and belongs to the field of solid propellant. The composite propellant mainly consists of the components by mass: 7%-9% of hydroxyl-terminated polybutadiene, 72%-80% of an oxidant, 6%-17% of aluminum powder, 1%-5% of diisocyanate, 1%-5% of triethanolamine and 1%-5% of a plasticizer. A composite propellant grain adopting the formula produces small deformation under the high overload of 1200 g, the structural integrity of the grain is ensured, contact and friction with a shell are avoided, no special components are added in the formula, the purpose of high overload resistance is achieved by adjusting the mass ratio of a non-cohesive solid to a binder in the formula, and the composite propellant has the advantage of easy realization.

Description

technical field [0001] The invention relates to a high-overload-resistant composite propellant and a preparation method thereof, belonging to the field of solid propellants. Background technique [0002] Composite propellants are solid energetic materials mainly composed of binders, oxidizers, metal fuels, curing agents, crosslinking agents, and plasticizers. Widely used in solid rocket motors and missile motors. The artillery-launched missile has a high acceleration during launch, and the engine has to withstand a high overload of several thousand g or even tens of thousands of g. Under this high overload, the propellant grain will produce axial compression and radial thickening deformation. When the deformation reaches a certain level, the grain will contact with the casing to generate friction, and the heat generated by the friction will endanger the safety of the engine; Deformation can also destroy the structural integrity of the grain and cause the engine to fail, ev...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06B33/12C06B21/00C06D5/06
CPCC06B21/0058C06B33/12C06D5/06
Inventor 李月洁谢侃白龙周海霞王宁飞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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