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A polyether solid propellant with ultra-low glass transition temperature and preparation method thereof

A technology of glass transition temperature and solid propellant, which can be used in offensive equipment, explosive processing equipment, and the generation of compressed gas.

Active Publication Date: 2021-07-13
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the temperature is lower than -65°C, the propellant has become brittle and cannot meet the harsh requirements of the extremely low temperature environment

Method used

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  • A polyether solid propellant with ultra-low glass transition temperature and preparation method thereof
  • A polyether solid propellant with ultra-low glass transition temperature and preparation method thereof
  • A polyether solid propellant with ultra-low glass transition temperature and preparation method thereof

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preparation example Construction

[0040] The preparation process of the solid propellant provided by the embodiment of the present invention includes: preparing raw materials according to the above-mentioned raw material formula, using a vertical or horizontal mixer for mixing, and using a vacuum pouring system to realize the production of engine grains; during preparation, (1) the mixer The temperature of the water bath was set between 30 and 35°C. Adhesives, plasticizers, chain extenders, fuels, crosslinking agents, chain extenders, bonding agents and curing catalysts are premixed before mixing. After the premixed materials are added to the mixing pot, explosives and perchloric acid are added in sequence. Ammonium (AP), curing agent; and then mixed, the mixing time is between 80-120min, and the speed of the mixer is between 100-150r / min. (2) After mixing evenly, use the vacuum pouring system to pour the propellant slurry into the engine casing or various molds. (3) Put the poured engine or various molds int...

Embodiment 1

[0045] (1) The propellant composition is shown in Table 1-1:

[0046] Table 1-1 Composition of propellant

[0047]

[0048] (2) Propellant properties:

[0049] 1. Propellant T g = -93.0°C;

[0050] 2. The mechanical properties of the propellant are shown in Table 1-2;

[0051] Table 1-2 Mechanical properties of propellants

[0052]

Embodiment 2

[0054] (1) The propellant composition is shown in Table 2-1:

[0055] Table 2-1 Composition of propellants

[0056]

[0057]

[0058] (2) Propellant properties:

[0059] 1. Propellant T g = -92.2°C;

[0060] 2. The mechanical properties of the propellant are shown in Table 2-2:

[0061] Table 2-2 Mechanical properties of propellants

[0062]

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Abstract

The invention relates to a polyether solid propellant with an ultra-low glass transition temperature and a preparation method thereof, belonging to the technical field of solid propellants. The propellant raw material includes the following components in mass percentage: 6.0-8.0% of binder, 9.0-15.0% of plasticizer, 0.5-1.5% of crosslinking agent, 1.0-2.0% of chain extender, 0.1-0.3% of bonding agent %, 40.0-60.0% oxidant, 0.0-15.0% explosive, 16.0-20.0% fuel, 0.5-1.5% curing agent and 0.02%-0.03% curing catalyst; the plasticizer is 1,3-diazide- 2‑Ethyl‑2‑nitropropane. The plasticizing ratio of the propellant is controlled between 1.0 and 2.0. The glass transition temperature of the propellant is less than -90°C. The propellant has good adaptability to ultra-low temperature environments, and can meet the strict requirements of solid propellant ultra-low temperature performance for special-purpose solid rocket motors such as deep space exploration and advanced tactical missiles.

Description

technical field [0001] The invention relates to a polyether solid propellant with an ultra-low glass transition temperature and a preparation method thereof, belonging to the technical field of solid propellants. The glass transition temperature of the propellant is less than -90°C, which endows the polyether propellant with good low-temperature environment adaptability sex. Background technique [0002] With the vigorous development of modern missile tactical weapons, rocket motors and deep space exploration, people's demand for high-performance solid rocket motor technology is also increasing. at low temperature. The high ignition pulse of the tactical rocket engine may cause the propellant particles or charge to rupture during ignition, which not only affects its internal ballistic performance, but also has the risk of unstable combustion. The propellant must have good adaptability to low temperature environments. [0003] The glass transition temperature of existing pr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C06D5/06C06B33/08C06B23/00C06B21/00
CPCC06B21/0058C06B23/009C06B33/08C06B45/10C06D5/06
Inventor 周水平张鑫胡翔汪越唐根徐星星吴芳
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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