Core-shell type aluminum-coated perchlorate/catalyst composite microsphere and solid propellant based on microsphere

Abstract

The invention provides a core-shell type aluminum-coated perchlorate / catalyst composite microsphere and a solid propellant based on the microsphere so as to reduce the pressure index of an existing Al-based composite solid propellant and improve the catalytic efficiency of a catalyst. The core-shell type aluminum-coated perchlorate / catalyst composite microsphere is composed of the following components in percentage by mass: 25%-80% of a perchlorate oxidant, 5%-75% of aluminum powder and 0%-20% of a catalyst, wherein the aluminum powder is tightly coated with the perchlorate oxidant to form the core-shell type composite microsphere with the particle size of 1.0-400 microns. When the composite microspheres contain a catalyst, the catalyst is embedded among the perchlorate oxidizing agent crystals, and all the components are in close contact.

Description

technical field

[0001] The invention belongs to the technical field of composite solid propellants, in particular to a core-shell aluminum@perchlorate / catalyst composite microsphere and a solid propellant based on the microsphere. Background technique

[0002] As the energy and working fluid source of Solid Rocket Motor (SRM), solid propellant is widely used in various launch vehicles and weaponry, and its combustion performance largely determines the performance of SRM. With the exception of solid propellants for variable thrust SRMs, designers generally desire propellants with low burn rate pressure exponents. A high pressure index means that a small pressure disturbance during the SRM working process will cause a large change in the burning rate, resulting in pressure oscillations in the SRM combustion chamber. This not only brings great challenges to the structural design of SRM, but also may cause major safety accidents.

[0003] Researchers usually use the method of ...

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