A gas cylinder heat protection structure and gas cylinder for the influence of large plume of attitude control engine

Abstract

The invention relates to a gas cylinder thermal protection structure and a gas cylinder for a large plume influence of an attitude control engine. The thermal protection structure includes a flexibleheat protection layer and a multi-layer heat insulation assembly, wherein the multi-layer heat insulation assembly is coated on the surface of a cylindrical section of the gas cylinder, and the hemispherical surface at both ends of the gas cylinder and the surface of the multi-layer heat insulation assembly in the cylindrical section of the gas cylinder are covered with the flexible heat protection layer; and the multi-layer heat insulation assembly includes n reflecting layers, n-1 isolation layers and an outer cladding layer, wherein the n reflecting layers are alternately arranged with then-1 isolation layers, the innermost layer and the outermost layer are the reflecting layers, the reflecting layer of the innermost layer is in contact with the outer surface of the cylindrical sectionof the gas cylinder, the reflecting layer of the outermost layer is in contact with the outer cladding layer, the outer cladding layer is in contact with the flexible heat protection layer, and n isa positive integer and satisfies the following relational expression: n= k[rho]n[lambda]mli / hmli. The thermal protection structure of the invention ensures that the gas cylinder meets temperature control requirements, also ensures the design quality of a heat protection material, enables the weight to be effectively reduced, and enables the cost of a product to be saved.

Description

technical field [0001] The invention relates to a thermal protection design method for a gas cylinder of a space vehicle, in particular to a thermal protection structure of a gas cylinder and a gas cylinder aimed at the influence of a large plume of an attitude control engine, and belongs to the technical field of thermal protection of aircraft. Background technique [0002] The traditional thermal protection design method for launch vehicles is to use heat-resistant materials with low thermal diffusivity (such as glass fiber reinforced plastics) to ensure that the protected object does not exceed the required temperature limit within the specified time range by reducing the propagation speed of high temperature to the protected object. The thermal protection design method of spacecraft such as satellites is to adopt a high-temperature resistant multi-layer heat insulation component composed of low-emissivity reflective layers and low-thermal conductivity spacer layers altern...

AI Technical Summary

Problems solved by technology

Excessively high temperature of the gas cylinder may affect its safety, and too low temperature of the gas cylinder will affect its pressurization capability, and the existing thermal protection technology for launch vehicles and satellites generally only meets one thermal protection requirement

Images