Launch vehicle upper stage transient heat balance test device and method

Abstract

The invention provides a launch vehicle upper stage transient heat balance test device and method. The launch vehicle upper stage transient heat balance test device comprises an infrared lamp array, heat flow meters, an electric heater, and a baffle plate. According to an upper-stage in-orbit combination flight state, a temperature boundary is simulated by the electric heater in a satellite anda carrier docking surface, transient outer heat flux is simulated by the electric heater in a regular structure area including an instrument cabin, and transient outer heat flux is simulated by the infrared lamp array in a complicated structure area including a power cabin. The outer heat flux area of the instrument cabin simulated by the electric heater is equally divided into a plurality of regions along the circumferential direction. The outer heat flux area of the power cabin simulated by the infrared lamp array is divided into a circumferential direction and a bottom, wherein the circumferential direction is equally divided into a plurality of regions, and the bottom is divided into a plurality of regions. The heat flux value of each region is obtained by two heat flow meters. The infrared lamp array regions are blocked by baffles to prevent the influences of the heat flux between the regions. The launch vehicle upper stage transient heat balance test device and method solve thatit is difficult to simulate the transient outer heat flux during the in-orbit flight of the launch vehicle upper stage.

Description

technical field [0001] The invention relates to a transient heat balance test of an orbiter, in particular to a transient heat balance test device and method for an upper stage of a carrier rocket. Background technique [0002] Unlike ordinary satellites that operate in orbit for a long time, the mission of the upper stage of the launch vehicle is short. During the orbital deployment mission, the upper stage undergoes multiple orbit changes, and the thermal control system faces a more complex orbital and space environment. [0003] In addition, when the upper stage is equipped with different satellites, its orbital conditions and launch windows will be very different. At the same time, it will also go through stages such as launch, ascent orbit section, transition orbit section, and orbit star distribution. The thermal control system is faced with a more complicated orbit. And the space environment, and there is a complex thermal boundary with the power system, and the exter...

AI Technical Summary

Problems solved by technology

Through the combination of electric heater and infrared light array, the simulation of transient external heat flow in the large-scale heat balance test of the complex structure of the upper stage of the launch vehicle is realized during the orbital flight. It has the advantages of simple design and convenient operation, and solves the problem of the upper stage of the launch vehicle Difficulties in simulating transient external heat flow during flight

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