Satellite borne active temperature control system

Abstract

The invention provides a satellite borne active temperature control system which comprises an electrical-control heat insulating screen, an electric heater, an LHP (loop heat pipe) evaporator and an LHP radiator, wherein the electrical-control heat insulating screen is mounted on a side plate of a spacecraft; the electric heater and the LHP evaporator are mounted on heat tubes in different areas of a single machine mounting plate; the single machine mounting plate forms a heat pipe network through pre-embedded heat tubes; and the LHP radiator is mounted on the side plate of the spacecraft. The satellite borne active temperature control system solves the difficulty of a thermal control design of an inclined rail spacecraft, greatly realizes self-heating and self-cooling functions of the spacecraft, and can be applied to spacecraft thermal control with a complex rail external thermal flux environment and an internal power consumption varying condition.

Description

technical field [0001] The invention relates to a highly adaptable and highly reliable spaceborne active temperature control system, which can be applied to spacecraft or related fields with complex orbital heat flow environment and internal power consumption variation conditions. Background technique [0002] The traditional sun-synchronous orbit spacecraft is consistent with the orbital plane perturbation and the earth's revolution, and the orbital plane is always constant relative to the sun; the three-axis stable attitude of the spacecraft is the flight direction in the +X direction, and the ground-facing direction in the +Z direction. direction. Therefore, the +Y surface of the spacecraft is always the backside, and the external heat flow is close to 50W / m2, which is the most ideal heat dissipation surface for the spacecraft. [0003] The orbital perturbation of a spacecraft in an inclined orbit is opposite to the revolution direction of the earth. Taking the orbital i...

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Problems solved by technology

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a highly adaptable and highly reliable space-borne active te

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