Ultrahigh-temperature thermal current simulation system used for spacecraft vacuum thermal test

Abstract

The invention discloses an ultrahigh-temperature thermal current simulation system used for a spacecraft vacuum thermal test in a vacuum container. The ultrahigh-temperature thermal current simulation system mainly comprises a semi-cylindrical graphite heating array, high-reflectivity high-temperature thermal insulation assembly units, a graphite heating array installing support, an ultrahigh temperature measuring unit and a power-regulator power control unit. A plurality of graphite heating rods are arranged and combined into the semi-cylindrical graphite heating array according to the requirements for the density and uniformity of thermal currents. Each graphite heating rod is composed of a graphite heating body and a graphite electrode, alternating-current electricity supply is adopted, and wiring electrode leads penetrate through a high-current cabin-penetrating electricity supply flange arranged on a container wall of the vacuum low-temperature environment simulation container and are electrically connected with the temperature measuring unit and the power-regulator power control unit respectively. Through the unique design of the graphite heating array, the high-reflectivity high-temperature thermal insulation assembly units and the ultrahigh temperature measuring unit, measurement of and control over temperatures over 1800 DEG C in the space environment simulation container are achieved, and the ultrahigh-temperature thermal current simulation system is also suitable for high-temperature and high-thermal-current environment simulation requirements in vacuum thermal tests of all types of spacecraft.

Description

technical field [0001] The invention belongs to the field of vacuum heat tests on the ground of spacecraft. Specifically, the invention relates to a heating simulation system for ultra-high temperature and extremely high heat flow conditions in the vacuum heat test of spacecraft and its components in a space environment simulation container. Background technique [0002] Spacecraft vacuum thermal test is an important procedure in the development of spacecraft, generally divided into two parts: spacecraft thermal balance test and spacecraft thermal vacuum test. Through the thermal balance test of the spacecraft, the temperature distribution data of the spacecraft can be obtained, the correctness of the thermal design can be verified, the thermal analysis mathematical model can be modified, the temperature distribution in the orbital flight of the spacecraft can be checked, and the thermal control subsystem of the spacecraft can be assessed to maintain the spacecraft components...

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Problems solved by technology

The high-temperature wind tunnel test can only assess the performance of the surface thermal protection material, and cannot simulate the thermal environment of the cabin load during re-entry

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