Tracking temperature control device for spacecraft thermal vacuum test
A vacuum thermal test and temperature control device technology, applied in the direction of measuring devices, machine/structural component testing, instruments, etc., can solve the problems of test data deviation, affect the effectiveness of thermal balance tests, and affect satellite temperature distribution, etc., to achieve accurate data effective effect
Active Publication Date: 2013-04-17
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology
During the test, the heat leakage between the satellite and the test support will affect the temperature distribution of the satellite itself, thereby bringing deviations to the test data and affecting the effectiveness of the heat balance test
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Embodiment Construction
[0015] Hereinafter, the present invention will be further described through specific embodiments in conjunction with the accompanying drawings.
[0016] Such as figure 1 As shown, the tracking temperature control device used in the spacecraft vacuum heat test of the present invention includes the heat insulation insulation pad 2, the heat insulation insulation pad 4, the satellite docking flange 1, and the test bracket flange by using M6 titanium bolts 5 to connect the components. 3 connections are fixed. The tracking heating circuit is composed of two thin film heaters 6, and the heating circuit is set, preferably adhered to the inner elevation of the flange 3 of the test bracket, and distributed according to the positions of the installation holes. The tracking thermocouple 7 is arranged between the two thin film heaters corresponding to the heating circuit, and the distance between the two thin film heaters is about 10mm. Among them, polyimide insulation material is used ...
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The invention relates to a tracking temperature control device for spacecraft thermal vacuum test, which comprises a test support flange, a satellite butt joint flange, two film heaters, a tracking temperature control thermocouple, and a temperature program control system, wherein the test support flange is mechanically and adiabatically connected to the butt joint flange through a heat insulation pad, the nearby of a connection hole of the satellite butt joint flange is determined as a thermocouple temperature measuring point as a tracked point, a tracking temperature control heating loop formed by two film heaters and the tracking temperature control thermocouple arranged between the two film heaters and used for measuring the tracking point temperature are arranged near the connection hole of the test support butt joint flange which is taken as the tracking point, the temperatures of the tracked point and tracking point are collected by the temperature program control system, and the heating of the film heaters in the heating loop is controlled after comparison of a difference of the two temperatures and the temperature difference is arranged within a range of + / -1.0 DEG C. The tracking temperature control device for spacecraft thermal vacuum test enables the data obtained from a heat balance test to be accurate and effective, and provides test data for checking and modifying a thermo network model.
Description
technical field [0001] The invention belongs to the field of spacecraft vacuum heat test, in particular to a large-scale satellite vacuum heat test tool for a horizontal container. Background technique [0002] Thermal balance test is a key project in the development of spacecraft. One of the main purposes of this test is to verify the accuracy of the satellite thermal network model and provide test data for correcting the model. During the test, the heat leakage between the satellite and the test support will affect the temperature distribution of the satellite itself, which will bring deviation to the test data and affect the effectiveness of the heat balance test. [0003] Aiming at the requirement of this technical background, a method to reduce the heat leakage between the satellite and the test support during the test was invented. This method can reduce the heat leakage between the two as much as possible, so that the temperature difference between the two is within ...
Claims
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IPC IPC(8): G01M99/00G05D23/22
Inventor 刘守文袁伟峰高庆华
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG