The invention relates to an iterative approximation heat balance test method of a heat dissipation surface and heat pipe system for a thermal test, which comprises the following steps of: when a special heat dissipation surface-heat pipe system for the thermal test is used, removing an on-orbit real heat pipe under an original configuration, arranging a set of simulated heat pipe and heat dissipation surface for the thermal test, and finishing the construction of a thermal test configuration; through multiple times of test iteration of two parameters of different heat dissipation plates in the heat test process, the heat transfer amount between the heat dissipation plate or the heat dissipation surface and a heat pipe, the heat dissipation amount between the heat dissipation plate or the heat dissipation surface and the environment and the heat exchange amount between the heat dissipation surface and other structures are accurately obtained, the accurate heat boundary condition is determined, the problem of insufficient verification of the heat test is solved, and the test efficiency is improved. And the thermal design reliability of the spacecraft can be effectively improved.
一种热试验散热面及热管系统的迭代逼近热平衡试验方法,使用热试验专用散热面‑热管系统时,通过去除原构型下的在轨真实热管,布置一套热试验的模拟热管及散热面,完成热试验构型建设,通过热试验进行过程中对不同散热板双参数的数次试验迭代,准确获知散热板或散热面与热管的传热量、散热板或散热面与环境的散热量、散热面与其他结构的换热量,确定准确的热边界条件,解决了热试验的验证不充分问题,可有效提高航天器热设计可靠性。
Iterative approximation heat balance test method for heat test radiating surface and heat pipe system
一种热试验散热面及热管系统的迭代逼近热平衡试验方法
2025-01-14
Patent
Electronic Resource
Chinese
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