基于外热流等效的航天器热平衡试验方法应用研究OA

Application research of spacecraft thermal balance test methods based on external heat flux equivalence is presented.Firstly,the theoretical basis and conditions for equivalent thermal balance test are elaborated.Subsequently,the methodology for determining on-orbit absorbed external heat flux is established as the input condition for implementing equivalent tests.Finally,specific application cases for two external heat flux equivalence methods-the infrared heat flux method and the direct heater heating method-are discussed.Combined with common spacecraft engineering practices,some important precautions are summarized to guide test design.These precautions include:adherence to the principle of the real temperature field in external heat flux analysis;calculation of heating power in the direct heater method as the external heat flux exclu-ding the background heat flux absorbed during test;equivalence conditions between the absorbed heat flux corrected by the post-test thermal analysis model and that measured by heat flux gau-ges;and the requirement for heat flux gauge layouts to cover distinct temperature zones.These findings provide a valuable reference for spacecraft thermal balance test design.