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在航天器热平衡方程的基础上,分析了表面涂层材料热辐射性质或布局调整对内热源变化和轨道变化的适应能力,并对若干情形进行了定量分析。研究表明,该方法有利于继承和保持成熟的航天器平台技术,提高了对不同类型轨道的航天器热设计的灵活性。
Based on the heat balance equation of the spacecraft, the capability of adapting the heat radiation property or layout adjustment of the surface coating material to the change of internal heat source and orbital change is analyzed, and a number of cases are quantitatively analyzed. The research shows that this method is beneficial to inherit and maintain the mature spacecraft platform technology, and improves the flexibility of spacecraft thermal design for different types of orbits.