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METHOD OF DETERMINING THERMAL RESISTANCE OF SPACECRAFT TEMPERATURE CONTROL VACUUM SHIELD THERMAL INSULATION SYSTEM FOR THERMAL-VACUUM TESTS
METHOD OF DETERMINING THERMAL RESISTANCE OF SPACECRAFT TEMPERATURE CONTROL VACUUM SHIELD THERMAL INSULATION SYSTEM FOR THERMAL-VACUUM TESTS
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机译：确定用于热真空试验的航天器温度控制真空屏蔽屏蔽隔热系统的热阻的方法
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摘要
FIELD: aircraft engineering.;SUBSTANCE: invention relates to the ground simulation tests of spacecraft elements and can be used in designing and experimental development of multi-layer vacuum shield thermal insulation (VSTI). In compliance with this invention, with the temperature control system stable thermal conditions, temperatures T1 and T2 of outer (on both sides) layers of analysed VSTI section are measured. Given T1 ≠ T2, equilibrium temperatures (Tch and TIR) of radiation energy receivers are measured. One of aforesaid receivers features a high heat radiation absorbing capacity (As), approximating to As of ideal black body. The other one features As(0.1 to 0.2) in the visible spectrum band. Aforesaid receivers are fitted in the area of analysed VSTI. Thermal resistance of VSTI (RVSTI) is determined, via VSTI, from the formula derived from the condition of balance of heat radiant flow and heat conductivity. The proposed method allows controlling the local value of RVSTI during ground development and testing of the spacecraft heat control system in thermal vacuum chamber, including testing on curved surfaces of spacecraft with due allowance for its configuration. The effect of residual gas amount in VSTI on RVSTI and the process of the said gas draining, as well as defects of separate sections of VSTI, etc. can be determined during above-described tests.;EFFECT: ease of use, possibility of automation.;1 dwg, 3 ex
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机译：技术领域本发明涉及航天器元件的地面模拟测试，并且可以用于多层真空屏蔽隔热层（VSTI）的设计和实验开发中。根据本发明，在温度控制系统稳定的热条件下，测量所分析的VSTI截面的外（两侧）层的温度T 1 和T 2 。给定T 1 ≠T 2 ，可以测量辐射能接收器的平衡温度（T ch 和T IR ） 。上述接收器之一具有高的热辐射吸收能力（A s ），接近理想黑体的A s 。另一个在可见光谱带中具有A s <（0.1至0.2）。前述接收机安装在分析后的VSTI区域中。 VSTI的热阻（R VSTI ）是通过VSTI由热辐射流量和热导率平衡条件得出的公式确定的。提出的方法允许在地面开发过程中控制R VSTI 的局部值，并在热真空室中测试航天器热控制系统，包括在航天器弯曲表面上进行测试，并适当考虑其配置。在上述测试过程中，可以确定VSTI中残留气体量对R VSTI 的影响以及所述气体的排放过程，以及VSTI各部分的缺陷等。 ：易于使用，自动化的可能性。; 1 dwg，3 ex
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