| 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 ëá 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 |
