METHOD OF DETERMINING THERMAL RESISTANCE OF SPACECRAFT TEMPERATURE CONTROL VACUUM SHIELD THERMAL INSULATION SYSTEM FOR THERMAL-VACUUM TESTS Russian patent published in 2009 - IPC B64G1/58 B64G7/00 

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 (T_ch and T_IR) of radiation energy receivers are measured. One of aforesaid receivers features a high heat radiation absorbing capacity (A_s), approximating to A_s of ideal black body. The other one features A_s<(0.1 to 0.2) in the visible spectrum band. Aforesaid receivers are fitted in the area of analysed VSTI. Thermal resistance of VSTI (R_VSTI) 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 R_VSTI 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 R_VSTI 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