Evaluation and Simulation Verification of Thermal Insulation Property of Fiber Fabric Materials in Space Environment

doi:10.15541/jim20190110

Abstract

Abstract:

Equivalent experimental conditions to those in space were used to characterize the effective thermal conductivity of the fiber fabric insulation used in the multilayer insulation system of the material preparation furnace loaded on Tiangong-2 Space Station. By evaluating the material following variations in the on-orbit temperature and on-track pressure, the microscopic heat transfer mechanism was studied. The furnace internal temperature field under different working conditions was also simulated according to the characterization results, and the data reliability was verified. The results showed that the effective thermal conductivity of the fiber fabric increases non-linearly with rising temperature; moreover, with lower pressures, the growth trends are gentler. With a pressure drop, the results present the trend of a decaying exponential function with a critical pressure value. Radiation and gas phase heat conduction are the main factors affecting the heat transfer of the fiber fabric under the microgravity environment. Simulation results of the temperature field demonstrate that the temperature field distribution trend matches well with that of the measured results. The maximum calculation error of the furnace center is 1.3% of the measured temperature. This method can be used to evaluate the thermal insulation performance of the multilayer fiber material close to the practical working conditions more reasonably, and also to improve the accuracy of thermal simulation prediction models.

Key words: space microgravity environment, fiber fabric insulation material, effective thermal conductivity, steady-state heat flow meter method, temperature field simulation

CLC Number:

O482

LUO Cai-Yun, YANG Li-Ping, TAO Ye, ZHONG Qiu, LI Hui-Dong. Evaluation and Simulation Verification of Thermal Insulation Property of Fiber Fabric Materials in Space Environment[J]. Journal of Inorganic Materials, 2019, 34(11): 1238-1244.

Figures/Tables 10

Fig. 1 SEM image showing the surface morphology of the fiber fabric

Fig. 2 Application of fiber fabric in the space material furnace

Fig. 3 Principle of steady-state heat flow meter test

Fig. 4 Vacuum heat flow meter with the high-temperature thermal conductivity instrument

Fig. 5 Effective thermal conductivity changes with different temperatures

Fig. 6 Effective thermal conductivity changes with different pressures

Fig. 7 SEM image showing the fiber filament morphology

Fig. 8 Calculation cross section of the temperature field in the material preparation furnace

Parameters	Condition 1	Condition 2
Pressure	101 kPa	3 kPa
Ambient temperature outside the furnace	18.5 ℃	21 ℃
Emissivity	0.98 (W·m^-2·sr^-1)
Convective heat transfer coefficient (outside the furnace shell)	3.8 (W·m^-2·K)
Heating power × time	97 W × 6 h

Fig. 9 Comparison of the calculated data for the temperature field with the test data (a) 101 kPa-ground; (b) 3 kPa-ground

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