Influence of External Insulation and Coating Transparence on Thermal Regimes of Space Vehicle 972546
The numerical/experimental method for, and results of, evaluating insulation solar radiation transmission effects on in-flight temperature field of a space vehicle are presented.
The experiment subsection describes a new experimental method for evaluating materials solar-radiation transmittance, reflectance, and absorptance, as well as demonstrates test results for silica samples with various thicknesses.
The calculation subsection includes (1) interpolation of the experimental data into a function of the insulation layer thickness and (2) the numerical solution of the transient heat conduction equation for a thermal protection fragment consisting of an insulation layer cemented to a metal plate. Fragment temperature calculation results for various near-Earth orbits and fibrous silica insulation layer thicknesses are presented.
The results obtained show the essential influence of insulation solar-radiation transmission on space vehicle structure temperature in space flight.
Citation: Paderin, L., "Influence of External Insulation and Coating Transparence on Thermal Regimes of Space Vehicle," SAE Technical Paper 972546, 1997, https://doi.org/10.4271/972546. Download Citation
Author(s):
L. Ya. Paderin
Pages: 7
Event:
International Conference On Environmental Systems
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1997 Transactions - Journal of Aerospace-V106-1
Related Topics:
Spacecraft
Plating
Sun and solar
Insulation
Fibers
Transmissions
Coatings, colorants, and finishes
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