A family of user-friendly, DOS PC based, Microsoft BASIC programs written to provide spacecraft designers with empirical predictions of space debris damage to orbiting spacecraft are described. Spacecraft wall temperatures and condensate formation is also predicted. The spacecraft wall configuration is assumed to consist of multilayered insulation (MLI) placed between a Whipple style bumper and the pressure wall. Impact damage predictions are based on data sets of experimental results obtained from simulating debris impacts on spacecraft using light gas guns on earth. A module of the program facilitates the creation of the database of experimental results that is used by the damage prediction modules to predict damage to the bumper, the MLI, and the pressure wall. A finite difference technique is used to predict temperature distributions in the pressure wall, the MLI, and the bumper. Condensate layer thickness is predicted for the case where the pressure wall temperature drops below the dew point temperature of the spacecraft atmosphere.
MLITEMP: A Computer Program to Predict the Thermal Effects Associated with Hypervelocity Impact Damage to Space Station MLI
1991
79 pages
Report
No indication
English
Manned Spacecraft , Unmanned Spacecraft , Computer programs , Hypervelocity impact , Impact damage , Space debris , Space station freedom , Temperature effects , Multilayer insulation , Prediction analysis techniques , Computerized simulation , Condensates , Finite difference theory , Light gas guns , Spacecraft design , Temperature distribution , Thermal analysis , Wall temperature
Hypervelocity impact damage assessment for Space Station
AIAA | 1988
|Hypervelocity impact damage assessment for Space Station
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