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Transient Thermal Simulation of Apollo Spacecraft and ECS
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1967 by SAE International in United States
Annotation ability available
An analytical thermal model of the project Apollo Command Module has been developed by the General Electric Co., Apollo Support Dept. for the National Aeronautics and Space Administration, Manned Spacecraft Center. This model simulates the entire spacecraft structure and the four closed fluid loops of the Environmental Control System.
The configuration of the model is discussed as well as the correlation of this type model with test data. Also covered are the environmental data used in conjunction with the model for mission analysis. Typical results of the mission analyses are discussed in more detail.
CitationFrahm, J. and Walthall, H., "Transient Thermal Simulation of Apollo Spacecraft and ECS," SAE Technical Paper 670837, 1967, https://doi.org/10.4271/670837.
- Hixon, C. W. et al., “Apollo Block II Command Module Thermal Simulator.” LTV Aerospace Corp., Missiles and Space Div., Report No. 350.2, July 28, 1967.
- Finch H. L. and Sommerville, D. “Development of a Computer Program for Determining External Radiation Absorbed by the Apollo Spacecraft.” Midwest Research Institute, Final Report Contract No. NAS9-3860, April 19, 1966.