A Food Refrigeration and Habitable Atmosphere Control System for Space Vehicles, Design, Fabrication and Test Phases
Report Number: AMRL TDR 62-149
Author(s): Miller, R. A., Halpert, S.
Corporate Author(s): General Electric Company
Laboratory: Life Support Systems Laboratory
Date of Publication: 1962-12
Pages: 206
Contract: AF 33(616)-6902
DoD Project: 6373
DoD Task: 637303
Identifier: AD0404844
Abstract:
The purpose of this development project was to design, fabricate, and evaluate a food refrigeration and habitable atmosphere control system which will support a three-man crew for an extreme altitude mission of 14 days and have additional capabilities for the storage, heating and chilling of recovered water. The feasibility study and design study phases of the program indicated that a flight optimized system (i.e., a system with minimum power, weight, and volume characteristics) would be a system which utilizes a direct radiation to space concept to remove excess heat from the confines of a space vehicle. The equipment and systems were fabricated to assure their operability under the following extremes of environment: (1) cabin pressure will vary between 0.5 to 1.0 atmosphere, (2) equipment must operate in the presence of normal gravitational conditions as well as under a weightless condition, and (3) acceleration forces of up to 8 G's must be withstood.
Provenance: RAF Centre of Aviation Medicine
Author(s): Miller, R. A., Halpert, S.
Corporate Author(s): General Electric Company
Laboratory: Life Support Systems Laboratory
Date of Publication: 1962-12
Pages: 206
Contract: AF 33(616)-6902
DoD Project: 6373
DoD Task: 637303
Identifier: AD0404844
Abstract:
The purpose of this development project was to design, fabricate, and evaluate a food refrigeration and habitable atmosphere control system which will support a three-man crew for an extreme altitude mission of 14 days and have additional capabilities for the storage, heating and chilling of recovered water. The feasibility study and design study phases of the program indicated that a flight optimized system (i.e., a system with minimum power, weight, and volume characteristics) would be a system which utilizes a direct radiation to space concept to remove excess heat from the confines of a space vehicle. The equipment and systems were fabricated to assure their operability under the following extremes of environment: (1) cabin pressure will vary between 0.5 to 1.0 atmosphere, (2) equipment must operate in the presence of normal gravitational conditions as well as under a weightless condition, and (3) acceleration forces of up to 8 G's must be withstood.
Provenance: RAF Centre of Aviation Medicine