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  • Other Sources  (3)
  • LAUNCH VEHICLES AND SPACE VEHICLES  (3)
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  • 1
    Publication Date: 2019-06-28
    Description: Candidate techniques for thermal management of unmanned modules docked to a large 250 kW platform were evaluated. Both automatically deployed and space constructed radiator systems were studied to identify characteristics and potential problems. Radiator coating requirements and current state-of-the-art were identified. An assessment of the technology needs was made and advancements were recommended.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-165307 , REPT-2-53020/1R-52778
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-28
    Description: Techniques for the management of the thermal energy of large space platforms using many hundreds of kilowatts over a 10 year life span were evaluated. Concepts for heat rejection, heat transport within the vehicle, and interfacing were analyzed and compared. The heat rejection systems were parametrically weight optimized over conditions for heat pipe and pumped fluid approaches. Two approaches to achieve reliability were compared for: performance, weight, volume, projected area, reliability, cost, and operational characteristics. Technology needs are assessed and technology advancement recommendations are made.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-165238 , REPT-2-53020/OR-52578
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-27
    Description: The characteristics of a cryogenic cooling system for the Pollution Monitoring Satellite (PMS) are discussed. Studies were conducted to make the following determinations: (1) the characteristics and use of proven and state-of-the-art cryogenic cooling systems for six specified ranges of performance, (2) the system most applicable for each of the six cooling categories, and (3) conceptual designs for candidate system for each of the six representative cooling categories. The six cooling categories of electrical loads are defined. The desired mission life for the cooling system is two years with both continuous and intermittent operating conditions.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-132517 , REPT-2-53002/4R-3182
    Format: application/pdf
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