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  • 1
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    Unknown
    Integrated temperature sensor (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Proposed temperature-sensor/failure-detection system utilizes liquid-filled sensors attached as matrix to monitored surface. Fluid passages are integral part of monitored surface or are small-diameter tubing in good thermal contact with monitored surface. System offers significant advantages over discrete sensors in terms of simplicity, reliability, cost, ease of installation, maintainability, and weight.
    Keywords: MACHINERY
    Type: LAR-12056 , NASA Tech Briefs (ISSN 0145-319X); 2; 2; P. 3
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Evaluation of a large capacity heat pump concept for active cooling of hypersonic aircraft structure (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of engineering analyses assessing the conceptual feasibility of a large capacity heat pump for enhancing active cooling of hypersonic aircraft structure are presented. A unique heat pump arrangement which permits cooling the structure of a Mach 6 transport to aluminum temperatures without the aid of thermal shielding is described. The selected concept is compatible with the use of conventional refrigerants, with Freon R-11 selected as the preferred refrigerant. Condenser temperatures were limited to levels compatible with the use of conventional refrigerants by incorporating a unique multipass condenser design, which extracts mechanical energy from the hydrogen fuel, prior to each subsequent pass through the condenser. Results show that it is technically feasible to use a large capacity heat pump in lieu of external shielding. Additional analyses are required to optimally apply this concept.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145301
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Study of fail-safe abort system for an actively cooled hypersonic aircraft, volume 2 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conceptual designs of a fail-safe abort system for hydrogen fueled actively cooled high speed aircraft are examined. The fail-safe concept depends on basically three factors: (1) a reliable method of detecting a failure or malfunction in the active cooling system, (2) the optimization of abort trajectories which minimize the descent heat load to the aircraft, and (3) fail-safe thermostructural concepts to minimize both the weight and the maximum temperature the structure will reach during descent. These factors are examined and promising approaches are evaluated based on weight, reliability, ease of manufacture and cost.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144920 , MDC-A3313-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Thermal design for areas of interference heating on actively cooled hypersonic aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerous actively cooled panel design alternatives for application in regions on high speed aircraft that are subject to interference heating effects were studied. Candidate design concepts were evaluated using mass, producibility, reliability and inspectability/maintainability as figures of merit. Three design approaches were identified as superior within certain regimes of the matrix of design heating conditions considered. Only minor modifications to basic actively cooled panel design are required to withstand minor interference heating effects. Designs incorporating internally finned coolant tubes to augment heat transfer are recommended for moderate design heating conditions. At severe heating conditions, an insulated panel concept is required.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-2828
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Study of a fail-safe abort system for an actively cooled hypersonic aircraft. Volume 1: Technical summary (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conceptual designs of a fail-safe abort system for hydrogen fueled actively cooled high speed aircraft are examined. The fail-safe concept depends on basically three factors: (1) a reliable method of detecting a failure or malfunction in the active cooling system, (2) the optimization of abort trajectories which minimize the descent heat load to the aircraft, and (3) fail-safe thermostructural concepts to minimize both the weight and the maximum temperature the structure will reach during descent. These factors are examined and promising approaches are evaluated based on weight, reliability, ease of manufacture and cost.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-2652 , MDC-A3313-VOL-1
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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