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Evaluation of a large capacity heat pump concept for active cooling of hypersonic aircraft structure

Author:
Herring, R. L.
Published:
Feb 1, 1978.
Physical Description:
1 electronic document
Additional Creators:
Pagel, L. L.
Online Version

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Restrictions on Access:
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary:
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.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19780009396.
Accession ID: 78N17339.
NASA-CR-145301.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15729944