FEASIBILITY STUDY AND INVESTIGATION OF THERMOELECTRIC POWER GENERATION AND COOLING FOR FLIGHT VEHICLES. Final Phase I Summary Report (Report No. 11) March 1, 1962 thru April 1, 1962
The feasibility of thermoelectric cooling systems for fiight vehicles was studied. Applications considered were occupied compartments in the aircraft and avionic equipment cooling. Thermoelectric cooling systems compare favorably with existing cooling systems for subsonic aircraft electronic equipment, having a cooling load up to 1.5 kw and an allowable temperature level equivalent to MIL- E-5400, class I. Thermoelectric cooling loads greater than 1.5 kw are feasible for subsonic aircraft electronic equipment having an allowable temperature level higher than specified in MIL-E-5400, class I (such as class II equipment). An improvement of 43% in thermoelectric material propenties doubles the feasible range of cooling loads for class I equipment to 3 kw. Special classes of equipment requiring temperature levels lower than class I also become feasible for cooling loads under 3 kw; with the maximum feasible cooling load depending upon the maximum allowable temperature of the equipment. Cooling of cockpits or of electronic equipment for supersonic airplanes is not feasible with current thermoelectric materials. (auth)
- Research Organization:
- Douglas Aircraft Co., Inc., Long Beach, Calif.
- DOE Contract Number:
- NOW 61-0404-1
- NSA Number:
- NSA-17-012387
- OSTI ID:
- 4771273
- Report Number(s):
- AD-278078
- Resource Relation:
- Other Information: Orig. Receipt Date: 31-DEC-63
- Country of Publication:
- United States
- Language:
- English
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