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Thermal Management of Advanced Aircraft Secondary Power Systems
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English
Abstract
This paper presents a thermal management system study for a hydrocarbon-fueled Mach 6 aircraft equipped with the following three types of secondary power systems: (i) conventional system with hydraulic actuators and turbine-driven fuel pumps; (ii) more-electric system with electromechanical actuators and turbine-driven fuel pumps; and (iii) all-electric system with electromechanical actuators and electrically driven fuel pumps.
The thermal management system was designed to provide environmental control for the crew cabin, avionics, flight controls, and electrical generators. Engine fuel was used as the ultimate heat sink for all cases.
Details of thermal protection concepts for the three cases are discussed and compared in this paper. A brief overview of integrated thermal management for the total aircraft is also presented.
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Citation
Iya, S., "Thermal Management of Advanced Aircraft Secondary Power Systems," SAE Technical Paper 901959, 1990, https://doi.org/10.4271/901959.Also In
References
- Advanced Aircraft Secondary Powerr System Design U.S. Air Force contract number F33615-88-C-2837
- Thermal Management and Environmental Control of Hypersonic Vehicles Iya S. K. Trikha A. K. Ladd M. M. SAE paper No. 891440 19th Intersociety Conference on Environmental Systems San Diego, CA July 24-26 1989
- Advanced Aircraft Secondary Power System Design Woods E. J. Rubertus C. S. Mehdi I. S. paper No.900392, IECEC '90 Reno, NV August 16 1990