Comparative Evaluation of Flight Control Power Distribution Systems for Hypersonic Aircraft 670530
Hypersonic aircraft represent a radical departure from contemporary air vehicles in terms of system performance requirements and operating envirnoment. Flight control components may encounter environmental temperatures as high as 1600 F during high Mach number cruise.
A basic re-evaluation of auxiliary power distribution techniques has been made to determine the type of system most suitable for use under these conditions. Five types were considered:
Cooled hydraulic system.
Liquid metal system.
Pulsating flow hydraulic system (using conventional fluid in the moderate temperature, and liquid metal in the higher temperature portions of the vehicle).
These systems have been evaluated for use in a high Mach number cruise aircraft on the basis of weight, power requirements, and cooling requirements. As a result of this study, a cooled hydraulic system appears to be the most desirable choice for a first generation hypersonic cruise aircraft.