Comparative Evaluation of Flight Control Power Distribution Systems for Hypersonic Aircraft Aircraft Engineering Dept., Douglas Aircraft Company, Incorporated

Format:

Conference/Event

Author/Creator:

Caplan, M. L., author.

Conference Name:

Aerospace Systems Conference and Engineering Display (1967-06-27 : Los Angeles, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1967

Summary:

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: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

Notes:

Vendor supplied data

Publisher Number:

670530

Access Restriction:

Restricted for use by site license