Accession Number:

AD0253295

Title:

STUDY OF HYPERSONIC AERODYNAMIC DECELERATORS INCORPORATING LIFT

Descriptive Note:

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE NAVAL SUPERSONIC LAB

Personal Author(s):

Report Date:

1960-08-01

Pagination or Media Count:

1.0

Abstract:

The use of lightweight lifting surfaces for the re-entry of earth satellites into the atmosphere is evaluated. The flight paths considered begin with a pullout to horizontal flight high in the atmosphere. After some deceleration in horizontal flight the vehicle enters a classic equilibrium glide and eventually a subsonic glide to a landing point. The flight path is analyzed in a very general form. The results of the analysis which include estimates of the temperatures and deceleration rates encountered, are applicable for a very wide range of aerodynamic coefficients and wing loadings. A general design for an inflatable vehicle is proposed, and results are presented of wind-tunnel tests of 22 variations of the basic configuration the aerodynamic coefficients measured at M equals 7.6 are approximately corrected to flight conditions at 24,000 fps and 295,000 ft. The wing loadings required to limit the heating to acceptable values are computed for a range of entry angles. Finally, rough vehicle weight estimates are presented for a range of payload weights. It is concluded that the kind of vehicle proposed is useful for the re-entry of satellites at entry angles up to about 3 degrees. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE