System studies have shown that Earth entry test could be used to demonstrate value of atmospheric sensing instrumentation systems to be used during descent into Martian atmosphere, in its "proofing " of operation of aerodynamic retardation systems, and in demonstration of communications link operation under actual conditions of vehicle motion and plasma sheath blackout; factors and limitations of test are discussed; hypothetical test program for small (28 in. diam. 30-lb) Mars atmospheric probe illustrates application of type of test, using three-stage Scout as launch vehicle.
Earth entry flight test of mars entry vehicles
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 4
1966
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Earth entry flight test of mars entry vehicles
AIAA | 1965
|Earth entry flight test of Mars entry vehicles.
AIAA | 1966
|