Author: LIONEL L. JR. LEVY

Publisher:

Published: 1962

Total Pages: 1

ISBN-13:

ATMOSPHERE ENTRY TRAJECTORIES WERE STUDIED TO DETERMINE THE RANGE FOR TWO TYPES OF MANEUVERS. For one type range was controlled principally by varying the point in the trajectory where the lift-drag ratio was reduced to maximum negative lift-drag ratio. For the other maneuver range was controlled principally by varying the value to which the lift-drag ratio was reduced. The influence on range of maximum deceleration limit and an error in lift-drag ratio were included; the convective and radative heating to the stagnation point of the spacecraft were also studied. The analysis was made for a spacecraft with a maximum lift-drag ratio of 0.5 entering the earth's atmosphere at parabolic velocity. The results for both types of maneuvers indicate that the spacecraft aerodynamics can provide range up to global range.