Solution to problem of performing earth-orbital rendezvous with Saturn-class payload is provided by using analytical methods to choose among competing guidance laws and to select criteria and gains giving smooth acceleration demand while retaining fuel economy and low sensitivity to trajectory errors; typical mission is selected and digital simulation is used to optimize parameters for homing and homing-docking mission; rendezvous is achieved with less than 30% throttling for propulsion system developing 30,000lb thrust and carrying Saturn V payload.
Rendezvous guidance with limited engine throttling
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 10
1966
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Rendezvous guidance with limited engine throttling.
AIAA | 1966
|NTRS | 1990
|NTIS | 1990
|Rendezvous Guidance Technology
NTRS | 1962
|NTRS | 1955
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