Trajectory optimization for the Atlas/Centaur launch vehicleA state-of-art survey of computational techniques employed in design and optimization of trajectories for the Atlas/Centaur launch vehicle is presented. Attention is focused on the constrained optimization technique, related to Hestenes' (1969) method of multipliers, with various formulas used in updating the multipliers. Advantages of applying multiplier method to trajectory optimization, with gains in computing speed, are argued, and optimization of the HEAO-A (high energy astronomical observatory) is discussed. Open-loop atmospheric guidance strategy and closed-loop exoatmospheric pitch and yaw guidance equations are dealt with, and the full range of constraints to be observed during the flight is discussed.
Document ID
19770045971
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Brusch, R. G. (General Dynamics Corp. Convair Div., San Diego, Calif., United States)