A retargeting procedure is developed for use as a nonlinear low thrust guidance scheme. The selection of a control program composed of a sequence of inertially fixed thrust-acceleration vectors permits all trajectory computations to be made with closed form expressions, and allows the controls to be represented by constant parameters, thrust-acceleration vectors and thrusting times. By requiring each trajectory to be time optimal, the guidance problem is transformed into a parameter optimization problem which is solved by the conjugate gradient method. The scheme is applied to a low thrust capture mission, and the results of computer simulations are presented.
Iterative explicit guidance for low thrust spacecraft.
American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Palo Alto
1972-09-01
Conference paper
No indication
English
Iterative explicit guidance for low thrust spacecraft
AIAA | 1972
|Iterative Explicit Guidance for Low Thrust Spaceflight
AIAA | 1974
|Explicit guidance law for manned spacecraft
AIAA | 1992
|Explicit and unified methods of spacecraft guidance
NTRS | 1965
|