Difficulties arise in guiding a solar electric propulsion spacecraft due to nongravitational accelerations caused by random fluctuations in the magnitude and direction of the thrust vector. These difficulties may be handled by using a low thrust guidance law based on the linear-quadratic-Gaussian problem of stochastic control theory with a minimum terminal miss performance criterion. Explicit constraints are imposed on the variances of the control parameters, and an algorithm based on the Hilbert space extension of a parameter optimization method is presented for calculation of gains in the guidance law. The terminal navigation of a 1980 flyby mission to the comet Encke is used as an example.
Limited variance control in statistical low thrust guidance analysis
Astrodynamics Specialist Conference ; 1975 ; Nassau, Bahamas
1975-07-01
Conference paper
No indication
English
Low-thrust perturbation guidance
AIAA | 1982
|Constrained low-thrust guidance.
NTRS | 1973
|