Several mathematical models, including a minimum integral square criterion problem, were used for the qualitative investigation of fuel optimal maneuvers for spacecraft with fixed thrusters. The solutions consist of intervals of "full thrust" and "coast" indicating that thrusters do not need to be designed as "throttleable" for fuel optimal performance. For the primary model considered, singular solutions occur only if the optimal solution is "pure translation". "Time optimal" singular solutions can be found which consist of intervals of "coast" and "full thrust". The shape of the optimal fuel consumption curve as a function of flight time was found to depend on whether or not the initial state is in the region admitting singular solutions. Comparisons of fuel optimal maneuvers in deep space with those relative to a point in circular orbit indicate that qualitative differences in the solutions can occur. Computation of fuel consumption for certain "pure translation" cases indicates that considerable savings in fuel can result from the fuel optimal maneuvers.
Fuel optimal maneuvers for spacecraft with fixed thrusters
1982-01-01
Miscellaneous
No indication
English
Fuel-Time Optimal Control of Spacecraft Maneuvers
Online Contents | 1997
|Fuel/time optimal control of spacecraft maneuvers
AIAA | 1996
|Fuel/Time Optimal Control of Spacecraft Maneuvers
British Library Conference Proceedings | 1996
|Fuel/Time Optimal Control of Spacecraft Maneuvers
AIAA | 1997
|