Angular maneuver, an optimum one from the point of its quick action maximum for a case of a flat turn around the spatial axis
Abstract
The paper deals with the problem of optimizing a non-linear control system cum non-zero initial and final conditions and, in particular the problem of obtaining analytical interrelationships determining the phase trajectories and working moments of control. Here, the optimality shall be understood in the sense of quick action or a minimum of energy expenditure. As a controlled body, a flying spacecraft of the 'HOPE' type is considered. A case of a flat turn around the spatial axis, which provides for new possibilities of improving the qualitative indexes of the angular maneuver control system is scrutinized. The approaches described here for solving the problem of time-optimal control can be adapted to systems having fuel-conserving requirements. The paper offers methods of solving fuel-conserving or time-optimal problems when switching the spacecraft from an arbitrary initial position to the arbitrary final one by angle and angular velocity. The results of modeling are cited.
- Publication:
-
Space Technology and Science
- Pub Date:
- 1992
- Bibcode:
- 1992spte.symp..929M
- Keywords:
-
- Aerospace Planes;
- Control Systems Design;
- Nonlinear Systems;
- Optimization;
- Spacecraft Control;
- Spacecraft Maneuvers;
- Turning Flight;
- Boundary Conditions;
- Control Theory;
- Fuel Consumption;
- Nonlinear Equations;
- Space Communications, Spacecraft Communications, Command and Tracking