The atmospheric portion of the trajectories for the aeroassisted coplanar orbit transfer was investigated. The equations of motion for the problem are expressed using reduced order model and total vehicle energy, kinetic plus potential, as the independent variable rather than time. The order reduction is achieved analytically without an approximation of the vehicle dynamics. In this model, the problem of coplanar orbit transfer is seen as one in which a given amount of energy must be transferred from the vehicle to the atmosphere during the trajectory without overheating the vehicle. An optimal control problem is posed where a linear combination of the integrated square of the heating rate and the vehicle drag is the cost function to be minimized. The necessary conditions for optimality are obtained. These result in a 4th order two-point-boundary-value problem. A parametric study was made of the optimal guidance trajectory in which the proportion of the heating rate term versus the drag varies is made. Simulations of the guidance trajectories are presented.
Optimal Aeroassisted Coplanar Orbital Transfer Using an Energy Model
1989
67 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Spacecraft guidance , Spacecraft reentry , Transfer orbits , Aeroassist , Coplanarity , Energy transfer , Equations of motion , Mathematical models , Optimal control , Trajectory control , Atmospheric density , Boundary value problems , Control simulation , Heat flux , Kinetic energy , Lift drag ratio , Potential energy
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