ORBITAL RENDEZVOUS OPTIMIZATION USING THE PONTRYAGIN MAXIMUM PRINCIPLE.
Rept. for Nov 63-Jan 65,
AEROSPACE CORP EL SEGUNDO CA EL SEGUNDO TECHNICAL OPERATIONS
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The Pontryagin Maximum Principle is employed to generate the control law for achieving optimal rendezvous between a space vehicle and a satellite in circular orbit about a body possessing a central force field similar to the earths gravitational field. Optimality is with respect to minimal expenditure of space vehicle propellant in achieving rendezvous. A digital computer simulation of the system equations, known as the Orbital Rendezvous Optimization program, is described. A method of estimating the adjoint variable initial values corresponding to the optimal rendezvous trajectory is given. Refinement of these estimates by an iteration sub-routine in the digital computer program is described. Possible uses of the equations machine program in real-time rendezvous operations are described. Uses of the equations machine program in studying errors occurring during the rendezvous maneuver are discussed. Use of the equations in studying types of rendezvous other than minimum-propellant-expenditure is also discussed. Details of two test cases run successfully with the Orbital Rendezvous Optimization program are given. The test cases, relatively simple in design, are for satellites in orbit about the earth. Present limitations of the program, status of program testing, and work remaining to be done, are topics which conclude the paper. Author
- Theoretical Mathematics
- Spacecraft Trajectories and Reentry