OPTIMAL TRAJECTORIES FOR LEO-TO-LEO AEROASSISTED ORBITAL TRANSFER

作     者：MIELE, A LEE, WY MEASE, KD 

作者机构：Aero-Astronautics Group Rice University Houston Texas Jet Propulsion Laboratory Pasadena California USA 

出 版 物：《ACTA ASTRONAUTICA》 (Acta Astronaut)

年 卷 期：1988年第18卷第C期

页      面：99-122页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：Boeing Military Aircraft Company Jet Propulsion Laboratory, JPL, (956415) 

主　　题：Orbital transfer coplanar orbital transfer noncoplanar orbital transfer LEO-to-LEO transfer aeroassisted orbital transfer transfer between circular orbits plane change lift coefficient modulation angle of bank modulation optimal trajectories optimal control problems minimax problems Bolza problems Chebyshev problems transformation techniques numerical methods computing methods sequential gradient-restoration algorithm 

摘      要：This paper considers both classical and minimax problems of optimal control arising in the study of noncoplanar, aeroassisted orbital transfer. The maneuver considered involves the transfer from one planetary orbit to another having different orbital inclination, but the same radius. An example is the LEO-to-LEO transfer of a spacecraft with a prescribed plane change, where LEO denotes low Earth orbit. The basic idea is to employ the hybrid combination of propulsive maneuvers in space and aerodynamic maneuvers in the sensible atmosphere. Hence, this type of flight is also called synergetic space flight. With reference to the atmospheric part of the maneuver, trajectory control is achieved by modulating the lift coefficient (hence, the angle of attack) and the angle of bank. The presence of upper and lower bounds on the lift coefficient is considered. Three different transfer maneuvers are studied. Type 1 involves four impulses and four space plane changes; Type 2 involves three impulses and three space plane changes; and Type 3 involves three impulses and no space plane change. In Type 1, the initial impulse directs the spacecraft away from Earth, and then is followed by an apogee impulse propelling the spacecraft toward Earth; in Types 2 and 3, the initial impulse directs the spacecraft toward Earth. A common element of these maneuvers is that they all include an atmospheric pass, with velocity depletion coupled with plane change. Within the framework of classical optimal control, the following problems are studied: (P1) minimize the energy required for orbital transfer; (P4) maximize the time of flight during the atmospheric portion of the trajectory; (P5) minimize the time integral of the square of the path inclination. Within the framework of minimax optimal control, the following problem is studied: (Q1) minimize the peak heating rate. Numerical solutions for Problems (P1), (P4), (P5), (Q1) are obtained by means of the sequential gradient-restoration algorithm