Maximum Payload Orbital Transfers for a Space Shuttle Solid-Fuel Upper Stage Vehicle.

摘要

A two-stage, solid-fuel proposal for the Interim Upper Stage Vehicle of th Space Transportation System has been selected for use by the Department of Defense. It is the purpose of this study to investigate the capabilities of such a vehicle in terms of the maximum payload which can be delivered to orbit. This optimal payload problem is examined in light of three energy management techniques. The first technique, thrust termination, involves shutting off engine thrust prior to complete use of propellant. The second technique investigates the effects on payload of varying the central angle through which the transfer is made. The third technique, offloading, examines the possibility of reducing the amount of available fuel for either stage prior to the mission to determine if payloads can be increased. Finite burn periods are assumed in this study. A multipoint boundary value problem results from the appearance of interior constraints in the problem. A numerical technique is used to generate solutions for a range of transfers in the special coplanar problem. Conclusions are discussed for each of the three energy management techniques in the coplanar transfer. Even though non-optimal noncoplanar results were obtained it is believed that the general coplanar results can be extended to the noncoplanar problem. (Author)