Detail A Method for Trajectory Optimization of a Spacecraft Flying in the Atmosphere   Oleh:  TAKANO, Hiroyuki ; BABA, Yoriaki Jenis: Article from Article Dalam koleksi: Final Program and Book of Abstracts: The 4th Asian Control Conference, September 25-27, 2002 (Sep. 2002), page 863-868. Topik: Guidance And Control; Trajectory Optimization; AOTV Fulltext: AC021507.PDF (247.57KB) Isi artikel In this paper, we determine and characterize necessary properties of the control system for the heat rate constrained atmospheric flight of a spacecraft, Aeroassisted Orbital Transfer Vehicle (AOTV) that minimizes the propellant mass required for the maneuver. Generally speaking, atmospheric flights for plane changes of the earth orbits, save fuel and increase the final mass considerably, but the problem is the aerodynamic heating. It results in a multi-dimensional trajectory optimization with a state variable inequality constraint. The solutions obtained in this research show that the optimal thrust usage is sensitive to the magnitude of the heat rate limit and one should be careful to choose the limit value to design the thrust controller. We also considered the thrust vectoring in the atmosphere and studied its influence on the trajectory optimization. Opini Anda Klik untuk menuliskan opini Anda tentang koleksi ini! Kembali

Copyright © 2006, 2007 Unika Atma Jaya, all rights reserved