Affiliation:
1. Nanjing University of Aeronautics and Astronautics
Abstract
An entry range correction scheme for reusable launch vehicle (RLV) is developed to reduce the deviation between the predicted range and the computed range. Firstly the physical mechanism is turned out to verify the scheme , then implementation is demonstrated. At last, simulation results illustrate this scheme is able to reduce the deviation, and this scheme is practicality useful.
Publisher
Trans Tech Publications, Ltd.
Reference5 articles.
1. Harpold J C, Graves C A. Shuttle Entry Guidance[J]. Journal of the Astronautical Science, 1979, 27(3): 239-268.
2. Wingrove R C. A Survey of Atmosphere Reentry Guidance and Control Methods. IAS Paper No. 63-86, (1963).
3. K D Mease, J P Kremer. Shuttle Entry Guidance Revisited. AIAA-92-4450, (1992).
4. Shen Z, Lu P. On-board Generation of Three-dimensional Constrained Entry Trajectories[J]. Journal of Guidance, Control, and Dynamics. 2003, 26(1): 111-121.
5. Zimmerman C, Dukeman G, Hanson J. Automated method to compute orbital reentry trajectories with heating constraints[J]. Journal of Guidance, Control, and Dynamics. 2003, 26(4): 523-539.