Computation method for reachable domain of aerospace plane under the influence of no-fly zone

被引：0
作者：
Zhang J. [1 ]
Zhou D. [2 ]
Yang D. [2 ]
Liu R. [2 ]
Liu K. [1 ]
机构：
[1] School of Aeronautics and Astronautics, Dalian University of Technology, Dalian
[2] AVIC Shenyang Aircraft Design and Research Institute, Shenyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2021年 / 42卷 / 08期
基金：
中国国家自然科学基金;
关键词：
Aerospace plane; Avoid guidance; No-fly zone; Predictor-corrector; Reachable domain;
D O I：
10.7527/S1000-6893.2021.25771
中图分类号：
学科分类号：
摘要：
The no-fly zone influences the reachable domain of the aerospace plane in the reentry phase. An ultimate circumnavigation based method is proposed to obtain the reachable area no matter where the no-fly zone is. First, considering the residual flight capability of the aerospace plane after avoidance of the no-fly zone, the sub-reachable domain of the plane is derived from the tangent point between the ultimate circumnavigation trajectory and the no-fly zone. On this basis, the boundary of the reachable domain and the unreachable domain is obtained. Then, classifying and solving algorithms for the possible positions of the no-fly zone within the longitude-latitude profile are given to acquire the sub-reachable domains in different situations. The ray method is used to judge whether the target point is located in the reachable domain. The piecewise predictor-corrector guidance method is applied to realize the feasible target point. Finally, classification results of circular no-fly zones dispersed in the longitude/latitude profile are given in simulation. The influenced reachable domain for each class is also obtained. Simulation results show that regardless of the position of the no-fly zone, the proposed method has good stability in terms of obtaining the reachable domain at any situation. For the target points within the reachable domain, the precision requirement can be satisfied by using the piecewise predictor-corrector guidance method. © 2021, Beihang University Aerospace Knowledge Press. All right reserved.
引用
收藏
相关论文
共 26 条
  • [1] BENITO J, MEASE K D., Reachable and controllable sets for planetary entry and landing, Journal of Guidance, Control, and Dynamics, 33, 3, pp. 641-654, (2010)
  • [2] HSU F K, KUO T S, CHERN J S., Landing domain analysis of shuttle re-entry vehicles, International Journal of Systems Science, 22, 7, pp. 1145-1158, (1991)
  • [3] CHEN S Y., The longitudinal and lateral range of hypersonic glide vehicles with constant bank angle
  • [4] NYLAND F S., Hypersonic turning with constant bank angle control
  • [5] ZENG X J, ZHONG F J, DING X L, Et al., Method for landing footprint generation in reusable vehicles, Manned Spaceflight, 23, 1, pp. 14-20, (2017)
  • [6] WANG T, ZHANG H B, LI Y Y, Et al., Landing footprint generation of entry vehicle based on Gauss pseudospectral method, Journal of National University of Defense Technology, 38, 3, pp. 75-80, (2016)
  • [7] FU Y, YANG W L, CUI N G., Calculation of reachable landing locations of lift entry vehicle, Journal of Harbin Institute of Technology, 44, 11, pp. 13-19, (2012)
  • [8] FU Y., Autonomous guidance method for lift transportation vehicle, (2012)
  • [9] WANG L, LIU X, YANG T, Et al., Footprint calculation for hypersonic glide vehicle, Journal of Ballistics, 26, 1, pp. 50-55, (2014)
  • [10] FENG B M, NIE W S, LI K., Research on closest-aproach of footprint and coverage for reentry vehicle, Aerospace Control, 30, 6, pp. 43-49, (2012)
123