Citation: | FENG Yue, WANG Rongshun, MEI Yingxue, et al. Reentry trajectory planning for range-extended hypersonic vehicles with boosters[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(8): 1503-1513. doi: 10.13700/j.bh.1001-5965.2019.0519(in Chinese) |
A reentry trajectory for a hypersonic vehicle with an accessory rocket-powered engine is optimized in terms of the ignition time of boosters and the fuel consumption, based on which a reentry mode of range-extended trajectory is proposed. The analytical solution of Sanger trajectory reveals the conditions of the attack angle and initial velocity for the vehicle to travel the longest distance, which can be used to manipulate the boosters with the goal of maximum travel distance and minimum fuel consumption. The reentry trajectory is designed as a combination of Sanger trajectory and quasi-equilibrium glide trajectory. In the first stage of reentry, the vehicle flies along an equal altitude quasiperiodic trajectory guaranteed by boosters interval ignition, and ensures that the range is longest. In the second stage of reentry, the vehicle flies along a quasi-equilibrium gliding trajectory which is the solution of an optimal control problem with trajectory smoothness and distance as the performance index and the problem is converted and solved by constrained nonlinear programming. Finally, the proposed reentry trajectory is simulated and the results show that the trajectory is quite analogous to the so called "stone skipping" under the conditions of sufficient fuel and appropriate path angle, which can efficiently use its mechanical energy of a stone to long range over a lake. Compared with the trajectories with boosters working in different modes and the trajectories solved in different ways, the proposed reentry trajectory has 3.47-3.84 times range, 1.04-1.18 times end kinetic energy and 4.47-15.79 times fuel availability.
[1] |
孙国庆, 杨大光.再入航天器返回过程简介[J].科技创新导报, 2011(18):88. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kjzxdb201118076
SUN G Q, YANG D G.Brief introduction of reentry spacecraft reentry process[J].Science and Technology Innovation Herald, 2011(18):88(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kjzxdb201118076
|
[2] |
SANGER E, BREDT J.A rocket drive for long range bombers[M].HAMERMESH M, translated.Washington D. C.:Technical Information Branch, Navy Department, 1994:108-135.
|
[3] |
LU P.Reentry guidance trajectory control for reusable launch vehicle[J].Journal of Guidance, Control, and Dynamics, 1997, 20(1):143-149.
|
[4] |
卢宝刚, 傅瑜, 崔乃刚, 等.基于拟平衡滑翔的数值预测再入轨迹规划算法[J].哈尔滨工业大学学报, 2015, 47(1):14-19. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hebgydxxb201501003
LU B G, FU Y, CUI N G, et al.Numerical prediction method of reentry trajectory planning based on quasi equilibrium glide condition[J].Journal of Harbin Institute of Technology, 2015, 47(1):14-19(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hebgydxxb201501003
|
[5] |
张科南.基于坡度率的再入飞行器在线轨迹规划[J].战术导弹技术, 2015(5):24-29. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201505005
ZHANG K N.On-board trajectory planning for reentry vehicle based on slope rate[J].Tactical Missile Technology, 2015(5):24-29(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201505005
|
[6] |
RAO A V, MEASE K D.Entry trajectory tracking law via feedback linearization[J].Journal of Guidance, Control, and Dynamics, 1998, 21(5):726-740. http://cn.bing.com/academic/profile?id=6a7f31545ea08eaa91fa573fcf2ee98f&encoded=0&v=paper_preview&mkt=zh-cn
|
[7] |
ELANGAR G N, KAZEMI M A.Pseudospectral Chebyshev optimal control of constrained nonlinear dynamical systems[J].Computational Optimization and Applications, 1998, 11(2):195-217. http://cn.bing.com/academic/profile?id=af9c5fe190dc3fb692a9ce9f1d0fa47a&encoded=0&v=paper_preview&mkt=zh-cn
|
[8] |
呼卫军, 卢青, 常晶, 等.特征趋势分区Gauss伪谱法解再入轨迹规划问题[J].航空学报, 2015, 36(10):3338-3348. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201510014
HU W J, LU Q, CHANG J, et al.Reentry trajectory planning method based on Gauss pseudospectral with characteristics of trend partion[J].Acta Aeronautica et Astronautica Sinica, 2015, 36(10):3338-3348(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201510014
|
[9] |
雍恩米.高超声速滑翔式再入飞行器轨迹优化与制导方法研究[D].长沙: 国防科学技术大学, 2008: 48-68.
YONG E M. Study on trajectory optimization and guidance approach for hypersonic glide-reentry vehicle[D].Changsha: National University of Defense Technology, 2008: 48-68(in Chinese).
|
[10] |
宋超, 黎志强, 刘旭.考虑航路点的飞行器再入轨迹优化与仿真[J].航空计算技术, 2019, 49(1):19-23. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkjsjs201901005
SONG C, LI Z Q, LIU X.Reentry trajectory optimization and simulation of aircraft with waypoints considered[J].Aeronautical Computing Technique, 2019, 49(1):19-23(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkjsjs201901005
|
[11] |
杨鹏宇, 齐瑞云, 郭小平.故障下高超声速飞行器再入在线轨迹重构[J].战术导弹技术, 2017(4):73-81. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201704011
YANG P Y, QI R Y, GUO X P.On-line trajectory reconfiguration for reentry hypersonic vehicle under failures[J].Tactical Missile Technology, 2017(4):73-81(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=zsddjs201704011
|
[12] |
CARTER P H, PINES D J, RUDD L V.Approximate performance of periodic hypersonic cruise trajectories for global reach[J].IBM Journal of Research and Development, 2000, 44(5):703-714.
|
[13] |
蔺君, 何英姿, 黄盘兴.基于改进分段Gauss伪谱法的带推力高超声速飞行器再入轨迹规划[J].控制理论与应用, 2019, 36(9):1662-1671. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kzllyyy201910010
LIN J, HE Y Z, HUANG P X.Powered hypersonic vehicle reentry trajectory optimization based on improved multi-phase Gauss spectral method[J].Control Theory & Applications, 2019, 36(9):1662-1671(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=kzllyyy201910010
|
[14] |
VINH N X.Optimal trajectories in atmospheric flight[M].Amsterdam:Elsevier Scientific Publishing Co., 1981:47-75.
|
[15] |
郑伟, 汤国建.弹道导弹自由段解算的等高约束解析解[J].宇航学报, 2007, 28(2):269-272. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200702006
ZHENG W, TANG G J.Contour restricted analytical solution for free flight trajectory of ballistic missile[J].Journal of Astronautics, 2007, 28(2):269-272(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200702006
|
[16] |
EGGERS A J J, ALLEN J H, NEICE S E.A comparative analysis of the performance of long-range hypervelocity vehicles: NACA-1958-1382[R].Washington, D.C.: NACA, 1958.
|
[17] |
TIMOSHENKO S, YOUNG D H.Advanced dynamics[M].New York:McGraw-Hill Company, 1948:106-190.
|
[18] |
雍恩米, 陈磊, 唐国金.飞行器轨迹优化数值方法综述[J].宇航学报, 2008, 29(2):397-406. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200802002
YONG E M, CHEN L, TANG G J.A survey of numerical methods for trajectory optimization of spacecraft[J].Journal of Astronautics, 2008, 29(2):397-406(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200802002
|