A Multi-Constraint Guidance Method for Terminal Stages of Small Solid Launch Vehicles

被引：0
|
作者：
Zhang Q. [1 ,2 ]
Xu Z. [1 ,2 ]
Li X.-G. [1 ,2 ]
Gao F. [3 ]
Huang J.-Y. [3 ]
机构：
[1] School of Astronautics, Northwestern Polytechnical University, Xi'an
[2] Shaanxi Key Laboratory of Aerospace Flight Vehicle Technology, Xi'an
[3] China Academy of Launch Vehicle Technology, Beijing
来源：
Yuhang Xuebao/Journal of Astronautics | 2020年 / 41卷 / 03期
关键词：
Burn-coast-burn; Depleted shutdown; Pointing algorithm; Solid launch vehicle; State coupling restrain; Velocity control;
D O I：
10.3873/j.issn.1000-1328.2020.03.006
中图分类号：
学科分类号：
摘要：
In order to solve the problem of multi-constraint guidance for terminal stages of solid launch vehicles which shut off by the fuel exhaustion, a multi-constraint guidance method with the velocity control ability is designed in vacuum. For the coupling problem of state vectors caused by the process of the velocity control, an improved theoretical algorithm for exhaustion shutdown based on the pointing algorithm is deduced, which restrains the coupling by controlling the direction of the alternating attitude. The improved pointing algorithm is used as the base guidance method to obtain the required velocity vector and ignition time for the "burn-coast-burn" task mode in the exoatmosphere, satisfies with the terminal multi-constraint orbit elements and solves the two-point boundary value problems with the given arc length constraint. The proposed guidance algorithm is verified by the Monte Carlo simulations and the testing results demonstrate the powerful adaptability to different load masses, the strong robustness and excellent performance to the deviations and uncertainties, which has a certain theoretical significance and reference value for practical engineering applications. © 2020, Editorial Dept. of JA. All right reserved.
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页码：298 / 308
页数：10
相关论文
共 15 条
  • [1] Liu Y.-F., Luo J., Zhao S.-F., Application of closed loop guidance in small solid launch vehicle, Aerospace Control, 23, 3, pp. 46-51, (2005)
  • [2] Li H.-B., Li L., Iterative explicit guidance for small solid launch vehicle, Aerospace Control, 2, pp. 29-37, (2002)
  • [3] Chen X.-M., Yu M.-L., Study of iterative guidance application to launch vehicles, Journal of Astronautics, 24, 5, (2003)
  • [4] Lv X.-G., Song Z.-Y., Guidance methods of long-march launch vehicles, Journal of Astronautics, 38, 9, pp. 895-902, (2017)
  • [5] Zhang Z.-G., Yu M.-L., Geng G.-Y., Et al., Research on application of pseudo-spectral method in online guidance method for a launch vehicle, Journal of Astronautics, 38, 3, pp. 262-269, (2017)
  • [6] Castro W., Filho L., Guidance strategy for solid propelled launchers, Journal of Guidance, Control, and Dynamics, 21, 6, pp. 1006-1009, (1998)
  • [7] Pietrobom H.C., Filho C.L., Closed loop guidance algorithm for solid propellant rocket, The 19th IFAC Symposium on Automatic Control in Aerospace, (2013)
  • [8] Zhou J., Pan Y.-P., Hu W.-J., A robust and adaptive depleted shutdown guidance method of solid rocket, Aerospace Control, 31, 3, pp. 34-39, (2013)
  • [9] Yan X.-D., Lv S., Jia X.-J., Energy management analysis of ascent phase for solid rocket booster, Journal of Northwestern Polytechnical University, 31, 4, pp. 584-589, (2013)
  • [10] Li X.-G., Wang C.-X., Wang W.-H., Energy management trajectory design of solid launch vehicle based on modified Newton method, Journal of Solid Rocket Technology, 36, 1, pp. 1-6, (2013)
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