[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2021 , Vol. 41 >Issue 3: 57 - 61

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2021.03.013

A Two-parameter Reentry Trajectory Design Method with Time Constraints

  • QIAO Hao ,
  • MAO Rui ,
  • BAI Fengke ,
  • DU Fenghuai
Expand
  • Xi’an Modern Control Technology Research Institute,Xi’an 710065, China

Received date: 2020-07-08

  Online published: 2025-02-20

Fold

Abstract

In order to control the reentry flight time, expand the application scenarios of existing reentry vehicles and improve the strike capability against time sensitive targets, this paper proposes an improved drag acceleration profile which could determine the trajectory length and the total flight time simultaneously based on the two-parameter Newton iterative method. The iteration of reference drag acceleration profile can be done quickly and the reference trajectory with different constraints can be generated using the proposed method. Finally, the regulation law of the total reentry flight time is obtained by simulation analysis, which provides a basis for the cooperative problem of multiple reentry vehicles.

Key words： reentry trajectory; two-parameter Newton iterative method; drag acceleration profile; reentry time constraints

Cite this article

QIAO Hao , MAO Rui , BAI Fengke , DU Fenghuai . A Two-parameter Reentry Trajectory Design Method with Time Constraints[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2021 , 41(3) : 57 -61 . DOI: 10.15892/j.cnki.djzdxb.2021.03.013

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
JEON I S, LEE J I, TAHK M J. Impact-time-control guidance law for anti-ship missiles[J]. IEEE Transactions on Control Systems Technology, 2006, 14(2): 260-266.

[2]
LEE J I, JEON I S, TAHK M J. Guidance law to control impact time and angle[J]. IEEE Transactions on Aerospace and Electronic Systems, 2007, 43(1): 301-310.

[3]
KANG S H, KIM H J. Differential game missile guidance with impact angle and time constraints[J]. IFAC Proceedings Volumes, 2011, 44(1): 3920-3925.

[4]
Z Y, W X L, W H L. A distributed cooperative guidance law for salvo attack of multiple anti-ship missiles[J]. Chinese Journal of Aeronautics, 2015, 28(5): 1438-1450.

[5]
Z Y, S Y Z, LIU X D. Trajectory reshaping based guidance with impact time and angle constraints[J]. Chinese Journal of Aeronautics, 2016, 29(4): 984-994.

[6]
LIANG Z X, Y J L, REN Z, et al. Trajectory planning for cooperative flight of two hypersonic entry vehicles[C]//AIAA. Proceedings of 21st AIAA International Space Planes and Hypersonics Technologies Conference. Reston: AIAA, 2017: 51-63.

[7]
方科, 张庆振, 倪昆, 等. 高超声速飞行器时间协同再入制导[J]. 航空学报, 2018(5):202-217.

[8]
王肖, 郭杰, 唐胜景, 等. 基于解析剖面的时间协同再入制导[J]. 航空学报, 2019, 40(3):234-245.

[9]
徐瑞民. 二元非线性方程组求根的牛顿迭代法[J]. 山东轻工业学院学报(自然科学版), 2009, 23(4):89-91.

[10]
PHILLIPS T H. A Common aero vehicle (CAV) model, description, and employment guide[EB/OL].(2003-01-27)[2020-07-10]. http://www.dtic.Mil/matrics/sbir/sbir041/srch/af031a.doc.

[11]
王智, 唐硕, 闫晓东. 高超声速滑翔飞行器约束预测校正再入制导[J]. 飞行力学, 2012, 30(2):175-180.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]