Trajectory reshaping based impact angle and time control

ZHANG Youan; LIANG Yong; LIU Jingmao; SUN Yumei

doi:10.7527/S1000-6893.2018.22009

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2018 , Vol. 39 >Issue 9: 322009 - 322017

DOI: https://doi.org/10.7527/S1000-6893.2018.22009

Electronics and Electrical Engineering and Control

Trajectory reshaping based impact angle and time control

ZHANG Youan ,
LIANG Yong ,
LIU Jingmao ,
SUN Yumei

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1. Department of Electrical and Electronic Engineering, Yantai Nanshan University, Yantai 265713, China;
2. School of Coast Defence, Naval Aeronautical and Astronautical University, Yantai 264001, China;
3. Shandong Nanshan International Flight Co., Ltd., Yantai 265713, China

Received date: 2018-01-10

Revised date: 2018-02-10

Online published: 2018-06-05

Supported by

National Natural Science Foundation of China (61273058)

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Abstract

The reshaped trajectory of the missile is supposed to be consisted of a circular arc and a straight line. The straight line goes through the target and satisfies the final impact angle constraint. The circular arc starts from the initial position of the missile, and is tangent to the straight line at a point to be determined. This point is obtained by the given impact time through an iterative algorithm. The feasible range of the impact time is given. On the basis of the reshaped trajectory, a new trajectory tracking control approach is presented based on the concept of virtual target, i.e., a compound control law composed of a feed-forward term and a feedback term is proposed for tracking the circular arc, and a proportional navigation guidance law with impact angle control is proposed for the straight line part. The proposed method is a geometry approach, and is thus easy to implement. The simulation results show that the proposed method is effective in controlling the impact angle and impact time simultaneously.

Key words： trajectory reshaping; impact angle; impact time; virtual target; trajectory tracking control; iterative algorithm; compound control; proportional navigation guidance

Cite this article

ZHANG Youan , LIANG Yong , LIU Jingmao , SUN Yumei . Trajectory reshaping based impact angle and time control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018 , 39(9) : 322009 -322017 . DOI: 10.7527/S1000-6893.2018.22009

References

[1] 姚郁, 郑天宇, 贺风华, 等. 飞行器末制导中的几个热点问题与挑战[J]. 航空学报, 2015, 36(8):2696-2716. YAO Y, ZHENG T Y, HE F H, et al. Several hot issues and challenges in terminal guidance of flight vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(8):2696-2716(in Chinese).
[2] 董晨, 晁涛, 王松艳, 等. 考虑扰动及控制饱和的多约束末制导方法[J]. 航空学报, 2014, 35(8):2225-2233. DONG C, CHAO T, WANG S Y, et al. Terminal guidance method with multiple constraints in the presence of disturbances and control saturation[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(8):2225-2233(in Chinese).
[3] CHEN K, GUO Y, WANG S C, et al. A survey on guidance law with impact time constraint[C]//Proceedings of the 35rd Chinese Control Conference (CCC2016), 2016:5711-5715.
[4] ZHANG Y A, WANG X L, WU 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] WANG X F, ZHENG Y, LIN H. Integrated guidance and control law for cooperative attack of multiple missiles[J]. Aerospace Science and Technology, 2015, 42:1-11.
[6] 赵启伦, 陈建, 李清东, 等. 高超武器与常规导弹协同攻击策略可行域研究[J]. 航空学报, 2015, 36(7):2291-2300. ZHAO Q L, CHEN J, LI Q D, et al. Feasible region of hypersonic and ballistic missiles' cooperative attack strategy[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7):2291-2300(in Chinese).
[7] 赵启伦, 陈建, 董希旺, 等. 拦截高超声速目标的异类导弹协同制导律[J]. 航空学报, 2016, 37(3):936-948. ZHAO Q L, CHEN J, DONG X W, et al. Cooperative guidance law for heterogeneous missiles intercepting hypersonic weapon[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(3):936-948(in Chinese).
[8] KUMAR S R, GHOSE D. Impact time guidance for large heading errors using sliding mode control[J]. IEEE Transactions on Aerospace & Electronic Systems, 2015, 51(4):3123-3138.
[9] SALEEM A, RATNOO A. A nonlinear guidance law for impact time control[C]//American Control Conference, 2015:651-656.
[10] SALEEM A, RATNOO A. Lyapunov-based guidance law for impact time control and simultaneous arrival[J]. Journal of Guidance, Control, and Dynamics, 2016, 39(1):164-173.
[11] KIM M, JUNG B, HAN B, et al. Lyapunov-based impact time control guidance laws against stationary targets[J]. IEEE Transactions on Aerospace and Electronic Systems, 2015, 51(2):1111-1122.
[12] 李辕, 闫梁, 赵继广, 等. 顺轨拦截模式剩余飞行时间估计方法[J]. 航空学报, 2015, 36(9):3082-3091. LI Y, YAN L, ZHAO J G, et al. Method of time-to-go estimation for head-pursuit interception mode[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(9):3082-3091(in Chinese).
[13] 杨哲, 林德福, 王辉. 带视场角限制的攻击时间控制制导律[J]. 系统工程与电子技术, 2016, 38(9):2122-2128. YANG Z, LIN D F, WANG H. Impact time control guidance law with field-of-view limit[J]. Systems Engineering and Electronics, 2016, 38(9):2122-2128(in Chinese).
[14] 张春妍, 宋建梅, 侯博, 等. 带落角和时间约束的网络化导弹协同制导律[J]. 兵工学报, 2016, 37(3):431-438. ZHANG C Y, SONG J M, HOU B, et al. Cooperative guidance law with impact angle and impact time constraints for networked missiles[J]. Acta Armamentarii, 2016, 37(3):431-438(in Chinese).
[15] ZHAO J, ZHOU R, DONG Z N. Three-dimensional cooperative guidance laws against stationary and maneuvering targets[J]. Chinese Journal of Aeronautics, 2015, 28(4):1104-1120.
[16] ZHAO J, ZHOU R. Obstacle avoidance for multi-missile network via distributed coordination algorithm[J]. Chinese Journal of Aeronautics, 2016, 29(2):441-447.
[17] ZHAO Y, SHENG Y Z, LIU X D. Analytical impact time and angle guidance via time-varying sliding mode technique[J]. ISA Transactions, 2016, 62:164-176.
[18] ZHANG Y A, MA G X, WU H L. A biased proportional navigation guidance law with large impact angle constraint and the time-to-go estimation[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2014, 228(10):1725-1734.
[19] ZHAO Y, SHENG 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.
[20] TSALIK R, SHIMA T. Inscribed angle guidance[J]. Journal of Guidance, Control, and Dynamics, 2015, 38(1):30-40.
[21] 周须峰, 孟博. 空空导弹越肩发射的虚拟目标比例导引律[J]. 飞行力学, 2014, 32(3):248-252. ZHOU X F, MENG B. Virtual target proportional navigation guidance law for air-to-air missile over the shoulder[J]. Flight Dynamics, 2014, 32(3):248-252(in Chinese).
[22] 张友安, 寇昆湖, 柳爱利. 基于地标被动观测的飞航导弹INS误差估计方法[J]. 控制与决策, 2013, 28(7):1055-1059. ZHANG Y A, KOU K H, LIU A L. INS error estimation method based on passive observation to feature target for cruise missile[J]. Control & Decision, 2013, 28(7):1055-1059(in Chinese).

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