Energy-optimal guidance law with virtual hand-over point

LI Chendi; WANG Jiang; LI Bin; HE Shaoming; ZHANG Tong

doi:10.7527/S1000-6893.2019.23249

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2019 , Vol. 40 >Issue 12: 323249 - 323249

DOI: https://doi.org/10.7527/S1000-6893.2019.23249

Electronics and Electrical Engineering and Control

Energy-optimal guidance law with virtual hand-over point

LI Chendi ,
WANG Jiang ,
LI Bin ,
HE Shaoming ,
ZHANG Tong

Expand

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
2. Beijing Key Laboratory of UAV Autonomous Control, Beijing Institute of Technology, Beijing 100081, China;
3. Hua An Industry Group Company Limited, Qiqihar 161006, China

Received date: 2019-06-27

Revised date: 2019-08-01

Online published: 2019-09-16

Supported by

National Natural Science Foundation of China (U1613225)

Fold

Abstract

Aiming at the problem of fixed target missile guidance with virtual hand-over point, a global energy optimal guidance law with/without terminal angle constraint is designed based on the optimization theory in Hilbert space. By linearizing the model, the proposed optimal guidance model is transformed into a linear quadratic opti-mal control problem. Then the concept of Zero-Effort-Miss (ZEM) is used to reduce the order of the system, deriving the analytical solution. The proposed guidance law can ensure the missile pass through the virtual hand-over point accurately and reached the desired terminal angle. The simulation results show that, compared with the classical guidance law, the proposed guidance law can significantly reduce the energy consumption of global control.

Key words： optimal guidance; virtual hand-over point; terminal angle constraint; path following; proportional navigation guidance; trajectory shaping guidance

Cite this article

LI Chendi , WANG Jiang , LI Bin , HE Shaoming , ZHANG Tong . Energy-optimal guidance law with virtual hand-over point[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019 , 40(12) : 323249 -323249 . DOI: 10.7527/S1000-6893.2019.23249

References

[1] 刘海军, 王丽娜. 复合制导防空导弹中末制导交班问题研究[J]. 现代防御技术, 2006, 34(2):29-33. LIU H J, WANG L N. Study on handover problem of compound guidance missile weapon[J]. Modern Defense Technology, 2006, 34(2):29-33(in Chinese).
[2] 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. Several hot issues and challenges in terminal guidance of flight vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2015,36(8):2696-2716(in Chinese).
[3] 唐明南, 郑学合,王天舒,等.多平台信息下机动目标拦截中末制导交班研究[J].系统工程与电子技术,2017,39(12):2757-2764. TANG M N, ZHENG X H, WANG T S, et al. Handover of guidance from midcourse to terminal in the maneuvering target interception based on multi-platform information[J]. Systems Engineering and Electronics, 2017,39(12):2757-2764(in Chinese).
[4] SHEHAB S, RODRIGUES L. Preliminary results on UAV path following using piecewise-affine control[C]//IEEE Conference on Control Applications. Piscataway, NJ:IEEE Press, 2005.
[5] YU M J, ATKINS E M, KOLMANOVSKY I, et al. Trim-commanded adaptive control for waypoint-defined trajectory following[C]//AIAA Guidance, Navigation, and Control (GNC) Conference. Reston, VA:AIAA, 2013.
[6] 张友安, 梁勇, 刘京茂, 等. 基于轨迹成型的攻击角度与时间控制[J]. 航空学报, 2018, 39(9):322009. ZHANG Y A, LIANG Y, LIU J M, et al. Trajectory reshaping based impact angle and time control[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(9):322009(in Chinese).
[7] WHANG I H, HWANG T W. Horizontal waypoint guid ance design using optimal control[J]. IEEE Transactions on Aerospace and Electronic Systems, 2002, 38(3):1116-1120.
[8] MOON G, KIM Y. Optimum flight path design passing through waypoints for autonomous flight control system[J]. Engineering Optimization, 2013, 37(7):755-774.
[9] RYOO C K, SHIN H S, TAHK M J. Energy optimal waypoint guidance synthesis for antiship missiles[J]. IEEE Transactions on Aerospace & Electronic Systems, 2010, 46(1):80-95.
[10] 孙胜, 张华明, 周荻. 考虑自动驾驶仪动特性的终端角度约束滑模导引律[J]. 宇航学报, 2013, 34(1):69-78. SUN S, ZHANG H M, ZHOU D. Sliding mode guidance law with autopilot lag for terminal angle constrained trajectories[J]. Journal of Astronautics, 2013, 34(1):69-78(in Chinese).
[11] RYOO C K, CHO H, TAHK M J. Optimal guidance laws with terminal impact angle constraint[J]. Journal of Guidance, Control, and Dynamics, 2005, 28(4):724-732.
[12] RYOO C K, CHO H, TAHK M J. Time-to-go weighted optimal guidance with impact angle constraints[J]. IEEE Transactions on Control Systems Technology, 2006, 14(3):483-492.
[13] 张友安, 黄诘,孙阳平.带有落角约束的一般加权最优制导律[J].航空学报, 2014,35(3):848-856. ZHANG Y A, HUANG J, SUN Y P. Generalized weighted optimal guidance laws with impact angle constraints[J]. Acta Aeronautica et Astronautica Sinica, 2014,35(3):848-856(in Chinese).
[14] 闫梁, 赵继广,沈怀荣, 等.带末端碰撞角约束的三维联合偏置比例制导律设计[J].航空学报,2014,35(7):1999-2010. YAN L, ZHAO J G, SHEN H R, et al. Three-dimensional united biased proportional navigation guidance law for interception of targets with angular constraints[J]. Acta Aeronautica et Astronautica Sinica, 2014,35(7):1999-2010(in Chinese).
[15] ERER K S, MERTTOPCUOGLU O. Indirect impact-angle-control against stationary targets using biased pure proportional navigation[J]. Journal of Guidance, Control, and Dynamics, 2012, 35(2):700-704.
[16] 郭建国, 韩拓,周军, 等.基于终端角度约束的二阶滑模制导律设计[J]. 航空学报, 2017,38(2):210-219. GUO J G, HAN T, ZHOU J, et al. Second-order sliding-mode guidance law with impact angle constraint[J]. Acta Aeronautica et Astronautica Sinica, 2017,38(2):210-219(in Chinese).
[17] JEON I S, LEE J I. Optimality of proportional navigation based on nonlinear formulation[J]. IEEE Transactions on Aerospace and Electronic Systems, 2010, 46(4):2051-2055.
[18] ZARCHAN P. Tactical and strategic missile guidance[M]. Reston, VA:AIAA, 2012:569-577.
[19] SHAFERMAN V, SHIMA T. Linear quadratic guidance laws for imposing a terminal intercept angle[J]. Journal of Guidance, Control, and Dynamics, 2008, 31(5):1400-1412.
[20] RATNOO A, HAYOUN S Y, GRANOT A, et al. Path following using trajectory shaping guidance[C]//AIAA Guidance, Navigation, and Control (GNC) Conference. Reston, VA:AIAA, 2013.
[21] HE S, LEE C-H, SHIN H-S. Minimum-effort waypoint-following guidance[J/OL]. Journal of Guidance, Control, and Dynamics,(2019-01-30)[2019-06-27].http://dspace.lib.cranfield.ac.uk/handle/1826/13904.
[22] 王日爽. 泛函分析与最优化理论[M]. 北京:北京航空航天大学出版社, 2003:98-105. WANG R S. Functional analysis and optimization theory[M]. Beijing:Beihang University Press, 2003:98-105(in Chinese).

Options

Outlines

模态框（Modal）标题

Abstract

Cite this article

References