Integrated guidance and control design method based on finite-time state observer

doi:10.21629/JSEE.2018.06.12

Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (6): 1251-1262.doi: 10.21629/JSEE.2018.06.12

• Control Theory and Application • Previous Articles Next Articles

Integrated guidance and control design method based on finite-time state observer

Ping MA(), Denghui ZHANG(), Songyan WANG(), Tao CHAO*()

Control and Simulation Center, Harbin Institute of Technology, Harbin 150080, China

Received:2017-09-26 Online:2018-12-25 Published:2018-12-26
Contact: Tao CHAO E-mail:pingma@hit.edu.cn;zdh_hit_2016@163.com;sywang@hit.edu.cn;chaotao2000@163.com
About author:MA Ping was born in 1970. She received her Ph.D. degree in control science and engineering from Harbin Institute of Technology in 2003. She is currently a professor in the Control and Simulation Center at Harbin Institute of Technology. Her research interests are the design and implement ation of distributed simulation system and verification validation and accreditation of complex simulation system. E-mail: pingma@hit.edu.cn|ZHANG Denghui was born in 1992. He received his M.S. degree in automation from Harbin Institute of Technology in 2016. He is now a Ph.D. degree candidate in the Control and Simulation Center at Harbin Institute of Technology. His research interests are navigation, guidance and control. E-mail: zdh_hit_2016@163.com|WANG Songyan was born in 1976. She received her Ph.D. degree in navigation, guidance and control from Harbin Institute of Technology in 2007. She is currently an associate professor in the Control and Simulation Center at Harbin Institute of Technology. Her research interests include navigation, guidance and control and performance evaluation. E-mail: sywang@hit.edu.cn|CHAO Tao was born in 1983. He received his Ph.D. degree in navigation, guidance and control from Harbin Institute of Technology in 2011. He is currently an associate professor in the Control and Simulation Center at Harbin Institute of Technology. His research interests include navigation, guidance and control and performance evaluation. E-mail: chaotao2000@163.com
Supported by:
the National Natural Science Foundation of China(61627810);the National Natural Science Foundation of China(61790562);the National Natural Science Foundation of China(61403096);This work was supported by the National Natural Science Foundation of China (61627810; 61790562; 61403096)

Abstract

Abstract:

A composited integrated guidance and control (IGC) algorithm is presented to tackle the problem of the IGC design in the dive phase for the bank-to-turn (BTT) vehicle with the inaccuracy information of the line-of-sight (LOS) rate. For the sake of theoretical derivation, an IGC model in the pitch plane is established. The high-order finite-time state observer (FTSO), with the LOS angle as the single input, is employed to reconstruct the states of the system online. Besides, a composited IGC algorithm is presented via the fusion of back-stepping and dynamic inverse. Compared with the traditional IGC algorithm, the proposed composited IGC method can attenuate effectively the design conservation of the flight control system, while the LOS rate is mixed with noise. Extensive experiments have been performed to demonstrate that the proposed approach is globally finite-time stable and strongly robust against parameter uncertainty.

Key words: integrated guidance and control (IGC), finite-time state observer (FTSO), back-to-turn (BTT) vehicle, composited control

Ping MA, Denghui ZHANG, Songyan WANG, Tao CHAO. Integrated guidance and control design method based on finite-time state observer[J]. Journal of Systems Engineering and Electronics, 2018, 29(6): 1251-1262.

Figures/Tables 13

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References 34

1	ZHANG Y, GUO J, TANG S J, et al. Integrated missile guidance and control three-channel decoupling design method. Acta Aeronautica et Astronautica Sinica, 2014, 35 (12): 3438- 3450.
2	ZHA X, CUI P Y, CHANG B J. An integrated approach to guidance and control for aircraft applying to attack the ground fixed targets. Journal of Astronautics, 2005, 26 (1): 13- 18.
3	YIN Y X, YANG M, WANG Z C. Three dimensional guidance and control for missile. Electric Machines and Control, 2010, 14 (3): 83- 91.
4	ZHOU H, ZHAO H, HUANG H Q, et al. Integrated guidance and control design of the suicide UCAV for terminal attack. Journal of Systems Engineering and Electronics, 2017, 28 (3): 546- 555. doi: 10.21629/JSEE.2017.03.14
5	HE S M, SONG T, LIN D F. Impact angle constrained integrated guidance and control for maneuvering target interception. Journal of Guidance, Control, and Dynamics, 2017, 40 (10): 2652- 2660.
6	HE S M, WANG W, WANG J. Three-dimensional multivariable integrated guidance and control design for maneuvering targets interception. Journal of The Franklin Institute, 2016, 353 (16): 4330- 4350. doi: 10.1016/j.jfranklin.2016.08.008
7	TIAN B L, FAN W R, ZONG Q. Integrated guidance and control for reusable launch vehicle in reentry phase. Nonlinear Dynamic, 2015, 80 (1/2): 397- 412.
8	SUN X Y, CHAO T, WANG S Y, et al. Integrated guidance and control design method considering channel coupling. Journal of Astronautics, 2016, 37 (8): 936- 945.
9	XIN M, BALAKRISHNAN S N, OHLMEYER E J. Integrated guidance and control of missile with θ-D method. IEEE Trans. on Control Systems Technology, 2006, 14 (6): 981- 992. doi: 10.1109/TCST.2006.876903
10	MENON P K, OHLMEYER E J. Integrated design of agile missile guidance and autopilot system. Control Engineering Practice, 2001, 9 (10): 1095- 1106. doi: 10.1016/S0967-0661(01)00082-X
11	PANCHAL B, MATE N, TALOLE S E. Continuous-time predictive control-based integrated guidance and control. Journal of Guidance, Control, and Dynamics, 2017, 40 (7): 1579- 1595. doi: 10.2514/1.G002661
12	YAN H, TAN S P, HE Y Z. A small-gain method for integrated guidance and control in terminal phase of reentry. Acta Astronautica, 2017, 132, 282- 292. doi: 10.1016/j.actaastro.2016.12.027
13	VADDI S, MENON P K, OHLMEYER E J. Numerical statedependent Riccati equation approach for missile integrated guidance control. Journal of Guidance, Control, and Dynamics, 2009, 32 (2): 699- 703. doi: 10.2514/1.34291
14	DONG F Y, LEI H M, ZHOU C J, et al. Research of integrated robust high order sliding mode guidance and control for missile. Acta Aeronautica et Astronautica Sinica, 2013, 34 (9): 2212- 2218.
15	DONG F Y, LEI H M, LI J, et al. Design of integrated adaptive optimal sliding-mode guidance and control for interceptor. Journal of Astronautics, 2013, 34 (11): 1456- 1641.
16	SONG H T, ZHANG T. Fast robust integrated guidance and control design of interceptors. IEEE Trans. on Control Systems Technology, 2016, 24 (1): 349- 356. doi: 10.1109/TCST.2015.2431641
17	ZHANG C, WU Y J. Non-singular terminal dynamic surface control based integrated guidance and control design and simulation. ISA Transactions, 2016, 63, 112- 120. doi: 10.1016/j.isatra.2016.03.013
18	WANG J H, LIU L H, ZHAO T, et al. Integrated guidance and control for hypersonic vehicle in dive phase with multiple constraints. Aerospace Science and Technology, 2016, 53, 103- 115. doi: 10.1016/j.ast.2016.03.019
19	WANG X, WANG J. Partial integrated missile guidance and control with finite time convergence. Journal of Guidance, Control, and Dynamics, 2013, 36 (5): 1399- 1409. doi: 10.2514/1.58983
20	SUN X J, ZHOU R, HOU D L. Output-feedback based partial integrated missile guidance and control law design. Journal of Systems Engineering and Electronics, 2016, 27 (6): 1238- 1248. doi: 10.21629/JSEE.2016.06.12
21	SUN X Y, WANG S Y, SHENG S J, et al. Adding a power integrator technique based integrated guidance and control design. Control and Decision, 2018, 33 (2): 242- 248.
22	SHIMA T, IDAN M, ODED M G. Sliding-mode control for integrated missile autopilot guidance. Journal of Guidance, Control, and Dynamics, 2006, 29 (2): 250- 260. doi: 10.2514/1.14951
23	YAN H, JI H B. Integrated guidance and control for dualcontrol missile based on small gain theorem. Automatica, 2012, 48 (10): 2686- 2692. doi: 10.1016/j.automatica.2012.06.084
24	HOU M Z, DUAN G R. Adaptive dynamic surface control for integrated missile guidance and autopilot. International Journal of Automation and Computing, 2011, 8 (1): 122- 127. doi: 10.1007/s11633-010-0563-z
25	GURFIL P. Zero-miss-distance guidance law based on lineof-sight rate measurement only. Control Engineering Practice, 2003, 11 (7): 819- 832. doi: 10.1016/S0967-0661(02)00208-3
26	CHWA D, CHOI J Y. Adaptive nonlinear guidance law considering control loop dynamcis. IEEE Trans. on Aerospace and Electronic Systems, 2003, 39 (4): 1134- 1143. doi: 10.1109/TAES.2003.1261117
27	BHAT S P, BERNSTEIN D S. Finite-time stability of continuous autonomous systems. SIAM Journal on Control and Optimization, 2000, 38 (3): 751- 766. doi: 10.1137/S0363012997321358
28	DING S H, LI S H, ZHENG W X. Nonsmooth stabilization of a class of nonlinear cascaded systems. Automatica, 2012, 48 (10): 2597- 2606. doi: 10.1016/j.automatica.2012.06.060
29	DU H B, QIAN C J, YANG S Z, et al. Recursive design of finite-time convergent observers for a class of time-varying nonlinear system. Automatica, 2013, 49 (2): 601- 609. doi: 10.1016/j.automatica.2012.11.036
30	HUANG S, XIANG Z. Finite-time stabilization of switched stochastic nonlinear systems with mixed odd and even powers. Automatica, 2016, 73, 130- 137. doi: 10.1016/j.automatica.2016.06.023
31	SUN S. Guidance laws with finite time convergence for homing missiles. Harbin, China: Harbin Institute of Technology, 2010. (in Chinese)
32	BHAT S P, BERNSTEIN D S. Continuous finite-time stabilization of the translational and rotational double integrators. IEEE Trans. on Automatic Control, 1998, 43 (5): 678- 682. doi: 10.1109/9.668834
33	QIAN C, LIN W. A continuous feedback approach to global strong stabilization of nonlinear systems. IEEE Trans. on Automatic Control, 2001, 46 (7): 1061- 1079. doi: 10.1109/9.935058
34	BACCIOTTI A, ROSIER L. Liapunov functions and stability in control theory. Automatica, 2005, 41 (12): 2183- 2184. doi: 10.1016/j.automatica.2005.08.002

State variable	Value
Simulation step/s	0.001
Position of vehicle/m	[0, 16 000]
Velocity of vehicle/(m/s)	1 800
Position of target/m	[0, 32 000]
Velocity of target/(m/s)	0

Constraint index	Range
Terminal precision/m	(0, 10]
Amplitude of Angle of attack/(°)	[0, 12.5]
Amplitude of de?ection/(°)	[–30, 30]
Rate of de?ection/(°/s)	[–50, 50]

[1]	Hang GUO, Zheng WANG, Bin FU, Kang CHEN, Wenxing FU, Jie YAN. Impact angle constrained fuzzy adaptive fault tolerant IGC method for Ski-to-Turn missiles with unsteady aerodynamics and multiple disturbances [J]. Journal of Systems Engineering and Electronics, 2022, 33(5): 1210-1226.
[2]	Huan Zhou, Hui Zhao, Hanqiao Huang, and Xin Zhao. Integrated guidance and control design of the suicide UCAV for terminal attack [J]. Systems Engineering and Electronics, 2017, 28(3): 546-555.

Integrated guidance and control design method based on finite-time state observer

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Index	Inclination/(°)	Velocity/(m/s)
1	0	25
2	0	50
3	45	25
4	45	50
5	135	25
6	135	50
7	180	25
8	180	50