Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method

doi:10.21629/JSEE.2018.06.13

Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (6): 1263-1270.doi: 10.21629/JSEE.2018.06.13

• Control Theory and Application • Previous Articles Next Articles

Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method

Bin FU^1,*(), Hang GUO¹(), Kang CHEN¹(), Wenxing FU¹(), Xingyu WU²(), Jie YAN¹()

¹ School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
² Xi'an Microelectronic Technology Institute, Xi'an 710065, China

Received:2018-08-18 Online:2018-12-25 Published:2018-12-26
Contact: Bin FU E-mail:binfu@mail.nwpu.edu.cn;jsguoh@mail.nwpu.edu.cn;mars_legend@163.com;wenxingfu@nwpu.edu.cn;wxy910112@163.com;yanjie@nwpu.edu.cn
About author:FU Bin was born in 1989. He received his B.S. degree in 2011 from Northwestern Polytechnical University, and M.S. degree from School of Astronautics, Northwestern Polytechnical University in 2014. He is a Ph.D. candidate at the School of Astronautics, Northwestern Polytechnical University. He has presented papers in national and international journals and conferences. His research interests are guidance, navigation and control. E-mail: binfu@mail.nwpu.edu.cn|GUO Hang was born in 1990. He received his B.S. degree in 2011 from Northwestern Polytechnical University, and M.S. degree from School of Astronautics, Northwestern Polytechnical University in 2014. He is a Ph.D. candidate at the School of Astronautics, Northwestern Polytechnical University. He has presented papers in national and international journals and conferences. His research interests are guidance, navigation and control. E-mail: jsguoh@mail.nwpu.edu.cn|CHEN Kang was born in 1980. He received his Ph.D. degree from School of Astronautics, Northwestern Polytechnical University in 2010. As an associate professor, he is working in School of Astronautics, Northwestern Polytechnical University. His research interests are flight control, guidance and aircraft design. E-mail: mars_legend@163.com|FU Wenxing was born in 1974. He received his Ph.D. degree from School of Astronautics, Northwestern Polytechnical University in 2006. As a professor, he is working in the School of Astronautics, Northwestern Polytechnical University. His research interests are system simulation and aircraft design. E-mail: wenxingfu@nwpu.edu.cn|WU Xingyu was born in 1991. She received her M.S. degree from School of Astronautics, Northwestern Polytechnical University in 2017. As an engineer, she is working in Xi'an Microelectronics Technology Institute. Her research interests are system simulation and aircraft design. E-mail: wxy910112@163.com|YAN Jie was born in 1960. He received his Ph.D. degree from School of Astronautics, Northwestern Polytechnical University in 1988. He is currently working as a professor and Ph.D. candidate supervisor in School of Astronautics, Northwestern Polytechnical University. His research interests are flight control, guidance, system simulation and aircraft design. E-mail: yanjie@nwpu.edu.cn
Supported by:
the National Natural Science Foundation of China(61503302);the joint fund of the National Natural Science Foundation Committee and China Academy of Engineering Physics(U1630127);This work was supported by the National Natural Science Foundation of China (61503302) and the joint fund of the National Natural Science Foundation Committee and China Academy of Engineering Physics (U1630127)

Abstract

Abstract:

This paper proposes a multiple-constraints-guaranteed midcourse guidance law for the interception of the hypersonic targets. In traditional midcourse law design, the constraints of the aero-thermal heating are rarely taken into consideration. The performance of the infrared detection system may be degraded and the instability of the flight control system may be induced. To address this problem, a state-constrained model predictive static programming method is introduced such that both terminal constraints (position and angle) and optimal energy consumption can be ensured. As a result, a sub-optimal midcourse guidance, guaranteeing the aforementioned multiple-constraints to be never violated, is synthesized. Simulation results demonstrate the effectiveness of the proposed method.

Key words: midcourse guidance, model predictive control, optimal control, state constraint

Bin FU, Hang GUO, Kang CHEN, Wenxing FU, Xingyu WU, Jie YAN. Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method[J]. Journal of Systems Engineering and Electronics, 2018, 29(6): 1263-1270.

Figures/Tables 9

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References 25

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Parameter	Value
Initial position/km	(0, 0, 12)
Target position/km	(30, 10, 15)
Initial angle/(°)	${\gamma _{\rm{0}}}{\rm{ = 10, }}{\psi _{\rm{0}}}{\rm{ = 0}}$
Desired angle/(°)	${\gamma _d}{\rm{ = 0, }}{\psi _{\rm{0}}}{\rm{ = 10}}$
Initial velocity/(m/s)	${V_0} = 1200$
Missile mass/kg	$mM = 160$
Drag force coef?cient	$CD = 0.4$
Reference area/m²	${S_{ref}} = 0.0324$
Step length/m	$h = 10$
Position limit/m	${\varepsilon _1} = 10$
Angle limit/(°)	${\varepsilon _2} = 0.5$
Heating rate limit	$3.6{\rm{ \times 1}}{{\rm{0}}^{\rm{9}}}$
Navigation ratio	${k_{\gamma 1}} = 3, {k_\gamma }_2 = 1.5, {k_{\psi 1}} = 3, {k_\psi }_2 = 1.5$

Method	Number of iteration	Total time cost/s
SC-MPSP	4	0.255
RPM	8 241	10.251
NTSM	1	0.023

Method	Max heating rate	Final heating rate
SC-MPSP	3.54×10⁹	1.54×10⁹
RPM	3.53×10⁹	2.24×10⁹
NTSM	3.72×10⁹	1.83×10⁹

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Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method

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