Impact angle constrained fuzzy adaptive fault tolerant IGC method for Ski-to-Turn missiles with unsteady aerodynamics and multiple disturbances

doi:10.23919/JSEE.2022.000116

Journal of Systems Engineering and Electronics ›› 2022, Vol. 33 ›› Issue (5): 1210-1226.doi: 10.23919/JSEE.2022.000116

收稿日期:2021-10-27 接受日期:2022-07-12 出版日期:2022-10-27 发布日期:2022-10-27

Impact angle constrained fuzzy adaptive fault tolerant IGC method for Ski-to-Turn missiles with unsteady aerodynamics and multiple disturbances

Hang GUO^1,*(), Zheng WANG¹(), Bin FU²(), Kang CHEN²(), Wenxing FU²(), Jie YAN¹()

¹ Research Center for Unmanned System Strategy Development, Northwestern Polytechnical University, Xi’an 710072, China
² Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an 710072, China

Received:2021-10-27 Accepted:2022-07-12 Online:2022-10-27 Published:2022-10-27
Contact: Hang GUO E-mail:jsguoh@nwpu.edu.cn;wz_nwpu@126.com;binfu@nwpu.edu.cn;mars_legend@163.com;wenxingfu@nwpu.edu.cn;jyan@nwpu.edu.cn
About author:|GUO Hang was born in 1990. He received his B.S., M.S., and Ph.D. degrees in navigation, guidance, and control from Northwestern Polytechnical University, in 2011, 2014, and 2019 respectively. He is currently an associate research fellow in Northwestern Polytechnical University. His research interests are hypersonic vehicle flight dynamics, guidance, and control. E-mail: jsguoh@nwpu.edu.cn||WANG Zheng was born in 1992. He received his B.S., M.S., and Ph.D. degrees in navigation, guidance, and control from Northwestern Polytechnical University in 2013, 2016, and 2020 respectively. He is currently an associate research fellow in Northwestern Polytechnical University. His research focus on vehicle flight control theory. E-mail: wz_nwpu@126.com||FU Bin was born in 1989. He received his B.S., M.S., and Ph.D. degrees in navigation, guidance, and control from Northwestern Polytechnical University in 2011, 2014, and 2019 respectively. He is currently an associate research fellow in Northwestern Polytechnical University. His research interests are interception for high maneuver targets and intelligent air combat. E-mail: binfu@nwpu.edu.cn||CHEN Kang was born in 1980. He received his B.S., M.S., and Ph.D. degrees in navigation, guidance, and control from Northwestern Polytechnical University in 2001, 2004, and 2009 respectively. He is currently an associate professor in Northwestern Polytechnical University. His research focuses on interception for high maneuver targets. E-mail: mars_legend@163.com||FU Wenxing was born in 1974. He received his Ph.D. degree in navigation, guidance, and control from Northwestern Polytechnical University in 2006. He is currently an professor in Northwestern Polytechnical University. His research interests are system simulation and intelligent unmanned aircraft design. E-mail: wenxingfu@nwpu.edu.cn||YAN Jie was born in 1960. He received his Ph.D. degree in navigation, guidance, and control from Northwestern Polytechnical University in 1988. He is currently an professor in Northwestern Polytechnical University. His research interests are flight guidance and control, and modern combat concept. E-mail: jyan@nwpu.edu.cn
Supported by:
This work was supported by the National Natural Science Foundation of China (62003264)

摘要/Abstract

Abstract:

An impact angle constrained fuzzy adaptive fault tolerant integrated guidance and control method for Ski-to-Turn (STT) missiles subject to unsteady aerodynamics and multiple disturbances is proposed. Unsteady aerodynamics appears when flight vehicles are in a transonic state or confronted with unstable airflow. Meanwhile, actuator failures and multisource model uncertainties are introduced. However, the boundaries of these multisource uncertainties are assumed unknown. The target is assumed to execute high maneuver movement which is unknown to the missile. Furthermore, impact angle constraint puts forward higher requirements for the interception accuracy of the integrated guidance and control (IGC) method. The impact angle constraint and the precise interception are established as the object of the IGC method. Then, the boundaries of the lumped disturbances are estimated, and several fuzzy logic systems are introduced to compensate the unknown nonlinearities and uncertainties. Next, a series of adaptive laws are developed so that the undesirable effects arising from unsteady aerodynamics, actuator failures and unknown uncertainties could be suppressed. Consequently, an impact angle constrained fuzzy adaptive fault tolerant IGC method with three loops is constructed and a perfect hit-to-kill interception with specified impact angle can be implemented. Eventually, the numerical simulations are conducted to verify the effectiveness and superiority of the proposed method.

Key words: integrated guidance and control (IGC), impact angle constraint, unsteady aerodynamics, fault tolerant control (FTC), actuator failures

. [J]. Journal of Systems Engineering and Electronics, 2022, 33(5): 1210-1226.

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.

图/表 15

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Initial condition parameter	Value
Initial position of the missile $\left( {{x_M},{y_M}} \right)$ /m	(0.0, 3 000.0)
Initial flight path angle of the missile ${\theta _M}$ /rad	0.0
Initial velocity of the missile ${V_M}$ /(m·s^?1)	300.0
Initial pitch angular velocity of the missile ${\omega _z}$ /(rad·s^?1)	0.0
Initial pitch angle of the missile ${\vartheta _M}$ /rad	0.0
Initial position of the target $\left( {{x_T},{y_T}} \right)$ /m	(8 000.0, 6 000.0)
Initial flight path angle of the target ${\theta _T}$ /rad	0.0
Initial velocity of the target ${V_T}$ /(m·s^?1)	100.0

Parameter of aerodynamics coefficients of the missile	Value
$ {C_{D0}},{C_{L0}},C_L^M\left( \alpha \right) $	0.197 7, 0.001 8, ?0.001 8
$C_D^{ {\alpha ^2} },\;C_D^{\alpha _A^2}$ /deg^?2	5.383 8e?4, 5.383 8e?5
$C_L^\alpha ,\;C_L^{ {\alpha _A} }$ /deg^?1	0.271 3, 0.135 7
${m_{z0} },\;m_z^M\left( \alpha \right)$	0.000 8, ?0.000 2
$m_z^\alpha ,\;m_z^{ {\alpha _A} },\;m_z^{ {\delta _z} }$ /deg^?1	?0.040 8, ?0.068 5, ?0.020 4

Missile structural parameter	Value
Mass of the missile m/kg	59.3
Reference area of the missile S/m²	0.02
Reference length of the missile $\bar L$ /m	2.12
Moment of inertia of the missile ${J_z}$ /(kg·m²)	13.94

Parameter	Case 1	Case 2	Case 3
${\lambda ^*}$ /deg	60.0	65.0	50.0
${\alpha _A}$ /deg	0.5	0.5	0.8
${\omega _A}$ /(rad·s^?1)	31.415 9	62.831 9	31.415 9
$ \chi \left( t \right) $	0.7	0.65	0.7

Parameter	Value	Parameter	initial value
k	40.0	s₀	0.0
${c_0},\;{c_1},\;{c_2},\;{c_3}$	1.0, 3.0, 10.0, 30.0	$ {\hat D_{aT}} $	0.5
${\tau _{y2} },\;{\tau _{y3} }$	0.01, 0.01	$ {\hat \tau _{g1}} $	1.0
${p_{ {D_{aT} } } },\;{p_{ {\tau _{g1} } } },\;{p_{ {q_{g1} } } },\;{p_{\mu 1} }$	0.01, 0.01, 0.01, 0.01	$ {\hat q_{g1}} $	1.0
$ {\sigma _{{D_{aT}}}},{\sigma _{{\tau _{g1}}}},{\sigma _{{q_{g1}}}},{\sigma _{\mu 1}} $	10.0, 10.0, 10.0, 20.0	$ {\hat \mu _1} $	0.5
${\varepsilon _{ {D_{aT} } } },\;{\varepsilon _{ {\tau _{g1} } } },\;{\varepsilon _{\mu 1} }$	100.0, 200.0, 20.0	$ {\hat D_{\alpha 2}} $	0.5
${p_{ {D_{\alpha 2} } } },\;{p_{ {\tau _{g2} } } },\;{p_{ {q_{g2} } } },\;{p_{\mu 2} }$	0.01, 0.001, 1e?10, 0.01	$ {\hat \tau _{g2}} $	1.0
${\sigma _{ {D_{\alpha 2} } } },\;{\sigma _{ {\tau _{g2} } } },\;{\sigma _{ {q_{g2} } } },\;{\sigma _{\mu 2} }$	10.0, 50.0, 10.0, 20.0	$ {\hat q_{g2}} $	1e?4
${\varepsilon _{ {D_{\alpha 2} } } },\;{\varepsilon _{ {\tau _{g2} } } },\;{\varepsilon _{\mu 2} }$	100.0, 200.0, 100.0	$ {\hat \mu _2} $	0.5
${p_{ {D_{\alpha 3} } } },\;{p_{ {\tau _{g3} } } },\;{p_{\mu 3} }$	0.005, 1e?4, 0.01	$ {\hat D_{\alpha 3}} $	0.5
${\sigma _{ {D_{\alpha 3} } } },\;{\sigma _{ {\tau _{g3} } } },\;{\sigma _{\mu 3} }$	20.0, 10.0, 20.0	$ {\hat \tau _{g3}} $	1.0
${\varepsilon _{ {D_{\alpha 3} } } },\;{\varepsilon _{ {\tau _{g3} } } },\;{\varepsilon _{\mu 3} }$	100.0, 200.0, 100.0	$ {\hat \mu _3} $	0.5

Impact angle constrained fuzzy adaptive fault tolerant IGC method for Ski-to-Turn missiles with unsteady aerodynamics and multiple disturbances

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