Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints

doi:10.21629/JSEE.2018.01.14

Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (1): 142-151.doi: 10.21629/JSEE.2018.01.14

• Control Theory and Application • Previous Articles Next Articles

Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints

Ran LI^1,²(), Qiuqiu WEN^1,*(), Wangchun TAN¹(), Yijie ZHANG³()

¹ School of Aerospace Engineering, Beijing Institute of technology, Beijing 100081, China
² China North Industries Group Corporation, Beijing 100081, China
³ Beijing Institute of Aerospace Automatic Control, Beijing 100081, China

Received:2016-11-21 Online:2018-02-26 Published:2018-02-23
Contact: Qiuqiu WEN E-mail:liran@acftu.org.cn;wenqiuqiu82@gmail.com;evan_here@163.com;07nys@163.com
About author:LI Ran was born in 1982. He received his master's degree in 2007 from Beijing Institute of Technology. Now he is a senior engineer in China North Industry Group Corporation. His research interests are missile guidance and control. E-mail: liran@acftu.org.cn|WEN Qiuqiu was born in 1982. He received his Ph.D. degree in 2010. Now he is a postdoctoral fellowship in Beijing Institute of Technology. His research interests are missile guidance and control and optimal control technology. E-mail: wenqiuqiu82@gmail.com|TAN Wangchun was born in 1993. He is a postgraduate in Beijing Institute of Technology. His research interests are missile control and guidance technology. E-mail: evan_here@163.com|ZHANG Yijie was born in 1980. She received her master's degree in 2005. Now she is a senior research engineer in Beijing Institute of Aerospace Automatic Control. Her research interests are missile guidance and control. E-mail: 07nys@163.com
Supported by:
the Aeronautical Science Foundation of China(20150172001);This work was supported by the Aeronautical Science Foundation of China (20150172001)

Abstract

Abstract:

In this paper, a new adaptive optimal guidance law with impact angle and seeker's field-of-view (FOV) angle constraints is proposed. To this end, the generalized optimal guidance law is derived first. A changeable impact angle weighting (IAW) coefficient is introduced and used to modify the guidance law to make it adaptive for all guidance constraints. After integrating the closed-form solution of the guidance command with linearized engagement kinematics, the analytic predictive models of impact angle and FOV angle are built, and the available range of IAW corresponding to constraints is certain. Next, a calculation scheme is presented to acquire the real-time value of IAW during the entire guidance process. When applying the proposed guidance law, the IAW will keep small to avoid a trajectory climbing up to limit FOV angle at an initial time but will increase with the closing target to improve impact position and angle accuracy, thereby ensuring that the guidance law can juggle orders of guidance accuracy and constraints control.

Key words: optimal guidance law, impact angle constraint, fieldof-view (FOV) angle constraint, weighting coefficient

Ran LI, Qiuqiu WEN, Wangchun TAN, Yijie ZHANG. Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints[J]. Journal of Systems Engineering and Electronics, 2018, 29(1): 142-151.

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Description	Parameter	Value
Missile initial conditions	H₀/km	2
	V₀/(m/s)	234
	θ₀/(°)	0
Target initial conditions	x_t0/m	0
	y_t0/m	0
	V_t0/(m/s)	0
Seeker detection range	R_s0/km	6
Time constants of the pitch autopilot	T_ay/s	0.3
Time constants of the seeker	T_s0/s	0.1

Description	Notation	Value
Impact position miss-distance	ΔR/m	< 0.5
Standard impact angle	q_Fc/(°)	-85
Minimum impact angle	q_Fc_min/(°)	-60
Seeker maximum FOV angle	ϕ_c_max/(°)	30

Description	Notation	Value
Rate of LOS angle error	σ_dq/(°/s)	0.1
LOS angle error	σ_q/(°)	2
Time-to-go estimation error	σ_tgo/s	1

Guidance law		Miss-distance/m	q_F/(°)	ϕ_max/(°)
GL/AIAW	Mean	0.34	-85.6	26.1
GL/AIAW	Standard deviation	0.01	3.1	1.33
OGL/IAC	Mean	0.27	-83.4	33.5
OGL/IAC	Standard deviation	0.01	3.2	2.47

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Adaptive weighting impact angle optimal guidance law considering seeker's FOV angle constraints

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