Coupled dynamic model of state estimation for hypersonic glide vehicle

doi:10.21629/JSEE.2018.06.15

Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (6): 1284-1292.doi: 10.21629/JSEE.2018.06.15

• Control Theory and Application • Previous Articles Next Articles

Coupled dynamic model of state estimation for hypersonic glide vehicle

Kai ZHANG¹(), Jiajun XIONG^2,*(), Tingting FU²()

¹ Department of Graduation, Air Force Early Warning Academy, Wuhan 430019, China
² Early Warning Intelligence Department, Air Force Early Warning Academy, Wuhan 430019, China

Received:2017-09-27 Online:2018-12-25 Published:2018-12-26
Contact: Jiajun XIONG E-mail:christophzhang@163.com;jiajunxiong@yahoo.com;124611796@qq.com
About author:ZHANG Kai was born in 1990. He received his B.S. degree from School of Aerospace Science and Engineering, National University of Defense Technology in 2014. He is currently working toward his Ph.D. degree in the Air Force Early Warning Academy. So far he has published more than ten papers, in which three papers are indexed by EI. His research interests include information fusion and hypersonic vehicle tracking. E-mail: christophzhang@163.com|XIONG Jiajun was born in 1961. He received his Ph.D. degree from School of Computer, Huazhong University of Science and Technology in 2004. He now is a professor in Air Force Early Warning Academy. So far he has published more than 100 papers, in which more than ten papers are indexed by EI or SCI. His research interests are early-warning intelligence analysis, and information fusion. E-mail: jiajunxiong@yahoo.com|FU Tingting was born in 1988. She received her B.S. degree from School of Optoelectronic Science and Engineering, National University of Defense Technology in 2014. She now is a lecturer in Air Force Early Warning Academy. Her research interests include information fusion and systems engineering. E-mail: 124611796@qq.com
Supported by:
the National High-tech R & D Program of China (863 Program)(2015AA7326042);the National High-tech R & D Program of China (863 Program)(2015AA8321471);This work was supported by the National High-tech R & D Program of China (863 Program) (2015AA7326042; 2015AA8321471)

Abstract

Abstract:

Aiming at handling complicated maneuvers or other unpredicted emergencies for hypersonic glide vehicle tracking, three coupled dynamic models of state estimation based on the priori information between guidance variables and aerodynamics are presented. Firstly, the aerodynamic acceleration acting on the target is analyzed to reveal the essence of the target's motion. Then three coupled structures for modeling aerodynamic parameters are developed by different ideas: the spiral model with a harmonic oscillator, the bank model with trigonometric functions of the bank angle and the guide model with the changing rule of guidance variables. Meanwhile, the comparison discussion is concluded to show the novelty and advantage of these models. Finally, a performance assessment in different simulation cases is presented and detailed analysis is revealed. The results show that the proposed models perform excellent properties. Moreover, the guide model produces the best tracking performance and the bank model shows the second; however, the spiral model does not outperform the maneuvering reentry vehicle (MaRV) model markedly.

Key words: hypersonic glide vehicle, state estimation, dynamic model, aerodynamic parameter, guidance variable

Kai ZHANG, Jiajun XIONG, Tingting FU. Coupled dynamic model of state estimation for hypersonic glide vehicle[J]. Journal of Systems Engineering and Electronics, 2018, 29(6): 1284-1292.

Figures/Tables 8

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References 32

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Model	State variable $X$
MM	${[x, y, z, {u_{xT}}, {u_y}, {u_z}, {a_u}, {a_t}, {a_c}]^{\rm{T}}} $
SM	${[x, y, z, {u_{xT}}, {u_y}, {u_z}, {a_u}, {a_t}, {a_c}\varpi ]^{\rm{T}}}$
BM	${[x, y, z, {u_{xT}}, {u_y}, {u_z}, {a_u}, {a_l}, k]^{\rm{T}}}$
NTSM	${[x, y, z, {u_{xT}}, {u_y}, {u_z}, {a_u}, {a_t}, {a_c}]^{\rm{T}}}$

Case	Estimator	Measurement parameter
Case	Estimator	Noise variance	Sampling period
1	UKF	R	T
3	EKF	2R	T
4	EKF	R	2T

Type	Example	Case 1	Case 2	Case 3	Case 4
Position/m	MM	107.8	102.7	192.0	167.6
	SM	105.7	101.5	187.4	160.3
	BM	97.00	92.54	171.3	142.6
	GM	78.11	74.05	151.3	132.6
Velocity/(m/s)	MM	23.94	22.85	37.12	33.59
	SM	23.00	21.47	32.65	32.89
	BM	19.34	18.71	26.80	26.48
	GM	18.64	17.34	26.83	23.48
$ {a_\upsilon }/({10^{ - 6}})$	MM	7.069	6.904	9.132	18.04
	SM	6.770	6.548	8.585	17.49
	BM	1.861	1.811	2.047	12.56
	GM	2.861	2.659	4.097	15.82
$ {a_\upsilon }/({10^{ - 6}})$	MM	80.85	76.20	86.51	100.7
	SM	77.95	75.25	83.78	97.70
	BM	71.22	69.94	76.37	89.97
	GM	67.76	65.13	70.38	85.87
$ {a_\upsilon }/({10^{ - 6}})$	MM	19.86	17.07	21.82	23.25
	SM	20.06	19.05	22.18	23.32
	BM	17.50	17.80	18.35	19.41
	GM	14.20	15.56	16.97	17.50

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Coupled dynamic model of state estimation for hypersonic glide vehicle

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