Optimal feedback based control for Mars entry trajectory tracking

doi:10.21629/JSEE.2018.01.13

Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (1): 134-141.doi: 10.21629/JSEE.2018.01.13

• Control Theory and Application • Previous Articles Next Articles

Optimal feedback based control for Mars entry trajectory tracking

Yuechen HUANG¹(), Haiyang LI^1,*(), Hongxin SHEN²()

¹ College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
² State Key Laboratory of Astronautic Dynamics, Xi'an Satellite Control Center, Xi'an 710043, China

Received:2016-06-26 Online:2018-02-26 Published:2018-02-23
Contact: Haiyang LI E-mail:yuechen_huang@nudt.edu.cn;lihaiyang@nudt.edu.cn;shxnudt@163.com
About author:HUANG Yuechen was born in 1989. He received his M.S. degree from National University of Defense Technology in 2014. He is currently a Ph.D. degree candidate in National University of Defense Technology. His research interests are spacecraft trajectory planning and control, dispersion analysis and robust optimization. E-mail: yuechen_huang@nudt.edu.cn|LI Haiyang was born in 1972. He received his Ph.D. degree in mechanics from National University of Defense Technology in 2000. He is now a professor and doctoral supervisor in National University of Defense Technology. His research interests include dynamic system modeling and simulation, spacecraft trajectory design and optimization. E-mail: lihaiyang@nudt.edu.cn|SHEN Hongxin was born in 1986. He received his Ph.D. degree in aeronautical and astronautical science and technology from National University of Defense Technology in 2014. He is now an engineer in State Key Laboratory of Astronautic Dynamics. His research interests include spacecraft trajectory design and optimization, and nonlinear control. E-mail: shxnudt@163.com
Supported by:
the National Natural Science Foundation of China(11372345);This work was supported by the National Natural Science Foundation of China (11372345)

Abstract

Abstract:

The various uncertainties of Mars environment have great impact on the process of vehicles entering the atmosphere. To improve the robustness of control system against the model errors and to reduce the computational burden, an optimal feedback based tracking control law is developed. The control scheme presented in this paper determines the amplitude and the reversals of bank angle respectively in the longitudinal and lateral flight plane. At each control cycle, the amplitude of the bank angle is obtained by an optimal feedback controller to minimize tracking errors. The control gains are tuned according to the closed-loop error dynamics by using optimization methods. The bank reversals are executed if the crossrange exceeds a predetermined corridor which is designed by setting a boundary function. The accuracy and robustness of the proposed closed-loop optimal feedback based control law in tracking the reference trajectory is verified via 500 deviation simulations, in which modeling errors and external disturbances are considered.

Key words: optimal control, feedback gains, Mars entry, trajectory tracking, Pontryagin's minimum principle

Yuechen HUANG, Haiyang LI, Hongxin SHEN. Optimal feedback based control for Mars entry trajectory tracking[J]. Journal of Systems Engineering and Electronics, 2018, 29(1): 134-141.

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References 21

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Parameter	Value
S_ref/m²	15.9
m/kg	2 804
C_L	0.387 6
C_D	1.415

State variable	Value
h₀/km	124.56
θ₀/(°)	-90.072
φ₀/(°)	-43.898
V₀/(m/s)	5 505
γ₀/(°)	-13.12
ψ₀/(°)	84.193 1

State variable	Value
h_f/km	8.85
θ_f/(°)	-70.66
φ_f/(°)	-41.45

Parameter	Value
h/m	1 000
θ/(°)	0.02
φ/(°)	0.02
V/(m/s)	5
γ/(°)	0.1
ψ/(°)	0.5
C_L/%	15
C_D/%	15
ρ/(°)	30

Statistics	OFB	FBL	NPC
Mean range to target/km	0.465	7.377	2.443
Three-sigma range to target/km	6.125	21.546	6.462

Optimal feedback based control for Mars entry trajectory tracking

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