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Novel guidance model and its application for optimal re-entry guidance

Published online by Cambridge University Press:  02 October 2018

C.W. Jiang ,
G.F. Zhou ,
B. Yang ,
C.S. Gao  and
W.X. Jing
C.W. Jiang*
Affiliation:
China Academy of Launch Vehicle TechnologyBeijing China
G.F. Zhou
Affiliation:
China Academy of Launch Vehicle TechnologyBeijing China
B. Yang
Affiliation:
School of Astronautics Harbin Institute of TechnologyHarbin China
C.S. Gao
Affiliation:
School of Astronautics Harbin Institute of TechnologyHarbin China
W.X. Jing
Affiliation:
School of Astronautics Harbin Institute of TechnologyHarbin China
*
*cwjiang2010@163.com
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Abstract

Aiming at three-dimensional (3D) terminal guidance problem, a novel guidance model is established in this paper, in which line-of-sight (LOS) range is treated as an independent variable, describing the relative motion between the vehicle and the target. The guidance model includes two differential equations that describe LOS’s pitch and yaw motions in which the pitch motion is separately decoupled. This model avoids the inaccuracy of simplified two-dimensional (2D) guidance model and the complexity of 3D coupled guidance model, which not only maintains the accuracy but also simplifies the guidance law design. The application of this guidance model is studied for optimal re-entry guidance law with impact angle constraint, which is presented in the form of normal overload. Compared with optimal guidance laws based on traditional guidance model, the proposed one based on novel guidance model is implemented with the LOS range instead of time-to-go, which avoids the problem of the time-to-go estimation of traditional optimal guidance laws. Finally, the correctness and validity of the guidance model and guidance law are verified by numerical simulation. The guidance model and guidance law proposed in this paper provide a new way for the design of terminal guidance.

Keywords

Terminal guidanceGuidance modelLOS rangeOptimal guidance lawImpact angle constraint
Type
Survey Papers
Information
The Aeronautical Journal , Volume 122 , Issue 1257 , November 2018 , pp. 1811 - 1825
Copyright
© Royal Aeronautical Society 2018 

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