Load relief control of launch vehicle using aerodynamic angle estimation

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A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.
Publisher
SAGE PUBLICATIONS LTD
Issue Date
2018-06
Language
English
Article Type
Article
Citation

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.232, no.8, pp.1598 - 1605

ISSN
0954-4100
DOI
10.1177/0954410017699435
URI
http://hdl.handle.net/10203/242455
Appears in Collection
AE-Journal Papers(저널논문)
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