NDLI: Autopilot design for missile with morphing wings

Content Provider	IEEE Xplore Digital Library
Author	Duan Chao-yang Guo Jian-guo Zhou Jun
Copyright Year	2010
Description	Author affiliation: School of Automation Science & Electrical Engineering, Beijing University of Aeronautics and Astronautics, China (Duan Chao-yang) \|\| Institute of Precision Guidance and Control, Northwestern Polytechnical University Xi'an, China (Guo Jian-guo; Zhou Jun)
Abstract	Morphing concepts for missiles have been a topic of current research interest in aerospace engineering. For the morphing wings technology of missile, a kind of autopilot design method is proposed by H∞ control theory. In order to have the better flight performance in the different regimes, the missile can automatically change the wings area symmetrically. The nonlinear dynamic model is established, applying the approach of the multi-rigid body dynamics model, a whole body is viewed as composed of fixed body section and morphing section. By introducing the acceleration and the dynamic characteristic of control surface in the tail of missile, the nonlinear autopilot control system is derived. A linear autopilot controller is designed by solving the Riccati inequation. Finally an illustrative example is given to show that proposed autopilot control law is robust and suitable to the missile with morphing wings in the case of the different aerodynamic parameter, and the acceleration of missile can be tracked the command acceleration.
File Size	399706
File Format	PDF
ISBN	9781424465392
ISSN	21547491
e-ISBN	9781424465422
DOI	10.1109/ICACTE.2010.5579191
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2010-08-20
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Missiles Tracking Atmospheric modeling Stability analysis autopolit nonlinear dynamic stability morphing wings
Content Type	Text
Resource Type	Article

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