NDLI: Integrated design of ballistic missile guidance and autopilot using adaptive sliding control with 5 DOF inputs

Content Provider	IEEE Xplore Digital Library
Author	Fu-Kuang Yeh Jian-Ji Huang Chia-Wei Huang
Copyright Year	2011
Description	Author affiliation: Department of Computer Science and Information Engineering, ChungChou Institute of Technology, Changhua, Taiwan, R.O.C. (Fu-Kuang Yeh; Jian-Ji Huang; Chia-Wei Huang)
Abstract	In this research, we propose an integrated controller of missile guidance and autopilot systems based on adaptive sliding-mode control with actuators, mainly consisting of thrust vector control and divert control system, for the task of intercepting of a theater ballistic missile. The aim of the present work is to achieve bounded target interception under the mentioned 5 degree-of-freedom (DOF) control such that the distance between the intercepting missile and the target missile will enter the range of triggering the missile's explosion. First, the adaptive sliding-mode guidance law of the intercepting missile considering external disturbances is designed to minimize the distance between the center of the intercepting missile and that of the target missile while coping with variation of missile's mass. Next, a quaternion-based adaptive sliding-mode autopilot controller is developed to track the attitude command while grasping the variation of missile's inertia and uncertain aerodynamic force/wind gusts. Finally, the stability of the overall system is analyzed thoroughly via Lyapunov stability theory to achieve the integrated controller design of missile guidance and autopilot systems based on adaptive sliding-mode control. Furthermore, Extensive simulation results are conducted to validate the effectiveness of the proposed integrated guidance and autopilot systems by use of the 5 DOF inputs.
Starting Page	639
Ending Page	644
File Size	525476
Page Count	6
File Format	PDF
ISBN	9781457707148
e-ISBN	9784907764395
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2011-09-13
Publisher Place	Japan
Access Restriction	Subscribed
Rights Holder	SICE (The Society of Instrument and Cont
Subject Keyword	Missiles Adaptive systems Navigation Force Quaternions Sliding mode control Mathematical model Thrust vector control Adaptive sliding-mode control Guidance law Autopilot system
Content Type	Text
Resource Type	Article

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4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
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