NDLI: Dynamic inverse control of feedback linearization in ballistic correction based on nose cone swinging

Content Provider	Springer Nature Link
Author	Qin, Hua wei Wang, Hua
Copyright Year	2013
Abstract	It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets. By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging, the linear control is realized by the dynamic inverse nonlinear controlling theory and the three-time-scale separation method. The control ability and the simulation results are also tested and verified. The results show that the output responses of system track the expected curve well and the error is controlled in a given margin. The maximum correction is about ±314 m in the lengthwise direction and ±1 212 m in the crosswise direction from the moment of 5 s to the drop-point time when the angle of fire is 55°. Thus, based on the dynamic inverse control of feedback linearization, the trajectory correction capability of nose cone swinging can satisfy the requirements of two-dimensional ballistic correction, and the validity and effectiveness of the method are proved.
Starting Page	2447
Ending Page	2453
Page Count	7
File Format	PDF
ISSN	20952899
Journal	Journal of Central South University of Technology
Volume Number	20
Issue Number	9
e-ISSN	22275223
Language	English
Publisher	Springer Berlin Heidelberg
Publisher Date	2013-09-06
Publisher Place	Berlin, Heidelberg
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	nose cone swinging two-dimensional ballistic correction feedback linearization dynamic inverse control three-timescale separation method Engineering Metallic Materials
Content Type	Text
Resource Type	Article
Subject	Metals and Alloys Engineering

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