Paper Title:
Dynamic Inversion Guidance Law for a Hypersonic Vehicle
  Abstract

An adapting dynamic inversion guidance law developed by using integral of time multiply by absolute error (ITAE) performance index for a hypersonic vehicle was studied. As a nominal trajectory, Maximum-Range glide trajectory was obtained by using collocation and successive quadratic programming. Dynamic inversion technique was employed to produce a guidance law which contains two PID controllers. To find optimal guidance parameters, ITAE criteria were used to tune the PID parameters. The numerical result showed that the guidance law was simple and efficient for a hypersonic vehicle flies along the optimal trajectory.

  Info
Periodical
Advanced Materials Research (Volumes 383-390)
Chapter
Chapter 17: Manufacturing Process Planning and Scheduling
Edited by
Wu Fan
Pages
4451-4456
DOI
10.4028/www.scientific.net/AMR.383-390.4451
Citation
Q. Q. Qiao, W. C. Chen, "Dynamic Inversion Guidance Law for a Hypersonic Vehicle", Advanced Materials Research, Vols. 383-390, pp. 4451-4456, 2012
Online since
November 2011
Export
Price
$32.00
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