Citation

Geng F, Zhu XP. Chin. Soc. Astronaut. J. 2008; 29(3): 922-927.

Copyright

(Copyright © 2008, Yuhang Xuebao)

DOI

unavailable

PMID

unavailable

Abstract

High Speed Unmanned Attack Air Vehicle (HSUAAV) was a suicide-type precision guided weapon. Because it had a lot of advantages that cruise missile didn't possess, HSUAAV played an important role in modem warfare. In order to attack all kinds of maneuvering targets precisely, a nonlinear mixed H2/H robust guidance law for HSUAAV was introduced. Because the mixed H2/H control had good qualities of H2 control and good robustness of H control, this guidance law wasn't sensitive to target maneuvering and other uncertainties. A group of associated nonlinear Hamilton-Jacobin Partial Differential Inequality (HJPDI) had to be solved first, because the solvability of it decided whether the nonlinear mixed H2/H robust guidance law-could be implemented. In this paper, a pair of numerical solution was obtained through transforming equivalently and solving the group of associated nonlinear HJPDI. By simulation research, it is demonstrated that the proposed guidance law has better guidance precision and stronger robustness against target maneuvering and other uncertainties.