New Guidance Law and Autopilot Design for Launch Rockets
نویسندگان
چکیده
In this paper, the decision parts of a launch rocket—guidance law (GL) and autopilot—are discussed. In the controller design, the differential geometry and sliding mode control are employed. In addition to the individual GL and autopilot system, stability of the integrated guidance/autopilot (G/A) system are discussed. Finally, various simulations are demonstrated to examine the feasibility and performance of the rocket’s integrated G/A system. Copyright c ©2005 IFAC
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تاریخ انتشار 2005