A sliding mode missile pitch autopilot synthesis for high angle of attack maneuvering

被引：94

作者：

Thukral, A ^{[1
]}

Innocenti, M

机构：

[1] Tuskegee Univ, Dept Mech Engn, Tuskegee, AL 36088 USA

[2] Univ Pisa, DSEA, I-56126 Pisa, Italy

来源：

IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY | 1998年 / 6卷 / 03期

关键词：

control systems; missile control; robustness; scheduling; variable structure systems;

D O I：

10.1109/87.668037

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

A new approach to the synthesis of longitudinal autopilots for missiles flying at high angle of attack regimes is presented, The methodology is based on sliding mode control, and uses a combination of aerodynamic surfaces and reaction jet thrusters, to achieve controllability beyond stall. The autopilot is tested on a small section of the flight envelope consisting of a fast 180 degrees heading reversal in the vertical plane, which requires robustness with respect to uncertainties in the system's dynamics induced by large variations in dynamic pressure and aerodynamic coefficients, Nonlinear simulation results show excellent performance and capabilities of the control system structure.

引用

页码：359 / 371

页数：13