Title :
Design of a CLOS guidance law via feedback linearization
Author :
Ha, In-Joong ; Chong, Song
Author_Institution :
Dept. of Control & Instrum. Eng., Seoul Nat. Univ., South Korea
fDate :
1/1/1992 12:00:00 AM
Abstract :
An application of the feedback linearization technique to the design of a new command to line-of-sight (CLOS) guidance law for short-range surface-to-air missiles is described. The key idea lies in converting the three-dimensional CLOS guidance problem to the tracking problem of a time-varying nonlinear system. The result may shed new light on the role of the feedforward acceleration terms used in the conventional CLOS guidance laws. Through computer simulation, the effect of the dynamics of the ground tracker and the autopilot on the guidance performance of the new CLOS guidance law is investigated
Keywords :
aerospace control; command and control systems; control system CAD; control system synthesis; digital simulation; feedback; linearisation techniques; military computing; missiles; nonlinear control systems; time-varying systems; tracking; 3D; autopilot; command to line-of-sight guidance law; computer simulation; dynamics; feedback linearization; feedforward acceleration; ground tracker; short-range surface-to-air missiles; time-varying nonlinear system; Acceleration; Aerodynamics; Azimuth; Feedback; Linearization techniques; Missiles; Nonlinear systems; Optimal control; Target tracking; Time varying systems;
Journal_Title :
Aerospace and Electronic Systems, IEEE Transactions on
