Application of H∞ Control to pitch autopilot of missiles

IEEE Transactions on Aerospace and Electronic Systems

Volumn 32, Issue 1, 1996, Pages 426-433

  Yang, S M ^a   Huang, N H ^a  

^a NATIONAL CHENG KUNG UNIVERSITY   (Taiwan)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; AUTOMATIC PILOTS; CONTROL SYSTEMS; CONTROL THEORY; ITERATIVE METHODS; MATHEMATICAL MODELS; RICCATI EQUATIONS; ROBUSTNESS (CONTROL SYSTEMS); STABILITY; TRACKING (POSITION); VIBRATIONS (MECHANICAL);

AIRFRAME FLEXIBILITY EFFECT; AIRFRAME STRUCTURE VIBRATION; LINEAR QUADRATIC GAUSSIAN; PITCH RATE CONTROL; PROPORTIONAL INTEGRAL DERIVATIVE CONTROL SYSTEM; THREE LOOP AUTOPILOT;

MISSILES;

EID: 0029753168     PISSN: 00189251     EISSN: None     Source Type: Journal    
DOI: 10.1109/7.481283     Document Type: Article

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