Nonlinear missile autopilot design with θ - D technique

Journal of Guidance, Control, and Dynamics

Volumn 27, Issue 3, 2004, Pages 406-417

  Xin, Ming ^a,d   Balakrishnan, S N ^a,d   Stansbery, Donald T ^b,e   Ohlmeyer, Ernest J ^c,d  

^a MISSOURI UNIVERSITY OF SCIENCE AND TECHNOLOGY   (United States)

^b BOEING COMPANY   (United States)

^c Naval Surface Weapon Center   (United States)

^d Department of Mechanical Engineering ^*  (United States)

^e Phantom Works   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ACCELERATION; AIRCRAFT; COMPUTER SIMULATION; DEGREES OF FREEDOM (MECHANICS); ELEVATORS; FEEDBACK; FLIGHT DYNAMICS; MANEUVERABILITY; MISSILES; RICCATI EQUATIONS; RUDDERS; SCHEDULING;

AUTOPILOT DESIGN; FEEDBACK LAW; HAMILTON-JACOBIBELLMAN (HJB) EQUATION; ROLL-MOMENT COEFFICIENT;

NONLINEAR CONTROL SYSTEMS;

EID: 2642530353     PISSN: 07315090     EISSN: 15333884     Source Type: Journal    
DOI: 10.2514/1.1217     Document Type: Article

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