Nonlinear aeroelastic analysis of a deployable missile control fin

Journal of Spacecraft and Rockets

Volumn 41, Issue 2, 2004, Pages 264-271

  Bae, Jae Sung ^a,d   Kim, Dae Kwan ^b,d   Shin, Won Ho ^b,d   Lee, In ^b,d   Kim, Seung Ho ^c,d  

^a VIRGINIA POLYTECHNIC INSTITUTE AND STATE UNIVERSITY   (United States)

^b Korea Advanced Institute of Science and Technology (KAIST)   (South Korea)

^c Korea Aerospace Industries Inc   (South Korea)

^d Department of Mechanical Engineering ^*  (South Korea)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; APPROXIMATION THEORY; CONTROL SYSTEMS; ELASTIC MODULI; FLUTTER (AERODYNAMICS); FREQUENCY DOMAIN ANALYSIS; FUNCTION EVALUATION; HINGES; OSCILLATIONS; PROBLEM SOLVING; STIFFNESS; SUPERSONIC AERODYNAMICS; TIME DOMAIN ANALYSIS; VIBRATIONS (MECHANICAL);

DEPLOYABLE MISSILE CONTROL FIN; DOUBLET-POINT METHOD; LIMIT CYCLE OSCILLATIONS (LCO); LINEAR FLUTTER BOUNDARY;

MISSILE LAUNCHING SYSTEMS;

EID: 2342646208     PISSN: 00224650     EISSN: 15336794     Source Type: Journal    
DOI: 10.2514/1.1052     Document Type: Article

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