Method of analysis for determining transient forced flexural vibrations of accelerating missiles and space vehicles is presented; equations of motion are in matric form and may be adapted to computers; matric formulation for problem is written to include effects of engine gimballing resulting from structural coupling of flight control system, inertial axial loads along missile, variable shear stiffness, structural damping, structurally coupled aerodynamic forces and arbitrary transient forces applied along missile; only basic data for system are required in matrices.
Transient vibrations of missiles and space vehicles
Aircraft Eng
Aircraft Engineering ; 34 , n 406
1962
17 pages
Aufsatz (Zeitschrift)
Englisch
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Transient Vibrations of Missiles and Space Vehicles
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