A general theory and analysis of the dynamic stability of flexible-bodied missiles /
Robert L. Swaim.

Description

Main Author

Swaim, Robert L.

Related Names

United States. Air Force.

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Control Laboratory, Aeronautical Systems DIvision, Air Force Systems Command, United States Air Force, 1962.

Subjects

Guided missiles.
Equations of motion.
Aeroelasticity.
Aeroelasticity.
Guided missiles.
Mathematical analysis > Mathematical analysis / Equations.
Equations of motion.

Summary

This report presents a detailed and general derivation of the linear equations of motion for flexible-bodied missiles. In addition to the six rigid body equations, modal equations are derived for an arbitrary number of elastic degrees of freedom about all three coordinate axes. By incorporating typical automatic contron system servo element equations, a closed-loop missile-autopilot system is formed. The dynamic response of this systems is represented by a series of simultaneous, linear, variable-coefficient, ordinary differential equations. The dynamic stability of the system can be determined by making any desired number of point stability analyses along the missile trajectory. By making point analyses, the variable coefficients become constant coefficients for each time instant or point along the trajectory, and the differential equations are then amenable to Laplace transform techniques. The coefficients of the resulting stability determinant are tabulated in general form.

Note

Research supported by the United States Air Force, Air Force Systems Command.
AD0291770 (From http://www.dtic.mil).
"October 1962."

Physical Description

xiv, 126 pages : illustrations ; 28 cm.

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