
Accession Number : AD0600544
Title : ANALYTIC SOLUTIONS TO THE EQUATIONS OF MOTION OF MISSILES HAVING SIX DEGREES OF FREEDOM.
Descriptive Note : Aerodynamics research rept.
Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD
Personal Author(s) : DeGrafft,W. E.
Report Date : 02 JAN 1964
Pagination or Media Count : 70
Abstract : The angular motions of several vehicles flying at a constant altitude and flight speed but accelerating in spin rate were studied. Calculations of the amplitudes and frequencies of the natural modes of motion, using the approximate solutions, are compared to results obtained from a sixdegreeoffreedom computer program. It was found that the amplitudes were fairly sensitive to spinrate accelerations and that the accuracy of the approximate expressions for the amplitudes decreases as the spin acceleration increases. The frequencies, however, were insensitive to spin acceleration and are given very accurately by the approximate solutions. An alternate solution for the modal amplitudes, assuming that the frequencies are known, is derived. Results obtained using this alternate solution are in excellent agreement with the computer program results. The approximate expression for the rolling trim angle obtained shows that for a vehicle flying at a constant speed in horizontal flight the peak rolling trim angle experienced when passing through resonance is reduced as the acceleration in spin rate increases. (Author)
Descriptors : (*GUIDED MISSILE TRAJECTORIES, MATHEMATICAL ANALYSIS), (*BALLISTICS, GUIDED MISSILES), (*NUMERICAL METHODS AND PROCEDURES, BALLISTICS), AERODYNAMIC CHARACTERISTICS, STABILIZATION SYSTEMS, EQUATIONS, MOTION
Distribution Statement : APPROVED FOR PUBLIC RELEASE