During series of Nike-Tomahawk sounding rocket flights, large extra-atmospheric coning angles were observed which were not predicted by preflight calculations; probable causes were concluded to be Magnus forces, aeroelastic bending, and/or lee-side boundary-layer separation; report of investigation of aeroelastic behavior of missile, analysis made, and equations of motions are presented; additional bending is attributed to opening of payload separation joint caused by rapid aerodynamic heating and sudden loss of acceleration at second-stage burnout.
Calculated aeroelastic bending of sounding rocket based on flight data
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 11
1967
6 pages
Aufsatz (Zeitschrift)
Englisch
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Aeroelastic bending of a sounding rocket vehicle
AIAA | 1970
|Aeroelastic analysis of sounding rocket vehicles
AIAA | 1973
|