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Theoretical study of self-balancing missilesA theoretical study based on linear theory is presented for two types of 'self-balancing' missiles, designed to accelerate vertically or laterally without pitching or yawing. One type of missile had a variable-incidence wing and the other type had wing flaps to provide acceleration. The main objective of this investigation is to compare the maximum available acceleration for these self-balancing missiles with that of conventional pitching-type missiles. Ten different configurations were considered. The results indicate that self-balancing missiles with either variable wing incidence or wing flaps are feasible, but that the maximum available acceleration for these missiles is less than for a conventional pitching-type missile having the same wing and tail surfaces.
Document ID
19760043598
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hopkins, E. J.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 13
Subject Category
Aircraft Stability And Control
Accession Number
76A26564
Distribution Limits
Public
Copyright
Other

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