Factors influencing magnitude of hover control power, and methods of scanning control effectiveness and specifying control criteria are discussed; it is mathematically shown that amount of simultaneous roll and pitch acceleration establishes location of axis of rotation and magnitude of resulting acceleration about axis; optimum distance from aircraft center of gravity for various control system lift device arrangements is analyzed and effects of aircraft moment of inertia and control response lag are discussed.
Some fundamentals for efficient VTOL aircraft hover control
Am Helicopter Soc -- J
American Helicopter Society -- Journal ; 11 , n 1
1966
8 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
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