Development and evaluation of an inverse solution technique for studying helicopter maneuverability and agility
- Whalley, Matthew S.
- Jul 1, 1991.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
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- An inverse solution technique for determining the maximum maneuvering performance of a helicopter using smooth, pilotlike control inputs is presented. Also described is a pilot simulation experiment performed to investigate the accuracy of the solution resulting from this technique. The maneuverability and agility capability of the helicopter math model was varied by varying the pitch and roll damping, the maximum pitch and roll rate, and the maximum load-factor capability. Three maneuvers were investigated: a 180-deg turn, a longitudinal pop-up, and a lateral jink. The inverse solution technique yielded accurate predictions of pilot-in-the-loop maneuvering performance for two of the three maneuvers.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19910022831.
Accession ID: 91N32145.
- No Copyright.
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