This paper presents the development of the V-22 Engineering and Manufacturing Development (EMD) static and fatigue design loads for the airframe, rotor system, and drive system. V-22 Full-Scale Development (FSD) flight test data was the primary source for selected airframe and dynamic component loads. The data base was also used to validate the loads prediction capabilities of the various analytical and computational methods. The lessons learned from the FSD flight test data are discussed along with comparisons of the predicted and measured loads. The V-22 design requirements represent a significant technological advancement, leading to new challenges in both analysis and design. The V-22 designed to execute maneuvers up to the maximum aerodynamic capability in both fixed-wing and rotary-wing modes. This requires loads analysis for the rotor system at very high thrust coefficients with significant rotor stall. In order to minimize the design weight, the flight control system has been developed employing additional control laws designed to reduce structural loads. The data is presented to show the development of design loads for various aircraft components using V-22 FSD flight test measured loads.
V-22 EMD design loads development using V-22 FSD flight test data
Die Entwicklung der U22-EMD(Planung/Herstellung/Entwicklung)-Auslegungsbelastung mittels der im Maßstab 1:1 angewandten V-22 Flugtestdaten
Forum, Annual Forum, American Helicopter Society, 50 ; 1 ; 613-622
1994
10 Seiten, 17 Bilder, 4 Quellen
Conference paper
English
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