The test objective of the maneuvering flying qualities evaluation on the OH-6A, OH-58A, BO-105, and L-286 helicopters was to evaluate the suitability of three types of rotor systems (articulated, teetering, and hingeless) to perform the proposed utility tactical transport aircraft system (UTTAS) pull-up and pushover maneuvers. The testing consisted of 41 flights for a total of 22 productive hours. The results obtained during this test established a data base to assess the applicability of the presently stated UTTAS maneuverability requirements. It was determined that present-day rotary-wing aircraft can be tested against the prescribed maneuver criteria with meaningful results. Three flying quality deficiencies were noted, correction of which is mandatory if procurement or envelope expansion is anticipated. There were two shortcomings, correction of which is desirable if procurement or envelope expansion is anticipated.
Utility Tactical Transport Aircraft System (UTTAS) Maneuver Criteria
1972
59 pages
Report
Keine Angabe
Englisch
Aircraft , Helicopters , Helicopter rotors , Flight control systems , Maneuverability , Military requirements , Test methods , Terrain avoidance , Yaw , Roll , Aerodynamic loading , Vibration , Aircraft landings , Airspeed , Acceleration , Load distribution , Hovering , Rotor blades(Rotary wings) , Utility aircraft , Observation aircraft , Acceptability , Articulated rotor blades , Bo-105 aircraft , Hingeless helicopter rotors , H-6 aircraft , H-58 aircraft , L-286 aircraft , Oh-6a aircraft , Oh-58a aircraft , Pull up maneuvers , Push over maneuvers , Teetering rotors , Transition flight , Utility tactical transport aircraft system , Uttasutility tactical transport aircraft
IuD Bahn | 2002
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