V/STOL TILT ROTOR STUDY - VOLUME VI HOVER, LOW SPEED AND CONVERSION TESTS OF A TILT ROTOR AERO ELASTIC MODEL

摘要

Two series of tests evaluated the stability and control charac-teristics of a one-fifth scale powered aeroelastic model of the Model 300 Tilt Rotor Research Aircraft in hover, low speed heli¬copter, and conversion flight. Hover tests took place in the Bell Helicopter Company rotor whirl cage from September 13, 1972 to December 22, 1972. Helicopter and conversion mode tests took place in the Vought low speed wind tunnel from January 15, 1973 to March 30, 1973. This testing was performed under NASA Con¬tract NAS 2-6599.nThe hover testing was directed at measuring hover performance and roll static stability characteristics. During part of this testing, the model was secured to a mount which simulated free flight to investigate stability characteristics and control response.nThe helicopter and conversion mode testing was in two phases, with a different mount for- each. The first phase had the model mounted on the vertical rod shown in Figure 1-1. This mount gave the model freedom to pitch, roll, and yaw and to translate vertically. Model "pilots" could adjust cyclic pitch, collec¬tive pitch, and elevator position to make the model fly in a trimmed flight condition. Trimmed flight conditions tested included level flight (OGE and IGE), climbs, descents, auto-rotation, and rearward and sideward flight. At selected flight conditions the model was disturbed from trim to investigate dynamic stability characteristics.