Investigation of the Airflow at Rocket Trajectory and Wind Sensor Locations of a Model Helicopter Simulating Low Speed Flight. Application of Model Helicopter Testing, Laser Velocimetry, and Rotor Wake Flow Visualization to Invest

摘要

An experimental investigation was conducted to determine the airflow characteristics in the vicinity of a model helicopter to determine the aerodynamic interference at representative rocket trajectories and wind sensor locations of an Army AH-1G helicopter operating in low speed forward flight. Laser velocimetry and flow visualization techniques were applied in a wind tunnel to provide flow velocity and wake geometry data for use in a rocket aeroballistics analysis, correlation with theory, and for a systematic determination of the influence of the helicopter components (rotor, fuselage, and wing) and significant operating condition parameters (flight speed, flight direction, ground effect, gross weight, and aircraft/rocket attitude) on the airflow influencing rocket trajectories. In addition, the flow velocities at potential locations for a fire control wind sensor mounted on the helicopter were determined to evaluate potential wind sensor locations for accurately measuring flow velocities at the low flight speeds required in accordance with current terrain flying/rocket firing tactics.