SINGLE ROTOR HELICOPTER DYNAMICS FOLLOWING POWER FAILURE AT HIGH SPEED
Abstract
The program was conducted to investigate the effects of a loss of power on a single rotor helicopter at high speeds. A normal mode flexible blade analysis was combined with generalized helicopter equations of motion on a hybrid computer to predict the effects of rotor design variables and corrective control inputs on the transient response of a helicopter following a loss of main rotor power. At high forward speeds (200 to 235 knots) a loss of power can seriously affect the safety of single rotor helicopters unless there is a rapid and appropriate application of main rotor and tail rotor control. Rotor propulsive force, hinge offset, and rotor blade inertia were found to be important design considerations which effect helicopter and blade motion and loading following a loss of power. The aircraft response is due primarily to the fuselage aerodynamic characteristics associated with the sideslip and yaw motion generated by the unbalanced tail rotor yawing moment. The loss of power is less critical when a partial loss of power occurs or for a reduced rotor propulsive force.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1966
- Accession Number
- AD0635125
Entities
People
- C. Hansen
- Dean E. Cooper
- Thaddeus T. Kaplita
Organizations
- United Technologies Corporation