Written in English
|The Physical Object|
|Number of Pages||104|
ABSTRACT The performance and aeroelastic stability in hover of a. m-diam, hingeless helicopter rotor system was evaluated. Rotor performance and inplane damping data were obtained for rotor operation between and rpm for thrust coefficients (CT/CT) between and File Size: 4MB. The aeroelastic stability and response problem of the coupled flap-lag-torsional dynamics of an isolated hingeless rotor blade in forward flight is considered. A small scale, m diam, torsionally soft, hingeless helicopter rotor was investigated in hover to deter-mine isolated rotor stability characteristics. The two bladed, untwisted rotor was tested on a rigid test stand at tip speeds up to m/sec. The rotor mode of interest in this investigation was the lightly damped lead-lag by: Dynamics and aeroelasticity of a coupled helicopter rotor-propulsionsystem in hover. A coupled helicopter rotor/fuselage aeroelastic response model for ACSR. Hingeless-rotor aeromechanical stability in hover and forward flight with wake dynamics.
Since the original publication of "Helicopter Dynamics" by A.R.S. Bramwell in , this book has become the definitive text on helicopter dynamics. As such it is an essential aid to those studying the behavior of helicopters. The second edition builds on the strengths of the original, and hence the approach of the first edition is retained. hingeless rotor will greatly enhance flying qualities and maneuverability, and the simpler hub design will result in reduced maintenance and improved reliability. The AHA Cheyenne is an example of a compound helicopter using a hingeless rotor and i is likely that at least one of the UTTAS candidate aircraft will have a hingeless Size: KB. less rotor analyses are discussed by Chopra (). The Army's Aeroflightdynamics Directorate at Ames performed extensive aero- mechanical stability testing in hover on hingeless and bearingless rotor models. These data form a part of the ITR data set (McNulty & Bousman ) and are widely used. In the low-speed modes, while the relationship between the roll and yaw movements is still small, and the roll motion, like the hovering, is unstable, the lateral motion of a single-rotor helicopter is unstable. Static stability of helicopters with two main rotors differs slightly from the stability of the helicopter with one main : Constantin Rotaru, Michael Todorov.
Toward that end the book offers thorough, comprehensive coverage of the theory of helicopter flight: the elements of vertical flight, forward flight, performance, design, mathematics of rotating systems, rotary wing dynamics and aerodynamics, aeroelasticity, stability /5(19). SUMMARY A hover test of a full-scale, hingeless rotor system was conducted in the NASA Ames by Foot Wind Tunnel. The rotor was tested on the Ames Rotor Test Apparatus (RTA). Rotor aeroelastic stability, performance, and loads at various rotational speeds and . Several nonlinear structural and inertial terms in the final equations were identified that can substantially influence the aeroelastic stability of hingeless helicopter rotor blades. The flap-lag-torsion analysis was displacement-based and included no shear by: aeromechanical stability characteristics for hingeless and bearingless rotor . Gaonkar investigated an experimental and analytical investigation of isolated rotor flap-lag stability in forward flight . The bearingless main rotor hub system has a few important composite parts. The primary part is the.