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| Author | : Peter D. Talbot |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1982 |
| Genre | : Helicopters |
| ISBN | : |
| Author | : K. B. Hilbert |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1984 |
| Genre | : Helicopters |
| ISBN | : |
This report documents the revisions made to a mathematical model of a single main rotor helicopter. These revisions were necessary to model the UH-60 helicopter accurately. The major modifications to the model include fuselage aerodynamic force and moment equations that are specific to the UH-60, a canted tail rotor, a horizontal stabilator with variable incidence, and a pitch bias actuator (PBA). In addition, the model requires a full set of parameters which describe the helicopter configuration and its physical characteristics.
| Author | : |
| Publisher | : DIANE Publishing |
| Total Pages | : 118 |
| Release | : |
| Genre | : |
| ISBN | : 1428916784 |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 30 |
| Release | : 2018-07-25 |
| Genre | : |
| ISBN | : 9781724220202 |
The model was developed for real-time pilot-in-the-loop investigation of helicopter flying qualities. The mathematical model included the tip-path plane dynamics and several primary rotor design parameters, such as flapping hinge restraint, flapping hinge offset, blade Lock number, and pitch-flap coupling. The model was used in several exploratory studies of the flying qualities of helicopters with a variety of rotor systems. The basic assumptions used and the major steps involved in the development of the set of equations listed are described. The equations consisted of the tip-path plane dynamic equation, the equations for the main rotor forces and moments, and the equation for control phasing required to achieve decoupling in pitch and roll due to cyclic inputs. Chen, R. T. N. Ames Research Center NASA-TM-78575, A-7538 RTOP 505-10-23
| Author | : Eugen Bernard Johan Siepker |
| Publisher | : |
| Total Pages | : 602 |
| Release | : 1990 |
| Genre | : Helicopters |
| ISBN | : |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 118 |
| Release | : 2018-07-17 |
| Genre | : |
| ISBN | : 9781722897840 |
A mathematical model of a helicopter system with a single main rotor that includes rigid, hinge-restrained rotor blades with flap, lag, and torsion degrees of freedom is described. The model allows several hinge sequences and two offsets in the hinges. Quasi-steady Greenberg theory is used to calculate the blade-section aerodynamic forces, and inflow effects are accounted for by using three-state nonlinear dynamic inflow model. The motion of the rigid fuselage is defined by six degrees of freedom, and an optional rotor rpm degree of freedom is available. Empennage surfaces and the tail rotor are modeled, and the effect of main-rotor downwash on these elements is included. Model trim linearization, and time-integration operations are described and can be applied to a subset of the model in the rotating or nonrotating coordinate frame. A preliminary validation of the model is made by comparing its results with those of other analytical and experimental studies. This publication presents the results of research compiled in November 1989. Takahashi, Marc D. Unspecified Center AERODYNAMIC FORCES; DOWNWASH; DYNAMIC MODELS; FLAPPING; HELICOPTERS; MATHEMATICAL MODELS; RIGID ROTORS; TORSION; DEGREES OF FREEDOM; FUSELAGES; HINGES; LINEARIZATION; NONLINEARITY; ROTATION; TAIL ASSEMBLIES; TAIL ROTORS...
| Author | : |
| Publisher | : |
| Total Pages | : 120 |
| Release | : 1990 |
| Genre | : |
| ISBN | : |
A mathematical model of a helicopter system with a single main rotor that includes rigid, hinge-restrained rotor blades with flap, lag, and torsion degrees of freedom is described. The model allows several hinge sequences and two offsets in the hinges. Quasi-steady Greenberg theory is used to calculate the blade-section aerodynamic forces, and inflow effects are accounted for by using a three-state nonlinear dynamic inflow model. The motion of the rigid fuselage is defined by six degrees of freedom, and an optional rotor rpm degree of freedom is available. Empennage surfaces and the tail rotor are modeled, and the effect of main-rotor downwash on these elements is included. Model trim, linearization, and time-integration operations are described and can be applied to a subset of the model in the rotating and nonrotating coordinate frame. A preliminary validation of the model is made by comparing its results with those of other analytical and experimental studies. This publication presents the results of research completed in November 1989.
| Author | : Peter D. Talbot |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1977 |
| Genre | : |
| ISBN | : |
| Author | : John Damian Shaughnessy |
| Publisher | : |
| Total Pages | : 154 |
| Release | : 1979 |
| Genre | : Helicopter flight simulators |
| ISBN | : |
| Author | : J. D. Shaughnessy |
| Publisher | : |
| Total Pages | : 120 |
| Release | : 1979 |
| Genre | : Helicopter flight simulators |
| ISBN | : |
