A Flight-Dynamic Helicopter Mathematical Model with a Single Flap-Lag-Torsion Main Rotor
Author:
Publisher: DIANE Publishing
Published:
Total Pages: 118
ISBN-13: 1428916784
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Author:
Publisher: DIANE Publishing
Published:
Total Pages: 118
ISBN-13: 1428916784
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-17
Total Pages: 118
ISBN-13: 9781722897840
DOWNLOAD EBOOKA 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...
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Published: 1990
Total Pages: 120
ISBN-13:
DOWNLOAD EBOOKA 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.
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Published: 1993
Total Pages: 556
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Published: 1992
Total Pages: 48
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Published: 1991
Total Pages: 538
ISBN-13:
DOWNLOAD EBOOKAuthor: American Helicopter Society
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Published: 2001
Total Pages: 324
ISBN-13:
DOWNLOAD EBOOKAuthor: Greg Schulein
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Published: 2001
Total Pages: 172
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DOWNLOAD EBOOKAuthor: American Institute of Aeronautics and Astronautics
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
Published: 1997
Total Pages: 838
ISBN-13:
DOWNLOAD EBOOKThis volume is the proceedings of the Atmospheric Flight Mechanics Conference, which took place in New Orleans, August 1997. It focuses on the technical progress, issues and challenges associated with atmospheric flight. Technical papers address stability and control, flying qualities (including one session dedicated to pilot-induced oscillations), unsteady and vortex aerodynamics, system and parameter identification, aircraft flight dynamic re-entry and aero assist technologies, and reusable launch vehicles.