| Summary: | 碩士 === 國立臺北科技大學 === 機電整合研究所 === 91 === The purpose of this research is to build a helicopter real-time flight simulation model based on the rotor blade element method. The research consists of three parts: the rotor dynamic model, the aircraft equation-of-motion trim recursive program and the real-time simulation hardware interface.
The blade element theory of rotor aerodynamics is applied as the foundation of the rotor dynamic model. It can provide the detailed flow and loading analysis of the blades. The rotor mechanism, rotor kinematics and blade aerodynamics have been considered in the analysis of the rotor loading. The other parts of the helicopter, such as the fuselage, engine, etc., are integrated to complete the full scale helicopter model and to trim the aircraft using equation of motion and trim recursive routines. The trim parameters are calculated by equilibrium of the inertial and aerodynamics force and moments about the center of gravity of aircraft. At trim, the stability and control derivatives have been calculated and analyzed for different flight conditions.
The mathematical model are programmed with the C++ language on a personal computer which can accepts a stick input as the pilot’s inputs to control the blade pitch and outputs attitude parameters to other devices for analysis. The simulated results have been compared with those based on the rotor disc/momentum theory. The correlation has shown the feasibility of this model which can be applied as the core component of the helicopter pilot training simulation as well as the helicopter rotor design and research.
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