Most rotorcraft flight dynamic studies employed higher fidelity rotor modelling approach to precisely resemble the dynamic behaviour of the real rotorcraft in simulation. However, high-fidelity calculations always implemented at the expense of other simulation costs, such as the CPU run-time and the machine hardware. This paper is aimed to highlight the used of lower fidelity rotorcraft calculation approach for light autogyros in normal flight mode where extensive calculations are less vital. A lower fidelity helicopter simulation package, named Helicopter Generic Simulation (HGS) is used as the basis where the structural features are modified according to the unique autogyro’s kinematics. Due to the common longitudinal stability issues previously experienced by typical light autogyros, validations are made in longitudinal steady-state flight mode against the real flight data of the test autogyro. Simulation results show tolerable steady-state predictions of important parameters, such as the fuselage pitch attitude and the longitudinal shaft tilt. Hence, it is recommended to employ the rotor-disc modelling approach for autogyro’s applications that are not subjected to complex rotor blade dynamics, such as in automatic flight control and inverse simulations in normal flight mode.
Validation of Rotor-Disc Model for Light Autogyro in Steady-State Flight Mode
Lect.Notes Mechanical Engineering
Proceedings of International Conference of Aerospace and Mechanical Engineering 2019 ; Chapter : 42 ; 481-492
2020-06-13
12 pages
Article/Chapter (Book)
Electronic Resource
English
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