Abstract
In this paper, the flight dynamic model of Vertical Take-Off and Landing (VTOL) aircraft which equips a propeller-wing-flap system that produces slipstream is established. The complete aircraft is modeled by combining experimental results, theoretical calculation, and empirical data. Firstly, the propeller deflected slipstream effects and the parameters of ducted fan are obtained by bench test. The DATCOM are used for generating the aerodynamic coefficients. Then, the 6-DoF nonlinear flight dynamic model in both hover and forward flight conditions are deducted by employing the assumption of linear superposition. The gyro effect and gravity are considered. Finally, specific trim conditions in hovering, transitional and level flight states are determined, and dynamic characteristics at trim are studied by both full model simulation and linear system analysis obtained through small-perturbation theory. It is found that the aircraft is critically stable in hovering condition. The damping ratio of short-period mode is relatively small, and the phugoid mode divergence in the transition state. The aircraft is less well damped in the level flight condition. The built model accurately reflects the dynamic characteristics of the VTOL aircraft and provides help for the design of the flight control system afterward.
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Jia, S., Zhang, Z., Wang, W., Yang, C. (2022). Flight Dynamics Modeling and Simulation of Propeller Deflected Slipstream VTOL Aircraft. In: Proceedings of the 5th China Aeronautical Science and Technology Conference. Lecture Notes in Electrical Engineering, vol 821. Springer, Singapore. https://doi.org/10.1007/978-981-16-7423-5_76
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DOI: https://doi.org/10.1007/978-981-16-7423-5_76
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