Automatic Flight Control Requirements for Transition Flight Phases When Converting Long Endurance Fixed Wing UAV to VTOL Aircraft

This paper investigates the design of a long-endurance unmanned helicopter (LEUH) with low rotor disc loading (LRDL) and low rotor speed (LRS). Due to the flaws in flying qualities caused by the LRDL and the LRS, this paper establishes a flying quality evaluation model in which handling qualities (FQs) and flight control (FC) are introduced into the distributed multi-objective collaborative optimization (DMOCO) of the helicopters. The comprehensive design optimization on preliminary parameters of the LEUH in wind shear is also carried out. Numerical simulation results show that the LRDL and the LRS technologies are successfully applied to LEUH, with the FQs and the flight performance considered. Compared with A160 LEUH, the payload load ratio is significantly improved.

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Transition flight control for Canard Rotor/Wing rotorcraft

2011 2nd International Conference on Artificial Intelligence, Management Science and Electronic Commerce (AIMSEC) ◽

10.1109/aimsec.2011.6010405 ◽

2011 ◽

Author(s):

Tengfei Guo ◽

Honglun Wang ◽

Wendong Gai

Keyword(s):

Flight Control ◽

Rotor Wing ◽

Transition Flight

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Transition flight control of a cyclic tiltrotor UAV based on the Gain-Scheduling strategy

2015 International Conference on Unmanned Aircraft Systems (ICUAS) ◽

10.1109/icuas.2015.7152383 ◽

2015 ◽

Cited By ~ 6

Author(s):

Rogelio G. Hernandez-Garcia ◽

H. Rodriguez-Cortes

Keyword(s):

Flight Control ◽

Gain Scheduling ◽

Scheduling Strategy ◽

Transition Flight

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Development of Dual Power Multirotor System

International Journal of Aerospace Engineering ◽

10.1155/2017/9821401 ◽

2017 ◽

Vol 2017 ◽

pp. 1-19 ◽

Cited By ~ 6

Author(s):

Chin E. Lin ◽

Thanakorn Supsukbaworn

Keyword(s):

Gasoline Engine ◽

System Development ◽

Motor Power ◽

Brushless Dc Motors ◽

Gasoline Engines ◽

Brushless Dc ◽

Dc Motors ◽

Long Endurance ◽

Vtol Aircraft ◽

Dual Power

Vertical take-off and landing (VTOL) aircraft has good flight characteristics and system performance without runway. The multirotor system has been tried to expand into larger size for longer endurance or higher payload. But the motor power to endurance ratio has been limited. Due to the specific energy of gasoline being much higher than battery, introducing gasoline engine into multirotor system can be considered. This paper proposes a dual power multirotor system to combine a quadrotor using gasoline engines to provide major lift in shorter arm with another quadrotor using brushless DC motors to offer most controllable force with longer arm. System design, fabrication, and verification of the proposed dual power multirotor system development are presented. Preliminary flights have achieved 16 kg payload for long endurance flight. This is useful for various applications with advanced improvements.

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