Modeling and Design of a Lift-Augmented Quadcopter

Staub, Franco M.; Tsukada, Dai; Inoue, Shota; Raabe, Christopher T.; Tsuchiya, Takeshi

doi:10.2514/6.2021-1988

Cited by 5 publications

(3 citation statements)

References 2 publications

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“…The authors in [22][23][24] present the design and aerodynamic testing of a quadcopter with short lifting wings attached at a fixed angle to the frame. The authors develop a model in [22] by balancing aerodynamic forces on the vehicle and assuming power consumption varies as a cubic function airspeed. In [23] the authors measure lift, drag and reduction in thrust for a similar vehicle.…”

Section: B Suas Wind Tunnel Testingmentioning

confidence: 99%

“…In [23] the authors measure lift, drag and reduction in thrust for a similar vehicle. The baseline model introduced in [22] was established using wind tunnel data from the quadcopter without wings. Wind tunnel tests were conducted for different wing mounting angles and the vehicle was trimmed at each airspeed before data collection.…”

Section: B Suas Wind Tunnel Testingmentioning

confidence: 99%

“…Ref. [22] describes the design and mathematical modelling of a quadrotor augmented with small lifting wings. Computational Fluid Dynamics (CFD) simulation of a lift+cruise vehicle is presented in [34], while a preliminary control design is described in [35].…”

Section: Evtol Suas Designs and Configurationsmentioning

confidence: 99%

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Wind Tunnel Testing and Aerodynamic Characterization of a QuadPlane Uncrewed Aircraft System

Mathur¹,

Atkins²

2023

Preprint

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Electric Vertical Takeoff and Landing (eVTOL) vehicles will open new opportunities in aviation. This paper describes the design and wind tunnel analysis of an eVTOL uncrewed aircraft system (UAS) prototype with a traditional aircraft wing, tail, and puller motor along with four vertical thrust pusher motors. Vehicle design and construction are summarized. Dynamic thrust from propulsion modules is experimentally determined at different airspeeds over a large sweep of propeller angles of attack. Wind tunnel tests with the vehicle prototype cover a suite of hover, transition and cruise flight conditions. Net aerodynamic forces and moments are distinctly computed and compared for plane, quadrotor and hybrid flight modes. Coefficient-based models are developed. Polynomial curve fits accurately capture observed data over all test configurations. To our knowledge, the presented wind tunnel experimental analysis for a multi-mode eVTOL platform is novel. Increased drag and reduced dynamic thrust likely due to flow interactions will be important to address in future designs.

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