Analytical Model for Ring-Wing Propulsors at Angle of Attack

Werle, M. J.

doi:10.2514/1.c036326

Cited by 3 publications

(2 citation statements)

References 14 publications

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Section: Model Of Rotor and Shroud Under Aero-propulsion Coupling Effectmentioning

confidence: 99%

“…Then, the airflow velocity on the centerline is derived from four important components: induced velocities by free-stream, by rotor disc, by airfoil camber of shroud, and by cross-sectional area variation (please see Figure 5). However, different from Werle [32,33], the induced effect by the airfoil camber of the shroud is divided into two parts for consideration, so that we can consider the conditions of asymmetric shroud lips or non-zero attack angle, and further analyze the changes in normal flow velocity on the centerline. Taking u ∞ as a benchmark [33,34], the dimensionless expression of axial velocity on the centerline in the internal passage is Similarly, the normal velocity could also be dimensionless based on u ∞ , Taking u ∞ as a benchmark [33,34], the dimensionless expression of axial velocity on the centerline in the internal passage is…”

Section: Model Of Rotor and Shroud Under Aero-propulsion Coupling Effectmentioning

confidence: 99%

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The Modeling and Control of a Distributed-Vector-Propulsion UAV with Aero-Propulsion Coupling Effect

Xia,

Zhou

2024

Aerospace

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A novel distributed-vector-propulsion UAV (DVPUAV) is introduced in this paper, which has the capability of Vertical takeoff and landing (VTOL), and can realize relatively high-speed cruise. As the core of the DVPUAV, the propulsion wing designed under the guidance of the integration idea is not only a lifting body but also a propulsion device and a control mechanism. However, this kind of aircraft has a series of difficult problems with complex aero-propulsion coupling, flight modes switching, and so many inputs and control coupling. In order to describe this coupling effect to improve the accuracy of dynamics, an aero-propulsion coupling model is developed, considering both computation reliability and real-time. Afterward, a unique control framework is designed for the DVPUAV. By optimizing control logic, this control framework realizes the decoupling of longitudinal and lateral directional control and even the decoupling of roll and yaw control. Next, based on the Iterative linear quadratic regulator (ILQR), a new Model Predictive Control (MPC) controller with the ability to solve complex nonlinear problems is proposed which achieves the unification of the controller for the full flight envelope. Finally, the good performance of the control framework and controller is verified in the whole process of the flight simulation from take-off to landing.

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Section: Model Of Rotor and Shroud Under Aero-propulsion Coupling Effectmentioning

confidence: 99%

Section: Model Of Rotor and Shroud Under Aero-propulsion Coupling Effectmentioning

confidence: 99%

The Modeling and Control of a Distributed-Vector-Propulsion UAV with Aero-Propulsion Coupling Effect

Xia,

Zhou

2024

Aerospace

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Modeling and Transition Flight Control of Distributed-Propulsion-Wing Vtol Uav with Induced Wing Configuration

Zhao,

Zhou,

Wang

2024

Preprint

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Model Predictive Control Based on ILQR for Tilt-Propulsion UAV

XIA

Zhou

2022

Aerospace

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The transition flight of tilt-propulsion UAV is a complex and time-varying process, which leads to great challenges in the design of a stable and robust controller. This work presents a unified model predictive controller, which can handle the full envelope from vertical take-off and landing to cruise flight, to mean that the UAV can achieve a near-optimal transition flight under uncertainty conditions. Firstly, the nonlinear dynamic model of the tilt-propulsion UAV is developed, in which the aerodynamic/propulsion coupling effect of the ducted propeller is considered. Then, a control framework, including global trajectory planning and finite horizon control, is designed. Taking the planned global trajectory as the reference input, a controller is proposed with an inner layer based on ILQR optimization and an outer layer based on feedback correction and forward rolling of the MPC frame. The ILQR-MPC controller has high computational efficiency to deal with nonlinear problems, and has the ability to give full play to UAV’s control ability and suppress uncertainty. Finally, the simulation results show that ILQR-MPC controller obviously performs better than the ILQR feedforward controller, and gains a scheduling PID controller and MPC controller.

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Analytical Model for Ring-Wing Propulsors at Angle of Attack

Cited by 3 publications

References 14 publications

The Modeling and Control of a Distributed-Vector-Propulsion UAV with Aero-Propulsion Coupling Effect

The Modeling and Control of a Distributed-Vector-Propulsion UAV with Aero-Propulsion Coupling Effect

Modeling and Transition Flight Control of Distributed-Propulsion-Wing Vtol Uav with Induced Wing Configuration

Model Predictive Control Based on ILQR for Tilt-Propulsion UAV

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