Analytical Model for Ring-Wing Propulsor Thrust Augmentation

Werle, M. J.

doi:10.2514/1.c035922

Cited by 5 publications

(1 citation statement)

References 32 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Moreover, the most important stations are the rotor station and exit station, which will be mentioned multiple times in subsequent derivation. The disk model [30] of the rotor could describe the flow changes through the rotor from upstream to downstream inviscid regions, so the rotor thrust could be written as T r = r r 0 2πr(P r2 − P r1 )dr (1) where P r1 , P r2 , respectively, represent the pressure before as well as after the rotor disc. The total thrust of the propulsion wing is composed of the rotor thrust and the shroud thrust caused by the induced low-pressure area of the shroud lip.…”

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

View full text Add to dashboard Cite

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.

show abstract

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

View full text Add to dashboard Cite

show abstract

Analytical Model for Ring-Wing Propulsors at Angle of Attack

Werle¹

2022

Journal of Aircraft

View full text Add to dashboard Cite

Double-Ducted Fan as an Effective Lip Separation Control Concept for Vertical-Takeoff-and-Landing Vehicles

Aktürk

2022

Journal of Aircraft

View full text Add to dashboard Cite

This paper describes a novel inlet flow conditioning concept that significantly improves ducted fans' performance and controllability. High angle of attack operation of ducted fans is very common in VTOL systems. The new concept named Double Ducted Fan (DDF) uses a secondary shroud to control inlet lip-separation-related momentum deficit at the inlet of the fan rotor during edgewise flight. The DDF is helpful in a wide edgewise flight velocity range, and its corrective aerodynamic effect becomes more pronounced with increasing flight velocity. A conventional baseline duct operating at 90 o angle of attack is compared to other novel double ducted fan designs via 3D, viscous, and turbulent flow computations. A custom actuator-disk model replaces the zonal computation of the complex and three-dimensional rotor flow field in the rotating frame of reference. Both hover and edgewise flight conditions are considered around the ducted fan unit and inside the ducts. Significant improvements from several novel ducted fan designs are in the areas of vertical thrust enhancement, noseup pitching moment reduction, and recovery of fan through-flow mass flow rate in a wide horizontal flight range. A variable DDF design (VDDF), a partial DDF design (PDDF), and a Fan-in-Wing implementation of the DDF are introduced.

show abstract

Analytical Model for Ring-Wing Propulsor Thrust Augmentation

Cited by 5 publications

References 32 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

Analytical Model for Ring-Wing Propulsors at Angle of Attack

Double-Ducted Fan as an Effective Lip Separation Control Concept for Vertical-Takeoff-and-Landing Vehicles

Contact Info

Product

Resources

About