Ducted-Fan Force and Moment Control via Steady and Synthetic Jets

Ohanian, Osgar John; Karni, Etan D.; Londenberg, W. Kelly; Gelhausen, Paul; Inman, Daniel J.

doi:10.2514/1.c031110

Cited by 18 publications

(12 citation statements)

References 31 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The peak pitching moment decreases when the angle of crosswind increases. These results have similar tendencies as the results of Ohanian and Karni 10) and Mort and Yaggy. 23) A positive pitching moment is generated by the crosswind.…”

Section: Aerodynamic Characteristicssupporting

confidence: 89%

See 1 more Smart Citation

Aerodynamic Analysis of the Ducted Fan for a VTOL UAV in Crosswinds

Ryu

Cho

2016

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

An aerodynamic analysis of a ducted fan for vertical take-off and landing unmanned aerial vehicles was performed using computational simulation. A commercial computational fluid dynamics tool was used to solve the Reynolds-averaged Navier-Stokes equations. The calculated results were validated in the subsonic wind tunnel at Hanyang University. The objective of this study is to investigate the aerodynamic performance of a ducted fan in crosswinds. The thrust, normal and side forces of the ducted fan are affected by the velocity magnitude and in-flow angle of the crosswind. The pitching moment of the ducted fan is significantly influenced by the crosswind due to asymmetric lift force created by the difference in suction velocity magnitude on the duct lip. Flow separation at the duct lip occurs under hovering and crosswind conditions. The inlet flow fields of the ducted fan are distorted by the duct lip separation. In conclusion, to improve the stability of the ducted fan, the pitching moment must be reduced.

show abstract

Section: Aerodynamic Characteristicssupporting

confidence: 89%

“…Performance of the ducted fan unit can be adversely affected in transition or crosswind. 5,10) Flow separation can also affect the inlet lip of a ducted fan. To overcome unstable flight, control devices for the ducted fan can be adopted in the vehicle and the duct lip shape can be modified.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Analysis of the Ducted Fan for a VTOL UAV in Crosswinds

Ryu

Cho

2016

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

show abstract

“…NA -N Panel method validation available Graf et al (31) 5 10(11.25) NA NA NA NA -N Lip shape and control methods study Akturk et al (32) NA 5 0.25 NA NA NA -N PIV measurements Ohanian et al (66) NA NA NA NA NA NA -N Synthetic jet Akturk and Camci (34) NA 23.6 0.28 A NA A -N Tip clearance study Rhee et al (35) 4.65 9.5 0.21…”

Section: Namentioning

confidence: 99%

“…Actively morphing the duct geometry would be a much better solution for controlling flow separation. Ohanian et al (66) and Kondor and Moore (67) applied synthetic jets at the inlet and outlet to insert momentum into the boundary layer, thereby triggering or suppressing flow separation. Further, inlet flow separation can be used to decrease the thrust.…”

Section: Cross-wind Effectsmentioning

confidence: 99%

Review on ducted fans for compound rotorcraft

Zhang

Barakos

2020

Aeronaut. j.

View full text Add to dashboard Cite

This paper presents a survey of published works on ducted fans for aeronautical applications. Early and recent experiments on full- or model-scale ducted fans are reviewed. Theoretical studies, lower-order simulations and high-fidelity CFD simulations are also summarised. Test matrices of several experimental and numerical studies are compiled and discussed. The paper closes with a summary of challenges for future ducted fan research.

show abstract

“…The attitude control is the key problem in the ducted fan UAV control, and it will affect the vehicle's other actions. In the flight, because the vehicle's flow field is complex [8][9][10][11][12][13], the nonlinear effect is obvious [14][15][16][17], and these will be big problems in the vehicle's control. In references [18,19], an evolutionary pinning control is put toward which is applied in unmanned aerial vehicle coordination.…”

Section: Introductionmentioning

confidence: 99%

RobustD-Stability Controller Design for a Ducted Fan Unmanned Aerial Vehicle

Ren

Wang

2014

Mathematical Problems in Engineering

View full text Add to dashboard Cite

This paper deals with the aerodynamic modeling of a small ducted fan UAV and the problem of attitude stabilization when the parameter of the vehicle is varied. The main aerodynamic model of the hovering flight UAV is first presented. Then, an attitude control is designed from a linearization of the dynamic model around the hovering flight, which is based on theH∞output feedback control theory withD-stability. Simulation results show that such method has good robustness to the attitude system. They can meet the requirements of attitude control and verify further the feasibility of such a control strategy.

show abstract

Ducted-Fan Force and Moment Control via Steady and Synthetic Jets

Cited by 18 publications

References 31 publications

Aerodynamic Analysis of the Ducted Fan for a VTOL UAV in Crosswinds

Aerodynamic Analysis of the Ducted Fan for a VTOL UAV in Crosswinds

Review on ducted fans for compound rotorcraft

RobustD-Stability Controller Design for a Ducted Fan Unmanned Aerial Vehicle

Contact Info

Product

Resources

About