Flow Structure Modification Using Plasma Actuation for Enhanced UAV Flight Control

Torres, Antonio Jesús Conesa

doi:10.1002/9781118928691.ch16

Cited by 2 publications

(2 citation statements)

References 43 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The research of Zhang and Torres showed that the SJA had a strong ability to control the high-speed flow field (Zhang et al 2018;Torres 2017). The experiments of Neuberger and Wygnanski, Bar Sever and Seifert could confirm the following conclusions: the separation of airflow could be delayed or even prevented completely by the method of synthetic jet (Neuburger and Wygnanski 1988;Bar-Sever 1989;Margalit et al 2005).…”

Section: Introductionmentioning

confidence: 96%

Investigations on the Interfering Factor of Single Synthetic Jet Actuator on Improving the Efficiency of Wing Control Surface

2022

JAFM

View full text Add to dashboard Cite

After the deflection of the wing control surface, flow separation is easily generated at the trailing edge of the wing, which will reduce the lift coefficient and the control surface efficiency. The rudder of the wing is aileron. If the lift generated by the wing is used to improve the efficiency of the control surface, the flow separation caused by the deflection of the control surface must be restrained. Using synthetic jet to change the flow state of boundary layer is the main method to solve the problem of flow separation. Synthetic jet actuator (SJA) has the advantages of no energy loss and simple structure. In this paper, a method of using synthetic jet actuator to suppress the flow separation at the rear of the wing when the aileron deflects is proposed, and the lift coefficient is obtained. The increase of aileron efficiency is calculated by the change of lift coefficient. The EPPLER555 wing with aileron deflection angle of 3°~9° is simulated, and the changes of lift coefficient and aileron efficiency under corresponding working conditions are obtained. The results show that the average lift coefficient of the wing is 0.5 when the deflection angle of the aileron is 3°~9° without SJA. After SJA employed, the lift coefficient will be greatly improved, and the control surface efficiency of EPPLER555 wing will be effectively improved, the lift coefficient will increase by about 20% to 0.6-0.7. For example, when the deflection angle of aileron is 4°, using a SJA with a maximum outlet velocity of 200m/s and an excitation frequency of 400/2π, the effective lift coefficient generated by the wing is 0.5931. Under the effect of SJA, the control surface efficiency of EPPLER555 wing will be effectively improved. The lift coefficient is reflected by the ratio of the change of lift coefficient after SJA employed to the lift coefficient without synthetic jet actuator.

show abstract

Section: Introductionmentioning

confidence: 96%

Investigations on the Interfering Factor of Single Synthetic Jet Actuator on Improving the Efficiency of Wing Control Surface

2022

JAFM

View full text Add to dashboard Cite

show abstract

“…In the field of flight control, Marques and Pascual [7] studied the feasibility of PSJ in flight control. Zhang et al [8] and Torres [9] found that the PSJ has a strong ability to control the high-speed flow field. Seifert et al [22] describes a series of experiments that enabled a flight demonstration of roll-control without moving control surfaces.…”

Section: Introductionmentioning

confidence: 99%

Active Flow Control Based on Plasma Synthetic Jet for Flapless Aircraft

et al. 2021

View full text Add to dashboard Cite

Active flow control (AFC) based on plasma synthetic jet actuator (PSJA) has been attracted a lot of researchers since Anderson and Knight put forward the concept of PSJA for the first time. Since then the characteristic of PSJA has been studied by means of many numerical simulations and experiments. This article showed a series of studies that manipulated a vehicle without moving control surfaces. Firstly, we research the characteristics of the aviation actuator, including the effects of structure and parameters on performance. Secondly, we explore the influence of the actuator on the air field around the aircraft by simulation, including the influence of the actuator on the aerodynamic coefficients and pitching moment coefficient. Finally, since these changes are similar to those caused by the deflection of the rudder surface, we can equivalent the effect of the PSJA to the deflection of the rudder surface, and simulate the threedegree-of-freedom pitch control channel of the aircraft to illustrate the effectiveness of PSJA on the flapless control system.INDEX TERMS Plasma synthetic jet actuator, active flow control, flapless control system.

show abstract

Flow Structure Modification Using Plasma Actuation for Enhanced UAV Flight Control

Cited by 2 publications

References 43 publications

Investigations on the Interfering Factor of Single Synthetic Jet Actuator on Improving the Efficiency of Wing Control Surface

Investigations on the Interfering Factor of Single Synthetic Jet Actuator on Improving the Efficiency of Wing Control Surface

Active Flow Control Based on Plasma Synthetic Jet for Flapless Aircraft

Contact Info

Product

Resources

About