Parametric Study of Synthetic-Jet-Based Control for Performance Enhancement of a Vertical Tail

Rathay, Nicholas; Boucher, Matthew J.; Amitay, Michael; Whalen, Edward A.

doi:10.2514/1.j052887

Cited by 26 publications

(18 citation statements)

References 33 publications

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“…Selecting α 3 with different values, we obtain the following table of Ω(α 3 ), Ω(α 2 ) and Ω 3 (α 1 ): Table 1 Values of Ω(α 3 ), Ω(α 2 ) and Ω(α 1 ) with respect to α 3…”

Section: Frequency Characteristic With Different ε and αmentioning

confidence: 99%

“…Define (x, y, z) and (ẋ,ẏ,ż) as the position of center of gravity and the velocity to frame Ξ g , body force F ∈ ℜ 3 and torque τ ∈ ℜ 3 . The total external force F consists of the thrust F c generated by the jet engine, aerodynamic forces on the fixed wing F w , aerodynamic forces on the fuselage F f , the forces created by the verticals F v , the forces created by the elevators F e , and uncertainties and external disturbances F d .…”

Section: ) Coordinates and Framesmentioning

confidence: 99%

“…Unmanned jet aircraft control has been an active area of investigation for several years, and some inertial sensors were used and supplemented by GPS [1,2,3]. This interest was motivated by the enormous military and civil applications of such aircraft.…”

Section: Introductionmentioning

confidence: 99%

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Navigation and Control Based on Integral-Uncertainty Observer for Unmanned Jet Aircraft

Wang

Cai

2017

IEEE Trans. Aerosp. Electron. Syst.

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A note on versions:The version presented here may differ from the published version or from the version of record. If you wish to cite this item you are advised to consult the publisher's version. Please see the repository url above for details on accessing the published version and note that access may require a subscription. This article has been accepted for publication in a future issue of this journal, but has not been fully edited. Content may change prior to final publication. Abstract: A nonlinear integral-uncertainty observer is presented, which can estimate the integral of measurement output signal and the uncertainty in system, synchronously. In order to be satisfied with the existing hardware computational environments and to select the parameters more easily, a simplified linear version of the nonlinear integral-uncertainty observer is also developed. The effectiveness of the proposed observers are verified through the numerical simulations and experiments: i) through the integral-uncertainty observers, the attitude angle and the uncertainties in attitude dynamics are estimated synchronously from the measurements of angular velocity, and the estimate results by the two observers are compared; ii) a control law is designed based on the observers to drive the jet aircraft to track a reference trajectory.

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“…Selecting α 3 with different values, we obtain the following table of Ω(α 3 ), Ω(α 2 ) and Ω 3 (α 1 ): Table 1 Values of Ω(α 3 ), Ω(α 2 ) and Ω(α 1 ) with respect to α 3…”

Section: Frequency Characteristic With Different ε and αmentioning

confidence: 99%

Section: ) Coordinates and Framesmentioning

confidence: 99%

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Navigation and Control Based on Integral-Uncertainty Observer for Unmanned Jet Aircraft

Wang

Cai

2017

IEEE Trans. Aerosp. Electron. Syst.

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“…The experiments of Rathay 15 and Rathay et al 16,17 , which are the motivation of the present work, focused on understanding the effect of various synthetic jet parameters on the performance enhancement of 1/19 th scale and 1/9 th scale vertical tail models based on the geometry of a Boeing 767. The smaller 1/19 th scale model was named the Beta model and the larger 1/9 th scale model named the Gamma model (a prior model was named the Alpha model 17 ).…”

Section: A Previous Work At Rpimentioning

confidence: 99%

“…Research specific to the vertical tail has been carried out by the University of Arizona, NASA, and Boeing, in addition to the work performed at RPI 15,16,17,18 . Seele et al 19,20 investigated the use of sweeping jet actuators on the same 1/9 th scale model (discussed further below) used by Rathay 15 and Rathay et al 18 and showed that the sweeping jets substantially increased the side force as much as 50% (albeit, at much larger momentum coefficient than tested at RPI) for a large number of test conditions.…”

Section: Introductionmentioning

confidence: 99%

Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

Monastero

Amitay

2016

8th AIAA Flow Control Conference

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Synthetic-jet-based active flow control for separation control over a vertical tail is an ongoing area of research, the goal of which is reducing the size of the vertical tail on commercial airplanes. Before placing the actuators on an airplane, a detailed understanding of the effect different jets and test parameters have on side force enhancement must be obtained. Previous work investigated the performance enhancement of 1/19 th scale and 1/9 th scale vertical tail models and showed that the side force could be augmented by as much as 34%. The authors found an unexpected relationship between jet spacing (and number of jets) and side force enhancement that did not agree between the two models, where, under specific conditions, increasing the spacing between actuators increased the side force on the larger 1/9 th scale model while decreasing it on the smaller 1/19 th scale model. To further understand the interactions among jets as spacing varied, a new model was designed and tested in the Rensselaer Polytechnic Institute (RPI) Subsonic Wind Tunnel. The model was designed such that it is capable of varying sweep angle, rudder characteristics (chord length and deflection), and various actuator parameters. The experiments discussed in this paper focus on the unswept case with the rudder at a moderate deflection angle of 20 o and the sensitivity of the side force produced by the unswept model to different parameters. The flow field around the new model was first characterized using particle image velocimetry and pressure measurements. The effect of synthetic jet flow control was found to significantly modify the pressure distribution globally around the model, which resulted in up to 17% improvement in the side force. The effect of sideslip angle and jet spacing were also studied and found to agree with the trends observed in previous work. The work discussed here is the foundation for continuing tests on a swept configuration of the model. These future tests will study how the addition of spanwise flow and variations in separation severity affect the performance trends as spacing is varied. Nomenclature= area-based momentum coefficient produced by a single jet c = total chord c r = rudder chord F + = non-dimensional actuation frequency n = number of active jets in the array Re c = chord-based Reynolds number S = model planform area

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A parametric study of rectangular jets issuing into a laminar crossflow

2023

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Parametric Study of Synthetic-Jet-Based Control for Performance Enhancement of a Vertical Tail

Cited by 26 publications

References 33 publications

Navigation and Control Based on Integral-Uncertainty Observer for Unmanned Jet Aircraft

Navigation and Control Based on Integral-Uncertainty Observer for Unmanned Jet Aircraft

Performance Enhancement of an Airfoil Model with a Control Surface using Synthetic Jets

A parametric study of rectangular jets issuing into a laminar crossflow

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