Forebody vortex control for suppressing wing rock on a highly-swept wing configuration

Suarez, Carlos J.; Kramer, Brian R.; Ayers, Bert F.; Malcolm, Gerald N.

doi:10.2514/6.1992-2716

Cited by 13 publications

(7 citation statements)

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“…The primary causes of wing rock are the interactions between the forebody and the wing vortices at high angle of attack. 10 This has been verified using video-based experimental investigation for wing rock of sharp-edged delta wings with leading-edge sweep angles of 70 o and 80 o . 11 In order to predict roll divergence as well as other characteristics in the oscillation, a highly nonlinear analytical models of wing rock has been developed.…”

Section: Wing Rock Suppression Of Slender Delta Wingmentioning

confidence: 69%

Sensitivity Analysis of Disturbance Accommodating Control with Kalman Filter Estimation

Georgeand

2007

AIAA Guidance, Navigation and Control Conference and Exhibit

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The design of controllers that can automatically compensate the effects of uncertain disturbances in a system has become an important topic in modern control engineering. The general theory of disturbance accommodating control provides a method for designing feedback controllers which automatically detect and minimizes the effect of waveformstructured disturbances. This approach has been applied on linear systems with small modeling errors and uncertainties. Based on the disturbance accommodating control theory, a control technique for nonlinear systems with time-varying modeling errors and uncertainties is presented in this paper. This control approach exploits an Extended Kalman Filter for the simultaneous estimation of the system states and the uncertain disturbances. Validity of this control approach is verified by implementing the proposed technique on a highly nonlinear wing-rock system. The simulation results indicated that the closed-loop stability of the controlled system is extremely sensitive to the user selected process noise covariance value. A Lyapunov stability analysis is conducted on a controlled linear system, which reveals a lower bound requirement on the process noise covariance norm to facilitate the asymptotic stability of the closed-loop system. This lower bound on the process noise covariance norm depends on the model uncertainties, external disturbances and the amount of noise associated with the measurements.

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Section: Wing Rock Suppression Of Slender Delta Wingmentioning

confidence: 69%

Sensitivity Analysis of Disturbance Accommodating Control with Kalman Filter Estimation

Georgeand

2007

AIAA Guidance, Navigation and Control Conference and Exhibit

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“…The primary causes of wing rock are the interactions between the forebody and the wing vortices at high angles of attack. 17 This has been verified using a video-based experimental investigation for wing rock of sharp-edged delta wings with leading-edge sweep angles of 70°and 80°, which also suggests that the limit cycle behavior is due to the relative phasing between model oscillations and vortex movements. 18 Analytical models of this highly nonlinear phenomenon have been developed and used to predict roll divergence as well as other characteristics in the oscillations, such as the period and amplitude of the oscillations.…”

Section: Wing Rock Suppressionmentioning

confidence: 70%

Robust Control of Nonlinear Systems Using Model-Error Control Synthesis

Crassidis

1999

Journal of Guidance, Control, and Dynamics

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A new approach for the robust control of nonlinear systems is presented. This approach employs an optimal real-time nonlinear estimator to determine model error corrections to the control input using a one time-step ahead technique. Control compensation is achieved by using the estimated model error as a signal synthesis adaptive correction to the nominal control input so that maximum performance is achieved in the face of extreme model uncertainty and disturbance inputs. A significant advantage of this approach over other adaptive methods is that model parameters need not be updated online. Instead, the effects of these errors are used to update the actual control signal, which leads to a simple design strategy. The model-error control synthesis approach is used in conjunction with a variable structure controller to suppress the wing-rock motion of a slender delta wing. Simulation results indicate that the model-error control synthesis approach is extremely effective in providing closed-loop robustness in the face of significant model uncertainties and disturbance inputs.

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“…Ng and Malcolm used forebody strakes 57 and steady blowing and suction 52 over a slender delta wing (Ã ¼ 78 ) space-plane model and found that the wing rock can be suppressed by relocating or altering the strength of the forebody vortices. A similar space-plane model was also studied by Suarez et al, 53 who discovered that by applying pulse-blowing with frequency, that is, 2-3 times the wing rock frequency, optimum attenuation can be achieved. Moreover, the full length tangential leading-edge blowing on a double delta configuration was tested by Wong et al 54 It emerged that the blowing technique effectively altered the position and strength of the leading-edge vortices and hence the roll oscillations were suppressed at high angle of attack.…”

Section: Control Of Slender Wing Rockmentioning

confidence: 83%

“…As aforementioned, self-induced roll oscillations can occur in various LAR planforms regardless of whether they are delta or non-delta, slender or nonslender planforms. Earlier studies focused on suppressing the roll oscillations of slender delta wings and regarding these, both active [52][53][54][55][56] and passive [57][58][59][60] flow control techniques were applied. Ng and Malcolm used forebody strakes 57 and steady blowing and suction 52 over a slender delta wing (Ã ¼ 78 ) space-plane model and found that the wing rock can be suppressed by relocating or altering the strength of the forebody vortices.…”

Section: Control Of Slender Wing Rockmentioning

confidence: 99%

Review of self-induced roll oscillations and its attenuation for low-aspect-ratio wings

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Micro aerial vehicles are currently receiving growing interest because of their broad applications in many fields. In their flight tests, the onset of unwanted large amplitude roll oscillations was reported, which resulted in difficulties with flight control, and this has become one of the major challenges of current micro aerial vehicles design. In this review type of article, the low Reynolds number flow characteristics of a low-aspect-ratio wing are reviewed, and the self-induced roll oscillations are discussed with special attention being payed to the interaction between the three-dimensional flow structure and wing in reciprocatively rolling motion. The roll attenuation methods are introduced via flow control approaches, which can suppress the roll oscillations effectively by manipulating the leading-edge flow separation and tip vortices of the low-aspect-ratio wings.

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Forebody vortex control for suppressing wing rock on a highly-swept wing configuration

Cited by 13 publications

References 0 publications

Sensitivity Analysis of Disturbance Accommodating Control with Kalman Filter Estimation

Sensitivity Analysis of Disturbance Accommodating Control with Kalman Filter Estimation

Robust Control of Nonlinear Systems Using Model-Error Control Synthesis

Review of self-induced roll oscillations and its attenuation for low-aspect-ratio wings

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