Gust Load Alleviation Flight Control System Design for a SensorCraft Vehicle

Vartio, Eric; Shaw, E.; Vetter, Travis K.

doi:10.2514/6.2008-7192

Cited by 14 publications

(6 citation statements)

References 2 publications

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“…III, experimental results have demonstrated the effectiveness of INDI-QP-V in GLA, MLA, and simultaneous GLA and MLA tasks. In the literature, the LQG control is one of the most popular methods for load alleviation [10,13,30,35]. Therefore, the proposed INDI-QP-V control will be compared with LQG control.…”

Section: Comparisons With Linear Quadratic Gaussian Controlmentioning

confidence: 99%

“…[9], the nonlinear flexible aircraft model is linearized successively, and then MPC controllers are designed at every linearization point. A linear quadratic Gaussian (LQG) control is designed for a SensorCraft vehicle GLA problem in [10]. Besides, a wind tunnel experiment for alleviating the gust loads of a flexible wing with piezoelectric control is presented in [11].…”

Section: Introductionmentioning

confidence: 99%

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Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Wang

Mkhoyan

et al. 2021

Journal of Guidance, Control, and Dynamics

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This paper deals with the simultaneous gust and maneuver load alleviation problem of a seamless active morphing wing. The incremental nonlinear dynamic inversion with quadratic programming control allocation and virtual shape functions (denoted as INDI-QP-V) is proposed to fulfill this goal. The designed control allocator provides an optimal solution while satisfying actuator position constraints, rate constraints, and relative position constraints. Virtual shape functions ensure the smoothness of the morphing wing at every moment. In the presence of model uncertainties, external disturbances, and control allocation errors, the closed-loop stability is guaranteed in the Lyapunov sense. Wind tunnel tests demonstrate that INDI-QP-V can make the seamless wing morph actively to resist "1-cos" gusts and modify the spanwise lift distribution at the same time. The wing root shear force and bending moment have been alleviated by more than 44% despite unexpected actuator fault and nonlinear backlash. Moreover, during the experiment, all the input constraints were satisfied, the wing shape was smooth all the time, and the control law was executed in real time. Furthermore, as compared with the linear quadratic Gaussian control, the hardware implementation of INDI-QP-V is easier; the robust performance of INDI-QP-V is also superior.

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Section: Comparisons With Linear Quadratic Gaussian Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Wang

Mkhoyan

et al. 2021

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

show abstract

“…III, experimental results have demonstrated the effectiveness of INDI-QP-V in GLA, MLA and simultaneous GLA and MLA tasks. In the literature, the Linear Quadratic Gaussian (LQG) control is one of the most popular methods for load alleviation [10,13,28,32]. Therefore, the proposed INDI-QP-V control will be compared to LQG control.…”

Section: Comparisons With Linear Quadratic Gaussian Controlmentioning

confidence: 99%

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Wang

Mkhoyan

et al. 2020

Preprint

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This paper deals with the simultaneous gust and maneuver load alleviation problem of a seamless active morphing wing. The incremental nonlinear dynamic inversion with quadratic programming control allocation and virtual shape functions (denoted as INDI-QP-V) is proposed to fulfill this goal. The designed control allocator provides an optimal solution while satisfying actuator position constraints, rate constraints, and relative position constraints. Virtual shape functions ensure the smoothness of the morphing wing at every moment. In the presence of model uncertainties, external disturbances, and control allocation errors, the closed-loop stability is guaranteed in the Lyapunov sense. Wind tunnel tests demonstrate that INDI-QP-V can make the seamless wing morph actively to resist "1-cos" gusts and modify the spanwise lift distribution at the same time. The wing root shear force and bending moment have been alleviated by more than 44 % despite unexpected actuator fault and nonlinear backlash. Moreover, during the experiment, all the input constraints were satisfied, the wing shape was smooth all the time, and the control law was executed in real time. Furthermore, as compared to the linear quadratic Gaussian (LQG) control, the hardware implementation of INDI-QP-V is easier; the robust performance of INDI-QP-V is also superior.

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“…achieved in overall design, aerodynamics, structure, aeroelasticity, flight control, prototype manufacturing, and flight testing of scaled prototypes [1][2][3][4][5].…”

mentioning

confidence: 99%

Gust Alleviation by Active–Passive Combined Control of the Flight Platform and Antenna Array for a Flying Wing SensorCraft

Hao

Wang³

et al. 2023

Aerospace

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SensorCraft is an intelligence, surveillance, and reconnaissance (ISR) system that integrates unmanned flight platforms and airborne antenna arrays. Under gust loads, the high–aspect–ratio, light–wing structure of SensorCraft has considerable bending and torsion deformation, affecting the flight performance of unmanned flight platforms and leading to the loss of antenna arrays’ electromagnetic performance. Taking SensorCraft as the background, a wing conformal antenna array was designed, an aircraft model with a passive wingtip device was established, a control law was developed by the LQG/LTR method, and a gust alleviation active–passive combined control method of a “LQG/LTR active controller + passive wingtip device” was proposed. By constructing an unsteady aerodynamic reduced–order model (ROM) based on the Volterra series and a conformal array pattern fast method based on the modal form, the effectiveness of the gust alleviation active–passive combined control method on the aircraft platform and antenna array was analyzed. The results show that structural deformation of the wing conformal antenna leads to changes in the main lobe gain, beam direction, and sidelobe level. The active–passive gust alleviation method has obvious advantages. Compared with the LQG/LTR active gust alleviation method, the peak value of wingtip displacement is reduced by 15.6%, and the peak value of the gain loss is reduced by 0.72 dB, which is conducive to better performance of the airborne conformal antenna array.

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Gust Load Alleviation Flight Control System Design for a SensorCraft Vehicle

Cited by 14 publications

References 2 publications

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Gust Alleviation by Active–Passive Combined Control of the Flight Platform and Antenna Array for a Flying Wing SensorCraft

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