Model Predictive Control Architectures for Maneuver Load Alleviation in Very Flexible Aircraft

Pereira, Mateus d. Virgilio; Kolmanovsky, Ilya; Cesnik, Carlos E. S.; Vetrano, Fabio

doi:10.2514/6.2019-1591

Cited by 7 publications

(3 citation statements)

References 23 publications

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“…Therefore, from the perspective of control design, the actuator system cannot satisfy multiple objectives simultaneously. Generally, the typical approach is to separate the control tasks over the available control surfaces when control design must address multiple objectives [35,36]. To prevent conflicts between various tasks such as pitch control, roll control or load alleviation, the control surfaces are either assigned to specific tasks [37].…”

Section: Distributed Morphingmentioning

confidence: 99%

Morphing wing design using integrated and distributed trailing edge morphing

Mkhoyan

Thakrar

DeBreuker

et al. 2022

Smart Mater. Struct.

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The presented study investigates the design and development of an autonomous morphing wing concept developed in the scope of the SmartX project, which aims to demonstrate in-flight performance optimisation with active morphing. To progress this goal, a novel distributed morphing concept with six translation induced camber morphing trailing edge modules is proposed in this study. The modules are interconnected using elastomeric skin segments to allow seamless variation of local lift distribution along the wingspan. A fluid-structure interaction optimisation tool is developed to produce an optimised laminate design considering the ply orientation, laminate thickness, laminate properties and actuation loads of the module. Analysis of the kinematic model of the integrated actuator system is performed, and a design is achieved, which meets the required continuous load and fulfils both static and dynamic requirements in terms of bandwidth and peak actuator torque with conventional actuators. The morphing design is validated using digital image correlation measurements of the morphing modules. Characterisation of mechanical losses in the actuator mechanism is performed. Out-of-plane deformations in the bottom skin and added stiffness of the elastomer are identified as the impacting factors of the reduced tip deflection.

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Section: Distributed Morphingmentioning

confidence: 99%

Morphing wing design using integrated and distributed trailing edge morphing

Mkhoyan

Thakrar

DeBreuker

et al. 2022

Smart Mater. Struct.

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“…By contrast, Ref. [8] uses a linear model predictive controller (MPC) and a linear quadratic regulator (LQR) to satisfy the load constraints at various critical locations. In Ref.…”

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

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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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“…Model predictive control is experiencing a growing interest for aeroelastic applications for the versatility and ease with which constraints (on states and/or inputs) can be handled [7]. It has widely been used both in gust and manoeuvre load alleviation [8][9][10] and in trajectory tracking [11] problems. However, linearisation of the discretised state-space representation of aeroelastic systems about a reference steady state or a sequential linearisation about the instantaneous configuration has been the main strategy when applying MPC to date.…”

mentioning

confidence: 99%

Aeroelastic Control and Estimation with a Minimal Nonlinear Modal Description

et al. 2021

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Modal-based, nonlinear Moving Horizon Estimation (MHE) and Model Predictive Control (MPC) strategies for very flexible aeroelastic systems are presented. They are underpinned by an aeroelastic model built from a 1D intrinsic (based on strains and velocities) description of geometrically-nonlinear beams and an unsteady Vortex Lattice aerodynamic model. Construction of a nonlinear, modal-based, reduced order model of the aeroelastic system, employing a state-space realisation of the linearised aerodynamics around an arbitrary reference point, allows us to capture the main nonlinear geometrical couplings at a very low computational cost.

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Model Predictive Control Architectures for Maneuver Load Alleviation in Very Flexible Aircraft

Cited by 7 publications

References 23 publications

Morphing wing design using integrated and distributed trailing edge morphing

Morphing wing design using integrated and distributed trailing edge morphing

Seamless Active Morphing Wing Simultaneous Gust and Maneuver Load Alleviation

Aeroelastic Control and Estimation with a Minimal Nonlinear Modal Description

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