Longitudinal Manoeuvre Load Control of a Flexible Large-Scale Aircraft

Burlion, Laurent; Poussot-Vassal, Charles; Vuillemin, Pierre; Leitner, Martin; Kier, Thiemo

doi:10.3182/20140824-6-za-1003.01588

Cited by 10 publications

(7 citation statements)

References 12 publications

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“…Second, (ii) 5 Indeed, in the context of this study, this attenuation will lead to wing root bending moment minimization which is immediately linked to the mass at the wing/fuselage junction. In a more general framework of the actual civilian aircraft research, one objective is to the increase of the laminar flow working zone which are central objectives in consumption optimization [16]. 6 The H∞-norm, with appropriated weighting functions can also minimizes the root mean square over the frequency range Ω (see Section III).…”

Section: B Contributionsmentioning

confidence: 99%

“…Remark 3 (About optimality conditions): The truncation performed when applying the SVD in (16) does not guarantee the so-called H 2 -optimality conditions of the projected model (see e.g. [22]).…”

Section: A First Approach: Frequency-domain Matrix Function Interpolmentioning

confidence: 99%

“…Application to the WT data. For the considered application, Algorithm 1 has been involved with N = 292 sampled data points, n y = 3 outputs (acceleration at stations #4, #12 and #15) and n u = 2 inputs (wind gust and actuator) and a sample frequency f s = 4096Hz 16 . When applying Algorithm 1, the considered LMI region is an ellipse defined by the constraint (27) with a = 1, b = 0.92 and c 0 = 0.…”

Section: Algorithm 1 Subspace With Lmi Constraintsmentioning

confidence: 99%

See 2 more Smart Citations

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

Poussot-Vassal

Demourant

Lepage

et al. 2017

IEEE Trans. Contr. Syst. Technol.

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One important element in the progression of aircraft environmental impact reduction is to reduce their overall weight (without impacting other consumption-oriented performance index, such as drag). In addition to the numerous work conducted in material and structural engineering, from a control viewpoint, this challenge is strongly connected to the need of the development and assessment of dedicated load control strategies in response to gust disturbances. Indeed, the load factors due to gust are considered as a sizing criteria during the aircraft conception steps and require specific verification according to the certification process. To this end, a dedicated experimental research program based on Wind Tunnel (WT) campaigns has been carried out. More specifically, the paper contributions are twofold: (i) to identify the gust load effect using two different versatile frequency-domain techniques, namely the Loewner interpolation and a modified subspace approach, and (ii) to design and implement an active closed-loop control to alleviate the gust main effect. The entire procedure is validated in a wind tunnel setup , involving a gust generator device and a 2D aeroelastic airfoil, for varying configuration travelling from sub to transonic airflow and varying angles of attack, emphasizing the effectiveness and robustness of the overall approach.

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Section: B Contributionsmentioning

confidence: 99%

Section: A First Approach: Frequency-domain Matrix Function Interpolmentioning

confidence: 99%

Section: Algorithm 1 Subspace With Lmi Constraintsmentioning

confidence: 99%

See 1 more Smart Citation

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

Poussot-Vassal

Demourant

Lepage

et al. 2017

IEEE Trans. Contr. Syst. Technol.

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“…In this paper, we propose a novel UAV obstacle avoidance technique which uses the OIST methodology. OIST means Output to Input Saturation Transformation ; it was first detailed in [9] and further applied to visual servoing [10], [11] or load control alleviation of a civil aircraft [12]. Its core idea is to reformulate expected bounds on a regulated variable into saturations on the control input.…”

Section: Introductionmentioning

confidence: 99%

UAV obstacle avoidance scheme using an output to input saturation transformation technique

Chauffaut

Defaÿ

Burlion

et al. 2016

2016 International Conference on Unmanned Aircraft Systems (ICUAS)

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This paper presents a novel obstacle avoidance scheme for UAVs. This scheme is based on the use of a technique recently developed by one of the authors, which is based on a transformation of a variable constraint into an input saturation. In the case of obstacle avoidance, this saturation is designed so as to ensure a safe trajectory around the obstacles, offering a proof of this desired behavior. A low-cost RGB-D sensor has been used to detect obstacles as its output measurements of the environment are effortlessly interpreted even with a low power embedded processor. Experimental results are provided, together with a simulation, to prove the efficiency of the approach.

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“…Although being conservative, this Onera -The French Aerospace Lab, F-31055 Toulouse, France, Emmanuel.Chambon@onera.fr approach has been successfully tested on an uncertain rigid launch vehicle model with unknown wind input. Other successful applications of Output to Input Constraint Transformation (OIST) include visual servoing applied to a loworder known UAV model [6] and longitudinal load control of an aircraft [7] where a known linear large-scale model is considered.…”

Section: Introductionmentioning

confidence: 99%

Robust output interval constraint using O/I saturation transformation with application to uncertain linear launch vehicle

Chambon

Burlion

Apkarian

2015

2015 European Control Conference (ECC)

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In this article, we consider the case where a regulated output of an uncertain system with unknown disturbance input is constrained to lie between two specified timevarying bounds. We suppose a controller has already been designed using any desired technique. This controller may not satisfy expected output constraints. The objective is to design saturations on the control signal so that the closed-loop is altered only when those specifications are not met. The theory is presented in the linear case with linear dependence on an unknown disturbance. Application to an uncertain launcher linear model with unknown wind disturbance is presented.

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Longitudinal Manoeuvre Load Control of a Flexible Large-Scale Aircraft

Cited by 10 publications

References 12 publications

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

Gust Load Alleviation: Identification, Control, and Wind Tunnel Testing of a 2-D Aeroelastic Airfoil

UAV obstacle avoidance scheme using an output to input saturation transformation technique

Robust output interval constraint using O/I saturation transformation with application to uncertain linear launch vehicle

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