Gust Load Alleviation for a Regional Aircraft Through a Static Output Feedback

Fonte, Federico; Ricci, Sergio; Mantegazza, Paolo

doi:10.2514/1.c032995

Cited by 47 publications

(15 citation statements)

References 36 publications

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“…The calculation results of an Airbus 300 aircraft indicated that the NID control logic works effectively in the aircraft trajectory control during the penetration of wind shear. Fonte, et al (199) designed a symmetric, active GLA system for a regional transport aircraft based on a static output feedback (SOF) with a constrained structure. The control surfaces of two ailerons and the elevator were taken into consideration.…”

Section: Analytical Investigationsmentioning

confidence: 99%

Gust loads on aircraft

Cao

Ismail

2019

Aeronaut. j.

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An important prerequisite for the design, assessment and certification of aircraft and their associated control systems is a quantitative specification of the environment in which the aircraft is intended to operate, for example, atmospheric gust. Gust loads on aircraft may induce detrimental influences such as increased aerodynamic and structural loads, structural deformation and decreased flight dynamic performance. This paper presents a systematic and comprehensive overview of important concepts and applications of gust loads on aircraft. This overview includes a brief research background, concepts, research techniques, influences and load alleviation measures of gust. Finally, we summarise some potential improvements in the future work. It is also recommended to learn from previous experiences to avoid aviation accidents due to flight through atmospheric gusts and turbulence.

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Section: Analytical Investigationsmentioning

confidence: 99%

Gust loads on aircraft

Cao

Ismail

2019

Aeronaut. j.

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“…However, this does not adversely a↵ect our main conclusions because our approach leads to similar structural component thickness distributions to those obtained from studies that include more load conditions [11,12]. Furthermore, active maneuver and gust load alleviation systems could potentially reduce the need to include many critical structural load cases [13]. It is important to note that our objective in the present work is to study the main trends, not to perform detailed wing design.…”

Section: Nasa Had Experimentally Investigated the Drooped Wing Concepmentioning

confidence: 79%

Aerostructural Optimization of Drooped Wings

Khosravi

Zingg

2018

Journal of Aircraft

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Through aerostructural optimization, this paper presents progress towards characterizing the potential e ciency gains of drooped wings for commercial aircraft in transonic flight. The drooped wing is a nonplanar configuration with downward spanwise camber from the wing root to the tip. The aerostructural optimization cases include two load conditions: cruise and 2.5g. The single 2.5g maneuver load condition is used for structural sizing of the wing. In all cases, the projected span of the wing remains unchanged. The results show that such a wing has the potential to improve aircraft range by 2.6% relative to an optimized planar wing of the same projected span. The reason is that the drooped wing pushes the tip vortex further away than the planar wing and increases the projected span at the deflected state. Furthermore, if the drooped wing is permitted to have curved leading and trailing edges, a 4.9% range improvement in comparison to an optimized planar wing with straight leading and trailing edges is possible by further reducing wing weight and wave drag.

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“…However, the dependence of the unsteady aerodynamic forces on the second time derivative resulting from the classical RFA fit [4] for compressible flow may be seen as a low frequency residualization of its high frequency behaviour [41]. In this work, a residualization of the aerodynamic forces is also done in the limit of s → ∞ when considering compressible flow, see Section 3.1.…”

Section: Application To Unsteady Incompressible Flowmentioning

confidence: 99%

A Generalized State-Space Aeroservoelastic Model Based on Tangential Interpolation

2019

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In this work, a new approach for the generation of a generalized state-space aeroservoelastic model based on tangential interpolation is presented. The resulting system of differential algebraic equations (DAE) is reduced to a set of ordinary differential equations (ODE) by residualization of the non-proper part of the transfer function matrix. The generalized state-space is of minimal order and allows for the application of the force summation method (FSM) for the aircraft loads recovery. Compared to the classical rational function approximation (RFA) approach, the presented method provides a minimal order realization with exact interpolation of the unsteady aerodynamic forces in tangential directions, avoiding any selection of poles (lag states). The new approach is applied first for the generation of an aerodynamic model for the bidimensional unsteady incompressible flow in the time domain. Next, an application on the generation of an aeroservoelastic model for loads evaluation of the flutter reduced order assessment (FERMAT) model under atmospheric disturbances is done, showing an excellent agreement with the reference model in the frequency domain. The proposed aeroservoelastic model of minimal order is suited for loads analysis and multivariable control design, and an application to a gust loads alleviation (GLA) strategy is shown.

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Gust Load Alleviation for a Regional Aircraft Through a Static Output Feedback

Cited by 47 publications

References 36 publications

Gust loads on aircraft

Gust loads on aircraft

Aerostructural Optimization of Drooped Wings

A Generalized State-Space Aeroservoelastic Model Based on Tangential Interpolation

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