Parametric reduced order model approach for rapid dynamic loads prediction

Castellani, Michele; Lemmens, Yves; Cooper, Jonathan E.

doi:10.1016/j.ast.2016.02.015

Cited by 14 publications

(4 citation statements)

References 30 publications

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“…There has not been sufficient focus in the literature on using the MOR methods for such solvers. Only recently Castellani et al [18] applied MOR technique to the potential flow based aeroelastic system for rapid prediction of dynamic gust loads. For the determination of critical loads, Castellani et al created a reduced aeroelastic model at different flight points and used interpolation techniques to cover the entire flight envelope.…”

Section: Introductionmentioning

confidence: 99%

Preliminary aeroelastic design of composite wings subjected to critical gust loads

Rajpal

Gillebaart

Breuker

2019

Aerospace Science and Technology

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Including a gust analysis in an optimization framework is computationally expensive as the critical load cases are not known a priori and hence a large number of points within the flight envelope have to be analyzed. Model order reduction techniques can provide significant improvement in computational efficiency of an aeroelastic analysis. In this paper, after thorough analysis of 4 commonly used model order reduction methods, balanced proper orthogonal decomposition is selected to reduce the aerodynamic system which is based on potential flow theory. The reduced aerodynamic system is coupled to a structural solver to obtain a reduced-order aeroelastic model. It is demonstrated that the dominant modes of the aerodynamic model can be assumed to be constant for varying equivalent airspeed and Mach number, enabling the use of a single reduced model for the entire flight envelope. A dynamic aeroelastic optimization method is then formulated using the reduced-order aeroelastic model. Results show that both dynamic and static loads play a role in optimization of the wing structure. Furthermore, the worst case gust loads change during the optimization process and it is important to identify the critical loads at every iteration in the optimization.

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Section: Introductionmentioning

confidence: 99%

Preliminary aeroelastic design of composite wings subjected to critical gust loads

Rajpal

Gillebaart

Breuker

2019

Aerospace Science and Technology

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“…It is noted that a set of time-history curves cannot easily be used to simultaneously display the correlations of the GLA performances between two physical quantities. This issue can be remedied by plotting a convex hull diagram about two physical variables [36]. First, the gust-induced response data for a set of physical quantities are computed by open-and closed-loop simulations, respectively.…”

Section: Gla Control In a Continuous Dryden Gust Fieldmentioning

confidence: 99%

Adaptive Feed-Forward Control for Gust Load Alleviation on a Flying-Wing Model Using Multiple Control Surfaces

Zhang,

Zhao

2023

Aerospace

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Based on measured gust information, a multi-input multi-output (MIMO) adaptive feed-forward control scheme for gust load alleviation (GLA) on a semi-span flying-wing aircraft using multiple control surfaces is proposed. In order to remedy weight drift and biased estimation problems that are commonly encountered in adaptive control, the circular leaky LMS (CLLMS) algorithm is employed, which utilizes gust measurement information, filtered reference signals, and error signals to update controller parameters online. The results demonstrate that good load reductions are achieved in both continuous and discrete gust environments. For instance, the designed GLA control system leads to an 80.72% reduction in the root-mean-square (RMS) values of wing-root bending moment in the Dryden gust environment and a 77.59% reduction of its maximum value in the 1-cos discrete gust condition. Based on the limited power of the actuator and the limited authority for control surface deflections when integrating GLA into the flight control system, a weight-updating algorithm with deflection angle and rate constraints on control surfaces is proposed. The simulation results show that the strict constraints on control surface deflections will degrade the GLA performance. Finally, the influence of the partial jamming fault of actuators on GLA performance is studied. It is found that good GLA performance can be preserved despite the degraded performance during the initial stage of the actuator jamming fault. This is due to the robustness brought about by multiple control surfaces and the adaptability of the control algorithm.

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“…Load-based life monitoring requires real-time fatigue load monitoring for the aircraft structure throughout the service. Much literature currently aims at fatigue load monitoring research on aircraft structures, such as [8][9][10][11]. Overall, they can be divided into two categories.…”

Section: Load-based Individual Aircraft Life Monitoringmentioning

confidence: 99%

“…Load monitoring of aircraft structures is a prerequisite. It can be realized based on flight parameter monitoring systems and strain gauges in critical parts, incorporating techniques such as finite element analysis, multiple linear regression, and artificial neural networks [8][9][10][11]. This lays a solid foundation for individual aircraft life monitoring.…”

Section: Introductionmentioning

confidence: 99%

A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment

Fu,

2023

Machines

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Individual life monitoring is crucial for ensuring aircraft flight safety. Conventional life-consumption-based monitoring methods ignore reliability, thus disjoining them from the aircraft’s reliable life determination and extension, where high confidence and reliability are required. Therefore, this paper proposes a reliable life consumption and individual life monitoring method for aircraft structure fatigue. In the paper, the P-S-N curve, i.e., the relationship between the aircraft structure’s life (N) and fatigue load (S) under a certain probability (P), is established, by which the lower confidence limit of the aircraft structure’s reliable life can be evaluated under any fatigue loads. Based on that and the aircraft’s monitored fatigue loads, the indexes of reliable life consumption and remaining reliable life percentages are proposed and assessed in real time for individual aircraft life monitoring and online life management. Case studies indicate that the proposed method can guarantee high confidence and reliability requirements in individual life monitoring, consistent with the aircraft’s life determination and extension, which are widely accepted nowadays in engineering practice.

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Parametric reduced order model approach for rapid dynamic loads prediction

Cited by 14 publications

References 30 publications

Preliminary aeroelastic design of composite wings subjected to critical gust loads

Preliminary aeroelastic design of composite wings subjected to critical gust loads

Adaptive Feed-Forward Control for Gust Load Alleviation on a Flying-Wing Model Using Multiple Control Surfaces

A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment

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