An effective computer modelling approach to the study of aeroelastic characteristics of an aircraft composite wing with high aspect ratio

Wang, Fusheng; Huo, Shihui; Qiao, Shengjun; Zhang, Junran; Yue, Zhufeng

doi:10.1080/13873954.2014.903283

Cited by 7 publications

(2 citation statements)

References 12 publications

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“…e research results show that the effect of geometric nonlinearity on such wings cannot be ignored. Similarly, taking the HARW as the research object and using the loose coupling CFD/CSD method, Wang et al [12] established an efficient model for the analysis of aeroelastic characteristics. Demasi et al [13] established an unsteady aerodynamic model in the frequency domain and combined the updated Lagrange (UL) method to conduct aeroelastic coupling research on composite thin-walled structures.…”

Section: Introductionmentioning

confidence: 99%

Effect of Stiffness on Flutter of Composite Wings with High Aspect Ratio

Qiao

Jiao

et al. 2021

Mathematical Problems in Engineering

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High aspect ratio wing (HARW) structures will deform greatly under aerodynamic loads, and changes in the stiffness will have a great impact on the flutter characteristics of such wings. Based on this, this paper presents an effective method to determine the effect of the stiffness on the flutter characteristics of HARWs. Based on the calculation theory of the mechanical profile of thin-walled structures, the torsional stiffness and bending stiffness of the wing are obtained through calculation. We use the fluid-structure coupling method to analyze the flutter characteristics of the wing, and we use our research results based on the corotational (CR) method to perform structural calculations. The load is calculated using a computational fluid dynamics (CFD) solver. The results show that, compared with the original wing, when the bending stiffness and torsional stiffness of the wing along the spanwise direction increase by 8.28% and 5.22%, respectively, the amplitude of the flutter decreases by approximately 30%. Increasing the stiffness in the range of 0.4 to 0.6 Mach has a greater impact on the flutter critical velocity, which increases by 12.03%. The greater the aircraft’s flight speed is, the more severe the stiffness affects the wing limit cycle oscillation (LCO) amplitude.

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Section: Introductionmentioning

confidence: 99%

Effect of Stiffness on Flutter of Composite Wings with High Aspect Ratio

Qiao

Jiao

et al. 2021

Mathematical Problems in Engineering

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“…Industrial frameworks are highly complex and aimed at supporting certification activities. These often couple computational fluid dynamics (CFD) with computational structural mechanics (CSM) resulting in processes that provide the desired insight, but are computationally very expensive (Cooper et al 2016;Lindhorst et al 2014;Wang et al 2015). Reduced order models such as VARLOADS (Kier et al 2005) have also been developed, but these have only seen limited research usage.…”

Section: Introductionmentioning

confidence: 99%

Modelling Framework for Flight Dynamics of Flexible Aircraft

2016

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The flight dynamics and handling qualities of any flexible aircraft can be analysed within the Cranfield Aircraft Accelerated Loads Model (CA2LM) framework. The modelling techniques and methods used to develop the framework are presented. The aerodynamic surfaces were modelled using the Modified Strip Theory (MST) and a state-space representation to model unsteady aerodynamics. With a modal approach, the structural flexibility and each mode’s influence on the structure deflections are analysed. To supplement the general overview of the framework equations of motion, models of atmosphere, gravity, fuselage and engines are introduced. The AX-1 general transport aircraft model is analysed as an example of the CA2LM framework capabilities. The results showed that, according to the Gibson Dropback criterion, the aircraft with no control system lacks the stability and its longitudinal handling qualities are unsatisfactory. Finally, the steps for future developments of the CA2LM framework are listed within conclusions.

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A model‐based flight qualities evaluation approach for civil aircraft

Zhong

Qu²,

Mora‐Camino

2018

Concurrency and Computation

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SummaryEvaluation of flight qualities plays an important role in the design of a civil aircraft. An appropriate level of flight qualities will be the key to achieve the airworthiness certification. With the objective to provide an overall view of flight qualities evaluation for a civil aircraft, a model‐based approach is proposed. Some terms related to flight qualities are defined formally, and the model‐based flight qualities evaluation approach under different situations is formed and proposed. Two working conditions of actuators are considered in the evaluation of flight qualities. When no actuator fails, linearization is adopted to build a linear flight dynamics model for analyzing the main parameter of flight qualities. When some actuators fail, a new off‐line approach for handling qualities evaluation, which employs a controller that generates appropriate commands for healthy actuators, is proposed. The design of the controller is following the idea of classical predictive control technique, and a recurrent linear quadratic programming problem is formulated to find the maximum remaining maneuverability while not avoiding any constraints. Taking the rotational maneuver as a study example, a test‐bed for handling qualities evaluation is built. The numerical simulation results show the feasibility of proposed evaluation approach.

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An effective computer modelling approach to the study of aeroelastic characteristics of an aircraft composite wing with high aspect ratio

Cited by 7 publications

References 12 publications

Effect of Stiffness on Flutter of Composite Wings with High Aspect Ratio

Effect of Stiffness on Flutter of Composite Wings with High Aspect Ratio

Modelling Framework for Flight Dynamics of Flexible Aircraft

A model‐based flight qualities evaluation approach for civil aircraft

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