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.

/pdf/gust-loads-on-aircraft-4dmau1qusa.pdf

Gust loads on aircraft

Non-linearities can be present in an aeroelastic system due to some aerodynamic factors that occur in transonic flight regime or at large angle of attack. The sources are motions of shock wave and separated flow. By using high-fidelity CFD codes, complex aeroelastic problem due to the aerodynamic nonlinearity can be studies. However, the computational cost of this method is very high. It is convenient to solve this kind of problem by constructing a proper unsteady aerodynamic model previously. Many research works are carried out in reduced order modeling (ROM) for aeroelastic analysis. Most of the reduced order aerodynamic models are dynamic linear models and in proportion to the structural motions. By using Radial Basis Function (RBF) neural network model, the nonlinear unsteady reduced order aerodynamic model is constructed. ROM is used to analyze LCOs behaviors for two linear struc tural models with large shock motion in transonic flow. Different from the traditional design method of the input signals, signals of self-excited vibration of the aeroelastic system are designed as the input signals in this paper. Coupling the structural equations of motion and nonlinear aerodynamic ROM, the system responses are determined by time marching of the governing equations using a kind of hybrid linear multi -step algorithm and the limit cycle behaviors changing with velocities (dynamic pressure) can be analyzed. Two transonic aeroelastic examples show that both the structural responses and the limit cycle oscillation (LCO) characteristics simulated by ROM are agree well with those obtained by direct CFD method while the computational efficiency of ROM based method is improved 1-2 orders of magnitude comparing with the direct CFD method.

High Efficient Numerical Method for Limit Cycle Flutter Analysis Based on Nonlinear Aerodynamic Reduced Order Model

1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China 2. School of Aerospace; Tsinghua University; Beijing 100084, China Non-linearities can be present in an aeroelastic system due to some aerodynamic factors that occur in transonic flight regime or at large angle of attack. The sources are motions of shock wave and separated flow. By using high-fidelity CFD codes, complex aeroelastic problem due to the aerodynamic nonlinearity can be studies. However, the computational cost of this method is very high. It is convenient to solve this kind of problem by constructing a proper unsteady aerodynamic model previously. Many research works are carried out in reduced order modeling (ROM) for aeroelastic analysis. Most of the reduced order aerodynamic models are dynamic linear models and in proportion to the structural motions. By using Radial Basis Function (RBF) neural network model, the nonlinear unsteady reduced order aerodynamic model is constructed. ROM is used to analyze LCOs behaviors for two linear structural models with large shock motion in transonic flow. Different from the traditional design method of the input signals, signals of self-excited vibration of the aeroelastic system are designed as the input signals in this paper. Coupling the structural equations of motion and nonlinear aerodynamic ROM, the system responses are determined by time marching of the governing equations using a kind of hybrid linear multi-step algorithm and the limit cycle behaviors changing with velocities (dynamic pressure) can be analyzed. Two transonic aeroelastic examples show that both the structural responses and the limit cycle oscillation (LCO) characteristics simulated by ROM are agree well with those obtained by direct CFD method while the computational efficiency of ROM based method is improved 1-2 orders of magnitude comparing with the direct CFD method.

High Efficient Numerical Method for Limit Cycle Flutter Analysis Based on Nonlinear Aerodynamic Reduced Order Model Reduced Order Model

Gust load alleviation using computational fluid dynamics as source of the aerodynamic predictions is carried out in the time domain. To this goal, an aeroservoelastic reduced-order model is generat...

/pdf/computational-fluid-dynamics-based-aeroservoelastic-analysis-6g504q42ac.pdf

Computational-Fluid-Dynamics-Based Aeroservoelastic Analysis for Gust Load Alleviation

Aeroelastic Moving Gust Responses and Alleviation based on CFD

Gust response analysis plays a very important role in large aircraft design. Most of existing aerodynamic models for gust response analysis are linearized models that can’t be used for nonlinear aeroelastic analysis, such as transonic problems. In this paper, based on CFD technique and system identification method, a CFD-based reduced order model (ROM) is constructed in state space. It is compact and computationally efficient. Gust response analysis is completed by coupling structural equations with CFD-based ROM. A squareedged gust response for a typical wing is shown. The results of the responses of generalized displacements and root bending moment (RBM) are compared well with that of direct CFD method and the reference paper. It validates the correctness and precision of the CFD-based ROM method.

Gust Response Analysis Using CFD-Based Reduced Order Models

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Gust Response Analysis Using CFD-Based Reduced Order Models