A High Efficiency Aeroelastic Analysis Method based on Rigid External Aerodynamic Force and Elastic Correction by High-Order Panel Method

2017 ◽  
Author(s):  
Yunzhen Liu ◽  
Siyan Zhu ◽  
Zhiqiang Wan ◽  
Chao Yang
Keyword(s):  
High Efficiency ◽  
Aerodynamic Force ◽  
High Order ◽  
Panel Method ◽  
Analysis Method ◽  
Aeroelastic Analysis

scholarly journals Application of High-order Panel Method in Static Aeroelastic Analysis of Aircraft

2012 ◽  
Vol 31 ◽  
pp. 136-144
Author(s):  
Yaokun Wang ◽  
Zhiqiang Wan ◽  
Chao Yang
Keyword(s):  
High Order ◽  
Panel Method ◽  
Aeroelastic Analysis

Improve the Free-Piston Stirling Engine Design with High Order Analysis Method

2010 ◽  
Vol 44-47 ◽  
pp. 1991-1995 ◽  
Author(s):  
Chen Lin ◽  
Xian Zhou Wang ◽  
Xi Chen ◽  
Zhi Guo Zhang
Keyword(s):  
High Efficiency ◽  
Stirling Engine ◽  
High Order ◽  
Working Fluid ◽  
Model Parameters ◽  
Analysis Method ◽  
Free Piston ◽  
Stirling Cycle ◽  
Engine Design ◽  
Free Piston Stirling Engine

Stirling engine is a heat engine which is enclosed a fixed quantity of permanently gaseous fluid as the working fluid. The free-piston Stirling engine is noted for its high efficiency, quiet operation, long life without maintenance in ten years and the ease with which it can use almost any heat source. Stirling cycle analysis method has been successfully applied to improve the free-piston Stirling engine design by its step-by-step development on order. This study presents the development and application of Stirling cycle analysis method. Discussions about use of multi-dimension CFD software simulating free piston Stirling engine when there’s not any available experimental data for its design will provide. Since it needs less computing resource and time to get 1D simulation results with some accuracy, the application of multi-dimension CFD could be very helpful to improve accuracy of 1D result with the details of the different simplified model parameters used in 1D model. The research demonstrates that with the combination of high order Stirling cycle analysis method, the design of the free-piston Stirling engine with the aid of numerical method could be much more effectively and accurately.

A method for static aeroelastic analysis based on the high-order panel method and modal method

2011 ◽  
Vol 54 (3) ◽  
pp. 741-748 ◽  
Author(s):  
Chao Yang ◽  
BoCheng Zhang ◽  
ZhiQiang Wan ◽  
YaoKun Wang
Keyword(s):  
High Order ◽  
Panel Method ◽  
Aeroelastic Analysis ◽  
Modal Method

scholarly journals Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

2019 ◽  
Vol 2019 ◽  
pp. 1-15
Author(s):  
Sen Mao ◽  
Changchuan Xie ◽  
Lan Yang ◽  
Chao Yang
Keyword(s):  
Vortex Lattice ◽  
Deflection Angle ◽  
Aircraft Design ◽  
Analysis Method ◽  
Lattice Method ◽  
Trailing Edge ◽  
Vortex Lattice Method ◽  
Analysis And Design ◽  
Aeroelastic Analysis ◽  
Typical Model

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corresponding simulations were carried out. Finally, the analysis results are compared with those of a traditional wing with a rigid trailing edge using the traditional linearized VLM. The results indicate that the geometrically exact VLM can better describe the aerodynamic nonlinearity of a morphing TE wing in consideration of geometrical deformation in aeroelastic analysis. Moreover, out of consideration of the angle of attack, the deflection angle of the trailing edge, among others, the wing system does not show divergence but bifurcation. Consequently, the aeroelastic analysis method proposed in this paper is more applicable to the analysis and design of a morphing TE wing.

scholarly journals High-order compact LOD methods for solving high-dimensional advection equations

2021 ◽  
Vol 40 (3) ◽  
Author(s):  
Bo Hou ◽  
Yongbin Ge
Keyword(s):  
Truncation Error ◽  
Three Dimensional ◽  
Taylor Series Expansion ◽  
High Order ◽  
High Dimensional ◽  
Analysis Method ◽  
Order Accuracy ◽  
Von Neumann ◽  
One Dimensional ◽  
Von Neumann Analysis

AbstractIn this paper, by using the local one-dimensional (LOD) method, Taylor series expansion and correction for the third derivatives in the truncation error remainder, two high-order compact LOD schemes are established for solving the two- and three- dimensional advection equations, respectively. They have the fourth-order accuracy in both time and space. By the von Neumann analysis method, it shows that the two schemes are unconditionally stable. Besides, the consistency and convergence of them are also proved. Finally, numerical experiments are given to confirm the accuracy and efficiency of the present schemes.

Dynamic Analysis of the Pipe Lifting Mechanism on the Deepwater Pipelaying Vessel

2011 ◽  
Vol 199-200 ◽  
pp. 251-256
Author(s):  
Kai An Yu ◽  
Ke Yu Chen
Keyword(s):  
Numerical Analysis ◽  
Dynamic Analysis ◽  
High Efficiency ◽  
Transport Systems ◽  
Kinematic Pair ◽  
Analysis Method ◽  
Numerical Analysis Method ◽  
Upper Limit ◽  
Lifting Capacity ◽  
Limit Position

Based on requirements of pipe transport systems on deepwater pipelaying vessel, a new pipe lifting mechanism was designed. It was composed of crank-rocker and rocker-slider mechanism with good lifting capacity and high efficiency. When the slider went to the upper limit position, the mechanism could approximatively dwell, meeting the requirement for transverse conveyor operation. According to the theory of dynamics, numerical analysis method was used to the dynamic analysis of the mechanism. The results showed the maximum counterforce was at the joint between the rocker and ground, and this calculation could be a guideline for the kinematic pair structure designing.

scholarly journals A general high order two-dimensional panel method

2018 ◽  
Vol 60 ◽  
pp. 1-17
Author(s):  
Anders Goude ◽  
Stefan Engblom
Keyword(s):  
High Order ◽  
Panel Method ◽  
Two Dimensional

Evaluation of High-Order Resonance of Blade Under Wake Excitation

2010 ◽  
Author(s):  
Lin Li ◽  
Peiyi Wang
Keyword(s):  
Force Field ◽  
Aerodynamic Force ◽  
Engineering Problem ◽  
High Order ◽  
Order Resonance ◽  
High Order Resonance ◽  
Resonance Frequencies ◽  
The Common ◽  
Turbo Machinery ◽  
Two Parameters

Avoiding the low-order resonances of blades is one of the main design goals for a mechanical structure designer of turbo machinery. However, we have to accept that there are resonance frequencies in the operating speed range of the blade, for the following reasons: Firstly, the natural frequencies of the blade are closely spaced sometimes, it is impossible to avoid them all. Secondly, in general, the higher of the resonance frequency, the lower the energy of resonance will be. But in recent 10 years, the high-order blade resonances present more and more frequently in turbo machinery, which induce a lot of HCF problems. As the considerations above, studies on the high-order vibration of blades become necessary and important. In the cascade, the high-order vibration of blades is mainly induced by the wakes from upstream. An obvious difference of the wake excitation from the common excitations resides in its asynchronism, that is, the maximum value of aerodynamic force from wakes at each point doesn’t appear at the same time, because except the frequency, the distribution of the aerodynamic force field depends on two parameters: not only amplitude but also phase angle. Both are functions of coordinates. In this paper, the related position in Euclidean Space between the asynchronous excitation field and the modal displacement of blade were deal with to evaluate the strength of the high-order resonance of blade. The effect of the asynchronous aerodynamic force field on the blade resonance was studied either. Finally a method for evaluation of high-order resonance of blade excited by wake fluid is proposed. A numerical case was studied either, which demonstrates that the proposed evaluation on high-order resonance is practical in engineering problem.

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