A Vortex-Lattice Method for Calculating Longitudinal Dynamic Stability Derivatives of Oscillating Delta Wings

AIAA Journal ◽  
1984 ◽  
Vol 22 (1) ◽  
pp. 6-12 ◽  
Author(s):  
D. Levin
Keyword(s):  
Dynamic Stability ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Delta Wings ◽  
Vortex Lattice Method ◽  
Longitudinal Dynamic ◽  
Stability Derivatives ◽  
Derivatives Of

Longitudinal Dynamics Response of M-Wing Morphing Aircraft

2012 ◽  
Vol 538-541 ◽  
pp. 2627-2630
Author(s):  
Lai Bin Xu
Keyword(s):  
Vortex Lattice ◽  
Equations Of Motion ◽  
Lattice Method ◽  
Morphing Aircraft ◽  
Simulation Methodology ◽  
Vortex Lattice Method ◽  
Longitudinal Dynamic ◽  
Aerodynamic Properties ◽  
Dynamics Response ◽  
Wing Morphing

A simulation methodology suitable for morphing wing aircraft is presented, accounting for the changes in both inertial and aerodynamic properties. The aerodynamics was generated with vortex lattice method and solved concurrently with 6DOF nonlinear extended equations of motion. Due to the wing morphing, there are 4 additional forces and moments exhibiting in the extended equations of motion. The simulation mythology was applied to M-wing morphing aircraft, and the longitudinal dynamic response was analyzed with the wing morphing symmetrically. The results show that the additional forces and moments influence the flight dynamic considerably

scholarly journals Typhoon: A vortex-lattice code for assessing dynamic stability characteristics of hydrofoil crafts

2021 ◽  
pp. 1-18
Author(s):  
Alec Bagué ◽  
Joris Degroote ◽  
Toon Demeester ◽  
Evert Lataire
Keyword(s):  
Stability Analysis ◽  
Dynamic Stability ◽  
Vortex Lattice ◽  
Theoretical Explanation ◽  
Surface Boundary ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Lattice Codes ◽  
Cheap Alternative ◽  
The Difference

In this paper an open-source implementation of the vortex-lattice method to perform a dynamic stability analysis for hydrofoil crafts is discussed. The difference with existing vortex-lattice codes is the addition of a free-surface boundary condition which is needed to analyse surface piercing foils. This code, called Typhoon, can be used to perform a dynamic stability analysis (DSA) on hydrofoil vessels. The goal of this code is to have an easy-to-use and cheap alternative to compare different designs in early design stages. This paper gives a brief background to all the concepts used, followed by a short theoretical explanation of the vortex-lattice method. The second part of this paper focuses on a practical example of how this code can be used on an example.

Generalized vortex lattice method for planar supersonic flow

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 1230-1233
Author(s):  
Paulo A. O. Soviero ◽  
Hugo B. Resende
Keyword(s):  
Supersonic Flow ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice 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.

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