Transition flight control simulations of bioinspired FWMAV with extended unsteady vortex-lattice method

2018 ◽  
Author(s):  
Jae-Hung Han ◽  
Jong-Wan Lee ◽  
Anh Tuan Nguyen
Keyword(s):  
Flight Control ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Transition Flight

Mechanism Modeling and Analysis of a Small Unmanned Vehicles Using Vortex Lattice Method

2014 ◽  
Vol 496-500 ◽  
pp. 1068-1072
Author(s):  
Xiao Jie Zang ◽  
Zhi Dong Zhang ◽  
Chang Liu
Keyword(s):  
Performance Analysis ◽  
Flight Control ◽  
Vortex Lattice ◽  
Static Stability ◽  
Unmanned Vehicles ◽  
Practical Significance ◽  
Lattice Method ◽  
Modeling And Analysis ◽  
Vortex Lattice Method ◽  
Mechanism Modeling

For a certain type of small unmanned aerial vehicles (SUAV), using the vortex lattice method (VLM) estimated the aerodynamic derivatives, establishing linear small-perturbation equations based on level and non-sideslipping flight. Analyzed the static stability and mode characteristics based on the dimensionless derivative and matlab simulation. Early in the design, by mechanism modeling and performance analysis for the UAV through pneumatic calculations could get a lot of valuable reference data of the UAV. This has some practical significance for system performance analysis and flight control system design.

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.

scholarly journals Analysis of wing flap configurations by a nonplanar vortex lattice method

1988 ◽  
Vol 25 (2) ◽  
pp. 97-98 ◽  
Author(s):  
B. Rajeswari ◽  
H. N. V. Dutt
Keyword(s):  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method

Thruster and FPSO Hull Interaction

2014 ◽  
Author(s):  
Ye Tian ◽  
Spyros A. Kinnas
Keyword(s):  
Experimental Data ◽  
Hybrid Method ◽  
Computational Efficiency ◽  
Vortex Lattice ◽  
Numerical Results ◽  
Navier Stokes ◽  
Dynamic Positioning ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Number Of Cells

A hybrid method which couples a Vortex-Lattice Method (VLM) solver and a Reynolds-Averaged Navier-Stokes (RANS) solver is applied to simulate the interaction between a Dynamic Positioning (DP) thruster and an FPSO hull. The hybrid method could significantly reduce the number of cells to fifth of that in a full blown RANS simulation and thus greatly enhance the computational efficiency. The numerical results are first validated with available experimental data, and then used to assess the significance of the thruster/hull interaction in DP systems.

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