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 Stability Characteristics of Wing Span and Sweep Morphing for Small Unmanned Air Vehicle: A Mathematical Analysis

2020 ◽  
Vol 2020 ◽  
pp. 1-15
Author(s):  
Hafiz Muhammad Umer ◽  
Adnan Maqsood ◽  
Rizwan Riaz ◽  
Shuaib Salamat
Keyword(s):  
Equations Of Motion ◽  
Small Scale ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Flight Stability ◽  
Longitudinal Modes ◽  
Flight Vehicles ◽  
Stability Derivatives ◽  
Wing Sweep ◽  
Wing Morphing

Morphing aircraft are the flight vehicles that can reconfigure their shape during the flight in order to achieve superior flight performance. However, this promising technology poses cross-disciplinary challenges that encourage widespread design possibilities. This research aims to investigate the flight dynamic characteristics of various morphed wing configurations that can be incorporated in small-scale UAVs. The objective of this study was to analyze the effects of in-flight wing sweep and wingspan morphing on aerodynamic and flight stability characteristics. Longitudinal, lateral, and directional characteristics were evaluated using linearized equations of motion. An open-source code based on Vortex Lattice Method (VLM) assuming quasi-steady flow was used for this purpose. Trim points were identified for a range of angles of attack in prestall regime. The aerodynamic coefficients and flight stability derivatives were compared for the aforementioned morphing schemes with a fixed-wing counterpart. The results indicated that wingspan morphing is better than wing sweep morphing to harness better aerodynamic advantages with favorable flight stability characteristics. However, extension in wingspan beyond certain limits jeopardizes the advantages. Dynamically, wingspan and sweep morphing schemes behave in an exactly opposite way for longitudinal modes, whereas lateral-directional dynamics act in the same fashion for both morphing schemes. The current study provided a baseline to explore the advanced flight dynamic aspects of employed wing morphing schemes.

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
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