28-08-2014, 03:27 PM
MODELING AND ANALYSIS OF UAV WING
[attachment=67255]
ABSTRACT
Wing provides the required lift, drag, and control of the UAV’s flight. By morphing the wing structure we can obtain desirable variables for the flight. Uav wing is designed and modeled for desirable variables for the flight by using SMA (shape memory alloy) wires.
The SMA wires are placed in between leading edge spar and trailing edge spar in few of the ribs of the wing. This wing is modeled using catia software. Meshing and F.E analysis is done with the help of hyper mesh software. NASTRAN is used as solver for the F.E model. The aerodynamic analysis is carried in XFLR software for incompressible flow through wing plan form at free stream speed of 0.218 Mach air flow.
What is a shape memory alloy?
Materials possessing shape memory properties to return to their original shape after having suffered some form of deformation after they are heated to temperatures above their transformation temperature.
How do they work?
Over a range of temperatures, starting at the transformation temperature, the alloy undergoes a reversible solid state transformation. The transformation temperature is influenced by composition and other factors.
What metals exhibit shape memory characteristics?
Nickel/Titanium alloys such as Nitinol and Tinel
Copper/Zinc/Aluminum Alloys
Copper/Aluminum/Nickel Alloys
MORPHING OF WING
TMORPHING OF WING
he main objective of this project is to design and analyze a structure that is able to morph its shape for different flight conditions. In order to do so, a review of the available morphing concepts is first needed. Following that, designing novel morphing concepts and comparing potential ones to select the most promising of the group is the next logical step. Lastly, a detailed analysis of the most promising concept can be conducted to highlight the advantages and shortcomings of the design and set the base for future work.
Compliant Mechanism
Compliant Mechanism
The complaint mechanism of skeleton of the segmented adaptive wing is constructed using two airfoils, which are positioned 100mm apart. The wing has got the front spar, located at 1/4th chord and the rear spar is placed at 3/4th chord. The X-shaped cross sections are obtained through optimization process by satisfying both load carrying and flexibility requirements. Therefore, conformable airfoil is made using X-shaped design, connecting hexagonal structures to form a morphing wing section.
[attachment=67255]
ABSTRACT
Wing provides the required lift, drag, and control of the UAV’s flight. By morphing the wing structure we can obtain desirable variables for the flight. Uav wing is designed and modeled for desirable variables for the flight by using SMA (shape memory alloy) wires.
The SMA wires are placed in between leading edge spar and trailing edge spar in few of the ribs of the wing. This wing is modeled using catia software. Meshing and F.E analysis is done with the help of hyper mesh software. NASTRAN is used as solver for the F.E model. The aerodynamic analysis is carried in XFLR software for incompressible flow through wing plan form at free stream speed of 0.218 Mach air flow.
What is a shape memory alloy?
Materials possessing shape memory properties to return to their original shape after having suffered some form of deformation after they are heated to temperatures above their transformation temperature.
How do they work?
Over a range of temperatures, starting at the transformation temperature, the alloy undergoes a reversible solid state transformation. The transformation temperature is influenced by composition and other factors.
What metals exhibit shape memory characteristics?
Nickel/Titanium alloys such as Nitinol and Tinel
Copper/Zinc/Aluminum Alloys
Copper/Aluminum/Nickel Alloys
MORPHING OF WING
TMORPHING OF WING
he main objective of this project is to design and analyze a structure that is able to morph its shape for different flight conditions. In order to do so, a review of the available morphing concepts is first needed. Following that, designing novel morphing concepts and comparing potential ones to select the most promising of the group is the next logical step. Lastly, a detailed analysis of the most promising concept can be conducted to highlight the advantages and shortcomings of the design and set the base for future work.
Compliant Mechanism
Compliant Mechanism
The complaint mechanism of skeleton of the segmented adaptive wing is constructed using two airfoils, which are positioned 100mm apart. The wing has got the front spar, located at 1/4th chord and the rear spar is placed at 3/4th chord. The X-shaped cross sections are obtained through optimization process by satisfying both load carrying and flexibility requirements. Therefore, conformable airfoil is made using X-shaped design, connecting hexagonal structures to form a morphing wing section.