Anemometer Study
Wing Design
In wing design, aerodynamic and structural are major consideration that the design required to consider the loading condition of the wing and the layout of the wing structure to ensure that the wing structure are able to withstand all possible loading condition with minimum if the weight. Since it is often that don’t able to have best solution for the consideration at the same time. The wing design will be optimized.
Before processing the wing design, it is necessary to understand the structure of the wing. In the figure-x , it shown the elements and layout of wing structure of the Pilatus PC9/A which include spars, shear webs, ribs, skin and skin stingers. This section will be process the design of those elements base on the loads calculated in section 4. Note that the calculation is for one wing only as the load same for both wings as assumed.
Figure xx: The wing structure layout of Pilatus PC9/A (reference)
In the process of optimum design of the wing, there are several assumptions are made,
The wing root thickness is 12% of the chord.
The contribution of the auxiliary spar is neglected.
The spar can be treated as tension field beam.
The stringer/skin can contribute up to 50% of the bending moment, but the bending moment contribution of spar remains 100% because of safety.
The material for the entire wing structure is AL2024-T3.
The compressive strength of the material is equal to tensile strength of the material.
In rib sizing section, the cross section of the wing is constant that the wing thickness and chord are wing root thickness and mean geometric chord length to simplify the sizing process.
Wing structure design requirements,
No structural failures at design ultimate limit which is 50% more than design limit load. All loading will be added factor of 1.5 to meeting this requirement.
No buckling allow at 110% of design limit load.
Rib sizing
In the wing design, the ribs used to support and stiffen the skin to maintain
In wing design, aerodynamic and structural are major consideration that the design required to consider the loading condition of the wing and the layout of the wing structure to ensure that the wing structure are able to withstand all possible loading condition with minimum if the weight. Since it is often that don’t able to have best solution for the consideration at the same time. The wing design will be optimized.
Before processing the wing design, it is necessary to understand the structure of the wing. In the figure-x , it shown the elements and layout of wing structure of the Pilatus PC9/A which include spars, shear webs, ribs, skin and skin stingers. This section will be process the design of those elements base on the loads calculated in section 4. Note that the calculation is for one wing only as the load same for both wings as assumed.
Figure xx: The wing structure layout of Pilatus PC9/A (reference)
In the process of optimum design of the wing, there are several assumptions are made,
The wing root thickness is 12% of the chord.
The contribution of the auxiliary spar is neglected.
The spar can be treated as tension field beam.
The stringer/skin can contribute up to 50% of the bending moment, but the bending moment contribution of spar remains 100% because of safety.
The material for the entire wing structure is AL2024-T3.
The compressive strength of the material is equal to tensile strength of the material.
In rib sizing section, the cross section of the wing is constant that the wing thickness and chord are wing root thickness and mean geometric chord length to simplify the sizing process.
Wing structure design requirements,
No structural failures at design ultimate limit which is 50% more than design limit load. All loading will be added factor of 1.5 to meeting this requirement.
No buckling allow at 110% of design limit load.
Rib sizing
In the wing design, the ribs used to support and stiffen the skin to maintain