Method of designing an airfoil assembly
View Patent ↗A method of analyzing a finite element model of an airfoil assembly. The airfoil assembly comprises a main airfoil element and a plurality of control surfaces. The method comprises: generating a loads interface model of the airfoil assembly comprising: data which defines the spatial positions of a set of nodes, and data which associates each node with either the main element or one of the control surfaces. Load data is generated which defines loads acting on the nodes of the loads interface model, and mapped onto a finite element model to produce a loaded finite element model. A stress analysis is then performed on the loaded finite element model, and the finite element model can be refined as a result of the stress analysis.
1. A method of analysing a finite element model of an airfoil assembly, the airfoil assembly comprising a main airfoil element and a plurality of control surfaces, the method comprising:
a. generating a loads interface model of the airfoil assembly comprising:
i. data which defines the spatial positions of a set of nodes, and
ii. data which associates each node with either the main airfoil element or one of the control surfaces;
b. generating load data which defines loads acting on the nodes of the loads interface model;
c. generating a finite element model of the airfoil assembly comprising:
iii. data which defines the spatial position of a set of nodes, and
iv. data which defines forces acting between the nodes;
d. mapping the load data onto the finite element model to produce a loaded finite element model; and
e. performing a stress analysis on the loaded finite element model, said method steps implemented on a data processor.
2. The method of claim 1 further comprising generating multiple loads interface models of the airfoil assembly, each comprising: data which defines the spatial positions of a set of nodes, and data which associates each node with either the main airfoil element or one of the control surfaces; each loads interface model modelling the control surfaces in a different configuration; and selecting one of the multiple loads interface models for step b.
3. The method of claim 1 wherein the airfoil comprises an aircraft wing.
4. The method of claim 1 wherein the control surfaces comprise droop nose devices, slats, flaps or ailerons.
5. The method of claim 1 wherein the load data comprises aerodynamic load data.
6. The method of claim 1 wherein the load data comprises inertial load data.
7. The method of claim 1 wherein the load data comprises inertial fuel load data.