madrid2i

Resumen

[0001] A computer-aided method suitable for assisting in the design of an aircraft by providing the values of dimensional variables, dependant of a predefined set of parameters, for the complete aircraft or an aircraft component, comprising the following steps: a) Defining a parametric space grid; b) Obtaining a suitable Reduced Order Model (ROM) model, particularly a Proper Orthogonal Decomposition (POD) model, for calculating said variables for whatever point over the parametric space through an iterative process. Computer Fluid Dynamics (CFD) is used to calculate said variables for an appropriately selected set of points over the parametric space, which are used to approximate, via ROM and ad hoc interpolation, the variables in any other point over the parametric space. The method minimizes the required number of CFD calculations (to minimize the computational cost, which dramatically depends on this number) for a given level of error. <img class="EMIRef" id="74294506-iaf01" />

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1. A computer-aided method suitable for assisting in the design of an aircraft by providing the values of one or more dimensional variables for the complete aircraft or an aircraft component, being said one or more variables dependant of a predefined set of parameters, characterized by comprising the following steps: a) Defining a parametric space grid setting predetermined distances between its values; b) Obtaining a suitable model for calculating said one or more dimensional variables for whatever point over the parametric space through an iterative process with respect to a reduced group of points, of increasing number of members in each iteration, comprising the following sub-steps: b1) Calculating the values of said one or more dimensional variables for an initial group of points using a CFD model; b2) Obtaining an initial ROM model from said CFD computations and calculating the values of said one or more dimensional variables for said initial group of points using the initial ROM model; b3) Selecting the e-point of the group with the largest deviation ε between the results provided by the CFD and the ROM models and finishing the iterative process if ε is lesser than a predefined value ε<0>; b4) Selecting new points over the parametric space to be added to the group of points as those points placed inside the parametric space grid at a predefined distance from said e-point; b5) Calculating the values of said one or more dimensional variables for the new points using the CFD and the ROM model and going back to sub-step b3). 2. A computer-aided method according to claim 1, characterized in that said complete aircraft or an aircraft component is divided into blocks and said CFD and ROM models are applied block by block. 3. A computer-aided method according to any of claims 1-2, characterized in that said one or more dimensional variables includes one or more of the following: aerodynamic forces, skin values, values distribution around the complete aircraft or aircraft component. 4. A computer-aided method according to any of claims 1-3, characterized in that said set parameters includes one or more of the following: angle of attack, Mach number. 5. A computer-aided method according to any of claims 1-4, characterized in that said aircraft component is one of the following: a wing, an horizontal tail plane, a vertical tail plane. 6. A computer-aided method according to any of claims 1-5, characterized in that said ROM model is a POD model. 7. A computer-aided method according to claims 6, characterized in that the deviation ε between the results provided by the CFD and the POD models is obtained as the root mean square error between said results. 8. A computer-aided method according to any of claims 6-7, characterized in that the POD model is obtained eliminating the less relevant modes of the group of points.

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