This often causes an aircraft to generate more lift than if it were a rigid body, which can quickly eat into the margins an analyst thought they had when applying CFD aerodynamic loads. Like with the linear static case, the load can change and reduce the stiffness of the structure, causing additional deformation and additional loading. If all aspects of an aircraft are very rigid, calculating the aerodynamic loads using CFD is sufficient. When structures are too flexible, in addition to running a simple linear static analysis (SOL 101), you often have to consider running a linear buckling analysis (SOL 105) as well. This means that with minimal input about the aircraft geometry, accurate loads can be easily, and quickly generated and applied in the sizing process, without ever needing to consult an aerodynamicist. The aeroelasticity solution even has the capability to trim the aircraft under any of those cases. These loads can be generated to simulate any part of the flight envelope (steady level flight at altitude, coordinated turn, etc.). One of the largest benefits of using the NX NASTRAN Aeroelasticity solution is that those loads can be calculated internally using potential flow methods. Generate Accurate Trimmed Aircraft Loads without CFDĪs a structural/stress engineer, it may not always be convenient or possible to generate fluid dynamic loads during the structural sizing process using CFD (or other methods) and apply them to the structure. Simcenter FEMAP with NX Nastran Training.Adina – FEA program for linear and nonlinear analysis.Solid Edge – Create and manage 3D digital prototypes.NX CAD – Mach Series – High-performance modeling, drafting, and assembly design.Fibersim – Easily modify, update, and iterate composite designs.STAR-CCM+ – Metaphysics solution for simulation.Simcenter Nastran – Finite element solver with solutions for any project. ![]() FEMAP – Pre/post-processor for FEA modeling and simulation.
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