Full-aircraft beam frame type reduction stiffness combination modeling method

Abstract

The invention belongs to the technical field of aeroelasticity, and relates to a full-aircraft beam frame type reduction stiffness combination modeling method. A reduction method is used for obtaining a stiffness matrix of a connecting portion of a rear fuselage large opening and a wing body, and therefore the problem that accurate stiffness data of the complex structures are difficult to obtain through a previous computing method; moreover, a full-aircraft beam frame type reduction stiffness combination model is established in combination with a beam frame model for wings, a vertical tail, a horizontal tail and other components, as a result, accurate simulation of full-aircraft stiffness characteristics is realized, the computing scale is greatly reduced, computing efficiency is improved, model adjustment and parameter variation analysis after a full-aircraft ground resonance test are facilitated, the deficiency of the current modeling technology is remedied, and a novel path is opened up for aeroelastic simulation modeling.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity, and relates to a beam frame-reduced stiffness combined modeling method of the whole machine. Background technique [0002] At present, the commonly used finite element models in flutter analysis include beam-frame model and bar-plate model. The beam frame model has a simple structure and few degrees of freedom. The disadvantage is that it is necessary to accurately calculate the section stiffness data through single closed chamber, multi-closed chamber or force deformation method, so it is difficult to accurately simulate the dynamic characteristics of some complex structures, and the modeling accuracy is relatively low. Low; the rod-plate model has great advantages in modeling accuracy, but the units and degrees of freedom involved are extremely large, and the amount of calculation is too large, which is not convenient for variable parameter analysis and model correction. In the whole ma...

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Problems solved by technology

The beam frame model has a simple structure and few degrees of freedom. The disadvantage is that it is necessary to accurately calculate the section stiffness data through single closed chamber, multi-closed chamber or force deformation method, so it is difficult to accurately simulate the dynamic characteristics of some complex structures, and the modeling accuracy is relatively low. Low; the rod-plate model has a great advantage in modeling accuracy, but the units and degrees of freedom involved are extremely large, and the amount of calculation is too large, which is not convenient for variable parameter analysis and model correction

In the whole machine dynamics simulation modeling of large military transport aircraft, we encountered the problem that the stiffness of the rear fuselage large opening and the wing body connection cannot be simulated accurately, and we need to seek new breakthroughs in modeling technology

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