Aircraft wing rib dynamics determination method based on formation superposition method

A technology of rib dynamics and determination method, which is applied in the field of aircraft wing rib structure design, and can solve problems such as difficulty in solving sensitivity

Active Publication Date: 2013-01-16
BEIHANG UNIV
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Problems solved by technology

[0004] The technical solution problem of the present invention: overcome the deficiencies in the prior art, provide a kind of aircraft wing rib dynamics determination method based on formation superposition method, adopt compatible variable performance as dy

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  • Aircraft wing rib dynamics determination method based on formation superposition method
  • Aircraft wing rib dynamics determination method based on formation superposition method
  • Aircraft wing rib dynamics determination method based on formation superposition method

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[0033] like figure 2 As shown, the implementation steps of the present invention are specifically as follows:

[0034](1) Import the initial geometric model or finite element model of the aircraft wing rib, as well as the periodic excitation dynamic load under flight conditions;

[0035] (2) The initial geometric model of the aircraft wing rib is discretized as shown in figure 1 The finite element model composed of finite element elements is shown. If there is a finite element model, go to the next step directly;

[0036] (3) Determine the part of the wing rib structure of the aircraft that needs topology optimization, assign different attributes to the finite element elements in the finite element model in the step (1) to distinguish the parts that need to be optimized from the parts that do not need to be optimized, and then initialize the aircraft Pseudo-density value ρ of each element in the rib finite element model that needs to be optimized n , n is the number of fin...

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Abstract

An aircraft wing rib dynamics determination method based on the formation superposition method. The determination method includes steps: guiding into an aircraft wing rib initial geometric model and a dynamic load; transforming the geometric model of a wing rib into a finite element model; initializing pseudo density values of units of portions needed to be optimized of the finite element model, integrally substituting the wing rib finite element model attached with the pseudo density values in a solver for modal analysis; based on modal analysis results, adopting the formation superposition method for approximate analysis of wing rib dynamic response; based on dynamic analysis result, solving deformation energy of the wing rib, and adopting the Newman expansion difference method to solve the deformation energy and sensitivity of the pseudo density values of restriction; transmitting these values to an optimizer to obtain pseudo density value after updating; and if convergence criteria are met, stopping iteration, if not, returning to the finite element solving portion to generate a final dynamic design scheme for the wing rib. By the aircraft wing rib dynamics determination method based on the formation superposition method, working conditions of dynamics are taken into consideration, aircraft weight is lowered and aircraft performance is improved.

Description

technical field [0001] The invention relates to an aircraft wing rib dynamics determination method based on a formation superposition method, and belongs to the field of aircraft wing rib structure design. Background technique [0002] The aircraft structure is inevitably affected by aerodynamic, wind load and other vibrations or shocks from the external environment. Aircraft, rockets, missiles and other aircraft often require the circular frequency of the structure to be far away from the vibration frequency of the engine to avoid the occurrence of structural resonance. It is usually required that the vibration caused by carrier bumps will minimize the damage to instruments, meters and other devices, and also increase the comfort of the occupants. Effectively reducing the vibration intensity can eliminate the fatigue and discomfort of the occupants and ensure the normal operation of the device. Obviously, to reduce the weight of the aircraft while improving the dynamic ch...

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Application Information

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IPC IPC(8): G06F19/00
Inventor 邱志平李琦王晓军王凯仇翯辰
Owner BEIHANG UNIV
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