Aircraft flutter analysis grid model Walsh modeling method

A grid model, flutter analysis technique, used in aerospace and information fields

Active Publication Date: 2018-08-10
XIAN FEISIDA AUTOMATION ENG
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Problems solved by technology

[0006] In order to overcome the problem that the existing technology cannot effectively express the complex flutter model under the influence of aerodynamic force and strength changes, the present invention provides a method for modeling the aircraft flutter analysis grid model Walsh, which is selected in the aircraft body axis system Multiple grid points, under the influence of aerodynamic and strength changes such as different flight speeds, atmospheric densities, airflow environments, and different temperatures, the complex flutter grid model is represented according to the body shaft system decomposition method, and the installation of sensors is proposed ...

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  • Aircraft flutter analysis grid model Walsh modeling method

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[0062] Step 1: Analyze the complex flutter model with the aircraft body shaft system OXYZ, and select n grid points in the body shaft system: x i ,y i ,z i , i=1,2,...,n, when vibrating, the dynamic three-axis position components x(y,z,t),y(x,z,t),z(x,y,t) of grid points are time t and other two-axis position functions, for the convenience of expression, x ix (y, z, t) as an example, the subscript i=1, 2,..., n is the grid point label, the second letter x, y, z of the subscript respectively represent the three axes of vibration in the body axis system OXYZ component, in order to simplify the problem, when considering the i=1,2,...,n grid points vibrating in the x-axis direction, x(y,z,t)=x ix (t),y(x,z,t)=y ix (x),z(x,y,t)=z ix (x), when considering the i=1,2,...,n grid points vibrating in the y-axis direction, x(y,z,t)=x iy (y),y(x,z,t)=y iy (t),z(x,y,t)=z iy (y), when considering the i=1,2,...,n grid points vibrating in the z-axis direction, x(y,z,t)=x iz (z),y(x,z,...

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Abstract

In order to overcome the problem in the prior art that a complex flutter model under aerodynamic force and strength change influences can not be effectively expressed, the invention provides an aircraft flutter analysis grid model Walsh modeling method. The method is characterized in that a plurality of grid points are selected in an aircraft engine body shaft system; under aerodynamic force and strength change influences including different flight speeds, atmospheric densities, airflow environments, different temperatures and the like, according to an engine body shaft system decomposition method, a complex flutter grid model is expressed; according to a requirement for establishing the model, the requirements of installing sensors and data and image records are put forward; through an effective flutter flight experiment, data is obtained, and an excitation function is obtained through a measured value of an airflow sensor; a Walsh function is adopted to carry out approximation and equivalent description on a vibration variable; according to a distinguishing method, the solving of three axial vibration equations on an engine body axial system coordinate grid point can be simultaneously determined, and the technical problem in the prior art that the complex flutter model under aerodynamic force and strength change influences can not be effectively expressed is solved.

Description

technical field [0001] The invention relates to a ground comprehensive test method for flight safety of civil aircraft, fighter jets, unmanned aerial vehicles and the like, in particular to a flutter analysis grid model Walsh modeling method for aircraft, and belongs to the field of aerospace and information technology. Background technique [0002] Flutter is a large-amplitude vibration phenomenon that occurs when an elastic structure is coupled by aerodynamic, elastic, and inertial forces in a uniform airflow. For aircraft, vibration occurs after an uncertain disturbance in flight. At this time, due to the effect of the airflow, the elastic structure of the aircraft such as the wing, empennage or control surface will generate additional aerodynamic force; as an exciting force, the additional aerodynamic force will aggravate the vibration of the structure. At the same time, the damping force of the air on the aircraft structure tries to weaken the vibration; when flying at...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG
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