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An Aeroelastic Analysis Method Considering Engine Dynamic Characteristics

A technology of aeroelasticity and dynamic characteristics, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as aeroelastic analysis methods and gyro effect considerations, and achieve high engineering application value and easy operation , Improve the effect of analysis accuracy

Active Publication Date: 2020-12-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

The influence of the dynamic characteristics associated with the large rotating mass engine on the elastic aircraft, the structural vibration problems caused by the coupling of the engine and the elastic wing structure, and the gyroscopic effect are not considered in the aeroelastic analysis by traditional calculation methods
At present, there is no aeroelastic analysis method that considers these influencing factors in China.

Method used

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  • An Aeroelastic Analysis Method Considering Engine Dynamic Characteristics
  • An Aeroelastic Analysis Method Considering Engine Dynamic Characteristics
  • An Aeroelastic Analysis Method Considering Engine Dynamic Characteristics

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Embodiment Construction

[0026] 1 Extract the engine reference point:

[0027] Before performing aeroelastic analysis, there must be a structural finite element model, such as an aircraft finite element model such as figure 1 shown. There are a total of 1361 nodes in the finite element model, and the node numbers of the left and right engine gravity centers are 168 and 968 in all nodes, and the engine gravity nodes are the extracted engine reference points. According to the finite element model, the dimensions of mass matrix M, damping matrix D and stiffness matrix K are 8166*8166, and the positions of the matrices corresponding to the center of gravity of the left and right engines are Matrix(1003:1008, 1003:1008) Matrix(5803: 5808, 5803:5808).

[0028] 2 Assuming that the dynamic characteristics of the left and right engines are the same, the thrust vector and torque vector of the engines are respectively F=(-16501.2, 0, 0)M v =(0, 15008.6, 0), the rotation angle vector and angular velocity of th...

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Abstract

The invention belongs to the technical field of aeroelastic analysis of an aircraft and relates to an aeroelastic analysis method in consideration of dynamic characteristics of an engine. The method comprises the steps of I, extracting engine reference points; II, establishing following matrixes according to extracted engine reference point positions and the dynamic characteristics of the engine: an engine thrust rigidity correction matrix as shown in the description, wherein j is engine number, F is a thrust vector of the engine reference point positions, and M is a moment vector caused by engine thrust, and a gyroscopic moment damping correction matrix as shown in the description, wherein omega is an angular velocity of the engine reference point positions, and theta is a turn angle vector of the engine reference point positions; III, correcting an aeroelastic motion equation without considering the dynamic characteristics of the engine according to the correction matrix established in step II, wherein the aeroelastic motion equation is as shown in the description, deltaM*= phiTdeltaMphi, deltaD*= phiTdeltaDphi, deltaK*= phiTdeltaKphi, deltaM* is a mass correction matrix, and phi is a modal matrix; and IV, calculating aeroelastic stability or dynamic response according to the corrected aeroelastic motion equation.

Description

technical field [0001] The invention belongs to the technical field of aircraft aeroelastic analysis and relates to an aeroelastic analysis method considering the dynamic characteristics of an engine. Background technique [0002] More and more modern aircraft are equipped with high bypass ratio engines in order to improve fuel efficiency, reduce noise emissions, as well as environmental and energy considerations. The effect of large diameter rotating blades on the dynamics of this type of aircraft needs to be studied. The influence of the dynamic characteristics related to the large rotating mass engine on the elastic aircraft, the structural vibration problem caused by the coupling of the engine and the elastic wing structure, and the gyroscopic effect are not considered in the aeroelastic analysis by traditional calculation methods. At present, there is no aeroelastic analysis method considering these influencing factors in China. Contents of the invention [0003] Pu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15
CPCG06F30/15G06F30/23
Inventor 党云卿李俊杰胡志勇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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