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Aircraft landing gear cabin flow oscillation control method

A landing gear cabin and control method technology, applied in aircraft parts, computer-aided design, computer material science, etc., can solve problems such as failure to respond to dynamic characteristics, damage to aerodynamic performance, and change of configuration, so as to improve the flow environment in the cavity, Effect of suppressing noise level and reducing pressure oscillations

Active Publication Date: 2022-05-10
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention provides a method for controlling the flow oscillation of the landing gear compartment of an aviation aircraft, so as to solve the problem of changing the configuration and destroying the noise control technology of the landing gear compartment in the prior art. Aerodynamic performance, huge energy consumption, and inability to respond to dynamic characteristics, etc., to achieve the purpose of improving the flow environment in the cavity and suppressing radiation noise as simply as possible while maintaining the same configuration of the landing gear compartment

Method used

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  • Aircraft landing gear cabin flow oscillation control method
  • Aircraft landing gear cabin flow oscillation control method
  • Aircraft landing gear cabin flow oscillation control method

Examples

Experimental program
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Effect test

Embodiment 1

[0062] Such as figure 1 A method for controlling the flow oscillation of an aviation aircraft landing gear compartment includes the following steps:

[0063] A numerical model of the landing gear compartment is established, in which the bottom of the landing gear compartment is set as a porous material;

[0064] determine the boundary conditions;

[0065] Substituting the boundary conditions into the numerical model to solve the porous wall flow of the bilge;

[0066] Calculate the radiated noise amplitude based on the flow data on the porous wall of the bilge;

[0067] Estimate the noise level and adjust the porous wall parameters based on the noise level:

[0068] If the noise level in the main radiation direction meets the set requirements, the control process ends;

[0069] If the noise level in the main radiation direction does not meet the set requirements, maintain the porosity of the porous material β No change, adjust back pressure p , re-solve the porous wall ...

Embodiment 2

[0072] A method for controlling the flow oscillation of an aircraft landing gear compartment. In this embodiment, a typical M219 type landing gear compartment is used as the research object. The landing gear compartment and the corresponding aircraft such as figure 2 and image 3 shown. In the configuration of the landing gear compartment, the length: width: depth is 5:1:1. When Mach number Ma=0.85, Reynolds number Re=0.6×10 7 When flowing through this configuration, a typical self-sustained oscillation occurs.

[0073] This embodiment will first image 3 The configuration of the landing gear compartment is modeled in Figure 4 The model shown in . During the modeling process, the undercarriage with the downward opening is symmetrically changed to the upward opening with respect to the horizontal plane, and the following is obtained: Figure 4 For the model shown, this setup eases modeling without changing the flow characteristics.

[0074] Then determine the boundary ...

Embodiment 3

[0097] A flow oscillation control system for an aircraft landing gear compartment, based on the oscillation control method of any of the above embodiments, comprising:

[0098] The modeling module is used for establishing the numerical model of the landing gear compartment, and setting the bilge of the landing gear compartment as a porous material in the numerical model;

[0099] Boundary module for determining boundary conditions;

[0100] Calculation module, used to calculate the porous wall flow of the bilge and the corresponding radiation noise amplitude;

[0101] A control module is used to regulate the porous wall parameters according to the noise level.

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Abstract

The invention discloses an aviation aircraft undercarriage cabin flow oscillation control method, which comprises the following steps: establishing a numerical model of an undercarriage cabin, and setting the cabin bottom of the undercarriage cabin to be a porous material in the numerical model; determining boundary conditions; substituting the boundary conditions into a numerical model, and solving porous wall surface flow of the cabin bottom; calculating a radiation noise amplitude based on the porous wall surface flow data of the cabin bottom; evaluating the noise level, and regulating and controlling the porous wall surface parameters based on the noise level. The invention provides a flow oscillation control method for an aviation aircraft landing gear cabin, and aims to solve the problems of configuration change, aerodynamic performance damage, huge energy consumption, incapability of responding to dynamic characteristics and the like in a noise control technology for the landing gear cabin in the prior art and realize the purpose of controlling the flow oscillation of the landing gear cabin on the premise of keeping the configuration of the landing gear cabin unchanged. The flow environment in the cavity is improved as simply as possible, and radiation noise is suppressed.

Description

technical field [0001] The invention relates to the field of aircraft flow oscillation control, in particular to a flow oscillation control method for an aircraft landing gear compartment. Background technique [0002] With the rapid development of the air transport industry and the demand for quiet flight, aviation noise has become a key issue that disturbs the residents around the airport and affects the comfort of the aircraft. Aviation aircraft noise mainly includes airframe noise, engine noise, and interference noise between the propulsion system and the airframe. The landing gear system is the main source of commercial aircraft fuselage noise. During the approach stage of the aircraft, the noise generated by the landing gear accounts for about 30%, and the landing gear compartment is the main source of landing gear noise, so the focus of the control of landing gear noise is to suppress the noise of the landing gear compartment. [0003] Accompanied by strong pressure ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G16C60/00G06F30/28B64F5/00G06F111/10G06F113/08G06F119/10G06F119/14
CPCG06F30/20G16C60/00G06F30/28B64F5/00G06F2119/10G06F2111/10G06F2113/08G06F2119/14Y02T90/00
Inventor 李博周清清袁先旭刘朋欣陈坚强
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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