Elastic aircraft trailing vortex encountering dynamic response analysis method

An analysis method and dynamic response technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of elastic aircraft wake vortex encounter dynamic response analysis that have not seen the introduction of public research results, etc. Airport take-off and landing density and the effect of reducing flight intervals

Active Publication Date: 2017-05-10
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Domestically, there is a certain basis for the study of wake vortex on the flight safety of civil aviation aircraft, but so far no public research results have been released on the analysis of the dynamic response of elastic aircraft wake vortex encounters.

Method used

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  • Elastic aircraft trailing vortex encountering dynamic response analysis method
  • Elastic aircraft trailing vortex encountering dynamic response analysis method
  • Elastic aircraft trailing vortex encountering dynamic response analysis method

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Embodiment

[0033] Wake vortex generating aircraft parameters: weight 27.6t, extension 27.9m, cruising speed 152.7m / s, wake vortex encounter aircraft flight speed 100m / s, 90° in-plane crossing, other parameters are consistent with wake vortex generating aircraft.

[0034] The first step is to calculate the strength of the wake vortex generated by the aircraft behind it based on the weight, overload, wingspan, and airfoil parameters of the aircraft generated by the wake vortex.

[0035]

[0036] In the formula: Γ is the strength of the wake vortex, that is, the amount of the wake vortex; m is the mass of the aircraft; n z Is the aircraft normal overload; b 0 = SB, is the distance between the left and right wake vortex cores; B is the wingspan; s is the airfoil parameter, which is related to the shape of the wing, and is acceptable for an elliptical wing For swept wings, you can take 0.75 to 0.80.

[0037] The second step, figure 1 It is a schematic diagram of the anti-rotating wake vortex system ...

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Abstract

The invention belongs to the technical field of aeroelasticity, and relates to an elastic aircraft trailing vortex encountering dynamic response analysis method. The method comprises the steps that according to a formula shown in the description, the elastic aircraft encountering trailing vortex strength is worked out; 2, elastic aircraft encountering despinning trailing vortex system induced speed is calculated; 3, the elastic aircraft encountering trailing vortex unsteady aerodynamic force is obtained; 4, a frequency domain method is adopted for obtaining elastic aircraft trailing vortex encountering frequency domain dynamic response; 5, according to the elastic aircraft trailing vortex encountering frequency domain dynamic response obtained in the step 4, and Fourier inversion is adopted for obtaining elastic aircraft trailing vortex encountering time domain dynamic response; 6, according to the elastic aircraft trailing vortex encountering time domain dynamic response obtained in the step 5, a modal displacement method is adopted for working out load dynamic response through the aircraft structure. The elastic aircraft trailing vortex encountering dynamic response analysis method is built, and a means is provided for trailing vortex encountering analysis in the inland aircraft design.

Description

Technical field [0001] The invention belongs to the technical field of aeroelasticity, and relates to a method for analyzing the dynamic response of an elastic aircraft tail vortex encounter. Background technique [0002] The wake vortex encounter directly affects military aircraft's aerial refueling, formation flying and maneuvering flight, etc. It is also a major factor restricting airport traffic and endangering the flight safety of civil aviation aircraft. Research on the aerodynamic characteristics of the wake vortex and the safety of aircraft wake vortex encounters has been carried out abroad. Since 2007, Karpel et al. in Israel, German Aerospace and Airbus researchers have begun to study the analysis method of elastic aircraft wake vortex encounter dynamic response. , And successively launched undistributed analysis software such as Dynresp, VarLoads and Gusto. In addition, foreign countries have carried out wake vortex encounter flight test studies based on Airbus A400M ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 杨佑绪赵冬强张红波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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