Method for calculating wing shielding effect based on diffraction principle

A calculation method and occlusion effect technology, applied in design optimization/simulation, geometric CAD, etc., can solve the cumbersome problems of ray tracing and diffraction paths

Active Publication Date: 2020-06-26
XIDIAN UNIV
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Problems solved by technology

[0006] Although the UTD theory is widely used in calculations such as antenna propagation, the ray tracing and the determination of the diffraction path in the algorithm are very cumbersome and often require a lot of calculations

Method used

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  • Method for calculating wing shielding effect based on diffraction principle
  • Method for calculating wing shielding effect based on diffraction principle
  • Method for calculating wing shielding effect based on diffraction principle

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Embodiment Construction

[0107] Such as figure 1 As shown, a calculation method of wing occlusion effect based on the principle of diffraction, including:

[0108] Step 1, according to the Fresnel zone theory of electromagnetic propagation, the occlusion factor is defined outside the aircraft fuselage to describe the occlusion degree of the Fresnel zone;

[0109] In free space, the electric wave radiated from the wave source to the observation point, from the perspective of wave optics, can be regarded as propagating from multiple Fresnel zones. If the rotational symmetry with the propagation path as the axis is considered, the Fresnel The outer contour of the area should be a rotating ellipsoid with the source point and the observation point in the far area as the focus, in which the first Fresnel ellipsoid is the main channel for electromagnetic propagation, so the influence of the wing on the conformal array on the side of the fuselage Mainly depends on the area covered by the first Fresnel area, ...

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Abstract

The invention belongs to the technical field of antennas, particularly relates to a method for calculating a wing shielding effect based on a diffraction principle, and discloses a method for calculating a wing shielding effect based on a diffraction principle. The core of the design method is that the UTD is simplified by an electromagnetic propagation shielding algorithm based on a Fresnel zonetheory, and the complexity of ray tracing is reduced. Then, on the basis, establishing an electromechanical coupling model of the shielded conformal array in the presence of structural errors; by means of the method, the influence of the shielding object on the array far field can be calculated more quickly and accurately, and reference is provided for array layout design under next shielding. Themethod can be used for calculating the influence of the fixed shielding object on the carrier on the array conformal on the body of the large carrier. The method is suitable for calculating the influence of the fixed shielding object on the carrier aircraft on the conformal array located on the carrier aircraft on the far-field directional diagram.

Description

technical field [0001] The invention belongs to the technical field of antennas, and in particular relates to a method for calculating the shielding effect of wings based on the principle of diffraction, which is suitable for calculating the influence of a conformal array on a carrier aircraft on a far-field pattern by a fixed shield on the carrier aircraft. Background technique [0002] There are usually more than 20 or even as many as 70 antennas installed on an aircraft, and most of these antennas protrude from the outside of the fuselage. Taking the Boeing 737NG aircraft as an example, the captain of more than 30 meters is covered with various types of antennas, such as high-frequency communication antennas located on the front edge of the vertical stabilizer, localizer antennas, glideslope antennas, and pointing beacon antennas. Therefore, in a limited fuselage area, antenna performance will be affected by fixed obstructions on the carrier aircraft. For example, the Il...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
CPCY02T90/00
Inventor 曾元琛李娜段宝岩钟旺张烁孙梓涵
Owner XIDIAN UNIV
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