Simulation method for super speed aircraft conformal sub-grid electromagnetic scattering characteristic analysis

Abstract

The invention discloses a simulation method for super speed aircraft conformal sub-grid electromagnetic scattering characteristic analysis. The simulation method includes the following steps: performing aerothermodynamics simulation according to an aerodynamic configuration, the flight speed and the flight height of an aircraft, and determining the plasma collision frequency and the plasma oscillation frequency of all parts through simulation information; performing subdivision on an aircraft model and a plasma sheath through a tetrahedron to obtain structure information of the aircraft model; mapping flow field point information to ridges of a finite difference time domain computing grid, and determining a zone with a relative dielectric constant more than 6 according to the collision frequency and the oscillation frequency on the ridges to perform sub-grid processing; processing junctions between the ridges of the finite difference time domain computing grid and a metal surface through a finite difference universal time domain method; and computing the plasma zone through an iterative formula of plasma to finally determine the radar cross section of the super speed aircraft. The simulation method has good adaptability and high computational efficiency.

Description

technical field [0001] The invention belongs to the technical field of electromagnetic scattering characteristics of ultra-high-speed aircraft, in particular to a simulation method for analysis of conformal sub-grid electromagnetic scattering characteristics of ultra-high-speed aircraft. Background technique [0002] In modern warfare, the radar cross section (RCS) of a weapon system is an important indicator of the "observability" of a radar system to a target. Carrying out research on the electromagnetic characteristics of hypersonic targets in near space can provide technical support for the effective detection of hypersonic aircraft and weapon penetration in near space. Most of the traditional RCS calculation software is developed based on the target of the aircraft body. The interaction mechanism between the plasma sheath and the electromagnetic wave is very complicated, and the traditional optical approximation analysis method is difficult to analyze. Therefore, it is...

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Problems solved by technology

[0004] (1) The modeling of the finite difference time domain method (FDTD) is not flexible enough. Due to the different shapes of the plasma sheaths generated by the high-speed flight of the hyperspeed aircraft, the aerodynamic shape of the aircraft is different, and the ordinary finite difference time domain method FDTD cannot simulate the hyperspeed aircraft. aerodynamic shape;

[0005] (2) Since the electromagnetic parameters of each part of the plasma sheath are different, the subdivision size of the calculation grid is determined according to the largest dielectric parameter, and the part with a larger dielectric parameter may be a small part, so it is bound to be For the small part of the relative dielectric parameter, the overall fine mesh is used, thus sacrificing the overall calculation time

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