Method for quickly calculating influence of high-temperature ablation of high-speed aircraft cover body on electrical property of antenna

Abstract

The invention discloses a method for quickly calculating the influence of high-temperature ablation of a high-speed aircraft cover body on the electrical property of an antenna. The method comprises the steps that material attributes and thermal boundary conditions of a high-speed aircraft antenna cover are determined; the simulated antenna cover body ablation process undergoes transient thermal analysis; overall temperature distribution and outer surface ablation morphology of the antenna cover are extracted at a certain moment; dielectric constants and loss tangent under the temperature distribution at the moment are calculated; the thickness after antenna ablation is calculated; transmission coefficients after change of the dielectric constants, the loss tangent and thickness are calculated; the transmission coefficients of the ablated antenna cover are calculated; the electrical property functions of an ideal antenna cover-antenna system are determined; a model is established, andthe electric property of the antenna after the high-speed aircraft antenna cover is ablated is calculated. By adopting the method, the influence of high-temperature ablation of the high-speed aircraftcover body on the electrical property of the antenna in the process of flying in a near space can be quickly and effectively calculated, a theoretical guidance is provided for design, real-time compensation and the like, and thus reliable work of a high-speed aircraft guiding system is ensured.

Description

technical field [0001] The invention belongs to the technical field of antennas, and in particular relates to a fast calculation method for the influence of high-temperature ablation of a cover of a high-speed aircraft on the electrical performance of an antenna. Background technique [0002] A vehicle that cruises and flies at a speed above Mach 5 in the atmosphere or across the atmosphere is called a hypersonic vehicle. Compared with traditional aircraft, hypersonic aircraft has great advantages, and its extremely high flight speed can ensure that it can reach any location in the world within 2 to 3 hours. [0003] The radome at the front end of the hypersonic vehicle is an important part of the spacecraft, and the radome working under the hypersonic flight environment will be subjected to severe aerodynamic heating during the long-term flight near space, causing high-temperature burns on the surface of the radome. erosion, and the ablation of the radome can have a signif...

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Problems solved by technology

[0004] At present, the research results on the influence of radome on electrical performance after high temperature ablation are different, such as How Lihua. Research on transmission characteristics of radome in asymmetrical thermal environment [D]. University of Electronic Science and Technology of China, 2006, the radome cover according to The temperature distribution interval is segmented, and the dielectric of each segment is represented by the average value of the segment. The influence of the asymmetric thermal environment on the electrical performance under the influence of ablation is analyzed. This method only considers the aerodynamic heat on the temperature distribution of the radome. , ignoring the effect of the thickness change on the radome after ablation

Zhang Junwu, Liu Lianyuan. Thermal-electrical joint simulation calculation method for hypersonic vehicle radome[J]. High Speed ​​Vehicle and Space Vehicle Technology, 2012(4): 53-57, using one-dimensional ablation calculation program and ANSYS Multiphysics simulation module for a certain The model radome is respectively ablated and calculated for the temperature field, and the appearance of the radome is obtained by interpolation method,

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