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A novel method for calculating broadband electrical performance of high-speed aircraft radome under thermo-mechanical-electrical coupling

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CHINESE JOURNAL OF AERONAUTICS 2024年第9期37卷 463-474页

作者： Ji, Jianmin Ren, Jianhua Jiang, Xunya Wang, Wei Yu, Huilong Yin, Kai Chen, Bo Beijing Inst Remote Sensing Equipment Beijing 100854 Peoples R China Shanghai DongJun Informat & Technol Co Ltd Shanghai 200050 Peoples R China

The electrical performance of radomes on high-speed aircraft can be influenced by the thermal and mechanical loads produced during high-speed flight, which can affect the detection distance and accuracy of the guidance system. This paper presents a new method that uses the Finite Difference Time Domain (FDTD) method to calculate the electrical performance of radomes under Thermo-Mechanical-Electrical (TME) coupling. This method can accurately characterize the effects of material dielectric temperature drift and structural deformation on the electrical performance of the radome under flight conditions, enabling high-precision full-wave calculations of the broadband electrical performance of the radome. The method initiates by utilizing a Finite Element Grid Model (FE-GM) of the radome to sequentially acquire the radome's response temperature field and structural deformation field through thermal and mechanical simulations. Subsequently, spatial mapping techniques are developed to accurately incorporate the dielectric temperature drift and structural deformation of the radome into its Yee grid Electromagnetic (EM) simulation model. A verification case was designed to test the proposed method, and the results confirmed its high computational accuracy. Additionally, the effectiveness and necessity of the method were further demonstrated by analyzing the electrical performance of a fused silica ceramic radome used on a high-speed aircraft. (c) 2024 Production and hosting by Elsevier Ltd. on behalf of Chinese Society of Aeronautics and Astronautics. This is an open access article under the CC BY-NC-ND license (http://***/ licenses/by-nc-nd/4.0/).

关键词： high-speed aircraft Radomes Thermo-Mechanical- Electrical (TME) coupling Finite Difference Time Domain (FDTD) method Spatial mapping DESIGN

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Analysis and comparison of potential power and thermal management systems for high-speed aircraft with an optimization method

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能源与人工环境(英文) 2021年第1期2卷 13-20页

作者： Rong A Liping Pang Xinying Jiang Bin Qi Yong Shi Institute of Manned Space System Engineering China Academy of Space TechnologyBeijing10094China School of Aeronautic Science and Engineering Beijing University of Aeronautics and AstronauticsBeijing100191China

Under the dual effects of aerodynamic heating and high-power electronic equipment heating,the heat sink and power demand of advanced high-speed aircraft have been exponentially rising,which seriously restricts the aircraft *** improve system cooling and power supply performance and reduce engine performance loss,a power and thermal management system(PTMS)with high performance,low energy consumption,and light weight urgently needs to be *** this paper,three modes of a potential PTMS with different heat sinks and bleed air sources are further discussed to analyze and compare the optimal matching with the flight mission at Mach *** equivalent mass method is used to uniformly assess the costs of the fixed weight,bleed,resistance,*** a function of the fuel weight penalty,which is chosen as the optimization *** optimization variables consist of the compressor outlet temperature,cooling air flow rate,and fan duct heat exchanger structure *** results show that the intermediate-stage bleed air and fan duct heat sink are more suitable when the Mach number is less than 2,but the ram air bleed is highly suitable for flight missions at a high Mach *** at Mach 3.4-4.4,the ram air bleed mode can respond to the cooling and power demands with a simple architecture.

关键词： Power and thermal management system high-speed aircraft Fuel weight penalty Optimization design

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