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Load-carrying Capacity Analysis and Experimental Study of Radome Joint Structure
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Baojiang HOU1, 2, Jiao WANG2, Yufeng XING1, Yanxi LI2
Missiles and Space Vehicles | 2024, 47(4) : 88 - 94
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Missiles and Space Vehicles | 2024, 47(4): 88-94
• Simulation and Experimental Research •
Load-carrying Capacity Analysis and Experimental Study of Radome Joint Structure
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Baojiang HOU1, 2, Jiao WANG2, Yufeng XING1, Yanxi LI2
Affiliations
  • 1School of Aeronautic Science and Engineering,Beihang University,Beijing,100191
  • 2Beijing Institute of Space Long March Vehicle,Beijing,100076
Published: 2024-08-25 doi: 10.7654/j.issn.2097-1974.20240415
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As an important component of aircraft guidance system, non-metal radomes have multiple functions such as heat protection, wave transmission and load bearing. It is connected to the aircraft body through high-temperature resistant adhesive agent. Radome is frequently subjected to harsh mechanical and thermal loads during the period of service, and the joint structure is often the weakness of strength design. Therefore, accurate simulation for mechanical behavior of the joint structure and achieving accurate prediction of load-carrying capacity are crucial for the structural design and optimization of radome. Based on bilinear cohesive model, the failure behavior of radome adhesive interface is numerically described by ABAQUS. And then the damage evolution of adhesive layer is simulated, and the accurate prediction of bearing performance of radome joint structure under flight thermo-mechanical environment is achieved. The corresponding experimental study is carried out. The experimental results are in good agreement with the simulated ones, verifying the validity of numerical method. It provides an effective way to solve bearing problem of aircraft-level radome joint structure.

radome  /  cohesive model  /  joint structure  /  strength prediction  /  experimental study
Baojiang HOU, Jiao WANG, Yufeng XING, Yanxi LI. Load-carrying Capacity Analysis and Experimental Study of Radome Joint Structure[J]. Missiles and Space Vehicles, 2024 , 47 (4) : 88 -94 . DOI: 10.7654/j.issn.2097-1974.20240415
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Year 2024 volume 47 Issue 4
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doi: 10.7654/j.issn.2097-1974.20240415
  • Receive Date：2024-04-28
  • Online Date：2025-07-04
  • Published：2024-08-25
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  • Received：2024-04-28
  • Revised：2024-06-30
Affiliations
    1School of Aeronautic Science and Engineering,Beihang University,Beijing,100191
    2Beijing Institute of Space Long March Vehicle,Beijing,100076
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Citations
表12种不同金属材料的力学参数
科
Family		 属数
Number of
genus		 种数
Number of
species		 占总种数比例
Percentage of
total species (%)		 属
Genus		 种数
Number of
species		 占总种数比例
Percentage of total
species (%)
鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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