Dr. Xianghao Kong Profile

Dr. Xianghao Kong

at Harbin Institute of Technology

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Publications (3)

Proceedings Article | 15 April 2010 Paper

Dynamic response of metal honeycomb sandwich structure under high-speed impact

Xiaodong He, Xianghao Kong, Liping Shi, Mingwei Li

Proceedings Volume 7522, 752211 (2010) https://doi.org/10.1117/12.851563

KEYWORDS: Metals, Foam, Aluminum, Ceramics, Composites, Mechanics, Failure analysis, Experimental mechanics, Current controlled current source, Satellites

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Proceedings Article | 31 March 2010 Paper

Tensile mechanical properties of metal honeycomb sandwich structure with interface connection defects

Xiaodong He, Xianghao Kong

Proceedings Volume 7644, 764421 (2010) https://doi.org/10.1117/12.847264

KEYWORDS: Metals, Interfaces, Finite element methods, Composites, Failure analysis, Manufacturing, Tolerancing, Statistical modeling, Satellites, Mechanics

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Proceedings Article | 8 April 2009 Paper

Mechanical analysis of confectioning flaw of refractory alloy honeycomb sandwich structure

Xiaodong He, Xianghao Kong, Liping Shi, Mingwei Li

Proceedings Volume 7294, 72940J (2009) https://doi.org/10.1117/12.815677

KEYWORDS: Metals, Optical spheres, Composites, Mechanics, Heat treatments, Aerospace engineering, Temperature metrology, Lithium, Thermal modeling, Nondestructive evaluation

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Thermal protection system is one of the key technology of reusable launch vehicle (RLV). After C/C and ceramic-matrix composite used in space orbiter, one new-typed thermal protection systems (TPS)-ARMOR TPS is coming forth. ARMOR TPS is means adaptable, robust, metallic, operable, reusable TPS. The ARMOR TPS has many advantages, for example: fixing easily, longer life, good properties, short time of maintenance and service. The ARMOR TPS is one of important candidate structure of RLV. ARMOR thermal protection system in foreign countries for reusable launch vehicle is used instead of the traditional ceramic-matrix composite thermal protection system and C/C thermal protection system. Also the constituent feature of ARMOR thermal protection system is much better than the traditional TPS. In comparison with traditional TPS, the ARMOR TPS will be the best selection for all kinds of RLV. So the ARMOR thermal protection system will be used in aviation and spaceflight field more and more widely because of its much better performance. ARMOR TPS panel is above the whole ARMOR TPS, and the metal honeycomb sandwich structure is the surface of the ARMOR TPS panel. So the metal honeycomb sandwich structure plays an important role in the ARMOR TPS, while it bears the flight dynamic pressure and stands against the flight dynamic calefaction. The metal honeycomb sandwich structure is made using the technique of the whole braze welding. In the course of the vacuum high temperature braze welding, its surface will appear concave. The reasons which lead to the shortage are summarized and discussed. The difference of thermal expansion coefficient and pressure between the core and the panels may be the chief reasons. This paper will analyze the mechanics behavior of metal honeycomb sandwich structure in the course of the vacuum high temperature braze welding, then make sure the reasons and get a way to solve it. Haynes214 is a good material of face sheet at present. γ - TiAl and microlaminate materials are the candidate materials in the future.

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