Aluminum honeycomb sandwich plate of high thermal conductivity carbon fiber panel pre-embedded heat pipe and preparation method thereof

Abstract

The invention provides an aluminum honeycomb sandwich plate of a high thermal conductivity carbon fiber panel pre-embedded heat pipe and a preparation method thereof. The aluminum honeycomb sandwich plate includes high thermal conductivity carbon fiber panels, room temperature cured structural adhesive layers, an aluminum honeycomb core, a foam adhesive, a heat pipe and positioning rivets. The aluminum honeycomb core is internally provided with the heat pipe, the foam adhesive is arranged around the heat pipe, and the high thermal conductivity carbon fiber panels are laid on the upper surface and lower surface of the aluminum honeycomb core respectively through the room temperature cured structural adhesive layers. The invention solves the problem of insufficient shearing resistance of bonding interface caused by thermal expansion coefficient mismatch between an aluminum alloy material heat pipe and a carbon fiber panel material. By utilizing the high rigidity, micro-deformation and high thermal conductivity properties of the material, the application range of the spacecraft carbon fiber material panel aluminum honeycomb plate is further expanded, and the problems of spacecraft on-orbit deformation and high power consumption single-machine heat dissipation are solved.

Description

technical field [0001] The invention relates to aerospace vehicle structural plates, in particular to an aluminum honeycomb sandwich plate with heat pipes embedded in a high thermal conductivity carbon fiber panel and a preparation method thereof. Background technique [0002] The upper and lower panels of honeycomb sandwich structural panels widely used in spacecraft structures are generally made of aluminum alloy. With the improvement of high-resolution satellites’ requirements for on-orbit thermal deformation, the application requirements of high-modulus and high-strength carbon fiber materials in the entire satellite structure are gradually expanding. The thermal conductivity of the panel is only 10W / (m·K), which is 1 / 12 of the 120W / (m·K) of the aluminum alloy material, which greatly limits the heat dissipation of the high-power consumption stand-alone, so it is necessary to become a carbon fiber panel honeycomb sandwich panel On the other hand, if the aluminum alloy he...

AI Technical Summary

Problems solved by technology

With the improvement of high-resolution satellites’ requirements for on-orbit thermal deformation, the application requirements of high-modulus and high-strength carbon fiber materials in the entire satellite structure are gradually expanding. The thermal conductivity of the panel is only 10W / (m·K), which is 1 / 12 of the 120W / (m·K) of the aluminum alloy material, which greatly limits the heat dissipation of the high-power consumption stand-alone, so it is necessary to become a carbon fiber panel honeycomb sandwich panel On the other hand, if the aluminum alloy heat pipe is embedded in the carbon fiber panel honeycomb sandwich panel, the thermal expansion coefficients of the carbon fiber composite material and the aluminum alloy heat pipe are 22.7×10 -6 / °C, 0.8×10 -6 / °C, the difference in thermal expansion coefficient between the two will cause a large shear stress at the bonding interface, so it cannot pass the spacecraft ground thermal test assessment

[0003] In order to solve the problem of insufficient shear resistance of the bonded interface caused by the thermal expansion coefficient mismatch between the aluminum alloy material heat pipe and the carbon fiber panel material

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