Composite multilayer structure for launch vehicle fuel tank and release method

By employing a composite multi-layer structure and active deformation mechanism on the launch vehicle's fuel tank, the skin layer is transformed into a large-area configuration after the mission ends, solving the problem that the fuel tank cannot autonomously deorbit, and achieving efficient orbital debris mitigation and lightweight design.

CN122170710BActive Publication Date: 2026-07-07LUZHOU VOCATIONAL & TECHN COLLEGE
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
LUZHOU VOCATIONAL & TECHN COLLEGE
Filing Date
2026-05-12
Publication Date
2026-07-07

AI Technical Summary

Technical Problem

Existing technologies cannot effectively solve the problem of autonomous deorbiting of launch vehicle fuel tanks after the mission, resulting in them becoming long-term orbital debris. Furthermore, existing deorbiting devices increase system complexity and weight, violating the requirements for lightweight design.

Method used

The fuel tank, which adopts a composite multi-layer structure, includes a sealed inner liner, a composite material load-bearing layer, and a multi-functional skin layer. After the mission is completed, the skin layer changes from conforming to the shape of the tank to a large-area configuration through an active deformation mechanism, and the mechanical connection with the load-bearing layer is released. The deorbiting is driven by shape memory materials and energy harvesting devices.

Benefits of technology

It achieved autonomous deorbiting of the fuel tank, reducing the thermal load and aerodynamic disturbances during atmospheric reentry, decreasing recovery costs, and meeting international space debris mitigation standards.

✦ Generated by Eureka AI based on patent content.

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    Figure CN122170710B_ABST
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Abstract

The application discloses a composite multi-layer structure and a release method for a launch vehicle fuel tank, wherein the tank comprises, from inside to outside, a sealing inner liner, a composite material load-bearing layer and a multifunctional skin layer, and the method comprises the following steps: S1, in a task service stage, the multifunctional skin layer is rigidly connected with the composite material load-bearing layer, and the multifunctional skin layer and the composite material load-bearing layer are used as a main load-bearing shell and an external protection system of the tank; S2, after receiving a task end instruction, a preset active deformation mechanism in the multifunctional skin layer is triggered; S3, under the driving of the active deformation mechanism, the multifunctional skin layer is changed from a first configuration which is attached to the shape of the tank to a second configuration which has a larger space-wise dimension; S4, in the configuration changing process or after reaching the second configuration, the mechanical connection between the multifunctional skin layer and the composite material load-bearing layer is released; and S5, the multifunctional skin layer which is changed into the second configuration has a magnitude order of improvement in aerodynamic characteristic area relative to the first configuration, so as to drive or assist the tank body to accelerate off the orbit.
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