A lightweight shell aerial vehicle

By using the synergistic design of buffer energy absorption components and shock absorption protection components, and utilizing the combined effects of gas and mechanical energy absorption, the problem of balancing the buffering performance and lightweight structure of lightweight aircraft under impact is solved, thus achieving effective energy dissipation and pilot protection.

CN224392942UActive Publication Date: 2026-06-23GUANGDONG YUFEI AVIATION INVESTMENT CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
GUANGDONG YUFEI AVIATION INVESTMENT CO LTD
Filing Date
2025-07-29
Publication Date
2026-06-23

AI Technical Summary

Technical Problem

When traditional lightweight aircraft land, the impact energy is directly transferred to the fuselage shell, causing significant vibration in the cockpit. Existing cushioning designs increase weight and lack reliability, making it difficult to balance lightweight design with cushioning performance.

Method used

By employing buffer energy absorption components and shock absorption protection components, and utilizing a buffer shell, piston plate, energy absorption mechanism, shock absorption mechanism and elastic reset mechanism, energy is absorbed through gas and mechanical synergy, replacing the traditional hydraulic system, simplifying transmission components and improving energy dissipation efficiency.

Benefits of technology

It effectively absorbs impact energy without increasing weight, reduces body vibration, optimizes energy distribution, solves the problems of increased weight and insufficient reliability caused by traditional hydraulic systems, and maintains the requirements of lightweight design.

✦ Generated by Eureka AI based on patent content.

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Abstract

The utility model discloses a kind of lightweight shell aerospace vehicles, it is related to aerospace vehicle technical field.The utility model includes aircraft body, the rear side fixedly connected with seat in aircraft body inner chamber top, the bottom of aircraft body is installed with buffer energy-absorbing component, the bottom of seat inner chamber is installed with shock protection component.The utility model passes through buffer energy-absorbing component, landing impact energy is converted into gas pressure change using the cooperation of buffer shell and piston plate, airflow damping is formed by repulsion between strong magnet in energy-absorbing mechanism and magnetic ring, in combination with the absorption of shock-absorbing mechanism to landing gear impact force, effectively replace traditional multistage hydraulic shock-absorbing structure, while avoiding rigid impact transmission path in simplifying transmission component, significantly reduce the risk of local deformation caused by stress concentration in fuselage, both maintain lightweight design requirements, and improve energy dissipation efficiency through gas and mechanical collaborative buffering.
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