一种模块化与轻量化相结合的固定翼无人机
The modular and lightweight design of the fixed-wing drone solves the problems of high maintenance costs, inconvenient deployment, and mismatched power configuration of traditional drones, enabling partial replacement, rapid deployment, and efficient flight.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHENYANG AEROSPACE UNIVERSITY
- Filing Date
- 2025-06-12
- Publication Date
- 2026-07-17
AI Technical Summary
Traditional fixed-wing UAVs have easily damaged fuselage structures that require complete replacement, resulting in high maintenance costs, low repair efficiency, and difficulty in rapid deployment using general-purpose vehicles due to their fixed wingspan structure. Furthermore, their power configuration is not compatible with flight requirements.
It adopts a modular and lightweight design. The fuselage, main wing and tail are joined by mortise and tenon joints and glued splicing. The main wing is foldable and uses carbon fiber and aviation paulownia wood composite material. The skin is made of light wood board and heat shrink film composite material. The main wing airfoil is MH114, the tail is NACA0009, the engine is 2216-9KV1100, and the propeller is 9060 saber propeller.
It allows for individual replacement in case of partial damage, reducing maintenance costs and improving repair efficiency. The main wing can be quickly deployed via general-purpose vehicles after folding. The power configuration matches flight requirements, reducing energy consumption and improving range and wind resistance.
Smart Images
Figure CN224511477U_ABST
Abstract
Claims
1. A fixed-wing unmanned aerial vehicle (UAV) combining modularity and lightweight design, comprising a fuselage, main wings, and a tail fin, wherein the main wings are symmetrically distributed on both sides of the fuselage, and the tail fin is located at the rear of the fuselage, characterized in that: The fuselage, main wing, and tail are all assembled using mortise and tenon joints and glued splicing; the main wing adopts a folding structure with an aerospace-grade aluminum alloy hinge in the middle; the fuselage frame is made of carbon fiber and aerospace paulownia wood composite material; the skin of the fuselage, main wing, and tail is made of balsa wood and heat shrink film composite material.
2. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The assembly tolerance of the mortise and tenon joint surface of the mortise and tenon joint and the glue fixation splicing assembly structure is ±0.1mm, and a seamless connection structure is formed after glue fixation.
3. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The main wing and tail wing are manufactured using a modular segmented debugging process. During the final assembly of the main wing and tail wing, they are connected to the carbon fiber tubes via metal connectors, and the connection points are coated with two-component epoxy resin AB glue.
4. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The root rib of the main wing adopts a horizontal wood grain support structure, which is made of 2mm plywood strips bonded vertically.
5. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The skin is made using a segmented semi-coating process, and electronic equipment assembly windows are reserved on the main wing and tail wing. The electronic equipment assembly windows are sealed after being coated.
6. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The carbon fiber in the carbon fiber and aerospace paulownia wood composite material is 3K carbon fiber, and the thickness ratio of 3K carbon fiber to aerospace paulownia wood is 7:
9.
7. A fixed-wing UAV combining modularity and lightweight design according to claim 1, characterized in that: A Kevlar reinforcement layer is bonded to the ground-contacting part of the fuselage using two-component epoxy resin AB adhesive.
8. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The thickness of the balsa wood board in the composite material of balsa wood board and heat shrink film is 0.75 mm.
9. The fixed-wing unmanned aerial vehicle of claim 1, wherein: The main wing has an airfoil of MH114, and the tail wing has an airfoil of NACA0009.
10. The fixed-wing unmanned aerial vehicle of claim 1, wherein: An engine mount is fixedly installed in the middle of the half-wing body on the root side of the main wing, and the engine is mounted on the engine mount; the engine model is 2216-9KV1100, the engine propeller is a 9060 saber propeller, the engine ESC is a 40A ESC, and the engine power supply battery is a 2200mAh 4s 120c battery.