Composite Wing UAV Plug-In Assembly for Vibration-Safe Reuse
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Solution Overview
Problem
The assembly process of composite wing UAVs is complex and prone to electrical system damage due to body vibration, making repeated disassembly and use inconvenient.
Innovation Solution
A plug-in assembly structure comprising a first component with a positioning sleeve and a second component with a limit hole, utilizing elastic elements for quick assembly and disassembly, and a limit releasing mechanism for secure electrical connections.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multi segment structure is adopted for composite wing UAV, then the UAV can achieve vertical takeoff and long endurance flight capabilities, but the assembly process becomes complex and electrical system cables are damaged by body vibration
Solution Approach 1:
The UAV is divided into separable modules (fuselage, wings, tail) that can be independently assembled and disassembled. The plug-in assembly structure allows these segments to be quickly connected and disconnected without complex assembly procedures, resolving the contradiction between versatility and assembly complexity.
Solution Approach 2:
A plug-in assembly structure with positioning sleeves, limit assemblies, and releasing mechanisms serves as an intermediary component between UAV segments. This intermediary mechanism simplifies the connection process, enabling quick assembly and disassembly while protecting electrical cables from vibration damage.
2Adaptability or versatility
If multi segment structure is adopted for composite wing UAV, then the UAV can achieve vertical takeoff and long endurance flight capabilities, but repeated disassembly and use becomes inconvenient
Solution Approach 1:
The plug-in assembly structure incorporates dynamic elements including elastic limiting elements that can be easily compressed and released, and releasing mechanisms that enable quick disassembly. This dynamic design allows the UAV to be repeatedly assembled and disassembled without complexity, maintaining ease of operation while achieving versatile flight capabilities.
3Stability of the object's composition
If traditional assembly structure is used, then structural integrity is maintained, but assembly efficiency is low and electrical system cables are severely damaged by body vibration
Solution Approach 1:
The plug-in assembly structure includes pre-designed positioning sleeves with positioning holes and limit assemblies that are prepared in advance. These preliminary structural arrangements ensure proper alignment and secure connection during assembly, maintaining structural integrity while dramatically improving assembly efficiency.
Solution Approach 2:
The plug-in assembly structure acts as an intermediary connection mechanism that protects electrical system cables from body vibration damage while maintaining structural integrity. The positioning sleeves and limit assemblies create a stable connection that isolates electrical components from vibrational stresses.
4Productivity
If plug-in assembly structure is implemented, then assembly efficiency is improved, but additional components such as positioning sleeves and limit assemblies are required
Solution Approach 1:
The plug-in assembly structure merges multiple functions into integrated components. The positioning sleeve combines positioning, alignment, and connection functions; the limit assembly combines limiting, securing, and releasing functions. This merging reduces the overall number of separate components needed while maintaining high assembly efficiency.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables efficient and reliable assembly and disassembly of the UAV's fuselage and tail, reducing electrical system damage from vibrations and improving overall assembly efficiency.
Implementation Method 1
one end of the first elastic element is abutted against the bottom of the limit hole, and the other end of the first elastic element is connected to the limit element; the limit element is at least partially located in the limit hole, and the first elastic element is used to push the limit element toward the outside of the limit hole
Implementation Method 2
one end of the second elastic element can be butted with the sleeve, and the other end of the second elastic element can be butted with the firing pin, so that the firing pin can move back and forth along the axis direction of the sleeve
Data Source
AI summary
A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).