Folding UAV Wing Mechanism for Compact Transport
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Solution Overview
Problem
Existing UAV designs face challenges in transportation due to large wingspans or rotors, requiring disassemblable and foldable designs, and often lack suitable launch devices for horizontal takeoff, especially for specific UAV designs.
Innovation Solution
A UAV with a folding mechanism featuring a central wing section and outer wing sections that pivot from a folded configuration to a deployed configuration, utilizing torsion and tension springs for biasing and a latch system for remote or automatic deployment, allowing the wing to unfold post-launch.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If the UAV has a large wingspan to create low drag fixed wing aircraft for long flight times, then flight duration is improved, but transportation becomes difficult
Solution Approach 1:
The wing is divided into multiple sections that can pivot independently relative to the fuselage and to each other, allowing the wingspan to be reduced for transportation while maintaining the full wingspan for flight operations
Solution Approach 2:
The wing structure transitions from a static fixed configuration to a dynamic foldable configuration, enabling the UAV to adapt its wingspan between transportation and flight modes
2Ease of operation
If the UAV uses a foldable wing design for easy transportation, then transportation ease is improved, but device complexity increases
Solution Approach 1:
The outer wing sections are positioned to nest within or alongside the central wing section when folded, maximizing space efficiency while minimizing the number of external components needed
3Adaptability or versatility
If the UAV lacks a suitable launch device for horizontal takeoff, then launch capability is limited, but device complexity is reduced
Solution Approach 1:
The wing is pre-configured in a folded state during launch, allowing the UAV to be propelled horizontally without requiring a complex launch device, and the wing deploys after launch when aerodynamic forces are sufficient
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 compact storage and efficient transportation of the UAV, facilitating horizontal takeoff and extended flight times by maintaining a low drag configuration, while enhancing stability through adjustable wing angles.
Implementation Method 1
The central wing section may be biased by means of a torsion spring.
Implementation Method 2
Each of the outer wing sections may be biased by means of a tension spring.
Implementation Method 3
The tension spring may be connected at one end to the central wing section and at the other end to the outer wing section via a pulley such that rotation of the outer wing section relative to the central wing section extends the tension spring.
Data Source
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AI summary
An unmanned aerial vehicle 2 comprising: a fuselage 4; and a wing 6 comprising a central wing section 12 pivotably mounted to the fuselage 4 and a pair of outer wing sections 14a, 14b pivotably mounted to the central wing section 12; wherein the wing 6 has a folded configuration in which the central wing section 12 and the outer wing sections 14a, 14b are stacked on top of one another and are aligned with a longitudinal axis of the fuselage 4; and a deployed configuration in which the central wing section 12 is substantially perpendicular to the fuselage 4 and the outer wing sections 14a, 14b extend from the central wing section 12 away from the fuselage 4.