Aircraft Folding Wing System with Segmented Hinges
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Solution Overview
Problem
Conventional folding wing systems for aircraft are either not flexible or robust enough, and they lack independent control of wing segments, which affects stability and space efficiency during flight and landing.
Innovation Solution
A folding wing system with a support structure, segmented wings, and a strut that allows for independent control of wing segments through hinged connections and drives, enabling robustness and flexibility, and accommodating a third segment for increased surface area and efficiency, along with a landing foot for safe ground support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If conventional cable actuation is used to fold wing sections, then the construction is lightweight, but the wing sections cannot be moved individually and stability is low
Solution Approach 1:
The wing is divided into multiple independently controllable segments (first wing section, second wing section, third wing section) that can be folded and positioned separately. Each segment has its own drive mechanism, allowing independent movement and stabilization, resolving the contradiction between lightweight construction and stability by enabling precise positional control of each segment.
Solution Approach 2:
The folding mechanism transitions from a static, concerted movement system to a dynamic system where each wing section can be moved and positioned independently at different times and to different positions. The drives enable sequential and individual actuation of hinge connections, providing dynamic control over wing configuration for enhanced stability.
2Reliability
If robust folding mechanism is designed for flight, then stability is improved, but the mechanism becomes heavier and less flexible
Solution Approach 1:
The robustness is achieved through segmented architecture where each wing section has dedicated support structures and drive mechanisms. This segmentation allows each component to be optimized for its specific function, maintaining reliability during flight while avoiding the need for an overly robust (and heavy/complex) monolithic folding mechanism.
Solution Approach 2:
The hinge connections and drive mechanisms are designed to serve multiple functions: enabling folding during landing, providing structural support during flight, and allowing independent positioning of wing sections. This multi-functionality reduces the need for separate components, thereby reducing overall complexity while maintaining robustness.
3Adaptability or versatility
If wing segments are controlled independently, then flexibility and maneuverability are improved, but the control system becomes more complex
Solution Approach 1:
The control system is segmented into independent drive units, each controlling specific hinge connections. This segmentation allows flexible and independent control of each wing section while keeping each individual control unit relatively simple, avoiding the need for a single complex centralized control system.
Solution Approach 2:
The drive mechanisms are positioned and configured to directly actuate the hinge connections, enabling preliminary positioning of each wing section before final configuration is achieved. This preliminary action simplifies the overall control sequence by breaking down complex maneuvers into simpler, independently controlled steps.
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
The system provides a lightweight yet robust wing structure, enhanced stability, and increased maneuverability, allowing for vertical take-off and landing, reduced drag, and improved landing safety, while maintaining a compact folded configuration.
Implementation Method 1
the support structure is connected to a proximal end of the first segment via a first hinged connection and wherein a distal end of the first segment is connected to a proximal end of the second segment via a second hinged connection such that the wing is foldable from a cruise position to a folded position by pivoting the first segment up and the second segment down
Implementation Method 2
said second segment has a bearing supporting a distal end of the strut both slidably along a longitudinal direction running from the proximal end to a distal end of the second segment and pivotably about an axis transverse to said longitudinal direction
Data Source
AI summary
A folding wing system for an aircraft, comprises a support structure mountable on the aircraft, and a wing segmented into at least a first and a second segment. The support structure is connected to the first segment via a first hinged connection and the first segment is connected to the second segment via a second hinged connection such that the wing is foldable from a cruise position to a folded position. The support structure is connected to a strut via a third hinged connection. The second segment has a bearing supporting a distal end of the strut both slidably and pivotably. A first drive is configured to drive one of the first and third hinged connections, and a second drive is configured to drive one of the second hinged connection, the bearing, and the other one of the first and third hinged connections.