Aircraft Hinge Mechanism Without Cut-Outs for Low-Drag Deployment
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Solution Overview
Problem
Aircraft components with cut-out designs for flight control surfaces create high-speed drag and integration constraints due to the need for cut-outs for hinge mechanisms, limiting aerodynamic performance.
Innovation Solution
A hinge mechanism utilizing a 4-bar mechanism with natural gooseneck features that allows flight control members to rotate without cut-outs, enabling a larger panel area when deployed and improved integration by replicating a hingeline through a 4-bar mechanism, adaptable for spoilers, Krueger flaps, and landing gear doors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If cut-out designs are used for flight control surfaces to facilitate movement between stowed and deployed positions, then ease of operation is improved, but aerodynamic drag increases and manufacturing precision is worsened
Solution Approach 1:
The hinge mechanism is divided into multiple segments including a first hinge member, a second hinge member, and a connector. This segmentation allows each component to perform a specific function while collectively enabling the flight control surface to move between stowed and deployed positions without requiring cut-outs in the aerodynamic surface, thus reducing drag while maintaining ease of operation.
2Ease of operation
If cut-out designs are used for hinge mechanisms to facilitate flight control surface movement, then ease of operation is improved, but device complexity is worsened
Solution Approach 1:
The hinge mechanism components are nested within each other, with the first hinge member connected to the second hinge member through a connector. This nested arrangement allows the entire hinge mechanism to be integrated into the aircraft structure without requiring cut-outs, reducing device complexity while maintaining ease of operation for flight control surface movement.
3Area of moving object
If larger panel area is used when deployed, then aerodynamic efficiency is improved, but device complexity is worsened
Solution Approach 1:
The hinge mechanism is designed with dynamic characteristics, allowing the flight control surface to achieve a larger deployed panel area while the mechanism itself remains relatively compact. The first hinge member, second hinge member, and connector work together to provide the necessary motion range, enabling larger panel area without proportionally increasing device complexity.
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 solution reduces drag and enhances integration by allowing complex motion of hinged items, providing an expanded design space for trajectory and better integration, while maintaining aerodynamic efficiency.
Implementation Method 1
a first hinge member pivotably coupled to the flight control member about a first axis and slidingly coupled to the aircraft component and a second hinge member pivotably coupled to the aircraft component about a second axis and slidingly coupled to the flight control member
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
A hinge mechanism (100) for hingedly coupling a flight control member (150) having a top surface (152) to an aircraft component (160) having a top surface (162) includes a first hinge member (110) pivotably coupled to the flight control member (150) about a first axis and slidingly coupled to the aircraft component (160) and a second hinge member (120) pivotably coupled to the aircraft component (160) about a second axis and slidingly coupled to the flight control member (150). The first hinge member (110) is pivotably coupled to the second hinge member (120) about a central axis. The first hinge member (110) and the second hinge member (120) are configured to cooperatively facilitate movement of the flight control member (150) relative to the aircraft component (160) between at least a stowed position (10) and a deployed position (20).