Aircraft Wing Slat Track Hinge Mechanism
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Solution Overview
Problem
Existing aircraft wing designs with slat tracks require penetration of the front spar, leading to complex constructions and increased costs due to the need for a track can to seal the area behind the front spar.
Innovation Solution
A rotatable connection assembly where the slat track is connected to the slat via a hinge and a link element, allowing movement without penetrating the front spar, with the link element mounted to the main wing via another hinge, enabling a compact design that eliminates the need for a track can.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the slat track is fixedly connected to the first track end and moves along a curved path, then the slat achieves the required curved movement path for takeoff and landing, but the front spar must be penetrated requiring a complex track can construction
Solution Approach 1:
The connection assembly is divided into separate functional components: the slat track remains external to the front spar, while the link element with hinges (first hinge connecting slat track to slat, second hinge connecting link element to slat, third hinge connecting link element to main wing) provides the necessary movement control without penetrating the spar structure. This segmentation eliminates the need for track can construction.
Solution Approach 2:
The link element acts as an intermediary mechanism between the slat track and the main wing. It translates the linear movement of the slat track into the required curved movement path of the slat through rotational joints (hinges), achieving the desired slat trajectory without requiring the slat track to penetrate the front spar.
2Volume of moving object
If the slat track penetrates the front spar to achieve compact mounting, then the connection assembly is more compact, but the construction becomes complex requiring sealing of fuel tank areas
Solution Approach 1:
The connection assembly components are arranged externally to the front spar rather than penetrating it. The slat track, link element, and hinges are positioned in the leading edge portion of the main wing without compromising the front spar integrity, eliminating the need for complex sealing constructions while maintaining compact overall dimensions.
Solution Approach 2:
The connection assembly utilizes the three-dimensional space in the leading edge portion of the main wing more effectively. By arranging the slat track and link element in a spatial configuration that extends in multiple dimensions rather than requiring linear penetration through the front spar, the design achieves compact mounting without compromising structural integrity or requiring sealing modifications.
3Device complexity
If the slat track is mounted externally without penetrating the front spar, then the construction is simplified and no track can is required, but the connection assembly requires more space in the leading edge portion
Solution Approach 1:
The link element is designed as a rotating arm that pivots about hinge axes, creating curved movement paths. This curved kinematic mechanism allows the connection assembly to achieve the necessary slat movement range within a more compact spatial footprint in the leading edge portion, reducing the area required compared to straight-line actuation mechanisms.
Solution Approach 2:
The connection assembly uses dynamic rotational joints (hinges) instead of static fixed connections. The first hinge, second hinge, and third hinge allow the link element and slat track to rotate and adapt their position dynamically, enabling the assembly to occupy variable space configurations that minimize the required leading edge area while maintaining full functionality.
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
This solution allows for a more compact and cost-effective wing design by avoiding the penetration of the front spar and simplifying the construction, reducing maintenance efforts and costs.
Implementation Method 1
The slat track is connected to the slat in a rotatable, in particular pivotable, manner via a first hinge, preferably at the first track end. Further, the connection assembly comprises a link element which is rotatably, in particular pivotably, connected to the slat via a second hinge, preferably at its first link end. The link element is, further, rotatably, in particular pivotably, mounted to the main wing via a third hinge spaced apart from the second hinge
Data Source
AI summary
A wing for an aircraft, comprising a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, allowing the slat to be moved between a retracted and at least one extended position. The assembly comprises an elongate slat track mounted to the main wing movably along a track longitudinal axis and connected to the slat. The wing has a compact connection assembly that does not require the front spar to be penetrated, in that the slat track is rotatably connected to the slat via a first hinge. The assembly further comprises a link element rotatably connected to the slat via a second hinge, and rotatably mounted to the main wing via a third hinge spaced apart from the second hinge. Also, a first axis of rotation of the first hinge is spaced apart from a second axis of rotation of the second hinge.