Aircraft Control Device Hinge Line Positioning for Chord Optimization
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Solution Overview
Problem
Conventional aircraft wing designs face limitations in chord length and span-wise extent of control surfaces due to the arrangement of hinge assemblies, leading to reduced lift performance, increased weight, and complex installation processes, particularly when routing cables and pipes through closed gaps.
Innovation Solution
The hinge line is positioned closer to the rear spar than the control device spar, allowing for adjustable actuator length to increase chord length and reduce the span of control devices, with flexible lines routed outside the hinge assembly for simplified installation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the hinge line is positioned closer to the control device spar, then the chord length available for the control device is increased, but the span-wise extent of the flaps is limited
Solution Approach 1:
The patent inverts the conventional hinge line positioning by placing it closer to the rear spar rather than closer to the control device spar. This reversal of the traditional arrangement resolves the contradiction by simultaneously providing sufficient chord length for effective control surfaces while maintaining adequate span-wise extent for high lift performance.
2Reliability
If a conventional spar bracket arrangement is used, then the control device can be coupled to the rear spar, but the bracket is complex and bulky resulting in cost and weight penalties
Solution Approach 1:
The patent extracts the hinge line from the complex conventional spar bracket arrangement and positions it directly on the rear spar. This eliminates the need for bulky spar brackets while maintaining reliable control device coupling, thereby reducing both weight and manufacturing cost.
3Ease of manufacture
If cable and pipe runs are routed through the closed gap in the spar bracket, then connections can be made, but the process is difficult and time consuming
Solution Approach 1:
The patent converts the previously harmful closed gap in the spar bracket into a beneficial open configuration. By positioning the hinge line directly on the rear spar without requiring a closed bracket structure, cable and pipe runs can be easily routed through the open space, significantly reducing installation difficulty and time.
Data Source
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AI summary
An aircraft structure comprising: a main structure element comprising a rear spar (10, 11, 12), a control device(15) comprising an control device spar (16, 17, 18), and a hinge assembly comprising: a spar bracket(21) attached to the rear spar, and a control device bracket (23, 24, 25) attached to the control device spar and pivotally coupled to the spar bracket about a hinge line (22); and an actuator (27) for rotating the control device about the hinge line. The actuator is pivotally coupled to the main element at a first pivot point (28) and to the controldevice at a second pivot point (29), the length ofthe actuator between the pivot points being adjustable so as to rotate the control device in a first direction about the hinge line from a neutral position to a first deployed position, and in a second opposite direction about the hinge line from the neutral position to a second deployed position. The hinge line is positioned closer (A) to the rear spar than to (B) the control device spar. A flexible line (30) is fixed to the main structure element, and extends in a span-wise direction along the structure.