Aircraft Wing Section Assembly with Coordinated Aileron Linkage
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Solution Overview
Problem
High aspect ratio aircraft wings experience significant deformation and aileron reversal when ailerons are moved, due to torsional flexibility and limited space for actuation mechanisms, leading to reduced efficiency and increased complexity.
Innovation Solution
An aircraft wing section assembly featuring a structural spine with a support rod extending chordwise, connected to first and second levers that control moveable control surfaces, allowing for coordinated movement of leading and trailing edge cambering devices to enhance roll control and reduce deformation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a single long aileron is used on high aspect ratio wings, then roll control authority is improved, but wing deformation and aileron reversal increase
Solution Approach 1:
The aileron control system is segmented into two separate ailerons (inboard and outboard) on each wing, rather than using a single long aileron. This segmentation allows independent control of each aileron surface, reducing the slenderness ratio and twisting of individual ailerons while maintaining overall roll control authority through coordinated operation of multiple surfaces.
Solution Approach 2:
Instead of accepting wing deformation as an inevitable consequence of using long ailerons for roll control, the invention inverts the approach by using multiple shorter ailerons that actively counteract the deformation. The coordinated movement of inboard and outboard ailerons creates a more favorable aerodynamic environment that reduces adverse wing twisting and prevents aileron reversal.
2Stability of the object's composition
If the aileron is split into multiple shorter ailerons, then wing deformation is reduced, but device complexity increases
Solution Approach 1:
The control mechanisms for the inboard and outboard ailerons are merged into a single integrated system. A common actuation mechanism controls both ailerons through a linkage system, reducing the overall complexity compared to having completely separate control systems. The levers and connection mechanisms are designed to coordinate the movement of multiple ailerons through a unified control architecture.
Solution Approach 2:
The aileron system is designed with multi-functionality, where the same control mechanism serves multiple purposes: it controls both the inboard and outboard ailerons, and can operate in different configurations (split aileron mode or combined mode). This universality reduces the need for separate dedicated mechanisms for each aileron, thereby reducing overall device complexity.
3Force
If flaperons are used to provide both flap and aileron functions, then roll moment is improved, but flap efficiency decreases
Solution Approach 1:
The wing control surfaces are segmented into dedicated flaps and dedicated ailerons, with the ailerons positioned outboard of the flaps. This spatial segmentation allows each component to perform its specialized function optimally: flaps for lift enhancement during takeoff and landing, and ailerons for roll control during cruise and maneuvering, without compromising the efficiency of either system.
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 provides a compact, lightweight mechanism for actuating both leading and trailing edge cambering devices simultaneously, reducing wing deformation, enhancing roll control, and optimizing wing space for flaps, thereby improving fuel efficiency and reducing operating costs.
Implementation Method 1
a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the first end of the support rod, for pivotal movement with respect to the support rod, a second lever, for connection to and for moving a second moveable control surface, pivotally mounted to the second end of the support rod, for pivotal movement with respect to the support rod
Implementation Method 2
a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever with respect to the support rod causes pivotal movement of the second lever with respect to the support rod
Data Source
AI summary
An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.