Morphing Wing Spar Assembly with Pivoted Linkages
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Solution Overview
Problem
Morphing wings face challenges such as heavy and cumbersome actuation mechanisms, significant cost and weight penalties, and stress generation due to camber changes, which impact their aerodynamic efficiency and structural integrity.
Innovation Solution
An aircraft wing design featuring a spar assembly with adjustable, pivoted linkages between upper and lower attachment structures, allowing for warping by altering the distance between pivots, which provides mechanical advantage and reduces the load on actuators, enabling efficient control without discrete control surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If actuation mechanisms are used to manipulate wing geometry in morphing wings, then the wing can change shape for aerodynamic efficiency, but the actuation mechanisms become heavy and cumbersome to accommodate flight load requirements
Solution Approach 1:
The wing structure is segmented into discrete modular units (wing box sections) spaced along the span, each equipped with its own actuation mechanism. This segmentation allows each actuator to control a specific section independently, reducing the overall weight compared to a continuous actuation system while maintaining the ability to change wing geometry for aerodynamic efficiency
Solution Approach 2:
The invention employs a compliant rib structure that dynamically changes geometry in response to actuator input. The rib includes a leading edge portion, trailing edge portion, and web that can flex and deform to alter the aerofoil shape. This dynamic compliance allows the wing to achieve morphing capability with lighter actuators compared to rigid actuation systems
2Strength
If morphing mechanisms are required at regular spanwise intervals to perform structural rib functions, then the wing can maintain structural integrity, but this represents a significant cost and weight penalty
Solution Approach 1:
The actuation mechanisms are integrated with the rib structures to serve dual functions: they act as both the morphing actuation system and the structural ribs simultaneously. The actuator housing forms part of the rib assembly, eliminating the need for separate structural ribs at each actuation station. This multi-functionality reduces the total weight and cost compared to having dedicated structural ribs in addition to morphing mechanisms
Solution Approach 2:
The invention merges the actuation mechanism and rib structure into a single integrated assembly. The actuator is mounted within the wing box such that its housing and mounting structure form part of the rib, combining the functions of shape control and structural support into one component, thereby reducing overall weight and complexity
3Adaptability or versatility
If the wing covers need to bend and distort to change camber of the aerofoil section, then the wing can achieve morphing capability, but this generates stresses in the covers that may impact their overall size
Solution Approach 1:
The wing covers are designed as flexible shells that can bend and distort to accommodate camber changes. The cover structure includes skin panels and spars that are configured to flex within acceptable stress limits, allowing the aerofoil camber to change while maintaining structural integrity. This flexibility enables morphing capability without requiring excessive cover thickness that would add weight
Data Source
AI summary
A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.