Rotary Drive Assembly for Aircraft Wing Tip Rotation
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Solution Overview
Problem
Existing wing assemblies for aircraft face challenges in reducing wingspan for operation at smaller airports due to large strains on rotation mechanisms and the need for complex, large components that may not fit within the wing, limiting the number of airports an aircraft can serve.
Innovation Solution
A rotary drive assembly comprising a tip hinge box, a body hinge box, a rotary actuator, and a linkage mechanism that allows the wing tip to rotate relative to the wing body, providing a mechanical advantage by reducing stress on the actuator and enabling a smaller actuator size, with a geared rotary actuator and bushings for efficient operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a direct drive system is used to rotate the wing tip, then the rotation mechanism can be simplified, but large strains are placed on the rotation mechanism requiring larger and more complex components
Solution Approach 1:
A linkage mechanism acts as an intermediary between the rotary actuator and the wing tip rotation system. This linkage mechanism includes a four-bar linkage with a ground link, input link, coupler link, and output link that transfers and transforms the actuator's rotational motion into wing tip rotation while reducing the strain on the actuator through mechanical advantage
Solution Approach 2:
The rotation mechanism is segmented into multiple components: a rotary actuator, a linkage mechanism with multiple links, a tip hinge box, and a body hinge box. This segmentation allows each component to be optimized for its specific function, distributing the mechanical loads across multiple elements rather than concentrating them in a single direct drive system
2Force
If larger actuator size is used to reduce strain on the rotation mechanism, then the strain is reduced, but the actuator may become too large to fit within the wing
Solution Approach 1:
The linkage mechanism serves as a mechanical intermediary that provides force multiplication and motion transformation. By incorporating a four-bar linkage with strategically positioned pivot points and link lengths, the system achieves mechanical advantage that reduces the torque requirement on the actuator, enabling a smaller actuator size that can fit within the wing structure
Solution Approach 2:
The linkage mechanism dynamically adapts the force transmission path during wing tip rotation. As the wing tip moves through its range of motion, the linkage geometry changes, maintaining optimal mechanical advantage throughout the rotation arc and allowing the use of a compact actuator that can still generate sufficient torque at all positions
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
Enables efficient reduction of the aircraft's overall length by allowing the wing tip to rotate, facilitating operation at smaller airports without the need for large or complex components, thereby expanding the number of airports an aircraft can serve.
Implementation Method 1
providing a mechanical advantage by reducing stress on the actuator
Implementation Method 2
with a geared rotary actuator and bushings for efficient operation
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
An aircraft wing tip rotary drive assembly (230) is provided. The assembly includes a tip hinge box (404), a body hinge box (402) pivotably coupled to the tip hinge box (404), a rotary actuator (430) positioned within the body hinge box (402), and a linkage mechanism (434) coupled between the rotary actuator (430) and the tip hinge box (404), the linkage mechanism (434) including a first linkage (440) fixedly coupled to the rotary actuator (430), and a second linkage (442) coupled between the first linkage (440) and the tip hinge box (404), wherein rotation of the rotary actuator (430) causes the tip hinge box (404) to rotate relative to the body hinge box (402).