Aircraft Droop Panel Linkage Weight Reduction via Single-Lever Design
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing droop panel linkage for aircraft incurs a significant weight penalty due to its complex double-lever configuration, which affects the overall structure's weight and efficiency.
Innovation Solution
A lightweight droop panel linkage design featuring a single-lever type of main lever and a main tube with spline engagement mechanisms, reducing the weight and complexity while maintaining functionality by using a single load path and simplified structural components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a double-lever type of main lever is used, then the droop panel linkage can transfer motion from the flap to the droop panel, but the weight of the linkage increases significantly
Solution Approach 1:
The main lever is divided into two separate levers: a first lever connected to the flap and a second lever connected to the drive strut. This segmentation eliminates the need for a complex double-lever main lever while maintaining the motion transfer function. Each lever is simpler in structure, reducing overall weight while preserving reliability.
Solution Approach 2:
The function of the double-lever main lever is merged into two separate levers with simplified structures. The first lever handles the connection from the flap, and the second lever handles the connection to the drive strut, eliminating redundant structural elements and reducing weight while maintaining the same functional outcome.
2Reliability
If a double-lever type of main lever is used, then the motion can be transferred through the linkage, but the structural complexity increases
Solution Approach 1:
The complex double-lever main lever is segmented into two separate, simpler levers. The first lever connects the flap to the main tube, and the second lever connects the main tube to the drive strut. This segmentation reduces structural complexity while maintaining the motion transfer function through a series of simpler mechanical connections.
Solution Approach 2:
The complex double-lever configuration is extracted and replaced with two separate levers and a main tube assembly. This extraction eliminates the complexity of the integrated double-lever structure while preserving the essential motion transfer function through simpler, more modular components.
3Weight of moving object
If a single-lever type of main lever with single load path is used, then the weight is reduced, but the engagement mechanism must be simplified
Solution Approach 1:
The engagement mechanism is extracted as a separate functional element between the levers and the main tube. Splines are provided on the levers that engage with corresponding splines in the main tube, creating a dedicated engagement interface. This extraction allows for a simplified single-lever design while maintaining adequate engagement through the spline mechanism.
Solution Approach 2:
The spline engagement mechanism acts as an intermediary between the simplified single-lever design and the main tube. The splines on the levers engage with splines in the main tube, providing the necessary mechanical coupling and motion transfer without requiring complex engagement mechanisms, thus enabling weight reduction while maintaining functional integrity.
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
The new design significantly reduces the total weight of the droop panel linkage, mitigating the weight penalty and enhancing the structural efficiency of the aircraft's droop panel mechanism.
Implementation Method 1
The main lever and main tube engage mechanically by means of a suitable engagement means which will impart the displacement of the main lever into rotational movement of the main tube. In a preferred embodiment, the engagement means is a spline construction.
Data Source
AI summary
A droop panel linkage for aircraft includes a lever arm, a main lever, a main tube and at least one drive strut. The lever arm is pivotally attached at a first end to a flap and is pivotally connected at a second end to a first end of the main lever. A second end of the main lever is provided with a first engagement element for engaging with a second engagement element incorporated into or associated with the main tube. The main tube is pivotally connected to a proximal end of the drive strut. A distal end of the drive strut is pivotally attached to the droop panel.