Aircraft Fuselage Panel Gripping Device for Shape Maintenance
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Solution Overview
Problem
Existing gripping devices for aircraft fuselage panels are not adapted to the shape of the panels, leading to deformation during transportation and assembly, which affects the geometric conformity of the fuselage sections.
Innovation Solution
A gripping device with multiple subsystems that apply tension to the panel's skin using adjustable pressurizers and suction cups, ensuring the panel's shape during transportation and assembly by fastening to reference holes and using actuators and control units to adjust the position of the pressurizers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If bulky carriages are used to transport panels, then the panels can be transported, but the panels deform and lose geometric conformity
Solution Approach 1:
The gripping device is divided into multiple independent gripping subsystems (at least two) arranged parallel to the longitudinal axis, each subsystem comprising a central element and two lateral elements that can be independently adjusted to apply tension at different locations along the panel
Solution Approach 2:
The lateral elements include pressurizers with legs that are translationally movable and adjustable in position perpendicular to the skin, allowing the device to dynamically adapt to the panel's arcuate shape and apply uniform tension throughout the transport process
2Manufacturing precision
If the gripping device applies tension to the skin, then the shape is ensured, but the device complexity increases
Solution Approach 1:
The device replaces complex mechanical gripping mechanisms with a tensioning system using pressurizers that apply distributed pressure to the skin, converting point-contact gripping into surface-contact tensioning to maintain shape with simpler components
Solution Approach 2:
The pressurizers can be adjusted in position perpendicular to the skin, allowing the device to adapt to different panel curvatures and sizes by changing the geometric parameters of the gripping configuration rather than requiring different physical structures
3Stability of the object's composition
If multiple gripping subsystems are used, then the shape is maintained, but the device becomes more complex
Solution Approach 1:
Each gripping subsystem is designed with universal components that can perform multiple functions: the central element and lateral elements serve both as structural support and as tensioning mechanisms through integrated pressurizers, eliminating the need for separate gripping and shaping mechanisms
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 device effectively maintains the panel's shape and geometric conformity, allowing for precise handling and assembly of fuselage sections by applying tension uniformly across the arcuate shape, preventing deformation and ensuring nominal conformity.
Implementation Method 1
each leg comprises a suction cup which is intended to maintain the leg against the skin
Implementation Method 2
each leg comprises a suction cup which is intended to maintain the leg against the skin
Data Source
AI summary
A gripping device for a panel of a section of a fuselage of an aircraft, the panel including a skin and having an arcuate shape about a longitudinal axis X. The gripping device includes two gripping subsystems arranged at a distance from one another parallel to the longitudinal axis X, and each gripping subsystem includes a central element fastened to the panel, and two lateral elements fastened on either side of the central element by fasteners, and each lateral element includes pressurizers which come against the skin to apply a tension thereto in the opening direction of the arcuate shape. Such a gripping device makes it possible to ensure the shape of the panel when it is transported and until it is fastened to other panels in order to produce the section of the fuselage.