Aircraft Equipment Mounting Structure for Drill-Free Tolerance Compensation
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Solution Overview
Problem
Existing aircraft design methods for attaching equipment are time-consuming and require manual drilling of holes for alignment, which is inefficient and not adaptable to manufacturing tolerances.
Innovation Solution
A structural system with circumferential stiffening frames and attachment devices that include pre-drilled holes and adjustable brackets, allowing for flexible and fast installation of equipment by compensating for manufacturing-induced tolerances using rotatable and adjustable components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If manual drilling with laser beam alignment is used for installing equipment, then spatial alignment precision is improved, but installation time increases significantly
Solution Approach 1:
The patent pre-drills holes in the stiffening frames during manufacturing and creates a pre-established hole pattern. This preliminary action eliminates the need for time-consuming on-site laser alignment and drilling, while maintaining precise spatial alignment through the pre-configured hole positions that accommodate manufacturing tolerances.
Solution Approach 2:
The patent introduces a bracket as an intermediary component that connects equipment to the stiffening frame. The bracket includes a mounting portion with holes that align with the pre-drilled holes in the stiffening frame, serving as a mediator that transfers the pre-established alignment to the equipment installation process.
2Stability of the object's composition
If rigid fixed-distance brackets are used for attaching equipment, then structural stability is improved, but adaptability to manufacturing tolerances deteriorates
Solution Approach 1:
The patent transforms the rigid fixed-distance bracket into a dynamic adjustable bracket. The bracket includes an adjustable portion that can be extended or retracted, and a locking mechanism that secures the bracket at different positions. This dynamic design allows the bracket to adapt to manufacturing tolerances while maintaining structural stability when locked in place.
Solution Approach 2:
The patent enables parameter changes in the bracket's radial distance from the stiffening frame. The adjustable portion allows the bracket's position to be varied within a range, and the locking mechanism fixes it at the optimal position. This parameter adjustability compensates for manufacturing tolerances in both the stiffening frame and equipment mounting interfaces.
3Adaptability or versatility
If pre-drilled holes with adjustable brackets are used, then installation flexibility is improved, but device complexity increases
Solution Approach 1:
The patent divides the bracket into distinct functional segments: a mounting portion that attaches to the stiffening frame, an adjustable portion that provides radial adjustment, and a locking mechanism that secures the position. This segmentation allows each component to perform its specific function independently, simplifying the overall design while providing installation flexibility.
Solution Approach 2:
The patent introduces a support frame as an intermediary structure that connects multiple brackets and provides additional structural support. The support frame with its attachment regions mediates between multiple mounting points, distributing loads and providing a stable platform for equipment while simplifying the overall installation process.
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 faster and more flexible installation of equipment within the aircraft structure, reducing installation time and accommodating manufacturing deviations without the need for additional drilling.
Implementation Method 1
The attachment device (26) has a rotatable and arrestable sleeve (28) with an eccentric borehole (30) for tolerance compensation in a radial direction
Data Source
Figure 1~2
Figure 3~4a
Figure 4b~4d
AI summary
A structural system (2, 48) for an aircraft (66) is proposed, comprising circumferential stiffening frames (4) for stiffening a fuselage (68) of the aircraft, the stiffening frames comprising a cross-sectional profile having a web (6) enclosed by a radial inner flange (8) and a radial outer flange, at least one first bracket (22), and at least one attachment device (26) connectable to the at least one first bracket for fastening a piece of equipment (24, 50) to the at least one first bracket, wherein the stiffening frames each comprise a first pattern (18) of drill holes (20) adapted for receiving the at least one first bracket, wherein the at least one first bracket is adapted to protrude from the stiffening frames in a radial direction when attached, and wherein the attachment device is adapted for fastening the piece of equipment in a variable, arrestable distance to the respective first bracket.