Aircraft Door Stop Fitting Assembly with Removable Fasteners
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Solution Overview
Problem
Conventional aircraft door stop fittings have complex and time-consuming installation processes due to unique designs and multiple components, leading to increased manufacturing, installation, and maintenance costs and time.
Innovation Solution
A stop fitting assembly comprising a common stop fitting with a shaft, flange, and holes, combined with a connecting bracket and removable fasteners, allowing for easy installation and maintenance by using a single connecting bracket with interchangeable stop fittings and pins, reducing the number of unique parts and shimming requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional stop fittings with unique designs and multiple components are used, then structural reliability is improved, but installation time and complexity increase
Solution Approach 1:
The patent applies universality by designing a common stop fitting assembly that can be used across multiple aircraft door locations. The standardized connecting bracket and stop fitting components can be interchangeably installed at different positions, replacing location-specific unique designs. This reduces the variety of unique parts needed while maintaining structural reliability through consistent design standards.
Solution Approach 2:
The patent segments the stop fitting system into distinct, separable components: the connecting bracket, the stop fitting, and the fasteners. This segmentation allows for pre-assembly and standardized manufacturing of each component, which can then be quickly installed together. The modular approach reduces installation complexity compared to monolithic conventional designs.
2Reliability
If conventional stop fittings with multiple components are used, then structural reliability is improved, but device complexity increases
Solution Approach 1:
The patent merges multiple conventional stop fitting components into an integrated connecting bracket assembly. The connecting bracket incorporates mounting features, alignment elements, and fastening mechanisms into a single standardized component that interfaces with the stop fitting. This merging reduces the total number of unique parts while maintaining structural integrity through the integrated design.
3Adaptability or versatility
If conventional stop fittings with unique designs are used, then location-specific requirements are met, but manufacturing and installation costs increase
Solution Approach 1:
The patent achieves location-specific adaptability through the universal connecting bracket design that can be configured for different door locations using standardized mounting patterns. The same basic component serves multiple locations, eliminating the need to manufacture unique parts for each position. This universality significantly reduces manufacturing costs while maintaining the ability to meet specific local structural requirements.
4Manufacturing precision
If conventional stop fittings require shimming for alignment, then installation precision is improved, but installation time and complexity increase
Solution Approach 1:
The patent incorporates preliminary alignment features directly into the connecting bracket and stop fitting components during manufacturing. These pre-built alignment elements (such as precision-machined surfaces,定位 holes, or guide features) eliminate the need for field shimming operations. The alignment precision is achieved during controlled manufacturing conditions rather than during installation, significantly reducing installation time and complexity.
Data Source
AI summary
A stop fitting assembly for an aircraft door is presented. The stop fitting assembly comprises a stop fitting, a connecting bracket, and a number of removable fasteners. The stop fitting has a shaft, a flange extending outward from the shaft, and a number of holes extending through the shaft. The connecting bracket has a stop fitting receptacle configured to receive the shaft of the stop fitting, a number of holes extending through walls of the stop fitting receptacle, the connecting bracket configured to be joined to structural members of the aircraft door. The number of removable fasteners is configured to pass through the number of holes in the stop fitting and the number of holes of the stop fitting receptacle to removably join the stop fitting and the connecting bracket.