Aircraft Support Pin Assembly for Jig Lock and Binding Release
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Solution Overview
Problem
Existing methods for full size determinant assembly of aircraft structures face challenges such as assembly jig lock and pin binding, which hinder accurate positioning and support, leading to over-constraining, build-up, and potential damage to holes in frame sections.
Innovation Solution
A support pin assembly comprising a block with intersecting bores, a bushing, a barrel nut, and a pin with protruding circumferential portions, allowing for nominal adjustment and release from binding conditions by rotating the pin via flat surface portions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If pins are inserted through holes in frame sections held by assembly jig, then positioning accuracy is improved, but pin binding and jig lock occur
Solution Approach 1:
The support pin assembly incorporates a floating pin mechanism that allows the pin to move dynamically within the support block, enabling automatic adjustment to accommodate dimensional variations and prevent binding. The pin can float within a controlled range while maintaining precise positioning, resolving the contradiction between positioning accuracy and preventing pin binding.
Solution Approach 2:
The invention changes the positional parameters of the pin by allowing it to float within the support block rather than being fixed. This parameter change enables the pin to adapt its position dynamically, maintaining manufacturing precision while avoiding binding conditions that would compromise reliability.
2Stability of the object's composition
If pins are fixed in assembly jig, then positioning stability is improved, but adjustment capability is lost
Solution Approach 1:
The floating pin mechanism transforms the static fixed pin into a dynamic component that can adjust its position while maintaining stability. The pin floats within the support block, providing both positional stability for accurate assembly and adjustment capability to accommodate dimensional variations in frame sections.
Solution Approach 2:
The floating pin assembly is self-adjusting, automatically positioning itself to accommodate frame section variations without requiring external intervention. The pin self-regulates its position within the support block, maintaining stability while providing necessary adjustment capability.
3Ease of operation
If assembly jig is removed due to pin binding, then pin release is achieved, but hole damage occurs
Solution Approach 1:
The floating pin mechanism provides beforehand cushioning by incorporating clearance between the pin and support block, allowing the pin to float and absorb dimensional variations before binding occurs. This prevents the need to remove the assembly jig, thereby protecting the holes from damage while enabling pin release if needed.
Solution Approach 2:
The support block acts as an intermediary between the pin and the assembly jig, providing a floating mechanism that prevents direct transmission of binding forces to the frame section holes. This intermediary structure enables pin release without causing hole damage.
4Manufacturing precision
If over-constraining is applied to prevent movement, then positioning precision is improved, but pin binding increases
Solution Approach 1:
The invention applies dynamic constraint rather than static over-constraining. The floating pin mechanism provides controlled movement within the support block, maintaining positioning precision while avoiding the binding that results from excessive static constraints.
Solution Approach 2:
The invention changes the constraint parameters by allowing controlled浮动 movement rather than fixed positioning. This parameter change maintains manufacturing precision through controlled boundaries while reducing pin binding by permitting necessary adjustments.
Data Source
AI summary
There is provided a support pin assembly for full size determinant assembly of an aircraft structure. The support pin assembly includes a block having a vertical bore and a horizontal bore; a bushing within the horizontal bore; a barrel nut having a cylindrical body within the vertical bore and a barrel nut hole; and a pin. The pin includes an insertion portion within the bushing, an interface element, and an extending portion having at least one protruding circumferential portion having two or more flat surface portions on opposing sides to enable rotation of the pin. The at least one protruding circumferential portion is positioned within a hole in a frame section of the aircraft structure, and provides nominal adjustment of the pin, so that with any binding condition of the pin, the pin is released by rotating the pin via the two or more flat surface portions.