Removable Aircraft Equipment Support with Hinged Link Arms
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Solution Overview
Problem
Existing aircraft equipment supports are either limited in the loads they can carry due to their design, either being too bulky and heavy or unable to accommodate aerodynamic deformations of the aircraft structure, and they often require additional reinforcement which adds weight and complexity.
Innovation Solution
A removable support system for aircraft that uses an elongate beam with fastener means having triangular structures, allowing for attachment at two points on the aircraft structure, with hinged components to accommodate deformation and manufacturing tolerances, and adjustable rods for precise positioning, enabling the support of heavy loads without the need for a third attachment point.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a support is fastened to a single take-up point on the aircraft structure, then the support structure is simple, but the support capability is limited to relatively small forces
Solution Approach 1:
The support system is divided into multiple independent fastening points (first and second fastening points) distributed on the aircraft structure, with each point having its own fastener and link arm. This segmentation allows the system to distribute loads across multiple attachment points, significantly increasing support capability while maintaining modular simplicity in each individual component.
2Strength
If a support is fastened to two take-up points on the aircraft structure, then the support capability increases, but the structure becomes incompatible with aerodynamic deformations
Solution Approach 1:
The link arms are designed with hinged connections at both ends (to the fastener and to the beam), creating a dynamic structure that can adapt its configuration. This allows the support system to accommodate aerodynamic deformations of the aircraft structure during flight, as the hinged link arms can flex and adjust to structural movements while maintaining load-bearing capability.
Solution Approach 2:
The system allows changes in the geometric parameters of the link arms through hinged connections, enabling the support structure to adapt to varying aircraft structural configurations caused by aerodynamic forces. The hinged joints permit angular adjustments that compensate for structural deformations without compromising support strength.
3Strength
If a support uses three take-up points to support heavy loads, then the support capability for heavy loads is achieved, but the support becomes bulky and heavy
Solution Approach 1:
The invention extracts and eliminates the need for the third fastening point that would be required in traditional three-point support systems. By using only two strategically positioned fastening points with hinged link arms, the system achieves heavy load support capability while removing the excess weight and bulk associated with third attachment points and their associated hardware.
4Ease of operation
If the support arm extends over a considerable distance to reach the take-up point, then the equipment can be positioned correctly, but the lever arm limits the load that can be supported
Solution Approach 1:
The hinged link arms provide dynamic adjustment capability that allows the support system to maintain optimal load-bearing geometry. The hinges enable the link arms to adjust their angles and positions, effectively reducing the lever arm length under load while still achieving the required equipment positioning, thereby maintaining both positioning accuracy and load capacity.
Data Source
AI summary
The present invention relates to a removable support (10) for optional equipment (6) on an aircraft (1). The support (10) comprises an elongate beam (20) fitted with at least one attachment point for a piece of equipment and extending from a first end portion (21) to a second end portion (22), and the support (10) is provided with first fastener means (30) provided with a first fastener arm (31) connected to a first link arm (32) that is releasably fastened to the first end portion (21), and with second fastener means (40) provided with a second fastener arm (41) connected to a second link arm (42) that is releasably fastened to the second end portion (22), a first support rod (34) also connecting the first fastener arm (31) to the first link arm (32), and a second support rod (44) also connecting the second fastener arm (41) to the second link arm (42).