Aircraft Strut Primary Structure Using Connecting Rods
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Solution Overview
Problem
The existing aircraft strut primary structures are complex and costly to produce due to their intricate machining and assembly requirements, which complicates their manufacturing process and increases production expenses.
Innovation Solution
The primary structure of the aircraft strut is optimized by replacing the complex box structure with a front part formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels, and a rear part composed of connecting rods that intersect at a main rib, simplifying the design and reducing the dimensions of the elements involved, allowing for a set of connecting rods to be used instead of multiple ribs, and enabling a more straightforward integration with an aerodynamic fairing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a complex box structure with multiple ribs is used for the primary structure, then the stiffness and strength are improved, but the manufacturing cost and complexity increase
Solution Approach 1:
The primary structure is divided into a front part (box structure) and a rear part (connecting rods), with the box structure further segmented into longitudinal members and lateral panels. This segmentation allows each component to be optimized independently, reducing overall complexity while maintaining structural integrity.
Solution Approach 2:
The complex internal rib structure is extracted and replaced with a simpler configuration where the main rib serves multiple functions. The connecting rods replace the need for multiple reinforcing ribs, simplifying the overall structure while maintaining necessary strength.
2Strength
If a complex box structure with multiple ribs is used for the primary structure, then the stiffness and strength are improved, but the manufacturing cost increases
Solution Approach 1:
The structure is segmented into modular components (front part, rear part, connecting rods) that can be manufactured separately and assembled. This reduces manufacturing complexity and cost while maintaining the required strength through optimized component design.
Solution Approach 2:
The design uses simpler, more cost-effective materials and construction methods for the connecting rods compared to traditional complex rib structures. The connecting rods can be manufactured using standard aerospace materials and processes, reducing overall manufacturing cost.
3Ease of manufacture
If the dimensions of longitudinal members and lateral panels are reduced, then the manufacturing cost is reduced, but the structural strength may be compromised
Solution Approach 1:
The structure implements local quality by concentrating material where it is most needed - the front part maintains a robust box structure for strength, while the rear part uses lighter connecting rods. The main rib is strategically positioned and dimensioned to provide local reinforcement at critical interfaces.
Solution Approach 2:
The design effectively creates a composite structure combining the rigid box front part with the lighter connecting rod rear part. This composite approach allows optimization of each section for its specific function, reducing overall mass and manufacturing cost while maintaining structural integrity through the main rib connection.
Data Source
AI summary
A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.