Open-Section Composite Thrust Reverser Support Structure
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Solution Overview
Problem
Aeronautical thrust reverser support structures require further lightweighting while maintaining mechanical strength and reducing production costs, as existing composite materials with closed sections are not optimal for this purpose.
Innovation Solution
A support structure for a turbojet engine nacelle with a base body made of composite material having a substantially open cross-section, incorporating reinforcement means and produced using resin infusion molding, which allows for reduced mass and manufacturing costs, improved accessibility, and better integration with aerodynamic designs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If an essentially closed composite structure is used for the support beam, then mechanical strength is ensured, but mass is increased and manufacturing complexity increases
Solution Approach 1:
The support beam is divided into a base structure and separate reinforcing elements. The base structure has an open cross-section for weight reduction, while discrete reinforcing means (such as ribs or stiffeners) are added only where structurally necessary to provide localized strength enhancement without the full overhead of a closed-section design.
Solution Approach 2:
The invention employs composite materials with strategically oriented fibers or plies within the open-section base structure and reinforcing elements. By optimizing fiber placement and material composition in high-stress regions, the structure achieves enhanced mechanical properties comparable to closed sections while maintaining the weight advantages of an open configuration.
2Strength
If an essentially closed composite structure is used for the support beam, then mechanical strength is ensured, but manufacturing costs increase due to complex molds requiring internal cores
Solution Approach 1:
The manufacturing process is segmented into forming the simple open-section base structure using a straightforward mold, followed by separate attachment or integration of reinforcing elements. This eliminates the need for complex internal cores required for closed-section molding, significantly simplifying tooling and reducing mold fabrication and maintenance costs.
Solution Approach 2:
The invention changes the structural parameter from a closed-section geometry to an open-section geometry with added reinforcements. This parameter change fundamentally simplifies the molding process, allowing for easier material infusion, simpler demolding operations, and elimination of core extraction steps, thereby reducing overall manufacturing complexity and cost.
3Stability of the object's composition
If an essentially closed composite structure is used for the support beam, then structural rigidity is maintained, but accessibility for maintenance and quality control is reduced
Solution Approach 1:
The support beam structure is segmented such that the base structure provides the primary load path while reinforcing elements provide localized stiffening. This segmentation creates accessible interfaces and open spaces that allow maintenance personnel to reach internal components, inspection points, and connection areas without requiring disassembly of a fully enclosed structure.
Solution Approach 2:
Rather than providing uniform reinforcement throughout a closed section, the invention applies reinforcing means only in specific locations where structural demands require enhanced rigidity. This localized approach maintains overall structural stability while leaving other areas open and accessible for maintenance activities, quality control inspections, and repairs.
4Shape
If a closed-section composite beam is used, then aerodynamic integration is achieved, but mass increases and manufacturing simplicity is lost
Solution Approach 1:
The invention applies aerodynamic shaping and reinforcement only in specific regions where aerodynamic performance or structural strength is critical. The majority of the beam maintains an open, simplified geometry that is easier to manufacture and lighter in weight, while localized features provide the necessary aerodynamic integration and structural enhancement.
Solution Approach 2:
The invention transitions from a two-dimensional closed-section profile to a three-dimensional open-section structure with strategically placed reinforcing elements extending in multiple directions. This dimensional approach allows for aerodynamic shaping and structural reinforcement without requiring a fully enclosed cross-section, achieving performance goals with reduced mass.
Data Source
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AI summary
The present invention relates to a supporting structure (200) for a nacelle of a jet engine, in particular provided with a thrust reverser device, including at least one base body (201) made of a composite material, characterised in that the base body has a transverse section which is essentially open and provided with at least one reinforcement means.