Composite Hinge with Connecting Reinforcement for Compression Resistance
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Solution Overview
Problem
Existing non-articulated built-in hinges lack sufficient mechanical characteristics for applications in space and aeronautical domains, particularly in terms of reliability, mechanical, thermo-mechanical, and vibratory stress resistance, and provide mediocre longitudinal traction or compression resistance.
Innovation Solution
A device featuring a non-articulated built-in hinge with flexible portions made of composite materials, where the flexible portion connects stiffer portions and includes a reinforcement structure and a matrix, allowing for enhanced mechanical properties, flexibility, and resistance, including longitudinal compression and traction resistance, while being simple to manufacture and reliable.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a local reduction in thickness is used to form a flexible portion between two stiffer portions, then flexibility is improved, but mechanical strength and reliability deteriorate
Solution Approach 1:
The patent applies composite materials by embedding a reinforcement structure (such as fibers or rigid framework) within the flexible portion material. This creates a composite structure where the reinforcement provides mechanical strength while the flexible matrix maintains bending capability, thus resolving the contradiction between flexibility and mechanical strength.
Solution Approach 2:
The patent implements local quality by creating a hinge structure with spatially varying properties: the flexible portion has different material composition and thickness compared to the stiffer portions. The reinforcement structure is specifically placed in the flexible portion to provide localized strength without compromising overall flexibility, allowing each region to have optimized properties for its specific function.
2Ease of operation
If a local reduction in thickness is used to form a flexible portion, then flexibility is improved, but resistance to mechanical, thermo-mechanical and vibratory stresses deteriorates
Solution Approach 1:
The patent uses composite materials with reinforcement structures embedded in the flexible portion to provide enhanced resistance to mechanical, thermo-mechanical, and vibratory stresses. The reinforcement elements (such as fibers or rigid framework) maintain structural integrity under various stress conditions while allowing the flexible portion to maintain its bending capability.
Solution Approach 2:
The patent applies local quality by strategically placing reinforcement structures within the flexible portion to address specific stress concerns. The reinforcement is concentrated where needed to resist mechanical, thermal, and vibratory stresses without compromising the overall flexibility of the hinge structure.
3Ease of manufacture
If a homogeneous thermoplastic synthetic material is used, then ease of manufacture is improved, but mechanical characteristics and reliability deteriorate
Solution Approach 1:
The patent transitions from homogeneous thermoplastic material to composite materials by embedding reinforcement structures within the flexible portion. This composite approach maintains manufacturability through integrated molding processes while dramatically improving mechanical characteristics and reliability for space and aeronautical applications.
4Ease of operation
If the flexible portion is made with reduced thickness, then flexibility is improved, but longitudinal traction or compression resistance deteriorates
Solution Approach 1:
The patent uses composite materials with embedded reinforcement structures in the flexible portion to maintain longitudinal traction and compression resistance despite reduced thickness. The reinforcement elements (fibers or rigid framework) provide the necessary force resistance while the thin flexible matrix maintains bending capability.
Solution Approach 2:
The patent applies local quality by orienting and distributing reinforcement structures within the flexible portion to specifically address longitudinal force resistance. The reinforcement is positioned and configured to resist traction and compression forces along the hinge axis while maintaining flexibility for bending motion.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution provides improved mechanical resistance, flexibility, and reliability for the hinge, enabling it to withstand repeated folding and unfolding with small radii of curvature, and offers reduced manufacturing costs and weight, making it suitable for diverse applications including space and aeronautical uses.
Implementation Method 1
a reinforcement structure which is formed by at least a first material, and is designed to confer mainly properties of mechanical strength on the said composite material... this reinforcement structure being embedded in a matrix... the purpose of which is to transmit the stresses, at least the longitudinal traction stresses
Implementation Method 2
each flexible portion connecting the said stiff portions and being designed to form a flexible hinge between the stiff portions... at least in flexure around an axis which is parallel to, or combined with, a theoretical axis of pivoting of the hinge thus formed
Implementation Method 3
this reinforcement structure being embedded in a matrix, which is made of at least a second, polymer material... the purpose of which is to confer the general form and dimensions of the material, to support the reinforcement structure, and to provide transverse compression resistance
Data Source
AI summary
A device includes at least one built-in flexible portion (1) between two stiffer portions (10) that are made of a stiff composite material, the flexible portion (11) being suitable for forming a flexible hinge and made of a flexible material including a reinforcing armature that includes at least one connecting layer (13) common to the material(s) forming each stiff portion (10). The device has end surfaces (20) that oppose each other when extended, the opposing end surfaces being arranged to be suited to serve as a longitudinal compression abutment while enabling the thus-made hinge to fold back at least in a direction away from the extended state.