Metal Matrix Composite Plies with Vacuum Sheath Diffusion Bonding
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Solution Overview
Problem
Conventional materials used in aerospace and hypersonic applications face limitations in high-temperature strength, creep resistance, and oxidation resistance, with existing materials being either heavy or brittle, and susceptible to stress corrosion and hydrogen embrittlement.
Innovation Solution
The method involves plating dry reinforcement fibers with an electroless or electrodeposited nickel or cobalt matrix to form metal matrix composite (MMC) laminates, which are then stacked and consolidated using diffusion bonding within a vacuum-sealed metallic sheath at high temperatures, creating a strong, lightweight part with improved high-temperature capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If aluminum and magnesium alloys are used for lightweight structures, then weight is reduced, but elevated temperature strength and creep resistance deteriorate
Solution Approach 1:
The patent applies composite materials by combining carbon fiber reinforcement with metal matrix (nickel or cobalt) to create a hybrid structure that achieves both lightweight properties and high-temperature strength. The carbon fibers provide tensile strength while the metal matrix provides creep resistance and temperature stability, resolving the contradiction between weight reduction and elevated temperature strength.
2Strength
If titanium alloy structures are used for high strength and corrosion resistance, then strength and corrosion resistance are improved, but stress corrosion cracking and hydrogen embrittlement susceptibility increase
Solution Approach 1:
The patent changes the material composition parameters by using nickel or cobalt as the metal matrix instead of titanium, and incorporating carbon fiber reinforcement. This parameter change eliminates the susceptibility to stress corrosion cracking and hydrogen embrittlement while maintaining high strength properties, as the nickel/cobalt-carbon fiber composite does not exhibit the same chemical reactivity issues as titanium alloys.
3Strength
If nickel and cobalt base superalloys are used for elevated temperature performance, then high temperature strength and creep resistance are improved, but weight increases
Solution Approach 1:
The patent applies composite materials by combining carbon fiber reinforcement with nickel or cobalt matrix. The carbon fibers provide high strength-to-weight ratio, while the metal matrix provides creep resistance and temperature stability. This composite structure achieves superior high-temperature performance with reduced weight compared to conventional nickel and cobalt base superalloys.
4Reliability
If ceramic matrix composites are used for oxidation resistance and high temperature properties, then oxidation resistance and elevated temperature properties are improved, but impact strength and fracture toughness deteriorate
Solution Approach 1:
The patent changes the matrix material parameter from ceramic to metal (nickel or cobalt), while maintaining carbon fiber reinforcement. This parameter change preserves oxidation resistance and elevated temperature properties while dramatically improving impact strength and fracture toughness, as the metal matrix provides ductility and toughness that ceramic matrices lack.
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
This approach results in parts with enhanced strength, creep resistance, and oxidation resistance, exceeding the performance of titanium and nickel-based superalloys, while maintaining a density similar to titanium alloys and offering a lighter alternative to ceramic matrix composites, with application temperatures up to 1500-2100°F.
Implementation Method 1
plating dry reinforcement fibers with an electroless or electrodeposited nickel matrix and/or electrodeposited nickel or cobalt matrix
Implementation Method 2
plating dry reinforcement fibers with an electroless or electrodeposited nickel matrix and/or electrodeposited nickel or cobalt matrix
Implementation Method 3
The vacuum sealed envelope may be heated to the desired curing or fusing temperature and pressure to metallurgically bond and consolidate the bundle of MMC laminates or plies into a single cured/consolidated or fused part
Implementation Method 4
hot consolidated into an MMC part via diffusion bonding of plies to one another
Data Source
Figure 1~2
Figure 3A~3B
Figure 4~5
AI summary
A method of manufacturing metal matrix composite (MMC) parts, including the steps of applying a metallic sheath around a bundle of MMC laminates, heating the bundle of MMC laminates in the metallic sheath at a curing or fusing temperature to consolidate the bundle of MMC laminates into a single cured or fused part, and then cooling the cured or fused part. The bundle of MMC laminates may be formed by removing surface contamination from the dry reinforcement fibers, creating a plurality of individual MMC laminates by plating dry reinforcement fibers with electroless nickel, and/or electrodeposited nickel or cobalt, and stacking each of the plurality of individual MMC laminates into a bundle. Autocatalytic and/or electroplating may be used as the primary means to incorporate fiber reinforcement into the metal matrix composite by covering and bonding fiber reinforcement into MMC laminates/plies and/or 3-D woven parts.