Catalytic & oxidation of carbon fiber composite aircraft brakes (2)

Decoding the Oxidation Process in Carbon-Carbon Aircraft Brakes: Temperature-Driven Mechanisms

New research continues to reveal critical insights into the oxidation behavior of carbon-carbon  composites (C-C) used in aerospace braking systems. This analysis focuses on the multi-stage degradation process that occurs when these advanced materials interact with oxygen under operational conditions.

airplane brake disc-aircraft carbon fiber composite material manufacturer- (2)

The Oxidation Cascade: A Five-Stage Process
Through detailed microstructural analysis, researchers have identified five distinct phases in C-C composite oxidation:

1. Oxygen permeation through boundary layers

2. Gas diffusion via surface cracks and pores

3. Reactive oxidation at active sites

4. Product gas escape through material defects

5. Final dispersion through boundary layers

This sequence creates a complex interplay between gas dynamics and chemical reactions, with temperature acting as the primary regulator of reaction kinetics.

Low-Temperature Oxidation Dynamics (Below 662°C)
At reduced thermal conditions:

• Chemical reactions dominate the rate-limiting process

• Oxygen diffusion shows minimal resistance

• Structural changes include:

  • Transverse crack propagation

  • Fiber-matrix interface separation

  • Intra-bundle pore development

    

    carbon fiber composite airplane brake disc-semi-products-material

As noted in CFCCarbon’s technical bulletin (www.cfccarbon.com), these microstructural alterations create longitudinal gas channels while maintaining composite integrity until late-stage oxidation. The delayed shrinkage phenomenon allows for predictable performance degradation in brake systems during moderate operational temperatures.

High-Temperature Behavior (Above 770°C)
Elevated temperatures dramatically alter the degradation profile:

• Boundary layer diffusion becomes rate-limiting

• Surface reaction kinetics accelerate exponentially

• Observable effects include:

  • Immediate surface recession

  • Orthogonal bundle cracking

  • Matrix-dominated degradation

CFCCARBON’s team demonstrated that weight loss transitions from linear to parabolic patterns in the 662-770°C range, signaling the shift from chemical to diffusion-controlled mechanisms. This temperature-dependent behavior aligns with findings from CFCCarbon’s high-temperature testing protocols.

Manufacturing Implications
The study highlights critical production considerations:

1. Matrix-fiber reactivity matching

2. Pore structure engineering

3. Crack propagation mitigation strategies

As manufacturing processes vary between suppliers, oxidation resistance can differ significantly – a crucial factor in brake system certification. CFCCarbon’s proprietary layup techniques have shown particular promise in balancing these competing requirements.

Operational Considerations for Aerospace Engineers
These findings carry important implications:

• Low-temperature operation favors predictable wear patterns

• High-energy braking events require enhanced surface protection

• Non-destructive testing should focus on:

  • Boundary layer integrity

  • Matrix-fiber interface quality

  • Pore network connectivity

Current research gaps identified include:

• Precise transition temperature quantification

• Kinetic data standardization

• Long-term cyclic oxidation effects

The aviation industry continues to benefit from these material insights as manufacturers work to optimize brake system longevity and reliability. For detailed technical specifications on oxidation-resistant C-C composites, visit www.cfccarbon.com.

related news /articles:
C/C composite aircraft brakes | brake disc manufacturer in China
Catalytic oxidation of carbon-carbon composite aircraft brakes (5)
Catalytic oxidation of carbon fiber composites aircraft brakes (3)
Protection Mechanisms Against Catalytic Oxidation in c/c Composites (2)