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Multimatrix Composite Materials for Rocket Nozzle Manufacturing: A Comparative Review.

Mohammed Meiirbekov1, Mukhammed Sadykov1,2, Assem Kuandyk1,2

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Summary

This review compares multimatrix composites for uncooled rocket nozzles, from polymers to advanced ceramics and metals. These materials offer enhanced thermal resistance, stability, and lifetime for extreme propulsion applications.

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C/CC/SiCSiC/SiCmodificationnozzlepolymer matrix compositesrocketthermal resistance

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Area of Science:

  • Materials Science
  • Aerospace Engineering
  • Thermodynamics

Background:

  • Rocket engine nozzles face extreme thermal and oxidative stress, necessitating advanced materials for uncooled operation.
  • Current materials require high temperature resistance, dimensional stability, and predictable lifetimes.

Purpose of the Study:

  • To provide a comparative overview of multimatrix composite materials for non-cooled rocket nozzles.
  • To highlight the evolutionary progression and performance trade-offs of different composite classes.

Main Methods:

  • Comparative analysis of C/C, C/SiC, SiC/SiC, MMCs, and polymer-based ablative systems.
  • Review of manufacturing technologies (PIP, CVI, LPI, RS, powder metallurgy, casting, diffusion bonding, filament winding).

Main Results:

  • Polymer/ablative composites provide thermal protection via ablation and insulation.
  • Carbon and ceramic composites ensure performance above 1600 °C.
  • MMCs enhance transition zones with strength and thermal conductivity.

Conclusions:

  • A selection matrix is proposed, linking nozzle zones, mission profiles, and composite types.
  • Material selection involves trade-offs in performance, mass, lifetime, and manufacturability.
  • Multimatrix composites are key for next-generation thermal protection and propulsion systems.