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Multimatrix Composite Materials for Rocket Nozzle Manufacturing: A Comparative Review.
Mohammed Meiirbekov1, Mukhammed Sadykov1,2, Assem Kuandyk1,2
1JSC "National Center of Space Research and Technology", Almaty 050010, Kazakhstan.
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.
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.
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