Composite solid propellants (CSPs), composed of fuel binder, metal powder, oxidizer, and functional additives, are indispensable to modern rocketry because of their high energy density, processability, and proven reliability. Their macroscopic performance, however, is governed by microscopic chemistry: catalyst identity, binder and oxidizer interactions, thermal decomposition behaviour, and microstructural design. This review synthesizes recent advances in two-dimensional MXene oxide and carbide hybrids (e.g., TiC2, V2C combined with V2O5, TiO2, NiO, MgCo2O4) as catalytic burn rate modifiers for AP (Ammonium perchlorate) based CSPs. MXenes furnish conductive, defect-rich frameworks that supply redox active centers and oxygen vacancies; when synergized with transition metal oxides, they markedly accelerate AP decomposition (reported HTD(high thermal decomposition) reductions from 471.2 to ∼208 for MgCo2O4 MXene composites) and lower activation energies (up to ∼59.7 % reduction). At propellant scale, these hybrids increase specific thrust (reported gains of about +15 s), enhance burning rates (examples up to +202 % or about 70–80 % for certain MXV formulations), and shorten ignition delays (reported reductions of about 30–80 %). Rational morphological engineering, including layered, mesoporous, and flower-like architectures, optimizes surface area, mass diffusion, and electron and heat transport, improving catalytic accessibility and thermal propagation. Compared with conventional oxide catalysts, MXene-based composites combine electrical conductivity, redox flexibility, and structural tunability, yielding multifunctional catalysts that both accelerate kinetics and enable tunable, cleaner combustion. The review concludes that MXene oxide hybrids represent a promising materials pathway for next-generation, higher-performance, and more controllable solid propellant formulations.
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