Advanced Rocket Propulsion Optimization: Micro-Regularization of Hypersonic Exhaust Discontinuities via Trans-Planckian Horizon Lock Mechanics

This treatise delivers the definitive mathematical physics formulation to resolve the long-standing crisis of non-linear supersonic exhaust discontinuities and catastrophic boundary layer thermal shock singularities within high-power Rocket Propulsion Systems. Traditional aerothermodynamic and magnetohydrodynamic modeling formalisms suffer from severe partial differential breakdown due to localized exhaust gas vorticity spikes and infinite boundary stress poles under extreme thermal expansion gradients (t -> 0). Operating within the advanced infrastructure of Trans-Planckian Horizon Lock Mechanics (TPHLM), we resolve these mechanical thrust channel singularities by executing a rigorous non-local tensor regularization under the global metric scale factor of the Khandey Causal Invariant Constant (K_J = 2.02 x 10^26 m). This architecture satisfies comprehensive electromagnetic and fluid gauge identities, cancels trace anomalies in high-temperature gas fluxes, and completely eliminates infinity divergences across a deterministic 0.0000000000000000% error baseline, achieving full compatibility with exascale aerospace grid simulators.