COMPREHENSIVE ABSTRACT Title: Integrated Flight Dynamics, Magnetohydrodynamic Propulsion, and Aerodynamic Trajectory Optimization of Multi-Scale Radial Discoid Aerospace Systems for Earth-Orbit and Interplanetary Logistics Authors: Murtazin Ilgiz Faritovich, Lead Mathematical Engineer Affiliation: TNG-Group LLC, Deep Space Exploration & Propulsion Division Abstract This compendium of research papers presents a rigorous mathematical, electrodynamic, and structural framework for a novel class of multi-scale, multi-purpose radial discoid aerospace vehicles utilizing advanced air-breathing and exoatmospheric Magnetohydrodynamic (MHD) propulsion architectures. The investigated systems span a 132-metric ton, 22-meter diameter expeditionary class vehicle optimized for deep-space transit and Mars-surface operations, as well as an 1120-metric ton, 65-meter diameter heavy interplanetary passenger liner (Magistral-100) capable of zero-combustion sea-level vertical liftoff and long-range trans-lunar payload insertion. The fundamental operational mechanism across both scales relies on high-frequency ultraviolet laser arrays that execute multiphoton pulse ionization of the surrounding atmospheric boundary layer, establishing an active plasma front with high electrical conductivity. High-Temperature Superconducting (REBCO) magnetic systems distributed along the discoid periphery generate a static magnetic field up to 6. 0--9. 0\, Tesla. When crossed with an active circumferential current, the system delivers a massive volumetric Lorentz body force (FL = (j B) dV) that drives high-velocity fluid acceleration. A core aerodynamic finding detailed within this bundle is the exploitation of the Coanda effect over the vehicle’s curved upper dome. Due to the scaled geometry, this pressure differential contributes up to 65\%--78\% of total vertical lift in dense air, significantly decoupling the initial ascent trajectory from traditional fuel-mass expenditure. Numerical flight dynamic simulations confirm that for the 132-ton vehicle, a circumferential plasma current of 125\, kA provides an initial thrust-to-weight ratio (TWR) of 1. 28, while the 1120-ton liner requires 285\, kA across a scaled 1020\, m³ interaction zone to achieve stable vertical liftoff powered by an integrated graphene supercapacitor energy bank. Furthermore, the papers address critical structural and trajectory constraints of the discoid profile: The Stratospheric Pitch Transition: Flight dynamics at the 35\, km boundary are modeled, where the rarefied atmosphere triggers a 90^ continuous S-curve pitch maneuver. This rotates the discoid airframe "on-edge" to minimize dynamic pressure profiles during hypersonic acceleration. Active Passenger Stabilization: A feedforward PID control law is derived for a 65-ton internal passenger cabin isolating personnel via a triaxial active magnetic gimbal suspension. The system continuously negates hull angular velocities, bounding passenger floor misalignment to 0. 02^ while keeping net G-loads at a comfortable 1. 35\, g. Extreme Electrodynamic Strength Requirements: Structural calculations employing the Mariotte formulation demonstrate that the immense Maxwell stresses (32. 23\, MPa at 9. 0\, T) are safely constrained by a 22. 4\, cm high-modulus carbon fiber reinforced polymer (CFRP) external structural bandage operating under continuous pre-tension. Hybrid Thermal Protection System (TPS): A robust, multi-zoned TPS is established, pairing seamless monolithic silicon carbide and carbon nanotube (SiC + MWCNT) coating at the high-velocity leading edges with replaceable hexagonal quartz tiles over the flat hulls to tolerate up to +2200^ thermal fluxes, further mitigated by non-contact active MHD plasma shielding. Finally, a systemic deep-space logistical pipeline is outlined, wherein a cluster of modular 22-meter discoid landers docks symmetrically around a megawatt-class Nuclear Electric/Thermal Propulsion Tug. This hybrid architecture isolates the long-duration interplanetary cruise phase from planetary landing tasks, showcasing how the discoid shape exploits low-density atmospheric entry environments—such as the Martian surface boundaries—to achieve precise vertical-takeoff, vertical-landing (VTVL) capabilities without auxiliary infrastructure. Collectively, these papers establish the mathematical and engineering viability of transitioning deep-space exploration from single-use chemical rockets to infinitely reusable, solid-state electrodynamic aerospace systems.
Ilgiz Murtazin (Fri,) studied this question.