Abstract
This technical disclosure presents a modular, non-linear, two-stage interplanetary spacecraft architecture designed to isolate human crew members from the severe thermal, mechanical, and radiological stresses of a high-field High-Temperature Superconducting (HTS) REBCO magnetic confinement fusion core.
Rather than relying on traditional linear truss layouts, this architecture introduces the Citadel-Concentric Topology. The design embeds an ultra-lightweight, spherical crew habitat inside a rigid, cylindrical, reusable boost and propulsion stage (The Transit Box). The interface between the two nested stages is bridged by an open-cell silicon-carbide ceramic foam matrix. This foam acts as a multi-functional isotropic shock absorber, high-temperature thermal barrier, and passive safeguard against vacuum cold-welding.
Furthermore, this disclosure defines a post-separation operational protocol. Upon deploying the crew vehicle at its planetary destination, the hollow, spent boost stage automatically deploys geometric shutter walls to form a sleek aerodynamic nosecone. Powered by an auxiliary radioisotope thermoelectric generator (RTG), the stage reboots as an autonomous, long-range robotic science probe, executing high-velocity planetary gravity assists (Oberth maneuvers) to survey the outer solar system.
Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 License.
Recommended Citation
Eckes, Christopher L., "Technical Disclosure: The Citadel-Concentric Transit Architecture", Technical Disclosure Commons, (June 30, 2026)
https://www.tdcommons.org/dpubs_series/10669