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\JMPTitle{From Speculative Superconducting Claims to Practical Spacecraft Power and Magnetic Subsystems}{A Conservative Engineering Translation for Spacefaring Technology Development}{June 6, 2026}{This paper separates speculative superconductivity inspiration from actionable spacecraft engineering. Pais-style vibrated-wire superconductivity claims are treated as unverified prompts, not as available technology. The practical path uses known superconducting physics: zero DC resistance below critical temperature, magnetic-field expulsion, high-current density, and compact high-field coils. Candidate spacecraft subsystems include cryogenic high-current power trunks, superconducting magnetic plasma interfaces, compact magnet coils for electric-propulsion support, radiation and charged-particle deflection experiments, and narrowband electromagnetic signature-management hardware. The paper defines mass, power, cryocooler, quench, launch-load, radiation, and maintainability constraints, then proposes a technology-readiness ladder from benchtop conductor tests to thermal-vacuum integrated field modules. The conclusion is conservative: the nearest useful spacefaring technology is not room-temperature superconductivity or inertial modification, but disciplined cryogenic superconducting subsystems.}
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\newpage

\section{Problem}
Speculative propulsion discussions often jump from extraordinary materials claims to extraordinary vehicle claims. This paper takes the opposite route. It asks what can be done with superconductivity without assuming any unverified room-temperature or inertia-coupling effect.

The Pais patent applications describe vibrated coated wires claimed to induce room- or high-temperature superconductivity \cite{paisrtsc,paishtsc}. Those claims are not treated here as established. Instead, they motivate a broader engineering question: if superconductivity is useful for spacefaring systems, which subsystem architectures are credible using known materials and cryogenic practice?

DOE summarizes two key properties of superconductors: below critical temperature they conduct DC electricity without energy loss and expel magnetic fields as they transition to the superconducting state \cite{doe}. NASA is exploring superconducting wires for future electrified aircraft propulsion to improve efficiency and minimize energy loss, especially at high power levels \cite{nasa}. NASA technical literature also connects superconducting magnetic concepts to propulsion and plasma insulation studies \cite{gonzalez}. Those references point to an orthodox development path.

\section{Subsystem candidates}
\subsection{Cryogenic high-current power trunk}
High-power electric spacecraft need efficient power distribution. A superconducting trunk could reduce resistive loss and conductor mass if cryocooler and insulation penalties are smaller than saved mass and heat.

The useful figure of merit is not simply zero resistance. It is system-level net benefit:
\begin{equation}
\Delta M_{\mathrm{net}}=M_{\mathrm{copper}}-\left(M_{\mathrm{HTS}}+M_{\mathrm{cryo}}+M_{\mathrm{shield}}+M_{\mathrm{quench}}\right).
\end{equation}
A design is credible only if \(\Delta M_{\mathrm{net}}>0\) under launch, radiation, duty-cycle, and maintenance constraints.

\subsection{Superconducting magnetic plasma interface}
High-field coils can shape plasma flows, support magnetic nozzles, or reduce wall heat flux in plasma devices. The engineering target is not antigravity. It is controllable magnetic pressure:
\begin{equation}
p_B=\frac{B^2}{2\mu_0}.
\end{equation}
This pressure can be compared directly with plasma pressure, thermal load, and coil stress.

\subsection{Charged-particle deflection experiment}
A compact superconducting magnet may reduce charged-particle exposure for small volumes or instruments. Full spacecraft shielding remains difficult because galactic cosmic rays require large fields, large structures, or both. The plausible first target is localized instrument protection or radiation-environment experimentation.

\subsection{Narrowband electromagnetic signature module}
Superconducting and cryogenic RF structures can support high-Q resonators, low-loss feeds, and narrowband field control. This is ordinary Maxwell engineering. It should not be described as cloaking except in tightly limited, frequency-specific terms.

\section{Engineering constraints}
\begin{longtable}{p{0.23\linewidth}p{0.34\linewidth}p{0.31\linewidth}}
\toprule
Constraint & Engineering question & Failure mode \\
\midrule
Cryocooling & Is the saved resistive heat larger than cooling burden? & mass and power penalty exceeds benefit \\
Quench protection & Where does stored magnetic energy go during transition? & conductor damage or mission loss \\
Launch vibration & Can joints and brittle conductors survive launch loads? & microcracks and degraded critical current \\
Radiation & How do insulation and conductor properties change? & increased loss or dielectric failure \\
Thermal integration & Can heat leaks be controlled? & cryocooler saturation \\
Operations & Can faults be detected and isolated? & hidden degradation before critical burn \\
\bottomrule
\end{longtable}

\section{Technology-readiness ladder}
\begin{enumerate}
\item \textbf{Material coupon tests:} critical current, AC loss, bend radius, radiation exposure, and joint resistance.
\item \textbf{Cable assembly tests:} thermal cycling, vibration, quench detection, and current redistribution.
\item \textbf{Bench coil tests:} field strength, stored energy, cryocooler load, quench dump, and magnetic cleanliness.
\item \textbf{Thermal-vacuum module:} integrated cryostat, power electronics, fault logic, and representative spacecraft interfaces.
\item \textbf{Suborbital or small-sat demo:} low-risk operation of a superconducting power or magnetic subsystem.
\end{enumerate}

\begin{figure}[h]
\centering
\begin{tikzpicture}[node distance=1.55cm, every node/.style={draw, rounded corners, align=center, font=\small, minimum width=2.6cm, minimum height=0.75cm}]
\node (mat) {Material\\coupon};
\node[right of=mat, xshift=2.5cm] (cable) {Cable\\assembly};
\node[right of=cable, xshift=2.5cm] (coil) {Bench\\coil};
\node[below of=coil] (tvac) {Thermal-vacuum\\module};
\node[left of=tvac, xshift=-2.5cm] (flight) {Small-sat\\demo};
\draw[->] (mat) -- (cable);
\draw[->] (cable) -- (coil);
\draw[->] (coil) -- (tvac);
\draw[->] (tvac) -- (flight);
\end{tikzpicture}
\caption{Conservative TRL ladder for superconducting spacecraft subsystems.}
\end{figure}

\section{Claims}
\begin{claim}
The most credible superconducting contribution to near-term spacefaring is subsystem efficiency and field generation, not exotic propulsion.
\end{claim}

\begin{claim}
A superconducting spacecraft subsystem must be evaluated by total mass, heat, failure, and operational burden, not by conductor resistance alone.
\end{claim}

\begin{claim}
Speculative superconductivity papers should be paired with conservative subsystem papers so that the research program has a useful path even if the speculative claims fail.
\end{claim}

\section{Reference architectures}
\subsection{Architecture A: electric-propulsion power trunk}
A solar-electric spacecraft routes megawatt-class power from arrays or storage to electric thrusters. Superconducting trunks may reduce waste heat and conductor mass. The core trade is among operating temperature, current, cable length, redundancy, and cryocooler mass.

\subsection{Architecture B: magnetic plasma module}
A compact superconducting coil shapes plasma exhaust or studies magnetic insulation. The module is not sold as a propellantless drive. Its measurable outputs are field map, plasma plume modification, wall heat-flux change, and net energy cost.

\subsection{Architecture C: instrument shielding experiment}
A small cryogenic magnet protects a radiation-sensitive detector volume. Success is a measured reduction in selected charged-particle fluxes, not whole-spacecraft shielding.

\section{Release notes}
The release should include mass budgets, thermal budgets, quench calculations, wiring diagrams, cryocooler models, field maps, radiation assumptions, and a failure-mode-and-effects table.

\begin{thebibliography}{99}
\bibitem{paisrtsc} Salvatore Cezar Pais. \emph{Piezoelectricity-induced Room Temperature Superconductor}. US Patent Application 20190058105, 2019. \url{https://patents.justia.com/patent/20190058105}.
\bibitem{paishtsc} Salvatore Cezar Pais. \emph{Piezoelectricity-induced High Temperature Superconductor}. US Patent Application 20190348597, 2019. \url{https://patents.justia.com/patent/20190348597}.
\bibitem{doe} U.S. Department of Energy. \emph{DOE Explains...Superconductivity}. \url{https://www.energy.gov/science/doe-explainssuperconductivity}.
\bibitem{nasa} NASA. \emph{Superconducting Wires}. \url{https://www.nasa.gov/eap-technology/superconducting-wires/}.
\bibitem{gonzalez} D. E. Gonzalez and G. R. Karr. \emph{Superconducting applications in propulsion systems. Magnetic insulation for plasma propulsion devices}. NASA-CR-184401, 1990. \url{https://ntrs.nasa.gov/citations/19930002825}.
\bibitem{tinkham} M. Tinkham. \emph{Introduction to Superconductivity}. 2nd ed., Dover, 2004.
\end{thebibliography}
\end{document}
