Conclusions

The derived success criterion based on the induced current provides clear results for design assessment. The analysis path is applicable to any two coil context provided the appropriate winding geometry substitutions are made. This leads to the conclusion that the paper’s objective of isolating a general success criterion is achieved despite no presented scenario being successful in achieving propulsion.
Discussion of the presented scenarios is able to inform future design thinking to prioritise solenoid inductivity, coil width and current carrying capacity to generate the maximum force and overcome any conductive object above’s inertia. Further investigation of multicoil solenoids and cargo plate design is suggested as the solution to creating a successful scenario. The noted sources of variance in electromagnetic results from plate decomposition to theoretical ERC’s is an area suggested for significant research to resolve the presented complexities in an analytical manner without resorting to finite element methods.
These challenges can be addressed with the application of numerical methods in industry verified FEM software such as MATLAB’s Simulink multiphysics suite however all models are still reliant on the validity of their base assumptions. Thus the investigation of geometry to frame this problem and bound it with current material limits and design thinking is the key to constructing a valid model.
In summary, solenoid coil design determines inductance, which is assessed against stored power to determine the induced current and resultant repulsion force required to overcome an object above’s inertia. The proposed propulsion method combines multiple maglev propulsion vectors to reduce the requirements on individual satellites and must be investigated with numerical methods. The swarm satellite application of high energy pulsed solenoids in freight transport is a new use case for both technologies. It is proposed here for peer review and to initiate further research on design and componentry.
Reaching Mars is achievable today with our current technology, the only barrier to entry is cost. Just as reusable rocket systems are drastically reducing the cost of orbital entry, mass produced, reusable, interorbital freight transport satellite swarms could drive down the cost of freight crossing the void. Establishment of freight shipping lanes between orbits will be the connector that enables crewed missions to commence safely and provide the ongoing support required for humanity to become an interplanetary species.