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.