Context
The vacuum of space is cold and causes no drag on propulsion or
hindrance to electromagnetic fields, presenting advantageous operating
conditions for distributed maglev propulsion. This problem is framed
analytically in ideal conditions to isolate the interaction of one
satellite to the object above. The mechanics of this interaction can be
viewed in the Ring Launcher experiment where the maglev effect is
demonstrated by propelling a small steel ring upwards from its original
position sitting on top of a solenoid as current flows into the coil
[3]. The calculated force required to lift the ring against gravity
is compared to the force experienced between the applied and induced
magnetic fields to determine if lift is achievable.
These mechanics are replicated in the satellite swarm, as each
satellite’s pulse acts as a ring launcher and each parallel layer acts
as a flat plate pushing upwards from its position. In total, this system
of parallel layers acts like the coils of a large spring. The swarm base
layer must be held in a fixed orbital position requiring thruster offset
during launch, however all forces are distributed across the
electromagnetically XY tethered layers that act as combined inertial
masses. In this context, the square arrangement of four satellites below
each higher layer object and combination of the four pulse vectors
generates a combination vector in the Z direction, at a tangent to the
system’s orbital arc. The objects centre of mass is then moved along the
resultant sum of vectors by the net forces work. Application of the
procedure in reverse would then be capable of decelerating payloads at
the destination swarm. This novel propulsion method is not possible in
single point thrust designs and is only functional in the advantageous
orbital setting.
Satellite design is considered as a component size constraint, the
operational limitations such as heat loss, solar absorption and orbital
maintenance are beyond the scope of this paper. These factors and others
will be addressed by modelling and research provided the electromagnetic
problem construction, context and solution are valid. No further
treatment is given to the orbital context as the electromagnetic
interaction is the core problem to resolve and there is a wide variety
of research available on the development and cutting edge of satellite
componentry [4, 15, 38]. The satellite frame material selection
determines the mechanical stress limits while power storage
subcomponents establish the maximum power supply limit.
Literature on various material limits establish the boundary conditions
of the problem and current design thinking establishes relative sizing
of components within the satellites available volume [38].
Evaluation of the concept within the framework of material limits is
sought by deriving a simple propulsion success criterion from the
construction of the problem. Provided the foundational mechanics are
valid, no material limits are exceeded and the success criterion is
satisfied, the proposed design is theoretically capable of propelling a
shipping container on an unpowered interorbital arc for arrival in an
extraterrestrial orbit.