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.