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Asymmetric Inertial Forcing with Phase-Locked Counter-Rotating Rotors: Distinguishing Ground-Reaction Motion from Free-Space Payload Push
No full textThis manuscript analyzes an inertial actuation concept using phase-locked, counter-rotating rotor sets that generate time-asymmetric internal force waveforms while canceling reaction torque. It distinguishes two operational mechanisms for producing net external impulse: (A) ground-reaction motion via tribological rectification (stick during constructive lobes and slip during destructive lobes), and (B) free-space payload push via a phase-selective couple/decouple interface that transfers impulse to a separate mass only during the constructive window. The manuscript explicitly notes that an isolated, continuously coupled platform cannot self-accelerate in free space; net impulse requires an external reaction path (ground contact or a separate payload), consistent with conservation of momentum.
A Hann-shaped force model is used to derive per-cycle impulse I_cycle = (1 - alpha) * F_peak * T / 4 and to relate impulse transfer to expected acceleration and energy. The reported 59/41 constructive-to-destructive ratio is treated as a time-integrated difference in center-of-mass excursions rather than evidence of reactionless thrust. Control and timing targets for phase-selective coupling (millisecond-level repeatability and kHz-class control loops) are discussed along with proposed prototype tests and validation instrumentation.
An optional extension (Mode C) is included in which the payload-push mechanism is operated as an open-system kinetic mass-ejection thruster by ejecting discrete reaction-mass packets (pellets or sintered regolith pucks). In this configuration, performance follows conventional reaction-mass propulsion relations, with average thrust approximately F_avg ~ I_cycle * f_cycle and F_avg = m_dot * v_e, limited by available electrical power and reaction mass. Also, ablative/Thermal mass ejection methods are explored.
F_avg = average thrust (N)
I_cycle = impulse per cycle (N*s)
f_cycle = cycle frequency (1/s)
m_dot = mass flow rate (kg/s)
v_e = effective exhaust velocity (m/s)
Keywords: kinetic mass driver, mass driver propulsion, reaction mass propulsion, in-situ resource utilization, ISRU, regolith propellant, asteroid propulsion, electric propulsion, pulsed thruster, impulse propulsion, phase-selective coupling, time-asymmetric forcing, inertial actuation, counter-rotating rotors, torque cancellation, impulse per cycle, thrust-to-power, exhaust velocity, mass flow rate, pellet thruster, particulate exhaus
