Asymmetric Inertial Forcing with Phase-Locked Counter-Rotating Rotors: Distinguishing Ground-Reaction Motion from Free-Space Payload Push_v2

This manuscript analyzes an inertial actuation concept using phase-locked, counter-rotating rotor sets that generate time-asymmetric internal force waveforms while canceling net reaction torque. The work is framed as an impulse-transmission problem: an isolated, continuously coupled platform cannot self-accelerate in free space, and any net momentum change requires momentum exchange across a defined boundary (ground contact, coupling to a separate mass, or expelled reaction mass), consistent with conservation of momentum. Two boundary mechanisms are distinguished: (A) Ground-reaction motion via tribological rectification (e.g., stick during constructive lobes and slip during destructive lobes), producing an asymmetric transmitted impulse to the ground. (B) Free-space payload push via a phase-selective couple/decouple interface that transfers impulse to a separate mass only during the constructive window (with the complementary impulse not transmitted during the decoupled window). This mode transfers momentum between subsystems; it does not generate reactionless thrust. A Hann-shaped transmitted-force model relates per-cycle impulse to a measurable interface parameter alpha, defined by: |I_minus| = alpha * I_plus yielding: I_cycle = (1 - alpha) * F_peak * T / 4 The commonly discussed “59/41” ratio is treated as an illustrative example corresponding to alpha = 0.41 (i.e., the destructive-window transmitted impulse cancels 41% of the constructive-window impulse), not as a universal property of the oscillator. The manuscript outlines control/timing targets for phase-selective coupling (millisecond-scale repeatability and high-bandwidth control loops) and proposes prototype tests and instrumentation to distinguish internal force asymmetry from externally transmitted impulse. An optional open-system extension (Mode C) treats the payload-push mechanism as a conventional reaction-mass thruster by ejecting mass after impulse transfer. Practical reaction-mass implementations include: (C1) discrete packets (pellets / engineered pucks, including processed in-situ materials), (C2) ablation-driven exhaust (thermal/plasma ejection), and (C3) electromagnetic launchers (coilgun/railgun) to accelerate discrete packets and set effective exhaust velocity. In Mode C, performance follows standard relations: F_avg ≈ I_cycle * f_cycleF_avg = m_dot * v_e Where: 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) Thrust and achievable v_e are constrained primarily by available power, efficiency, thermal management, and reaction-mass throughput. Contact: please use the author’s ORCID profile.This manuscript has not been peer reviewed.