METRIC FLIGHT / MISSION ENGINEERING / 24 OCTOBER 2026
Follow the measurement gates from reference momentum closure through magnetic redesign, system comparison and a possible uncrewed demonstration.
Calculated
Calibrated
Reproduced
Mission-specific
Animated sequence explains dependencies; it does not depict measured performance.
Define the maneuver and its timeline. Scheduled low thrust needs time and available power. Time-critical maneuvers require separately sized capability. Validate the engine before station integration.
THE ENGINEERING / Magnetic-nozzle propulsion validation roadmap
Specify the operating point, apparatus, uncertainty budget, calibration method and acceptance criteria before running. Record thrust, propellant flow, source diagnostics, chamber pressure and complete electrical input on a synchronized timeline. Keep raw observations and analysis versions together.
Compare measured thrust with a physically complete account of exhaust and other momentum exchange. Sweep chamber pressure, including lower-pressure conditions where feasible, and characterize source-mouth conditions rather than assuming a remote gauge represents them. Resolve stand drift, thermal effects, electromagnetic coupling and measurement bandwidth. A pressure null by itself is not decisive.
Compare the reference assembly with a candidate hybrid permanent-magnet and trim-coil arrangement at matched, declared conditions. Record field topology, thermal exposure, demagnetization margin, RF coupling, thrust and lifetime. A successful field match is an input to this comparison, not its conclusion.
Measure total electrical input and installed hardware mass, then include tanks, feed, power processing, cooling and control. Compare against an appropriate established propulsion family at the same mission requirements. A component improvement can disappear when the complete installation is counted.
Require independent reproduction and an application-specific qualification program. Consider a separately reviewed uncrewed demonstration before operational station use. No present calculation closes that flight gate.
For an isolated-device claim, include actuators, stored fields, supports, heat, leaks and escaping radiation in the momentum boundary. A repeatable residual merits investigation; it does not identify a new force carrier. Our work has not established a sustained internal-only propulsion mechanism.
These pages describe Metric Flight proposals and calculations, not qualified hardware. External references establish engineering context; they do not validate our station architecture.
CONTINUE THE MISSION
Explore how propulsion research connects to ARLO, lunar transport, power, cooling and investment milestones.
Read the study ↗02 / EXPLOREStudy the additional electrical load, radiator demand and eclipse storage that an electric propulsion option would impose on ARLO.
Read the study ↗03 / EXPLORESeparate long-duration station reboost from time-critical avoidance, docking constraints and verified end-of-life disposal.
Read the study ↗04 / EXPLOREUnderstand the separate launch, transfer, landing, ascent and return requirements behind the Metric Flight Moon station concept.
Read the study ↗06 / EXPLOREReview current computational assets, proposed hardware, station concepts and the evidence required before stronger commercial or IP claims.
Read the study ↗FROM UNDERSTANDING TO REVIEW
Get the propulsion white paper through our company-email access page, or start a technical conversation about a defined engineering scope.