METRIC FLIGHT / MISSION ENGINEERING / 24 OCTOBER 2026
Understand the separate launch, transfer, landing, ascent and return requirements behind the Metric Flight Moon station concept.
Payload to orbit
Power versus time
Separate lander
Close the chain
Animated sequence explains dependencies; it does not depict measured performance.
Launch delivers the vehicle to space. Transfer propulsion delivers cargo to the lunar vicinity. Landing needs a separate descent design. Crew missions must close ascent and return before departure.
THE ENGINEERING / Lunar cargo transport and landing architecture
A launch vehicle must deliver a defined payload, envelope and orbit. Mass and geometry must come from packaging and integration studies, not a deployed station illustration. Provider selection, launch agreements and payload qualification remain open.
Solar-electric propulsion is a candidate for suitable uncrewed cargo transfers. NASA’s published Gateway trajectory study provides an external example of low-thrust orbital transfer planning. It does not qualify a Metric Flight magnetic nozzle or provide a trajectory for our cargo. Compare delivery time, available power, radiation exposure, navigation and propellant against a conventional transfer architecture.
A transfer engine is not automatically a lander. Descent requires an independently designed thrust and throttle envelope, guidance, terrain sensing, landing structure and contingency plan. Lunar dust and plume interaction constrain landing distance from habitats and utilities. No landing mass, descent trajectory or flight-qualified vehicle is claimed here.
For a crewed mission, define ascent, rendezvous, transfer and Earth-return capability before committing people to the surface. A cargo delivery architecture does not demonstrate a crew return system. Fuel production from local resources is a future trade, not a dependency of the initial logistics concept.
Field mapping, power accounting, plasma diagnostics and thermal methods can inform a future cargo-engine comparison. They do not establish lunar landing performance. Required next inputs are delivered mass, destination orbit, arrival date window, surface location, reserve policy and an end-to-end trajectory and vehicle study.
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 ↗05 / EXPLOREFollow the measurement gates from reference momentum closure through magnetic redesign, system comparison and a possible uncrewed demonstration.
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.