The missing link in the Space Pipeline. Blue Origin and SpaceX are building the lunar landers. NASA is flying Artemis crews every 10 months. Nobody yet has a way to get cargo into low Earth orbit cheaply enough to feed a permanent moon base. BGKPJR is a 37-km evacuated coilgun tunnel that accelerates unmanned cargo pods to Mach 5 (1,700 m/s) on ground-based magnets — no first-stage propellant, no booster to recover. Operational cargo pipeline in 7–9 years.
Watch all four stages in real-time: maglev acceleration, Gryphon wing deploy and atmospheric climb, hybrid propulsion burn to orbit, and Kepler solar sail deployment. Use the controls to scrub through mission time or jump to any stage.
BGKPJR is the missing link in the Space Pipeline. Blue Origin builds the landers (Blue Moon Mk2) and ISRU refuel tech (Blue Alchemist). SpaceX builds HLS. NASA builds Artemis crew flights. Nobody yet has a way to get cargo into LEO cheaply enough to feed sustained lunar operations. We do.
Assuming a 2026 program start, an operational unmanned cargo pipeline can be in service by 2033–2035. Parallel to NASA Artemis crew launches every 10 months using SpaceX HLS or Blue Moon Mk2 landers. Lunar base target: 2029. Every Artemis crew that arrives finds a base already supplied by BGKPJR cargo.
Phase 1 critical path: cargo pods only. The crewed Gryphon vehicle is deferred to Phase 2 — same 37 km rail accommodates both, but the unmanned cargo pipeline ships first.
A 37-km evacuated coilgun tube at 15° incline accelerates the cargo pod to Mach 5 in 43.5 seconds. Tube pressure 0.05 atm. Linear synchronous motor architecture: copper drive coils on the rail, REBCO superconducting armature on the vehicle (cooled to 20 K). Peak field 8 T. Sustained at 4 G.
| Rail length | 37 km |
| Exit velocity | Mach 5 (1,700 m/s) |
| Peak G-load | 4 G |
| Tube pressure | 0.05 atm |
| Drive architecture | LSM coilgun · 7,400 coils @ 5 m |
| Magnet field | 8 T (REBCO armature @ 20 K) |
| Muzzle seal | LH₂ + thermite (trade study) |
Pods exit the rail at Mach 5, fire a small 2nd-stage rocket to push apogee to ~166 km (sub-orbital). A permanent in-space BGKPJR Space Tug (Size of a delivery van) catches the pod at apogee, circularizes it to LEO with a 6.13 km/s burn, refuels from a co-orbiting Manna-F propellant pod, then performs trans-lunar injection. The Tug hands off to a Blue Moon Mk2 or SpaceX HLS lander in lunar orbit. The Tug never lands and never fights Earth's gravity — it lives in space, refuels in space, and works in space.
| Tug dry mass | 5,000 kg |
| Propellant capacity | 25,000 kg per refuel |
| Catch + circularize Δv | 6.13 km/s (largest burn) |
| TLI Δv (after refuel) | 3.15 km/s |
| Total outbound Δv | 11.5 km/s (LEO refuel required) |
| Refuel interface | Manna-F pods · long-term ISRU water |
| Lifetime | 50 cycles (refurbishable) |
Lander delivers pods to the surface. Cargo offloaded by crane. Empty pods don't get wasted — they become "Space LEGOs." NASA in-situ resource utilization research is designing ways to fill empty pressure vessels with lunar regolith, converting them into radiation-proof walls, storage sheds, and roads. Every pod we ship is a free building block for the first permanent moon city.
| Pod end-of-life | Regolith-filled structure |
| Lunar lander partner | Blue Moon Mk2 · SpaceX HLS |
| Refuel source (long-term) | ISRU lunar water |
| Crew arrival cadence | Artemis · every 10 mo |
| Cargo cadence (initial) | 21 pods / year |
| Cargo cadence (mature) | 50 pods / year |
The crewed Gryphon waverider and the Kepler solar sail are technically valid concepts within the same 37 km rail architecture, but they are deferred until the unmanned cargo pipeline is operational. Constants retained for forward-compatibility — the rail accommodates both vehicles. Showcase only; not on Phase 1 critical path.
Hypersonic waverider with variable-geometry wings. At tube exit, wings deploy instantly. Aerodynamic lift to Mach 8, then hybrid propulsion to LEO. Glides back unpowered — no recovery propellant. Same rail as cargo pods.
| Wingspan | 18 m deployed |
| Dry mass | 50 t (provisional) |
| Payload | 5,000 kg |
| Max Mach | Mach 8 |
| Glide ratio | 6.5:1 |
Above 400 km, a 1,200 m² CP1 Polyimide solar sail deploys. Zero propellant; solar pressure at 1 AU gives 0.208 mm/s² continuous Δv. For Phase 4 deep-space missions only — no role in cargo-to-Moon pipeline.
| Sail area | 1,200 m² |
| Sail mass | 50 kg |
| Material | CP1 Polyimide |
| Deploy altitude | 400 km |
| Solar ΔV | 0.208 mm/s² |
The 37 km barrel is the largest electromagnetic accelerator ever proposed. 7,400 copper drive coils at 5 m spacing form a Linear Synchronous Motor: stationary coils on the tube, REBCO superconducting armature on the vehicle. The pod surfs a traveling magnetic wave from zero to Mach 5 in 43.5 seconds — then breaches a liquid-hydrogen cryogenic membrane that holds the vacuum behind it. The membrane breach is the engineered event that gates the entire architecture.
Each copper drive coil along the 37 km tube is energized individually, timed to the pod's exact position. Leading coils fire first, generating forward magnetic attraction. Trailing coils de-energize immediately to prevent back-pull. The result is a traveling magnetic wave that the vehicle's onboard REBCO armature continuously chases — Linear Synchronous Motor architecture, identical in principle to a maglev train scaled to launch energies.
The midsection of the vehicle carries a REBCO high-temperature superconducting armature ring, chilled to 20 K by an onboard cryostat that doubles as the LH₂ propellant tank. The armature couples magnetically to the tube's traveling field. No physical contact with the bore wall. No friction. No rail erosion. The vehicle rides a magnetic cushion at 4 G for 43.5 seconds.
A single launch transfers ~123 GJ of kinetic energy to a fully-loaded vehicle (mass 85 t at 1,700 m/s). With drive efficiency ~60%, the SMES (Superconducting Magnetic Energy Storage) bank stores 580 GJ. Peak discharge lasts 43.5 seconds. Charge rate: 650 MW. Peak draw: 39 GW. Rail Δv represents 18% of the 9,400 m/s required to reach LEO — the rest is rocket propulsion.
When a vehicle exits the tube at Mach 5 (1,700 m/s), it transitions from 0.05 atm vacuum into ~1 atm atmosphere in milliseconds. Dynamic pressure at exit is 1.77 MPa — without mitigation, the structural shock destroys the vehicle. The membrane that holds the tube vacuum, and how the vehicle breaches it, is the single most-load-bearing engineering decision in the architecture.
Two parallel alternatives are under study. A formal trade study in Phase 0 will determine the canonical choice. We document both honestly here:
A thin 20 K liquid-hydrogen membrane sealed behind a structural diaphragm. As the vehicle breaches it, the LH₂ vaporizes (~1000× volume expansion), mixes with atmospheric oxygen in the wake, and detonates. The detonation wave is engineered to propagate behind the vehicle, providing a ~50 m/s thrust impulse rather than a destructive shock.
A three-layer membrane: structural carbon-fiber diaphragm + aerogel buffer + L1 thermite (Al/Fe₂O₃). On tungsten-carbide tip contact at 1,700 m/s, friction initiates thermite combustion across the membrane in <50 μs. The membrane self-consumes into alumina dust and iron vapor — zero solid debris field. The vehicle passes through a brief plasma aperture rather than a solid barrier. 2,000 °C peak.
Detailed layer-by-layer specification for the current canonical (LH₂) muzzle architecture.
Vehicle nose architecture engineered for the LH₂ membrane breach event. Five concentric material layers, each solving a different physics problem in sequence:
Where Gryphon carries crew at 4G human-rated acceleration, Manna pods carry cargo at 2.5G–108G — unlocking dramatically higher exit velocities, smaller propellant fractions, and per-kg costs that make sustained lunar operations economically viable. Three variants cover every cargo class. Four more are in design.
On April 30, 2026, the entire BGKPJR repository set was audited dimensional-integrity-end-to-end before being sent for review by Scott Lukens, Senior Systems Engineer at Victory Solutions Inc. (a NASA Marshall Space Flight Center contractor in Huntsville, AL). We caught and reconciled three different baselines that had drifted apart, fixed mutually-incompatible math, and aligned every visualization with a single source of truth. The full audit and decision record are public.
📄 PRE-LUKENS-AUDIT-2026-04-30.md · 📄 CANONICAL-BASELINE.md · 🐍 bgkpjr_dimensions.py (single source of truth)
This honesty matters. Pre-Phase-A aerospace concepts that hide their gaps fail review on first contact. The goal here is to know the gaps better than any reviewer will, document them publicly, and ladder up to the level where NIAC Phase I funding pays to close the next layer. The 7-9-year Manhattan timeline depends on this discipline, not optimism.
By providing 1,700 m/s from ground-based magnets, BGKPJR delivers 18.1% of the 9,400 m/s needed to reach LEO. Every m/s of rail Δv is a kg of propellant the vehicle no longer carries.
For the 37 km rail at Mach 5 exit: a = 1700² / (2 × 37,000) = 39.1 m/s² (3.98 G). Sustained at 4 G — within the 5 G patent envelope and well below the 5.0 G human limit.
At 1 AU, solar pressure = 4.56 × 10⁻⁶ Pa. With 1,200 m² sail and 3.2 kg mass, effective acceleration ≈ 1.8 mm/s² — low but continuous. Over 6 months: Δv ≈ 2.8 km/s with zero propellant.
Eliminating the first stage cuts propellant cost by 40%. Amortizing fixed costs over N = 50 launches/year achieves the $800/kg Phase 1 target. Serial production (N = 200/year) achieves $200/kg — a 96% reduction vs. Falcon 9.