5-Gear Earth Launch Planner — External Beam + 2-Stage Rocket (Grounded)

This is a physics-grounded launch dashboard: thrust + rocket equation + gravity + drag/heat proxies. Beam/magnetics are modeled as external infrastructure (power-limited, fades quickly). m = E/c² appears only as an accounting readout (photon component uses F = P/c, ṁ = P/c²). Clocks (UTC/CST/Interstellar/Geodisc/Galactic) are display frames, not propulsion.

Label refinement (for consistency): You’re not wrong conceptually — you’re just:

Assigning gravity to rotation instead of mass/curvature.
Treating orbit as resistance instead of free-fall along a geodesic.

Once those labels are corrected, your framework becomes physically consistent and simulation-ready. Next step options: geodesic ladder (Earth → escape → solar) or map it to your multi-stage momentum steps.

Inputs — 2 Stages, External Assist, Cooling, Power

Total liftoff mass m₀ (kg) Total dry mass m_dry (kg) Stage-1 propellant fraction (0–1) Stage separation dead mass penalty (kg)

Propellant = m − m_dry. Stage-1 burns its fraction, then drops stage hardware (toy) + penalty.

Stage 1 engine mode Stage 1 thrust (MN) Stage 1 Isp (vac) (s)

Chemical typical 300–450 s. NTR typical ~850–950 s but not sea-level optimized.

Stage 2 engine mode Stage 2 thrust (MN) (chem/NTR) Stage 2 Isp (vac) (s)

Photon uses F = P/c (needs gigantic power). If thrust can’t lift, it will NO-GO.

External assist: track / mass-driver boost (m/s)

Use track boost (Gear 1)

Launch latitude (deg) (Earth rotation boost)

Include Earth rotation boost (eastward)

Ground “beam push” (kN) (external EM infrastructure)

Use beam assist (Gear 2–early Gear 3)

Beam is modeled as external momentum transfer onto a conductive “pusher plate” on the rocket base. It is power-limited and fades with altitude/time (coupling drops).

Cooling: coolant mass (kg) Coolant capacity (kJ/kg·K) Available electrical power (MW) (pumps + controls + beam budget) Photon share (%) (only matters if Stage 2 = Photon)

Photon thrust is tiny unless power is enormous. Mass↔energy accounting is shown: ṁ_eq = P/c² and F = P/c.

Guidance: “gravity turn” start (km) Guidance: “gravity turn” end (km) Max-Q proxy limit

Reality constraint: Time dilation does not create lift or Δv. It is an effect of speed & gravity. This simulator shows it as a measurement, while propulsion comes from momentum exchange.

Rocket View — Atmosphere Layers + Beam/Magnetics + Hotspots

Gear: 0 / 5

Stage: 0 / 2

Phase: Idle

t: 0.0 s

The rocket is surrounded by “magnetic field” in this sim only as a control/containment proxy (plasma shaping), while real lift/Δv comes from thrust + external assist (track/beam).

Run Log (Step-by-step)

Ready.

5 Gears — What the rocket is doing (GO/NO-GO gates)

Gear	What happens	Gate (GO / NO-GO)	Status
1	External momentum setup (Earth rotation + track)	Track boost enabled OR Stage-1 TWR ≥ 1.2	—
2	Liftoff through dense air (beam allowed early)	TWR ≥ 1.2 and heat/max-Q below limits	—
3	Max-Q wall (smart throttle)	qProxy ≤ limit (throttle if needed)	—
4	Upper atmosphere climb + gravity turn (build vx)	Enough propellant and dvRem ≥ requirement	—
5	Orbit insertion (toy) (vx target + altitude)	alt ≥ 200 km AND vx ≥ 7800 m/s (toy)	—

Notes: This is a simplified 2-D model. Drag/heating are proxies. It’s meant to be consistent, not high-fidelity.