Cislunar Relay Mass Driver Network (CRMDN)

Cislunar Relay Mass Driver Network (CRMDN)

1. Executive Summary

This proposal outlines a scalable, propellant-efficient system for transferring bulk payloads from the Moon into Low Earth Orbit (LEO). The objective is singular and explicit: enable large-scale placement of lunar-derived mass into circular LEO for orbital construction, infrastructure, and industrial expansion.

Payloads remain inert and propulsion-free. All propulsion, capture, energy absorption, and momentum management are centralized within reusable orbital infrastructure nodes. The architecture incrementally reduces orbital energy across multiple relay stages to enable controlled LEO circularization.

2. Design Philosophy

  • Dumb Payloads: No onboard propulsion, tanks, avionics, or propellant.
  • Centralized Delta-V: All velocity changes occur at reusable stations.
  • Energy Processing Infrastructure: Stations function as orbital kinetic-energy processors.
  • Momentum Balancing: Bidirectional transfers minimize net station recoil.
  • LEO-Optimized Architecture: All orbital transitions are tuned specifically for circular LEO insertion.
  • Scalable Industrial Growth: Infrastructure expands with throughput demand.

3. System Overview

The CRMDN consists of:

  • Lunar Surface Mass Drivers
  • Orbital Relay & Energy-Exchange Stations
  • Autonomous Intercept & Capture Drones
  • Final LEO Circularization Node

Each relay station performs:

  • Velocity-matched intercept support
  • Electromagnetic kinetic energy absorption
  • Momentum redistribution
  • Re-acceleration toward the next lower-energy orbit

4. Orbital Architecture

Stations are positioned in energetically staged locations between lunar orbit and LEO, such as:

  • High Lunar Orbit
  • Earth–Moon L1 Halo Orbits
  • Distant Retrograde Orbits (DRO)
  • Highly Elliptical Earth Orbits
  • Pre-LEO Capture Elliptical Orbits

The specific orbital energy per unit mass is:

\[ \epsilon = -\frac{\mu}{2a} \]

where \( \mu \) is the gravitational parameter and \( a \) is the semi-major axis.

Each relay stage reduces orbital energy incrementally until final circularization into LEO at approximately 7.8 km/s orbital velocity.

5. Payload Transfer Sequence

Step 1: Lunar Launch

Lunar mass drivers accelerate inert payload capsules onto precomputed Earth-intercept trajectories. Lunar escape velocity:

\[ v_{esc,moon} = \sqrt{\frac{2\mu_{moon}}{r_{moon}}} \]

Launch parameters are optimized to minimize excess velocity at the first relay intercept.

Step 2: Velocity-Matched Intercept

Relay stations occupy orbits chosen to closely match incoming payload velocities. Relative velocity:

\[ \Delta v = |v_{payload} - v_{station}| \]

Autonomous ion-drive drones perform only fine trajectory corrections. Primary kinetic energy removal is handled electromagnetically at the station.

Step 3: Electromagnetic Capture & Energy Absorption

Incoming payload kinetic energy relative to station is absorbed using:

  • Linear electromagnetic braking rails
  • Regenerative generator tracks
  • Magnetic deceleration channels

Energy absorbed per payload:

\[ E_k = \frac{1}{2} m v^2 \]

Recovered energy is stored in:

  • Capacitor banks
  • High-mass flywheel systems
  • Station energy grids

Energy is later reused for outbound acceleration.

Step 4: Momentum Management

Momentum conservation requires station mass \( M \) to absorb recoil:

\[ \Delta v_{station} = \frac{m}{M} v \]

To minimize net station drift:

  • Inbound and outbound transfers are phased 180° apart in orbital position.
  • Opposing-direction transfers are scheduled to balance momentum.
  • Counter-rotating flywheels absorb residual impulse.

Balanced bidirectional operations reduce station-keeping propellant requirements.

Step 5: Re-Acceleration Toward LEO

After staging, payloads are electromagnetically accelerated toward progressively lower-energy Earth orbits until reaching a final pre-LEO elliptical orbit.

The final node circularizes payloads into stable LEO without onboard propulsion.

6. Power Systems

Solar Power

Primary power source for most stations:

\[ P = A \cdot I \cdot \eta \]

  • \( A \) = solar array area
  • \( I \) = solar irradiance
  • \( \eta \) = conversion efficiency

Nuclear Baseload (Optional High-Throughput Nodes)

High-volume nodes may employ compact fission reactors to:

  • Increase launch frequency
  • Provide eclipse resilience
  • Stabilize energy storage systems

7. Throughput and Energy Scaling

For payload mass \( m \) and velocity adjustment \( v \), energy processed per stage:

\[ E = \frac{1}{2} m v^2 \]

At industrial-scale throughput (10^5–10^7 tons/year), stations function as large orbital energy conversion facilities.

Energy cannot be canceled via momentum balancing and must be stored, redistributed, or radiated as losses.

8. Infrastructure Phasing

Phase I – Terrestrial Bootstrapping

  • Station cores launched from Earth.
  • Precision electronics and reactors Earth-supplied.
  • Initial structural mass terrestrial.

Phase II – Hybrid Expansion

  • Lunar-derived structural components integrated.
  • Regolith shielding added.
  • Partial lunar material resupply.

Phase III – Lunar Autonomy

  • Structural mass sourced from lunar metals.
  • Replacement rails and components fabricated from lunar materials.
  • Reduced Earth dependence.

9. Safety and Operational Stability

  • No atmospheric reentry.
  • No Earth-surface targeting.
  • Incremental energy reduction per stage.
  • Failure containment within defined orbital zones.
  • Redundant routing paths.

10. Advantages Over Direct Lunar-to-LEO Ballistic Transfer

  • No Payload Propulsion: Maximized mass efficiency.
  • Centralized Energy Infrastructure: Reusable high-capacity systems.
  • Momentum Balancing: Reduced station-keeping cost.
  • Scalable Throughput: Network expansion increases capacity.
  • Controlled LEO Circularization: Eliminates per-payload capture systems.

11. Strategic Impact

The CRMDN enables sustained, large-scale transfer of lunar mass into LEO, making orbital construction materially feasible. By centralizing propulsion and energy handling into reusable infrastructure, the network transforms LEO from a launch-dependent environment into an industrially supplied zone.

This architecture establishes a long-term pathway toward economically scalable orbital development based on lunar resources.