Necklace of Selene Mission Profile

This architecture utilizes established 2026-era lunar technologies—specifically the 3,000 kg payload capacity of the Blue Moon Mark 1 and comparable CLPS (Commercial Lunar Payload Services) heavy landers. By leveraging these existing delivery platforms, we move from theoretical concepts to a feasible infrastructure project.

Additionally, a modern lunar base cannot survive on power alone. By integrating a single-mode silica fiber optic core into the power cable, we are establishing the Moon's first high-bandwidth ground network alongside the power grid. This "Lunar Nervous System" provides a redundant physical backbone for 5G/6G wireless overlays and direct-to-Earth (DTE) connectivity.

1. Logistical Baseline (3 Heavy-Lift Missions)

Each of the three missions delivers a 3,000 kg payload pack, totaling 9,000 kg of infrastructure. This capacity is consistent with current aerospace specs for uncrewed cargo landers.

Generation (18 Solar Nodes):

Mass: 150 kg per node (1 kW capacity). 

Tech: Utilizes high-efficiency III-V multijunction solar cells (~30% efficiency) on modular, self-deploying masts. The 150 kg mass budget includes a redundant power management system and the node's ground-interface frame.

Locomotion (3 "Heavy Engineer" Rovers):

Mass: 900 kg per rover.

Manipulators: Equipped with modular robotic arms (e.g., Lunar-TARS architecture) for autonomous station assembly and cable splicing.

Locomotion: The "Spool-Wheel" drive. The 320 km cable spool is integrated as the primary drive wheel. This turns dead weight into a locomotion advantage, providing a wide footprint for regolith flotation and zero-delay deployment.

Dual-Purpose Infrastructure: Power & Data (960 km):

Mass: 2,016 kg total (2.1 kg/km).

Tech: The composite cable is an Optical Power Ground Wire (OPGW) optimized for the lunar vacuum. The silica core serves a dual role as the 6 GPa tensile backbone and the high-bandwidth data conduit. This eliminates the latency and "line-of-sight" issues of satellite-only communication at the poles. This core is surrounded by Space-grade stranded aluminum core (AXALU-style) with a thin polyimide/PTFE dielectric layer and a helical carbon-fiber overwrap. This provides the necessary specific conductivity (22.6) and thermal flexibility to survive the lunar surface.

5G/6G Wireless Overlay: Solar nodes function as Lunar Small-Cell Base Stations. These nodes provide localized high-speed wireless coverage for rovers and EVA suits, using the fiber backbone to relay data back to the primary Earth-link nodes.

Earth-Link Gateways: Nodes positioned on the "Near Side" longitude at higher elevations will be equipped with mechanically steerable K-band reflector antennas. Since Earth sits at roughly 5° above the horizon at 85°S, these gateways provide the primary DTE (Direct-to-Earth) bridge for the entire grid.

2. Phased Deployment Schedule

The mission follows the Moon's axial rotation to stay within "sunlight windows" for the initial startup, avoiding the complexity of landing in the dark.

Mission 1 (T+0): Lands at 0° longitude (Lunar Dawn). 

    Rover 1 initializes Node 1 and Node 18.

Mission 2 (T+24 hours): Lands at 120° longitude (Sunlight Window).

    Rover 2 initializes its local nodes and moves toward Rover 1.

Mission 3 (T+14 days): Lands at 240° longitude (Lunar Dawn for that sector).

    Rover 3 completes the final 320 km stretch.

3. Operational Logic

The system uses the grid to build the grid. 

Grid-Powered Transit: Once the first 60 km segment is connected, the rovers draw power directly from the HVDC line. They are no longer limited by their internal battery or local sunlight. They can drive through shadowed regions (craters or the 14-day night) at a steady 5 km/h, using grid energy to maintain the electronics' thermal survival.

Redundancy: The 18 active nodes form a self-healing ring main. If a segment is damaged, the bi-directional HVDC logic automatically reroutes power from the sun-facing side of the pole to the explorer.

Terrain-Resilient Data: At 85°S, terrain occlusion (crater rims) can block Earth's signal up to 80% of the time in certain spots. The Fiber Backbone solves this; even if a rover is in a "dead zone" behind a mountain, it plugs into the grid and its data travels via fiber to the nearest Earth-link node with a clear line-of-sight.

Current Hardware: We are using space-qualified 0.4m K-band antennas and radiation-tolerant 5G/6G digital processing units. The 1 kW power budget per node is more than sufficient to run a high-gain telecom hub and a local base station simultaneously.

4. Technical Feasibility Summary

This design avoids the massive thermal/mechanical hurdles of a 40 kW nuclear reactor. 

Mass Efficiency: 9 tons of modular infrastructure vs. a 40+ ton nuclear transport/radiator assembly.

Reliability: 18 distributed generators vs. a single point of failure.

Utility: Provides a 950 km "Power Railway" that supports 1 kW average consumption for rovers—exceeding the power of current Mars rovers by a factor of ten.

The Spool-Wheel Advantage: The rovers deploy the grid and the network at the same time. Every meter of cable laid is a meter of high-speed internet. As a result, there is no risk of losing connectivity with the service robots.

The Necklace of Selene is a multi-domain utility. It provides the Circulatory System (Power) and the Nervous System (Data) for the lunar south pole. By using 3 missions to deploy a redundant mesh, we achieve a capability that exceeds NASA's fission projects while providing a permanent, high-bandwidth corridor for all future lunar exploration.

Necklace of Selene 2

Almost a year ago, I proposed the Necklace of Selene which outlined a series of flexible, wire-shaped solar sections circling the lunar poles. It utilized the Moon's rotation and axial geometry to ensure a 7/24 energy supply through a high-voltage, low-current system with bypass circuitry for shadowed segments. I would like to improve on that idea further to make it more feasible.

The primary competitor for lunar power, the NASA Fission Surface Power (FSP) project, faces significant feasibility hurdles. A 40 kW electrical reactor requires roughly 160 kW to 200 kW of thermal generation due to 20-25 percent efficiency. In the lunar vacuum, heat dissipation is limited to radiation governed by the Stefan-Boltzmann law. Without convection, this necessitates immobile radiator panels exceeding 100 square meters that are prone to mechanical failure during deployment and localized damage.

The refined Necklace of Selene architecture replaces this immobile, single-point-of-failure reactor with a 16-node distributed mesh grid. Each station provides approximately 1 kW, ensuring a constant 8 kW to 9 kW across the polar region. This is roughly 10 times the 110 W provided to Mars rovers like Perseverance, allowing for high-speed robotic mobility and active thermal management over a much larger lunar surface area.

The technical backbone of the grid is a three-tier composite cable. The core consists of a single-mode silica fiber optic strand providing a terabit-scale data link and a 6 GPa tensile backbone. Electrical conduction is handled by aluminum strands helically wrapped around the core. This helical geometry acts as a mechanical spring to manage the Coefficient of Thermal Expansion (CTE) mismatch between aluminum and silica over 300 K temperature swings. Aluminum is utilized instead of copper due to its twice the electrical performance per kilogram. The outer layer is a stranded carbon fiber overwrap that provides armor against abrasive regolith and serves as a high-emissivity thermal radiator.

Deployment utilizes a kinetic energy recovery method. Instead of sacrificing fuel to bleed off all momentum, the lander performs a constant-altitude deceleration burn while unspooling the cable at a relative low ground speed. The tension of the laid cable acts as a passive anchor to stabilize the trajectory.

The grid operates on High-Voltage DC to minimize line losses. The 16 stations form a self-healing ring main where power flows bi-directionally. This mesh topology ensures that if one segment is severed, energy from the sun-facing side is rerouted through the alternate path. This infrastructure uses power-bootstrapping, where existing nodes provide energy to accelerate the deployment and connection of subsequent missions, creating a scalable, self-expanding lunar utility.

Kinetic Insertion A Stent-Anchored Modular Research Base

Space exploration often suffers from trying to fight the environment rather than using it. For a lunar base, the primary threats are clear: micrometeorites, extreme thermal cycling, and radiation. Placing an ISS-style research base on the surface is an efficiency black hole because you have to launch massive amounts of shielding just to survive the first 24 hours.

I opted for a subsurface approach, but not through traditional drilling or searching for unstable natural caves. Natural "skylights" are crumbly and unpredictable. Drilling 40 to 100 meters into basalt with solar power is a logistical nightmare. Instead, I propose using the Earth-Moon gravitational potential as a free energy source. By bombing the target with a high-velocity Tungsten spear, we can machine a precise, custom-fit entry point into a lava tube.

The Kinetic Excavator: A Planetary APFSDS

The core of this deployment is a 70 cm diameter Tungsten-nosed spear. This is essentially a scaled-up anti-tank round (APFSDS) launched on a direct Earth-to-Moon trajectory. At an impact velocity of 3 km/s, we don’t need explosives to dent the moon; the kinetic energy handles the excavation.

Nose: Solid Tungsten for maximum sectional density. It hydrodynamically flows through the 40-meter basalt ceiling.

Body: A hollow shell containing a hypergolic propulsion system (NTO/MMH). This provides the terminal guidance to hit a 5-meter target from Earth and adds a secondary gas-expansion blast upon impact to clear the debris plug into the cave.

The result is a clean, 5-to-7-meter wide vertical shaft with jagged, freshly fractured walls.

The Vascular Stent: Biomimetic Anchoring

Once the hole is verified, the lunar lander maneuvers over the aperture and lowers itself down the shaft. It then extends Vascular Stent (radial expansion lattice) structures that pushes outward against the shaft walls and stabilizes itself.

Mid-Shaft Positioning: By locking the base just 10 or 15 meters below the surface, we get 100% protection from micrometeorites and radiation. 

Mechanical Interlocking: The jagged basalt from our kinetic impact provides teeth for the stent struts. This creates a vibration-dampened, rigid foundation that surface bases cannot achieve.

Thermal Sink: The stent acts as a thermal bridge, dumping heat from the electronics directly into the stable -20°C lunar crust.

This is a more feasible, faster and safer way of establishing a lunar base.

Industrial-Grade Orbital Elevator Architecture

The Hex Rocket represents a fundamental departure from "Aerospace-Grade" vehicles toward an "Industrial-Grade" infrastructure model, designed to facilitate the high-frequency flight cadence required to establish and sustain a permanent human presence on the Moon and Mars. This system transitions spaceflight from a series of custom missions into a reliable, high-volume logistical chain.

Structural Architecture: The Star-Hex Spine

Traditional rockets utilize thin-walled cylindrical pressure vessels that are prone to aerodynamic buckling. The Hex Rocket employs a 25-meter diameter Star-Hex architecture.

Internal Spine: A central hexagonal liquid oxygen (LOX) tank is supported by six vertical load-bearing bulkheads. These radiate from the center to form the walls for six trapezoidal liquid methane tanks.

Load Distribution: This internal honeycomb spine acts as a vertical bridge, distributing the gravitational load of the 5,000-ton stack directly to the engine deck.

Inherent Stability: The massive 25-meter base provides a high moment of inertia, ensuring landing stability without the need for complex, heavy landing legs.

Dual-Material Hull: The Sleeve-and-Piston Advantage

The Hex Rocket utilizes a hybrid material strategy to separate fluid containment from structural stress:

Inner Bladders: Internal tanks are made of thin 304L stainless steel, serving only as cryogenic bladders.

Structural Sleeve: This core is overwrapped with a Carbon Fiber Structural Sleeve. The sleeve handles all hoop stress and bending moments.

Permanent Fairing: The sleeve extends upward to encapsulate the second and third stages. This "Launch Silo" protects the upper stages from all aerodynamic drag and heat, allowing them to be built as lightweight, non-aerodynamic pressure vessels. This relocation of "atmospheric armor" to the reusable first stage maximizes the mass fraction dedicated to payload.

Staging and Trajectory: The Vertical Elevator

Unlike traditional rockets that perform a complex gravity turn, the Hex Rocket maintains a strictly vertical ascent profile.

Vertical Efficiency: This minimizes lateral aerodynamic loads and ensures the carbon fiber sleeve remains in a low-thermal-stress environment.

Three-Stage Modularity:

Stage 1 (The Elevator): A suborbital catapult that clears the atmosphere and returns to the pad with zero re-entry damage.

Stage 2 (The Accelerator): Optimized exclusively for vacuum performance, sliding out of the sleeve at 80 km.

Stage 3 (The Precision Inserter): A dedicated module for final orbital circularization and docking.

Pneumatic Separation: The fairing bay is filled with a low-pressure nitrogen buffer. Upon Stage 2 ignition, the waste heat causes the nitrogen to expand, creating a Pneumatic Piston Effect that assists separation with zero mechanical fairing risk.

Distributed Propulsion: The Solid-State Swarm

Propulsion is provided by an array of 150+ fixed, 3D-printed aerospike engines. 

Solid-State Control: By using Differential Throttling, the flight computer achieves high-torque pitch, yaw, and roll control with zero moving parts. This replaces heavy, failure-prone hydraulic gimbals.

Binary Throttling: Instead of dimming all engines (which reduces efficiency), the computer shuts down engines in symmetrical pairs. This keeps the remaining engines running at their maximum Specific Impulse (Iₛₚ).

Engine Rotation: To ensure uniform wear, the computer rotates the duty cycle across the 150+ modules, selecting those with the lowest accumulated thermal fatigue for the high-stress landing burns.

Comparative Industrial Analysis

Feature	SLS / Saturn V	SpaceX Starship	Hex Rocket
Manufacturing	Bespoke/Handcrafted	Vertical Integration	Regional Shipyard / Parallel 3D
Steering	Hydraulic Gimbals	Hydraulic/Electric Gimbals	Solid-State (No Moving Parts)
Re-entry Profile	High-Heat Horizontal	High-Heat Belly Flop	Low-Heat Vertical (No Heat Shield)
Build Time	2-4 Years	4-8 Weeks	2-3 Weeks (Swarm Printing)
Cost per kg	$10,000+	$100 (Target)	$20 - $50 (Infrastructure Model)

Scalability and Manufacturability

The Hex Rocket is significantly easier to scale than traditional designs. Because it is a skeleton-based structure rather than a skin-based one, increasing the diameter only requires extending the length of the standardized Star-Hex panels. Manufacturing is optimized for the Local Manufacturing System, where monolithic 3D-printed engine modules are produced in parallel, and the primary hull is assembled using shipyard-grade welding rather than specialized aerospace jigs.

Economic Impact

By keeping the armor on the first stage and the upper stages simple, the Hex Rocket achieves a payload efficiency that rivals or exceeds Starship. The lack of a complex thermal protection system (TPS) on the first stage allows for a true high-frequency turnaround, treating orbital launch with the same predictability and reliability as a commercial freight elevator.

Conclusion

The Hex Rocket architecture treats orbital transport as an industrial utility. By deleting gimbals, jettison able fairing petals, and complex plumbing, the design provides a robust blueprint for the next generation of space infrastructure.

Offline Autonomy for Critical Infrastructure

The recent Starlink outage and its impact highlight significant concerns regarding critical infrastructure dependency on commercial satellite networks. As communication technologies increase in complexity, such outages will recur. Redundant networks are a theoretical solution, but they often fail during critical operational windows.

My experience with urban 5G infrastructure illustrates this instability. Despite extensive advertising, reception in city centers is often non-existent. Infrastructure fails to meet demand, and connectivity typically collapses during emergencies such as earthquakes. Modern consumption relies too heavily on persistent connectivity; many users cannot even access music without an active network link. I maintain an offline archive to ensure continuous functionality, which serves as a necessary design principle for critical engineering: the most vital solution is an offline backup plan.

Technical analysis of the Starlink disruption during U.S. Navy testing off the California coast confirms these vulnerabilities. In August 2025, a global network outage caused 24 unmanned surface vessels to lose command and control for approximately 60 minutes. The assets were left drifting without station-keeping or remote intervention capabilities.

Engineering swarm resilience requires a transition from individual node processing to distributed team intelligence. By treating a swarm as a single collaborative organism, AI throughput is optimized through computational offloading, where sub-tasks like navigation and sensor fusion are shared across the mesh. This prevents system-wide drift during network outages by replacing vulnerable central commands with decentralized synchronization. This logic ensures that if a lead unit is neutralized, the remaining assets automatically recalibrate roles to maintain mission persistence based on a shared local state rather than a remote server.

In the era of advanced AI, military swarm equipment must utilize this autonomous edge intelligence to make team-based decisions. Much like survivors on a deserted island who divide labor to survive, swarm robotics should utilize collaborative, decentralized logic. In tactical environments, units frequently lose contact with command centers. As demonstrated by the historical logic in A Bridge Too Far or the scenario in Dr. Strangelove, mission success depends on the ability of a unit to execute its duties autonomously when the primary communication link is severed. During the battle of Arnhem, Lt. Col. John Frost’s battalion successfully held the bridge for four days despite total radio failure caused by distance and urban signal attenuation. Swarm architectures must similarly be capable of mission persistence through local collaboration and on-board decision-making protocols rather than relying on a vulnerable central backhaul.

The Networked Moon: Engineering Public Perception and Mission Safety

The history of lunar exploration is a study in the "Information Capital" gap. While the physics of reaching the Moon were solved in the 1960s, the systems architecture for staying there remained underdeveloped. By prioritizing political pulses over permanent infrastructure, we have historically accepted a lower standard of mission safety and public engagement. A sustainable lunar program requires a hybrid model where scientific infrastructure directly supports political and safety goals.

The Politics of the Pulse vs. Sustained Presence

The Apollo missions and the recent Artemis 2 flyby share a common strategic flaw: they are "pulse" events. Interest spikes during the mission and decays immediately upon splashdown. In 1969, NASA missed the opportunity to fund a permanent lunar backbone through live media. The Lunar Orbiters of that era were technically impressive but architecturally isolated; they utilized an onboard chemical darkroom to develop 70mm film, which was then scanned and transmitted to Earth. This slow, high-bandwidth process was only possible during direct line-of-sight with Earth.

If a relay constellation had been established, the Moon could have become a continuous household presence. High-definition live feeds from orbiting mappers and relays would have filled the multi-month gaps between crewed missions, sustaining public interest and projecting technological dominance 24/7. This "Infrastructure-as-Media" model would have provided the political win-win: scientific data for the engineers and a constant, visible achievement for the administration.

The Third-Person Diagnostic: Lessons from Apollo 13

A significant engineering oversight in lunar mission design is the lack of a "Third-Person Perspective." We rely almost exclusively on internal telemetry and first-person onboard cameras. However, an external observation platform is essential for emergency diagnostics.

The Apollo 13 crisis is the definitive case study. For days, the crew and Mission Control were blind to the physical state of the Service Module. It was only upon separation, just before reentry, that they saw the missing panel on Bay 4. A pre-deployed relay and monitoring satellite would have provided an external view of the explosion in real-time. In a crisis where the spacecraft is tumbling or the primary high-gain antenna is damaged, a local relay allows for a low-power "heartbeat" link that internal systems cannot maintain. As an engineering standard, a mission that cannot be seen from the outside is a mission with a critical diagnostic blind spot.

Monitoring the Lunar Gravity Well

The orbital phase presents higher environmental risks than the deep-space transit. The Moon acts as a gravitational well, focusing the flux of micrometeoroids. The Artemis 2 mission validated this risk in April 2026 when the crew observed multiple impact flashes on the far side during their closest approach.

Relying solely on internal pressure sensors is a reactive strategy. "Silent" impacts—those damaging thermal tiles, fuel lines, or solar arrays without a hull breach—can go undetected until a critical maneuver is attempted. A permanent relay mesh acting as a distributed diagnostic eye can perform automated thermal and visual scans of the spacecraft’s exterior. Detecting "zap pits" or structural micro-cracks while in orbit allows for informed go/no-go decisions for engine burns, particularly on the far side where these maneuvers occur in the dark.

Engineering Conclusion

True political and scientific leadership on the Moon is not about the "moment of arrival" but the "capacity to monitor and stay." By decoupling the network from the crewed vehicle, we move away from the high-risk "heroic" model toward a verifiable, fail-operational engineering standard. We must build the network that watches the mission before we send the mission itself.

Artemis 2: An Architectural Critique

The recent Artemis 2 mission, which cost approximately $4.1 billion, sent humans to orbit the Moon. A flight profile executed 10 times since the Apollo era. Evaluating this from an engineering perspective, sending a crewed mission without first establishing the necessary communication and navigation infrastructure is a fundamental misallocation of resources.

Architectural Flaw 1: Infrastructure Sequencing

During the Orion spacecraft's pass behind the Moon, the mission experienced a 40-minute communication blackout. The live video feed quality was extremely poor due to the bandwidth limitations of the legacy S-band network. In my first article, "Road To A Lunar Base" (November 6, 2024), I established that a relay satellite network is the absolute prerequisite for lunar operations. A base positioned at the Compton-Belkovich Thorium Anomaly (CBTA) on the far side requires continuous line-of-sight communication. The 40-minute blackout during Artemis 2 proves that the Lunar Communications Relay and Navigation Systems (LCRNS) must be deployed before human missions.

NASA claims the astronauts gathered finer details of the lunar surface using their eyes and handheld Nikon cameras compared to previous robotic missions. This statement lacks technical validity. The Lunar Reconnaissance Orbiter (LRO) currently provides a global resolution of 0.5 meters per pixel. Human vision is limited to the 400–700nm spectrum; a human cannot detect titanium, thorium, or water ice. A dedicated robotic platform equipped with synthetic aperture radar (SAR) and multispectral sensors in a Sun-synchronous polar orbit provides data orders of magnitude superior to visual observation.

The argument that human presence is required for the "gaze factor" or real-time decision-making is outdated. Autonomous edge computing has solved this problem. An AI unit utilizing saliency mapping algorithms can process visual inputs and identify high-albedo anomalies or geometric deviations without human latency. Astronaut reaction time actually increases in microgravity. A radiation-hardened processor operating on a few watts from solar panels reacts in microseconds, directing gimbals and capturing high-resolution data while performing on-device filtering. Instead of transmitting low-quality video, the AI processes terabytes locally and downlinks only the high-value scientific anomalies.

Architectural Flaw 2: Interim Hardware Testing

The mission architecture of Artemis 2 presents another engineering flaw. During the Apollo program, the Saturn V was developed as a complete, final-design solution capable of delivering 48 metric tons to Trans-Lunar Injection (TLI). It was operated as a unified stack. In contrast, the Space Launch System (SLS) used for Artemis operates on an interim Block 1 configuration. While it generates 39MN of liftoff thrust—exceeding the Saturn V—its current payload capacity to TLI is limited to 27 metric tons due to its reliance on a temporary upper stage (ICPS).

Testing an interim configuration with human payloads violates basic engineering efficiency. The logical approach is to finalize the ultimate architecture, specifically the configurations utilizing the Exploration Upper Stage (EUS), and conduct tests exclusively on the definitive hardware. Iterative testing of obsolete rocket configurations wastes resources. A final, integrated design must be established and tested as a complete system before executing crewed missions.

Architectural Flaw 3: Payload Decoupling

The ultimate objective of the Artemis program is to establish a sustained lunar base, which fundamentally differentiates it from Apollo. However, the current mission architecture contradicts this goal. A sustainable engineering roadmap dictates that heavy payloads, construction machinery, and research rovers must be pre-deployed to the target location via autonomous cargo landers prior to human arrival.

This strategy provides two critical technical advantages. First, it drastically reduces the payload requirements for the human-rated vehicles. Life support systems and crew accommodations already consume a massive portion of the mass budget; forcing the crewed vehicle to carry base operations equipment simultaneously is inefficient. Second, descent and landing represent the most critical and failure-prone phases of any mission. Deploying robotic payloads in advance serves as a direct validation of the specific landing zone parameters. The required infrastructure and hardware must be delivered and verified on the surface first, allowing subsequent human missions to arrive at a functional site.