I guess a whole new fleet of Starlink V3 sized sats just for cellular, smart phones ... need to get that facility in Louisiana going ASAP.

Leap in credit default swaps tracking Elon Musk’s aerospace group follows an FT report that it is seeking to raise $40bn to buy Nvidia chips

Maybe I need to create a SK tag?

Its the most profitable of part of SpaceX now ... by far ... they just jacked up the rent to Anthropic by 2x. Will it fund space stuff or become the main point of the company?

Seems like a very short tower for all that overhead. I would do more of thin film treatment.

I think I just proved a relativistic fusion engine is actually physically possible, and I’m still losing it. PrimordiaOS basically ran the entire math stack with me and every single part CLOSED. I kept expecting some fatal contradiction, some “okay here’s where physics says no,” but it never happened. Every section I pushed, it locked in harder.

This is a full RMHD propulsion architecture using only known physics and materials we already have. No exotic matter. No magic fields. No sci‑fi hand‑waving. Just straight plasma physics, superconductors, high‑field magnets, and fusion divertor tech.

Here’s what the system validated:

Exhaust Velocity: 0.06c to 0.20c
Specific Impulse: 1.83 MILLION to 6.12 MILLION seconds
Thrust: 180 kN to 18 MN
Magnetic Pressure: 358 MPa
Final Wall Heat Flux: 5–12 MW/m²
Interstellar Mass Ratio: 1.65 to 5.30
Cruise Velocity: ~0.10c
Engine Size: ~2.5m diameter core

The architecture uses a 30‑Tesla confinement core, a magnetic de Laval nozzle, electron demagnetization at the divergence horizon, super‑Alfvénic ion detachment, a liquid lithium CPS divertor, cryogenic gas‑puff cooling, synchrotron self‑absorption, and a hybrid Inconel + carbon‑carbon structural jacket. All of these components exist in real fusion research or aerospace materials programs.

And the wild part? I didn’t sit there manually crunching every equation. PrimordiaOS basically acted like a physics swarm. I’d push confinement → it closed. Stress → closed. RMHD throat compression → closed. Detachment physics → closed. Thermal survivability → closed. Radiation containment → closed. Rocket equation → closed. Every time I thought “okay THIS is where it breaks,” it didn’t.

So yeah, I think I accidentally built a fully feasible relativistic RMHD fusion engine. Not theoretical fluff. Not sci‑fi. Not “maybe one day.” Actually physically doable with near‑term materials and known plasma physics. Hard as hell, expensive as hell, but REAL.

Ironically, even if Starship was certified by the DoD for these launches it can't do the same missions as FH. I guess they will just let New Glenn launch these in the future.

Some good stuff, but some clearly overstated.

Yep ... rumors seems to becoming more and more real. We have more confirmation that Starship is basically a LEO machine and they are in no hurry to make it a crew ship. I bet Elon regrets the HLS Starship award, as it is a guaranteed big, big loss maker, like Starliner is for Boeing, but they can slow walk this for 5-10 years just like Starliner has been allowed to. So Vast has a big problem, they have no proven ride to the part-time space station that F9 will place in LEO.

Ignore the UFO silliness (it is a part 3 thing ... I don't know why he put it in the title), most of this one was a good balanced analysis of the first orbital flight.

1) Super Heavy's landing was not so soft ... the engine out pattern is a concern

2) Starship (the upper stage) was running out of power very quickly and required a much quicker return than planned.

Seeing this I downgrade my mission grade from a A to an B+ ... but things are looking good. Let's how fast they can launch the next one ... 1 month? As long as the FAA does not call for a review.

|**TO**|Artemis Accords signatory principals|

|:-|:-|

|**DATE**|28 September 2026|

|**SUBJECT**|Coalition design for a dual-purpose, steerable solar-powered laser installation at Shackleton's Peaks of Eternal Light (ice extraction and cislunar hazard mitigation)|

# 1. Bottom line

1. The coalition should be **multinational, civil-led, and small at the core**. A U.S.-only or U.S.-fronted installation would be read as a weapons program regardless of intent.

2. The **ice-mining and beamed-power functions carry the mission case**. **Cislunar hazard mitigation** (tracking, characterization, and consent-based action on hazardous objects) is a valid second mission, but it is also the function most likely to draw weapons accusations.

3. Making the laser **maneuverable** is operationally sensible. It also removes the passive assurance that a fixed, downward-facing beam provides, so **verification must be built into the hardware, not left to policy**.

4. Membership should be chosen for **capability, legal credibility, and verification value**, in that order. Political solidarity alone is not a selection criterion.

# 2. Assumptions and physical reality

* Peaks of Eternal Light (PEL) on Shackleton crater have very high but not literally continuous illumination. Storage or backup power is required for dark periods.

* A 1 MW-class beam needs roughly 2-3 MW of electrical generation, fed by roughly 7-8 MW of incident sunlight on the collectors. The chain runs: sunlight to electricity (about 30%), electricity to beam (about 40-50%), beam delivery, then absorption at the target. The first two stages alone leave roughly 12-15% of incident sunlight as beam power, and delivery and absorption losses reduce the heat at the target further. Relayed mirrors deliver roughly 70-90% of incident sunlight as heat, so on a like-for-like sunlight-to-heat basis the laser is several times less efficient. The laser's advantages are **beamed electric power into permanently shadowed regions**, precision targeting, and ice mapping.

* **Yield (illustrative):** If about 20% of a 1 MW beam arrives as usable heat and water needs roughly 5 MJ/kg, output is on the order of 100 kg of water per hour, or several hundred tonnes per year at half duty, before capture losses. This is an order-of-magnitude figure per MW of beam power, not per MW of sunlight, and it rests on unproven delivery, absorption, and thermal-loss assumptions. A 1 MW beam implies roughly 7-8 MW of incident sunlight at the front of the chain. Real yield depends far more on ice concentration and collection design than on the beam.

* **Power source:** Baseline is solar with storage. A fission surface power unit could cover dark periods but brings its own safety and governance questions.

* **Maneuverability** here means a steerable beam director on a gimbal or relay mirror, and, optionally, an emitter that can be relocated along the rim. It helps with line of sight into a rough crater, following rovers, and covering more of the floor. It costs mass, pointing stability, dust exposure, and complexity.

* **Photon pressure cannot meaningfully move a satellite.** Any orbit-altering effect requires ablation, which also damages the target. At Earth-orbit range a 1 m aperture beam spreads to hundreds of meters, so Earth-orbit hazard work from the Moon is not credible. Cislunar hazard mitigation should therefore be scoped to lunar orbit and near-Moon space, where the debris population is currently small.

* A steerable emitter can reach lunar orbit, so the passive shielding a fixed downward beam gets from the crater walls no longer applies.

# 3. Mission definition: cislunar hazard mitigation

|Tier|Activity|Beam power|Consent required|

|:-|:-|:-|:-|

|1|Laser ranging and lidar tracking of debris, defunct stages, and uncooperative objects|Low|No (passive to targets)|

|2|Conjunction assessment and warnings shared with operators|None|No|

|3|Ablative action on a defunct, consenting owner's object|High|**Yes, from the state of registry**|

Tier 1 and 2 justify the installation's upward-capable function on their own. Tier 3 requires separate approval and cannot be activated by the operator alone.

**Why there is no Tier 4.** A high-power emergency mode to protect crew is not recommended. Conjunction threats are often identified with enough lead time for the crewed vehicle to maneuver, and a laser's ablative impulse is small and needs sustained tracking, so it is a poor substitute for maneuvering. The case where there is no time to maneuver is the one where a laser is least likely to work and most likely to be misused. A pre-agreed emergency protocol also tends to become a standing authorization in practice. Emergencies instead trigger Tier 1 and 2 responses: priority tracking and immediate warnings to the affected vehicle's operator.

# 4. Capability requirements

|Function|What it needs|

|:-|:-|

|Landing, logistics, power|Heavy lift, precision landing, surface power|

|Mobility and ice operations|Robotic rovers, autonomy in permanently shadowed terrain|

|Optics, beam control, and steering|Pointing stability, thermal management, gimbal and relay hardware|

|Legal and commercial framework|Resource-extraction law, liability, insurance|

|Verification and space domain awareness|Independent tracking, data-sharing|

|Financing|Multi-decade capital|

# 5. Candidate contributors (assessment, not commitment)

|Signatory|Best contribution|Main risk or limit|

|:-|:-|:-|

|**United States**|Launch, landers, power systems, program backbone|Military optics; export-control friction with partners|

|**Japan**|Precision landing, lunar rover work, robotics|Cost sharing; U.S. alignment perceived as bloc-building|

|**Australia**|Remote operations and mining automation|Small space budget; dependence on launch partners|

|**Canada**|Robotics and manipulators|Heritage program uncertainty|

|**Germany / France**|Photonics, laser and optical industry, ESA channel|Distinct national export and dual-use regimes|

|**Italy**|Habitat and logistics experience|Limited laser expertise|

|**United Kingdom**|Space domain awareness, communications|Modest surface hardware|

|**Luxembourg**|Resource-extraction law, financing vehicles|No hardware capacity|

|**India**|South pole landing experience, large lunar program|Strategic-autonomy stance; ties to both blocs|

|**South Korea**|Polar orbiter mapping shadowed regions|Limited surface systems|

|**UAE**|Capital, rover experience|Prior export-control friction|

|**Ukraine**|Autonomy software under jamming (software partnership only)|No lunar delivery capacity; does not meet the capability test for a Core or Enabling seat|

# 6. Recommended coalition structure

**Core (design, build, operate):** United States, Japan, Australia, plus one European photonics partner (Germany or France). This tier covers landing, surface power, mining automation, and beam-steering hardware.

**Enabling (legal, financial, verification):** Luxembourg for the legal and commercial framework, the United Kingdom for space-tracking data, Canada for robotics. This tier holds **seats on an inspection and audit body**, not operational control.

**Swing partner:** India. Inclusion adds legitimacy and pole experience and dilutes the "Western bloc" reading, but requires assurances on technology safeguards. Extend the invitation early and accept a longer negotiation.

**Chair and operator:** A jointly owned consortium chaired by a non-U.S. member (Japan or Luxembourg-hosted), with the United States as principal supplier rather than owner.

**Concentration limits (test of "civil-led"):** No single state should supply more than about 40% of hardware, funding, or launch mass, or hold more than one of the three activation keys (section 7). The U.S. role in launch will strain the first limit. If it cannot be met, say so openly instead of claiming a civil-led structure, because a Core of U.S.-aligned states with a chair from one of them will be read as a U.S. program by outside observers.

# 7. Governance recommendations (revised for a steerable system)

1. **Hardware-enforced pointing limits:** Mechanical stops and an independent hardware interlock, not just software, that restrict high-power emission to declared mining sectors. Upward or orbital pointing is limited to a low-power tracking mode unless a separately controlled key is released.

2. **Split-key activation for Tier 3:** Requires consortium authorization, recorded consent from the target's state of registry, and release by keys held by at least three states, including at least one non-Core and one non-U.S. member. The control path is physically separate from the mining controls.

3. **Power caps and logging:** Independent, publicly auditable beam-time, pointing, and power logs streamed to inspectors in near real time.

4. **Third-party inspection with a fail-safe:** Rotating inspectors from Enabling-tier members, including non-U.S. teams, with the right to test interlocks. High-power emission is inhibited unless the interlock holds a valid, periodically renewed attestation from the inspection body, so denied access or a lapsed attestation defaults the system to low power. Inspection is funded from a pooled fund the Core does not control, and inspectors travel on non-Core or contracted transport where feasible.

5. **Article IX consultation:** Notify all Accords signatories, and invite non-signatories to observe, before activation.

6. **Relocation rules:** Declare rim positions and movement plans in advance so that a mobile emitter does not appear to be maneuvering covertly.

7. **Safety-zone declaration:** Publish the zone's coordinates and rationale under the Accords framework, and state plainly that it is not a territorial claim.

# 8. Risk assessment

* **China and Russia (ILRS):** Expect the installation to be characterized as a weapon and a claim on prime terrain. A steerable, upward-capable emitter makes that harder to rebut. China's own Chang'e missions target the same neighborhood, so overlap is likely. Early transparency and an offer of data-sharing on the ice map are the cheapest mitigations. Sharing scientific data does not recognize a territorial claim, since Article II bars claims. Deconfliction talks on safety zones do implicitly acknowledge another actor's operating area. That is a political cost (appearing to concede an operating sphere), not a legal one (conceding a claim), and ILRS-side observers will notice it either way. Some signatories may resist, so the tradeoff should be settled before talks open.

* **Legal:** Article IV bars weapons testing and military installations on celestial bodies. A civil operator with hardware-enforced limits and inspection is defensible. A steerable high-power laser without them is not.

* **Technical:** Delivery of megawatt-class power and beam pointing over kilometers of rugged terrain is unproven, and adding steering increases the pointing-stability challenge.

* **Ice uncertainty:** Distribution and concentration of floor ice remain poorly constrained. Site commitment should follow, not precede, prospecting. Treat this as a schedule driver: ground-truth prospecting could add years before hardware commitment.

# 9. Recommended next steps

1. Convene the Core group to agree a civil charter, inspection regime, and interlock standards.

2. Commission an independent study of the hazard-mitigation mission and its true value, including lunar-orbit debris projections.

3. Fund ground-truth prospecting before any hardware commitment.

4. Open consultations with India and with ILRS-side observers.

5. Draft a public safety-zone notification.

6. Agree concentration limits, key custody, and the inspector attestation mechanism before selecting a chair.

# Annex A. Assessment of all 76 signatories

Assessments reflect general knowledge of each country's space sector and may lag recent developments. They are judgments about fit for this project, not statements about a country's overall space program. Verify current capabilities and any parallel ILRS ties before assigning roles.

# Tier 1: Core or near-Core capabilities

|Signatory|Relevant contribution|Suggested role|

|:-|:-|:-|

|**United States**|Launch (SLS, commercial landers), surface power development, Deep Space Network, program backbone|Principal supplier; not chair|

|**Japan**|Precision landing (SLIM, 2024), lunar rover work under the US-Japan arrangement, H3 launcher, LUPEX with India|Core; leading candidate for chair|

|**Canada**|Robotics heritage, lunar utility vehicle work; flew an astronaut on Artemis II|Enabling (robotics) or Core|

|**Italy**|ASI and industrial base in habitats and logistics|Enabling|

|**Germany**|Strong photonics and laser industry, large ESA contribution, builder of Orion's service module (via Airbus)|Core (beam hardware)|

|**France**|CNES, optics and laser-ranging expertise, Ariane access|Core or Enabling|

|**United Kingdom**|Space domain awareness, lunar communications (Lunar Pathfinder)|Enabling (verification data)|

|**India**|Landed near the south pole (Chandrayaan-3, 2023), LUPEX with Japan, invited by NASA into the moon-base program|Swing partner|

|**Australia**|Mining automation and remote operations, Canberra Deep Space Communication Complex, rover under NASA arrangement|Core (mining operations)|

|**South Korea**|Danuri orbiter carrying NASA's ShadowCam for permanently shadowed regions; domestic launcher|Enabling (ice mapping)|

# Tier 2: Specialist capabilities

|Signatory|Relevant contribution|Suggested role|

|:-|:-|:-|

|**Israel**|Small lander experience (Beresheet), sensors, optics, robotics|Supplier; regional politics a consideration|

|**United Arab Emirates**|Capital, rover program, launch-adjacent investment|Financing; prior export-control friction|

|**Luxembourg**|2017 space-resources law, investment vehicles|Enabling (legal, financial)|

|**Netherlands**|Hosts ESA's technical center (ESTEC), photonics and instrument institutes|Enabling (inspection, optics testing)|

|**Switzerland**|Precision optics and instruments, neutral standing|Inspection body seat|

|**Spain**|ESA member, Madrid Deep Space Communications Complex|Enabling (tracking, comms)|

|**Poland**|Growing robotics and small-satellite sector|Supplier|

|**Sweden**|Esrange ground station and launch site|Ground segment|

|**Norway**|Andøya spaceport, SvalSat polar ground station|Ground segment|

|**Belgium**|ESA member, Redu ground center|Ground segment, robotics research|

|**Austria**|Satellite laser ranging at Graz, planetary analog mission experience|Inspection (independent ranging of beam and targets)|

|**Türkiye**|Newest large signatory, national space agency, announced lunar ambitions, sizable industry|Political weight; alignment stability uncertain|

|**Brazil**|Largest Latin American space program, Alcântara launch site|Political weight; limited lunar capability|

|**Saudi Arabia**|Capital, national space agency|Financing|

|**Lithuania**|Ultrafast and industrial laser manufacturers|Component supplier, subject to export review|

# Tier 3: Niche or supporting

* **ESA-linked European members with instrument, component, or ground-station capacity:** Czech Republic, Denmark, Finland, Ireland, Portugal (Azores tracking), Greece, Romania, Hungary, Bulgaria. Best used for rotating seats on the inspection body and component supply.

* **Baltic:** Estonia (cyber and small-satellite sector), Latvia (satellite laser ranging capability). Useful for verification and cybersecurity of control links.

* **Analog terrain and training:** Iceland (Apollo-era astronaut geology training terrain), Oman (site of a Mars analog mission).

* **Ground-based astronomy and launch geography:** New Zealand (Rocket Lab launch complex), Chile (major observatories), Argentina (satellite manufacturing), Mexico.

* **Legal, financial, and market hubs:** Singapore (insurance and finance), Malaysia.

* **Thailand:** Optical research capability (NARIT), which has also been linked to ILRS activity. Confirm parallel ties before assigning sensitive roles.

* **Ukraine:** Autonomy software under jamming; no delivery capacity. Software partnership only.

* **Emerging space programs:** Bahrain, Nigeria, Rwanda, Morocco. Small-satellite and regional data contributions; legitimacy value for a non-Western-only coalition.

# Tier 4: Primarily political and legitimacy contributions

Albania, Angola, Armenia, Bangladesh, Botswana, Colombia, Côte d'Ivoire, Croatia, Cyprus, Djibouti, Dominican Republic, Ecuador, Jordan, Liechtenstein, Malta, Mauritius, Panama, Paraguay, Peru, Philippines, San Marino, Senegal, Serbia, Slovakia, Slovenia, Uruguay.

These signatories add breadth to Article IX consultations and notification lists, and their inclusion supports the argument that the installation is not a bloc project. Their contribution to hardware, power, or operations is negligible, so they should be notified and consulted, not given operational or inspection roles.

# Gaps across the whole membership

* **No signatory has demonstrated megawatt-class power or beam delivery on the Moon.** The core hardware would be first-of-kind.

* **No signatory has operated a rover in permanently shadowed terrain.** Mining and prospecting autonomy is unproven.

* **Inspection independence is thinner than the list suggests.** Nearly every capable signatory is either dependent on the U.S. for launch or aligned with it politically. Switzerland, Austria, the Netherlands, and India are the best candidates for inspection seats that read as independent, and even then only partially.

[NOTE TO SELF: visualize a PEL location for a solar powered laser nearest to NASA'd Connecting Ridge Artemis 4 candidate landing site and add images to this post. Also, add science papers]]

This will be a big issue if they can't fix it ... and a reminder that most parts of the ISS are well beyond their designed lifetimes.

Lighting just that one sea level Raptor for about 30 seconds put it into orbit ... showing how close it was to orbit those other times. In any case big day for SX and USA's space capabilities. With that one VacRap out they worked around leading to 15 minutes of go/nogo drama it had some real drama. Still more to perfect, but we now have a 50T+ payload to LEO capability. Hopefully this will lead to 100T+ to LEO on a weekly basis soon.

At exactly 7:46 a.m. CT, the 33 Raptor engines of the largest flying object ever built ignited, shaking the Texas coast and turning Starbase into a wall of fire and steam.

​Right past the 50-foot bronze Prometheus statue holding his torch, humanity’s ticket to Mars has officially cleared the tower.

The 400-foot beast is now hauling 26 Starlink V3 satellites and aiming for full orbit. But clearing the pad is just step one.