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Currently waiting on more decision making from KBD512 for many more items to support its construction.
The Trans-Hab was also being built with this same materials. to which we may be able to learn about the floors for internal decks.
Long before we start the building we have built up at the site of the crater a collection of ships, equipment, plus many other things on the todo list in preparation for the day we begin pulling out the "double toroid" inflatable.
The site will need to be leveled and made safe for those that will be there to build.
Of course with the steps forward the metal salvage needs to have happened which will be time consuming with plenty of risks.
The mini smelter will need to up and running to allow for the tubing to be made, cut to lengths for location, bent to its shape and then made to fit within each end to end by flaring each end so that they can be placed through loops on the fabric.
Other things that should have been running since the near beginning is an automated mar regolith bagging and sealing so that all we need to do once the structure is up is to start the radiation protection that is needed from the bags.
Erecting crew will need to have protection all during the process of building, There is mostly not going to be the 1,000 to take part in these actions. Or any time from the first landing as its going to take time to get started.
I did want this to get broke out to its own topic a bit ago when a complaint of keeping topic simple to only being the end goal. Back when we were looking at stainless reuse, Basalt casting and for using mars Iron to make from the surface if present at the site of the crater It should contain all of the equipment to make the structure happen.
After the Korolev crater was chosen There should be create a Wiki on this location and assets that could be made use of.
Well that fits into a single starship and is quite the change in direction from solid building construction that most think of but I do remember NASA doing this for the moon quite some time ago but in quite, smaller vision than to a colony or settlement..
So we have two doughnuts with a separation from the inner radius of each that brings a large common area in the center.
I see that the circular portion of the shape is mainly 20 meter diameter. So what are we doing for the internal floors with in the shape as it gives basically 8 levels at 2.5 m height each?
The center 4 floors would get to use most of the floor space due to circular shape. While the 2 upper and lower ones would get to use less of the volume.
of course we need to add into this shape multiple entry airlocks. Having separate in and out I think makes it easier on the crew
This is the size of the iss cygnus to attach like the BEAM did
I also noticed that we are not making use of the crop, greenhouse area as a volume which means the number was for horizontal growth.
The average height for common food crops grown above the soil ranges significantly based on the plant type, with most annual vegetables maturing between 1 and 4 feet (12 to 48 inches) above the ground. For optimal growth, raised bed heights usually need to be 6 to 12 inches for leafy greens and herbs, and 12 to 18 inches for fruiting plants, accommodating both above-ground growth and root development.
Average Mature Heights of Common Crops
Leafy Greens & Herbs (6–15 inches): Lettuce, spinach, kale, parsley, chives.Root Crops & Low Growers (6–18 inches): Radishes, carrots, beets, turnips, strawberries.
Fruiting/Bush Plants (18–36 inches): Peppers, eggplants, broccoli, summer squash, zucchini, bush beans.
Tall/Vining Plants (4–10+ feet): Pole beans, tomatoes, corn, cucumbers (trellised), pole beans.
Above-Soil Growth Characteristics
Annual Vegetables: Most common garden vegetables (cabbage, broccoli, kale) have their edible portion 1–3 feet above the soil.Vining Crops: Crops like cucumbers, melons, and vining squash can be trained to grow vertically, with some vining plants reaching heights of 6–10 feet or more when trellised.
Small Fruits: Strawberries, blueberries, and raspberries grow relatively low, typically staying under 2–3 feet.
Optimal Raised Bed Height (Soil Surface Height)
Minimum Depth: 8–10 inches of soil is generally sufficient for most vegetables, especially if they can access ground soil below.
Ideal Depth: 16–18 inches allows for the best productivity for a wide variety of vegetables, from lettuce to large squash.
Deep-Rooted Perennials: Asparagus or berries may require 20–24 inches of soil for maximum productivity
The average height of food grown in hydroponic systems varies significantly based on the crop type, but for common, leafy, and herb-based vertical systems, plants generally mature at a height of 40–45 cm (approx. 16–18 inches).
Average Heights by Crop Type
Basil: Typically measures 30–44 cm at the end of the growth cycle.Bok Choy: Reaches an average height of around 12 cm by the end of its cycle.
Lettuce & Leafy Greens: Generally have compact canopy growth, often in the 10–20 cm range.
Vining/Large Crops (Tomatoes, Cucumbers): These require vertical support and are far taller, often reaching several feet/meters, but are kept compact through training and pruning.
Vertical System Heights
Tower Systems: Individual towers (like those from Tower Farms) can reach over 9 feet high, though they contain multiple, shorter-height plants.Small-Scale/Home Units: Often designed to fit on counters or shelves, with vertical clearance requirements ranging from 28 cm to several feet.
Key Factors Influencing Height
Nutrient Solutions: Lower nutrient levels (within reasonable limits) sometimes result in larger plant heights.Flow Rates: Studies show higher plant heights often occur at specific water flow rates, such as 20 L/h.
System Type: Nutrient Film Technique (NFT) often produces higher plant growth compared to Ebb & Flow or soil, with one study showing 40 cm for NFT vs. 30 cm for Ebb & Flow
The Trans-Hab was also being built with this same materials. to which we may be able to learn about the floors for internal decks.
Long before we start the building we have built up at the site of the crater a collection of ships, equipment, plus many other things on the todo list in preparation for the day we begin pulling out the "double toroid" inflatable.
The site will need to be leveled and made safe for those that will be there to build.
Of course with the steps forward the metal salvage needs to have happened which will be time consuming with plenty of risks.
The mini smelter will need to up and running to allow for the tubing to be made, cut to lengths for location, bent to its shape and then made to fit within each end to end so that they can be placed through loops on the fabric.
Other things that should have been running since the near beginning is an automated mar regolith bagging and sealing so that all we need to do once the structure is up is to start the radiation protection that is needed from the bags.
Erecting crew will need to have protection all during the process of building, There is mostly not going to be the 1,000 to take part in these actions. Or any time from the first landing as its going to take time to get started.
What collections of people think people should be property?
What collections of people think people should be property?
Why Artemis is “better” than Apollo.
Why Artemis is “better” than Apollo.
Why Artemis is “better” than Apollo.
Martian Calender - I have created a martian calender...
Martian Calender - I have created a martian calender...
Copper, Silver, and other Metals
SpaceX's Starship megarocket will get off the ground again in mid-March, if all goes according to plan.
The company plans to launch Starship's next test flight in six weeks, Elon Musk said Sunday (Jan. 25) via X, the social media platform he bought in October 2022 (when it was still known as Twitter).
The flight will be the 12th overall for Starship but the first of the bigger, more powerful "Version 3" (V3) iteration of the vehicle.
SpaceX is developing Starship, the biggest and most powerful rocket ever built, to help humanity colonize Mars.
The giant vehicle consists of two elements: a booster called Super Heavy and an upper-stage spacecraft known as Starship, or simply Ship. Both stages are designed to be fully reusable, and both are powered by SpaceX's Raptor engine.
Starship debuted in April 2023 and now has 11 suborbital test flights under its belt, five of which occurred last year. The most recent two, which lifted off on Aug. 26 and Oct. 13, were completely successful, but there was a hiccup in the leadup to Flight 12: The Super Heavy originally slated for the mission buckled during testing in November, forcing SpaceX to get another booster ready.
Flight 12 will mark the debut of Starship V3, which is slightly taller than V2 — 408.1 feet (124.4 meters) vs. 403.9 feet (123.1 m) — but considerably more powerful. V3 can loft more than 100 tons of payload to low Earth orbit, compared to about 35 tons for V2, according to Musk.
The increased brawn comes courtesy of Raptor 3, a new variant of the engine that will fly for the first time on the upcoming test mission.
Flight 12 will be a pretty big deal, because Starship V3 is the first iteration of the megarocket that's capable of flying to Mars. If things go well with this and other upcoming test missions — which must demonstrate key capabilities such as reaching Earth orbit and in-space refueling — SpaceX could potentially launch a small fleet of uncrewed Starship V3 vehicles to the Red Planet late this year, Musk has said.
NASA scrambles as Orion’s heat shield glitch forces a total reentry rethink
NASA’s return to crewed lunar flight is now hinging on a slab of material at the bottom of Orion that did not behave the way engineers expected. Instead of a straightforward fix, the agency is reworking how the capsule will slice back through Earth’s atmosphere, a late-stage pivot that has scrambled planning for Artemis II and beyond. The stakes are blunt: four astronauts, a 50-year gap in human lunar voyages, and a heat shield that has already surprised its designers once.
What began as an engineering anomaly on an uncrewed test has grown into a full campaign to rethink reentry, timelines, and risk tolerance. The result is a program that is still moving toward the Moon, but now with a visibly more cautious and contested path to getting its crew home alive.
The anomaly that turned a test flight into a warning shot
The trouble started when the first integrated Artemis flight, Artemis I, sent The Orion around the Moon and back to Earth as a high energy test of the Space Launch System and Orion and associated systems. As Orion slammed into the atmosphere at 25,000 miles per hour, or 40,200 kilometers per hour, the capsule’s ablative material did not erode in the smooth, predictable way models had forecast. Instead, chunks of the Avcoat coating came off in a pattern that suggested gases failed to vent properly and Pressure behavior inside the material was not fully understood, turning what should have been a textbook demonstration into a red flag for future crews.In the months after the Orion spacecraft splashed down, NASA acknowledged that the base of the capsule had lost more of its protective layer than expected as it returned to Earth from the uncrewed Artemis 1 mission. Internal reviews and an external Audit Identifies Significant Issues with the Orion Heat Shield, documented by the agency’s OIG, flagged concerns such as bolt melting and the possibility that unexpected erosion paths could threaten the vehicle and loss of crew. Those findings pushed the heat shield from a routine certification item into the central technical risk for the entire Artemis campaign.
NASA’s investigation and the decision not to rebuild
NASA responded with a sprawling investigation that, according to agency leaders, involved more than 100 tests across the country to understand why Avcoat had behaved so differently in flight. After that test campaign, Nelson and other officials said the U.S. space agency was moving forward with Ori hardware for the next mission rather than tearing the system apart. The agency’s decision comes after an extensive internal review of the Artemis I heat shield issue showed the Artemis II heat shield configuration could be flown safely if the mission profile was adjusted, a conclusion that has become the backbone of the current strategy.Experts who briefed the public described how NASA, Orion program managers, and materials specialists dissected flight data, ground tests, and modeling to isolate the root cause. In parallel, a separate Jan briefing framed how Artemis and later Mars ambitions depend on getting this right, since the same family of materials and design philosophies will be needed for crewed Mars missions. Another Jan discussion of the real cause of the Orion heat shield behavior, tied directly to Artemis and NASA’s broader exploration roadmap, underscored that the agency believes it understands the physics well enough to proceed, but will change how the spacecraft comes home rather than rebuild the shield from scratch.
A reentry profile rewritten on the fly
Instead of replacing the heat shield on the already assembled Artemis II capsule, NASA is flying the spacecraft as-is and instead modifying the re-entry profile. That choice, described in a Dec update that noted Last week NASA announced the new approach, effectively trades hardware changes for trajectory and attitude tweaks that reduce peak heating and alter how loads are distributed across the Avcoat surface. The issue relates to a special coating applied to the bottom part of the spacecraft, called the heat shield, and the new plan is to manage how that coating is stressed rather than to redesign it this late in the flow.Further complicating the situation was the fact that by the time the anomaly was fully understood it was already too late to fix the heat shield for Artemis II without a major schedule reset, as a Jan analysis of the program noted. NASA’s Artemis II Orion heat shield is now at the center of an ongoing safety debate in the lead-up to Artemis II, with engineers planning a reentry that uses the Moon’s gravitational pull and a carefully shaped corridor through the atmosphere to keep conditions within the bounds of what the investigation says the system can tolerate. In practice, that means a total rethink of how Orion will descend, from entry angle to roll maneuvers, all aimed at ensuring the Avcoat never again surprises the people riding behind it.
Schedules slip, rockets roll, and the Moon stays in sight
The heat shield saga has rippled directly into timelines. In Dec, NASA is hitting a reset on its Artemis Moon schedule, with In April 2026 now targeted for launching a crew of four as part of the Artemis II mission on a 10 day circumlunar flight. A separate Dec update on NASA’s Artemis II mission, which aims to return humans to the Moon after a 50-year hiatus, confirmed that the flight had already been delayed from an earlier September 2025 target, illustrating how thermal protection concerns and other integration work have pushed the calendar to the right.Accordingly, a Dec briefing announced new target launch dates for its Artemis II crewed test flight and Artemis III crewed lunar landing, with Both missions shifted so that the landing now moves from 2026 to mid 2027. A related Dec overview of the SLS hardware highlighted how the Core stage, which holds two propellant tanks for Liquid oxygen and Liquid hydrogen, stacks into a Total height fully stacked of 322 feet, or 98 meters, underscoring the scale of the system that must work in lockstep with Orion’s revised reentry plan. Even as schedules move, the physical rocket is advancing: Jan imagery shows NASA’s Artemis II Space Launch System, or Artemis II Space Launch System, and Orion illuminated at Launch Complex 39B as teams prepare for a fueling test and a simulated countdown known as terminal count, while a separate Jan community piece noted that The Space Launch System, or SLS, was rolled out to Launch Pad 39B with John Saccenti describing how the vehicle is expected to support a launch window that opens next week on Feb. 6.
Astronauts, risk, and a public test of trust
Behind the engineering charts are four people who will strap into this vehicle. Jan social media posts from NASA framed the mission in aspirational terms, with Our Artemis II crew highlighted as heading to the Moon and a reel noting that @astro_reid, @astro_victor, @astro_christina, and the @canadianspaceagency’s @astrojeremy will fly the first crewed Orion. Another Jan update on NASA’s Artemis II mission stressed that NASA’s Artemis II mission, which aims to return humans to the Moon after a 50-year gap, is not just a symbolic milestone but a critical systems test that must prove the heat shield, life support, and navigation can all function together in deep space before any landing attempt.
How Artemis II’s free return path could save astronauts if everything fails
Artemis II is designed to carry humans around the Moon and back on a path that can bring them safely home even if their main engine never lights again. Instead of relying solely on propulsion, the mission leans on a carefully tuned “free return” loop that lets gravity do the work if everything else fails. I see that choice as the quiet centerpiece of NASA’s push to send people farther from Earth than any crew has ever gone in more than 50 years.
That backup path is not a bolt‑on contingency but a core part of how the flight is built, from launch through the swing behind the Moon and the plunge back into Earth’s atmosphere. It shapes the ten‑day timeline, the way Orion tests its systems, and even how far past the lunar far side the astronauts will travel before turning for home.
Why Artemis II needs a built‑in way home
Artemis II is the first crewed outing of the Artemis program, and it will send four astronauts on a roughly ten day loop around the Moon without landing. According to Artemis II mission descriptions, the flight is planned as a lunar spaceflight under the broader Artemis campaign led by NASA. It will be the first time humans travel toward the Moon since the Apollo program ended, and planning documents describe it as the first return of people to the lunar vicinity in over 50 years.That distance raises the stakes. The Artemis II crew will travel approximately 4,600 miles beyond the far side of the Moon, making it the farthest human spaceflight from Earth so far. With the Space Launch System rocket still relatively new, with only one full mission behind it, even supporters acknowledge that, as one analysis put it, Plus the rocket and its components do not yet have a deep flight record. In that context, a trajectory that can carry the crew home without further engine burns is not a luxury, it is a risk‑reduction tool.
How a lunar free return actually works
The free return concept is simple to describe and fiendishly complex to design. Mission planners set Orion on a path where, as it swings behind the Moon, the spacecraft falls into the grip of lunar gravity and then naturally arcs back toward Earth without needing another major burn. One explanation of the physics puts it this way: Here, as Orion approaches our lunar neighbor, the Moon’s immense gravity takes over and bends the track into a loop that guarantees a safe return home if nothing else intervenes.Visualizations of the Artemis II Trajectory show the Nominal path of Artemis II from Earth orbit around the Moon and back. As Orion nears the far side, the trajectory is tuned so that the spacecraft’s momentum and the Moon’s pull combine to “slingshot” it home. Commentators in one spaceflight group describe this as a backup engine in its own right, noting that On February, Artemis II will rely on a route where the spacecraft will automatically slingshot them home if needed.
From launch to lunar swingby: threading the needle
The safety net only works if the early part of the mission hits its marks. On Day 1, mission plans describe Day 1 as Launch and Earth orbit, with the rocket climbing through the atmosphere and, As the ascent continues, shedding its solid boosters and protective hardware. A major change from the uncrewed Artemis I flight is that the second mission will not enter a long lunar orbit but will instead approach and back away on a tighter loop, as outlined in comparisons of the two missions.On Day 2, while still flying around Earth, the crew will run Systems checks and a departure burn while Orion is still close enough for quick troubleshooting. That burn is what actually commits the spacecraft to the translunar trajectory. Flight dynamics specialists have published detailed work on optimized trajectory correction burns for NASA Artemis II mission, showing how small midcourse tweaks keep the path aligned with the free return corridor. Once those are complete, the crew is effectively riding a gravitational rail toward the Moon.
Why Artemis II will not orbit the Moon like Apollo 8
One of the most striking differences between Artemis II and its Apollo predecessors is that it will not brake into lunar orbit. As one mission manager put it when comparing the flights, Apollo 8 actually went into lunar orbit, did 10 revolutions and then came home, while Artemis II is not actually going into lunar orbit at all. That choice is deliberate. By skipping the braking burn that would capture Orion around the Moon, the mission avoids a point of no return where a failed engine firing could leave the crew stranded.Some enthusiasts have debated how closely Artemis II mirrors the Apollo era. One widely shared comment, attributed to JimEd Howland False, notes that Only Apollo 8, 10 and 11 used a free return trajectory before firing their main engine to get into lunar orbit. Artemis II, by contrast, is built so that the free return is not just a starting condition but the entire shape of the flight. That means the crew will still see the far side and travel thousands of miles beyond it, but they will always be on a path that naturally bends back toward Earth.
When everything fails: the “backup engine” of gravity
The real test of the free return design is what happens if something goes badly wrong. Mission briefings emphasize that Artemis II will return to Earth using what is called a lunar free return trajectory, which allows the astronauts to get back even in the event of engine failure. Another technical overview notes that The Artemis II mission will use a similar free return path precisely to provide that safety margin in the event of an engine failure. In other words, if Orion’s main engine refused to fire after the outbound burn, the spacecraft would still loop behind the Moon and head home.Fans of the program have seized on that feature as the most remarkable part of the mission. One viral post framed it this way: On February 6th the Artemis II mission will launch, but the most interesting part is not the rocket, it is the route that acts as a built‑in rescue plan. Another discussion of the same idea stresses that But the route is the backup engine, a technique that was used by the Apollos and that will automatically slingshot them home if the hardware goes quiet.
So far for today
Martian Calender - I have created a martian calender...1-29-26
Why Artemis is “better” than Apollo.
Why Artemis is “better” than Apollo.
Ring Habitat on Mars Doughnut Torus
Daily Recap - Recapitulation of Posts in NewMars by Day
Daily Recap - Recapitulation of Posts in NewMars by Day
Daily Recap - Recapitulation of Posts in NewMars by Day
Trying to do without prefilling of numbers being generated
starting post is carried from the previous days 2026-01-27 last number for the day 237690 - last post 237706
1-28-26 posting
What collections of people think people should be property?
Multi-Ship Expeditions, Starboat & Starship, Other.
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kbd512 Postings
kbd512 Postings
kbd512 Postings
kbd512 Postings
kbd512 Postings
kbd512 Postings
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Trying to do without prefilling of numbers being generated
starting post is carried from the previous days 2026-01-27 last number for the day 237669 - last post 237689
Daily Recap - Recapitulation of Posts in NewMars by Day
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
Ring Habitat on Mars Doughnut Torus
GW Johnson Postings and @Exrocketman1 YouTube videos
Multi-Ship Expeditions, Starboat & Starship, Other.
Bookmark Bookmarks Find it Again help
Martian Calender - I have created a martian calender...
Martian Calender - I have created a martian calender...
Multi-Ship Expeditions, Starboat & Starship, Other.
kbd512 Postings
kbd512 Postings
kbd512 Postings
Well that fits into a single starship and is quite the change in direction from solid building construction that most think of but I do remember NASA doing this for the moon quite some time ago but in quite, smaller vision than to a colony or settlement..
So we have two doughnuts with a separation from the inner radius of each that brings a large common area in the center.
I see that the circular portion of the shape is mainly 20 meter diameter. So what are we doing for the internal floors with in the shape as it gives basically 8 levels at 2.5 m height each?
The center 4 floors would get to use most of the floor space due to circular shape. While the 2 upper and lower ones would get to use less of the volume.
of course we need to add into this shape multiple entry airlocks. Having separate in and out I think makes it easier on the crew
This is the size of the iss cygnus to attach like the BEAM did
I also noticed that we are not making use of the crop, greenhouse area as a volume which means the number was for horizontal growth.
The average height for common food crops grown above the soil ranges significantly based on the plant type, with most annual vegetables maturing between 1 and 4 feet (12 to 48 inches) above the ground. For optimal growth, raised bed heights usually need to be 6 to 12 inches for leafy greens and herbs, and 12 to 18 inches for fruiting plants, accommodating both above-ground growth and root development.
Average Mature Heights of Common Crops
Leafy Greens & Herbs (6–15 inches): Lettuce, spinach, kale, parsley, chives.Root Crops & Low Growers (6–18 inches): Radishes, carrots, beets, turnips, strawberries.
Fruiting/Bush Plants (18–36 inches): Peppers, eggplants, broccoli, summer squash, zucchini, bush beans.
Tall/Vining Plants (4–10+ feet): Pole beans, tomatoes, corn, cucumbers (trellised), pole beans.
Above-Soil Growth Characteristics
Annual Vegetables: Most common garden vegetables (cabbage, broccoli, kale) have their edible portion 1–3 feet above the soil.Vining Crops: Crops like cucumbers, melons, and vining squash can be trained to grow vertically, with some vining plants reaching heights of 6–10 feet or more when trellised.
Small Fruits: Strawberries, blueberries, and raspberries grow relatively low, typically staying under 2–3 feet.
Optimal Raised Bed Height (Soil Surface Height)
Minimum Depth: 8–10 inches of soil is generally sufficient for most vegetables, especially if they can access ground soil below.
Ideal Depth: 16–18 inches allows for the best productivity for a wide variety of vegetables, from lettuce to large squash.
Deep-Rooted Perennials: Asparagus or berries may require 20–24 inches of soil for maximum productivity
The average height of food grown in hydroponic systems varies significantly based on the crop type, but for common, leafy, and herb-based vertical systems, plants generally mature at a height of 40–45 cm (approx. 16–18 inches).
Average Heights by Crop Type
Basil: Typically measures 30–44 cm at the end of the growth cycle.Bok Choy: Reaches an average height of around 12 cm by the end of its cycle.
Lettuce & Leafy Greens: Generally have compact canopy growth, often in the 10–20 cm range.
Vining/Large Crops (Tomatoes, Cucumbers): These require vertical support and are far taller, often reaching several feet/meters, but are kept compact through training and pruning.
Vertical System Heights
Tower Systems: Individual towers (like those from Tower Farms) can reach over 9 feet high, though they contain multiple, shorter-height plants.Small-Scale/Home Units: Often designed to fit on counters or shelves, with vertical clearance requirements ranging from 28 cm to several feet.
Key Factors Influencing Height
Nutrient Solutions: Lower nutrient levels (within reasonable limits) sometimes result in larger plant heights.Flow Rates: Studies show higher plant heights often occur at specific water flow rates, such as 20 L/h.
System Type: Nutrient Film Technique (NFT) often produces higher plant growth compared to Ebb & Flow or soil, with one study showing 40 cm for NFT vs. 30 cm for Ebb & Flow
From the number crunching for "For a "double toroid" 250,000m^3 interior volume structure,"
Here is the shape
It was decided to make " inflatable tori with an inner radius of 50m and an outer radius of 70.50385m, which provides an interior volume of 125,000.430m^3 and surface area of 24,385.748m^2 per torus. "
It is supported by "37,050m of 30mm OD / 2mm wall thickness 304L tubing per Starship primary structure.
10 Starships provide 370,500m of tubing to work with." external stainless tubing will support the mass of this toroidal Hesco-type structure. We'll use the basalt tiles later after we figure out how to make those and where to source the material from.two layers of 300g/m^2 Vectran fabric, which we will fill with finely pulverized regolith- sort of like an enormous Hesco barrier, with regolith scooped off the surface of the planet and poured into silicone-impregnated Vectran bags, and supported externally by stainless steel tubing to absorb the tensile loads from internal pressurization. The 304L tubing will be threaded through loops sewn into the exterior of the bags. This is a steel and regolith bag reinforced "pup tent" structure, for all intents and purposes.
Based on typical industrial standards, the specifications for 30mm OD x 2mm wall thickness 304L stainless steel tubing are: Dimensional Specifications Outside Diameter (OD): 30 mmWall Thickness: 2 mmInner Diameter (ID): 26 mm (Approximate, \(30-(2\times 2)\))
Configuration: Commonly available in seamless (for high pressure) or welded (for general service)
Surface Finish: Often available as annealed and pickled, or polished (inside and outside)
Material Properties (304L) Material Grade: 304L (UNS S30403 / Werkstoff Nr. 1.4306/1.4307)
Chemical Composition: Carbon \(\le 0.030\%\), Chromium 18-20%, Nickel 8-12%
Tensile Strength: 500 - 700 MPa (approx. 75 ksi min)
Yield Strength: \(\ge 200\) MPa (approx. 30 ksi min)
Elongation: \(\ge 45\%\)Density: 8.00 g/cm³ Standards & Tolerances Manufacturing Specs: ASTM A269 (General Service), ASTM A213 (Seamless), or ASTM A249 (Welded)
OD Tolerance: Often ±0.05mm for precision tubing, or ±10% for standard wall thickness
Straightness Tolerance: ~0.075" in 7 feet (standard) Key Features Corrosion Resistance: Good, with superior resistance to intergranular corrosion after welding due to low carbon content.
Temperature Range: Suitable for high-temperature service up to 870°C.
Applications: Frequently used in food processing, pharmaceuticals, dairy, medical, and instrumentation,, due to its non-magnetic properties and cleanliness
Understanding the Relationship Between O/D and Wall Thickness in Tubing: A Comprehensive Guide
Most want to support the canvas tent from the inside like this on

rather than on the outside.
My post about stainless steel Isogrid talked about inflatable as an option.
More good news from the number crunching for "For a "double toroid" 250,000m^3 interior volume structure,"
Here is the shape
It was decided to make " inflatable tori with an inner radius of 50m and an outer radius of 70.50385m, which provides an interior volume of 125,000.430m^3 and surface area of 24,385.748m^2 per torus. "
It is supported by "37,050m of 30mm OD / 2mm wall thickness 304L tubing per Starship primary structure.
10 Starships provide 370,500m of tubing to work with." external stainless tubing will support the mass of this toroidal Hesco-type structure. We'll use the basalt tiles later after we figure out how to make those and where to source the material from.two layers of 300g/m^2 Vectran fabric, which we will fill with finely pulverized regolith- sort of like an enormous Hesco barrier, with regolith scooped off the surface of the planet and poured into silicone-impregnated Vectran bags, and supported externally by stainless steel tubing to absorb the tensile loads from internal pressurization. The 304L tubing will be threaded through loops sewn into the exterior of the bags. This is a steel and regolith bag reinforced "pup tent" structure, for all intents and purposes.
Here is the above posts consolidated and boiled down
Absolutely — here’s a clean, simplified version of the huge block of content you provided. I’ve boiled it down to the core ideas, removing repetition while keeping the engineering logic intact.
⭐ Simplified Summary of Your Habitat + Power + Volume Analysis
You’re designing a 1,000 person Mars ring habitat, and your original calculation (250 sleeping units × 125 m³ = 31,250 m³) only captured bunk volume, not the full colony. The missing pieces fall into four big categories:
? 1. Missing Habitat Volume (the big oversight) 250,000m^3
Your original math only counted sleeping quarters. A real colony needs many more spaces, each with significant volume:
Essential living spaces
• Bathrooms, showers, sinks
• Laundry and linen storage
• Galley/kitchen
• Mess hall seating
• Exercise and recreation
• Medical center (50 monitored beds + OR + imaging)
• Workspaces, labs, offices
• Social/quiet rooms
• Greenhouse (≈40,000 m³ by your estimate)
Infrastructure spaces
• Hallways, nodes, airlocks
• Doors and pressure vestibules
• Curved ring geometry losses
• Structural voids (walls, insulation, ducts, cables)
Systems rooms
• CO₂ scrubbers
• O₂ generation
• Water processors
• Waste management
• Power distribution
• Thermal control
• Spare parts storage
• Logistics/cargo areas
Result
A realistic 1,000 person ring habitat is 130,000–160,000 m³, not 31,250 m³.
⚡ 2. Missing Power Loads (life support is only the beginning)
Your ISS based numbers give a solid baseline:
Life support minimum
• CO₂ scrubbing + water recovery: ~0.42 MW
• Ventilation: 0.06–0.9 MW
• Crop lighting (potatoes): ~9.2 MW
Subtotal: ~10–11 MW
But a real colony needs much more:
Habitat overhead
• Heating (Mars is −70 to −120°C): 1–2 MW
• Medical facilities: 0.3–0.8 MW
• Computing/comms: 0.2–0.5 MW
Industrial & operational loads
• Manufacturing & fabrication: 1–3 MW
• Construction ISRU (bricks, glass, metals): 1–5 MW
• Mining & hauling: 1–3 MW
• Rover fleet: 0.5–1 MW
• Solid waste processing: 0.2–0.4 MW
• Nitrogen/argon extraction: 1–2 MW
Total realistic power
16–29 MW base 20–40 MW with redundancy and peak load margin
This is the power consumption of a small Earth town.
?️ 3. Missing Thermal Loads
Mars is extremely cold. Even insulated habitats leak heat.
Estimated heating requirement:
• ~400 kW to 2 MW depending on burial and insulation.
This is a major missing category.
? 4. Missing Industrial & Logistics Volume
A real colony must:
• Build things
• Repair things
• Store spares
• Process waste
• Handle cargo
• Maintain vehicles
These require warehouse scale spaces, not closets.
? The Big Picture (fully simplified)
Your original estimate captured sleeping space and basic life support, but a real 1,000 person Mars colony also needs:
Much more volume
• Sleeping quarters are only ~20–25% of total habitat volume.
• Full colony volume is 130k–160k m³.
Much more power
• Life support + food: ~10–11 MW
• Industry + heating + mining + redundancy: ~10–25 MW
• Total: 20–40 MW continuous
Much more infrastructure
• Circulation space
• Systems rooms
• Industrial shops
• Medical
• Social spaces
• Storage
• Thermal control
• Power conversion
• Airlocks and nodes
A Mars colony is not just “ISS × 150 people.” It’s a small city, a factory, a farm, and a mine all in one.
If you want, I can now produce a super clean table of:
• Total volumes
• Total power
• Per person requirements
• Ring geometry sizing
Just tell me which direction you want to go next.
Will print this out to be able to update as we go making changes as we fill in the blanks for volume and power for each item still blank.
Somethings once the shape as drawn with the basic concepts will solve some stuff.
Here is the above posts boiled down
Absolutely — here’s a clean, simplified version of the huge block of content you provided. I’ve boiled it down to the core ideas, removing repetition while keeping the engineering logic intact.
⭐ Simplified Summary of Your Habitat + Power + Volume Analysis
You’re designing a 1,000 person Mars ring habitat, and your original calculation (250 sleeping units × 125 m³ = 31,250 m³) only captured bunk volume, not the full colony. The missing pieces fall into four big categories:
? 1. Missing Habitat Volume (the big oversight)
Your original math only counted sleeping quarters. A real colony needs many more spaces, each with significant volume:
Essential living spaces
• Bathrooms, showers, sinks
• Laundry and linen storage
• Galley/kitchen
• Mess hall seating
• Exercise and recreation
• Medical center (50 monitored beds + OR + imaging)
• Workspaces, labs, offices
• Social/quiet rooms
• Greenhouse (≈40,000 m³ by your estimate)
Infrastructure spaces
• Hallways, nodes, airlocks
• Doors and pressure vestibules
• Curved ring geometry losses
• Structural voids (walls, insulation, ducts, cables)
Systems rooms
• CO₂ scrubbers
• O₂ generation
• Water processors
• Waste management
• Power distribution
• Thermal control
• Spare parts storage
• Logistics/cargo areas
Result
A realistic 1,000 person ring habitat is 130,000–160,000 m³, not 31,250 m³.
⚡ 2. Missing Power Loads (life support is only the beginning)
Your ISS based numbers give a solid baseline:
Life support minimum
• CO₂ scrubbing + water recovery: ~0.42 MW
• Ventilation: 0.06–0.9 MW
• Crop lighting (potatoes): ~9.2 MW
Subtotal: ~10–11 MW
But a real colony needs much more:
Habitat overhead
• Heating (Mars is −70 to −120°C): 1–2 MW
• Medical facilities: 0.3–0.8 MW
• Computing/comms: 0.2–0.5 MW
Industrial & operational loads
• Manufacturing & fabrication: 1–3 MW
• Construction ISRU (bricks, glass, metals): 1–5 MW
• Mining & hauling: 1–3 MW
• Rover fleet: 0.5–1 MW
• Solid waste processing: 0.2–0.4 MW
• Nitrogen/argon extraction: 1–2 MW
Total realistic power
16–29 MW base 20–40 MW with redundancy and peak load margin
This is the power consumption of a small Earth town.
?️ 3. Missing Thermal Loads
Mars is extremely cold. Even insulated habitats leak heat.
Estimated heating requirement:
• ~400 kW to 2 MW depending on burial and insulation.
This is a major missing category.
? 4. Missing Industrial & Logistics Volume
A real colony must:
• Build things
• Repair things
• Store spares
• Process waste
• Handle cargo
• Maintain vehicles
These require warehouse scale spaces, not closets.
? The Big Picture (fully simplified)
Your original estimate captured sleeping space and basic life support, but a real 1,000 person Mars colony also needs:
Much more volume
• Sleeping quarters are only ~20–25% of total habitat volume.
• Full colony volume is 130k–160k m³.
Much more power
• Life support + food: ~10–11 MW
• Industry + heating + mining + redundancy: ~10–25 MW
• Total: 20–40 MW continuous
Much more infrastructure
• Circulation space
• Systems rooms
• Industrial shops
• Medical
• Social spaces
• Storage
• Thermal control
• Power conversion
• Airlocks and nodes
A Mars colony is not just “ISS × 150 people.” It’s a small city, a factory, a farm, and a mine all in one.
If you want, I can now produce a super clean table of:
• Total volumes
• Total power
• Per person requirements
• Ring geometry sizing
Just tell me which direction you want to go next.
You’re thinking about the right thing—if 1,000 people are going to live on Mars, not just survive, a gym isn’t a luxury, it’s medical infrastructure.
Here’s a compact set of requirements for a gym designed to support the health of a 1,000‑person crew inside a ring‑shaped Quonset‑hut‑style structure.
1. Space and layout requirements
Item Rule of thumb For 1,000 people
Active users at once 10–15% of crew 100–150 people
Area per active user 4–6 m² (mixed cardio/strength) 400–900 m²
Total gym area ~1–1.5 m² per person 1,000–1,500 m²
Practical target:
1,200–1,500 m² of gym space distributed around the ring
Broken into zones: cardio, resistance, rehab/physio, flexibility, and small group classes
For a ring habitat, this works well as a continuous “fitness band” around part of the circumference, doubling as a circulation corridor.
2. Equipment mix (Mars‑appropriate)
Key principle: minimize mass, moving parts, and maintenance; maximize bone and muscle loading.
Cardio:
Treadmills: 10–20 units (with harness options if partial‑g is an issue)
Bikes/ergometers: 20–30 units
Rowers/ski‑ergs: 10–15 units
Strength & bone loading:
Resistance machines using bands/flywheels instead of heavy plates
Squat/deadlift platforms with adjustable resistance devices
Multi‑station cable/flywheel rigs (high utility per kg of mass)
Pull‑up/dip stations, suspension trainers
Rehab & mobility:
Mats, balance tools, light dumbbells/kettlebells, physio tables
Scheduling assumption:
Each crew member gets ~1 hour/day of structured exercise
Gym must support 100–150 concurrent users without bottlenecks
3. Power requirements for the gym
Most power goes to cardio machines, lighting, and ventilation.
Cardio equipment:
Treadmills: ~1–2 kW each × 15 → 15–30 kW
Bikes/rowers: 0.1–0.3 kW each × 40 → 4–12 kW
Total cardio peak: ~20–40 kW
Lighting:
10–15 W/m² × 1,500 m² → 15–22 kW
Ventilation & air handling:
Higher CO₂ and humidity from exercise
Plan for 6–10 air changes per hour in gym zone
Fans/blowers: 10–30 kW (depending on ducting and pressure drops)
Electronics & controls:
Displays, sensors, monitoring: 1–3 kW
Total gym power budget:
Peak: ~50–90 kW
Average (over a sol): ~20–40 kW (since not all equipment runs at once)
4. Structural and ring‑geometry considerations
In a ring‑shaped Quonset hut:
Location:
Place gym near the outer radius if the ring is spun for artificial gravity—this maximizes g‑level for exercise.
Use the gym as a buffer zone between noisy/industrial and quiet/sleep areas.
Floor loading:
Dynamic loads from running/jumping/lifting: design for 3–5 kN/m²
Add vibration isolation to avoid transmitting shocks through the ring.
Ceiling height:
Minimum 2.7–3.0 m for safe overhead movements and psychological comfort.
5. Environmental and life‑support coupling
The gym is a CO₂ and heat hotspot:
CO₂:
Exercising humans can produce 2–3× resting CO₂
Local CO₂ scrubbing or high‑flow ventilation from main loop is needed.
Heat:
100–150 people exercising → 10–20 kW of metabolic heat
This is useful in cold climates but must be removed to keep comfort.
Humidity:
Sweat drives local humidity up; dehumidification or dedicated air handling is important.
6. Health and operational goals
Design the gym to support:
Bone density maintenance: heavy‑load resistance, impact or pseudo‑impact training
Cardiovascular fitness: daily moderate‑to‑vigorous cardio
Injury prevention: mobility, physio, and rehab space
Mental health: open, bright, visually varied space—this is a pressure valve for stress
If you want, next step could be:
tie this gym into your overall power budget and ring geometry (radius, spin rate, g‑level),
or sketch a ring cross‑section showing how the gym, living quarters, and utilities stack together.
You’re thinking about the right thing—if 1,000 people are going to live on Mars, not just survive, a gym isn’t a luxury, it’s medical infrastructure.
Here’s a compact set of requirements for a gym designed to support the health of a 1,000‑person crew inside a ring‑shaped Quonset‑hut‑style structure.
1. Space and layout requirements
Item Rule of thumb For 1,000 people
Active users at once 10–15% of crew 100–150 people
Area per active user 4–6 m² (mixed cardio/strength) 400–900 m²
Total gym area ~1–1.5 m² per person 1,000–1,500 m²
Practical target:
1,200–1,500 m² of gym space distributed around the ring
Broken into zones: cardio, resistance, rehab/physio, flexibility, and small group classes
For a ring habitat, this works well as a continuous “fitness band” around part of the circumference, doubling as a circulation corridor.
2. Equipment mix (Mars‑appropriate)
Key principle: minimize mass, moving parts, and maintenance; maximize bone and muscle loading.
Cardio:
Treadmills: 10–20 units (with harness options if partial‑g is an issue)
Bikes/ergometers: 20–30 units
Rowers/ski‑ergs: 10–15 units
Strength & bone loading:
Resistance machines using bands/flywheels instead of heavy plates
Squat/deadlift platforms with adjustable resistance devices
Multi‑station cable/flywheel rigs (high utility per kg of mass)
Pull‑up/dip stations, suspension trainers
Rehab & mobility:
Mats, balance tools, light dumbbells/kettlebells, physio tables
Scheduling assumption:
Each crew member gets ~1 hour/day of structured exercise
Gym must support 100–150 concurrent users without bottlenecks
3. Power requirements for the gym
Most power goes to cardio machines, lighting, and ventilation.
Cardio equipment:
Treadmills: ~1–2 kW each × 15 → 15–30 kW
Bikes/rowers: 0.1–0.3 kW each × 40 → 4–12 kW
Total cardio peak: ~20–40 kW
Lighting:
10–15 W/m² × 1,500 m² → 15–22 kW
Ventilation & air handling:
Higher CO₂ and humidity from exercise
Plan for 6–10 air changes per hour in gym zone
Fans/blowers: 10–30 kW (depending on ducting and pressure drops)
Electronics & controls:
Displays, sensors, monitoring: 1–3 kW
Total gym power budget:
Peak: ~50–90 kW
Average (over a sol): ~20–40 kW (since not all equipment runs at once)
4. Structural and ring‑geometry considerations
In a ring‑shaped Quonset hut:
Location:
Place gym near the outer radius if the ring is spun for artificial gravity—this maximizes g‑level for exercise.
Use the gym as a buffer zone between noisy/industrial and quiet/sleep areas.
Floor loading:
Dynamic loads from running/jumping/lifting: design for 3–5 kN/m²
Add vibration isolation to avoid transmitting shocks through the ring.
Ceiling height:
Minimum 2.7–3.0 m for safe overhead movements and psychological comfort.
5. Environmental and life‑support coupling
The gym is a CO₂ and heat hotspot:
CO₂:
Exercising humans can produce 2–3× resting CO₂
Local CO₂ scrubbing or high‑flow ventilation from main loop is needed.
Heat:
100–150 people exercising → 10–20 kW of metabolic heat
This is useful in cold climates but must be removed to keep comfort.
Humidity:
Sweat drives local humidity up; dehumidification or dedicated air handling is important.
6. Health and operational goals
Design the gym to support:
Bone density maintenance: heavy‑load resistance, impact or pseudo‑impact training
Cardiovascular fitness: daily moderate‑to‑vigorous cardio
Injury prevention: mobility, physio, and rehab space
Mental health: open, bright, visually varied space—this is a pressure valve for stress
If you want, next step could be:
tie this gym into your overall power budget and ring geometry (radius, spin rate, g‑level),
or sketch a ring cross‑section showing how the gym, living quarters, and utilities stack together.
Here’s a clean power budget table for your 1,000‑person Mars colony, based on what you already calculated plus the big missing pieces.
Power budget summary for 1,000 colonists
Subsystem Power (MW electric) Notes
Minimal life support (air + water) 0.42 CO₂ scrubbing + wastewater recovery (your 417 kW)
Ventilation & circulation 0.06–0.90 4–15 ACH, depending on how “wind‑tunnel” you go
Crop lighting (potato staple) ~9.2 Your 9.23 MW constant for 2,083,333 kg/year potatoes
Food processing & storage 0.5–1.0 Refrigeration, drying, milling, cooking
Habitat heating 1.0–2.0 Depends heavily on insulation, burial, and layout
Computing & communications 0.2–0.5 Local servers, comms, control systems
Medical facilities 0.3–0.8 Small hospital + labs
Manufacturing & fabrication 1.0–3.0 Machine shops, 3D printers, CNC, welding
Construction ISRU (bricks, glass, etc.) 1.0–5.0 Regolith processing, kilns, furnaces
Mining & raw materials 1.0–3.0 Regolith, ice, ores, hauling
Transportation (rovers, haulers) 0.5–1.0 Fleet of pressurized and utility vehicles
Waste processing (solid, chemical) 0.2–0.4 Beyond water: compost, plastics, hazardous waste
Atmospheric N₂/Ar extraction 1.0–2.0 Compression + separation from Martian air
Margin & redundancy +30–50% Backup systems, peak loads, failures
Roll‑up totals
Life support core (air + water + crops):
CO₂ + water: ~0.4 MW
Crop lighting: ~9.2 MW
Food processing: ~0.5–1.0 MW
→ ~10–11 MW
Habitat & people overhead:
Heating: 1–2 MW
Ventilation: 0.06–0.9 MW
Medical: 0.3–0.8 MW
Computing/comms: 0.2–0.5 MW
→ ~1.5–4 MW
Industrial & expansion capability:
Manufacturing: 1–3 MW
Construction ISRU: 1–5 MW
Mining: 1–3 MW
Transportation: 0.5–1 MW
Waste processing: 0.2–0.4 MW
N₂/Ar extraction: 1–2 MW
→ ~4.7–14.4 MW
Now add them:
Base continuous load (no margin):
Low end: ~10 + 1.5 + 4.7 ≈ 16 MW
High end: ~11 + 4 + 14.4 ≈ 29 MW
With 30–50% margin and redundancy:
Rough design target: 20–40 MWe continuous
How this compares to your original estimate
Your ~12 MWe for air/water/food is a solid core number.
Once you add industry, construction, heating, mining, and redundancy, the realistic colony looks like:
~20–30 MWe for a capable, growing settlement
Up to ~40 MWe if you want generous margin and aggressive ISRU/build‑out
So the “American‑style” energy footprint still holds—what changes is that life support is only a slice of the pie. The rest is everything that makes the colony more than a survival bunker.
If you’d like, next step could be: pick one architecture (e.g., “3×10 MWe reactors + geothermal + some solar‑thermal”) and we can see how many units, how much mass, and what failure modes look like.
Here’s a clean power budget table for your 1,000‑person Mars colony, based on what you already calculated plus the big missing pieces.
Power budget summary for 1,000 colonists
Subsystem Power (MW electric) Notes
Minimal life support (air + water) 0.42 CO₂ scrubbing + wastewater recovery (your 417 kW)
Ventilation & circulation 0.06–0.90 4–15 ACH, depending on how “wind‑tunnel” you go
Crop lighting (potato staple) ~9.2 Your 9.23 MW constant for 2,083,333 kg/year potatoes
Food processing & storage 0.5–1.0 Refrigeration, drying, milling, cooking
Habitat heating 1.0–2.0 Depends heavily on insulation, burial, and layout
Computing & communications 0.2–0.5 Local servers, comms, control systems
Medical facilities 0.3–0.8 Small hospital + labs
Manufacturing & fabrication 1.0–3.0 Machine shops, 3D printers, CNC, welding
Construction ISRU (bricks, glass, etc.) 1.0–5.0 Regolith processing, kilns, furnaces
Mining & raw materials 1.0–3.0 Regolith, ice, ores, hauling
Transportation (rovers, haulers) 0.5–1.0 Fleet of pressurized and utility vehicles
Waste processing (solid, chemical) 0.2–0.4 Beyond water: compost, plastics, hazardous waste
Atmospheric N₂/Ar extraction 1.0–2.0 Compression + separation from Martian air
Margin & redundancy +30–50% Backup systems, peak loads, failures
Roll‑up totals
Life support core (air + water + crops):
CO₂ + water: ~0.4 MW
Crop lighting: ~9.2 MW
Food processing: ~0.5–1.0 MW
→ ~10–11 MW
Habitat & people overhead:
Heating: 1–2 MW
Ventilation: 0.06–0.9 MW
Medical: 0.3–0.8 MW
Computing/comms: 0.2–0.5 MW
→ ~1.5–4 MW
Industrial & expansion capability:
Manufacturing: 1–3 MW
Construction ISRU: 1–5 MW
Mining: 1–3 MW
Transportation: 0.5–1 MW
Waste processing: 0.2–0.4 MW
N₂/Ar extraction: 1–2 MW
→ ~4.7–14.4 MW
Now add them:
Base continuous load (no margin):
Low end: ~10 + 1.5 + 4.7 ≈ 16 MW
High end: ~11 + 4 + 14.4 ≈ 29 MW
With 30–50% margin and redundancy:
Rough design target: 20–40 MWe continuous
How this compares to your original estimate
Your ~12 MWe for air/water/food is a solid core number.
Once you add industry, construction, heating, mining, and redundancy, the realistic colony looks like:
~20–30 MWe for a capable, growing settlement
Up to ~40 MWe if you want generous margin and aggressive ISRU/build‑out
So the “American‑style” energy footprint still holds—what changes is that life support is only a slice of the pie. The rest is everything that makes the colony more than a survival bunker.
If you’d like, next step could be: pick one architecture (e.g., “3×10 MWe reactors + geothermal + some solar‑thermal”) and we can see how many units, how much mass, and what failure modes look like.
Here’s a first‑cut volume budget so you can see what’s missing, not just feel it.
Rough volume budget for 1,000‑person ring habitat
Category Basis / assumption Area (m²) Volume (m³)
Crew quarters 250 × 4‑person units @ 125 m³ each – 31,250
Hygiene & laundry 1.0–1.5 m²/person @ 2.5 m height 1,000–1,500 2,500–3,750
Galley + mess Seats for 1/3 crew at once (~0.8–1.0 m²/seat) + kitchen 600–800 1,500–2,000
Medical (incl. support) 50 monitored beds @ 23–28 m² + OR, imaging, support 2,000–2,500 5,000–6,250
Exercise & recreation ~1.5–2.0 m²/person shared 1,500–2,000 3,750–5,000
Workspaces & labs Offices, control, labs, shops (~1.0–1.5 m²/person) 1,000–1,500 2,500–3,750
Greenhouse / crops Your estimate – 40,000
Life support machinery CO₂, O₂, water, waste, tanks, thermal plant – 5,000–10,000
Power & distribution Switchgear, batteries, control rooms – 2,000–4,000
Logistics & spares Warehousing, cargo, spares, tools – 3,000–6,000
Waste management Sorting, storage, processing – 1,000–2,000
Social / “soft” spaces Lounges, small rooms, quiet areas 500–1,000 1,250–2,500
Circulation & nodes Corridors, nodes, airlocks (~30–40% of net spaces) – 25,000–35,000
Structural & service voids Walls, insulation, ducts, cable chases (~10–20%) – 10,000–20,000
Very roughly, that puts you in the ballpark of:
Net functional volume (rooms, greenhouses, etc.):
~95,000–110,000 m³
Plus circulation + structure overhead:
another ~35,000–55,000 m³
Total ring pressurized volume:
? On the order of 130,000–160,000 m³, not 31,250 m³.
So the big things you were “missing” in the original 4‑crew‑quarters × 250 calculation are:
Circulation and geometry overhead
Corridors, nodes, airlocks, and the inefficiency of packing rectangles into a curved ring.
All the non‑bunk functions
Hygiene, galley/mess, medical, exercise, workspaces, social spaces.
Industrial‑scale systems volume
Life support machinery, power distribution, thermal control, waste management.
Logistics, spares, and growth margin
Warehousing and spare parts for a remote, 1,000‑person outpost.
Structural and service voids
The “hidden” volume in walls, floors, ducts, and cable runs.
If you’d like, next step could be: pick a ring radius and width, and see what cross‑section and length you actually need to enclose ~150,000 m³—then we can talk about how many decks, how wide the corridors are, and where those 4‑person units realistically fit in the curve.
“Volume tables” can mean a few different things depending on the context, and your earlier message was deeply technical—so I want to make sure we’re talking about the same concept.
In engineering, architecture, and life‑support design, volume tables usually refer to one of these:
? 1. A table listing the internal volumes of habitats or structures
Used to calculate:
Air mass
Required air changes per hour
CO₂ scrubbing load
Heating/cooling load
Pressurization requirements
For example:
Structure Internal Volume (m³) Notes
Habitat Module A 8,000 Crew quarters
Greenhouse 20,000 High humidity
Workshop 12,000 High ventilation load
Total 40,000 Used for life‑support sizing
This is the kind of table you’d use to size fans, radiators, and CO₂ scrubbers.
? 2. A table of volume conversions
Used when switching between ft³, m³, liters, gallons, etc.
Unit Equivalent
1 m³ 35.3147 ft³
1 ft³ 0.0283168 m³
1 gallon (US) 3.78541 L
1 L 0.001 m³
This is common when mixing NASA data (often in English units) with engineering calculations (usually SI).
? 3. A table of volume requirements per person
Used in habitat design to estimate:
Minimum breathable air volume
Comfortable living volume
Emergency shelter volume
Typical values:
Category Volume per Person
Absolute minimum (ISS‑like) 25–30 m³
Comfortable long‑term 100–150 m³
Spacious / Earth‑like 300–500 m³
Your earlier example used a 125,000 m³ structure for 1,000 colonists → 125 m³ per person, which fits the “comfortable long‑term” category.
? 4. A table of volume flows
Used for ventilation and air‑handling calculations.
For example:
Flow Rate Equivalent
1 CFM 0.0004719 m³/s
36,000 CFM 16.99 m³/s
15 ACH (air changes/hr) for 4,078 m³ 61,170 m³/hr
This is exactly the kind of table you’d use to compute the 36,000 CFM fan load you mentioned.
? 5. A table of volume for storage (water, gases, food)
For example:
Resource Daily Use (1,000 people) Required Storage Volume
Water ~2,146 gallons/day ~8.1 m³/day
O₂ ~210 kg/day ~150 m³ at 1 atm
N₂ ~780 kg/day ~600 m³ at 1 atm
This is essential for sizing tanks and ISRU plants.
If you tell me which type of “volume table” you meant, I can build the exact table you need.
You might be asking for:
the volume table for the 125,000 m³ habitat,
the volume table for air changes,
or the volume table for water/CO₂ processing.
Just point me toward the one you want to work with next.
We need to be careful when using ISS numbers as they are based on a crew of typical 7 with short duration of more.
I did put your and my post through copilot and we have a long ways to go. for numbers as the fact that we are in a circular ring makes for much volume that due to a square layout is a problem.
You’re asking the right question—“what did we miss?”—because the big gap isn’t a single number, it’s a whole layer of overhead you haven’t turned into volume and power yet.
Let me pull it together and show you what’s still “un-costed” in your ring/Quonset concept.
1. Net vs gross volume
Sleeping volume vs habitat volume:
You sized 4‑person quarters at
125 m^3
2. For 1,000 crew, that’s 250 units →
31,250 m^3
3. That’s net bunk volume. What’s missing is the gross volume:
Walls, structure, insulation, MMOD/radiation shielding
Ducts, pipes, cable runs
Access corridors, stairways/ladders, airlocks, nodes
Once you add circulation and systems, net habitable volume is typically only a fraction of total pressurized volume.
2. Circulation, layout, and geometry penalties
Hallways and nodes:
Main spines, cross‑corridors, junction nodes, airlock lobbies, elevator/lift shafts (if any).
Egress routes sized for emergency evacuation of 1,000 people, not just “enough to walk through.”
Curved ring / Quonset geometry:
Rectangular modules in a curved ring waste edge volume.
You’ll have wedge-shaped gaps, unusable corners, and “dead” spaces that still need to be pressurized and serviced.
Doors and pressure breaks:
Every compartment boundary, fire zone, and pressure zone adds doors, vestibules, and clearances.
Those doors and vestibules have non‑trivial volume and lengthen the ring.
Right now, you’ve counted rooms but not the “streets” between them.
3. Support spaces you listed but haven’t volumized
You already named most of these—what’s missing is turning them into square meters and cubic meters:
Sanitation and hygiene:
Toilets, showers, sinks, grey/black water plumbing chases.
Central vs distributed bathrooms changes both volume and complexity.
Laundry and linen:
Washers, dryers, folding/clean storage, dirty storage, carts, and circulation space.
Galley and mess:
Kitchens, prep areas, dishwashing, food staging, serving lines, seating for some fraction of 1,000 at once.
Dry, refrigerated, and frozen storage sized for your resupply cadence.
Exercise and recreation:
Treadmills, resistance machines, free weights, VR/rec rooms, open space for group activities.
These are big volume hogs if you want them to be genuinely useful for 1,000 people.
Medical:
You quoted ~23–28 m² per monitored bed. For 50 beds, that’s ~1,150–1,400 m².
Add OR(s), imaging, pharmacy, lab, waiting, storage, staff areas, decontamination, and isolation rooms.
Greenhouse / food production:
You already estimated ~40,000 m³ for crops. That’s larger than the sleeping quarters volume.
You still need: nutrient mixing rooms, seed storage, tools, maintenance access, and buffer corridors.
All of these need to be explicitly sized and then placed in the ring geometry.
4. Systems volume (the “machine rooms” of the colony)
You’ve got good power and mass numbers for life support hardware—but not their physical footprint:
Life support equipment rooms:
CO₂ scrubbers, O₂ generation, water processors, tanks, pumps, compressors, filters, spare units.
Redundancy (N+1 or N+2) multiplies both mass and volume.
Power systems and distribution:
Switchgear, inverters, transformers, batteries, control rooms, cable trunks.
If you’re using nuclear, geothermal, or solar‑thermal, you also need heat‑to‑power conversion plant and interface spaces.
Thermal control:
Heat exchangers, coolant loops, pumps, manifolds, expansion tanks, radiator interface hardware.
Internal ducting and plenum spaces for air distribution.
Waste management:
Sorting, compacting, storage, recycling, and possibly incineration or feedstock processing.
1,000 people over years means industrial‑scale trash handling, not a closet with a bin.
These are often stacked in “utility decks” or dedicated rings that can easily rival or exceed the volume of living spaces.
5. Redundancy, spares, and logistics
Spares storage:
Filters, pumps, valves, electronics, suits, tools, structural repair materials, medical supplies, etc.
For a remote colony, spare parts inventory is huge—think warehouse, not cabinet.
Logistics and cargo:
Incoming cargo staging, unpacking, inspection, and distribution.
Outgoing waste or return cargo storage.
Emergency infrastructure:
Refuge rooms, extra air and water tanks, emergency rations, firefighting gear, emergency power and comms.
None of that is in the 125 m³/crew‑quarters math yet.
6. Human factors and “soft” space
This is the stuff that keeps 1,000 people sane over years:
Quiet zones and privacy:
Sound‑isolated areas, small meeting rooms, private work pods.
Workspaces and labs:
Offices, mission control, science labs, engineering shops, fabrication/repair bays.
Social and cultural spaces:
Common rooms, lounges, “town square” or auditorium, art/music spaces, spiritual/meditation rooms.
If you don’t allocate this up front, it gets squeezed into leftover corners—which is exactly what you don’t want in a long‑duration, high‑stress environment.
7. Power: you’ve got a floor, not a ceiling
You already see the gap:
Life support baseline:
~0.4–0.5 MW for CO₂ and water processing is just “keep them alive.”
Ventilation and thermal:
Tens to hundreds of kW more, depending on air change rates and radiator design.
Food production:
LED grow lights and associated systems push you into multi‑MW territory by themselves.
Everything else:
IT, comms, robotics, mining/ISRU, manufacturing, vehicles, construction, science.
So 5 MW for 1,000 people is a minimum survival plus a bit. Once you include food and industry, 10–15 MWe for a thriving settlement is very plausible.
The short answer
What you “missed” in the ring Quonset hut sizing is:
Circulation and geometry overhead (hallways, nodes, airlocks, curvature losses).
All the support spaces you listed but haven’t turned into area/volume.
Systems and utility volume for life support, power, thermal, and waste.
Redundancy, spares, and logistics storage.
Work, social, and psychological spaces beyond bunks and a mess hall.
Growth and contingency margin—you’ve sized for exactly 1,000, not 1,000 + failures + expansion.
If you want, we can take a next step and build a rough “volume budget” table—sleeping, hygiene, food, medical, greenhouse, systems, circulation—and see what the total ring volume really looks like.
You’ve done a very thorough first‑pass accounting of the power, air, water, and food loops for a 1,000‑person Mars settlement. The numbers you’re using are grounded in real ISS hardware performance, which is exactly the right way to avoid sci‑fi hand‑waving. What you’ve built is essentially a “minimum viable colony” energy budget.
But you asked: what did we miss?
A few major categories haven’t been included yet, and they matter a lot—some even more than the life‑support loops themselves. I’ll walk through the big ones, explain why they matter, and give you a sense of how they change the overall power and mass picture.
?️ 1. Thermal Control: The Hidden Giant
You accounted for radiator load from life support, but you haven’t accounted for habitat heating.
Mars is cold. Really cold.
Typical equatorial night: −70°C
Mid‑latitudes: −100°C
Worst‑case: −120°C
Even with insulation, a large pressurized structure leaks heat. On Earth, a well‑insulated building loses 30–50 W/m² in winter. On Mars, with a 100°C temperature delta, you’re looking at 100–200 W/m² unless you bury the structure.
For a 125,000 m³ habitat, even assuming a modest 2,000 m² exposed surface area:
200 W/m² × 2,000 m² = 400 kW continuous heating
That’s before you add greenhouses, workshops, airlocks, or tunnels.
If the colony uses multiple pressurized modules, the heating load can easily reach 1–2 MW thermal.
This is one of the biggest missing items.
?️ 2. Manufacturing, Fabrication, and Maintenance
A real colony must repair and build things. That means:
CNC machines
Metal 3D printers
Kilns and smelters
Plastics extrusion
Electronics repair
Welding equipment
Machine shops
Rover maintenance bays
Industrial equipment is power‑hungry.
A modest terrestrial workshop consumes 200–500 kW.
A small industrial fab shop: 1–3 MW.
A Mars colony needs the latter, not the former.
This is another multi‑megawatt category missing from your tally.
? 3. Transportation (Rovers, Haulers, Drones)
Electric rovers on Mars will be the backbone of logistics.
A single large pressurized rover (think “Mars bus”) uses:
50–100 kWh per sol
Peak draw: 20–40 kW
A fleet of 20–30 vehicles adds:
0.5–1 MW continuous equivalent power
If you include mining trucks or regolith haulers, the number jumps.
? 4. ISRU for Construction Materials
If the colony builds anything locally—bricks, concrete, glass, metals—then you need:
Regolith heating
Sintering
Electrolysis
Chemical processing
High‑temperature furnaces (1,000–1,600°C)
These processes are extremely energy‑intensive.
A small regolith‑to‑brick plant alone can require:
1–5 MW thermal
0.5–1 MW electrical
If you want to produce metals (iron, aluminum, magnesium), multiply that by 5–10.
This is one of the largest missing power sinks.
? 5. Food Processing, Refrigeration, and Storage
You accounted for crop lighting, but not:
Refrigeration
Freezers
Drying and milling
Cooking
Packaging
Waste composting
Greenhouse climate control (fans, pumps, humidity control)
A 1,000‑person food system on Earth uses 1–2 MW of electrical power.
Even if you optimize heavily, you’re still looking at 0.5–1 MW.
? 6. Medical Facilities
A real colony needs:
Imaging (X‑ray, ultrasound, maybe MRI)
Sterilization
Labs
Surgical suites
Pharmacy production
A small hospital consumes 300–800 kW.
?️ 7. Communications and Computing
You haven’t included:
High‑gain antennas
Data centers
Navigation beacons
Local servers
Robotics control systems
A modest data center for 1,000 people is 200–500 kW.
If you want AI‑assisted operations or simulation labs, add more.
? 8. Safety Systems and Redundancy
A Mars colony must have:
Backup life support
Backup power
Emergency shelters
Fire suppression
Airlock cycling
Pressure monitoring
Leak detection
Spare parts manufacturing
Redundancy typically adds 30–50% overhead to all life‑support power.
? 9. Waste Processing Beyond Water
You included wastewater, but not:
Solid waste
Plastics recycling
Composting
Hazardous waste
Medical waste
Sewage sludge drying
Methane capture (if used)
A small waste‑to‑energy plant is 200–400 kW.
? 10. Atmospheric Processing for N₂ and Ar
You noted the need for nitrogen but didn’t include the power cost.
To extract N₂ and Ar from Mars’ atmosphere:
You must compress the atmosphere from 0.6 kPa to ~100–200 kPa
Then cryogenically separate gases
This is extremely energy‑intensive.
A rough estimate: 1–2 MW continuous for a colony this size.
? 11. Mining and Raw Material Extraction
If the colony wants to be even partially self‑sufficient:
Water ice mining
Regolith excavation
Gypsum mining
Sulfur extraction
Iron ore mining
Basalt fiber production
Mining equipment is power‑hungry.
A small terrestrial mine uses 5–10 MW.
A Mars colony version might use 1–3 MW.
? So What’s the Real Total?
Your estimate for basic life support + food was ~12 MW.
Adding the missing categories:
Category Estimated Power
Heating 1–2 MW
Manufacturing 1–3 MW
Transportation 0.5–1 MW
Construction ISRU 1–5 MW
Food processing 0.5–1 MW
Medical 0.3–0.8 MW
Computing & comms 0.2–0.5 MW
Waste processing 0.2–0.4 MW
Atmospheric N₂/Ar 1–2 MW
Mining 1–3 MW
Redundancy overhead +30–50%
Realistic total: 20–30 MW electrical + 5–10 MW thermal
This is very close to the power consumption of a small town or industrial campus on Earth.
? The Big Picture
Your original conclusion—that a Mars colony ends up looking like a high‑tech American town in terms of per‑capita energy use—is absolutely correct.
But the full system is larger:
Life support is only ~30–40% of total power.
Industry, construction, and heating dominate the rest.
A 1,000‑person Mars settlement is basically:
A small city
A mining operation
A farm
A factory
A research base
A hospital
A power plant
A water treatment facility
All rolled into one.
If you want, I can help you:
Build a full power budget spreadsheet
Model different energy architectures (geothermal vs nuclear vs solar‑thermal)
Estimate radiator area, mass, and heat rejection
Size the nitrogen extraction plant
Model food production with mixed crops
Estimate habitat insulation requirements
Just tell me where you want to take this next.
Here’s a first‑cut volume budget so you can see what’s missing, not just feel it.
Rough volume budget for 1,000‑person ring habitat
Category Basis / assumption Area (m²) Volume (m³)
Crew quarters 250 × 4‑person units @ 125 m³ each – 31,250
Hygiene & laundry 1.0–1.5 m²/person @ 2.5 m height 1,000–1,500 2,500–3,750
Galley + mess Seats for 1/3 crew at once (~0.8–1.0 m²/seat) + kitchen 600–800 1,500–2,000
Medical (incl. support) 50 monitored beds @ 23–28 m² + OR, imaging, support 2,000–2,500 5,000–6,250
Exercise & recreation ~1.5–2.0 m²/person shared 1,500–2,000 3,750–5,000
Workspaces & labs Offices, control, labs, shops (~1.0–1.5 m²/person) 1,000–1,500 2,500–3,750
Greenhouse / crops Your estimate – 40,000
Life support machinery CO₂, O₂, water, waste, tanks, thermal plant – 5,000–10,000
Power & distribution Switchgear, batteries, control rooms – 2,000–4,000
Logistics & spares Warehousing, cargo, spares, tools – 3,000–6,000
Waste management Sorting, storage, processing – 1,000–2,000
Social / “soft” spaces Lounges, small rooms, quiet areas 500–1,000 1,250–2,500
Circulation & nodes Corridors, nodes, airlocks (~30–40% of net spaces) – 25,000–35,000
Structural & service voids Walls, insulation, ducts, cable chases (~10–20%) – 10,000–20,000
Very roughly, that puts you in the ballpark of:
Net functional volume (rooms, greenhouses, etc.):
~95,000–110,000 m³
Plus circulation + structure overhead:
another ~35,000–55,000 m³
Total ring pressurized volume:
? On the order of 130,000–160,000 m³, not 31,250 m³.
So the big things you were “missing” in the original 4‑crew‑quarters × 250 calculation are:
Circulation and geometry overhead
Corridors, nodes, airlocks, and the inefficiency of packing rectangles into a curved ring.
All the non‑bunk functions
Hygiene, galley/mess, medical, exercise, workspaces, social spaces.
Industrial‑scale systems volume
Life support machinery, power distribution, thermal control, waste management.
Logistics, spares, and growth margin
Warehousing and spare parts for a remote, 1,000‑person outpost.
Structural and service voids
The “hidden” volume in walls, floors, ducts, and cable runs.
If you’d like, next step could be: pick a ring radius and width, and see what cross‑section and length you actually need to enclose ~150,000 m³—then we can talk about how many decks, how wide the corridors are, and where those 4‑person units realistically fit in the curve.
“Volume tables” can mean a few different things depending on the context, and your earlier message was deeply technical—so I want to make sure we’re talking about the same concept.
In engineering, architecture, and life‑support design, volume tables usually refer to one of these:
? 1. A table listing the internal volumes of habitats or structures
Used to calculate:
Air mass
Required air changes per hour
CO₂ scrubbing load
Heating/cooling load
Pressurization requirements
For example:
Structure Internal Volume (m³) Notes
Habitat Module A 8,000 Crew quarters
Greenhouse 20,000 High humidity
Workshop 12,000 High ventilation load
Total 40,000 Used for life‑support sizing
This is the kind of table you’d use to size fans, radiators, and CO₂ scrubbers.
? 2. A table of volume conversions
Used when switching between ft³, m³, liters, gallons, etc.
Unit Equivalent
1 m³ 35.3147 ft³
1 ft³ 0.0283168 m³
1 gallon (US) 3.78541 L
1 L 0.001 m³
This is common when mixing NASA data (often in English units) with engineering calculations (usually SI).
? 3. A table of volume requirements per person
Used in habitat design to estimate:
Minimum breathable air volume
Comfortable living volume
Emergency shelter volume
Typical values:
Category Volume per Person
Absolute minimum (ISS‑like) 25–30 m³
Comfortable long‑term 100–150 m³
Spacious / Earth‑like 300–500 m³
Your earlier example used a 125,000 m³ structure for 1,000 colonists → 125 m³ per person, which fits the “comfortable long‑term” category.
? 4. A table of volume flows
Used for ventilation and air‑handling calculations.
For example:
Flow Rate Equivalent
1 CFM 0.0004719 m³/s
36,000 CFM 16.99 m³/s
15 ACH (air changes/hr) for 4,078 m³ 61,170 m³/hr
This is exactly the kind of table you’d use to compute the 36,000 CFM fan load you mentioned.
? 5. A table of volume for storage (water, gases, food)
For example:
Resource Daily Use (1,000 people) Required Storage Volume
Water ~2,146 gallons/day ~8.1 m³/day
O₂ ~210 kg/day ~150 m³ at 1 atm
N₂ ~780 kg/day ~600 m³ at 1 atm
This is essential for sizing tanks and ISRU plants.
If you tell me which type of “volume table” you meant, I can build the exact table you need.
You might be asking for:
the volume table for the 125,000 m³ habitat,
the volume table for air changes,
or the volume table for water/CO₂ processing.
Just point me toward the one you want to work with next.
We need to be careful when using ISS numbers as they are based on a crew of typical 7 with short duration of more.
I did put your and my post through copilot and we have a long ways to go. for numbers as the fact that we are in a circular ring makes for much volume that due to a square layout is a problem.
You’re asking the right question—“what did we miss?”—because the big gap isn’t a single number, it’s a whole layer of overhead you haven’t turned into volume and power yet.
Let me pull it together and show you what’s still “un-costed” in your ring/Quonset concept.
1. Net vs gross volume
Sleeping volume vs habitat volume:
You sized 4‑person quarters at
125 m^3
2. For 1,000 crew, that’s 250 units →
31,250 m^3
3. That’s net bunk volume. What’s missing is the gross volume:
Walls, structure, insulation, MMOD/radiation shielding
Ducts, pipes, cable runs
Access corridors, stairways/ladders, airlocks, nodes
Once you add circulation and systems, net habitable volume is typically only a fraction of total pressurized volume.
2. Circulation, layout, and geometry penalties
Hallways and nodes:
Main spines, cross‑corridors, junction nodes, airlock lobbies, elevator/lift shafts (if any).
Egress routes sized for emergency evacuation of 1,000 people, not just “enough to walk through.”
Curved ring / Quonset geometry:
Rectangular modules in a curved ring waste edge volume.
You’ll have wedge-shaped gaps, unusable corners, and “dead” spaces that still need to be pressurized and serviced.
Doors and pressure breaks:
Every compartment boundary, fire zone, and pressure zone adds doors, vestibules, and clearances.
Those doors and vestibules have non‑trivial volume and lengthen the ring.
Right now, you’ve counted rooms but not the “streets” between them.
3. Support spaces you listed but haven’t volumized
You already named most of these—what’s missing is turning them into square meters and cubic meters:
Sanitation and hygiene:
Toilets, showers, sinks, grey/black water plumbing chases.
Central vs distributed bathrooms changes both volume and complexity.
Laundry and linen:
Washers, dryers, folding/clean storage, dirty storage, carts, and circulation space.
Galley and mess:
Kitchens, prep areas, dishwashing, food staging, serving lines, seating for some fraction of 1,000 at once.
Dry, refrigerated, and frozen storage sized for your resupply cadence.
Exercise and recreation:
Treadmills, resistance machines, free weights, VR/rec rooms, open space for group activities.
These are big volume hogs if you want them to be genuinely useful for 1,000 people.
Medical:
You quoted ~23–28 m² per monitored bed. For 50 beds, that’s ~1,150–1,400 m².
Add OR(s), imaging, pharmacy, lab, waiting, storage, staff areas, decontamination, and isolation rooms.
Greenhouse / food production:
You already estimated ~40,000 m³ for crops. That’s larger than the sleeping quarters volume.
You still need: nutrient mixing rooms, seed storage, tools, maintenance access, and buffer corridors.
All of these need to be explicitly sized and then placed in the ring geometry.
4. Systems volume (the “machine rooms” of the colony)
You’ve got good power and mass numbers for life support hardware—but not their physical footprint:
Life support equipment rooms:
CO₂ scrubbers, O₂ generation, water processors, tanks, pumps, compressors, filters, spare units.
Redundancy (N+1 or N+2) multiplies both mass and volume.
Power systems and distribution:
Switchgear, inverters, transformers, batteries, control rooms, cable trunks.
If you’re using nuclear, geothermal, or solar‑thermal, you also need heat‑to‑power conversion plant and interface spaces.
Thermal control:
Heat exchangers, coolant loops, pumps, manifolds, expansion tanks, radiator interface hardware.
Internal ducting and plenum spaces for air distribution.
Waste management:
Sorting, compacting, storage, recycling, and possibly incineration or feedstock processing.
1,000 people over years means industrial‑scale trash handling, not a closet with a bin.
These are often stacked in “utility decks” or dedicated rings that can easily rival or exceed the volume of living spaces.
5. Redundancy, spares, and logistics
Spares storage:
Filters, pumps, valves, electronics, suits, tools, structural repair materials, medical supplies, etc.
For a remote colony, spare parts inventory is huge—think warehouse, not cabinet.
Logistics and cargo:
Incoming cargo staging, unpacking, inspection, and distribution.
Outgoing waste or return cargo storage.
Emergency infrastructure:
Refuge rooms, extra air and water tanks, emergency rations, firefighting gear, emergency power and comms.
None of that is in the 125 m³/crew‑quarters math yet.
6. Human factors and “soft” space
This is the stuff that keeps 1,000 people sane over years:
Quiet zones and privacy:
Sound‑isolated areas, small meeting rooms, private work pods.
Workspaces and labs:
Offices, mission control, science labs, engineering shops, fabrication/repair bays.
Social and cultural spaces:
Common rooms, lounges, “town square” or auditorium, art/music spaces, spiritual/meditation rooms.
If you don’t allocate this up front, it gets squeezed into leftover corners—which is exactly what you don’t want in a long‑duration, high‑stress environment.
7. Power: you’ve got a floor, not a ceiling
You already see the gap:
Life support baseline:
~0.4–0.5 MW for CO₂ and water processing is just “keep them alive.”
Ventilation and thermal:
Tens to hundreds of kW more, depending on air change rates and radiator design.
Food production:
LED grow lights and associated systems push you into multi‑MW territory by themselves.
Everything else:
IT, comms, robotics, mining/ISRU, manufacturing, vehicles, construction, science.
So 5 MW for 1,000 people is a minimum survival plus a bit. Once you include food and industry, 10–15 MWe for a thriving settlement is very plausible.
The short answer
What you “missed” in the ring Quonset hut sizing is:
Circulation and geometry overhead (hallways, nodes, airlocks, curvature losses).
All the support spaces you listed but haven’t turned into area/volume.
Systems and utility volume for life support, power, thermal, and waste.
Redundancy, spares, and logistics storage.
Work, social, and psychological spaces beyond bunks and a mess hall.
Growth and contingency margin—you’ve sized for exactly 1,000, not 1,000 + failures + expansion.
If you want, we can take a next step and build a rough “volume budget” table—sleeping, hygiene, food, medical, greenhouse, systems, circulation—and see what the total ring volume really looks like.
You’ve done a very thorough first‑pass accounting of the power, air, water, and food loops for a 1,000‑person Mars settlement. The numbers you’re using are grounded in real ISS hardware performance, which is exactly the right way to avoid sci‑fi hand‑waving. What you’ve built is essentially a “minimum viable colony” energy budget.
But you asked: what did we miss?
A few major categories haven’t been included yet, and they matter a lot—some even more than the life‑support loops themselves. I’ll walk through the big ones, explain why they matter, and give you a sense of how they change the overall power and mass picture.
?️ 1. Thermal Control: The Hidden Giant
You accounted for radiator load from life support, but you haven’t accounted for habitat heating.
Mars is cold. Really cold.
Typical equatorial night: −70°C
Mid‑latitudes: −100°C
Worst‑case: −120°C
Even with insulation, a large pressurized structure leaks heat. On Earth, a well‑insulated building loses 30–50 W/m² in winter. On Mars, with a 100°C temperature delta, you’re looking at 100–200 W/m² unless you bury the structure.
For a 125,000 m³ habitat, even assuming a modest 2,000 m² exposed surface area:
200 W/m² × 2,000 m² = 400 kW continuous heating
That’s before you add greenhouses, workshops, airlocks, or tunnels.
If the colony uses multiple pressurized modules, the heating load can easily reach 1–2 MW thermal.
This is one of the biggest missing items.
?️ 2. Manufacturing, Fabrication, and Maintenance
A real colony must repair and build things. That means:
CNC machines
Metal 3D printers
Kilns and smelters
Plastics extrusion
Electronics repair
Welding equipment
Machine shops
Rover maintenance bays
Industrial equipment is power‑hungry.
A modest terrestrial workshop consumes 200–500 kW.
A small industrial fab shop: 1–3 MW.
A Mars colony needs the latter, not the former.
This is another multi‑megawatt category missing from your tally.
? 3. Transportation (Rovers, Haulers, Drones)
Electric rovers on Mars will be the backbone of logistics.
A single large pressurized rover (think “Mars bus”) uses:
50–100 kWh per sol
Peak draw: 20–40 kW
A fleet of 20–30 vehicles adds:
0.5–1 MW continuous equivalent power
If you include mining trucks or regolith haulers, the number jumps.
? 4. ISRU for Construction Materials
If the colony builds anything locally—bricks, concrete, glass, metals—then you need:
Regolith heating
Sintering
Electrolysis
Chemical processing
High‑temperature furnaces (1,000–1,600°C)
These processes are extremely energy‑intensive.
A small regolith‑to‑brick plant alone can require:
1–5 MW thermal
0.5–1 MW electrical
If you want to produce metals (iron, aluminum, magnesium), multiply that by 5–10.
This is one of the largest missing power sinks.
? 5. Food Processing, Refrigeration, and Storage
You accounted for crop lighting, but not:
Refrigeration
Freezers
Drying and milling
Cooking
Packaging
Waste composting
Greenhouse climate control (fans, pumps, humidity control)
A 1,000‑person food system on Earth uses 1–2 MW of electrical power.
Even if you optimize heavily, you’re still looking at 0.5–1 MW.
? 6. Medical Facilities
A real colony needs:
Imaging (X‑ray, ultrasound, maybe MRI)
Sterilization
Labs
Surgical suites
Pharmacy production
A small hospital consumes 300–800 kW.
?️ 7. Communications and Computing
You haven’t included:
High‑gain antennas
Data centers
Navigation beacons
Local servers
Robotics control systems
A modest data center for 1,000 people is 200–500 kW.
If you want AI‑assisted operations or simulation labs, add more.
? 8. Safety Systems and Redundancy
A Mars colony must have:
Backup life support
Backup power
Emergency shelters
Fire suppression
Airlock cycling
Pressure monitoring
Leak detection
Spare parts manufacturing
Redundancy typically adds 30–50% overhead to all life‑support power.
? 9. Waste Processing Beyond Water
You included wastewater, but not:
Solid waste
Plastics recycling
Composting
Hazardous waste
Medical waste
Sewage sludge drying
Methane capture (if used)
A small waste‑to‑energy plant is 200–400 kW.
? 10. Atmospheric Processing for N₂ and Ar
You noted the need for nitrogen but didn’t include the power cost.
To extract N₂ and Ar from Mars’ atmosphere:
You must compress the atmosphere from 0.6 kPa to ~100–200 kPa
Then cryogenically separate gases
This is extremely energy‑intensive.
A rough estimate: 1–2 MW continuous for a colony this size.
? 11. Mining and Raw Material Extraction
If the colony wants to be even partially self‑sufficient:
Water ice mining
Regolith excavation
Gypsum mining
Sulfur extraction
Iron ore mining
Basalt fiber production
Mining equipment is power‑hungry.
A small terrestrial mine uses 5–10 MW.
A Mars colony version might use 1–3 MW.
? So What’s the Real Total?
Your estimate for basic life support + food was ~12 MW.
Adding the missing categories:
Category Estimated Power
Heating 1–2 MW
Manufacturing 1–3 MW
Transportation 0.5–1 MW
Construction ISRU 1–5 MW
Food processing 0.5–1 MW
Medical 0.3–0.8 MW
Computing & comms 0.2–0.5 MW
Waste processing 0.2–0.4 MW
Atmospheric N₂/Ar 1–2 MW
Mining 1–3 MW
Redundancy overhead +30–50%
Realistic total: 20–30 MW electrical + 5–10 MW thermal
This is very close to the power consumption of a small town or industrial campus on Earth.
? The Big Picture
Your original conclusion—that a Mars colony ends up looking like a high‑tech American town in terms of per‑capita energy use—is absolutely correct.
But the full system is larger:
Life support is only ~30–40% of total power.
Industry, construction, and heating dominate the rest.
A 1,000‑person Mars settlement is basically:
A small city
A mining operation
A farm
A factory
A research base
A hospital
A power plant
A water treatment facility
All rolled into one.
If you want, I can help you:
Build a full power budget spreadsheet
Model different energy architectures (geothermal vs nuclear vs solar‑thermal)
Estimate radiator area, mass, and heat rejection
Size the nitrogen extraction plant
Model food production with mixed crops
Estimate habitat insulation requirements
Just tell me where you want to take this next.
Good news from the numbers run for just the sleeping part of the ring. We were off by a factor of 2-4 time the number of volume required for building just that part of the structure.
Like wise the greenhouse for soil use would have been 5 time the area as its not making use of vertical height, energy was also up but within the margin I had guessed at.
The hydroponic portion was still off even after i doubled what nasa had but only by another factor of 2 times.
So you can hopefully this would not been good.
I have more numbers to work out still but due to needing to have more power beyond the 10 meg watts should have a couple more for the ability to expand.
Still lots of other stuff to compute.
In discussions you will need to put the opinions with in the topics and then do the branch for what you feel is off topic. It allows for those reading to understand the topics fishbone discussions that are being found and created. This happened to some degree with the large ship.
So its expected to have many related topics that are the branches in which some support the original while others are separate projects to be under taken that may or may not support the actions to which is the goal.
Take for instance power requirement for crew life support and then what power that is required for the green house for food plus recycling of co2 to oxygen which each are branches in the ring structure we are trying to come up with.
These are both power but its the sum of each which must be achieved.
So right now we are trying to get to the volumes as required in total for each portion of the ring Quonset shaped simple from making the first section unit until finished and internal work can be done for how each portion is used.
Please continue in discussion what you think are off topics but make the efforts to bring those fishbone out include your thought so that the project lead can read them as much as possible in one location root topic to the branches.