Tuesday, October 18, 2016

Inflatable Biospheres for the New Frontier

X-Ray of a notional regolith shielded 16 meter in diameter biosphere (Credit: NASA)
by Marcel F. Williams 

At least 0.1 g is required for  unaided human traction when walking  on a low gravity world. And some studies suggest that some individuals may have difficulty-- non-visually-- perceiving up and down under a gravity that is less than 1.5 g. There are also some questions as to whether rigorous exercise will be enough to prevent human bones from losing  significant amounts of calcium  under low gravity environments that could cause bone fractures-- especially when returning to Earth.

Planets and Moons within the solar system that are potentially suitable for human colonization:


surface gravity relative to the Earth: 0.17g

diameter relative to the Earth: 27.3%

surface area relative to the Earth: 7.4%


surface gravity relative to the Earth: 0.38g 

diameter relative to the Earth: 53.1%

surface area relative to the Earth: 28.4%


surface gravity relative to the Earth: 0.38g 

diameter relative to the Earth:  38.3%

surface area relative to the Earth:  14.7%


surface gravity relative to the Earth: 0.13g 

diameter relative to the Earth:  37.8%

surface area relative to the Earth:  14.3%

Note: Land area comprises ~ 29% of the Earth's surface with ~71% covered by water

But even if future human colonist  can physically and psychologically  adjust to living and reproducing  on the surfaces of low gravity worlds, its  unlikely that such individuals would spend more than ten percent of their time outside of the protective envelope of their pressurized habitats. Even on the surface of Mars, during solar minimum conditions, cosmic rays could expose colonist to levels of radiation exceeding that legally allowed for radiation workers on Earth in just two months. And on extraterrestrial worlds without atmospheres such as the Moon, Mercury, and Callisto,   pressure suits with more massive radiation shielding would be required to protect the human brain and cardiovascular system from the enhanced dangers of  heavy ions.

Radiation levels on the Moon and Mars

Surface of the Moon:

38 Rem - annual amount  of cosmic radiation on the Lunar surface during the solar minimum

11 Rem - annual amount of cosmic radiation on the Lunar surface during the solar maximum

Surface of Mars:

33 Rem - annual rate of cosmic radiation on the surface of Mars beneath 16 gm/cm3 of Martian atmosphere during the solar minimum

8 Rem - annual rate of cosmic radiation on the surface of Mars beneath 16 gm/cm3 of Martian atmosphere during the solar maximum

Pressurized habitats in extraterrestrial environments can easily be protected from dangerous levels of cosmic radiation and their  heavy nuclei component with just a few meters of  regolith or several meters of water.  However, the fetuses of pregnant women and children growing up on   extraterrestrial  worlds are substantially more vulnerable to higher levels of  radiation exposure and will probably have to spend a lot more time within the protective confines of pressurized habitats.  

Internal configuration of a  lunar habitat derived from  SLS propellant tank technology. A  regolith wall composed of kevlar sandwiched between eight rigid aluminum panels is deployed around the habitat cylinder and filled with regolith to protect astronauts from cosmic radiation, micrometeorites, and fluctuating temperatures on the lunar surface. The airlocks are derived from ETLV propellant tank technology.

So it appears likely that future colonist  living on the surfaces of extraterrestrial worlds will  probably have to spend at least 90% of their time inside of radiation protected pressurized  habitats. Therefore, pressurized habitats that are spacious enough  and aesthetically comfortable enough for people not to mind spending  90% of their lives living and raising their families in indoor environments will probably be necessary.

The deployment of huge— inflatable biospheres— could provide a large variety of aesthetically spacious and comfortable environments for colonist on extraterrestrial worlds-- especially if the upper half of a biosphere is utilized to provide open spaces for parks and recreational activities. 

NASA researchers have previously proposed deploying a 16 meter  biospheres to the lunar surface weighing 2.2 tonnes with a safety factor of five. The mass of the inflatable material increases in proportion to the mass of the atmosphere that it envelopes.   Here, I propose using the SLS in combination with large cargo landing vehicles to deploy 28 tonne Kevlar-29 biospheres to the surfaces of the Moon and Mars  with an inflated  pressurized volume of 33,510 m3 and a diameter of 40 meters.  Nitrogen and oxygen environments could be provided in such pressurized biospheres with an Earth-like  14.7 psi (101.3 kPa) of pressure similar to atmosphere aboard the ISS— with a safety factory of four.

Notional Lunar Cargo landing vehicle that could transport regolith habs and deflated Kevlar biospheres to the lunar surface.

An extraterrestrial cargo landing vehicle with 30 tonnes of LOX/LH2 propellant could deploy a deflated 28 tonne biosphere to the surface of the Moon from EML1. Similar biospheres could be deployed to the surface of Mars using lunar landing vehicles coupled with  ADEPT deceleration shields currently being developed by NASA. An ADEPT deceleration shield would be capable of deploying up to 40 tonnes of cargo to the Martian surface.

Notional ADEPT deceleration shield for deploying payloads to the Martian surface. (Credit: NASA)

Possible ADEPT architectures that could deliver up to 40 tonnes of cargo to the Martian surface. (Credit: NASA)

On Mars, the nitrogen component for the pressurized atmosphere of the biosphere could be extracted from the Martian atmosphere which contains nitrogen at  approximately 1.89%. On the moon, nitrogen would have to be derived from possible ammonia deposits at the lunar poles or exported from Earth.

The oxygen component of the biosphere's pressurized atmosphere could be derived from the electrolysis of water extracted from ice deposits from the lunar poles or directly derived from the pyrolysis of lunar regolith. Oxygen derived from water on Mars could be derived from various regions on Mars that are rich in water ice.

Notional 40 meter in diameter regolith bag shielded Lunar biosphere connected to two Lunar Regolith habs
Since the top half of a Lunar  biosphere would be above the surface,   the upper hemisphere would be protected from micrometeorites and extreme temperature fluctuations by covering the upper exterior dome with regolith bags. Regolith bags would also protect humans inside from heavy nuclei while reducing overall cosmic radiation exposure to appropriate levels. Constructing a supporting geodesic dome inside of the upper dome area of the biosphere   could be  protected from a rapid collapse if the Kevlar walls are punctured.   Light fixtures could even be placed on the internal geodesic dome for internal illumination.

Notional 40 meter in diameter biosphere covered with a water filled biodome to protect inhabitants from cosmic and UV radiation. Since there would be no danger from micrometeorites on Mars, regolith shielding the upper dome would be unnecessary.
On Mars, a transparent water filled biodome could be placed on top of the top hemisphere of a transparent Kevlar biosphere to protect the inhabitants from radiation while still allowing in sunlight.  The transparent water filled biodome could be embedded a transparent UV protective film to shield inhabitants from ultraviolet radiation.  This would allow inhabitants occupying the top half of the biosphere to enjoy the Martian sunlight during the day and to view the stars at night. Since the atmosphere of Mars is so thin (~ one percent of the Earth’s atmosphere) the high heat conductivity from the thick Earth-like pressurized biosphere would keep the liquid water in the external water dome from freezing. The water dome could be  replaced if it becomes  soiled with dust from periodic dust storms on Mars or an enormous tent could be  temporarily placed over the water dome to   protect it from being soiled during dust storms. 

The upper half of a biosphere could be used for open space recreational activities and sports while the lower, underground, half of the biosphere could be used for housing and commercial structures.  But,  homes and apartment buildings similar to those found on Earth could also be assembled and  placed on the bottom surface of the top half of the biosphere, if desired,  along with grass and trees and other foliage to enhance the aesthetic environment.
X-ray of a 40 meter in diameter lunar biosphere with a 20 meter circular swimming pool. Multiple levels of habitats could be constructed in the bottom half of the biosphere with some base support by lunar regolith. A central area could utilize scissor elevators to access different floor levels. 

Some biospheres could be specifically dedicated for agriculture, providing space in the upper half for grazing animals used for milk and meat and cheese while the lower half could provide compartments for hen houses and aquaculture. For growing crops, the top half could be used grow fruit trees: apple trees, orange trees, cherry trees, peach trees, pear trees, lemon trees, etc. while underground compartments in the bottom half of the biosphere could be used for growing corn, potatoes, wheat, rice, tomatoes, lettuce, yams, sugar beets, etc.

Much thinner but larger  biospheres could also be deployed to the surfaces of extraterrestrial worlds. But once they are inflated, they would have to be internally thickened with additional adhesive layers of Kevlar in order to provide the same safety factor as the smaller domes. This would probably require the deployment of modular Kevlar manufacturing factories on the surface of these worlds by cargo landing vehicles. But this would make it possible to deploy biospheres that are 100 to 200 meters in diameter in the near future. Once the Moon and Mars become fully industrialized worlds with significant populations then  Kevlar biospheres that are 300 meters to 1000 meters in diameter might eventually be deployed. 

Mass of a Kevlar-29 biosphere for an atmospheric pressure of of  14.7 psi (101.3 kPa) with a structural safety factor of four.

40 meters in diameter - 28 tonnes

100 meters in diameter - 430 tonnes

200 meters in diameter - 3438 tonnes

300 meters in diameter - 11,600 tonnes  

1000 meters in diameter - 430,000 tonnes 

Biospheres as large as 200 meters in diameter could allow colonist to enjoy familiar sporting activities such as America football and baseball and international soccer. Some biospheres could be specifically designed for sporting activities, allowing baseball, American football, and international soccer to be played on the bottom surface of the top half of the biosphere while the bottom half, extending nearly 100 meters below, could easily accommodate large variety of  underground stadiums for playing basketball,  hockey, volleyball, and  tennis while also being able to accommodate a few  Olympic sized swimming pools.

Dimensions for professional sporting activities

Volleyball Court - 9 meters by 18 meters

Doubles Tennis Court - 10.97 meters by 23.77

Basketball Court -  15 meters by 29 meters

Olympic sized swimming pool - 25 meters by 50 meters

International Hockey Rink - 30.5 meters by 61 meters

NFL Football field 48.76 meters  by 110 meters (110 m)

Baseball outfield fence from home plate -  91 meters  to 128 meters

But biospheres that are only 100 meters in diameter on the Moon could be spacious enough to allow people to don wings to fly within the upper biodome or even withing the entire biosphere.  This could perhaps initiate of a new era of aerial extraterrestrial sports! Who knows! Someday flying inside of  Lunar biospheres or watching Lunar Aeroball could be a major attraction for space tourist from Earth!

Links and References

Inflatable Habitation for the Lunar Base

The Economic Viability of Mars Colonization

The Architecture of Artificial-Gravity Environments for Long-Duration Space Habitation

Protecting Spacefarers from Heavy Nuclei

Landing on Mars with ADEPT Technology

ADEPT Technology for Crewed and Uncrewed Missions to the Planets

Living and Reproducing on Low Gravity Worlds

Cosmic Radiation and the New Frontier

Pioneering and Commercial Advantages of Permanent Outpost on the Moon and Mars

Monday, August 29, 2016

Protecting Spacefarers from Heavy Nuclei

Buzz Aldrin on the surface of the Moon (Credit: NASA)
by Marcel F. Williams

In July of 2016, researchers on the health of NASA astronauts dropped a bombshell concerning the cardiovascular mortality of the Apollo Lunar astronauts. Despite the enhanced levels of radiation exposure by astronauts at LEO and beyond LEO, there were no indications of increased levels of cancer for space faring astronauts relative to people living on Earth. The research also showed no significant increase in cardiovascular deaths (the leading cause of death for Americans) relative to people living on the Earth's surface. Surprisingly, the research did reveal that the  frequency of  cardiovascular deaths of Apollo Lunar astronauts was four to five times higher than in LEO astronauts and in NASA astronauts that have yet to have the opportunity to fly into space.

Although astronauts are exposed to enhanced levels of radiation beyond the Earth's magnetosphere, astronauts at LEO are completely shielded from the most lethal component of cosmic radiation, heavy nuclei (heavy ions), most of the time.

Cosmic radiation beyond the Earth's surface (Annual levels)

Low Earth Orbit (LEO): 20 Rem (solar maximum) to 40 Rem (solar minimum) 

Interplanetary Space: 28 Rem (solar maximum) to 73 Rem (solar minimum)

Surface of the Moon: 11 Rem (solar maximum) to 38 Rem (solar minimum) 

Surface of Mars: 8 Rem (solar maximum) to 33 Rem (solar minimum) 

Cosmic rays are relativistically accelerated particles  resulting from the  explosions of ancient super nova mostly within the galaxy. Approximately 87% of cosmic radiation particles are composed of  protons;  12% are alpha particles derived from helium atoms.  But approximately, 1% of the population of cosmic rays are composed of heavy nuclei, large ionized accelerated particles derived from heavier nuclei such as carbon, oxygen, silicon, and iron.

Most of the protons and alpha particles from cosmic radiation pass harmlessly though the vacuous space between the atoms of the human body. But the relentless rain of cosmic radiation inevitably results in impacts upon our corporeal components. Heavy nuclei, on the other hand,  have relatively-short interaction lengths when encountering matter. Such interactions with human tissue can be significantly deleterious DNA molecules and can pose a challenge to cellular repair. 

It has been estimated that during a future-- 6 month-- journey to Mars, the nucleus of  one out of every three  cells in the human body would receive at least one hit from a cell damaging heavy ion. With the inability of neurons to repair themselves, it has been predicted that a mere six months of heavy nuclei exposure could potentially destroy a third of the total neurons in the central nervous system.

Approximately, 15 to 20 g/cm2 of mass is required to effectively stop the penetration of heavy ions. However, its estimated that Astronauts aboard the Apollo Command Module (CM), were only provided with about 10 g/cm2 of radiation shielding. And some parts of the Command Module were more heavy shielded than other areas of the CM. The window areas were particularly thinly shielded which would have allowed heavy nuclei to easily penetrate into the CM interacting with the body tissues of the astronauts. 

Astronauts on there way to and from the Moon experience retinal flashes aboard the CM when they were outside of the Earth's magnetosphere. And NASA believes that this was the result of heavy nuclei traversing the human retina. Retinal flashes occurred at an average frequency of every 2.9 minutes which sometimes made sleeping a challenge for the astronauts.  At least 90% of the Apollo astronaut's exposure to heavy nuclei bombardment occurred during their voyage to and from the lunar surface and not on the lunar surface itself.  

But there was even less shielding against heavy nuclei for astronauts when the were aboard the Lunar Module (LM) and when they were on the surface of the Moon. However, half of the heavy nuclei would have been blocked by the mass of the Moon when astronauts were on the lunar surface.

 Since the cardiovascular health of  Apollo Lunar astronauts relative to humans on Earth has now been shown to be significantly effected after less than two weeks beyond the Earth's magnetosphere, its now clear that astronauts in the future will have to be adequately protected from heavy nuclei when traveling beyond the magnetosphere to the Earth-Moon Lagrange points, the lunar surface and on interplanetary journeys to Mars. 

Since there is virtually no atmosphere on the surface of the Moon, lunar astronauts venturing outside of their regolith shielded habitats would be exposed to the relentless penetration of heavy nuclei. Lunar astronauts would, therefore, have to wear pressure suits with enhanced shielding (~ 20 g/cm3). Helmets could easily be shielded with iron 2.6 cm2  thick.  But the helmet visor for lunar excursions would probably have to be composed of lead iron glass nearly 5 centimeters thick. Thickening the rest of the lunar pressure suit with 2.6 centimeters of iron shouldn't be too difficult. The increased weight of the iron shielded pressure suit should be easily mitigated by the Moon's 1/6 gravity. 

On the surface of Mars, the thin carbon dioxide atmosphere is still thick enough (~ 15 g/cm2) to shield astronauts on the surface from any direct interaction from most heavy nuclei. So enhanced shielding of pressure suits on the surface of Mars will probably not be required. 

Notional reusable EUS with an internally water shielded  Cygnus habitat module rendezvousing with an EUS derived  propellant producing water depot at LEO
Since traveling from LEO to other important regions within cis-lunar space can take several days, its pretty obvious that crewed spacecraft traveling within cis-lunar space will have to be  appropriately shielded against heavy nuclei. However, substantially increasing the shielding requirements of the Orion spacecraft to protect against heavy ions  could make it to heavy for the   ATV derived  Service Module (SM) to push the Orion capsule on a trajectory return to Earth. 

Delta-v to important destinations within cis-lunar space

Earth surface to LEO - 9.3 km/s to 10 km/s

LEO to EML1 - 3.77 km/s (~3 days)

LEO to EML1 - 4.5 km/s (~2 days)

LEO to EML2 - 3.43 km/s (~8 days)

LEO to EML2 - 3.95 km/s (~4 days)

Lunar surface to EML1 - 2.52 km/s (~3 days)

Lunar surface to EML2 - 2.53 km/s (~3 days)  

Notional ETLV-2 crew landing vehicle with internal radiation water shielding compartment.

However, if the ATV derived SM is replaced with a reusable EUS that uses IVF technology and orbiting water/propellant depots, then the Orion capsule  could be coupled with an appropriately water shielded Cygnus habitat.  The water shielded (20 cm thick) area within the Cygnus habitat could be dumped just before the final trajectory burns into the desired cis-lunar destinations. Water could be replenished for the Cygnus habitat for return trips at the water/propellant depots. 

Notional reusable ETLV rendezvousing with an EUS derived  propellant producing water depot at LEO

In the long run, however, it would be even more fuel efficient if an Extraterrestrial Landing Vehicle (ETLV) were also used as an orbital transfer vehicle between LEO and the Lagrange points. Again, 20 centimeters of water shielding could be provided with an designated area of the ETLV and then dumped before the final trajectory burns to the Lagrange points, Low Lunar Orbit, or to LEO. While water shielding  the ETLV crew transport area before its departure from the lunar surface would require more propellant at take off, there should be no shortages of lunar derived oxygen and hydrogen propellant on the lunar surface. 

Notional reusable ETLV rendezvousing with an EUS derived  propellant producing water depot at EML-1.

And ETLV using a ADEPT or HIAD deceleration shield could dump its water shielding just before entering Mars orbit or descending from from Mars orbit to the surface of Mars. Returning to Mars orbit, an ETLV could dock with a Mars orbiting water/propellant depot at Low Mars Orbit to add water shielding and propellant to the vehicle in order for it to return its astronauts to an interplanetary spacecraft parked in High Mars orbit.

Notional reusable ETLV returning from the martian surface rendezvousing with an EUS derived  propellant producing water depot at Low Mars Orbit before returning to High Mars Orbit. 

Protecting astronauts from the deleterious effects of heavy ion bombardment beyond the Earth's magnetosphere will increase mass shielding and propellant requirements for crewed spacecraft. But  the utilization of extraterrestrial water and regolith resources should make it easy and affordable to protect the health of astronauts from the dangers of heavy nuclie in the New Frontier.  

Links and References

 The SLS and the Case for a Reusable Lunar Lander

Monday, July 11, 2016

Substantially Enhancing the Capability of the SLS Architecture by Utilizing EUS Derived Propellant Depots and Reusable Orbital Transfer Vehicles

Left: Orion space capsule with hypergolic fueled Service Module; right:  notional Orion spacecraft with a reusable EUS derived orbital transfer vehicle.  
It now appears that Congress will direct NASA to return Americans to the surface of the Moon in order to prepare for future crewed journeys to the surface of  Mars. But the Moon could prove to be much more than just a beyond LEO testing ground for astronauts and components.

At minimum, an interplanetary round trip to the Red Planet would require several hundred tons of  water for drinking, washing, food preparation, radiation shielding, the production of air, and for the production of liquid oxygen (LOX) and liquid (LH2)  for rocket propellant.

Supplying the water needed for an interplanetary spacecraft parked at LEO  would require a delta-v ranging from  9.3 km/s to 10 km/s from the Earth's surface. Minimum energy launch windows during the 2030s would require an additional delta-v ranging from 3.59 km/s to 4.81 km/s for Trans Mars Injections (TMI)  that could send humans to Mars in less than a year.

But at different locations within cis-lunar space, substantially lower levels of delta-v could be taken advantage of in order to launch cargo and crew into a Trans Mars Injection. And these interplanetary launch points within cis-lunar space are most easily accessible from the lunar surface rather than from within the Earth's deep gravity well. So utilizing lunar ice resources could greatly reduce the cost and the complexity of sending humans to Mars.

Delta-v to important destinations within cis-lunar space

Earth surface to LEO - 9.3 km/s to 10 km/s

LEO to EML1 - 3.77 km/s (~3 days)

LEO to EML1 - 4.5 km/s (~2 days)

LEO to EML2 - 3.43 km/s (~8 days)

LEO to EML2 - 3.95 km/s (~4 days)

Lunar surface to EML1 - 2.52 km/s (~3 days)

Lunar surface to EML2 - 2.53 km/s (~3 days)

Delta-v from cis-lunar space to Trans Mars Injection

LEO to TMI (2030s) - 3.59 km/s to 4.81 km/s

EML1 to TMI (2030s) - 1.04 km/s to 1.3 km/s

Because of its shorter travel times from Earth orbit,  EML1 would appear to be the optimal region for locating Deep Space Habitats (DSH), reusable lunar shuttles,  propellant manufacturing water depots that receive water from the lunar surface and for launching cargoes and crew on interplanetary journeys to the orbits of Mars and Venus.

A delta-v of   3.77 can transport crews to EML1 in approximately 4 days. It would require 3.95 km/s to travel to EML2 in 4 days but 8 days of travel and radiation exposure would be required to take advantage of a lower delta-v to EML2 at 3.43 km/s. A delta-v of 2.52 km/s would be required for a 3 day journey between EML1 to the lunar surface. 2.53 km/s would be required for a similar journey between EML-2 and the lunar surface. The significant presence of habitats and depots and reusable vehicles at EML-2 could also interfere with future radio astronomy on the back side of the Moon.

Taking full advantage of polar ice resources on the Moon would require a space architecture that utilizes orbiting depots to supply water and propellant to reusable interplanetary spacecraft and landing vehicles. Some space advocates have argued that propellant depots make heavy lift vehicle's an unnecessary expense. However, heavy lift vehicles would make it possible to easily deploy propellant manufacturing water depots to  EML1  for crewed interplanetary journeys to the orbits of Mars and Venus.

Similar depots located at LEO could also enable large payloads  originally deployed  to LEO by heavy lift vehicles to be later  deployed by reusable orbital transfer vehicles practically anywhere within cis-lunar space.

Expendable EUS for SLS launch vehicle (Credit: NASA)

In 2018, NASA will launch the first SLS heavy lift vehicle with an unmanned Orion space capsule and a hypergolic fueled Service Module and an interim upper stage. But NASA currently envisions crewed SLS launches in the 2020s to include an Orion space capsule with a hypergolic fueled Service Module and a large LOX/LH2 fueled Exploratory Upper Stage (EUS). 

But two of the principal companies (Boeing and Lockheed Martin) currently developing the SLS/Orion architecture are also--  privately developing-- an alternate space architecture through their joint company, the  ULA (the United Launch Alliance). In this alternate architecture, the ULA  will utilize their emerging  IVF (Integrated Vehicle Fluids ) technology to deploy a reusable ACES upper stage that could eventually utilize LOX/LH2  propellant depots for travel within cis-lunar space during the 2020s. IVF technology allows a spacecraft to utilize hydrogen and oxygen ullage gases for attitude control, power production, and for autogenously pressurizing propellant tanks, eliminating  the need for hydrazine and liquid helium. 

NASA could greatly enhance the capability, efficiency, and the safety of the SLS/Orion architecture by taking full  advantage of the ULA’s  emerging IVF  technology. While there's no reason to stop Boeing from developing the EUS as an expendable upper stage for the SLS, it would still be technologically advantageous for NASA to commission the ULA to use its IVF technology to convert some EUS vehicles into  reusable orbital transfer vehicles and others into propellant depots.

EUS derived propellant manufacturing water depot and reusable Orion orbital transfer vehicle.

 An SLS/Orion architecture utilizing EUS derived Orbital Transfer Vehicles (OTV-125) and EUS derived propellant producing water depots (WPD-OTV-125) would no longer require the expense and the enhanced risk of launching astronauts on top of a super heavy lift vehicle. So for beyond LEO missions in the 2020s, under this scenario, astronauts would simply be transported to LEO by Commercial Crew vehicles that would have already been in operational service since 2018.

Once in orbit, the commercial crew capsule would dock directly with the Orion-OTV-125 reusable spacecraft, transferring its crew aboard the Orion for its beyond LEO mission. Alternatively, a crew capsule could dock at the port of  a space station where the Orion-OTV-125 would also be docked at a different port. Both scenarios would mean that the ATV based hypergolic Service Module being manufactured by the Europeans would not be required for crewed beyond LEO missions, and would only be used once during the 2018 test mission. So only  the domestically manufactured Orion capsule being developed by Lockheed Martin would be preserved in this architecture.

A single SLS Block I cargo launch could be used to deploy two WPD-OTV-125 depots to LEO plus a two 1 MWe solar arrays. With at least 35 tonnes of propellant, one of the water/propellant depots could self deploy itself to EML1 along with its 1.4 to 2.8  MWe solar array. Another basic SLS Block I cargo launch could be used to deploy two reusable Orion-OTV-125 vehicles to LEO. But once this reusable depot based extraterrestrial architecture is deployed by the SLS,  private commercial launch vehicles will only be required to conduct crewed beyond LEO missions. This will allow the SLS to be used exclusively as a cargo launcher for the deployment of large and heavy spacecraft and habitats and other large and heavy structures.

Notional lunar water ice extraction, storage, and LOX/LH2 manufacturing facility.

Water for the propellant manufacturing orbital depots could be regularly supplied to LEO and to EML1 from commercial launch vehicles (Atlas V, Delta IV heavy, Falcon 9, and the future Falcon Heavy, Vulcan, and Vulcan Heavy vehicles).  However, once water is being manufactured on the lunar surface, water transported to EML1 would be supplied  exclusively from the lunar surface.

Since the  Orion-OTV-125 would derived from the EUS, it would be capable of accommodating up to 125 tonnes of propellant. But less than 35 tonnes of propellant would be required for an Orion-OTV-125 to transport its crew to EML1. And an equal amount of fuel would be needed to return astronauts to LEO. No aerobraking would be required.

A reusable Extraterrestrial Landing Vehicle (ETLV) would transport astronauts from EML1 to the surface of the Moon and back  to EML1 with a single fueling of LOX/LH2. A single SLS Block I cargo launch could deploy three ten tonne ETVL-2 vehicles to LEO, each with enough propellant to travel to EML1. The ETLV-2 could also serve as an back up OTV in case one or both of the Orion-OTV-125 vehicles becomes inoperable.

Until new RS-25 engines are in production, perhaps by 2021 to 2023, NASA will only be able to launch four SLS vehicles. And one of those launches will be an unmanned test launch in 2018. So after 2018, only three SLS launches will be possible before the RS-25 engines go into production.

Notional EUS derived propellant manufacturing water depot @ EML1 after refueling a reusable Extraterrestrial Landing Vehicle.

But  just three basic  SLS Block I cargo launches would be required to deploy a reusable EUS derived cis-lunar transport architecture (WPD-OTV-125, Orion-OTV-125, and the ETLV-2) capable of transporting humans to EML1 and to the lunar surface and back.

However, the deployment of the lunar landing vehicles could be delayed until the new RS-25 engines are in production. This would allow NASA to use their last four Space Shuttle Main Engines to be used to launch a DHS (Deep Space Hab) to EML1. An SLS propellant tank derived habitat with over 510 cubic meters of pressurized habitable volume would have a dry weight of 22.4 tonnes. So in theory,  a single SLS Block I cargo launch could be used to deploy two or three pressurized habitats to LEO. A partially fueled Orion-OTV-125 could then be used to transport one of the pressurized habitats to EML1.
SLS propellant tank derived habitat (Credit: NASA).

This would leave one or two pressurized habitats at LEO with a combined pressurized habitable volume exceeding that of the ISS! All of that would be achieved with  a single SLS launch and a reusable propellant producing water depot architecture routinely and sustainably  supplied with water from commercial launch vehicles.

Links and References

Moon first, then Mars? Congress moves to shift space priorities

The return to the moon, Lori Garver, and the price of ambition

Lori Garver Questioned Astronauts about NASA's Next Destination?

Seeing the end of Obama’s space doctrine, a bipartisan Congress moves in

What about Mr. Oberth

Human Lunar exploration architectures

Earth Departure Options for Human Missions to Mars

A Study of CPS Stages for Missions beyond LEO

Deep Space Habitats

First Human Voyages to the Martian Moons Using SLS and IVF Derived Technologies

Congress Requires NASA to Develop a Deep Space Habitat

UltraFlex Solar Array Systems

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Destination Moon

glennwsmith said... Very nice, Marcel. This is one of the most beautifully put together, forward-looking, and yet also understated videos which I've yet seen from a major space agency -- and it just goes to show that there's a lot of good material out there if you know where to find it.

G. W. (Glenn) Smith


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