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BART/Muni California High-Speed Rail down Geary and 19th Avenue 2.0

Thanks for the insight! (@kieran)  I am an SF rent HUD/Vash refugee as in they refused to allow me to transfer my housing voucher back to SF so I have been away for a long time. Yes, I was not suggesting sharing of tracks for any of these systems and I can not imagine high-speed rail wanting to do this unless there was an economic argument for at least 1 station somewhere along the Geary to south route.Also, it would seem Highspeed rail would want to be compensated for a portion of its tunneling costs.It seems to me I saw BART maps (2050) that show a BART out to the beach and then south but I like 19th street better for all the reasons you mention.The agency with bond selling powers or by agreement could pay for more upfront costs or the lead agency and the other agency could pay the others. The 19th street above ground might cost a lot less but the mayhem and noise from operations seem to rule that out.you could excavate 19th and infill this system perhaps? So my main question is was MUNI/Bart under market street twice as expensive?when BART was set up SF Muni got that for free! My thoughts are Geary and points south drives more passengers to both systems and that would increase that 15% revenue to both systems. Ummm just now I realized why you do want high-speed rail down part of Geary or some other route; that some day you will have a Sacramento to SF connection that’s when BART could share systems such as a light rail infill between SF and Sacramento 🙂

http://hoodline.com/2016/12/sf-transit-agencies-say-brt-improvements-will-set-stage-for-future-rail-line-on-geary

Article above by Carrie Sisto @http://twitter.com/carries1981 

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Tunnel Arbitrage to fund a Geary street MUNI/BART subway

I to enjoy blogging about bay area mass transit and light rail and subways, most of my blogging as to about the economics of tunneling for multiple systems such as MUNI/BART under Market street. What is that economics? digging two or more tunnels would cost more right? but would cost twice as much or less.Can two or more agencies share costs and/or loan to one another parts of the costs? I call this on my blog TUNNEL ARBITRAGE 🙂 This would be shared costs of some percentage (?) and one agency owes the other payment on bonds or future taxes for a portion of that percentage. California high-speed rail even proposed private-public partnerships where the infrastructure and even the rolling stock might be leased from a for-profit firm, I discuss my response to their RFP here https://yellowdragonblog.com/2015/07/28/utilizing-a-esop-to-capitalize-infrastructure-for-california-high-speed-rail/ As to the Tunnel arbitrage I discuss that here https://yellowdragonblog.com/2014/11/19/vtabart-and-california-high-speed-rail-potential-synergies/ My thoughts are a common tunnel under Geary for MUNI/BART/CHSR need not run all the way to the beach so MUNI would borrow and/or share the tunnel costs with BART to some well-studied midway point and head south.South might mean 19th avenue and even here this tunnel could be a two-decker with MUNI?

More discussion here http://hoodline.com/2016/12/sf-transit-agencies-say-brt-improvements-will-set-stage-for-future-rail-line-on-geary

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A Grand Unified AO; A novel decadal survey proposal to explore the ice giants and more

A Grand Unified AO; A novel decadal survey proposal

Conduct a single master AO for a build of 4 spacecraft and 5-atmosphere probes with a goal of commonality in spacecraft avionics and bus design and common probe and probe attachment points.Cost engineering is a must as a part of this master AO.Secondary AO’s are done to determine 5 PI’s and teams and 5 PI’s for the probes.Mariner Mark 2 was an early concept along these line of thought.

decadal survey wish list

5 mass-produced outer planet atmosphere probes

Jupiter(flyby)

Saturn(flyby)

Titan

Uranus

Neptune

There is an opportunity for a Saturn flyby on the way to Uranus for a Saturn/titan probe delivery but perhaps this is also an opportunity for a Saturn orbital mission with a Titan escape to Uranus with the same spacecraft okutsu_cassini_saturn_escape

The grand Unified AO would require proposers to accept language that atmosphere probes be serially produced all with the following decadal survey requirements, http://www.lpi.usra.edu/opag/meetings/aug2016/presentations/day-2/Hofstadter.pdf Page 9

The mass of the heat shield for all of the serially produced probes is subject to trade and cost engineering study.Does it cost less to produce one heat shield of the same weight with a weight penalty to some destinations?

Hofstadter et al appear to have omitted not only multiple planet orbiters but also Saturn flybys en route to Saturn page 22 to 23 and page 15 ;

“Dual-planet mission of interest
because of its high science
value, but not considered for
next study due to expected
high cost.”

 We acknowledge multiple planet orbital missions will be expensive in operational costs, however, Hofstadter et al do a disservice by dismissing a look at the idea, as already mentioned they did not look at Saturn-Uranus duel orbital missions with 1 spacecraft.

Indeed we have used the OPAG forum to suggest 1 spacecraft could perform a combined Enceladus sample return and LUCY trojan asteroid tour; this calls for an early earth flyby with LUCY aerodynamics after a 4 year Saturn mission.Could this mission carry the Saturn probe as well?

5-atmosphere probes on only 3 to 4 missions might be a mission design problem, however, a creative set of competitive bids on a master AO might solve this.There are options to think about.

Here,

Commercial bid to the industry but also to labs a planetary AARM derived stage.Must meet planetary specs (decades in space) there should be a commercial R & D match of 40% in exchange of flights if a win.there should be two winners or more(a fly off)these are delivered to the master AO as government equipment not charged against the mission cap

(A)One ARRM derived SEP stage carries 3-atmosphere probes to Jupiter/Saturn/Uranus

(B)One ARRM derived orbiting spacecraft does the Saturn/Enceladus/LUCY mission using SEP and Titan Saturn escape(spacecraft # 1)

(C) One spacecraft is ARRM derived SEP to Saturn with Titan flyby escape to Uranus, I see an opportunity here, A Titan orbit radar imaging experiment could image Uranus moons(subsurface ?)(spacecraft #2)

(D)Saturn flyby to Neptune with Saturn probe ( spacecraft #3)My blog has proposed the outer planet SEP might have enough power to run its own small payloads happily this idea has been borrowed by Hofstadter et al and My thoughts are a spacecraft with RPG and the SEP stage can work together at the distance of the outer planet in till separation.

Budget questions?

Use the present decadal survey for the start of the NASA HQ idea of building two spacecraft for the ice giants.Do build and budget for flight ready engineering spares for the next vehicles.In some cases pay as you go, place on the shelf these “spares” The grand AO places this process as policy.This a start of the third spacecraft leading into the next decadal…….

The cost of this is for certain the cost of a flagship mission plus several Discovery and /or missions, we would not want to spend the entire decades budget on a Master AO but this idea comes close to that.We would want a social contract that we employ most of the community this way, but competition is expected on the master AO and the subsidiary AO’s.Indeed this idea calls for SBAG and OPAG joint proposals in the case of the Enceladus LUCY tour.

Cons

This idea might leave out Lunar polar missions as well as Venus in a competition so it would a nice world where at least one Discovery mission is funded in addition to the proposed master AO plan.

How to choose?

a proposal may submit a decadal complaint idea if it satisfies certain percentages of decadal goals across multiple targets, A combined Enceladus/LUCY tour would satisfy say 40% of LUCY and 90% Enceladus while a LIFE Enceladus in situ probe is 40% and 60% LUCY goals.The SEP stage returning the Enceladus sample and leaving the probe at Saturn might work but this would receive negative marks for unproven tech SKG skills( informally proposed myself and Hafsteder et al for ice giants flybys).

How to plan a Titan flyby escape from Saturn to Jupiter and into a LUCY asteriod and earth sample return flyby

2013_aas_stuhowwil

2014_aas_stuhowwil

ssb_059316

Possibly the SEP stage carries the Enceladus sample return and the trojan tour instruments back to Earth and leaves an orbiter at Saturn, intillSuch a system  involves sharing SEP and RTG until undocking

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Proposed Decadal survey of findings of programatic planning

The Proposed SEP system for ARRM should be provided as government furnished equipment without charge to the Next Mars orbiter mission cost cap as NASA-developed technologies for infusion.

.nex-sag_draft_v29_final

The Proposed SEP system for ARRM should be provided as government furnished equipment without charge to the Next New frontiers and Discovery mission cost cap as NASA-developed technologies for infusion.

 

 

 

New Glenn and Delta-IV Propellent tank derived Skylab-II

Let us COMPARE LAUNCH VEHICLE CORE STAGE DIAMETERS; SATURN 5; 25.1 Meters long  LH2 tank Skylab.6.6-meter diameter

SLS  LH2 tank 39.624 meters long Skylab-II MAX, diameter 8.5 meters.Almost 1500 cubic meters.

SLS LH2 tank 11.15 meters long skylab-II, diameter 8.5 meters.495 cubic meters

Vulcan New Glenn BFR

Mars DRM 5 drop tanks Meters LH2 tank 22.7 Meters length 10 meters diameter

(A)Delta-IV Core stage and CBC LH2 tanks, The Liquid Hydrogen Tank is about 26.3 meters in length and capable of holding 29,500 Kilograms (416 cubic meters)The entire Delta V first stage is 40.8 meters in length and according to Delta V CBC mass minus the engine is 20 MT.Delta V heavy can loft 28 MT to LEO so Delta V heavy could loft another core stage as a space station.Delta V space station would be 92 meters tall

(B) Proposed Skylab-II (496 cubic meters)SLS LH2 tank two barrows. 

(C) SLS LH2 tank comes to (9,152 cubic Meters)
5.1 meters in diameter
These launch vehicles are due to size and propellants make good candidates for retrofitting their LH2 or LCH4 tanks into LEO space stations.These space stations would serve to encourage additional space station modules such as Bigelow to purchase docking rights and to serve as backup power and consumables and refuge & rescue in event of malfunction.Both ends of the propellant tank could have multiple docking ports.The SLS and Delta V LH2 tanks at more than 100 feet in length easily clears ISS geometry hazards from solar arrays and radiators to allow multiple docking ports at the aft end.ISS would appear to have a keel as was originally planned for space station freedom in the 1980s.

New Glenn and Delta IV LH2 propellant tanks would make for excellent space station components 

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Poor human’s refinement for a in space liquefication fractionation unit

Poor human’s refinement for a in space liquefication fractionation unit
The Neon “battery” or cryogenic SEP/Presserant tank is inside the LH2 tank, we stole this idea from Elon Musk and ULA; After LH2/LCH4 depletion the cryogenic Neon expansion ratio produces electricity the Gas pressurizes chemical/oxidizer tank. GH2 or GCH4 and Go2 mixed with GNe burn in the IVF internal combustion engine to produce H2O and GNe.GNe is shunted to the SEP engine after the H2O freezes out in the spent Oxidizer tank.

ULA IVF system and the ISS Hamilton standard common use for produced Methane
ULA could sell  to ISS/Habitat orbit maneuver with a Space liner two engine Centaur equipped with IVF and Neon.GO2 and GH2 could be mixed with GCH4 in the IVF internal combustion engine to produce power I asked Torrey Bruno if the engine could burn a mix? And what of the IVF rocket engine? After all the GH2 would be exhausted at some point and the ISS would only provide methane
This could be paid for with an NASA agreement ULA poneys up the R & D and Nasa under a commercial reboost contract pays down the R & D and costs(60/40 % costs)

“shit in the desert” 1 million Martian colonists and 1 million compost toilets
At the IAC in Guadalajara a question was asked in regards to ECLSS and human fecal matter or bio solids on mars. Civil engineering of large water rich bio solid treatment plants are major costs to human community’s and use a great deal of energy. The question to Elon Musk did have to do with water and waste processing in the desert and the answer I think is dry compost toilets. We could fly one to mars with a Red Dragon with frozen bio solids and a soil and earthworm culture. On Mars feed the frozen bio solids mixed with saw dust and toilet paper over time to the earthworms. This experiment would need a freezer and some sort of mechanism to feed samples daily to the vermiculture

 

 

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ACES/Xues augmented with a Cryogenic Neon expansion battery and power generator

ACES augmented with a Cryogenic Neon expansion battery and power generator

Cryogenic Neon expansion ratio generates eletrical power for a permenant shadow South Ackinson mission after ACES/Zues LH2 depletion

The ULA proposed ACES upper stage hopes to utilized autogenesis pressurization of propellant and oxidizer tanks thus replacing the helium pressurizer system and its mass and to use GH2 and GO2 from the spent tanks in an internal combustion engine to produce electrical power and to run a IVF rocket engine. We have proposed the GNe could pressurize the tanks however trades might indicate not to do this and instead utilize cryogenic Neon to generate electrical power after the GH2 and GO2 have been exhausted. The absence of LH2 and LO2 boil off has terminated cooling to our battery and the expanding gas would provide some power for a time. How long a time? How much pressure is left in gasses Neon? Enough to create thrust? To accomplish the mission of Neon cold gas thrusters you would want to save the mass of a dedicated Gasses neon tank so this trade brings up back to the idea of Oxidizer tank presserent. How much cryogenic neon would expend out to bring us to 50 PSI in the O2 tank? Is 50 PSI enough to create thrust that’s worthwhile in regards to the thruster mass penalty?

In the case of the ULA Xues Lunar Lander proposal the Cryogenic Neon expansion battery electricity generator could power for a time an Atkinson Basin permanent shadow lander as a probe. With a suitable sunshade ULA Xues could explore Mercury permanent shadow science targets extending battery and IVF systems

 

 

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SLS EUS Lunar Impactor with CubeSat observers and impactors

Use The SLS EUS stage as a lunar impacter as in the LCROSS mission

After payload separation EUS performs Lunar South Pole targeted burn. Safe the stage and deploy Cubesats.Cubesats fly a LCROSS science profile and trajectory and follow the EUS to impact with Polar ice. Some CubeSat’s could impact first observed by others (The “B” train).

Xenon inflated Hypersonic atmospheric decelerator CubeSat demonstrator

This concept test fly’s a Xenon inflated HIAD that we call Xe-HIAD.It would deploy from a Lunar Impacting EUS or more intriguing a EUS in an Earth free return trajectory. Xe-HAID would demonstrate a Xenon SEP engine and Xenon inflated HIAD at Earth atmosphere. HAID and SEP would research using Xenon as propellant post-Earth encounter.

A follow-on mission would be to recover a EUS with a human rated Xe-HIAD to recover the EUS itself with an Earth free return from Cislunar space. This would also demonstrate a Human rated HIAD for Human Mars missions. This EUS would need Solar array and avionics/comnav powered up for the Lunar free return and Earth XE-HAID.We can do trades on what earth orbit to place EUS into for the design of stage recovery or subsequent CubeSat deployments. Xenon recover from the Xe-HIAD would be repurposed as SEP propellant. ARRM Xenon tanks are placed in the EUS inter tank area. EUS and ACES with Xe-HIAD are the start of a Lunar cycler fleet that can be refueled and reused with both chemical and SEP propellants. On the underside of the Xe-HIAD you could deploy additional Com/Nav/solar array/science instruments

 

 

 

Such a mission design could work for dual manifested payloads on the proposed ULA Vulcan ACES.Conops for ACES might be GTO/GEO for a payload. Lunar flyby with secondary payloads. Earth return for Oberth effect and more interplanetary payloads. You would think a Xe-HIAD would cancel out most of an oberth gain for secondary payloads released here? ACES could provide Com/Nave for a fleet of smallsats on an interplanetary trajectory utilizing ELECTRA radio system

The XE-HIAD SEP powered CubeSat demonstrator

This might also be a larger space craft deployed from an SLS EUS however a size progression in flight experiments might be in order, CubeSat, larger spacecraft and finally a very large Xe-HIAD that does the Lunar earth free return experiment. The HIAD team could do an earth atmosphere Xe inflation experiment at Hawaii that would complement a small CubeSat XE-HIAD

 

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Leveraged ESOP and tax exempt bond capitalized mars colonization; The ethical choice

Leveraged ESOP and tax exempt bond capitalized mars colonization

English Colonization of North America often took the form of a joint stock company to finance the ship and voyage not always successfully initially. Voyages funded this way often had the features of the participants funding his own voyage along with other fellow colonists. The closest analogy to this would be to days Employee Stock ownership program and Coops. In the United States of America, the risky proposition of the self-funded ESOP is permitted. This is the concept of a leveraged ESOP with borrowed capital. Profits on capital loaned to a ESOP is tax free.

Another concept worth mentioning is community support in exchange for employment through the issue of tax free bonds. A ESOP/SpaceX subsidiary would manufacture components for the $500mars colony in the community or state issuing the bonds. The most common form is the municipal tax free bond. I propose to study the tax effects of the municipal tax free bond loaned to the ESOP.These ESOP-owned intitys are legaly independent in many cases from SpaceX and can purchase competing products and services from ULA and Blue Origins 

We have several ESOPS that agree to have the IRS rule are related to one another to provide ESOP portability. This most likely would mean some sort of SpaceX minority ownership but not as SpaceX subsidiary’s. One ESOP would provide Mars colony services to SpaceX for a fee so in effect the Mars colony ESOP is paying for a part of its passage to Mars with earnings from SpaceX, however it should be noted that we propose that the Mars colony be a special tax district with property and sales taxes that would then pay a fee to the ESOP for mars Municipal services.

The mars spaceport outside of town might become a busy enough place to charge a fee for services itself.

The leveraged ESOP could fund a fleet of ITS vehicles acting as an airline to earn income from other non-ESOP and ESOP funded passage. SpaceX could then sell ITS vehicles for an immediate return of capital to be reinvested in new projects.

 

1 million X $500,000 = $500 Billion / by 20 years = $25 Billion per year

1 Million / by 20 years is 50,000 persons a year so the hypothesis of this white paper is that this scenario is likely to operate better in the out years, IE it’s unlikely for this number of yearly immigrants to become a reality early. Any ESOP feasibility study will reflect this. This means that SpaceX and other public private funding sources are the revenue to fund the mars and earth based ESOPs. “ISRU” funding of a Mars based ESOP society would be a small portion of a leveraged ESOP’s funded liability’s so the second hypotheses of this white paper are we are bootstrapping multiple ESOP; s for services provided in “ISRU” and in the first decades this is only partially from an internal colony (profits and municipal taxes to pay bonds) back on earth, however, the municipal bonds are paid early from manufacture of goods for transport to Mars.

 

100 passengers X $500,000 + $50 Million

B Corporation, we pledge our happiness and honor to one another and to all us all and state we are here on a mission for humanity and to those of us here

We pledge to own automated machines together or to lease automated machines to our commonly owned endeavors as a part of our pledge we make to one another, this is true when we all deal with commonly owned business of our close neighbors.

 

Mars family of ESOP’s borrows $100 Billion over 20 years to build infrastructure that is for private use(sold) and is for public use or is part of the Mars Commons. Over 20 years this is $5 Billion per year. Gradual implementation of a mars property and VAT tax over time takes over the expansion of the commons and the upkeep of the existing commons, works best 10 to 20 years after colonization.

  • (1) SpaceX contracts with a subsidiary that’s majority ESOP owned for goods for transport to mars. (2) there are many of these but we aim to incorporate them as B Corporations with majority ESOP ownership (*) (C) We will perform ESOP feasibility studies as to the risk of an earth based ESOP also taking on the risk of ownership of space or Mars based leveraged ownership (**) (D) Earth based leveraged ESOP/s may be involved in CDC and leveraged tax exempt bonds to build mars bound cargoes and we need to factor this possibility into ESOP feasibility studies. ESOP’s as pension plans do not pay federal income taxes, still levering an ESOP assets with CDC municipals bonds may be safer than the market leveraging the ESOP(E) levering an ESOP in a zip code that has lent its support to a long-term earth based manufacturer of Mars based goods makes for good public corporate policy (***).
  • (1) Representative examples of B corporation incorporation and the majority ESOP owned entity. The Mars colony will need a construction crane that is designed like earth based ones except it’s made of carbon fibers and titanium. The SpaceX ITS with its crane could deploy this construction crane alongside the ITS. The Mars crane could assemble mars domes up to 20 to 30 stories. (2) the crane manufacturer and the deployment at mars are performed by an B corporation ESOP that is leveraged with borrowed capital and over 10 to 15 years SpaceX pays the ESOP a fee to this ESOP for manufacture and deployment. (3) repeat 2 above for a crane at a Mars spaceport and this smaller crane might be the first deployed(?)
  • (1) How to entice 100 passengers at $500,000 each? The ESOP borrows(leverages) the $500 K fair as a business expenses the 100 are ESOP employees of a Mars transport space line. They own the transporter and will profit from its reuse. The problem here, of course, is ERISA and the IRS require that the 100 passengers be employees so this idea requires work.
  • $100 Billion over 30 years as an example loaned to a large collection of ESOP’s comes out to $3,333,333,000 per year, If the last capitalization to a leveraged ESOP occurs 30 years’ from now then our mutual enterprises are paid off 60 years from now

 

Another concept that might prove useful in a Mars colonization attempt that would complement the family of ESOP’s would be condominiums associations of many ESOPS and individual homeowners who would share in individual tunnels costs of boring and infrastructure costs. Condominiums allow joint private ownership of shared building and infrastructure costs. In the 1980’s I proposed that the SEIU fund leveraged ESOP’s to build Condominiums that would lead to Unionized buildings and in the case of apartments for rent the Building would end up under the ownership of the doorman housemen and the building manager.

My research back then uncovered a flaw in my idea that involved the ownership of capital in the form of real estate to be owned by just a few employees under ERISA in the 1980’s prohibited this sort of concentration. On the other hand, there are IT firms that have few employees that are ESOP owned. My solution was that a San Francisco high-rise worth tens of millions of dollars but with only 10 to 15 employees could have in the lobby an employee intensive restaurant union represented restaurant. High end service restaurants in san Francisco’s union square and pacific heights are often near the apartment house districts. A study of SF building codes and zoning may turn up no outright prohibition to an apartment house having a retail lobby’s hotels often have a retail lobby and on Mars habitual real estate may be at a premium so it might be our artists license to take a page from the Asian city with its small alleyways full of people and commerce. Once there was a plan to have BART subway stops full of people with their BBQ ducks hanging from their feet and retail spaces to help pay down BART bonds. It never came to be and today BART is a sterile lobby in all its stations.

Mars, I believe must be s closer friendlier society built on closer ties as well as closer proximity to one another. ESOP theory is that employees are more happy and innovative when charged with and allowed to be so. It’s no accident that microbrewery industry is full of ESOP’s the craft of brewing artisanal products is an invitation to innovation in production and management by the whole team. The mars colony is a place where it may not make economic since to have wage workers in the earth concept of the thing but May I suggest another read of the Hogan novel of the “voyage to yesteryear” in it the colonist of an exoplanet have no concept of capital as having ownership, the computers and robots and free energy provide for all. The concept of people gathering to eat together and for people to want to serve others persists. On mars, perhaps they might want to operate restaurants for the pleasure of it.

In the case of the owned housing, a condominium like a leveraged ESOP is a funding mechanism for the boring of the tunnel utilizing mortgages paid down over time to fund tunnel borings of these costs will be shared by the future municipal commons such as sharing tunnel wall costs with housing and retail ESOPS and condominium associations.

The idea of wage workers on Mars does not sound plausible with a $500,000 ticket for passage and the idea mars colonists would want to gather to be served by robots so the idea of the ESOP takes on new meaning; The cost of passage could be amortized by an ESOP as a cost of doing business but this cost would reflect a price on the product. Perhaps skilled passengers with a love of food and wine or the arts could have that time-honored part time business. Early Mars colonists will have to grow their own food without regard to profit. It’s important that early colonists who are tasks with auxiliary tasks to have some interests in those tasks. Early ESOPS and other ventures must take into consideration the multiple part time ventures of each individual and take into consideration the ERISA rules on hours worked as a part of the formula for ESOP share ownership. 100 fare paying passengers cannot own equally the ITS space ship in a ESOP because it does not take over time all 100 of them to be employees at any single time. For many being a part time worker over time for many ESOPS most closely matches the highly skilled astronaut worker colonists. This brings us almost full circle. ESOP’s work best with an engaged innovated effort. Highly skilled workers are at their best when multiskilled in small groups and it’s this that best describes the colonists of our future.

Another possibility is that those who show a passion for the arts of the trades make their passage as some form of indentured servant to others, this should never be a model for a future world indeed the B corporation model, indeed a wage skilled artisan ESOP should never be indentured or exploited by the other ESOP’s

 

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Three Thoughts for the day

Poor human’s refinement for a in space liquefication fractionation unit

The Neon “battery” or cryogenic SEP/Presserent tank is inside the LH2 tank, we stole this idea from Elon Musk After LH2/LCH4 depletion the cryogenic Neon expansion ratio produces electricity the Gas pressurizes chemical/oxidizer tank. Gh2 or GCH4 and Go2 mixed with GNe burn in the IVF internal combustion engine to produce H2O and GNe.GNe is shunted to the SEP engine.

 

ULA IVF system and the ISS Hamilton standard common use for produced Methane

ULA could sell ISS/Habitat orbit maneuver with a Space liner two engine Centaur equipped with IVF and Neon.GO2 and GH2 could be mixed with GCH4 in the IVF internal combustion engine to produce power I asked Torrey Bruno if the engine could burn a mix? And what of the IVF rocket engine? After all the GH2 would be exhausted at some point and the ISS would only provide methane

This could be paid for with an NASA agreement ULA poneys up the R & D and Nasa under a commercial reboost contract pays down the R & D and costs(60/40 % costs)

 

“shit in the desert” 1 million Martian colonists and 1 million compost toilets

At the IAC in Guadalajara a question was asked in regards to ECLSS and human fecal matter or bio solids on mars. Civil engineering of large water rich bio solid treatment plants are major costs to human community’s and use a great deal of energy. The question to Elon Musk did have to do with water and waste processing in the desert and the answer I think is dry compost toilets. We could fly one to mars with a Red Dragon with frozen bio solids and a soil and earthworm culture. On Mars feed the frozen bio solids mixed with saw dust and toilet paper over time to the earthworms. This experiment would need a freezer and some sort of mechanism to feed samples daily to the vermiculture