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What we should do next 2.0 ?

(A)(1) Investigate with ground based systems miscibility of noble ullage gases with cryogenic LH2, LO2 and LCH4

(A)(2) investigate mixing of noble gas ullage with Cryogenic propellants over hours, days and  weeks

(B)(1) investigate in space liquefaction/fractionation machinery in conjunction with a zero boil off unit.

(B)(2) this machinery would be used to process gasses H2 and O2 out of noble ullage/ion propellant in hybrid chemical ion powered systems; investigate with ground based experiments a Liquid air fractionation unit

(B)(3) removal of noble elements out of LH2 and LO2 in the case of a chemical refueling of a hybrid powered stage

(C)(1) investigate with ground based experiments with removing Noble gasses from Nitrogen oxygen gases in the case of habitat’s being re-purposed as ion propellant tank.This is also done with an in space liquid air liquefaction/fraternization system.

https://yellowdragonblog.com/2015/03/30/sls-skylab-iieus-deployed-pressurized-with-argonxenon-after-a-chemical-burn-sep-variant/ 

And;

https://yellowdragonblog.com/2015/04/11/liquefactionfractionation-unit-to-remove-gases-xenonargon-from-a-gases-hydrogen-or-methane-propellent/

(D)(1) We need to use a ground based experiment to study of Noble gas ullage/Ion propellants with hypergolic propellants; If these behave better on longer term missions and behave better on miscible issues then Hyperbolic chemical/ion powered hybrid stages then we could in future do trades with cryogenic ion powered hybrids

(E)(1) The ground based Air liquefaction/fractionation unit leads the way to IRSU of rocks.Imagine the system at work on a landed hybrid propellent Xues/Centuat lander coupled to a Oxygen production system.

(F)(1) Air Liquefaction/Fractionation unit allows for the GH2/GO2/GCH4 in the propellent tanks to be separated from one another and fed to both The IVF and Ion propulsion systems since we envision that both systems are present and that both use the same propellent and oxidizer  tanks.

EDIT 16 March 2016

(G) (1) Does Noble element ice sink or float in cryogenic oxidisers or propellant? I think if large Noble element ice forms it sinks

 

Relocate American and Japanese Military assets from Okinawa to a city at sea to reduce local tensions

Relocate American and Japanese Military  assets from Okinawa to a city at sea to reduce local tensions

 

(A) (1)relocate American and Japanese military assets from Okinawa to reduce tensions there among the two nations citizens by building a city at sea that has these military assets as an economic anchor tenant.(A)(2) This requires a military and commercial airport and seaport at sea that creates an economic base for the city and its inhabitants.(A)(3) This city at sea would be built by both nations and the citizens of the city at sea would be from both nations.(A)(4)Property taxes would pay down a minority portion of the cost to build for the civilian portion and the military assets by America. and Japan. (A)(5) Military Sealift Command ships could resupply the military assets.

(B)(1) American and Japanese oceanographic research ships could be ported at the city at sea furthering the economic base and adding to the cities expertise. civil servants who work as ocean researchers would be encouraged to be a city at sea homeowners.

(B)(2) American aircraft carrier reactors and life support equipment could power the American military assets based at the city at sea.

(B)(3)This city at sea would have both American and Japanese addresses with postal codes, it would be a home of record for the military, civil service, contractors for the purpose of being a home of record and to calculate cost of living and housing allowances.These allowances are used for mortgages.

 

 

Cities at sea-1

Cities at sea-2

cities at sea-3

Cities at sea-4

Cities at sea-5

Cities at sea-6

Cities at sea-7   (C)(1)This link has a model not likely to be used in this proposal in that this proposal is not a Libertarian Nirvana.This proposal envisions American and Japanese military commanders and personnel and a civilian elected city government.(C)(2)Perhaps a portion of the city at sea could be a special economic zone with different laws and nationalities from many other countries.I am not interested in Libertarians who inadvertently encourage labor and human rights exploitation.(C)(3)Non-American Japanese residence should be allowed to vote in local government elections.(C)(4) I would see the civil government owning the cities hull and common spaces along with condominium associations but much of the business would be well served by ESOP’s or employee ownership as an important part of the community.(C)(5)

 

DEROC ; Distributed Evolved Recovery Of Jettisoned Components

DEROM ; Distributed Evolved Recovery Of Jettisoned Matter. (DEROC ) components might be a better choice.

How would it work? not sure but here is a guess( see Rappolee Flower post) Payload adapter and payload shroud/fairing would be brought to LEO.Payload fairing would deploy around payload but would not jettison from payload adapter (Rappolee Post ).Payload separates.Rappolee flowers deploy photovoltaic on the inside of the fairing.A mesh deploys around the fairing halves that has more photovoltaic cells and acts as an antenna.The mesh is designed to deploy with the fairing halves to create a circular object.

We need to dock and store these somewhere for later use or use them as is somehow(power)the underside of the former payload adapter could have a grapple fixture or a docking mechanism with the power connector for other docked power users.

We are selling power and communications to some communications provider perhaps?

 

Nocturnal Synchronous polar orbiter utilizing ACES IVF and ICE power sources and Distributed Launch

Nocturnal Synchronous polar orbiter utilizing ACES IVF and ICE power sources and Distributed Launch

Nocturnal Synchronous polar orbits are defined as the opposite of Sun-synchronous polar orbits.It envisioned as a method to conceal from observation spysats.These orbits are not ideal for large expensive satellites but might be worthwhile as ride share on ACES upper stages as a power source to replace solar panels.

Possibly we could do a nonfunded RFP to find out from the scientific community of possible uses of permanently shaded spacecraft for earth observation, astronomy, and intelligence gathering.

(A) What is the maximum polar orbit that can stay in darkness? (B) In some cases, spacecraft illumination might be allowed at Apogee in remote southern ocean areas.(C) What is the boil off ratio for ACES in a Nocturnal orbit?

(D) CONOPS; An ACES stage fully fueled delivers a payload to Polar orbit, after Spacecraft separation ACES maneuvers into a Nocturnal polar orbit with rideshare IR instruments or a secondary payload.IVF and ICE powers and cools the IR instruments.LH2 cools LNe2 to cool IR instruments (see the ACES Spider proposal) same could be claimed for an astronomy instrument.Future ACES to polar orbit refuel the Nocturnal ACES in a form of distributed Launch.

Terrestrial & Cislunar Exploration Technologies ESOP colonization compact

We the 200 passengers on the spaceship hereby pledge our mutual fortunes and future prosperity and wellbeing and happiness to one another through our California public benefit corporation and ESOP.

We pledge to share our intellectual and entrepreneurial ideas to one another through our ESOP to advance our cause of making mars and other worlds our home.We pledge to spread the joy of new found knowledge with everyone back in our original home.

We will Borrow $ 200 Million for our passage and purchase of the spaceship and reuse the spaceship to earn revenue to bring yet more passengers.Our passage there for is a business expense towards future revenues and is a liability of the ESOP corporation.If we fail we do not owe as individuals but if we work hard and succeed the $200 million plus our other investments in mars architecture becomes our pension plan in the decades ahead.

Think of the Mayflower compact but I have added in the philosophy of Employee ownership together with that of the for profit public benefit corporation.

 

Hybrid Strongback/Crane

Hybrid Strongback/Crane

This planetary lander would serve as a dock at a spaceport to assist other landers to unload bulky or heavy cargo.

Also, this strongback/crane would serve to build buildings

 

image1

Chinese city state,overseas communities & diasporia commercial space stations and colonization

Chinese city-state, overseas community’s & diaspora commercial space stations, and colonization 

Private-Public partnerships between Chinese city-states and overseas Chinese communities to loft space stations and to colonize the solar system using the Chinese neighborhood associations.

https://en.wikipedia.org/wiki/Chinese_Consolidated_Benevolent_Association

Chinese nation states such as Taiwan, disporaiSingapore could join with the Worldwide diaspora to embarlk on this endeaver.

 

 

nation states

 

 

 

 

No ISS after 2024? not in the interests of commercial crew and cargo, what to do?

No ISS after 2024? not in the interests of commercial crew and cargo, what to do?No ISS after 2024? not in the interests of commercial crew and cargo, what to do?

 

Extend to 2028 is really what we want even if it comes out of SLS cargoes beyond LEO budgets, WHY? SpaceX is spending capital gained from government and commercial launch of its Mars project.The rest of us should do something similar in the interests of individual projects.No ISS beyond 2024 gores the Ox of Sierra Nevada the most I think to do to it’s not being a candidate for Cislunar.So it’s Sierra Nevada that gains the most in joining in with a  ULA propellant tank space station deployment.ULA, of course, loses out it Dream Chaser comes to an end or is curtailed.

This line of argument means we sell the Sierra Nevada on funding, loaning, transaction owning and then selling an interest in the Propellant tank derived space station to the transaction is tax-free to the seller to the ESOP shares.If Sierra Nevada manufacturers equipment in a cash-free transaction to the Space station and later sells that contribution to the ESOP this might work as well.

 

Its in the interests of ULA to further the goals of Dream Chaser beyond 2024/28

Starliner is not a vehicle immeadetly intended for beyond LEO to Cis lunar so Boeing and ULA are best served with a back up to an early ISS deorbit. Likewise, Bigelow may or may not be ready and/or Bigalow might need a backup to its ECLASS and propulsion by docking to another space station.Indeed a Bigalow without ECLASS and its own propulsion could be docked.So it might very be in Bigelow’s interests to partner with another docking port provider.We could very well propose that the ESOP has purchased from partnership shares in ownership of both ULA and Bigalow.Or Bigalow rents docking space as per my original idea.

Bigalow might be one a transitional part owner in the ULA station as well as contributing its inflatables.

It might be in our interests for the ESOP to purchase Starliner flights and resale them to customers(tax reasons?)also if the ESOP owns the Starliner that revenue is tax-free (ESOP is a pension plan)Possibly the ESOP purchase Dream Chasers to bring their future revenues tax-free, under ERISA this means the astronauts are the employee owners of this project(plus support staff and my manufacturing worker proposal) At one time a pilot ESOP-owned United Airlines that ended unhappily a cautionary tale.

orbital ATK might lose out to an early end to ISS so it to could have an interest in funding or partner with a large Propellant tank derived space station.

We can rent docking space to those entity’s that would own the modules removed from the ISS

Possibly the ESOP also owns the launch site flare gas cogeneration sites as suggested in prior posts.

ESOP’s may be S Corporation partners so ULA, Orbital, Sierra Nevada, Boeing and terrestrial & cislunar technologies and the ESOP all could be S corporation partners as well as subcontractors who have non-cash equipment contributions (solar arrays,nanoracks,post ISS module owners?)

 

 

 

 

 

 

Inoculated American Chestnut with Truffle spores to displace harmful fungi

Inoculated American Chestnut with Truffle spores to displace harmful fungi

A novel proposal?

Also, might create a new Forrest agriculture or polyculture

 

 

Sonoma county first ever truffle harvest

truffles

https://www.nytimes.com/2016/11/24/business/has-a-start-up-found-the-secret-to-farming-the-elusive-truffle.html?_r=0

http://www.natruffling.org/links.htm

http://trufflegrowers.com/

http://www.syracuse.com/food/index.ssf/2014/04/move_over_maple_syrup_researchers_in_syracuse_are_tapping_black_walnut_trees_and.html

 

http://www.cornell.edu/video/untapped-potential-of-birch-syrup-walnut-syrup-and-maple-water

 

 

The Hypothesis is that Tuber Melanosporum the truffle organism could displace The American Chestnut deleterious fungal organism Cryphonectria parasitica, an added benefit would be that this could also be a harvested crop as well.Perhaps inoculating American Chestnuts with a native truffle would also work to ward off the Cryphonectria parasitica?

Commercial space and the use of Liquid propellant SLS CBC development seed money

Commercial space and the use of Liquid propellant SLS CBC development seed money

The folks at the center for strategic and international studies have put out a study on the industrial base and contracting strategies for a post RD-180 world.Mention is made of the synergies of mass production of the Blue Origins engines for use with the Vulcan and ULA launch vehicles.The report makes no mention of the SpaceX ITS and its engines despite the reports mention of the New Glenn vehicle.In the case of ITS you need a scaled down version to serve as a SLS CBC.

I believe there is a use for SLS development funding put to use to move up work on the proposed future SLS CBC competition.This funding now has been delegated to the SLS EUS stage instead. J.Goff Et al has proposed that this EUS could have been a very large ACES stage a sentiment I share.This is a lost opportunity I believe.

In the case of the SLS CBC, there would be synergies of scale in Vulcan or STS derived CBC’s that could not only capitalize “commercial space” but use that SLS capital to venture forth on private journeys to the inner solar system.I am fond of both STS and a Vulcan CBC does to the possibility of cross feeding LCH4 into the LH2 propellant tank in the core stage.However, a Falcon XX with its dense RP-1 could do the job better.This would increase the production of the engines to yet another contractor.

What I am about to propose would cost money and that would be to have a flyoff SLS CBC competition!  At least two contractors would fly their CBC on at least 1 flight of the SLS, The contract would specify that the government is looking to increase the industrial base of engines and vehicles with an EELV or commercial goal in mind and/or the engines or vehicles are meeting an exploration goal.This means reviving the F1 or proposing a one-off solution with a product that has no other use would score poorly.The Government, of course, means the DOD as well so the Air Force EELV contracting office should have a seat at the table

Funding for R & D could go like this; NASA 80% AF 5% contractor 15% in exchange for so many future orders

The Vulcan derived SLS CBC would be a larger launch vehicle so this could be a joint ULA/Blue venture.The SpaceX ITS already in the works could be the competitor.In this case, the competition could allow the reverse funding order

ULA/Blue 75%

SpaceX 75%

NASA 20% AF 5%

Two CBC contractors would fly for a decade or two with the SLS core stage

The social contract is SLS subsidizes the private journey to mars with the government’s vehicles.perhaps this should be called the RLS or Rappolee Lunch system 🙂 After all, I have done a much better job of handing out jobs to every congressional district out there and my thoughts are that using SpaceX engines and Blue Origin engines that are in use on their other vehicles stand the most chance of bringing those costs down.ULA has pie charts with engine costs as a percentage of the stage costs to manufacture.

I have blogged in the past about SSME/RS-25 as an EELV reusable engine but those folks are very stubborn when it comes to the very idea of Public/Private partnerships and I fear that it may not be possible to plan on anything from them except an RS-25E CBC, this, however, would be a suboptimum Delta IV on steroids at sea level.SLS needs LCH4 CBC’s.

“Beyond the RD-180.” Csis.org. n.d. Web. 25 Mar. 2017. <https://www.csis.org/analysis/beyond-rd-180&gt;

Post RD-180 study

Notes for a future blog entry, A Vulcan 56/ACES can loft more than a Delta IV first stage at 28 Mt that has been converted into a space station. According to space launch report, a Delta IV first stage at burn out is 27 Mt and the Vulcan 551 can loft 17.3 Mt to LEO.Why the entire first stage? the intertank area is more real estate for docking mechanisms and the structures around the tanks can serve as micrometeorite protection.Space launch report tells us the Delta IV LH2 tank is made of 5 segments so let’s say that’s 5.4 Mt per segment? Atlas V could loft a shorter Delta LH2 tank with fewer segments with an adapter.

Real estate is docking mechanisms, geometry, and volumes.I see a future propellant tank derived space stations with docking ports at the aft and forward ends and the intertank regions, we sell these to (Bigelow?) & the ISS.Geometry is the asset to sell of distance/length from ISS obstructions to follow on docking partners.The Delta IV first stage is 36.6 meters so this places intertank and aft docking ports some distance away from ISS solar arrays.LH2 propellant tanks have large volumes that would complement greatly the customers.

Kyle, Ed. “Delta IV Data Sheet.” Spacelaunchreport.com. 18 Mar. 2017. Web. 25 Mar. 2017. http://spacelaunchreport.com/delta4.html

&

Kyle, Ed. “Vulcan Data Sheet.” Spacelaunchreport.com. 15 Nov. 2015. Web. 25 Mar. 2017. http://www.spacelaunchreport.com/vulcan.html

 

ULA ACES ICE & Telsa Powerwall as part of a luanchpad cogeneration of flare gas

ULA ACAS ICE & Telsa Powerwall as part of a launchpad cogeneration of flare gas

(A)(1) Launch site flare gas is now lost to the ATM, without energy recovery. ULA and Telsa technologies could burn these flare gasses to produce electricity and store it for sell at peak power demand and prices.(A)(2) mass produced ULA ICE engines and Tesla powerwalls for this terrestrial application spreads the costs over many units.ULA and SpaceX could agree to use these two products across all launch sites they  control with an agreement.This Tesla ULA combination can also coogenerate power at SLS and other launch sites.

(A)(C) with out storage or little storage of GH2 and GO2 at the flare sites . many ULA ICE engines would need to be produced

(A)(D) or how many safe gases storage units would need to be made, trades?

(A) E) these ideas make since if the florida and california luanch rates increase. this increases launch site boil off of flare gas, it make since at spaceX Texas site to .

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