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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

 

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 .

Serially produced ice giant planetary probes and components

Serially produced ice giant planetary probes and components

(A)(1) conduct a unfunded RFP to ascertain cost engineering for flight spares beyond a two spacecraft buy for ice giant missions.flight spares are to be construed as spacecraft Bus and a docked ARRM derived SEP stage.

(A)(2) compete ARRM derived SEP for Mars MRO follow on and 4 more serially produced SEP for outer solar system missions.These are all government provided equipment to the AO not counted towards mission caps.(3) two providers build flight units for competition into the future.(A)(3) serially produce those items most sensitive to price drops due to serially production and a single contracted purchase,perhaps propellant tanks and the spacecraft bus structure itself would lend themselves to this.(A)(4) funding under a grand unified AO would purchase these lead items for a third and  fourth Ice Giant spacecraft;These spacecraft would likely become under sub competed AO’s to SBAG and ROW targets. This together with the serially produced COPAP atmospheric probes should answer 80 to 90 or better of minimum scientific goals as set by OPAG and SBAG communities.(A)(5) This purchasing formula together with a grand unified AO with follow on sub competed AO’s should also allow for follow-on missions back to Saturn and the Ice Giants with updated avionics and flight computers and science instruments.The 3rd and 4th Ice Giant spacecraft would observe a different set of SBAG/ROW targets and KBO targets after and during the prime missions.

COPAP; Common outer planet atmosphere probe are serially produced, build 5 for Jupiter, Saturn, Titan, Uranus, decadal survey order of preference is  Saturn, Uranus Neptune.

CACNCUR, Cryogenic ACES Neon cooled university ride share IR telescopes

PBOFTS, ?  I wrote this term at OPAG Feb 2017 but can not recall the meaning perhaps “Previously bought off the shelf”

“The Spider” 8 University IR rideshare telescopes mounted on the ACES or SLS forward Dome

“The Spider” 8 University IR rideshare telescopes mounted on the ACES or SLS forward Dome

This idea I have blogged about before but it was a part of the Cryogenic Neon expansion ratio battery series of posts, this will be a stand alone post and practice for submission to this years NIAC and Itech opportunities and if there is ever a second round of “cold tech”

40-k-liquid-neon-energy-storage-unit_icec251-publicado

de_Sousa_2015_IOP_Conf._Ser._Mater._Sci._Eng._101_012191

de_Sousa_2015_IOP_Conf._Ser._Mater._Sci._Eng._101_012121

The above paper describes well the power of Neon expansion ratios and the device described by Bonfait, Gregoire, et al. “40 K Liquid Neon Energy Storage Unit.” Physics Procedia (2015): 1-6. I am sure this type of system could also be cooled by LH2 propellant and generate electrical power and cool the proposed university IR telescopes proposed here.This might like the most ideas here are shared with those who twitter such as the ULA folks.

The OPAG Feb 2017 conference gave me further impetus on the idea that small University IR telescopes might be possible with long live Cryogenic propellant upper stages and could be integrated into the upper stage IVF system.GNe could be vented into the LH2 tank and would not react in the IVF combustion engine and vent the H2O exhaust and GNe to the O2 tank poor humans easy method of liquefaction/Fractionation.The idea here is at some future Depot you freeze the water out onto the tank walls and scavenge the Neon back out and recover the water by reheating the tank walls.Then reuse the upper stage.

IMG_2772[1]

The image depicted represents the eight eyes of the spider or 8 university IR telescopes mounted on the forward endcap of an upper stage as rideshares.The Cryogenic Neon used to cool them is in a tank inside the LH2 propellant tank.The first suggested target is Lunar south pole shaded craters.More challenging would be to get this system landed in those craters or the second target would be Mercury polar craters.

Common Evolved ARRM derived SEP docking system for planatary missions

Allow for Planetary orbiters and flyby mission designs that can feed spacecraft RTG electrical power through the docking mechanism to the SEP/NEP hybrid stage.

The spacecraft might be in partial hibernation during the cruise and can share the power to the docked SEP to augment its engines.At some point, the two can part ways and a smaller science payload remains with the SEP stage that now can devote all the power from the solar arrays to this mission.The light is dim way out here in the outer solar system so this idea should be looked into.

Distributed Decadal survey launch on HLLV’s

At OPAG 2017 it was suggested to me that SLS could loft an Ice giant mission with a venus probe delivered through a Venus flyby, this thought reminded me of my Grand Unified AO proposal.The difference here of course is you would propose an Ice Giant mission in the same time frame as a Venus Discovery AO or an AO Discovery AO for any decadal survey object of interest that matches the SLS manifest.This presents problems with funding for one-off venus probes or any other probe co-manifested on SLS.Perhaps

Perhaps concepts of serially produced Ice giant/Ocean world probes with costs distributed over a decade and a half could lower costs enough for a robust discovery program that launches with those probes. Except for Venus, it’s unlikely for this idea to work, my thoughts are that many Discovery class missions are in fact ride share with the Ice Giant Missions under my grand unified AO proposal. 

 

 

 

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