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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

 

The ULA or (insert your company here) Funded leveraged ESOP feasibility study to create new customers ( the new customer spin off)

The ULA or(insert your company here) Funded leveraged ESOP feasibility study to create new customers ( the new customer spin-off). ULA funds a Leveraged ESOP feasibility on behalf of terrestrial & cislunar exploration technologies to purchase Delta IV LH2 propellant tanks outfitted as space stations

These LH2 propellant tanks would initially  be  white tail tanks.

Most likely these Delta IV LH2 propellant tanks would be lofted by Vulcan launchers do to costs and possibly to reduce the height of the vehicle, this would require an adapter to the core Vulcan stage.We have asked ULA to assit us in using or modifying the New ULA rocket builder to make a case for this.

Use of a ULA ACES as a cryocooler for IR CubeSat space telescopes utilizing a Neon expansion ratio battery

Use of a ULA ACES as a cryocooler for IR CubeSat space telescopes utilizing a Neon expansion battery

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

A new paper we have found gives insight into the power of cryogenic Neon expansion ratios,

Martins, D., Borges P. de Sousa, I. Catarino, and G. Bonfait. “40 K Liquid Neon Energy Storage Unit.” Physics Procedia. 67 (2015): 1193-1198.

(A)(1) use the Cryogenic Xenon thermal Battery to cool CubeSat IR telescopes held in a Ring or other cube sat deployment mechanism with the exception that they would remain attached to the upper stage.

(A)(2) The Cryogenic Thermal battery would be cooled at first by ACES LH2 propellent; Cryogenic Neon expansion gas expelled to ACES LH2 tank after LH2 exhaustion.(3)ULA ACES internal combustion engine redesigned to burn GH2 and GO2 with Neon and other Noble gas contaminants with H2O exhausted back with the Neon into the ACES propellant tanks to freeze out for later resource utilization See here and for possible Neon reuse without H2O contamination the Neon thermal battery See here,(4) thermal expansion battery also might produce its own electricity by expanding the gas through an impeller or turbine or Stirling engine(5) solar arrays allow us to bank the gases H2 and O2 for internal combustion engine for planetary and lunar shadow.

(B)(1) Many space telescopes CubeSats with cryogenic cooling brings this capability to the university level investigation and a first target could be the lunar poles.

Golf Course Sugar Maple “polyculture”

Golf Course Sugar Maple “polyculture”

The USDA does not subsidize Maple syrup or maple wood products and more importantly does not keep Sugar maple trees in its botanical collections

The University of Cornell in New York state does have a Sugar Maple experiment station with a botanical collection.Our idea is that the university in all Sugar Maple producing states could set up university golf courses for students and staff that would generate revenue and host sugar maple experiment stations and this could be a model for other university agricultural experiment stations.Are there for example agricultural experiments for the grasses?(yes) could we incorporate prairie grasses as traps in a golf course?

Phase 2 RPS RFP Air Force EELV synergies with reusable/recoverable SSME/RS-25 and other engine manufacters

the post is made without using any information in the  Phase 2 RPS RFP Bidder’s Library, and only uses information that is in the public domain and ideas from previous posts from this blog

My company signed an NDA to this effect not to disclose anything to be found there, I am hoping however that the bidders list and contractors Q & A forms might become public in some form with the permission of the Air Force and those contractors some day as those are a teachable moment for students  and the public.

So the blog posts here have to do with synergies between government agency’s(NASA and AF/DOD NRO) and perhaps the international ISS partners who might have an  American subsidiary here in America.

The Air Force wants products that can withstand the commercial marketplace and the earlier draft RPS talked of synergy’s with other government customers so that the thought that occurs to us is that the RPS RFP has Congressional mandated language in regards to our Russian ISS partners, it does not have language that prohibits European contractors

ULA  and Ariane space have proposed methods to recover engines from first stages, SpaceX also proposes to recover the first stage and the air force requires that any bidder shares this with all providers.

We think that the Europeans could build their winged fly-back the vehicle in both the unites states and Europe and recover the SSME/RS-25 and their engine from their launch vehicle.We would need a winged flyback vehicle to recover a two SSME engine core EELV. An SLS strap On? if this was a 3 SSME engine core CBC might not be recoverable by air as ULA suggests and would require the winged lander.

We contend along with the white house that a kerosene engine without a launch vehicle warrants a veto threat, it should be noted the RFP will not consider such a proposal in any event.So lets examine this idea, If the air force wants to share of the product you would want to submit separate bids for your launcher and engine, The engine must be sold to all your launch vehicle not so….

Delta IV(and EELV) propellant tank derived space station business case

Delta IV propellant tank derived space station business case

Delta IV CBC stage without its engine is 20 metric tons wich is 8 MT tons less than Delta Heavy to LEO

The Stage atop the Delta IV Heavy would reach above 92 meters

The stage as space station would require a robust stage adapter (weight?)An option would be to design a stage adapter between the future Vulcan first stage and a Delta IV derived space station

The stage would need a 4-way docking port forward and aft and in the LH2 &LO2  intertank area (weight?)weight issues might lead us to have one simple docking collar with approach radar and a 4-way docking mechanism in the intertank region and aft.

This is 12 docking ports and is the business case along with the cubic meters offered by the Delta IV derived space station.The length of this space station places the docking port well clear of the existing ISS geometry if docked there.The original ISS had long X, Y & Z Keels, and backup this EELV derived space stations expands the geometry of the ISS outwards.

EELV derived space stations as stand-alone stations provide docking and backup about options for other space station operators.space stations buy and sell to one another power and docking space as well as consumables.An EELV derived space station could be lofted with Gases propellants and oxidizer and generate power with the ULA proposed internal combustion engine for power and space station reboost and would produce a great deal of residual H2O.In another blog post we proposed the ULA ACES internal combustion engine could burn a mix of ISS produced methane and GH2/GO2.

EELV derived space station architectures expand the payback on invested EELV manufacturing capacity, this might make the case for white tail Delta IV common core boosters left in partially unfinished state in order to modify into space stations later.ULA has a pie chart that explains the manufacturing costs of launch vehicles, it’s the engines that make up much of the costs so EELV derived space stations might be a profit and marketing center for EELV manufacturers.

Distributed launch of Noble gasses SEP propellant for Noble gas pressurized habitats

Distributed launch of Noble gasses SEP propellant for Noble gas pressurized habitats

Come back later today or tomorrow for the results or read our previous posts on dual use habitats as SEP propellant tanks and as habitats. Might require distributed launch of breathable atmosphere.Look up ULA’s Distributed launch.

SpaceX Dragon auto gyrating helicopter as planetary descent probe

SpaceX Dragon auto gyrating helicopter as planetary descent probe

would this work for planetary atmosphere probes and/or soft landers?

Kickstarter campaign to raise funds to hire a SBIR grant writer

Kickstarter campaign to raise funds to hire a SBIR grant writer

(A)(1) Hire the SBIR professional writer you propose to hire for that SBIR proposal to write with you the Kickstarter campaign.

(A)(2) Design the kickstarter to account for phases of research not funded by SBIR or to perform low cost research before SBIR win.

(A)(3) write design the Kickstarter campaign to account for Phase I SBIR loss but set up the possibility to perform research on a Phase II SBIR.This means the Kickstarter might be able to fund Phase I with appropriate rewards to donors

(B)(1) A related idea that can be used in conjunction with the Kickstarter campaign to raise funds to hire a SBIR grant writer would be this earlier post;                                                  https://yellowdragonblog.com/2015/06/15/intern-to-subcontractor-mentor-protege-a-model-program/

 (C)(1) Use Kickstarter IndieGoGo funds to transfer to NASA space act agreement  NASA center work on behalf of our terrestrial & cislunar exploration technologies start up.

Best use of our propellent tank ring atomizer/diffuser

Best use of our propellant tank ring atomizer/diffuser

Launch from Earth is best served with dense fuel so a heavy launch vehicle might be best served with Propane propellent CBC’s that feed into a Methane core stage using our proposed ring atomizer/diffuser in the core stage with crossfeeding.

The propane should form a slush in the cryogenic Methane or alkenes gelled in alkanes for our proposed dial a propellant with a gravity feed ring atomizer at the bottom of the core stage.

BE-3 LH2/LO2 core stage, BE-4 LNG CBC

This would be a three core heavy launch vehicle with a cluster of 8 to 10 BE-3 in the core stage and two CBC with two each LNG pBE-4’s.The Blue Origin core stage would appear remarkably similar to the SpaceX heavy core stage.

Crossfeed The LNG into a ring atomizer in the bottom of the LH2 Tank to gell it.The alternative is to have two Vulcan CBC’s on the existing Delta-IV and modify the RS-68 to take a gelled propellant for a minute and a half of flight.

Gelled Methane in LH2

 

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