Draco burst inflated hypersonic Decelerator
The chief question here is can a brief mini burst of the Dragon Thrusters inflate a hypersonic decelerator? A additional question would be to examine the question of the exhaust gas temperature to the material of the SIAD? Siad is then jettisoned and Draco engines perform a landing burn.
the following thoughts are inspired by this NYT article I discovered on facebook
(A)(1) Prison industries manufacture everything license plates for states to decks for GSA
(A)(2)prisoners are paid sub minimum wages
(B)(1) We propose a new policy; Prison industries should be owned by a corporation owned by an ESOP that employes the prisoners
(B)(2) needs modification to ERISA and wage and hour rules
(B)(3) modify ERISA to allow for the prisoner to not have the right to roll over ESOP shares except as part of a release program ( representative payee program?)
(B)(4) life terms prisoners would be allowed to participate as well with any future roll over of ESOP funds to benefit the prisoners family
(B)(5) prisoners shall receive the minimum wage with the IRS 20% rule waived so to fund the ESOP at higher rates.
(B)(6) for profit prisons shall be owned by both the prisoners and the guards who work there,this might make for common cause between guards and prisoners
(B)(7) a leveraged ESOP could build more prisons
(B)(8) A prisoner/guard REIT could own prisons that are leased by state and federal governments
Social policy, over decades this system would transfer wealth from government prison spending to income equality to the poor and their relatives.This might make a contribution to poverty alleviation and less crime committed by future generations. In the case of the private prison owned by both the guards and the prisoners could lead to novel ESOP team building plans that lead both parties to recognize their common cause to make a profit from the states prison spending.Would this lead to less prison violence over time?
We have proposed a propellant/pressurant gas tank with LXe or LAr that expands to a gas to pressurize LH2 , LO2 and Liquid Methane propellant tanks
LH2 and/0r LO2 boil off refrigerated the LXe before gas expansion as a pressurant gas
This in principle should be able to use LCH4 boil off as well
Presserant gases now act as fuel for an Ion propulsion engine, however, the gases Xenon or Argon must have some Gases hydrogen or oxygen residuals ratios mixed in, Can we run this through the ion engine? if not then we need a Liquefaction fractionation unit to remove the Xenon from the hydrogen/oxygen/Methane by cryogenic liquefaction.Possibly this system is integrated with near zero boil off cryocoolers proposed for long term space flight.
Possibly the cryocooler/liquefaction systems could allow refueling of a cryogenic chemical stage that utilizes Argon/Xenon ullage gases by returning the noble gasses to a cryogenic state and removal back to the cryogenic LXe tank.The problem here would be Gases Xenon becoming miscible with the LH2.There is a possibility that using residual gases H2 and O2 to fuel a small rocket engine might also be ruled out by Noble gasses as propellant pressurant.
Removing Methane residuals from Xenon ullage gases or are noble gases miscible in Liquid Methane? And at what rate?
http://www.pd.infn.it/~conti/xe.pdf
Density
Xenon Gas 421 Kg/CM -3
Xenon liquid 1987 Kg/CM-3 under pressure
Boiling point
1 ATM Xenon gas 9.86 KG/CM-3
1 ATM Xenon liquid 3057 KG/CM -3
1 liter of LXe produces 550 liters gas
In our chemical in space stage, this would be under pressure.
Methane boiling point -258.68 °F
Argon boiling point -302.526 °F)
Krypton −244.147 °F
Xenon boiling point −162.578 °F
Xenon has a much lower boiling point to cryogenic Methane so it might mean that it would freeze and gell with LCH4(and LH2) Gelling as ice crystals being a somewhat different from Miscibility! Both over time is most likely an unwanted outcome.(A)So missions involving a complete chemical burn followed by the start of ion engine operations might make sense over long term ZBO of LH2.(B) Liquid Argon has a much lower boiling point to that of Liquid Xenon so this might imply slower gelling or miscibility with liquid Methane(somewhat LH2)? (C)So LAr might be the better choice with trades as to its performance as an ion propellant stored in the tanks as ullage gas.(D) Liquid Argon might make a better choice in the case of longer duration ZBO of Methane propellants with assistance from a Liquefaction fractionation unit slaved to the ZBO unit.Can Liquefaction fractionation unit process out Liquid Argon out liquid Methane if needed?And would you really want to have to do this? ZBO Methane chemical stage might not be able to be compatible with an ion engine system over long periods of time but could be a solution to periods intermediate in nature beyond the 5 to 10 day loiter capabilities of the EUS (SLS)
(E) using staging of a in space upper stage(chemical) and a third stage ion powered stage is a known efficient use of the rocket equation, using the chemical stages propellant tanks with Noble gases as ullage involves a lot of noble gases mass and would be a stage much larger than the proposed ARM (10 metric tons of Xenon)So the question here is the in space stages chemical propellant tank PSI/Bar/ATM limits,what does this represent in molar mass of noble gasses? Is there a trade to strengthen chemical in space stages propellant tanks to be able to handle a higher noble ullages gas propellant load? (F) such a hybrid stage is with the mass of the solar array and the mass of the chemical engines that have not been jettisoned are subject of study( there are images of the SLS/EUS with a very large solar array)(G) such very large Ion powered stages could transfer very large cargo payloads beyond the capabilities of the ARM
greetings to Mr Borowski,
Con ops
EUS Skylab-II performs burn to(based on system mass) to
(A) GTO( a heavy variant)
(B) Highly elliptical Lunar orbit crossing and flyby trajectory
(C) Direct to L-2
EUS LH2/LO2 is pressurized with Argon/Xenon ullage gasses after chemical stage burnout a IVF system utilizes any remaining propellent however the Argon/Xenon system retains the ullage gas bottle and lines(formerly Helium)
If the propellent tanks can handle a known PSI of chemical fuel then the same PSI of the Argon/Xenon pressurize gas using the ideal gas law should tell us how many moles of Argon/Xenon gas are available to an ion powered engines
The hybrid nature of this chemical/ion powered SLS EUS greatly enables the capability of the SLS launch system as the mass of the propellent tanks are performing a repurposed double duty and the mass of the noble gasses and the tank and line system should make for good ratio or gears in with the ion powered engines
We have however imagined a yet another more powerful idea that extends this system even further,The habitat itself the proposed skylab-II that is it self repurposed EUS tankage would also be pressurized with Argon/Xenon to feed the EUS ion engines, perhaps the Argon/Xenon in the Skylab-II is expended first so that the habitat can be pressurized with a breathable atmosphere and the EUS now has a maximized fuel load for extended missions after deploying the habitat
The Argon/Xenon EUS is in fact a very large version of the proposed ARM mission and would benefit from ARM mission design.The EUS in the mars system depleted of noble gases could be refueled by some future chemical fuel depot so it would require the EUS to have long-lived deep space avionics.Future fuel depots should also have cryogenic Argon/Xenon on hand.This would require the knowledge of the gear ratios of cryogenic ion engine propellants stockpiled from an Earth based source
We think this makes sense only in the case of self ferry of the EUS back to earth from Mars orbit under ion engine power to pick up another cargo.Fuel depots that have some boil off of LH2/LO2 and perhaps LCH4 could keep Noble gases cryogenic to refuel the EUS ion engines.
In nuclear reactors Noble gasses are neutron poisons, would a noble gas upper/in space stage provide some protection against deep space radiation?( see our previous posts on this topic)
Parallel development of the ARM and Ion powered hybrid EUS might make for synergys,ion powered EUS is much to big for most ARM proposed missions( very large cargo missions) yet a ion powered EUS could enable beyond Mars cargo missions very large asteroid as resource missions
Future versions of this hybrid engine could have in space removable chemical engines(for reuse?) or refuel with cryogenic propellants back in cislunar space
It is hoped this would lead to incorporation into any future EELV in space stage such as the proposed ACES
Edit
The ARM ion propulsion system could inform us as to whether a much larger EUS SEP could be scaled up, we might need for example a space based air liquefier to remove Argon/Xenon for Oxygen/Nitrogen in the skylab-II or remove Oxygen/Hydrogen from the EUS (remove the noble gasses and vent remaining H and O to the ULA IVF)
Con Ops
Spent stage in GTO or in super synchronous orbit after payload deployment
equipped with;
wrap around solar array
station keeping thrusters(also Ion powered)
Argon/Xenon ullage gas to pressurize empty propellent tanks***
Ion engine
GPS transponder
Electra or Electra light interplanetary radio
NEO Scout and/or Cubesat type payloads integrated into spent stage but also can deploy same
(A)(1)Removes all GTO spent stages into heliocentric or cis lunar orbits(A)(2)GPS transponders demonstrates and sells data from cislunar and DRO(A)(3)Argon/Xenon Ullage gas/pressurent allows spent stage to become long-lived Ion tug***(A)(4)Electra radio allows for a fleet of NEO scouts and cubesats to relay with “spent stage” mother ship(A)(5) GTO spent stage as mini-me ARM mission?(A)(6)GTO spent stage with GPS lowered with Ion engine to GPS fleet orbits(A)(7)GTO spent stage ion engine lowers a secondary payload to internet fleet orbits(A)(8) other hosted payloads on spent GTO stages
SpaceX GTO stage manufactured in Seattle
Centaur GTO with LCROSS becomes standard Heliocentric disposal model with ion engines and secondary payloads
An earlier post describes the fact it takes less Delta V to raise a spent stage to a lunar orbit/flyby apogee from GTO then to deorbit from GTO***
***This coupled with an ion powered Spent GTO stage sets the stage for the business model of selling data from NEO’s and even Deimos and Phobos,selling data relay services to
seeking Mentor protegé
Veteran small business set aside
Steven Torry Rappolee
Terrestrial & Cislunar Exploration technologies
A Post 9/11 Veteran owned concern
810 334 4374
Fax 810 449 5484
UM Flint Student Business Incubator, #207
423 North Saginaw Street,Flint, Michigan, 48502
Con ops
Build skylab-II every three years or less
(A) This is 3 to 4 Skylab-II’s built per decade
(A)(1) Serial production lowers costs for Skylab-II and also SLS
(B) GEO ISS/Skylab-II
(B)(1) Requires a merger of ISS/SLS budgets by 2028, this makes it policy that the payload is Skylab-II for 15 years or more or 4 to 5 vehicles
(B)(2) Requires commercial cargo and crew to GEO!
(C)LDRO
(C)(1) Supports ISRU with captured asteroid later in 2028( a delay in favor of Deimos boulder)
(C)(2) Supports DBRM science and ARM science
(C)(3) Supports teleoperated Lunar Science
(D)Commercial crew and cargo to GEO ISS/Skylab-II
(D)(1) requires that the chemical second stage from cargo and crew flights be dual fueled with Xenon/Argon Ullage gas for ion powered disposal to heliocentric orbits
(2)provides for Cubesat missions
(3) salvaged ISS truss’s and modules and merges ISS budgets with the Skylab-II series budgets
(4)Skylab-II to DRO and Orion from LEO to LRO as well as Orion from GEO to LRO.
(5) Commercial cargo to DRO, Orion crew to DRO
(E)Skylab-II to Deimos
(1) Most likely ship number 4 late in the 2020’s
(2) Supports Mars telerobotics
(3) Supports prepositioning of cargo for human crews
(4) Builds on the ISS experience
The Grand challenge uncrewed shakedown cruise challenge; Orion VS Dragon
(A)(1) Falcon Heavy launches two Dragon capsules one with a dragon trunk, after Mars trajectory burn Dragon and Trunk shall separate and turn and dock with second Dragon and extract.
(A)(2) Second Dragon is Red Dragon and performs Mars EDL possibly an aerodynamic deceleration experiment is performed with subsequent EDL
(A)(3) Dragon and Trunk perform mars flyby and Earth EDL test
(B)(1) SLS and Orion with Deimos derived ARM as secondary payload
(B)(2) Orion docks and extracts ARM post Mars trajectory burn, good practice for future missions!
(B)(3)Orion performs Mars flyby followed by Earth EDL
This is a friendly competition meant to inspire the public to further fund space exploration, both after all provide an Apollo 8 moment of a grandeur as photography shows us the mars approach and earth approach
Possibly the Orion and Dragon could have a common docking mechanism so that on the way back from Mars both spacecraft could perform the first ever docking in space by automated spacecraft. Commercial crew special studies funding could be used for this
Both projects should share PI’s and co investigators as well as data and lessons learned
Mars 2020 and uncrewed Orion co-manifested on one SLS flight?(70 Tons to LEO)
(A)(1) Saves $ 350 Million from EELV launch costs to Mars 2020
(A)(2) use this savings to build second Mars 2020 spacecraft(like MER)
(A)(3)fly EML-2 with one of the Mars 2020 spacecraft for a Orion shakedown cruise on a mars fly by instead of Lunar flyby,captures the public imagination!
(A)(4) fly second Mars 2020 co manifested on a SLS or Mars sample return; this is Mars 2022 or Mars sample return with a ARM deimos bouder return
DUPIC as a molten salt reactor fuel
https://www.linkedin.com/groups/CANDU-reactors-in-China-use-7415001.S.5843821112886075396
(A)(1) Declad PWR/BWR fuel assemblies
(A)(2) Remove pellets from matrix
(B)(1) Directly input DUPIC fuel into Molten salt reactor(DI-DUPIC/MS)
Yellow Dragon, a mission to repurpose existing ideas into new ideas 