Saturday, September 14, 2013

Budget Moon flights: will Canada and Europe take us back to the Moon?


Copyright 2013 Robert Clark





 Canada and Europe want to send manned missions to the Moon, despite NASA's disinterest:

Canadian on Moon possible under latest space plan.
Roadmap for future missions includes lunar space station and trips to Mars.
The Canadian Press
Posted: Aug 25, 2013 8:39 AM ET
http://www.cbc.ca/news/canada/story/2013/08/25/tech-space-station-canadian-on-moon.html

In the blog post Medium Lift Circumlunar Flights, I noted that current medium lift rockets such as the Atlas V 401, Delta IV Medium, Falcon 9 could launch a Cygnus-sized capsule on a circumlunar flight. Then if the Cygnus were provided with a heat shield and life support this would provide a low cost means of performing a manned circumlunar flight.
 Orbital Sciences is investigating giving the Cygnus a heat shield based on the inflatable ones NASA is developing:


>


  Another possibility for the heat shield would be to give the Cygnus capsule the same degree of small taper as the Dragon capsule. Then you could use the same type of PICA material, which was invented by NASA Ames, as used on the Dragon.
 Still another possibility is suggested by what SpaceX is proposing for the reentry of the upper stage of a reusable Falcon 9. The stage is a cylindrical structure, but according to the images released by SpaceX, heat shield material, presumably their PICA-X material, is applied to the entry end of the upper stage and partially along one side.



 Another possibility would be to use the capsule originally designed by Andy Elson for SpaceX, called "Magic Dragon". This was to be carried by the smaller Falcon 5 and only carry 3 crew. Since the Falcon 5 had half the payload capability to the Falcon 9 and the crew size was half of the current Dragon, this smaller version likely was also half-size, at ca. 2 mT.





 In the blog post Budget Moon Flights I discussed that two cryogenic in-space stages about half-size to the Centaur could take a Cygnus-sized capsule to an actual lunar landing and back. It will actually even be possible to do it with just one of these stages: the Falcon Heavy, according to Elon Musk, will be able to send 35,000 lb, about 16,000 kg to TLI.
 Use the same Ariane 4 H10-3 upper stage used in the "Budget Moon Flights" post. This had a propellant mass of 11.86 mT and dry mass of 1.24 mT. As discussed there, take the round-trip delta-v of 8,650 m/s. The delta-v to TLI is about 3,150 m/s. Then 5,500 m/s would have to be supplied by this single stage. The stage could carry 2.9 mT payload to greater than that delta-v:

445*9.81ln(1 + 11.86/(1.24 +2.9)) = 5,900 m/s.

 Actually, it could take 3.4 mT to a delta-v of 5,500 m/s but we are limited to how much total mass the Falcon Heavy can take to TLI.
 According to the Astronautix page on the Ariane H10-3 the cost of the stage was only $12 million. Then this could serve for a low cost demonstration mission for the Canadian Space Agency (CSA) and ESA to launch as early as the 2014 expected first test flight of the Falcon Heavy.
 It is important that such low cost missions be done to break the mindset that any manned flights to the Moon have to involve super heavy lift rockets such as the Saturn V, Ares V, or SLS.


   Bob Clark





Monday, August 26, 2013

The Coming SSTO's: Page 2.

Copyright 2013 Robert Clark

 In the blog post, The Coming SSTO's I calculated some delta v's that suggested we already have the capability to do SSTO's with significant payload. However, here I'll provide some more accurate estimates by using Dr. John Schilling's Launch Vehicle Performance Calculator page. I'll go back to the Atlas rocket SLV-3 Atlas / Agena B. The specifications are given here:

SLV-3 Atlas / Agena B.
Family: Atlas. Country: USA. Status: Hardware. Department of
Defence Designation: SLV-3.
Standardized Atlas booster with Agena B upper stage.
Specifications
Payload: 600 kg. to a: 19,500 x 103,000 km orbit at 77.5 deg
inclination trajectory.
Stage Number: 0. 1 x Atlas MA-3 Gross Mass: 3,174 kg. Empty Mass:
3,174 kg. Thrust (vac): 167,740 kgf. Isp: 290 sec. Burn time: 120 sec.
Isp(sl): 256 sec. Diameter: 4.9 m. Span: 4.9 m. Length: 0.0 m.
Propellants: Lox/Kerosene No Engines: 2. LR-89-5
Stage Number: 1. 1 x Atlas Agena SLV-3 Gross Mass: 117,026 kg.
Empty Mass: 2,326 kg.
 Thrust (vac): 39,400 kgf. Isp: 316 sec. Burn
time: 265 sec. Isp(sl): 220 sec. Diameter: 3.1 m. Span: 4.9 m. Length:
20.7 m. Propellants: Lox/Kerosene No Engines: 1. LR-105-5
Stage Number: 2. 1 x Agena B Gross Mass: 7,167 kg. Empty Mass: 867
kg. Thrust (vac): 7,257 kgf. Isp: 285 sec. Burn time: 240 sec. Isp(sl): 0
sec. Diameter: 1.5 m. Span: 1.5 m. Length: 7.1 m. Propellants: Nitric
acid/UDMH No Engines: 1. Bell 8081

http://www.friends-partners.org/partners/mwade/lvs/slvgenab.htm

 We see stage 1 called the sustainer stage has nearly a 50 to 1 mass ratio. However, the Atlas had an unusual "stage and a half" structure where engines needed to lift off from the pad were jettisoned later on in the flight, leaving only a smaller, lower thrust engine behind. This engine which is the one used in stage 1, did not have enough thrust to lift off from the pad. So as in The Coming SSTO's post,  I'll replace it with the NK-33 engine which has now flown successfully on the Orbital Sciences Antares. 
 The propellant load remains 114,700 kg as in the original Atlas but the dry mass increases to 3,086 because of the heavier engine. The vacuum Isp is 331 s for the NK-33, and the vacuum thrust is 1,638 kN. Now input these numbers into Schilling's calculator. Select "No" for the "Restartable Upper Stage?" option and Cape Canaveral for the launch site. For the orbital inclination choose 28.5 degrees to match the latitude of Cape Canaveral. Then the Calculator gives these results:

====================================================
Mission Performance:
Launch Vehicle:   User-Defined Launch Vehicle
Launch Site:   Cape Canaveral / KSC
Destination Orbit:  185 x 185 km, 28 deg
Estimated Payload:   4113 kg
95% Confidence Interval: 2860 - 5625 kg

====================================================

 This value of 4,113 kg is remarkable in being close to that of the payload capability of the full Antares at 5,000 kg, a rocket of twice the gross mass, using two stages and two of the NK-33 engines on the first stage.
 Based on this, this SSTO version could be significantly cheaper than the current Antares. Plus in being only liquid fueled, it could be used as a manned launcher. Note that Orbital already has the Cygnus capsule which with the addition of a heat shield and life support could be a manned capsule.

 The mass ratio of 50 to 1 for the original Atlas is so high it would be interesting to calculate the payload capacity if we used instead the lower Isp Merlin 1D engine. By the SpaceX page, nine Merlin 1D's have total vacuum thrust of 6,672 kN. So one is 741 kN. We will need two to lift off, at 1,482 kN vacuum thrust. The two Merlin 1D's together weigh about 330 kg less than the NK-33 case, so subtract that much from the dry mass of the NK-33 case. However, the Isp is also reduced to 311 s Isp for the Merlin:
 Then Schilling's calculator gives:

====================================================

Mission Performance:
Launch Vehicle:   User-Defined Launch Vehicle
Launch Site:   Cape Canaveral / KSC
Destination Orbit:  185 x 185 km, 28 deg
Estimated Payload:   3025 kg
95% Confidence Interval: 1952 - 4331 kg
====================================================

 It is the quite high mass ratio that leads to these rather high payload capabilities.

 SpaceX might not be inclined to support such an experiment, as they are deeply invested in keeping the Falcon 9 first stage and Merlin 1D engines. However, Orbital Sciences farms out its construction of the Antares first stage to a company in the Ukraine.  So they may be inclined to try a new stage that would at the same time prove to be a revolutionary step of creating an operational SSTO.                                                                                            

   Bob Clark

Saturday, July 27, 2013

Medium lift circumlunar flights.

Copyright 2013 Robert Clark

 In the post  "Golden Spike" circumlunar flights I argued the new Falcon 9 v1.1 would be able to do manned circumlunar flights carrying a Dragon capsule. Note that this could also prove Elon's claims that the Dragon could serve as a lunar mission capsule. Moreover, such a unmanned test could be carried out this year with the first test flight of the Falcon 9 v1.1.

This is important because the original circumlunar flight carrying Apollo 8 used the huge Saturn V rocket. Then the feeling came about that even to do a manned circumlunar flight required a super heavy lift rocket such as the Saturn V. Then showing a much smaller rocket such as the Falcon 9 v1.1 could accomplish such a mission would be important to confirming the idea that lunar landing missions also could be much smaller, and much cheaper, than imagined.

 As further support of that, currently existing medium class launchers such as the Delta IV Medium and Atlas V without side boosters, can also do circumlunar missions by using a capsule half-sized to the Dragon. One such half-sized capsule would be the Orbital Sciences Cygnus, given life support systems and heat shield, as discussed in Budget Moon flights: lightweight crew capsule

 Another possibility might be the capsule designed by Andy Elson for SpaceX for the Falcon 5 rocket. Since the Falcon 5 had half the payload capability of the Falcon 9, and this capsule was to carry half the passengers of the Dragon, quite likely it would be about half-size to the Dragon:

Magic Dragon: The UK's first commercially built manned capsule demonstrator.
By Rob Coppinger on April 9, 2008 4:13 PM | 
http://www.flightglobal.com/blogs/hyperbola/2008/04/magic-dragon-the-uks-first-com.html

  The Delta IV Medium and Atlas V without side boosters have a payload capability of about 10 metric tons (mT) to LEO. Page 2 of Boeing's "Delta IV Technical Summary"  gives the translunar injection (TLI) payload capability of the Delta IV Medium as 3 mT, sufficient for the dry mass of the Cygnus. 

 The payload capability to TLI for the Atlas V can be estimated by Dr. John Schilling's Launch Performance Calculator by selecting the escape trajectory option. This gives about 3.4 mT capability to TLI.

 The Ariane 6 is to be a medium class launcher comparable to the Delta IV Medium and Atlas V. Then the liquid-fueled version would not only have the advantage over the solid-fueled version of being able to do manned missions to LEO but manned circumlunar missions as well.


  Bob Clark



Wednesday, July 17, 2013

Budget Moon Flights: Ariane 5 as SLS upper stage.

Copyright 2013 Robert Clark

Delta IV Heavy Orion Circumlunar Test Flight.
I’m fairly sure looking at the capabilities of the Delta IV Heavy with the upgraded RS-68a engine, about 28 metric tons to LEO, that it could launch the Orion on that 2014 test launch on an actual circumlunar flight, not just to 3,600 miles out as currently planned. A circumlunar flight would result in a much more capable test of the Orion.

The Orion test is planned to only carry a dummy service module, so that will be much lighter. The flight is planned though to carry the launch abort system (LAS) so that detracts from the weight that can be launched.

Without the LAS the DIVH could definitely send the Orion on a circumlunar flight. With the LAS, it makes it a little more difficult to estimate since it is jettisoned before reaching orbit.

This makes the use of the SLS for that unmanned circumlunar test flight in 2017 even more dubious, since the DIVH could do that, even if removing the LAS is required. That is another reason why I argue NASA should be aiming for an actual unmanned lunar landing test with that 2017 SLS flight.

Low Cost Lunar Lander and Crew Module.
ULA has done studies on adapting the Centaur upper stage as a lunar lander stage so you would not need a huge, and hugely expensive, Altair lander. We already even have a crew module that could be used for such a lander in NASA’s SEV, which can be ready by 2017 for test flights:


Inside NASA’s New Spaceship for Asteroid Missions | Space.com.
by Clara Moskowitz, SPACE.com Assistant Managing Editor
Date: 12 November 2012 Time: 02:30 PM ET

If the current schedule holds, NASA could test-drive a version of the SEV at the International Space Station in 2017. http://www.space.com/18443-nasa-asteroid-spacecraft-sev.html

Ariane 5 Core as SLS Upper Stage.
NASA is considering a version of the upper stage to be used with the Block II version of the SLS that uses RL-10 engines instead of the J-2X:

SLS prepares for PDR – Evolution eyes Dual-Use Upper Stage.
June 1, 2013 by Chris Bergin
http://www.nasaspaceflight.com/2013/06/sls-pdr-evolved-rocket-dual-upper-stage/

This is expected to save on costs.

NASA also wants to encourage European participation in the proposed asteroid retrieval mission:

NASA Pitches Asteroid Capture To International Partners.
By Frank Morring, Jr.
Source: Aerospace Daily & Defense Report
June 28, 2013
http://www.aviationweek.com/Article.aspx?id=/article-xml/asd_06_28_2013_p01-01-592208.xml

Then a way to save further on development costs and to get European involvement would be to use the Ariane 5 core as the upper stage. It’s of common-bulkhead design to save mass. I recently learned it also uses the pressure-stabilized, “balloon tank”, method a la the Centaur to further save on tank mass.

The ESA also believes its Vulcain II engine can be made air-startable since this was planned for the Liberty rocket. The Vulcain uses a rather short nozzle since it is meant for ground launch, giving it a 432 s Isp. But simply giving it a nozzle extension would give it the ca. 462 s ISP of the RL-10.

Another key advantage is that because little additional development would be needed it might even be ready by the 2017 first launch of the SLS. Then this first 2017 launch of what was only to be a 70 mT interim version could have the 100+ mT capability of the later versions of the SLS. Such a version would clearly have the capability to do manned lunar lander missions.

You could also give this stage the RL-10 engines, instead of the Vulcain. The Vulcain weighs about 1,800 kg. Four RL-10′s would weigh 1,200 kg. So this would save 600 kg off the stage dry mass.

The NasaSpaceFlight.com article mentions the advantage of having different diameters for the hydrogen and oxygen tanks to maintain commonality with tooling of existing stages, and that is the reason for not having both tanks the same diameter. That would not be a problem of course with using the Ariane 5 core at a common 5.4 meter diamter. And someone noted on the Nasaspaceflight forum thread on this topic that for a uniform 8.4 m diameter, NASA could just use the same tooling for both that is used for the 8.4 meter SLS core stage tank.

For any of these possibilities it would be very good if NASA could use the composite tanks Boeing is investigating. Aerospace engineer Jon Goff on his blog noted ULA estimated their ACES proposed upgrade of the Centaur could get a 20 to 1 mass ratio by switching to aluminum-lithium for the tanks. And according to Boeing, an additional 40% can be saved off the Al-Li tank mass by using composites, resulting in an even larger mass ratio than 20 to 1:


NASA Sees Potential In Composite Cryotank.
By Frank Morring, Jr. morring@aviationweek.com
Source: AWIN First
July 01, 2013
http://www.aviationweek.com/Article.aspx?id=/article-xml/awx_07_01_2013_p0-592975.xml


Scaling up your stage mass, such as to the DUUS size, is also known to be able to improve your mass ratio. Imagine then all these mass ratio improving factors being applied. How high could the mass ratio get, perhaps to the 25 to 1, or even 30 to 1 range???

Imagine what you could do with a hydrolox stage with an ISP as high as ca. 462 s with a mass ratio as high as 30 to 1. (*)

Bob Clark


(*) By rocket equation, the delta-v is:  462*9.81ln(30) = 15,400 m/s.


Update, Sept. 28, 2013:

 Finally, NASA has acknowledged that the Block 1, first version of the SLS to launch in 2017 will have a 90+ mT payload capacity not the 70 mT always stated by NASA:

SLS Dual Use Upper Stage (DUUS).
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20130013953_2013013757.pdf

 This is important since it means we will have the capability to do manned lunar landing missions by the 2017 first launch of the SLS:

SLS for Return to the Moon by the 50th Anniversary of Apollo 11, page 5: A 90+ metric ton first launch of the SLS.
http://exoscientist.blogspot.com/2013/09/sls-for-return-to-moon-by-50th.html

Monday, June 17, 2013

On the lasting importance of the SpaceX accomplishment, Page 5: a letter to the European space industry.

Copyright 2013 Robert Clark



Subject : A low cost, all European, manned launcher.
Date :     Sun, Jun 16, 2013 07:37 AM EDT
From :     "Robert Clark" <****@****>
To :     ****@****


 This article discusses the possibility of using the ATV as a manned spacecraft:

Shifting Constellations: Europe Eyes China in Space Race.
By Kevin Holden Platt in Beijing February 08, 2013 – 03:17 PM
http://www.spiegel.de/international/europe/esa-mulls-new-alliance-as-china-becomes-space-leader-a-882212.html

 Russia and China have their own manned spaceflight program, as will the U.S. once again soon. Even India and Japan are planning their own manned spaceflight programs. The European Union has been the greatest economic power in the world or a close second to the U.S. over the last few years. European space advocates then should regard it as unacceptable that Europe has no plans to develop a manned spaceflight capability.

 The main impediment has been cost. But such costs would be reduced greatly if the focus was on small rather than large. The ATV is a large, expensive spacecraft as is the Ariane 5. But there is no need to have a spacecraft as large as the ATV simply to carry a crew, or a rocket as large as the Ariane 5 to launch them to orbit. My recommendation is instead to adapt, for example, the much smaller Cygnus, designed and built in Italy, for the purpose.

 This would allow a much smaller vehicle of Ariane 6 size to be used as the launcher. The complaint that the Cygnus does not have life support or a heat shield is not valid since that would have to be provided to the ATV as well. Another possibility for the capsule would be the 'Magic Dragon' capsule developed by Elson Space:

PICTURE: UK built SpaceX capsule revealed.
By: ROB COPPINGER LONDON 11:25 15 Apr 2008
http://www.flightglobal.com/news/articles/picture-uk-built-spacex-capsule-revealed-222995/

 For this to be the case, you would have to adopt the liquid-fueled version for the Ariane 6, eventhough the solid-fueled version has been decided upon. The Academy of Air & Space in France has criticized the choice of the solid-fueled version on the grounds that it does not advance the technology and has limited flexibility:

Academy Urges Europe To Halt Work on ‘Wrong Choice’ Ariane 6 Design.
By Peter B. de Selding | May. 30, 2013
http://www.spacenews.com/article/launch-report/35546academy-urges-europe-to-halt-work-on-‘wrong-choice’-ariane-6-design#.Ubqa4cu9KSO

 But another key advantage was not mentioned by the Academy, that the liquid-fueled version could serve as a manned launcher. To me this is an overwhelmingly important fact that needs to be mentioned in regards to their relative merits. This would be a profoundly important advance in European technology. Look at how the Chinese space program was regarded as having been advanced by developing its manned spaceflight program.

 Because of this advance, to some the Chinese space program is regarded as having surpassed both the European and American ones. I am aware of the fact that the choice of the solid-fueled Ariane 6 was largely political, shaped by the requirements of geographical return which the ESA has to follow. However, I am a strong proponent of the commercial space approach to launcher/spacecraft development. To me it is an extremely important fact that the costs to the government were reduced by 90%(!) by both SpaceX and Orbital Sciences in developing their respective launchers.

 For a commercial enterprise in the business world, if you found a way to reduce your costs by 90% that would be a development that would be hailed for decades as an extremely important advance. But because space programs are government run this is something that still is only spoken of in hushed tones by NASA.

 Still nevertheless NASA's commercial space program was a tremendous success in producing launchers at greatly reduced costs to the government. Note that NASA was forced to this because of the high cost of producing manned launchers under normal governmental financing procedures. This success then should be modeled by European space agencies in producing manned launchers even if it requires bypassing the ESA, with its geographical return requirements.

 Here I discuss how the liquid-fueled Ariane 6 could serve as a manned spaceflight vehicle:

On the lasting importance of the SpaceX accomplishment, Page 4: how the Ariane 6 can beat both SpaceX and the Russians.
http://exoscientist.blogspot.com/2013/06/on-lasting-importance-of-spacex.html


   Bob Clark

Saturday, June 8, 2013

On the lasting importance of the SpaceX accomplishment, Page 4: how the Ariane 6 can beat both SpaceX and the Russians.

Copyright 2013 Robert Clark


Europe Urged To Halt Work on ‘Dead End' Ariane 6 Design.
By Peter B. de Selding | May. 30, 2013
The academy is urging the agencies to stop work on the Ariane 6 they approved in November with a view to beginning full development in 2014. The academy-favored rocket would use liquid propulsion instead of solid, and would face four more years of preparatory work before moving to full development in 2018.
In the meantime, the academy says, Europe should focus on an upgraded heavy-lift Ariane 5 that would fly for a decade before both it and the Europeanized version of Russia’s medium-lift Soyuz rocket are replaced by the all-liquid Ariane 6 in 2027. This rocket, called Ariane 5 ME, has been in design for several years. Continued work on it was approved, alongside Ariane 6, at the November meeting of European Space Agency (ESA) governments.
http://www.spacenews.com/article/launch-report/35546europe-urged-to-halt-work-on-%E2%80%98dead-end-ariane-6-design
 The Academy should also emphasize another key advantage of the liquid-fueled version of the Ariane 6 that it could be used for a manned launch vehicle.
 Note that Russia is raising their prices to $73 million per seat or $220 million for three. This is greater than the launch cost of the full 20 metric ton class Ariane 5. The smaller Ariane 6 would certainly be cheaper than that. By producing this liquid fueled Ariane 6, Europe could also get their own manned space flights and more cheaply than by paying the Russians.
 Both Russia and China have their own manned spaceflight programs, as will the U.S. in the near, short time frame. And even India and Japan are planning their own manned spaceflight programs. The Japan case is quite notable in that their plan is to use twin cryogenic engines of similar characteristics to the Vulcain II.
 The European Union has been the highest economic power or a close second to the U.S. in the world over the last few years. It should be regarded as unacceptable by European space advocates, private, governmental, and industry, that there has been no plan to give Europe a manned space program as with these other space agencies.
 Such a manned-capable launcher could be done more quickly and cheaply by using a commercial space approach. The Falcon 9 and the Antares only took 4 years and a few hundred million dollars in development cost that had to be paid by NASA.
 I also estimate the cost per launch of a single stage version could be done for half the $127 million cost given by the Academy in that report for their version of the Ariane 6, vastly undercutting the Russians:

On the lasting importance of the SpaceX accomplishment, Page 3: towards European human spaceflight.
http://exoscientist.blogspot.com/2013/05/on-lasting-importance-of-spacex.html

 Here's an argument for producing the Ariane 6 at a faster time frame than just 2027. The Ariane 6 is supposed to be one-half to one-third as expensive as the Ariane 5. The Ariane 5 is already being used to deliver cargo to the ISS but using the very expensive to develop and produce ATV. In fact ESA doesn't want to produce any more ATV's after the last one to launch in 2014.
 But if you have this less expensive launcher in the Ariane 6 then you have a much less expensive route to sending cargo to the ISS. But then you need a pressurized capsule to transport it. Why spend the expense of developing a new small pressurized capsule when you already have one in the European developed Cygnus? (By the way this raises an interesting economic question I'll discuss at the end.)
 SpaceX is charging NASA $133 million to transport a maximum of 6,000 kg to the ISS. Note this is well above the launch cost of the Falcon 9 alone. The large extra cost is due to the use of the expensive Dragon capsule. The Ariane 6 would have comparable payload capacity as the Falcon 9 but using a 2,000 kg lighter capsule in the Cygnus. Then it could be at or above the cargo capability of the Falcon 9 to the ISS. And from the estimated launch cost of the Ariane 6 and the low cost of the Cygnus compared to the Dragon their price could be at or below that of the Falcon 9/Dragon. How's that for wanting to be competitive with SpaceX?
 Now, the Academy wants ESA to make a liquid-fueled version of the Ariane 6 instead of the planned solid-fueled one. Imagine you have that and it is being used to send cargo via the Cygnus capsule to the ISS. It's not much of leap at all that if you add life support and a heat shield to the Cygnus then you would have a European vehicle capable of sending astronauts to the ISS as well. And you could do it at a price to undercut the Russians.
 I want to argue again here for the commercial space approach for accomplishing this. The 2027 time frame for such a liquid fueled Ariane 6 is following the usual glacial pace of government financed space programs. This would be near the end of the ISS (expected) extended life time. However, both SpaceX and Orbital Sciences by following the commercial space approach were able to develop their launchers in 4 years. Commercial space is both cheaper and faster than government space.
 To do the cost sharing of commercial space though the industry partners, or their investors, would have to be convinced it could be profitable. Note that SpaceX has gotten a $1.6 billion contract from NASA for delivering cargo to the ISS. The $127 million per launch cost estimated by the Academy is coming from the large, billion dollar, development costs under the usual governmental financing approach that would need to be recouped. Commercial space has proven though that both total development cost and the portion paid by the government are a fraction of those of the usual governmental financing. Then getting a similar billion dollar ISS supply contract as SpaceX and with a development cost that, literally, might only be a few hundred million dollars, would result in such a contract being highly profitable.

 About that economic question I mentioned above, Orbital Sciences paid for the development of the Cygnus to the Italian Space Agency(ISA). But certainly the ISA would not want to turn over the full rights to the Cygnus to a foreign company. It's quite likely ISA retains ownership of the Cygnus. This becomes interesting in regards to the price they would charge for the Cygnus compared to the price Orbital Sciences would charge.
 Because Orbital paid for the development of the Cygnus they would want to recoup that cost in the price they charge. But the ISA does not have to recover that cost. This means they could charge much less. But then why would anyone pay for the higher cost from Orbital when they could get it cheaper from the ISA?
 A puzzling question. It may be Orbital retains the rights to sell the Cygnus to NASA or even for all American launches.


    Bob Clark

Saturday, June 1, 2013

Budget Moon Flights: letter to NASA.

 Copyright 2013 Robert Clark


 The cost to NASA for lunar or other BEO missions can be cut drastically, perhaps by three orders of magnitude, by following a combination of four cost-cutting approaches.

1.)Commercial space approach. SpaceX and now Orbital Sciences have shown that as much as 90% off of the development cost can be cut by the cost-sharing of the commercial space approach.

2.)Go small. NASA’s SEV weighs about a third that of Orion. Orbital’s Cygnus weighs about a quarter. Imagine how small, and low cost, your lunar mission could be if you only had to transport a quarter of the mass to the Moon.

3.)Use existing components. The huge development costs for the Apollo program and of Constellation were because they had to use all newly developed components. Those costs would be reduced greatly if you only had to adapt already existing components. No Saturn V, Ares V, or SLS, and their huge development costs, required.

4.)Use international partners. The cut in development cost by engaging in cost-sharing is already included in the commercial space approach. However, the cost to NASA can be cut even further by sharing development costs with our international space partners such as the ESA and Japan.


   Bob Clark

****************************************************************


Subject :

Budget Moon Flights.

Date :Fri, May 31, 2013 07:40 AM EDT
From :"Robert Clark" <****@****.edu>
To :****.****@nasa.gov
 Charles Bolden has said that NASA won't us return to the Moon in our
lifetime. However, it's important to keep in mind that such negative reactions
to lunar return are based on the false premise that such a return has to be
hugely expensive. It doesn't.

 Simply by going small such a return can be done for costs in the range NASA
typically spends on its lowest cost, "discovery class", planetary missions,
i.e., in the range of a few hundreds of millions of dollars. This is very
important because rather than going over the constant wrangling with Congress
about funding such multi-billion dollar missions, NASA can simply pull it out
of their discretionary spending.

  I discuss such low cost flights here:

Budget Moon flights: lightweight crew capsule.
http://exoscientist.blogspot.com/2013/04/budget-moon-flights-lightweight-crew.html

  If one uses false premises, one draws false conclusions. So it's very
important to bring to light the fact that expensive policy decisions are being
made by NASA based on incorrect assumptions.

 Given the success NASA has had at cutting costs with its commercial
spaceflight program, NASA should be directed to solicit proposals from
industry for following the cost-cutting commercial approach to produce
small-sized return to the Moon missions.

  The proposals should have as requirement to use at most a crew capsule the
size of the SpaceX Dragon, which is half-size to NASA’s Orion capsule. And
ideally the capsule should even be the size of Orbital Science’s Cygnus
capsule (adapted to carry crew), which is only one-fourth the size of Orion. 
 

  Imagine how small, and low cost, a Moon mission could be if you only had to
send one-fourth the mass to the Moon?

  Still, such a small, low cost approach, would be controversial on safety
grounds. Then the Robonaut would be ideal to test the feasibility of such a
plan:

SpaceX Dragon spacecraft for low cost trips to the Moon, page 3: Falcon Heavy
for BEO test flights.
http://exoscientist.blogspot.com/2012/12/spacex-dragon-spacecraft-for-low-cost.html

 This suggests using the Falcon Heavy test flights beginning in 2014 to do
unmanned test flights to the Moon and to NEO's with the NASA SEV as crew
capsule, "manned" by Robonauts.

 It would be even of lower cost if using the smaller Cygnus as the "crew"
capsule, instead of the SEV. In this case, when carrying Robonauts, you would
not even have to give it life-support, though you would still need to give it
a heat shield. This scenario could be done with a single launch of the Delta
IV Heavy, Ariane 5, or Atlas V 551, no Falcon Heavy needed. 

 Such a mission would have even greater significance if we used it to return
samples from the permanently shadowed craters on the Moon. That way we could
prove definitely that there is abundant water ice on the Moon that can be used
for propellant. Some measurements by the LCROSS mission tentatively have also
identified valuable minerals on the Moon. Then such a sample return could also
provide justification for commercial development of the Moon.

 This scenario with the Cygnus would require one or two half-size Centaur-like
stages. A key viewpoint for such a low cost approach is to use existing
components if possible. Then rather than developing such half-size Centaurs
anew we could use the fact that the ESA already has such stages in the H10-3.
This would actually be beneficial since the current administration wants to
encourage cost-sharing partnerships in space with our international partners
and the ESA wants to do near term robotic Moon missions. We could even use the
German humanoid robot Justin as part of the "crew":

Humanoid Robot Justin Learning To Fix Satellites.
By Erico Guizzo
Posted 17 Jun 2010 | 14:14 GMT
http://spectrum.ieee.org/automaton/robotics/industrial-robots/humanoid-robot-justin-learning-to-fix-satellites

 In addition to partnering with the ESA on such missions, NASA could also
engage in a partnership with the private ventures proposing BEO flights.
Golden Spike, Inc. would be an obvious one but so also would be the asteroid
mining ventures Planetary Resources, Inc. and Deep Space Industries. This is
because flights to many NEO's have a lower delta-v requirement than flights to
the Moon. Then the in-space stages to be used for the Moon flights could also
be used for the flights to the asteroids. Then we could have flights in the
short near term to the asteroids that returned samples that proved
definitively that NEO's can have the trillion dollar deposits of valuable
minerals that has been estimated. 

 SpaceX and now Orbital Sciences have proven that development costs can be cut
by an order of magnitude over those of the traditional fully-government funded
space projects. By following this commercial approach and also going *small*,
the development costs for BEO flights can in fact be cut by orders (plural) of
magnitude over those commonly thought needed.


 Sincerely,


    Bob Clark
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Lightweight thermal protection for reentry of upper stages.

 Copyright 2025 Robert Clark   In the blog post “Reentry of orbital stages without thermal protection, Page 2”,  http://exoscientist.blogspo...