Author Topic: SLS Flexibility: Exploration roadmap focus taking center stage  (Read 86063 times)

Offline clongton

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While I am not wildly enthusiastic about what NASA has done to the recommended configuration that the President signed off on in October 2010, the fact remains that it incorporates almost all the systems changes that we recommended. So it has that going for it. In my opinion, SLS is too big and too expensive, unnecessarily so, but be that as it may, it will work well.

CxP was depending on a 2-vehicle solution that would have cost so much that no real missions would be affordable, and made some very bad design choices that drove it over the edge, thus imploding on itself. But there is something else going for SLS as well that wasn't a factor before that may derail any attempts to kill it. There is a burgeoning commercial industry which is on the verge of stepping up and taking NASA's place wrt human spaceflight. Regardless of all the accomplishments of the past, historic glory can only carry the space agency just so far and for the last 40 years NASA has not sent a manned spacecraft BLEO. Well we have several companies on the verge of equaling that, one of whom have already orbited their spacecraft and successfully recovered it "for reuse" no-less. And *that* spacecraft (Dragon) is being designed to enable BLEO missions to the moon in *direct* competition to NASA's unbuilt Orion spacecraft. I don't believe that the Congress is willing to let the national space agency be overwhelmed by private companies doing things that NASA can't do, and for less money than NASA's minimum budget, if only to save face and not let commercial companies humiliate it. If NASA is allowed to stumble at this point then it's game over for NASA. Congress knows that and in my opinion won't allow that to happen. SLS-Orion, for all its enormous bloat, will fly.

IMHO, and YMMV.


Too big to fail... well, we've heard it before...

I hope your right... because the alternative isn't pretty and will only delay things for years or more...

Later!  OL JR :)

I hope so too. I love NASA and it would be a shame to see her eclipsed because of bad management, impotent leadership and really dumb and shortsighted decisions.
Chuck - DIRECT co-founder
I started my career on the Saturn-V F-1A engine

Offline clongton

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.....
But there is something else going for SLS as well that wasn't a factor before that may derail any attempts to kill it. There is a burgeoning commercial industry which is on the verge of stepping up and taking NASA's place wrt human spaceflight. Regardless of all the accomplishments of the past, historic glory can only carry the space agency just so far and for the last 40 years NASA has not sent a manned spacecraft BLEO. Well we have several companies on the verge of equaling that, one of whom have already orbited their spacecraft and successfully recovered it "for reuse" no-less. And *that* spacecraft (Dragon) is being designed to enable BLEO missions to the moon in *direct* competition to NASA's unbuilt Orion spacecraft. I don't believe that the Congress is willing to let the national space agency be overwhelmed by private companies doing things that NASA can't do, and for less money than NASA's minimum budget, if only to save face and not let commercial companies humiliate it. If NASA is allowed to stumble at this point then it's game over for NASA. Congress knows that and in my opinion won't allow that to happen. SLS-Orion, for all its enormous bloat, will fly.

IMHO, and YMMV.

I respect your enormous knowledge on this subject but in my opinion you are overly optimistic at where SpaceX stands with Dragon, particularly with regards to BLEO flights.

Not so much where it stands today but what it has been designed to be capable of.  Just as Elon designed the Dragon Cargo ship to meet crew requirements, so the crew vehicle is designed to BLEO standards, even though they are not yet installed. He did not design a LEO spacecraft. He designed a BLEO spacecraft that is comfortable with LEO operations.
« Last Edit: 02/25/2012 03:09 am by clongton »
Chuck - DIRECT co-founder
I started my career on the Saturn-V F-1A engine

Offline deltaV

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Now that they have deleted the 5th SSME the next thing would be to go back to the STS ET capacity and fly the SRB with the central barrel omitted, a 4-seg SRB using the new designs. It will actually perform better than the as-designed SLS. Without the US it will lift in the neighborhood of 85 tons IMLEO. Add a single J-2X powered US and it will approach 120 tons.

Removing an SRB segment changes the thrust but not the burn time, right? Scaling all the masses and forces down by 20% would scale the payload down by 20% as well. In what way does your proposal differ from a uniform 20% reduction that enables it to perform better?
« Last Edit: 02/25/2012 03:58 am by deltaV »

Offline clongton

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Removing an SRB segment changes the thrust but not the burn time, right? Scaling all the masses and forces down by 20% would scale the payload down by 20% as well. In what way does your proposal differ from a uniform 20% reduction that enables it to perform better?

It's not a "proposal" as you say. It is what the DIRECT vehicles were actually capable of. Our publicly released baseball cards all included a 20% margin built into the base masses in addition to the MR. All our calculations were verified by Aerospace Corp in Los Angles when The Augustine Commission sent us out there to be examined. And that was still retaining the recovery systems in the nose of the SRB's, a non-trivial mass, something that the SLS won't be keeping.

The math is nowhere near as simple as what you suggest. Many things are affected by the loss of the mass of the center segment. For example, the 5th SSME with it's mass is gone together with a 20% reduction in the size and mass of the propellant feed line running down the side of the vehicle and a much lighter thrust structure, along with the mass of the stretched core and the mass of the propellant contained in that stretch, all of which allows the remaining 4 SSME's to function more efficiently, which changes the aerodynamic profile of the entire vehicle. And that's just for starters. There are literally dozens of other things which also change, all of which contribute to a completely different flight profile. Calculating the IMLEO is a complex series of analyses and can't be done with a simple ratio change such as you have done. You will need to use a piece of software such as POST or some equivalent. You can do the math by hand without the software but each iteration, and there are dozens to examine and then individually iterate, will take you about a full day to accomplish - each.

Returning to a 4-segment SRB would be a major driver in many ways to a far more efficient and capable vehicle. But the SLS, at least at this time, is a 5-segment SRB vehicle and even though it will be running only 4xSSME's it still retains the thrust structure and associated core stretch and plumbing for a 5th SSME. As interesting as this discussion can be, and as dear to me as it may be, let's be careful not to allow this "sidebar explanation" to take the thread off topic. I hope I have answered your question. If you want to pursue this further there are 2 options. (1) PM me and we can do this ourselves or (2) start a new thread specific to this sidebar. I would prefer the former as I don't want to create SLS competition here. The design has been settled and it's time to work with what we have been given.
Chuck - DIRECT co-founder
I started my career on the Saturn-V F-1A engine

Offline deltaV

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Thanks Chuck, PM sent.

Offline Thunderbill

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Excuse my ignorance but I take it from the article that the second test flight will be crewed and use the Delta IV Heavy Upperstage.  When was this stage man rated?

Offline Robotbeat

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Excuse my ignorance but I take it from the article that the second test flight will be crewed and use the Delta IV Heavy Upperstage.  When was this stage man rated?

the first manned flight will be the 3rd flight of the Orion and the 2nd flight of the SLS.  Orion will fly on a DIVH for its first flight in 2017 or so and SLS all flights following.
That doesn't answer Thunderbill's question. The interim cryogenic propulsion stage for SLS will almost surely be a Delta IV Heavy upper stage.

And the first test-flight of Orion is currently set for 2014 on a Delta IV Heavy, not 2017.
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Offline edkyle99

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Excuse my ignorance but I take it from the article that the second test flight will be crewed and use the Delta IV Heavy Upperstage.  When was this stage man rated?

Clearly, ICPS will be man-rated.  If Delta IV Heavy CPS is the starting point for ICPS, there will have to be engine and flight control system modifications (to provide abort modes, etc.).  Aerospace Corp. did a paper describing the needed mods a few years ago.  It is all very possible.  There is time - likely nine years from now until the first crewed flight.

 - Ed Kyle
« Last Edit: 02/27/2012 06:23 pm by edkyle99 »

Offline Ben the Space Brit

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Excuse my ignorance but I take it from the article that the second test flight will be crewed and use the Delta IV Heavy Upperstage.  When was this stage man rated?

Clearly, ICPS will be man-rated.  If Delta IV Heavy CPS is the starting point for ICPS, there will have to be engine and flight control system modifications (to provide abort modes, etc.).  Aerospace Corp. did a paper describing the needed mods a few years ago.  It is all very possible.  There is time - likely nine years from now until the first crewed flight.

I believe that there is a thread somewhere that discusses this.  NASA has already decided what modifications the DIVHUS needs to become iCPS and published those details.
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Online sdsds

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"Interim Cryogenic Propulsion Stage (ICPS) for SLS"
http://forum.nasaspaceflight.com/index.php?topic=27737.0

Responses to the solicitation (which was only for information about capabilities, not for prices) were due Feb 7.  Note also there was a modification to the solicitation on Jan 25, 2012, with great Q&A.  http://prod.nais.nasa.gov/cgi-bin/eps/synopsis.cgi?acqid=149896
— 𝐬𝐝𝐒𝐝𝐬 —

Offline deltaV

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Suppose that funding for the large upper stage never materializes. Is there a cheaper way to improve on block 1A to lift those rare payloads that want a bit more performance?

Offline Robotbeat

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Suppose that funding for the large upper stage never materializes. Is there a cheaper way to improve on block 1A to lift those rare payloads that want a bit more performance?
Multiple launches. SEP tug.
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Offline clongton

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Suppose that funding for the large upper stage never materializes. Is there a cheaper way to improve on block 1A to lift those rare payloads that want a bit more performance?

We are a long time away from the large US for Block-2.
I suspect that a large US, but smaller than the Block-2 stage, will ultimately find its way into service, powered by a cluster of RL-10's. It will be a Block-1A1 configuration. Mind you that's just speculation, but it's what I think will actually happen, assuming that SLS actually flies. Personally I don't think Block-2 will ever become reality. It's just off-the-scale too expensive.
Chuck - DIRECT co-founder
I started my career on the Saturn-V F-1A engine

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