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What direction should NASA go after SLS?


Skyler4856

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Crazyewok, the op said: "where should NASA go after SLS". Meaning after the SLS is finished. The SLS (If done correctly) should be in service for a VERY long time. Meaning we can still use it after it was finished. After the Space shuttle was completed, NASA didn't just go and say: "Yay, we finished it. Now to make its replacement." No. They went and kept on using it for decades.

Erm yeah hense why I took "after the SLS program is finnished" to mean 30-50 years in the future. I took after SLS to mean after the program rather after the first one flys.

Edited by crazyewok
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For what purpose though ? As it wont really sort the main problem out, Earth to orbit cost. That the BIG problem. We can get to mars on chems. For a simple manned mission NERVA is just a nice luxury.

You're right, Earth to orbit is a big part of the cost problem. NERVA has probably 3 times the specific impulse of a chemical rocket, this means that for the same delta-v mission to Mars the required mass ratio drops by half. Which is a way of saying you can do the mission with like 6 multi-billion dollar SLS launches instead of 12. If the development costs are less than the cost of building and launching 6 SLS's (which seems likely), then NERVA is anything but a luxury.

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How about canceling SLS, what if it gets canceled? I would just cancel it and start working with ESA and try to coordinate to creat a common launch vehicle (CLV).

This would be based on the Ariane 5, or perhaps the Falcon 9, maybe Atlas 5? This would allow for flexible designs ranging from 9 metric tons to 30 metric tons, thus allowing for the construction of an orbital vehicle to go to Mars/Moon. No heavy launchers! And I would also accelerate the CCDev program, and try to persuade congress to accept an increase in budget to about 30 billion (double what I would start with). I would also help the ESA with a manned program, and get the RSA in on the CLV. I woud promote mass-production of CLV components to allow for amortization of the costs, as well as 3D printing, to get some rapid prototyping in.

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Nibb31 is right politicaly it wont get off the ground. It is the best way, but the best isnt all ways popular and popularity in this day and age is all that matters. And the masses are violenty opposed to anything nuclear rational or not.

We can dream though.

Okay then, lets swap Orion-style propulsion with, say, VASIMR. My point was, for long-range missions such as Mars manned missions, new and powerful propulsion systems must be developed, otherwise travel time would be significant. Orion was the highest-performing systems I knew of, which is why I put it as an example. Should better systems arrive, I would happily use it instead.

The MSL Curiosity rover takes months on a single one-way trip to Mars. Is it more effective to supply manned missions for that long, plus their stay and return trip, or is it better to develop new propulsion systems to reduce the journey to a matter of days, rather than months?

I myself would favor the latter.

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I agree. It is getting a lot tedious. I know it is a bit of a stretch, but maybe we could ask the mods to sticky an Orion thread and make it a rule that all discussion about project Orion goes there and there only? I don't think the rule would affect a lot of people. After all, there's really only one member on these forums who keeps bringing it up and subjecting the rest of us to the same arguments over and over, ad nauseam.

http://i.imgur.com/4JpEPPN.jpg

At the very least, can we at least agree to stop referring to it as "Orion" (yes, I know that was the name given to it originally) and instead refer to it as nuclear pulse propulsion? I suggest this because the capsule NASA is designing to be used with SLS is called Orion.

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Mars, to stay. Use some of the Mars Direct architecture and technologies to make it possible. Also, do more than one launch per year... that's just stupid and drives up the price per unit for the rocket.

Maybe do some NEO scouting missions, but it depends on if there's a suitable candidate.

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