icefire

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The real question is if you could tell the difference between simulated and actual events.

This tool is awesome

Well, given that most planets orbit with low inclinations relative to the ecliptic, most interplanetary missions have a 10 degree variance at most. What this means is that it would be plausible to have an orbital refueling depot at somewhere like the Earth-Sun L2 lagrange point that\'s available for most missions to other planets. With only minor plane corrections needed after refueling and final orbit injection. So no, course variance isn\'t the largest hurtle for such an installation. It\'s simply finding a cost effective way to get it up there in the first place.

Besides when it does. How about \'Harvest\' or something similar

Last person to post is the last person to post Tautology round 2 GO.

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Post of the year 2011

DV capacities, though any real rocket will have lower values as these are calculated assuming that nothing but the booster itself is being used. RT-10: 6210 m/s RT-20: 7985 m/s RTX-20: 5803 m/s RT-B20: 10.5 km/s

He said send it to mars, not getting back.

Has RP-1 ever been used outside of a launch propellant? It\'s pretty heavy and has a lower Isp than LH2

So guys have you ever made model rockets or something similar? ponies

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So the trunk just stays in orbit? Doesn\'t help the space junk problem does it?

The other way? :S I don\'t understand what you\'re trying to say. Sea level thrust is 2,950 kN so... 2950000/767097=3.84 Still can get off the ground. Edit: I probably am wrong about the mass weight thing? Ohh well I have to go to work so I\'ll have to deal with being an idiot later.

T/W = 3370000/767097=4.39 It\'ll get off the ground. Also you mislabled the statistics, what you listed is weight, not mass. Weight = Mass*g So Mass = Weight/g Full Mass = 767097/9.807=78,219kg The DV capacity is still accurate though, as the weight and mass values are proportional.

would you rather have a job that paid $80k, had flexible hours, and you got 7.5 hours of sleep a night or one that paid $140k, long hours, and 6 hours op + (1/2)*\[Rho]* U^2 - (1/2)*\[Rho]*(-2*U*Sin[\[Theta]] - \[CapitalGamma]/(2*Pi*R))^2f

I was going to make a counter argument but I can\'t right now my brain has the dumb

Seeing the image uses an RS-68, and has an MPCV docked to it, I am assuming this isn\'t supposed to be for kerbals. How about a section for some actual research?

is 12 km/s enough to orbit when you incorporate drag from the atmosphere? edit: apparently it is, 10 km/s is the rough dv requirement according to wiki Regardless I feel like something is wrong with the numbers here, if SSTO with a 20,000kg payload was this easy we would have done it ages ago.

Low energy transfers are too sloooooooooooooooooooooooooooow

If the tank were to stay in orbit it would need a form of reflective coating to deal with heat/uv light problems, even a simple paint job would be better than exposed tank insulation. The only reason there isn\'t one on the shuttle tank is because it doesn\'t stay around long before breaking up during its sub-orbital reentry

Fun fact the tracks that will be left behind by MSL\'s wheels will spell out \'JPL\' in morse code

or you can watch it on nasa\'s channel