The man with the plans

[icefire]

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.

[NovaSilisko]

Initial ship mockup

From left to right:

Propulsion stage with two Merlin 1C Vacuum engines

Solar arrays (hard to see)

Centrifuge as a crew sleep module

BA-330 module

Docking port

Modified Dragon capsule + trunk (trunk is jettisoned before leaving LEO, it\'s only used to transfer supplies to the ship)

While also being the initial crew ascent vehicle, the Dragon capsule is modified to serve as an unmanned lander, and is sent into the Martian atmosphere after reaching mars. A second Dragon docks with the ship once it returns to earth to recover the crew.

[icefire]

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

[NovaSilisko]

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

Install very basic propulsion system into the trunk and deorbit it later.

The main problem right now is delta-v. The design I posted above, assuming it\'s filled with 4 tanks with 9000 kg of RP-1 each, only gets 1.6 km/s delta-v...

[NovaSilisko]

A new modular design for the fuel container and improved weight estimations tell me that, if you want to send this craft to mars using RP-1, LOX and a Merlin Vacuum engine, you need the following:

[JupiterII]

A new modular design for the fuel container and improved weight estimations tell me that, if you want to send this craft to mars using RP-1, LOX and a Merlin Vacuum engine, you need the following:

My scroll wheel burnt off.

[NovaSilisko]

I shall repurpose this design as a lunar space station.

[icefire]

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

[Kryten]

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

Think about it-by the time you need it for leaving Mars, half of your LH2 will have boiled off.

[icefire]

He said send it to mars, not getting back.

[Guest Flixxbeatz]

A new modular design for the fuel container and improved weight estimations tell me that, if you want to send this craft to mars using RP-1, LOX and a Merlin Vacuum engine, you need the following:

[thorfinn]

Long ship is loooooooooooooooooooooooong.

[NovaSilisko]

He said send it to mars, not getting back.

No, the 22 tank model has propellant for getting back.

[RedRockets]

are you doing a landing or a flyby the apollo had a venus flyby only using the last stage (S IV- and the service engine, and they used a similar wet workshop setup...or they were to use this was just a plan of course.

http://en.wikipedia.org/wiki/Manned_Venus_Flyby

[NovaSilisko]

are you doing a landing or a flyby the apollo had a venus flyby only using the last stage (S IV- and the service engine, and they used a similar wet workshop setup...or they were to use this was just a plan of course.

http://en.wikipedia.org/wiki/Manned_Venus_Flyby

Neither, a mars orbit insertion and extended stay. I\'m repurposing the vehicle to be a Manned Lunar Research Outpost.

[Guest Flixxbeatz]

Neither, a mars orbit insertion and extended stay. I\'m repurposing the vehicle to be a Manned Lunar Research Outpost.

Sounds plausible.

[RedRockets]

Nuclear Powered departure stage? Like a NERVA engine?

[NovaSilisko]

Not depicted is the Earth Departure Stage, the propellant tank shown is the hydrazine/tetroxide 'Replaceable Stationkeeping Unit', based on the Apollo service module propulsion system (The same the space shuttle\'s OMS is based on, but it used a different propellant. This uses the same prop as the shuttle)

1.3 km/s delta-v in total, more than enough for stationkeeping over a long period.

These components will all fit in 3 Falcon Heavy launches and 1 Falcon 9 launch. 2 Falcon 9 launches if you want to send a Dragon capsule with the ship on its way to the moon.

Replacement of RSU would consist of two launches, one for an EDS, and one for the stage itself. The stages delivered to the moon later have their own navigation systems, allowing them to be docked to the station without an EVA being performed. The initial one has a very basic system, only enough to deorbit itself after being jettisoned. This might seem like a lot of effort to replace the module, but it won\'t be needed very often as the amount of delta-v needed for stationkeeping is minimal, provided you are in a good orbit. As such, much of the initial propellant sent would be used to put the station into as stable of an orbit as possible without making it too difficult for visiting spacecraft to rendezvous with it.

Centrifuge is 17m across, and spins at 6 rpm to generate 0.7g. Can easily be tweaked to move slower, but 0.7 seems like it would be the upper limit for comfort at the given size). The centrifuge is also only a sleep area, and since you\'re laying down in the pods at either end, the Coriolis force is minimized on your body. Should pods contain windows? Would this help or hurt motion sickness?

Further capsules are delivered to the station via Falcon Heavy launches, for crew replacement. Future developments include additions such as multiple docking ports, allowing the station to be used as a 'rest stop' for lunar landing missions.

Current job: calculate the EDS and figure out if a Dragon capsule launched at the moon full of cargo and crew could have the ability to put itself in orbit and rendezvous with the station, or if it needs a new propulsion system (if so, a scaled down RSU could work nicely)

Minor todo: Decide exactly how the station is assembled: LIDS docking system, APAS system or Common Berthing Mechanism, or something in-house

Future: add comms equipment, work out interior of BA-330