Halo_003

No love for us East Coast players? Over 1k hours here.

You never notice how lame KSP's stock sun is until the sun flare mods get broken.

I would kick some butts for the ability to use ion engine clusters with RCS controls.

Derp, good call, wasn't thinking of that.

Why would they need a diameter change to use CH4+LOX? Also, do you know by chance what temperature they're using for the LOX?

Additional warning: Be safe and don't get SWAT'd if you take up the challenge here. Especially if you're in America.

That looked for the most part to be a bunch of old dudes in the video. Should be fine regardless of age, but for RC planes that big I'm pretty sure it would take some sort of license.

I should have put that in, RSS is Real Solar System for KSP. I would have attached the Excel file but I'm not sure how frankly. Very interesting! I have a few questions though: How would I run the program you made for me? (Thank you!) I have Matlab but haven't ever used it. Or, how would you do it in Excel? If for I wanted to compare switching the first stage to run on LOX/Methane, how would I figure out the amount of CH4/LOX? Is there an easy way to do that? Why does changing the mass ratio of the first to second stage affect it so much? Currently 21.3% is assigned to second stage, and the remaining 78.7% is the first stage.

Hi, this may or may not be the right place. I'm making my own fuel tanks for use in RSS, just for fun really, but I'm trying to work out the math behind it. So I have it set up in 2 stages, both LH2/LOX fueled, at a 6:1 mixture ratio. I'm assuming 95% of the volume in each stage is available volume for fuel, which is sort of a guess. I'm using 381s ASL, 455s VAC isp. So each tank is a 6' radius cylinder. Stage 1 is 140' height, stage 2 is 40' height. I figured out volumes etc, and worked all of this out in Excel, I just want a math check to see if I'm doing this right. Assumptions: ISP @ VAC: 455s ISP @ SL: 381s 95% volume of each cylinder is available for fuel storage. (referred to in Excel as Efficiency) Stage 1 height: 140' Stage 2 height: 40' Stage radii: 6' (both) Went from liters to kgs of fuel by multiplying by density of O2 and H2 (1.1417kg/L O2, 0.07078kg/L H2). Used volume ratio of SS ET to find amount in liters of each fuel per stage. (72.81% volume is H2, 27.19% volume is O2) The +5000kg, +10000kg, etc relates to payload capacity. Am I on the right track here? To simplify the math some I just used SL ISP for Stage 1, and VAC ISP for Stage 2. So this would result in a maximum payload of less than 10,000kg, or am I missing something? If yes, how could I modify it to reach a 20,000kg payload to LEO? *SS kg/L refers to the weight to volume ratio of the space shuttle ET just as a sanity check.

No worries, sorry if that came off harshly, it's just one of my earliest memories and I take it very seriously.

edit: removed

Why ask the question if you aren't prepared to hear the answers? I typically just put 4 Vernor engines at the top of the first stage.

Wouldn't the hours and days part depend on orbit inclination? If it went to a polar orbit it could be just a few hours couldn't it?

The moon will be the first one, as a proof of concept for one on Mars IMO.

IMO, priorities should be: Unity 5 Stable 64 bit Long term purpose/mission for rovers/orbital probes Refinishing rocket parts like the jet part treatment. Antennas I am totally okay with pushing antennas back, I have RemoteTech to use in the mean time. There's no mod for 64bit and Unity 5.