starplayer

Tried that, my craft went right trough the station. I don\'t think collision works. Although the thrust from my engines affected the rotation of the station.

Not as nice as mine, I\'m afraid ;P

You should point that maximum efficiency is reached when the velocity is less, so some times it\'s more efficient to move to a higher orbit and change the inclination there, and then move the the lower orbit. http://en.wikipedia.org/wiki/Orbital_inclination_change

Now it\'s correct, 95701

My mistakeXD

No one beats me? I want a challenge

Seems like the problem was indeed with time compression. 4x time compression works okay though. Got 1 338 702 Beat me

Could someone please post a map viewer pic of the your 500 000 ish landing spots? Cos I think my Kerbal is broken in reading the distances, sometimes if I go further, the ground distance is less wtf. So I want to know what is the correct 500 000 distance. I\'d really apreciate your help guys. In my game it says this is at a ground distance of 192665.9. Is it about right?

Hey mate, I think the Specific impulse of the engines depicted in the stage and multi stage calculators should be in m/s, instead of s. Thanks a lot for your work btw, it helps a lot=) Edit: Forget it, it's okay in the latest version=P thanks again

Oh right, thanks a lot, that thing slipped me. =) However, the specific impulse in the KSP calculator is in seconds, I'll message the creator of the calculator. Thanks again

I've been reading more, and in this article http://en.wikipedia.org/wiki/Specific_impulse , in the Examples part, you can see that the specific impulse for the listed liquid engine is only 450, with an exhaust velocity of 4400, which comes from 450*9.81. The specific impulse shouldn't be equal to the exhaust velocity. The Kerbal liquid engine's specific impulse that is in the wiki, 5682 s, is greater than that of a Ion thruster, that can't be right. I think the liquid's engine specific impulse is only 5682/9.81

Hi guys. I'm using the data from the KSP calculator, using a simple stage with just one liquid fuel ttank and one engine. So, to calculate the Delta V by the Rocket equation, it is DeltaV = Ve * ln(m0/m1), where Ve is the effective exhaust velocity, m0 is the inicial mass, and m1 is the mass after burnout. Ve = Specific Impulse / g at surface according to wikipedia. Using the data from the calculator, Ve=5541 * 9.81=54366 m/s and Delta V = 54366 * ln(4500/2300) = 36488 m/s, which is obviously wrong. Can somebody tell me where's the error?