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The problem was the change of Proton LV Rocket from multistage to propietary DLL. Chameleon, i'll recomend contact Thornton.

Take by referent the rocket's fairing .ini file (particularly the angle and number). Model yours basing on this reference.

Maybe i'll do some good fairing meshes. And an aeroshell if you later pretend go to mars with this beast XD. The ISP of EDS is 448 sec or 4394.8 Ns/kg. Both things mean the same, but Orbiter's API only understand the second. While... i'll do also the rival for Ares 5: an almost unknown...

Excellent!!! Now the only thing to adjust is the visuals :P -Your stages (again) have a diameter of 12 meters, when the core diameter is 10.17 :P. You shoud scale back on X and Y axis all the groups of the first stage except 6 and 7 by a factor of 0.845, and all your EDS, Interstages and the...

No. You shouldn't change nothing. This info is for the aerodynamical model. Your meshes in fact are already 10 meters in diameter. This is the nominal performance. The EDS should use more or less the 50% of its fuel for reaching LEO. There is nothing bad about it. I conducted a TLI with...

Well... there is a unique possible variable... burn time for both stages: For the First Stage: Burn Time = Fuel Mass * Isp * 9.81 / Thrust Burn Time = 1587300 kg * 415 sec * 9.81 M/s^2 / 21690787.1334 N = 297 seconds (Recomend you preserve the original 330 sec burn time... ) For the...

Two possible solutions: The first: copy some aerodynamics parameters of the CVEL soyuz TMA to the [AERODYNAMICS] section of your .ini file for the capsule. The second: Spacecraft3 manages a rudimentary "Capsule" aerodynamic model. The rest of stuff is on spacecraft3.dll user manual :P Good...

HMMM!!!! That's the possible reason of malfunction of Ares V... I've given Columbia42 the SEA LEVEL Thrust, not the Vacuum Thrust :P So, the vacuum thrust for Ares 5 will be... 2169078.71334 kgf (21690787.1334 N) using 6 RS 68A engines :P

Remember that the Loiter interstage structure should be ejected before the TLI :P

Nope: 15 800 000 N :P

Well, let's increase the thrust level of the SRB to 15.8 MN :P

Hmmm (oh s***) Well... Let's Try with these other masses, i hope you've read the attachments previoulsy posted by me... 'cos these are the sources of these data: 5.5 Segment RSRM: These are Ok both in thtust and in empty mass. Let's add 100 tons extra of fuel, so we reduce the specific impulse...

Whith the empty masses adjusted?

From N to Kg/Kgf: Divide the Magnitude in Kg/KgF per 9.81 (g at sea level) From Kgf/Kg to N: Multiply the Magnitude in Newtons per 9.81 (g at sea level) A rough approach could be done by moving the decimal dot to the left (conversion from N to Kg/Kgf) or to the right (Conversion from Kg/KgF to N).

Kilogram-force. It's for avoiding me the complicated conversion from lbf (pounds-force) to Newtons :P Passing from Kgf to Newtons is as easy as passing from kg to ... Newtons :P

1.2 * Your 5 engines thrust = :P In case of normal RS 68 Engines, the thrust will be 6 * 272155.422 kgf = 1632932.532 kgf Or, if we use the improved RS 68A engines, the thrust will increase to 6 * 317514.659 = 1905087.954 kgf But the Ares 5 uses the RS 68B engines, and the data for them is...

Sometimes i can be a sooo evil person.... :P Here you have more info. See my attachments. :P The sources are these and these :P

http://www.slideshare.net/astrosociety/ares-v-supporting-space-exploration-from-leo-to-beyond-presentation Maybe this could help you :P

Can you give exactly the page from Astronautix that you gathered the info? 'Cos the http://www.astronautix.com/lvs/ares.htm link has information very outdated. :( EDIT: HERE i've found the data for the Ares 5 2008 Edition. There are the masses that i based for an estimated Ares 5 2009 empty...

Well, here is a possible solution: Diagnostic exams for the teachers. The info is available in spanish at http://infierno.ticoblogger.com/2009/12/pruebas-diagnosticas-docente-una-buena.html I'll try to translate it because i doubt that all the readers understand the "costarican" spanish (this...