kraisee - 11/5/2007 4:21 AMI won't be around tomorrow to field questions, but let me have a stab at these ones so far...Marsman: The 232 can place a 38mT LSAM into LEO immediately and perform a routine EOR-LOR mission in precisely the same fashion as Ares-I/V.However, with 45mT of lift capability, the CLV flight has a 'spare' 23mT of performance available on top of lifting the Orion to orbit. This extra capacity is not initially required, but as the program evolves and confidence is built with the equipment, it could be utilised to increase performance later for almost no additional cost.
Extra payload can theoretically be transferred to the LSAM during the 3 day voyage between the Earth and the Moon. The most logical material to transfer would be a single type of propellant or oxidixer. Note: For safety only one or the other should be transferred, not both.
This general technique also applied to the 232/232 LOR-LOR mission profile available later too. The first 232 is capable of launching a 48mT, partially fuelled LSAM to Lunar Orbit. The second brings the 22mT Orion and 28mT of extra propellant to the LSAM. The propellant is transferred to the LSAM prior to descent, and suddenly you have a 76mT LSAM in Lunar orbit and you're still only using a 2-launch strategy based on one single launch vehicle design.
JIS - 11/5/2007 9:00 AMAre those 3 RS-68 inline ... or in star :. arrangement? If it is the star one there will be somewhat higher bending moment for the two engine core than for Ares 1 / Ares 5 config. Could the recent Orion with LSAM stand this lateral load?If it is an inline config can 3 engine nozzles fit under the 27.5' core? Ofcourse, there could be some aerodynamic (debris) shield above them with wider and loger thrust structure.
Jim - 11/5/2007 2:06 PMThere isn't a lateral load for a .: 3 engine configuration. It is symmetrical
JIS - 11/5/2007 8:17 AMQuoteJim - 11/5/2007 2:06 PMThere isn't a lateral load for a .: 3 engine configuration. It is symmetricalBut there is also Direct with only two engines. Anyway, its inline config.
JIS - 11/5/2007 6:07 AMIf I understand that correctly you are requiring to scrap current Orion SM proposal.
clongton - 11/5/2007 9:09 AMQuoteJIS - 11/5/2007 9:00 AMAre those 3 RS-68 inline ... or in star :. arrangement? If it is the star one there will be somewhat higher bending moment for the two engine core than for Ares 1 / Ares 5 config. Could the recent Orion with LSAM stand this lateral load?If it is an inline config can 3 engine nozzles fit under the 27.5' core? Ofcourse, there could be some aerodynamic (debris) shield above them with wider and loger thrust structure.3-Engine is in-line with aerodynamic skirts, like Saturn-VOutboard engines gimbal, center engine fixed, again, like Saturn-V
JIS - 11/5/2007 6:51 AMWhat is the performance margin for the new components (EDS, Core, shrouds)?
kevin-rf - 11/5/2007 3:10 PMSo Chris, any chance of getting Dr. Doug Stanley back to comment on Direct 2.0?