A question: the presentation that contains information on the asteroid heist mission,
http://www.nasa.gov/pdf/742920main_20130419_heoc_gerstenmaier.pdf , has a table that shows the delta-v to be supplied by the iCPS and the MPCV: 2,779.23 and 1,200 meters per second, respectively. In addition, it says that a Block 1 SLS is to be used.
Can any of our rocketeers use these numbers and the characteristics of the DRO capture orbit currently being discussed in another thread to back out the required propulsive performance of the Block 1 SLS?
Edit/Addendum: About iCPS:
http://www.spaceref.com/news/viewsr.html?pid=40747
NASA Solicitation: Interim Cryogenic Propulsion Stage for the Space Launch System
Source: Marshall Space Flight Center
Posted Thursday, May 3, 2012
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Design parameters/ performance characteristics for the ICPS are as follows:
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2. Burns (accelerating MPCV) following placement of ICPS and MPCV at 975 x -50 nmi insertion point by the SLS Launch Vehicle -- three engine ignitions to achieve greater than 3050 m/s delta-V;
3. Lift Capability -- total weight of 53404 lbs which includes crew module, service module, and crew;
4. Mass -- less than 71400 lbs.;
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7. Constraints -- axial acceleration, during stage burns, not to exceed 2g; and
8. Reference Missions -- support MPCV free lunar return without crew and MPCV High Lunar Orbit (HLO) with crew.
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Isn't all we can infer about Block 1's capability pretty much right there in the quote that you provide? Orion's mass is given as 53,404 lb and ICPS is to be less than than 71,400 lb -- I'll call it 71,399 lb. So, Block 1 can put at least 124,804 lb (56.6 tonnes) into a 50 x 975-nmi. orbit. But we knew that already....