Interim Cryogenic Propulsion Stage For SLS Orion Flights
NASA Solicitation: Interim Cryogenic Propulsion Stage (Space Launch System)
“NASA/MSFC is hereby seeking potential sources to provide an Interim Cryogenic Propulsion Stage (ICPS) for the early Space Launch System (SLS) missions. Recently, NASA announced the architecture of the SLS with a manifested first flight in late 2017. The early flights of the SLS architecture will require the use of an ICPS to ensure the placement of the Orion Multi-Purpose Crew Vehicle (MPCV) and/or Payload on the required trajectory. In order to support the flight schedule, the initial ICPS flight unit must be delivered to Kennedy Space Center (KSC) no later than late in the fourth quarter of the 2016 government fiscal year (GFY). The second flight unit must be delivered to KSC by the fourth quarter of the 2020 GFY. NASA is seeking in-space propulsion capabilities with performance data that can meet its schedule and funding constraints.”
Looks like the ULA has a chance to get their ACES upper stage booster technology funded for free.
Marcel F. Williams
This is for existing upper stages so that they can meet their schedule, not for any new development.
And so the trough is topped off for the porkers…
Oh it’s very likely to be an EELV-derived pork product. The J-2X upper state is a separate thing. ICPS has been described before as “Delta IV kick stage” so expect bids for some kind of Boeing-flavoured RL-10 stage. Hey at least it’s not Fregat, so it should be safe from space-evildoers on the shadow side of the planet.
Why would SLS need an upper stage to place Orion in orbit? It would seem to me that two 4-segment Shuttle SRB’s and an ET-derived core with SSME’s could place 250,000 lb in LEO, just as the STS did (we just brought 200,000 lb back in the form of the Orbiter). I would think it would even have slightly better performance due to the smaller cross-section (i.e., less drag) and in-line thrust from SSME’s (not canted as on STS). If we can’t do that in 5 years, NASA ought to be eliminated (at least the HSF portion of NASA).
Would someone please explain to a dumb ground systems guy why we can’t have a 110 Mt SLS right out of the gate with this method? The only structural mods I see are redesigning the LO2 ogive tank to a cylinder, adding boattail with SSME thrust structure, and payload adapter. I know it’s a little more complicated that that, but c’mon. Adding 5-segment SRB’s and a stretched ET core with RS-68’s should get a Block 1 upgrade into the 130 Mt range easily. I guess NASA just doesn’t want to succeed.
You realize that the ICPS is not being used to place Orion to LEO right? It’s being used to place Orion in a Lunar Orbit.
If you can check Aviation Week, they explain that due to tight budgets, they are looking at obtaining an upper stage for two SLS test flights in 2017 and 2021. This is not a new development. This is for two test flights.
I assume that it would have the capability to carry Orion but might not be the final choice if they need higher launch weight capability.
And that the two test flights need to inject the payload into a lunar return orbit before the SLS upper stage is ready and perhaps before a service module is ready