Points of interest include:2. What appears to be a minimum thrust single engine ullage burn starting half way through the flip at 2:40.
Can someone here please calculate from available data what is performance of expendable F9 1.2 block 3 and expendable F9 1.2 block 5 to GTO (with some reserve for sending 2nd stage to graveyard orbit)
Quote from: Rebel44 on 07/06/2017 08:31 pmCan someone here please calculate from available data what is performance of expendable F9 1.2 block 3 and expendable F9 1.2 block 5 to GTO (with some reserve for sending 2nd stage to graveyard orbit)There are no available data on Block 5 right now.
...There are no available data on Block 5 right now.
Quote from: Rebel44 on 07/06/2017 08:31 pmCan someone here please calculate from available data what is performance of expendable F9 1.2 block 3 and expendable F9 1.2 block 5 to GTO (with some reserve for sending 2nd stage to graveyard orbit)If you mean direct to GSO, then my my calculations Block 3/4 will put about 1200 kg and Block 5 about 4000 kg direct to GSO. The spacecraft RCS can probably handle the move to graveyard orbit, it's a >1 second burn on a 38% throttled MVac.
Quote from: envy887 on 07/06/2017 08:56 pmQuote from: Rebel44 on 07/06/2017 08:31 pmCan someone here please calculate from available data what is performance of expendable F9 1.2 block 3 and expendable F9 1.2 block 5 to GTO (with some reserve for sending 2nd stage to graveyard orbit)If you mean direct to GSO, then my my calculations Block 3/4 will put about 1200 kg and Block 5 about 4000 kg direct to GSO. The spacecraft RCS can probably handle the move to graveyard orbit, it's a >1 second burn on a 38% throttled MVac.Yeah, I mixed up GTO and GEOThanks for the estimate!
The Formosat-5 mission had an unusually light payload of 475kg, and so there was a lot of excess ΔV available. A conventional mission profile would require at least two S2 burns: first to an elliptical orbit, and a second circularisation burn at apogee. But Formosat-5 was delivered to a 730km x 717km orbit with a single S2 burn. So what then was the mass penalty for this? Here is a compari-sim between Formosat-5 and a modified BulgariaSat profile, also with a 475kg payload, and polar injection to a 725km circular orbit.
The FCC STA for mission 1346 (the FH Demo mission) has the coordinates for the ASDS landing of the core booster about 340kms downrange from LC-39A. This corresponds with an extremely lofted trajectory, not unlike that used for Formosat-5. In the Formosat-5 case, a single S2 burn took the satellite to a circular orbit. What could FH achieve with a similar profile?Here is a speculative FH simulation bounded by an ASDS landing about 340kms downrange, and a 6mT payload, the same as advertised by SpaceX to GTO. By tuning the orientation towards the end of the S2 burn, it is possible to set the perigee of the orbit achieved to a suitable re-entry altitude about 5.5 hours after lift-off. Entry velocity would be about 10km/s.
What are you using as the simulator?