Landing video.https://www.instagram.com/p/BSfJDjMFzwR/Kind of bouncy on landing.
Some clear shots of flames around the legs after touchdown in the landing video.I know SES-10 is the heaviest F9 GTO launch to date with booster recovery, but how does it compare with JCSAT-16? I'm afraid I have no idea in terms of orbital parameters which launch required more dV?
Quote from: FutureSpaceTourist on 04/05/2017 08:15 amSome clear shots of flames around the legs after touchdown in the landing video.I know SES-10 is the heaviest F9 GTO launch to date with booster recovery, but how does it compare with JCSAT-16? I'm afraid I have no idea in terms of orbital parameters which launch required more dV?JCSAT-16 massed 4.6 tonnes; SECO-2 was at 9,789 m/s at 208 km.SES-10 massed 5.3 tonnes. Neither the hosted webcast nor the technical webcast showed the S2 velocity at SECO-2 -- perhaps because they knew it was going to fall short? -- but a glance at Heavens Above shows that the post-separation rocket body is currently floating in a 236x33,407 km orbit at an inclination of 26.2°.If we know roughly the amount of impulse provided by the decoupler then a little bit of math should allow us to calculate the performance difference.
Payload Stage 2 Orbit Payload Orbit Mass Delta-v----------------------------------------------------------------------------------JCSAT 14 181 x 35869 km x 23.7 189 x 35957 km x 23.7 4.7 t 3 m/sThaicom 8 384 x 89872 km x 23.7 350 x 90226 km x 21.2 3.03 t 4 m/sEutelsat 117WB 402 x 62603 km x 21.2 395 x 62591 km x 24.7 4.15 t 3 m/sJCSAT 16 74 x 34400 km x 20.9 181 x 35898 km x 20.9 4.6 t 69 m/sEchosat 23 179 x 35775 km x 22.5 179 x 35903 km x 22.4 5.6 t 2 m/sSES 10 217 x 33395 km x 26.3 247 x 35673 km x 26.2 5.3 t 39 ms----------------------------------------------------------------------------------
SES-10 massed 5.3 tonnes. Neither the hosted webcast nor the technical webcast showed the S2 velocity at SECO-2 -- perhaps because they knew it was going to fall short? -- but a glance at Heavens Above shows that the post-separation rocket body is currently floating in a 236x33,407 km orbit at an inclination of 26.2°.
I've probably just missed this, and please remove if not L2-worthy, but is it known if SES 10 had the same engines that flew with 1021 on her first flight?
It may be that this was a "burn to depletion" mission, however, and so final SECO velocity was considered sensitive.
It didn't "fall short." We have direct word on that in L2.
https://www.shelby.senate.gov/public/index.cfm/mobile/newsreleases?ID=25F3AD2E-802A-23AD-4960-F512B9E205D2
Quote from: Scylla on 04/05/2017 02:55 amLanding video.https://www.instagram.com/p/BSfJDjMFzwR/Kind of bouncy on landing. About 100ms late on MECO-3, IMO.
Here's a list of the six most recent Falcon 9 GTO missions, showing first track for the second stage and payload. I've added my rough, often inaccurate, guesses for delta-v difference. All of these had or attempted first stage landings downrange except for Echostar 23, which was an expendable flight. The JCSAT 16 stage reentered after a month after appearing to have lowered its orbit post-separation on launch day. It weighed 0.7 tonnes less than SES 10.Payload Stage 2 Orbit Payload Orbit Mass Delta-v----------------------------------------------------------------------------------JCSAT 14 181 x 35869 km x 23.7 189 x 35957 km x 23.7 4.7 t 3 m/sThaicom 8 384 x 89872 km x 23.7 350 x 90226 km x 21.2 3.03 t 4 m/sEutelsat 117WB 402 x 62603 km x 21.2 395 x 62591 km x 24.7 4.15 t 3 m/sJCSAT 16 74 x 34400 km x 20.9 181 x 35898 km x 20.9 4.6 t 69 m/sEchosat 23 179 x 35775 km x 22.5 179 x 35903 km x 22.4 5.6 t 2 m/sSES 10 217 x 33395 km x 26.3 247 x 35673 km x 26.2 5.3 t 39 ms---------------------------------------------------------------------------------- - Ed Kyle
The values you are showing for the SES-10 are after a velocity augmentation maneuver. The apogee height of Elset One was 33,460 km, about 1,200 km lower than what you are showing.
Quote from: BabaORileyUSA on 04/05/2017 06:03 pmThe values you are showing for the SES-10 are after a velocity augmentation maneuver. The apogee height of Elset One was 33,460 km, about 1,200 km lower than what you are showing.I'm using the oldest TLE listed at Space-Track, Epoch Fri Mar 31 2017 13:57:30 GMT, 14 or 15 hours after launch so time enough for one complete orbit. - Ed Kyle
Quote from: edkyle99 on 04/05/2017 06:57 pmQuote from: BabaORileyUSA on 04/05/2017 06:03 pmThe values you are showing for the SES-10 are after a velocity augmentation maneuver. The apogee height of Elset One was 33,460 km, about 1,200 km lower than what you are showing.I'm using the oldest TLE listed at Space-Track, Epoch Fri Mar 31 2017 13:57:30 GMT, 14 or 15 hours after launch so time enough for one complete orbit. - Ed KyleIsn't it odd that the stage is now at a 240 km perigee, over 20 km higher than the first TLE?