Given that B1046 and B1049 are on the West Coast..... only B1047 and B1048 remain (in theory) on the East Coast ....... As a result, the only booster that is realistically available for PSN-6/GTO-1 is Falcon 9 B1047 for what would be its third launch.
fromhttps://www.teslarati.com/spacex-falcon-9-booster-highway-spotted-radar-satellite-launch-slip/QuoteGiven that B1046 and B1049 are on the West Coast..... only B1047 and B1048 remain (in theory) on the East Coast ....... As a result, the only booster that is realistically available for PSN-6/GTO-1 is Falcon 9 B1047 for what would be its third launch.That reasoning could be wrong: I can't see how they ruled out B1047 being the inflight abort test and B1048 being Nusantara Satu. However, it does seem more likely the other way around as they have more time for any integrating work with B1047 and Nusantara Satu both present. (Is this an issue, when did B1048 arrive at CC?)
Is the IFA even close enough to have had a booster assigned to it?
Beresheet would want zero inclination correction. The Moon's orbit is inclined ~5.14° above the ecliptic - which is ~23.4° above the Earth's equatorial plane (equal to the tilt of the Earth's axis). That comes to ~28.5°, which is - not entirely coincidentally - the inclination you get by launching due east from Cape Canaveral.Any inclination change to assist Nusantara would have to be undone by the lander. So I would expect a greater apogee in preference to inclination change.
Quote from: jcm on 02/11/2019 08:32 pmQuote from: Lar on 02/08/2019 04:41 amFor the record, "Nusantara Satu" translates exactly to "one archipelago" (word order gets reversed so Satu which means 1, comes first) without "Indonesian" in it.I asked my wife, a native Indonesian and teacher of Bahasa Indonesia (Indonesian language) to non Indonesian speakers, and that's what she told me. The material in the intro post isn't quite right, it has too much stuff in it. That's very odd since they have also talked about a second sat, Nusantara Dua :https://kumparan.com/@kumparantech/april-2020-psn-luncurkan-satelit-nusantara-dua-pengganti-palapa-d-1548246721064822411Doesn't contradict what I said. My point is that "Indonesian" isn't part of the name, except allegorically (in that Indonesia occupies the vast majority of the largest archipelago in the world) because nusantara just means collection of islands. The header got fixed by gongora to remove that. satu dua tiga empat lima enam tujuh delapan sembilan sepuluhone two three four five six seven eight nine tenIndonesian is an interesting language. It lacks tense, plural, and gender for the most part, and many words are overloaded. Kepuluan means both island and archipelago depending on context. Pulua just means island and nusantara just means archipelago.
Quote from: Lar on 02/08/2019 04:41 amFor the record, "Nusantara Satu" translates exactly to "one archipelago" (word order gets reversed so Satu which means 1, comes first) without "Indonesian" in it.I asked my wife, a native Indonesian and teacher of Bahasa Indonesia (Indonesian language) to non Indonesian speakers, and that's what she told me. The material in the intro post isn't quite right, it has too much stuff in it. That's very odd since they have also talked about a second sat, Nusantara Dua :https://kumparan.com/@kumparantech/april-2020-psn-luncurkan-satelit-nusantara-dua-pengganti-palapa-d-1548246721064822411
For the record, "Nusantara Satu" translates exactly to "one archipelago" (word order gets reversed so Satu which means 1, comes first) without "Indonesian" in it.I asked my wife, a native Indonesian and teacher of Bahasa Indonesia (Indonesian language) to non Indonesian speakers, and that's what she told me. The material in the intro post isn't quite right, it has too much stuff in it.
Video of the Static Fire!
Quote from: RocketLover0119 on 02/19/2019 02:16 amVideo of the Static Fire!Granted that this is a long distance, low resolution shot, but that static fire looked longer than normal. I count nine seconds of engines burning, before tail off. Even if you allow for the TEA/TEB start, it seems long.
Couldn't find it with a simple search, but somewhere it was discussed that Beresheet will execute several perigee boosts to increase apogee, with some intermediate orbit close to halfway to the moon. At that point cancelling inclination takes very little delta V.Setting the GTO burn of the second stage to the optimum balance, or even over-weighting the reduction of inclination, should have little impact on the moon lander's flight.It just occurred to me that when we did this optimization in graduate orbital mechanics class, the goal was minimum total delta-V. However, not all velocity change is created equal. For this kind of flight, GTO and GEO insertions come from different engines, specifically the F9 second stage and the GSO satellite respectively. That would change the formulation from the minimum total delta-V to the minimum delta-V from the satellite, with full use of the second stage. Then adding in the possibility of suprasynchronous transfer makes the problem a whole lot more interesting.
Quote from: scr00chy on 02/11/2019 06:44 pmSo, with all that, what is the launch profile supposed to look like? The rocket needs to carry this pretty heavy payload to an orbit with 60,000 km apogee while still allowing for ASDS landing of the first stage. When looking at other GTO launches, it doesn't seem possible. What am I missing? [..][...] Another possibility is "burn to depletion". Most launches target an explicit orbit. To do that, they need to have slightly more fuel than they really need, typically something like 1%. (So if your performance is normal you have 1% left. If's it's 3-sigma bad, you have barely enough fuel. If performance is 3-sigma good, you have 2% remaining.) If you don't care about the exact orbit, you can use these last reserves by simply burning until the fuel runs out. This reduces the needed delta-AV for the payload, but it's a pain in the butt since you can't plan any of your post-launch maneuvers in advance, since you don't know what orbit you'll get. From fitting to performance curves, SpaceX normally stops with the second stage, with residuals, at 5.5t. If they burn the last ton (a little more than 1%) of the propellants, they will get an additional 300 m/s, enough for a 67,000 km apogee. So if SpaceX tries this, in the worst case they get about 40,000 km. In the average case, about 67,000 km, and in the best case about 150,000 km.
So, with all that, what is the launch profile supposed to look like? The rocket needs to carry this pretty heavy payload to an orbit with 60,000 km apogee while still allowing for ASDS landing of the first stage. When looking at other GTO launches, it doesn't seem possible. What am I missing? [..]
The nominal orbit is 215 by 60,000 kilometers, and may be higher, depending on the Falcon 9's performance.
Quote from: Comga on 02/13/2019 04:00 pmCouldn't find it with a simple search, but somewhere it was discussed that Beresheet will execute several perigee boosts to increase apogee, with some intermediate orbit close to halfway to the moon. At that point cancelling inclination takes very little delta V.Setting the GTO burn of the second stage to the optimum balance, or even over-weighting the reduction of inclination, should have little impact on the moon lander's flight.It just occurred to me that when we did this optimization in graduate orbital mechanics class, the goal was minimum total delta-V. However, not all velocity change is created equal. For this kind of flight, GTO and GEO insertions come from different engines, specifically the F9 second stage and the GSO satellite respectively. That would change the formulation from the minimum total delta-V to the minimum delta-V from the satellite, with full use of the second stage. Then adding in the possibility of suprasynchronous transfer makes the problem a whole lot more interesting.Take a look at the orbital trajectory and maneuvers used to get the LADEE spacecraft to the Moon in 2013. This Beresheet spacecraft/lander mission is much like that.In the Wikipedia article I linked, there is a very helpful "Animation of LADEE's trajectory from September 7, 2013, to October 31, 2013" graphic to illustrate, and the article prose described in the Lunar Transit section is quite thorough, and based on detailed sources on the astrogation for that mission.
Event Time Apoapsis Periapsis Orbit period Revs (UTC) (km) (km) (hr)AM1 Optional apogee maneuver 11:50 22 Feb 59998 258 19 2 AM2 Apogee maneuver 02:24 24 Feb 59997 599 19 1.5 PM1 Perigee maneuver 07:29 25 Feb 123246 600 49 5 PM2 Perigee maneuver 11:18 07 Mar 276126 462 152 2 PM3 Perigee maneuver 02:24 20 Mar 396887 1447 258 0.14 OPM Out of plane maneuver 14:25 21 Mar 391974 1422 253 1.3 LOI1 Lunar orbit insertion 14:07 04 Apr 10012 289 14 1.5 LOI1A Lunar orbit insertion 11:29 05 Apr 10002 247 14 2.5 LOI2 Lunar orbit insertion 22:48 06 Apr 752 243 2.6 10 LOI2B Lunar orbit insertion 01:10 08 Apr 245 200 2.2 29.5 DM1 Descent maneuver 17:00 10 Apr 197 15 2.0 14.5
Will this be the first night time attempt at recovering a fairing? Don't seem to recall any reports of them testing the process at night on the west coast.
scr00chy, I have some sources that list the actual mass numbers of all three payloads:https://space.skyrocket.de/doc_sdat/s5.htmS5 weighs 60 kilograms (~132 pounds).https://space.skyrocket.de/doc_sdat/psn-6.htmNusantara Satu weighs 4,735 kilograms (~10,439 pounds).https://www.bbc.com/news/world-middle-east-44777305Beresheet weighs 585 kilograms (~1,290 pounds).Altogether, the total payload mass is 5,380 kilograms (~11,861 pounds). Also, I'm still under the assumption that the booster WILL land on the drone ship while the final geosynchronous transfer orbit's apogee WILL be 60,000 kilometers (might be a bit higher or lower depending on how much delta-v Stage 2 will use up).
The manifest for this Falcon 9 GTO rideshare mission is completely full. It features several undisclosed payloads along with an unmanned lunar spacecraft from SpaceIL, an Israeli nonprofit organization that was competing in the Google Lunar XPrize to land a spacecraft on the Moon. The first rideshare satellites will separate in GTO and then the SSL host spacecraft will continue on to Geostationary Orbit (GEO) where the remaining rideshare satellites will be separated.
