С прибытием новых ракет "Союз", общее число ракет этого семейства, находящихся сейчас на Байконуре возросло до шести: три ракеты-носителя "Союз-ФГ", две ракеты "Союз-У" и одна "Союз-2".
Just browsing Nicolas Pillet's excellent website.
When were they delivered?
Anik, did you mean that launch pad 23 will never hoist any launch again?
Why does it take Soyuz 2 days to reach the ISS or Mir in the past, whereas it took only 1 day to get to Salyut stations?Thanks.
Quote from: Nicolas PILLET on 03/15/2010 05:33 pmAnik, did you mean that launch pad 23 will never hoist any launch again?Yes, I was told so. Launch pad 81/23 is for Proton-K launches only, and there will be only one Proton-K launch in future. It is very expensive to modernize this launch pad for Proton-M.
Quote from: Stan Black on 03/15/2010 11:56 amWhen were they delivered?Soyuz-2 - September 25, Soyuz-U and Soyuz-FG - December 3, Soyuz-U and Soyuz-FG - March 9. One Soyuz-FG is for Kanopus-V #1 satellite. I did not see when this rocket has arrived to Baikonur.
3. satellite adapter 110-155 kg
Quote from: mdo on 04/29/2010 12:49 am3. satellite adapter 110-155 kgA good rule of thumb for a payload adapter is 3% - 5% of payload mass. In this case, the payload is quite heavy, as its filled with prop - the GEO mass of the satellite may be only 2 tons and change, but the GTO mass lifted by Proton is much higher, and the payload adapter must support the GTO mass, not the GEO mass.
Here is an update after fitting some 15 ILS Proton M/Breeze M missions flown in the past 2 years:1. Breeze-M core dry/fuel mass 1550/5200 kg2. APT dry/fuel mass 950/14600 kg3. satellite adapter 110-155 kgThe accumulated burn times before and after Auxiliary Propellant Tank (APT) separation vary significantly from launch to launch: Ranges found in the ILS provided mission overviews are 1959-2521 s before and 617-741 s after jettison. There was even a 3-burn mission with just 370 s of Breeze core usage. I suspect that fuel loading of the APT and core stage may vary by 3+ mT.Furthermore, the APT capacity can support burns <2400 s. This is regularly exceeded prior to APT separation. That raises the question whether the S5.98/14D30 engine performance of 19.62 kN and an Isp of 326 s is accurate or whether some other dynamic element comes into play.Also, the four 11D458 Vernier thrusters provide some 4x400 N. Whether they operate continuously and what fuel budget they have got is causing further uncertainty.Obviously the final burn is very sensitive to the dry mass of the Breeze-M core. At 1600 kg as per Eurockot manual for the Breeze-KM version (thanks to Danderman for the reference) my model underperforms. 1550 kg barely works with zero margin. Maybe the satellite adapter (110-155 kg) is integrated in the figure of 1600 kg after all. To conclude, the assumptions given in the previous post still hold and the uncertainties remain. The level of reverse engineering involved is way too much to be confident in these numbers.
СОЗ vernier timings timings can be found in http://coopi.khrunichev.ru under ‘newsposting’.
Briz maximum burn time 1,000 secondshttp://www.eurockot.com/pb-pic/20041083.pdfSo if there is upto 14,600 kg in the extenal APT / ДТБ and the Briz core has up to 5,200 kg; then external tank should be able to provide 2,808 seconds of burn time?