1999-004A
Launch 1999 Feb by Starsem Soyuz-Ikar. Ikar flew over 30 missions as a spacecraft propulsion system. Used as Kometa propulsion. The dispenser was built by Aerospatiale/Aquitaine.
Ikar dry mass 820 kg, fuel 842 kg, dispenser 390 kg, satellites dry 1524 kg, fuel for satellites 288 kg, total 3864 kg. Ikar uses 17D61 N2O4/UDMH with 2943 N thrust (3383N including 4 side thrusters) Isp for Ikar is 326 s so Ve = 3197 m/s, mdot = 0.92 kg/s or 1.06 kg/s. (If all fuel used in 610s, mdot is 1.38 kg/s for T=4412N)
Burn 1 was 352s, so 372 kg, dV = ln 3864 / 3492 = 324 m/s. Actual more like 180m/s implies 211 kg used, for mdot of 0.6 kg/s and mean thrust 1.9 kN. This means Ikar mass now 820 + 390 + 631 = 1841 kg. Maybe inefficiencies used up more prop. Ikar is then 820 + 390 + 470 = 1680 kg.
| Globalstar FM36 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Feb 9 | 0354:00 | Launch by Soyuz-U | KB |
| 0355:58 | T+1:58 Blok B-D sep | ||
| 0356:38 | T+2:38 Fairing sep | ||
| 0358:47 | T+4:43 Blok A sep, 215 km | ||
| 0358:56 | T+4:56 Interstage sep | ||
| 0402:45 | T+8:45 MECO | ||
| 0402:48 | T+8:48 Stage 3 sep | 236 x 884 x 52.0 | |
| 0623:31 | T+2:29:31 Ikar burn | ||
| 0629:23 | Ikar MECO after 5:52 | ||
| 0724:30 | T+3:30:30 Sep from Ikar | 915 x 947 x 52.0 | |
| 0724:34 | T+3:30:34 Sep KA-4 | ||
| 1999 Feb 10 | 0546:48 | Ikar deorbit burn 4:18 | |
| 0633? | Entry, Impact Pacific 50 55S 140 W | ||
| 1999 Feb 13 | 103.59 908 x 947 x 52.0 | ||
| 1999 Feb 25 | 105.53 1004 x 1033 x 52.0 | ||
| 1999 Mar 4 | 110.63 1240 x 1270 x 52.0 | ||
| 1999 Mar 8 | 112.61 1336 x 1355 x 52.0 | ||
| 1999 Mar 14 | 114.07 1410 x 1415 x 52.0 | ||
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