Saturday, March 21, 2015
Progress M-24M
2014-042A
Vehicle 423, mission 56P. Mass 7280 kg. Carried 2322 kg of cargo (accounted SKK, Expose as 14 kg).. Undock mass 6769 kg or (NK) 5601 kg; mass at beginning of deorbit burn 5514 kg.
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 Jul 23 | 2144:44 | Launch by Soyuz-U | KB |
| 2149 | Blok-A sep | ||
| 2153 | Blok-I sep | ||
| 2231:12 | DV1 42m/s | 236 x 336 | |
| 2313:45 | DV2 | 333 x 394 | |
| 2348:51 | DV3 | 356 x 402 | |
| 2014 Jul 24 | 0019:36 | DV4 | 367 x 406 |
| 0310 | 600m range | ||
| 0313 | 400m flyaround starts | ||
| 0319 | Complete flyaround, Stationkeeping | ||
| 0320 | Begin final approach | ||
| 0328 | 35m range | ||
| 0331:37 | Dock with Pirs | ||
| 2014 Oct 27 | 0538:24 | Undock | |
| 0541 | Sep-1 burn | ||
| Engineering tests | |||
| 0842 | SKD burn 20s 11.5ms | 386 x 420 | |
| 2014 Nov 1 | 0626:00 | DV 14.13s 7.2m/s | |
| Otrazhelenie-5 experiment | |||
| 2014 Nov 19 | 2300 | Deorbit 106.9m/s 186s | 379 x 438 x 51.6 |
| 2303:06 | DO CO | ||
| 2346 | Debris impact | ||
USA-240
2012-071A
Flight vehicle 1 made its second flight as OTV-3.
| X-37B | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2012 Dec 11 | 1803 | Launch by Atlas V 501 AV-034 | CC SLC40 |
| T+3:36 Fairing sep | |||
| T+3:42 CFLR sep | |||
| T+4:23 Atlas BECO | |||
| T+4:29 Atlas sep | |||
| T+4:39 Centaur MES-1 | |||
| 1820 | T+17:35 MECO | ||
| AV-034 sep | 343 x 360 x 43.5 | ||
| 1843? | T+40? AV-034 deorbit | -1500? x 350? | |
| 1900? | AV-034 impact IOR W of Australia | ||
| 2014 Oct 17 | 1540? | Deorbit | |
| 1624 | Landed RW12 VAFB | ||
Friday, March 20, 2015
O3b 3
2014-083A
Third O3b cluster with Fregat 133-01.
| O3b | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 Dec 18 | 1837 | Launch by 372RN21B No. T15000-007 (VS10) | |
| T+1:58 strapon sep | |||
| T+3:58 Fairing sep | |||
| T+4:48 Blok A sep | |||
| Blok I burn | |||
| St 3 MECO | |||
| T+9:23 St 3 sep | -1186 x 194 x 5.27 | ||
| 1847 | T+10:23 MES-1 | ||
| 1851 | T+14:20 MECO-1 | 160 x 203 x 5.15 | |
| 1859 | T+22:50 MES-2 | ||
| 1908 | T+31:21 MECO-2 | 242 x 7875 x 3.24 | |
| 2029 | T+1:52:25 MES-3 | ||
| 2034 | T+1:57:27 MECO-3 | 7831 x 7835 x 0.02 | |
| 2037 | T+2:00:46 SC2/SC4 sep | ||
| MES-4 preburn 10s? | |||
| T+2:15:47? MES-4 | |||
| T+2:16:03 MECO-4 | |||
| 2059 | T+2:22:27 SC1/SC3 sep | ||
Turksat 4A
2014-007A
MELCO DS-2000, 3850 kg launch by Proton to 42E.
| Turksat 4A | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 Feb 14 | 2109:03 | Launch by Proton | KB LC81/24 |
| T+2:03 St 1 sep | |||
| T+5:24 St 2 MECO | |||
| T+5:27 St 2 sep | |||
| T+5:33 St 3 MES | |||
| T+5:47 Fairing sep | |||
| 2118 | T+9:22 St 3 MECO | ||
| 2118 | T+9:42 St 3 sep | -497 x 171 x 51.57 | |
| 2120 | T+11:16 Briz-M MES-1 | ||
| 2124 | T+15:47 MECO-1 | 171 x 173 x 51.57 | |
| 2216 | T+1:07:33 MES-2 | ||
| 2234 | T+1:25:17 MECO-2 | 269 x 4998 x 50.37 | |
| 2014 Feb 15 | 0037 | T+3:28:12 MES-3 | |
| 0048 | T+3:39:42 MECO-3 | 351 x 22185 x 49.4 | |
| 0049 | T+3:40:32 DTB sep | ||
| 0051 | T+3:41:59 MES4 | ||
| 0056 | T+3:47:52 MECO4 | 428 x 35858 x 49.1 | |
| 0602 | T+8:53:08 MES5 | ||
| 0608 | T+8:59:24 MECO-5 | 823.69 9675 x 35782 x 12.7 | |
| 0621 | T+9:12:00 Briz-M sep | ||
| Briz-M depletion | 763.91 8406 x 34200 x 13.1 | ||
| 2014 Feb 15 | 823.69 9674 x 35782 x 12.7 | ||
| 2014 Feb 18 | 1376.65 33448 x 35781 x 0.5 | ||
| 2014 Feb 20 | 1431.99 35632 x 35799 x 0.0 GEO +1.0E/d | ||
| 2014 Feb 27 | 1436.00 35769 x 35799 x 0.0 GEO 50.0E | ||
| 2014 Jun 2 | 1436.06 35771 x 35800 x 0.1 GEO 50.0E | ||
| 2014 Jun 3 | Move out | ||
| 2014 Jun 16 | On station at 42E | 1436.15 35784 x 35791 x 0.07 GEO 42.0E | |
| 2014 Jul 18 | 1436.05 35781 x 35789 x 0.1 GEO 42.0E | ||
BSat-3C
2011-041B
Broadcast Satellite Systems corp and Sky Perfect JSat Corp. will launch a LMCSS/Newton A2100A in 2011 on Ari 5ECA.
At 110E.
Mass 2910 kg. 5.3 x 2.0 x 1.9m,, 18.9m span.
Following a regulatory change which allowed Japanese operators to fly a broadcasting and communications payload on the same satellite, JSAT and B-SAT procured a joint satellite, JCSAT-110R. The JSAT side would backup JCSAT-110. B-SAT would operate the satellite in orbit as B-SAT 3c.
| BSAT3C | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2011 Aug 6 | 2252:37 | Launch by Ariane 5 L560 | |
| T+2:14 SRB sep | |||
| T+3:05 Fairing sep | |||
| 2301:22 | T+8:45 EPC MECO | -1029 x 188 x 6.79 | |
| 2301:28 | T+8:51 EPC sep | ||
| 2301:32 | T+8:55 ESC-A burn | ||
| 2011 Aug 7 | |||
| 0017:30 | T+24:53 ESC-A MECO | ||
| 0019:42 | T+27:05 Astra 1N sep | ||
| 0029:15 | T+36:38 Sylda sep | ||
| 0030:41 | T+38:04 BSAT sep | ||
| T+49:34 End of mission | |||
| 2011 Aug 8 | 630.88 264 x 35712 x 1.97 | ||
| 2011 Aug 16 | 1435.88 35768 x 35796 x 0.0 GEO 109.9E | ||
| 2011 Oct 4 | 1436.12 35784 x 35789 x 0.0 GEO 110.0E | ||
Thursday, March 19, 2015
Gsat 16
2014-078B
Mass 3182 kg full 1458 kg dry, size 3.1 x 1.77 x 2.0m with 15.4m span using I-3K bus. Colocated with GSAT-8 and IRNSS-1A/1B.
| DTV14 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 Dec 6 | 2040 | Launch by Ariane VA221 | CSG ELA3 |
| 2042 | T+2:13 EAP sep | ||
| 2043 | T+3:12 Fairing sep | ||
| 2048 | T+8:52 EPC MECO | -983 x 161 x 6.32 | |
| 2048 | T+8:58 EPC sep | ||
| 2049 | T+9:13 ESC-A burn | ||
| 2105 | T+25:02 ESC-A MECO | ||
| 2107 | T+27:47 DTV 14 sep | ||
| 2109 | T+29:12 Sylda sep | ||
| 2112 | T+32:13 GSAT-16 sep | ||
| ESC-A depletion | |||
| 2014 Dec 8 | 0003 | LAM-1 6130s | 16006 x 35769 x 1.05 |
| 2014 Dec 9 | 0735 | LAM-2 2203s | 32307 x 35765 x 0.4 |
Wednesday, March 18, 2015
IXV
2015-U01
ESA Intermediate Experimental Vehicle (IXV). Launch by Vega to 180 x 307 km x 70 deg from CSG. or 470 km 1 orbit, deorbit burn using Vega AVUM upper stage over -90 -40 Pacific, reentry over -70 +35 at 7.70 km/s, -1.19 deg, 120 km (earth-relative; azimuth unknown) with recovery after splashdown. AVUM reached orbit, deorbited on 2nd pass over Kourou, probably with entry over the Indian Ocean.
| IXV | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2015 Feb 11 | 1340 | Launch by Vega VV04 | CSG ELV |
| T+1:52 P80 sep | |||
| T+3:35 Z23 sep | |||
| T+3:59 Z9 burn | |||
| T+4:02 Fairing sep | |||
| 1346 | T+6:39 Z9 sep 171 km 7.15km/s | ||
| 1348 | T+8:00 AVUM burn 1 | ||
| Z9 impact 68.75E 2.75S +- 7 deg E | |||
| 1353 | T+13:49 AVUM MECO-1 332 km 7.656 km/s | 76 x 416 x 5.4 | |
| 1357 | T+17:59 IXV sep | ||
| 1411 | T+31:14 AVUM MES-2 | ||
| 1411 | T+31:30 AVUM MECO-2 | 220 x 430 x 5.4 | |
| 1427? | Z9 entry in IO | ||
| 1444 | IXV reentry | ||
| Parachute panel ejection | |||
| Drogue para | |||
| 1509 | Para deploy | ||
| 1515? | Flotation device panels ejected | ||
| 1518? | IXV splash 123W 3N | ||
| 1529 | T+1:49:31 AVUM MES-3 | ||
| T+1:50:30 AVUM MECO-3 | |||
| 1610? | AVUM reentry 86.25E 4.5S | ||
| Recovery ship Nos Aries | |||
Tuesday, March 17, 2015
Monday, March 16, 2015
STPSat-2
2010-062A
Space Test Program Standard Interface Vehicle. Ball/AeroAstro generic bus based on AeroAstro STPSat-1
STP-SIV 1. Box + panels, attaches to ESPA ring.
Launch by Minotaur 4 from Kodiak on mission STP S26 which includes MSFC FastSat and three other sats: FASTRAC A/B
Size 0.6 x 1.0m, mass 135 kg.
The GCA contains the Ori 38 motor.
The HAPS stage contains the HAPS engine and the MPA (Multi Payload Adapter).
GCA stage is 2.34m dia 2.2m long Orion motor inside is 1.4long 1.0dia HAPS is a trunc cone 0.8l 1.0 dia; HAPS stage is 1.8m long 1.0m main diameter, with MPA at front 1.5m dia and truss at back possibly 2.1m dia.
68 mm = 2.34 0.0344/mmm
We have no data on the mass of the HAPS stage or the ballast. Guessing wildly we have 270-370 kg full, HAPS prop is 73 kg and thrust is 0.67 kN, Ve = 2314 m/s so mdot is 0.29 kg/s. Total HAPS burn time is 316s, implies 92 kg prop total, 40 kg in burn 1 and 52 kg in burn 2.
Low end mass: 270 kg to 230 kg to 178 kg, dV = 371 and 593 m/s. High end mass: 370 kg to 330 kg to 278 kg, dV = 265 and 397 m/s. Actual required dV to get to 635 x 1200: 142; then to 1201 x 1202: 145 m/s.
2314 ln m2/m3 = 145 so m2/m3 = 1.065; m1 = 1.134m3 and m1=m3+92 implies 0.134m3 = 92 so m3=686 kg. True mass of HAPS stage is much larger because of MPA and stage structure. Guess stage+MPA = 386 kg dry, ballast = 300 kg. HAPS stage full = 478 kg.
Total payload mass 509 kg; ballast+HAPS 778 kg. GCA stage 500 empty? GCA propellant 770 kg. Gives Orion 38 burn
of 1787 / 2557 for dV of 1008 m/s.
The UN registration confirms that the ballast payloads were in a 1200 x 1204 km x 72.0 deg orbit.
| S26 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2010 Nov 20 | 0125:00 | Launch by Minotaur IV | V SLC8 |
| T+0:57 St 1 sep 25 km | |||
| T+1:56 St 2 burnout 88 km | |||
| T+1:56 St 2 sep 106 km | |||
| T+1:56? SR120 burn 106 km | |||
| 0127 | T+2:20 92-in Fairing sep 133 km | ||
| T+3:08 St 3 burnout 192 km? | |||
| 0138 | T+13:21 St 3 sep | -2773? x 651 x 72.0 | |
| 0138 | T+13:32 St 4 burn | ||
| 0139 | T+14:39 St 4 burnout | ||
| B+0:00 Stage 4 burnout | 641 x 652 x 72.0 | ||
| 0141 | B+2:00 T+16:39 STPSat-2 sep | ||
| 0142 | B+3:00 T+17:39 RAX sep from PPOD-1 | ||
| 0143 | B+4:00 T+18:39 O/OREOS sep from PPOD-2 | ||
| B+5:00 Rotate stage 180 deg | |||
| 0146 | B+7:00 T+21:39 FASTSAT sep | ||
| B+8:00 Rotate stage 150 deg | |||
| 0151 | B+12:00 T+26:39 FS-5 sep | ||
| 0156 | B+17:00 T+31:39 FASTRAC1/2 sep from stage | ||
| B+17:30 Reorient to vel vector | |||
| 0159 | B+20:00 T+34:39 Stage 4 GCA sep from HAPS | ||
| 0200 | T+35:39 HAPS burn 1 136s over 102W 54S? | ||
| 0202 | T+37:55 HAPS cutoff 1 | ||
| 0251 | T+1:27:00 HAPS burn 2 180s | ||
| 0255 | T+1:30:00 cutoff 2 | 1201 x 1202 x 72 | |
| 0258 | T+1:33:00 Ballast mass 1 and 2 sep from HAPS | ||
| 0305 | T+1:40:00 HAPS depletion | ||
| 0309 | T+1:44:00 RCS depletion | ||
| FASTRAC1/2 sep from each other | |||
| NS-D separate from FASTSAT | |||
| 2012 Apr | Mission extended to Feb 2013 | ||
Payload:
- Space Phenomenology Experiment (sensor test)
- SCP SCP-2 Satellite Comms Payload, Data-X Data exfiltration experiment (ONR/Praxis/), IP based buoy comms with ODTML Ocean Data Telemetry Microsat Link (ONR/)