Friday, August 18, 2017
IRNSS-1F
2016-015A
Shape is box + 2 pan. Size is 1.58 x 1.50 x 1.50m, plus ? solar panel span. Control from MCF-Hassan.
| IRNSS-1F | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2016 Mar 10 | 1031 | Launch by PSLV-XL C32 | SHAR SLP |
| T+0:25 PSOM5,6 on | |||
| T+1:10 SOM 1,2 sep | |||
| T+1:10 SOM 3,4 sep | |||
| T+1:32 SOM 5,6 sep | |||
| T+1:51 St 1 sep 56 km | |||
| T+1:51 St 2 burn | |||
| T+3:18 Fairing sep | |||
| T+4:23 St 2 sep | |||
| T+4:24 St 3 burn 112s | |||
| 1036 | T+6:26 St 3 burnout | ||
| 1041 | T+10:06 St 3 sep 163 km 7.7585 km/s | ||
| T+10:16 St 4 burn 186 km 7.7320 km/s | |||
| 1049 | T+18:43 St 4 MECO 455 km 9.638 km/s | ||
| 1050 | T+19:20 St 4 sep | 362.36 271 x 20645 x 17.9 | |
| 1125? | Stage 3 impact Pacific W of Lima | ||
| 2016 Mar 11 | 1046 | Apogee raise | 318 x 35828 x 17.9 |
| 2016 Mar 12 | 0228 | LAM-2 burn 1918s | |
| 2016 Mar 12 | 825.95 9796 x 35768 x 9.8 | ||
| 2016 Mar 13 | 1373.11 33348 x 35740 x 5.3 | ||
| 2016 Mar 16 | 1371.46 33333 x 35690 x 5.3 | ||
| 2016 Mar 20 | 1433.31 35628 x 35834 x 5.1 | ||
Wednesday, August 16, 2017
Mangalyaan
2013-060A
The spacecraft name is Mars Orbiter Satellite; mission name is Mars Orbiter Mission. It was known as Mangalyaan 1 in some media sources but this was not official.
Mars Orbiter Mission is mainly a technology mission, but carries a small, 15 kg, science payload to study the Martian atmosphere and in particular search for methane. However, US scientists claimed that the methane sensor, while able to measure Martian albedo, was not designed properly; background subtraction issues prevented a reliable measurement [839]
ISRO Mars orbiter. HAL structure, ISAC spacecraft. The Insat/IRS derived bus has an improved comms system and a 440N propulsion system designed for restart after a year in cruise. A single solar array is used, made of three 1.4 x 1.8m panels, with the 2.2m dia HGA on the opposite side. Box + panel + dish. 1337 kg probe full (850 kg prop, 500 kg dry) in 370 x 80000 km orbit. Mass prior to MOI was 801.3 kg. Mission requires 2.592 km/s. Comms via Indian Deep Space Station IDSN32, a 32-m antenna in Bangalore/Byalalu.
The PSLV-XL has 6 PSOM-XL, the S139 core, PL40 stage 2, HPS3 stage 3, L2.5 stage 4.
| MOM | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2013 Nov 5 | 0908 | Launch by PSLV-XL C25 | SDSC |
| T+0:25 PSOM 5-6 on | |||
| T+1:10 PSOM 1-2 sep | |||
| T+1:10 PSOM 3-4 sep | |||
| T+1:32 PSOM 5-6 sep | |||
| T+1:52 PS1 sep | |||
| T+1:53 PS2 burn | 58 km, 2.387 km/s | ||
| T+3:21 Fairing | 113 km, 3.625 km/s | ||
| 0912 | T+4:24 PS2 sep | ||
| 0912 | T+4:26 PS3 burn 132 km, 5.379 km/s | -4364 x 132 | |
| 0917 | T+9:43 PS3 sep | -70? x 300? | |
| Long coast, 27:24 | |||
| 0943 | T+35:00 PS4 burn 271 km, 7.642 km/s | -70? x 300? | |
| 0951 | T+43:39 PS4 off | 342 km, 9.833 km/s | |
| 0952 | T+44:16 Stage 4 sep | 251 x 23892 x 19.35 | |
| 247 x 23563 x 19.27 (ISRO) | |||
| 2013 Nov 6 | 1947 | Peri burn 1 | 250 x 28814 km |
| 2013 Nov 7 | 2048:51 | Peri burn 2 570.6s | x 40186 km |
| 2013 Nov 8 | 1940:43 | Peri burn 3 707s | x 71636 km |
| 2013 Nov 10 | Peri burn 4 35m/s | x 78276 | |
| 2013 Nov 11 | 2333:50 | Peri burn 4b 303.8s | 276 x 118642 x 19.3 |
| 2013 Nov 15 | 1957 | Peri burn 5 243s 101.6m/s | x 192874 |
| 853 x 194683 x 19.4 | |||
| 2013 Nov 16 | 1503 | Pass EL1:4 | |
| 2013 Nov 30 | 1919 | Peri burn 6, SOI to Mars Transfer Traj 648m/s 1351s 198 kg | |
| 1328.9s 647.96 m/s | |||
| 2013 Dec 5 | 2056 | Leave Earth Hill sphere 1.5Mkm | |
| 2013 Dec 11 | 0100 | TCM-1 40.5s burn; R=2.9Mkm | |
| 2014 Jun 11 | 1100 | TCM-2 16s 1.577m/s | |
| 2014 Aug | TCM-3 cancelled | ||
| 2014 Sep 20 | 0427 | Mars sphere 1.08Mkm | |
| 2014 Sep 22 | 0040 | Mars SOI | |
| 2014 Sep 22 | 0900s | TCM-4 4.0s 0.6kg 2.1m/s | |
| 2014 Sep 24 | 0200 | MOI 1.099km/s | 3.66d 365 x 80000 x150.0 |
| 0142 | Eclipse starts | ||
| 0147:32 | MOI burn (SCET) 515 km 24:14 249.5 kg 1098.7m/s | ||
| 0207 | Eclipse ends | ||
| 0211:46 | MOI CO, 40 kg prop left | ||
| 4371.85 419 x 76872 x 150.04 | |||
| 0217 | Resume telem | ||
| 2014 Oct 5 | 392 x 76776 x 150.1 | ||
| 2014 Oct 6 | 0445 | TCM to avoid comet, 1.9 km | 392 x 70998 x 150.1 |
| 2015 Mar 24 | Primary mission complete, 37 kg prop remain | ||
| 2015 Jun 6 | Begin conjunction | ||
| 2015 Jun 22 | End conjunction | ||
| 2017 Jan 17 | 500 x 71050 x 150 | ||
Sunday, August 13, 2017
Alphasat
2013-038A
Inmarsat/ESA Astrium/Thales Alenia Alphabus class satellite with large GEO Mobile antenna. 6650 kg. Size 2.8 x 2.5m x 7.1m; 40m span. Tanks carry max 4200 kg prop and 350 kg Xe.
ESA Alcatel/Astrium new gen AlphaBus sat, with 500N EADS-ST/D apogee engine. Inmarsat Global Limited will operate the satellite. EADS Astrium is prime. Also has TDP (Technology Demo Payloads)
Will be stationed at 25E for at least 3 years of ESA demos.
Service Module (SM) and Repeater Module (RM). SM Main structure by TAS/Cannes. RM structure at TAS/Torino, payload integration at EADS Astrium/Portsmouth. Integration at EADS Astrium/Toulouse.
Alphabus prop tanks can carry 3500 to 4200 kg of prop. EAM (European Apogee Motor) MMH/MON-3 engine with Astrium/Lampoldshausen 500N thruster, 16 RCS thrusters, and a Xe plasma thruster electrical propulsion system (XPS).
| IXL | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2013 Jul 25 | 1954:07 | Launch by Ariane 5ECA | CSG |
| T+2:15 EAP sep | |||
| T+3:10 Fairing sep | |||
| 2002:54 | T+8:47 EPC MECO | ||
| 2003:00 | T+8:53 EPC sep | -1051 x 169 x 6.04 | |
| 2003:04 | T+8:57 ESC-A burn | ||
| 2019:10 | T+25:03 ESC-A MECO | ||
| 2021:45 | T+27:38 Alphasat sep | 631.89 221 x 35807 x 3.5 | |
| 2023:35 | T+29:28 Sylda 56D sep | ||
| 2026:48 | T+32:41 Insat 3D sep | ||