https://web.archive.org/web/20080504032647/http://digest-archive.degrassi.ca/DD17.htm
Monday, November 30, 2009
Saturday, November 28, 2009
GOES-11
2000-022A
GOES L mass is 2218 kg. It was another FS-1300 based GOES I series craft launched by ILS Atlas IIA. Span is 26.9m from the solar sail end to the solar panel trim tab. The spacecraft solar sail is a boom with a conical sail on the end; on the opposite site of the bus there is one solar panel array (two panels) with a small tab on the end.
From 2000 to 2006 GOES 11 was kept drifting back and forward between 98W and 115W. In mid-2006 it was moved to the Pacific at 135W.
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 May 3 | 0707 | Launch by Atlas IIA /LPF | CC LC36A |
| BECO | |||
| T+4:41 SECO | |||
| T+4:43 Atlas sep | |||
| T+5:00 MES-1 | |||
| T+9:36 MECO-1 | 91.09 180 x 475 x 28.8 | ||
| T+22:04 MES-2 | |||
| T+23:37 MECO-2 | 751.09 274 x 41710 x 20.0 | ||
| 0734 | T+27:04 Centaur sep | 763.50 275 x 42311 x 20.0 | |
| 2000 May 3 | 0822 | Solar panel deploy | 784.32 459 x 43128 x 20.0 |
| 2000 May 4 | 760.66 240 x 42208 x 20.1 | ||
| 2000 May 5 | 0330? | T+1d:20:07 AMF-1 | |
| 2000 May 6 | 999.32 11233 x 42230 x 5.9 | ||
| 2000 May 7 | 2200? | T+4d:15:38 AMF-2 | |
| 2000 May 8 | 1466.14 29196 x 43548 x 1.3 | ||
| 2000 May 8 | 0300? | AMF? | |
| 2000 May 9 | 1374.00 26869 x 42255 x 1.1 | ||
| 2000 May 9 | 2000? | AMF-3 | 1602.80 35625 x 42353 x 0.3 |
| 2000 May 11 | 1334 | AAM | |
| 2000 May 11 | Renamed GOES 11 | ||
| 2000 May 13 | 1602.89 35628 x 42354 x 0.3 | ||
| 2000 May 18 | T+14d TMF-1 | ||
| 2000 May 19 | T+16d TMF-2 | ||
| 2000 May 21 | T+17d TMF-3 | ||
| 2000 May 25 | 1435.57 35756 x 35795 x 0.6 GEO 101.8W+0.12W | ||
| 2000 May 26 | 1436.19 35782 x 35794 x 0.2 GEO 104.1W+0.0W | ||
| 2002 Aug 24 | 1436.34 35782 x 35799 x 0.3 GEO 105.1W+0.07W | ||
| 2003 Feb 22 | 1436.18 35774 x 35802 x 0.1 GEO 113.5W+0.03W | ||
| 2003 Jul 11 | Reverse drift | ||
| 2003 Dec 21 | 1435.83 35756 x 35806 x 0.0 GEO 104.1W+0.06E/d | ||
| 2004 Jun 8 | Reverse drift | 1436.15 35781 x 35793 x 0.42 96.1W | |
| 2004 Jul 18 | 1436.23 35781 x 35796 x 0.4 GEO 96.5W+0.04W/d | ||
| 2004 Aug 22 | GEO 98W | ||
| 2005 Mar 16 | GEO 111W | ||
| 2005 Jun 7 | Reverse drift | GEO 114.5W | |
| 2006 Mar 5 | GEO 105W | ||
| 2006 May 23 | 1435.93 35767 x 35798 x 0.4 GEO 100.9W | ||
| 2006 May 24 | Move out | 1439.91 35796 x 35926 x 0.4 | |
| 2006 Jun 28 | Move in at 135W | ||
| 2008 Mar 25 | 1436.03 35779 x 35791 x 0.5 GEO 135.5W | ||
Saturday, November 21, 2009
Friday, November 20, 2009
Thursday, November 19, 2009
Wednesday, November 18, 2009
IGS-3
2007-005A
Radar-2, Launch Jan-Feb 2007 on H2A 2024, with Optical-3 experimental satellite and probably with 4/4D-LC fairing.
Re-da 2 gouki and Kougaku 3 gouki jisshou eisei. (Optical No. 3 test satellite).
On 2010 Dec 23, 2007-05E, a debris object from the launch broke up into 4 pieces for unknown reasons.
| IGS | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Feb 24 | 0441 | Launch by H2A F12 | TNSC Y LP1 |
| T+1:40 SRB-A burnout | |||
| T+1:47 SRB-A sep | |||
| T+4:20 4/4D-LC PLF sep | |||
| T+6:35 St 1 MECO | |||
| T+6:43 St 1 sep | |||
| T+6:49? Stage 2 burn | |||
| 0456? | T+15? SECO | ||
| 0501 | Payloads separate | ||
2007-005B
Kougaku 3 gouki jisshou eisei. (Optical No. 3 test satellite).
| IGS | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Feb 24 | 0441 | Launch by H2A F12 | TNSC Y LP1 |
| T+1:40 SRB-A burnout | |||
| T+1:47 SRB-A sep | |||
| T+4:20 4/4D-LC PLF sep | |||
| T+6:35 St 1 MECO | |||
| T+6:43 St 1 sep | |||
| T+6:49? Stage 2 burn | |||
| 0456? | T+15? SECO | ||
| 0501 | Payloads separate | ||
Tuesday, November 17, 2009
Intelsat 602
1989-087A
Intelsat 602 had a launch mass of 4286 kg including the LV adapter. BOL mass was 2560 kg, dry mass 1906 kg. Size is cylinder 11.8m high deployed 6.4m stowed, diameter 3.6m.
| Intelsat VI F-2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1989 Oct 27 | 2305:00 | Launch by Ariane 44L V34 | CSG ELA2 |
| T+2:31 PAL sep | |||
| T+3:34 St 1 sep | |||
| T+3:37 St 2 MES | |||
| 2309 | T+4:22 Fairing sep | ||
| 2310 | T+5:45 St 2 sep | ||
| 2310 | T+5:51 St 3 MES | ||
| 2322 | T+17:53 St 3 MECO | ||
| 2327 | T+22:09 St 3 sep | ||
| 1989 Oct 28 | 0600s | LAM0, 0.75min test burn | |
| 1800s | LAM1, 15 min | ||
| 1989 Oct 29 | LAM 2, 43 min burn | ||
| 1989 Oct 30 | LAM 3, 7 min burn | ||
| 1989 Oct 31 | LAM 4, 21 min burn | ||
| 1989 Oct 31 | 1436.33 35715 x 35867 x 0.1 GEO 37.4W+0.06W | ||
| 1989 Nov 1 | LAM 5, 3 min burn | ||
| 1989 Nov 1 | 1435.73 35714 x 35844 x 0.1 GEO 37.4W+0.09E | ||
| 1989 Nov 6 | 1436.00 35729 x 35840 x 0.1 GEO 37.1W+0.01E | ||
| 1989 Nov 14 | 1436.13 35725 x 35848 x 0.1 GEO 37.3W | ||
| 1989 Dec 7 | IOT (In orbit testing) begins | ||
| 1989 Dec 30 | 1436.10 35736 x 35836 x 0.1 GEO 38.0W | ||
| 1990 Jan 18 | IOT complete | ||
| 1990 Apr 7 | 1436.07 35738 x 35833 x 0.0 GEO 37.4W | ||
| 1990 May | AOR, replaced 510 | GEO 24.5W | |
| 1990 May 5 | 1436.10 35783 x 35789 x 0.1 GEO 24.4W | ||
| 1990 Dec 7 | 1436.13 35775 x 35798 x 0.0 GEO 24.5W | ||
| 1991 Oct 19 | mv out | 1436.12 35780 x 35793 x 0.1 GEO 24.5W | |
| 1991 Oct | Replaced by 605 | ||
| 1991 Nov 28 | mv in, temporary | 1436.08 35729 x 35843 x 0.1 GEO 55.1E | |
| 1991 Dec 31 | 1436.05 35481 x 36089 x 0.1 GEO 55.7E | ||
| 1992 Jan 7 | mv out | ||
| 1992 Jan 28 | mv in | 1436.14 35775 x 35799 x 0.1 GEO 59.9E | |
| 1992 Jun 4 | mv out | 1436.06 35780 x 35791 x 0.1 GEO 60.0E | |
| 1992 Jun 10 | mvin | 1436.09 35780 x 35792 x 0.0 GEO 62.9E | |
| 1992 Oct 5 | 1436.07 35769 x 35803 x 0.0 GEO 62.9E | ||
| 1993 Apr 15 | 1436.07 35783 x 35789 x 0.0 GEO 62.9E | ||
| 1996 Apr 15 | 1436.06 35781 x 35790 x 0.0 GEO 62.9E | ||
| 1997 Aug 1 | 1436.12 35777 x 35796 x 0.0 GEO 62.9E | ||
| 1997 Aug | drift to 62E | ||
| 1997 Nov 12 | 1436.08 35724 x 35848 x 0.0 GEO 62.1E | ||
| 1998 Jan 5 | 1436.11 35777 x 35795 x 0.0 GEO 61.9E | ||
| 1999 Jun 10 | 1436.08 35778 x 35794 x 0.0 GEO 62.0E | ||
| 2002 Dec 13 | mv in | GEO 32E | |
| 2003 May 20 | mv out | GEO 32E | |
| 2003 Jul 17 | mv in | GEO 50E | |
| 2003 Sep 2 | 1436.06 35774 x 35797 x 1.6 GEO 50.6E | ||
| 2005 Dec 18 | mv out | GEO 50.7E | |
| 2005 Jun 28 | mv in | ||
| 2005 Jul 18 | 1436.10 35774 x 35779 x 3.3 GEO 150.6E | ||
| 2006 Jul 25 | 1436.11 35783 x 35790 x 4.3 GEO 150.6E | ||
| 2007 May 25 | 1436.11 35782 x 35791 x 5.0 GEO 150.4E | ||
| 2007 May 29 | Move out | ||
| 2007 Jun 25 | Move in | 1436.09 35781 x 35791 x 5.1 GEO 157.1E | |
| 2008 Aug 3 | 1436.11 35781 x 35792 x 6.1 GEO 157.0E | ||
| 2008 Aug 12 | Move out | ||
| 2008 Nov 22 | Move in | 1436.09 35776 x 35796 x 6.4 GEO 178.0E | |
| 2009 Sep 18 | 1436.09 35781 x 35791 x 7.1 GEO 177.8E | ||
Monday, November 16, 2009
Beidou 4
2007-003A
This payload remained in transfer orbit for several months with solar panel problems, but was eventually recovered. The satellite was an in-orbit reserve vehicle for Beidou 1.
One Chinese source refers to the satellite as "the fourth Big Dipper (Beidou) navigation experiment satellite"; di si ke beidou daohang shiyan weixing.
Bei is 'north' and Dou is 'cup', the "North Cup" is the Big Dipper asterism in Ursa Major (Ursa Major itself is daxiong zuo, great-bear constellation).
| Beidou 4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Feb 2 | 1628 | Launch by CZ-3A | XSC |
| T+2:25? Stage 1 MECO | |||
| T+2:27? Stage 2 MES, Stage 1 sep | |||
| T+3:52? Fairing sep | |||
| T+4:15? St 2 MECO | |||
| T+4:20? St 2 VECO | |||
| 1632? | T+4:21? St 2 sep, St 3 MES-1 | ||
| 1638? | MECO-1 | ||
| 1644? | MES-2? | ||
| 1646? | MECO-2 | ||
| 1650 | Perigee | ||
| 1652 | T+0:24 Stage 3 sep | ||
| 2300? | Debris event detected | ||
| 2007 Feb 4 | 194 x 41769 x 25.0 | ||
| 2007 Mar 8 | 181 x 41591 x 25.0 | ||
| 2007 Apr 4? | Solar panels deployed | ||
| 2007 Apr? | GEO insertion burn | ||
| 2007 Apr 13 | 1436.17 35333 x 36242 x 6.4 | ||
| 2007 May 3 | 1436.11 35332 x 36241 x 142.8E | ||
| 2009 Feb 16 | 1436.10 35269 x 36303 x 4.7 GEO 144.4E | ||
Tuesday, November 10, 2009
Sunday, November 8, 2009
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