Wednesday, October 9, 2002
Tuesday, October 8, 2002
DFH-2
1971-018A
China's second satellite was Shi Jian 1 (SJ 1, PRC 2). Shi Jian has been translated as `Practice' or `Test'. SJ 1 was similar in construction to DFH 1. It carried a magnetometer and solar cells, and cosmic ray detectors. SJ 1 transmitted until at least 1977. Transmissions continued on 20.008MHz from the final stage rocket until Mar 11, after which 19.995 MHz transmissions from the payload began, and it appears that the rocket did not separate until then.| Shi Jian 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1971 Mar 3 | 1202? | Launch by CZ1 | JQ |
| 1203? | T+1:00 Stage 2 burn | ||
| 1204? | T+3:00? Stage 2 burnout | ||
| 1206? | Stage 2 sep | ||
| 1209? | Stage 3 burn | ||
| 1210? | Stage 3 burnout | ||
| 106.2 268 x 1830 x 69.9 | |||
| 1971 Mar 10 | Stage 3 separated | ||
| 1971 Mar 26 | end of tx from stage 3 | ||
| 1977? | end of transmissions | ||
| 1979 Jun 17 | Reentered over Lake Michigan | ||
Explorer 8
1960-014
The S-030A ionospheric studies payload was launched on 1960 Nov 3 at 0523 by a Juno II from LC26B at Cape Canaveral. Jupiter AM-19D was used with JPL Cluster 17. S-30A entered a 417 x 2288 km x 49.95 deg orbit (planned inc was 50.3) and operated until 1960 Dec 27. S-30A was also called the Ionosphere Direct Measurements Satellite. Explorer 8 studied the temporal and spatial distribution of ionospheric properties and confirmed the presence of a helium layer in the upper atmosphere.
S-30A was developed by MSFC with GSFC experiments.
The despin weights were 0.3 kg on a 5.2m wire.
| Explorer 8 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1960 Nov 3 | 0523:10 | Launch by Juno II | CC LC26B |
| 0526:09 | MECO | ||
| 0526:16 | Stage 1 sep | ||
| 0526:44 | Fairing sep | ||
| 0531:13 | Stage 2 burn | ||
| 0531:18 | Burnout | ||
| 0531:22 | Stage 3 | ||
| 0531:29 | Burnout | ||
| 0531:32 | Stage 4 | ||
| 0531:38 | Burnout | ||
| 0533:45 | T+10:35 Stage 4 sep | 370 x 2341 x 49.9 | |
| 0534? | Despin stage 1 (yo-yo) | ||
| 0535? | Despin stage 2 (RF impedance probe) | ||
| 1960 Dec 27 | 1220 | Last transmission | |
Payload:
- Electric field meter
- Single grid ion trap
- Langmuir probe
- Multigrid ion trap
- Micrometeor energy detector
- Micrometeor microphone board
- RF impedance probe, 2 x 3.0-m booms
Kosmos 1152
1980-006A
| Kosmos-1152 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1980 Jan 24 | 1545 | Launch by Soyuz | PL |
| 1553 | Blok-I sep | ||
| 1980 Jan 24 | 89.70 167 x 351 x 67.1 | ||
| 1980 Jan 25 | 89.66 171 x 343 x 67.1 | ||
| 1980 Jan 29 | 89.71 166 x 354 x 67.1 | ||
| 1980 Jan 30 | 89.49 151 x 346 x 67.1 | ||
| 1980 Jan 30 | 89.39 147 x 341 x 67.1 | ||
| 1980 Jan 31 | Orbit raise | 89.72 148 x 373 x 67.1 | |
| 1980 Feb 2 | SpK-1 fid | ||
| 1980 Feb 3 | 89.19 142 x 326 x 67.1 | ||
Raduga 2
1976-092A
Raduga (Gran') No. 12 was launched in Sep 1976 and stationed at 85E. NORAD stopped tracking in 1980 and resumed in 1987. The satellite was drifting slowly in the Indian Ocean gravitational stable point in the late 1990s.
| Raduga No. 12 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1976 Sep 11 | 1824 | Launch by Proton-K | KB |
| 1833 | Stage 3 MECO | 177 x 184 x 51.5 | |
| 1941? | DM burn 1 | 331 x 35802 x 47.3 | |
| 1976 Sep 12 | 0057? | DM burn 2 | |
| 0101? | DM sep | ||
| GEO 85E | |||
| 1977 Sep 5 | 1436.24 35770 x 35808 x 0.4 GEO 85.3E | ||
| 1978 Apr 29 | 1436.14 35776 x 35797 x 0.9 GEO 85.9E | ||
| 1980 May 23 | 1436.09 35764 x 35808 x 2.4 GEO 85.7E | ||
| 1985? | end of ops | ||
| 1987 Apr 23 | 1435.71 35661 x 35896 x 8.0 GEO 72.7E | ||
| 1987 Jul 26 | 1435.77 34675 x 35885 x 8.2 GEO 81.6E+0.07 | ||
| 1988 | Drift 85E-67E | ||
| 1999 Apr 20 | 1436.07 35694 x 35877 x 15.0 GEO 63.2E | ||
Inmarsat 201
1990-093A
The Matra/BAe Eurostar 1000 spacecraft built for Inmarsat as the first of the second generation Inmarsat system carried an L-band payload for mobile communications. BAe was lead contractor.
In 1996 it was replaced as the prime IOR satellite by Inmarsat III F1.
| Inmarsat II F-1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Oct 30 | 2316:00 | Launch by Delta 6925 | CC LC17 |
| T+0:56 SRM 1-3,7-9 out | |||
| T+1:01 SRM 4-6 on | |||
| T+1:02 SRM 1-3 sep | |||
| T+1:03 SRM 7-9 sep | |||
| T+1:57 SRM 4-6 off | |||
| T+2:02 SRM 4-6 sep | |||
| T+4:25 MECO | |||
| T+4:31 VECO | |||
| T+4:33 Stage 1 sep | |||
| 2320 | Stage 2 TIG (T+4:38) | ||
| 2320 | Fairing sep (T+4:50) | ||
| 2327 | SECO-1 (T+11:37) | 186 x 186? x 29.4? | |
| 2335 | Delta SES-2 | ||
| 2336 | Delta SECO-2 | 186? x 1170? x 25.0? | |
| spinup | |||
| 2337? | T+21 Delta sep | ||
| 2337? | TES | ||
| 2338? | TECO | ||
| 2340? | T+24:55 Stage 3 sep | ||
| 1990 Oct 31 | 0001 | T+45:05 Stage 3 sep | 647.28 188 x 36629 x 23.6 |
| 0002 | despin weights | ||
| 0018 | Stage 2 depletion | 100.39 379 x 1174 x 24.8 | |
| 1990 Nov 1 | 1300? | LAM-1 | 718.47 3922 x 36466 x 14.55 |
| 1990 Nov 2 | 1600? | LAM-2 | 1271.08 28510 x 36472 x 2.9 |
| 1990 Nov 4 | 1200? | LAM-3 | 1453.78 35681 x 36582 x 2.9 GEO 38.3W+46.8E |
| 1990 Nov 9 | 1436.22 35704 x 36582 x 2.7 GEO 49.2E+4.3W | ||
| 1990 Nov 16 | 1436.51 35661 x 35927 x 2.6 GEO 29.9E+0.1W | ||
| 1990 Nov 24 | 1436.35 35658 x 35928 x 2.6 GEO 29.2E | ||
| 1990 Nov | Move to IOR | ||
| 1990 Nov | Due at IOR 64.5E | ||
| 1991 Feb 19 | 1436.03 35701 x 35869 x 2.4 GEO 64.5E | ||
| 1991 Mar 28 | 1436.06 35734 x 35837 x 2.3 GEO 64.5E | ||
| 1993 Jun 20 | 1436.03 35726 x 35844 x 1.7 GEO 64.5E | ||
| 1996 Apr 16 | 1436.04 35771 x 35799 x 1.8 GEO 64.5E | ||
| 1996 Jul | IOR Spare | GEO 65E | |
| 1996 Sep 4 | 1435.97 35759 x 35808 x 1.9 GEO 65.2E | ||
| 1996 Sep | Move to POR | ||
| 1996 Nov 22 | 1436.18 35773 x 35803 x 1.9 GEO 179.0E | ||
| 1997 Jan 7 | 1435.95 35770 x 35797 x 1.9 GEO 179.6E | ||
| 1999 Jun 10 | 1436.02 35768 x 35801 x 1.8 GEO 179.1E | ||
| 2002 Apr 5 | 1436.02 35772 x 35797 x 2.1 GEO 179.0E | ||
Monday, October 7, 2002
Kosmos 1385
1982-068A
Two-tone telemetry; Medium res satellite
| Kosmos-1385 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1982 Jul 6 | 0750 | Launch by Soyuz-U | Plesetsk |
| 0754 | Blok-I burn | ||
| 0758 | Blok-I sep | ||
| 1982 Jul 6 | 88.76 186x238x82.3 | ||
| 1982 Jul 7 | 91.55 309x389x82.3 | ||
| 1982 Jul 15 | 91.52 305x391x82.3 | ||
| 1982 Jul 20 | |||
| 0320? | Deorbit | ||
| 0330? | PO sep | ||
| 0346? | Entry | ||
| 0358? | Landed | ||
Kosmos 404
1971-027A
Kosmos-404 was launched in Apr 1971 and intercepted Kosmos-400 on its second revolution, with a slow pass. It was maneuvered to a lower orbit and then deorbited. Orbital data from Apr 5 and 6 may refer to a fragment from the second stage or the DU; 1971-27D appears to be the same object.
| Kosmos-404 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1971 Apr 4 | 1427 | Launch by 11K69 | KB |
| 1429 | Stage 2 burn | ||
| 1432? | Stage 2 sep | 92.34 148 x 632 x 65.1 (RAE) | |
| 168 x 800? x 65.3 | |||
| 1520? | DU burn | ||
| 1736 | 103.11 801 x 1009 x 65.7 | ||
| 1743? | Flypast Kosmos-400, 4W 24N 1000 km | ||
| 1971 Apr 4 | ? | Deorbit | |
| 1971 Apr 5 | 0915 | 94.27 168 x 797 x 65.32 | |
| 1971 Apr 6 | 1700 | 92.41 125 x 659 x 65.0 | |
Kosmos 468
1971-114A
The 9th Strela-2 satellite was Kosmos-468, launched in Dec 1971 from Plesetsk. Kosmos-468 was placed in an orbital plane which would become the basis of a satellite constellation; I designate it as Strela-2 plane A.
| Kosmos-468 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1971 Dec 17 | 1300:01 | Launch by 11K65M | PL |
| 1302? | Stage 2 burn | ||
| 1308? | Stage 2 coast | ||
| 1334? | Stage 2 burn 2 | ||
| 1334? | Stage 2 sep | ||
| 1971 Dec 27 | 0500 | 100.83 786 x 809 x 74.0 | |
Telstar 301
1983-077A
AT&T;'s Telstar 301, or Telstar 3A, was launched by a Delta 3920 in 1983. In 1994 it was leased to Telesat. Telesat later leased it to Arabsat and it was renamed Arabsat 1D-R.
| Telstar 301 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1983 Jul 28 | 2249:02 | Launch by Delta 3920/PAM-D | CC LC17A |
| T+3:44 St 1 MECO | |||
| T+3:52 St 1 sep | |||
| T+3:57 SES-1 7:08 | |||
| T+4:00 Fairing | |||
| 2300 | T+11:05 SECO-1 | 180? x 190? x 29? | |
| 2309 | T+20:14 St 2 sep | ||
| 2309 | T+20:52 TES 86s | ||
| 2311 | T+22:18 TECO | ||
| 2313 | T+24:26 Stage 3 sep | 197 x 37264 x 22.8 | |
| 2355? | St 2 depletion | 263 x 379 x 25.99 | |
| 1983 Jul 29 | 0700? | Apo 1 | |
| 1600? | Apo 2 | ||
| 1983 Jul 29 | 1555? | Star 30B burn 54s at 2nd apo | |
1983 Jul 29 | 1405.54 33112 x 37260 x 0.5 GEO 76.7W+7.8E | ||
| 1983 Jul 30 | Tests | GEO 66W | |
| 1983 Aug 1 | 1436.04 35437 x 36133 x 0.2 GEO 65.4W | ||
| 1983 Sep 17 | 1436.32 35459 x 36122 x 0.2 GEO 66.2W | ||
| 1983 Sep? | GEO 96W | ||
| 1983 Oct 16 | 1436.10 35781 x 35791 x 0.0 GEO 96.0W | ||
| 1984 Apr 25 | 1436.11 35778 x 35795 x 0.0 GEO 96.0W | ||
| 1985 May 15 | 1436.11 35779 x 35794 x 0.0 GEO 96.0W | ||
| 1985 May 25 | 1436.12 35782 x 35791 x 0.1 GEO 104.8W | ||
| 1985 Jul 17 | Spacing for T303? | 1436.58 34540 x 37052 x 0.1 GEO 103.1W+0.1W | |
| 1985 Aug 26 | 1436.13 35783 x 35791 x 0.0 GEO 96.1W | ||
| 1985 Nov 25 | 1436.08 35781 x 35791 x 0.0 GEO 96.0W | ||
| 1986 Jun 11 | 1436.10 35779 x 35794 x 0.0 GEO 96.0W | ||
| 1987 Jul 6 | 1436.12 35779 x 35795 x 0.0 GEO 96.0W | ||
| 1988 Sep 9 | 1436.11 35778 x 35795 x 0.0 GEO 96.0W | ||
| 1989 Aug 25 | 1436.11 35781 x 35792 x 0.0 GEO 96.0W | ||
| 1991 Mar 7 | 1436.10 35770 x 35802 x 0.0 GEO 96.0W | ||
| 1992 Sep 27 | 1436.11 35778 x 35795 x 0.0 GEO 96.0W | ||
| 1993 Nov 20 | 1436.11 35756 x 35817 x 0.1 GEO 95.9W | ||
| 1993 Dec | Replaced by Telstar 401 | ||
| 1994 Feb 27 | mv out | 1436.11 35778 x 35794 x 0.3 GEO 96.0W | |
| 1994 Mar 14 | 1437.30 35801 x 35819 0.4 GEO 100.9W+0.3W | ||
| 1994 Mar 28 | Leased to Telesat | ||
| 1994 Apr | Moved to colocate with Anik E-2 | ||
| 1994 Apr 17 | mv in | 1436.08 35779 x 35793 x 0.5 GEO 107.1W | |
| 1994 Jun 7 | Sell to Arabsat | ||
| 1994 Jun 10 | 1436.10 35774 x 35798 x 0.6 GEO 107.1W | ||
| 1994 Aug 3 | 1436.08 35775 x 35797 x 0.7 GEO 107.0W | ||
| 1994 Aug 6 | Move out | GEO 104W drift 0.8/d | |
| 1994 Dec 1 | GEO 11W drift | ||
| 1995 Jan 13 | GEO 13E drift | ||
| 1995 Feb 6 | GEO 20E | ||
| 1995 Feb 6 | GEO 34.5E (mis-id?) | ||
| 1995 Feb 13 | GEO 34.5E (mis-id?) | ||
| 1995 Feb 14 | Mv in as Arabsat 1D-R | GEO 20E | |
| 1995 Feb 18 | 1436.03 35776 x 35793 x 1.1 GEO 20.0E | ||
| 1996 Aug 16 | 1436.04 35778 x 35792 x 2.3 GEO 20.0E | ||
Soyuz TM-32 (Crystal)
2001-017A
Souuz TM 206 (ISS 2S) was the first taxi flight, with the MKS-T1 crew (Kristall). EP-1 (orig MirCorp Citizen Explorer flight) with Dennis Tito, a rich investment management executive and former JPL trajectory guy. Commander was Talgat Musabaev and BI was Yuriy Baturin.
During reentry, the crew were subjected to 7g instead of the planned 4.8g. One rumour said the astronauts armed the deorbit engine later than intended, but official Russian statements indicated an error in the loaded guidance commands causing an incorrect entry angle.
| Soyuz TM-32 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Apr 28 | 0737:20 | Launch by Soyuz-U No 674 | KB PU5 |
| 0746:06 | Blok I sep | ||
| 1119:32 | TCM1 49 kg 19.3m/s | ||
| 1129:48 | TCM2 75 kg 29.5m/s | ||
| 2001 Apr 29 | 0.8m/s TCM | ||
| 2001 Apr 30 | 0730 | Rendezvous with ISS | |
| 0757:47 | Docking Zarya -Z port | ||
| 0928 | HO to ISS | ||
| 2001 Oct 19 | 0620 | HC to ISS; EX-3 aboard | |
| 1048:10 | Soyuz undocked from Zarya | ||
| 1058 | Begin lateral move | ||
| 1102 | Approach | ||
| 1104:10 | Dock with Pirs | ||
| 1240? | HO to ISS | ||
| 2001 Oct 30 | 2237 | HC to ISS | |
| 2001 Oct 31 | 0138:30 | Undocked from Pirs | |
| 0142 | Sep burn 8s 0.7m/s | ||
| 0404:10 | Deorbit 4:12 115.2m/s | ||
| 0407 | Deorbit MECO | 88.39 5? x 384 x 51.6 | |
| 0430? | Modules sep | ||
| 0459:26 | Landed | ||
DASH
2002-003B
The ISAS Demonstrator of Atmospheric Reentry System at Hypervelocity (DASH) is a secondary payload on H-IIA-F2. It will deorbit from GTO at high (hyperbolic) velocity. The mission is a test for MUSES-C. It was meant to reenter at 10.2 km/s between -18.5 and -16.5 at 200 km (corresponding to -423 x 34153 x 28.5 to -574 x 34305 x 28.5) and land in Africa (Mauritania? at about 8.5W 17.2N. in the Hodh el Gharbi region. In the event it failed to separate from VEP-3.
DASH consists of a hexagonal bus with a deorbit motor (DOM), and a blunt cone reentry capsule, and two DFM thrusters for orbit adjust at apogee. The size of DASH is 0.99m x 0.70m x 0.54m. including the comms antenna; bus size is 0.7 x 0.5m. Mass of the orbiter and DOM is 70 kg. The reentry capsule has a mass of 16 kg and is 0.40m dia, 0.20m high. A 3 kg adapter is mounted to the H-2A upper adapter.
In Japanese DASH is
\uni{ 高速再突入実験機}{ }
(Kosoku sai totsunyu jikken ki, High speed reentry experimental machine).| DASH (planned) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Jan 31 | Launch | ||
| T+0:10 SSB 1-2 on | |||
| T+1:10 SSB 1-2 sep | |||
| T+1:16 SSB 3-4 on | |||
| T+2:16 SSB 3-4 sep | |||
| SRB-A sep | |||
| Stage 1 sep | |||
| Stage 2 MES | |||
| Fairing sep | |||
| Stage 2 MECO-1 | |||
| Stage 2 MES-2 | |||
| Stage 2 MECO-2 | |||
| DASH/VEP-3 separates from Stage 2 | |||
| Stage 2 deploy MDS-1 | |||
| VEP-3 failed to deploy DASH | |||
| D+5:00 Sep ENA | |||
| D+5:56 SPM | |||
| D+37h DFM | |||
| D+43h DFM | |||
| 2002 Feb 4 | D+76h DOM burn | ||
| Yo-yo despin | |||
| Capsule separation | |||
| T+85h Reentry | |||
Skynet 2B
1974-094A
The Skynet 2B satellite was similar to Skynet 2A in design. It was launched in Nov 1974 and began an extremely successful career relaying UK military communications. It ran out of stationkeeping fuel in the 1980s but it was still working in 1994. The spacecraft is currently drifting between 0 and 150 deg E longitude.
| Skynet 2B | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1974 Nov 23 | 0028:01 | Launch by Delta DSV-3P-11A (2313) | CC LC17B |
| T+0:38 SRM 1-3 out | |||
| T+1:10 SRM 1-3 sep | |||
| 0031:45 | T+3:45 MECO | ||
| 0031:54 | T+3:54 VECO | ||
| 0031:56 | Stage 1 sep | ||
| 0032:03 | T+4:02 SES-1 4:43 | ||
| T+4:37 Fairing | |||
| 0037:16s | T+9:15 SECO-1 | 176 x 200 km | |
| 0049:48 | T+21:47 SES-2 16s | ||
| 0050:06 | T+22:05 SECO-2 | 183 x 1152 x 28.17 | |
| 0050:58 | T+22:57 St 2 sep | ||
| 0051:31 | T+23:30 TES 44s | ||
| 0052:15 | T+24:14 TECO Star 37 burnout | 175 x 36965 x 24.6 | |
| 0053:31 | T+25:30 Star 37 sep | 185 x 36944 x 24.6 | |
| 1974 Nov 23 | 0104? | SES-3 engineering burn | 311 x 3347 x 28.3 |
| 0600? | Apo 1 95E | ||
| 1700? | Apo 2 70W | ||
| 1974 Nov 24 | 0400? | Apo 3 125E | |
| 1500? | Apo 4 40W | ||
| 1974 Nov 25 | 0130? | Apo5 170E | |
| 1974 Nov 25 | 0110 | Star 24 AKM 42s, apo 5 | GEO +6E/d |
| 36255 x 36621 x 2.3 | |||
1975 Jan 3 | On station IOR GEO 50E | ||
| 1975 Dec 30 | GEO 55E (Morgan) | ||
| 1977 early | Command system failure | GEO dr | |
| 1977 Mar 1 | 1435.25 35757 x 35782 x 0.8 | ||
| 1978 Sep | GEO dr | ||
| 1979 Oct 31 | 1435.75 35753 x 35806 x 1.5 GEO 4.4E+0.1E | ||
| 1979 Dec | GEO 1W | ||
| 1980 Dec 6 | 1435.17 35740 x 35796 x 2.2 GEO 123.8E+0.2E | ||
| 1981 Feb | GEO 137E | ||
| 1981 Jun | GEO 140.4E+0.03 | ||
| 1981 Sep 8 | 1436.81 35791 x 35809 x 2.7 GEO 130.2E+0.2W | ||
| 1982 Nov | GEO 6E | ||
| 1983 Jan | GEO 1E | ||
| 1983 Sep | GEO 9E | ||
| 1984 May 25 | 1434.48 35753 x 35756 x 4.7 GEO 93.3E+0.4E | ||
| 1985 Apr | GEO 138E | ||
| 1985 Jun 2 | 1436.82 35799 x 35801 x 5.6 GEO 130.1E+0.2W | ||
| 1985 Jul | GEO 0W | ||
| 1985 Sep | Drifting | ||
| 1988 Jun 27 | 1435.36 35759 x 35784 x 8.1 | ||
| 1994 Jan 13 | 1436.68 35776 x 35819 x 12.3 | ||
| 1994 | Still operating | ||
| 1998 Sep 8 | 1435.87 35751 x 35812 x 14.1 | ||
Sunday, October 6, 2002
CONTOUR
2002-034A
Contour, the Comet Nucleus Tour, is the 2002 Discovery mission. Its goal is to image comet nuclei at 4m resolution, and provide nuclear spectral maps at 100-200m resolution. It will also make composition measurements on cometary gas and dust. The APL-built probe is led by a Cornell University team.
Mass is 970 kg at launch - 387 kg dry, 503 kg Star 30BP S/N 074, 80 kg hydrazine. Size is a 2.0m dia, 2.0m long octagonal cylinder.
Contact was lost at solid motor firing. Three fragments were observed: A, B and C. A design error meant that the spacecraft overheated and key components were destroyed. B is a small 4 kg piece based on acceleration measurements. A had a mass of around 300 kg, and is probably the main bit of Contour.
| Contour | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Jul 3 | 0647:41 | Launch by Delta 7425-9.5 | |
| T+1:03 SRM 1-4 burnout | |||
| T+1:08 SRM 1-4 sep | |||
| 0652:05 | T+4:24 MECO | ||
| T+4:32 Stage 1 sep | |||
| 0652:18 | T+4:37 SES-1 | ||
| T+4:42 Fairing sep | |||
| 0659:17 | T+11:36 SECO-1 | 185 x 197 x 29.7 | |
| 0746:11 | T+58:30 SES-2 | ||
| 0746:15 | T+58:34 SECO-2 | 185 x 308 x 29.7 | |
| 0747:08 | T+59:27 St 2 sep | ||
| 0747:47 | T+1:00:06 PAM-D burn 2921 m/s | ||
| 0749:13 | T+1:01:32 TECO | 2423.6 90 x 106689 x 30.5 | |
| 0751:11 | T+1:03:30 St 3 sep | ||
| 0751:13 | T+1:03:32 Yo weight sep | ||
| SES-3 depletion | 174 x 300 x 30.4 | ||
| 2002 Jul 4 | Apogee 1 | ||
| 2002 Jul 5 | 0325 | Perigee 1 | |
| 2002 Jul 6 | Apogee 2 | 236 x 109000? | |
| 1644 | OCM-2, +3.8m/s, phasing period | ||
| 2002 Jul 6 | 2106 | Perigee 2 | |
| 2002 Jul 7 | Apogee 3 | 268 x ? | |
| 2002 Jul 8 | 1458 | Perigee 3 | |
| 2002 Jul 11 | 2018 | Perigee 5 OCM-4 +0.9m/s | |
| 2002 Jul 18 | 217 x 108466 x 30.24 | ||
| 2002 Jul 20 | 231 x 108441 x 30.21 | ||
| 2002 Jul 23 | 2150 | OCM-5 +0.12m/s | 225 x 108484 x 30.26 |
| 2002 Jul 27 | 198 x 108481 x 30.56 | ||
| 2002 Jul 27 | 1202 | OCM6, 58s 3.0m/s at TRUE=148.5 | 197 x 108457 x 30.6 |
| 2002 Jul 28 | 230 x 108704 x 30.6 | ||
| 2002 Jul 30 | 246 x 108685 x 30.74 | ||
| 2002 Jul 31 | 1713 | OCM7 3.2m/s 63s lower perigee | 266 x 108645 x 30.7 |
| 2002 Aug 2 | 228 x 108610 x 30.5 | ||
| 2002 Aug 3 | 0715 | OCM8 Perigee 0.7m/s 18s at 12021 km, return to 1.75d | 242 x 108618 x 30.5 |
| 2002 Aug 5 | 238 x 109658 x 30.5 | ||
| 2002 Aug 6 | 1722 | OCM-9 0.22m/s to adjust time and C3 | |
| 2002 Aug 13 | 1521 | Perigee | |
| 2002 Aug 14 | 1206 | Apogee R = 115058 km | |
| 2002 Aug 15 | 0849 | Perigee | |
| 2002 Aug 15 | 0849 | Solar orbit injection with SRM, 50 s, 1.926 km/s planned | |
| Actual dV 1.850 km/s | |||
| Loss of signal | 240 x -33995 x 30.6 | ||
| 225 x -34869 x 30.98 (A) | |||
| 2002 Aug 15 | 1446 | C Pass EL1:4 | |
| 2002 Aug 15 | 1450 | B Pass EL1:4 | |
| 2002 Aug 15 | 1450 | A Pass EL1:4 | |
| 2002 Aug 17 | 0400 | C leaves E/M SOI | |
| 2002 Aug 17 | 0500 | A leaves E/M SOI | 225 x Inf x 30.97 |
| 2002 Aug 17 | 0500 | B leaves E/M SOI | |
| 2002 Aug 18 | 0242 | C leaves Earth sphere 1.5Mkm | |
| 2002 Aug 18 | 0342 | B leaves Earth sphere 1.5Mkm | |
| 2002 Aug 18 | 0342 | A leaves Earth sphere 1.5Mkm | |
| 2003 Jan 1 | Fragment A | 0.876 x 1.131 AU x 8.71 | |
| 2003 Jan 1 | Fragment B | 0.875 x 1.132 AU x 8.72 | |
| 2003 Jan 1 | Fragment C | 0.871 x 1.129 AU x 8.91 | |
| 2003 Aug 14 | 0800 | C within E/M SOI | 742000 x Inf x 37.45 |
| 2003 Aug 15 | 1329 | Fragment C flies 742000 km +/- 1.3Mkm from Earth | |
| 2003 Aug 16 | 1333:12 | Fragment A flies 4926000 km from Earth | |
| 2003 Aug 16 | 2000 | C leaves E/M SOI | |
| 2003 Aug 17 | 0015 | Fragment B flies 6820000 km from Earth | |
| planned | |||
| Star 30 cutoff | 225 x Inf | ||
| 2002 Aug 16 | TCM-1 | 0.80 x 1.35 AU | |
| 2003 Aug 15 | Earth flyby 58000 km | ||
| 2003 Aug | 0.9 x 1.2 AU? | ||
| 2003 Nov 12 | 2P/Encke flyby 100 km at 1.07AU from Sun | ||
| 2004 Aug 14 | Earth flyby 40180 km | ||
| Orbit i = 12.0 | 1.0 x 1.0 AU x 12.0? | ||
| 2005 Feb 10 | Earth flyby 218770 km | ||
| 2006 Feb 10 | Earth flyby 30000 km | ||
| 2006 Feb | 0.9 x 1.1 AU? x 0? | ||
| 2006 Jun 18 | 73P/Schwassmann-Wachmann-3 flyby at 0.95AU from Sun | ||
| 2007 Feb 10 | Earth flyby 7600 km | ||
| 2007 Feb | 0.8 x 1.35 AU? | ||
| 2008 Feb 11 | Earth flyby 19000 km | ||
| 2008 Aug 15 | 6P/d'Arrest flyby at 1.35 AU from Sun. | ||
Payload:
- CRISP Contour Remote Imager/Spectrograph
- CAI Contour Aft Imager
- CIDA Dust Analyser
- NGIMS Neutral Gas Ion Mass Spectrometer