2001-057A
US-PM launched 0400 UTC Dec 21 from KB LC90 by 11K69. Possibly KB Arsenal 17F120 US-PU, mass 3150 kg, RCS 22m2.
| Kosmos-2383 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Dec 21 | 0400:00 | Launch by 11K69 | KB LC90 |
| 0402 | Stage 1 sep | ||
| 0404 | Fairing sep | ||
| 0404:39 | Stage 2 sep | 90.02? 145? x 415 x 65.0 | |
| 0448:31 | Orbit insertion 78m/s? | 92.77 404 x 415 x 65.0 | |
| 0535 | St 2 first perigee | ||
| 1243 | St 2 orbit | 87.62 104 x 207 x 65.0 | |
| 1317? | Stage 2 reentered over Iran? | ||
| 2004 Feb 15 | 92.78 400 x 421 x 65.0 | ||
1994-064A
Intelsat 703 was launched on 1994 Oct 6 at 0635:02 UT by Atlas Centaur AC-111. The satellite is a 3-axis stabilized Space Systems/Loral FS-1300 with 26 C-band and 10 Ku-band transponders and will serve the Pacific Ocean region. The Martin Marietta Atlas IIAS Centaur delivered the satellite into a geostationary transfer orbit. The MA-5A main engine and two of the four Castor IVA solid rocket boosters ignited at liftoff; the other two solids ignited at 0636:02. The first two solids were jettisoned at 0636:14 and the second two at 0636:57. The MA-5A propulsion system on the Atlas consists of two booster engines and a central sustainer engine. At 0637:47 the booster engines were shut down, and at 0637:50 the tail section of the Atlas IIA fell away leaving the main sustainer engine exposed. At 0638:31 the payload fairing around the Intelsat payload was discarded - AC-111 was now high enough that aerodynamic protection was not needed. The Atlas sustainer cut off at 0639:53 and the Atlas IIA stage separated onto its suborbital trajectory at 0639:55. Intelsat 703 was now attached to the AC-111 Centaur IIA. At 0640:17 the two RL10-4A liquid hydrogen/liquid oxygen engines on the Centaur ignited and burned until 0645:17. The combination was now in a parking orbit. After a coast period, AC-111 reignited at 0659:29. It shut off at 0701:12, and separated from Intelsat 703 at 0703:22. Intelsat 703 was now in a 283 x 38575 km x 25.9 deg orbit. The apogee was higher than initially expected and will let the satellite save fuel on reaching its final orbit. Over the next few days it fired its R4D liquid apogee engine to enter first a 7598 x 38540 km x 11.2 deg orbit (Oct 9) and then a 35670 x 38552 km x 0.2 deg orbit (Oct 11). This final orbit is a little higher than geostationary; on Oct 11 at 1815 UT the satellite was over 138 deg East and drifting 16 degrees per day.
Ownership was transferred in 1998 to New Skies.
| Intelsat 703 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Oct 6 | 0635:02 | Launch by Atlas Centaur | |
| 0636:14 | SRB 1-2 sep | ||
| 0636:57 | SRB 3-4 sep | ||
| 0637:47 | BECO | ||
| 0637:50 | Booster sep | ||
| 0638:31 | Fairing sep | ||
| 0639:53 | MECO | ||
| 0639:55 | Atlas sep | ||
| 0640:17 | Centaur MES1 | ||
| 0645:17 | Centaur MECO1 | ||
| 0659:29 | Centaur MES2 | ||
| 0701:12 | Centaur MECO2 | ||
| 0703:22 | Centaur sep | 283 x 38575 x 25.9 | |
| 1994 Oct 6 | 688.06 284 x 38593 x 25.9 | ||
| 1994 Oct 8 | 1030? | LAM-1 at 120E | |
| 1994 Oct 8 | 769.42 4293 x 38578 x 15.5 | ||
| 1994 Oct 9 | 1240? | LAM-2 at 94E | |
| 1994 Oct 9 | 838.16 7598 x 38540 x 11.2 | ||
| 1994 Oct 10 | 1600? | LAM-3 | |
| 1994 Oct 11 | 0850? | LAM-4 | |
| 1994 Oct 11 | 1504.40 35671 x 38555 x 0.2 GEO 140.7E+16.4W | ||
| 1994 Oct 12 | 2240? | LAM-5 | |
| 1994 Oct 12 | 1434.22 35667 x 35832 x 0.2 GEO 121.0E+0.5E | ||
| 1994 Oct 14 | 1437.06 35671 x 35939 x 0.2 GEO 120.7E+0.1W | ||
| 1994 Nov | Move to POR | ||
| 1994 Dec 9 | 1436.07 35774 x 35797 x 0.1 GEO 177.0E | ||
| 1994 Dec 26 | 1436.10 35776 x 35796 x 0.1 GEO 177.0E | ||
| 1996 May 27 | mv out | GEO 177E | |
| 1996 Jun 22 | mv in | GEO 56E | |
| 1996 Nov 20 | 1436.11 35772 x 35800 x 0.0 GEO 57.0E | ||
| 1998 Nov 30 | To New Skies NV | ||
| 1999 Oct 14 | 1436.01 35681 x 35888 x 0.1 GEO 57.1E | ||
| 2002 May 5 | 1436.10 35773 x 35799 x 0.2 GEO 57.0E | ||
2001-040A
The first of a new generation of NOSS satellites was launched in Sep 2001. The AC-160 launch was codenamed 'Gemini'.
There are two spacecraft operating in polar orbit to intercept radio transmissions. It is probably a followon to NOSS. The contract was awarded to LMA/Denver in 1994 (TRW was the rival bidder). In late 1998 it was reported that the program had large overruns.
AC-160 used a Centaur with RL10A-4-1 engines and a 14' PLF.
As well as USA 160 and the Centaur, a third object was cataloged. This was registered with the UN as a debris object but appears to be the second payload.
| NRO | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Sep 8 | 1525:05 | Launch by Atlas IIAS AC-160 | V SLC3E |
| T+0:57 SRB 3-4 ignition | |||
| T+1:59 SRB 1-2 sep | |||
| T+2:02 SRB 3-4 sep | |||
| T+2:47 BECO | |||
| T+2:50 Booster sep | |||
| T+3:39 14' PLF sep | |||
| T+4:33 SECO | |||
| T+4:35 Atlas sep | |||
| T+4:52 MES-1 | |||
| 1535:45 | T+10:40 MECO-1 | 160 x 1200 x 63? (guess) | |
| 1629 | T+1:04:10? MES-2 12s | ||
| 1629 | T+1:04:22? MECO-2 | ||
| 1633 | T+1:08 Centaur sep | 1000 x 1200? x 63? | |
| 2001 Sep 26 | 999 x 1203 x 63.4 (UN) | ||
1971-008A
Apollo CSM 110 was flown on the Apollo 14 mission to Fra Mauro. Commander Alan Shepard, CMP Stuart Roosa, and LMP Ed Mitchell named it `Kitty Hawk. On Feb 7 the crew carried out some of the first materials processing experiments done in space, including electrophoresis tests and a composite casting test.
| Kitty Hawk (CSM 110) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1971 Jan 31 | 2103:02 | Launch by Saturn V (SA-509) | KSC LC39A |
| 2105:17 | S-IC CECO | ||
| 2105:45 | S-IC OECO | ||
| 2105:47 | S-IC sep, S-II ignition | -6009 x 112 x 30.70 | |
| 2106:16 | Interstage sep | -5952 x 120 x 30.76 | |
| 2106:22 | LES jet | -5937 x 122 x 30.77 | |
| 2110:45 | S-II CECO | ||
| 2112:21 | S-II OECO, sep 182.6 km | -1977 x 184 x 31.12 | |
| 2112:22 | S-IVB ignition | ||
| 2112:33 | Ullage case jettison | -1897 x 184 x 31.1 | |
| 2114:42 | S-IVB cutoff | ||
| 2114:51 | Earth orbit insertion | 183 x 189 x 31.11 | |
| 185 x 185 x 31.11 (MPR) | |||
| 2115:32 | 184 x 185 x 31.1 | ||
| 2123:02 | 184 x 190 x 31.1 | ||
| 2124 | Optics cover jettison | ||
| 2148:02 | 180 x 200 x 31.1 | ||
| 2220:32 | 187 x 203 x 31.2 | ||
| 2236:22 | T+1:33:20 | 191 x 192 x 31.1 | |
| 2331:33 | S-IVB TLI burn | ||
| 2337:24 | S-IVB cutoff | ||
| 2337:34 | Translunar injection at 337 km | 214 x 461334 x 30.8 | |
| 1971 Feb 1 | 0005:32 | CSM sep from SLA/S-IVB | 217 x 455424 x 30.8 |
| Transposition and docking maneuver | |||
| 0016:56 | CSM failed to dock with LM, attempt 1A | ||
| 0017:03 | Attempt 1B | ||
| 0017:06 | Attempt 1C | ||
| 0017:11 | Attempt 1D | ||
| 0017:46 | Attempt 2 | ||
| 0019:45 | Attempt 3 | ||
| Stationkeep for 6 minutes | |||
| 0026:44 | Attempt 4, failed to dock with LM | ||
| Stationkeep for 70 minutes | |||
| 0037 | S4B venting | ||
| 0136 | Attempt 5, CSM failed to dock with LM | ||
| Stationkeep for 20 min | |||
| 0157 | At 3m | ||
| 0159:46 | Attempt 6 to dock with LM, successful | ||
| 0159:58 | CSM docked with LM | ||
| 0250:27 | CSM/LM sep from S-IVB | 220 x 454981 x 31.0 | |
| 1419 | Pass EL1:4 | ||
| 1971 Feb 2 | 0339:09 | MCC-2 burn 10s | 120 x 456123 x 31.1 |
| 0339:20 | MCC-2 CO | -520 x 441384 x 31.2 | |
| 1971 Feb 3 | 1512:03 | Equigravisphere | |
| 1971 Feb 4 | 0201:13 | MCC-4 burn 0.7s | 140 x -14916 x 154.4 |
| 134 x -14907 x 154.3 | |||
| 0659:42 | SPS LOI-1 burn 370.8s | 111 x -14833 x 167.0 | |
| 0705:54 | Lunar orbit insertion cutoff | 109 x 315 x 166 | |
| 1113:54 | SPS LOI-2 burn (DOI) 20.8s | 18 x 109 x 166 | |
| 1114:16 | DOI cutoff | 19 x 109 x 156.1 (MR) | |
| 1971 Feb 5 | Photography of Descartes site | ||
| CDR and LMP transfer to LM | |||
| 0450:45 | LM undocked | 15 x 112 x 149.2 | |
| 0452 | CSM sep burn | 14 x 111 | |
| 0614:48 | Circ burn 4s | ||
| 0614:52 | Circ cutoff | 104 x 118 | |
| 1832:35 | LOPC-1 burn 18.5s | 106 x 115 | |
| 1832:54 | LOPC-1 cutoff | ||
| 1971 Feb 6 | Rendezvous by LM | ||
| 2035:52 | LM docked with CSM | ||
| CDR and LMP return to CSM | |||
| 1971 Feb 6 | 2248:00 | Antares undocked | |
| 2252:45 | Sep burn | 105 x 115 | |
| 1971 Feb 7 | 0139:04 | SPS TEI burn 2:29 | |
| 0141:33 | Transearth injection | 110 x -10361 x 172.7 | |
| 1530 | Homebound equigravisphere | ||
| 1837:58 | MCC-5 burn 3s | -885 x 658137 x 42.37 | |
| 1971 Feb 9 | 2035:44 | SM-110 sep | 40 x 663641 x 40.6 |
| 2050:47 | Entry | 42 x 733353 x 40.47 | |
| 2104:59 | Splashdown in Pacific 27 02 24S 172 41 24W | ||
| Recovered by USS New Orleans | |||
1978-012A
The International Ultraviolet Explorer was designed for a six month mission but was still operating 16 years later. IUE took ultraviolet spectra of astronomical objects - tens of thousands of them. It was the first astronomy satellite to be operated as an observatory, available for use by the whole astronomical community. Uniquely, it was in geosynchronous orbit, so that astronomers at the NASA-Goddard or ESA-Villafranca control centers could control the spectrographs in real time. IUE was jointly funded by NASA, ESA, and the UK Science Research Council; the orbit drifted back and forward across the Atlantic and observing was handled from the ESA ground station for 8 hours a day and from Goddard for 16 hours a day.
IUE was launched on 1978 Jan 26 at 1736 by a Delta 2914 from Cape Canaveral's Launch Complex 17A. The Delta stage entered a 96.6 min, 164 x 1024 km x 28.7 deg and separated from the third stage. The Star 37E third stage fired and placed IUE in a 846.7 min, 177 x 46367 km x 28.7 deg orbit. The Star 24 apogee motor fired to put the satellite in a final orbit of 1435.7 min, 25669 x 45888 km x 28.6 deg. Observations began a few days later. The internal propulsion system was used occasionally to maintain the satellite at the correct longitude.
On 1995 Oct 1 operational control of IUE was transferred completely to ESA-Villafranca. ESA and PPARC (the successor to SERC) would operate the spacecraft. IUE was shut down at 1842 UT on 1996 Sep 30.
| IUE | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Jan 26 | 1736:00 | Launch by Delta 2914 | CC LC17A |
| 0135:38 | SRM 1-6 cutoff | ||
| 0135:39 | SRM7-9 burn | ||
| 0136:17 | SRM7-9 cutoff | ||
| 0136:27 | SRM 1-9 sep | ||
| T+3:42 MECO | |||
| T+3:49 Stage 1 sep | |||
| T+3:55 Stage 2 burn | |||
| 1740 | T+4:33 Fairing sep | ||
| 1745 | T+8:47 SECO-1 164 km vrel 7.807 | 167 x 167? x 28.7 | |
| 1816 | T+40:12 SES-2 172 km vrel 7.797 | ||
| 1816 | T+40:30 SECO-2 172 km 8.024 | 96.6 164 x 1024 x 28.7 | |
| 1817 | T+41:22 Stage 2 sep 170 km 8.026 | ||
| 1818 | T+42:03 TES 172 km 8.025 | ||
| 1818 | T+42:47 TECO 176 km | 846.7 177 x 46367 x 28.7 | |
| 1819 | T+43:50 S/C sep 204 km | ||
| 1978 Jan 27 | 0300? | Apo 1 | |
| 1978 Jan 27 | 1454 | Star 24 burn, apo 2 | 1435.7 25669 x 45888 x 28.6 |
| 1978 Jan 28 | Despin using HAPS | ||
| 1978 Jan 28 | 0602 | 1435.64 25668 x 45886 x 28.6 55.2W | |
| 1978 Jan 30 | 1630 | Dust cover ejected | |
| 1978 Feb 1 | First images from FES | ||
| 1978 Feb 9 | First data currently in archive | ||
| 1978 Feb 13 | Orbit correction | ||
| 1978 Mar 30 | 1436.38 25711 x 45872 x 28.6 51.8W | ||
| 1978 Jul 24 | Orbit correction | ||
| 1979 Jun 20 | Orbit correction | ||
| 1980 Feb 13 | Orbit correction | ||
| 1980 Apr 18 | 1435.66 25888 x 45667 x 28.2 | ||
| 1980 Jun 24 | Orbit correction | ||
| 1980 Dec 16 | Orbit correction | ||
| 1981 May 8 | Orbit correction | 1436.07 26080 x 45491 x 28.3 | |
| 1981 Oct 29 | Orbit correction | ||
| 1982 Aug 17 | Orbit correction | 1435.54 26426 x 45125 x 28.6 | |
| 1983 May 27 | Orbit correction | ||
| 1984 Jan 12 | Orbit correction | ||
| 1984 Feb 14 | Orbit correction | ||
| 1984 Nov 16 | Orbit correction | ||
| 1985 Jul 16 | 1436.63 27451 x 44142 x 29.7 | ||
| 1985 Aug 9 | Orbit correction | ||
| 1985 Sep 6 | 1435.59 27533 x 44020 x 29.8 | ||
| 1986 Mar 19 | Orbit correction | ||
| 1986 Jul 29 | Orbit correction | 1435.81 27952 x 43609 x 30.2 | |
| 1986 Dec 18 | Orbit correction | ||
| 1987 Sep 9 | Orbit correction | ||
| 1988 Mar 18 | Orbit correction | ||
| 1988 Sep 8 | Orbit correction | ||
| 1989 Mar 13 | Orbit correction | ||
| 1989 Sep 8 | Orbit correction | ||
| 1990 Jun 6 | Orbit correction | ||
| 1990 Dec 3 | 1436.35 29787 x 41795 x 32.6 53.5W | ||
| 1991 Jan 14 | 1436.46 29799 x 41787 x 32.3 56.9W | ||
| 1991 Jan 12 | Orbit correction | ||
| 1991 Feb 6 | 1435.64 29811 x 41743 x 32.7 | ||
| 1991 Nov 5 | 1436.74 29881 x 41716 x 33.0 57.4W | ||
| 1991 Oct 18 | Orbit correction | 1435.91 30045 x 41520 x 33.3 51.7W | |
| 1992 Aug 18 | 1436.86 30160 x 41443 x 33.5 68.6W | ||
| 1992 Aug 19 | Orbit correction | 1435.72 30162 x 41395 x 33.5 68.0W | |
| 1992 Nov 19 | 1436.07 30208 x 41363 x 33.7 64.3W | ||
| 1992 Nov 20 | Orbit correction | 1435.41 30213 x 41333 x 33.7 64.1W | |
| 1993 Aug 17 | 1436.53 30264 x 41325 x 34.1 45.2W | ||
| 1993 Aug 19 | Orbit correction | 1435.77 30256 x 41304 x 34.1 46.1W | |
| 1993 Sep 20 | 1435.84 30264 x 41299 x 34.2 51.1W | ||
| 1994 Feb 14 | 1436.49 30242 x 41346 x 34.5 57.4W | ||
| 1994 Feb 15 | Orbit correction | 1435.67 30243 x 41312 x 34.5 57.4W | |
| 1994 Sep 20 | 1436.60 30235 x 41357 x 34.8 55.4W | ||
| 1994 Sep 20 | Orbit correction | 1435.55 30243 x 41308 x 34.8 52.9W | |
| 1995 Apr 30 | 1436.58 30207 x 41384 x 35.1 48.4W | ||
| 1995 May 3 | Orbit correction | 1435.85 30183 x 41380 x 35.1 48.1W | |
| 1995 Jun 5 | 1435.98 30178 x 41389 x 35.2 | ||
| 1995 Jun 6 | Orbit correction | 1435.19 30162 x 41374 x 35.2 | |
| 1996 Mar 5 | 1436.21 30095 x 41482 x 35.6 35.8W | ||
| 1996 Mar 6 | Command error, control lost | ||
| 1996 Mar 11 | One-gyro control enabled | ||
| 1996 Sep 29 | 1437.04 29992 x 41617 x 35.9 65.5W | ||
| 1996 Sep 30 | 1357 | Science cameras off | |
| 1730 | Propellant drained (18 kg) | ||
| 1842 | Spacecraft deactivated | ||
| 1996 Oct 10 | 1439.04 30216 x 41472 x 35.6 | ||
| 1999 Apr 27 | 1438.85 29739 x 41941 x 37.2 | ||
2001-021A
The next ferry, spacecraft 11F655 No. 255, carried food and equipment to ISS including backup parts for the Destiny C+C computers. Launch of ISS supply flight 4P was by the first Soyuz-FG, a Soyuz-U with uprated engines featuring improved fuel injection.
The vehicle carried 2478 kg of cargo including 900 kg of fuel for Zvezda and 1300 kg dry cargo.
| Progress M1-6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 May 20 | 2232:40 | Launch by Soyuz-FG | KB PU5 |
| T+1:58 St 1 sep | |||
| T+2:32 GO sep | |||
| T+4:47 St 2 sep | |||
| T+4:57 KhO sep | |||
| T+8:44 St 3 MECO | |||
| 2241:29 | Blok I sep | ||
| 2001 May 23 | Rendezvous with ISS | ||
| 0023:57 | Docked with Zvezda -Y | ||
| 0210 | HO to ISS | ||
| 2001 Aug 22 | 0601 | Undocked from Zvezda -Y | |
| 0900? | Deorbit | ||
1972-101A
The fifth CANYON appears to have been a new spacecraft design. The Agena was cataloged immediately after launch and may have separated from the payload once it reached its geosynchronous station.
| CANYON 5 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1972 Dec 20 | 2220 | Launch by Atlas Agena D | CC |
| BECO | |||
| Atlas sep | |||
| 2225? | Agena MES-1 | ||
| 2230? | Agena MECO-1 | 190 x 190 x 28.5? | |
| 2245? | Agena MES-2 | ||
| Agena MECO-2 | 190 x 40000 x 28.5? | ||
| 1972 Dec 21 | 0420? | Agena MES-3 | |
| Agena MECO-3 | 31012 x 40728 x 9.7 | ||
| 0430? | Agena sep | ||
2001-001A
Shenzhou 2's orbital module was designed to operate for 6 months in space following the 7 day main mission. The spacecraft contains animals and scientific experiments. As well as reentry and orbital modules, an attached segment exposure facility was added with 37 experiments. A monkey, a dog and a rabbit were carried according to some sources. Little information was released about the landing and observers speculated that some kind of failure may have occurred.
| Shenzhou 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Jan 9 | 1700:03 | Launch by CZ-2F | JQ |
| T+2:16 SRM burnout, sep | |||
| T+2:38 St 1 MECO | |||
| T+2:39 St 1 sep, St 2 burn | |||
| T+2:40 Fairing sep | |||
| T+7:41 St 2 MECO | |||
| 1709:46? | T+9:43? St 2 VECO | ||
| 1710 | Stage 2 sep | 197 x 335 x 42.6 | |
| 2001 Jan 10 | 1325 | Orbit raise | 329 x 334 |
| 2001 Jan 12 | 327 x 334 | ||
| 1220 | Orbit raise | 330 x 340 x 42.6 | |
| 2001 Jan 15 | 330 x 339 | ||
| 1047 | Orbit raise | 330 x 346 x 42.6 | |
| 2001 Jan 16 | 1023 | OM sep | |
| 1033 | Deorbit 34.2S 7.3W | ||
| Reentry | |||
| 1122 | Landing in Inner Mongolia | ||
1994-068A
The IRS P2 satellite was launched aboard the second PSLV test flight. PSLV-D2 took off from Sriharikota on 1994 Oct 15. The 805 kg satellite entered polar orbit successfully.
| IRS-P2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Oct 15 | 0505 | Launch by PSLV-D2 | SHAR |
| T+00:30 PSOM 5-6 ignite | |||
| T+00:54 PSOM 1-4 cutoff | |||
| T+01:18 PSOM 1-4 sep | |||
| T+01:19 PSOM 5-6 cutoff | |||
| T+01:30 PSOM 5-6 sep | |||
| 0506 | T+01:43 PS-1 cutoff and sep | ||
| 0506 | T+1:46 PS2 burn 2:29 | ||
| T+3:02 Fairing | |||
| 0509 | T+4:15? PS2 burnout | ||
| 0509 | PS2 sep | ||
| 0509 | T+4:21 PS3 burn 78s | ||
| 0510 | T+5:33? PS3 burnout | ||
| 0511 | T+6:20 PS3 sep | ||
| 0516? | T+9:50 PS4 burn, 397s | -4100? x 818 x 98.7 | |
| 0521 | T+16:37 PS4 burnout | ||
| 0521 | T+16:57 PS4 sep | ||
| 1994 Oct 17 | 101.74 798 x 883 x 98.7 | ||
| 2000 Sep | end of ops | ||
1978-093A
Navstar 3 was the third GPS development satellite.
| Navstar 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Oct 7 | 0030? | Launch by Atlas F/SVS | V SLC3 |
| T+2:04 Booster sep | |||
| T+5:21 SECO | |||
| 0036? | T+6:00? Atlas sep | -2622 x 172 (nominal) | |
| 0036? | T+6:21? SVS burn 1 42s? | ||
| 0037? | T+7:03? burnout | 36? x 172? x 63.1 | |
| T+7:04? sep | |||
| T+7:05? SVS burn 2 | 163? x 20144? | ||
| 0037 | T+7:47? burnout | ||
| 0041? | SVS-2 sep | ||
| 1978 Oct 8 | 1530? | Star 27 burn | |
| 1978 Oct 12 | Nav system on | ||
| 1978 Oct 17 | 722.1 20283 x 20309 x 62.8 | ||
| 1978 Nov 8 | 718.06 20181 x 20186 x 62.8 | ||
| 1978 Nov 13 | Operational | ||
| 1990 | Operating at A-3 on Rb clock | ||
| 1992 Apr 19 | end of nav use | ||
| 1992 Nov 16 | end of ops | ||
1990-100B
GTE Satellite Corp.'s final Gstar was launched in 1990 aboard the same Ariane as Satcom C-1. The spacecraft was another GE Astro Space series 3000, and provided VSAT (very small aperture terminal) communications relay services.
| GStar 4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Nov 20 | 2311 | Launch by Ariane 42P (V40) | CSG |
| T+1:28 PAL sep | |||
| T+3:20 St 1 sep | |||
| T+3:22 St 2 MES | |||
| T+4:29 Fairing | |||
| T+5:33 St 2 sep | |||
| T+5:37 St 3 MES | |||
| 2328 | T+17:41 St 3 MECO | ||
| 2330 | T+19:16 Satcom C1 sep | ||
| 2332 | T+21:27 Sylda sep | ||
| 2334 | T+23:03 Gstar 4 sep | ||
| 1990 Nov 21 | 0500? | Apo 1 | 629.13 216 x 35670 x 7.0 ? |
| 1000? | Peri 1 | ||
| 1500? | Apo 2 | ||
| 2030? | Peri 2 | ||
| 1990 Nov 22 | 0230? | Apo 3 125E | |
| 0700? | Peri 3 | ||
| 1300? | Apo 4 30W | ||
| 1800? | Peri 4 | ||
| 2300? | Apo 5 170E | ||
| 1990 Nov 23 | 0430? | Peri 5 | |
| 1000? | Apo 6 10E | ||
| 1500? | Peri 6 | ||
| 2000? | Apo 7 140W | ||
| 1990 Nov 23 | 1937? | Star 30C burn | |
| 1990 Nov 24 | 1421.20 35268 x 35720 x 0.1 GEO 136.3W+3.8E | ||
| 1990 Nov 24 | 0800? | Braking | 1424.29 35338 x 35771 x 0.1 GEO 136.3W+3.0E/d |
| 1990 Dec 1 | mv in | 1436.24 35784 x 35794 x 0.0 GEO 125.1W | |
| 1991 Mar 4 | 1436.07 35781 x 35790 x 0.0 GEO 125.1W | ||
| 1992 Aug 28 | 1436.06 35776 x 35795 x 0.0 GEO 125.0W | ||
| 1992 Aug 30 | mv out | ||
| 1992 Oct 11 | 1436.23 35780 x 35797 x 0.1 GEO 104.9W | ||
| 1992 Dec 29 | 1436.10 35785 x 35788 x 0.0 GEO 105.0W | ||
| 1994 Mar 20 | 1436.09 35784 x 35789 x 0.0 GEO 105.0W | ||
| 1995 Jan 21 | 1436.09 35785 x 35787 x 0.0 GEO 105.0W | ||
| 1997 Apr 24 | 1436.09 35779 x 35794 x 0.1 GEO 105.0W | ||
| 1999 Jun 15 | 1436.09 35770 x 35802 x 0.0 GEO 105.0W | ||
| 2003 Sep 5 | 1436.10 35779 x 35793 x 1.0 GEO 105.0W | ||
1976-059A
The first Phase II satellite, spaceraft DSP 6, was launched on 1976 Jun 26 by Titan IIIC from Cape Canaveral. It was stationed over the Atlantic until 1982, when it was moved to the Indian Ocean.
| DSP 6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1976 Jun 26 | 0300:01 | Launch by Titan IIIC | CC |
| 0302? | SRM sep | ||
| 0304? | Stage 1 sep | ||
| 0305? | Fairing | ||
| 0307? | Stage 2 MECO | ||
| 0308? | Stage 2 sep | ||
| 0400? | Transtage MES-1 | ||
| 0930? | MES-2 | ||
| 0930? | MECO-2 | ||
| 1000? | Transtage sep | ||
| 1976 Jun 27? | Cover sep | ||
| 1976 Jul 1 | GEO 35W | ||
| 1977 Jan | GEO 35W | ||
| 1977 Feb | GEO 65W | ||
| 1979 Nov late | mv | ||
| 1979 Dec | GEO 35W | ||
| 1980 Mar 10? | mv out | GEO 35W | |
| 1980 Mar 28? | GEO 65W | ||
| 1980 Aug 20 | GEO 65W | ||
| 1981 Apr 20 | mv out | GEO 65W | |
| 1981 Jun | GEO 129W | ||
| 1981 Aug | GEO 135W | ||
| 1981 Sep 1 | GEO 115W drift? | ||
| 1982 Mar 26 | GEO 129W | ||
| 1982 Apr | GEO 140W | ||
| 1982 Jun | GEO 140W | ||
| 1982 Jul | mv out | ||
| 1982 Dec 2 | mv in DSP East-Reserve | GEO 75E | |
| 1983 Jun 20 | GEO 75E | ||
| 1984 Jul | GEO 75E | ||
| 1985 Feb | end of ops | ||
