1976-071A
The third test in the 1976 series used Kosmos-839 as a target. The US orbital tracking would suggest a failed intercept attempt but I suspect the object tracked is actually the rocket stage, at least for the later epochs.
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1976 Jul 21 | 1514 | Launch by 11K69 | KB |
| 1516 | Stage 2 burn | ||
| 1519 | Stage 2 MECO | ||
| 1976 Jul 21 | 89.3 132x346x65.1 | ||
| 1976 Jul 21 | 1650? | Maneuver | -700? x 1500? x 65? |
| 1976 Jul 21 | 1730? | Intercept | |
| 1976 Jul 21 | 1800? | reentered | |
2000-063A
Glonass triplet block 29, launched with Kosmos-2375 and Kosmos-2376.
| Kosmos-2374 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Oct 13 | 1412:45 | Launch by Proton 393-01 | KB LC81R |
| 1422 | Stage 3 sep | ||
| 1423 | Upper adapter sep | ||
| DM2 burn 1 | |||
| 1800? | DM2 burn 2 | ||
| 1810? | DM2 dispense | ||
| 2001 Jan 5 | In service | ||
1998-047A
The EO-26 crew of Gennadiy Padalka (callsign Al'tair) and Sergey Avdeev were launched on Soyuz TM-28 (11F732 No 77) in Aug 1998. Former national security adviser Yuriy Baturin also was on the crew as cosmonaut-researcher. Baturin, once a test pilot, was chairman of the Defense Council until Aug 1997.
Launch mass of Soyuz was 7000 kg. It used a GPS system for the first time.
Flight 2 was a docking port switch in Feb 1999, with Padalka and Avdeev aboard.
Flight 3 was return to Earth, with Padalka and Bella. The Phantom dosimeter carried up on Progress M-34 was probably returned on this flight.
| Soyuz TM-28 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Aug 13 | 0943:11 | Launch by Soyuz-U | |
| 0947 | Blok A MECO | ||
| 0951:56 | Blok I MECO | ||
| 0952:00 | Blok-I sep | ||
| 1323:52 | TCM-1 33s | ||
| 1416:12 | TCM-2 16s | 220 x 273 | |
| 1998 Aug 14 | 1033:02 | TCM-3 3s | |
| 1998 Aug 15 | 0852:29 | TCM-4 71s | |
| 0935:47 | TCM-5 76s | ||
| 1998 Aug 15 | Auto approach | ||
| 1055 | To manual docking mode at 12m | ||
| 1998 Aug 15 | 1056:54 | Docked with Kvant | |
| 1229 | Hatch open | ||
| 1998 Aug 27 | 0130? | Hatch closed | |
| 1998 Aug 27 | 0547 | Undocked Kvant +X | |
| Flyaround | |||
| 0600 | Stationkeeping with -X | ||
| 0607:11 | Docked PKhO -X | ||
| 0740? | Hatch open | ||
| 1999 Feb 8 | 1123:03 | Undocked PKhO -X | |
| 1139:07 | Docked Kvant +X | ||
| 1999 Feb 27 | 1954 | HC | |
| 2255:11 | Undocked | ||
| 2259:20 | DPO 8s sep burn | ||
| 1999 Feb 28 | 0122:19 | Deorbit SKD 4:16, 115m/s | 346 x 362 x 51.6 |
| 0126:35 | DO CO | -38? x 359 x 51.7 | |
| 0146? | Modules sep | ||
| 0150? | Entry interface | ||
| 0152? | Entry | ||
| 0214:30 | Landed | ||
1978-113A
Satellite 9441 (DSCS II C-11) was launched on 1978 Dec 14 by Titan 3C from Cape Canaveral. It was checked out on orbit by SAMSO and delivered to the Defense Communications Agency on 1979 Jan 15.
| DSCS II C-11 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Dec 14 | 0040:02 | Launch by Titan IIIC | CC LC40 |
| T+1:49 Stage 1 ignition | |||
| T+2:02 SRM sep | |||
| T+4:18 Stage 1 MECO, sep | |||
| 0045 | T+5:00? Fairing | ||
| 0047 | T+7:40? SECO | ||
| 0048? | Stage 2 sep (T+8:00) | 150 x 260 x 28.5 | |
| 0150? | Transtage burn 1 | ||
| 0650? | Transtage burn 2 | ||
| 0700 | 1452 min. | ||
| 0704 | Sep from Transtage | ||
| 1978 Dec 14 | 1452.36 35796 x 36412 x 2.5 GEO 92.8W+4.0W | ||
| 1979 Jan 15 | To DCA from SAMSO | ||
| 1979 Feb 13 | 1435.98 35776 x 35792 x 2.3 GEO 134.7W | ||
| 1980 Jan 12 | 1436.04 35782 x 35788 x 1.6 GEO 135.3W | ||
| 1982 Jan 4 | 1436.09 35777 x 35795 x 0.5 GEO 135.3W | ||
| 1983 May 1 | mv out | 1435.87 35765 x 35798 x 1.4 GEO 134.2W+0.04E | |
| 1983 May 15 | mv in | 1436.11 35768 x 35804 x 1.4 GEO 130.1W | |
| 1983 Jun 26 | 1435.93 35763 x 35802 x 1.5 GEO 129.2W | ||
| 1985 Jan 1 | 1435.88 35777 x 35787 x 2.8 GEO 129.4W | ||
| 1986 Jan 1 | 1435.93 35773 x 35793 x 3.7 GEO 129.7W | ||
| 1989 Jan 2 | 1436.17 35784 x 35791 x 5.5 GEO 130.0W | ||
| 1989 Apr 29 | 1435.6 35771 x 35784 x 5.9 | ||
| 1989 May 3 | 1435.6 35770 x 35785 x 5.9 | ||
| 1989 Sep 11 | 1436.64 35786 x 35808 x 6.2 GEO 131.9W+0.15W | ||
| 1989 Sep 14 | orbit adjust | 1435.92 35751 x 35815 x 6.2 GEO 132.2W+0.04E | |
| 1989 Sep | Begin drift | ||
| 1989 Oct 13 | 1435.74 35745 x 35812 x 6.3 GEO 130.0W+0.09E | ||
| 1990 Jan 21 | 1435.39 35744 x 35801 x 6.5 GEO 116.2W+0.16E | ||
| 1991 Jun 4 | 1436.81 35780 x 35820 x 7.8 GEO 95.9W+0.2W | ||
| 1993 Apr 28 | 1435.80 35760 x 35801 x 9.3 GEO 78.7W+0.1E | ||
| 1993 May 31 | Orbit raise | 1454.04 36132 x 36141 x 9.4 | |
| 1993 Jun 28 | Orbit raise | 1462.24 36288 x 36302 x 9.4 | |
| 1993 Nov 10 | Orbit raise | 1524.04 37485 x 37496 x 9.7 | |
| 1993 Dec 13 | Orbit raise | 1531.16 37506 x 37748 x 9.8 | |
| 1993 Dec 16 | Decommissioned | ||
2001-041A
Progress M-SO1 is a modified vehicle, serial 301 (essentially the Progress service module) used to deliver the 240GK Pirs module to the ISS.
| M-SO1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Sep 14 | 2334:55 | Launch by Soyuz-U No 677 | |
| T+1:58 Blok BVGD sep | |||
| T+2:37 GO sep | |||
| T+4:47 St 2 sep | |||
| T+5:01 KhO sep | |||
| T+8:45 Blok I MECO | |||
| 2343:44 | T+8:49 Blok-I sep | 88.0? 170 x 180 x 51.6 | |
| 2001 Sep 15 | 0320:57 | DV1A 47s 18.4m/s | |
| 0358:02 | DV1B 9.6m/s 25s | ||
| 2001 Sep 16 | 0029:47 | DV2 6.3s 2.0m/s | |
| 1153 | 89.55 239 x 265 x 51.6 | ||
| 2001 Sep 16 | 2230 | Begin auto docking sequence | |
| 2255 | DV3A Burn 26m/s | ||
| 2301 | 89.53 238 x 264 x 51.6 | ||
| 2318 | DV3B Burn 1m/s | ||
| 2341 | MC1 Burn 43 m/s | ||
| 2001 Sep 17 | 0026 | MC2 Burn 7m/s | |
| 0032 | MC3 Burn 5m/s | ||
| 0034 | MC4 Burn 1.5m/s | ||
| 0038 | At 200m, begin flyaround | ||
| 0045 | At 165m, stationkeep below Zvezda | ||
| 0105:14 | Docked with Zvezda nadir | ||
| 92.36 385 x 395 x 51.6 | |||
| HO to ISS | |||
| 2001 Sep 26 | 1536 | Progress undocks | |
| 1545 | Progress sep burn | ||
| 1600 | Progress at range 24 km | ||
| 2330 | Progress deorbit 609.8s 102.3m/s | ||
| 2001 Sep 27 | 0009 | Reentry over Pacific | |
1964-U02
The Project FIRE High Velocity Reentry Package studied a blunt body reentry at 11.3 km/s and 15 degree angle. Total launch mass was 2000 kg including the velocity package shell and control system, 1400 kg without but including the Antares IIA5 with 1179 kg of propellant. Fairing is a modified DAC Nimbus fairing. Velocity package contractor was LTV. Reentry package was Republic Aviation Corp. Planned apogee was 837 km.
FIRE 1 reached 11.5736 km/s (or 11.52 km/s, TN-D-2996) at 16.6W 7.8S, 122 km on descent from 840 km, at an angle of -14.608 deg and azimuth 122.5 deg. Range was 8370 km. Possible initial trajectory -2900 x 840 x 30.0. Post burn trajectory -219 x Inf x 32 deg.
| FIRE 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1964 Apr 14 | 2142:25 | Launch by Atlas 263D | CKAFS LC12 |
| 2144:38 | T+2:13 BECO, 24.4 deg ascent | ||
| 2144:39? | Booster sep | ||
| 2147:13 | T+4:48 SECO | ||
| 2147:20 | VP fairing jettison | ||
| 2147:31 | T+5:09 VECO, 8.0 deg ascent | ||
| 2147:25 | 6.28km/s rel, 15.0 deg 299 km | -2920 x 840 x 31.1 | |
| 2147:36 | Spacecraft sep from Atlas | ||
| 2147:45 | Fire 1 orientation | ||
| 2149:26 | Coast phase | ||
| 2158:05 | Apogee 840 km | ||
| 2208:39 | Spinup | ||
| 2208:42 | Velocity package shell sep | ||
| 299.43 km -15.32 deg 6.3395 km/s rel | -2820 x 841 x 30.8? | ||
| 2208:45 | Antares burn dV = 5.2km/s | ||
| 2209:17 | Antares burnout | ||
| 2209:43 | Simulation fidiucial time 149.5 km -15 deg 11.55 km/s | ||
| 2209:45 | Reentry package sep | -219 x -51626 x 32.1 | |
| 2209:52 | Reentry 122 km 11.5736 km/s -14.608 deg 16.7W 7.8S | ||
| 2209:57 | Yaw disturbance; Antares bow shock hits Fire | ||
| 2210:14 | Heat shield 1 sep | ||
| 2210:21 | Heat shield 2 sep | ||
| 2210:31 | End of blackout | ||
| 2215:10 | Impact 10.227S 12.643W | ||
1991-050A
The European Space Agency's ERS-1 Earth Resources Satellite was launched on 1991 Jul 17 into a sun-synchronous orbit. Built by Dornier but based on Matra's SPOT Mk 1 bus, ERS 1 carried a 10-m x 1m SAR antenna used by the 5.3GHz Active Microwave Instrument, as well as altimeters and laser reflectors.
The orbit adjust engine restores the orbit when it drifts by 1 km, in a two-burn maneuver half an orbit apart. The burns are needed every 2 weeks at solar maximum, once a month otherwise, with inclination maneuvers every 9 to 10 months.
| ERS 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Jul 17 | 0146:31 | Launch by Ariane | |
| T+2:37 St 1 sep | |||
| T+2:40 St 2 MES | |||
| T+3:20 Fairing 02 sep | |||
| T+4:46 St 2 sep | |||
| T+4:51 St 3 MES | |||
| 0203:16 | T+16:45 St 3 MECO | ||
| 0204:14 | T+17:43 ERS-1 sep | ||
| 0205:54 | T+19:23 ASAP payloads sep | ||
| 100.44 776 x 782 x 98.52 | |||
| 1991 Jul 20 | TCM | ||
| 1991 Jul 26 | TCM to `Venice orbit' | ||
| 1996 Aug | end of regular ops | ||
| 1997 Jun 22 | 100.54 783 x 785 x 98.5 | ||
| 1997 Jun 25 | TCM COLA 1 m/s to avoid K-614 | 100.58 784 x 788 x 98.6 | |
| 1997 Jun 26 | 100.54 783 x 785 x 98.5 | ||
| 2000 Mar 10 | end of ops | ||
1967-094A
The Pacific 2 (Intelsat II F-4) satellite was launched at the end of 1967, completing an operational constellation. It was stationed as the POR backup satellite over the international date line in Oct 1967, and remained between 167W and 180W until Jan 1971 when it was retired and began to drift.
| Intelsat II F-4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1967 Sep 28 | 0045:00 | Launch by Delta E1 | CK LC17B |
| 0046:25 | SRM sep | ||
| 0047:29 | T+2:29 Thor S/N 20201 MECO | ||
| 0047:32 | St 1 sep | ||
| 0047:35? | Delta S/N 20215 burn 6:18 | ||
| 0053:53? | Delta SECO | ||
| 0108? | St 2 sep | ||
| 0108? | FW-4D S/N 41104 burn 31.3s | ||
| 0108? | FW-4D burnout | 307 x 37471 x 26.7 | |
| 0109? | FW-4D sep | 308 x 35408 x 26.4 | |
| 1967 Sep 29 | Adjust orbit | 656.4 333 x 36951 x 26.4 | |
| 1967 Sep 30 | 2345 | SVM-1 S/N 33 burn | |
| 1967 Oct 9 | 1438.31 35747 x 35912 x 0.9 GEO 180.0W+0.5E | ||
| 1967 Oct | POR backup | GEO 176E | |
| 1969 Jan 13 | 1436.07 35761 x 35811 x 0.3 GEO 178.0W+0.0E | ||
| 1970 Jan 26 | 1435.43 35764 x 35782 x 1.2 GEO 165.7W+0.16W | ||
| 1970 Apr 13 | 1436.32 35773 x 35808 x 1.5 GEO 171.4W+0.06E | ||
| 1970 Jul | POR backup | ||
| 1970 Oct 26 | 1436.09 35751 x 35821 x 2.0 GEO 170.8W+0.0E | ||
| 1971 Jan 4 | 1435.67 35751 x 35804 x 2.2 GEO 166.5W+0.1W | ||
| 1971? | Retired | ||
| 1972 Apr | GEO 42W | ||
| 1972 Jul 31 | Mv in | GEO 31.5W+0.0E | |
| 1973 Jun | GEO 91.4W+0.4 4.4 | ||
| 1973 Oct | GEO 130.1W+0.3 | ||
| 1974 Jun 28 | GEO 170.2W+0.0W | ||
| 1975 Sep | GEO 49.6W+0.2 6.21 | ||
| 1977 May | |||
| 1996 Apr 19 | 1436.14 35712 x 35862 x 14.8 GEO 172.0W+0.02E | ||
| 1997 Dec 16 | 1435.78 35719 x 35841 x 14.7 GEO 34.2W+0.07W | ||
