Friday, June 21, 1996
Thursday, June 20, 1996
Kosmos 2209
1992-059A
This mission saw the third use of the 5th orbit northbound equator crossing burn.
| Kosmos-2209 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Sep 10 | 1801:18 | Launch by Proton | KB |
| 1810 | Stage 3 sep | ||
| 1992 Sep 10 | 1918 | First NEC | |
| 1992 Sep 10 | 2045 | NEC 2 | |
| 1992 Sep 10 | 2215 | NEC 3 | |
| 1992 Sep 10 | 2344 | NEC 4 | |
| 1992 Sep 11 | 0111? | NEC 5 | |
| 1992 Sep 11 | 0111? | DM burn 1 | |
| 0728? | DM burn 2 over 14W | ||
| 0730? | DM sep | ||
| 1992 Sep 11 | 1446.03 35902 x 36058 x 1.4 GEO 15.2W+2.5W | ||
| 1992 Sep 18 | 1435.98 35763 x 35806 x 1.3 GEO 23.8W+0.02E | ||
| 1992 Sep 30 | 1436.02 35764 x 35806 x 1.3 GEO 23.5W | ||
| 1992 Oct 19 | 1436.12 35766 x 35808 x 1.3 GEO 23.5W | ||
| 1993 Nov 24 | 1436.18 35786 x 35789 x 0.4 GEO 24.1W | ||
| 1995 Mar 30 | 1436.09 35764 x 35808 x 0.7 GEO 23.3W | ||
| 1995 Sep 1 | 1436.10 35773 x 35800 x 1.0 GEO 24.3W | ||
Wednesday, June 19, 1996
Progress M-29
1995-053A
Launch mass of Progress 229 was 7122 kg. It was undocked from the Kvant module on Dec 19 and deorbited over the Pacific; mass prior to deorbit was 5694 kg.
| Progress M-29 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 Oct 8 | 1850:40 | Launch by Soyuz-U | KB LC1 |
| 194 x 242 x 51.7 | |||
| 2232 | TCM-1 | ||
| 2350 | TCM-2 | ||
| 1995 Oct 10 | 2032:40 | Docked with Kvant-1 +X | |
| 1995 Dec 19 | 0915:05 | Undocked | 92.47 391 x 400 x 51.6 |
| 1526:00 | Deorbited over Pacific, 217s | ||
| 1615 | Reentered over 48 34 S 174 18 E | ||
Tuesday, June 18, 1996
Monday, June 17, 1996
Corona 87
1964-067A
KH-4A Mission 1012 was launched on 1964 Oct 17 into a 75 degree inclination orbit. Mass was 1667 kg. The first SRV was recovered in mid-air over the Pacific on Oct 20. The second part of the mission, 1012-2, was cut short when attitude control became erratic, but bad weather on Oct 23 prevented a second mid-air recovery, and SRV-2 landed in the Pacific ocean, being successfully retrieved later albeit with minimal film content. Targets included Cuba and Algeria.
| KH-4A Mission 1012 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1964 Oct 17 | 2202:23 | Launch by Thor Agena D | V PALC1-1 |
| 2203:28 | Castor sep (T+1:05) | ||
| 2204:52 | Thor MECO (T+2:29) | ||
| 2205:00 | Thor VECO (T+2:37) | ||
| 2205:08 | Thor sep (T+2:45) | ||
| 2205:13 | Agena burn (T+2:50) | ||
| 2209:10 | Agena MECO (T+6:47) | 90.62 185 x 436 x 74.99 (VCR) | |
| 1964 Oct 18 | 1707 | 90.55 177 x 426 x 75.0 | |
| 1964 Oct 19 | 0230 | 90.59 189 x 416 x 74.99 (RAE) | |
| 1964 Oct 20 | 2356? | SRV-1 ejected rev 49 | |
| 1964 Oct 21 | 0030? | SRV-1 recovered in mid-air | |
| Reactivated | |||
| 1964 Oct 23 | 0015? | SRV-2 ejected rev 81 | |
| 1964 Oct 23 | 0050? | SRV-2 splashdown | |
| SRV-2 recovered from sea | |||
| 1964 Oct 25 | 0555 | 90.15 171 x 392 x 75.0 | |
| 1964 Oct 31 | 2024 | 89.07 168 x 289 x 75.0 | |
| 1964 Oct 31 | 89.9 176 x 309 x 75.0 (SSR) | ||
| 1964 Nov 4 | 0435? | Reenteered | |
Friday, June 14, 1996
Kosmos 2120
1990-115A
The Kosmos-2120 mission had an extended 23-day duration and flew in three phases with progressively lower apogees.
| Kosmos-2120 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Dec 26 | 1110:00 | Launch by Soyuz | PL |
| 1114 | Blok-I burn | ||
| 1118 | Blok-I sep | ||
| 1990 Dec 26 | 88.54 178 x 225 x 82.6 | ||
| 1990 Dec 27 | 90.34 236 x 346 x 82.6 | ||
| 1991 Jan 8 | 90.19 233 x 333 x 82.6 | ||
| 1991 Jan 11 | 89.79 236 x 291 x 82.6 | ||
| 1991 Jan 15 | 89.77 235 x 290 x 82.6 | ||
| 1991 Jan 16 | 89.30 228 x 250 x 82.6 | ||
| 1991 Jan 17 | 89.25 227 x 248 x 82.6 | ||
| 1991 Jan 19 | Landed after 23d | ||
| 0641? | Deorbit | ||
| 0652? | PO sep | ||
| 0700? | Entry | -201 x 245 | |
| 0716? | Landed | ||
Monday, June 10, 1996
Cluster 1A
1996-F03
The four Cluster satellites, part of ESA's Cornerstone 1 (CS1) project, were lost in the launch failure of the first Ariane 5.
Cluster F1 was paired with Cluster F2 above the Speltra structure on Ariane 501. The Dornier built satellite had a mass of 1200 kg at launch. 650 kg of this is N2O2/MMH fuel. DDS (Dornier Satellitensysteme) is a unit of Daimler-Benz Aerospace (DASA). The propulsion system was built by Matra Marconi Space/Bristol (formerly British Aerospace) using a DASA 400N/8 x10N thruster system.
The plan was for the Ariane 5 EPS to leave the four spacecraft in a 280 x 36000 km x 10 deg orbit. Cluster F1 and F2 separate from Speltra and then from each other. Five burns with the 400N engine on each satellite leaves them in a 25000 x 140000 km polar orbit. The four spacecraft are maintained in a tetrahedral cluster with 200 to 18000 km separations. The satellite has four 50-m booms with 100m span, and is 2.9m diameter and 1.3m tall. There are also two 5-m booms with magnetometers. Science goals include study of the bow shock, the polar cusp, and the magnetotail. The mission is commanded from ESOC with a science center at RAL.
The Ariane 5 took off from ELA3 at Kourou, but half a minute into the flight, travelling at an altitude of 3500 m, the on-board computer incorrectly read the vehicle's attitude and ordered the vehicle to turn sharply, causing structural failure. The vehicle automatically self destructed when the solid boosters and core stage broke apart.
| Cluster F1/Ariane 501 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Jun 4 | 1233:59 | EPC Vulcain ignition (H0) | |
| 1234:06 | EAP ignition | ||
| 1234:06 | Launch by Ariane 5 (501) | CSG ELA3 | |
| 1234:36 | Altitude 3.5 km | ||
| 1234:36 | EAP nozzles hard over | ||
| 1234:37? | Vulcain nozzle hard over | ||
| 1234:37 | L0+31.3s: EPS N2O4 tank rupture? | ||
| 1234:38.5 | L0+32.5s: 90 deg angle of attack | ||
| 1234:38 | L0+32.8s? EPC structural breakup | ||
| 1234:39 | Vehicle destroyed | ||
Payload:
- ASPOC Active SC Potential Control
- CIS Cluster Ion Spectrometry
- DWP Digital Wave Processor
- EFW Electric Fields and Waves
- EDI Electron Drift Instrument
- FGM Fluxgate Magnetometer
- PEACE Plasma Electron and Current Analyser
- RAPID Research with Adaptive Particle Imaging Detectors