Friday, February 10, 1995
Foton 8
1992-065A
The spacecraft had a mass of 6057 kg.
| Foton No. 8 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Oct 8 | 1900:00 | Launch by Soyuz | PL LC43/4 |
| 1904 | Blok-I burn | ||
| 1908 | Blok-I sep | ||
| 1992 Oct 9 | 90.31 219 x 360 x 62.8 | ||
| 1992 Oct 24 | 90.04 214 x 338 x 62.8 | ||
| 1992 Oct 24 | 0852? | Deorbit | |
| 0902? | PO sep | ||
| 0911? | Entry | ||
| 1992 Oct 24 | 0925:30 | Landed in Kazakhstan 52 42N 61 17E | |
Payload:
- DLR experiments: Hermes reentry tiles
- ESA Biopan external
Thursday, February 9, 1995
Kosmos 131
1966-105A
Zenit-4 No. 28 was launched from Plesetsk and flew an 8 day mission at 72.9 degrees.
| Kosmos-131 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Nov 12 | 0950 | Launch by 11A57 | PL |
| 0954 | Blok-I burn | ||
| 0959 | Blok-I sep | 89.9 204 x 337 x 72.9 | |
| 1966 Nov 14 | 0300 | 89.89 202 x 335 x 72.9 | |
| 1966 Nov 16 | 0632 | 89.85 201 x 332 x 72.9 | |
| 1966 Nov 20 | 0452? | Retrofire | |
| 0512? | Landed | ||
Wednesday, February 8, 1995
Gambit-3 1
1966-069A
The first KH-8 satellite, Mission 4301, was launched on 1966 Jul 29. It was the 31st flight in the GAMBIT program. The week long test flight was in a low 158 x 250 km orbit, at an inclination of 94 degrees. The launch saw the introduction of the three-stage Titan IIIB Agena D launch vehicle. A single pad at Vandenberg, Space Launch Complex 4-West, was dedicated to the Titan IIIB missions. The pad was previously known as PALC2-3 and had been used for KH-7 GAMBIT launches.
The SRV was similar to those flown on CORONA missions.
A Lockheed report described the first Program 206-II mission with SLV-5B (i.e. Titan 3B) 66-8131, satellite control section 58205/4751, and a forward satellite vehicle section (FSVS) with a recovery capsule. The PPS was flight model FM-1. Insertion was accomplished with a 2.7 m/s underspeed. The SRV was recovered in mid-air on orbit 83. Following this, the spacecraft was tested for three days with three yaw manuevers and three SPS burns. The engine was then used to deorbit the vehicle.
| KH-8 Mission 4301 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Jul 29 | 1830:19 | Launch by Titan IIIB Agena D | V SLC4W |
| 1832 | T+2:46? Stage 1 sep | ||
| T+2:46 Stage 2 ignition | |||
| 1836 | T+6:50? Stage 2 sep | ||
| 1836 | T+6:52 Agena MES | ||
| 1840 | T+10:35 Agena MECO | 88.6 158 x 250 x 94.1 | |
| 1966 Jul 29 | 2354 | 88.66 150 x 266 x 94.1 | |
| 1966 Jul 31 | 2312 | 88.53 157 x 246 x 94.1 | |
| 1966 Aug 3 | 2104? | SRV recovered rev 83 | |
| 2109? | Entry | ||
| 2130? | Recovered | ||
| 1966 Aug 3 | 0421 | 88.42 145 x 247 x 94.1 | |
| 1966 Aug 3 | 1440 | 88.32 149 x 233 x 94.1 | |
| 1966 Aug 4 | 0530? | TCM rev 89 | |
| 1966 Aug 4 | 1700? | TCM rev 97 | |
| 1966 Aug 5 | 2120 | 88.76 151 x 274 x 94.1 | |
| 1966 Aug 6 | 0600? | TCM rev 122 | |
| 1966 Aug 7 | Reentered | ||
CTS-1
1976-004A
The Communications Research Centre of the Canadian Dept. of Communications developed and operated the CTS communications technology satellite, renamed Hermes after launch in Jan 1976. ESA also participated in the program.
During transfer and early orbit ops, the spacecraft was spin-stabilized and got power from arrays mounted on the two JBSAs (Jettisonable Body Solar Arrays) mounted as covers on the main solar arrays. The JBSAs were ejected to begin solar array deployment. They were 4 kg each and around 1.8m x 0.5m x 0.1m (guess). AKM was postponed from the 5th to the 7th apogee while the thrusters were debugged. 10 kg of hydrazine was used in reaching station at 116W. It was used for tele-education, medecine,conferencing, community development in remote regions, and broadcasting. CTS was stationed at 116W until 1979, when it moved to 142W for joint experiments with the Australian Postal and Telecoms Dept.
| CTS 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1976 Jan 17 | 2327:54 | Launch by Delta 2914 | CC LC17B |
| T+38s SRM 1-6 burnout | |||
| T+77s SRM 7-9 burnout | |||
| T+85s SRM 1-9 sep | |||
| T+226s MECO | |||
| T+234s St 1 sep | |||
| T+238s St 2 burn | |||
| T+276s Fairing | |||
| 2337:50 | T+556s SECO-1 | 185 x 185 x 28.3 | |
| 2352:40 | T+1486s SES-2 | ||
| 2352:48 | T+1494s SECO-2 | 177 x 547 x 28.7 | |
| 2353:19 | T+1525s St 2 sep | ||
| 2353:32 | T+1538s St 3 burn | ||
| 2354:16 | T+1582s St 3 burnout | 182 x 36220 x 27.2 | |
| 2355:56 | T+1682s St 3 sep | ||
| 1976 Jan 18 | 1551 | 627.47 164 x 35635 x 27.2 | |
| 1976 Jan 20 | 0019 | 205 x 36022 x 27.29 | |
| 1976 Jan 20 | 2041 | Star 27 AKM burn 143W, 11.4E/d | 33711 x 36016 x 0.71 |
| 1976 Jan 21 | 2024 | TCM-1 to 9.4E/d at 131W | |
| 1976 Jan 22 | 1943 | TCM-2 to 2.2E/d | 35198 x 36027 x 0.68 |
| 1976 Jan 26 | 1853 | TCM-3 to 1.5W/d | |
| 1976 Jan 28 | 0656 | TCM-4 to 0.3W/d | |
| 1976 Jan 29 | 0705 | TCM-5, at 116W | 35781 x 35797 x 0.66 |
| 1976 Jan 30 | Despin | ||
| 1976 Feb 1? | JBSA jettison | ||
| 1976 Feb 1? | Solar arrays extended | ||
| 1976 Feb 1 | Declared operational | ||
| 1976 Feb 4 | SKM 0.04m/s | ||
| 1976 Feb 7 | SKM | ||
| 1976 Mar 12 | SKM | ||
| 1976 Apr 2 | SKM | ||
| 1976 May 17 | SKM | ||
| 1976 May 21 | In service, named Hermes | ||
| 1976 Jun 25 | SKM | ||
| 1976 Jul 29 | SKM | ||
| 1976 Aug 26 | SKM | ||
| 1977 Jan 20 | 1436.08 35759 x 35813 x 0.1 GEO 116.2W | ||
| 1979 Jan | TV broadcasts to remote communities | ||
| 1979 Jun | Hermes program complete | ||
| 1979 Jul 25 | 1436.14 35753 x 35821 x 1.3 GEO 116.8W | ||
| 1979 Jul | Move to 142W | ||
| 1979 Aug 20 | 1436.19 35747 x 35829 x 1.3 GEO 142.0W+0.03W | ||
| 1979 Sep 2 | GEO 142W | ||
Kosmos 2164
1991-072A
Kosmos-2164 was the fourth mission to an intermediate elliptical 74 degree orbit.
| Kosmos-2164 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Oct 10 | 1400:01 | Launch by Kosmos-3M | PL |
| 1420? | Stage 2 sep | ||
| 94.55 285 x 707 x 74.0 | |||
| 1992 Dec 12 | Reentered | ||
Tuesday, February 7, 1995
Proton 3
1966-060A
The last N-4 satellite, Proton-3, was launched on 1966 Jul 6 by UR-500 from Baikonur. The two stage rocket reached orbit successfully.
| Proton-3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Jul 6 | 1246 | Launch by UR-500 | KB |
| 1248 | T+2:04? Stage 1 sep | ||
| 1250 | T+4:44? Stage 2 MECO | ||
| 1251? | Fairing sep | ||
| 1966 Jul 7 | 92.46 181 x 608 x 63.5 | ||
| 1966 Jul 28 | 92.15 184 x 575 x 63.5 | ||
| 1966 Aug | Still operating | ||
| 1966 Aug 19 | 90.87 170 x 463 x 63.5 | ||
| 1966 Sep 25 | Reentered | ||
Gambit 29
1966-048A
KH-7 29 was launched on 1966 Jun 3 by Atlas Agena D from Vandenberg. The 87 degree inclination orbit was the only case of a GAMBIT flying in a direct rather than retrograde plane.
| KH-7 29 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Jun 3 | 1925 | Launch by Atlas Agena D | V |
| T+2:18? BECO | |||
| T+4:37? SECO | |||
| T+4:54? VECO | |||
| T+4:59? Atlas sep | |||
| T+5:51? Agena MES | |||
| 1934 | T+9:50? Agena MECO | ||
| 1966 Jun 4 | 88.9 143 x 288 x 87.0 | ||
| 1966 Jun 9 | 1700? | Rev 96 last image | |
| 1966 Jun 9 | 2200? | SRV recovered | |
| 1966 Jun 10 | 0340? | Reentered | |
Sunday, February 5, 1995
Molniya 179
1990-101A
Molniya-1 (F85, N79) was launched in Nov 1990 into the E plane.
| Molniya-1 F85 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Nov 23 | 0351 | Launch by 8K78M | PL |
| BVGD sep | |||
| GO sep | |||
| T+4:46 Blok A sep | |||
| T+4:56 KhO sep | |||
| T+8:46 Blok-I MECO | |||
| 0359 | T+8:50 Blok-I sep | ||
| T+53:16 BOZ burn | |||
| 0444 | T+53:56 BOZ sep | ||
| ML burn | |||
| T+56:46 ML MECO | |||
| 0447 | T+56:54 ML sep | ||
| 735.05 603 x 40599 x 62.8 | |||
| 1990 Nov 27 | 0700 | 735.31 608 x 40607 x 62.82 | |
| 1990 Nov 28 | 1900 | 717.51 607 x 39734 x 62.82 | |
Meteor 302
1985-100A
Meteor-3 No. 2 was launched in Oct 1985 and entered a 1227 x 1250 km orbit. The 1750 kg satellite was 6.5m long and 2.4m diameter. Over the first two months of the mission an on-board engine lowered the orbit to 1200 km.
| Meteor-3 No. 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1985 Oct 24 | 0230:00 | Launch by Tsiklon-3 11K68 | PL LC32 |
| 0232 | T+2:00 Stage 1 MECO | ||
| 0234 | T+4:37 Stage 2 off, sep | ||
| 0235 | T+5:20 S5M burn 1 | ||
| 0237 | T+7:03 S5M cutoff 1 | 135? x 1230? x 82.5 | |
| 0318? | T+48m? S5M burn 2, 15s? | ||
| 0319? | T+49m? S5M cutoff 2 | ||
| 0319? | T+49m? S5M sep from Meteor-2 | ||
| 1227 x 1250 x 82.6 | |||