Saturday, December 27, 2003
Ekspress 1
1994-067A
The first Ekspress satellite was launched in 1994. Ekspress No. 11L was designated Ekspress-2 on orbit at 14W. The satellite failed in Jun 2001, interrupting Intersputnik services briefly until traffic was transferred to Ekspress-3A.
| Ekspress No. 11 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Oct 13 | 1619:00 | Launch by Proton | KB |
| 1628 | Stage 3 sep | ||
| 1628 | Adapter sep | 185? x 200? x 51.6 | |
| 1732? | DM burn 1 | ||
| DM MECO-1 | 200? x 36000? x 48.0? | ||
| 2250? | DM burn 2 | ||
| 2300? | DM sep | ||
| 1994 Oct 13 | 1440.78 35862 x 35893 x 0.2 GEO 91.1E+1.1W | ||
| 1994 Oct 24 | 1441.47 35863 x 35920 x 0.2 GEO 76.2E+1.3W | ||
| 1994 Nov 8 | 1435.87 35778 x 35785 x 0.2 GEO 70.7E+0.05E | ||
| 1994 Dec 28 | 1436.12 35781 x 35792 x 0.1 GEO 71.3E | ||
| 1995 Jan 4 | 1436.11 35779 x 35793 x 0.1 GEO 71.3E | ||
| 1995 Jan 5 | mv out | ||
| 1995 Feb 14 | mv in | 1436.04 35776 x 35794 x 0.1 GEO 14.0W | |
| 1995 Jun 14 | 1436.14 35773 x 35801 x 0.1 GEO 13.9W | ||
Kosmos 2290
1994-053A
Kosmos-2290 was deorbited in Apr 1995 over the Pacific, reentering approx 2720 km E of Wellington, NZ. According to Phillip Clark, mass of Kosmos-2290 was around 10600 kg.
The Yuzhnoe book implies the name Orlets.
At launch, the usual four high-orbit Zenit rocket separation motor covers were cataloged. In addtion, two small debris objects were found in the payload orbit, which may be sensor covers of some kind. The satellite was deorbited on 1995 Apr 4; two days earlier four objects were ejected.
Debris was found in Mexico, including parts from a 17D62 engine.
| Kosmos-2290 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Aug 26 | 1200:00 | Launch by Zenit-2 | KB |
| 1202:28 | Stage 1 sep | ||
| 1204:58 | Fairing sep | ||
| 1207:18 | Stage 2 MECO | ||
| 1210:28 | Stage 2 VECO | ||
| 1210:29 | Stage 2 sep | ||
| 1994 Aug 26 | 89.55 211 x 292 x 64.8 | ||
| 1994 Aug 30 | 89.50 210 x 288 x 64.8 | ||
| 1994 Sep 6 | 89.38 208 x 279 x 64.8 | ||
| 1994 Sep 6 | Orbit raise | 90.08 208 x 347 x 64.8 | |
| 1994 Sep 30 | 89.66 201 x 314 x 64.8 | ||
| 1994 Oct 1 | Orbit raise | 89.84 209 x 323 x 64.8 | |
| 1994 Oct 14 | 89.53 204 x 298 x 64.8 | ||
| 1994 Oct 14 | Orbit raise | 89.89 206 x 330 x 64.8 | |
| 1994 Oct 20 | 89.79 203 x 323 x 64.8 | ||
| 1994 Oct 20 | Orbit raise | 90.13 205 x 356 x 64.8 | |
| 1994 Oct 29 | 89.96 201 x 342 x 64.8 | ||
| 1994 Oct 29 | Orbit raise | 90.32 213 x 366 x 64.8 | |
| 1994 Nov 5 | 90.21 212 x 357 x 64.8 | ||
| 1994 Nov 10 | 90.12 210 x 350 x 64.8 | ||
| 1994 Nov 11 | Orbit raise | 90.28 209 x 366 x 64.8 | |
| 1994 Nov 15 | 90.22 209 x 361 x 64.8 | ||
| 1994 Dec 14 | 89.74 200 x 322 x 64.8 | ||
| Orbit raise | |||
| 1994 Dec 14 | 90.37 202 x 382 x 64.8 | ||
| 1994 Dec 28 | 90.13 200 x 361 x 64.8 | ||
| Orbit raise | |||
| 1994 Dec 28 | 90.63 200 x 410 x 64.8 | ||
| 1995 Jan 26 | 90.16 193 x 371 x 64.8 | ||
| 1995 Jan 26 | Orbit adjust | ||
| 1995 Jan 27 | 89.88 192 x 344 x 64.8 | ||
| 1995 Jan 30 | 89.79 190 x 337 x 64.8 | ||
| 1995 Jan 31 | Orbit raise | 90.34 191 x 391 x 64.8 | |
| 1995 Feb 7 | 89.96 177 x 367 x 64.8 | ||
| 1995 Feb 8 | Orbit raise | 90.35 181 x 401 x 64.8 | |
| 1995 Feb 12 | 89.19 179 x 387 x 64.8 | ||
| 1995 Feb 13 | Orbit raise | 90.33 181 x 399 x 64.8 | |
| 1995 Feb 22 | 89.97 178 x 367 x 64.8 | ||
| 1995 Feb 23 | Orbit raise | 90.72 180 x 439 x 64.8 | |
| 1995 Mar 5 | 90.31 177 x 401 x 64.8 | ||
| Orbit raise | 90.96 184 x 458 x 64.8 | ||
| 1995 Mar 15 | 90.65 183 x 429 x 64.8 | ||
| 1995 Mar 16 | Orbit lower | 90.39 182 x 404 x 64.8 | |
| 1995 Mar 27 | 90.00 179 x 370 x 64.8 | ||
| 1995 Mar 28 | Orbit raise | 82.14 181 x 576 x 64.80 | |
| 1995 Apr 2 | 53J,K,L,M ejected | ||
| 1995 Apr 3 | 91.93 180 x 557 x 64.80 | ||
| 1995 Apr 4 | 2355 | Deorbited over Pacific | |
| 1995 Apr 5 | 0155? | Entry over Mexico? | |
Friday, December 26, 2003
USA-82
1992-037A
The second Atlas II launch for DSCS III carried the B-12 satellite, named USA 82 on orbit. The IABS placed B-12 in the correct orbit, but the IABS IRU/gyro system had an electronics failure that precluded its use on-orbit, and the satellite operated using the standard DSCS system.
| DSCS III B-12 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Jul 2 | 2154 | Launch by Atlas II | CC LC36A |
| 2156 | Booster sep (T+2:49) | ||
| 2159 | Centaur MES1 (T+5:00) | ||
| 2205 | Centaur MECO1 (T+11:20) | ||
| 2218 | Centaur MES2 (T+24:00, burn 1:50) | ||
| 2220 | Centaur MECO2 | ||
| 2223 | Centaur sep (T+29:10) | 617.3 223 x 35053 x 26.5 (UN) | |
| 1992 Jul 4? | IABS burn | ||
| 1416.6 35289 x 35520 x 0.3, IABS (UN) | |||
| 1436.2 35775 x 35800 x 0.2 (UN) | |||
| 1995 Jul | ELANT Prime | GEO 12.0W | |
| 1997 Oct | ELANT Prime | GEO 12.0W | |
| 2002 Jun | Orbit raised | ||
| 2002 Jul 30 | Decommissioned | ||
Thursday, December 25, 2003
Westar 6 (Asiasat 1)
1984-011B / 1990-030A
The Westar 6 satellite was carried into orbit on the Space Shuttle Challenger in Feb 1984. Deployment from the cargo bay was normal, but when the PAM-D upper stage ignited the nozzle failed and the satellite was left in a low elliptical orbit. It was recovered by the 51-A mission. The underwriters, Merritt Syndicates, sold the satellite to Asiasat. Asiasat (the Asia Satellite Telecommunications Co. of Hong Kong) is a consortium of Cable & Wireless, Hutchinson Wampoa and the China International Trust and Investment Corp. (CITIC). Asiasat got Hughes to refurbish the satellite; it was then relaunched from China aboard a CZ-3 rocket, this time reaching GEO successfully. It was used for regional SE Asian communications.
| Westar 6 (Asiasat 1) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1984 Feb 3 | 2059:23 | Westar 6 deploy from OV-099 | |
| 1984 Feb 3 | 2145 | PAM-D burn | |
| 1984 Feb 3 | PAM-D loss of control | ||
| 1984 Feb 3 | 2146? | PAM-D sep | 100.0 300 x 1214 x 27.7 |
| 1984 Feb 6 | 100.02 303 x 1215 x 27.7 | ||
| 1984 Feb 8 | 100.02 303 x 1215 x 27.7 | ||
| 1984 Feb 9 | 99.94 295 x 1215 x 27.7 | ||
| 1984 Feb 27 | 99.89 296 x 1210 x 27.7 | ||
| 1984 May 5 | 99.74 305 x 1186 x 27.7 | ||
| 1984 May 12 | 99.75 305 x 1187 x 27.7 | ||
| 1984 May 12 | mv up | 107.64 357 x 1192 x 27.9 | |
| 1984 May 12 | 1648 | AKM fired | 107.64 1070 x 1164 x 28.5 |
| 1984 Jul 19 | 107.64 1070 x 1165 x 28.5 | ||
| 1984 | Ownership to Merritt Syndicates | ||
| 1984 Aug 6 | mv | 106.11 1042 x 1050 x 28.5 | |
| 1984 Oct 9 | 106.11 1042 x 1050 x 28.5 | ||
| 1984 Oct 11 | lower orbit | 103.81 820 x 1056 x 28.5 | |
| 1984 Oct 12 | 100.34 490 x 1058 x 28.5 | ||
| 1984 Oct 13 | lower orbit | 99.06 370 x 1056 x 28.5 | |
| 1984 Oct 14 | 99.05 364 x 1061 x 28.5 | ||
| 1984 Oct 16 | 98.76 352 x 1046 x 28.5 | ||
| 1984 Oct 18 | 97.75 354 x 947 x 28.5 | ||
| 1984 Oct 19 | 96.96 355 x 867 x 28.5 | ||
| 1984 Oct 23 | 95.27 357 x 706 x 28.5 | ||
| 1984 Oct 27 | 92.73 352 x 463 x 28.5 | ||
| 1984 Oct 28 | 91.72 342 x 375 x 28.5 | ||
| 1984 Nov 2 | 91.91 361 x 375 x 28.5 | ||
| 1984 Nov 14 | 91.77 353 x 369 x 28.5 | ||
| 1984 Nov 14 | OV-103 rendezvous with Westar 6 | ||
| 1232 | MMU/Gardner dock Westar | ||
| RMS grapple Westar | |||
| MMU undock ACD | |||
| 1327? | MMU berthed | ||
| 1442 | Base adapter on | ||
| Westar berthed | |||
| 1984 Nov 16 | OV-103 landed | ||
| 1987 Jun 25 | Sold to Asiasat | ||
| 1990 Apr 7 | 1330:02 | Launch by CZ-3 | XSC |
| 1332:09 | Stage 1 sep, 50km | ||
| 1334:25 | Stage 2 sep | ||
| 1334:25 | Stage 3 MES1 | ||
| 1341:30 | T+11:28 Stage 3 MECO | ||
| 1345:32 | Stage 3 MES2 | ||
| 1351:29 | Stage 3 sep at perigee | ||
| 1990 Apr 9 | 0343? | Star 30C burn | |
| 1990 Apr 9 | 1438.01 34902 x 36745 x 0.3 GEO 130.3E+0.4W | ||
| 1990 Apr 14 | 1456.17 35797 x 36559 x 0.3 GEO 109.1E+4.9W | ||
| 1990 Apr 15 | On station | GEO 105.5E | |
| 1990 Apr 19 | 1436.10 35782 x 35790 x 0.2 GEO 105.6E | ||
| 1992 Mar 29 | 1436.16 35776 x 35799 x 0.1 GEO 105.5E | ||
| 1994 Feb 10 | 1436.11 35785 x 35788 x 0.0 GEO 105.5E | ||
| 1996 Mar 5 | 1436.06 35777 x 35794 x 0.0 GEO 105.6E | ||
| 1999 Jun 14 | 1436.15 35785 x 35789 x 0.2 GEO 105.6E | ||
| 1999 Jun 17 | mv out | ||
| 1999 Aug 14 | Move in to 122E | ||
| 2000 Jun 10 | 1436.10 35783 x 35790 x 1.0 GEO 122.1E | ||
| 2003 Jan 23 | 1436.28 35784 x 35796 x 3.2 GEO 121.4E | ||
Wednesday, December 24, 2003
USA-174
2003-057A
The contract for an extra UHF satellite was given in 1999. HS-601 launch by Atlas 3B/SEC AC-203. Launch mass 3041 kg.
| UHF F11 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 Dec 18 | 0230 | Launch by Atlas 3 AC-203 | CC SLC36B |
| 0224:00 | Launch per Cleary report | ||
| T+3:00 BECO | |||
| T+3:07 Atlas sep | |||
| T+3:18 MES1 | |||
| 0233 | T+3:26 Fairing sep | ||
| T+4:40 | 172 km 3.933 km/s | ||
| 0244 | T+14:54 MECO-1 | 185 x 1092 x 28.1 | |
| 0254 | T+24:37 MES-2 | ||
| 0257 | T+27:42 MECO-2 | ||
| 0302 | T+32:25 Centaur sep | 288 x 35905 x 27.0 | |
| 2003 Dec 19? | LAM burn | ||
Gruzomaket
2003-055A
978 kg dummy Kondor-E satellite on Strela test launch. Refurbished UR-100NU. NPO-M (Mashinostroenie). The satellite is a box
KGCh-2 payload section; rocket is 29.2l 2.5d 100t (Strela can also have KGCh-1 normal warhead fairing). Third stage is APB-OIA: agregatno-priborniy blok, equipment-service stage, with extra 2.4m dia 0.8m long otsek ismeritel'noy apparaturi, instrumentation module. The Strela rocket has the designation 14A036 and the APB is 14S425.
Mark Wade's site suggested an APB mass of 1100 kg full 725 kg empty with an Isp of 200s. With a 1000 kg payload this gives a delta-V of 1961 ln ( 2100 / 1725 ) = 386 m/s implying a preburn orbit of around -770 x 460 km. A plausible range given uncertainties in mass and Isp is 350-450 m/s, giving (-950 to -650) x 460 km.
The Strela user manual gives details of an ascent to a 1000 km orbit; the stage 2 sep, pre-APB orbit is then -600 x 1000 km. The fairing jettison at 114 km is to a -5485 x 190 km orbit; the stage 1 seps to -5740 x 165 km at 70 km.
The RKN 14A036 Strela used the 15S300 booster, the 14S425 APB, and the payload was KGCh 14S135, consisting of the 14S620 OIA, the 14S134 fairing, and the mass model GVM30201-14S135.
| Gruzomaket | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 Dec 5 | 0600:00 | Launch by Strela | KB PL175/2 |
| 0602 | T+2:07 Stage 1 MECO | ||
| 0602 | T+2:07 Stage 2 burn 3:03 | ||
| 0602 | T+2:08 St 1 sep | ||
| T+2:59 Fairing sep at 114 km | |||
| 0604 | T+4:48 Stage 2 MECO | ||
| 0605 | T+5:06 Stage 2 VECO | ||
| 0605 | T+5:07 Stage 2 sep at 200 km | ||
| 0605 | T+5:07 OIA burn for attitude control | ||
| 0616 | T+16:27 OIA cutoff | ||
| 0616 | T+16:27 APB burn | ||
| 0619 | T+19:20 APB MECO | ||
| 0619 | T+19:52 APB sep | 93.74 452 x 461 x 67.08 | |
| 0620 | T+20:17 APB depletion | 93.04 389 x 457 x 67.08 | |
Tuesday, December 23, 2003
Monday, December 22, 2003
STS-83 (Columbia)
1997-013A
STS-83 was the MSL-1 (Microgravity Science Lab) Spacelab/EDO mission. An afternoon launch on April 4 followed a one-day technical delay; the count was held at the T-19 hour mark to add thermal insulation to a water coolant line. Columbia carried the Spacelab Long Module as well as the OARE acceleration monitor and a Hitchhiker-G experiment (CRYOFD) in the cargo bay. The middeck included a set of protein crystallography experiments.
Commander Jim Halsell was on his third flight, but his first as commander. Susan Still became the second woman to sit in the pilot's seat, while Janice Voss was payload commander with mission specialists Michael Gernhardt and Don Thomas. Thomas was lucky to be aboard - he broke an ankle during training, and Cady Coleman was named as a last-minute backup. A couple of weeks before launch, however, Thomas was cleared for flight and Coleman stood down. Two payload specialists completed the crew, both materials scientists. Roger Crouch was a long-time NASA scientist currently stationed at NASA Headquarters. He had been alternate PS for an earlier Spacelab mission. Gregory Linteris worked at the National Institute for Standards and Technology.
Problems with Fuel Cell 2 became apparent on Apr 5, and on Apr 6 after hours of discussion Mission Control declared a Minimum Duration Flight (MDF), with a return to Earth on Apr 8 instead of the originally planned Apr 19.
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Mar 5 | Tow to VAB | ||
| 1997 Mar 11 | 1130 | Rollout to LC39A | |
| 1997 Apr 4 | 1920:32 | Launch | KSC LC39A |
| 1922:35 | SRB sep | ||
| 1929:04 | MECO | ||
| 1929:23 | ET sep | 88.22 69 x 303 x 28.46 | |
| 2000:27 | OMS 2 2:23 68m/s | 90.56 300 x 303 x 28.46 | |
| 2002:50 | OMS 2 CO | ||
| 2109 | PLBD open complete | ||
| 2120? | Fuel cell problem | ||
| 1997 Apr 5 | 90.55 299 x 303 x 28.47 | ||
| 1997 Apr 6 | 1930 | Fuel Cell 2 shut down | |
| MDF declared | |||
| 1997 Apr 7 | 90.53 298 x 303 x 28.47 | ||
| 1997 Apr 8 | 1455 | PLBD closed | 90.52 297 x 301 x 28.47 |
| 1731:18 | OMS DO 3:22 99.0m/s | -34 x 301 x 28.5 | |
| 1734:40 | OMS DO CO | ||
| 1801 | Entry interface | ||
| 1833:11 | MGTD KSC RW33, 3:23:12:39 | ||
| 1833:23 | NGTD | ||
| 1834:10 | Wheels stop | ||
Sunday, December 21, 2003
Apollo 8
1968-118A
- Commander: Frank Borman, Col. USAF
- Senior Pilot: James Lovell Jr., Capt. USN
- Pilot: William Anders, Maj. USAF
Apollo 8 Crew
Apollo CSM 103 was launched on the AS-503 mission (Apollo 8) at 1251 on 1968 Dec 21. Apollo 8 was a historic mission - for the first time human beings would leave Earth's gravitational sphere of influence and head for the Moon. Apollo 8 entered a 179 x 190 km x 32.6 deg Earth parking orbit at 1302, and at 1541 the S-IVB stage reignited for translunar injection - TLI. The Apollo separated from the Saturn, turned around for practice at stationkeeping, and then moved away to begin its cruise to the Moon.
At 2029 on 1968 Dec 23, Borman, Lovell and Anders passed through the point at which the Moon's gravity became greater than the Earth's. At 1003 on Dec 24 they fired up the SPS engine to enter an elliptical orbit around the Moon. The orbit apogee was lowered to circularize the path at 1426.
The Apollo 8 spaceship spent a day in lunar orbit, taking the famous `Earthrise' photo of the Earth rising above the lunar horizon.
CSM 103 began its flight back to the Earth at 0610 on 1968 Dec 25, the SPS engine boosting it out of lunar orbit. At 1519 on Dec 27 the Service Module was jettisoned to burn up in the Earth's atmosphere. The CM began reentry at 1537, at 122 km altitude, making the first piloted `skip reentry'. CM-103 descended to 55 km and then rose again to 64 km before descending toward the Pacific. It would fly a range of 2500 km from entry to splashdown. The Command Module touched down in the Pacific at 1551 on 1968 Dec 27.
| Apollo CSM 103 Mission Log | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1968 Dec 21 | 1251:00 | Launch of SA-503 | |
| 1968 Dec 21 | 1253:06 | S-IC center engine cutoff | |
| 1968 Dec 21 | 1253:33 | S-IC outboard engines cutoff | |
| 1968 Dec 21 | 1253:34 | S-IC-503 separation, altitude 80.5 km | |
| 1968 Dec 21 | 1254:08 | LES separation | |
| 1968 Dec 21 | 1259:44 | S-II-3 separation | -2286 x 192 x 32.66 |
| 1968 Dec 21 | 1259:45 | S-IVB burn ignition | |
| 1968 Dec 21 | 1302:25 | S-IVB main engine cutoff | |
| 1968 Dec 21 | 1302:35 | Earth orbit insertion, | 179 x 190 km x 32.6 deg |
| 1333:05 | Optics cover jettison | ||
| 1968 Dec 21 | 1541:38 | S-IVB TLI burn | |
| 1968 Dec 21 | 1546:55 | S-IVB main engine cutoff | |
| 1968 Dec 21 | 1547:05 | Translunar injection | 214 x 544356 x 30.71 |
| C3 = -1.479 | 218 x 545303 x 31.07 | ||
| 1968 Dec 21 | 1611:59 | S-IVB-503 separation | 141 x 538222 x 30.71 |
| 1968 Dec 21 | 1613 | Stationkeeping exercise | |
| 1968 Dec 21 | 1631:01 | Sep (RCS) | |
| 1968 Dec 21 | 1736:01 | Sep-2 (RCS) 2.3m/s | |
| 1968 Dec 21 | 2351 | MCC-1 (SPS mid course correction) | 308 x 535599 x 30.6 |
| 1968 Dec 23 | 2029 | Equigravisphere | |
| 1968 Dec 24 | 0150:55 | MCC-4 (RCS mid course correction) | |
| 1968 Dec 24 | 0959:02 | Begin LOI-1 | 122 x -11021 x 145.49 |
| 1003:27 | LOI-1 (SPS lunar orbit insertion, 4:06) | 110 x 293 x 151.2 | |
| 1968 Dec 24 | 1007:34 | Lunar orbit insertion, | 112 x 313 km x 168 deg |
| 1968 Dec 24 | 1426:07 | LOI-2 (SPS burn, 10s) | 109 x 305 x 156.8 (MR) |
| 1426:17 | LOI-2 CO | 112 x 113 km x 168 deg | |
| 1968 Dec 25 | 0610:16 | TEI (SPS 3min23s burn) | 105 x 115 x 150 |
| 1968 Dec 25 | 0613:39 | Transearth Injection | 110 x -8518 x 153.7 |
| Return to Earth gravity sphere | |||
| 1968 Dec 25 | 2050:54 | MCC-5 (midcourse correction) | -585 x 982887 x 37.7 |
| 1968 Dec 27 | 1519:48 | SM-108 separation | |
| 1968 Dec 27 | 1537:12 | Entry interface 11.040km/s at -6.50deg | 38 x 1038993 x 37.2 |
| 1968 Dec 27 | 1551:42 | Splashdown, 08 08 N, 165 W, Pacific Ocean | |
| 1968 Dec 27 | 1645 | Recovery by USS Yorktown | |
Transit 4A
1961-015A
The Transit IVA satellite tested out the SNAP 3A radioisotope thermoelectric generator (RTG), a nuclear power supply. The spacecraft bus was a new cylindrical design and used magnetic rather than yo-yo despin. The SR and Injun satellites separated from Transit.
The Ablestar rocket exploded when residual propellants ignited.
Gatland (1961) reports a launch time of 1623 UTC (1223 EDT), 12 hours off from the value I have.
| Transit IVA | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1961 Jun 29 | 0423 | Launch by Thor Ablestar | CC LC17 |
| 0425 | Thor sep | ||
| 0426? | Ablestar burn 1 | ||
| Ablestar MECO | 150? x 1000? x 66 | ||
| Ablestar burn 2 | |||
| 0451 | Ablestar MECO-2 | ||
| Ablestar sep | |||
| SR/Injun sep | |||
| 881 x 998 x 66.81 | |||
| 0608:10 | Ablestar exploded | ||
| 1961 Jul 15 | Solar cell experiment end of ops | ||
| 1970 May | Beacon still transmitting | ||
| 1974? | End of transmissions? | ||
Payload:
- Beacons C 54/324 MHz Z 150/400 MHz
- SNAP 3A RTG
- Solar cell test panel