Tuesday, December 26, 1978
Sunday, December 24, 1978
Monday, December 18, 1978
Thursday, December 14, 1978
Friday, December 1, 1978
Thursday, November 30, 1978
Sunday, November 26, 1978
Thursday, November 23, 1978
Monday, November 20, 1978
Saturday, November 4, 1978
Kosmos 1043
1978-094A
| Kosmos-1043 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Oct 10 | 1944? | Launch by 8A92M | Plesetsk |
| 1949? | Blok E burn | ||
| 1954? | Blok E sep | ||
| 1978 Oct 10 | 97.3 622x641x83.2 | ||
Monday, October 23, 1978
Monday, September 18, 1978
Saturday, July 1, 1978
Thursday, June 29, 1978
Kosmos 955
1977-091A
| Kosmos-955 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 Sep 20 | 0102 | Launch by 8A92M | Plesetsk |
| 0106? | Blok E burn | ||
| 0111? | Blok E sep | ||
| 1977 Nov 16 | 97.5 630x641x81.2 | ||
Tuesday, June 27, 1978
Saturday, June 24, 1978
Explorer 47
1972-073A
IMP H (Interplanetary Monitoring Platform H) was the first of a new series of IMP probes placed in distant circular orbits. The IMP H series carried a Star 17A apogee motor to circularize the orbit. The probe, which became Interplanetary Monitoring Platform 7 (Explorer 47), was launched at 0120 on 1972 Sep 23 by Delta 1604 from Cape Kennedy. The Delta delivered the probe to a 153 x 411 km x 28.8 deg parking orbit at 0126. After an 11 min coast the Star 37E third stage ignited at 0137 and placed IMP VII in a 248 x 254800 km x 28.6 km orbit. The Star 17A solid motor fired at first apogee placing IMP 7 in a 201100 x 235600 km x 17.2 deg orbit. The satellite operated until 1978 Oct 31 when it was switched off.
Mass was 390 kg launch 1.58m high 1.36m dia. 16-sided cylinder with two 3.4m experiment booms and two 1.2m attitude control system booms for an estimated span of 8.2m. Star 17A was 124 kg full 12 kg empty 0.71m dia. The Delta 1604 introduced the extended long tank booster.
| IMP 7 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1972 Sep 23 | 0120:00 | Launch by Delta 1604 | CC |
| 0120:00 | T+0:00 SRM 1-6 burn | ||
| 0120:39 | T+0:34 SRM 1-6 burnout | ||
| 0121:25 | T+1:25 SRM sep | ||
| 0124:28 | T+4:28 MECO | ||
| 0124:34 | T+4:34 VECO | ||
| 0124 | T+4:36 St 1 (S/N 20006) sep | ||
| 0124:40 | T+4:40 SES-1 | ||
| 0124:57 | T+4:57 Fairing sep | ||
| 0130:12 | T+10:12 SECO-1 | 153 x 411 x 28.8 | |
| 0135:31 | T+15:31 St 2 sep | ||
| 0135:45 | T+15:45 Star 37C burn 43.6s | ||
| 0136:27 | T+16:27 Star 37C burnout | ||
| 0138:09 | T+18:09 Star 37C sep | 248 x 254800 x 28.6 | |
| 0138:11 | Star 37C yo weight release | ||
| 247 x 237796 x 28.6 (MOR Post) | |||
| 1972 Sep 23 | 1815 | Pass EL1:4 | |
| 1972 Sep 25 | 1536 | Star 17A burn | |
| Star 17A burnout | 201100 x 235600 x 17.2 | ||
| 1930? | ACS burn to reduce spin rate | ||
| Boom deploy | 207836 x 235558 x 17.72 (FFR) | ||
| 1972 Sep 26 | Begin experiment turnon | ||
| 1978 Sep 30 | end of operations (TM-80758) | ||
| 1978 Oct 31 | end of tx | ||
Payload:
- H1 Magnetometer (GSFC/Ness)
- H2 Electric and magnetic fields (TRW/Scarf) Plasma Wave Experiment, AC Electric and magnetic fields (TRW/Scharf), 3.1m boom with loop antenna and 61cm dipole antenna
- H3 LASL electrostatic analyser (LASL/Bame) e 4 eV-20 keV, p 70 eV -20 keV.
- H4 Faraday cup (MIT/Bridge) e 17 ev-7 keV, p 50 eV-7 keV.,
- H5 GSFC electrostatic analyser (GSFC/Olgivie)
- H6 Crystal scintillator (GSFC/Cline) Solar Electrons and solar flare X-rays (GSFC/Cline), e 100 keV-2 MeV; X-rays 20 keV-1 MeV
- H7 LEPEDEA (Iowa/Frank)
- H8 U Md. SSD (UMd/Gloeckler) Ions and electrons, electrostatic analyser
- H9 SS and GM detectors (APL/Krimigis)
- Solar and galactic X-ray detector 1.75-16A with GM tubes
- H10 SS and Scint. telescopes (GSFC/McDonald)
- H11 Chicago solid state telescope (Chicago/Simpson)
- H12 CIT solid state telescope (CIT/Stone) Electrons and Isotopes, solid state telescope 0.16-2.8 Mev e, 0.5-40 Mev/n (Caltech/Stone)
Thursday, June 15, 1978
Saturday, May 20, 1978
Tuesday, May 9, 1978
Wednesday, April 5, 1978
Apollo 6
1968-025A
Apollo CSM 020 flew the AS-502 mission, or Apollo 6. The spacecraft used CM 020 and SM 014. The mission was to test launch vehicle and spacecraft compatibility, Saturn stage separations, and Apollo propulsion, guidance and control, and electrical systems. The S-IVB was to insert Apollo 4 in orbit and reignite to place it
in a high apogee trajectory of 224 x 513752 km. The CSM would then have separated and made a retro burn to a 35 x 22194 km orbit, followed prior to reentry with a second SPS burn to 39 x Inf with a reentry velocity of 11.12 km/s. The S-IVB would have carried on to the vicinity of the Moon and presumably made a flyby to solar orbit. However, all this was not to be.
The launch of the second Saturn V, SA-502, was the only serious failure of the Saturn program. The rocket lifted off at 1200 on 1968 Apr 4. The first stage underwent `pogo' oscillations which shook the stack. At 1202:14 part of the SLA adapter broke away. Two engines on the Saturn S-II stage shut down only 4 minutes into second stage burn. The Instrument Unit automatically commanded the stage to burn its three remaining engines for an extra minute to make up. At S-IVB ignition, the rocket's attitude was incorrect and the guidance system commanded the stage to point downward towards the Earth. Then it pitched up, and detected that it had developed more speed than planned, so started to try and cut the speed - it actually went into orbit thrusting backward. The orbit achieved was 172 x 395 km instead of the planned 175 x 175 km one.
The S-IVB failed to restart properly on the second orbit, and as a backup plan the CSM separated in the low orbit and ignited its own SPS engine, reaching an apogee of 22225 km. A second planned SPS burn was cancelled due to lack of fuel. The Service Module, SM-014, was jettisoned and CM-020 reentered the Earth's atmosphere at 10.0 km/s. It splashed down successfully in the Pacific.
| Apollo CSM 020 Mission Log | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1968 Apr 4 | 1200:00 | Launch of SA-502 | |
| 1968 Apr 4 | 1202:05 | Pogo oscillations in S-IC stage for 10s | |
| 1968 Apr 4 | 1202:13 | T+2:13 SLA-9 -Z panel debris breaks off, 46 km | |
| 1202:24 | IECO | ||
| 1202;28 | OECO 59 km | -6009 x 109 x 32.21 | |
| 1968 Apr 4 | 1202:29 | S-IC separation, S-II ignition | |
| 1202:59 | Interstage | ||
| 1203:04 | LES jettison | ||
| 1968 Apr 4 | 1206:53 | S-II engines 2 and 3 shut down | |
| 1968 Apr 4 | 1209:36 | S-II cutoff | |
| 1209:37 | S-II staging | -2475 x 202 x 32.74 | |
| 1968 Apr 4 | 1209:37 | S-IVB ignition | |
| 1968 Apr 4 | 1212:27 | S-IVB cutoff, Earth orbit insertion | 89.92 178 x 367 x 32.63 (T3-I) |
| 90.04 178 x 373 x 32.74 (T.3-II) | |||
| 1220:51 | S-II impact | ||
| 1968 Apr 4 | 1513:35 | 90.01 183 x 370 x 32.63 | |
| 90.40 191 x 397 x 32.74 (T.3-II) | |||
| 1513:35 | S-IVB reignition | ||
| 1513:50 | S-IVB cutoff | 90.50 191 x 406 x 32.73 | |
| 1968 Apr 4 | 1514:27 | CSM separated from S-IVB | 90.52 191 x 408 x 32.73 |
| 1968 Apr 4 | 1516:06 | SPS-1 burn (7:22) to high apogee orbit | |
| 1523:28 | SPS-1 cutoff 517 km | 384.8 33 x 22260 x 32.58 | |
| 386.60 29 x 22373 x 32.65 | |||
| 1968 Apr 4 | 1828:58 | Apogee at 22225 km | |
| 2129:19 | RCS +X translation | ||
| 2130:09 | RCS +X cutoff | 389.33 33 x 22533 x 32.66 | |
| 1968 Apr 4 | 2136:57 | SM-014 separation 238 km | |
| 1968 Apr 4 | 2138:29 | Reentry 10.0 km/s -5.85 deg | 35 x 22618 x 32.73 |
| 2140 | Begin skip, 58 km | ||
| 2143 | Skip apogee, 67 km | ||
| 2145 | Descending at 58 km | ||
| 2151:27 | Drogue parachute deployed | ||
| 1968 Apr 4 | 2157:20 | Splashdown | |
| 1968 Apr 4 | 2330 | Recovered by USS Okinawa. | |
Saturday, March 25, 1978
Saturday, February 25, 1978
Friday, February 24, 1978
Monday, February 20, 1978
Thursday, February 16, 1978
Friday, February 10, 1978
Kosmos 92
1965-083A
Zenit-4 No. 16, which flew in Oct 1965, carried a set of scientific experiments and some equipment for Meteor weather satellite development.
| Kosmos-92 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1965 Oct 16 | 0814:59 | Launch by 11A57 | KB |
| 0819? | Blok-I burn | ||
| 0824? | Blok-I sep | 89.85 201 x 334 x 64.97 | |
| 1965 Oct 24 | 0623? | Retrofire | |
| 0643? | Landed after 7.94d | ||
Monday, January 30, 1978
Thursday, January 19, 1978
Saturday, January 7, 1978
Molniya 106
1966-035A
Molniya-1 F6 carried a TV camera for weather observations.
| Molniya-1 F6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Apr 25 | 0710 | Launch by Molniya | KB |
| 0715? | Blok-A sep | ||
| 0715? | Blok-I burn | ||
| 0719? | Blok-I sep | ||
| 0810? | BOZ burn | ||
| 1966 Apr 25 | 91.19 183 x 482 x 64.9 | ||
| 0811? | Blok-L burn | ||
| 0815? | Blok-L sep | ||
| 1966 May 9 | 709.36 455 x 39483 x 64.7 | ||
| 1966 Jun 11 | 710.15 429 x 39548 x 65.0 | ||
| 1966 Sep 2 | end of ops | ||
| 1966 Nov 23 | 710.68 538 x 39465 x 65.0 | ||
| 1967 Jul 4 | 705.71 754 x 39003 x 65.2 | ||
| 1970 May 24 | 705.54 1628 x 38121 x 65.1 | ||
| 1973 Jan 30 | 701.63 200 x 39354 x 64.6 | ||
| 1973 May 7 | 651.62 135 x 36903 x 64.5 | ||
| 1973 Jun 8 | 134.07 261 x 4336 x 64.4 | ||
| 1973 Jun 11 | Reentered | ||
Thursday, January 5, 1978
Kosmos 291
1969-066A
Kosmos-291 was an interceptor mass model (IS GVM) used as a test payload for the first launch of the 11K69 (Tsiklon-2) production version of the 11K67 launch vehicle. There was an accident during launch preparations but the launch itself was successful. The IS version was the 5V91T, part of the Lira system.
| Kosmos-291 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1969 Aug 6 | 0540 | Launch by 11K69 | KB PL90L |
| 0542 | Stage 2 burn | ||
| 0546? | Stage 2 sep | ||
| 1969 Aug 7 | 0500? | 91.46 147 x 548 x 62.24 | |
| 1969 Aug 11 | 0824? | Stage 2 reentered | |
| 1969 Sep 8 | 87.78 117 x 211 x 62.2 | ||
| 1969 Sep 8 | 2233? | Reentered | |