Saturday, February 22, 1997
Wednesday, February 19, 1997
Kosmos 575
1973-043A
Kosmos-575 was launched in Jun 1973 from Plesetsk on a 12 day mission.
| Kosmos-575 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1973 Jun 21 | 1329:57 | Launch by 11A57 | PL |
| 1334 | Blok-I burn | ||
| 1338 | Blok-I sep | ||
| 1973 Jun 22 | 2328 | 89.24 203 x 269 x 65.4 | |
| 1973 Jun 23 | 0000 | 89.25 204 x 271 x 65.41 (RAE) | |
| 1973 Jun 27 | 1926 | 89.16 201 x 264 x 65.4 | |
| 1973 Jul 2 | 1817 | 89.08 199 x 258 x 65.4 | |
| 1973 Jul 3 | 0604? | Retrofire | |
| 0614? | PO sep | ||
| 0620? | Entry | ||
| 0636? | Landed after 11.71d | ||
Kosmos 1140
1979-089A
| Kosmos-1140 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1979 Oct 11 | 1636 | Launch by 11K65M | Plesetsk |
| Stage 2 burn | |||
| 1644? | T+8 min Stage 2 MECO-1 | ||
| Stage 2 MES-2 | |||
| T+34min Stage 2 MECO-2 | |||
| 1710? | Stage 2 sep | ||
| 1979 Oct 11 | 100.7 780x805x74.1 | ||
Tuesday, February 18, 1997
Kosmos 1539
1984-020A
The Feb 1984 Kobal't mission continued the existing pattern.
| Kosmos-1539 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1984 Feb 28 | 1400:00 | Launch by Soyuz | PL |
| 1408 | Blok-I MECO | ||
| 1984 Feb 28 | 89.60 167 x 340 x 67.2 | ||
| 1984 Feb 29 | 90.11 182 x 376 x 67.1 | ||
| 1984 Mar 1 | 90.03 181 x 370 x 67.1 | ||
| 1984 Mar 2 | 89.25 170 x 304 x 67.1 | ||
| 1984 Mar 5 | 89.01 166 x 284 x 67.1 | ||
| 1984 Mar 6 | 88.95 165 x 280 x 67.1 | ||
| 1984 Mar 6 | 90.25 167 x 405 x 67.1 | ||
| 1984 Mar 7 | 90.19 166 x 400 x 67.1 | ||
| 1984 Mar 8 | 89.21 165 x 304 x 67.1 | ||
| 1984 Mar 11 | 88.83 159 x 273 x 67.1 | ||
| 1984 Mar 12 | 89.05 172 x 282 x 67.1 | ||
| 1984 Mar 13 | 88.93 170 x 273 x 67.1 | ||
| 1984 Mar 14 | 89.73 175 x 346 x 67.1 | ||
| 1984 Mar 22 | 89.10 166 x 293 x 67.1 | ||
| 1984 Mar 23 | 89.78 165 x 360 x 67.1 | ||
| 1984 Mar 29 | 89.11 158 x 301 x 67.1 | ||
| 89.65 184 x 329 x 67.1 | |||
| 1984 Apr 2 | 89.17 177 x 289 x 67.1 | ||
| 1984 Apr 6 | 89.53 175 x 327 x 67.1 | ||
| 1984 Apr 9 | |||
| 2224? | Deorbit | ||
| 2240? | Entry | ||
| 2256? | Landing | ||
Pegsat
1990-028A
Pegsat was a test satellite for the first Pegasus launch and it remained attached to the Pegasus Orion 38 third stage motor. Developed by NASA-Goddard and built in-house, it carried Barium release canisters left over from the CRRES program as a bonus scientific experiment. The NB52 008 carrier aircraft took off from RW04/22 at Edwards AFB at 1803 on 1990 Apr 5 and flew out over the Point Arguello Warning Area 80 km W of Vandenberg AFB. At 1910:17 the B-52 dropped the Pegasus at an altitude of 13 km. First stage ignition was at 1910:22, burnout at 1911:38 at an altitude of 70 km. Stage 2 ignited at 1911:47 at 76 km, and burnt out at 1912:59 at 198 km. The second and third stages remained attached for a coast period, then at 1918:39 the second stage separated and stage 3 ignited for a 66 s burn at 537 km altitude. Earth orbit insertion was at 1919:45 into a 508 x 687 km x 94.2 deg orbit. The first barium canister was released on 1990 Apr 15; the second was probably released on 1990 Apr 17.
| Pegsat | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Apr 5 | 1803 | B-52 takeoff EAFB | |
| 1910:15 | Drop 13.2km | ||
| 1910:20 | Stage 1 burn | ||
| 1911:35 | T+1:20 Stage 1 cutoff, 70 km | ||
| 1911:43 | T+1:28 Stage 1 sep | ||
| 1911:45 | T+1:30 Stage 2 burn | ||
| 1912:10 | T+1:50 Fairing sep | ||
| 1912:59 | T+2:39 Stage 2 cutoff, 198 km | ||
| 1918:39 | T+8:19 Stage 2 sep | ||
| 1918:39 | Stage 3 burn, 537 km, 2.5 deg 4.552 km/s | ||
| 1919:45 | T+9:25 Stage 3 cutoff 7.580 | ||
| 1919:47 | SECS/TERCEL sep | |
| 1921:32 | Stage 3 end of tx | ||
| 1990 Apr 16 | Canister R1 sep | ||
| 0545:07 | Canister R1 release Ba at 244E | ||
| 1990 Apr 25 | Canister R2 sep | ||
| 0449:01 | R2 release Ba | ||
| 1991 Jan? | end of ops | ||
| 1996 Nov 14 | Reentered | ||
Zond 4
1968-013A
The L-1 No. 6 spacecraft was given the code-name Zond-4 after launch. The earlier Zond space probes were planetary probes in the MV series and entirely unrelated to the L-1 lunar program.
In an interview with Bert Vis, Vitaliy Sevastyanov reported that he and Popovich were participating in a simulated L-1 mission at Yevpatoria during the flight; their communications from the L-1 simulator were routed through Zond-4 in deep space and then back to TsUP. He said that the spacecraft reentered on Mar 9 over the Atlantic in the Gulf of Guinea, but was destroyed at an altitude of 15 km by ground command because no recovery fleet was available at that time. Another report claimed that attitude control failed on reentry and still other rumours suggested that it landed accidentally in China, but the Sevastyanov report has now been confirmed.
The Energiya history states that an orientation system problem led to a ballistic reentry and use of the auto destruct above the Gulf of Guinea. The intent was to make a 46 km pass and skip out to 145 km for final reentry,but the skip did not work and the auto destruct fired at 15 km altitude.
The reentry time implies an apogee of about 294000 km and a TLI velocity of 10.84 km/s.
| Zond-4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1968 Mar 2 | 1829:23 | Launch by Proton | KB |
| 1838 | Stage 3 sep | -1500 x 200 x 51.5 | |
| 1842? | Blok D burn 1, 150s? | ||
| 1844? | Blok D MECO-1 | ||
| 1940 | 88.4 192 x 205 x 51.5 | ||
| SOK cone sep | |||
| 1941:19 | Blok-D burn, TLI, 459s | ||
| SOZ units sep | |||
| 1948:50 | Blok-D MECO-2, TLI | ||
| 1949? | Blok-D sep | ||
| 1968 Mar 4 | 0435 | TCM cancelled | |
| 1968 Mar 6 | TCM 15s | ||
| 1968 Mar 9 | 1811 | PAO sep from SA | |
| 1819 | Entry | ||
| 1819:58 | Reentry, attitude control failed | ||
| 1821 | APO destruct activated | ||