Saturday, May 15, 2004
Tuesday, May 11, 2004
Saturday, May 8, 2004
Intelsat 805
1998-037A
An LM 7000 satellite, Intelsat 805 had a hemi beam covering the Americas and Europe, allowing distribution to both sides of the Atlantic with a single transponder of video services, telephony and VSAT applications.
Intelsat 805 was launched into standard GTO by an Atlas IIAS with a 14' fairing. Launch mass was 3524 kg. EMBRATEL leased several transponders for Internet traffic at the time of launch.
Intelsat 805 was the last payload built at LMAS/East Windsor.
| Intelsat 805 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Jun 18 | 2248 | Launch by Atlas IIAS AC-153 | CC LC36A |
| T+00:59 SRB-3,4 burn | |||
| T+1:15 SRB-1,2 sep | |||
| T+1:56 SRB-3,4 sep | |||
| T+2:43 BECO | |||
| T+2:46 Booster sep | |||
| T+3:24 Fairing sep | |||
| T+4:51 SECO | |||
| T+4:53 Atlas sep | |||
| T+5:10 MES 1 | |||
| 2257 | T+9:45 MECO 1 | 90.50 150 x 598 x 27.8 | |
| T+24:30 MES 2 | |||
| 2314 | T+26:07 MECO-2 | 633.20 166 x 35930 x 24.0 | |
| 2318 | T+30:07 Centaur sep | 633.40 171 x 35935 x 24.0 | |
| 1998 Jun 19 | 0054 | T+2:05:59 Centaur depletion burn | 629.90 170 x 35756 x 23.1 |
| 1998 Jun 19 | 629.56 177 x 35731 x 23.9 | ||
| 1998 Jun 20 | 0130? | LAM1 | |
| 1998 Jun 20 | 676.51 2598 x 35701 x 17.0 | ||
| 1998 Jun 22 | 2130? | LAM2 | |
| 1998 Jun 22 | 1045.57 19797 x 35694 x 3.2 | ||
| 1998 Jun 23 | 1500? | LAM3 | |
| 1998 Jun 24 | 1429.51 35575 x 35739 x 0.1 GEO 59.7W+1.6W | ||
| 1998 Jul 10 | 1436.05 35771 x 35800 x 0.1 GEO 55.4W | ||
Wednesday, April 28, 2004
DSCS-2 F5
1977-034A
DSCS II C-5 was the first C model, with improved design life.
| DSCS II C-5 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 May 12 | 1426:58 | Launch by Titan 3C | CC LC40 |
| T+1:49 Stage 1 ignition | |||
| T+2:02 SRM sep | |||
| T+4:18 Stage 1 MECO, sep | |||
| 1432 | T+5:00? Fairing | ||
| 1434? | T+7:40? SECO | ||
| 1435? | Stage 2 sep (T+8:00) | ||
| 1540? | Transtage burn 1 | ||
| 2030? | Transtage burn 2 | ||
| 2040? | Transtage sep | ||
| 1977 May 13 | 0858 | 1428.17 35475 x 35787 x 2.5 GEO 94.3W+2.0E | |
| 1977 May 13 | 0955 | 1426.80 35448 x 35760 x 2.5 GEO 91.9W+2.3E | |
| 1977 May 21 | 0701 | 1426.62 35438 x 35763 x 2.4 GEO 82.7W+2.3E | |
| 1977 Jun 12 | 1436.10 35779 x 35793 x 2.4 GEO 12.4W+0.0W | ||
| 1977 Nov 12 | 1436.10 35771 x 35801 x 2.0 GEO 11.9W | ||
| 1979 Jul 31 | 1436.11 35772 x 35801 x 0.8 GEO 12.8W | ||
| 1979 May 7 | TWTA fails, in storage | ||
| 1979 Aug 22 | 1436.05 35770 x 35801 x 0.8 GEO 12.5W | ||
| 1979 Aug | Move to 5W | ||
| 1979 Aug 28 | 1436.11 35774 x 35800 x 0.8 GEO 5.1W | ||
| 1979 Nov 30 | 1436.04 35765 x 35805 x 0.6 GEO 4.4W | ||
| 1979 Dec 12 | Mv out | ||
| 1980 Apr 1 | 1430.10 35554 x 35783 x 0.5 GEO 66.1+1.5E | ||
| 1980 Apr 30 | 1430.43 35569 x 35781 x 0.5 GEO 107.4E+1.4E | ||
| 1980 May 23 | mv in | 1436.15 35786 x 35789 x 0.5 GEO 139.4E | |
| 1980 Nov | removed from operational inventory | ||
| 1981 Mar 7 | 1435.97 35772 x 35795 x 0.9 GEO 140.1E | ||
| 1981 Dec 17 | 1436.07 35776 x35795 x 1.5 GEO 140.3E | ||
| 1981 Dec 20 | end of ops, mv out | 1489.56 36763 x 36890 x 1.5 | |
| 1985 Oct 23 | 1489.53 36740 x 36912 x 5.0 | ||
| 1991 Apr 9 | 1489.55 36753 x 36899 x 10.2 | ||
| 1999 Apr 16 | 1489.56 36757 x 36895 x 15.1 | ||
Monday, April 26, 2004
Kosmos 653
1974-031A
Kosmos-653 flew a 62.8 degree mission from Plesetsk. PDM telemetry and a TG recovery beacon were observed.
| Kosmos-653 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1974 May 15 | 1230 | Launch by 11A57 | NIIP-53 |
| 1234 | Blok-I burn | ||
| 1238 | Blok-I sep | ||
| 1974 May 16 | 0136 | 89.27 190 x 286 x 62.8 | |
| 1974 May 16 | 0930 | 89.27 192 x 287 x 62.8 (RAE) | |
| 1974 May 26 | 0649 | 89.07 186 x 270 x 62.8 | |
| 1974 May 27 | 0332? | Deorbit | |
| 0342? | PO sep | ||
| 0347? | Entry | ||
| 0404? | Landed after 11.65d | ||
Friday, April 23, 2004
ISEE 1/2
1977-102A
The ISEE A `Mother' satellite was one of a pair designed to study the magnetosphere. It was launched together with the European Space Agency's ISEE B `daughter' satellite on 1977 Oct 22 at 1353 by a Delta 2914 from Cape Canaveral and received the post launch name International Sun-Earth Explorer 1. The Delta delivered the satellites into a 337 x 137904 km x 29.0 deg orbit. The satellite was still operating when it reentered on 1987 Sep 26.
| ISEE 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 Oct 22 | 1353:00 | Launch by Delta 2914 | CC |
| T+0:38 SRM 1-6 out | |||
| T+0:39 SRM 7-9 on | |||
| T+1:18 SRM 7-9 out | |||
| T+1:27 SRM 1-9 sep | |||
| 1357? | T+3:45 Thor MECO at 91 km | ||
| T+3:54 Thor sep at 96 km | |||
| 1357? | T+3:56 Delta SES-1 4:48 at 99 km | ||
| T+4:56 Fairing 126 km | |||
| 1401:44 | T+8:44 Delta SECO-1 157 km | 157? x 285? x 28.8 | |
| 1446:31 | T+53:31 Delta SES-2 21s 285 km | ||
| 1446:52 | T+53:52 Delta SECO-2 | ||
| T+54:50 Spinup | |||
| 1447:52 | T+54:52 Delta sep | 95.84 276 x 842 x 28.74 | |
| 1448 | Delta perigee over 22S 115E from elset 1 | ||
| 1448:33 | T+55:33 TES | ||
| 1449:17 | T+56:17 TECO 287 km | ||
| 1450:30 | Stage 3 sep T+57:30 | ||
| 1455? | ISEE-B sep from ISEE-A | ||
| 1500 | Delta ascending node from elset 1 | ||
| 1504? | ISEE A perigee over 22S 115E from elset 1 | ||
| 1987 Sep 26 | 0640? | Reentry over Brazil 38W 7S? | |
International Sun-Earth Explorer 2, the ISEE B `Daughter' satellite, was built by STAR/Dornier-Freidrichsafen for the European Space Agency. It was launched on 1977 Oct 22 by a Delta 2914 from Cape Canaveral together with NASA's ISEE 1 satellite. The initial orbit was 341 x 137847 km x 29.0 deg. ISEE 2 was designed to measure magnetospheric and solar wind properties close in space and time to ISEE 1 for comparative purposes. In 1979 Oct its onboard thrusters were used to adjust the orbit and re-approach the ISEE 1 satellite. The perigee increased to a maximum of 3300 km around Jan 1980 and then decreased to 300 km or so around Mar 1982 before increasing again to a new maximum of over 6000 km in early 1985 and decreasing again until reentry. ISEE 2 was still transmitting when it reentered on 1987 Sep 26.
| ISEE 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 Oct 22 | Launch by Delta 2914 | CC | |
| 1977 Oct 28 | 3438.71 340 x 137837 x 29.0 | ||
| 1977 Nov 29 | 3442.61 780 x 137511 x 30.4 | ||
| 1978 Apr 9 | 3441.79 441 x 137826 x 37.1 | ||
| 1978 Aug 2 | 3439.08 1413 x 136775 x 41.2 | ||
| 1979 Jan 25 | 3439.05 2305 x 135882 x 47.1 | ||
| 1979 Mar 24 | 3439.18 1927 x 136263 x 49.5 | ||
| 1979 late | Maneuvers | ||
| 1979 Sep 1 | 3441.33 2669 x 135585 x 51.6 | ||
| 1980 Apr 10 | 3440.99 2664 x 135580 x 53.2 | ||
| 1980 Jun 28 | 3441.16 3284 x 134965 x 51.7 | ||
| 1982 Apr 3 | 3439.82 703 x 137506 x 37.3 | ||
| 1983 Apr 20 | 3440.40 1675 x 136552 x 27.4 | ||
| 1985 Jan 30 | 3440.93 6321 x 131921 x 31.1 | ||
| 1986 Jun 4 | 3439.83 3992 x 134218 x 27.5 | ||
| 1987 Sep 21 | 3438.78 224 x 137956 x 8.7 | ||
| 1977 Sep 26 | 0643? | Reentry over Brazil 44W 7S? | |
Thursday, April 22, 2004
Kosmos 2347
1997-079A
Kosmos-2337 continued the tradition of annual December US-P launches. It ended operations in late 1999 with no replacement. A small destruct event released 8 tracked objects. RCS was 23m2.
| Kosmos-2347 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Dec 9 | 0717 | Launch by 11K69 | KB LC90 |
| 0719 | Stage 1 sep | ||
| 0719 | Stage 2 burn | ||
| 0721 | Stage 2 sep | ||
| AKM burn | |||
| 0803? | Orbit insertion | 403 x 418 x 65.0 | |
| 1999 Nov 19 | 92.78 402 x 418 x 65.0 | ||
| 1999 Nov 19 | 2200? | End of mission burn | |
| 1999 Nov 20 | 91.43 278 x 410 x 65.0 | ||
| 1999 Nov 22 | 0440 | small destruct event | |
| 1999 Nov 30 | 90.11 211 x 347 x 65.0 | ||
Wednesday, April 21, 2004
Iridium 38
1997-069A
Delta Iridium MS-5 was launched on 1997 Nov 9, placing a further five satellites in orbit. The MS-5 launch returned to using the higher 625 x 642 km parking orbit, since the satellite was given a lighter fuel load, reducing mass to 662 kg.
Iridium SV038 raised its orbit in late November, but only reached the engineering orbit of 765 km instead of the operational orbit of 780 km. Its orbit was finally raised to operational height in Apr 1998.
| Iridium 38 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Nov 9 | 0134:26 | Launch by Delta | V SLC2 |
| 0135 | T+1:04 SRM burnout x 6 | ||
| 0135 | T+1:27 SRM sep | ||
| 0136 | T+2:09 SRM burnout x 3 | ||
| 0136 | T+2:11 SRM sep | ||
| 0138 | T+4:20 MECO | ||
| 0138 | T+4:34 St 2 TIG | ||
| 0138 | T+4:43 Fairing sep | ||
| 0145:39 | T+11:13 SECO1 | 170 x 647 x 86.4 | |
| 0232 | T+58:20 TIG 2 | ||
| 0232 | T+58:36 SECO2 | 639 x 639 x 86.6 | |
| 0236:56 | T+1:02:30 SV1 deploy | ||
| 0246:56 | T+1:12:30 SV2 deploy | ||
| 0251:06 | T+1:16:40 SV3 deploy | ||
| 0256:06 | T+1:21:40 SV4 deploy | ||
| 0259:26 | T+1:25:00 SV5 deploy | ||
| 0320 | T+1:45:50 Delta depletion | 254 x 627 x 83.56 | |
| 0320 | T+1:46:05 SECO3 | ||
| 1997 Nov 9 | 97.38 625 x 641 x 86.6 | ||
| 1997 Nov 12 | 97.40 626 x 642 x 86.6 | ||
| 1997 Nov 15 | 97.42 626 x 643 x 86.6 | ||
| 1997 Nov 20 | 98.82 699 x 705 x 86.5 | ||
| 1997 Nov 22 | 100.03 756 x 762 x 86.5 | ||
| 1997 Nov 23 | 100.22 766 x 770 x 86.4 | ||
| 1997 Nov 28 | 100.23 768 x 770 x 86.4 | ||
| 1998 Jan 6 | 100.24 768 x 771 x 86.4 | ||
| 1998 Jan 7 | 100.17 764 x 768 x 86.4 | ||
| 1998 Feb 4 | 100.19 765 x 769 x 86.4 | ||
| 1998 Apr 5 | 100.20 766 x 769 x 86.4 | ||
| 1998 Apr 25 | 100.39 775 x 778 x 86.4 | ||
Sunday, April 18, 2004
Friday, April 16, 2004
Meteosat 5
1991-015B
The second EUMETSAT MOP satellite, MOP 2/Meteosat 5, was launched in Mar 1991. On 1995 Dec 1, EUMETSAT took control of the spacecraft at its Darmstadt mission control center, taking over from the European Space Agency's ESOC site. In Jan 1998 Meteosat-5 was replaced by Meteosat 7 and began drifting to the Indian Ocean to participate in the Indoex program at 67E, studying cloud formation and atmospheric pollution in an international experiment.
| Meteosat 5 (MOP 2) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Mar 2 | 2336:00 | Launch by Ariane 44LP | CSG ELA2 |
| T+1:06 PAP sep | |||
| T+2:29 PAL sep | |||
| T+3:32 St 1 sep | |||
| T+3:35 St 2 MES | |||
| 2340 | T+4:33 Fairing sep | ||
| 2341 | T+5:43 St 2 sep | ||
| 2341 | T+5:46 St 3 MES | ||
| 2353:47 | T+17:47 St 3 MECO | 640.93 240 x 36252 x 7.1 | |
| 2356:11 | T+20:11 Astra 1B sep | ||
| 2358:39 | T+22:39 Spelda sep | ||
| 1991 Mar 3 | 0000:35 | T+24:35 MOP 2 sep | |
| 1991 Mar 3 | 0021:00 | T+45m spinup, 40 kg fuel; 682 kg total | |
| 0250:00 | Sun angle correction | ||
| 0345 | Attitude slew 1 | ||
| 1210 | Attitude slew 2 | ||
| 1434:14 | Attitude slew 3 | ||
| 1991 Mar 4 | 632.57 194 x 35869 x 7.05 | ||
| 1991 Mar 4 | 1334:12 | MAGE 1 burn | |
| 1339 | MAGE 1 eject | ||
| 1410 | Spin axis erection; mass 322.1 kg | ||
| 1991 Mar 4 | 1424.84 35146 x 35985 x 1.2 GEO 32.1W+2.8E | ||
| 1991 Mar 5 | 0105:42 | Drift correction 4.9m/s | |
| 1991 Mar 5 | 1200 | Control to payload commissioning | 1431.52 35413 x 35980 x 1.20 GEO 29.5W-1.1/d |
| 1991 Mar 7 | 1000 | 1431.65 35413 x 35985 x 1.20 GEO 27.9W-1.1/d | |
| 1991 Mar 23 | 1435.66 35767 x 35788 x 1.2 GEO 4.3W | ||
| 1991 Mar 29 | 1435.79 35770 x 35791 x 1.2 GEO 3.9W | ||
| 1991 Apr | mv to 1W | ||
| 1991 Apr 3 | Radiometer baffle cover ejected | ||
| Radiometer cooler cover ejected | |||
| 1125 | First image | ||
| 1991 May 1 | 1435.72 35771 x 35786 x 1.1 GEO 1.0W | ||
| 1991 May 24 | moving to 4W | ||
| 1991 Jun 4 | 1436.53 35784 x 35805 x 1.0 GEO 3.9W | ||
| 1991 Oct 22 | 1436.08 35777 x 35795 x 0.8 GEO 4.0W | ||
| 1992 Jan 14 | Ownership to EUMETSAT | ||
| 1992 Jul 12 | 1436.04 35777 x 35793 x 0.6 GEO 3.9W | ||
| 1992 Aug 3 | 1435.87 35778x 35786 x 0.2 GEO 3.6W+0.05E | ||
| 1992 Aug | Move to 1W | ||
| 1992 Sep 7 | 1435.75 35771 x 35788 x 0.2 GEO 0.8W | ||
| 1992 Nov 6 | 1436.45 35786 x 35800 x 0.1 GEO 0.8W | ||
| 1992 Nov | Move out, drift to 8W? | ||
| 1992 Nov 20 | 1436.33 35782 x 35799 x 0.1 GEO 3.6W+0.06W | ||
| 1993 Feb 9 | 1436.23 35782 x 35796 x 0.2 GEO 6.7W+0.04W | ||
| 1993 Jun 29 | 1436.19 35785 x 35791 x 0.2 GEO 7.3W+0.03W | ||
| 1993 Sep 3 | 1436.10 35781 x 35792 x 0.2 GEO 7.8W | ||
| 1993 Sep 24 | 1436.09 35781 x 35791 x 0.2 GEO 7.7W | ||
| 1993 Oct | Move to 0E | ||
| 1993 Oct 29 | 1436.02 35757 x 35812 x 0.3 GEO 0.5E | ||
| 1993 Nov 18 | 1436.22 35784 x 35793 x 0.3 GEO 0.3W | ||
| 1994 Apr 5 | 1436.05 35779 x 35792 x 0.2 GEO 1.2W | ||
| 1994 Jul 24 | 1436.12 35779 x 35794 x 0.3 GEO 0.1E | ||
| 1995 Jan 28 | 1436.24 35783 x 35794 x 0.1 GEO 1.0W | ||
| 1995 Dec 1 | Control to EUMETSAT-Darmstadt | ||
| 1996 Apr 14 | 1436.19 35781 x 35795 x 0.4 GEO 0.2E | ||
| 1997 Mar 13 | 1436.84 35789 x 35814 x 1.1 GEO 1.6E | ||
| 1997 Mar 15 | GEO mv out | GEO 0E | |
| 1997 May 18 | mv in | ||
| 1997 May 22 | 1436.07 35782 x 35780 x 1.2 GEO 9.7W | ||
| 1998 Jan 13 | 1436.07 35768 x 35803 x 1.7 GEO 9.2W | ||
| 1998 Jan 18 | mv out | ||
| 1998 May 19 | mv in | GEO | |
| 1998 Jun 23 | 1436.00 35756 x 35812 x 2.0 GEO 63.4E | ||
| 1998 Jul 1 | Start Indoex data | ||
| 1998 Nov 30 | 1435.98 35779 x 35789 x 2.3 GEO 63.3E | ||
| 1999 Jun 15 | 1436.04 35758 x 35812 x 2.8 GEO 62.5E | ||
| 2003 Aug 26 | 1436.11 35779 x 35793 x 6.1 GEO 62.8E | ||
Wednesday, April 14, 2004
Raduga 28
1991-087A
Raduga No. 39 was launched in Dec 1991. In Feb 2000 the satellite began to drift. Orbital data indicates that after it made a natural oscillation around the 35-40E region, a significant maneuver in Jan 2001 moved it back to 35E to begin another loop. Alternatively, this may represent a misidentification of the satellite.
| Raduga No. 39 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Dec 19 | 1141 | Launch by Proton-K | KB LC81L |
| 1150 | Stage 3 sep | ||
| 1258? | T+1:17 DM burn 1 | 296 x 36493 x 47.3 | |
| 1813? | T+6:33? DM burn 2 | ||
| 1817? | T+6:37? DM sep | ||
| 1991 Dec 19 | 1472.70 36434 x 36565 x 1.5 GEO 93.3E+8.9W | ||
| 1992 Jan 14 | 1436.42 35760 x 35825 x 1.5 GEO 34.1E+0.1W | ||
| 1992 Mar 11 | 1436.41 35773 x 35812 x 1.3 GEO 35.6E+0.1W | ||
| 1992 Jun 17 | 1436.30 35779 x 35801 x 1.1 GEO 34.9E | ||
| 1993 Oct 29 | 1436.18 35776 x 35799 x 0.1 GEO 34.5E | ||
| 1995 Feb 4 | 1436.26 35787 x 35792 x 1.1 GEO 34.6E | ||
| 1997 May 26 | 1435.93 35777 x 35789 x 2.8 GEO 34.9E | ||
| 1999 Mar 3 | 1435.86 35772 x 35791 x 4.0 GEO 35.4E | ||
| 1999 Mar 8 | mv out | ||
| 1999 Apr 1 | mv in | 1436.15 35765 x 35810 x 4.1 GEO 44.8E | |
| 1999 Jun 11 | 1436.09 35770 x 35803 x 4.2 GEO 45.1E | ||
| 2000 Feb | Begin drift | 1435.88 35763 x 35801 x 4.7 GEO 45.2E | |
| 2000 Mar 15 | 1437.04 35795 x 35814 x 4.7 | ||
| 2001 Jan 9 | mv out | 1434.97 35723 x 35805 x 5.3 GEO 52.0E dr | |
| 2001 Jan 15 | 1440.76 35749 x 36005 x 5.3 GEO 36E+1.2W | ||
| 2001 Jan 27 | mv in | 1436.29 35755 x 35825 x 5.4 GEO 31.0E | |
| 2001 Jun 7 | 1435.39 35743 x 35801 x 5.6 GEO 39.0E dr | ||
| 2003 Sep 4 | 1435.94 35760 x 35806 x 7.2 GEO 30.7E dr | ||
Monday, April 12, 2004
Sunday, April 11, 2004
Kosmos 613
1973-096A
7K-T 11F615A8 No. 34A was the third test flight of the stripped-down Soyuz ferry. It flew a 60 day long duration test to confirm that the systems would survive an extended stay powered down while docked to a DOS or Almaz station. The orbital module was jettisoned prior to retrofire and remained in orbit until 1974 Mar 9.
| Kosmos-613 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1973 Nov 30 | 0520 | Launch by Soyuz 11A511 | KB |
| 0524 | Blok-I burn | ||
| 0529 | Blok-I sep | ||
| 1430 | 89.04 187 x 268 x 51.61 | ||
| 1973 Dec 1 | 0230 | 89.11 188 x 273 x 51.60 | |
| 1973 Dec 3 | 88.97 185 x 263 x 51.60 | ||
| Orbit raise | |||
| 1973 Dec 3 | 0930 | 89.26 200 x 277 x 51.6 | |
| 1973 Dec 5 | 89.10 201 x 259 x 51.6 | ||
| 1200? | Orbit raise | 91.06 253 x 400 x 51.62 | |
| 1974 Jan 11 | 90.78 250 x 377 x 51.59 | ||
| 1974 Jan 28 | 0930 | 90.58 239 x 366 x 51.59 | |
| 1974 Jan 29 | |||
| 0340? | Orbital module sep 96C | ||
| 0458? | Rev 953/TLE24: Node 2E good opp | ||
| 0449? | Retrofire | ||
| 0452? | DO CO | ||
| 0507? | PAO sep? | ||
| 0513? | Entry | ||
| 0536? | Landed after 60.1d | ||
Saturn S-IVB-507
1969-099B
SA-507 was launched on 1969 Nov 14 at 1622. The TLI burn was at 1909, and Apollo 12 separated at 2035. The propellants were dumped and the stage flew past the Moon at 5724 km on 1969 Nov 18 at 0610. A trajectory error left S-IVB-507 in a 165000 x 850000 km Earth orbit instead of the intended solar orbit.
The closest apporach of 5715 km above the lunar surface was not close enough to accelerate the stage to escape; an inaccurate state vector meant that the commanded ullage burn was too long. The flyby increased the geocentric speed of the stage by 0.548 km/s.
| S-4B-507 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1969 Nov 14 | 1622:00 | Range zero | |
| 1622:00 | Launch by Saturn V (SA-507) | KSC LC39A | |
| 1622:36 | Lightning strike on SA-507, 1.95 km alt | ||
| 1622:52 | Second small lightning strike | ||
| 1624:15 | S-IC CECO | ||
| 1624:42 | S-IC OECO, sep | -6009 x 123 x 32.1 | |
| 1624:44 | S-II ignition | ||
| 1625:12 | Interstage | ||
| 1625:18 | LES jett | ||
| 1629:41 | S-II CECO | ||
| 1631:12 | S-II OECO | ||
| 1631:13 | S-II sep | -2011 x 191 x 32.70 | |
| 1631:14 | T+9:14 SIC impact 30.27N 73.90W | ||
| 1631:16 | S-IVB ignition | ||
| 1631:25 | Ullage case sep | ||
| 1631:41 | T+9:41 S-II apogee | ||
| 1633:34 | S-IVB shutdown | ||
| 1633:44 | Earth orbit insertion | 88.2 181 x 185 x 32.54 | |
| 1642:21 | T+20:21 S-II impact 31.47N 34.21W | ||
| 1909:25 | S-IVB TLI burn | ||
| 1915:04 | S-IVB cutoff | ||
| 1915:14 | Translunar injection | 215 x 409386 x 30.360 | |
| 215 x 409138 x 30.36 | |||
| 215 x 428571 x 30.36 | |||
| V tab 4.6 | 215 x 428200 x 30.36 | ||
| C3 tab 4.6 | 1940:05 | Sep from S-IVB/SLA | 219 x 424147 x 30.42 |
| Transposition and docking maneuver | |||
| 1948:53 | Docked with LM/S-IVB | ||
| 2035:01 | CSM/LM sep from S-IVB | ||
| 2048:40 | APS evasive 2.9m/s | ||
| 2058:20 | CVS LH2 vent 2.8m/s | ||
| 2110:00 | LOX dump 10.0 | ||
| 2110:58 | LOX dump end | ||
| 2112:07 | LH2 NPV | ||
| APS-1 11.8m/s 300s | |||
| APS-2 10.7m/s 270s | |||
| 2150:20 | APS burn end | ||
| 1969 Nov 17 | 1344 | Enter lunar sphere 66183 km | |
| 1969 Nov 18 | 0610 | Lunar flyby | 5709 x -19546 x 20.43 |
| Trailing edge, 7000 km | |||
| 1969 Nov 18 | 2236 | Depart lunar sphere 66183 km | |
| 1969 Dec | 150000-176000 x 830000-890000 | ||
| 1969 Dec | 165000 x 850000 | ||
| 1971 Mar? | Escape via L1 | ||
| 2002 Apr | Capture via L1 | ||
| 2002 | Detected as J002E3 | ||
| 2002 Jun 12 | 1358 TDB | 160967 km from Moon | |
| 2002 Jun 15 | 1957 | 193878 km perigee | |
| 2002 Aug 9 | 0752 | 238608 km from Moon | |
| 2002 Aug 11 | 0250 | 365916 km perigee | |
| 2002 Aug 21 | 2119 | 252222 km from Moon | |
| 2002 Sep 28 | 1402 | 232175 km perigee | |
| 2002 Dec 16 | 144062 km perigee | ||
| 2003 Jun 19 | 0100 | Depart Earth sphere via L1 | |
Saturday, April 10, 2004
Ranger 6
1964-007A
The first Block III Ranger, Ranger VI (Ranger A, P-53) was launched at 1549:09 on 1964 Jan 30 by Atlas Agena B from Canaveral on a 95.0 deg azimuth. The fairing was jettisoned at 1554:15, the Atlas separated at 1554:19, and the Agena ignited at 1555:00. After a coast period the Agena reignited at 1616:27 for translunar injection. Ranger VI separated at 1619:23 and the Agena made a retro maneuver at 1626:09. Ranger VI made a course correction at 0857 on Jan 31, when the range to Earth was 170130 km. However the cameras failed the same day, and although the 368 kg probe impacted the lunar surface at 0924:33 on Feb 2, at 9.33N 21.52E, pictures weren’t returned.
According to the JPL mission report, the Agena flew past the lunar trailing edge at 3630 km and entered a 383.7 day heliocentric orbit.
The lunar impact trajectory was at 8.656 km/s at -48.49 deg, corresponding to a -608 x -3007 x 19.80 deg selenocentric orbit.
| Ranger 6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1964 Jan 30 | 1549:09 | Launch by Atlas Agena B | CKAFS LC12 |
| T+2:16 BECO | |||
| 1550:16 | Cameras failed, arcing | ||
| 1553:57 | T+4:48 SECO | ||
| 1554:13 | T+5:04 VECO | ||
| 1554:15 | T+5:06 Fairing sep | ||
| 1554:17 | T+5:08 Atlas sep | ||
| 1555:01 | T+5:52 Agena burn | ||
| 1557:33 | T+8:24 Agena MECO-1 | 185 x 185 x 28.5 | |
| 1615:19 | T+26:10 Agena MES-2 | ||
| 1616:45 | T+27:36 Agena MECO-2 | ||
| 1619:23 | T+30:14 Agena sep | ||
| 1626:09 | Agena solid retro 13.7 m/s | ||
| 1650:06 | Solar panels extended | ||
| 1701:00 | Agena last data at 12400 km | ||
| 1964 Jan 31 | 0857:09 | MCC 67s 41.3m/s | |
| 0858:16 | MCC off | ||
| 1964 Feb 2 | 0924:33 | Lunar impact | |
Luna 22
1974-037A
Like Luna-19, Luna-22 (E-8LS No. 206) was a modified Lunokhod-based lunar orbiter.
| Luna-22 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1974 May 29 | 0856:51 | Launch by Proton-K | KB |
| 0906 | Stage 3 sep | ||
| 0910? | Blok D burn | ||
| 0912? | Blok D MECO-1 | ||
| 0932 | Desc node | ||
| 1014? | Blok D MES-2 | ||
| 1017 | Asc node | ||
| 1020? | Blok D MECO-2, TLI | ||
| 1974 May 30 | TCM | ||
| 1974 Jun 2 | Lunar orbit insertion | 220 x 220 x 19.7 | |
| 1974 Jun 9 | TV survey | 25 x 244 x 19.7 | |
| 1974 Jun 13 | TCM | 131.5 194 x 285 x 19.7 | |
| 1974 Aug 26 | 131.6 234 x 246 x 19.6 | ||
| 1974 Nov 11 | TCM | 191.8 171 x 1438 x 19.3 | |
| 1975 Jan 7 | 191.8 172 x 1438 x 19.3 | ||
| 1975 May 8 | 191.8 193 x 1415 x 19.9 | ||
| 1975 Aug 24 | TCM for TV tests | 30 x 1400 x 19 | |
| 1975 Aug 26 | TCM | 180.0 100 x 1286 x 21 | |