https://web.archive.org/web/20070807073255/http://digest-archive.degrassi.ca/DD145.htm
Saturday, December 29, 2007
Wednesday, December 26, 2007
Astra 2D
2000-081A
BSS 376HP at 28.2E. Launch 2000 late. Launch mass 1414 kg. Size 8m high 2.2m dia.
The V138 Ariane 5G had EPS, ASAP-5/LDREX, ACU/GE-5, SYLDA, Astra 2D.
Astra 2D will serve the British Isles.
Assume that the apogee burn was Dec 23 0800 over 42E. In 5.4 days it had moved to 24E, so -3.3 deg/d. Simulate a burn at Dec 28 0800 over 24.7E to 3.46deg/d: 6m/s does the trick. Get good agreement with transfer orbit. However, a late transfer orbit elset on Dec 30 suggests the possibility of an apogee burn at that time.
| Astra 2D | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Dec 20 | 0026 | Launch by Ariane 5 | CSG ELA3 |
| T+2:40 EAP sep | |||
| T+3:24 Fairing sep | |||
| 0036 | T+10:06 EPC cutoff | ||
| 0036 | T+10:12 EPC sep | 59 x 1839 x 6.6 | |
| 0036 | T+10:27 EPS MES | ||
| 0052 | T+26:55 EPS MECO | ||
| 0054 | T+28:44 Astra 2D sep | ||
| 0057 | T+31:20 Sylda 5 sep | ||
| 0100 | T+34:40 GE-8 sep | ||
| 0106 | T+40:15 LDREX deploy | ||
| 0130 | T+1:04:37 LDREX sep | ||
| 0210? | EPC reentry | ||
| 2000 Dec 20 | 630.58 185 x 35775 x 2.0 | ||
| 2000 Dec 21 | 1838? | Orbit raise | |
| 2000 Dec 22 | 633.82 292 x 35835 x 2.2 | ||
| 2000 Dec 23 | 0800? | AKM | |
| 2000 Dec 28 | 1441.44 35886 x 35895 x 0.3 GEO 24.1E | ||
| 2000 Dec 30 | 0900? | late possible AKM | |
| 2000 Dec 31 | 1436.22 35763 x 35814 x 0.3 GEO 24.0E | ||
| 2001 Jan 18 | 1434.18 35744 x 35753 x 0.1 GEO 26.7E+0.5E | ||
| 2001 Mar 17 | 1436.05 35732 x 35838 x 0.1 GEO 28.1E | ||
| 2006 Jul 28 | 1436.16 35770 x 35804 x 0.1 GEO 28.2E | ||
Tuesday, December 25, 2007
Monday, December 24, 2007
Sunday, December 23, 2007
Saturday, December 22, 2007
Intelsat 804
1997-083A
Intelsat 804 was launched to the IOR position, covering Asia, Europe and Africa. Mass is 3455 kg launch, 2079 kg BOL, 1601 kg dry. The bus is 2.5 x 2.2 x 5.2 m with 10.8m solar panel span. Location was be 64 E (IOR); it was moved to the Pacific 176E location in 2002 and then to the 174E location (replacing I-802) in 2004.
| Intelsat 804 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Dec 22 | 0017 | Launch by Ariane 42L (V104) | |
| 0019 | T+02:36 PAL sep | ||
| 0020 | T+03:23 St 1 sep | ||
| 0021 | T+04:13 Fairing sep | ||
| 0022 | T+05:41 St 2 sep | ||
| 0022 | T+05:50 St 3 burn | ||
| 0035 | T+18:51 St 3 cutoff | ||
| 0037 | T+20:46 St 3 sep | ||
| 0040 | T+23:41 St 3 depletion | ||
| 1997 Dec 22 | 631.81 363 x 35760 x 7.0 | ||
| 1997 Dec 23?? | LAM-1 | ||
| 1997 Dec 25?? | LAM-2 | ||
| 1997 Dec 29 | 1436.11 35767 x 35805 x 0.1 GEO 47.0E | ||
| 1998 Jan 21 | 1435.93 35776 x 35789 x 0.1 GEO 47.0E | ||
| 1998 Jan 25 | mv out | ||
| 1998 Feb 3 | mv in | 1436.11 35774 x 35798 x 0.1 GEO 64.1E | |
| 1999 Oct 17 | 1436.07 35767 x 35804 x 0.0 GEO 64.1E | ||
| 2002 Oct 19 | 1436.07 35771 x 35800 x 0.0 GEO 64.1E | ||
| 2002 Oct | Move to Pacific | ||
| 2002 Dec 4 | 1436.08 35772 x 35799 x 0.1 GEO 176.0E | ||
| 2004 Aug 3 | mv out | 1436.10 35768 x 35804 x 0.1 GEO 176.0E | |
| 2004 Aug 27 | 1436.09 35771 x 35801 x 0.0 GEO 174.0E | ||
Thursday, December 20, 2007
USA-114
1995-057A
UHF F6, the third UHF F/O Block II satellite, was launched by Atlas II from Cape Canaveral on 1995 Oct 22. It had a launch mass of 3017 kg and was stationed at 100W, replacing Leasat 3.
| UHF F/O F6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 Oct 22 | 0800:02 | Launch by Atlas II (AC-119) | |
| 0802 | BECO | ||
| 0802 | Booster sep | ||
| 0803 | Fairing sep | ||
| 0804 | SECO | ||
| 0804 | Atlas sep | ||
| 0805 | Centaur AC-119 MES1 | ||
| 0811 | Centaur AC-119 MECO1 | ||
| 0822? | Centaur AC-119 MES2 | ||
| 0824? | Centaur AC-119 MECO2 | ||
| 0827? | Centaur AC-119 sep | 551.9 320 x 31500 x 27.0 | |
| 0845? | Centaur AC-119 depletion | 478.1 267 x 27483 x 27.0 (AC-119) | |
| 1995 Oct 22 | 482.12 276 x 27701 x 27.0 | ||
| 1995 Oct 23 | 1630? | LAM-1 perigee | |
| 1995 Oct 23 | 551.94 320 x 31500 x 27.0 | ||
| 1995 Oct 25 | 0100? | LAM-2 apogee | |
| 1995 Oct 25 | 798.58 7657 x 36612 x 14.6 | ||
| 1995 Oct 26 | 1630? | LAM-3 | |
| 1995 Oct 27 | 1151.13 23391 x 36620 x 7.3 | ||
| 1995 Oct 28 | 0630? | LAM-4 | |
| 1995 Oct 28 | 1411.73 34033 x 36583 x 5.3 | ||
| 1995 Oct 29 | 0800? | LAM-5 | |
| 1995 Oct 29 | 1430.25 34761 x 36583 x 5.3 GEO 170.4W+1.4E | ||
| 1995 Nov 6 | 1436.02 34984 x 36585 x 5.1 GEO 171.4W | ||
| 1995 Nov 22 | 1435.98 34979 x 36589 x 5.1 GEO 172.1W | ||
| 1995 Nov 27 | mv out | ||
| 1995 Dec 18 | 1436.05 35773 x 35798 x 5.0 GEO 105.3W | ||
| 1996 Apr 14 | 1436.09 35773 x 35799 x 4.9 GEO 105.4W | ||
| 1998 Jan 29 | 1436.12 35776 x 35797 x 4.2 GEO 104.7W | ||
| 1999 Jul 29 | 1436.09 35774 x 35798 x 3.5 GEO 105.9W | ||
| 2005 May 12 | 1436.12 35771 x 35802 x 9.0 GEO 104.5W | ||
Wednesday, December 19, 2007
Progress M-59
2007-002A
PM-59 11A615A55 No 359 Soyuz U, flight 24P. Mass 7274 kg. Cargo 2561 kg, 1390 in GO.
| PM59 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Jan 18 | 0212:15 | Launch by Soyuz-U No. Ts15000-107 | |
| 0220:58 | T+8:45 Blok-I MECO | ||
| 0221:04 | T+8:49 Blok-I Sep | ||
| 0610:18 | DV1 11.8m/s | ||
| 0640:27 | DV2 13m/s | ||
| 2007 Jan 19 | 0257:08 | DV3 1.0m/s | |
| 2007 Jan 20 | 0102:06 | DV4 22m/s | |
| 0125:21 | DV 0.8m/s | ||
| 0146:16 | DV 17.6m/s | ||
| 0227:43 | DV 7.1m/s | ||
| 0232:41 | DV 5.0m/s 2.6km range | ||
| 0235:11 | DV 2.2m/s 1.0km range | ||
| 0236 | Begin flyaround | ||
| 0244 | Complete flyaround at 170m | ||
| 0250 | Approach | ||
| 0258:53 | Docked with Pirs | ||
| 2007 Aug 1 | 1407:05 | Undocked from Pirs | |
| 1842 | Deorbit burn | ||
| 1927 | Impact in Pacific | ||
Saturday, December 15, 2007
Monday, December 10, 2007
Spaceway 1
2005-015A
DirecTV (formerly Hughes Network Systems) Ka-band Spaceway constellation will have 8 satellites covering N America (101W, two), Latin and South America (49W, two), Europe-Africa-Middle East (25E, two), and Asia-Pacific (111E, two). Also reservations at 99W 54E 101E and 164E.
F1 is BSS 702 satellite at 102.8W. Launch 2005 for in-orbit delivery by Zenit-3SL.
Mass 6080 kg (or 6067 kg or 5993 kg) at launch, 3832 kg BOL, 3691 EOL. Size is 3.2 x 3.4 x 5.1m with 40.9m span.
After launch, the satellite reached GEO height very slowly - presumably using XIPS.
| Spaceway | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2005 Apr 26 | 0731:29 | Launch by Zenit-3SL No. 15 | |
| T+2:30 St 1 sep 70 km | |||
| T+3:52 Fairing sep 118 km | |||
| T+8:31 St 2 sep | -2339 x 198 x 0 | ||
| 0740:09 | T+8:40 DM-SL MES-1 | ||
| 0751:49 | T+20:20 MECO-1 | 246 x 34290 x 0 | |
| 0801:35 | T+30:10 DM sep | ||
| 2005 Apr 26 | 599.73 261 x 34097 x 0.02 | ||
| 2005 Apr 28 | Perigee raise | 619.18 1061 x 34311 x 0.36 | |
| 2005 Apr 30 | Apogee raise | 680.44 1068 x 37247 x 0.41 | |
| 2005 May 1 | Apogee raise | 744.18 1070 x 40578 x 0.34 | |
| 2005 May 2 | Apogee raise | 846.89 1068 x 45478 x 0.4 | |
| 2005 May 4 | Perigee raise | 922.00 4493 x 45509 x 0.3 | |
| 2005 May 6 | Perigee raise | 1057.90 10507 x 45519 x 0.13 | |
| 2005 May 7 | Perigee raise | 1312.52 21197 x 45465 x 0.13 | |
| 2005 May 9 | 1900? | 1418.88 25415 x 45482 x 0.25 | |
| 2005 May 11 | 1435.16 26062 x 45473 x 0.23 | ||
| 2005 May 12 | 1436.05 26097 x 45474 x 0.26 | ||
| 2005 May 24 | 1440.11 26911 x 44818 x 0.23 | ||
| 2005 Jun 1 | 1435.81 28119 x 43442 x 0.3 | ||
| 2005 Jul 12 | 1435.93 33226 x 38340 x 0.2 | ||
| 2005 Jul 31 | 1436.12 35784 x 35789 x 0.1 GEO 102.8W | ||
Wednesday, November 28, 2007
DemoFlight 2
2007-F02
Falcon 1 Demo Flight 2, with payload carrying AFSS (Autonomous Flight Safety System) and LCT2.
LCT2 (Low Cost TDRSS Transceiver) is a low-cost transceiver for launch vehicles that would allow them to relay telemetry to the ground through the agency's TDRS satellites. The current goal of the LCT2 effort is to produce a transceiver that will significantly lower the flight hardware costs required to communicate through NASA's Tracking and Data Relay Satellite System (TDRSS) and will meet the suborbital and orbital launch vehicle needs for Space Based Range Communications (SBRC).
AFSS (Autonomous Flight Safety System) is a real-time onboard hardware and software system for tracking and possible flight termination. AFSS is designed primarily for small expendable vehicles at remote launch sites where providing traditional ground-based range safety infrastructure, including radio frequency (RF) communication and command links, radar stations, data processing, display facilities, and trained operators, would be extremely expensive. Advantages of using AFSS include global coverage and decreased costs during remote launch site operations.
Remains attached to Falcon stage 2 (although one report claimed it separated).
Planned orbit 330 x 684 km x 9 deg. Actual velocity 5.1 km/s and apo 289 km.
Slosh instability in second stage caused the launch to fail - it was addressed with baffles in later missions.
| F2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Mar 21 | 0110 | Launch from Omelek | |
| T+2:50? Stage 1 sep | |||
| T+2:55? Stage 2 burn, planned 6.5min | |||
| T+3:20 Fairing | |||
| T+4:25 Oscillation in control system | |||
| Oscillation grows with time | |||
| T+7:54 Stage 2 cutoff | |||
| Stage 2 sep from payload? 5.1 km/s | -4200? x 289 x 9 | ||
| Payload and stage 2 reentry | |||
Monday, November 19, 2007
Sunday, November 18, 2007
Gorizont 28
1993-069A
In 1998 Gorizont No. 40 was reportedly subleased to Lockheed Martin Global Telecommunications and moved to a Tongasat slot,however an orbital move was not made. This is probably a misreporting of the Gorizont 41 sale. It was in service in 2000 as a GPKS satellite.
| Gorizont No. 40 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1993 Oct 28 | 1517:00 | Launch by Proton-K | KB |
| Stage 2 burn | |||
| Stage 3 burn | |||
| 1526 | Stage 3 sep | 179 x 197 x 51.7 | |
| 1634? | DM burn 1 | 233 x 35782 x 47.3 | |
| 2150? | DM burn 2 | ||
| 2154? | Blok-DM No. 72L sep | ||
| 1993 Oct 29 | 1435.33 35753 x 35789 x 1.5 GEO 90.6E+0.2E | ||
| 1993 Nov 9 | 1435.94 35765 x 35802 x 1.4 GEO 89.8E | ||
| 1993 Dec 16 | 1436.11 35770 x 35803 x 1.4 GEO 90.4E | ||
| 1994 Jul 15 | 1436.03 35778 x 35791 x 0.9 GEO 90.4E | ||
| 1995 Sep 8 | 1436.00 35777 x 35791 x 0.2 GEO 90.0E | ||
| 1997 Feb 28 | 1436.23 35777 x 35800 x 1.1 GEO 89.6E | ||
| 1999 Oct 18 | 1436.10 35778 x 35795 x 3.0 GEO 90.2E | ||
| 2000 Apr 19 | 1436.04 35775 x 35795 x 3.4 GEO 90.2E | ||
| 2000 May | Move to 96E | ||
| 2000 May 9 | 1435.99 35760 x 35808 x 3.4 GEO 96.7E | ||
| 2004 Oct 19 | 1436.19 35779 x 35796 x 7.0 GEO 96.3E | ||
| 2004 Oct 28 | mv out | ||
| 2004 Oct 28 | mv in | ||
| 2004 Dec 30 | 1435.97 35779 x 35788 x 7.1 GEO 102.5E | ||
| 2006 Aug 4 | 1436.06 35780 x 35791 x 8.5 GEO 103.0E | ||
| 2006 Sep 28 | Depart 103E | ||
| 2006 Oct | Move to 126E | ||
| 2006 Nov 10 | 1436.20 35780 x 35796 x 8.7 GEO 126.2E | ||
Wednesday, November 14, 2007
Kosmos 2431
2007-052A
Satellite block 36, Glonass-M 18,19,20 as Kosmos-2431/2432/2433 were launched in Oct 2007. Launch by Proton K No 41017 and Blok DM2 11S861 No 110L.
| Kosmos-2431 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Oct 26 | 0735:24 | Launch by Proton 41017 | KB PL81/24 |
| 0737:31 | Stage 1 sep | ||
| 0738:42 | Fairing sep | ||
| 0741:02 | Stage 2 sep | ||
| 0745:04 | Stage 3 MECO | ||
| 0745:17 | Stage 3 sep | ||
| 94 x 131 x 64.8 | |||
| 0812:03 | T+36:39 DM 11S861 No 110L MES-1 | ||
| 0817:49 | DM MECO-1 | 401 x 19130 x 64.9 | |
| 1104:47 | DM MES-2 | ||
| 1107:10 | DM MECO-2 | ||
| 1107:25 | GLONASS sats sep from DM | ||
Saturday, November 10, 2007
Thursday, November 8, 2007
Navstar 26
1992-039A
Navstar SVN 26 (USA 83) was launched on 1992 Jul 7 and became operational in plane F-2 on Jul 23.
| Navstar 26 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Jul 7 | 0920:01 | Launch by Delta 7925 | CC LC17B |
| SRM 1-9 sep | |||
| St 1 sep | |||
| 0924 | T+4:40? SES-1 | ||
| 0931 | T+11:00? SECO-1 | 185 x 185 x 34? | |
| T+20? SES-2 36s? | |||
| 0940 | T+20? SECO-2 | 180? x 728? x 34.0? | |
| 0941 | T+21? St 2 sep | ||
| 0942 | T+22? TES 1:24 | ||
| 0943 | T+23? TECO | ||
| 0945 | T+25? St 3 sep | 186 x 20459 x 34.76 | |
| 1024? | T+1:04 SES-3 depletion | 564 x 728 x 20.72 | |
| 1992 Jul 10 | 0030? | Star 37XFP burn | |
| 1992 Jul 23 | In service | ||
| 1992 Jul 24 | 717.95 19959 x 20403 x 55.0 | ||
| 1995 Mar 15 | 718.03 19933 x 20434 x 54.86 | ||
| 1997 Feb 1 | Operating at slot F-2 | ||
| 2005 May | Operating at F-2 | ||
Progress M-58
2006-045A
PM-58 11F615A55 No. 358. 7320 kg launch. Flight 23P.
Launch by Soyuz-U No. 102. It soft-docked with the Zvezda module at 1429 UTC on Oct 26. However there were indications that the Kurs rendezvous orientation antenna mounted on the docking ring at the forward end of the Progress did not retract correctly. The Station remained in free drift for several hours; eventually it was decided that the antenna was fine, the latches between Progress and Zvezda were driven closed at around 1806 UTC, and the Station resumed active attitude control.
Launch mass 7093 kg. Probably carried BTN-M1 experiment. Cargo 2394 kg, with 16 kg of EVA accounted cargo.
| PM58 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2006 Oct 23 | 1340:36 | Launch by Soyuz-U | KB |
| T+1:58 Strapons sep | |||
| T+2:42 Fairing sep | |||
| T+4:45 Blok A MECO | |||
| T+4:47 Blok-A sep | |||
| T+4:57 KhO sep | |||
| T+8:46 Blok-I MECO | |||
| 1349:25 | T+8:49 Blok-I sep | ||
| 1731:37 | DV1 15.7m/s 39s | ||
| 1756:33 | DV2 2.2m/s 6s | ||
| 2006 Oct 25 | 1419:54 | DV3 7.0s 0.5m/s | |
| 2006 Oct 26 | 1232:04 | DV4 14.9m/s | |
| 1256:20 | DV5 1m/s | ||
| 1317:42 | DV6 33.6m/s | ||
| 1358:38 | TCM 8.4m/s | ||
| 1404:49 | TCM 4m/s | ||
| 1407:12 | TCM 2.5m/s | ||
| 1408 | At 400m from ISS and begin flyaround | ||
| 1419 | Begin approach to Zvezda from 190m | ||
| 1429:18 | Soft docked with Zvezda | ||
| 2AO-VKA antenna fouled SM | |||
| 1801 | Hard docked | ||
| 2006 Nov 29 | 2305 | TCM; aborted after 3:16; 0.50m/s, 1 km | |
| 2006 Dec 4 | 2136 | TCM, successful 23min | |
| 2007 Mar 21 | 1810:32 | Undocked from Zvezda | |
| 1814 | Sep burn | 325 x 352 x 51.6 | |
| 2244:30 | Deorbit 2:29 85.4m/s | ||
| 2319 | Reentry | ||
| 2330 | Impact Pacific 44 15S 142 24W | ||
Wednesday, November 7, 2007
Tuesday, November 6, 2007
Satcom C4
1992-057A
Satcom C-4 was owned by GE Americom and built by GE Astro Space using the Series 3000 bus. Launched in Aug 1992, it was to replace the Satcom 4R (aka Anik D-2) satellite at 82W. In fact, it was moved soon after launch to 135W. In 2001, C-4 became the property of SES Americom, with communications services provided by SES Gibraltar.
| Satcom C4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Aug 31 | 1041 | Launch by Delta | CC LC17B |
| Az 93 deg | |||
| Delta SES-1 | |||
| 1051? | Delta SECO-1 | 185 x 185 x 28.5 ? | |
| 1105? | Delta SES-2? | ||
| 1105? | Delta SECO-2? | 185 x 1785? x 27.5 | |
| 1156? | Delta SES-3? | ||
| 1156? | Delta SECO-3? | 1750 x 1800? x 26.2? | |
| 1156? | Stage 2 sep | ||
| 1157? | Stage 3 burn | ||
| 1158? | T+1:17:00? Stage 3 sep | 662.08 1785 x 35784 x 20.6 | |
| 1208? | SES-4 depletion | 1768 x 2639 x 25.2 | |
| 1992 Sep 4 | 2052? | Star 30C burn | 1446.59 35815 x 36167 x 0.1 GEO 153.7W+2.6W |
| 1992 Sep 7 | 1430.24 35470 x 35873 x 0.1 GEO 155.7W+1.4E | ||
| 1992 Oct 6 | 1436.08 35764 x 35808 x 0.1 GEO 135.1W | ||
| 1992 Nov 30 | 1436.06 35782 x 35789 x 0.1 GEO 135.0W | ||
| 1994 Jul 4 | 1436.06 35772 x 35799 x 0.1 GEO 135.1W | ||
| 1999 Jun 14 | 1436.05 35770 x 35801 x 0.1 GEO 135.0W | ||
| 2001 | Transfer to SES | ||
| 2004 Jun | end active orbit maintenance | ||
| 2004 Aug 11 | 1436.06 35775 x 35796 x 0.3 GEO 135.0W | ||
| 2004 Oct 4 | mv out | ||
| 2005 Jan 20 | mv in | 1436.09 35777 x 35795 x 0.7 GEO 84.8W | |
| 2006 May 15 | 1436.11 35776 x 35797 x 1.9 GEO 84.7W | ||
| 2006 May 16 | mv out | ||
| 2006 Jun 25 | mv in | ||
| 2006 Aug 4 | 1436.05 35784 x 35786 x 2.1 GEO 105.7W | ||
| 2006 Sep 30 | 1436.10 35778 x 35794 x 2.3 GEO 104.9W | ||
| 2007 Feb 22 | 1436.11 35763 x 35808 x 2.7 GEO 104.6W | ||
Thursday, November 1, 2007
Thursday, October 25, 2007
Soyuz TMA-6 (Basalt)
2005-013A
11F732 No. 216 on ISS Flight 10S, callsign Bazal't. Expedition 11 crew and EP-8 visiting crew of Roberto Vittori (ASI) on ENEIDE mission for ESA/ASI. Launch mass 7195 kg.
EP-8 backup was CSA's R. Thirsk.
At docking, the Soyuz rolled about 15 degrees and it took a while to damp down the motion.
Mass 7195 kg, BO 1244 kg and SA 2894 kg, prop in PAO 880 kg. Docking mass 6829 kg.
| Soyuz TMA-6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2005 Apr 15 | 0046:25 | Launch by Soyuz-FG 11A511U-FG No. 0014 | |
| T+1:53 SAS sep | |||
| T+1:57 St 1 sep | |||
| T+2:37 GO sep | |||
| T+4:47 St 2 sep | |||
| T+4:57 KhO sep | |||
| 0055:10 | T+8:45 St 3 MECO | ||
| 0055:13 | T+8:48 St 3 sep | ||
| 0421:41 | DV1 17m/s 45s | 221 x 269 x 51.7 | |
| 0441:55 | DV2 5.6m/s 15s | 232 x 270 x 51.6 | |
| 2005 Apr 16 | 0159:01 | DV3 2,/s 6s | 238 x 270 x 51.6 |
| 2005 Apr 17 | 0023 | DV4 SKD 24m/s 63s | |
| 0046 | 1.4m/s DPO 34s, range 198 km | ||
| 0107 | 24m/s SKD 99 km range | ||
| 0148 | 7m/s SKD 2.6m/s | ||
| 0155 | 5m/s SKD range 1 km | ||
| 0157 | 1.5m/s DPO Range 0.6 km | ||
| 0202 | Range 900m | ||
| 0205 | Flyaround 400 m | ||
| 0208 | Range 250 m | ||
| 0210 | Range 166 m, nadir and roll | ||
| 0211 | Stationkeep 161m | ||
| 0212 | Resume approach | ||
| 0215 | 75m | ||
| 0218 | 30m | ||
| 0220 | 12m | ||
| 0220:23 | Soft Docking to Pirs | ||
| Docking complete | |||
| 0445 | Hatch open | ||
| 2005 Jul 19 | 1038:10 | Undock Pirs | |
| Back off 25 m | |||
| 1107:59 | Dock Zarya | ||
| 2005 Oct 10 | 1848 | HC | |
| 2149:14 | Undocking | 346 x 348 x 51.6 | |
| 2152 | 8s sep burn | ||
| 2005 Oct 11 | 0018:43 | deorbit 115.2m/s 4:11 | |
| 0043 | modules sep | -40 x 348 x 51.6 | |
| 0046 | entry | ||
| 0109:48 | landing 57 km NE from Arkalyk | ||
USA-134
1997-065A
B-13 was the first DSCS satellite to complete testing at Lockheed Sunnyvale following construction at Valley Forge. By 1996, the DSCS system customer was the MILSATCOM Joint Program Office at AF Space and Missile Systems Center, LAAFB.
Launch mass of combined DSCS and IABS was 2733 kg. The Falcon Gold experiment was attached to the Centaur stage.
| DSCS III B-13 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Oct 25 | 0046 | Launch by Atlas IIA Centaur AC-131 | CC SLC36A |
| 0048? | T+2:44? Atlas BECO | ||
| 0048? | T+2:47? Atlas booster sep | ||
| T+3:53? Fairing sep | |||
| T+4:41? Atlas SECO | |||
| 0050? | T+4:43? Atlas sep | ||
| 0051? | T+5:00? Centaur MES-1 | ||
| 0056? | T+10:07? Centaur MECO-1 | 150? x 900? x 29? | |
| 0108? | T+22:17? Centaur MES-2 | ||
| 0109? | T+23:43? Centaur MECO-2 | ||
| 0112 | T+26:38 Centaur sep | 619.1 316 x 35771 x 25.3 (UN) | |
| 1997 Oct 30 | IABS final burn | 1424.9 35533 x 35602 x 0.0 (UN) | |
Wednesday, October 24, 2007
Tuesday, October 23, 2007
Voyager 2
1977-076A
Voyager SC3 (Voyager 2, VGR-2) was launched at 1429:44 on 1977 Aug 20 by Titan IIIE Centaur from LC41 at Cape Canaveral. Although it immediately encountered problems with its science boom and other systems, these were soon resolved and it would become probably the most successful probe ever, visiting four planets and revolutionizing our knowledge of the outer solar system.
The Centaur stage cutoff into an orbit with an aphelion of around 2.8AU. The VGR propulsion module - a Star 37 motor - fired to increase aphelion to 6.3AU.
The scan platform stuck during deployment; an attempt to shake it by jettisoning a dust cover failed when the command sent VGR-2 into safemode.
VGR-2 settled into Cruise mode on Sep 2, and made a TCM on Oct 11. However, the success of launch led to complacency and the Voyager program ran into management problems at this time, with operations errors nearly losing the vehicle. Many Voyager team members moved on to work on the future Galileo project, with Voyager project manager John Casani's attention had been split between Voyager and Galileo Bob Parks was brought in to take over Voyager full-time in April 1978, soon after a crisis in which the main radio receiver switched to the backup when no message was sent to the spacecraft for over a week. A capacitor in the backup shorted, but when controllers ordered a switch back to the main reciever it failed permanently, and a week later the backup cut back in, to be used thereafter.
The first Jupiter imaging was done on 1979 Apr 24, with Jupiter Observatory Phase starting in May 1979. TCMs on May 26 and Jun 27 were made before encounter on Jul 9. TCM5, 6 and 7 were made on Jul 9, Jul 23 and 1981 Feb 26.
The Saturn Observatory Phase began on 1981 Jun 5. TCM-8 on Jul 19 and TCM-9 on Aug 18 set up the final encounter geometry. Far Encounter phases 1 and 2 began on Jul 31 and Aug 11 respectively, with Near Encounter on Aug 25. Periapsis was at 0324 on Aug 26. Voyager 2 crossed the ring plane at the G ring at 0415. The scan platform failed at 0514 on Aug 26, but most of the imaging had been taken. A Saturn Post Encounter phase lasted from Aug 27 to Sep 28.
Voyager 2 was now on course for Uranus. TCM-10 (1981 Sep 29), TCM-11 (1984 Nov 13), and another TCM on 1985 Dec 24 set up the encounter, which happened on 1986 Jan 26. The results were eclipsed by the loss of the Space Shuttle Challenger two days later.
During the Neptune cruise phase, TCM B15 (1987 Mar 13), TCM B16 (late 1988), TCMB17C (1989 Apr 20), TCM B18 (about 1989 Aug 1) and TCM B20 (1989 Aug 21) set up the accurate flyby. The Neptune Observatory Phase began on Jun 5, and transitioned to Far Encounter on Aug 6 and Near Encounter on Aug 24. Voyager 2 encountered Neptune at a distance of 4h 6min from Earth. At 2356 on Aug 24, it passed 4.6 million km from Nereid; at 0253 on Aug 25 it crossed the Neptune ring plane inbound. Closest approach to Neptune was 4905 km at 0355. The ring plane was traversed outbound at 0514, and Voyager 2 made its final flyby, of Triton, at a distance of 38360 km on 1989 Aug 25 at 0919. A Neptune Post Encounter phase from Aug 20 to Oct 2 marked the end of the Voyager outer planets exploratory mission. Voyager now began the search for the heliopause - the boundary between the solar system and interstellar space. Beginning of the Voyager Interstellar Mission was declared on 1990 Jan 1. By 1992 Oct 9, Voyager 2 was 38 AU from the Sun.
In 1999, five experiments were still operating: the CR, LEPI, PSI, PWI, and MAG.
| Voyager 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 Aug 20 | 1429:44 | Launch by TC | CC LC41 |
| T+1:50 SRM cutoff | |||
| T+1:51 St 1 burn | |||
| T+2:02 SRM sep | |||
| T+4:15 St 1 MECO | |||
| T+4:15 St 1 sep, St 2 MES | |||
| T+4:26 CSS jettison | |||
| T+7:44 St 2 MECO | |||
| T+7:50 St 2 sep | |||
| T+8:01 TC MES-1 | |||
| 1439:25 | T+9:48 TC MECO-1 | 167 x 167 x 37.6 | |
| T+53:00? Science boom deploy failed | |||
| 1523:20 | T+53:36 TC MES-2 | ||
| 1527:52 | T+59:16 TC MECO-2 | 195 x -29536 x 41.87 | |
| 1530:42 | T+1:02:06 TC sep | ||
| T+1:02:08 TC avoidance | |||
| 1530:58 | T+1:02:21s PMI burn | ||
| 1531:40 | T+1:03:06 PM burnout | 326 x -20835 x 41.86 | |
| 1543:01 | T+1:12:33 PM sep | ||
| 1937 | VGR pass EL1:4 | ||
| 2050 | Centaur pass EL1:4 | ||
| 1977 Aug 21 | 0200 | VGR pass lunar orbit | |
| 1977 Aug 21 | 1600? | VGR exit SOI/929 at Vinf=10.14 km/s | |
| 1977 Aug 22 | 0824 | VGR exit SOI/L1 | |
| 1977 Aug 22 | 0300? | Centaur exit Earth SOI (929k) at Vinf = 6.93 km/s | 1.02 x 3.02 AU x 3.7 deg? |
| 1977 Aug 23 | 0215? | Centaur exit Earth Hill sphere per orbit soln | |
| 1977 Aug 26 | Attempt to jettison IRIS cover aborted | ||
| 1977 Aug 29 | IRIS cover jettisoed | ||
| 1977 Sep 2 | Begin cruise | ||
| 1977 Oct 11 | TCM B-1 | ||
| 1978 Apr | Main radio receiver fail | ||
| 1978 May 3 | TCM B-2 | ||
| 1979 Apr 24 | First Jupiter image | ||
| 1979 Apr 30 | 1830? | Enter Jupiter sphere | |
| 1979 May 1 | 48M km from Jupiter | ||
| 1979 May | Jupiter Observatory Phase | ||
| 1979 May 26 | TCM B-3 | ||
| 1979 Jun 27 | TCM B-4 | ||
| 1979 Jul 8 | Jupiter Near Encounter | ||
| 1979 Jul 8 | 1313 | Callisto, 214930 km C/A | |
| 1979 Jul 9 | 0806 | Ganymede, 62130 km C/A | |
| 0850 | Max earth-rel velocity 55.91 km/s | ||
| 1843 | Europa, 205720 km C/A | ||
| 2030? | Amalthea 558370 km C/A | ||
| 2229:00 | Jupiter, 650178 km (721670 km C/A) | ||
| 1979 Jul 9 | TCM B-5 peri+2hr, 76min | ||
| 1979 Jul 23 | TCM B-6 | ||
| 1979 Aug 5 | Cruise phase | ||
| 1979 Sep 18 | 0240? | Exit Jupiter sphere | |
| 1979 Sep 23 | 48Mkm from Jupiter | ||
| 1981 Feb 26 | TCM B-7 | ||
| 1981 Jun 5 | Saturn Observatory Phase, 77 Mkm | ||
| 1981 Jun 18 | 2000? | Enter Saturn sphere 64.5M | |
| 1981 Jun 22 | 55 Mkm from Saturn | ||
| 1981 Jul 19 | TCM B-8 | ||
| 1981 Jul 31 | Saturn Far Encounter 1 | ||
| 1981 Aug 11 | Saturn Far Encounter 2 | ||
| 1981 Aug 18 | TCM B-9 | ||
| 1981 Aug 25 | Saturn Near Encounter | ||
| 1981 Aug 23 | 0127 | Iapetus, 908680 km C/A | |
| 1981 Aug 25 | 0125 | Hyperion 471370 km C/A | |
| 1981 Aug 25 | 0937 | Titan 666190 km C/A | |
| 2258 | Helene, 270000 km C/A | ||
| 1981 Aug 26 | 0105 | Dione, 502310 km C/A | |
| 0222 | Calypso, 200000? km C/A | ||
| 0234 | Mimas, 309930 km C/A | ||
| 0308 | Atlas, 287000 km C/A | ||
| 0319 | Pandora, 107000 km C/A | ||
| 1981 Aug 26 | 0324 | Saturn, 100800 km | |
| 0333 | Prometheus, 247000 km C/A | ||
| 0345 | Enceladus, 87010 km C/A | ||
| 0350 | Janus, 223000 km C/A | ||
| 0406 | Epimetheus, 147000 km C/A | ||
| 0415 | Ring plane crossing, in G ring | ||
| 0440 | Max earth-rel velocity, 61.7 km/s | ||
| 0514 | Scan platform fail | ||
| 0603 | Telesto, 300000 km? | ||
| 0612 | Tethys, 93010 km C/A | ||
| 0629 | Rhea, 645260 km C/A | ||
| 1981 Aug 27 | Saturn Post Encounter | ||
| 1981 Sep 4 | 0130? | Phoebe, 2075640 km C/A | |
| 1981 Sep 28 | Cruise Phase | ||
| 1981 Sep 29 | TCM-10 | ||
| 1981 Nov 2 | 1030? | 64.5M exit Saturn SOI | |
| 1981 Nov 10 | 55Mkm exit Saturn SOI | ||
| 1984 Nov 13 | TCM-11 | ||
| 1985 Nov 4 | Uranus Observatory Phase 103 Mkm | ||
| 1985 Dec 1 | 0430? | 69.6M enter U SOI | |
| 1985 Dec 24 | TCM-12? | ||
| 1985 Dec 31 | Uranus SOI | ||
| 1986 Jan 24 | Uranus near encounter | ||
| 1530? | Titania, 365200 km C/A | ||
| 1600? | Oberon, 470600 km C/A | ||
| 1700? | Ariel, 127000 km C/A | ||
| 1986 Jan 24 | 1730? | Miranda, 28260 km C/A | |
| 1986 Jan 24 | 1759 | Uranus 81541 km (71000 km old) (107100 km C/A) | |
| 1800? | Umbriel, 325000 km C/A | ||
| 1986 Feb 25 | Cruise phase | ||
| 1986 Mar 20 | 0630? | Leave Uranus Sphere 69.6M | |
| 1987 Mar 13 | TCM B15 | ||
| 1988 late | TCM B16 | ||
| 1988 Nov 11 | TCM B17B 0.45 km/s | ||
| 1989 Apr 20 | TCM B17C 0.3 km/s | ||
| 1989 Jun 5 | Neptune Observatory Phase | ||
| 1989 Jun 6 | 1200 | N Sphere 115.2M | |
| 1989 Jun 30 | Neptune SOI 87Mkm | ||
| 1989 Aug 1 | TCM B18 0.92 km/s | ||
| 1989 Aug 6 | Neptune Far Encounter | ||
| 1989 Aug 21 | TCM B20 0.47 km/s | ||
| 1989 Aug 24 | Neptune Near Encounter | ||
| 2356 | Nereid, 4.6Mkm | ||
| 1989 Aug 25 | 0253 | Ring plane inbound | |
| 1989 Aug 25 | 0356 | Neptune, 4476 (old 4905 km) (29242+-2 km C/A) | |
| 0514 | Ring plane outbound | ||
| 0910 | Triton, 38360 km (39780+-20 km C/A) | ||
| 1989 Aug 26 | Post Encounter | ||
| 1989 Oct 2 | Cruise | ||
| 1989 Oct 25 | Leave Neptune SOI | ||
| 1989 Nov 12 | 2000? | Leave Neptune sphere 115.2M | |
| 1990 Jan 1 | Voyager Interstellar Mission | ||
| 1998 Nov 12 | Comms lost | ||
| 1998 Nov 14 | Comms restored | ||
| 1998 Nov | Scan platform turned off | ||
| 1999 Feb 1 | OWLT 16 hr | ||
| 2007 Aug 30 | First helioshock pass at 84AU | ||
Payload:
- MHW RTG
- Imaging TV cameras (2), 1500mm f/8.5 narrow angle, 200mm f/3 wide angle
- UVS Ultraviolet spectrometer 534-1701A Plasma spectrometers
- IRIS IR spectrometer/radiometer
- LEPI Low energy charged particle analyser/telescope
- Multifilter photometer 2200-7300A, 8-in, F/1.1 scope
- Triaxial fluxgate magnetometers
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