Wednesday, January 4, 2017
Monday, January 2, 2017
Skynet 5C
2008-030A
Skynet 5C is an Astrium (Stevenage) Eurostar E3000 bus. Astrium delivers the satellite in orbit to Paradigm.
Early in-service tests from AFSCF-Sunnyvale, with control assumed by RAF Oakhanger for routine operations. To be stationed at 17.8W.
mass 4638 kg launch. Size 4.5 x 2.9 x 3.7m with 34m span.
| Skynet 5C | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Jun 12 | 2205:02 | Ignition | |
| 2205:09 | Launch | ||
| 2206:55 | T+1:53 EAP sep | ||
| 2208:06 | T+3:04 Fairing sep | ||
| 2213:51 | T+8:49 EPC MECO | ||
| 2213:57 | T+8:55 EPC sep | -1062 x 172 x 6.8 | |
| 2214:01 | T+8:59 ESC-A burn | ||
| 2229:47 | T+24:45 ESC-A MECO | ||
| 2232:04 | T+27:02 Skynet 5C sep | ||
| 2234:27 | T+29:25 SYLDA sep | ||
| 2236:41 | T+31:39 Turksat 3A sep | ||
| 2008 Jun 12 | 631.18 267 x 35724 x 2.0 | ||
| 2008 Jun 18 | 1430.10 35563 x 35775 x 0.8 | ||
| 2008 Jun 24 | 1436.00 35768 x 35801 x 0.8 GEO 17.9W | ||
| 2008 Jul 29 | 1436.10 35772 x 35800 x 0.7 GEO 17.7W | ||
| 2015 Mar 31 | 1436.09 35776 x 35796 x 0.1 GEO 17.9W | ||
Sunday, January 1, 2017
Akatsuki
2010-020D
Akatsuki (Dawn, Daybreak), Planet C is a Venus Climate Orbiter. Studies the distribution of clouds, trace gases, lightning discharges, and temperature, as well as plasma measurements and a search for active volcanism.
Mass 480 kg at launch.
320 kg prop? in 300 x 79000 km retrograde equatorial orbit. Box + 2 panels.
Box 1.04 x 1.45 x 1.40m. AOCS has 500N NTO/N2H4 thruster and 23N and 3N attitude thrusters.
HIIA 202 with 4m fairing. Launch provider is MHI with JAXA as range control.
Type 2 trajectory with 107.5 x 155.2 Mkm orbit.
Unfortunately Venus orbit insertion failed with damage to the insertion engine, and Planet C sailed on past in solar orbit. The post encounter orbit reported in Dec 2010 is 90 x 110 Mkm with 203d period.
puranetto c - Planet C kanaboshi tansaki - Venus probe
The OME test burns in Sep 2011 showed that the engine was severely damaged and could only generate small amounts of thrust. JAXA will dump all remaining 64 kg of oxidizer to reduce mass and then eventually perform VOI on monoprop RCS alone (4 x 23N).
As of early 2015, the plan was for VOI on 2015 Dec 7 into a 300 x 300000 - 400000 km orbit.
| VCO | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2010 May 20 | 2158:22 | Launch by HIIA 202 F17 | YoLP1 |
| Az 93 deg | |||
| 2200 | T+2:05 SRB-A jettison | ||
| T+4:25 Fairing sep | |||
| T+6:36 St 1 MECO | |||
| T+6:44 St 1 sep 223 km 5.5 km/s | |||
| T+6:50 SES-1 | |||
| 2209:51 | T+11:29 SECO-1 | 300 x 300 x 30.0 | |
| J-POD ejects WASEDA, Negai, KSAT | |||
| 2210:54 | T+12:32 NEGAI* sep | ||
| 2211:04 | T+12:42 Waseda-Sat2 sep | ||
| 2211:14 | T+12:52 KSAT sep | ||
| 2220:54 | T+22:32 Stage 2 MES-2 3:51 | ||
| 2224:45 | T+26:23 Stage 2 MECO-2, solar orbit | ||
| 2225:49 | T+27:27 PLANET C sep 407 km to 478 km 11.7 km/s | ||
| Deploy solar arrays | |||
| 2234:09 | T+35:47 PAF900M Payload attach fitting sep | ||
| 2241:04 | T+42:42 Ikaros sep | ||
| 2246:14 | T+47:52 Unitec-1 sep | ||
| 2010 May 21 | 0100 | C3=18.46 | 298 x -56249 x 31.47 |
| 0600 | Pass EL1:4 | ||
| 2010 May 21 | 2000 | Pass lunar orbit | |
| 2010 May 23 | 0840 | Leave Earth SOI | 0.717 x 1.066 AU x 2.02 |
| 2010 May 24 | 1810 | Leave Earth Hill sphere | |
| 2010 May 25 | 307.22d 0.716 x 1.066 AU x 2.03 | ||
| 2010 Jun 28 | 500N thruster test 13s 12m/s | ||
| 2010 Jul 1 | 307.78d 0.719 x 1.066 AU x 2.03 | ||
| 2010 Nov 8 | RCS-1 approach tweak | ||
| 2010 Nov 22 | RCS-2 approach tweak | ||
| 2010 Dec 1 | RCS-3 approach tweak | ||
| 2010 Dec 1 | 309.69 0.719 x 1.073 AU x 2.01 | ||
| 2010 Dec 3 | 1859 | Enter V sphere 1.008Mkm | 700 x -73500 |
| 2010 Dec 6 | 2349:00 | VOI burn | |
| 2351:38 | S+2:32 Burn aborted, Venus flyby | ||
| 2010 Dec 10 | 1307 | Depart V sphere | 700 x -88760 |
| 2011 Apr 17 | Perihelion 1 0.6 AU x 0.72? AU | ||
| 2011 Sep 7 | 0250 | 2s OME test burn, failed (13 pc thrust) | |
| 2011 Sep 14 | 0250 | OME test burn, 5s, failed | |
| 2011 Sep 30 | 0302 | DOX test 60s 1.9m/s | |
| 2011 Oct 6 | 0253 | Oxidizer dump 360s 65 kg total, DOX1 7.6m/s | |
| 2011 Oct 12 | 0323 | Oxidizer dump 540s DOX2 8.1m/s | |
| 2011 Oct 13 | 0453 | Oxidizer dump 540s DOX3 8.1m/s | |
| 2011 Nov 1 | 0422 | DV1 RCS burn 587s 88.6m/s | |
| 2011 Nov | Perihelion 2, T=203d | ||
| 2011 Nov 10 | 0437 | RCS DV-2 dV 544s 90.6m/s | |
| 2011 Nov 21 | 0457 | RCS DV-3 342s 63.5m/s | |
| Total aphelion reduction 3M km | |||
| 2012 Mar 9 | 0.611 x 0.722 AU x 3.5 deg | ||
| 2012 Jun | Perihelion 3, T=199d? | ||
| 2015 Jul 17 | DV4-1 | ||
| 2015 Jul 24 | DV4-2 | ||
| 2015 Jul 31 | DV4-3 Total 87m/s | ||
| 2015 Aug 30 | Perihelion | ||
| 2015 Nov 13 | 3 Mkm from Venus | ||
| 2015 Dec 1 | 0820 | Enter Venus sphere(L1) | |
| 2015 Dec 6 | Attitude change for VOI | ||
| 2351:29 | Enter Venus shadow, begin burn 20:28 | ||
| 2015 Dec 7 | 0000 | Periapsis | |
| 2015 Dec 7 | VOI-R1, | ||
| 0011:57 | End burn | ||
| 0230 | Exit shadow? period 13d14h | 400 x 440000 x 3 | |
| 2015 Dec 20 | Orbit adjust 1000? x 360000 10.5 days | ||
| 2016 Jan 31 | 1136 | At 91000 km | |
| 1336 | At 76000 km | ||
| 2016 Feb 20 | Comms problem | ||
| 2016 Apr 4 | Orbit tweak to delay eclipses | ||
| 2016 Apr 4 | 0728 | Orbit adjust 4 of 8 thrusters, 15s burn | 10.8d ? x 370000 |
Payload:
- IR1 NIR camera 1 1.0mu
- IR2 NIR camera 2 1.7-2.4mu
- LIR LWIR camera 9-11 mu
- UVI UV imager 2800-3600A
- LAC Lightning/Airglow camera 5510/5580/7770A
- USO Ultrastable oscillator
- EUV scanner 530-1300A
- Ion/electron particle analysers
- Magnetometer/Wave analysers 10 MHz
- Orbit maneuver engine 500N (new Si3N4 silicon nitride design)
Van Allen Probes
2012-046B
JHU/APL Radiation Belt Storm Probe, 2 satellites in equatorial GTO. NASA GSFC STP/LWS mission.
Mass 658 kg full 630 kg dry? Oct+4 pan + 8 booms, approx 0.9h 2.0d? Launch by Atlas V 401
| RBSP | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2012 Aug 30 | 0805:27 | Launch by Atlas V 401 | CC SLC41 |
| T+4:03 BECO | |||
| T+4:09 Atlas sep | |||
| T+4:19 MES-1 | |||
| T+4:27 PLF sep | |||
| 0819:04 | T+13:37 MECO-1 | 167 x 600 x 25.5 | |
| 0914:52 | T+1:09:25 MES-2 | ||
| 0919:31 | T+1:14:04 MECO-2 | ||
| 0924:17 | T+1:18:50 A sep from B | 597 x 30645 x 10.0 | |
| 0932 | Centaur RCS orbit adjust 140s, raise apo 60 km | ||
| 0936:31 | T+1:31:04 B sep from Centaur | 601 x 30709 x 10.0 | |
| 0948? | Centaur deorbit adjust, 36s | -220 x 36062 x 10.3 | |
| 1940? | Centaur impact in Atlantic, 22W 5S? | ||
Payload:
- ECT Energetic particle, composition and thermal plasma suite (UNH/Spence)
- MagEIS Magnetic electron-ion spectrometer 30 keV-4MeV e, 20 keV-1 MeV ions);
- HOPE Helium Oxygen Proton Electron from 20 eV to 45 keV;
- REPT Relativistic E/P telescope, e 4-10 MeV, p 20-75 MeV
- EMFISIS E.and M. field instrument suite and integrated science (U Iowa/Kletzing) with triaxial magnetometer on rigid booms (2 booms, 3m each,from end of solar panels), central DPU, E field WAVES receiver
- EFW Electric Field and Waves suite (UMn/Wygant),
- spin plane booms, 4, 80m and 100m tip to tip
- axial booms, 2, 12m tip to tip
- RBSPICE RBSP Ion Composition Experiment (NJIT/Lanzerotti) Puck, ring current ion comp. snesor
- RPS Relativistic Proton Spectrometer (NRO/), 50 - 400 MeV Si detectors, 400 MeV-2 GeV p Cerenkov detector
USA-252
2014-027A
NROL-33 orbited a GEO QUASAR satellite, USA 252. The satellite is thought to use a Boeing 601 bus.
| USA 252 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 May 22 | 1309 | Launch by Atlas AV-046 | CC |
| T+3:37? BECO | |||
| T+4:11? CCB Stage 1 sep | |||
| T+4:30? Fairing sep | |||
| 1321? | MECO-1 | ||
| 180 x 1080 x 27.0 (my guess) | |||
| 1332? | MES-2 at S eq crossing | ||
| 1334? | MECO-2 | 1077? x 35661? x 25.2? | |
| 644.5 831 x 35844 x 28.7 (UN) | |||
| 1336? | Centaur sep | ||
| 1338? | Centaur CCAM | 1000? x 30000? x 25? | |
| 1650? | Apogee | ||
| 1700? | Centaur deorbit | ||