Tuesday, August 6, 2019

HTV-3

 2012-038A


Kounotori 3 gouki (Stork unit 3,

\uni{ 「こうのとり」3 号機)}{ }
was the first HTV to use IHI's HBT-5 and HBT-1 thrusters instead of the Aerojet R-4D and R-1E. It also has the first use of the EP-MP Multipurpose-type exposed pallet (Tomokuteki bakuro paretto-gata,
\uni{ 多目的曝露パレット型 }{ }
)

The HTV has a Pressurized Logistics Carrier (hokyu kyaria yoatsu-bu,

\uni{ 補給キャリア与圧部 }{ }
) and an Exposed Pallet (baruko paretto,
\uni{ 曝露パレット)}{ }

The SCAN Testbad will be installed on ELC-3 Site 3. MCE will go to JEM-EF EFU-8.

The H-IIB LV will perform a controlled second stage reentry test.

The J-SSOD deployers will be placed on the MPEP (Multi Purpose Experiment Platform), a plate that fits on the end of the JEM RMS. The RMS grapples the MPEP and positions it, then the J-SSODs eject their cubesats.

MPEP is Oya amu sentan toritsuke-gaka kikken purattoformu (

\uni{ 親アーム先端取付型実験プラットフォーム), }{ }
literally 'Experimental platform, for mounting on end of arm'.


HTV3 
 

DateTimeEventOrbit  

2012 Jul 21  0206:18 Launch by HIIB  TNSC LP2 
  Ascent on azimuth 108.5 
  T+1:54 SRB burnout 
  T+2:04 SRB 1-2 sep 
  T+2:07 SRB 3-4 sep at 63 km 
  T+3:40 Fairing sep at 120 km 
  T+5:47 MECO 
  T+5:54 St 1 sep 
 0212 T+6:01 SEIG 
 0220:38 T+14:20 SECO  89.40 186 x 304 x 51.7  
 0221 T+15:11 St 2 sep  89.83 231 x 301 x 51.7 
  T+1:39:05 SEIG-2 at end of orbit 1 over Japan 
  Burn in 'idle mode' 
 0346 T+1:39:58 SECO-3 
 0414? St 2 entry over S Pacific 138W 50S? 
2012 Jul 25  1701  HAM1 burn 
2012 Jul 27  0235  HAM2 burn 
 0540  HAM3 burn  
 0626s  Arrive at 5km AI (Approach Init) point 
 0845s  Approach initiation burn 
 0928?  RI burn  
 0947  R-bar Initiation (RI), 500 m nadir hold 
 0950? R-bar approach from 500m 
2012 Jul 27    
  Hold at 250m nadir 
 1100  250m nadir, begin final approach 
 1126  Hold at 30m 
 1148  Resume approach 
 1209  Hold at 10m, capture point 
 1233  SSRMS grapple HTV 
 1347  Moving HTV 
 1419  HTV at Ready-to-latch on Harmony nadir 
 1425  Stage 1 berthing complete 
 1434  Stage 2 capture complete 
  SSRMS ungrapple HTV 
  SSRMS grapple HTV EP 
2012 Jul 28  0805  HO 
 0815  Crew ingress 
  Begin cargo transfers 
2012 Jul 30   Continue cargo transfers 
2012 Aug 6    
 0709  SSRMS Unberth EP  
  JEMRMS grapple EP 
  SSRMS ungrapple EP 
 1204  JEMRMS berth EP on Kibo EFU-10 
2012 Aug 7    
  SSRMS grapple Dextre SPDM 
  MT translate 
  SSRMS/SPDM transfer SCAN to ELC-3 
2012 Aug 9    
  JEMRMS transfer MCE to EF? 
 0902  Unberth MCE  
 1101  Install MCE on EF EFU-8 
2012 Aug 10  
 0419  JEM RMS unberth EP from EF 
  JEM RMS transfer EP to SSRMS  
 1102  SSRMS install EP in HTV 
2012 Sep 12  
 1030  SSRMS already grappled to HTV-3 
 1150  HTV-3 unbolted from Harmony 
 1202? HTV-3 unberthed 
 1500  HTV-3 on arm  
 1550  HTV-3 release 
 1555  Abort burn separates from ISS after computer failed 
  Main engine on Vbar 
2012 Sep 14  0000  DOM-1 
 0131  DOM-2 
 0451?  DOM-3 
 0502  DOM-3 cutoff 
 0527  Entry 

Thursday, August 1, 2019

July 20,2006

 https://en.wikipedia.org/wiki/Enceladus

Beidou 16/17

 2012-018A/B


'shier ke Beidou er hao weixing' and 'shisan ke Beidou er hao weixing' COMPASS MEO 3, 4 BDW 12 and 13 were launched stacked on a CZ-3B to inclined MEO. They were based on an improved DFH-3.

The dual payload adapter is the 'shuangxing chuanlian wai zhichengjiegou' - dual satellite (shuangxing) serial (chuanlian) external (wai) support (zhicheng) structure (jiegou).

PRN codes 11 and 12 are used.


BDW12/13 
 

DateTimeEventOrbit  

2012 Apr 29  2050:03  Launch by CZ-3B Y14 
  T+2:21 / 2:07 Boosters sep 
  T+2:39 / 2:27 St 1 sep 
  T+3:55 / 3:52 Fairing sep
  T+5:44 / 5:32 St 2 sep, St 3 MES-1 
 2100  T+10:20 / 10:31 St 3 MECO-1 
 2111 T+21:04 / 21:21 MES-2 
 2114 T+24:00 / MECO-2 
 2114 T+24:20 VECO-2 
 2115 T+25:40 / 25:59 B12 sep   
 2117? Adapter sep 
 2119? B13 sep? 
2012 May 3    376.05 200 x 21559 x 55.0 (A) 
2012 May 3    374.18 144 x 21500 x 55.0 (B) 
2012 May 3    375.86 199x 21549 x 55.0 (D) 
2012 May 9    375.16 203 x 21502 x 55.0 
2012 May 10    773.20 21459 x 21594 x 55.2 
2015 Jun 4    773.22 21465 x 21590 x 55.8 

Wednesday, July 31, 2019

Gaia

 2013-074A


EADS-Astrium/Toulouse satellite. Planned ESA CS6. 2011 Dec. Mass 1934 kg launch, 1392 kg dry. Mass 2013 kg at L2 insertion.

Astro 1 and Astro 2 telescopes sep by 106 deg. 1.7 x 0.7 m aperture each. Radial velocity spectrophotometer with 0.75m aperture.

9.5m sunshield diameter. Payload module and service module, 3.0m dia, hexagonal frustum to 1.6m dia.

Astrometry of 1E9 stars. uas, 100 x Hip. 4-color photom and radial vels. L2, with PLM and SVM and shield.

Launch by Soyuz-ST from CSG.

L2 Lissajous of 120000 x 340000 x 180000 km, period 180 days


Gaia 
 

DateTimeEventOrbit  

2013 Dec 19  0912:19 Launch by Soyuz E15000-004  CSG ELS 
  T+1:58 Blok BVGD sep 
  T+3:40 Fairing sep
  T+4:48 Blok A sep 
  T+4:54 KhO sep 
 0921 T+9:23 Blok I sep  -681 x 180 x 14.98  
 0922 T+10:23 Fregat MES-1 2:16  
 0924:58 T+12:39 MECO-1  175 x 175 x 14.98  
 0933:44 T+21:25 MES-2 15:34 
 0949:18 T+36:59 MECO-2  344 x 962690 x 14.98  
 0954:18 T+41:59 Fregat/Gaia sep 
 0955 T+43 Pressurize CPS (chemical prop) 
  Fregat MES-3 
  Fregat MECO-3  374 x 2150152 x 14.99  
 1029 T+1:17 Sun shield deploy 
 1039 T+1:27 SS deploy complete 
2013 Dec 19  2333 Pass EL1:4 
2013 Dec 20   TCM 23.5m/s 
2013 Dec 30   L+12d TCM, L2 cal burn 
2014 Jan 3   Sci payload on 
2014 Jan 7  1858 OIM-1 2hrm/s into SEL2 lissajous, period 180d 
 2041 OIM complete  
2014 Jan 13  0234  Pass GSEx = -1.2Mkm 
2014 Jan 14  OIM-2  263000 x 707000 x 370000 
2019 Jan  
Eclipse avoidance burn 14m/s 

Payload:

  • Twin telescopes, 1.7 x 0.6 deg FOV, 106.5 deg sep

  • Primary mirrors are 1.45 x 0.5m rectangular SiC. M1 and M'1.

  • Secondary mirrors M2,M3 0.65 x 0.28m

  • Fold mirrors M5,M6 0.54 x 0.36m.

  • Radial velocity spectrometer, 8470-8740A Uses CaII triplet lines at 8498, 8542, 8552A

  • Gaia Focal Plane Assembly, 106 CCDs, each 4500 x 1996 pixel, total 952 Mpix.. Operating temp -115C., scan at 0.9828ms per pixel due to SC spin.

    • SkyMapper CCDs, 7 x 2 array

    • Astrometric Field CCDs, 7 x 9 array

    • Blue Photometer CCDs, 1 x 7 3300-6800A

    • Red Photometer CCDs, 1 x 7 6400A-1mu

    • Radial Velocity Spectrometer CCDs, 4 x 3

Sunday, July 21, 2019

GRAIL

 2011-046A


DISCOVERY mission, lunar equivalent of GRACE. Gravity Recovery and Interior Laboratory. Managed by JPL, with PI MIT/Maria Zuber. Lockheed Martin/Denver satellites based on XSS-11 bus with Ka-band rangers.

Each satellite is a box 1.1m high 0.95m wide 0.76m deep. Mass is 307 kg wet, 201 kg dry. Launch by Delta II 7920H-10C.

On 2011 Jan 17, GRAIL-A was renamed Ebb and GRAIL-B was renamed Flow.

In operational phase, orbits from 51 to 16 km. In early April at circular phase, minimized solar perturbations and avoided momentum dumps for maximal sensitivity to lunar core parameters. Orbit determined to 20 cm accuracty; determined that 98 percent of lunar gravity variation is due to surface topography rather than deep interior, and distinguished true lunar basins from many postulated but spurious ones.


GRAIL 1 
 

DateTimeEventOrbit  

2011 Sep 10 1308:52.8 Launch by Delta 7920H  CC LC17B 
  99 deg az 
  T+1:20 SRM 1-6 burnout 
  T+1:20? SRM 7-9 on 
  T+2:40? SRM 7-9 out 
  SRM 1-9 sep 
  T+4:23 MECO 
  St 1 sep 
  SES-1 
 1316 T+7:10 SECO-1  167 x 167 x 29.2? 
   155 x 175 x 29.3 
  1 hr coast 
 1414:44 T+1:05:51 SES-2 (TLI) 272s 
 1419:16 T+1:10:23 SECO-2  175? x 1129400? x 29.2?  
 1428:46 T+1:19:53 S2+9:30, Grail-A sep 
 1434  Solar arrays deployed 
   174 x 1108206 x 29.3 
 1436  T+1:28:08 S2+17:45, Grail-B sep C3=-0.70  
   173 x 1109774 x 29.3 
 1442  Solar arrays deployed 
 1508:02 T+1:59:10 SES-3 depletion 
2011 Sep 11  0057  Stage 2 pass EL1:4 
2011 Sep 11  0358  Pass EL1:4 
2011 Sep 12  0009  Stage 2 orbit  1274 x -179292 x 29.3  
2011 Sep 16   A TCM-1 
2011 Sep 17  0730  Stage 2 at 1.5Mkm   
2011 Sep 23   1 Mkm from Earth 
  Coast to Sun-Earth L1 
2011 Sep 30  1043  Pass GSEx 1.2Mkm 
2011 Sep 30   A TCM-2 
2011 Oct 5   B TCM-2 
  Translunar coast 
2011 Nov 1   Stage 2  347.32d 0.879 x 1.055 AU x 0.01 
2011 Nov 21?  TCM B3 
2011 Nov 22  0814  Inside GSEx 1.2Mkm 
2011 Dec 14?  TCM B4 
2011 Dec 25?  TCM B5 
2011 Dec 30  0938  Enter L sphere 
2011 Dec 31 2121  LOI Grail-A 40min 
  burn over S pole, 191 m/s 
 2201  LOI complete 
  11.5 hr insertion orbit 
2012 Jan 1  2205 LOI Grail-B 39min 
 2244  LOI complete 
2012 Jan 2   OPR phase - Orbit Period Reduction 
2012 Feb 6   TSF phase - Transition to Science Formation 
2012 Mar 7 0115  Science phase begins, sep at 80 km 
  Science orbit 25 x 86 km 
2012 Apr 8    55 x 55 k  
2012 Apr 21   Sep at 220 km, Trim to reverse drift 
2012 May 20    20 x 90 km  
2012 May 29   End of primary mission 
2012 May 29   Science instruments off 
2012 May 30   Orbit adjust 
2012 Aug   Science instruments on 
2012 Aug 31   Extended mission 23 km avge  15 x 35 km  
2012 Nov 2?  Orbit  7 x 40 km  
2012 Nov 28   Decommissioning, 40 days  15 x 55 km 
2012 Dec 6   lower orbit, Endgame phase  2 x 40 km  
2012 Dec 14   Science instruments off 
2012 Dec 14   A TCM for impact 
2012 Dec 17  2139  A depletion 4:03 
  Impact 1.7 km/s 1 deg  -8? x 40? x 90 
2012 Dec 17  2228:51  A Impact 75.62N 26.63W 
  Sally K Ride Impact Site 
  on S face of mountain near Goldschmidt Crater 
2019 Jan 1   Stage 2  346.6d 0.877 x 1.054 AU x 0.01 

Payload:

  • Lunar Gravity Ranging System (USO, Ka-band microwave system) (MIT/Zuber)

  • MoonKAM (Ecliptic/UCSD/)

2011-046B


GRAIL 1 
 

DateTimeEventOrbit  

2011 Sep 10 1308:52.8 Launch by Delta 7920H  CC LC17B 
  99 deg az 
  T+1:20 SRM 1-6 burnout 
  T+1:20? SRM 7-9 on 
  T+2:40? SRM 7-9 out 
  SRM 1-9 sep 
  T+4:23 MECO 
  St 1 sep 
  SES-1 
 1316 T+7:10 SECO-1  167 x 167 x 29.2? 
   155 x 175 x 29.3 
  1 hr coast 
 1414:44 T+1:05:51 SES-2 (TLI) 272s 
 1419:16 T+1:10:23 SECO-2  175? x 1129400? x 29.2?  
 1428:46 T+1:19:53 S2+9:30, Grail-A sep 
 1434  Solar arrays deployed 
   174 x 1108206 x 29.3 
 1436  T+1:28:08 S2+17:45, Grail-B sep C3=-0.70  
   173 x 1109774 x 29.3 
 1442  Solar arrays deployed 
 1508:02 T+1:59:10 SES-3 depletion 
2011 Sep 11  0359  Pass EL1:4 
2011 Sep 12  0009  Stage 2 orbit  1274 x -179292 x 29.3  
2011 Sep 16   A TCM-1 
2011 Sep 17  0730  Stage 2 at 1.5Mkm   
2011 Sep 23   1 Mkm from Earth 
2011 Sep 30   A TCM-2 
2011 Sep 30  1150  B pass GSEx=1.2Mkm 
2011 Oct 5   B TCM-2 
  Coast to Sun-Earth L1 
  Translunar coast 
2011 Nov 1   Stage 2  347.32d 0.879 x 1.055 AU x 0.01 
2011 Nov 21?  TCM B3 
2011 Nov 4  0637  B inward of GSEx=1.2Mkm 
2011 Dec 14?  TCM B4 
2011 Dec 25?  TCM B5 
2011 Dec 31  1019  Grail-B in L Sphere 
2011 Dec 31 2121  LOI Grail-A 40min 
  burn over S pole, 191 m/s 
 2201  LOI complete 
  11.5 hr insertion orbit 
2012 Jan 1  2205 LOI Grail-B 39min 
 2244  LOI complete 
2012 Jan 2   OPR phase - Orbit Period Reduction 
2012 Feb 6   TSF phase - Transition to Science Formation 
2012 Mar 7 0115  Science phase begins, sep at 80 km 
  Science orbit 25 x 86 km 
2012 Apr 8    55 x 55 k  
2012 Apr 21   Sep at 220 km, Trim to reverse drift 
2012 May 20    20 x 90 km  
2012 May 29   End of primary mission 
2012 May 29   Science instruments off 
2012 May 30   Orbit adjust 
2012 Aug   Science instruments on 
2012 Aug 31   Extended mission 23 km avge  15 x 35 km  
2012 Nov 2?  Orbit  7 x 40 km  
2012 Nov 28   Decommissioning, 40 days  15 x 55 km 
2012 Dec 6   lower orbit, Endgame phase  2 x 40 km  
2012 Dec 14   Science instruments off 
2012 Dec 14   B TCM for impact 
2012 Dec 17  2139  B depletion 5:07 
  Impact 1.7 km/s 1 deg  -8? x 40? x 90 
2012 Dec 17  2229:21  B Impact 75.62N 26.63W 
  Sally K Ride Impact Site 
  on S face of mountain near Goldschmidt Crater 

Women Spacefarers: Sixty Different Paths to Space

 https://welib.org/md5/d8bd44b1c2041a12d4d0cc1a4783dbc3

Friday, June 21, 2019

Something I might work on later,who knows?

 That's Terri MacGregor-Jeremiah behind the desk,she's my assistant and kinda my gal pal too. Her fiancé (yes,she's already taken his surname) is Craig Jeremiah,one of the new teachers at the high school.

Hey,Cameron,I see you're filming,eh?

You're on candid camera,Ter! Mind being interviewed?

No,I don't. Lemme just.....okay,I'm ready.

So,what's your full name,anyway? I've always wanted to know.

Theresa Claire MacGregor-Jeremiah.

How about some basic facts about yourself? Nice skirt-thing,by the way.

Thanks,I got it on layaway at Clifton Park Center! I graduated from Green High in 2010.....you were class of '16,right?

Indeed.

I'm originally from Carmelide, moved here in 1997 with my family. My parents are Todd and Bethany MacGregor: they manage a chain of farms and farming-related businesses across the Northeast and Maritime States and are worth about $450,000. I have one older sister, Olivia, who graduated from GHS in 2005. I played JV and varsity soccer and varsity tennis in high school and I got to be prom queen in 2009 alongside Gavin Mason as king.

What about college?

I did three years at D'Youville in Buffalo,and I returned here in early 2015.

And Craig,what about him? I remember he went to school here.

Yep,he was class of '09. We started dating late in my senior year here.


Monday, June 17, 2019

Artemis

 2001-029A


The second ESA heavy communications technology satellite was the SAT-2/DM Advanced Relay Technology Mission (Artemis) was built by Alenia Spazio for ESA using the Italsat bus. Originally scheduled for launch in 1996  [693], the DRS precursor technology mission was delayed until 2000 and oriented to mobile and inter-satellite communications. In 1996 it was moved from Ariane 5 to the Japanese H-IIA, but was later moved back again after H-II delays. Mass is 3105 kg full. Size is 4.8h 8.0wide (with antennas) and 25m span.

4.86 x 2.85 x 2.95m, span 24.73m.

Artemis was placed above SYLDA, which contained BSAT-2B.

Artemis together with Inmarsat 3 AOR and IOR provides the EGNOS European GPS augmentation. It opeated as an IOR-W (Congo) satellite.

The S400 LAE will perform GEO insertion; relocation will be done by the set of 10N RCS biprop thrusters attached to the S400. Biprop load is 1538 kg. Ion propulsion will be used for NSSK. Artemis carries two DASA RIT-10 thrusters and two MMS EIT T5 thrusters with 40 kg of Xe. Isp is 3000s and thrust is 20mN. Deduced dry mass is 1527 kg.

The EPS stage only got to 80 percent of planned thrust and cutoff 1min 20sec early, because of a combustion instability in the Aestus engine. Designers annouced that mixing the propellant more slowly would fix the problem.

Artemis was later raised to a 30900 x 30940 km orbit, significantly below geosynchronous, and then finally by Feb 2003 to GEO.

Avanti bought the satellite in 2014 and in 2016 relocated it to 123E under a contract from the Indonesian ministry of defence, preserving Indonesia's rights to the old Garuda-1.


Artemis 
 

DateTimeEventOrbit  

2001 Jul 12  2158:00  Launch by Ariane 5G  CSG ELA3 
  T+0:07 Liftoff 
  T+2:24 EAP sep 
  T+3:25 Fairing sep
 2207:59 T+9:59 EPC cutoff 
 2208:06 T+10:06 EPC sep 
 2208:28 T+10:28 EPS burn 
 2208:31 T+10:31 Aestus problem, 80 percent thrust 
 2223:28 T+25:28 Aestus cutoff early 
  T+26:48 Aestus cutoff due 
 2226 T+28:06 Artemis sep 
 2228 T+29:58 Sylda 5 sep 
 2233 T+35:35 BSAT-2b sep 
2001 Jul 14    318.48 592 x 17548 x 2.9 
2001 Jul 18  1519  Perigee burn 1  345.35 609 x 19245 x 3.0 
2001 Jul 19   Perigee burn 2  
2001 Jul 19   Perigee burn 3 
2001 Jul 20   Perigee burn 4 
2001 Jul 20   Perigee burn 5 
2001 Jul 21  1432   546.86 660 x 30886 x 2.9 
2001 Jul 22   Apogee burn 1  
2001 Jul 22  1211   579.84 2446 x 30864 x 2.2 
2001 Jul 23   Apogee burn 2  
2001 Jul 24   Apogee burn 3, parking orbit  
2001 Jul 27  1553   1195.43 30902 x 30964 x 0.8 
2001 Aug 12    1195.18 30897 x 30958 x 0.8 
2001 Dec 4    1194.85 30901 x 30941 x 0.8 
2002 Feb 20   Ion thruster burns resume 
2002 Feb 21    1195.50 30921 x 30948 x 1.0 
2002 Mar 31    1206.45 31118 x 31205 x 1.0 
2002 Apr 24    1222.75 31415 x 31583 x 1.0 
2002 Jul 18    1284.11 32678 x 32833 x 1.1 
2002 Aug 30    1312.77 33289 x 33384 x 1.2 
2002 Sep 27    1330.09 33628 x 33741 x 1.2 
2002 Oct 27    1353.26 34073 x 34225 x 1.3 
2002 Nov 26    1378.52 34589 x 34714 x 1.4 
2002 Dec 5    1386.40 34770 x 34845 x 1.4 
2003 Jan 3    1409.15 35224 x 35290 x 1.5 
2003 Jan 17    1421.28 35488 x 35504 x 1.5 GEO 7.0W+3.7E 
2003 Jan 31    1432.32 35664 x 35760 x 1.6 GEO 21.2E+1.0E 
2003 Feb 5    1436.29 35494 x 36086 x 1.5 GEO 21.0E 
 
2006 Aug 1    1436.11 35776 x 35797 x 4.8 GEO 21.4E 
2009 Jun 1    1436.08 35772 x 35799 x 7.4 GEO 21.5E 
2015 Feb 15   AVANTI takes over operation 
2016 Apr 22    1436.06 35773 x 35798 x 12.3 GEO 21.3E 
2016 May 20    1436.06 35775 x 35795 x 12.3 GEO 20.7E 
2016 May 25   Move out  1434.42 35732 x 35775 x 12.3 GEO 24.2E+0.5E/d 
2016 Nov 17   Move in 123E  1436.06 35772 x 35799 x 12.5 GEO 123.0E 
2017 Oct 29    1436.17 35776 x 35800 x 12.9 GEO 123.2E 

November 20,2006

  https://en.wikipedia.org/wiki/Association_football