Countdown to a Moon Launch: Preparing Apollo for Its Historic Journey

https://welib.org/md5/d923d58ea637bb6f1fcced08eaac10dc

Earth Orbiter 1

 2000-075A

---

EO-1 is the first Earth observing mission in the New Millenium Program, managed by NASA-GSFC. This is a next generation Landsat flight demo and will fly in the same orbit as Landsat 7 for comparisons, about one minute behind. Formation flying will involve a hydrazine thruster.

A PPT plasma thruster, with an SI of order 1000s, will be used for experimental attitude control.

The spacecraft frame is built by Swales Aerospace/Colorado Springs with heritage based on the MIDEX bus (also used for MAP). Mass is 588 kg full 566 dry (22 kg hydrazine). 2 kg of hydrazine will be used to reach initial orbit. Shape hexagon + 1 panel. 1.25dia 0.73high. Span about 5.5m.

The ALI has multispectral (30m) and panchromatic (10m) bands from 4000A to 2.5 microns, with a 36 km swath with a 0.12m SiC telescope.

In 2005, EO-1 entered an extended mission. It was taken out of formation with Landsat-7 and the orbit was slowly lowered while science operations continued. Orbit lowering was intended to reduce orbital life but in Mar 2017 when it was retired still in relatively high orbit, it was expected to stay up for another 4 decades.

EO-1
Date	Time	Event	Orbit
2000 Nov 21	1824:25	Launch by Delta 7320-10	V SLC2W
		T+1:04 SRM 1-3 out
		T+1:39 SRM 1-3 sep 31 km	-6350 x 35?
		T+4:24 MECO
		T+4:27 VECO
		T+4:29 St 1 sep
		T+4:37 SES-1 112 km 4.84 km/s	-4900 x 150 ?
		T+4:57 Fairing sep 126 km 4.90 km/s	-4830 x 165 ?
	1835:41	T+11:16 SECO-1	185 x 713 x 98.2
	1920:00	T+55:35 SES-2
		T+55:45 SECO-2	705 x 705 x 98.2
	1924:25	T+1:00:00 EO-1 sep
	1937:45	T+1:13:20 DPAF sep
		T+1:24:51 SES-3
		T+1:25:09 SECO-3	685 x 705 x 98.3
	1955:10	T+1:30:45 SAC-C sep
		T+1:48:20 SES-4 depletion
		T+1:48:31 SECO-4	697 x 1800 x 95.4
	2014:25	T+1:50:00 Munin sep
2000 Dec 31			98.83 701 x 703 x 98.2
2005 Sep 27			98.83 701 x 703 x 98.2
2005 Sep 28		Orbit lower	98.72 696 x 698 x 98.2
2005 Nov 15		Orbit lower	98.70 694 x 698 x 98.2
2005 Dec 14		Orbit lower	98.67 693 x 697 x 98.2
2006 Feb 14		Orbit lower	98.63 689 x 696 x 98.2
2006 Mar 1		Orbit lower	98.61 687 x 696 x 98.2
2006 Apr 5		Orbit lower	98.59 686 x 695 x 98.2
2006 Aug 4			98.59 687 x 695 x 98.2
2017 Mar 17			98.34 671 x 686 x 98.2
2017 Mar 30		end of ops

Payload:

• ALI Advanced Land Imager, visible and SWIR (MIT-LL)

• Atmospheric Corrector, hsi to measure reflectance

• Hyperion Imaging spectrometer, 30-m res and 220 bands.

• Primex Teflon pulsed plasma thruster

LKW-2

 2017-084A

---

Land Survey Satellite 2. Launched 2017 Dec 23 to LTDN SSO. Rumoured to be a CAST-developed high resolution imaging spy satellite. Launched into the same plane as LKW 1 but 180 degrees part in phase.

LKW
Date	Time	Event	Orbit
2017 Dec 23	0414	Launch by CZ-2D	JQ
	0423?	Stage 2 sep	489 x 502 x 97.5
	0431?	Stage 2 deorbit
	0457?	Stage 2 impact Antarctic?

LISA Pathfinder

 2015-070A

---

ESA/Airbus ST-7/SMART-2, a single spacecraft with separate NASA (ST7) and ESA (SMART-2) payloads as a LISA/DARWIN technology demonstrator. One satellite which will carry the LTP (Lisa Technology Package) and the DRS (NASA Disturbance Reduction System) in a 1.0m high 2.3m dia octagonal box. A liquid propulsion module will take it from LEO to L1. Launch by Vega.

LISA Pathfinder
Date	Time	Event	Orbit
2015 Dec 3	0404:01	Launch by Vega
		T+1:53 St 1 sep
		T+1:54 St 2 on
		T+3:37 St 2 sep
		T+3:49 St 3 ig
		T+4:19 Fairing
		Stage 3 burnout
		T+6:30 St 3 sep
		T+7:29 St 4 MES-1
	0420	T+16:23 MECO-1 428 km 7.30km/s	208 x 1166 x 6.0
	0454:07	T+50:46 Apogee 1165km 6.48 km/s
	0545	T+1:41:19 MES-2
	0546	T+1:42:53 MECO-2 215 km
	0549	T+1:45:33 LP sep	200 x 1540 x 6.5
	0559	T+1:55:10 AVUM MES-3 7s burn
		T+1:55:17 AVUM MECO-3
		PM burns
	0330:00	Test burn	207 x 1567
	0332:55	End burn, 8.88m/s
2015 Dec 7 0501:36	ARM-1 28m	123.65 293 x 3394 x 6.0
	0530:00	ARM-1 end, 393.2m/s
	1720:50	ARM-2 33m	440 x 7091
	1754:42	ARM-2 end, 552.3 m/s
2015 Dec 8	0730:47	ARM-3 20m	557 x 14137
	0801:50	ARM-3 end, 603.1 m/s
	2105:52	ARM-4 34m 806 m/s	733 x 43641
	2138:58	ARM-4 end, 806.7m/s
2015 Dec 10	0033:31	ARM-5 15m	748 x 124805
	0048:19	ARM-5 end 398.2m/s
	0500:00	RCS TCM test burn
	0500:26	TCM test end, 0.30m/s
2015 Dec 12	0518:23	Insertion (ARM-6) 9m	250m/s L1 transfer traj
	0527:00	Insertion end, 233.9m/s
	1832	Pass EL1:4
2015 Dec 23	0200:00	TCM-2
	0203:49	TCM-2 end, 2.87m/s
2016 Jan 3	0000?	Enter L1 region (GSEx past 1.2Mkm)
2016 Jan 20		TCM 64s, L1 arrival
			500000 x 800000 around L1
2016 Jan 22	1130	PRM sep
2016 Feb 15		1st Test mass released
2016 Feb 16		2nd Test mass released
2016 Mar 10	1010	PRM GSEx below 1.2Mkm
2016 Jul 5	1306	PRM perigee 23300 km	16950 x 1240000 x 39.8
2017 Mar 18		DRS operation
2017 Apr 9	1200	Departure burn, 1 m/s towards solar orbit
2017 Apr 29		DRS operations end
2017 Jun 30		end of ops
2017 Jul 18	1757	Decomissioned

Payload:

• LTP LISA Technology Package, Prototype LISA optical bench with two gravity sensors 30cm apart, and proof mass sensing (ESA/) - test masses Jake and Elwood

• DRS Disturbance Reduction System (ST7), two gravity sensors, drag free control, and laser interferometry.

Eros B

 2006-014A

---

IAI, 500 km SSO, 0.7m res. pan camera. 290 kg; 2.26m high, 1.23m dia, 3.6m span. In 2014 it was reported that the satellite was expected to continue operating until 2022.

EROS B
Date	Time	Event	Orbit
2006 Apr 25	1647:16	Launch by Start-1	SVOB
	1648?	T+1:26 St 1 sep, Stage 2 burn
		T+1:54 sep of 4 SO1 interstages
	1649?	T+2:27 St 2 sep, Stage 3 burn
		T+3:28 St 3 sep
		T+4:48 GO sep
	1655:47	T+8:31 Stage 4 burn
	1656:41	T+9:25 Stage 4 burnout, DDU burn
	1700:14	T+12:58 DDU burnout
	1702:53	T+15:37 St4-DDU sep from payload EROS-B	503 x 513 x 97.3

Payload:

• Imager, 0.7m resolution

Fenghuo 2

 2006-038A

---

Fenghuo-1 02 xing (\uni{ 烽火一号卫星（02星）)}{ } will go to 98E for tactical communications.

Zhongxing-22A
Date	Time	Event	Orbit
2006 Sep 12	1602	Launch by CZ-3A	XSC
		T+2:25 Stage 1 MECO
		T+2:27 Stage 2 MES, Stage 1 sep
		T+3:52 Fairing sep
		T+4:15 St 2 MECO
		T+4:20 St 2 VECO
		T+4:21 St 2 sep, St 3 MES
	1612?	T+10:19? St 3 MECO-1	200 x 200 x 28.5?
	1622?	T+20:00 St 3 MES-2
	1624?	T+22:00 St 3 MECO-2
	1627	Sep from Stage 3
2006 Sep 12			752.00 202 x 41826 x 25.0
2006 Sep		Apogee burns
2006 Sep 19			1436.60 35758 x 35834 x 0.3 GEO 97.8E+0.13W/d
2006 Oct 2			1436.08 35756 x 35816 x 0.4 GEO 98.0E+0.0W/d
2008 Jun 18			1436.08 35778 x 35794 x 0.1 GEO 98.1E
2008 Jun 25		Move in at 103E	1436.10 35785 x 35787 x 0.0 GEO 103.3E
2009 Dec		NSSK ends
2011 Jan 23			1436.17 35768 x 35807 x 1.1 GEO 103.2E
2012 Nov 4			1436.10 35776 x 35796 x 2.6 GEO 103.3E
2012 Nov		Drift to 101.5E
2012 Dec 17		Move in at 101.5E	1436.08 35779 x 35793 x 2.7
2015 Nov 14			1436.10 35755 x 35181 x 4.8 GEO 101.4E
2017 Nov 21		1436.11 35745 x 35828 x 6.1 GEO 101.2E
2017 Nov 24		Begin drift
2017 Dec 6			1437.16 35768 x 35847 x 6.1 GEO 101.4E+0.4W/d
2017 Dec 12			1439.00 35827 x 35860 x 6.1 GEO 97.4E+0.7W/d

Old money America : aristocracy in the age of Obama

https://welib.org/md5/b96d0316ffdd6fd70ad55dfc59e56081

Alcomsat 1

 2017-078A

---

ASAL comms satellite using CAST DFH4 bus. Control from Medea and Ouargla. Called Algeria yi hao tongxin weixing (Algeria No. 1 Communications Satellite) by China.

Alcomsat-1
Date	Time	Event	Orbit
2017 Dec 10	1641	Launch by CZ-3B	XSC
		T+2:07 Booster sep
		T+2:27 St 1 sep
		T+3:52 Fairing
		T+5:32 St 2 sep
		T+5:32 St 3 MES-1
	1651?	T+10:31? MECO-1	160? x 450? x 28.5?
	1702?	T+21:21? MES-2
	1705?	T+24:20? MECO-2	200 x 41991 x 26.4
	1707?	St 3 sep

LKW-1

 2017-077A

---

Land Survey Satellite 1. Launched 2017 Dec 3 to 1030 LTDN SSO. Rumoured to be a CAST-developed high resolution imaging spy satellite.

LKW
Date	Time	Event	Orbit
2017 Dec 3	0410	Launch by CZ-2D	JQ
	0420?	Stage 2 sep	489 x 502 x 97.5
	0428?	Stage 2 deorbit
	0454?	Stage 2 impact Antarctic?

AGILE

 2007-013A

---

AGILE (Astrorivelatore Gamma ad Imagini Leggero, Light Gamma-Ray Imaging Astronomical Detector) was developed for ASI using Carlo Gavazzi Space Spa/Milano MITA bus and CGS project management. PSLV to 550 x 550 x 6 deg, mass 352 kg. Perigee was a little low (523 km instead of 550 km).

PSLV modified to carry light payload; no PSOM and 400 kg of prop offloaded from the PS4 stage.

Sensitivity less than EGRET on-axis, but much better off-axis performance. 2.5 sr FOV. GRID has 5' to 20' resolution. The GRID MC (MiniCalorimeter) will also detect bursts in the 0.3-200 MeV range and Super-AGILE will give simultaneous hard X-ray data.

The AGILE (Light Imager for Gamma Astrophysics)

Launched with PSLV Advanced Avionics Module (180 kg) inside the Dual Launch Adapter.

SUPER AGILE 4 x 1D coded masks bibcode NIM-A 581, 728F Feroci et al 2007 45 sources seen to date, mostly XBs, some AGN, 2 GRB

In 2009 the reaction wheel malfunctioned, ending AGILE's ability to point at targets. Following this, AGILE was spun around the sun-pointing axis at 1 degree per second, surveying 70 percent of the sky each day.

AGILE
Date	Time	Event	Orbit
2007 Apr 23	1000	Launch by PSLV C-8	SDSC SLP
		T+0:53 Sep PS1 50 km 1.737 km/s	-6240 x 70? x 6
		T+0:53 PS2 burn 50 km 1.736 km/s
		T+3:23 Fairing sep 116 km 2.95 km/s	-5900? x 130? x 6
		T+4:23 PS2 sep 147 km 4.743 km/s
		T+4:24 HPS3 burn 148 km 4.7842 km/s	-4900? x 150? x 6
	1008	T+8:38 HPS3 burnout 283 km 7.581 km/s	-450? x 510 x 6
	1017	T+17:13 PS4 burn 508 km 7.317 km/s	-450? x 510 x 6
	1022	T+22:11 PS4 burnout 550 km 7.583 km/s
	1022	T+22:53 PS4 sep from Agile
2007 Apr 24			95.40 523 x 552 x 2.5
2009 Oct 18		Reaction wheel failed
2009 Nov 4		Spinning mode
2014 Mar 14		Mission restarted

Payload:

• GRID Gamma-ray Imaging Detector 30 MeV-50 GeV detector using a Si/W tracker, CsI mini-calorimeter (GRID-MC) and anticoincidence system.

• GRID-MC CsI mini-calorimeter 0.3-200 MeV

• Super-AGILE Hard X-ray detector 15-45 keV, FOV 0.8sr, 3' res

RazakSat

 2009-037A

---

Abdul Razak bin Haji Dato' Hussein Al-Haj (1922-1976), politician

Malaysia's MACSat (Medium size Aperture Camera sat), named RazakSat after Tun Abdul Razak Dato' Hussain, former Malaysian PM is based on a Korean satellite bus, the SI-200 (KitSat-3 and STSAT-1). Mass is 200 kg.

The ATSB/Kuala Lumpur project is cooperatibe with SatReci/Daejeon, S Korea. Size 1.20m dia 1.20m high hexagon+ 3 panels, 3.0? span.

Launch by Falcon 1.

MOSTI Ministry of Sci Tech and Industry.

The Angkasa (AAN, Agensi Angkasa Negara, National Space Agency) is also involved, and possibly the MACRES (Pusat Remote Sensing Negara, Malaysian Center for Remote Sensing). 

RazakSat
Date	Time	Event	Orbit
2009 Jul 14	0336	Launch by Falcon 1	Omelek
	0338	T+2:41 MECO
	0338	T+2:42 St 1 sep
	0338	T+2:45 St 2 burn
	0339	T+3:15 Fairing sep
	0339	Engine Bands sep
	0342	230 km alt
	0342	243 km 3800m/s
	0343	255 km 4150m/s
	0343	4800m/s 265 km
	0344	T+8m 5400 267 km
	0346	T+9:00 6400 266 km
	0346	T+9:35 SECO	266? x 688?
	0424?	SES-2
	0424?	SECO-2
	0426?	Sat sep
2009 Jul 14			98.30 665 x 688 x 9.0
	0438	Stage 2 depletion?
2009 Jul 14		Stage 2 orbit	97.77 616 x 687 x 9.0
2009 Jul 29			98.30 664 689 x 9.0
2014 Jul 21		End of ops

Payload:

• MAC 0.30m telescope-camera with CCD arrays

The Hutchinson Illustrated Encyclopedia of British History

 https://welib.org/md5/cc3d8255f777448963e55fd7a862aa76

The Ultimate Game of Thrones and Philosophy: You Think or You Die

 https://welib.org/md5/ab8b2b7459f97e097edd8ea251755d92

Sentinel 5 Precursor

 2017-064A

---

S5P is a gapfiller between Envisat and Sentinel 5. It flew in a 800 km polar, 1330LTDN SSO orbit, studying atmospheric chemistry at high temporal and spatial resolution. Sentinel 5's main payload will fly on Metop Second Gen.

S5P
Date	Time	Event	Orbit
2017 Oct 13	0927:44	Launch by Rokot	Plesetsk
		T+2:15? St 1 MECO
		T+2:16 St 1 sep
		T+3:03 GO sep
		T+5:17? Stage 2 MECO
	0933:03	T+5:19 Stage 2 sep
	0933	Briz-M MES-1
		SOZ-1 CO
	0941	T+14:19? MECO-1
	1045?	T+1:18:10? MES-2
		MECO-2
	1046	Briz-KM sep	816 x 820 x 98.7
	1124?	Briz-KM depletion	434 x 774 x 98.7

Payload:

• Tropomi UV/VIS/NIR/SWIR spectrometer tropospheric monitor (DutchSpace/) 2700A-4950A, 7100-7750A, 2.30-2.39 mu

The News of the World and the British Press, 1843-2011

 https://welib.org/md5/3ceb516f118315a5a8782f4a0c655004

The Big Book of the Hamptons

 https://welib.org/md5/0cc7595617eee13f7a1ea31aa6172a3c

Kodama

 2002-042B

---

DRTS, a Data Relay Test Satellite for data relay and intersatellite communications, was built by Mitsubishi. DRTS was named Kodama ('echo'). Originally two satellites were to be launched, but DRTS-E was cancelled in 2001 and only DRTS-W was retained.

DRTS was a box + 2 panels + antenna, mass 2800 kg launch, 1500 kg BOL. 1300 kg dry. Size 2.2 x 2.4 x 2.2m with 17m span. The 1700N IHI COMETS UPS was downrated to 500N for a gentler burn. Ka/S band 3.6m dia dish. At 90E. Kodama was launched in 2002 by H2A. The third apogee firing failed due to oxidizer depletion. RCS firings later got Kodama to GEO at 90.8E.

Carried out the High Speed Data Relay Experiment, 240 Mbit/s; High Accuracy Acquisition and Tracking Tech Expt., for onboard acquisition of the satellites that DRTS relays from and to; and the Communications Network Experiment, with time allocation methods on user satellites. Kodama relayed some Earth images from Midori-II; after that satellite failed, Kodama had to wait for the launch of Daichi.

DRTS
Date	Time	Event	Orbit
2002 Sep 10	0820	Launch by H2A 2024	TNSC
		T+1:10 SSB 1-2 on
		T+1:46 SRB-A sep
		T+1:47 SSB 3-4 sep
		T+2:24 SSB 1-2 sep
		T+4:10 upper fairing sep
		T+6:28 MECO (earlier than this)
		T+6:36 Stage 1 sep
		T+6:42 SES-1
		T+12:58 SECO-1 (later)
		T+13:48 USERS sep
		T+16:18 Lower fairing sep (2 pieces + adapter)
		T+26:17 SES-2
		T+28:42 SECO-2
		T+29:18 DRTS sep
2002 Sep 11	0021	LAM1 Apo 2, 60 min burn	780.99 7414 x 36013 x 12.0
2002 Sep 12	0221	LAM2 Apo 4, 60 min burn
2002 Sep 13	0126	LAM3 Apo 5; failed after 103s of 204s
2002 Sep 14		AOCS burn to correct for GEO
2002 Sep 15		Deploy antennas
2002 Sep 19			1446.16 35936 x 36029 x 0.1 GEO 134.4E-2.5W/d
2002 Oct 6			1441.04 35832 x 35934 x 0.1 GEO 93.4E-1.2W
2002 Oct 10			1436.56 35777 x 35814 x 0.1 GEO 90.8E
2002 Oct 11		On station
2003 Jan 10		Declared operational
2003 May 9			1436.11 35779 x 35794 x 0.1 GEO 90.8E
2003 Oct 29		Safemode after solar flare
2003 Nov 25		Operations resumed
2006 Jan		Tests with Daichi scheduled
2006 Aug 6			1436.11 35774 x 35799 x 0.1 GEO 90.7E
2017 Jul 28			1436.07 35778 x 35794 x 5.1 GEO 90.9E
2017 Jul 31		Orbit raise
2017 Aug 3		Orbit raise	1450.33 35971 x 36167 x 5.1

Insat 3C

 2002-002A

---

Mass 2750 kg launch, 1050 kg dry. Size 2.8 x 1.7 x 2.0 m with 15.4 m span. This was the last planned Ariane 42L launch, and used a trajectory with a high initial perigee of 570 km. 3C will be placed at 74E.

Insat 3C was colcated with Kalpana 1 at 74E.

\imps{2.5}{images/02002A}

Insat 3C
Date	Time	Event	Orbit
2002 Jan 23	2347	Launch by Ariane 42L	CSG ELA2
		T+2:19 PAL sep
		T+3:13 St 1 sep
		T+3:16 St 2 MES
		T+3:39 Fairing sep
		T+5:25 St 2 sep
		T+5:30 St 3 MES
		T+12:15	-2900 x 507
2002 Jan 24	0005	T+18:30 MECO
	0007	T+20:52 Insat 3C sep
		T+22:52 end of V147 mission
2002 Jan 24			638.54 580 x 35790 x 4.0
2002 Jan 25		LAM-1	817.02 9363 x 35780 x 1.7
2002 Jan 27		LAM-2	1015.11 18365 x 35794 x 0.8
2002 Jan 30	?	LAM-3	1428.37 35490 x 35779 x 0.19 GEO 67E+2E/d
2002 Feb 1	Deployment of solar panels
2002 Feb 9		LAM	1435.90 35760 x 35804 x 0.1 GEO 74E
2002 Jul 20			1436.11 35767 x 35805 x 0.0 GEO 74.0E
2004 Jul 21			1436.10 35771 x 35802 x 0.0 GEO 74.0E
2006 Aug 3			1436.09 35765 x 35807 x 0.1 GEO 74.0E
2017 Jan 12			1436.10 35764 x 35808 x 0.3 GEO 74.0E
2017 Jan 13		Move out
2017 Feb 27		Move in	1436.08 35756 x 35815 x 0.4 GEO 93.5E
2017 Jul 16			1436.17 35777 x 35798 x 0.7 GEO 93.3E

Endurance : My Year in Space, A Lifetime of Discovery

 https://welib.org/md5/f4c615d6b5c2a2c2fb2c83a98ede7451

STS-120 (Discovery)

 2007-050A

---

Mission 10A with Node 2 Harmony.

Landing mass 90713 kg. OMS prop 11308 kg. Node2 + PDGF mass 14371 kg per media reports, or 14355 kg per MR. Assume PDGF is 33 kg.

MBSU 2nd spare ORU on GABA beam up on STS-102, stow on ESP-2 nadir. The GABA beam is 80 kg, 122 kg including interface plate assembly. The ORU integrated assembly is 238 kg. SASA mass transferred from ISS 108 kg.

Another beam carries FSE to support the return of a SASA antenna to Earth.

RMS 202; IBA 203.

Parazynski is EV1 (STS EMU 3004), Wheelock is EV2 (STS EMU 3003), Tani is EV3 (3018), Whitson EV4 (3018), and Malenchenko EV5 (3006).

EVA-1. Para/Wheelock, retrieve SASA, prep Node 2, disconnect P6 umbilicals and install SSU shroud.

EVA-2 (Para/Tani), P6 disconnect, detach; node 2 outfitting, prep MBSU, install PDGF on Node 2.

EVA-3 (Para/Wheelock): P6 install on P5, connect, transfer MBSU.

EVA-4 (Para/Wheelock): T-RAD DTO 848.

EVA-5 (Whitson/Malenchenko): Umbilicals, CBM work, mate cables.

Pre-OMS-2 mass 116298 kg; post OMS-2 113665 kg.

STS120
Date	Time	Event	Orbit
2007 Sep 23		Roll to VAB
2007 Sep 25		ET mate
2007 Sep 30		Roll to LC39A
2007 Oct 23	1538:19	Launch	LC39A
	1540:22	T+2:03 SRB sep
	1540:32	OMS ASS
	1542:29	OMS ASS CO
	1546:44	T+8:24 MECO
	1547:06	T+8:50? ET sep	59 x 228
	1615:38	T+38:18 OMS-2 2:33 70.7m/s
	1618:10	OMS-2 CO	228 x 296 x 51.6
	1618		89.75 228 x 295 x 51.6
	1652?	ET-120 reentry
	1718:09	PLBD open
	1831:08	OMS-3 NC-1 26.0m/s
	1832:02	OMS 3 CO
	2329		90.64 292 x 319 x 51.6
2007 Oct 24	0113		90.64 293 x 318 x 51.6
	0850:44	OMS-4 burn 6m/s
	0850:57	OMS-4 CO
	1608		90.8 312 x 321 x 51.6
	1927?	burn 1m/s	90.89 313 x 322 x 51.6
2007 Oct 25	0726:20	OMS-5 burn 7.5m/s
	0726:36	OMS-5 CO
	0813:12	OMS-6 R
	0813:23	OMS-6 CO
	0955:25	OMS-7 L TI
	0955:37	OMS-7 CO
	1109:41	MC3
	1119:11	MC4
	1134	Begin RPM, 180 m below station
	1143	Complete RPM
	1150	On -Rbar, begin flyaround
	1200	On +Vbar at 119m, begin approach
	1239:58	Docking with PMA-2/Destiny
	1439	HO to ISS
	1612	Tani IELK transfer
2007 Oct 26		EVA-1 Wheelock, Para	91.37 339 x 343 x 51.6
	0949	At 2 psi
	1001	Depress, 0.5 psi
	1001	HO
	1002	Battery power
	1006	Egress Para
	1012	egress Wheelock
	1032	Remove SASA from Z1
	1125	Mounted SASA on FSE in bay
		Prep Harmony for unberth
	1200	PDGF unberthed by EV
	1206	PDGF tethered to Harmony
	1315	SSRMS grap Harmony
	1340	Unberth Harmony
	1430	P6/Z1 NH3 disconnects removed
	1538	Harmony soft capture at CBM on Unity stbd(?)
	1543	Wheelock ingress
	1545?	Para ingress
	1558	HC
	1610	Ungrap Harmony
	1616	Repress, end EVA-1 (NASA 6:14)
	1622	At 3.5 psi
2007 Oct 28		EVA-2 Para, Tani
	0051		339 x 343 x 51.6
	0827?	SSRMS ungrapple Lab
	0912	2.0 psi
	0917?	SSRMS grapple P6
	0927	0.8 psi
	0927?	Depress
	0932	HO
	0932	Battery power
	0948?	Para egress
	0950?	Tani egress
	1053	P6/Z1 bolts released
	1103	P6 unberthed from Z1
	1154	SSRMS and P6 in park position
	1300	Tani inspecting SARJ at S3/S4
	1330	Para installing handrails on Node-2
	1430	Tani working S0 cabling in prep for P6
	1445	Begin work on PDGF install
	1535	PDGF installation complete
	1540	Tani prep to ingress
	1550	Ingress Tani
	1553	Ingress Para
	1554	Closing TC
	1600	HC
	1605	Repress (NASA 6:33)
	2211		91.38 340 x 343 x 51.6
2007 Oct 29
	0530?	S1 radiator 1 deploy
	0550	S1 radiator 3 deploy
	0704	RMS grapple P6
	0832	SSRMS ungrapple P6
		MBS translate from WS4 to WS8
	1252	SSRMS in motion
	1314	SSRMS grapple P6
	1321	RMS ungrapple P6
2007 Oct 30		EVA-3 Para, Wheelock
	0834	Airlock at 2 psi
	0835	1.5 psi
	0840	0.9 psi
	0841	0.7 psi, Depress
	0843	0.5 psi, go for HO
	0844	HO
	0845	Battery power
	0851	WHeelock egress
	0900	Para egress
	0947	P6 at preinstall on P5
	1015	First contact P6/P5
	1017	Capture claw engaged
	1110	P6 bolted to P5
	1131	SSRMS ungrapple P6
	1250	P6 radiator deploy
	1253	P6 radiator deploy complete
	1310	Para Inspect port SARJ
	1352	Wheelock on RMS translating from Node1 to bay
	1401	At MBSU
	1407	Wheelock on RMS carrying MBSU
	1429	MBSU docked on ESP3
	1441	P6 2B one bay deployed
	1532	P6 SAW 2B fully deployed
	1540?	Ingress
	1542	In airlock
	1545	Hatch closed
	1553	Repress
	1609	4B deploy begin
	1624:38	4B array tears; abort deploy	91.38 340 x 343 x 51.6
2007 Nov 2	0946	MT WS8 to WS3
	1258	SSRMS unberth OBSS	91.38 339 x 344 x 51.6
	1340	SRMS grapple OBSS, SSRMS release
	1500	MT WS3 to WS8
2007 Nov 3
		EVA Para, Wheelock
	0852	SSRMS grapple OBSS
	0909	SRMS ungrapple OBSS
	0949	2.5psi
	1000	0.7 psi DEPRESS
	1002	HO
	1003	Battery power
	1012	Egress Para
	1019	Egress Wheels
	1110	Para on boom	91.38 340 x 344 x 51.6
		Wheelock along truss to base of 4B
	1203	Para parked near 4B
	1228	Completed inspection of site
	1250	Cufflink 3 one end installed
	1309	Cuff 3 installed
	1341	Cut hinge wire
	1352	Cut guide wire
	1418	Prep for cuff 1
	1425	Cuff 1 installed
	1432	Cuff 2 installed
	1447	Cuff 4 installed
		Cuff 5 installed
	1511	Extending array
	1523	Deploy complete
	1532	SSRMS moving Para back home
	1605	Egressing APFR
	1629	Prep for ingress
	1635	Lose loose pliers
	1640	Stowing stuff at airlock
	1642	Ready for 4B tensioning
	1655?	Wheelock ingress
	1706	Para ingress
	1712	HC
	1722	Repress
	1746	SRMS grapple OBSS
		SSRMS ungrapple OBSS
2007 Nov 4	1946	HC on OV side
	2003	HC
2007 Nov 5
	1032:02	Undocking
	1038	+V 25m
	1100	+V begin flyaround 100m
	1110	+R 150m
	1123	-V
	1133	-R nadir
	1146	+V Sep-1
	1214	+R Sep-2	91.38 339 x 344 x 51.6
2007 Nov 6			91.39 340 x 344 x 51.6
	1348	Maui burn
	1954:19	OMS-8 both, orbit adj 30m/s 56s	234 x 339 x 51.6
	1955:13	OMS-8 CO
2007 Nov 7
	1418:45	PLBD closed
	1658:49	OMS DO 1:53
	1700:43	OMS DO CO 65.5m/s	15 x 339
			22 x 348 (MR)
	1729:43	Entry interface
	1801:18	MGTD KSC RW33
	1801:32	NGTD
	1802:13	WS