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

https://welib.org/md5/d923d58ea637bb6f1fcced08eaac10dc

Earth Orbiter 1

 2000-075A

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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

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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

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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

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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

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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

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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

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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

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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