USA-147

 1999-067A

---

The first 5D-3, S-15 (F-15 after launch) launched by Titan II in Oct 1999. It was placed in a 0915/2115LT orbit, later than earlier missions to help tactical operations. F-15 replaced F-12 and F-14 in one of the two DMSP planes. S-15 used the 5D-3 bus but carried the old 5D-2 payload complement.

By the time 5D-3 was launched, DMSP was operated by NOAA although managed by USAF SMC. NOAA SOCC/Suitland, MD checks out the spacecraft. It's turned over to the NPOESS IPO (Nat. Polar Orbiting Env Satellite System Integrated Program Office), which delegates operations back to the NOAA OSO (Office of Satellite Operations). Mass was 1030 kg. Size was 7.3m long.

According to Jane's Spaceflight Directory, the 5D-3 was intended to carry a "Star 37FP" apogee motor with a 19 percent offload. This may be the same as the Star 37XFP.

DMSP F-15
Date	Time	Event	Orbit
1999 Dec 12	1738:01	Launch by Titan II	V SLC4W
		T+2:45 Stage 1 sep
		T+4:00? Fairing sep
	1743:41	T+5:40 Stage 2 MECO
	1744:15	T+6:14 Stage 2 sep
	1751:38	T+13:37 Star 37 burn
	1752:29	T+14:28 Star 37 burnout
	1757:31	T+19:30 Solar array deploy
	1805?	Stage 2 reentry
1999 Dec 19			101.81 837 x 851 x 98.9
2003 Nov		Secondary status
2006 Aug 14		orbit adjust
2007 Apr 29			101.69 833 x 843 x 98.5
2007 Jul		Still operating
2016 Mar		Secondary operational sat at 0240 LT

Eutelsat W3

 1999-018A

---

The W3 satellite replaces Eutelsat 2F4. W Loc are 7 10 and 16E. W3 will go to 7E. Type is Spacebus 3000B2. Launch mass 3177 kg. Dry mass 1380 kg.

Design similar to W2, with a main shaped reflector pair and a steerable antenna.

W3 moved to 22E in Nov 2004; it was observed there by amateurs on Nov 28 while the NORAD report still placed it at 48E.

Date	Time	Event	Orbit
1999 Apr 12	2250	Launch by Atlas 2AS AC-154	CC LC36A
		T+00:56 SRM1-2 burnout
		T+00:59 SRM3-4 burn
		T+1:09 SRM1-2 sep
		T+1:53 SRM3-4 burnout
		T+1:56 SRM3-4 sep
		T+2:43 BECO
		T+2:47 Booster sep
		T+3:19 Fairing sep
		T+4:59 SECO
		T+5:01 Atlas sep
		T+5:03 Nozzle deploy
		T+5:18 MES-1
	2259	T+9:45 MECO-1	89.90 153 x 385 x 27.4
	2314	T+24:31 MES-2
	2316	T+26:17 MECO-2
	2318	T+28:55 Centaur sep	166 x 46076 x 19.7
	2359:35	T+1:09:35 Depletion
1999 Apr 14	1002?	LAM-1
1999 Apr 14			946.41 5403 x 45701 x 10.9
1999 Apr 16	0921?	LAM-2	22278 x 45723 x 2.6
1999 Apr 21?		LAM-3
1999 Apr 21			1431.13 35460 x 35917 x 0.1 GEO 4.0W+1.2E
1999 Apr 27		Control from GSOC to ESCC/Paris
1999 May 6			1436.08 35771 x 35801 x 0.0 GEO 1.7E
1999 May		move to 7E
1999 Jun 1			1436.10 35780 x 35792 x 0.0 GEO 7.0E
1999 Nov 8			1436.07 35770 x 35801 x 0.0 GEO 7.0E
2004 May 20			1436.03 35770 x 35800 x 0.0 GEO 7.1E
2004 Jun		Move out
2004 Jul		Pass 22E
2004 Aug 26			1436.40 35778 x 35806 x 0.0 GEO 49.5E+0.1W/d
2004 Sep 10			1436.44 35778 x 35808 x 0.0 GEO 48.1E
2004 Nov		Move to 22E, renamed Eutelsat W6
2004 Nov 28			1436.10 35773 x 35800 x 0.0 GEO 48.0E
2004 Dec 2			1436.11 35778 x 35794 x 0.0 GEO 21.7E
2006 Aug 1			1436.09 35769 x 35803 x 0.1 GEO 21.6E
2012 Mar 1		Renamed EUTELSAT 21A
2012 Mar 2			1436.11 35768 x 35805 x 0.1 GEO 21.6E
2012 Dec 19			1436.06 35767 x 35803 x 0.1 GEO 21.6E
2012 Dec 20		Move out
		Replaced by 21B, moving to 48E
		Renamed Eutelsat 48C
2013 Jan 10			1432.88 35711 x 35735 x 0.1 GEO 38.5E+0.8E/d
2013 Jan 27		Move in	1436.03 35741 x 35828 x 0.2 GEO 48.0E

NASA Kennedy Space Center (Images of Modern America)

 https://welib.org/md5/91bd9ae7d74bb48268b9716d32d7bc91

Astronomy: A Self-Teaching Guide

 https://welib.org/md5/14d70b1abde59ab765151c15bb879938

Soyuz TMA-12M (Cliff)

 2014-013A

---

7220 kg launch mass of which 564 kg oxidizer and 316 kg fuel. At undocking, 6790 kg of which 432 kg prop.

Soyuz TMA-12M was launched on what was intended as a quick six-hour rendezvous. The DV3 and DV4 burns were computed to be smaller than normal because of launch vehicle overperformance, and a software glitch aborted them. The mission fell back on the old standard two-day rendezvous plan, which completed successfully on Mar 27.

Skvortsov, Artemev and Swanson returned to Earth on TMA-12 in September.

TMA12M
Date	Time	Event	Orbit
2014 Mar 25	2117:23	Launch by Soyuz-FG No, 47	KB LC1/5
		T+2:37 SAS sep
		T+4:45 Blok A MECO
		T+4:47 Blok A sep
		T+8:45 MECO
	2126:11	T+8:48 Blok I sep
	2202:15	DV1 33.9m/s 84s
	2246:43	DV2 25.8m/s 64s	302 x 350 km
	2338	T+2:04 DV3 10.1m/s planned, 0 achieved
		Rendezvous delayed
	0426:52	DV3, 84.6s 34.8 m/s
	0514:15	DV4, 60s 24.8m/s	414 x 440
2014 Mar 26	2238:59	DPO burn 28s 2.0m/s
2014 Mar 27
	2332	Begin flyround, 400m
	2342	Complete flyaround
	2345	Range 125m
	2353:28	Docked with Poisk
2014 Mar 28
	0245	HO to ISS
2014 Sep 10
	1951	HC to ISS
	2301:30	Undock from Poisk
	2304:30	Sep burn 15s 0.54m/s
2014 Sep 11
	0130:36	Deorbit burn 4:40 128 m/s
	0135:16	DO CO	-22 x 418 x 51.6
	0158:21	Modules sep
	0201:15	Entry 100 km
	0223:07	Landed

DSP-23

 2007-054A

---

S99-1 SABRS, Space Atmospheric Burst Reporting System, (originally SAVE, Space and Atmospheric Validation Experiment)

Test NUDET planned for SBIRS GEO-3, piggyback box on DSP-23. The package can detect small-yield nuclear tests.

Launch by Delta 4H

Early orbit control from SBIRS MOCR at Buckley AFB, then to 14th AF.

2349 kg launch mass. 1102 kg adapter.

Deliver to 4.0 deg inc drift orbit.

DSP 23
Date	Time	Event	Orbit
2007 Nov 11	0150:00	Launch by Delta 4H	CC SLC37B
		T+4:09 Strapon CBC sep
		T+5:33 MECO
		T+5:40 Stage 1 sep
		T+5:53 SES-1 158 km
		T+6:03 Fairing sep
	0202:55	T+12:55 SECO-1	217 x 1576 km x 29.11
		24+ debris particles released
		T+1:15:26 SES-2
		T+1:22:02 SECO-2	919 x 36325 x 26.6
			655.5 918 x 36319 x 26.6 (UN)
	0800:19s	T+6:10:19 SES-3 181s
	0803:20	T+6:13:20 SECO-3	35902 x 35902 x 4.0
	0809:52s	T+6:19:52 Stage 2 sep
2008 Sep 18			1436.12 35755 x 35818 x 3.6 GEO 7.9E
2008 Dec		Move out, drift E
2009 Jun		Over IOR, drifting
2011 Feb 20		Found over IOR, drifting E
2011 Apr		Reversed drift
2011 Dec 15			1436.96 35769 x 35794 x 0.3 GEO 9.3E
2012 Feb		Drifting E
2012 Feb 25			1435.73 35763 x 35795 x 0.3 GEO 13.7E
2012 Sep 7		Drifting over IOR
2016 Jan 1			1434.54 35738 x 35773 x 3.1 GEO 84.7E+0.3E/d

Satmex 5

 1998-070A

---

Hughes/El Segundo will build Morelos 3 (later renamed Satmex 5) to replace Morelos 2 at 116.8W, for Sat'ellites Mexicanos S.A. de C.V. (Satmex), the operator which replaced Telecomunicaciones de Mexico, the Mexican Comms and Transport Ministry. The HS-601HP satellite will have 8 kW of payload power. Launch will be by Ariane 42L with Fairing 01. Mass is 4135 kg launch, 1950 kg BOL. Launch was to a sub-synchronous orbit using the OURS reserve depletion strategy, with the satellite using PVA. Target wsa 200 x 21000 x 7. Size is 3.4 x 2.8 x 6.0m with 26m span.

This was the 4th HS-601HP to carry XIPS.

SATMEX 5
Date	Time	Event	Orbit
1998 Dec 6	0043	Launch by Ariane 42L V114	CSG ELA2
		T+2:21 PAL sep
		T+3:14 St1 sep
		T+3:17 St2 burn
		T+4:05 Fairing sep
	0048	T+5:27 St2 sep
		T+5:32 St3 burn
	0101	T+18:39 St3 MECO
	0102	T+19:37 St3 sep
		T+22:21 end of V114 mission
1998 Dec 6			735.54 211 x 21516 x 7.0
1998 Dec 7	0230?	LAM-1
1998 Dec 12			632.52 224 x 35837 x 7.0
1998 Dec 12	1300?	LAM-2
1998 Dec 15			1049.92 19525 x 35807 x 1.2
1998 Dec 16	0330?	LAM-3
1998 Dec 16			1234.03 27668 x 35795 x 0.5
1998 Dec 17?		LAM-4
1998 Dec 22?		LAM-5
1998 Dec 23			1435.65 35757 x 35798 x 0.1 GEO 116.5W+0.1E
1999 Jan 14			1436.16 35770 x 35805 x 0.0 GEO 116.8W
1999 Nov 5			1436.06 35781 x 35790 x 0.0 GEO 116.7W
2006 Aug 3			1436.08 35777 x 35794 x 0.1 GEO 116.8W
2010 Jan 27		XIPS failed
2013 Apr 30			1436.09 35780 x 35792 x 0.1 GEO 116.8W
2013 May 2		Drift?	1435.37 35764 x 35779 x 0.1 GEO 116.6W+0.2E/d
2013 May 9		On station 115W	1436.12 35775 x 35798x 0.1 GEO 114.9W
2014 May 21		Renamed Eutelsat 115 West A
2015 Jan 18			1436.09 35768 x 35804 x 1.4 GEO 114.9W
2015 Nov 24			1436.10 35764 x 35808 x 2.0 GEO 114.9W
2015 Nov 25		Move out
2016 Jan 6		Move in at 92.2W	1436.06 35776 x 35795 x 2.1 GEO 92.2W
		Reserve ARSAT slot
2016 Mar 7			1436.07 35765 x 35806 x 2.2 GEO 92.2W
2016 Apr 10			1436.11 35762 x 35811 x 2.3 GEO 92.2W

Navstar 47

 2003-058A

---

GPS IIR SV17 (Navstar SVN47) was launched as GPS 2R-10 to Plane E, slot 2 in Dec 2003. 

GPS 47
Date	Time	Event	Orbit
2003 Dec 21	0805:00?	Launch by Delta 7925-9.5	CC SLC17A
		T+1:06 GEM 1-6 sep
		T+2:08 GEM 7-9 off
		T+2:11 GEM 7-9 sep
		T+2:20 St 1 dogleg, 20s
		T+4:23 MECO
		T+4:31 St 1 sep
		T+4:36 SES-1
		T+4:43 St 2 dogleg, 10s
		T+4:58 Fairing sep
	0815:45	T+10:45 SECO-1	174 x 200 x 36.85
	0907:30	T+1:02:30.9 SES-2 39.6s
	0908:10	T+1:03:10.5 SECO-2	187 x 1152 x 37.20
		T+1:04:00 Spinup
	0909:03	T+1:04:03 St 2 sep, 2 clampbands
	0909:40	T+1:04:40.5 TES 86.7s
	0911:07	T+1:06:07.2 TECO	187 x 20368 x 39.0
	0913:00	T+1:08:00 St 3 sep	179 x 20305 x 39.0
	0913:02	T+1:08:02 St 3 yo deploy
	0951:40	T+1:46:40 SES-3
	0952:08	T+1:47:08 SECO-3 depletion	233 x 1131 x 29.86
		T+4:03:09 First apogee
2003 Dec 23	1105	Apogee, possible AKM burn
2003 Dec 23	2311?	AKM burn
2003 Dec 26			716.48 19963 x 20327 x 55.1
2015 Dec 19		Moved to new slot, replaced by IIF-11

Moon Bound: Choosing and Preparing NASA's Lunar Astronauts

 https://welib.org/md5/9f35ed2e8d61445f9018330dc037350c

Echostar 4

 1998-028A

---

Echostar 4, an A2100AX, used an ILS Proton launch. DM3 stage No. 7L placed the satellite in GTO. Mass was 3470 kg full, 1580 kg dry. Bus is 1.8 x 1.8 x 4.5m with 21m span.

Echostar 4 was intended to replace Echostar 1 at 119W (Echostar 1 would go to 148W). It was to become the primary DISH network provider to the US together with Echostar 2, with Echostar 1 and 3 providing local, educational, business and data transmission services for Echostar Satellite Services. However, two of five solar panels on one array did not unfold, limiting power; Echostar claimed a loss on the insurance. An insulation material melted during transfer orbit coast and glued the arrays in their folded position. Echostar was placed at 148W for local and educational broadcasting. In 1999 Echostar 4 was moved to 110W, starting off a new Dish Network service pending the launch of Echostar 5. Then, on 2004 Sep 4 the stuck solar array panels unexpectedly popped open, restoring full power.

In 2005, E4 was moved to 77E to provide service for Mexican company QuetzSat, partly owned by Echostar. It was replaced there by Echostar 1 and 8.

Echostar 4
Date	Time	Event	Orbit
1998 May 7	2345:00	Launch by Proton 393-02	KB
		T+02:02 Stage 2 burn
		T+02:06 Stage 1 sep
		T+05:35 Stage 2 MECO, Stage 2 sep
		T+05:40 Stage 3 burn
		T+05:44 Fairing sep
	2354:38	T+09:38 Stage 3 MECO
		T+09:49 Stage 3 vernier cutoff
	2354:49	T+09:49 Stage 3 sep
	2355:44	T+10:44 Adapter sep
1998 May 8	0059:19	T+1:14:19 DM burn 1
	0105:52	T+1:20:52 DM MECO	629.71 213 x 35702 x 48.5
	0603:55	T+6:18:55 DM burn 2
	0605:45	T+6:20:45 DM MECO	8318 x 35750 x 15.3 (ILS)
	0625:32	T+6:40:32 DM sep
1998 May 8			794.47 8346 x 35727 x 15.4
1998 May 9	2130?	LAM-1
1998 May 11			878.46 12263 x 35747 x 10.6
1998 May 13	1430?	LAM-2
1998 May 14			1079.10 21204 x 35739 x 4.7
1998 May		Solar panel deploy problem
1998 May 15?		LAM burn
1998 May 18?		LAM burn
1998 Jun 2			1436.10 35778 x 35795 x 0.0 GEO 127.0W
1998 Jul 14			1436.12 35782 x 35792 x 0.0 GEO 127.0W
1998 Jul 16		mv out	1440.86 35813 x 35946 x 0.0 GEO 128.0W+2.0W
1998 Jul 29		mv in
1998 Aug 15			1436.10 35782 x 35791 x 0.0 GEO 148.0W
1999 Jun 10			1436.04 35775 x 35795 x 0.1 GEO 147.8W
1999 Jun		Relocate to 110W
1999 Jul 29			1436.09 35780 x 35792 x 0.1 GEO 110.1W
1999 Oct 16			1436.06 35778 x 35793 x 0.1 GEO 110.1W
1999 Dec 22			GEO 110.5W
2000 Jan 20		Mv in	GEO 119.5W
2000 Jun 13			1436.13 35775 x 35798 x 0.0 GEO 119.5W
2003 May 16		mv out	GEO 119W
2003 Jul 20		mv in	GEO 157W
2004 Sep 4		Solar panels pop open
2005 May 27			1436.13 35773 x 35800 x 0.8 GEO 157.0W
2005 Jun 18		mv out	1436.06 35776 x 35794 x 0.8 GEO 157.0W
2005 Jul 6		mv in at 77W (Quetzsat)
2005 Jul 16			1436.20 35779 x 35797 x 0.9 GEO 76.8W
2006 Aug 4			1436.11 35771 x 35802 x 0.6 GEO 77.0W
2011 Jul 11			1436.11 35768 x 35804 x 2.8 GEO 76.7W

Zhongwei 1

 1998-033A

---

The China Orient Telecommunications Satellite Co. of Beijing (part of the Ministry of Posts and Telecommunications) contracted Lockheed Martin Astro Space to build the A2100 class Zhongwei I (Chinastar 1). The satellite was launched in the spring of 1998 by CZ-3B and has a mass of 2984 kg (1418 kg BOL). It will serve China, southeast Asia, India and Korea. It entered a supersynchronous orbit, later lowered to geostationary. However, the orbit remained eccentric.

China Orient was later merged into China Satcom and Zhongwei 1 was renamed Zhongxing 5A. China DBSAT was founded Dec 2007 and merged into China Satcom in Apr 2009.

Zhongwei 1
Date	Time	Event	Orbit
1998 May 30	1000	Launch by CZ-3B
		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
	1010	T+10:31 MECO-1	160? x 450? x 28.5?
	1021	T+21:21 MES-2
	1024	T+24:20 MECO-2
	1026?	T+26:00 Stage 3 sep	216 x 85035 x 24.4
1998 May 31			1799.28 216 x 85033 x 24.4
1998 May 31	0120	First apogee at 127E
1998 Jun 1	0720	Second apogee at 36E
1998 Jun 2	1320	Third apogee at 54W, LAM-1
1998 Jun 3			2337.39 14468 x 89459 x 7.0
1998 Jun 4	0300	Fourth apogee at 97E
1998 Jun 5	1753	Apogee 5 at 128W
1998 Jun 6?		LAM burn
1998 Jun 6			2860.72 35759 x 84992 x 1.3
1998 Jun 8	1340	LAM at perigee
1998 Jun 8			2203.06 35731 x 63682 x 1.0
1998 Jun 11	1500?	LAM at perigee
1998 Jun 13			1435.00 35678 x 35851 x 0.1 GEO 86.9E+0.3E
1998 Jun 15			1435.60 35742 x 35811 x 0.1 GEO 87.5E+0.1E
1998 Jun 30			1436.16 33915 x 37661 x 0.09
1998 Jul 20			1436.14 35779 x 35795 x 0.0 GEO 87.5E
1999 Oct 18			1436.07 35776 x 35795 x 0.0 GEO 87.6E
2006 Aug 3			1436.11 35774 x 35799 x 0.1 GEO 87.6E
2013 Aug 10			1436.06 35768 x 35803 x 0.0 GEO 87.6E