TeamNathanFTW’s New and Improved Blog : January 2005

Monday, January 31, 2005

Syncom 3

1964-047A

The Syncom C payload, Syncom III on orbit, was launched on 1964 Aug 19 at 1215.02 UT. The launch vehicle was the first (and one of only 2) Delta D model, with a Thrust Augmented Thor first stage and an Altair 2 third stage. By 1241 UT the Syncom was in transfer orbit, with apogee motor firing coming on Aug 20. The apogee motor was a JPL SR-12-1 like that of Syncom II. By around Sep 10 the satellite had reportedly reached geostationary orbit at 180 deg East. However, archival NORAD data indicates the initial position was actually 61W, and it reached 180W around Nov 3. On 1965 Apr 1, responsibility for the satellite was transferred to the Department of Defense. During 1965 the satellite was stationed over the Atlantic, but in late 1965 began to drift when fuel ran out. In 1973 Syncom III was revived for engineering tests, and the first geostationary satellite was finally switched off on 1974 Dec 29.

During launch, the second stage yawed 38 deg left, reducing third stage orbit inclination to 16.5 deg. Stage 2 velocity was 6.73 km/s, with Stage 3 adding 3.266 km/s for a stage 3 perigee velocity of 9.517 km/s (TN-D-3375).

Date	Time	Event	Orbit

Syncom 3



1964 Aug 19	1215:02	Launch by Thor Delta
	1216:12	SRM sep
	1217:30	Thor MECO
	1217:34	Thor S/N 20104 sep 112 km	-4832 x 384 x 28.6
	1217:34	Delta S/N 20010 burn
	1217:45	Fairing
	1220:26	Delta SECO 362 km alt, range 967 km	-796 x 1127 x 28.7
	1241:05	Spinup
	1241:07	Delta sep
	1241:12	Altair 2 RH-67 burn 22.6s at 1126 km
	1241:35	RH-67 burnout
	1242:22	Altair 2 sep	694.43 1112 x 38083 x 16.80
		Delta impact (vac) 28.5S 85.4E
1964 Aug 20	1717:56	AKM burn at 3rd apo
	1718:16	AKM burnout	3.3W/d
1964 Aug 22	0454	TCM	7.1E/d
1964 Aug 28	1407	TCM	3.3E/d
1964 Sep 10	1030	TCM On station 180E?	2.06W/d
	2245	TCM	1.01W/d
1964 Sep 11	2240	TCM	0.01W/d
1964 Sep 25	0257		Reduce inc to 0.006
1964 Sep 25	0347		1435.94 35640 x 35926 x 1.0 GEO 61.0W+0.0W
1964 Oct 1	0851	Orbit trim
	2050	Orbit trim
1964 Oct 2	0848	Orbit trim to 0.003 deg/d
1964 Oct 30	1701	Orbit longitude trim
1964 Nov 3			1436.53 35790 x 35799 x 0.1 GEO 180.0W+0.2E
1965 Jan		Over POR
1965 Mar 2			1436.63 35785 x 35808 x 0.2 GEO 2.0W+0.1E
1965 Apr 1		To DoD
1965 Jun 1			1436.13 35783 x 35791 x 0.1 GEO 24.9W+0.0E
1965 Jul 8		To DoD
1965 Sep 25			1436.20 35784 x 35792 x 0.1 GEO 27.0W+0.0E
1966 Mar 3			1436.84 35788 x 35813 x 0.7 GEO 20.5E+0.2E
1966 Jun 15			GEO 165 E
1966 Aug 24			GEO 161 E
1967 Mar 16			1536.49 35786 x 35802 x 1.5 GEO 21.2W+0.1E
1967 Apr 18			GEO 158 E
1967 May 17			GEO 157 E
1967 Jun 02			GEO 157 E
1967 Dec 07			GEO 160 E
1968 Apr 30			1436.43 35778 x 35808 x 2.6 GEO 158.3E+0.1E
1969 Apr		Out of service
1971 Apr 13			1438.17 35795 x 35858 x 5.5 GEO 150.6W+0.5E
1973 Aug 31			GEO 148 E
1974 May 14			GEO 63 E + 0.4W/d
1974 Oct 01			GEO 5 E + 0.2W/d
1974 Dec 6			GEO 1436.87 35744 x 35858 x 8.6 GEO 5.9W+0.2E
1974 Dec 24			GEO 2 W + 0.1W/d
1974 Dec 26		Revived for eng tests
1974 Dec 29		Decommissioned

Thursday, January 27, 2005

Aviation Week: October 18,2004

https://welib.org/md5/f66a5f2c81c0ba39598510abda337308

Saturday, January 22, 2005

Space Flyer Unit

1995-011A

The Space Flyer Unit was a free flying platform deployed by the expendable H-II launch vehicle and to be retrieved by the Shuttle. It was a precursor to NASDA's involvement in the ISSA project, and was a collaborative project with ISAS, MITI and NASA.

The H-II was launched on 1995 Mar 11 and delivered SFU to orbit. SFU maneuvered to the 486 km mission orbit at 0549 UT on Mar 23. It was planned to be retrieved after 6 months but the Shuttle retrieval was delayed. It was recovered by Space Shuttle Endeavour in Jan 1996.

The SFU satellite was an octagonal bus, 4.7m in diameter and 2.8m high. Its mass at launch was 3486 kg including a fuel load of 759 kg hydrazine. After orbit insertion, two 2.4m wide solar arrays are deployed from the bus for a total span of 24.4m. The monopropellant hydrazine RCS and orbit change thruster system had twelve 23-N thrusters and twelve 3-N thrusters.

Capacity was 100 kg RCS and 650 kg for the OCT system.

One of the main experiments on SFU is the EFFU, which was a test flight of equipment for the JEM Exposed Facility on the Space Station.

The IRTS was an ISAS/NASA experiment in infrared astronomy. The 2D experiment used the miura-ori folding technique to compress a tension stabilized membrane for launch and then deploy it on orbit, creating a roughly 10m diamond shaped array. During retrieval, the solar arrays would not retract correctly and had to be jettisoned.

Date	Time	Event	Orbit

SFU



1995 Mar 18	0801	Launch by H-II	TNSC
		T+1:16 SSB burnout 25 km 1.3 km/s
		T+1:30 SSB sep 36 km 1.6 km/s
		T+1:34 SRB burnout
		T+1:37 SRB sep 42 km 1.6 km/s
		T+3:39 Upper fairing sep 128 km 2.8 km/s
		T+5:47 MECO
		T+5:56 Stage 1 sep 222 km 5.3 km/s
		T+6:02 Stage 2 SES-1	-4400 x 250 ?
	0813	T+12:20 SECO-1
	0814	T+13:16 SFU separation
	0817	T+16:11 Lower fairing sep
	0826	T+25:03 SES-2
	0828	T+27:02 SECO-2
	0828	T+27:52 Stage 2 sep from GMS
			91.05 311 x 340 x 28.5
1995 Mar 19			91.23 320 x 349 x 28.5
1995 Mar 20			92.09 358 x 395 x 28.5
1995 Mar 21			92.15 365 x 394 x 28.5
1995 Mar 23		Operational orbit
1995 Mar 23			94.24 466 x 496 x 28.5
1995 Mar 29			94.24 467 x 494 x 28.5
		Begin Mission Operation Phase
1995 Mar 29		EPEX first burn
	1800	IRTS FPI on
	1815	IRTS sun shield extended
1995 Mar 29	2359	IRTS cover ejected
		IRTS survey begins
1995 Apr 24		IRTS survey ends
1995 Apr 24	0855	He tank venting
1995 Apr 26		Helium tank discharged
1995 Apr 26	0758	IRTS sun shield ejected
1995 May 26		2DHV deploy test
1995 Jul 4			94.21 466 x 493 x 28.5
1995 Jul 20		Residual EPEX hydrazine dumped
1995 Aug 3		2DHV locked
1995 Aug 23		EPEX hydrazine valves closed
1995 Sep		Post Mission Phase
1995 Oct 17		Begin OCT tests	94.18 464 x 492 x 28.5
		Orbit lower apogee
1995 Oct 19			94.02 461 x 480 x 28.5
1995 Dec 6			94.00 465 x 474 x 28.5
		Raise orbit
1995 Dec 7	0920		94.15 472 x 483 x 28.5
1995 Dec 18			94.15 471 x 483 x 28.5
		Raise orbit
1995 Dec 21	2052		94.33 481 x 491 x 28.5
		Lower orbit
1995 Dec 22	1102		94.08 470 x 478 x 28.4
1996 Jan 12			94.08 469 x 478 x 28.5
1996 Jan 13	0935	SFU panel 1 ejected
	0947	SFU panel 2 ejected
	1057	OV-105 RMS grapple SFU
	1139	RMS berth SFU
	1150?	RMS ungrapple SFU
1996 Jan 18	1530		94.08 469 x 478 x 28.5
1996 Jan 20	0742	Landed aboard OV-105

Excerpts from a Jem fanfiction I never quite got around to writing

Jeri!

Lindsey,it's been too long!

It's Lin-Z now. Same pronunciation,different spelling. I'm a VJ for Music TV.

A video jockey?

Exactly. I host my own show,"Music Morning with Lin-Z Pearce".

I've seen you on billboards.

I hope you don't go around telling people I'm your favorite cousin!

Who,me? I'm more modest than that,Lin-Z! Why'd you come down to Fairfield,anyway?

To meet Danny and Rebecca,of course! Kimber promised me I'd be Danny's future godmother. Her friend Emily is Rebecca’s.

Yes,she and Emily Novak are good friends,and she’s a good influence.

————

Stripping off her clothes,Shana Elmsford sank into her bath with a grimace that faded as her shoulder pain left her. Sewing was a harder task than most people believed it to be,and it could be pure hell on the shoulders and fingers if you weren't careful. Shana wanted to be a fashion designer someday. To that end she'd taken all the shop classes Norwalk High had on offer,and by the time she graduated in June 1981 she could confidently say she knew a fair bit about the subject. She moved from the shop classes she’d taken in high school to the larger playing field that was Fairfield University,where she put her business skills to good use getting a BBA like Jerrica was getting at NYU.

———-

At the same time that Jerrica and Jacqui were having their little talk,Kimber was lying on her bed,reading a Sweet Dreams teen romance novel as evening wore on. Danny and Rebecca were in their cribs sleeping,Kimber having given them some warm milk earlier. She'd lulled them to sleep by reading them The Hobbit,it being one of her favorite books when she was little.

The novel she was reading tonight was A Song for Us,about a girl named Anna whose crush Rick was in a band. Anna herself happened to be musically talented and the book's cover model strongly resembled Roxy which was rather a nice touch. For all I know,she's a fictional version of her!,Kimber thought as she flipped the pages.

Kimber let the fan in the corner blow air around her as she relaxed. She was completely naked,which was the way she usually slept.

—————

At Norman,Oklahoma,the news was so.......meh. Who cared that the first Mars crew had returned safely to Earth? There'd be others to come. Roxy ordered pancakes,Jacqui French toast,both of them coffee.
"I'm really glad I could do this,Mrs Benton. Like,I really needed to unwind!"
"Please,Roxy,for the hundredth time,you can call me Jackie. I'm your second mother,aren't I?"
Roxy goggled a little bit.
"You know Emmett and I adopted you when you were just two."
"Of course I do. Jerrica told me when we were in junior high. But why me and not some other girl?"
"Your father,Francis Pellegrini,was an old college friend of Emmett's,and he was there when Francis and your mother were married. Aja and Shana we adopted because they were local girls,and Raya we adopted from her family in the Kingdom of Haiti,but we already had a connection to you personally." Jacqui's eyes were moist,and when she looked at Roxy she could see tears in the corners of her eyes.
"Thanks,Jackie,thanks so much. I....I love you."
"Me too", Jacqui said as she stood over the table and hugged Roxy. "I want you to know that I think you and Aja and Shana and Raya,you four are as much Benton as Jeri and Kimber are. No matter whether by blood or adoption,family is family."

————-

1986-12-09 14:19:52

JEM AND THE HOLOGRAMS PLAN '87 TOUR

They're at it again,folks! Jem and the Holograms are planning a big tour in 1987,says entertainment columnist Lindsey "Lin-Z" Pearce,28. The tour will span America and Canada.

"The Holograms (my favorite band) have a big year ahead of them! Their "Open My Heart" tour,set to begin in early April,coincides with the planned release of their second album, "Truly Outrageous".
We can also expect a little surprise something-something this spring - what it is,I'm not saying! But watch this space,all you Jematics!"

The tour will cover 17 cities and should last about seven weeks. The band consists of lead singer Jerrica "Jem" Benton (24),vocalist and keytarist Kimber Benton (20),bassist Aja Leith (21),rhythm guitarist Shana Elmsford (23),vocalist Carmen "Raya" Alonzo (22),and drummer Roxanne Pellegrini (23).

——————

The wedding will be at St Martin's Church in Fairfield,which I believe is the traditional church of the Benton family,going back more than a century. Her mother Jacqui is today's matron of honor,then her bridesmaids are her sister Jerrica,Aja Leith,Shana Elmsford,Carmen Alonzo,Roxanne Pellegrini,and Mary Phillips of the Misfits.

What about her twin children,Danny and Rebecca?

According to Jerrica they will be the ring bearer and flower girl. Rather appropriate roles for them,given that it's their mom who's getting married today.

Her arm looped through Rio's,Kimber started down the aisle. Danny and Rebecca bore the rings and flowers. Stormer was not far behind,then Jerrica,Jacqui,Aja,Shana,Raya,and Roxy.

Kimber and Sean were now coming back up the aisle,Sean holding Rebecca’s hand and Kimber holding Danny's. When they had reached the head Jacqui tossed the bouquet - it landed in Shana's hands! Shana was getting all weepy,Roxy was holding her and laughing like a maniac,and it was all so much that Jerrica needed a break so she headed over to a bench. An old woman Jerrica thought she should remember sat down next to her.

"What a beautiful wedding that was,dear. That girl,Kimber - I can tell she's in love!"

"She's my younger sister", Jerrica replied. "Do I know you?"

"I'm Mrs Riddell,I used to live down the street from your family. My daughter Claire used to babysit you two."

Jerrica vaguely remembered Claire Riddell,a bottle blonde with a big smile and a bigger heart. "What happened to her?"

"She lives in Palm Beach now - she owns a restaurant with her husband Freddy."

Thursday, January 20, 2005

Progress M-35

1997-033A

Launch mass was 7150 kg. The redocking of Progress M-35 on Aug 17 was cancelled when the on board computer shut down automatically after ground controllers loaded incorrect commands to it. A successful redocking on Aug 18 was carried out under manual control by Solov'yov when the automatic system cut out at the last minute due to Mir's loss of attitude control.

A first undocking attempt failed because the crew forgot to remove one of the clamps.

Date	Time	Event	Orbit

Progress M-35



1997 Jul 5	0411:54	Launch by Soyuz-U	KB LC1
	0413:52	Blok BVGD sep T+1:58
	0416:41	Blok A sep T+4:47
	0420:43	Blok-I sep T+8:49
	0754:46	TCM-1 65.3s, 27m/s
	0841:59	TCM-2 54s, 22 m/s
1997 Jul 7	0559:24	Docked with Kvant (Kurs)
1997 Jul 8		Hatch open
1997 Aug 6	1146:45	Undocked from Kvant
	1149:39	sep burn
1997 Aug 17	1355	Docking cancelled
1997 Aug 17	1430:31	TCM 2m/s 6s
	1519:16	TCM 3m/s 6s
	1626:00	TCM 1m/s 3s
		Kurs shutdown at 20m
1997 Aug 18	1252:47	Docked with Kvant
1997 Oct 5		Failed to undock
1997 Oct 7	1203:49	Undocked
		Skeep at 10m
		Sep burn
	1641:00	Deorbit
	1723	Reentered over Pacific

Tuesday, January 18, 2005

OAO 2

1968-110A

The replacement satellite for OAO A1, called OAO A2, carried the WEP again, but the other experiments were replaced by the Smithsonian Observatory Telescope. Launched at 0640 on 1968 Dec 7 by an Atlas Centaur from Cape Kennedy, OAO II (Orbiting Astronomical Observatory 2) entered a 100.2 min, 765 x 778 km x 35.0 deg orbit. The satellite was a success, making the first extensive ultraviolet observations of stars, and transmitted until 1973 Feb 14.

Date	Time	Event	Orbit

OAO 2



1968 Dec 7	0840:09	Launch by Atlas Centaur AC-16	CKAFS LC36B
		T+2:33 BECO
		T+2:35 Booster sep
		T+3:17 Insulation panels
		T+3:54 SECO
		T+3:56 Atlas sep
	0844	T+4:07 Centaur 13D MES 1
		T+4:19 Fairing
		T+4:21 Yaw mvr begins
	0851:47	T+11:38 Centaur MECO
		T+11:49 Solar paddles deploy
		T+11:50? Balance weights jettisoned
	0852	T+12:29 Centaur sep
	0905	T+25:31 Centaur blowdown 49s
1969 Apr 12		Attitude control loss
1969 Apr 16		Attitude control recovered
1973 Feb 14		end of tx

Sunday, January 16, 2005

Reference Books Bulletin, 2000-2001: A Compilation of Evaluations September 2000 Through August 2001

https://welib.org/md5/7db2cc6213954598274cc28e58c0fadf

Vortex 9

1979-086A

A second mission was launched in 1979. At this point it is believed that the codename was VORTEX.

Date	Time	Event	Orbit

VORTEX 9



1979 Oct 1	1122:01	Launch by Titan IIIC	CC LC40
		T+1:50 Stage 1 ignition
		T+2:02 SRM sep
		T+4:35 St 1 sep
	1126	T+4:45 Fairing sep
	1130	Stage 2 MECO
	1130	T+8:05 Stage 2 sep
	1145	First descending node
	1145?	Transtage burn 1
	1800?	Transtage burn 2
	1802?	MECO-2
	1805?	Transtage sep
1979 Oct			1445.5 30443 x 41497 x 7.5 (UN)
1980 Apr?			GEO 34E

Friday, January 14, 2005

DirecTV-4S

2001-052A

4S is a BSS601HP Block 1, with spot beams for local US programming, at 101W. It is the first spot-beam DirecTV satellite. Mass is 4300 kg full, 2100 kg dry. Size 2.7 x 3.6 x 4.0m 26.2m span. 38 active transponders on spot beam, plus 2 two primary and eight backup national transponders.

Date	Time	Event	Orbit

DirecTV-4S



2001 Nov 27	0035	Launch by Ariane 44LP
		T+1:07 PAP sep
		T+2:27 PAL sep
		T+3:31 St 1 sep
		T+3:34 St 2 MES
		T+4:40 Fairing sep
		T+5:43 St 2 sep
		T+5:48 St 3 MES
	0053	T+18:19 St 3 MECO
	0056	T+21:02 St 3 sep
2001 Nov 27			630.04 219 x 35714 x 6.95
2001 Nov 29	2140?	LAM
2001 Dec 2			1393.64 34120 x 35782 x 0.14
2001 Dec 3	0500?	LAM
2001 Dec 4			1435.87 35780 x 35783 x 0.08 GEO 101.6W
2001 Dec 22			1435.98 35779 x 35789 x 0.04 GEO 101.2W

Sunday, January 9, 2005

Spektr

1995-024A

77KSO (TsM-O, TKS 173), the Spektr earth resources module, was finally launched on 1995 May 20. Extra solar arrays were added late in the design process to alleviate Mir's severe power shortages. Launch mass of Spektr was 22000 kg, which was reduced to 19500 kg by the time it docked with Mir. Docking was delayed following problems with reconfiguring Mir to receive the spacecraft. It docked with Mir on the first attempt, unlike the earlier modules.

Date	Time	Event	Orbit

Spektr log



1995 May 20	0333:22	Launch
	0335:28	St 1 sep
	0336:22	Fairing sep
	0338:57	St 2 sep
	0339	Stage 3 burn
	0342:59	Stage 3 MECO
	0343:11	Proton sep	89.84 215 x 318 x 51.7
1995 May 21	0211	TCM-1
	0419	TCM-2	90.55 262 x 341 x 51.6
1995 May 25	0212	TCM
	0247	TCM	91.39 312 x 372 x 51.65
1995 May 28	0109	TCM?
1995 Jun 1	0230	Docked Mir -X
1995 Jun 2	0445	Transfer to side port

Payload:

Solar array
Forward solar arrays
Module manipulator arm
Pelikan manipulator arm (2m) and science airlock
286K binocular radiometer
Astra-2 trace gases experiment
Balkan-1 lidar, 4.5m res with 5320A laser for cloud altitude measurements

Monday, January 3, 2005

Helios 2A

2004-049A

Second generation Franco-German recon sat, by Astrium (Matra Marconi Space/Toulouse). Launch by Ariane 5 with ASAP5 carrying Nanosat, Parasol, Essaim 1-4 into a 665 x 666 km x 98.1 deg orbit. The EPS depletion lowered the rocket stage's perigee to 608 km, while the ASAP payloads had slightly lower perigees than Helios, between 650 and 657 km.

Mass 4200 kg. Size 6.0 x 3.7 x 3.4m

Resolution is believed to be 0.5m.

Date	Time	Event	Orbit

Helios 2A



		T-0:07 EPC MES
2004 Dec 18	1626	T+0:00 Launch by Ariane 5G+ 520 (V165)	CSG ELA3
	1628:10	62 km, 2.04 km/s	-6180 x 90 ?
		T+2:14 EAP sep at 72 km
	1629:15	118 km, 2.21 km/s	-6130 x 150 ?
	1629:21	T+3:21 Fairing sep
	1630:20	160 km, 2.5 km/s	-6100 x 200 ?
	1634	205 km, 4.5 km/s	-5100 x 300?
	1635	T+9:47 EPC MECO
		T+9:53 EPC sep at 361 km	-2500 x 600 ??
	1635:59?	T+9:59 EPS burn
	1637:20	477 km, 6.55 km/s	-2500 x 600 ?
	1646		-1800 x 750 ?
	1651	Perigee positive?
	1652	T+26:54 EPS MECO at 680 km
	1658?	EPC impact Arctic
	1726	T+1:00:01 Helios 1A sep
	1732	T+1:06:08 Nanosat sep
	1732	T+1:06:29 ESSAIM 1 and 4 sep
	1732	T+1:06:30 ESSAIM 2 and 3 sep
	1734	T+1:08:27 Parasol sep
2004 Dec 19	0221		98.06 665 x 666 x 98.1
2004 Dec 22		Raise orbit	98.34 677 x 689 x 98.1
2004 Dec 25			98.39 680 x 682 x 98.1

Sunday, January 2, 2005

Nadezhda 7

2002-046A

Coplanar with 1991-19A. 17F118M No. 65006411.

Date	Time	Event	Orbit

Nadezhda-M



2002 Sep 26	1427:14	Launch by Kosmos-3M	PL LC132
	1429:23	St 1 MECO
	1429:25	T+2:12 St 1 sep
	1429:25	Stage 2 burn
	1429:40	Fairing sep
	1435:09	T+8:05 St 2 MECO	150? x 965? x 83
	1529:40	T+1:02:16 St 2 MES 0.232 km/s?
	1529:55	St 2 MECO2
	1530:14	St 2 sep
2002 Sep 27			104.93 965 x 1016 x 82.93
2002 Oct 19			104.93 965 x 1016 x 82.94

LAGEOS 1

1976-039A

The Laser Geodetic Satellite was a 1970s NASA-MSFC program to provide a precise geodetic target. In the 1980s the Italian Space Agency funded and built a copy of Lageos, Lageos 2, which was launched in 1992.

Lageos was built by NASA-GSFC for a program managed by NASA-MSFC under NASA's EODAP (Earth and Ocean Dynamics Applications Program). The satellite was a sphere 0.60 m in diameter. It consisted of a brass core surrounded by two aluminum hemispheres studded with 426 laser retroreflectors. This low drag satellite was used as a laser target for precise geodetic measurements. It provided direct evidence for plate tectonic motion (`continental drift').

Lageos was launched at 0800 on 1976 May 4 by a Delta 2913 launch vehicle from Space Launch Complex 2-West at Vandenberg Air Force Base. The Delta No. 123 second stage entered a 169 km apogee suborbital path at 0808. The Star 37D third stage burned at 0811 to place the payload in a 309 km x 5920 km x 109 degree transfer orbit. At 0932, the TE-M-604-1 solid apogee motor ignited, and at 0935 it separated, placing Lageos in its final 5837 x 5945 km x 109.9 deg orbit.

Date	Time	Event	Orbit

Lageos



1976 May 4	0800:00?	Launch by Delta 2913
		T+0:38 SRM 1-6 out
		T+0:39 SRM 7-9 on
		T+1:17 SRM 7-9 out
		T+1:27 SRM 1-9 sep
		T+3:50 MECO
	0803	T+3:57 Thor sep
	0804:03	T+4:03 SES-1 4:46
		T+5:25 Fairing
	0808:49	T+8:49 SECO-1
			-1440 x 309 x 109.7
	0811:30	T+11:30 Spinup
	0811:32?	Stage 2 sep
	0811:34	T+11:34 TES 1670 m/s
	0813:02	T+13:02 TECO	309 x 5920 x 109
	0814:14	T+14:14 Stage 3 sep
	0823?	Stage 2 reentry
	0931:19?	A+0 AKM 916.5m/s
	0931:49	T+1:31:49 AKM burnout A+30?
	0935:11	A+3:22 (T+1:35:11) AKM sep

Saturday, January 1, 2005

Spaceflight: July 2004

https://welib.org/md5/a33b3bc53b4231a7864ddd9c64623aba

Haruka

1997-005A

The VSOP (VLBI Space Observatory Program) was a project to do radio astronomy using spaceborne Very Long Baseline Interferometry. The space segment of VSOP was the MUSES-B satellite, named Haruka (`far-away') after launch. Mass of Haruka was 830 kg including 62 kg of RCS prop and 246 kg dish antenna. It has a 10m (8m effective) deployable dish with a central boom carring the subrelector. The main spacecraft is a 1.5m dia, 1.0m high box with 2 solar panels. MUSES B was built by NEC.

The second Mu Space Experiment System (MUSES B) was the 16th ISAS scientific satellite, to test large space structures and provide the first orbiting VLBI radio observatory. Initial orbit is 200 x 20000 km, with perigee raising maneuvers into a 1000 x 20000 km. The spacecraft has a box shaped bus, with 2 solar panels and the antenna. Haruka has also been assigned the English homonym HALCA (Highly Advanced Laboratory for Communications and Astronomy).

This was the first launch of the M-V rocket. A KM-V1 fourth stage kick motor was added. The third stage was not cataloged until 1999, when two objects were found in orbits with apogees of 1263 and 1674 km.

Date	Time	Event	Orbit

Haruka VSOP



1997 Feb 12	0450:00	Launch by M-V-1	Kagoshima
		Stage 1 burnout
	0451:15	Stage 1 sep T+1:15s
	0452:37	Stage 2 burnout T+2:37
	0453:17	Fairing T+3:17s
	0453:31		-4962 x 224 x 31.1
	0453:33	Stage 2 sep T+3:33s
	0453:39	Stage 3 burn T+3:39
	0455:33	T+5:33 St 3 burnout
	0455:33	Spinup T+333s
	0455:39	Stage 3 sep T+5:39s	233 x ? x 31.2
	0455:43	KM-V1 burn T+5:43s 71s?
		KM-V1 burnout
	0457:57	KM-V1 sep T+7:57s	233 x 21527 x 31.2
		Yo-yo deploy T+8:00
		Solar panel deploy T+90min
		Orbit raise
1997 Feb 14		TCM1
1997 Feb 16		TCM2
1997 Feb 21		TCM3
1997 Feb 24		Sub-reflector deployed
1997 Feb 27		Main antenna deploy begins
1997 Feb 28		Antenna deploy complete
1997 Mar 30		Eclipse period begins
1997 Apr		First fringes at 1.6 GHz
1998 Aug 30		Computer problem, observing halted
1998 Dec 10		Computer rebooted
1999 Oct		Gyro problem,
1999 Dec		Resume observing
1999 Dec		Orbit lower
2000 Feb		Resume attitude control
2000 Mar 8		Resume observing
2003 Oct		end of VSOP observations

Hexagon 5

1973-014A

It has been claimed that the short lifetime of KH-9 no. 5 was due to the fact that preparations for its launch were rushed. HEXAGON 5 carried the first mapping camera in the series, as well as a related secondary payload, the Doppler Beacon 7 transponder which was used in an APL geodetic program. Earlier Doppler Beacon payloads had been carried on the Agena D aft rack of CORONA missions. The doppler system was used to track the orbit of the satellite from sensors around the periphery of the USSR, providing a geodetic control net for the area. The mapping SRV, mission 1205-5, was recovered after 42 days. The mission was used in a deorbit experiment over a broad ocean area (over Shemya according to The HEXAGON Story).

Date	Time	Event	Orbit

HEXAGON 5



1973 Mar 9	2100	Launch by Titan IIID	V SLC4E
		T+1:54 Stage 1 burn 2:27
		T+1:55 SRM burnout
		T+2:05 SRM sep
		T+4:22 Stage 1 MECO
		T+4:22 Stage 1 sep
		T+4:22 Stage 2 burn
		T+4:36 Fairing
	2107	T+7:40 Stage 2 MECO
	2108	T+7:52 Stage 2 sep
		Solar arrays deployed, rev 1
		Payload ops begin, rev 5
1973 Mar 9			88.60 146 x 264 x 95.72
1973 Mar 10			88.75 153 x 271 x 95.72
1973 Mar 19	1834		88.73 161 x 261 x 95.69
1973 Mar 21	2250?	SRV-1 deorbit
1973 Mar 31			88.6 152 x 263 x 95.7 (SSR)
1973 Apr 4	2325?	SRV-2 deorbit
1973 Apr 7		op 121	88.64 152 x 261 x 95.7
1973 Apr 9		op 138
1973 Apr 10		op 140
1973 Apr 11		op 149
1973 Apr 16		op 173
1973 Apr 18	2250?	SRV-3 deorbit
1973 Apr 19		op 194
	0600?	Orbit adjust
1973 Apr 20	2300?	SRV-5 deorbit opp	151 x 268 x 95.7
		T+0:00 SRV sep
		T+0:03 Spinup 57 rpm
		TE-M-236B deboost
		Despin
		T+0:21? Thrust cone separation
		E+0:00 = T+5:51? Entry
		E+2:26 Cover sep
		E+2:36 Chute deploy
		E+22-25 min? Recovery at 5 km
	2335?	SRV-5 recovered
1973 Apr 28		DB-7 turned off	88.63 151 x 262 x 95.7
1973 May 6			88.85 169 x 265 x 95.6
1973 May 11			88.66 151 x 264 x 95.6
1973 May 11	2220?	SRV-4 deorbit
1973 May 12	0608	Raise perigee	88.96 179 x 266 x 95.6
	1502		88.94 169 x 274 x 95.6
1973 May 16	1344		88.39 155 x 233 x 95.6
1973 May 16	1809	Orbit raise	88.53 156 x 246 x 95.6
1973 May 17	1746		88.42 155 x 237 x 95.7
1973 May 18	1126	Lower perigee	88.13 143 x 220 x 95.7
1973 May 19		Reentered after 71d
	0000?	Deboost rev 1139, day 70	80? x 176 x 95.7
		VASP 1 reentry experiment over BOA (Shemya)
		Deboost (OAM burn along horizontal, vel vector)
		S+1:05:56 Alt 129 km
		S+1:09:52 Loss of signal 92 km
	0110	S+1:10:40 Solar panels break off 84 km
		S+1:11:15 Vehicle breakup 78 km

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