Kosmos 2377

 2001-022A

---

This was the first launch by the new KVR, Russian Space Forces.

Kosmos-2377
Date	Time	Event	Orbit
2001 May 29	1755:00	Launch by Soyuz-U	PL 43/4
	1804	Blok-I MECO
	1804	Blok-I sep	165 x 358 km x 67.1
2001 May 29			89.74 165 x 358 x 67.1
2001 May 31			89.60 163 x 344 x 67.1
2001 Jun 1		Orbit raise	89.91 184 x 355 x 67.1
2001 Jun 10			89.44 176 x 316 x 67.1
2001 Jun 13		Orbit raise	89.82 183 x 348 x 67.1
2001 Jun 26			88.98 168 x 278 x 67.1
2001 Jun 28		Orbit raise	89.81 185 x 344 x 67.1
2001 Jul 3		SpK-1 fid
	0441?	Deorbit
	0451?	Entry
	0503?	Landed
2001 Jul 7			89.31 177 x 302 x 67.1
2001 Jul 10		Orbit raise	89.82 184 x 347 x 67.1
2001 Jul 19			89.35 175 x 309 x 67.1
2001 Jul 22		Orbit raise	89.72 178 x 342 x 67.1
2001 Jul 26			89.48 171 x 326 x 67.1
2001 Jul 28		Orbit raise	89.97 180 x 365 x 67.1
2001 Aug 7			89.44 174 x 319 x 67.1
2001 Aug 12		Orbit raise	89.97 189 x 355 x 67.1
2001 Aug 15		SpK-2 fid
	1617?	Deorbit
	1627?	Entry
	1639?	Landed
2001 Sep 2			88.83 171 x 261 x 67.1
2001 Sep 6		Orbit raise	89.88 178 x 359 x 67.1
2001 Sep 12			89.43 171 x 321 x 67.1
2001 Sep 15		Orbit raise	89.71 167 x 352 x 67.1
2001 Sep 20		Orbit raise	89.80 174 x 354 x 67.1
2001 Sep 25			89.33 168 x 314 x 67.1
2001 Sep 30		Orbit raise	89.56 189 x 315 x 67.1
2001 Oct 3			89.34 184 x 298 x 67.1
2001 Oct 9			88.81 170 x 260 x 67.1
2001 Oct 10
	0037?	Deorbit
	0051?	Entry
	0103?	Landed

The Mabinogion

 https://www.gutenberg.org/files/5160/5160-0.txt

Soyuz 26

 1977-113A

---

Yuriy Romanenko and Georgiy Grechko stepped in to replace the Soyuz-25 crew as Salyut-6's first residents. Their spacecraft, 7K-T No. 43 (11F615A8 No. 43) was launched on 1977 Dec 10 and became Soyuz-26. It docked with the rear port of DOS 5 on 1977 Dec 11.

On 1978 Jan 16, the EP-1 crew launched on Soyuz-27, Vladimir Dzhanibekov and Oleg Makarov, entered the spacecraft. They undocked later that day and landed in Kazakhstan.

Soyuz-26
Date	Time	Event	Orbit
1977 Dec 10	0118:40	Launch by Soyuz-U	KB
	0120	Blok BVGD sep
	0123	Blok A sep
	0127	Blok I MECO
	0127	Blok I sep
			88.7 195 x 235 x 51.6
			205 x 245 x 51.6
			90.2 251 x 321 x 51.6
	0900	262 x 337 x 51.6
1977 Dec 11	0302	Docked with Salyut-6
		EO crew to Salyut-6
1978 Jan 15		Test burn
1978 Jan 16		EP crew from Salyut-6
	0805?	Undocked
	1039?	Retrofire
	1042?	DO CO
	1055?	Modules sep
	1100?	Entry
	1124:58	Landed

Kosmos 2360

 1998-045A

---

Kosmos-2360
Date	Time	Event	Orbit
1998 Jul 28	0915:00	Launch by Zenit-2	KB
	0917	T+2:23 St 1 MECO
	0917	T+2:25 Stage 1 sep
	0917	T+2:25 Stage 2 burn
	0917	T+2:40 GO sep
	0921	T+6:42 Stage 2 MECO	150? x 850? x 71.0
		Sep motor cover perigee
	0928?	T+13m? Stage 2 VECO
	0928?	Stage 2 sep motor covers
	0928?	T+13m? Stage 2 sep
1998 Aug 3			101.95 847 x 854 x 71.0

The Cambridge Dictionary of Space Technology

 https://welib.org/md5/e82d088095db9e46cae0f4de3f47cd56

Rocsat 1

 1999-002A

---

The Republic of China (Taiwan) NSPO National Space Program Office contracted TRW to built the ROCSAT (Republic of China Satellite) experimental satellite. Taiwan Aerospace/Taichung and ITRI/Hsinchu, as well as the NSPO/Hsinchu integration facility were involved in building the satellite. Rocsat has a mass of 403 kg and will be launched into a 600 x 600 x 35 orbit. The OCI will determine plankton levels for fisheries management. Size is 1.1 x 1.1 x 2.0 m with two 1.1 x 2.5 m solar arrays. The Rocsat bus will also be used for some EOS missions.

In some contexts ROCSAT is referred to in Chinese by the word whose Wade-Giles transliteration is Chunghua (meaning China). Taiwan at this time used Wade-Giles rather than Pinyin. However more generally the name Formosat-1 (

\uni{ 福爾摩沙衛星一號}{ }

Fuermosha weixing yi hao) is used.

The Athena has a Castor 120 stage 1 and an Orbus 21D ESBM (Equipment Section Boost Motor).

On 2004 Jun 16 the satellite lost Sun sensor capabilities and the spacecraft was unable to keep its solar panels oriented, losing power.

ESBM was 10810 kg full 1030 em, thrust 189.2 kN, 296s Isp. 2903 m/s. mdot 65.2 kg/s.

m1/m2 = 11213 / 1433 so dV = 5972 m/s

ROCSAT 1
Date	Time	Event	Orbit
1999 Jan 27	0034	Launch by Athena-1	SPFL SLC46
		T+1:34 St 1 burnout
		T+3:09 Model 92 Fairing sep
		T+3:14 St 1 sep
	0037	T+3:16 ESBM burn 149s	-6194? x 222 x 35.0
		T+5:45 ESBM burnout
	0039	T+5:45 ESBM sep	89.25 208 x 265 x 35.0 (ILAM)
		T+5:50 OAM burn 121s
	0041	T+7:51 OAM MECO	92.79 209 x 612 x 35.0 (ILAM)
	0125	T+51:55 OAM burn 2 164s
	0128	T+54:39 OAM MECO-2
	0139	T+1:05:08 OAM sep	96.74 596 x 608 x 35.0 (ILAM)
	0144	T+1:10:08 OAM CCAM burn
	0146	T+1:12:24 OAM CCAM cutoff	91.99 146 x 597 x 34.7 (ILAM)

Soyuz T-5

 1982-042A

---

7K-ST No. 11L was launched in May 1982 as Soyuz T-5, carrying the first DOS 6 crew (D-6-1, DOS 6 EO-1) to the new Salyut-7 (DOS 6) orbital station. Commander was Anatoliy Berezovoy and flight engineer was Valentin Lebedev. On Aug 27, the visiting crew of Leonid Popov, Aleksandr Serebrov and Svetlana Savitsakaya used Soyuz T-5 to return to Earth.

Soyuz T-5, Flight 1
Date	Time	Event	Orbit
1982 May 13	0958:05	Launch by Soyuz-U	KB
	1000	Blok BVGD sep
	1002	Blok A sep
	1006	Blok I MECO
	1006	Blok I sep
1982 May 14	1100:35	Docked with Salyut-7 -X
		EO-1 crew to Salyut

Soyuz T-5, Flight 2
Date	Time	Event	Orbit
1982 Aug 27		Popov crew to Soyuz
	1145	Undocked -X
	1245?	BO sep
	1418?	DO
	1422?	DO CO	-75? x 298
	1430?	PAO sep
	1441?	Entry
	1504:16	Landed 70 km NE of Arkalyk

USA-141

 1998-058A

---

Atlas flight AC-130 placed the UHF F/O F9 satellite in orbit  using a Lockheed Martin Astronautics Atlas IIA with a 14-ft fairing. It took off from Cape Canaveral's Space Launch Complex 36A. The Atlas IIA first stage main (sustainer) engine is the Boeing Rocketdyne RS-56SA, based on the RS-27 used in Delta. Wrapped around the main engine section is a booster section with two very similar RS-56BA engines. The booster engine cutoff (BECO) was at T+2:45 (i.e. 2min 45s after launch), followed 3s later by separation of the heavy booster package with its two engines. The sustainer engine cutoff (SECO) was at T+4:35.

After separation of the Atlas stage at T+4:37, the Centaur II second stage takes over. Centaur is a liquid hydrogen fuelled stage using two Pratt and Whitney RL10A-4-1 engines. At T+9:53 the Centaur shut down putting the vehicle in a 168 x 1090 km x 28.9 deg elliptical parking orbit. After coasting around the orbit, Centaur reignited at T+22:23 for about one minute until its fuel was almost depleted. and then at T+27:03 separated from the payload. Target orbit was at least a 286 x 26733 km x 27.0 deg orbit, with an apogee 10000 km below geostationary. This shortfall is to be made up by the Marquardt R-4D bipropellant liquid apogee motor on the Hughes HS-601 satellite payload.

The payload is UHF F/O F9, a Block III UHF Follow-On comsat for the US Naval Space Command. Earlier UHF F/O satellites were launched by Atlas II, which has now been retired. The satellite carries UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass is 3200 kg, dropping to around 1550 kg once geostationary orbit is reached. Dry mass of the satellite is probably around 1200-1300 kg, but I haven't seen a figure on this. UHF F/O F9 was checked out in a slightly elliptical synchronous orbit over 170-175W and then in Jan 1999 placed over the Atlantic Ocean for operational service.

Although operated by the Navy, the payload is considered a joint Dept. of Defense asset with support for all services. UHF satellites were operated by US Space Command 3 SOPS/Schriever AFB until 1999 Jun 15, when control passed to NAVSOC/Pt Mugu.

UHF 9
Date	Time	Event	Orbit
1998 Oct 20	0719	Launch by Atlas II AC-130	SLC 36A
		T+2:45 BECO
		T+2:48 Booster sep
		T+04:34 SECO
		T+04:36 Atlas sep
		T+04:53 MES 1
	0728	T+09:53 MECO1	168 x 1090 28.9
	0741	T+22:23 MES2
	0742	T+23:36 MECO2	465.2 286 x 26733 x 27.0
	0746	T+27:03 Centaur sep	465.1 287 x 26726 x 27.0
		T+1:07:44 Depletion burn	461.0 279 x 26499 x 27.0
1998 Oct 20			448.35 272 x 25780 x 27.0
1998 Oct 21	1340?	LAM-1
1998 Oct 22			533.47 269 x 30552 x 26.9
1998 Oct 23	2340?	LAM-2
1998 Oct 23			790.82 7126 x 36772 x 14.8
1998 Oct 27	0430?	LAM-3
1998 Oct 27			1428.51 34478 x 36798 x 6.3 GEO 175.3W+1.9E
1998 Oct 28			1436.55 34808 x 36782 x 6.1 GEO 173.8W+0.1W
1998 Nov 5			1436.18 34810 x 36769 x 6.0 GEO 172.8W+0.03W
1998 Dec 3			1436.04 34815 x 36754 x 6.0 GEO 170.6W
1998 Dec 18			1435.95 34815 x 36751 x 6.0 GEO 172.2W
1998 Dec		Move out
1999 Jan		In service at 22W
1999 Jan 19			1436.09 35774 x 35798 x 5.9 GEO 22.5W
1999 Jul 26			1436.05 35768 x 35803 x 5.6 GEO 22.5W

Canadian Almanac & Directory, 2002: Over 50,000 Facts And Figures About Canada

 https://welib.org/md5/62666893f50a85fb1d154b31a518e8d1