Saturn S-IVB-504N

  1969-018B

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SA-504 was launched at 1600:00 on 1969 Mar 3. The S-IVB entered earth orbit at 1611:15, and Apollo 9 separated from it at 2018. The S-IVB restarted at 2045:47, entering a 207 x 3087 km x 32.6 deg orbit. A third burn at 2207:19 sent the stage on an escape trajectory to solar orbit. The burn involved an experimental extended preburn fuel supply, and several anomalies were reported; pressurization was lost in the engine system, losing about 2 km/s of velocity. At MECO-3 the velocity was 9.628 km/s at an altitude of 2283 km, and C3 was 824712 m²/s². The S-IVB reached a 325.8d, 128.561 x 148.678 Mkm x 24.39 deg solar orbit instead of the planned 240d, 76.808 x 149.340 Mkm x 22.27 deg orbit.

S-4B-504
Date	Time	Event	Orbit
1969 Mar 3	1600:00	Launch by Saturn V (SA-504)	KSC LC39A
	1602:14	S-IC CECO
	1602:43	S-IC OECO
	1602:43	S-IC sep
	1602:44	S-II ignition
	1603:13	Interstage sep
	1603:19	LES sep
	1608:57	S-II ECO, sep
	1608:57	S-IVB ignition
	1609:09	Ullage case jettison
	1611:04	S-IVB cutoff
	1611:15	Earth orbit insertion	189 x 191 x 32.6
			184 x 186 x 32.55
	1612:03	CVS vent on
	1622		88.31 184 x 197 x 32.6
	1841:16	Sep from S-IVB/SLA, SLA panels sep
		Transposition and docking maneuver
	1902:07	Docked with LM 3 (Spider)/S-IVB
	2008:06	CSM/LM undocked from S-IVB
	2045:47	Burn 2
	2046:57	MECO-2	196 x 3096 x 32.30
	2206:27	Burn 3, solar orbit
	2211:21	MECO-3	2280 x Inf x 33.82
	2212:51	LOX NPV vent
	2224:11	LH2 vent
	2334:05	APS depletion burn 9.7m/s
	2341:53	APS depletion complete

Apollo 9 (Gumdrop)

  1969-018A

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The Command and Service Module for the Apollo 9 mission was CSM 104, named Gumdrop for its shape. On Mar 8 Gumdrop lowered its perigee to improve conditions for multispectral photography of the Earth.

Gumdrop (CSM 104)
Date	Time	Event	Orbit
1969 Mar 3	1600:00	Launch by Saturn V (SA-504)	KSC LC39A
	1602:14	S-IC CECO
	1602:43	S-IC OECO
	1602:43	S-IC sep	-6000 x 110 x 32.1
	1602:44	S-II ignition
	1603:13	Interstage sep
	1603:19	LES sep
	1608:57	S-II OECO, sep	-2070 x 189 x 32.7
	1608:57	S-IVB ignition
	1609:09	Ullage cases 1 and 2 jettison
	1611:04	S-IVB cutoff
	1611:15	Earth orbit insertion	189 x 191 x 32.6
	1622		88.31 184 x 197 x 32.6
	1845	Sep from S-IVB/SLA, SLA panels sep
	1850	Transposition and docking maneuver
	1902:08	Docked with LM 3 (Spider)/S-IVB
	2008:06	CSM/LM undocked from S-IVB	194 x 212 x 32.6 (FER)
	2159:01	SPS 1 docked burn	201 x 233 x 32.6
	2159:06	SPS 1 cutoff	201 x 250 x 32.6 (MR)
1969 Mar 4	0055		88.84 217 x 217 x 32.6
	0500		88.90 202 x 237 x 32.6
	0634		88.69 201 x 218 x 32.6
	1200		88.82 203 x 228 x 32.6
1969 Mar 4	1412:03	SPS 2 orbit shaping	199 x 250 x 32.7 (MR)
	1413:54	SPS 2 cutoff	199 x 351 x 32.6
			199 x 370 x 32.6 (MR)
	1717:38	SPS 3 propellant utilization test	201 x 372 x 33.6 (MR)
	1722:19	SPS 3 cutoff	205 x 524 x 34.0 (MR)
			202 x 503 x 33.8
	1800		91.58 295 x 498 x 33.8
	2024:40	SPS 4 test burn	205 x 528 x 34.0 (MR)
	2025:09	SPS 4 cutoff	204 x 524 x 34.0 (MR)
	2145		91.63 198 x 510 x 33.8
1969 Mar 5	0920		91.57 204 x 498 x 33.8
1969 Mar 5	1741:33	Docked DPS burn	202 x 499 x 32.6
			203 x 520 x 34.0 (MR)
	1747:46	DPS 1 cutoff	203 x 523 x 34.1 (MR)
	2226:11	SPS 5 reshaping	203 x 519 x 34.1 (MR)
	2226:56	SPS 5 cutoff	239 x 250 x 33.8 (MR)
			229 x 239 x 32.6
	2317		89.24 227 x 246 x 33.6
1969 Mar 6	0515		89.23 225 x 247 x 33.6
	1155		89.21 233 x 237 x 33.6
1969 Mar 6		CDR and LMP to LM
	1401		89.15 223 x 241 x 33.6
	1653	Depress for SEVA by CMP
	1659	Fully depressed
	1701	Hatch open
	1749:25	Hatch closed
	1754	Repress (1:01)
		CDR and LMP to CSM
1969 Mar 7		CDR and LMP to LM
	0621		89.12 231 x 231 x 33.6
	1239:30	LM Undocked
	1240	CSM flyaround inspection of LM
	1302:53	RCS sep burn	233 x 242 x 33.7 (MR)
			235 x 225 x 32.6
	1303:03	RCS cutoff	234 x 242 x 33.7 (MR)
		Rendezvous by LM
	1826		89.10 213 x 246 x 33.6
	1859	LM docked with CSM
		CDR and LMP transfer to CSM
	2122:45	LM undocked
	2132:44	CSM sep burn	224 x 235 x 32.6
1969 Mar 8	0710		89.14 231 x 231 x 33.6
	1212		89.05 226 x 228 x 33.7
	1302		89.15 226 x 238 x 33.6
1969 Mar 8	1925:06	SPS 6 burn	195 x 222
	1925:08	SPS 6 cutoff
	2145		88.74 191 x 232 x 33.6
1969 Mar 9	1155		88.67 194 x 222 x 33.6
	1911		88.52 192 x 209 x 33.6
1969 Mar 10	1738:59	SPS 7 burn
	1739:25	SPS 7 cutoff	183 x 484 x 33.7 (MR)
	1820		90.94 181 x 459 x 33.5
1969 Mar 11	1021		90.92 176 x 462 x 33.5
1969 Mar 12	0605		90.95 189 x 452 x 33.5
	1136		90.84 181 x 449 x 33.5
	1338		90.89 176 x 459 x 33.5
1969 Mar 13	0413		90.80 182 x 444 x 33.5
1969 Mar 13	1631:14	SPS 8 deorbit burn 11.8s	186 x 456 x 33.6 (MR)
	1631:25	SPS 8 cutoff	-7 x 444 x 33.5 (MR)
			3 x 446 x 33.6 (MR)
	1636:03	SM-104 sep
	1644:10	Entry interface	0 x 452 x 34.6 (MR)
	1700:54	Splashdown in Atlantic
	1750	Recovered by USS Guadalcanal

Apollo 9 (Spider)

  1969-018C

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LM 3 was the first piloted test flight of an LM, carried out in Earth orbit.

On Mar 6 the first spacewalk of the Apollo program was carried out. With Scott in the CSM, and McDivitt and Schweickart in the LM, the LM hatch was opened. Schweickart went out onto the LM porch. The spacecraft was repressurized after 1h 7min.

On Mar 7, Spider undocked and carried out tests of the DPS engine. After two burns of the DPS, the Descent Stage was jettisioned; it reentered on Mar 22. The APS was then put through its paces, with a successful rendezvous and docking. After the crew returned to the CSM, Spider was jettisoned and the APS burned again to leave the ship in an elliptical orbit.

Spider (LM3)
Date	Time	Event	Orbit
1969 Mar 3	1600:00	Launch by SA-504	KSC LC39
	2018	Removed from S-4B-504 by CSM 104
1969 Mar 5	1000?	Crew entry, power up
1969 Mar 5		RCS test, legs deployed
			202 x 503 x 33
	1741:33	Docked DPS burn	202 x 499 x 33
1969 Mar 6	1644	LM depressurized
	1646?	HO?
1969 Mar 6		EVA by LMP
	1707:37	Egress LMP
	1745	Ingress
	1749:57	Hatch closed
	1751	LM repress
1969 Mar 7		Transfer hatch closed
	1239:20	Undocked from CSM 104	229 x 239 x 33
			224 x 252 x 33.7 (MR)
	1347:34	DPS phasing burn	207 x 253 x 33
	1347:54	DPS cutoff	210 x 265 x 33.7 (MR)
	1539:07	DPS insertion burn	248 x 257 x 33
	1539:30	DPS cutoff
	1616:04	LM3 DS separation	89.3 242 x 246 x 33.6 (DS)
	1616:06	RCS 30s CSI burn	208 x 255 x 33
	1616:36	RCS cutoff
	1658:14	APS constant DH burn, 3s	207 x 215 x 33
	1658:17	APS cutoff
	1757:59	TPI burn 7m/s LM RCS	208 x 233 x 33
	1758:36	TPI burn off
	1827	2 km, at 10m/s
	1830	170m
	1830:51	TPF burn	224 x 234 x 33
	1834	Rendezvous with CSM 104 at 30m
	1859	Docked with CSM-104
	1940	Transfer hatch open, crew transfer to CSM
	2045?	Transfer hatch closed
	2122:45	Undocked from CSM-104	225 x 234 x 33 ?
	2132	CSM leaves LM vicinity
	2153:20	APS depletion burn 5:42
	2159:10	APS burn ends	164.7 230 x 6939 x 28.91
1969 Mar 8	0358		164.96 234 x 6936 x 28.9
1970 Oct 9			156.63 230 x 6263 x 29.0
1981 Jun 6			99.66 198 x 1285 x 28.8
1981 Oct 23	1500?	Reentered

Kosmos 1348

 1982-029A

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Kosmos-1348
Date	Time	Event	Orbit
1982 Apr 7	1342	Launch by 8K78M	Plesetsk
		BVGD sep
		GO sep
		T+4:46 Blok A sep
		T+4:56 KhO sep
		T+8:46 Blok-I MECO
	1350	T+8:50 Blok-I sep
		T+1:00? BOZ burn
	1442?	T+1:00? BOZ sep
		2BL burn
		2BL MECO
	1445?	T+1:03 2BL sep
1982 Apr 7			708.8 593x39316x62.8
1982 Apr 24			717.7 607x39745x62.9

Kosmos 469

 1971-117A

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A US-A satellite was launched in Dec 1971 from Baikonur,reached orbit and was named Kosmos-469. It operated in the low orbit for ten days before the reactor section was separated and boosted to a higher orbit. One solution for the orbit change is with burns at 0637, 0729 UTC on Jan 4; this is consistent with the claimed time of orbit change in the RAE tables. However, a pair of elsets for the separate reactor and propulsion sections for epoch around 0300 UTC suggests that separation took place before that time. I therefore adopt another solution with burns at 2013 and 2105 UTC on Jan 3.

Kosmos-469
Date	Time	Event	Orbit
1971 Dec 25	1130	Launch by 11K69	KB
	1132	Stage 2 burn
	1134	Stage 2 sep
	1144?	DU burn
		DU cutoff, orbit
	1154?	Stage 2 entry
	1549		89.63 244 x 267 x 64.9
1971 Dec 26	0000		89.60 249 x 262 x 64.94 (RAE)
1972 Jan 3	2013?	DU and radar section sep
1972 Jan 3	2013?	DV1
	2105?	DV2
1972 Jan 4	0255		89.48 242 x 254 x 65.0
1972 Jan 5	0754	Reactor section	104.72 946 x 1015 x 64.5
1972 Jan 7	1521?	DU reentered
1972 Jan 15	1430	Reactor section	104.74 941 x 1023 x 64.50
1972 Feb 9	0155?	Radar section reentered

ADEOS-1

 1996-046A

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The ADEOS satellite was launched in Aug 1996. NASDA's ADEOS Advanced Earth Observing Satellite was built by Mitsubishi Electric of Tokyo. The 3200 kg satellite has a 4m x 4m x 5m bus with a 3 x 13 m solar array. It carries a payload to study the ozone layer and the greenhouse effect, as well as an inter-satellite communications experiment. The satellite was named Midori (`green') on reaching orbit, but the ADEOS name was almost always used.

The main 20N thrusters malfunctioned, and initial orbit adjust was made by the small 1-N thrusters. In June 1997 the solar panels failed structurally and the spacecraft was lost.

ADEOS
Date	Time	Event	Orbit
1996 Aug 17	0153	Launch by H-II (4F)	TNSC
	0154	SRB burnout (T+1:33) and sep (T+1:40)	44km
	0156	Fairing sep (T+3:50), 151 km
	0158	T+5:45 Stage 1 cutoff
	0158	T+5:55 Stage 1 sep, 321 km
	0159	Stage 2 burn T+6:01
	0207	Stage 2 cutoff T+14:57), 802 km
	0208	ADEOS sep from Stage 2 (T+15:47)
	0234?	Stage 2 burn 2
	0234?	Stage 2 cutoff 2
	0234?	JAS sep from Stage 2
	0315?	Stage 2 depletion?
1996 Aug 24		Orbit raise begin
1996 Sep 8		In op orbit
1996 Sep 11		OCTS radiation cover deployed
1997 Jun 23		Solar panel problems
1997 Jun 27		Power decrease begins
1997 Jun 30		Battery power only, safemode
	0520	(1620JST) loss of signal
1997 Jul 2		end of ops

Payload:

• OCTS Japanese NASDA Ocean Color /Temp Scanner

• AVNIR Japanese NASDA Adv Vis/Near IR Radiometer

• IMGG Japanese MITI Interferometric Monitor for Greenhouse Gases (Greenhouse effect)

• ILAS Japanese Envir. Agency Improved Limb Atmospheric Spectrometer (spectrometer)

• Japanese Retroreflector (laser as atmospheric probe)

• NSCAT NASA Scatterometer (wind speed) NSCAT (Earth Probe)

• TOMS NASA Ozone Mapping Spectrometer TOMS