DFH-2

 1971-018A

---

China's second satellite was Shi Jian 1 (SJ 1, PRC 2). Shi Jian has been translated as `Practice' or `Test'. SJ 1 was similar in construction to DFH 1. It carried a magnetometer and solar cells, and cosmic ray detectors. SJ 1 transmitted until at least 1977. Transmissions continued on 20.008MHz from the final stage rocket until Mar 11, after which 19.995 MHz transmissions from the payload began, and it appears that the rocket did not separate until then.

Shi Jian 1
Date	Time	Event	Orbit
1971 Mar 3	1202?	Launch by CZ1	JQ
	1203?	T+1:00 Stage 2 burn
	1204?	T+3:00? Stage 2 burnout
	1206?	Stage 2 sep
	1209?	Stage 3 burn
	1210?	Stage 3 burnout
			106.2 268 x 1830 x 69.9
1971 Mar 10		Stage 3 separated
1971 Mar 26		end of tx from stage 3
1977?		end of transmissions
1979 Jun 17		Reentered over Lake Michigan

Explorer 8

  1960-014

---

The S-030A ionospheric studies payload was launched on 1960 Nov 3 at 0523 by a Juno II from LC26B at Cape Canaveral. Jupiter AM-19D was used with JPL Cluster 17. S-30A entered a 417 x 2288 km x 49.95 deg orbit (planned inc was 50.3) and operated until 1960 Dec 27. S-30A was also called the Ionosphere Direct Measurements Satellite. Explorer 8 studied the temporal and spatial distribution of ionospheric properties and confirmed the presence of a helium layer in the upper atmosphere.

S-30A was developed by MSFC with GSFC experiments.

The despin weights were 0.3 kg on a 5.2m wire.

Explorer 8
Date	Time	Event	Orbit
1960 Nov 3	0523:10	Launch by Juno II	CC LC26B
	0526:09	MECO
	0526:16	Stage 1 sep
	0526:44	Fairing sep
	0531:13	Stage 2 burn
	0531:18	Burnout
	0531:22	Stage 3
	0531:29	Burnout
	0531:32	Stage 4
	0531:38	Burnout
	0533:45	T+10:35 Stage 4 sep	370 x 2341 x 49.9
	0534?	Despin stage 1 (yo-yo)
	0535?	Despin stage 2 (RF impedance probe)
1960 Dec 27	1220	Last transmission

Payload:

• Electric field meter

• Single grid ion trap

• Langmuir probe

• Multigrid ion trap

• Micrometeor energy detector

• Micrometeor microphone board

• RF impedance probe, 2 x 3.0-m booms

Raduga 2

 1976-092A

---

Raduga (Gran') No. 12 was launched in Sep 1976 and stationed at 85E. NORAD stopped tracking in 1980 and resumed in 1987. The satellite was drifting slowly in the Indian Ocean gravitational stable point in the late 1990s. 

Raduga No. 12
Date	Time	Event	Orbit
1976 Sep 11	1824	Launch by Proton-K	KB
	1833	Stage 3 MECO	177 x 184 x 51.5
	1941?	DM burn 1	331 x 35802 x 47.3
1976 Sep 12	0057?	DM burn 2
	0101?	DM sep
			GEO 85E
1977 Sep 5			1436.24 35770 x 35808 x 0.4 GEO 85.3E
1978 Apr 29			1436.14 35776 x 35797 x 0.9 GEO 85.9E
1980 May 23			1436.09 35764 x 35808 x 2.4 GEO 85.7E
1985?		end of ops
1987 Apr 23			1435.71 35661 x 35896 x 8.0 GEO 72.7E
1987 Jul 26			1435.77 34675 x 35885 x 8.2 GEO 81.6E+0.07
1988		Drift 85E-67E
1999 Apr 20			1436.07 35694 x 35877 x 15.0 GEO 63.2E

Inmarsat 201

 1990-093A

---

The Matra/BAe Eurostar 1000 spacecraft built for Inmarsat as the first of the second generation Inmarsat system carried an L-band payload for mobile communications. BAe was lead contractor.

In 1996 it was replaced as the prime IOR satellite by Inmarsat III F1.

Inmarsat II F-1
Date	Time	Event	Orbit
1990 Oct 30	2316:00	Launch by Delta 6925	CC LC17
		T+0:56 SRM 1-3,7-9 out
		T+1:01 SRM 4-6 on
		T+1:02 SRM 1-3 sep
		T+1:03 SRM 7-9 sep
		T+1:57 SRM 4-6 off
		T+2:02 SRM 4-6 sep
		T+4:25 MECO
		T+4:31 VECO
		T+4:33 Stage 1 sep
	2320	Stage 2 TIG (T+4:38)
	2320	Fairing sep (T+4:50)
	2327	SECO-1 (T+11:37)	186 x 186? x 29.4?
	2335	Delta SES-2
	2336	Delta SECO-2	186? x 1170? x 25.0?
		spinup
	2337?	T+21 Delta sep
	2337?	TES
	2338?	TECO
	2340?	T+24:55 Stage 3 sep
1990 Oct 31	0001	T+45:05 Stage 3 sep	647.28 188 x 36629 x 23.6
	0002	despin weights
	0018	Stage 2 depletion	100.39 379 x 1174 x 24.8
1990 Nov 1	1300?	LAM-1	718.47 3922 x 36466 x 14.55
1990 Nov 2	1600?	LAM-2	1271.08 28510 x 36472 x 2.9
1990 Nov 4	1200?	LAM-3	1453.78 35681 x 36582 x 2.9 GEO 38.3W+46.8E
1990 Nov 9			1436.22 35704 x 36582 x 2.7 GEO 49.2E+4.3W
1990 Nov 16			1436.51 35661 x 35927 x 2.6 GEO 29.9E+0.1W
1990 Nov 24			1436.35 35658 x 35928 x 2.6 GEO 29.2E
1990 Nov		Move to IOR
1990 Nov		Due at IOR 64.5E
1991 Feb 19			1436.03 35701 x 35869 x 2.4 GEO 64.5E
1991 Mar 28			1436.06 35734 x 35837 x 2.3 GEO 64.5E
1993 Jun 20			1436.03 35726 x 35844 x 1.7 GEO 64.5E
1996 Apr 16			1436.04 35771 x 35799 x 1.8 GEO 64.5E
1996 Jul		IOR Spare	GEO 65E
1996 Sep 4			1435.97 35759 x 35808 x 1.9 GEO 65.2E
1996 Sep		Move to POR
1996 Nov 22			1436.18 35773 x 35803 x 1.9 GEO 179.0E
1997 Jan 7			1435.95 35770 x 35797 x 1.9 GEO 179.6E
1999 Jun 10			1436.02 35768 x 35801 x 1.8 GEO 179.1E
2002 Apr 5			1436.02 35772 x 35797 x 2.1 GEO 179.0E

Kosmos 1385

 1982-068A

---

Two-tone telemetry; Medium res satellite

Kosmos-1385
Date	Time	Event	Orbit
1982 Jul 6	0750	Launch by Soyuz-U	Plesetsk
	0754	Blok-I burn
	0758	Blok-I sep
1982 Jul 6			88.76 186x238x82.3
1982 Jul 7			91.55 309x389x82.3
1982 Jul 15			91.52 305x391x82.3
1982 Jul 20
	0320?	Deorbit
	0330?	PO sep
	0346?	Entry
	0358?	Landed

Uplink-Downlink: A History of the Nasa Deep Space Network, 1957-1997

 https://welib.org/md5/14477c328ad4834278062a6a7c53cf3d

Kosmos 404

  1971-027A

---

Kosmos-404 was launched in Apr 1971 and intercepted Kosmos-400 on its second revolution, with a slow pass. It was maneuvered to a lower orbit and then deorbited. Orbital data from Apr 5 and 6 may refer to a fragment from the second stage or the DU; 1971-27D appears to be the same object.

Kosmos-404
Date	Time	Event	Orbit
1971 Apr 4	1427	Launch by 11K69	KB
	1429	Stage 2 burn
	1432?	Stage 2 sep	92.34 148 x 632 x 65.1 (RAE)
		168 x 800? x 65.3
	1520?	DU burn
	1736		103.11 801 x 1009 x 65.7
	1743?	Flypast Kosmos-400, 4W 24N 1000 km
1971 Apr 4	?	Deorbit
1971 Apr 5	0915		94.27 168 x 797 x 65.32
1971 Apr 6	1700		92.41 125 x 659 x 65.0

Kosmos 468

  1971-114A

---

The 9th Strela-2 satellite was Kosmos-468, launched in Dec 1971 from Plesetsk. Kosmos-468 was placed in an orbital plane which would become the basis of a satellite constellation; I designate it as Strela-2 plane A. 

Kosmos-468
Date	Time	Event	Orbit
1971 Dec 17	1300:01	Launch by 11K65M	PL
	1302?	Stage 2 burn
	1308?	Stage 2 coast
	1334?	Stage 2 burn 2
	1334?	Stage 2 sep
1971 Dec 27	0500		100.83 786 x 809 x 74.0

King Arthur In America

 https://welib.org/md5/5fbc068073bb2cae8d85f39365d46d30

Graduation: A Time For Change: A For Better Or For Worse Collection

 https://welib.org/md5/0c2f6b92d7328cbf582f0785bee810a2

Luxury Dream Homes: 170 Lavish Designs

 https://welib.org/md5/03b4f10a267c39e27422a6d600d8de7a

Telstar 301

 1983-077A

---

AT&T;'s Telstar 301, or Telstar 3A, was launched by a Delta 3920 in 1983. In 1994 it was leased to Telesat. Telesat later leased it to Arabsat and it was renamed Arabsat 1D-R.

Telstar 301
Date	Time	Event	Orbit
1983 Jul 28	2249:02	Launch by Delta 3920/PAM-D	CC LC17A
		T+3:44 St 1 MECO
		T+3:52 St 1 sep
		T+3:57 SES-1 7:08
		T+4:00 Fairing
	2300	T+11:05 SECO-1	180? x 190? x 29?
	2309	T+20:14 St 2 sep
	2309	T+20:52 TES 86s
	2311	T+22:18 TECO
	2313	T+24:26 Stage 3 sep	197 x 37264 x 22.8
	2355?	St 2 depletion	263 x 379 x 25.99
1983 Jul 29	0700?	Apo 1
	1600?	Apo 2
1983 Jul 29	1555?	Star 30B burn 54s at 2nd apo
1983 Jul 29			1405.54 33112 x 37260 x 0.5 GEO 76.7W+7.8E
1983 Jul 30		Tests	GEO 66W
1983 Aug 1			1436.04 35437 x 36133 x 0.2 GEO 65.4W
1983 Sep 17			1436.32 35459 x 36122 x 0.2 GEO 66.2W
1983 Sep?			GEO 96W
1983 Oct 16			1436.10 35781 x 35791 x 0.0 GEO 96.0W
1984 Apr 25			1436.11 35778 x 35795 x 0.0 GEO 96.0W
1985 May 15			1436.11 35779 x 35794 x 0.0 GEO 96.0W
1985 May 25			1436.12 35782 x 35791 x 0.1 GEO 104.8W
1985 Jul 17		Spacing for T303?	1436.58 34540 x 37052 x 0.1 GEO 103.1W+0.1W
1985 Aug 26			1436.13 35783 x 35791 x 0.0 GEO 96.1W
1985 Nov 25			1436.08 35781 x 35791 x 0.0 GEO 96.0W
1986 Jun 11			1436.10 35779 x 35794 x 0.0 GEO 96.0W
1987 Jul 6			1436.12 35779 x 35795 x 0.0 GEO 96.0W
1988 Sep 9			1436.11 35778 x 35795 x 0.0 GEO 96.0W
1989 Aug 25			1436.11 35781 x 35792 x 0.0 GEO 96.0W
1991 Mar 7			1436.10 35770 x 35802 x 0.0 GEO 96.0W
1992 Sep 27			1436.11 35778 x 35795 x 0.0 GEO 96.0W
1993 Nov 20			1436.11 35756 x 35817 x 0.1 GEO 95.9W
1993 Dec		Replaced by Telstar 401
1994 Feb 27		mv out	1436.11 35778 x 35794 x 0.3 GEO 96.0W
1994 Mar 14			1437.30 35801 x 35819 0.4 GEO 100.9W+0.3W
1994 Mar 28		Leased to Telesat
1994 Apr		Moved to colocate with Anik E-2
1994 Apr 17		mv in	1436.08 35779 x 35793 x 0.5 GEO 107.1W
1994 Jun 7		Sell to Arabsat
1994 Jun 10			1436.10 35774 x 35798 x 0.6 GEO 107.1W
1994 Aug 3			1436.08 35775 x 35797 x 0.7 GEO 107.0W
1994 Aug 6		Move out	GEO 104W drift 0.8/d
1994 Dec 1			GEO 11W drift
1995 Jan 13			GEO 13E drift
1995 Feb 6			GEO 20E
1995 Feb 6			GEO 34.5E (mis-id?)
1995 Feb 13			GEO 34.5E (mis-id?)
1995 Feb 14		Mv in as Arabsat 1D-R	GEO 20E
1995 Feb 18			1436.03 35776 x 35793 x 1.1 GEO 20.0E
1996 Aug 16			1436.04 35778 x 35792 x 2.3 GEO 20.0E

Magill's Literary Annual 2001: Essay-Reviews of 200 Outstanding Books Published in the United States During 2000

 https://welib.org/md5/754ccb519e33a213f454c2ff7309868f

The Conquest of Space

https://welib.org/md5/68377b9cf3a10e8519b8f395084e0f89

Soyuz TM-32

 2001-017A

---

Souuz TM 206 (ISS 2S) was the first taxi flight, with the MKS-T1 crew (Kristall). EP-1 (orig MirCorp Citizen Explorer flight) with Dennis Tito, a rich investment management executive and former JPL trajectory guy. Commander was Talgat Musabaev and BI was Yuriy Baturin.

During reentry, the crew were subjected to 7g instead of the planned 4.8g. One rumour said the astronauts armed the deorbit engine later than intended, but official Russian statements indicated an error in the loaded guidance commands causing an incorrect entry angle.

 

Soyuz TM-32
Date	Time	Event	Orbit
2001 Apr 28	0737:20	Launch by Soyuz-U No 674	KB PU5
	0746:06	Blok I sep
	1119:32	TCM1 49 kg 19.3m/s
	1129:48	TCM2 75 kg 29.5m/s
2001 Apr 29		0.8m/s TCM
2001 Apr 30	0730	Rendezvous with ISS
	0757:47	Docking Zarya -Z port
	0928	HO to ISS
2001 Oct 19	0620	HC to ISS; EX-3 aboard
	1048:10	Soyuz undocked from Zarya
	1058	Begin lateral move
	1102	Approach
	1104:10	Dock with Pirs
	1240?	HO to ISS
2001 Oct 30	2237	HC to ISS
2001 Oct 31	0138:30	Undocked from Pirs
	0142	Sep burn 8s 0.7m/s
	0404:10	Deorbit 4:12 115.2m/s
	0407	Deorbit MECO	88.39 5? x 384 x 51.6
	0430?	Modules sep
	0459:26	Landed

A History of the American People

 https://welib.org/md5/014553c45df036be7219fec97c1949

DASH

 2002-003B

---

The ISAS Demonstrator of Atmospheric Reentry System at Hypervelocity (DASH) is a secondary payload on H-IIA-F2. It will deorbit from GTO at high (hyperbolic) velocity. The mission is a test for MUSES-C. It was meant to reenter at 10.2 km/s between -18.5 and -16.5 at 200 km (corresponding to -423 x 34153 x 28.5 to -574 x 34305 x 28.5) and land in Africa (Mauritania? at about 8.5W 17.2N. in the Hodh el Gharbi region. In the event it failed to separate from VEP-3.

DASH consists of a hexagonal bus with a deorbit motor (DOM), and a blunt cone reentry capsule, and two DFM thrusters for orbit adjust at apogee. The size of DASH is 0.99m x 0.70m x 0.54m. including the comms antenna; bus size is 0.7 x 0.5m. Mass of the orbiter and DOM is 70 kg. The reentry capsule has a mass of 16 kg and is 0.40m dia, 0.20m high. A 3 kg adapter is mounted to the H-2A upper adapter.

In Japanese DASH is

\uni{ 高速再突入実験機}{ }

(Kosoku sai totsunyu jikken ki, High speed reentry experimental machine).

DASH (planned)
Date	Time	Event	Orbit
2002 Jan 31		Launch
		T+0:10 SSB 1-2 on
		T+1:10 SSB 1-2 sep
		T+1:16 SSB 3-4 on
		T+2:16 SSB 3-4 sep
		SRB-A sep
		Stage 1 sep
		Stage 2 MES
		Fairing sep
		Stage 2 MECO-1
		Stage 2 MES-2
		Stage 2 MECO-2
		DASH/VEP-3 separates from Stage 2
		Stage 2 deploy MDS-1
		VEP-3 failed to deploy DASH
		D+5:00 Sep ENA
		D+5:56 SPM
		D+37h DFM
		D+43h DFM
2002 Feb 4		D+76h DOM burn
		Yo-yo despin
		Capsule separation
		T+85h Reentry

Skynet 2B

  1974-094A

---

The Skynet 2B satellite was similar to Skynet 2A in design. It was launched in Nov 1974 and began an extremely successful career relaying UK military communications. It ran out of stationkeeping fuel in the 1980s but it was still working in 1994. The spacecraft is currently drifting between 0 and 150 deg E longitude.

Skynet 2B
Date	Time	Event	Orbit
1974 Nov 23	0028:01	Launch by Delta DSV-3P-11A (2313)	CC LC17B
		T+0:38 SRM 1-3 out
		T+1:10 SRM 1-3 sep
	0031:45	T+3:45 MECO
	0031:54	T+3:54 VECO
	0031:56	Stage 1 sep
	0032:03	T+4:02 SES-1 4:43
		T+4:37 Fairing
	0037:16s	T+9:15 SECO-1	176 x 200 km
	0049:48	T+21:47 SES-2 16s
	0050:06	T+22:05 SECO-2	183 x 1152 x 28.17
	0050:58	T+22:57 St 2 sep
	0051:31	T+23:30 TES 44s
	0052:15	T+24:14 TECO Star 37 burnout	175 x 36965 x 24.6
	0053:31	T+25:30 Star 37 sep	185 x 36944 x 24.6
1974 Nov 23	0104?	SES-3 engineering burn	311 x 3347 x 28.3
	0600?	Apo 1 95E
	1700?	Apo 2 70W
1974 Nov 24	0400?	Apo 3 125E
	1500?	Apo 4 40W
1974 Nov 25	0130?	Apo5 170E
1974 Nov 25	0110	Star 24 AKM 42s, apo 5	GEO +6E/d
			36255 x 36621 x 2.3
1975 Jan 3		On station IOR GEO 50E
1975 Dec 30			GEO 55E (Morgan)
1977 early		Command system failure	GEO dr
1977 Mar 1			1435.25 35757 x 35782 x 0.8
1978 Sep			GEO dr
1979 Oct 31			1435.75 35753 x 35806 x 1.5 GEO 4.4E+0.1E
1979 Dec			GEO 1W
1980 Dec 6			1435.17 35740 x 35796 x 2.2 GEO 123.8E+0.2E
1981 Feb			GEO 137E
1981 Jun			GEO 140.4E+0.03
1981 Sep 8			1436.81 35791 x 35809 x 2.7 GEO 130.2E+0.2W
1982 Nov			GEO 6E
1983 Jan			GEO 1E
1983 Sep			GEO 9E
1984 May 25			1434.48 35753 x 35756 x 4.7 GEO 93.3E+0.4E
1985 Apr			GEO 138E
1985 Jun 2			1436.82 35799 x 35801 x 5.6 GEO 130.1E+0.2W
1985 Jul			GEO 0W
1985 Sep		Drifting
1988 Jun 27			1435.36 35759 x 35784 x 8.1
1994 Jan 13			1436.68 35776 x 35819 x 12.3
1994		Still operating
1998 Sep 8			1435.87 35751 x 35812 x 14.1

CONTOUR

 2002-034A

---

Contour, the Comet Nucleus Tour, is the 2002 Discovery mission. Its goal is to image comet nuclei at 4m resolution, and provide nuclear spectral maps at 100-200m resolution. It will also make composition measurements on cometary gas and dust. The APL-built probe is led by a Cornell University team.

Mass is 970 kg at launch - 387 kg dry, 503 kg Star 30BP S/N 074, 80 kg hydrazine. Size is a 2.0m dia, 2.0m long octagonal cylinder.

Contact was lost at solid motor firing. Three fragments were observed: A, B and C. A design error meant that the spacecraft overheated and key components were destroyed. B is a small 4 kg piece based on acceleration measurements. A had a mass of around 300 kg, and is probably the main bit of Contour.

 

Contour
Date	Time	Event	Orbit
2002 Jul 3	0647:41	Launch by Delta 7425-9.5
		T+1:03 SRM 1-4 burnout
		T+1:08 SRM 1-4 sep
	0652:05	T+4:24 MECO
		T+4:32 Stage 1 sep
	0652:18	T+4:37 SES-1
		T+4:42 Fairing sep
	0659:17	T+11:36 SECO-1	185 x 197 x 29.7
	0746:11	T+58:30 SES-2
	0746:15	T+58:34 SECO-2	185 x 308 x 29.7
	0747:08	T+59:27 St 2 sep
	0747:47	T+1:00:06 PAM-D burn 2921 m/s
	0749:13	T+1:01:32 TECO	2423.6 90 x 106689 x 30.5
	0751:11	T+1:03:30 St 3 sep
	0751:13	T+1:03:32 Yo weight sep
		SES-3 depletion	174 x 300 x 30.4
2002 Jul 4		Apogee 1
2002 Jul 5	0325	Perigee 1
2002 Jul 6		Apogee 2	236 x 109000?
	1644	OCM-2, +3.8m/s, phasing period
2002 Jul 6	2106	Perigee 2
2002 Jul 7		Apogee 3	268 x ?
2002 Jul 8	1458	Perigee 3
2002 Jul 11	2018	Perigee 5 OCM-4 +0.9m/s
2002 Jul 18			217 x 108466 x 30.24
2002 Jul 20			231 x 108441 x 30.21
2002 Jul 23	2150	OCM-5 +0.12m/s	225 x 108484 x 30.26
2002 Jul 27			198 x 108481 x 30.56
2002 Jul 27	1202	OCM6, 58s 3.0m/s at TRUE=148.5	197 x 108457 x 30.6
2002 Jul 28			230 x 108704 x 30.6
2002 Jul 30			246 x 108685 x 30.74
2002 Jul 31	1713	OCM7 3.2m/s 63s lower perigee	266 x 108645 x 30.7
2002 Aug 2			228 x 108610 x 30.5
2002 Aug 3	0715	OCM8 Perigee 0.7m/s 18s at 12021 km, return to 1.75d	242 x 108618 x 30.5
2002 Aug 5			238 x 109658 x 30.5
2002 Aug 6	1722	OCM-9 0.22m/s to adjust time and C3
2002 Aug 13	1521	Perigee
2002 Aug 14	1206	Apogee R = 115058 km
2002 Aug 15	0849	Perigee
2002 Aug 15	0849	Solar orbit injection with SRM, 50 s, 1.926 km/s planned
		Actual dV 1.850 km/s
		Loss of signal	240 x -33995 x 30.6
			225 x -34869 x 30.98 (A)
2002 Aug 15	1446	C Pass EL1:4
2002 Aug 15	1450	B Pass EL1:4
2002 Aug 15	1450	A Pass EL1:4
2002 Aug 17	0400	C leaves E/M SOI
2002 Aug 17	0500	A leaves E/M SOI	225 x Inf x 30.97
2002 Aug 17	0500	B leaves E/M SOI
2002 Aug 18	0242	C leaves Earth sphere 1.5Mkm
2002 Aug 18	0342	B leaves Earth sphere 1.5Mkm
2002 Aug 18	0342	A leaves Earth sphere 1.5Mkm
2003 Jan 1		Fragment A	0.876 x 1.131 AU x 8.71
2003 Jan 1		Fragment B	0.875 x 1.132 AU x 8.72
2003 Jan 1		Fragment C	0.871 x 1.129 AU x 8.91
2003 Aug 14	0800	C within E/M SOI	742000 x Inf x 37.45
2003 Aug 15	1329	Fragment C flies 742000 km +/- 1.3Mkm from Earth
2003 Aug 16	1333:12	Fragment A flies 4926000 km from Earth
2003 Aug 16	2000	C leaves E/M SOI
2003 Aug 17	0015	Fragment B flies 6820000 km from Earth
planned
		Star 30 cutoff	225 x Inf
2002 Aug 16		TCM-1	0.80 x 1.35 AU
2003 Aug 15		Earth flyby 58000 km
2003 Aug			0.9 x 1.2 AU?
2003 Nov 12		2P/Encke flyby 100 km at 1.07AU from Sun
2004 Aug 14		Earth flyby 40180 km
		Orbit i = 12.0	1.0 x 1.0 AU x 12.0?
2005 Feb 10		Earth flyby 218770 km
2006 Feb 10		Earth flyby 30000 km
2006 Feb			0.9 x 1.1 AU? x 0?
2006 Jun 18		73P/Schwassmann-Wachmann-3 flyby at 0.95AU from Sun
2007 Feb 10		Earth flyby 7600 km
2007 Feb			0.8 x 1.35 AU?
2008 Feb 11		Earth flyby 19000 km
2008 Aug 15		6P/d'Arrest flyby at 1.35 AU from Sun.

Payload:

• CRISP Contour Remote Imager/Spectrograph

• CAI Contour Aft Imager

• CIDA Dust Analyser

• NGIMS Neutral Gas Ion Mass Spectrometer