Deep Space 1

 1998-061A

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NASA carried out its first launch in the New Millenium Program (NMP) on 1998 Oct 24. Deep Space 1 was placed in solar orbit by a Boeing Delta 7326 rocket.

Delta 7326 is a new variant of Delta II which uses three solid Alliant GEM-40 strapons, the standard Delta II first and second stages, and a Thiokol Star 37FM solid motor as the third stage. This third stage is smaller than the usual Delta II Star 48 third stage, but much more powerful than the earlier Star 37E model used as Delta's third stage in the 1970s and 1980s.

Delta entered a 185 km parking orbit, then fired again to enter a 174 x 2744 km x 28.5 deg orbit. The third stage separated and accelerated to solar orbit with DS1, while the second stage burned again to a planned 556 x 1042 km x 31.5 deg orbit with SEDSAT.

The 475 kg Deep Space 1 probe's structure was built by Spectrum Astro/Gilbert for JPL using the SA-200HP bus. JPL and SA collaborated on building the spacecraft systems. Its mission is to test new technology for future probes, and the main experiment is a xenon ion propulsion drive. DS1 was the first space probe to use solar electric propulsion as its primary engine. The original plan was to fly past Mars, asteroid McAuliffe and a comet West-Kohoutek-Ikemura and measure their composition with an imaging spectrometer.Delay of the launch meant a new trajectory had to be chosen. DS1 flew past minor planet (9969) Braille, formerly 1992 KD. An additional 2001 flyby of Comet Borelly was added later.

DS1 found that Braille had a rotation period of 9.4 days and a size of 2.1 x 1 x 1 km - the elongated shape raising the possibility of a contact binary.

Mass is 373.7 kg dry; it carried 81.5 kg Xe and 31.1 kg of hydrazine at launch. Propulsion is one 90mN ion thruster and 8 1-N hydrazine thrusters. The bus is an SA-200HP. Electronics and thermal control are build into the multifunctional structure of the spacecraft. A beacon monitor experiment will send back a simple 'green, yellow, red' health state signal to tracking stations. DS1 used some backup hardware from Mars Pathfinder, including the high gain antenna, and used the same design for some electronics and the on board computer.

Launch vehicle is the Delta 7326-9.5.

DS 1
Date	Time	Event	Orbit
1998 Oct 24	1208:00	Launch
		T+1:03 SRM cutoff
		T+1:06 SRM 1-3 sep, 16 km
		T+4:24 MECO
		T+4:37 Stage 1 sep
		T+4:37 Delta burn 1
		T+4:58 Fairing sep, 125 km
	1218	T+10:29 Delta SECO-1	88.20 185 x 185 x 28.5
	1254	T+46:11 Delta burn 2	88.21 173 x 198 x 28.5
	1255	T+47:05 Delta SECO-2	115.10 174 x 2744 x 28.5
	1255	T+47:58 Delta sep
	1256:35	T+48:35 Star 37FM burn	115.10 174 x 2744 x 28.5
	1257:40	T+49:40 Star 37FM TECO
	1301	T+53:37 Yo-yo weights sep
	1301:43	T+53:43 Star 37FM sep 550 km Solar orbit C3=3.13	185 x -267640 x 28.5
	1310	T+1:02:54 Delta burn 3	115.13 180 x 2742 x 28.5
	1311	T+1:03:25 Delta SECO 3	100.86 556 x 1042 x 31.5
	1336	T+1:28:20 SEDSAT sep from Delta
1998 Oct 25	0015	Pass EL1:4
1998 Nov 1	1504	Depart Earth sphere (1.5Mkm)
1998 Nov 9			446.6d 0.990 x 1.287 AU x 0.37
1998 Nov 10	1930	NSTAR burn 4.5min, shutdown
1998 Nov 11	2005	Safemode after star tracker fail
1998 Nov 17		Safemode, star tracker
1998 Nov 24	2253	NSTAR burn begins
1998 Dec 8		NSTAR burn off	450.1d 0.991 x 1.298 AU x 0.37
1998 Dec 11		NSTAR on, burn few hr
1998 Dec 14		NSTAR on
1998 Dec 18	s	NSTAR off
1999 Jan 5		NSTAR off
1999 Jan 22		NSTAR 45min burn	459.5d 0.990 x 1.331 AU x 0.38
1999 Mar 15		NSTAR on	459.6d 0.991 x 1.331 AU x 0.38
1999 Apr 27		NSTAR off	470.4d 1.022 x 1.336 AU x 0.26
1999 Jun 10		RCS test burn 0.5m/s 2min
1999 Jun 14		AutoNav TCM part 1 NSTAR 4 hrs
1999 Jun 14		AutoNav TCM part 2 NSTAR 4 hrs
1999 Jun 18		AutoNav RCS burn 1m/s
1999 Jul 23		NSTAR TCM Autonav 1m/s, 6 hr
1999 Jul 28		Safemode	470.5d 1.022 x 1.336 AU x 0.26
1999 Jul 28	2245?	TCM 1m/s
1999 Jul 29	0446	Flyby (9969) 1992 KD Braille at 26 km from center at 15.5km/s
		Horizons orbit (2017 data)	103 x -105 x 92.5
		Hill sphere of 9969 is 217 km at this point
		In Hill sphere for about 30 sec
1999 Jul 30	1600	NSTAR on (for 3 months?)
1999 Sep 18		End of primary mission?
1999 Oct 20	1100	NSTAR off	490.8d 1.083 x 1.342 x 0.19
1999 Oct 27			492.56d 1.090 x 1.342 AU x 0.19
1999		Orbit 1.0 x 1.3 AU x 0.4
1999 Nov 11		Safemode, star tracker problem
2000 Jun 8		Upload new software
2000 Jun 21		MICAS attitude control enabled
2000 Jun 28		NSTAR on	492.8d 1.091 x 1.342 x 0.19
2000 Jul 5		NSTAR off; at 2.1AU from Earth OWLT=17
2000 Jul		NSTAR on
2000 Oct 18		NSTAR throttle for attitude control only
2001 Jan 2		NSTAR full thrust
2001		Orbit 1.12 x 1.42 AU x 0
2001 Jun 30			1.293 x 1.478 AU
2001 Sep 22	2230:37	Borrelly nucleus flyby 2171 km
2001 Dec 18	2000	end of ops
		1.225 x 1.462 x 0.1

Payload:

• Launch adapter propulsion module

• NSTAR Solar electric Ion drive Xe thruster

• Hydrazine thrusters

• SDST Small Deep Space Transponder, Miniaturized deep space antenna

• Ka-band solid state power amplifier

• Low power electronics

• Lithium ion batteries

• AutoNav Autonomous navigation system

• RA Remote Agent software test

• BMOE Beacon monitor Operations Experiment, JPL

• MICAS Miniature Integrated Camera/Imaging spectrometer, 12 kg UV, IR, visible channels.