1998-061A
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.
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| DS 1 |
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| Date | Time | Event | Orbit |
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| 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.
