Editing Deep Space 1 (section)

==Technologies==
The purpose of ''Deep Space 1'' was technology development and validation for future missions; 12 technologies were tested:<ref>{{cite web |url=http://www.jpl.nasa.gov/nmp/ds1/tech/index.php |title=Advanced Technologies |publisher=NASA/Jet Propulsion Laboratory |access-date=20 November 2016}}</ref>
#Solar Electric Propulsion
#Solar Concentrator Arrays
#Multi-functional Structure
#Miniature Integrated Camera and Imaging Spectrometer
#Ion and Electron Spectrometer
#Small Deep Space Transponder
#Ka-Band Solid State Power Amplifier
#Beacon Monitor Operations
#Autonomous Remote Agent
#Low Power Electronics
#Power Actuation and Switching Module
#Autonomous Navigation

===Autonav===
The Autonav system, developed by NASA's [[Jet Propulsion Laboratory]], takes images of known bright [[asteroid]]s. The asteroids in the inner Solar System move in relation to other bodies at a noticeable, predictable speed. Thus a spacecraft can determine its relative position by tracking such asteroids across the star background, which appears fixed over such timescales. Two or more asteroids let the spacecraft triangulate its position; two or more positions in time let the spacecraft determine its trajectory. Existing spacecraft are tracked by their interactions with the transmitters of the [[NASA Deep Space Network]] (DSN), in effect an inverse [[Global Positioning System|GPS]]. However, DSN tracking requires many skilled operators, and the DSN is overburdened by its use as a communications network. The use of Autonav reduces mission cost and DSN demands.

The Autonav system can also be used in reverse, tracking the position of bodies relative to the spacecraft. This is used to acquire targets for the scientific instruments. The spacecraft is programmed with the target's coarse location. After initial acquisition, Autonav keeps the subject in frame, even commandeering the spacecraft's attitude control.<ref name=ANS-PFR>{{cite conference |title=The Deep Space 1 Autonomous Navigation System: A Post-Flight Analysis |conference=AIAA/AAS Astrodynamics Specialist Conference. 14–17 August 2000. Denver, Colorado. |first1=S. |last1=Bhaskaran |first2=J. E. |last2=Riedel |first3=S. P. |last3=Synnott |first4=T. C. |last4=Wang |display-authors=1 |date=2000 |id=AIAA-2000-3935 |doi=10.2514/6.2000-3935 |citeseerx=10.1.1.457.7850}}</ref> The next spacecraft to use Autonav was ''[[Deep Impact (spacecraft)|Deep Impact]]''.

===SCARLET concentrating solar array===
Primary power for the mission was produced by a new solar array technology, the Solar Concentrator Array with Refractive Linear Element Technology (SCARLET), which uses linear [[Fresnel lens]]es made of [[silicone]] to concentrate sunlight onto solar cells.<ref>{{cite conference |url=http://nmp-techval-reports.jpl.nasa.gov/DS1/Scarlet_Integrated_Report.pdf |title=The Scarlet Solar Array: Technology Validation and Flight Results |conference=Deep Space 1 Technology Validation Symposium. 8–9 February 2000. Pasadena, California |first=David M. |last=Murphy |date=2000 |url-status=dead |archive-url=https://web.archive.org/web/20111015071801/http://nmp-techval-reports.jpl.nasa.gov/DS1/Scarlet_Integrated_Report.pdf |archive-date=15 October 2011}}</ref> ABLE Engineering developed the concentrator technology and built the solar array for DS1, with Entech Inc, who supplied the Fresnel optics, and the NASA [[Glenn Research Center]]. The activity was sponsored by the Ballistic Missile Defense Organization, developed originally for the SSI - Conestoga 1620 payload, METEOR. The concentrating lens technology was combined with dual-junction solar cells, which had considerably better performance than the [[GaAs]] solar cells that were the state of the art at the time of the mission launch.

The SCARLET arrays generated 2.5 kilowatts at 1 AU, with less size and weight than conventional arrays.

===NSTAR ion engine===
{{main article|NASA Solar Technology Application Readiness}}

Although [[ion engine]]s had been developed at NASA since the late 1950s, with the exception of the [[SERT-1|SERT]] missions in the 1960s, the technology had not been demonstrated in flight on United States spacecraft, though hundreds of [[Hall-effect thruster|Hall-effect engines]] had been used on Soviet and Russian spacecraft.  This lack of a performance history in space meant that despite the potential savings in propellant mass, the technology was considered too experimental to be used for high-cost missions. Furthermore, unforeseen side effects of ion propulsion might in some way interfere with typical scientific experiments, such as fields and particle measurements.  Therefore, it was a primary mission of the ''Deep Space 1'' demonstration to show long-duration use of an ion thruster on a scientific mission.<ref name="MD">{{cite journal |url=http://trs-new.jpl.nasa.gov/dspace/bitstream/2014/19098/1/98-0310.pdf |title=Mision Design for Deep Space 1: A Low-thrust Technology Validation Mission |journal=Acta Astronautica |first1=Marc D. |last1=Rayman |first2=Pamela A. |last2=Chadbourne |first3=Jeffery S. |last3=Culwell |first4=Steven N. |last4=Williams |volume=45 |issue=4–9 |pages=381–388 |date=August–November 1999 |doi=10.1016/S0094-5765(99)00157-5 |bibcode=1999AcAau..45..381R |url-status=dead |archive-url=https://web.archive.org/web/20150509172350/http://trs-new.jpl.nasa.gov/dspace/bitstream/2014/19098/1/98-0310.pdf |archive-date=9 May 2015}}</ref>

The [[NASA Solar Technology Application Readiness]] (NSTAR) [[electrostatic ion thruster]], developed at NASA Glenn, achieves a [[specific impulse]] of 1000–3000 seconds. This is an order of magnitude higher than traditional space propulsion methods, resulting in a mass savings of approximately half. This leads to much cheaper launch vehicles. Although the engine produces just {{convert|92|mN|lk=on}} thrust at maximal power (2,100 W on DS1), the craft achieved high speeds because ion engines thrust continuously for long periods.<ref name="MD"/>

The next spacecraft to use NSTAR engines was ''[[Dawn (spacecraft)|Dawn]]'', with three redundant units.<ref>{{cite web |url=http://dawn.jpl.nasa.gov/mission/spacecraft.asp |title=Dawn: Spacecraft |publisher=NASA/Jet Propulsion Laboratory |access-date=20 November 2016}}</ref>

{{Multiple image |align=center |direction=horizontal |total_width=600
 |image1=Ion Engine Being Installed in High Vacuum Tank - GPN-2000-000597.jpg |caption1=Technicians installing ion engine #1 in the High Vacuum Tank in the Electric Propulsion Research Building, 1959
 |image2=Deep Space 1 spacecraft.jpg |caption2=The fully assembled {{nowrap|''Deep Space 1''}}
 |image3=Deep Space 1 lifted.jpg |caption3=''Deep Space 1'' experimental solar-powered [[Ion thruster|ion propulsion engine]]
}}

===Remote Agent===
Remote Agent (RAX), remote intelligent self-repair software developed at NASA's [[Ames Research Center]] and the Jet Propulsion Laboratory, was the first artificial-intelligence control system to control a spacecraft without human supervision.<ref>{{cite web |url=https://ti.arc.nasa.gov/tech/asr/planning-and-scheduling/remote-agent/ |title=Remote Agent |publisher=NASA |access-date=22 April 2009 |archive-url=https://web.archive.org/web/20100413232345/http://ti.arc.nasa.gov/tech/asr/planning-and-scheduling/remote-agent/ |archive-date=13 April 2010 |url-status=dead }}</ref> Remote Agent successfully demonstrated the ability to plan onboard activities and correctly diagnose and respond to simulated faults in spacecraft components through its built-in REPL environment.<ref name="RAX.debug">{{cite AV media |url=https://www.youtube.com/watch?v=_gZK0tW8EhQ#t=2371s | archive-url=https://ghostarchive.org/varchive/youtube/20211211/_gZK0tW8EhQ| archive-date=2021-12-11 | url-status=live|title=The Remote Agent Experiment: Debugging Code from 60 Million Miles Away |work=YouTube.com |publisher=Google Tech Talks |first=Ron |last=Garret |date=14 February 2012}}{{cbignore}} [http://www.flownet.com/ron/RAX2.pdf Slides].</ref> Autonomous control will enable future spacecraft to operate at greater distances from Earth and to carry out more sophisticated science-gathering activities in deep space. Components of the Remote Agent software have been used to support other NASA missions. Major components of Remote Agent were a robust planner (EUROPA), a plan-execution system (EXEC) and a model-based diagnostic system (Livingstone).<ref name="RAX.debug" /> EUROPA was used as a ground-based planner for the [[Mars Exploration Rover]]s. EUROPA II was used to support the [[Phoenix (spacecraft)|''Phoenix'' Mars lander]] and the [[Mars Science Laboratory]]. Livingstone2 was flown as an experiment aboard [[Earth Observing-1]] and on an [[McDonnell Douglas F/A-18 Hornet|F/A-18 Hornet]] at NASA's [[Dryden Flight Research Center]].

===Beacon Monitor===
Another method for reducing DSN burdens is the [[Beacon mode service|Beacon Monitor]] experiment. During the long cruise periods of the mission, spacecraft operations are essentially suspended. Instead of data, Deep Space 1 transmitted a [[carrier signal]] on a predetermined frequency. Without data decoding, the carrier could be detected by much simpler ground antennas and receivers. If DS1 detected an anomaly, it changed the carrier between four tones, based on urgency. Ground receivers then signal operators to divert DSN resources. This prevented skilled operators and expensive hardware from babysitting an unburdened mission operating nominally. A similar system was used on the ''[[New Horizons]]'' Pluto probe to keep costs down during its ten-year cruise from Jupiter to Pluto.

===SDST===
[[File:MSL-SDST.jpg|thumb|A Small Deep Space Transponder]]
The [[Small Deep Space Transponder]] (SDST) is a compact and lightweight radio-communications system. Aside from using miniaturized components, the SDST is capable of communicating over the [[Ka band|K<sub>a</sub> band]]. Because this band is higher in frequency than bands currently in use by deep-space missions, the same amount of data can be sent by smaller equipment in space and on the ground. Conversely, existing DSN antennas can split time among more missions. At the time of launch, the DSN had a small number of K<sub>a</sub> receivers installed on an experimental basis; K<sub>a</sub> operations and missions are increasing.

The SDST has since been used on [[Small Deep Space Transponder#Missions|many other space missions]] such as the [[Mars Science Laboratory]] (the Mars rover ''[[Curiosity (rover)|Curiosity]]'').<ref>{{cite web |url=http://descanso.jpl.nasa.gov/DPSummary/Descanso14_MSL_Telecom.pdf |archive-url=https://web.archive.org/web/20100527101216/http://descanso.jpl.nasa.gov/DPSummary/Descanso14_MSL_Telecom.pdf |archive-date=2010-05-27 |url-status=live |title=Mars Science Laboratory Telecommunications System Design |series=Design and Performance Summary Series |publisher=NASA/Jet Propulsion Laboratory |first1=Andre |last1=Makovsky |first2=Peter |last2=Ilott |first3=Jim |last3=Taylor |date=November 2009}}</ref>

===PEPE===
Once at a target, DS1 senses the particle environment with the PEPE (Plasma Experiment for Planetary Exploration) instrument. This instrument measured the flux of ions and electrons as a function of their energy and direction. The composition of the ions was determined by using a [[time-of-flight mass spectrometer]].

===MICAS===
The MICAS (Miniature Integrated Camera And [[Spectrometer]]) instrument combined visible light imaging with infrared and ultraviolet spectroscopy to determine chemical composition. All channels share a {{convert|10|cm|in|abbr=on}} telescope, which uses a [[silicon carbide]] mirror.

Both PEPE and MICAS were similar in capabilities to larger instruments or suites of instruments on other spacecraft. They were designed to be smaller and require lower power than those used on previous missions.