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| A B C D E F G H I J K L M N O P Q R S T U V W X Y Z |
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Pioneer 10
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| Launch date | Mar. 2, 1972 |
| Jupiter flyby | Dec. 3, 1973 |
| Jupiter closest approach | 200,000 km |
| Launch vehicle | Atlas-Centaur SLV-3C |
| Launch site | Cape Canaveral |
| Mass | 258 kg |
| Nominal power output | 165 W |
Spacecraft details
Fifteen experiments were carried by Pioneer 10 to study the interplanetary and planetary magnetic fields; solar wind parameters; cosmic rays; transition region of the heliosphere; neutral hydrogen abundance; distribution, size, mass, flux, and velocity of dust particles; Jovian aurorae; Jovian radio waves; atmosphere of Jupiter and some of its satellites, particularly Io; and to photograph Jupiter and its satellites.
The instruments used to support these experiments were:
- magnetometer
- plasma analyzer
- charged particle detector
- ionizing detector
- non-imaging telescopes with overlapping fields of view to detect sunlight reflected from passing meteoroids
- sealed pressurized cells of argon and nitrogen gas for measuring the penetration of meteoroids
- UV photometer
- IR radiometer
- imaging photopolarimeter, which produced photographs and measured polarization
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The spacecraft body was mounted behind a 2.74-m-diameter parabolic dish antenna that was 46 cm deep. The spacecraft structure was a 36-cm-deep flat equipment compartment, the top and bottom being regular hexagons. Its sides were 71 cm long. One side joined a smaller compartment that carried the scientific experiments.
The high-gain antenna feed was situated on three struts, which projected forward about 1.2 m. This feed was topped with a medium-gain antenna. A low-gain omnidirectional antenna extended about 0.76 m behind the equipment compartment and was mounted below the high-gain antenna.
Power for the spacecraft was obtained by four SNAP-19 radioisotope thermonuclear generators (RTG), which were held about 3 m from the center of the spacecraft by two three-rod trusses 120° apart. A third boom extended 6.6 m from the experiment compartment to hold the magnetometer away from the spacecraft. The four RTG's generated about 155 W at launch and decayed to approximately 140 W by the time the spacecraft reached Jupiter, 21 months after launch.
There were three reference sensors: a star sensor for Canopus which failed shortly after Jupiter encounter and two sun sensors. Attitude position could be calculated from the reference directions to the earth and the sun, with the known direction to Canopus as a backup.
Three pairs of rocket thrusters provided spin-rate control and changed the velocity of the spacecraft, the spin period near the end of the mission being 14.1 seconds. These thrusters could be pulsed or fired steadily by command. The spacecraft was temperature-controlled between -23°C and +38°C.
A plaque was mounted on the spacecraft body with drawings depicting a man, a woman, and the location of the sun and the earth in our galaxy.
Communications were maintained via (1) the omnidirectional and medium-gain antennas which operated together while connected to one receiver and (2) the high-gain antenna which was connected to another receiver. These receivers could be interchanged by command to provide some redundancy. Two radio transmitters, coupled to two traveling-wave tube amplifiers, produced 8 W at 2292 MHz each. Uplink was accomplished at 2110 MHz, while data transmission downlink was at 2292 MHz. The data were received by NASA's Deep Space Network (DSN) at bit rates up to 2048 bps en route to Jupiter and at 16 bps near end of the mission.
Degradation
Space experiments mostly continued to operate for planetary or interplanetary measurements until failure or until insufficient spacecraft power from the RTG's was available for operation of all instruments, such that some were turned off permanently and others were cycled on and off in accordance with a power sharing plan implemented in September 1989. The Asteroid/Meteroid Detector failed in December 1973, followed by the Helium Vector Magnetometer (HVM) in November 1975 and the Infrared Radiometer in January 1974. The Meteroid Detector was turned off in October 1980 due to inactive sensors at low temperatures. The spacecraft sun sensors became inoperative in May 1986, and the Imaging Photopolarimeter (IPP) instrument was used to obtain roll phase and spin period information until being turned off in October 1993 to conserve power. The Trapped Radiation Detector (TRD) and Plasma Analyzer (PA) were respectively turned off in November 1993 and September 1995 for the same reason. As of January 1996 the final power cycling plan included part-time operations of the Charged Particle Instrument (CPI), the Cosmic Ray Telescope (CRT), the Geiger Tube Telescope (GTT), and the Ultraviolet Photometer (UV). By August 2000, only the GTT instrument was still returning data.
Various other spacecraft subsystems also either failed or were turned off for power or other reasons, and an account of these may be of interest for engineering design of long duration deep space missions. The primary antenna feed offset bellows failed sometime in 1976 but a redundant unit was available for use thereafter. The Program Storage and Execution (PSE) subsystem was turned off in September 1989 for power conservation, after which spacecraft maneuvers were performed by ground command sequences. A receiver problem in mid-1992 prevented uplink to the high gain antenna, after which uplink commands could only be sent with 70-meter DSN antennas which also supported the 16 bps downlink. The Backup Line Heater experienced a sticking thermostat operation in March 1993 for 30 days but the problem did not reoccur. Undervoltage Protection Logic was turned off in December 1993 to prevent loss of critical spacecraft systems in the event of a transient undervoltage condition. Duration and Steering Logic (DSL) was turned off in February 1995 to conserve power, after which it was turned on again only for spacecraft maneuvers. RTG power levels are low enough that the spacecraft occasionally relies in part on battery power (accumulated during inactive periods) to run experiments and other systems.
Interstellar trajectory
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The closest that it will come to another star system within the next 100,000 years is 3.27 light-years (1.00 parsec) from the red dwarf Ross 248 in about the year 32,608 AD. Even this distant passage will owe more to the relative motions of the stars themselves than the probe's own efforts. It so happens that Ross 248 is approaching the Sun at about 80 km/s (50 miles/sec.) so that by the year 34,923 AD the gap between the Sun and the red dwarf will have narrowed from its present value of 10.3 light-years (3.2 parsecs) to just 2.9 light-years (0.9 parsec). Uncertainties in the movements of stars over long periods are one of the main reasons that mission specialists cannot be absolutely sure when and at what range future stellar flybys of escaping probes will take place.1
On Oct. 8, 2005, Pioneer 10 was 89.081 astronomical units (13.26 billion km, 8.24 billion miles) from the Sun, equivalent to a round-trip light travel time of 24 hr 34 min, or just over one light-day. It was superseded as the most distant human-made object by Voyager 1 in mid-1998.
The power source on Pioneer 10 finally degraded to the point where the signal to Earth dropped below the threshold for detection in its latest contact attempt on Feb. 7, 2003. No more attempts at contact are planned at this time. The previous three contacts had very faint signals with no telemetry received. Pioneer's last, very weak signal was received on Jan. 23, 2003. The last time a Pioneer 10 contact returned telemetry data was on Apr. 27, 2002.
The Pioneer anomaly
Unexplained deviations in the trajectories of Pioneer 10 and 11 have lead to a number of theories to explain the so-called Pioneer anomaly. One of these theories involves a reevaluation of the nature of dark matter and is described by Robert Soberman and Maurice Dubin in their book Dark Matter Illuminated.
Science fiction references
Pioneer 10 was used for target practice and destroyed by a Klingon Bird of Prey in the film Star Trek V: The Final Frontier.
Reference
- Cesarone, R. J., Sergeyevsky, A. B., and Kerridge, S. "Prospects for the Voyager Interstellar Mission," AAS/AIAA Astrodynamics Specialist Conference Paper 83-308, Lake Placid, N.Y., Aug. 22-25, 1983.
Related category
• SATELLITES AND SPACE PROBES
Archived news
Lost asteroid clue to Pioneer puzzle (May 10, 2005)
Pioneer 10 still alive (Apr 30, 2001)
Star-bound Pioneer 10 still in touch – just (Jul 12, 2000)
External site
Pioneer 10/11 homepage (Ames)
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