|Operator||ARC / NASA|
|Launch date||1972-03-03 01:49:00 UTC
(41 years, 2 months, and 18 days ago)
|Launch site||Space Launch Complex 36A
Cape Canaveral Air Force Station
|Mission duration||March 2, 1972 – January 23, 2003
(30 years, 10 months, 22 days)
|Mission highlight||Jupiter flyby
|Homepage||Pioneer Project website(archived)
NASA Archive page
|Mass||258 kg (570 lb)|
|Power||155.0 W (4 SNAP-19 RTGs)|
Pioneer 10 (originally designated Pioneer F) is a 258-kilogram American robotic space probe that completed the first mission to the planet Jupiter and became the first spacecraft to achieve escape velocity from the Solar System. The project was managed by the NASA Ames Research Center and the spacecraft was constructed by TRW Inc. Pioneer 10 was assembled around a hexagonal bus with a 2.74 m parabolic dish high-gain antenna oriented along the spin axis. Power was supplied by four radioisotope thermoelectric generators that provided a combined 155 W at the start of the mission.
Pioneer 10 was launched on March 2, 1972 by an Atlas-Centaur expendable vehicle from Cape Canaveral, Florida. Between July 15, 1972, and February 15, 1973, it became the first spacecraft to traverse the asteroid belt. Imaging of Jupiter began November 6, 1973, at a range of 25 million km, and a total of more than 500 images were transmitted. The closest approach to the planet was on December 4, 1973, at a range of 132,252 km. During the mission, the on-board instruments were used to study the asteroid belt, the environment around Jupiter, solar wind, cosmic rays, and eventually the far reaches of the solar system and heliosphere. Communication was lost on January 23, 2003, due to power constraints, with the probe at a distance of 12 billion kilometers (80 AU) from Earth.
Mission background 
In the 1960s, American aerospace engineer Gary Flandro of the NASA Jet Propulsion Laboratory conceived of a mission, known as the Planetary Grand Tour, that would exploit a rare alignment of the outer planets of the Solar System. This mission would ultimately be accomplished in the late 1970s by the two Voyager probes, but in order to prepare for it, NASA decided in 1964 to experiment with launching a pair of probes to the outer Solar System. An advocacy group named the Outer Space Panel and chaired by American space scientist James A. Van Allen, worked out the scientific rationale for exploring the outer planets. Goddard put together a proposal for a pair of "Galactic Jupiter Probes" that would pass through the asteroid belt and visit Jupiter. These were to be launched in 1972 and 1973 during favorable windows that occurred only a few weeks every 13 months. Launch during other time intervals would have been more costly in terms of propellant requirements.
Approved by NASA in February 1969, the twin spacecraft were designated Pioneer F and Pioneer G before launch; later they were named Pioneer 10 and Pioneer 11. They formed part of the Pioneer program, a series of United States unmanned space missions launched between 1958 and 1978. This model was the first in the series to be designed for exploring the outer solar system. Based on multiple proposals issued throughout the 1960s, the early mission objectives were to explore the interplanetary medium past the orbit of Mars, study the asteroid belt and assess the possible hazard to spacecraft traveling through the belt, and explore Jupiter and its environment. Later development-stage objectives included the probe closely approaching Jupiter to provide data on the effect the environmental radiation surrounding Jupiter would have on the spacecraft instruments.
More than 150 scientific experiments were proposed for the missions. The experiments to be carried on the spacecraft were selected in a series of planning sessions during the 1960s, then were finalized by early 1970. These would be to perform imaging and polarimetry of Jupiter and several of its satellites, make infrared and ultraviolet observations of Jupiter, detect asteroids and meteoroids, determine the composition of charged particles, and to measure magnetic fields, plasma, cosmic rays and the Zodiacal Light. Observation of the spacecraft communications as it passed behind Jupiter would allow measurements of the planetary atmosphere, while tracking data would improve estimates of the mass of Jupiter and its moons.
NASA Ames Research Center, rather than Goddard, was selected to manage the project as part of the Pioneer program. Ames, under the management of Charles F. Hall, was chosen because of their previous experience with spin-stabilized spacecraft. The requirements called for a small, lightweight spacecraft that was magnetically clean and could perform an interplanetary mission. It was to use spacecraft modules that had already been proven in the Pioneer 6 through 9 missions.
In February 1970, Ames awarded a combined $380 million contract to TRW for building both the Pioneer 10 and Pioneer 11 vehicles, bypassing the bidding process to save time. B. J. O'Brien and Herb Lassen led the TRW team that assembled the spacecraft. Design and construction of the spacecraft required an estimated 25 million person-hours.
To meet the schedule, the first launch would need to take place between February 29 and March 17 so that it could arrive at Jupiter in November 1974. This was later revised to an arrival date of December 1973 in order to avoid conflicts with other missions over the use of the Deep Space Network for communications, and to miss the period when Earth and Jupiter would be at opposite sides of the Sun. The encounter trajectory for Pioneer 10 was selected to maximize the information returned about the radiation environment around Jupiter, even if this caused damage to some systems. It would come within about three times the radius of the planet, which was thought to be the closest it could approach and still survive the radiation. The trajectory chosen would give the spacecraft a good view of the sunlit side.
Spacecraft design 
The Pioneer 10 bus measures 36 centimetres (14 in) deep and with six 76-centimetre (30 in) long panels forming the hexagonal structure. The bus houses propellant to control the orientation of the probe and eight of the eleven scientific instruments. The equipment compartment lies within an aluminum honeycomb structure to provide protection from meteoroids. A layer of insulation, consisting of aluminized mylar and kapton blankets, provides passive thermal control. Heat is generated by the dissipation of 70 to 120 watts (W) from the electrical components inside the compartment. The heat range is maintained within the operating limits of the equipment by means of louvers located below the mounting platform. The spacecraft had a launch mass of 260 kilograms (570 lb).:42
At launch, the spacecraft carried 36 kilograms (79 lb) of liquid hydrazine monopropellant in a 42-centimetre (17 in) diameter spherical tank. Orientation of the spacecraft was maintained with six 4.5 N, hydrazine thrusters mounted in three pairs. Pair one maintained a constant spin-rate of 4.8-rpm, pair two controlled the forward thrust, and pair three controlled the attitude. The attitude pair were used in conical scanning maneuvers to track Earth in its orbit. Orientation information was also provided by a star sensor able to reference Canopus, and two sun sensors.
Power and communications 
Pioneer 10 used four SNAP-19 radioisotope thermoelectric generators (RTG). They were positioned on 2 three-rod trusses, each 3 metres (9.8 ft) in length and 120 degrees apart. This was expected to be a safe distance from the sensitive scientific experiments carried on board. Combined, the RTGs provided 155 W at launch, and decayed to 140 W in transit to Jupiter. The spacecraft required 100 W to power all systems.:44-45 The generators were powered by the radioisotope fuel plutonium-238, which was housed in a multi-layer capsule protected by a graphite heat shield.
The pre-launch requirement for the SNAP-19 was to provide power for two years in space; this was greatly exceeded during the mission. The plutonium-238 has a half-life of 87.74 years, so that after 29 years the radiation being generated by the RTGs was at 80% of its intensity at launch. However, steady deterioration of the thermocouple junctions led to a more rapid decay in electrical power generation, and by 2005 the total power output was 65 W. As a result, later in the mission only selected instruments could be operated at any one time.
The space probe includes a redundant system of transceivers, one attached to the narrow-beam, high-gain antenna, the other to an omni-antenna and medium-gain antenna. The parabolic dish for the high-gain antenna is 2.74 metres (9.0 ft) in diameter and made from an aluminum honeycomb sandwich material. The spacecraft is spun about an axis that is parallel to the axis of this antenna so that it can remain oriented toward the Earth. Each transceiver is 8 W and transmits data across the S-band using 2110 MHz for the uplink from Earth and 2292 MHz for the downlink to Earth with the Deep Space Network tracking the signal. Data to be transmitted was passed through a convolutional encoder so that most communication errors could be corrected by the receiving equipment on Earth.:43 The data transmission rate at launch was 256 bit/s, with the rate degrading by about −1.27 millibit/s for each day during the mission.
Much of the computation for the mission was performed on Earth and transmitted to the probe, where it was able to retain in memory, up to five commands of the 222 possible entries by ground controllers. The spacecraft included two command decoders and a command distribution unit, a very limited form of processor, to direct operations on the spacecraft. This system required that mission operators prepare commands long in advance of transmitting them to the probe. A data storage unit was included to record up to 6,144 bytes of information gathered by the instruments. The digital telemetry unit was used to prepare the collected data in one of the thirteen possible formats before transmitting it back to Earth.:38
Scientific instruments 
|Helium Vector Magnetometer (HVM)|
This instrument measures the fine structure of the interplanetary magnetic field, maps the Jovian magnetic field, and provides magnetic field measurements to evaluate solar wind interaction with Jupiter. The magnetometer consists of a helium-filled cell mounted on a 6.6–m boom to partly isolate the instrument from the spacecraft's magnetic field.
|Quadrispherical Plasma Analyzer|
Peers through a hole in the large dish-shaped antenna to detect particles of the solar wind originating from the Sun.
|Charged Particle Instrument (CPI)|
Detects cosmic rays in the Solar System.
|Cosmic Ray Telescope (CRT)|
Collects data on the composition of the cosmic ray particles and their energy ranges.
|Geiger Tube Telescope (GTT)|
Surveys the intensities, energy spectra, and angular distributions of electrons and protons along the spacecraft's path through the radiation belts of Jupiter.
|Trapped Radiation Detector (TRD)|
Includes an unfocused Cerenkov counter that detects the light emitted in a particular direction as particles pass through it recording electrons of energy, 0.5 to 12 MeV, an electron scatter detector for electrons of energy, 100 to 400 keV, and a minimum ionizing detector consisting of a solid-state diode that measures minimum ionizing particles (<3 MeV) and protons in the range of 50 to 350 MeV.
Twelve panels of pressurized cell detectors mounted on the back of the main dish antenna record penetrating impacts of small meteoroids.
|Asteroid/Meteoroid Detector (AMD)|
Meteoroid-asteroid detector looks into space with four non-imaging telescopes to track particles ranging from close-by bits of dust to distant large asteroids.
Ultraviolet light is sensed to determine the quantities of hydrogen and helium in space and on Jupiter.
|Imaging Photopolarimeter (IPP)|
The imaging experiment relies upon the spin of the spacecraft to sweep a small telescope across the planet in narrow strips only 0.03 degrees wide, looking at the planet in red and blue light. These strips were then processed to build up a visual image of the planet.
Provides information on cloud temperature and the output of heat from Jupiter.
Pioneer plaque 
At the behest of Carl Sagan, Pioneer 10 and Pioneer 11 carry a 152 by 229 mm (6.0 by 9.0 in) gold-anodized aluminum plaque in case either spacecraft is ever found by intelligent life-forms from another planetary system. The plaques feature the nude figures of a human male and female along with several symbols that are designed to provide information about the origin of the spacecraft. The plaque is attached to the antenna support struts to provide some shielding from interstellar dust.
Mission profile 
Launch and trajectory 
The Pioneer 10 probe was launched on March 3, 1972 at 01:49:00 UTC (March 2 local time) by the National Aeronautics and Space Administration from Space Launch Complex 36A at Cape Canaveral, Florida aboard an Atlas/Centaur launch vehicle. The third stage consisted of a solid fuel TE364-4 developed specifically for the Pioneer missions. This stage provided about 15,000 pounds of thrust and spun up the spacecraft. The spacecraft had an initial spin rate of 30 revolutions per minute. Twenty minutes following the launch, the vehicle's three booms were extended, which slowed the rotation rate to 4.8 per minute. This rate was maintained throughout the voyage. The launch vehicle accelerated the probe for net interval of 17 minutes, reaching a velocity of 51,682 kilometers/hour (32,114 miles/hour).
After the high-gain antenna was contacted, several of the instruments were activated for testing while Pioneer 10 was moving through the Earth's radiation belts. Ninety minutes after launch, the spacecraft reached interplanetary space. Pioneer 10 passed by the Moon in 11 hours and become the fastest man-made object at that time. Two days after launch, the scientific instruments were turned on, beginning with the cosmic ray telescope. After ten days, all of the instruments were active.
During the first seven months of the journey, the spacecraft made three course corrections. The on-board instruments underwent checkouts, with the photometers examining Jupiter and the Zodiacal light, and experiment packages being used to measure cosmic rays, magnetic fields and the solar wind. The only anomaly during this interval was the failure of the star sensor, which instead required the spacecraft to maintain its orientation using the two sun sensors.
While passing through interplanetary medium, Pioneer 10 became the first mission to detect interplanetary atoms of helium. It also observed high-energy ions of aluminum and sodium in the solar wind. On July 15, 1972, Pioneer 10 was the first spacecraft to enter the asteroid belt, located between the orbits of Mars and Jupiter. The project planners expected a safe passage through the belt, and the closest the trajectory would take Pioneer 10 to any of the known asteroids was 8.8 × 106 km (5.5 × 106 mi). One of the nearest approaches was to the asteroid 307 Nike on December 2, 1972.
The on-board experiments demonstrated a deficiency of particles below a micrometer (μm) in the belt, as compared to the vicinity of the Earth. The density of dust particles between 10–100 μm did not vary significantly during the trip from the Earth to the outer edge of the belt. Only for particles with a diameter of 100 μm to 1.0 mm did the density show an increase, by a factor of three in the region of the belt. No fragments larger than a millimeter were observed in the belt, indicating these are likely rare; certainly much less common than anticipated. As the spacecraft did not collide with any particles of substantial size, it passed safely through the belt, emerging on the other side about February 15, 1973.
Encounter with Jupiter 
On November 6, 1973, the Pioneer 10 spacecraft was at a distance of 25 million km from Jupiter. Testing of the imaging system began, and the data was successfully received back at the Deep Space Network. A series of 16,000 commands were then uploaded to the spacecraft to control the fly-by operations during next 60 days. The orbit of the outer moon Sinope was crossed on November 8. The bow shock of Jupiter's magnetosphere was reached on November 16, as indicated by a drop in the velocity of the solar wind from 451 km/s to 225 km/s. The magnetopause was passed through a day later. The spacecraft instruments confirmed that the magnetic field of Jupiter was inverted compared to that of Earth. By the 29th, the orbits of all of the outermost moons had been passed and the spacecraft was operating flawlessly.
Red and blue pictures of Jupiter were being generated by the imaging photopolarimeter as the rotation of the spacecraft carried the instrument's field of view past the planet. These red and blue colors were combined to produce a synthetic green image, allowing a three-color combination to produce the rendered image. On November 26, a total of twelve such images were received back on Earth. By December 2, the image quality exceeded the best images made from Earth. These were being displayed in real-time back on Earth, and the Pioneer Program would later receive an Emmy award for this presentation to the media. The motion of the spacecraft produced geometric distortions that later had to be corrected by computer processing. During the encounter, a total of more than 500 images were transmitted.
The trajectory of the spacecraft took it along the magnetic equator of Jupiter, where the ion radiation was concentrated. Peak flux for this electron radiation is 10,000 times stronger than the maximum radiation around the Earth. Starting on December 3, the radiation around Jupiter caused false commands to be generated. Most of these were corrected by contingency commands, but the Io image and a few close ups of Jupiter were lost. Similar false commands would be generated on the way out from the planet.  Nonetheless, Pioneer 10 did succeed in obtaining images of the moons Ganymede and Europa. The image of Ganymede showed low albedo features in the center and near the south pole, while the north pole appeared brighter. Europa was too far away to obtain a detailed image, although some albedo features were apparent.
The trajectory of Pioneer 10 was chosen to take it behind Io, allowing the refractive effect of the moon's atmosphere on the radio transmissions to be measured. This demonstrated that the ionosphere of the moon was about 700 km above the surface on the day side, and the density ranged from 60,000 electrons per cubic centimeter on the day side, down to 9,000 on the night face. An unexpected discovery was that Io was orbiting within a cloud of hydrogen that extended for about 805,000 km, with a width and height of 402,000 km. A smaller, 110,000 km cloud was believed to have been detected about Europa.
At the closest approach, the velocity of the spacecraft reached 132,000 km/h. The spacecraft came within 132,252 km of the outer atmosphere of Jupiter. Close-in images of the Great Red Spot and the terminator were obtained. Communication with the spacecraft then ceased as it passed behind the planet. The occultation data allowed the temperature structure of the outer atmosphere to be measured, showing a temperature inversion between the altitudes with 10 and 100 mbar pressures. Temperatures at the 10 mbar level ranged from -133° to -113°C, while temperatures at the 100 mbar level were -183° to -163°C. The spacecraft generated an infrared map of the planet, which confirmed the idea that the planet radiated more heat than it received from the Sun.
Crescent images of the planet were then returned as Pioneer 10 moved away from the planet. As the spacecraft headed outward, it again passed the bow shock of Jupiter's magnetosphere. As this front is constantly shifting in space because of dynamic interaction with the solar wind, the vehicle crossed the bow shock a total of 17 times before it escaped completely.
Deep space 
Pioneer 10 crossed the orbit of Saturn in 1976 and the orbit of Uranus in 1979. On June 13, 1983, Pioneer 10 crossed the orbit of Neptune, becoming the first man-made object to leave the proximity of the major planets of our solar system. The mission came to an official end on March 31, 1997, when it had reached a distance of 67 AU from the Sun, though the spacecraft was still able to transmit coherent data after this date.
Analysis of the radio tracking data from the Pioneer 10 and 11 spacecraft at distances between 20–70 AU from the Sun has consistently indicated the presence of a small but anomalous Doppler frequency drift. The drift can be interpreted as due to a constant acceleration of (8.74 ± 1.33) × 10−10 m/s2 directed towards the Sun. Although it is suspected that there is a systematic origin to the effect, none was found. As a result, there is sustained interest in the nature of this so-called "Pioneer anomaly". Extended analysis of mission data by Slava Turyshev and colleagues has determined the source of the anomaly to be asymmetric thermal radiation. In July 2012, the Pioneer anomaly was explained as a thermal recoil force (heat escaping) acting on the face of the Pioneers away from the Sun.
After March 31, 1997, Pioneer 10's weak signal continued to be tracked by the Deep Space Network to aid the training of flight controllers in the process of acquiring deep space radio signals. There was an Advanced Concepts study applying chaos theory to extract coherent data from the fading signal.
The last successful reception of telemetry was received from Pioneer 10 on April 27, 2002; subsequent signals were barely strong enough to detect, and provided no usable data. The final, very weak signal from Pioneer 10 was received on January 23, 2003 when it was 12 billion kilometers (80 AU) from Earth. Further attempts to contact the spacecraft were unsuccessful. The final attempt was made on the evening of March 4, 2006, the last time the antenna would be correctly aligned with Earth. No response was received from Pioneer 10. NASA decided that the RTG units had probably fallen below the power threshold needed to operate the transmitter. Hence, no further attempts at contact were made.
|Timeline of travel|
Current status 
On September 9, 2012, Pioneer 10 was 106.696 AU (1.59615×1010 km; 9.9180×109 mi) from the Earth and 106.676 AU (1.59585×1010 km; 9.9162×109 mi) from the Sun (about 10 billion miles); and traveling at 12.037 km/s (26,930 mph) (relative to the Sun) and traveling outward at about 2.539 AU per year. Sunlight takes 14.79 hours to get to Pioneer 10. The brightness of the Sun from the spacecraft is magnitude -16.6. Pioneer 10 is heading in the direction of the constellation Taurus.
If left undisturbed, Pioneer 10 and its sister craft Pioneer 11 will join two Voyager spacecraft in leaving the solar system to wander the interstellar medium. The trajectory is expected to take it in the general direction of the star Aldebaran, currently located at a distance of about 68 light years. If Aldebaran had zero relative velocity, it would require more than two million years for the spacecraft to reach the star.
A backup unit, Pioneer H, is currently on display in the "Milestones of Flight" gallery at the National Air and Space Museum in Washington, D.C. Many elements of the mission proved to be critical in the planning of the Voyager program.
See also 
|Wikimedia Commons has media related to: Pioneer program|
- Cassini probe
- Exploration of Jupiter
- Galileo, Jupiter orbiter
- Juno, en route Jupiter orbiter
- New Horizons, Pluto flyby
- Pioneer 11
- S band
- Unmanned space missions
- Voyager 1 & Voyager 2, Jupiter flybys
- List of artificial objects escaping from the Solar System
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- Pioneer Project Archive Page
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- NSSDC Pioneer 10 page
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