| Sojourner | |||||||
| Insignia: | Mars Pathfinder Insignia.png | ||||||
| Insignia Caption: | Mars Pathfinder mission patch | ||||||
| Mission Type: | Mars rover | ||||||
| Operator: | NASA | ||||||
| Dry Mass: | 11.5kg (25.4lb) | ||||||
| Power: | Solar panel 13 W | ||||||
| Launch Date: | December 4, 1996, 06:58:07 UTC | ||||||
| Launch Rocket: | Delta II 7925 D240 | ||||||
| Launch Site: | Cape Canaveral LC-17B | ||||||
| Launch Contractor: | McDonnell Douglas | ||||||
| Deployment From: | Mars Pathfinder | ||||||
| Deployment Date: | July 5, 1997 | ||||||
| Last Contact: | September 27, 1997 | ||||||
| Declared: | March 10, 1998 | ||||||
| Interplanetary: |
| ||||||
| Programme: | NASA Mars rovers | ||||||
| Next Mission: | Spirit | ||||||
Sojourner is a robotic Mars rover that landed in the Ares Vallis channel in the Chryse Planitia region of the Oxia Palus quadrangle on July 4, 1997. Sojourner was operational on Mars for 92 sols (95 Earth days). It was the first wheeled vehicle to rove on a planet other than Earth and formed part of the Mars Pathfinder mission.[1]
The rover was equipped with front and rear cameras, and hardware that was used to conduct several scientific experiments. It was designed for a mission lasting 7 sols, with a possible extension to 30 sols, and was active for 83 sols (85 Earth days). The rover communicated with Earth through the Pathfinder base station, which had its last successful communication session with Earth at 3:23 a.m. PDT on September 27, 1997.[2] The last signal from the rover was received on the morning of October 7, 1997.[3]
Sojourner traveled just over 100m (300feet) by the time communication was lost.[4] Its final confirmed command was to remain stationary until October 5, 1997, (sol 91) and then drive around the lander;[5] there is no indication it was able to do so. The Sojourner mission formally ended on March 10, 1998, after all further options were exhausted.
See main article: Mars Pathfinder.
Sojourner was an experimental vehicle whose main mission was to test in the Martian environment technical solutions that were developed by engineers of the NASA research laboratories. It was necessary to verify whether the design strategy followed had resulted in the construction of a vehicle suitable for the environment it would encounter, despite the limited knowledge of it. Careful analysis of the operations on Mars would make it possible to develop solutions to critical problems identified and to introduce improvements for subsequent planetary exploration missions. One of the mission's main aims was to prove the development of "faster, better and cheaper" spacecraft was possible. Development took three years and cost under $150 million for the lander, and $25 million for the rover; development was faster and less costly than all previous missions.[6]
These objectives required careful selection of the landing site to balance the technical requests with the scientific ones.[7] A large plain was needed for the probe to land and rocky terrain to verify the rover's systems. The choice fell on Ares Vallis in Chryse Planitia, which is characterized by alluvial-looking rock formations. Scholars believed the analysis of the rocks, which lie in what appears to be the outlet of a huge drainage channel, could have confirmed the past presence of liquid water on the surface of Mars and provide details of the surrounding areas, from which the rocks were eroded.[8]
Sojourner was developed by NASA's Jet Propulsion Laboratory (JPL). It is a six-wheeled, 65abbr=inNaNabbr=in long, 48abbr=inNaNabbr=in wide and 30abbr=inNaNabbr=in high vehicle. In the mission's cruise phase, it occupied an 18abbr=inNaNabbr=in high space and has a mass of 11.5kg (25.4lb).[9] [10] It was supported by a lander, a tetrahedron-shaped structure with a mass of 250kg (550lb), and had a camera, scientific instrumentation, three petals of solar panels, a meteorology mast,[11] and 6kg (13lb) of equipment that was required to maintain communications between the rover and the lander. Hardware included a steerable, high-gain X-band antenna that could send approximately 5.5 kilobits per second into a 70meter Deep Space Network antenna, 3.3sqm gallium-arsenide solar arrays that generated 1.1 kW⋅h/day and were capable of providing enough power to transmit for 2–4 hours per sol and maintain 128 megabytes of dynamic memory through the night.
One of the lander's main tasks was to support the rover by imaging its operations and sending data from the rover to Earth. The lander had rechargeable batteries and over 2.5meters of solar cells on its petals. The lander contained a stereoscopic camera with spatial filters on an expandable pole called Imager for Mars Pathfinder (IMP),[12] [13] and the Atmospheric Structure Instrument/Meteorology Package (ASI/MET)[14] which acted as a Mars meteorological station, collecting data about pressure, temperature, and winds. The MET structure included three windsocks mounted at three heights on a pole, the topmost at about 1m (03feet) and generally registered winds from the west.[15] To provide continuous data, the IMP imaged the windsocks once every daylight hour. These measurements allowed the eolian processes at the landing site, including the particle threshold and the aerodynamic surface roughness, to be measured.
The square eyes of the IMP camera are separated by 15cm (06inches) to provide stereoscopic vision and ranging performance to support rover operations. The dual optical paths are folded by two sets of mirrors to bring the light to a single charge-coupled device (CCD). To minimize moving parts, the IMP is electronically shuttered; half of the CCD is masked and used as a readout zone for the electronic shutter. The optics had an effective pixel resolution of one milliradian per pixel which gives 1mm per pixel at a range of 1m (03feet). The camera cylinder is mounted on gimbals that provide rotation freedom of 360° in azimuth and −67° to +90° in elevation. This assembly is supported by an extendible mast that was designed and built by AEC Able Engineering. The mast holds the camera at approximately 1.5meter above the Martian surface and extends Pathfinders horizon to 3.4km (02.1miles) on a featureless plane.[16] [17]
Sojourner had solar panels and a non-rechargeable lithium-thionyl chloride (LiSOCl2) battery that could provide 150 watt-hours and allowed limited nocturnal operations. Once the batteries were depleted, the rover could only operate during the day.[18] The batteries also allowed the rover's health to be checked while enclosed in the cruise stage while en route to Mars.[19] The rover had 0.22m2 of solar cells, which could produce a maximum of about 15 watts on Mars, depending on conditions. The cells were GaAs/Ge (Gallium Arsenide/Germanium) with approximately 18 percent efficiency. They could survive temperatures down to about . After about its 40th sol on Mars, the lander's battery no longer held a charge so it was decided to shut off the rover before sunset and wake it up at sunrise.
The rover's wheels were made of aluminum and were 13cm (05inches) in diameter and 7.9cm (03.1inches) wide. They had serrated, stainless steel tracks that could generate a pressure of in optimal conditions on soft ground.[20] No such need arose during the operational phase. Each wheel was driven by its own independent motor.[21] The first and third wheels were used for steering. A six-wheel-steering configuration was considered, but this was too heavy. As the rover rotated on itself, it drew a 74abbr=onNaNabbr=on wide circle.
The wheels were connected to the frame through specially developed suspension to ensure all six were in contact with the ground, even on rough terrain.[22] JPL's Don Bickler developed the wheels, which were referred to as "Rocker-bogie", for the experimental "Rocky" vehicles, of which the Sojourner is the eighth version.[23] [24] [25] They consisted of two elements; "Bogie" connected the front wheel with the central one and "Rocker" connected the rear wheel with the other two. The system did not include springs or other elastic elements, which could have increased the pressure exerted by each wheel. This system allowed the overcoming of obstacles up to 8cm (03inches) high but theoretically would have allowed the rover to overcome obstacles of 20cm (10inches), or about 30% of the rover's length. The suspension system was also given the ability to collapse on itself so the rover would occupy 18cm (07inches) in the cruising configuration.[26]
The locomotion system was found to be suitable for the environment of Mars—being very stable, and allowing forward and backward movements with similar ease—and was adopted with appropriate precautions in the subsequent Spirit and Opportunity rover missions.
In the ten-year development phase that led to the realization of Sojourner, alternative solutions that could take advantage of the long experience gained at JPL in the development of vehicles for the Moon and Mars were examined. The use of four or more legs was excluded for three reasons: a low number of legs would limit the rover's movements and the freedom of action, and increasing the number would lead to a significant increase in complexity. Proceeding in this configuration would also require knowledge of the space in front—the ground corresponding to the next step—leading to further difficulties. The choice of a wheeled vehicle solved most of the stability problems, led to a reduction in weight, and improved efficiency and control compared to the previous solution. The simplest configuration was a four-wheel system that, however, encounters difficulties in overcoming obstacles. Better solutions were the use of six or eight wheels with the rear ones able to push, allowing the obstacle to be overcome. The lighter, simpler, six-wheeled option was preferred.
The rover could travel 500m (1,600feet) from the lander—the approximate limit of its communication range— and had a maximum speed of 1cm/s.
Sojourners central processing unit (CPU) was an Intel 80C85 with a 2 MHz clock, addressing 64 kilobytes (Kb) of memory, and running a cyclic executive.[27] It had four memory stores; 64 Kb of RAM made by IBM for the main processor, 16 Kb of radiation-hardened PROM made by Harris, 176 Kb of non-volatile storage made by Seeq Technology, and 512 Kb of temporary data storage made by Micron. The electronics were housed inside the rover's warm electronics box (WEB).[28] The WEB is a box-like structure formed from fiberglass facesheets bonded to aluminum spars. The gaps between facesheets were filled with blocks of aerogel that worked as thermal insulation.[29] The aerogel used on the Sojourner had a density of approximately 20 mg/cc.[30] This insulator was designed to trap heat generated by rover's electronics; this trapped heat soaked at night through the passive insulation maintaining the electronics in the WEB at between -40and, while externally the rover experienced a temperature range between 0and.
The Pathfinder lander's computer was a Radiation Hardened IBM Risc 6000 Single Chip with a Rad6000 SC CPU, 128 megabytes (Mb) of RAM and 6 Mb of EEPROM memory,[31] [32] and its operating system was VxWorks.[33]
The mission was jeopardised by a concurrent software bug in the lander[34] that had been found in preflight testing but was deemed a glitch and given a low priority because it only occurred in certain unanticipated heavy-load conditions, and the focus was on verifying the entry and landing code. The problem, which was reproduced and corrected from Earth using a laboratory duplicate, was due to computer resets caused by priority inversion. No scientific or engineering data was lost after a computer reset but all of the following operations were interrupted until the next day.[35] [36] Resets occurred on July 5, 10, 11 and 14 during the mission[37] before the software was patched on July 21 to enable priority inheritance.[38]
Sojourner communicated with its base station using a 9,600 baud radio modem, although error-checking protocols limited communications to a functional rate of 2,400 baud with a theoretical range of about NaNabbr=outNaNabbr=out. Under normal operation, it would periodically send a "heartbeat" message to the lander. If no response was given, the rover could autonomously return to the location at which the last heartbeat was received. If desired, the same strategy could be used to deliberately extend the rover's operational range beyond that of its radio transceiver, although the rover rarely traveled further than 10meter from Pathfinder during its mission. The Ultra high frequency (UHF) radio modems operated in half-duplex mode, meaning they could either send or receive data but not both at the same time. The data was communicated in bursts of 2 kB.[39]
The rover was imaged on Mars by the base station's IMP camera system, which also helped determine where the rover should go.The rover had two monochrome cameras in front and a color camera at the rear. Each front camera had an array 484 pixels high by 768 wide. The cameras used CCDs manufactured by Eastman Kodak Company; they were clocked out by CPU, and capable of auto-exposure, Block Truncation Coding (BTC) data compression, bad pixel/column handling, and image data packetizing.
Both front cameras were coupled with five laser stripe projectors that enabled stereoscopic images to be taken along with measurements for hazard detection in the rover's path. The optics consisted of a window, lens, and field flattener. The window was made of sapphire while the lens objective and flattener were made of zinc selenide.
Another color camera was located on the back of the rover near the APXS, and rotated by 90°. It provided images of the APXS's target area and the rover's ground tracks.
The sensor of this color camera was arranged so 12 of 16 pixels of a 4×4 pixel block were sensitive to green light; while 2 pixels were sensitive to red light and the other 2 were sensitive to infrared and blue light.
Because the rover's cameras had zinc-selenide lenses, which block light with a wavelength shorter than 500 nanometers (nm), no blue light actually reached the blue-and-infrared-sensitive pixels, which therefore recorded only infrared light.[40]
Sojourner operation was supported by "Rover Control Software" (RCS) that ran on a Silicon Graphics Onyx2 computer on Earth and allowed command sequences to be generated using a graphical interface. The rover driver would wear 3D goggles supplied with imagery from the base station and would move a virtual model with a specialized joystick. The control software allowed the rover and surrounding terrain to be viewed from any angle, supporting the study of terrain features, the placing of waypoints, and virtual flyovers. Darts were used as icons to show where the rover should go. Desired locations were added to a sequence and sent to the rover to perform. Typically, a long sequence of commands were composed and sent once a day.[41] [42] The rover drivers were Brian K. Cooper and Jack Morrison.
See main article: Alpha particle X-ray spectrometer.
The Alpha Proton X-Ray Spectrometer (APXS) was designed to determine the chemical composition of Martian soil, rocks and dust by analyzing the return radiation in its alpha, proton, and X-ray components resulting from the sample's exposure to a radioactive source contained in the instrument.[43] [44] The instrument had a curium-244 source that emits alpha particles with an energy of 5.8 MeV and a half-life of 18.1 years. A portion of the incident radiation that impacted the analyzed sample's surface was reflected and the remainder interacted with the sample.
The principle of the APXS technique is based on the interaction of alpha particles from a radioisotope source with matter. There are three components of the return radiation; simple Rutherford backscattering, production of protons from reactions with the nucleus of light elements, and generation of X-rays upon recombination of atomic shell vacancies created by alpha particle bombardment by interaction with the electrons of the innermost orbitals.[45] The instrument was designed to detect the energy of all three components of the return radiation, making it possible to identify the atoms present and their quantities in a few tens of micrometers below the surface of the analyzed sample.[46] The detection process was rather slow; each measurement could take up to ten hours.[47]
Sensitivity and selectivity depends on a channel; alpha backscattering has high sensitivity for light elements like carbon and oxygen, proton emission is mainly sensitive to sodium, magnesium, aluminium, silicon, sulfur, and X-ray emission is more sensitive to heavier elements sodium to iron and beyond. Combining all three measurements makes APXS sensitive to all elements with the exception of hydrogen that is present at concentration levels above a fraction of one percent. The instrument was designed for the failed Russian Mars-96 mission.[48] The alpha particle and proton detectors were provided by the Chemistry Department of the Max Planck Institute and the X-ray detector was developed by the University of Chicago.
During each measurement, the front surface of the instrument had to be in contact with the sample. For this to be possible, the APXS was mounted on a robotic arm called the Alpha-Proton-X-ray Spectrometer Deployment Mechanism (ADM). The ADM was an anthropomorphic actuator that was equipped with a wrist that was capable of rotations of ±25°. The dual mobility of the rover and the ADM increased the potential of the instrument—the first of its kind to reach Mars.
The Wheel Abrasion Experiment (WAE) was designed to measure the abrasive action of Martian soil on thin layers of aluminum, nickel, and platinum, and thus deduce the grain size of the soil at the landing site. For this purpose, 15 layers—five of each metal—were mounted on one of the two central wheels with a thickness between 200 and 1000 ångström, and electrically isolated from the rest of the rover. By directing the wheel appropriately, sunlight was reflected towards a nearby photovoltaic sensor. The collected signal was analyzed to determine the desired information.[49] For the abrasive action to be significant on the mission schedule, the rover was scheduled to stop at frequent intervals and, with the other five wheels braked, force the WAE wheel to rotate, causing increased wear.[50] Following the WAE experiment on Mars, attempts were made to reproduce the effects observed in the laboratory.
The interpretation of the results proposed by Ferguson et al. suggests the soil at the landing site is made up of fine-grained dust of limited hardness with a grain size of less than 40 μm. The instrument was developed, built and directed by the Lewis' Photovoltaics and Space Environments Branch of the Glenn Research Center.
See main article: Materials Adherence Experiment.
The Materials Adherence Experiment (MAE) was designed by engineers at the Glenn Research Center to measure the daily accumulation of dust on the back of the rover and the reduction in the energy-conversion capacity of the photovoltaic panels.[51] [52] It consisted of two sensors.
The first was composed of a photovoltaic cell covered by transparent glass that could be removed on command. Near local midday, measurements of the cell's energy yield were made, both with the glass in place and removed. From the comparison, it was possible to deduce the reduction in cell yield caused by the dust. Results from the first cell were compared with those of a second photovoltaic cell that was exposed to the Martian environment. The second sensor used a quartz crystal microbalance (QCM) to measure the weight-per-surface unit of the dust deposited on the sensor.
During the mission, a daily rate equal to 0.28% of percentage reduction in the energy efficiency of the photovoltaic cells was recorded. This was independent of whether the rover was stationary or in motion. This suggests the dust settling on the rover was suspended in the atmosphere and was not raised by the rover's movements.
Since it was established transmissions relating to driving the Sojourner would occur once every sol, the rover was equipped with a computerized control system to guide its movements independently.[53]
A series of commands had been programmed, providing an appropriate strategy for overcoming obstacles. One of the primary commands was "Go to Waypoint". A local reference system, of which the lander was the origin, was envisaged. Coordinate directions were fixed at the moment of landing, taking the direction of north as a reference. During the communication session (once per sol), the rover received from Earth a command string containing the coordinates of the arrival point, which it would have to reach autonomously.
The algorithm implemented on the on-board computer attempted, as a first option, to reach the obstacle in a straight line from the starting position. Using a system of photographic objectives and laser emitters, the rover could identify obstacles along this path. The on-board computer was programmed to search for the signal produced by the lasers in the cameras' images. In the case of a flat surface and no obstacles, the position of this signal was unchanged with respect to the reference signal stored in the computer; any deviation from this position made it possible to identify the type of obstacle. The photographic scan was performed after each advance equal to the diameter of the wheels, 13cm (05inches), and before each turn.
In the confirmed presence of an obstacle, the computer commanded the execution of a first strategy to avoid it. The rover, still by itself, rotated until the obstacle was no longer in sight. Then, after having advanced for half of its length, it recalculated a new straight path that would lead it to the point of arrival. At the end of the procedure, the computer had no memory of the existence of the obstacle. The steering angle of the wheels was controlled through potentiometers.
In particularly uneven terrain, the procedure described above would have been prevented by the presence of a large number of obstacles. There was, therefore, a second procedure known as "thread the needle", which consisted of proceeding between two obstacles along the bisector between them, providing they were sufficiently spaced to allow the rover to pass. If the rover had encountered a clearing before reaching a predetermined distance, it would have had to rotate on itself to calculate a new straight trajectory to reach the target. Conversely, the rover would have had to go back and try a different trajectory. As a last resort, contact sensors were mounted on the front and rear surfaces of the rover.
To facilitate the rover's direction, an appropriate on-the-spot rotation could be commanded from Earth. The command was "Turn" and was performed using a gyroscope. Three accelerometers measured the acceleration of gravity along three perpendicular directions, making it possible to measure the surface's slope. The rover was programmed to deviate from routes that would require a slope greater than 30°, though it was designed not to tip over when tilted at 45°. The distance traveled was determined by the number of revolutions of the wheels.
Marie Curie is a flight spare for the Sojourner. During the operational phase on Mars, the sequences of the most complex commands to be sent to Sojourner were verified on this identical rover at JPL.[54] NASA planned to send Marie Curie on the canceled Mars Surveyor 2001 mission; it was suggested to send it in 2003, proposing Marie Curie to be deployed "using a robotic-arm attached to the lander".[55] Rather than this, the Mars Exploration Rover program was launched in 2003. In 2015, JPL transferred Marie Curie to the Smithsonian National Air and Space Museum (NASM).[56]
According to space historian and NASM curator Matt Shindell:
To test robotic prototypes and applications under natural lighting conditions, JPL built a simulated Martian landscape called "Mars Yard". The test area measured 21by and had a variety of terrain arrangements to support multiple test conditions. The soil was a combination of beach sand, decomposed granite, brick dust, and volcanic cinders. The rocks were several types of basalts, including fine-grained and vesicular in both red and black. Rock-size distributions were selected to match those seen on Mars and the soil characteristics matched those found in some Martian regions. Large rocks were not Mars-like in composition, being less dense and easier to move for testing. Other obstacles such as bricks and trenches were often used for specialized testing.[57] Mars Yard was expanded in 1998 and then in 2007 to support other Mars rover missions.[58]
The name "Sojourner" was chosen for the rover through a competition held in March 1994 by the Planetary Society in collaboration with JPL; it ran for one year and was open to students of 18 years and below from any country. Participants were invited to choose a "heroine to whom to dedicate the rover" and to write an essay about her accomplishments, and how these accomplishments could be applied to the Martian environment.[59] The initiative was publicized in the United States through the January 1995 edition of the magazine Science and Children published by the National Science Teachers Association.
Some 3,500 papers were received from countries including Canada, India, Israel, Japan, Mexico, Poland, Russia, and the United States, of which 1,700 were from students aged between 5 and 18. The winners were chosen on the basis of the quality and creativity of the work, the appropriateness of the name for a Martian rover, and the competitor's knowledge of the heroine and the probe mission. The winning paper was written by 12-year-old Valerie Ambroise of Bridgeport, Connecticut, who suggested dedicating the rover to Sojourner Truth,[60] a Civil War era African-American abolitionist and women's rights advocate. The second place went to Deepti Rohatgi, 18, of Rockville, Maryland, who proposed Marie Curie, a Nobel Prize-winning Franco-Polish chemist. Third place went to Adam Sheedy, 16, of Round Rock, Texas, who chose Judith Resnik, a United States astronaut and Space Shuttle crew member who died in the 1986 Challenger disaster. The rover was also known as Microrover Flight Experiment abbreviated MFEX.[61]
Sojourner was launched on December 4, 1996, aboard a Delta II booster, and reached Mars on July 4, 1997. It operated in Ares Vallis channel in the Chryse Planitia of the Oxia Palus quadrangle,[62] from July 5[63] to September 27, 1997, when the lander cut off communications with Earth. In the 83 sols of activity—twelve times the expected duration for the rover—Sojourner traveled 104meters, always remaining within 12meters of the lander. It collected 550 images, performed 16 analyzes through the APXS—nine of rocks and the remainder of the soil— and performed 11 Wheel Abrasion Experiments and 14 experiments on soil mechanics in cooperation with the lander.[64]
The landing site for the rover was chosen in April 1994 at the Lunar and Planetary Institute in Houston. The landing site is an ancient flood plain called Ares Vallis, which is located in Mars' northern hemisphere and is one of the rockiest parts of Mars. It was chosen because it was thought to be a relatively safe surface on which to land and one that contains a wide variety of rocks that were deposited during a flood. This area was well-known, having been photographed by the Viking mission.[65] [66] [67] After a successful landing, the lander was officially named "The Carl Sagan Memorial Station" in honor of the astronomer.[68]
Mars Pathfinder landed on July 4, 1997. The petals were deployed 87 minutes later with Sojourner rover and the solar panels attached on the inside. The rover exited the lander on the next day.[69]
The rocks at the landing site were given names of cartoon characters. Among them were Pop Tart, Ender, mini-Matterhorn, Wedge, Baker's Bench, Scooby Doo, Yogi, Barnacle Bill, Pooh Bear, Piglet, the Lamb, the Shark, Ginger, Souffle, Casper, Moe, and Stimpy. A dune was called Mermaid Dune, and a pair of hills were named Twin Peaks.[70] [71] [72]
The first analysis was carried out on the rock called "Barnacle Bill" during the third sol. The rock's composition was determined by the APXS spectrometer, which took 10 hours for a complete scan. The rock "Yogi" was analyzed on the 10th sol.[73] It has been suggested the conformation of the land close to the rock, even visually at a lower level than the surrounding surface, was derived from the evaporation of floodwater.[74]
Both rocks turned out to be andesites; this finding surprised some scholars because andesites are formed by geological processes that require an interaction between materials of the crust and the mantle. A lack of information on the surrounding highlands made it impossible to grasp all of the implications of the discovery.[75]
The rover was then directed to the next target and on the 14th sol, it analyzed the rock named "Scooby-Doo" and imaged the "Casper" rock. Both were deemed to be consolidated deposits. The rock called "Moe" showed evidence of wind erosion. Most of the rocks analyzed showed a high silicon content. In a region nicknamed "Rock Garden", the rover encountered crescent-moon-shaped dunes that are similar to dunes on earth.
The landing site is rich in varied rocks, some of which are clearly volcanic in origin, such as "Yogi"; others are conglomerates, the origins of which are the subject of several proposals. In one hypothesis, they formed in the presence of water in Mars' distant past. In support of this, high silicon contents would be detected. This could also be a consequence of sedimentation processes; rounded rocks of various sizes were discovered and the valley's shapes are compatible with a river channel environment. Smaller, more rounded stones may also have been generated during a surface impact event.
When the mission's final results were described in a series of articles in the journal Science (December 5, 1997), it was believed the rock Yogi had a coating of dust but was similar to the rock Barnacle Bill. Calculations suggested both rocks mostly contain orthopyroxene (magnesium-iron silicate), feldspars (aluminum silicates of potassium, sodium, and calcium), and quartz (silicon dioxide) with smaller amounts of magnetite, ilmenite, iron sulfide, and calcium phosphate.[76] [77]
The development of the rover and its instruments as well as its guidance during operations on Mars were done by a group of engineers from NASA, collectively referred to as "The Rover Team". The key personnel were:
Some sections of this article were originally translated from the Italian Wikipedia article. For original, see .