1. Mission overview
    History  Specifications  Launch  Landing  Surface mission  Communications from the surface  Presence of shallow subsurface water ice  Wet chemistry  End of the mission   Communication attempts 2010   Results of the mission  Landscape  Weather  Climate cycles  Surface chemistry 

2. Scientific payload
    Robotic arm and camera  Surface stereo imager  Thermal and evolved gas analyzer  Mars Descent Imager  Microscopy, electrochemistry, and conductivity analyzer  Sample wheel and translation stage  Optical microscope  Atomic force microscope  Wet Chemistry Laboratory (WCL)  Thermal and Electrical Conductivity Probe (TECP)  Meteorological station 

3. Phoenix DVD

4. References

5. External links

The multi-agency program was headed by the Lunar and Planetary Laboratory at the University of Arizona, under the direction of NASA's Jet Propulsion Laboratory. The program was a partnership of universities in the United States, Canada, Switzerland, Denmark, Germany, the United Kingdom, NASA, the Canadian Space Agency, the Finnish Meteorological Institute, Lockheed Martin Space Systems, MacDonald Dettwiler & Associates (MDA) and other aerospace companies.^[6] It was the first mission to Mars led by a public university in NASA history.^[7] It was led directly from the University of Arizona's campus in Tucson, with project management at the Jet Propulsion Laboratory in Pasadena, Calif., and project development at Lockheed Martin in Denver, Colorado. The operational funding for the mission extended through November 10, 2008.

Mission overview

The mission had two goals. One was to study the geologic history of water, the key to unlocking the story of past climate change. The second was to evaluate past or potential planetary habitability in the ice-soil boundary. Phoenix's instruments were suitable for uncovering information on the geological and possibly biological history of the Martian Arctic. Phoenix was the first mission to return data from either of the poles, and contributed to NASA's main strategy for Mars exploration, "Follow the water."

The primary mission was anticipated to last 90 sols (Martian days)—just over 92 Earth days. However, the craft exceeded its expected operational lifetime^[10] by a little over two months before succumbing to the increasing cold and dark of an advancing Martian winter.^[8] Researchers had hoped that the lander would survive into the Martian winter so that it could witness polar ice developing around it – perhaps up to 1 metre of solid carbon dioxide ice could have appeared. Even had it survived some of the winter, the intense cold would have prevented it from lasting all the way through.^[11] The mission was chosen to be a fixed lander rather than a rover because:^[12]

• costs were reduced through reuse of earlier equipment (the total mission cost was estimated to be about US $386 million, which includes the launch^[3][4][5]);
• the area of Mars where Phoenix landed is thought to be relatively uniform, thus traveling is of less value; and
• the weight budget needed for mobility could instead be used for more and better scientific instruments.

The 2003–2004 observations of methane gas on Mars were made remotely by three teams working with separate data. If the methane is truly present in the atmosphere of Mars, then something must be producing it on the planet now, because the gas is broken down by radiation on Mars within 300 years,^{[13][14][15][16][17]} therefore the importance to search for biological potential or habitability of the Martian arctic's soils.^[18] Methane could also be the product of a geochemical process or the result of volcanic or hydrothermal activity.^[19]

History

While the proposal for Phoenix was being written, the Mars Odyssey Orbiter used its gamma-ray spectrometer and found the distinctive signature of hydrogen on some areas of the Martian surface, and the only plausible source of hydrogen on Mars would be water in the form of ice, frozen below the surface. The mission was therefore funded on the expectation that Phoenix would find water ice on the arctic plains of Mars.^[20] In August 2003 NASA selected the University of Arizona "Phoenix" mission for launch in 2007. It was hoped this would be the first in a new line of smaller, low-cost, Scout missions in the agency's exploration of Mars program.^[21] The selection was the result of an intense two-year competition with proposals from other institutions. The $325 million NASA award is more than six times larger than any other single research grant in University of Arizona history.

On June 2, 2005, following a critical review of the project's planning progress and preliminary design, NASA approved the mission to proceed as planned.^[25] The purpose of the review was to confirm NASA's confidence in the mission.

Specifications

Mass

{{convert|350|kg|lb|abbr=on}}

Dimensions

About {{convert|5.5|m|ft|abbr=on}} long with the solar panels deployed. The science deck by itself is about {{convert|1.5|m|ft|abbr=on}} in diameter. From the ground to the top of the MET mast, the lander measures about {{convert|2.2|m|ft|abbr=on}} tall.

Communications

X-band throughout the cruise phase of the mission and for its initial communication after separating from the third stage of the launch vehicle. UHF links, relayed through Mars orbiters during the entry, descent and landing phase and while operating on the surface of Mars. The UHF system on Phoenix is compatible with relay capabilities of NASA's Mars Odyssey, Mars Reconnaissance Orbiter and with the European Space Agency's Mars Express. The interconnections use the Proximity-1 protocol.^[26]

Power

Power is generated using two gallium arsenide solar panels (total area {{convert|3.1|m2|ft2|abbr=on}}) mounted to the cruise stage during cruise, and via two gallium arsenide solar array panels (total area {{convert|7.0|m2|ft2|abbr=on}}) deployed from the lander after touchdown on the Martian surface. NiH₂ battery with a capacity of 16 A·h.^[27]

Lander systems include a RAD6000 based computer system for commanding the spacecraft and handling data.^[28] Other parts of the lander are an electrical system containing solar arrays and batteries, a guidance system to land the spacecraft, eight {{convert|1.0|lbf|abbr=on}} and {{convert|5.0|lbf|abbr=on}} monopropellant hydrazine engines built by Aerojet-Redmond Operations for the cruise phase, twelve {{convert|68.0|lbf|abbr=on}} Aerojet monopropellant hydrazine thrusters to land the Phoenix, mechanical and structural elements, and a heater system to ensure the spacecraft does not get too cold.

Launch

A noctilucent cloud was created by the exhaust gas from the Delta II 7925 rocket used to launch Phoenix.^[30] The colors in the cloud formed from the prism-like effect of the ice particles present in the exhaust trail.

Landing

The Jet Propulsion Laboratory made adjustments to the orbits of its two active satellites around Mars, Mars Reconnaissance Orbiter and Mars Odyssey, and the European Space Agency similarly adjusted the orbit of its Mars Express spacecraft to be in the right place on May 25, 2008 to observe Phoenix as it entered the atmosphere and then landed on the surface. This information helps designers to improve future landers.^[31] The projected landing area was an ellipse 100 km by 20 km covering terrain which has been informally named "Green Valley"^[32] and contains the largest concentration of water ice outside the poles.

For unknown reasons, the parachute was deployed about 7 seconds later than expected, leading to a landing position some 25–28 km east, near the edge of the predicted 99% landing ellipse.

The landing was made on a flat surface, with the lander reporting only 0.3 degrees of tilt. Just before landing, the craft used its thrusters to orient its solar panels along an east-west axis to maximize power generation. The lander waited 15 minutes before opening its solar panels, to allow dust to settle. The first images from the lander became available around 7:00 p.m. PDT (2008-05-26 02:00 UTC).^[41] The images show a surface strewn with pebbles and incised with small troughs into polygons about 5 m across and 10 cm high, with the expected absence of large rocks and hills.

Like the 1970s era Viking spacecraft, Phoenix used retrorockets for its final descent.^[42] Experiments conducted by Nilton Renno, mission co-investigator from the University of Michigan, and his students have investigated how much surface dust would be kicked up on landing.^[43] Researchers at Tufts University, led by co-investigator Sam Kounaves, conducted additional in-depth experiments to identify the extent of the ammonia contamination from the hydrazine propellant and its possible effects on the chemistry experiments. In 2007, a report to the American Astronomical Society by Washington State University professor Dirk Schulze-Makuch, suggested that Mars might harbor peroxide-based life forms which the Viking landers failed to detect because of the unexpected chemistry.^[44] The hypothesis was proposed long after any modifications to Phoenix could be made. One of the Phoenix mission investigators, NASA astrobiologist Chris McKay, stated that the report "piqued his interest" and that ways to test the hypothesis with Phoenixs instruments would be sought.

Surface mission

Communications from the surface

The robotic arm's first movement was delayed by one day when, on May 27, 2008, commands from Earth were not relayed to the Phoenix lander on Mars. The commands went to NASA's Mars Reconnaissance Orbiter as planned, but the orbiter's Electra UHF radio system for relaying commands to Phoenix temporarily shut off. Without new commands, the lander instead carried out a set of backup activities. On May 27 the Mars Reconnaissance Orbiter relayed images and other information from those activities back to Earth.

The robotic arm was a critical part of the Phoenix Mars mission. On May 28, scientists leading the mission sent commands to unstow its robotic arm and take more images of its landing site. The images revealed that the spacecraft landed where it had access to digging down a polygon across the trough and digging into its center.^[45]

The lander's robotic arm touched soil on Mars for the first time on May 31, 2008 (sol {{age in sols|2008|05|25|2008|05|31}}). It scooped dirt and started sampling the Martian soil for ice after days of testing its systems.^[46]

Presence of shallow subsurface water ice

The polygonal cracking at the landing zone had previously been observed from orbit, and is similar to patterns seen in permafrost areas in polar and high altitude regions of Earth.^[47] Phoenixs robotic arm camera took an image underneath the lander on sol 5 that shows patches of a smooth bright surface uncovered when thruster exhaust blew off overlying loose soil. It was later shown to be water ice.^[48][49][50]

On June 19, 2008 (sol {{age in sols|2008|05|25|2008|06|19}}), NASA announced that dice-sized clumps of bright material in the "Dodo-Goldilocks" trench dug by the robotic arm had vaporized over the course of four days, strongly implying that they were composed of water ice which sublimed following exposure. While dry ice also sublimes, under the conditions present it would do so at a rate much faster than observed.^[51][52][53]

On July 31, 2008 (sol {{age in sols|2008|05|25|2008|07|31}}), NASA announced that Phoenix confirmed the presence of water ice on Mars, as predicted in 2002 by the Mars Odyssey orbiter. During the initial heating cycle of a new sample, TEGA's mass spectrometer detected water vapor when the sample temperature reached 0 °C.^[54]

Liquid water cannot exist on the surface of Mars with its present low atmospheric pressure, except at the lowest elevations for short periods.^[55][56]

With Phoenix in good working order, NASA announced operational funding through September 30, 2008 (sol {{age in sols|2008|05|25|2008|09|30}}). The science team worked to determine whether the water ice ever thaws enough to be available for life processes and if carbon-containing chemicals and other raw materials for life are present.

Additionally during 2008 and early 2009 a debate emerged within NASA over the presence of 'blobs' which appeared on photos of the vehicle's landing struts, which have been variously described as being either water droplets or 'clumps of frost'.^[63] Due to the lack of consensus within the Phoenix science project, the issue had not been raised in any NASA news conferences.^[57]

One scientist thought that the lander's thrusters splashed a pocket of brine from just below the Martian surface onto the landing strut during the vehicle's landing. The salts would then have absorbed water vapor from the air, which would have explained how they appeared to grow in size during the first 44 sols (Martian days) before slowly evaporating as Mars temperature dropped.^[57]

Wet chemistry

On June 24, 2008 (sol {{age in sols|2008|05|25|2008|06|24}}), NASA's scientists launched a series of scientific tests. The robotic arm scooped up more soil and delivered it to 3 different on-board analyzers: an oven that baked it and tested the emitted gases, a microscopic imager, and a wet chemistry laboratory (WCL).^[58] The lander's robotic arm scoop was positioned over the Wet Chemistry Lab delivery funnel on Sol 29 (the 29th Martian day after landing, i.e. June 24, 2008). The soil was transferred to the instrument on sol {{age in sols|2008|05|25|2008|06|25}} (June 25, 2008), and Phoenix performed the first wet chemistry tests. On Sol 31 (June 26, 2008) Phoenix returned the wet chemistry test results with information on the salts in the soil, and its acidity. The wet chemistry lab (WCL)^[68] was part of the suite of tools called the Microscopy, Electrochemistry and Conductivity Analyzer (MECA).^[59]

{{Wide image|PIA13804-MarsPhoenixLander-Panorama-20080525b.jpg|800px|Panorama of rocks near the Phoenix Lander (May 25, 2008).}}{{Wide image|PIA11044-PhoenixLander-WorkspaceNames-20080819.jpg|800px|Panorama of rocks near the Phoenix Lander (August 19, 2008).}}

A 360-degree panorama assembled from images taken on sols 1 and 3 after landing. The upper portion has been vertically stretched by a factor of 8 to bring out details. Visible near the horizon at full resolution are the backshell and parachute (a bright speck above the right edge of the left solar array, about 300 m distant) and the heat shield and its bounce mark (two end-to-end dark streaks above the center of the left solar array, about 150 m distant); on the horizon, left of the weather mast, is a crater.

End of the mission

The solar-powered lander operated two months longer than its three-month prime mission. The lander was designed to last 90 days, and had been running on bonus time since the successful end of its primary mission in August 2008.^[10] On October 28, 2008 (sol {{age in sols|2008|05|25|2008|10|28}}), the spacecraft went into safe mode due to power constraints based on the insufficient amount of sunlight reaching the lander,^[62] as expected at this time of year. It was decided then to shut down the four heaters that keep the equipment warm, and upon bringing the spacecraft back from safe mode, commands were sent to turn off two of the heaters rather than only one as was originally planned for the first step. The heaters involved provide heat to the robotic arm, TEGA instrument and a pyrotechnic unit on the lander that were unused since landing, so these three instruments were also shut down.

On November 10, Phoenix Mission Control reported the loss of contact with the Phoenix lander; the last signal was received on November 2.^[63] Immediately prior, Phoenix sent its final message: "Triumph" in binary code.^[64][65] The demise of the craft occurred as a result of a dust storm that reduced power generation even further.^[66] While the spacecraft's work ended, the analysis of data from the instruments was in its earliest stages.

Communication attempts 2010

Though it was not designed to survive the frigid Martian winter, the spacecraft's safe mode kept the option open to reestablish communications if the lander could recharge its batteries during the next Martian spring.^[78] However, its landing location is in an area that is usually part of the north polar ice cap during the Martian winter, and the lander was seen from orbit to be encased in dry ice.^[79] It is estimated that, at its peak, the layer of CO₂ ice in the lander's vicinity would total about 30 grams/cm², which is enough to make a dense slab of dry ice at least {{convert|7+1/2|in|cm}} thick.^[67] It was considered unlikely that the spacecraft could endure these conditions, as its fragile solar panels would likely break off under so much weight.^[67][68]

Scientists attempted to make contact with Phoenix starting January 18, 2010 (sol {{age in sols|2010|05|25|2008|01|18}}), but were unsuccessful. Further attempts in February and April also failed to pick up any signal from the lander.^{[69][70][71][72]} Project manager Barry Goldstein announced on May 24, 2010 that the project was being formally ended. Images from the Mars Reconnaissance Orbiter showed that its solar panels were apparently irretrievably damaged by freezing during the Martian winter.^[73][74]

Results of the mission

Landscape

Unlike some other places visited on Mars with landers (Viking and Pathfinder), nearly all the rocks near Phoenix are small. For about as far as the camera can see, the land is flat, but shaped into polygons between 2–3 meters in diameter and are bounded by troughs that are 20 cm to 50 cm deep. These shapes are due to ice in the soil expanding and contracting due to major temperature changes. The microscope showed that the soil on top of the polygons is composed of flat particles (probably a type of clay) and rounded particles. Also, unlike other places visited on Mars, the site has no ripples or dunes.^[75] Ice is present a few inches below the surface in the middle of the polygons, and along its edges, the ice is at least 8 inches deep. When the ice is exposed to the Martian atmosphere it slowly sublimates.^[76] Some dust devils were observed.

Weather

Snow was observed to fall from cirrus clouds. The clouds formed at a level in the atmosphere that was around −65 °C, so the clouds would have to be composed of water-ice, rather than carbon dioxide-ice (dry ice) because, at the low pressure of the Martian atmosphere, the temperature for forming carbon dioxide ice is much lower—less than −120 °C. It is now thought that water ice (snow) would have accumulated later in the year at this location.^[77] This represents a milestone in understanding Martian weather. Wind speeds ranged from 11 to 58 km per hour. The usual average speed was 36 km per hour.^[78] These speeds seem high, but the atmosphere of Mars is very thin—less than 1% of the Earth's—and so did not exert much force on the spacecraft. The highest temperature measured during the mission was −19.6 °C, while the coldest was −97.7 °C.^[79]

Climate cycles

Interpretation of the data transmitted from the craft was published in the journal Science. As per the peer reviewed data the presence of water ice has been confirmed and that the site had a wetter and warmer climate in the recent past. Finding calcium carbonate in the Martian soil leads scientists to think that the site had been wet or damp in the geological past. During seasonal or longer period diurnal cycles water may have been present as thin films. The tilt or obliquity of Mars changes far more than the Earth; hence times of higher humidity are probable.^[80]

Surface chemistry

Chemistry results showed the surface soil to be moderately alkaline, with a pH of 7.7 ±0.5.^[81][82] The overall level of salinity is modest. TEGA analysis of its first soil sample indicated the presence of bound water and CO₂ that were released during the final (highest-temperature, 1,000 °C) heating cycle.^[83]

The elements detected and measured in the samples are chloride, bicarbonate, magnesium, sodium, potassium, calcium, and sulfate.^[82] Further data analysis indicated that the soil contains soluble sulfate (SO₃) at a minimum of 1.1% and provided a refined formulation of the soil.^[82]

Analysis of the Phoenix WCL also showed that the Ca(ClO₄)₂ in the soil has not interacted with liquid water of any form, perhaps for as long as 600 million years. If it had, the highly soluble Ca(ClO₄)₂ in contact with liquid water would have formed only CaSO₄. This suggests a severely arid environment, with minimal or no liquid water interaction.^[84] The pH and salinity level were viewed as benign from the standpoint of biology.

Perchlorate

On August 1, 2008, Aviation Week reported that "The White House has been alerted by NASA about plans to make an announcement soon on major new Phoenix lander discoveries concerning the "potential for life" on Mars, scientists tell Aviation Week & Space Technology."^[85] This led to a subdued media speculation on whether some evidence of past or present life had been discovered.^[86][87][88] To quell the speculation, NASA released the preliminary findings stating that Mars soil contains perchlorate ({{chem|ClO|4}}) and thus may not be as life-friendly as thought earlier.^[89][90] The presence of almost 0.5% perchlorates in the soil was an unexpected finding with broad implications.^[91]

Laboratory research published in July 2017 demonstrated that when irradiated with a simulated Martian UV flux, perchlorates become bacteriocidal.^[92] Two other compounds of the Martian surface, iron oxides and hydrogen peroxide, act in synergy with irradiated perchlorates to cause a 10.8-fold increase in cell death when compared to cells exposed to UV radiation after 60 seconds of exposure.^[92] It was also found that abraded silicates (quartz and basalt) lead to the formation of toxic reactive oxygen species.^[93] The results leaves the question of presence of organic compounds open-ended since heating the samples containing perchlorate would have broken down any organics present.^[94]

Scientific payload

During EDL, the Atmospheric Structure Experiment was conducted. This used accelerometer and gyroscope data recorded during the lander's descent through the atmosphere to create a vertical profile of the temperature, pressure, and density of the atmosphere above the landing site, at the that point in time.^[101]

Robotic arm and camera

The robotic arm was designed to extend 2.35 m from its base on the lander, and had the ability to dig down to 0.5 m below sandy surface. It took samples of dirt and ice that were analyzed by other instruments on the lander. The arm was designed and built for the Jet Propulsion Laboratory by Alliance Spacesystems, LLC^[102] (now MDA US Systems, LLC) in Pasadena, California. A rotating rasp-tool located in the heel of the scoop was used to cut into the strong permafrost. Cuttings from the rasp were ejected into the heel of the scoop and transferred to the front for delivery to the instruments. The rasp tool was conceived of at the Jet Propulsion Laboratory. The flight version of the rasp was designed and built by HoneyBee Robotics. Commands were sent for the arm to be deployed on May 28, 2008, beginning with the pushing aside of a protective covering intended to serve as a redundant precaution against potential contamination of Martian soil by Earthly life-forms.

The Robotic Arm Camera (RAC) attached to the robotic arm just above the scoop was able to take full-color pictures of the area, as well as verify the samples that the scoop returned, and examined the grains of the area where the robotic arm had just dug. The camera was made by the University of Arizona and Max Planck Institute for Solar System Research,^[103] Germany.^[104]

Surface stereo imager

The Surface Stereo Imager (SSI) was the primary camera on the lander. It is a stereo camera that is described as "a higher resolution upgrade of the imager used for Mars Pathfinder and the Mars Polar Lander".^[105] It took several stereo images of the Martian Arctic, and also used the Sun as a reference, to measure the atmospheric distortion of the Martian atmosphere due to dust, air and other features. The camera was provided by the University of Arizona in collaboration with the Max Planck Institute for Solar System Research.^[106][107]

Thermal and evolved gas analyzer

The Thermal and Evolved Gas Analyzer (TEGA) is a combination of a high-temperature furnace with a mass spectrometer. It was used to bake samples of Martian dust and determine the composition of the resulting vapors. It has eight ovens, each about the size of a large ball-point pen, which were able to analyze one sample each, for a total of eight separate samples. Team members measured how much water vapor and carbon dioxide gas were given off, how much water ice the samples contained, and what minerals are present that may have formed during a wetter, warmer past climate. The instrument also measured organic volatiles, such as methane, down to 10 ppb. TEGA was built by the University of Arizona and University of Texas at Dallas.^[108]

On May 29, 2008 (sol {{age in sols|2008|05|25|2008|05|29}}), electrical tests indicated an intermittent short circuit in TEGA,^[109] resulting from a glitch in one of the two filaments responsible for ionizing volatiles.^[110] NASA worked around the problem by configuring the backup filament as the primary and vice versa.^[111]

On June 11 the first of the eight ovens was filled with a soil sample after several tries to get the soil sample through the screen of TEGA. On June 17, it was announced that no water was found in this sample; however, since it had been exposed to the atmosphere for several days prior to entering the oven, any initial water ice it might have contained could have been lost via sublimation.{{citation needed|date=January 2018}}

Mars Descent Imager

The Mars Descent Imager (MARDI) was intended to take pictures of the landing site during the last three minutes of descent. As originally planned, it would have begun taking pictures after the aeroshell departed, about 8 km above the Martian soil.{{citation needed|date=January 2018}} Before launch, testing of the assembled spacecraft uncovered a potential data corruption problem with an interface card that was designed to route MARDI image data as well as data from various other parts of the spacecraft. The potential problem could occur if the interface card were to receive a MARDI picture during a critical phase of the spacecraft's final descent, at which point data from the spacecraft's Inertial Measurement Unit could have been lost; this data was critical to controlling the descent and landing. This was judged to be an unacceptable risk, and it was decided to not use MARDI during the mission.^[112] As the flaw was discovered too late for repairs, the camera remained installed on Phoenix but it was not used to take pictures, nor was its built-in microphone used.^[113]

MARDI images had been intended to help pinpoint exactly where the lander landed, and possibly help find potential science targets. It was also to be used to learn if the area where the lander lands is typical of the surrounding terrain. MARDI was built by Malin Space Science Systems.^[114] It would have used only 3 watts of power during the imaging process, less than most other space cameras. It had originally been designed and built to perform the same function on the Mars Surveyor 2001 Lander mission; after that mission was canceled, MARDI spent several years in storage until it was deployed on the Phoenix lander.

Microscopy, electrochemistry, and conductivity analyzer

The Microscopy, Electrochemistry, and Conductivity Analyzer (MECA) is an instrument package originally designed for the canceled Mars Surveyor 2001 Lander mission. It consists of a wet chemistry lab (WCL), optical and atomic force microscope, and a thermal and electrical conductivity probe.^[115] The Jet Propulsion Laboratory built MECA. A Swiss consortium led by the University of Neuchatel contributed the atomic force microscope.^[116]

Using MECA, researchers examined soil particles as small as 16 μm across; additionally, they attempted to determine the chemical composition of water-soluble ions in the soil. They also measured electrical and thermal conductivity of soil particles using a probe on the robotic arm scoop.^[117]

Sample wheel and translation stage

This instrument presents 6 of 69 sample holders to an opening in the MECA instrument to which the robotic arm delivers the samples and then brings the samples to the optical microscope and the atomic force microscope.^[118] Imperial College London provided the microscope sample substrates.^[119]

Optical microscope

The optical microscope, designed by the University of Arizona, is capable of making images of the Martian regolith with a resolution of 256 pixels/mm or 16 micrometers/pixel. The field of view of the microscope is a 2×2 mm sample holder to which the robotic arm delivers the sample. The sample is illuminated either by 9 red, green and blue LEDs or by 3 LEDs emitting ultraviolet light. The electronics for the readout of the CCD chip are shared with the robotic arm camera which has an identical CCD chip.

Atomic force microscope

The atomic force microscope has access to a small area of the sample delivered to the optical microscope. The instrument scans over the sample with one of 8 silicon crystal tips and measures the repulsion of the tip from the sample. The maximum resolution is 0.1 micrometres. A Swiss consortium led by the University of Neuchatel contributed the atomic force microscope.^[116]

Wet Chemistry Laboratory (WCL)

The wet chemistry lab (WCL) sensor assembly and leaching solution were designed and built by Thermo Fisher Scientific.^[120] The WCL actuator assembly was designed and built by Starsys Research in Boulder, Colorado. Tufts University developed the reagent pellets, barium ISE, ASV electrodes, and performed the preflight characterization of the sensor array.^[121]

The robotic arm scooped up some soil, put it in one of four wet chemistry lab cells, where water was added, and while stirring, an array of electrochemical sensors measured a dozen dissolved ions such as sodium, magnesium, calcium, and sulfate that have leached out from the soil into the water. This provided information on the biological compatibility of the soil, both for possible indigenous microbes and for possible future Earth visitors.^[122]

Each of the four wet chemistry labs were identical, containing 26 chemical sensors and a temperature sensor. The polymer Ion Selective Electrodes (ISE) were able to determine the concentration of ions by measuring the change in electric potential across the ISE ion selective membrane as a function of concentration.^[81] Two gas sensing electrodes for oxygen and carbon dioxide worked on the same principle but a gas permeable membrane. A gold micro-electrode array was used for the Cyclic voltammetry and Anodic Stripping Voltammetry. Cyclic voltammetry is a method to study ions by applying a waveform of varying potential and measuring the current-voltage curve. Anodic Stripping Voltammetry first deposits the metal ions onto the gold electrode with an applied potential. After the potential is reversed, the current is measured while the metals are stripped off the electrode.{{citation needed|date=January 2018}}

Thermal and Electrical Conductivity Probe (TECP)

The MECA contains a Thermal and Electrical Conductivity Probe (TECP).^[117] The TECP, designed by Decagon Devices,^[117] has four probes that made the following measurements: Martian soil temperature, relative humidity, thermal conductivity, electrical conductivity, dielectric permittivity, wind speed, and atmospheric temperature.

Three of the four probes have tiny heating elements and temperature sensors inside them. One probe uses internal heating elements to send out a pulse of heat, recording the time the pulse is sent and monitoring the rate at which the heat is dissipated away from the probe. Adjacent needles sense when the heat pulse arrives. The speed that the heat travels away from the probe as well as the speed that it travels between probes allows scientists to measure thermal conductivity, specific heat (the ability of the regolith to conduct heat relative to its ability to store heat) and thermal diffusivity (the speed at which a thermal disturbance is propagated in the soil).^[123]

The probes also measured the dielectric permittivity and electrical conductivity, which can be used to calculate moisture and salinity of the regolith. Needles 1 and 2 work in conjunction to measure salts in the regolith, heat the soil to measure thermal properties (thermal conductivity, specific heat and thermal diffusivity) of the regolith, and measure soil temperature. Needles 3 and 4 measure liquid water in the regolith. Needle 4 is a reference thermometer for needles 1 and 2.^[123]

The TECP humidity sensor is a relative humidity sensor, so it must be coupled with a temperature sensor in order to measure absolute humidity. Both the relative humidity sensor and a temperature sensor are attached directly to the circuit board of the TECP and are, therefore, assumed to be at the same temperature.^[123]

Meteorological station

The Meteorological Station (MET) recorded the daily weather of Mars during the course of the Phoenix mission. It is equipped with a wind indicator and pressure and temperature sensors. The MET also contains a LIDAR (light detection and ranging) device for sampling the number of dust particles in the air. It was designed in Canada by Optech and MDA, supported by the Canadian Space Agency. A team headed by York University oversaw the science operations of the station. The York University team includes contributions from the University of Alberta, University of Aarhus (Denmark),^[124] Dalhousie University,^[125] Finnish Meteorological Institute,^[126] Optech, and the Geological Survey of Canada. Canadarm maker MacDonald Dettwiler and Associates (MDA) of Richmond, B.C. built the MET.^[127]

The surface wind velocity, pressure and temperatures were also monitored over the mission (from the tell-tale, pressure and temperature sensors) and show the evolution of the atmosphere with time. To measure dust and ice contribution to the atmosphere, a LIDAR was employed. The LIDAR collected information about the time-dependent structure of the planetary boundary layer by investigating the vertical distribution of dust, ice, fog and clouds in the local atmosphere.{{citation needed|date=January 2018}}

There are three temperature sensors (thermocouples) on a 1 m vertical mast (shown at left in its stowed position) at heights of approximately 250, 500 and 1000 mm above the lander deck. The sensors were referenced to a measurement of absolute temperature at the base of the mast. A pressure sensor built by Finnish Meteorological Institute is located in the Payload Electronics Box, which sits on the surface of the deck, and houses the acquisition electronics for the MET payload. The Pressure and Temperature sensors commenced operations on Sol 0 (May 26, 2008) and operate continuously, sampling once every 2 seconds.{{citation needed|date=January 2018}}

The Telltale is a joint Canadian/Danish instrument (right) which provides a coarse estimate of wind speed and direction. The speed is based on the amount of deflection from vertical that is observed, while the wind direction is provided by which way this deflection occurs. A mirror, located under the telltale, and a calibration "cross," above (as observed through the mirror) are employed to increase the accuracy of the measurement. Either the SSI or RAC cameras could make this measurement, though the former was typically used. Periodic observations both day and night aid in understanding the diurnal variability of wind at the Phoenix landing site.{{citation needed|date=January 2018}}

The wind speeds ranged from 11 km to 58 km per hour. The usual average speed was 36 km per hour.^[78]{{Dead link|date=January 2019|fix-attempted=yes}}

The vertical pointing LIDAR detects multiple types of backscattering (for example Rayleigh scattering and Mie Scattering), with the delay between laser pulse generation and the return of light scattered by atmospheric particles determining the altitude at which scattering occurs. Additional information was obtained from backscattered light at different wavelengths (colors), and the Phoenix system transmitted both 532 nm and 1064 nm. Such wavelength dependence may make it possible to discriminate between ice and dust, and serve as an indicator of the effective particle size.{{citation needed|date=January 2018}}

The Phoenix LIDAR laser is a passive Q-switched YAG laser with the dual wavelengths of 1064 nm and 532 nm. It operates at 100 Hz with a pulse width of 10 ns. The scattered light is received by two detectors that operate (green and IR) and the green signal is collected in both analog and photon counting modes.^[128][129]

The LIDAR was operated for the first time at noon on Sol 3 (May 29, 2008), recording the first surface extraterrestrial atmospheric profile. This first profile indicated well mixed dust in the first few kilometers of the atmosphere of Mars, where the planetary boundary layer was observed by a marked decrease in scattering signal. The contour plot (right) shows the amount of dust as a function of time and altitude, with warmer colors (red-orange) indicating more dust, and cooler colors (blues-green), indicating less dust. There is also an instrumentation effect of the laser warming up, causing the appearance of dust increasing with time. A Layer at 3.5 km can be observed in the plot, which could be extra dust, or less likely given the time of sol this was acquired, a low altitude ice cloud.{{citation needed|date=January 2018}}

The image on the left shows the Lidar laser operating on the surface of Mars, as observed by the SSI looking straight up, the laser is the vertical "line". Overhead dust can be seen both moving in the background, as well as passing through the laser beam in the form of bright sparkles.^[130] The fact that the beam appears to terminate is the result of the extremely small angle at which the SSI is observing the laser.{{citation needed|date=January 2018}}

The laser device discovered snow falling from clouds; this was not known before the mission.^[131] It was also determined that cirrus clouds formed in the area.^[132]

Phoenix DVD

Attached to the deck of the lander (next to the US flag) is the "Phoenix DVD",^[158] compiled by the Planetary Society. The disc contains Visions of Mars,^[133] a multimedia collection of literature and art about the Red Planet. Works include the text of H.G. Wells' War of the Worlds (and the radio broadcast by Orson Welles), Percival Lowell's Mars as the Abode of Life with a map of his proposed canals, Ray Bradbury's The Martian Chronicles, and Kim Stanley Robinson's Green Mars. There are also messages directly addressed to future Martian visitors or settlers from, among others, Carl Sagan and Arthur C. Clarke. In 2006, The Planetary Society collected a quarter of a million names submitted through the Internet and placed them on the disc, which claims, on the front, to be "the first library on Mars." This Phoenix DVD is similar to the Voyager Golden Record that was sent on the Voyager 1 and Voyager 2 missions.

The Phoenix DVD is made of a special silica glass^[134] designed to withstand the Martian environment, lasting for hundreds (if not thousands) of years on the surface while it awaits discoverers.

The text just below the center of the disk reads:

References

External links

LPL, LMSS, JPL and NASA links

• [https://www.webcitation.org/5W4NeGhno?url=http://phoenix.lpl.arizona.edu/ Phoenix mission lead home page]
• [https://web.archive.org/web/20111023024529/http://mars.jpl.nasa.gov/missions/present/phoenix.html Phoenix summary] at JPL
• [https://web.archive.org/web/20151019071127/http://solarsystem.nasa.gov/missions/profile.cfm?MCode=Phoenix Phoenix Profile] by NASA's Solar System Exploration
• NASA's Phoenix Photojournal
• NASA's Phoenix Analyst's Notebook for accessing mission data and documents
• NASA Archives of raw Phoenix mission images, most recent first
• [https://www.youtube.com/watch?v=tR91HkTZ9VY NASA TV broadcast of Phoenix landing] (YouTube copy of NASA broadcast from 8 minutes before until 2 minutes after touchdown)
• Blogs of the scientists and engineers of the Phoenix team from launch through the end of the mission.

Other links

• Phoenix status at Space Flight Now
• [https://web.archive.org/web/20120413154945/http://www.planetary.org/programs/projects/messages/vom_contents.html Complete List of Works on the Phoenix DVD]
• [https://web.archive.org/web/20120318214847/http://www.planetary.org/programs/projects/messages/vom_intro.html Written Introduction to the Visions of Mars Project]
• [https://web.archive.org/web/20160106143921/http://www.jumpcut.com/view/?id=E794095644A711DCBF54000423CF0184 Phoenix Mission Details Video]
• [https://archive.is/20080528165747/http://orionspace.net/mars/phoenix/22 may 2008-2.html Mars Express Support to Phoenix Landing] Includes animation of Phoenix descent and landing, plus KSC images of pre-flight processing and launch
• [https://web.archive.org/web/20120314230936/http://www.finda.com.au/story/2008/05/27/nasa-probe-sends-first-pictures-mars/ Article and news footage on the Phoenix landing]
• [https://web.archive.org/web/20120724075008/http://www.isset.ualberta.ca/what_we_do.html Canadian contribution at the University of Alberta]
• [https://gizmodo.com/5075490/nasas-phoenix-mars-lander-guest-blogging-on-giz Mars Phoenix Blog Page]
• Software Behind the Mars Phoenix Lander (Audio Interview)
• Color panorama of the landing site
• [https://web.archive.org/web/20110629115003/http://video.google.com/videoplay?docid=1679027418837385215&hl=en Phoenix EDL Reconstruction 1B] – 9 minute video simulation based on actual EDL data
• Phoenix Mars Lander wins 2009 John L. "Jack" Swigert, Jr., Award for Space Achievement{{dead link|date=August 2016|bot=medic}}{{cbignore|bot=medic}}

• [https://www.youtube.com/watch?v=1plIgTG9x-A Chris McKay: Results of the Phoenix Mission to Mars and Analog Sites on Earth]

• Fritillaria acmopetala
• Fritillaria adamantina
• Fritillaria aintabensis
• Fritillaria alba
• Fritillaria albidiflora
• Fritillaria altaica
• Fritillaria amoena
• Fritillaria anhuiensis
• Fritillaria arabica
• Fritillaria austroanhuiensis
• Fritillaria barbata
• Fritillaria biflora var. ineziana
• Fritillaria bolensis
• Fritillaria borealixingjiangensis
• Fritillaria brandegeei
• Fritillaria camschatscensis
• Fritillaria caussolensis
• Fritillaria chekiangensis
• Fritillaria chitralensis
• Fritillaria chuanbeiensis
• Fritillaria cirrhosa
• Fritillaria collicola
• Fritillaria contorta
• Fritillaria corona-imperialis
• Fritillaria crassicaulis