Mars Polar Lander

Mars Polar Lander

Artist's depiction of the Mars Polar Lander on the Martian surface
Names	Mars Surveyor '98 Lander
Mission type	Mars lander
Operator	NASA / JPL
COSPAR ID	1999-001A
SATCAT no.	25605
Website	science.nasa.gov
Mission duration	334 days Mission failure
Spacecraft properties
Manufacturer	Martin Marietta
Launch mass	583 kg
Power	200 W solar array and NiH2 battery
Start of mission
Launch date	20:21:10, January 3, 1999 (UTC) (1999-01-03T20:21:10Z)
Rocket	Delta II 7425-9.5 D-265
Launch site	Cape Canaveral Air Force Station SLC-17A
Contractor	Boeing
End of mission
Disposal	Communication failure after landing
Declared	January 17, 2000 (2000-01-17)
Last contact	20:00, December 3, 1999 (UTC) (1999-12-03T20:00Z)
Mars impact (failed landing)
Impact date	~20:15 UTC ERT, December 3, 1999
Impact site	Ultimi Scopuli, 76°S 195°W (projected)
Mars impactor
Spacecraft component	Deep Space 2
Mars Surveyor 98 mission logo Mars Exploration Program Mars Surveyor '98

The Mars Polar Lander, also known as the Mars Surveyor '98 Lander, was a 290-kilogram uncrewed spacecraft lander launched by NASA on January 3, 1999, to study the soil and climate of Planum Australe, a region near the south pole on Mars. It formed part of the Mars Surveyor '98 mission. On December 3, 1999, however, after the descent phase was expected to be complete, the lander failed to reestablish communication with Earth. A post-mortem analysis determined the most likely cause of the mishap was premature termination of the engine firing prior to the lander touching the surface, causing it to strike the planet at a high velocity.

The total cost of the Mars Polar Lander was US$165 million. Spacecraft development cost US$110 million, launch was estimated at US$45 million, and mission operations at US$10 million.

Mission background

History

As part of the Mars Surveyor '98 mission, a lander was sought as a way to gather climate data from the ground in conjunction with an orbiter. NASA suspected that a large quantity of frozen water may exist under a thin layer of dust at the south pole. In planning the Mars Polar Lander, the potential water content in the Martian south pole was the strongest determining factor for choosing a landing location. A CD-ROM containing the names of one million children from around the world was placed on board the spacecraft as part of the "Send Your Name to Mars" program designed to encourage interest in the space program among children.

The primary objectives of the mission were to:

• land on the layered terrain in the south polar region of Mars;
• search for evidence related to ancient climates and more recent periodic climate change;
• give a picture of the current climate and seasonal change at high latitudes and, in particular, the exchange of water vapor between the atmosphere and ground;
• search for near-surface ground ice in the polar regions, and analyze the soil for physically and chemically bound carbon dioxide and water; and
• study surface morphology (forms and structures), geology, topography, and weather of the landing site.

Deep Space 2 probes

Main article: Deep Space 2

The Mars Polar Lander carried two small, identical impactor probes known as "Deep Space 2 A and B". The probes were intended to strike the surface with a high velocity at approximately 73°S 210°W to penetrate the Martian soil and study the subsurface composition up to a meter in depth. However, after entering the Martian atmosphere, attempts to contact the probes failed.

Deep Space 2 was funded by the New Millennium Program, and their development costs was US$28 million.

Spacecraft design

The spacecraft measured 3.6 meters wide and 1.06 meters tall with the legs and solar arrays fully deployed. The base was primarily constructed with an aluminum honeycomb deck, composite graphite-epoxy sheets forming the edge, and three aluminum legs. During landing, the legs were to deploy from stowed position with compression springs and absorb the force of the landing with crushable aluminum honeycomb inserts in each leg. On the deck of the lander, a small thermal Faraday cage enclosure housed the computer, power distribution electronics and batteries, telecommunication electronics, and the capillary pump loop heat pipe (LHP) components, which maintained operable temperature. Each of these components included redundant units in the event that one may fail.

Attitude control and propulsion

While traveling to Mars, the cruise stage was three-axis stabilized with four hydrazine monopropellant reaction engine modules, each including a 22-newton trajectory correction maneuver thruster for propulsion and a 4-newton reaction control system thruster for attitude control (orientation). Orientation of the spacecraft was performed using redundant Sun sensors, star trackers, and inertial measurement units.

During descent, the lander used three clusters of pulse-modulated engines, each containing four 266-newton hydrazine monopropellant thrusters. Altitude during landing was measured by a Doppler radar system, and an attitude and articulation control subsystem (AACS) controlled the attitude to ensure the spacecraft landed at the optimal azimuth to maximize solar collection and telecommunication with the lander.

The lander was launched with two hydrazine tanks containing 64 kilograms of propellant and pressurized with helium. Each spherical tank was located at the underside of the lander and provided propellant during the cruise and descent stages.

Communications

During the cruise stage, communications with the spacecraft were conducted over the X band using a medium-gain, horn-shaped antenna and redundant solid state power amplifiers. For contingency measures, a low-gain omnidirectional antenna was also included.

The lander was originally intended to communicate data through the failed Mars Climate Orbiter via the UHF antenna. With the orbiter lost on September 23, 1999, the lander would still be able to communicate directly to the NASA Deep Space Network through the Direct-To-Earth (DTE) link, an X band, steerable, medium-gain, parabolic antenna located on the deck. Alternatively, Mars Global Surveyor could be used as a relay using the UHF antenna at multiple times each Martian day. However the Deep Space Network could only receive data from, and not send commands to, the lander using this method. The direct-to-Earth medium-gain antenna provided a 12.6-kbit/s return channel, and the UHF relay path provided a 128-kbit/s return channel. Communications with the spacecraft would be limited to one-hour events, constrained by heat-buildup that would occur in the amplifiers. The number of communication events would also be constrained by power limitations.

Power

The cruise stage included two gallium arsenide solar arrays to power the radio system and maintain power to the batteries in the lander, which kept certain electronics warm.

After descending to the surface, the lander was to deploy two 3.6-meter-wide gallium arsenide solar arrays, located on either side of the spacecraft. Another two auxiliary solar arrays were located on the side to provide additional power for a total of an expected 200 watts and approximately eight to nine hours of operating time per day.

While the Sun would not have set below the horizon during the primary mission, too little light would have reached the solar arrays to remain warm enough for certain electronics to continue functioning. To avoid this problem, a 16-ampere-hour nickel–hydrogen battery was included to be recharged during the day and to power the heater for the thermal enclosure at night. This solution also was expected to limit the life of the lander. As the Martian days would grow colder in late summer, too little power would be supplied to the heater to avoid freezing, resulting in the battery also freezing and signaling the end of the operating life for the lander.

Scientific instruments

Scientific instruments

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  Mars Descent Imager
• 
  Stereo Surface Imager
• 
  LIDAR
• 
  Robotic Arm
• 
  Robotic Arm Camera
• 
  Meteorological Package
• 
  Thermal and Evolved Gas Analyzer
• 
  Mars Microphone

Images of the spacecraft

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  Annotated diagram of the Mars Polar Lander spacecraft
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  The spacecraft in stowed position just prior to encapsulation
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  Testing performed at the Spacecraft Assembly and Encapsulation Facility
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  The Mars Polar Lander entry capsule, just prior to being mounted to the Star 48 upper stage

Mars Descent Imager (MARDI)

Mounted to the bottom of the lander, the camera was intended to capture 30 images as the spacecraft descended to the surface. The images acquired would be used to provide geographic and geologic context to the landing area.

Surface Stereo Imager (SSI)

Using a pair of charge-coupled devices (CCDs), the stereo panoramic camera was mounted to a one-meter-tall mast and would aid in the thermal evolved gas analyzer in determining areas of interest for the robotic arm. In addition, the camera would be used to estimate the column density of atmospheric dust, the optical depth of aerosols, and slant column abundances of water vapor using narrow-band imaging of the Sun.

Light Detection and Ranging (LIDAR)

The laser sounding instrument was intended to detect and characterize aerosols in the atmosphere up to three kilometers above the lander. The instrument operated in two modes: active mode, using an included laser diode, and acoustic mode, using the Sun as the light source for the sensor. In active mode, the laser sounder was to emit 100-nanosecond pulses at a wavelength of 0.88-micrometer into the atmosphere, and then record the duration of time to detect the light scattered by aerosols. The duration of time required for the light to return could then be used to determine the abundance of ice, dust and other aerosols in the region. In acoustic mode, the instrument measures the brightness of the sky as lit by the Sun and records the scattering of light as it passes to the sensor.

Robotic Arm (RA)

Located on the front of the lander, the robotic arm was a meter-long aluminum tube with an elbow joint and an articulated scoop attached to the end. The scoop was intended to be used to dig into the soil in the direct vicinity of the lander. The soil could then be analyzed in the scoop with the robotic arm camera or transferred into the thermal evolved gas analyzer.

Robotic Arm Camera (RAC)

Located on the robotic arm, the charge coupled camera included two red, two green, and four blue lamps to illuminate soil samples for analysis.

Meteorological Package (MET)

Several instruments related to sensing and recording weather patterns, were included in the package. Wind, temperature, pressure, and humidity sensors were located on the robotic arm and two deployable masts: a 1.2-meter main mast, located on top of the lander, and a 0.9-meter secondary submast that would deploy downward to acquire measurements close to the ground.

Thermal and Evolved Gas Analyzer (TEGA)

The instrument was intended to measure abundances of water, water ice, adsorbed carbon dioxide, oxygen, and volatile-bearing minerals in surface and subsurface soil samples collected and transferred by the robotic arm. Materials placed onto a grate inside one of the eight ovens, would be heated and vaporized at 1,000 °C. The evolved gas analyzer would then record measurements using a spectrometer and an electrochemical cell. For calibration, an empty oven would also be heated during this process for differential scanning calorimetry. The difference in the energy required to heat each oven would then indicate concentrations of water ice and other minerals containing water or carbon dioxide.

Mars Microphone

The microphone was intended to be the first instrument to record sounds on another planet. Primarily composed of a microphone generally used with hearing aids, the instrument was expected to record sounds of blowing dust, electrical discharges and the sounds of the operating spacecraft in either 2.6-second or 10.6-second, 12-bit samples. The microphone was built using off-the-shelf parts including a Sensory, Inc. RSC-164 integrated circuit typically used in speech-recognition devices.

Mission profile

Timeline of observations

Date Event 1999-01-03 Spacecraft launched at 20:21:10 UTC 1999-12-03   Begin atmospheric entry and landing Time Event   1999-12-03 14:39:00 Turn spacecraft away from Earth for final stellar data acquisition, signal loss from spacecraft 14:42:00 Turn on heaters on descent engine 17:34:00 Turn on heaters on descent camera (MARDI) 18:49:00 Turn spacecraft back to Earth point, acquire spacecraft signal, acquire health & status 19:21:00 Begin Entry, Descent, Landing sequence 19:26:00 Pyros fire to pressurize helium tank 20:00:00 Guidance system initialization (2210 km, 6.2 km/s) 20:03:00 Turn spacecraft to entry attitude, loss of signal. We won't hear from the spacecraft again until after landing (1426 km, 6.4 km/s) 20:05:00 Cruise ring/Deep Space 2 probes separate from lander (959 km, 6.6 km/s) 20:10:00 Atmospheric entry (142 km, 6.9 km/s) 20:11:00 Descent radar powered on 20:12:00 MARDI instrument powered on 20:13:00 Parachute deployed (9.0 km, 496 m/s) 20:13:00 Descent imaging begins, heatshield jettisoned (8.0 km, 286 m/s) 20:13:00 Lander legs deployed, descent radar activated 20:14 Radar ground acquisition, altitude (2.438 km, 80 m/s) 20:14:00 Lander separates from backshell, powered descent begins (1.628 km, 78 m/s) 20:14:00 Radar ground acquisition, speed & direction (1.425 km, 82 m/s) 20:14 Gravity turn begins (1.394 km, 83 m/s) 20:14:00 Roll to landed orientation (1.307 km, 79 m/s) 20:14:00 Radar cutoff (40 meters, 13 m/s) 20:15:00 Constant Velocity Phase (12 meters, 2.4 m/s) 20:15:00 Touchdown. Mars Polar Lander on Mars surface. 20:20:00 Lander unfolds solar panels 20:20:00 Medium gain antenna pointed at Earth 20:39:00 Lander begins 1st transmission to Earth (45 minutes). Sends health & status, meteorology & 1 b/w image 21:24:00 Lander ends transmission to Earth 21:45:00 Lander powers down to sleep so it can recharge 22:10:00 Start of 1 hour backup downlink opportunity (if spacecraft went into safemode during landing) 1999-12-04 02:50:00 Lander wakes up, receives instructions from Earth 03:25:00 Begin DS2 microprobe data reception via Mars Global Surveyor relay (15 minute transmission) 04:25:00 2.5 hour downlink begins, could include lander and descent images 06:25:00 Lander shuts itself down until next day. End of Sol 0 activities. Items in red were planned events. 1999-12-03 Failure to regain communication after landing Time Event   1999-12-03 20:39:00 First communication from lander missed 22:04:00 Second communication from lander missed 1999-12-04 04:08:00 Third communication from lander missed 1999-12-05 04:30:00 Fourth communication from lander missed 18:50:00 First attempt to detect automatic fail-safe UHF communication to Mars Global Surveyor failed 1999-12-06 06:10:00 Second attempt to detect automatic fail-safe UHF communication to Mars Global Surveyor failed 1999-12-07 08:20:00 Third attempt to detect automatic fail-safe UHF communication to Mars Global Surveyor failed 1999-12-08 Radio sweeps of the surface by the Deep Space Network failed. Repeat of prior procedures to exhaust all possibilities of regaining contact. 2000-01-17 Mission declared a loss. No further attempts to contact.

Launch and trajectory

Mars Polar Lander was launched on January 3, 1999, at 20:21:10 UTC by the National Aeronautics and Space Administration from Space Launch Complex 17B at the Cape Canaveral Air Force Station in Florida, aboard a Delta II 7425–9.5 launch vehicle. The complete burn sequence lasted for 47.7 minutes after a Thiokol Star 48B solid-fuel third stage booster placed the spacecraft into an 11-month, Mars transfer trajectory at a final velocity of 6.884 kilometers per second with respect to Mars. During cruise, the spacecraft was stowed inside an aeroshell capsule and a segment known as the cruise stage provided power and communications with Earth.

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  Launch configuration diagram.
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  Launch photo of Mars Polar Lander aboard a Delta II launch vehicle.
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  Diagram of the interplanetary trajectory of Mars Polar Lander.

Landing zone

The target landing zone was a region near the south pole of Mars, called Ultimi Scopuli, because it featured a large number of scopuli (lobate or irregular scarps).

Landing attempt

Further information: Exploration of Mars

Cruise configuration

Landing procedure

Landing region

Mars Polar Lander entered the Martian atmosphere with an aeroshell for protection from atmospheric friction.

On December 3, 1999, Mars Polar Lander arrived at Mars and mission operators began preparations for landing. At 14:39:00 UTC, the cruise stage was jettisoned, which began a planned communication dropout to last until the spacecraft had touched down on the surface. Six minutes prior to atmospheric entry, a programmed 80-second thruster firing turned the spacecraft to the proper entry orientation, with the heat shield positioned to absorb the 1,650 °C heat that would be generated as the descent capsule passed through the atmosphere.

Traveling at 6.9 kilometers per second, the entry capsule entered the Martian atmosphere at 20:10:00 UTC, and was expected to land in the vicinity of 76°S 195°W in a region known as Planum Australe. Reestablishment of communication was anticipated for 20:39:00 UTC, after landing. However communication was not reestablished, and the lander was declared lost.

On May 25, 2008, the Phoenix lander arrived at Mars, and has subsequently completed most of the objectives of the Mars Polar Lander, carrying several of the same or derivative instruments.

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Interactive image map of the global topography of Mars, overlaid with the position of Martian rovers and landers. Coloring of the base map indicates relative elevations of Martian surface.

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(See also: Mars map; Mars Memorials list)

Beagle 2

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Intended operations

Traveling at approximately 6.9 kilometers/second and 125 kilometers above the surface, the spacecraft entered the atmosphere and was initially decelerated by using a 2.4 meter ablation heat shield, located on the bottom of the entry body, to aerobrake through 116 kilometers of the atmosphere. Three minutes after entry, the spacecraft had slowed to 496 meters per second, signaling an 8.4-meter polyester parachute to deploy from a mortar, followed immediately by heat shield separation and MARDI powering on while 8.8 kilometers above the surface. The parachute further slowed the speed of the spacecraft to 85 meters per second when the ground radar began tracking surface features to detect the best possible landing location and determine the vertical speed via the Doppler effect for thrust control.

When the spacecraft had slowed to 80 meters per second, one minute after parachute deployment, the lander separated from the backshell and began a powered descent at 1.3 kilometers aloft. Vertical speed was intended to drop to 2.4 meters per second at 12 m height and then be constant until touchdown. Below 40 meters, the radar would become unreliable by raised dust and was switched off already at that height; for the final seconds, the thrust would be controlled by inertial sensors. A function to switch off the thrust immediately at touchdown was also armed at 40 meters. Touchdown was expected at 20:01 UTC, given as 20:15 ″Earth-received time″.

Lander operations were to begin five minutes after touchdown, first unfolding the stowed solar arrays, followed by orienting the medium-gain, direct-to-Earth antenna to allow for the first communication with the NASA Deep Space Network. A 45-minute transmission was to be broadcast to Earth containing 30 landing images acquired by MARDI. Arrival of that signal of a successful landing was expected at 20:39 UTC. The lander would then power down for six hours to allow the batteries to charge. On the following days, the spacecraft instruments would be checked by operators and science experiments were to begin on December 7 and last for at least the following 90 Martian Sols, with the possibility of an extended mission.

Loss of communications

On December 3, 1999, at 14:39:00 UTC, the last telemetry from Mars Polar Lander was sent, just prior to cruise stage separation and the subsequent atmospheric entry. No further signals were received from the spacecraft. Attempts were made by the Mars Global Surveyor to photograph the area in which the lander was believed to be. An object was visible and believed to be the lander. However, subsequent imaging in September 2005 resulted in the identified object being ruled out. Mars Polar Lander remains lost.

The cause of the communication loss is not known. However, the Failure Review Board concluded that the most likely cause of the mishap was a software error that incorrectly identified vibrations, caused by the deployment of the stowed legs, as surface touchdown. The resulting action by the spacecraft was the shutdown of the descent engines, while still likely 40 meters above the surface. Although it was known that leg deployment could create the false indication, the software's design instructions did not account for that eventuality.

In addition to the premature shutdown of the descent engines, the Failure Review Board also assessed other potential modes of failure. Lacking substantial evidence for the mode of failure, the following possibilities could not be excluded:

• surface conditions exceed landing design capabilities;
• loss of control due to dynamic effects;
• landing site not survivable;
• backshell/parachute contacts lander;
• loss of control due to center-of-mass offset; or
• heatshield fails due to micrometeoroid impact.

The failure of the Mars Polar Lander took place two and a half months after the loss of the Mars Climate Orbiter. Inadequate funding and poor management have been cited as underlying causes of the failures. According to Thomas Young, chairman of the Mars Program Independent Assessment Team, the program "was under funded by at least 30%."

Quoted from the report

"A magnetic sensor is provided in each of the three landing legs to sense touchdown when the lander contacts the surface, initiating the shutdown of the descent engines. Data from MPL engineering development unit deployment tests, MPL flight unit deployment tests, and Mars 2001 deployment tests showed that a spurious touchdown indication occurs in the Hall Effect touchdown sensor during landing leg deployment (while the lander is connected to the parachute). The software logic accepts this transient signal as a valid touchdown event if it persists for two consecutive readings of the sensor. The tests showed that most of the transient signals at leg deployment are indeed long enough to be accepted as valid events, therefore, it is almost a certainty that at least one of the three would have generated a spurious touchdown indication that the software accepted as valid. The software—intended to ignore touchdown indications prior to the enabling of the touchdown sensing logic—was not properly implemented, and the spurious touchdown indication was retained. The touchdown sensing logic is enabled at 40 meters altitude, and the software would have issued a descent engine thrust termination at this time in response to a (spurious) touchdown indication. At 40 meters altitude, the lander has a velocity of approximately 13 meters per second, which, in the absence of thrust, is accelerated by Mars gravity to a surface impact velocity of approximately 22 meters per second (the nominal touchdown velocity is 2.4 meters per second). At this impact velocity, the lander could not have survived."

Planum Australe, which served as the exploration target for the lander and the two Deep Space 2 probes, would in later years be explored by European Space Agency's MARSIS radar, which examined and analyzed the site from Mars' orbit.

See also

• Mars Surveyor 2001, similar design lander, mission cancelled. Lander used for Phoenix.
• Phoenix lander, 2008
• Exploration of Mars
• ExoMars rover
• List of missions to Mars
• Mars Science Laboratory rover

• List of software bugs

Further reading

• Michael C. Malin (July 2005). "Hidden in Plain Sight: Finding Martian Landers". Sky and Telescope. 110 (7): 42–46. Bibcode:2005S&T...110a..42M. ISSN 0037-6604.