Mars Polar Lander
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The Mars Polar Lander was part of the Mars Surveyor '98 program, which consisted of two spacecraft launched separately, the Mars Climate Orbiter (formerly the Mars Surveyor '98 Orbiter) and the Mars Polar Lander (formerly the Mars Surveyor '98 Lander). Mars Polar Lander also conveyed the Deep Space 2 surface-penetrator mission to Mars. The two missions were designed to study the Martian weather, climate, and water and carbon dioxide budget, in order to understand the reservoirs, behavior, and atmospheric role of volatiles and to search for evidence of long-term and episodic climate changes.
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Loss of lander
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The last telemetry from Mars Polar Lander was sent just prior to atmospheric entry on December 3 1999. No further signals have been received from the lander. The cause of this loss of communication is not known.
According to the investigation that followed, the most likely cause of the failure of the mission was a software error that mistakenly identified the vibration caused by the deployment of the lander's legs as being caused by the vehicle touching down on the Martian surface, resulting in the vehicle's descent engines being cut off whilst it was still 40 meters above the surface, rather than on touchdown as planned. Another possible reason for failure was inadequate preheating of catalysis beds for the pulsing rocket thrusters: hydrazine fuel decomposes on the beds to make hot gases that throttle out the rocket nozzles; cold catalysis beds caused misfiring and instability in crash review tests.
Attempts were made in late 1999 and early 2000 to search for the remains of the Mars Polar Lander using images from the Mars Global Surveyor. These attempts were unsuccessful, but re-examination of the images in 2005 led to a tentative identification. This is described in the July 2005 issue of Sky and Telescope [1] (http://skyandtelescope.com/news/article_1509_1.asp). Higher resolution photos will be taken later in 2005 to attempt to confirm this. If this identification is correct, the relative positions of the spacecraft, its apparent rocket blast area, and parachute appear to confirm the software error theory of the mission's failure.
The Phoenix lander is planned to carry some instruments derived from those on Mars Polar Lander.
Scientific objectives
The Mars Polar Lander was to touch down on the southern polar layered terrain, between 73°S and 76°S, less than 1000 km from the south pole, near the edge of the carbon dioxide ice cap in Mars' late southern spring. The terrain appears to be composed of alternating layers of clean and dust-laden ice, and may represent a long-term record of the climate, as well as an important volatile reservoir. The mission had as its primary science objectives to:
- record local meteorological conditions near the martian south pole, including temperature, pressure, humidity, wind, surface frost, ground ice evolution, ice fogs, haze, and suspended dust
- analyze samples of the polar deposits for volatiles, particularly water and carbon dioxide
- dig trenches and image the interior to look for seasonal layers and analyze soil samples for water, ice, hydrates, and other aqueously deposited minerals
- image the regional and immediate landing site surroundings for evidence of climate changes and seasonal cycles
- obtain multi-spectral images of local regolith to determine soil types and composition.
These goals were to be accomplished using a number of scientific instruments, including a Mars Volatiles and Climate Surveyor (MVACS) instrument package which was comprised of a robotic arm and attached camera, mast-mounted surface stereo imager and meteorology package, and a gas analyzer. In addition, a Mars Descent Imager (MARDI) was planned to capture regional views from parachute deployment at about 8 km altitude down to the landing. The Russian Space Agency provided a laser ranger (LIDAR) package for the lander, which would be used to measure dust and haze in the Martian atmosphere. A miniature microphone was also be on board to record sounds on Mars. Attached to the lander spacecraft were a pair of small probes, the Deep Space 2 Mars Microprobes, which were to be deployed to fall and penetrate beneath the martian surface when the spacecraft reached Mars.
Spacecraft and subsystems
The Mars Polar Lander consists of a hexagonal base composed of aluminum honeycomb with composite graphite epoxy face sheets supported on three aluminum landing legs. The lander stands 1.06 m tall and approximately 3.6 m wide. The launch mass of the spacecraft is approximately 583 kg, including 64 kg of fuel, an 82-kg cruise stage, a 140-kg aeroshell/heatshield, and the two 3.5-kg microprobes. A thermally regulated interior component deck holds temperature-sensitive electronic components and batteries and the thermal control system. Two solar panels extend out from opposite sides of the base. Mounted on top of the base are the robotic arm, the stereo imager and mast, a UHF antenna, the LIDAR, the MVACS electronics, the meteorology mast, and the medium-gain dish antenna. The MARDI is mounted at the base of the lander, and the propellant tanks are affixed to the sides. During cruise, the lander is attached to the cruise stage and enclosed in the 2.4-m diameter aeroshell.
The spacecraft was three-axis stabilized during cruise using star cameras and sun sensors in conjunction with inertial measurement units. Four hydrazine cruise reaction engine modules, each consisting of one 5-lbf (22-N) trajectory correction maneuver thruster and one canted 1-lbf (4-N) reaction control system thruster, provided attitude control. The descent and landing propulsion system consists of three groups of four pulse modulated 266-N hydrazine engines. Control and knowledge for descent and landing is provided by a four-beam Doppler radar system and an AACS subsystem. The hydrazine is stored in two diaphragm tanks with a total capacity of 64 kg for both cruise and descent systems.
Communications between Earth and the spacecraft during cruise to Mars were via X band using two solid state power amplifiers and a fixed medium-gain antenna mounted on the cruise stage and backed up by a receive-only low-gain antenna. During surface operations communications (downlink and uplink) would be via the UHF antenna on the lander to the Mars Climate Orbiter, which will function as a relay to Earth. Eight to ten relay passes over the lander would have been available from the orbiter each day, but the number of communications sessions would be limited by power demands. Uplink-only communications to Earth were to be provided by the medium-gain DTE (direct to Earth) two-axis articulated antenna.
Power was provided during cruise phase by two gallium arsenide solar array wings with a total area of 3.1 m² attached to the cruise stage. After landing, two gallium arsenide solar array wings with a total area of 2.9 m² would have been deployed. Power is stored in 16 A·h nickel metal hydride common pressure vessel batteries for peak load operations and night time heating. The payload is allocated 25 W of continuous power when operating.
Mission profile
Mars Polar Lander and the attached Deep Space 2 probes were launched on a Delta 7425 (a Delta II Lite launch vehicle with four strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) which placed them into a low-Earth parking orbit. The third stage fired for 88 seconds at 20:57 UT 3 January 1999 to put the spacecraft into a Mars transfer trajectory and the spacecraft and third stage separated at 21:03 UT. Trajectory correction maneuvers were performed on 21 January, 15 March, 1 September, 30 October, and 30 November 1999.
After an 11-month hyperbolic transfer cruise, the Mars Polar Lander reached Mars on 3 December 1999. A final 30 minute tracking session begins at 12:45 UT (7:45 a.m. EST) and was used to determine if a final thruster correction was necessary. Final contact to retrieve data on the status of the propulsion system was made from 19:45 UT to 20:00 UT. At 20:04, 6 minutes before atmospheric entry, an 80 second thruster firing was to turn the craft to its entry orientation. The Star 48 upper cruise stage was to be jettisoned at about 20:05 UT, and about 18 seconds later the microprobes were to be dropped from the cruise stage into the martian atmosphere (also targeted at the southern polar layered terrain). The lander was to make a direct entry into Mars' atmosphere at 6.8 km/s at about 20:10 UT (3:10 p.m. EST). Due to lack of communication, it is not known at this time whether all these steps following final contact were executed, nor whether any of the descent plan described below took place as designed.
Initial deceleration would be simple aerobraking using the 2.4 m ablation heat shield. The maximum time from atmospheric entry to landing would be 4 minutes 33 seconds. The inertial measurement unit would estimate the velocity throughout the entry and descent phase and the thrusters would keep the craft aligned. At an altitude of about 7.3 km at 500 m/s the parachute would be deployed by a mortar followed by heat shield separation. Just before heat shield separation, the descent imager (MARDI) would turn on. The landing legs would be deployed 70 to 100 seconds before landing and the descent engines warmed up with short pulses. Then the parachute would be jettisoned and the descent engines fired, regulated by the spacecraft control system and the Doppler radar. The backshell would separate from the lander at about 1.4 km altitude at 80 m/s and the descent engines turned on to slow the descent and turn the flight path to vertical.
At 12 meters altitude the 2.4 m/s terminal descent phase was to begin. Engine shutoff would occur when one of the landing legs touched the ground. The horizontal landing velocity would be less than 2.4 m/s vertical and 1 m/s horizontal. The orientation of the lander is controlled by the AACS subsystem to maximize solar array efficiency and minimize obstruction of the DTE antenna. The lander would have touched down at 20:15 UT Earth received time (3:15 p.m. EST) in the late southern spring season, during which the Sun will always be above the horizon at the landing site. The other times listed above are also Earth received times, light travel time from Mars at that point was approximately 14 minutes.
Immediately after landing the solar panels were to be deployed. The first signal from the lander was to reach Earth at 20:39 UT (3:39 p.m. EST), but was never received. This was to be the start of a 45 minute communications session. After this session the lander was to recharge its batteries for about 6 hours. On 4 December at 04:30 UT (11:30 p.m. EST December 3) a communications session was to begin which would have lasted about 2¼ hours. This session would have included images, including pictures from the Mars Descent Imager, but again no transmission was received. The first sounds from the Mars Microphone were to be released as early as 4 December and the first robot arm dig occur on 7 December. Science experiments would continue over the 90 day primary mission, with an extended mission to follow based on lander performance.
Related articles
- Exploration of Mars
- Space exploration
- Unmanned space missions
- Phoenix lander, scheduled to land in 2008 and based on Mars Polar Lander hardware