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Mars Polar Lander Timeline


launch.jpg Jan 3, 1999: Lander Launched. The lander's first scheduled launch opportunity was at 3:21 PM EST, Jan 3, 1999. Subsequent launch opportunities would have occurred at approximately 3 pm each day of the primary launch window. The Delta rocket's four solid rocket motors separated from the vehicle at T+66 seconds and fell into the Atlantic Ocean. The Delta's first stage separated at T+4 minutes, 32 seconds. The Delta's second stage separated at T+35 minutes.

third_stage.jpg Jan 3, 1999: Lander Leaves Earth. At T+36 minutes, the lander's third stage fired for a 88 seconds, providing the lander with enough velocity to leave Earth orbit and set it on a course to rendezvous with Mars. At T+47 minutes after liftoff, the lander separated from the third stage. At approximately T+53 minutes, the lander deployed its solar panels and radioed back to Earth that all systems were go and it was safely on its way to Mars.

cruise.jpg Jan 3, 1999 -
Dec 3, 1999: Lander Interplanetary Cruise.
The lander is cruising to Mars powered by a cruise stage that provides maneuvering capability and solar power. During the 11-month cruise, a series of trajectory correction maneuvers will be performed to steer the lander towards its target entry point at the top of the Martian atmosphere.

msop.jpg Feb 3, 1999: New Management. Thirty days after launch, JPL's Mars Surveyor Operations Project (MSOP) formally took over the operation of the Mars Polar Lander. MSOP has responsibiltiy for operating all the spacecraft in the Mars Surveyor Program, which includes the Mars Global Surveyor (MGS) orbiter, the Mars Climate Orbiter (MCO) and the Mars Polar Lander (MPL). Richard A. Cook is the MSOP project manager. Sam Thurman is the Mars Polar Lander Mission Director.

landing_site.jpg Aug 24, 1999: Final Landing Site Selected. The final landing site for the Mars polar lander was selected on August 24, 1999. By this time, the Mars Global Surveyor Orbiter had achieved its final mapping orbit and obtained new photographic and topographic observations of the landing site region. These data augmented the existing data acquired by the Mariner-9 orbiter in 1971, the Viking orbiters in 1976-1982, and the Mars Global Surveyor orbiter in 1998. The final decision regarding the MPL landing site was made by NASA headquarters based on advice from MSOP and independent reviews by the scientific and engineering communities.

cruise2.jpg December 2, 1999: Final Trajectory Correction. Less than three days before landing, one, or possibly two final trajectory correction maneuvers will be performed to steer the lander as close as possible to its final landing site. The lander's error ellipse is expected to be 120 km long by 10 km wide.

jettison.jpg Dec 3, 1999: Cruise Stage Jettisoned. Ten minutes before landing, the lander's cruise stage will be jettisoned and the lander's heat shield will be oriented for atmospheric entry. For a successful landing, the lander must intercept the atmosphere within 1 degree of its nominal entry angle. Too shallow an entry angle will cause the lander to skip off the atmosphere back into space. Too steep an entry angle will cause the lander to burn up in the atmosphere.

ds2b.jpg Dec 3, 1999 Mars Microprobes Released. Prior to entry, two 3.5 kg penetrators provided by JPL's New Millenium Deep Space Project will be released. The probes will enter the atmosphere and impact the Martian surface approximately 100 km uprange of the lander. Each probe will consist of a forebody which will penetrate up to meter into the Martian soil, and an aftbody which will remain on the surface. The forebody contains accelleration sensors and a water experiment which will collect a small quantity of soil and heat it to release water. The aftbody contains electronics and an antenna to be used for one-way communication whith the Mars Global Surveyor Orbiter. The probes will be powered by non-rechargable batteries and are expected to survive for two days. Sarah Gavit of JPL is the New Millenium Microprobe program manager and Suzanne Smrekar of JPL is the New Millenium project scientist.

entry.jpg Dec 3, 1999: Atmospheric Entry. The lander will begin its encouter with the Martian atmosphere approximately 4 minutes and 33 seconds before landing. During this period, the lander will use the friction produced by the Martian atmosphere to decellerate rapidly from its initial velocity of 6.8 km per second. The temperature of the lander's heat shield will increase to 1650 °C and it will experience peak G forces of 12 times Earth's gravity.

parachute.jpg Dec 3, 1999: Parachute Opens. Approximately two minutes before landing, the lander's parachute will be deployed. By this time, the lander will be traveling at a speed of 493 meters per second and will be 7.3 km above the Martian surface.

mardi_simulation.jpg Dec 3, 1999: MARDI Acquires Descent Images. Ten seconds after the parachute opens, the Mars Descent Imager (MARDI) will begin taking images. The first image will be acquired 0.3 seconds before the heat-sheild is jettisoned. MARDI will take approximately 10 images of the Martian surface at increasing resolution as the lander descends. The fields of view of the MARDI images will decrease from 8 km across to 9 meters across just before landing.

on_bridal.jpg Dec 3, 1999: Lander Legs Deployed. Approximately 100 seconds before landing, the lander legs will be extended and a landing radar will be activated to determine the distance to the Martian surface.

touchdown.jpg Dec 3, 1999: Touchdown. Approximately 1.4 km above the surface, the lander's parachute and backshell will be separated and the lander will use a set of thrusters to perform a 35-second controlled descent to the Martian surface. Inertial gyros and accellerometers will be used to orient the lander during its final descent. The lander will land facing the best direction for its solar panels to generate power once it lands. The lander will not be in radio contact with the Earth at any point during the entry, descent and landing phase of the mission.

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