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Solar System Mars History of Space Exploration Mars Global Surveyor
Mars Global Surveyor
Mars Global Surveyor
NASA Mars Orbiter
Courtesy of NASA's National Space Science Data Center


Launch Date/Time: 1996-11-07 at 17:00:50 UTC
On-orbit dry mass: 1030.50 kg
Nominal Power Output: 980.00 W


Description

The Mars Global Surveyor (MGS) is designed to orbit Mars over a two year period and collect data on the surface morphology, topography, composition, gravity, atmospheric dynamics, and magnetic field. This data will be used to investigate the surface processes, geology, distribution of material, internal properties, evolution of the magnetic field, and the weather and climate of Mars.

Spacecraft and Subsystems

The spacecraft itself is a rectangular box approximately 1.17 x 1.17 x 1.7 meters in size, made up of two parts, the equipment module and the propulsion module. All instruments except the magnetometer are stored on the nadir equipment deck, on one of the 1.17 x 1.17 meter surfaces. This is the top of the equipment module, which is 0.735 m high. The main thruster and propulsion tanks are on the opposite side from the instruments, on the propulsion module, which is approximately 1 meter high. Two solar panels, each 3.5 x 1.9 m in size, extend out from opposite sides of the craft. A 1.5 meter diameter parabolic high gain dish antenna is mounted on an adjacent side, and attached to a 2 meter boom, which is extended for mapping operations so the antenna is held away from the body of the spacecraft.

The spacecraft is three-axis stabilized with no scan platform. The main 596 N thruster wil use hydrazine and N2O4 propellant. Control is through 12 4.45 N hydrazine thrusters, mounted in four groups of three (two aft facing and one roll control thruster). The initial propellant load was 216.5 kg of hydrazine and 144 kg of N2O4. Four solar array panels (2 GaAs, 2 SI) provide 980 W of power to the spacecraft. Energy is stored in two 20 Amp-hr nickel hydrogen batteries, and supplied at 28 V DC. Temperature control is primarily passive with multilayer insulation, thermal radiators, and louvers, augmented by electrical heaters. Communications is achieved via the deep space network using the high gain antenna and two low gain antennas, one mounted on the high gain antenna and one on the equipment module. Uplink is in the X-band, downlink in the X and Ka bands. Minimum downlink rate is 21.33 kbps, 2 kbps engineering data downlink, and 10 bps emergency downlink.

The instruments on the nadir equipment deck consist of a camera, thermal emission spectrometer, laser altimeter, and a radio transmission relay. A magnetometer/electron reflectometer sensor is attached to the end of each solar array, and an ultra-stable oscillator is used for tracking and gravity determination. An 8086 processor is used for the payload data subsystem, and 1750A processors for the standard controls processor and the engineering data formatter. Data is stored on four 0.75 Gb solid state recorders.

Mission Profile

After launch on a Delta 7925 (a Delta II Lite launch vehicle with nine strap-on solid-rocket boosters and a Star 48 (PAM-D) third stage) and a 10 month cruise phase, the Mars Global Surveyor was inserted into an elliptical capture orbit at 01:17 UT 12 September 1997. Over the next four months, it was intended that aerobraking maneuvers and thrusters would be used to lower the orbit to the final circular mapping orbit. However, one of the solar panels failed to latch properly when it was deployed and subsequently showed unexpected motion and moved past its fully deployed position when aerobraking began (thought to be due to the fracture of a damper arm and subsequent structural damage). A new aerobraking schedule was employed, which involved slower aerobraking putting less pressure on the solar panels through April 1998, at which time an 11.6 hour science phasing orbit with a 171 km periapsis was achieved and aerobraking was halted. After a 5 month hiatus, aerobraking was resumed on 23 September 1998. Science observations were made periodically during these maneuvers.

After aerobraking ended in February 1999, MGS was in a 118 minute circular polar science mapping orbit with an index altitude of 378 km. The orbit is sun-synchronous (2 a.m./2 p.m.) and maps over the 2 p.m. crossing from south to north (instead of north to south as originally planned). The orbit has a 7 day near-repeat cycle so Mars will be mapped in 26 day cycles. Science mapping began in mid-March 1999, which was summer in the northern hemisphere on Mars. The primary mission will last one martian year (687 Earth days) until January, 2001. After this time, the orbiter will act as a relay until January 2003 in support of the other missions of the Mars Surveyor program.

The Mars Global Surveyor mission cost about $154 million to develop and build and $65 million to launch. Mission operations and data analysis cost approximately $20 million/year.

Primary Investigations

The Mars Orbital Camera (MOC) - Michael Malin, Malin Space Science Systems
The Mars Orbital Camera will take high resolution images, on the order of a meter or so, of surface features. It will also take lower resolution images of the entire planet over time to enable research into the temporal changes in the atmosphere and on the surface.

Thermal Emission Spectrometer (TES) - Phil Christensen, Arizona State University
The Thermal Emission Spectrometer is a Michelson interferometer that will measure the infrared spectrum of energy emitted by a target. This information will be used to study the composition of rock, soil, ice, atmospheric dust, and clouds.

Mars Orbital Laser Altimeter (MOLA) - David Smith, Goddard Space Flight Center
This instrument will measure the time it takes for a transmitted laser beam to reach the surface, reflect, and return. This time will give the distance, and hence the height of the surface. Combining these measurements will result in a topographic map of Mars.

Radio Science Investigations (RS) - G. Leonard Tyler, Stanford University
Measurements of the Doppler shift of radio signals sent back to Earth will allow precise determination of changes in the orbit, which will allow for a model of the Mars gravity field. As the spacecraft passes over the poles on each orbit, radio signals pass through the Martian atmosphere on their way to Earth. The way in which the atmosphere affects these signals allows determination of its physical properties.

Magnetic Fields Investigation (MAG/ER) - Mario Acuna, Goddard Space Flight Center
A magnetometer will be used to determine whether Mars has a magnetic field, and the strength and orientation of the field if one exists. An electron reflectometer will measure remnant crustal magnetization.

Mars Relay - Jacques Blamont, Centre National d'Etudes Spatiales
The Mars Relay experiment consists of an antenna which will route received signals through the Mars Observer Camera for transmission to Earth. The relay will be used to support surface landers and rovers from other Russian, European, and U.S. missions.

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