mars global surveyor mass

mars global surveyor mass
October 28, 2020

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. The focal plane contains two 3456 element, 7 micrometer pixel CCD line arrays. This is the top of the equipment module, which is 0.735 m high. The dual-mode propulsion system (MMH/NTO or MMH monopropellant) had one 596 N and twelve 4.45 N thrusters. Two solar panels, each 3.5 x 1.9 m in size, extend out from opposite sides of the craft. It is in a near polar orbit (inclination = 93°) which is almost perfectly circular, moving from being over the south pole to being over the north pole in just under an hour. The 1.5 m diameter, articulated high gain antenna was mounted on a 1.5 m boom. Mars Global Surveyor was the first successful U.S. mission launched to Mars since the Viking mission in 1976. One wide-angle camera, optimized to operate in a band pass from 400-450 nm (``blue'') has a focal length of 11.4 mm (f/6.3). The wide-angle assembly consists of two cameras mounted on the side of the narrow-angle assembly. Total science payload mass was 78 kg. On-orbit mass: 1030.5 kg. These two assemblies are contained within a single cylindrical structure, approximately 80 cm in length and 40 cm in diameter. 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. Thermal Emission Spectrometer to map the mineral content of rocks, ice caps, and clouds. All instruments except the magnetometer are stored on the nadir equipment deck, on one of the 1.17 x 1.17 meter surfaces. Camera system included wide angle (140 degree) and narrow angle (0.4 degree) optics for producing global coverage (7.5 km/pixel), selective moderate resolution images (280 m/pixel) and very selective high resolution (1.4 m/pixel) images. 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). Images that provide evidence of recent water flows on Mars. Last Launch: 1996-11-07. The narrow-angle assembly, which comprises the principal part of the instrument, is a 35 cm aperture, 3.5 m focal length (f/10) Ritchey-Chretien telescope with a 0.4 degree field of view, filtered to operate in a band pass from 500-900 nm. Mission operations and data analysis cost approximately $20 million/year. › Slide Show: Mars Global Surveyor › View Archive The Mars Global Surveyor orbiter, which operated on Mars for more than nine years, was designed to study the composition of Mars, map its topography and monitor weather patterns. The Mars Global Surveyor (MGS) Mars Orbiter Camera (MOC) experiment is designed to obtain images of the surface and atmosphere of Mars for studying the meteorology/climatology and geology of Mars. This system is capable of providing an image resolution of 1.41 m/pixel at a nominal altitude of 380 km with an expected resolution of better than 1.5 m/pixel during the course of the mission. NASA NSSDC Master Catalog Description. The altitude was chosen to make the orbit Sun-synchronous, so that all images that were taken by the spacecraft of the same surface features on different dates were taken under identical lighting conditions. An extended mission took place until April 2002, further extensions were added until contact with the spacecraft was lost on 2 November 2006. Ka-Band Link Experiment (KaBLE) to provide Ka-band signal for atmospheric attenuation studies. The camera is controlled by a 32 bit (10 MHz, 1 MIPS) SA3300 microprocessor with four ASICs, 128 kbytes EPROM, and 192 kbytes SRAM. AKA: MGS. After collecting data for its prime mission of a full Martian year (nearly two Earth years), the spacecraft continued in operation for nearly ten years, observing changes to the Martian surface and acting as a data relay station for follow-on Mars missions. After the initial elliptical capture orbit, months of thruster firings and aerobraking maneuvers were used to reach the nearly circular mapping orbit. 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. The program was formulated in 1994 to economize costs and maximize returns by involving a single industrial partner with NASA's Jet Propulsion Laboratory (JPL) to design, build and deliver a flight-worthy vehicle for Mars every two years. The Mars Global Surveyor spac… 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. Mars Global Surveyor Launch Information: November 7, 1996 Fast Facts: Arrival at Mars: September 12, 1997 Mass: 767 kilograms (1,691 pounds) Science instruments: High-resolution camera, thermal emission spectrometer, laser altimeter, magnetometer/electron reflectometer, ultra … Radio Science (Ultrastable Oscillator) to study gravitational field, atmospheric refractive indices, and temperature profiles. Signs of Flowing Water on Mars. Power System: 4 Solar Array Panels, 667 W. The Mars Global Surveyor (MGS) mission is designed as a rapid, low-cost recovery of the Mars Observer mission objectives. In order to acquire images to satisfy these three objectives, the MOC consists of a narrow-angle assembly and a wide-angle assembly. Uplink is in the X-band, downlink in the X and Ka bands. The instruments on the nadir equipment deck consist of a camera, thermal emission spectrometer, laser altimeter, and a radio transmission relay. Mars Global Surveyor entered a 258 x 54021 km x 93.3 deg polar orbit around Mars on 12 September 1997 after a 22 minute burn of its main engine. The other, designed to operate in a band pass from 575-625 nm (``red''), has a focal length of 11.0 mm (f/6.4). First Launch: 1996-11-07. Science observations were made periodically during these maneuvers. Mapping operations begin in March 1998. Mars Orbiter Laser Altimeter (MOLA) provided local and global maps of Martian topography with 2 to 30 meter vertical resolution. 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. See just a few highlights from the spacecraft that has orbited Mars for nearly ten years. Further, the MOC can transfer these data (either to the on-board recording system or via real-time transmission) at any rate of which the spacecraft is capable. After a 5 month hiatus, aerobraking was resumed on 23 September 1998. Signs ofFlowing Water on Mars. The spacecraft is three-axis stabilized with no scan platform. In-flight calibration of the MOC is extremely limited due to the fixed pointing of the instrument. The orbit has a 7 day near-repeat cycle so Mars will be mapped in 26 day cycles. Because of the high volume of data which imaging experiments can generate, the MOC electronics contain not only a large amount of memory (~12 MB DRAM buffer) for processing and storing the images, but also have the capability of utilizing a number of data compression techniques (both lossless and lossy). Mars Global Surveyor was the first mission of the Mars Surveyor Program, which was an aggressive series of orbiters and landers designed to provide new global and close-up images of Mars. Temperature control is primarily passive with multilayer insulation, thermal radiators, and louvers, augmented by electrical heaters. The initial propellant load was 216.5 kg of hydrazine and 144 kg of N2O4. As a result, the equivalent of two, four, or eight (depending on mission phase) 2048 x 2048 pixel images can be processed on record-only days and, once every three days on average, fourteen such images can be processed and sent during an eight-hour real-time pass. The MIL-STD-1750A-based central computer had a total data storage capacity of 3 gigabits. The spacecraft circled Mars once every 117.65 minutes at an average altitude of 378 km (235 mi). The wide angle instruments have fields of view of 140 degrees, with resolution of 280 m/pixel at nadir and 2 km/pixel at the limb. Number: 1 . Magnetometer and Electron Reflectometer for global study of intrinsic magnetic field. Its primary objectives are to: (1) obtain global, synoptic views of the Martian surface and atmosphere on a daily basis in order to understand the meteorological and climatological changes during the mission; (2) monitor surface and atmospheric features for changes on temporal scales from hours to years and on a spatial scale necessary for resolving the details of their morphology; and, (3) systematically examine local areas at high spatial resolution so that surface/atmosphere interactions and geologic processes which operate on short time scales can be quantified. Available data rates are 700, 2856, 9120, and 29260 real-time bits/sec. An 8086 processor is used for the payload data subsystem, and 1750A processors for the standard controls processor and the engineering data formatter. The focal plane contains two 2048 element, 13 micrometer pixel CCD line arrays. Data is stored on four 0.75 Gb solid state recorders. Some opportunities for in-flight calibration are possible during regional or global dust storms. The main thruster and propulsion tanks are on the opposite side from the instruments, on the propulsion module, which is approximately 1 meter high. The Mars Global Surveyor mission cost about $154 million to develop and build and $65 million to launch. Energy is stored in two 20 Amp-hr nickel hydrogen batteries, and supplied at 28 V DC. Gullies, dunes and more. Science mapping began in mid-March 1999, which was summer in the northern hemisphere on Mars. 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. The science objectives involve high resolution imaging of the surface, studies of the topography and gravity, the role of water and dust on the surface and in the atmosphere of Mars, the … After aerobraking ended in February 1999, MGS was in a 118 minute circular polar science mapping orbit with an index altitude of 378 km. 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. The electronics for the MOC are completely redundant and the narrow-angle and wide-angle cameras can be operated by either set of electronics and all three cameras can be operated simultaneously. Mars Balloon Relay to serve as a data relay for planned future surface stations and atmospheric experiments. Four solar array panels (2 GaAs, 2 SI) provide 980 W of power to the spacecraft. Minimum downlink rate is 21.33 kbps, 2 kbps engineering data downlink, and 10 bps emergency downlink. Otherwise, pre-flight measurements made to characterize the instrument performance comprised the bulk of the instrument calibrations. After a year and a half spent trimming its orbit from a looping ellipse to a circular track around the planet, the spacecraft began its … 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). Control is through 12 4.45 N hydrazine thrusters, mounted in four groups of three (two aft facing and one roll control thruster). After a long aerobraking phase to a lower circular orbit, the spacecraft began its primary mission of photographing and observing changes on the Martian surface in March 1999. The spacecraft used X-band uplink at 500 bps and X-band and Ka-band downlinks at 85.3 kbps maximum. Height: 1.80 m (5.90 ft). The orbiter made a number of discoveries about the Red Planet, including evidence of liquid water at or near the Martian surface.

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