PDS_VERSION_ID = PDS3 LABEL_REVISION_NOTE = " 2001-11-29 GEO:nelson Original; 2002-01-17 RS:simpson Updated mission phases; 2002-01-23 RS:Simpson Grammatical cleanup; 2002-02-27 GEO:Slavney Updated mapping phase; 2002-02-28 GEO:Slavney Removed Sun and Moon targets; 2002-03-26 GEO:Slavney Revised MISSION_ALIAS_NAME" RECORD_TYPE = STREAM OBJECT = MISSION MISSION_NAME = "2001 MARS ODYSSEY" OBJECT = MISSION_INFORMATION MISSION_START_DATE = 2001-01-04 MISSION_STOP_DATE = UNK MISSION_ALIAS_NAME = "ODYSSEY" MISSION_DESC = " Mission Overview ================ The Mars Odyssey spacecraft was launched from the Cape Canaveral Air Station in Florida on 2001-04-07 aboard a Boeing Delta II 7925 launch vehicle. At launch Odyssey weighed 729.7 kilograms (1606.7 pounds), including the 331.8 kilogram (731.5 pound) dry spacecraft with all of its subsystems, 353.4 kilograms (779.1 pounds) of fuel and 44.5 kilograms (98.1 pounds) of instruments. The spacecraft traveled more than 460 million kilometers over the course of a 200-day cruise period to reach Mars on 2001-10-24. Upon reaching Mars, Odyssey fired its main rocket engine for a 19-minute Mars orbit insertion (MOI) burn. This maneuver slowed the spacecraft and allowed the planet's gravity to capture it into orbit. Initially, Odyssey whirled around the red planet in a highly elliptical orbit that took 45 hours to complete. After orbit insertion, Odyssey performed a series of orbit changes to drop the low point of its orbit into the upper fringes of the Martian atmosphere at an altitude of about 110 kilometers. During every atmospheric pass, the spacecraft slowed by a small amount because of air resistance. This slowing caused the spacecraft to lose altitude on its next pass through the atmosphere. Odyssey used this aerobraking technique over a period of three months to transition from an elliptical orbit into a 400 km nearly circular orbit for mapping. Mars Odyssey was intended to last for more than 2 full Mars years, or 1374 days. The orbiter had its own science mission and also acted as a relay for landed Mars missions in 2004. The primary mapping mission began in February 2002 and lasted until August 2004 for a total of 917 days. The inclination of the science orbit was 93.1 degrees, resulting in a nearly Sun- synchronous orbit [JPLD-16303]. The orbit period was just under two hours. The spacecraft was three-axis stabilized and powered by solar cells. It was built of lightweight composite materials and divided into two sub-assemblies: the equipment module and the propulsion module. The equipment module consisted of two decks - the equipment deck, containing engineering equipment and one science instrument, the Martian Radiation Environment Experiment (MARIE), and the science deck, which housed the remainder of the science instruments and other engineering components. Mars Odyssey carried three on-board science instruments. The Thermal Emission Imaging System (THEMIS) worked both in the visible and infrared spectral regions. It took multi-spectral thermal-infrared images to determine the surface mineralogy at a global scale and also acquired visible images with a per-pixel resolution of 18 meters (59 feet). The Gamma Ray Spectrometer (GRS) measured gamma rays emitted from the surface of Mars to determine the elemental composition of the surface, including mapping water deposits in water-ice form. It also studied cosmic gamma ray bursts. GRS was actually a suite of three instruments - the Gamma Ray Spectrometer, the Neuron Spectrometer (NS) and the High-Energy Neutron Detector (HEND). GRS and THEMIS could not operate at the same time due to conflicts in the parameters necessary for operation. The Martian Radiation Environment Experiment (MARIE) was intended to operate continuously throughout the science mission to collect data about the radiation environment of the planet, but the instrument failed to respond and was shut off 2001-08-18. Mission Phases ============== Six mission phases were defined for significant spacecraft activity periods. These were the Pre-Launch, Launch and Initialization, Cruise, Orbit Insertion, Aerobraking, and Mapping Phases. The Cruise Phase included three sub- phases: near-Earth, Earth-Mars, and Mars approach. The final Mapping phase was intended to support the 2003 twin Mars Exploration Rovers and the European Space Agency's Mars Express Beagle II Lander. Both missions were expected to conduct surface operations in 2004. PRELAUNCH --------- The Prelaunch Phase extended from the delivery of the spacecraft to the Eastern Test Range (ETR) until the beginning of the start of the launch countdown at the Kennedy Space Center. Mission Phase Start Time : 2001-01-04 Mission Phase Stop Time : 2001-04-07 LAUNCH AND INITIALIZATION ------------------------- The Launch Phase extended from the start of launch countdown until first contact with the Deep Space Network (DSN) 53 minutes after launch. Mission Phase Start Time : 2001-04-07 Mission Phase Stop Time : 2001-04-07 CRUISE ------ The Cruise Phase began with initial DSN contact and lasted until 24 hours prior to Mars orbit insertion (MOI). It included 4 trajectory control maneuvers (TCM). The near-Earth subphase included checkout of the spacecraft engineering functions, instrument checkouts, THEMIS imaging of the Earth/Moon system, and TCM-1. Flight commanders turned off the Martian Radiation Environment Experiment (MARIE) on 2001-08-18 because the instrument failed to reset after it did not respond during a downlink session the previous week. Mission Phase Start Time : 2001-04-07 Mission Phase Stop Time : 2001-10-23 Subphases Dates --------- ----- Near-Earth 2001-04-07 to 2001-04-21 Earth-Mars 2001-04-21 to 2001-09-04 Mars Approach 2001-09-04 to 2001-10-17 ORBIT INSERTION --------------- The orbit insertion phase began 24 hours before spacecraft arrival at Mars. It included the Mars Orbit Insertion (MOI) burn, which achieved an orbit with a 18.6 hour period, making the planned Period Reduction Maneuver (PRM) unnecessary. MOI was achieved through a 19 minute long bipropellant burn. Mission Phase Start Time : 2001-10-23 Mission Phase Stop Time : 2001-10-27 AEROBRAKING ----------- The Aerobraking phase began with the completion of the Orbit Insertion Phase and ended with the attainment of the 400 km science orbit. It consisted of brushing through the Martian atmosphere, using the solar panels to create drag and slow down the spacecraft and thus reduce the orbit. The phase also included the deployment of the GRS boom. GRS acquired data throughout the aerobraking phase. Aerobraking concluded with two weeks of transition into the Mapping Phase. The transition included the deployment of the high-gain antenna. Mission Phase Start Time : 2001-10-27 Mission Phase Stop Time : 2002-02-19 MAPPING ------- The Mapping Phase began once the 400 km science orbit with approximately 5 PM equator crossing was achieved, at 19-Feb-2002 17:14:32 UTC. This time marked the beginning of orbit number 816. The intensive science portion lasted 917 days, with at least one of the three science instruments operating at all times throughout that period. Mission Phase Start Time : 2002-02-19 Mission Phase Stop Time : 2004-08-24 " MISSION_OBJECTIVES_SUMMARY = " The 2001 Mars Odyssey Orbiter Mission had 5 detailed science goals each of which was to be addressed by a specific instrument [JPLD-16303]. (1) GRS globally mapped the elemental composition of the surface. (2) GRS determined the abundance of hydrogen in the shallow subsurface. (3) THEMIS acquired high spatial and spectral resolution images of the surface mineralogy. (4) THEMIS provided information of the morphology of the Martian surface. (5) MARIE characterized the Martian near-surface radiation environment as related to radiation-induced risk to human explorers. Each instrument had additional, more specific objectives: THEMIS ------ The Thermal Emission Imaging System (THEMIS) had five, more narrowly defined science objectives: (1) To determine the mineralogy and petrology of localized deposits associated with hydrothermal or sub-aqueous environments, and to identify sample return sites likely to represent these environments. (2) To search for pre-dawn thermal anomalies associated with active sub-surface hydrothermal systems. (3) To study small-scale geologic processes and landing site characteristics using morphologic and thermophysical properties. (4) To investigate polar cap processes at all seasons using infrared observations at high spatial resolution. (5) To provide a direct link to the global hyperspectral mineral mapping from the MGS TES by utilizing the same infrared spectral region at high (100m) spatial resolution. GRS --- The Gamma Ray Spectrometer (GRS) had the following more specific science objectives [JPLD-16303]: (1) To determine quantitatively the elemental abundances of the martian surface to an accuracy of 10% or better at a spatial resolution of 300 km. (2) To map the abundances of CO2 and hydrogen (with water depth inferred) over the entire planet. (3) To determine the depth of the seasonal polar ice caps and their variation with time. (4) To study the nature of cosmic gamma-ray bursts. MARIE ----- The Martian Radiation Environment Experiment (MARIE) had the following more specific science objectives: (1) To measure radiation from the Sun and from sources beyond the solar system that could cause cancer or damage the central nervous system. (2) To measure for the first time the radiation environment outside the Earth's protective magnetosphere. (3) To predict anticipated radiation doses that might be experienced by future astronauts and help determine possible effects of Martian radiation on human beings. Although not a recognized science objective of the 2001 Mars Odyssey mission, improvement of models of the Mars gravity field was supported by collection and archiving of spacecraft radio tracking data by the Planetary Data System." END_OBJECT = MISSION_INFORMATION OBJECT = MISSION_HOST INSTRUMENT_HOST_ID = "ODY" OBJECT = MISSION_TARGET TARGET_NAME = "MARS" END_OBJECT = MISSION_TARGET END_OBJECT = MISSION_HOST OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "JPLD-16303" END_OBJECT = MISSION_REFERENCE_INFORMATION END_OBJECT = MISSION END