The spacecraft was 3-axis stabilized and included eight hydrazine monopropellant thrusters (four 22N thrusters to perform trajectory corrections four 0.9N thrusters to control attitude). With the exception of the scientific instruments, battery and main engine, the spacecraft included dual redundancy on the most important systems. The internal structure was largely constructed with graphite composite/aluminum honeycomb supports, a design found in many commercial airplanes. The Mars Climate Orbiter bus measured 2.1 meters tall, 1.6 meters wide and 2 meters deep. look for evidence of past climate change.monitor the water vapor and dust content of the atmosphere.determine temperature profiles of the atmosphere.record changes on the martian surface due to wind and other atmospheric effects.monitor the daily weather and atmospheric conditions.determine the distribution of water on Mars.The primary science objectives of the mission included: Following Mars Global Surveyor, Mars Climate Orbiter carried two instruments, one originally intended for Mars Observer, to study the climate and weather of Mars. The first mission in the new program was Mars Global Surveyor, launched in 1996 to map Mars and provide geologic data using instruments intended for Mars Observer. In 1995, a new Mars Surveyor program began as a set of missions designed with limited objectives, low costs, and frequent launches. ![]() ![]() The panel determined that the new line of miniature spacecraft should be under 1000 kilograms with highly focused instrumentation. In 1994, the Panel on Small Spacecraft Technology was established to set guidelines for future miniature spacecraft. After the loss of Mars Observer and the onset of the rising costs associated with the future International Space Station, NASA began seeking less expensive, smaller probes for scientific interplanetary missions.
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