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This is an example concept for a Near-Earth-Object Flyby Second- Generation Microspacecraft. The spacecraft autonomously provides imaging and imaging spectroscopy of a near-Earth asteroid or comet for spacecraft solar ranges of 0.8 to 1.2 AU and Earth ranges up to 1.6 AU. Estimated spacecraft wet mass, launch configuration size, and load power are, respectively, 5.5 kg, 20 cm x 33 cm x 27 cm, and 5 to 13 W (depending on transmitter state: off or on). Developed in 1993-1995, a vision, approach, and example system concepts for Second-Generation Microspacecraft (SGM) have the intent of helping enable NASA's paradigm shift to less expensive, better, faster missions. Envisioned is a future in which a significant number of missions can be carried out with SGM that have low life-cycle cost, provide high return on investment, allow frequent flight, and contribute to innovation in technology. Key elements of the approach to realizing this vision include reducing spacecraft resource requirements and complexity, minimizing spacecraft size and mass, using production "core" building blocks and extensive spacecraft autonomy, and eliminating non-cost-effective redundancy. The first element of the approach also implies targeting appropriate, focused missions and payloads, using on-board analysis and data compression, minimizing spacecraft power needs, and using low-nuclear or, preferably, non-nuclear energy sources. Example spacecraft system concepts that are consistent with the approach include the Outer Solar System Flyby SGM, Near-Earth-Object Flyby SGM, Near- Earth-Object Rendezvous SGM, and Space Physics Fields and Particles SGM.
Description
This is an example concept for a Near-Earth-Object Flyby Second- Generation Microspacecraft. The spacecraft autonomously provides imaging and imaging spectroscopy of a near-Earth asteroid or comet for spacecraft solar ranges of 0.8 to 1.2 AU and Earth ranges up to 1.6 AU. Estimated spacecraft wet mass, launch configuration size, and load power are, respectively, 5.5 kg, 20 cm x 33 cm x 27 cm, and 5 to 13 W (depending on transmitter state: off or on). Developed in 1993-1995, a vision, approach, and example system concepts for Second-Generation Microspacecraft (SGM) have the intent of helping enable NASA's paradigm shift to less expensive, better, faster missions. Envisioned is a future in which a significant number of missions can be carried out with SGM that have low life-cycle cost, provide high return on investment, allow frequent flight, and contribute to innovation in technology. Key elements of the approach to realizing this vision include reducing spacecraft resource requirements and complexity, minimizing spacecraft size and mass, using production "core" building blocks and extensive spacecraft autonomy, and eliminating non-cost-effective redundancy. The first element of the approach also implies targeting appropriate, focused missions and payloads, using on-board analysis and data compression, minimizing spacecraft power needs, and using low-nuclear or, preferably, non-nuclear energy sources. Example spacecraft system concepts that are consistent with the approach include the Outer Solar System Flyby SGM, Near-Earth-Object Flyby SGM, Near- Earth-Object Rendezvous SGM, and Space Physics Fields and Particles SGM.
Description
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