An optimization method for nano-satellite and pico-satellite separation through a two mass-one spring system
This paper studies the picosatellite ejection system from a nanosatellite, using one spring two mass ejection model. It is desired that both satellites maintain a long communication time after separation though they do not carry propulsion system. Moreover, the picosatellite is required to return to...
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| Main Authors: | , , |
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| Other Authors: | |
| Format: | Conference or Workshop Item |
| Language: | English |
| Published: |
2014
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| Subjects: | |
| Online Access: | https://hdl.handle.net/10356/79574 http://hdl.handle.net/10220/24138 http://www.researchgate.net/publication/260821673_An_Optimization_Method_for_Nano-satellite_and_Pico-satellite_Separation_through_a_Two_Mass-One_Spring_System |
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| Institution: | Nanyang Technological University |
| Language: | English |
| Summary: | This paper studies the picosatellite ejection system from a nanosatellite, using one spring two mass ejection model. It is desired that both satellites maintain a long communication time after separation though they do not carry propulsion system. Moreover, the picosatellite is required to return to nanosatellite communication range in a given time period. The dynamic motion of the ejection system has been derived. The impact of ejection location, force and direction on the communication and separation time is studied. Results show that a continuous satellite communication could be maintained if the picosatellite is ejected in perpendicular to the flight path direction. However, the possible collision between the two satellites is to be taken into consideration. |
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