Nanosatellite aerobrake maneuvering device
In this paper, we present the project of the heliogyro solar sail unit for deployment of CubeSat constellation and satellite deorbiting. The ballistic calculations show that constellation deployment period can vary from 0.18 years for 450km initial orbit and 2 CubeSats up to 1.4 years for 650km init...
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| creator | Melnikova, Valeriia Borovikov, Alexander Koretskii, Maksim Smirnova, Yuliya Timakova, Ekaterina Yu, Zhaokai Kuznetsov, Arseniy Frolov, Kirill Tenenbaum, Stepan Rachkin, Dmitriy Kotsur, Oleg Nerovny, Nikolay Mayorova, Vera Grigorjev, Anton Goncharov, Nikita |
| description | In this paper, we present the project of the heliogyro solar sail unit for deployment of CubeSat constellation and satellite deorbiting. The ballistic calculations show that constellation deployment period can vary from 0.18 years for 450km initial orbit and 2 CubeSats up to 1.4 years for 650km initial orbit and 8 CubeSats. We also describe the structural and electrical design of the unit and consider aspects of its integration into a standard CubeSat frame. |
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| language | eng |
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| subjects | Aerobraking Cubesat Deorbiting Nanosatellites Satellite constellations Solar sails |
| title | Nanosatellite aerobrake maneuvering device |
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