Nanosatellite aerobrake maneuvering device

Autor:	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
Rok vydání:	2017
Předmět:	Astrophysics - Instrumentation and Methods for Astrophysics
Druh dokumentu:	Working Paper
Popis:	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. Comment: Change of paper's structure, size reducing. 18 pages total, 14 figures. This work has been submitted to the IEEE for possible publication
Databáze:	arXiv
Externí odkaz:	http://arxiv.org/abs/1708.07417 Zobrazit plný text záznamu View this record from Arxiv