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.
Cite
@article{arxiv.1708.07417,
title = {Nanosatellite aerobrake maneuvering device},
author = {Valeriia Melnikova and Alexander Borovikov and Maksim Koretskii and Yuliya Smirnova and Ekaterina Timakova and Zhaokai Yu and Arseniy Kuznetsov and Kirill Frolov and Stepan Tenenbaum and Dmitriy Rachkin and Oleg Kotsur and Nikolay Nerovny and Vera Mayorova and Anton Grigorjev and Nikita Goncharov},
journal= {arXiv preprint arXiv:1708.07417},
year = {2024}
}
Comments
Change of paper's structure, size reducing. 18 pages total, 14 figures. This work has been submitted to the IEEE for possible publication