Nanosatellite aerobrake maneuvering device
Valeriia Melnikova, Alexander Borovikov, Maksim Koretskii, Yuliya, Smirnova, Ekaterina Timakova, Zhaokai Yu, Arseniy Kuznetsov, Kirill Frolov,, Stepan Tenenbaum, Dmitriy Rachkin, Oleg Kotsur, Nikolay Nerovny, Vera, Mayorova, Anton Grigorjev, Nikita Goncharov
TL;DR
This paper introduces a heliogyro solar sail device designed for CubeSat constellation deployment and deorbiting, detailing its design, ballistic performance, and integration considerations.
Contribution
It presents a novel heliogyro solar sail unit with detailed structural, electrical, and deployment analysis for CubeSat applications.
Findings
Deployment time varies from 0.18 to 1.4 years depending on orbit and constellation size.
Ballistic calculations demonstrate effective deployment periods for different configurations.
Design considerations facilitate integration into standard CubeSat frames.
Abstract
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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Taxonomy
TopicsSpacecraft Design and Technology · Spacecraft Dynamics and Control · Satellite Communication Systems