Angular Motion of the TNS-0 # 2 Nanosatellite after Launch from the International Space Station


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Abstract

Description of the passive magnetic attitude control system of the TNS-0 # 2 nanosatellite is presented. The parameters of the main components of the attitude control system are given and their choice is justified. Using telemetry data, the passive angular motion of TNS-0 # 2 was determined after processing measurements of the on-board sensors after launching from the ISS on August 17, 2017. The damping time of the initial angular velocity was estimated. The accuracy of magnetic stabilization after the end of transient processes was determined.

About the authors

D. S. Ivanov

Keldysh Institute of Applied Mathematics, Russian Academy of Sciences

Author for correspondence.
Email: danilivanovs@gmail.com
Russian Federation, Moscow, 125047

M. Yu. Ovchinnikov

Keldysh Institute of Applied Mathematics, Russian Academy of Sciences

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 125047

O. A. Pantsyrnyi

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

A. S. Selivanov

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

A. S. Sergeev

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

I. O. Fedorov

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

O. E. Khromov

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

N. A. Yudanov

Russian Space Systems

Email: danilivanovs@gmail.com
Russian Federation, Moscow, 111250

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