Soft hardware efficiency estimation for a small spacecraft rotation angular velocity provision and monitoring

Аuthors

Sedel'nikov A. V.^*, Puzin Y. Y.^**, Filippov A. S.^***, Khnyreva E. S.^****

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: axe_backdraft@inbox.ru
**e-mail: georgy_sam@mail.ru
***e-mail: filippoval89@mail.ru
****e-mail: khnyryova@gmail.com

Abstract

The article presents the efficiency estimation of an AIST type small spacecraft rotation angular velocity provision and monitoring, employing the improved modification of the software hardware compared to the basic model, undergone flight tests as a part of the flight and trial samples of the “AIST” small spacecraft.

The article deals with magnetometer sensors application as a measuring tool for estimating the rotational motion parameters for various types of spacecraft.

The gist of the article is narrowed down to the fact that for there is no problem of mounting place selection for magnetometers and magnetic actuators (electromagnets) installation on the large-weight spacecraft and space stations. At the same time, for the small spacecraft this problem is topical in view of the impact of onboard scientific and supporting equipment together with magnetic devices of orientation hardware, while magnetic moment work out, on magnetometer sensors measuring data.

The article analyses in detail operation results of a number of devices, containing magnetometer sensors, as a part of various spacecraft types, such as “Foton” No 2,“AIST”, “AIST-2D”. The analysis results revealed that for “Foton” No 2 weighting 6546 kg, almost all deviations in magnetometer sensors measurements could be explained by the measurements instrumental error, while for the “AIST” series spacecraft weighting up to 50 kg the sensors readings demonstrated significant discord.

The authors conclude that the problem of magnetometer sensors' measurement data correctness for small spacecraft is specific due to the essentiality of the impact of scientific and supporting equipment operation, which arises from the dense layout of the payload in the inner space of a small spacecraft.

One of the ways of this problem solving may be the software hardware development, accounting for this impact for each normal operations mode of the equipment.

As an example of such solution, the article presents the software hardware installed on the “AIST-2D” small spacecraft. In the case of the “AIST-2D” small spacecraft, the discrepancies in estimating the angular velocities by two different magnetometer sensors were much lower than for “AIST” small spacecraft. This was achieved by the improvement of software hardware.

Keywords:

software hardware, small spacecraft, rotational motion parameters, magnetic measuring tools

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