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  • Choice of Magnetic Attitude Control System for Nanosatellites

    Paper number

    IAC-07-C1.8.02

    Author

    Prof. Michael Yu. Ovchinnikov, Keldysh Institute of Applied Mathematics, RAS, Russia

    Coauthor

    Mrs. Nadezhda Kupriyanova, Keldysh Institute of Applied Mathematics, RAS, Russia

    Coauthor

    Mr. Stanislav Karpenko, Keldysh Institute of Applied Mathematics, RAS, Russia

    Coauthor

    Dr. Vladimir Penkov, Keldysh Institute of Applied Mathematics, RAS, Russia

    Year

    2007

    Abstract
    Experience collected during launch campaign of the first Russian nanosatellite TNS-0 and its flight data processing, development of the attitude control systems (ACS) for the next satellites of the TNS series dictates approaches to be taken into account for choice the algorithms of attitude control of the satellites. TNS-0 satellite successfully launched from the International Space Station in March, 2005 was equipped with the passive magnetic ACS and a simple attitude determination system. At the moment the bus of TNS-0 is considered as a universal platform to execute a set of technological experiments for a short missions combined with education of students.
    
    Two main requirements are taken into account for algorithms of attitude control development. The first one is the satellite should be oriented in arbitrary but given attitude with certain accuracy and time-response. Possibility to provide a given attitude is more important than accuracy. The second requirement comprises low cost and energy consumption, usage of conventional sensors and actuators and autonomous activity. Reasonable candidate is magnetic ACS.
    
    For satellite with weak requirement for attitude like to predict chaotic rotation only the passive magnetic ACS is chosen with requirements to initial attitude motion and arrangement of ACS elements. To increase time-response the combination of passive and active magnetic elements providing both restoring and damping torques respectively is considered. For attitude motion modes unusual for magnetic ACS like with respect to the local vertical or alongwith the Sun direction an active magnetic ACS is used. Advantage of a satellite dynamics for required orientation to the Sun and alongwith the local geomagnetic field is that Sun-sensor or three-axis magnetometer can be used only with elementary algorithm of control. To track by satellite axis a given sub-satellite pass can be provided with active magnetic ACS too.
    
    We consider attitude dynamics of satellite with various magnetic ACS paying attention to advantage for given attitude mode. Since the systems considered have to satisfy to requirements listed above we give preference to combination of the requirements to attitude and hardware configuration which uses satellite dynamics rather than a control effect. Also, to choose algorithm we use results of our miniature laboratory facility attitude simulation. Testing sessions are presented.
    
    The Russian Foundation for Basic Research (06-01-00389) and the Russian Agency of Science and Innovations (02.514.11.4.4011) support this work.
    Abstract document

    IAC-07-C1.8.02.pdf

    Manuscript document

    IAC-07-C1.8.02.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.