Highlights Spin-stabilized method is applied to eliminate velocity pointing error. Analytical solutions with nonzero initial conditions are derived. Mechanism research on spinning thrusting Cubesat is carried out. The mechanism analysis can be used on Cubesat parameters design.

    Abstract To solve the problem of thrust vector misalignment from the Cubesat center of mass during orbital maneuver, spin-stabilized method is applied to eliminate velocity pointing error. Spinning thrusting Cubesat model involves the effects of mass variation and jet damping is established. Analytical solutions for the angular velocity, nutation angle, Euler angle, and inertial velocity with nonzero initial conditions are derived. Simulations show that the analytical solutions closely match numerical simulations. Based on the analytical solutions, the velocity pointing error influencing factors is analyzed. The results show that the velocity pointing error caused by initial transverse velocity, nutation angle and transverse disturbance torque can be reduced by raising the spin rate, but the initial Euler angle need to be limited. Also, the spinning thrusting maneuver can allow for a lower spin rate by increasing the axial moment of inertia.


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    Titel :

    Velocity pointing error analysis for symmetric spinning thrusting Cubesat


    Beteiligte:
    Liang, Zhenhua (Autor:in) / Liao, Wenhe (Autor:in) / Zhang, Xiang (Autor:in)

    Erschienen in:

    Advances in Space Research ; 63 , 11 ; 3621-3631


    Erscheinungsdatum :

    2019-02-05


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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