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V. A. Obukhov et al.
The EPT rotation angles with respect to the axis OX S are within ±15°. At the
moments of change in the momentum sign relative to the axis OY S , which are defined
by the achievement of ±10 Nm s by the total momentum projection, the signs of the
EPT rotation angles change.
Changes in the EPT rotation angles with respect to the axis OZ S are within ±35°.
When the momentum relative to the axis OY S changes its sign, which is defined by
the achievement of ±10 Nm s by the integral momentum, due to the change in the
EPT rotation angles sign with respect to the axis OX S , there are small jumps for one
of the angles in the graphs for the rotation angle changes relative to the axis OZ S . In
the above graphs, the second angle in this case takes the maximum allowable value.
In the graphs for the EPT rotation angle changes, there are sections, in which the
EPT rotation angles are small in magnitude and equal to each other. In these sections,
the lateral SSC motion is controlled only.
The performed numerical simulation demonstrates efficiency of the proposed
methodology for assessing reliability of the considered algorithms for controlling
the EPT rotation in the process of the SDO removal from the GEO region.
The possibility to vary parameters of the simulation model for the IB momentum
transfer to SDO allows us to analyze a wide range of different conditions for the ion
beam impact on SDO.
10.6 Conclusions
The problem of contactless space debris removal is considered, in which the orbit
is changed using a high-velocity ion beam injected from SSC of a given design,
following the space debris object in its immediate vicinity.
An arrangement for the SSC electric propulsion thrusters is proposed taking into
account various values of permissible thruster rotation angles in two planes, as well
as the arrangement of solar panels. An algorithm is proposed for controlling the
rotation of the electric propulsion system thrusters, taking into account the required
thrust vector projection values in the lateral and longitudinal directions, as well as
the value of the total momentum accumulated relative to the SSC longitudinal axis.
The simulation results demonstrate the efficiency of the proposed algorithm for
controlling the EPT rotation angles. The proposed simulation model of the ion beam
impact on SDO and the control algorithms can be used to formulate requirements to
the control system for the SDO removal to the disposal orbit.
Acknowledgements This work was supported by the Ministry of Science and Higher Education
of the Russian Federation. Agreement Number: 05.604.21.0211. Unique identifier of the project:
RFMEFI60419X0211.
V. A. Obukhov et al.
The EPT rotation angles with respect to the axis OX S are within ±15°. At the
moments of change in the momentum sign relative to the axis OY S , which are defined
by the achievement of ±10 Nm s by the total momentum projection, the signs of the
EPT rotation angles change.
Changes in the EPT rotation angles with respect to the axis OZ S are within ±35°.
When the momentum relative to the axis OY S changes its sign, which is defined by
the achievement of ±10 Nm s by the integral momentum, due to the change in the
EPT rotation angles sign with respect to the axis OX S , there are small jumps for one
of the angles in the graphs for the rotation angle changes relative to the axis OZ S . In
the above graphs, the second angle in this case takes the maximum allowable value.
In the graphs for the EPT rotation angle changes, there are sections, in which the
EPT rotation angles are small in magnitude and equal to each other. In these sections,
the lateral SSC motion is controlled only.
The performed numerical simulation demonstrates efficiency of the proposed
methodology for assessing reliability of the considered algorithms for controlling
the EPT rotation in the process of the SDO removal from the GEO region.
The possibility to vary parameters of the simulation model for the IB momentum
transfer to SDO allows us to analyze a wide range of different conditions for the ion
beam impact on SDO.
10.6 Conclusions
The problem of contactless space debris removal is considered, in which the orbit
is changed using a high-velocity ion beam injected from SSC of a given design,
following the space debris object in its immediate vicinity.
An arrangement for the SSC electric propulsion thrusters is proposed taking into
account various values of permissible thruster rotation angles in two planes, as well
as the arrangement of solar panels. An algorithm is proposed for controlling the
rotation of the electric propulsion system thrusters, taking into account the required
thrust vector projection values in the lateral and longitudinal directions, as well as
the value of the total momentum accumulated relative to the SSC longitudinal axis.
The simulation results demonstrate the efficiency of the proposed algorithm for
controlling the EPT rotation angles. The proposed simulation model of the ion beam
impact on SDO and the control algorithms can be used to formulate requirements to
the control system for the SDO removal to the disposal orbit.
Acknowledgements This work was supported by the Ministry of Science and Higher Education
of the Russian Federation. Agreement Number: 05.604.21.0211. Unique identifier of the project:
RFMEFI60419X0211.