Abstract: A spacecraft nutation inhibition method for low-orbit geomagnetic energy storage in-orbit delivery includes: S1, enabling a delivery connection rod to be slidably connected to two mass blocks in a length direction, and adjusting the center of mass of a spacecraft system to pass through a main connecting shaft; S2, respectively measuring, calibrating and adjusting the center of mass and the principal axis of inertia of the delivery connection rod that is to deliver the space target or de-orbit debris; S3, carrying out energy storage delivery; S4, respectively adjusting the center of mass and the moment of inertia of the delivery connection rod after delivering the space target or de-orbit debris; S5, carrying out energy dissipation and unloading; and S6, enabling the spacecraft system to prepare to grab the next space target or de-orbit debris and proceeding to the next delivery work cycle.

Abstract: A transfer type contra-rotating geomagnetic energy storage-release delivery system is disclosed. The system includes a control system, a three-axis control moment canceller and an energy system, which are arranged on a delivery mother spacecraft, and the delivery mother spacecraft is connected, through support rod structures, with a strong magnetic moment generating device, a contra-rotating transmission mechanism and two delivery connection rod structures arranged at the two ends of the contra-rotating transmission mechanism, the strong magnetic moment generating device is arranged between the contra-rotating transmission mechanism and the delivery mother spacecraft, the two delivery connection rod structures are provided with slidable mass blocks respectively, and the strong magnetic moment generating device and the contra-rotating transmission mechanism provide energy through the energy system.

Abstract: A spacecraft nutation inhibition method for low-orbit geomagnetic energy storage in-orbit delivery includes: S1, enabling a delivery connection rod to be slidably connected to two mass blocks in a length direction, and adjusting the center of mass of a spacecraft system to pass through a main connecting shaft; S2, respectively measuring, calibrating and adjusting the center of mass and the principal axis of inertia of the delivery connection rod that is to deliver the space target or de-orbit debris; S3, carrying out energy storage delivery; S4, respectively adjusting the center of mass and the moment of inertia of the delivery connection rod after delivering the space target or de-orbit debris; S5, carrying out energy dissipation and unloading; and S6, enabling the spacecraft system to prepare to grab the next space target or de-orbit debris and proceeding to the next delivery work cycle.

Abstract: A transfer type contra-rotating geomagnetic energy storage-release delivery system is disclosed. The system includes a control system, a three-axis control moment canceller and an energy system, which are arranged on a delivery mother spacecraft, and the delivery mother spacecraft is connected, through support rod structures, with a strong magnetic moment generating device, a contra-rotating transmission mechanism and two delivery connection rod structures arranged at the two ends of the contra-rotating transmission mechanism, the strong magnetic moment generating device is arranged between the contra-rotating transmission mechanism and the delivery mother spacecraft, the two delivery connection rod structures are provided with slidable mass blocks respectively, and the strong magnetic moment generating device and the contra-rotating transmission mechanism provide energy through the energy system.