Spacecraft nutation inhibition method for low-orbit geomagnetic energy storage in-orbit delivery

A spacecraft nutation inhibition method for a low-orbit geomagnetic energy storage in-orbit delivery, comprising:

• S1:
• dividing a spacecraft system into a first spacecraft main body and a second spacecraft main body which are fixedly connected by a main connecting shaft, enabling two mass blocks to be slidably connected to a delivery connection rod, which is vertically rotatably arranged in the main connecting shaft in a length direction, and adjusting a center of mass of the spacecraft system to pass through the main connecting shaft;
• S2:
• after the spacecraft system grabs a space target or de-orbit debris and the space target or the de-orbit debris is kept at a corresponding position of the delivery connection rod, respectively measuring, calibrating and adjusting a center of mass and a principal axis of an inertia of the delivery connection rod that is to deliver the space target or the de-orbit debris, enabling the main connecting shaft, which is a rotation axis of the adjusted delivery connection rod, to pass through the center of mass of the spacecraft system that has grabbed the space target or the de-orbit debris and to overlap with the principal axis of the inertia in the rotation direction of the delivery connection rod, and enabling a delivery plane in which the delivery connection rod rotates vertically around the main connecting shaft to pass through the center of mass of the spacecraft system that has grabbed the space target or the de-orbit debris;
• S3:
• carrying out an energy storage delivery:
• carrying out an energy storage acceleration to the delivery connection rod that is to deliver the space target or the de-orbit debris, and driving the delivery connection rod to rotate vertically around the main connecting shaft;
• S4:
• when delivery requirements for the space target or the de-orbit debris are satisfied, delivering the space target or the de-orbit debris, and respectively adjusting the center of mass and a moment of the inertia of the delivery connection rod that has delivered the space target or de-orbit debris;
• S5:
• carrying out an energy dissipation and unloading, wherein the unloading process is reverse to the energy storage delivery process, and is to dissipate and unload the moment of the inertia of the delivery connection rod that rotates vertically around the main connecting shaft until a rotation stops;
• and
• S6:
• enabling the spacecraft system to prepare to grab a next space target or de-orbit debris, and proceeding to a next delivery work cycle.