A method for on-orbit calibration and compensation of center of mass for electric propulsion satellites
A compensation method and electric propulsion technology, which are applied in space navigation equipment, space navigation aircraft, space navigation equipment, etc., can solve the problems of insufficient satellite autonomy, too much propellant, and large satellite attitude disturbance, and achieve improved position. The effect of ensuring control effect, low hardware implementation cost, and improving autonomous ability
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Embodiment 1
[0047] Define the mechanical system of the whole star: the origin O of the coordinate axis points to the center of mass of the satellite, the +X axis points to the east panel of the satellite, the +Y axis points to the south sailboard, and is parallel to the sailboard rotation axis, and the +Z axis forms the X axis and the Y axis Right-handed coordinate system, pointing in the direction of the satellite's back floor.
[0048] The scheme of diagonal layout of four electric thrusters is as follows: figure 1As shown, the four electric thrusters are all installed in the direction of the back floor of the whole star (-Z plane), and each electric thruster is connected to the back floor of the star through a vector adjustment mechanism. The four electric thrusters are arranged in a diagonal line, and their positions They are symmetrical in pairs with respect to the XOZ plane and the YOZ plane. Because the X-axis and Y-axis of the mechanical system divide the XOY plane into four inte...
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[0049] During the position keeping process, the vector adjustment mechanism needs to be adjusted so that the thrust directions of the four electric thrusters all pass through the center of mass of the satellite, so as to avoid affecting the attitude of the satellite. Therefore, the specific embodiment of the present invention is as follows:
[0050] 1) if figure 2 As shown, the stop control window is designed for the position keeping strategy with one week as a control period unit. The weekly position keeping strategy is as follows: on the first day of each control cycle, the satellite conducts orbit measurement autonomously and formulates a position keeping strategy. During this period, the satellite does not perform position keeping control. During the remaining six days, the satellite performs position hold fire control several times per orbit. position hold ignition as figure 2 Shown: Each rail is divided into 2 time periods separated by 180 degrees. Usually, one time...
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