The invention provides a method for identifying whole-
spacecraft flexibility vibration
modal parameters. The method for identifying the whole-
spacecraft flexibility vibration
modal parameters comprises the following steps that
pose angular speed is obtained, specifically, i-axis
pose angular speed data
omega' i (t) after filtering is obtained after
pose angular speed measuring data
omega i (t) corresponding to an i-axis of an underdamping free vibration area after
satellite on-
orbit air injection closed-
loop control, wherein the i-axis is any one of an X-axis, a Y-axis and a Z-axis in a spacerectangular coordinate
system; filtering is carried out, specifically, filtering is carried out on the
omega i (t) to obtain the i-axis pose angular speed data omega' i (t) after filtering; on-
orbit vibration frequency is calculated, specifically, the on-
orbit vibration frequency fi is calculated and obtained according to the omega' i (t);
time series is calculated, specifically, the
time series eta i (t) of a
modal variable is calculated and obtained according to the omega' i (t); and damping is calculated, specifically, the damping epsilon i of the i-axis vibration mode is obtained accordingto calculation. The method for identifying the whole-
spacecraft flexibility vibration modal parameters meets the requirement of flexible
satellite on-orbit structural dynamic characteristic identification, and on-orbit flexibility vibration modal frequency and
modal damping ratio and other whole-spacecraft flexibility vibration modal parameters are extracted.