초록 ▼

A system for controlling an attitude of an artificial satellite to decide the present attitude of the satellite on a spatial coordinate and angular velocities of rotation about body axes of the satellite, by the use of inertial sensors and star sensors, to calculate an objective attitude of the sate

A system for controlling an attitude of an artificial satellite to decide the present attitude of the satellite on a spatial coordinate and angular velocities of rotation about body axes of the satellite, by the use of inertial sensors and star sensors, to calculate an objective attitude of the satellite on the basis of the present attitude information, the angular velocities of rotation about the body axes and orbit information received from a ground station so that the attitude of the satellite and the changing rate thereof are controlled simultaneously.

대표청구항 ▼

A system for controlling an artificial attitude of a satellite and changing rate thereof on the basis of detected signals from inertial sensors for detecting angular velocities of rotation of the satellite about the body axes thereof and star sensors for detecting incident light from fixed stars so

A system for controlling an artificial attitude of a satellite and changing rate thereof on the basis of detected signals from inertial sensors for detecting angular velocities of rotation of the satellite about the body axes thereof and star sensors for detecting incident light from fixed stars so as to coincide with an objective attitude, comprising: a first means for deciding the present attitude of the satellite with respect to said body axes on the basis of said signals from said sensors to provide positional information for indicating present position of the satellite; a second means for deciding an objective attitude of the satellite to be established, on the basis of orbit information received from a ground station and said positional information to provide an objective attitude information indicating the objective attitude; a third means for calculating required operation values for controlling the attitude on the basis of said objective attitude information, said values being fed to actuators for controlling the attitude of the satellite; said first means including: means to calculate a unit vector representing the direction of an observed fixed star on the body coordinate of the satellite, on the basis of the detected signals from said star sensors; memory means for storing an initial estimated attitude information of the satellite and catalog information representing the spatial coordinates of fixed stars; edit means for reading the attitude information and catalog information from the memory means to edit a catalog of stars expected to be observed within the ranges of the field of view of the star sensors; means for identifying a catalog star corresponding to the observed fixed star, on the basis of said unit vector and said catalog; and means for calculating the present attitude of the satellite on the basis of said catalog star from said identifying means and the detected signals from the inertial sensor to provide the information of the present attitude of the satellite.