초록 ▼

A method of controlling the attitude of a satellite according to which the direction of a predetermined celestial object is defined in a frame of reference related to the satellite, the instantaneous angular velocity vector of the satellite is detected and, by means of an actuating assembly, torques

A method of controlling the attitude of a satellite according to which the direction of a predetermined celestial object is defined in a frame of reference related to the satellite, the instantaneous angular velocity vector of the satellite is detected and, by means of an actuating assembly, torques are applied to the satellite which are defined by a control law so as to rotate the satellite about the direction while orienting an aiming axis related to the satellite in the same direction, involves defining the direction of the predetermined celestial object in a frame of reference related to the satellite by a first quantity representing a first angle measured between an axis of sight and the projection of the direction onto a first reference plane containing the axis of sight and by a second quantity representing a second angle defined by the axis of sight and the projection of the direction onto a second reference plane containing the axis of sight, the second angle being calculated from the first angle and from the instantaneous angular velocity vector of the satellite, while a satellite for implementing the method includes a body; a sensor having the axis of sight; an actuating assembly; an attitude control unit for generating signals for applying the torques to the satellite; a unit for measuring the rotation velocity; and a processing unit calculating the second quantity.

대표청구항 ▼

A method of controlling the attitude of a satellite comprising the steps of: defining a direction of a predetermined celestial object in a frame of reference related to said satellite; detecting an instantaneous angular velocity vector of said satellite; applying torques to said satellite; defining

A method of controlling the attitude of a satellite comprising the steps of: defining a direction of a predetermined celestial object in a frame of reference related to said satellite; detecting an instantaneous angular velocity vector of said satellite; applying torques to said satellite; defining said torques by a control law to rotate said satellite about said direction; orienting an aiming axis related to said satellite in said direction; representing as a first quantity a first angle measured between an axis of sight and a projection of said direction onto a first reference plane containing said axis of sight; representing as a second quantity a second angle defined by said axis of sight and a projection of said direction onto a second reference plane containing said axis of sight; and calculating said second angle from said first angle and from said instantaneous angular velocity vector of said satellite.