Abstract The attitude of a satellite in an earth orbit is determined by a measuring arrangement which includes the body (1) of the satellite oriented with regard to the sun and a functional component (2) rotationally connected to the satellite body (1). The functional component 2, such as a turntable, carries functional elements, for example, antennas, which are directed or oriented toward the earth. During an earth orbit of the satellite, the turntable (2) carries out one full revolution in the direction of the earth orbit about a rotation axis (3) perpendicular to the orbit plane. A first star sensor (4) is arranged to sight in a direction along the rotation axis (3). In order to achieve a high attitude accuracy in the orientation of the turntable (2), the first star sensor (4) is mounted on the turntable(2) and at least one second star sensor (5) is also mounted on the turntable but with a sight direction (6) deviating from the direction of the rotation axis (3).
An earth satellite system, comprising an earth satellite body, an attitude control device, a functional component including functional elements to be oriented in orbit toward the earth, said functional elements being carried by said functional component, and means rotatably mounting said functional component to said satellite body for relative rotation thereto about a rotational axis (3) extending in a first direction perpendicularly to an orbit plane of said earth satellite body, said attitude control device comprising a first star sensor (4) mounted on said functional component and oriented for sighting in the direction of said rotation axis (3), and at least one second star sensor (5) also mounted on said functional component and oriented for sighting in a second direction deviating from said first direction of said rotation axis (3), at least said second star sensor (5) having only a very limited field of view centered about its sighting direction, said very limited field of view being imaged onto a photosensitive array of said second star sensor (5) for keeping said functional component exactly oriented toward the earth.
Claim 2
Dependent Claim
178 words
An earth satellite system, comprising an earth satellite body, an attitude control device, a functional component including functional elements to be oriented in orbit toward the earth, said functional elements being carried by said functional component, and means rotatably mounting said functional component to said satellite body for relative rotation thereto about a rotational axis (3) extending in a first direction perpendicularly to an orbit plane of said earth satellite body, said attitude control device comprising a first star sensor (4) mounted on said functional component and oriented for sighting in the direction of said rotation axis (3), and at least one second star sensor (5) also mounted on said functional component and oriented for sighting in a second direction deviating from said first direction of said rotation axis (3), at least said second star sensor (5) having only a very limited field of view centered about its sighting direction, said very limited field of view being imaged onto a photosensitive array of said second star sensor (5) for keeping said functional component exactly oriented toward the earth.
Claim 3
Dependent Claim
33 words
The measuring system of claim 1, wherein said very limited field of view of said second star sensor (5) is defined by an angle (β) which is in the range of several degrees.