Process for determining the position of a spacecraft with the aid of a directional vector and a total angular momentum measurement
In a method for determining the position of a spacecraft based on vector determinations, a direction vector is measured in a body-fixed coordinate system; a reference direction vector is determined within a reference coordinate system based on the path position of the spacecraft and an orbit model; the overall spin vector of the spacecraft is determined within the body-fixed coordinate system; and a reference overall spin vector of the spacecraft is determined within a reference coordinate system by time propagation of known initial values of the overall spin of the spacecraft or by time tracking of a reference model. The position of the spacecraft is determined based on the four vectors.
1. A method for determining the position of a spacecraft based upon a determination of direction vectors and spin vectors, in which sensor data and spin data are determined as input variables for position determination, said method comprising:
a sensor measuring a first unit vector as a direction vector, in a body-fixed coordinate system;
computing a second unit vector as a reference direction vector in a reference coordinate system, based on the path position of the spacecraft and an orbit model;
computing an overall spin vector of the spacecraft in the body-fixed coordinate system, as a third vector determination;
computing a reference overall spin vector of the spacecraft in the reference coordinate system by time propagation of known initial values of the overall spin of the spacecraft, as a fourth vector; and
determining the position of the spacecraft based on said first through fourth vectors.
2. The method of claim 1 , wherein:
based on at least the direction vector, the reference direction vector, and overall spin that is time propagated from known initial values there is first determined a longitudinal component, about the direction vector, of the speed of rotation between the body-fixed coordinate system and the reference coordinate system;
said step of determining the overall spin vector is performed with the aid of the longitudinal component; and
a transformation matrix is determined based on the direction vector, the reference direction vector, the overall spin vector, and the reference overall spin vector;
the transformation matrix describes deviations of orientation of the body-fixed coordinate system of the spacecraft relative to the reference coordinate system; and
the orientation of the reference coordinate system constitutes a target orientation of the body-fixed coordinates system.
3. The method of claim 2 , wherein the direction vector and the reference direction vector are also used to determine the overall spin vector.
4. The method of claim 2 , wherein the determination of the longitudinal rate component and the determination of the overall spin vector also take into account the measured or estimated spin vector of spin wheels of the spacecraft.
5. The method of claim 3 , wherein the determination of the longitudinal component and the determination of the overall spin vector are also based on the measured or estimated spin vector of spin wheels of the spacecraft.
6. A method for determining the position of a spacecraft based upon a determination of direction vectors and spin vectors, in which sensor data and spin data are determined as input variables for position determination, said method comprising:
a sensor measuring a first unit vector as a direction vector, in a body-fixed coordinate system;
computing a second unit vector as a reference direction vector in a reference coordinate system, based on the path position of the spacecraft and an orbit model;
computing an overall spin vector of the spacecraft in the body-fixed coordinate system, as a third vector determination;
computing a reference overall spin vector of the spacecraft in the reference coordinate system by time tracking a reference model of overall spin, as a fourth vector; and
determining the position of the spacecraft based on said first through fourth vectors.
7. The method of claim 6 wherein:
based on at least the direction vector, the reference direction vector, and overall spin that is time tracked by means of a reference model, there is first determined a longitudinal component, about the direction vector, of the speed of rotation between the body-fixed coordinate system and the reference coordinate system;
said step of determining the overall spin vector is performed with the aid of the longitudinal component;
a transformation matrix is determined based on the direction vector, the reference direction vector, the overall spin vector, and the reference overall spin vector;
the transformation matrix describes deviations of orientation of the body-fixed coordinate system of the spacecraft relative to the reference coordinate system; and
the orientation of the reference coordinate system constitutes a target orientation of the body-fixed coordinates system.
8. The method of claim 7 , wherein the direction vector and the reference direction vector are also used to determine the overall spin vector.
9. The method of claim 7 , wherein the determination of the longitudinal rate component and the determination of the overall spin vector also take into account the measured or estimated spin vector of spin wheels of the spacecraft.
10. The method of claim 8 , wherein the determination of the longitudinal component and the determination of the overall spin vector are also based on the measured or estimated spin vector of spin wheels of the spacecraft.