Navigator for spacecraft

Abstract

Abstract PURPOSE:To reduce calculations by using deviations of a position, speed from a refer ence orbit, and using a Kalman filter for obtaining an observed value from the deviations from distance.distance change rate of reference distance.distance change rate of a navigation supporting artificial satellite and a spacecraft. CONSTITUTION:An exclusive use receiver 4 receives a transmission signal 8 from a navigation supporting artificial satellite 6 on a global circulation orbit, interprets information for calculating absolute position.speed 7 (Xs) of the satellite 6 included in the signal, obtains observed value 9 (Z) of distance.distance change rate between the satellite 6 and a spacecraft 2, and sends information to a navigation calculator 5. The calculator 5 calculates the speed Xs of the satellite 6 based on the information from the receiver 4. Then, absolute position.speed 10 (X) of the spacecraft itself are presumed by considering the dynamics of the board 2 from the observed value Z and the speed Xs. At the stage of the presumption, a deviation 15 (deltax) from the position.speed 13 (Xref) of a reference point 12 on the reference orbit of the state variable X of the board 2, and a deviation 16 (deltaz) from the reference distance.distance change rate 14 of the observed value 9 are used as state variables and observed values, and the calculation can be largely reduced.

Inventors

• 👤 Norimasa Yoshida
• 👤 憲正 吉田

Bibliographic Details