Patent ID: 9296495
Filing Date: 2016-03-29
CPC Classification: B64G,G01C

Claim Text:
1. An attitude and orbit control system of a spacecraft for a spacecraft, comprising: a star sensor including an optical camera head, and a processing unit provided as a central master processing unit; additional kinematic sensors, each including a sensor element and an additional processing unit, one of the additional processing units being equivalent to the processing unit and being designated as a redundant central processing unit; a first bus connecting the additional kinematic sensors to the central master processing unit and the redundant central processing unit; a synchronization line for providing a uniform time pulse from the particular active central processing unit of the central master processing unit and the redundant central processing unit to the additional kinematic sensors; and a connection of the master central processing unit and the redundant central processing unit to a second bus of the spacecraft, via which the particular active central processing unit supplies a central computer of the spacecraft with hybridized kinematic measuring data generated according to a method for hybridization based on the synchronous kinematic measuring data of the star sensor and measuring data of the additional kinematic sensors.