INTEGRATED strapdown inertial-optical systems for spacecraft

摘要

The invention relates to systems of orientation, navigation and control spacecraft. It includes in its composition three angular rate gyro meters, infrared-based CCD vertical, star sensors, receivers of the satellite navigation system and the onboard computer, the majority element.; The object of the claimed utility model is a significant increase in the accuracy of the system due to input additional correction of SNA, star sensors and infrared vertical.; The problem is solved in that the integrated strapdown inertial-optical system for a spacecraft, comprising three gyro meters, receiver and antenna satellite navigation system, an onboard computer, mounted on a moving object body, the onboard computer associated with the triple gyro meters and receiver the antenna of the satellite navigation system according to the claimed technical solution is further administered three receiver antennas putnikovoy navigation system, also mounted on the housing, infrared chain of CCD-based, star sensors, the antenna receivers are offset in opposite directions from the center of suspension of the mobile object along the longitudinal and transverse axes at equal distances, in addition, the onboard computer three blocks administered orientation, wherein the outputs of the triple gyro meters vertically and infrared connected to the inputs of the first orientation of the onboard computer unit, the outputs of the triple gyro meters and star d tchikov connected to inputs of the second unit board computer orientation, outputs triple gyroscopic measuring instruments and receivers to the antennas of the satellite navigation system are connected to the inputs of the third unit board computer orientation, moreover, the onboard computer introduced majority element with three inputs and one output, the outputs orientation units are connected to the inputs of a majority element and the output element is the output of a majority of the entire system. Figure 3 .; 1 n.p.f.