PURPOSE:To enable realization of a high navigation guidance accuracy by processing outputs of a rate integration gyrocompass, a fixed star sensor, accelerometer, a solar sensor and a distance measuring device carried on an outerspace equipment by a navigation software within a navigation calculator. CONSTITUTION:This apparatus is equipped with a fixed star sensor 4 for detecting attitudes, a rate integration gyrocompass 3, a solar sensor 5 for detecting a locus position, a distance measuring device 6 between the earth and an outer space equipment, an accelerometer 7 and a navigation calculator 2 for processing a sensor data from said devices and a navigation soft ware. In a function of determining attitudes, an attitude increment 15 of the rate integration gyroscope 3 is taken into a navigation calculator 2 and with an attitude propagation part software 9, an integration of attitudes 28 for a solar center of gravity inertia coordinates system and a derivation of an angular velocity 27 for the solar center of gravity inertia coordinates system are performed. A two-dimensional angle and a grade 23 of a catalogue star are used to accomplish a star identification and a filter processing in an attitude updating part software 10 thereby updating attitude propagation errors 22 and bias estimated errors 21 of the rate integration gyroscope 3.
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