Abstract: In a method for determining navigation data, positional angle measurement values are determined using a first navigation device (310). A second navigation device (320) is then initialized using the positional angle measurement values determined by the first navigation device (310). Both navigation devices are supplied with rotational rate and acceleration measurement values from a common sensor unit in order to determine the positional angle measurement values. In the process, the first navigation device (310) produces erroneous measurements of the positional angle measurement values with a probability which is lower than as specified positional angle error rate, and the second navigation device (320) produces erroneous measurements of the positional angle measurement values with a probability which is higher than the specified positional angle error rate.

Abstract: In a method for determining navigation data, positional angle measurement values are determined using a first navigation device (310). A second navigation device (320) is then initialized using the positional angle measurement values determined by the first navigation device (310) Both navigation devices are supplied with rotational rate and acceleration measurement values from a common sensor unit in order to determine the positional angle measurement values. In the process, the first navigation device (310) produces erroneous measurements of the positional angle measurement values with a probability which is lower than as specified positional angle error rate, and the second navigation device (320) produces erroneous measurements of the positional angle measurement values with a probability which is higher than the specified positional angle error rate.

Abstract: The invention relates to a system for monitoring movements of a structure (1), which system comprises at least one inertial measurement device (5), mounted on said structure, for detecting rotation rates and acceleration values in the earth-fixed inertial system. A central unit (11) determines a monitoring value on the basis of the rotation rates and acceleration values, using a navigation algorithm. The invention further relates to an output unit (12) for outputting the monitoring value.

Abstract: An endoscopic suturing machine, having a housing with a housing upper part for receiving drives for the stitch-forming tools, a housing shaft adjoining the housing upper part for a receiving device for transmitting the motions generated by the drives to the stitch-forming tools, which have at least one needle bar guided in the housing shaft with a thread-carrying needle and a shuttle cooperating with same for forming stitches. The shuttle is received by a shuttle bar. The needle bar (5) is designed as a hollow body for receiving and guiding the thread. The thread guide elements are arranged between the thread spool 31 receiving the thread reserve and the needle bar (5) and are arranged in relation to the needle bar (5) such that the thread runs essentially in a straight line between the exit from the mounting device (17) and the entry into the needle bar (5).

Abstract: An endoscopic suturing machine, having a housing with a housing upper part for receiving drives for the stitch-forming tools, a housing shaft adjoining the housing upper part for a receiving device for transmitting the motions generated by the drives to the stitch-forming tools, which have at least one needle bar guided in the housing shaft with a thread-carrying needle and a shuttle cooperating with same for forming stitches. The shuttle is received by a shuttle bar. The needle bar (5) is designed as a hollow body for receiving and guiding the thread. The thread guide elements are arranged between the thread spool 31 receiving the thread reserve and the needle bar (5) and are arranged in relation to the needle bar (5) such that the thread runs essentially in a straight line between the exit from the mounting device (17) and the entry into the needle bar (5).

Abstract: In a GPS-supported inertial attitude and heading reference system equipped with a Kalman correction filter and a multiple axis fiber optic gyroscope, the invention provides for only that scale factor error which is determined for the measurement axis (e.g. the vertical axis) with relatively fast motion dynamics to be used as the Kalman filter correction value for the scale factor error correction for all the measurement axes of the FOG to determine and compensate for the scale factor error caused by changes in the wavelength of a common light source. The scale factor error correction is used only with a long time constant.

Abstract: In a GPS-supported inertial attitude and heading reference system equipped with a Kalman correction filter and a multiple axis fiber optic gyroscope, the invention provides for only that scale factor error which is determined for the measurement axis (e.g. the vertical axis) with relatively fast motion dynamics to be used as the Kalman filter correction value for the scale factor error correction for all the measurement axes of the FOG to determine and compensate for the scale factor error caused by changes in the wavelength of a common light source. The scale factor error correction is used only with a long time constant.