The paper presents the developed integrated GNSS/IMU gyrocompass which, unlike the existing systems, contains a single-axis rotating platform with two antennas installed on it and an inertial measurement unit with tactical grade fiber-optic gyros. It is shown that the proposed design provides attitude solution by observing the signals of only one navigation satellite. The structure of the integrated GNSS/IMU gyrocompass, its specific features and prototype model used in the tests are described. The given test results in urban conditions confirmed heading determination accurate to ±1.5° (3σ).
This paper examines the Implementation of the Inertial Measurement Unit (IMU) Sensor for Monitoring Rocket Attitude. The monitored rocket attitude data is in the form of vibration which is generated by the payload during the functional test and flight speed, acceleration and direction flight test. The rocket payload device is mounted in the rocket compartment for the function of measuring rocket behavior. Data is sent to ground stations via telemetry devices use baud rate of 57600. Based on the results of G-Shock, G-Force and Vibration testing shows that the payload can work well. In accordance with the results of reading the data on the Graphical user Interface (GUI) can be displayed and shows the rocket payload works well. This rocket payload can transmit data remotely.
Integrated GNSS/IMU-Gyrocompass with Rotating IMU. Development and Test Results
