HighlightsA configuration of distributed accelerometers with the aid of one gyro is proposed.The MEMS accelerometer and gyro sensors are integrated to form a GR-IMU.The development of accelerometer and gyro calibration procedure for the GR-IMU.Using GR-INS to avoid estimation of angular acceleration of rigid body motion.The GR-INS can be used to find a complete attitude solution for flight motion estimation.
AbstractIn this paper, a novel configuration of strategically distributed accelerometer sensors with the aid of one gyro to infer a flight vehicle’s angular motion is presented. The MEMS accelerometer and gyro sensors are integrated to form a gyroscope-reduced inertial measurement unit (GR-IMU). The motivation for gyro aided accelerometers array is to have direct measurements of angular rates, which is an improvement to the traditional gyroscope-free inertial system that employs only direct measurements of specific force. Some technical issues regarding error calibration in accelerometers and gyro in GR-IMU are put forward. The GR-IMU based inertial navigation system can be used to find a complete attitude solution for flight vehicle motion estimation. Results of numerical simulation are given to illustrate the effectiveness of the proposed configuration. The gyroscope-reduced inertial navigation system based on distributed accelerometer sensors can be developed into a cost effective solution for a fast reaction, MEMS based motion capture system. Future work will include the aid from external navigation references (e.g. GPS) to improve long time mission performance.
Gyroscope-reduced inertial navigation system for flight vehicle motion estimation
Advances in Space Research ; 59 , 1 ; 413-424
2016-09-01
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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