| With the rapid development of satellites, missiles, aerospace and aviationtechnology, attitude measurement technology has become the core of the flightvehicle navigation technology. The accurate profile information can providedecision-making basis for the research and design to new weapons and evaluateits mobility and precision strike. So studying the high precision attitudealgorithms for the navigation system is the key to ensure efficient navigation.Aimed at the problems of install complexed,high precision,hard to calculate ofaccelerometer,a attitude determinatio based on Magnetoresistance sensor andGyroscopes is introduced to restrain the output error.Firstly, this paper describe the the basic theory of the geomagnetic field, thechoice of the type of the geomagnetic theory geomagnetic sensor and gyrosensor based on the basic theory of attitude test.Secondly, in order to improve the calculating attitude parameters ability of attitudemeasurement system, a data record designed with DSP as the microprocessor, to completeinertial measurement combination signal acquisition, storage, calculating attitude information.The reliability of the data recorder has carried on the design and test. Finally, according to magnetic sensor and gyro output characteristic, themathematical model of attitude solving algorithm are established. To improvecalculating precision,kalman filter with information fusion ability is designed.The turntable simulation and experiment verify the feasibility and reliability ofthe algorithm. Results show that kalman filtering algorithm effectivelysuppresses the cumulative error of gyro solving algorithm, attitude informationcan be calculated accurate,and algorithm accuracy can be improving.Application of kalman filtering algorithm design in this article to solutionthe storage data for data recorder.The result can reflect the real attitude of themeasured information. Therefore, the test programme has the meaning and valueof further research. |
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