Attitude Algorithm Based On The Thin Film Geomagnetic Sensor

The attitude test has always been the core technology of the weapon precision-guided，lots of research have been invested in this regard at home and abroad. To obtain and calculatethe missile attitude information accurately is an important task in navigation technology.Aimed at the small range and drift deviations of the gyroscope, and the installation deviationsand complex solver algorithm of the accelerometer, a test technical program based on the thinfilm geomagnetic sensort is put forward for rotating missile attitude test.The main work of this thesis as follow:Firstly, based on the introduction of the attitude test basic theory, the geomagnetic field,geomagnetism sensor type and content of the geomagnetic sensor selection was introduced inthis thesis.Secondly, an attitude test system based on the thin film geomagnetic sensor was designedfor the missile attitude test demand. According to the geomagnetic sensor output’ scharacteristics, the geomagnetic sensor output model was established, and then a calibrationspeed algorithm based on the envelope and the attitude determination algorithm based on theimproved Euler method for the test program were proposed for the designed system.Finally, by the tri-axial non-magnetic turntable experiment and MATLAB simulation, thefactors that affect the accuracy of the thin film geomagnetic sensor were analyzed, and thenthe reliability and stability of the test technical program proposed were validated.As the thin film geomagnetic has the advantages of simple installation and its deviationdoes not accumulated over time, it will be widely used in the inertial navigation system. Theproposed test technology program based on the thin-film geomagnetic sensor not only canobtain the missile attitude information in the whole flight accurately, but also has theadvantage of wide test range and simple resolving algorithm, can be an effective accordancefor improving the missile body’s guidance accuracy.