A Study on Aerodynamic Model Applied to Aiding Inertial Navigation System

• Main Authors: Chen ,Feng-Heng, 陳豐亨
• Other Authors: T.M. Hsieh ; Jeng-Heng Chen
• Format: Others
• Language: zh-TW
• Published: 1995
• Online Access: http://ndltd.ncl.edu.tw/handle/86097435053893601461

碩士 === 中原大學 === 資訊工程研究所 === 83 === The main object of this paper describes a way to improve the precision of a hybrid inertial navigation system (INS) with aerodynamic model . A primitive hybird INS take advantage of global positioning system (GPS) to measure the position and the altitude of a flying body . Afer long flyiny time , the system error of the INS of the body is added because the error of the attitude of it is accumulated. 　　The external source of data , from GPS and aerodynamic model , of the flying body input to an indirect feedback Kalman Filter , an optimal filter , which combines them with the internal data from INS of the body for correcting the error of the INS . Because aerodynamic model compute the angle of the flying body , the error of the attitude of it can not be accumulated .　　Although only three motions were simulated , the results demonstrate that the way which uses additionally aerodynamic model can avoid happenning that the error of the INS of a flying body diverges because the errror for the attitude of it is not accumulated . So the way made the INS of a flying body have better precision .