| Summary: | 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 .
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