THE LONG PERIOD ERRORS OF DOPPLER AND INERTIAL NAVIGATION SYSTEMS.
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)
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Dead reckoning navigation systems making use of gyros have to take account of the earths rotation and the vehicles motion round the earth since these rotations will be sensed by the gyros. In general the gyro correction terms are functions of latitude and therefore the system generates a feedback loop within itself since the final output latitude is used to correct the mechanism which is producing this output. By good fortune the sense of this feedback in most cases is such that the errors are oscillatory rather than divergent. The period of oscillation is 24 hours for a stationary I.N. system but in general this is modified by the E-W component of vehicle velocity. The effects are shown to have little significance in Doppler systems but are helpful in some cases of long flights 4 hours with inertial systems. Author
- Navigation and Guidance