Print Email Facebook Twitter The long period errors of Doppler and inertial navigation systems Title The long period errors of Doppler and inertial navigation systems Author Smith, S.G. Thomas, I.L. Institution Royal Aircraft Establishment RAE Date 1966-03-31 Abstract 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 whitin 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 oscillatien is 24 heurs 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 heurs) with inertial systems. To reference this document use: http://resolver.tudelft.nl/uuid:fc6fa03f-81f8-46eb-8b5a-17e36a7666bd Publisher Ministry of Aviation, Royal Aircraft Establishment, RAE Farnborough Access restriction Campus only Source RAE Technical Report No. 66084 Part of collection Aerospace Engineering Reports Document type report Rights © 1966 Ministry of Aviation, Royal Aircraft Establishment Files PDF Tech_Report_66084.pdf 10.4 MB Close viewer /islandora/object/uuid:fc6fa03f-81f8-46eb-8b5a-17e36a7666bd/datastream/OBJ/view