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Questions for INERTIAL NAVIGATION SYSTEM (INS)

Answer the following questions

1. The computer of a north referenced Inertial Navigation System (INS) in flight, provides compensation for:
2. During initialisation of an INS the aircraft must not be moved until
3. Two checks that can be carried out to check that two selected sequential waypoints have been entered correctly are:
4. INS errors are classified as “Bounded errors” and “Unbounded errors”
5. In an INS the E/W accelerations are converted into an E/W speed (kt) at the first stage of integration and into E/W distance gone (nm) at the second stage of integration. This gives
6. At the second stage of integration E/W speed is converted into E/W distance gone. To convert this departure into change of longitude is has to
7. With reference to Inertial Navigation Systems, the functions of the integrators are: i) at the second stage of integration to suppress unbounded errors (when in the NAV mode). ii) at the first stage of integration to convert acceleration, with respect to time, into speed, (when in NAV mode). iii) at the second stage of integration to convert speed, with respect to time, into distance gone, (when in the NAV mode). iv) to align the platform (when in the level and align modes).
8. The amber ALERT light on an INS control and display unit