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|  MIL-N-81497A(AS)
3.4.1.2.1 (Continued)
Note
During the Standby Mode, and only during the Standby
Mode, the Self Test Submode shall be initiated.
Inertial Mode - The Inertial Mode shall be the
3.4.1.2.2
primary mode of operation of the equipment. In this mode the equipment
shall operate as an unaided inertial navigator or as a Doppler velocity
aided inertial navigator depending upon the submode of operation se-
lected and the availability of external Doppler reference velocity.
Acceleration data obtained from the Gyroscope Assembly shall be used
to compute heading, velocity and present position to provide the earth
referenced output signals as listed in Table I. The Inertial Mode
shall have 3 submodes: Ground Alingnment, Navigation, and Doppler
Damping On.
During this mode, the equipment shall
Slave Mode -
3.4.1.2.3
operate as a pendulous attitude and heading system. Equipment heading
shall be slaved to the external ML-1 magnetic heading after compensation
for magnetic anomolies. The degree of synchronism of the equipment
heading output shall be indicated on the Control, Navigation. Output
functions provided in this mode appear in Table I. Earth's rate correction
signals shall be supplied using the latitude control on the Control,
Navigation to assist in maintaining attitude and heading performance
When external Doppler radar velocity is present, it shall also be
utilized in the maintaining of the attitude and heading performance.
Automatic erection cutoff techniques shall be employed to limit attitude
degradation due to aircraft maneuvers. Self contained initial alignment
processes shall be included to permit operation within 3.5 MIN after
startup.
3.4.1.2.4 Free Mode - During this mode, the equipment shall
operate as a pendulous attitude and heading system. Heading shall be set-
table to an initial datum using the Grid Slew control on the Control,
Navigation. Earth`S rate correction to the heading output shall be
provided using the Latitude control on the Control, Navigation. When
external Doppler radar velocity is present, it shall be utilized
in the maintaining of the attitude performance. Automatic erection
cutoff techniques shall be employed to limit attitude degradation due
to aircraft maneuvers. Output functions shall be listed in Table I.
Self contained initial alignment processes shall be included to permit
operation within 3.5 MIN after startup.
Compass Mode - An unstabilized Magnetic Heading
3.4.1.2.5
Mode shall be Provided in the event of either Gyroscope Assembly or
Computer, Navigation failure. Magnetic heading-slaving rate shall be
approximately 300 DEG/MIN. Table I delineates the output functions that
shall be provided in the Compass Mode.
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