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|  MIL-N-81604C(AS)
3.5.1.3 Inertial Stabilized Platform - The mechanization of the
inertial platform shall provide a compact, reliable design with
attitude stabilization at high angular rates.
3.5.1.3.1 Gimbal Order - The gimbal arrangement from inside to
out shall be: azimuth, inner roll, pitch, and outer roll. Outer
roll and azimuth shall have full rotational Ofreedom; pitch and
inner roll may be instrumented to have 100 and 17 of freedom
(minimum), respectively.
The redundant inner roll gimbal shall
provide angular isolation of the stable element during vehicle
maneuvers around pitch angles of 90. By this arrangement, the
gimbal system shall provide all-attitude operation.
3.5.1.3.2 Gimbal Drive - The inertial platform shall use torquer
motors of high torque capacity, such that the Platform will not
impose any limitation on aircraft maneuverability as specified
*
in table IV.
3.5.1.3.3 Gimbal Readouts - The pitch and outer roll gimbals
shall have synchro transmitters mounted on their respective
axes. The azimuth gimbal shall have a two-speed resolver
mounted on its axis.
3.5.1.3.4 Azimuth Resolver - There shall be an additional
resolver mounted on the azimuth gimbal for the purpose of
resolving the level gyro pickoff output signals into pitch and
roll axis coordinates.
3.5.1.3.5 Vibration and Shock Isolation - The gimbal system
shall be designed to minimize the vibration effects which can
degrade gyroscope and accelerometer performance. The basic
requirements for the isolation system are that it have a low
natural frequency, low resonant rise, and good decoupling at
high frequencies.
*
3.5.1.4 Gtro/Torquing Performance Characteristics - The IMU gyro
torquing performance characteristics shall, as a minimum require-
*
ment, conform to the parameters as set forth in table XV.
3.5.1.5 Accelerometer\Quantizer Output Performance Characteristics -*
The IMU quantizer output performance characteristics shall, as a
minimum requirement, conform to the parameters as set forth in
*
table XVI.
.
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