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|  MIL-S-85018A(AS)
fast erection. Protective devices shall be provided which prevent application
when higher design or command functions are in operation or when thermal damage
can occur.
3.5.1.1.3.2 Automatic Fast Erection - Fast erection shall be automatically
initiated after initial power application and after loss of power as specified
herein. Fast erection shall be terminated and the system shall revert to normal
First Order erection when roll and pitch errors are detected to be no greater
than plus or minus .5 degree and the time since power has been applied is one
minute minimum.
3.5.1.1.3.3 Lateral Acceleration -An accelerometer mounted on the Dis-
placement Gyroscope with associated circuitry shall be provided to cut off the
roll erection during horizontal turn accelerations. For aircraft lateral
accelerations of plus or minus .07 plus or minus .02g or greater the roll
erection shall be reduced to cutoff. For lateral accelerations of .35 .05g,
pitch erection shall be cut off.
3.5.1.1.3.4 Fore-Aft Acceleration - An accelerometer mounted on the Dis-
placement Gyroscope with associated circuitry shall be provided to cut off the
pitch erection during horizontal fore-aft acceleration. For aircraft longitudi-
nal accelerations of plus or minus .07 plus or minus .02g or greater, the pitch
erection shall be cut off.
3.5.1.1.3.5 Earth's Rate Compensation - Precision torques from latitude
setting of Controller shall be applied to the vertical gyro to compensate for
apparent drift due to the rotation of the earth.
3.5.1.1.4 Erection Cycle - Second Order - pitch and roll erection shall
automatically sequence to the Second Order mode after the completion of the
initialization sequence or completion of the fast erection cycle and when the
system receives a valid velocity reference input. In this mode the reference
velocities resolved by the system into a compatible coordinate frame shall be
compared to the system velocities derived within the Second Order erection
loops. Differences from the velocity comparisons shall be utilized to damp the
Second Order erection control loop and produce the system vertical performance
of 3.4.2.
3.5.1.1.5 Reference Velocity Preference - Upon completion of the First
Order erection cycle (3.5.1.1 ), the system shall immediately switch to the
damped Second Order using the valid velocity reference. If at the completion of
First Order erection, the velocity reference source is unreliable, the system
shall remain in the compensated First Order erection. Thereafter, if the
reference velocity source is determined valid after 2 plus or minus 2 seconds
the system shall automatically sequence to damped Second Order erection utiliz-
ing the valid reference velocity.
3.5.1.1.6 Roll Performance - The roll outputs shall provide a measure of
angular displacement about the longitudinal axis of the aircraft. The assem-
bly's roll-output angle shall increase for a rotation about the aircraft longi-
tudinal axis that causes the right wing to drop below the horizontal plane.
Roll shall have a range of plus or minus 180 degrees.
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