Honeywell !#!#ii.cE
Dimensions (maximum):
Length ....................................
15.13 in. (384.3
mm)
Width ......................................
4.91 in. (124.7 mm)
Height .....................................
7.62 in. (193.5 mm)
Weight (approximate) ............................
13.1 lb (6.04 kg)
Power Requirements ..................................
28Vdc, 40W
Mating Connector:
J1 ...................... Cannon Part No. DPX2-67S-106P-33B-OOO4
J2 ...................... Cannon Part No. DPX2-67S-106P-33B-OO17
Mounting ..................... Tray, Honeywel1 Part No. 7003272-902
FZ-820 Flight Guidance Computer
Leading Particulars
Table 7-1
The FZ-820 Flight Guidance Computer (FGC) processes information about
aircraft actual attitude versus a desired attitude as a function of
selected flight mode to produce autopilot pitch, roll, and yaw contro”
outputs and flight director pitch and roll steering command outputs.
addition to the modes selectable on the GP-820 Flight Guidance
Controller, the computer will produce pitch and roll control outputs ~
any flight director mode except go-around.
the
In
or
The FGC has a dual processor architecture, each Drocessor Derformina
different control and computational functions. the A-processor per~orms
the outer-loop flight control computations while the B-processor performs
the inner-loop flight control computations, as well as the autopilot and
yaw damper servo loop closures.
Each processor monitors the other
processor’s flight control functions as well as its own functions. Each
processor has dedicated program memory and scratch pad memory. The data
gathered by the A-processor through the ASCB is simultaneously stored in
the bus data transfer RAM for access by the B-processor.
The status transfer RAM is used to exchange status information between
the A and B processors.
This transfer occurs once per 25 ms real time
cycle.
In addition, a set of discretes is provided for immediate
interaction between the processors.
22-14-00
Page 198.39
Aug 15/91
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