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Ground Speed, True Track, and Track Rate
The velocities integrator calculates:
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Ground speed
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True track
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Track rate.
This data goes to the output memory buffer only when the track is valid and the ground speed is more than 20 knots.
Vertical, Along Track, and Cross Track Accelerations
The rotate accelerations to earth reference circuit calculates:
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Vertical acceleration
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Along track acceleration
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Cross track acceleration.
This data goes to the output memory buffer only when the accelerations are valid and the ground speed is more than 20 knots.
Body Normal, Body Longitudinal, and Body Lateral Accelerations
The accelerometers supply these linear accelerations to the output memory buffer:
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Body normal
*
Body longitudinal
*
Body lateral.
Flight Path Angle
The air data function of the ADIRU supplies barometric altitude to the calculate flight path angle logic through vertical blending filters.
The calculate flight path angle logic also gets data from the velocities integrator.
The flight path angle goes to the output memory buffer only when the flight path is valid and the ground speed is more than 20 knots.
Vertical Speed and Inertial Altitude
Altitude from the ADIRU air data computing function combine with the rotational rates and linear accelerations through vertical blending filters. This data goes to the output buffer as vertical speed and inertial altitude.
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ADIRS -ADIRU INERTIAL REFERENCE DATA FUNCTION -2
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ADIRS -ADIRU INERTIAL REFERENCE DATA FUNCTION -3
Output
The ADIRU transmits inertial reference data to the left and right flight control ARINC 629 buses. The inertial reference data goes to these components:
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Left and right AIMS cabinets
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Left, center, and right primary flight computers (PFCs)
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Left, center, and right autopilot flight director computers (AFDCs).
Only one of the two connections to each flight controls ARINC 629 bus is active at a time.
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ADIRS -AIR DATA MODULE
ADM General
There are six air data modules (ADMs) in the air data inertial reference system (ADIRS). Three are for pitot pressure and three are for static pressure. All the ADMs operate in the same manner.
The air data module (ADM) measures absolute pressure. This pressure comes from a pitot probe or static pressure port. The ADM transmits this pressure on a flight controls ARINC 629 bus for use by the ADIRU and SAARU. All ARINC 629 ADMs are interchangeable and can be a pitot or a static ADM.
The pitot ADMs control the heat for the pitot probes and the angle of attack (AOA) sensors.
ARINC 629 Interface
The left ADM transmits and receives on the left flight controls ARINC 629 bus.
The center ADM transmits and receives on the center flight controls ARINC 629 bus.
The right ADM transmits and receives on the right flight controls ARINC 629 bus.
ADM Physical Description
The ADM weighs 2.6 pounds. The ADM has one pneumatic connector and two electrical connectors.
The ADM has a flange on each side. Each flange has two captive screws. The ADM mounts directly to the mounting tray flanges.
The pneumatic connector seals itself when removed from the ADM. You do not need to plug the pneumatic line when you remove the ADM.
One electrical connector is for program pins and power. The other electrical connector is for ARINC 629.
ADM Operation
The ADM gets 28v dc for power.
The ADM receives pneumatic pressure from a pitot probe or static ports. The pressure sensor changes the pressure value to an analog signal. The analog signal goes through an analog to digital converter. The ADM calibrates the pressure and compensates for temperature. The ARINC 629 transmitter/ receiver sends the data on a flight controls ARINC 629 bus.
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ADIRS -AIR DATA MODULE
Program pins define the location of the ADM. The input/output decoder logic sends the program pin ADM location data to the processor. 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：777 AMM 飛機(jī)維護(hù)手冊(cè) 導(dǎo)航 Navigation 1(12)
