A320飞机维护手册 AMM NAVIGATION 导航2(22)

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 the ECAM displays and by the FMGC to display a message on the MCDU.
 This mode needs a 30-second initialization phase with the aircraft in
 level flight. During this phase, all the ARINC bus outputs are sent
 with their status matrix coded NCD (No Computed Data). At the end of
 the initialization phase, the IR sends valid outputs:
 - body axis accelerations and angular rates
 - pitch and roll attitude and rate
 - vertical acceleration
 - vertical velocity
 - baro-inertial altitude and vertical speed.
 The magnetic heading may also be valid if an initialization value
 has been sent by the FMGC (through the MCDU) or the CDU (Ref. para.
 D - IR output data for the complete list of valid outputs).
 The GPIR ATT mode is activated when the IR is in ATT mode after
 manual selection on the ADIRS CDU.
 A GPIR ATT mode alignment processing is performed before Pseudo
 Range or Delta Range measurement are used to update the 21-state
 Kalman filter. The measurements and measurement matrices used for
 updating are the same as those used in the GPIR NAV processing. 
R  (3) Hybrid partition 
R  The ADIRU receives Global Position System Sensor data as defined by 
R  ARINC 743 and integrates it with the inertial reference data to 
R  produce a hybrid navigation solution. 
R  The Northrop Grumman ADIRU ensures the integrity of the hybrid 
R  solution using a unique GPS/IRS integration technique called 
R  Autonomous Integrity Monitored Extrapolation (AIME). The key to this 
R  mechanization is the ability to detect and isolate slowly drifting 
R  satellite clock drifts with as few as four satellites. AIME 
R  accomplishes this through a set of Kalman filter operations and a 
R  Failure Detection and Exclusion (FDE) mechanization. 
R  The ADIRS operational modes are slaved to the IR operational modes of 
R  Align, Navigate and Attitude Reference. The AIME function is not 
R  available if the IR is in the Attitude Reference Mode. 
R  When two MMR are installed on the aircraft, the ADIRU will select the 
R  primary input unless a fault is detected. 
R  In the case of a primary MMR fault, the secondary MMR will be 
R  selected for the hybrid solution. 
R  If both MMR are fault, the AIME may be able to extrapolate the GPIRS 
R  data depending on the flight phase.

 

 (1) Digital output characteristics The IRs have four independently buffered high-speed ARINC 429 digital output buses, designated bus output 1, 2, 3 and 4
 -digital output table: This table contains all the output parameters in the digital form. They are sorted as per the numerical order of their output label. The following table gives:
 -EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available
 -PARAMETER DEFINITION: parameter name
 -RANGE ACCURACY : measurement range maximum value transmitted. When the digital value changes, the change step is equal to the accuracy
 -UNIT : unit in which the digital value is transmitted
 -SIG BIT : indicates whether a sign bit is available
 -BITS : number of bits used by the parameter in the label
 -UPD/MSEC : output transmission interval. The refresh rate is given in milliseconds.
 -CODE:
 BNR: binary data word
 BCD: binary coded decimal data word
 ISO: data word coded in ISO5 code
 DIS: discrete data word
 HEX: hexadecimal coded
 HYB: mixed code.

 -ALPHA CODE: indicates the parameter mnemonic code
 -SOURCE ORIGIN: parameter source computer or system. When the GPS PRESENT programming pins input discretes are grounded (indicating GPS present), both the GPSSU outputs and the GPIRS integrated navigation solution outputs are transmitted on the IR output buses with the IR output data.
 1EFF : 001-004, 1 34-14-00Page 13 1 1 Config-1 Aug 01/03 1 1 1CES 1

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| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | -------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | -------------------------------------------------------------------------------| 010 |PPOS LAT |W +/- 180 |Deg | | 6 |500 |BCD |LATP | | | | |90S-90N |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 011 |PPOS LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |180E-180W |& | | | | | | | | | |0.1 |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 012 |GROUND |W 0 to 4096 |Kts | | 4 |500 |BCD | GS | | | |SPEED |0 to 1000 | | | | | | | | | | |R 1 | | | | | | | | | | |+/- 8 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 013 |TRK ANGLE |W 0 to 359 |Deg | | 4 |500 |BCD | | | | |TRUE |R 0.1 | | | | | | | | | | |+/- 2.3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | | | | |R 0.1 | | | | | | | | | | |+/- 3 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | | | | |R 1 | | | | | | | | | | |+/- 9 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | | | |TRUE |R 1 | | | | | | | | | | |+/- 10 | | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |90S-90N |& | | | | | | | | | |R 0.1 min |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | | | | |R 0.1 min |& | | | | | | | | | | |mn | | | | | | | |--------------|----------|------------|----|----|----|----|----|-----|-------| | 043 |SET MAG |W 0 to 359 |Deg | | 3 |500 |BCD | | |
　
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