(2)
attitude (pitch, roll, yaw)
(3)
true and magnetic heading
(4)
windspeed and direction
(5)
velocity
(6)
accelerations
(7)
angular rate data
(8)
altitude
E. The IRS outputs are displayed on the flight instrument system displays. They are also displayed on the flight management computer system control display unit (FMCS-CDU) (Ref 34-62-00). Preselected parameters are also displayed on the inertial system display unit (ISDU).
2. IRS Theory of Operation_______________________
A. General (Fig. 3)
(1)
The IRS provides basic heading and attitude reference accomplished through computations based on accelerometer and laser gyro sensed signals. Three accelerometers and three laser gyros are used. The accelerometers and laser gyros are of the strap-down type and are positioned in the inertial reference units so that they are oriented along each of the three axis of the airplane. This orientation allows the IRU to sense accelerations along and rotation about each of the three axis. Computer manipulation of the signals from all six sensors provide the basic heading and attitude reference signals along with present position, accelerations, ground speed, drift angle and attitude rate information. The first requirement which must be met for proper IRS operation is alignment. IRS alignment basically consists of determination of local vertical and initial heading.
(2)
Alignment (Fig. 4)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-28-00
ú ú 04 Page 1 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
AFT OVERHEAD PANEL FORWARD OVERHEAD PANEL
SEE H I SEE D
PILOTS
LIGHTSHIELD
SEE K
FIRST OFFICER'S PANEL
CAPTAIN'S PANEL SEE C E F
SEE C E F
FORWARD P10 PANEL
ELECTRONICS PANEL SEE J INERTIAL REFERENCE
SEE G UNIT 1 AND 2
SEE A
E-1 RACK
MAIN EQUIPMENT
CENTER DAA 1 AND 2 E-3 RACK
SEE B
E-2 RACK
FAULT INDICATOR
TOTAL TIME YELLOW = FAULT
INDICATOR BLACK = OK
TEST SWITCH
INERTIAL REFERENCE UNIT
DIGITAL/ANALOG ADAPTER AB Inertial Reference System Component Location Figure 1 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-28-00
ú ú 05 Page 2 ú Mar 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
VHF NAV COMPASS
BOTH BOTH BOTH BOTH
ON 1 ON 2 ON 1 ON 2
NORMAL NORMAL
ATTITUDE
BOTHBOTH
ON 2ON 1
NORMAL
COMPASS AND ATTITUDE TRANSFER SWITCHES
HSI ADI
Inertial Reference System Component Location
Figure 1 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-28-00
ú ú 10 Page 3 ú Feb 25/87
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
IRS MSU
FLT CONT ELEC
IRS APU
FUEL OVHT/DET
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 導航 NAVIGATION 2(13)
