Purpose
This document sets forth the basic features for a 10 MCUInertial Reference System (IRS) consisting of the necessaryinertial measuring devices and associated electronics specificallydesigned for installation in commercial transport-type aircraft.This system provides the basic outputs for aircraft angular rateand acceleration, and computed outputs of attitude, true heading,magnetic heading, velocity and present position. The inertialsensor outputs can be utilized as the primary reference for cockpitinstruments and automatic flight control systems.
The inertial reference system outputs can also be used with adisplay unit to provide data for standalone navigation, or,alternately, be utilized by a navigation computer in associationwith other inputs to generate horizontal and vertical steeringsignals. The inertial reference unit may also be interfaced to anARINC 743A Global Positioning System (GNSS) system to enhance theaccuracy of the inertially derived navigation data.
The GNSS system comprises an antenna subsystem and a GNSS sensorunit (GNSSU). Computational capabilities to assimilate theGNSS-derived information are contained within the IRU.
- Edition:
- 99
- Published:
- 03/19/1999
- Number of Pages:
- 88
- File Size:
- 1 file , 4.2 MB
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