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AUTOTILT MODE
Autotilt automatically adjusts the antenna tilt angle to attempt to keep the radar scanning approximately the same region of space when the aircraft climbs and descends.
Autotilt is designed to reduce the number of times the aircrew needs to adjust the TILT control whenever the aircraft altitude or radar range setting changes.
Autotilt may be selected on or off when the RADAR menu is active, or anytime the radar tilt value show on the on-side display. Autotilt may be enable continuously as the system always uses the current manual tilt setting as the starting point.
RADAR ANTENNA
The antenna sweep is selectable for either 120 degrees (60 degrees each side of the airplane) or 60 degrees (30 degrees each side). The antenna tilt is adjusted between -15 degrees (down) and + 15 degrees (up). The antenna maintains its stabilization with respect to the horizon regardless of the airplane attitude (within -15 to +15 degrees).
ANTENNA
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
17-01-32
DESCRIPTION
The Rockwell Collins FMS-5000 Flight Management System single or dual FMS is a fully integrated navigation and flight management system designed to provide the pilot with the following features:
-En-route, terminal, and Non-Precision Approach Lateral and Vertical Navigation with automatic transition to the
Precision Approach.
-Flight plan management.
-Multi sensor navigation.
-Maps and text data display.
-Performance management.
The system is integrated with a GPS receiver which processes the transmissions from multiple GPS satellites simultaneous-ly to calculate navigation solutions based on information from all satellites available. A minimum of four satellites with acceptable geometry, or three satellites plus calibrated barometric altitude are required in order to calculate a navigation solution. The computed GPS position, velocity and time are inputs to the FMS, which integrates this data into the flight plan based navigation solution. AHRS, ADC, DME, and VOR systems also supply data for use by the FMS. The FMS pro-vides necessary controls for all input sensors, when appropriate, via the control display unit (CDU).
When a single FMS system is installed, it is operated via the CDU installed on the right side of the center pedestal. When two FMS systems are installed, each CDU controls its on-side FMS.
The FMS can be initialized, waypoints and destination selected by a variety of means. SID, STAR, and airways are accom-modated. A great circle route is calculated between waypoints for enroute lateral navigation (LNAV), and roll steering is provided to the flight control system (FCS). A sophisticated interface with the FCS allows the FMS vertical navigation (VNAV) function to select various FCS vertical modes of navigation. This sophisticated VNAV interface is often referred to as coupled VNAV. The VNAV and LNAV capability can be advisory only, if the FMS is not coupled. The FMS provides vertical steering when required by the FCS.
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