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The ADC calculates the following air data parameters:
-Pressure altitude
-Static pressure
-Total pressure
-Vertical speed
-Airspeed
-Mach number
-Maximum airspeed (VMO)/maximum mach number (MMO)
-Baro correction
-Barometric corrected altitude
-Static air temperature
-Total air temperature
-True AIRSPEED
-Temperature difference from standard (ISA)
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
11-01-12 AIR DATA SYSTEM (Cont)
PITOT STATIC SYSTEM
The aircraft is equipped with a primary pitot static system and a standby pitot static system. The primary pitot static system provides total and static pressures to air data computers (ADC) 1 and 2. The pressures are sensed by left and right pitot static probes. The standby pitot static system provides total and static pressures to the integrated standby instrument. The pressures are sensed by a standby pitot probe and two flush mounted standby static ports.
The primary pitot static probes each have one total pressure port and two static pressure ports. The standby pitot probe has a single pressure port. All of the probes and the flush standby static ports are electrically heated. Probe heat is discussed in Chapter 14, Ice and Rain Protection.
STANDBY PITOT PROBE
LEFT STANDBY STATIC PORT
Feb 22/2006 Flight Crew Operating Manual Volume 2 REV 5 CSP 100-6
11-01-13 AIR DATA SYSTEM (Cont)
TOTAL AIR TEMPERATURE PROBE
An electrically heated total air temperature (TAT) probe is mounted on the right forward fuselage. The TAT probe has two independent temperature sensors. One sensor is connected to ADC 1 and the other to ADC 2.
The ADCs use the total air temperature to calculate the static air temperature (SAT) and the true airspeed (TAS).
The use and distribution of the pitot and static sources are as follows:
-P1 is the normal pitot input to ADC 1
-S1 is the normal static input to ADC 1
-P2 is the normal pitot input to ADC 2
-S2 is the normal static input to ADC 2
-
STANDBY
P2 S1S2 STATIC
STATIC
LEGEND
PITOT STATIC
CFO1101002_028
Volume 2 Flight Crew Operating Manual Feb 22/2006 CSP 100-6 REV 5
11-01-14 ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS)
INTRODUCTION
The aircraft attitude and heading reference system (AHRS) is a strapped gyro reference system that generates angular rate and linear acceleration information about the aircraft axes.
Combining the acceleration gyro information with heading data from the flux detector provides highly accurate three-axes AHRS information.
The AHRS interfaces with the following systems:
-EFIS
-Weather radar
-Autoflight control system (AFCS)
-Flight data recorder (FDR)
-Integrated avionics processor system (IAPS)
-Terrain awareness warning system (TAWS)
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