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INSTRUMENTATION > PT3 - Inertial nav & FMS & EFIS & FANS > Flashcards

PT3 - Inertial nav & FMS & EFIS & FANS Flashcards

1
Q

INS

A

Inertial Navigation System

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2
Q

INS _ Platform (= mounted on a gimbal assembly)

A

2 accelerometers (N/S and E/W)
Possible third for vertical acceleration
3 integrating gyros (Long, Lateral, Normal)
3 gimbal motors (Pitch, Roll, Vertical)

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3
Q

Integrator

A

Time multiplication device

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4
Q

Integrating gyroscope

A

One degree of freedom gyro using viscous spring

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5
Q

INS _ Compensate for apparent wander

A

Earth rate : 15 sin(lat)

Transport rate : V/R (R = earth radius)

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6
Q

INS _ Alignment

A 
Accelerometers leveled (velocity set to 0)
Platform orientated to True North
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7
Q

INS _ Alignment steps

A

Warm up period
Coarse alignment : roughly leveled and aligned in azimuth
Coarse leveling : pitch and roll at 90°
Fine leveling : zero output from accelerometers
Gyro compassing : verification of position

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8
Q

Schuler period

A

Oscillation of 84.4 minutes

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9
Q

Bounded error

A

Return to 0 within the Schuler cycle

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10
Q

Unbounded error

A

Cumulative error

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11
Q

INS mode

A

OFF - STBY - ALLIGN - NAV - ATT REF

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12
Q

INS _ STBY mode

A

Power supplied

Insert the start position

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13
Q

INS _ ALLIGN mode

A

Platform leveled and aligned

  • -> READY NAV illuminate
  • -> switch to NAV mode
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14
Q

INS _ ATT REF mode

A

Disconnect computing and loses alignment

Gyros used for attitude and heading informations

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15
Q

INS _ BATT light

A

INS running on battery

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16
Q

INS _ NAV mode

A

Used for navigation

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17
Q

INS _ FROM/TO display

A

Waypoints between which INS assume it is flying

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18
Q

INS _ DIM control

A

Change the brightness

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19
Q

INS _ ALERT light

A

Aircraft approaching next waypoint
2 min before in auto mode
2 min before : on - 30 sec : flashing in manual mode

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20
Q

INS _ WARN light

A

System malfunction occurs

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21
Q

INS _ AUTO-MAN_RMT switch

A

Pilot implication

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22
Q

INS _ INSERT control

A

Enter info into the system

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23
Q

INS _ HOLD control

A

Update INS position

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24
Q

INS _ TK/GS display

A

Aircraft track - Ground speed

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25
INS _ HDG/DA display
True heading - Drift angle
26
INS _ XTK/TKE display
Cross track distance - Track angle error
27
INS _ POS display
Present latitude - Present longitude
28
INS _ WPT display
Waypoint latitude - Waypoint longitude
29
INS _ DIS/TIME display
Distance to next waypoint - Time to next waypoint
30
INS _ WIND display
Wind direction - Wind speed
31
INS _ DSR TRK/STS display
Desired track - Blank
32
INS _ TEST display
All digits illuminates
33
INS _ Waypoint 0
Last INS position change
34
INS _ Initial set up
Slight latitude error : not recognized by INS Gross latitude error : recognized by INS Wrong longitude input : not verified
35
IRS
Inertial Reference System
36
IRS _ System
Strap down system | Laser gyros
37
INS _ System
Stand alone system | Mechanical gyros
38
Inertial navigation
Determination of vehicule's location without external reference
39
IRS _ Outputs
``` Primary attitude Heading Acceleration Angular rate Inertial velocity Position Wind data Calculated data ```
40
INS _ Outputs
``` Primary attitude Heading Acceleration Position Track Angle Error Distance to waypoint Time to waypoint ```
41
IRS _ Inputs
``` 3 laser gyros 3 inertial accelerometers Initial position Barometric altitude True Air Speed ```
42
IRS _ Laser gyros
Based on Sagnac effect
43
Sagnac effect
2 beams of light rotating in opposite direction Condition : whole number of wave length Measure of a frequency difference --> Compute a rotation
44
IRS _ Laser gyros - Construction
``` 3 mirrors 2 beams of light Helium neon 2 photo electric cells 1 piezo electric dither motor ```
45
IRS _ Laser gyros - Drift
Major source of error
46
IRS _ Laser gyros - Accuracy
The longer the path the greater the accuracy
47
IRS _ Laser gyros - Lock in
Synchronization of the beams | --> no more fringe pattern
48
IRS _ Alignment
True North : with earth rotation measured Latitude : compute and compare with the inserted one Alignment : mathematical leveling process = Establishing the trihedron
49
IRS/INS _ Advantages
Activation : no spin up time Maneuvering : insensitive to "g" attitude Construction : mechanically simple and highly reliable Range : wide dynamic range Drift : small drift rates
50
Radio altimeter _ Principle
Measuring aircraft's height above ground level from 2500ft.
51
Radio altimeter _ Use
Automatic landing system | Ground Proximity Warning System (GPWS)
52
Radio altimeter _ Emission
Frequency Modulated Continuous Wave | Change of frequency between emission and reception : compute frequency difference
53
SHF band
4200 to 4400 MHz
54
UHF band
1600 to 1660 MHZ
55
Radio altimeter _ Working angles
Pitch : 30° | Bank : 60°
56
Radio altimeter _ Pointer
Disappear behind mask Altitude over 2500 ft. Fault in transmitted signal Altimeter switched off
57
Radio altimeter _ Press to test button
Press : turn the indicator = test | Turned : select a Low Altitude Index
58
Radio altimeter _ Boeing
2500 to 1000 ft. : nothing 1000 ft. to decision height - 100 ft. : white circle decision height - 100 ft. to decision height : amber circle
59
Radio altimeter _ Accuracy
Higher between 3% and 1 ft.
60
Radio altimeter _ Delay
Residual height = difference between antenna on the fuselage and bottom of the trailing wheels Cable length
61
FSM _ LNAV
Lateral NAVigation
62
FSM _ VNAV
Vertical NAVigation
63
CDU
Control Display Unit
64
FGS
Flight Guidance System
65
FMC
Flight Management Computer
66
ADC
Air Data Computer
67
GPS
Global Positioning System
68
FMS _ CDU
Interface between aircraft and crew
69
FMS _ CDU - Independent mode
Decoupled operation
70
FMS _ CDU - Dual mode
2 computation compared
71
FMS _ CDU - Single mode
1 FMS active and distribute to 2 CDU
72
FMS _ Navigation database
Information referring to navigation charts Valid for 28 days (Nav aids, airports, runways, SIDs, STARs, approaches, company routes)
73
FMS _ Performance database
Information required to compute pitch and thrust commands
74
FMS _ Initial action
IDENT - POS INIT - RTE - PREF INIT - TAKE OFF
75
FMS _ IDENT page
Check databases & OS present and valid for aircraft model
76
FMS _ POS INIT page
Insert position and check for time
77
FMS _ RTE page
Enter starting and destination airport, select a route, flight number
78
FMS _ PERF INIT page
Weight (gross; zero fuel), fuel (qty; reserves), altitude (cruise; transition), cost index, high level winds
79
Cost index
Operating cost / Fuel cost
80
FMS _ LNAV
Great circle path
81
FMS _ Accuracy
Less than 0.5 NM/h
82
FMS _ CDU keys
Alphanumeric Function Line select
83
FMS _ MSG Annunciator
Color = white | Alerting or advisory message
84
FMS _ FAIL Annunciator
Color = amber | FMC failure detected
85
FMS _ DISPLAY Annunciator
Color = white | Page displayed not relative to active flight plan
86
FMS _ OFFSET Annunciator
Color = white | Actually flying on a trajectory with an offset
87
EFIS
Electronic Flight Instrument System
88
EFIS _ Displays
Attitude and navigation information Attitude Director Indicator (ADI) Horizontal Situation Indicator (HSI)
89
EFIS _ Components
``` Attitude Director Indicator (ADI) Horizontal Situation Indicator (HSI) Control panel Symbol generator Remote light sensor unit ```
90
EFSI _ Display unit
Cathode Ray Tubes OR Liquid Crystal Displays (LCD) : smaller & less heat
91
EFSI _ Colors
White : present situation Green : present situation with less priority Magenta : 'fly to' informations Cyan : sky heading & low priority information Yellow : ground shading & caution information display Red : heaviest precipitations levels
92
EFSI _ Remote Light Sensor
Automatically adjust the brightness
93
EFSI _ ADI control panel
BRT : brightness control DH SEL : selector for decision height DH RST : reset for decision height DH REF : display decision height
94
EFSI _ ADI display
``` Pitch and Roll attitude Attitude from IRS Flight director commands Localizer and glide slope deviation Ground speed Radio altitude Decision height Automatic Flight Control System Speed error scale ```
95
Decision height
Height above runway elevation by which a go around must be initiated unless adequate visual reference has been initiated
96
EFSI _ Full VOR mode
Full compass rose ``` VOR frequency Selected course Course deviation TO/FROM pointer and annunciator DME distance Current heading Current track Selected heading Wind speed and direction ```
97
EFSI _ Expanded VOR mode
90° of compass rose ``` VOR frequency Selected course Course deviation TO/FROM annunciator DME distance Current heading Current track Selected heading Wind speed and direction ``` Weather radar available with range arcs
98
EFSI _ Full ILS mode
Full compass rose ``` ILS frequency Selected course Localizer deviation Glide slope deviation DME distance Current heading Current track Selected heading Wind speed and direction ```
99
EFSI _ Expanded ILS mode
90° of compass rose ``` ILS frequency Selected course Localizer deviation Glide slope deviation DME distance Current heading Current track Selected heading Wind speed and direction ``` Weather radar available with range arcs
100
EFSI _ Map mode
Moving map background 90° of a compass rose ``` Heading Active route Active waypoint & Inactive waypoint Distance & Time to next waypoint Wind speed and direction Lateral & Vertical deviation from selected flight path ``` Weather radar available with range arcs
101
EFSI _ Plan mode
Static map background orientated to True North Top portion same as map Planned route
102
EFSI _ Failure annunciation
Failure of data signal displayed | Faul messages displayed
103
Present track
Predicted ground track from present heading and wind
104
Computers
Device or set of device that can store data and a program that operates on the data
105
Computers _ Basic components
Input device Output device Memory CPU
106
Computers _ CPU
Arithmetic Logic Unit (ALU) Shift registers Control unit
107
Computers _ ALU
Arithmetic calculations and logical operations
108
Computers _ Shift registers
Temporary stores
109
Computers _ Control unit
Computer's clock | Synchronize computer operations
110
ROM
Read Only Memory
111
PROM
Programmable Read Only Memory
112
EPROM
Erasable Programmable Read Only Memory
113
EEPROM
Electronically Erasable programmable Read Only Memory
114
Volatile memory
Loses data when shut down
115
Non-volatile memory
Keep data when shut down
116
RAM
Random Access Memory | Normally volatile
117
Permanent memory
Electronic chip Optical disk Magnetic disk
118
Computers _ Software safety
EUROCAE
119
Computers _ Level A
Catastrophic
120
Computers _ Level B
Hazardous
121
Computers _ Level C
Major
122
Computers _ Level D
Minor
123
Computers _ Level E
No effect
124
FANS _ ATC
Use radar to provide a positive control | Use VHF communications
125
FANS _ position update crossing the Atlantic
Every 30 to 60 minutes
126
FANS _ GNSS
Global Satellite Navigation System
127
FANS _ VHF limitation
200 NM
128
FANS _ SATCOM limitation with geostationary satellites
80° of latitude
129
FANS _ Data link
Connecting one location to another for the purpose of transmitting and receiving informations
130
FANS _ Uplink
From ground to satellite or airborne platform
131
FANS _ Downlink
From satellite or airborne platform to ground
132
FANS _ Organizations providing Data Link to aviation
Société Internationale de Télécommunication Aéronautiques (SITA) Air Radio Incorporated (AIRINC)
133
FANS _ Equipment for Data Link
Communications Management Unit (CMU) Data Communications Display Unit (DCDU) Multi Control and Display Unit (MCDU) Printer
134
FANS _ ACARS
Uses Data Link Messages between aircraft and Air Trafic Controller (ATC) Aircraft Operating Companies (AOC)
135
FANS _ ATSU
``` Provide: Flight information service Alerting service Air Traffic Advisory Service Air Traffic Control Service ```
136
FANS _ AOC important messages
Out of Gate Off Ground On Ground In Gate
137
FANS _ Logon
Manual logon to access the Data Link service
138
FANS _ FANS
Provide an integrated air traffic control system in areas where radar is not available
139
FANS _ FANS A
Communications, Navigation and Surveillance (CNS) Automatic Dependent Surveillance (ADS) Transmitted over the ACARS network
140
FANS _ ADS contracts
Periodic On demand On event Emergency
141
FANS _ CPLCD
Permis Data Link messages to be generated for all stages of flight
142
FANS _ FANS B
Operates within High Density airspace having good VHF coverage
143
Great circle displacement
shortest distance between two points on earth
144
INS _ Latitude
N/S acceleration integrated
145
INS _ Longitude
N/S acceleration integrated Use of a seccent gear to compute longitude E/W acceleration integrated
146
ILS
Instrument Landing System
147
DME
Distance Measuring Equipment
148
FMS _ Use
From climb after aircraft is cleaned up until LOC capture
149
EFSI _ HSI limit
Magnetic North between 73°N and 65°S
150
EFIS _ Engaged mode color
Green
151
EFIS _ Armed mode color
White / Cyan
152
EFIS _ Limit of flight enveloppe color
Red
153
FMS _ Position computing
2 INS/IRS : mean of INS/IRS positions + RadioNAV | 3 INS/IRS : ?
154
FMS_ TAKE OFF page
Check take off speeds

INSTRUMENTATION (3 decks)

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