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Nav Final Flashcards

1
Q

aim of basic phase

A

introduce to ct-142
intro to flight ops & multicrew environment
develop nav and comms call

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2
Q

what is INS

A

inertial navigation system: a navigation aid that uses a computer and accelerometers to continously calculate via DR the position, orientation and velocity of a moving object w/o external references

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3
Q

generic INS components

A

accelerometers
computers
cdu
stable platform

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4
Q

advantages of INS (6)

A 
self-contained
undetectable
unjammable
all wx
worlwide ops
accurate px and very accurate altittude
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5
Q

how INS calculates positions

A

acceleration = velocity -> velocity = distance

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6
Q

mechanical INS

A

free moving stable platform that uses gymbals and gyros to maintain a level reference for the accelerometers to sense movement

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7
Q

strapdown INS

A

all modern INS’s mounted to the a/c frame. the level reference is calculated by computers

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8
Q

advantages of a strapdown system (reduces):

A

weight/hardware
power consumption
maintenance
cost

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9
Q

advantages of a strapdown system (increases):

A

reliability

service life

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10
Q

what is an accelerometer

A

a basic device for measuring accelerations

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11
Q

desired characteristics of an accelerometer (4)

A

low threshold of sensitivity
wide range of sensitivity
linear output
high resolution

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12
Q

basic part of stable platform (5)

A 
gyros
gimbals
ac servo motors or DC torque motors
resolvers
synchros
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13
Q

parts of a simple gyro (3)

A

rotor
spin axis
gimbal

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14
Q

properties of a gyro

A

rigidity

precession

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15
Q

two types of precessions

A

real

apparent

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16
Q

what is the RLG in CT-142

A

honeywell

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17
Q

what are the parts of the honeywell (7)

A 
cervit block
mirrors
prism
cathode
anode
inert gas
photo cells
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18
Q

how does the honeywell work

A

uses angular rates of motion (phase difference)

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19
Q

2 types of errors of the RLG

A 
lock in (caused by non-perfect optics = back scatterint)
differential path length (Tc diff between cervit caveties)
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20
Q

what is the fix for back scattering

A

dithering

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21
Q

what are the main advantages to integration/hybridization

A

improved accuracy

better chance of mission completion

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22
Q

what are the main disadvantages of integration/hybridization

A

loss of self-containment

loss of covertness

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23
Q

define leveling

A

no component of gravity sensed by x and y accelerometers

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24
Q

what is azimuth alignment

A

alignment of the azimuth sensitive axis to True North

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25
Q

what are the 10 initial conditions

A

2 initial px coordinates (lat/long)
2 inital velocities
3 initial orientations
3 orientation rates

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26
Q

what are the types of alignment (4)

A

self-alignment (most popular)
reference alignment
moving allignment
in-flight alignment

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27
Q

what is the self-alignment sequence (6)

A 
initialization
warm-up
coarse leveling
coarse alignenment
fine leveling
fine alignment
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28
Q

what are high latitude alignement problems

A

undetectable tilt preventing initiation of gyro compassing

inability to accurately resolve True North

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29
Q

types of alignment errors (2)

A

unbounded: leveling gryo drift, azimuth gyro drift, inital azimuth misalignment
bounded: inital levelling, accelerometers, velocity errors

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30
Q

what is schuler theory

A

tilt error that tries to self-correct but then applies real gravity in the process. takes 84.4min for the cycle to repeat itself

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31
Q

what are the two components of the honeywell IRS

A

IRU inertial reference system

MSU mode selector unit

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32
Q

what is contained in the IRU (4)

A

inertial sensor assembly
microprocessors
power supply
a/c electronic interfaces

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33
Q

What does the MSU provide (3)

A

inertial mode selection
status indication
remote test initiation

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34
Q

what are the modes of operation of the IRS (4)

A

off
align
nav
attitude

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35
Q

what is provided to the FMS from the NAV mode of the IRS (8)

A 
a/c altitude
body rates
body acceleration
true heading
velocity vectors
wind data
lat/long
inertial altitude
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36
Q

what are the alignment requirements of the IRS

A

enter present px via FMS
IRU conducts reasonability test of new px
if the new px is >1° of stored value = test fail
entering identical coords twice will override

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37
Q

what does the IRU feed to ATS (6)

A 
true heading
true track
present lat/long
inertial g/s
wind velocity & direction
system status
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38
Q

what is the system that is most prone to failure during IRS initialization and alignment sequence

A

emulated INS

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39
Q

how many waypoints can be entered

A

20

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40
Q

what are the controls and display of the INS

A

nav sensor selection panel
emulated INS control panel
INS DID display

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41
Q

what is the principle of GPS

A

measures ranges between receiver and satellites

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42
Q

what are the 2 types of apparent precession

A

earth rate

transport wander

43
Q

what are unique capabilities of the GPS

A 
3D
velocity and time
global coverage
continous
passive
unlimited
resistant
allows common grid reference
(3 very gross children pucked up red ants)
44
Q

what are the 3 parts of the GPS system

A

space segment
control segment
user segment

45
Q

what are the components of the user segment of the GPS

A 
Antenna
Computer
Signal processing equipment
oscillator 
(ACSO)
46
Q

what are the 2 navigation services

A

sps (standard positioning service)

pps (precise positioning service)

47
Q

what are 3 types of GPS receivers

A

sequencial
multiplex
continous

48
Q

what are the type of codes for the GPS

A

c/a codes (37)
p code
y codes (p codes encrypted)

49
Q

what are the operating frequencies of L1 and L2

A
  1. 42

1227. 6

50
Q

what is pseudo ranging

A

3d position could be established with 3 satellites but due to inherent clock errors in the satellite, we need a 4th to resolve px using pseudo ranging

51
Q

what is contained in nav msg from GPS (5)

A 
clock correction
ephemeris data
ephemeris data
gps NOTAMs
Almanac/health status
52
Q

what are the components of the FMS (7)

A 
2 x CDUs
1 x DTU
2 x ACU
2 x Glareshield Advisorie
2 x GPS antennas
config module
53
Q

what are the FMS inputs (5)

A 
AHRS
DADC
IRU
DTU
GPS
54
Q

what are the FMS outputs (4)

A

flight instruments
FGC
IRU
DTU

55
Q

what is the kalman filter

A

it blends the 2 GPS positions with the IRU in a satistical model to determine the best position

56
Q

what is in the FMS database

A 
VORs
Approaches & Rwy info
NDBs
En-route intersections
SIDs
STARS
Airports with >4000' hard sfc rwy
57
Q

what is the GPS process

A

satellite selection
searching the sky
satellite acquisition

58
Q

what are two types GPS errors

A

User Radial Error

Dilution of Precision

59
Q

what does LAAS and WAAS stand for and what do they do

A

local area augmentation system
wide area augmentation system
used to eliminate GPS errors

60
Q

how many waypoints can be stored in the emulated GPS

A

20

61
Q

what are the emulated GPS inputs (aircraft gps to emulated) (8)

A 
gps position
time
satellite info
system status
altitude
g/s
ground track
TAS
62
Q

what are the GPS outputs (emulated to user interface) (6)

A 
position & time
satellite info
altitude
ground track
g/s
TAS
63
Q

what is the TDS

A

tactical display system

a visual aid presents user specified information on display system to enhance situational and tactical awareness

64
Q

what can be displayed on TDS

A 
fly to points
contacts
reference marks
vectors
SAR patterns
free form graphics
range circles
65
Q

3 sources of the TDS

A

GPS
INS
DR

66
Q

what are the functions of the TDS

A 
FTP
reference marks
lines (fixed vectors)
lines (normal vectors)
circles
radar circle
SAR patterns
67
Q

what are the components of an ADF

A

adf receiver
antenna
RMI

68
Q

what are the nav aids that use ADF

A

NDBs

69
Q

what is the accuracy of the ADF

A

±3 degree

70
Q

what is the range of the ADF

A

200nm (200kHz)- 50nm (1600kHz) and decreases at night

71
Q

what is the ADF on the dh8 and what are its components

A 
king 806 ARL
radio compass receiver
CDU
antennas
bearing indicators
72
Q

what are the operating limits of the King 806

A

190.0 - 1799.0 kHz

73
Q

what is a VOR

A

VHF omni directional range

74
Q

accepted accuracy limitations of the VOR

A

±2.5 degrees

75
Q

characteristics of the VOR

A

affected by echos from hills and bldgs
80° cone of confusion
LOS

76
Q

capabilites of a TACAN

A 
LOS
max 252 users
cone of confusion 60° - 110°
accuracy ±0.75°
1m slant range
77
Q

what is the TACAN in dh8

A

King 709 TACAN

in the second avionics rack

78
Q

What is an EPL

A

a line along which the A/C was known to have been at a particular time

79
Q

what are 3 sources of position line

A

visual
electronic
celestial

80
Q

what are the types of EPL

A

straight

curved

81
Q

what are the advantages of fuel management

A

increase safety and efficiency
conservation fuel on ferry flight
optimize payload
saving on fuel in long rage tactical flights
efficiency fuel conservation on a long range flight when max range is required
controls maybe adjusted in flight

82
Q

what is the definition of cruise control

A

organized control of A/C in flight to obtain max flight profile efficiency

83
Q

factors that affect fuel management

A 
en-route weather
w/c
T°c
fuel capacity
fuel availability
amount of fuel reserve req'd
max T/O and Min landing weight
payload
distance
ATC restriction
84
Q

what is endurance

A

a specific speed and altitude to achieve the lowest FF -> max time A/B

85
Q

what is range

A

specific speed and altitude to achieve max ground range/lb fuel

86
Q

what is the specific fuel consumption

A

ratio of fuel used to the amount of thrust produced

Ff/ESHP

87
Q

why do we manage fuel

A

ensure enough fuel for mission
detect early fuel leaks
check if fuel consumption matches predicted
be aware of fuel in case of diversion or re-task

88
Q

what is specific Air Range

A

measure of efficiency with which an a/c flies through the air SAR=TAS/FF

89
Q

what is Specific Ground range

A

mesaur of efficiency with which an a/c flies over the ground SGR= G/S / FF

90
Q

what factors causes change in planned fuel burn

A 
ISA
wind
wx avoidance
a/c not to spec
fuel leak
ATC rerouting
91
Q

what is a radius of action

A

max ground distance that an a/c can fly from a start point and back to that start point in a specific time. Time out/time back = g/s back / g/s out

92
Q

what is the point of safe return

A

a point beyond which an a/c cannot fly and return to it’s own or same place withing a safe limit of endurance. SLE = total endurance - 1500lbs
PSR = (SLE)G/S home / G/S out + G/S home

93
Q

what is an ETP

A

a point on the intended track from which it will take the same amount time to fly to either critical point A/D

94
Q

what are the deisred properties of a map

A

orthomorphic
conformal
sufficient details

95
Q

what are the different types of map projections

A

cylindrical, conical and azymuthal

96
Q

what are the most common projections used for topographical maps in the CF

A

lambert conformal

transverse mercator

97
Q

what are the four ways to integrate INS

A

ground reference system in which a ground based flying system is intergrated with the INS
GPS
Dopple
Celestial

98
Q

what is the electrical requirement of the IRU

A

receives AC and DC power from the a/c 115v AC or 28v DC

99
Q

what are the four ways to integrate INS

A

ground reference system in which a ground based flying system is intergrated with the INS
GPS
Dopple
Celestial

100
Q

what is the electrical requirement of the IRU

A

receives AC and DC power from the a/c 115v AC or 28v DC

101
Q

What are characteristics of a Mercator projection

A 
Great circles - curved
Rhumb lines - straight
Angle - correct
Shape - correct
Scale - correct and constant
Size - correct
102
Q

What is magnetic dip

A

Angle between the local horizon and total magnetic field

103
Q

What is magnetic meridian

A

Direction of the horizontal component of the earth’s mag field at a point

104
Q

What is variation

A

Horizontal angle between true and mag north

Nav (1 decks)

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