CHAPTER 16 LONG RANGE COMMUNICATIONS - … range communications • rich history ... isdn pstn gsm...
Transcript of CHAPTER 16 LONG RANGE COMMUNICATIONS - … range communications • rich history ... isdn pstn gsm...
Wireless Communication
Networks and Systems 1st edition
Cory Beard, William Stallings
© 2016 Pearson
Higher Education, Inc.
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CHAPTER 16
LONG RANGE
COMMUNICATIONS
Long Range Communications 16-1
LONG RANGE COMMUNICATIONS
• Rich History
• Satellite
– Communications
– GPS
– Television
Long Range Communications 16-2
SATELLITE-RELATED TERMS
• Earth Stations – antenna systems on or near earth
• Uplink – transmission from an earth station to a
satellite
• Downlink – transmission from a satellite to an earth
station
• Transponder – electronics in the satellite that convert
uplink signals to downlink signals
Long Range Communications 16-3
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.4
base station
or gateway
CLASSICAL SATELLITE SYSTEMS
Inter Satellite Link
(ISL) Mobile User
Link (MUL) Gateway Link
(GWL)
footprint
small cells
(spotbeams)
User data
PSTN ISDN GSM
GWL
MUL
PSTN: Public Switched
Telephone Network
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.5
BASICS
• Satellites in circular orbits
– attractive force Fg = m g (R/r)²
– centrifugal force Fc = m r ²
– m: mass of the satellite
– R: radius of the earth (R = 6370 km)
– r: distance to the center of the earth
– g: acceleration of gravity (g = 9.81 m/s²)
– : angular velocity ( = 2 f, f: rotation frequency)
• Stable orbit
– Fg = Fc 32
2
)2( f
gRr
WAYS TO CATEGORIZE
COMMUNICATIONS SATELLITES
• Coverage area
– Global, regional, national
• Service type
– Fixed service satellite (FSS)
– Broadcast service satellite (BSS)
– Mobile service satellite (MSS)
• General usage
– Commercial, military, amateur, experimental
Long Range Communications 16-6
CLASSIFICATION OF SATELLITE
ORBITS
• Circular or elliptical orbit – Circular with center at earth’s center
– Elliptical with one foci at earth’s center
• Orbit around earth in different planes – Equatorial orbit above earth’s equator
– Polar orbit passes over both poles
– Other orbits referred to as inclined orbits
• Altitude of satellites – Geostationary orbit (GEO)
– Medium earth orbit (MEO)
– Low earth orbit (LEO)
Long Range Communications 16-7
GEOMETRY TERMS
• Elevation angle - the angle from the horizontal to the
point on the center of the main beam of the antenna
when the antenna is pointed directly at the satellite
• Minimum elevation angle
• Coverage angle - the measure of the portion of the
earth's surface visible to the satellite
Long Range Communications 16-8
MINIMUM ELEVATION ANGLE
• Reasons affecting minimum elevation angle of earth station’s antenna (>0o)
– Buildings, trees, and other terrestrial objects block the line of sight
– Atmospheric attenuation is greater at low elevation angles
– Electrical noise generated by the earth's heat near its surface adversely affects reception
Long Range Communications 16-9
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.11
ELEVATION
Elevation:
angle e between center of satellite beam
and surface
e minimal elevation:
elevation needed at least
to communicate with the satellite
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.12
INCLINATION
inclination d
d
satellite orbit
perigee
plane of satellite orbit
equatorial plane
FIGURE 16.2 SATELLITE PARAMETERS AS A FUNCTION OF
ORBITAL HEIGHT Long Range Communications 16-13
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.14
SATELLITE PERIOD AND ORBITS
10 20 30 40 x106 m
24
20
16
12
8
4
radius
satellite
period [h] velocity [ x1000 km/h]
synchronous distance
35,786 km
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.15
LINK BUDGET OF SATELLITES
• Parameters like attenuation or received power determined by four parameters:
sending power
gain of sending antenna
distance between sender and receiver
gain of receiving antenna
• Problems
varying strength of received signal due to multipath propagation
interruptions due to shadowing of signal (no LOS)
• Possible solutions
Link Margin to eliminate variations in signal strength
satellite diversity (usage of several visible satellites at the same time) helps to use less sending power
24
c
frL
L: Loss
f: carrier frequency
r: distance
c: speed of light
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.16
ATMOSPHERIC ATTENUATION Example: satellite systems at 4-6 GHz
elevation of the satellite
5° 10° 20° 30° 40° 50°
Attenuation of
the signal in %
10
20
30
40
50
rain absorption
fog absorption
atmospheric
absorption
e
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.17
ORBITS
earth
km
35768
10000
1000
LEO
(Globalstar,
Irdium)
HEO
inner and outer Van
Allen belts
MEO (ICO)
GEO (Inmarsat)
Van-Allen-Belts:
ionized particles
2000 - 6000 km and
15000 - 30000 km
above earth surface
GEO ORBIT
• Advantages of the the GEO orbit
– No problem with frequency changes
– Tracking of the satellite is simplified
– High coverage area
• Disadvantages of the GEO orbit
– Weak signal after traveling over 35,000 km
– Polar regions are poorly served
– Signal sending delay is substantial
Long Range Communications 16-18
LEO SATELLITE
CHARACTERISTICS
• Circular/slightly elliptical orbit under 2000 km
• Orbit period ranges from 1.5 to 2 hours
• Diameter of coverage is about 8000 km
• Round-trip signal propagation delay less than 20 ms
• Maximum satellite visible time up to 20 min
• System must cope with large Doppler shifts
• Atmospheric drag results in orbital deterioration
Long Range Communications 16-20
FIGURE 16.4 LEO AND MEO ORBITS
Long Range Communications 16-21
FIGURE 16.5 MINIMUM FREE SPACE LOSS AS A FUNCTION OF
ORBITAL HEIGHT Long Range Communications 16-22
LEO CATEGORIES
• Little LEOs
– Frequencies below 1 GHz
– 5MHz of bandwidth
– Data rates up to 10 kbps
– Aimed at paging, tracking, and low-rate messaging
• Big LEOs
– Frequencies above 1 GHz
– Support data rates up to a few megabits per sec
– Offer same services as little LEOs in addition to voice and positioning services
Long Range Communications 16-23
MEO SATELLITE
CHARACTERISTICS
• Circular orbit at an altitude in the range of 5000 to
12,000 km
• Orbit period of 6 hours
• Diameter of coverage is 10,000 to 15,000 km
• Round trip signal propagation delay less than 50 ms
• Maximum satellite visible time is a few hours
Long Range Communications 16-24
FREQUENCY BANDS AVAILABLE
FOR SATELLITE
COMMUNICATIONS
Long Range Communications 16-25
SATELLITE LINK PERFORMANCE
FACTORS
• Distance between earth station antenna and satellite
antenna
• For downlink, terrestrial distance between earth
station antenna and “aim point” of satellite
– Displayed as a satellite footprint
• Atmospheric attenuation
– Affected by oxygen, water, angle of elevation, and higher
frequencies
Long Range Communications 16-26
FIGURE 16.7 SIGNAL ATTENUATION DUE TO
ATMOSPHERIC ABSORPTION (C BAND) Long Range Communications 16-28
FIGURE 16.8 SATELLITE COMMUNICATION
CONFIGURATIONS Long Range Communications 16-29
CAPACITY ALLOCATION
STRATEGIES
• Frequency division multiple access (FDMA)
• Time division multiple access (TDMA)
• Code division multiple access (CDMA)
Long Range Communications 16-30
FIGURE 16.9 TYPICAL VSAT CONFIGURATION
Long Range Communications 16-31
GLOBAL POSITIONING SYSTEM
• GPS was developed by U.S. Department of Defense
• 24 MEO satellites
– Six orbital planes at 20,350 km altitude
– Orbit every 12 hours
• GPS receiver must observe at least 4 satellites
– Three provide distance measurement
– Intersection of three spheres provides two points of intersection, one of which is unrealistic
– Fourth satellite is used to adjust timing offsets
Long Range Communications 16-32
GLOBAL POSITIONING SYSTEM
• Uses Direct Sequence Spread Spectrum
– Can keep from unauthorized use
• Until 2000, GPS signals were intentionally degraded
– Low received signal energy is required
– All satellites can use the same frequency band
• Complexities of operation
– Knowing satellite locations
– Atmospheric effects
– Differential GPS can provide more accuracy if a terrestrial reference point is also known
Long Range Communications 16-33
FIGURE 16.16 GLOBAL POSITIONING SYSTEM
Long Range Communications 16-34
DIRECT BROADCAST SATELLITE
• Provides television services
• C-band (4-8 MHz) requires 3 m dishes
• Ku band (12-18 GHz) requires 1 m dishes
• Providers send signals up to satellites
– Satellites rebroadcast on various frequencies
– Receivers decrypt by permission of service
provider
• High compression for best use of the channel
Long Range Communications 16-35
FIGURE 16.17 DIRECT BROADCAST SATELLITE
Long Range Communications 16-36
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.37
LINK BUDGET
• Pr = Pt - 92.4 - 20 Log F(GHz) - 20 Log D(Km) - At + Gt + Gr
• G- Gain of antenna t – transmission; r – reception
• At – atmospheric attenuation (dust, rain)
• D = 36000 Km -> 20 LogD = 91,1
• F= 2 GHz -> 20 LogF = 6
• A=10 dB
• Gt = Gr = 30 dBi
• Pt = 40 dBm (10 W) -> Pr = - 99,5 dBm
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.38
ANGLES - DIVERGENCE & SPOT SIZE
1 mrad
1 km
1 m
Small angle approximation:
Angle (in milliradians) * Range (km)= Spot Size (m)
Divergence Range Spot Diameter
1 mrad 36000 km 36 Km
17 mrad (1 deg) 36000 km 612 Km
1° ≈ 17 mrad → 1 mrad ≈ 0.0573°
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.39
ANTENNA GAIN VS DIVERGENCE
• Gain(dBi) = 10 Log (2 / Div) = 10 Log (360º/Divº)
• Isotropic Antenna -> Div = 2 / 360º (both Vert. and Hor.)
Gain(dBi) = 0
• Examples:
• Div =2º -> Gain(dBi) = 22,6 dBi (2x 22,6 if in both planes)
• Div =4º -> Gain(dBi) = 19,6 dBi
• Div =8º -> Gain(dBi) = 16,6 dBi
• Div=12º -> Gain(dBi) = 14,7 dBi (Vert and Hor: 14,7 x 2 = 29,4 dBi)
• Nota: a antena da Cisco com Div= 12º tem 21 dBi de ganho, (vs 29.4 dBi teórico) devido a perdas noutras direcções.
Cisco AIR-ANT3338
21dBi Parabolic Dish Azimuth 3dB BW =12º
Elevation 3dB BW =12º
Prof. Dr.-Ing. Jochen Schiller, http://www.jochenschiller.de/ MC SS02 5.40
RECEIVED POWER BASED ON
ANTENNA APERTURE AREA (AE)
• Ae = Aphysical * h (h - Antenna efficiency 50%-80%)
• Pr = Pt – 10 Log(4 * Footprint / (PI2 *Ae)) – At
• Pt = 40dBm (10W)
• Footprint = 471 716 Km2 (PI x 387.5km x 387.5km) (Iberian peninsula 582 860 km2)
• Aphy = 1m2 ; h = 50%
• At = 10 dB
• Pr = 40 – 115.6 -10 = - 85.6 dBm
36000 Km
775 Km 1.2º