SATELLITE LINKS
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Transcript SATELLITE LINKS
SATELLITE LINKS
BASIC LINK BUDGETS
ALLOCATING THE AVAILABLE
SATELLITE RESOURCES TO
ACCOMODATE THE PARAMETERS OF
THE TX & RX EARTH STATIONS ...
C (dBW)
CARRIER POWER RECEIVED IS DEFINED BY :
C = PtAe / [4pi(radius^2)]
(WATTS)
where,
4pi(radius^2) = SURFACE AREA OF A SPHERE
Pt = ISOTROPICALLY SPREAD Tx POWER
Ae = EFFECTIVE AREA OF THE Rx ANTENNA
WHEN A DIRECTIONAL ANTENNA IS USED :
C = PtGtAe / [4pi(radius^2)]
where,
Gt = Tx GAIN
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pi
A CONSTANT OF PROPORTIONALITY
(USEFUL IN SOLVING FOR THE AREA OF A CIRCLE)
THE EGYPTIAN RULE FOR FINDING THE AREA :
EQUALS 3.16 TIMES THE RADIUS SQUARED
WHICH WAS CLOSER TO THE TRUTH THAN
THE BABYLONIAN VALUE OF 3
(BASED ON THE BIBLE)
IN ACTUALITY, THE MATHEMATICAL VALUE
OF pi IS AN IRRATIONAL NUMBER
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C/T (dBW/K)
CARRIER-TO-THERMAL NOISE
where,
C = EIRP - LOSSES + Gr
and,
C/T = EIRP - LOSSES + G/T
THIS IS THE HEART OF THE LINK
BUDGET
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C/kT (dBHz)
CARRIER-TO-THERMAL NOISE DENSITY
(WITH BOLTZMANNS CONSTANT k)
C/kT = C/No = C/T + 228.6
where,
kT = No = N/B = N (dBW/Hz)
(IN A 1Hz BANDWIDTH)
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C/N (dB)
CARRIER-TO-NOISE IN BANDWIDTH B
C/N = C/kTB
where,
C/kTB = C/kT - 10log(BW)
and,
C/kT = C/No
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Eb/No (dB)
ENERGY PER BIT - NOISE DENSITY
Eb/No = C/No - 10log(R)
where,
R = BIT RATE (BITS/SECOND)
PERFORMANCE OF DIGITAL CIRCUITS IS OFTEN
MEASURED AS A SPECIFIC BER.
WHICH IS RELATIVE TO THE Eb/No.
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E (dBuV/m)
ELECTRIC FIELD STRENGTH
(POWER PER UNIT AREA)
W = 1/2[c(PERMITTIVITY)] x E^2
W = [1/2(E^2)] / Z
(W/m^2)
(W/m^2)
where,
Z = 1 / [c(PERMITTIVITY)]
W = 2E - 148.77
E = 1/2(W + 148.77)
(dBW/m^2)
(dBuV/m)
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EIRP (dBW)
EQUIVALENT ISOTROPICALLY RADIATED POWER
EIRP = PGt
(WATTS)
EIRP = 10log(P) + 10log(Gt)
(dBW)
TYPICAL VALUES OF EIRP RANGE FROM :
0-90 dBW FOR EARTH STATIONS
20-60 dBW FOR SATELLITES
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G (dBi)
GAIN OF AN ANTENNA
(AS REFERENCED TO AN ISOTROPIC RADIATOR)
G = Tx PWR OF ANTENNA / ISOTROPIC Tx PWR
G (PARABOLIC) = (4pi x eff x A) / WAVELENGTH^2
G = eff{[(piD x FREQ)/C]^2}
G = 20logD + 20logFREQ + 10log(eff) + 20.4
TYPICAL E/S GAIN FIGURES ARE 1-60dBi
SATELLITE GAIN FIGURES RANGE FROM 14-40dBi
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eff
Antenna efficiency (assumed 60-70%)
Actual values range from .2 to .75
Conventially illuminated (large) Earth stations
typically are 65-75%
Flat plate antennas are 75% efficient
(Superconductive surfaces on these may further
increase this value)
Satellite spacecraft antennas are usually less
efficient.
(40-55%, or 20-30% for multi-beam)
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BASICS OF ANTENNA GAIN
A Tx SHAPED ANTENNA FOCUSES THE Tx PWR
IF NO BEAM DIRECTIVITY IS APPLIED, THE
RESULT IS AN ISOTROPIC RADIATOR.
(THE SUN COULD BE USED AS AN EXAMPLE)
THEORETICAL GAIN OF A PARABOLIC IS INFINITE
(THUS, THE LIMITATION IS BASED ON WAVELENGTH)
GAIN CALCULATED BY VIRTUE OF THEORETICAL IS
USUALLY CONSIDERED PEAK (ON-AXIS) GAIN.
OFF-AXIS GAIN IS ALSO A SERIOUS CONSIDERATION
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ANTENNA BEAMWIDTH
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G/T (dBi/K)
FIGURE OF MERIT
G/T = Gr - 10logTs
where,
Gr = Rx ANTENNA GAIN (dBi)
Ts = Rx SYSTEM NOISE TEMP (DEGREES KELVIN)
Gr IS A FACTOR OF THE EFFICIENCY, OR SIZE OF THE
ANTENNA.
Ts IS THE SUM OF ANTENNA NOISE TEMP, LNA TEMP &
NOISE CONTRIBUTED BY RESISTIVE COMPONENTS
BETWEEN THE ANTENNA AND LNA.
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k (dBW/Hz-K)
BOLTZMANNS
CONSTANT (OF PROPORTIONALITY)
k = 1.3806 x 10^-23 (W/Hz-K)
k = -228.6 (dBW/Hz-K)
Pn (MAX NOISE OUTPUT) = kTB
where,
T = ABSOLUTE TEMPERATURE
B = BANDWIDTH OF INTEREST
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L (dB)
FREESPACE LOSS
C = (EIRP x eff x AREA) / (4pi x S^2)
G = (4pi x eff x AREA) / WAVELENGTH^2
C = EIRP x [(WAVELENGTH^2) / (4piS)^2] x Gr
L = (4piS)^2 / (WAVELENGTH^2)
C = EIRP - L + Gr
L = 20logS(km) + 20logFREQ(GHz) + 92.45
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W (dBW/m^2)
ILLUMINATION LEVEL
W = PGt / [4pi(S^2)]
W = EIRP - 20logS - 71
where,
THE CONSTANT 71 = 10log{4pi[(1000m/km)^2]
THE MAXIMUM DISTANCE (S) = 41,679km
THIS CORRESPONDS TO A SATELLITE ON THE HORIZON @
0 DEGREES ELEVATION & MAXIMUM CENTRAL ANGLE
WITH THIS VALUE USED, THE WORST-CASE LEVEL IS :
W = EIRP - 163.4
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PFD (dBW/m^2)
POWER FLUX DENSITY
(USUALLY DEFINED WITHIN A SPECIFIED BW)
PFD = W - 10log(B/Bccir)
where,
W = EIRP - 163.4
(dBW/m^2)
PFD = EIRP - 163.4 - 10log(B/Bccir)
THE STANDARD CCIR BANDWIDTH = 4kHz
(FOR C & Ku BAND SYSTEMS)
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DEFINITION OF SIGNAL QUALITY
(C/T)
CXR-to-THERMAL NOISE RATIO
(C/No)
CXR-to-NOISE DENSITY
(C/N)
CXR-to-NOISE POWER
(S/N)
SIGNAL-to-NOISE POWER
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LINK BUDGET (COMPONENTS)
TRANSMITTER POWER
ANTENNA GAIN
RADIATED EIRP
ILLUMINATION LEVEL @ RCVR
FREE SPACE LOSS
SYSTEM NOISE TEMPERATURE
RECEIVE FIGURE OF MERIT
CXR-to-THERMAL NOISE RATIO
CARRIER-to-NOISE DENSITY
CARRIER-to-NOISE RATIO
P (W)
G (dBi)
(dBW)
(dBW/m^2)
(dB)
Ts (K)
G/Ts (dBi/K)
C/T (dBW/K)
C/No (dBHz)
C/N (dB)
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BASIC LINK BUDGETS
COME IN VARIOUS LENGTHS & STYLES
(THERE IS NO STANDARD FORMAT)
3 KEY EQUATIONS FORM THE BASIS :
FOR MOST UPLINK BUDGETS :
EIRP = 10logP + Gt
C/T = EIRP - L + G/T
C/kT = C/T + 228.6
FOR MOST DOWNLINK BUDGETS :
C/T = EIRP - L + G/T
C/kT = C/T + 228.6
C/N = C/kT - 10logB
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THE TRANSPONDER
CHARACTERISTIC PARAMETERS
THE TX/RX FREQUENCY BANDS & POLARISATIONS
THE TX/RX COVERAGE (SFD & GAIN CONTOURS)
THE TX EIRP & CORRESPONDING PFD ACHIEVED
THE RX PFD REQUIRED TO ACHIEVE THE REQ’D TX EIRP
THE G/T BASED ON THE SFD CONTOUR
NON-LINEAR CHARACTERISTICS
RELIABILITY AFTER x YEARS FOR y PERCENTAGE OR
NUMBER OF CHANNELS TO REMAIN IN WORKING ORDER
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TRANSMITTER POWER (P)
USUALLY SPECIFIED IN WATTS
THE 1st NUMBER OF THE LINK BUDGET
(OFTEN ADJUSTED TO OBTAIN THE DESIRED PERFORMANCE)
FOR SATELLITES, Tx POWER IS LIMITED BY THE DC
POWER AVAILABLE VIA THE SOLAR ARRAY. (10-200W)
EARTH STATION TRANSMITTERS RANGE FROM 1-10KW
IF LOSSES ARE SIGNIFICANT, THE Tx POWER IS
MEASURED @ THE ANTENNA INPUT FLANGE.
(LOSSES BEFORE THIS POINT MAY BE DEDUCTED FROM THE Tx PWR)
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