ITU-R S.1503-2
(2013/12)
22
S
ITU-R S.1503-2
ii
(IPR)
1
(ITU-T/ITU-R/ISO/IEC)
ITU- R 1
http://www.itu.int/ITU -R/go/patents/en
http://www.itu.int/publ/R-REC/en
BO
BR
BS
BT
F
M
P
RA
RS
S
SA
SF
SM
SNG
TF
V
ITU-R 1
2015
 ITU 2015
(ITU)
1
ITU-R S.1503-2
ITU-R S.1503-2
22
(2013-2005-2000)
(epfd)
()
(e.i.r.p.)
epfd(IS)
epfd(up)
1.5C.22
(epfd)
epfd(down)
epfd(up)
epfd(IS)
epfd(down)
pfd
(X) X
(WCG)
(epfd)
ITU-R S.1503-2
2
ITU-R BO.1443-2
30
ITU-R S.672-4
ITU-R S.1428-1
(non-GSO)
GHz 30 GHz 10,7
22
(WRC-2000) 2000-
(non-GSO)
(FSS)
(GSO)
GHz 30-10,7
31.11 35.9
1A-22
(RR)
22
3-22 2-22 1E-22 1D-22 1C-22 1B-22
(BR)
(BSS)
1
22
3-22 2-22 1E-22 1D-22 1C-22 1B-22 1A-22
1
3
ITU-R S.1503-2
1
3
A
9
B
21
(pfd/e.i.r.p.)
C
40
D
119
E
121
F
A
1
1.1
1D-22 1C-22 1B-22 1A-22
22
5
7B.9 7A.9
22
3-22 2-22 1E-22
ITU-R S.1503-2
7B.9 7A.9
4
22
5
2.1
1
(e.i.r.p.)
1
(pfd)
3
2
(pfd)
1
C
(e.i.r.p.)
2
3
1
pfd/e.i.r.p.
5
ITU-R S.1503-2
1
non-GSO
pfd/e.i.r.p.
1
EPFD
non-GSO
pfd/e.i.r.p.
EPFD
EPFD
EPFD
2
3
epfd
4
S.1503-01
3.1
(epfd)
pfd/e.i.r.p.
pfd/e.i.r.p.
ITU-R S.1503-2
2
6
22
3
4
A
B
pfd/e.i.r.p.
C
1
D
4 3 2
D
F E
7
ITU-R S.1503-2
2
1.2
1
1
1
(km)
(s)
km/s
(GHz)
(kHz)
dBW
dB(W/Hz)
dB(W/(m2 · BWref))
(pfd)
2
km 1
dB(W/BWref)
epfdis
epfd
epfd
dBi
2.2
2
2
km
km
3
km /s
6 378,145
Re
42 164,2
Rgeo
5
10  3,986012

10  2,99792458
c
10  4,1780745823
e
2
5
km/s
3–
s
86 164,09054
Te
0,001082636
J2
ITU-R S.1503-2
8
3.2
3.6.D
3.6.D
4.2
3
3
A
B
C
D
E
3
4.D
9
ITU-R S.1503-2
B
1
1.1
pfd
(epfd↑)
1
e.i.r.p.
2
(epfd↓)
pfd/e.i.r.p.
3
A
3.1.A
2
pfd/e.i.r.p
2.1
2
pfd/e.i.r.p.
pfd/e.i.r.p.
4
B
2
7B 9 7A 9 22
RunType
SystemID
ITU-R S.1503-2
11
epfd
{Down, Up, IS}
epfddirection
{FSS, BSS}
VictimService
epfd
StartFrequencyMHz
epfd
EndFrequencyMHz
VictimAntennaType
DLL
VictimAntennaDishSize
DLL
VictimAntennaBeamwidth
DLL
RefBandwidthHz
epfd
NumPoints
epfd
dBW/m2
epfd
epfdthreshold[N]
epfdpercent[N]
epfdthreshold
3
1.3
Nsat
(km)
H_MIN
DoesRepeat
AdminSuppliedPrecession
Wdelta
ORBIT_PRECESS
MIN_EXCLUDE
lat
Nco[latitude]
ES_TRACK
ES_MINELEV
ES_MIN_GSO
2
(km )
ES_DENSITY
(km)
ES_DISTANCE
ES_LAT_MIN
ES_LAT_MAX
11
ITU-R S.1503-2
2.3
(km)
A[N]
E[N]
I[N]
O[N]
W[N]
V[N]
e.i.r.p. pfd
4
1.4
pfd
FreqMin
pfd
FreqMax
pfd
RefBW
22
MHz 1 kHz 40 22
epfd
(az,el)

X
MaskType
–
–


1
pfd_mask
L X
–
4.4.6.D
L
X

4.4.6.D
–
5.4.6.D
5.4.6.D
2
pfd_mask
E1 Az
ITU-R S.1503-2
12
(e.i.r.p.)
pfd
2.4
(MHz)
pfd
FreqMin
(MHz)
FreqMax
e.i.r.p.
22
MHz 1 kHz 40 22
RefBW
epfd
e.i.r.p.
NumMasksLat
ES_e.i.r.p.
Latitude[Lat]
1-
ES_ID
e.i.r.p.
ES_e.i.r.p. [][Lat]
3.4
e.i.r.p.
FreqMin
e.i.r.p.
FreqMax
e.i.r.p.
22
MHz 1 kHz 40 22
RefBW
epfd
SAT_e.i.r.p.
Latitude[Lat]
e.i.r.p.
SAT_e.i.r.p.[][Lat]
B
epfd
B
4
2
(BR)
4
(SNS)
4
2
X
9
X(9)
X(3)
XXX
9
‘.’
S
999,99+
999,9999
S999,99
0
99
13
ITU-R S.1503-2
2
sat_oper
non_geo
orbit
s_beam
phase
s_as_stn
grp
e_as_stn
emiss
assgn
e_srvcls
srvcls
srv_area
S.1503-02
ITU-R S.1503-2
14
4
4
value != Null
9(9)
ntc_id
X
ntc_type
9(8)
d_rcv
X
ntf_rsn
XX
st_cur
[G]
[N]
[T]
N
[S]
C
[N] RR1488
[C] RR1060
[A] 9,1 [D] RR1107
[D] 9,7A [C] 9,6
[N] 11,2 [D] 9,17
-AP30/30A [N] 11,12
[B] 5 4 2A
[P] 7 6
-AP30B
[N] 8
-AP30B
[U] Res49
50
7A.9
Non-geo
9(9)
ntc_id
X(20)
sat_name
value != Null && value > 0
9(4)
nbr_sat_td
value != Null && value > 0
9(3).9
avg_dist
value != Null && value > 0
9.9(6)
density
X
f_x_zone
99.9
x_zone
km2
value != Null && (value = ‘Y’ ||
‘N’)
[N] X
value != Null && value > 0
[Y]
15
ITU-R S.1503-2
orbit
9(9)
ntc_id
99
orb_id
value != Null && value > 0
99
nbr_sat_pl
value != Null
999.99
right_asc
value != Null
999.9
inclin_ang
value != Null && value > 0
9(5).99
apog
99
apog_exp
9(5).99
perig
99
perig_exp
999.9
perig_arg
km 99999
apog_exp
105 × 1,25
apog
125 000
value != Null && value >= 0
10
1 100
102
2 101
value != Null && value > 0
km 99999
perigee
perig_exp
105 × 1,25 125 000
value != Null && value >= 0
10
2 101
11A.9
1 100
102
ITU-R S.1503-2
16
orbit
value != Null && value > 0
99.99
op_ht
99
op_ht_exp
X
f_stn_keep
999
rpt_prd_dd
99
rpt_prd_hh
99
rpt_prd_mm
99
rpt_prd_ss
X
f_precess
999.99
precession
km 99
op_ht
op_ht_exp
102 × 2,5
250
value != Null && value >= 0
10
2 101
1 100
102
value != Null &&
(value == ‘Y’ || ‘N’)
[Y]
[N]
(s)
(s)
(s)
(s)
value != Null &&
(value == ‘Y’ || ‘N’)
[N]
[Y]
J2
If f_precess == ‘Y’ then value
!= Null && value > = 0
J2
17
ITU-R S.1503-2
value != Null && value > = 0
999.99
long_asc
99.9
keep_rnge
j
(0° =j < 360°)
If f_stn_keep == ‘Y’ then
value != Null && value > = 0
9(9)
ntc_id
99
orb_id
value != Null && value > = 0
99
orb_sat_id
value != Null && value > = 0
999.9
phase_ang
11A.9
Grp
value != Null &&
(value == ‘E’ || ‘R’)
[R]
value != Null && value > = 0
9(9)
ntc_id
9(9)
grp_id
X
emi_rcp
X(8)
beam_name
S9(3).99
elev_min
9(6).9(6)
freq_min
[E]
(VLBI)
value != Null && value > 0
(MHz)
ITU-R S.1503-2
value != Null && value > 0
(MHz)
18
9(6).9(6)
freq_max
9(8)
d_rcv
9(6)
noise_t
9.7A/B
srv_cls
value != Null && value > = 0
9(9)
grp_id
9(4)
seq_no
XX
stn_cls
Mask_info
value != Null &&
(value == ‘E’ || ‘S’|| ‘P’)
9(9)
ntc_id
9(4)
mask_id
X(20)
sat_name
X
f_mask
X(20)
f_mask_type
[S]
[E]
[P]
If f_mask == ‘P’ then
(value != Null &&
(value ==
‘alpha_deltaLongitude’ ||
‘X_deltaLongitude’||
‘azimuth_elevation’))
If f_mask == ‘S’ then (value
!= Null && (value ==
‘Offaxis’ ||
‘azimuth_elevation’))
value != Null && value > 0
GHz
9(6).9(6)
freq_min
value != Null && value > 0
(GHz)
9(6).9(6)
freq_max
19
ITU-R S.1503-2
e_as_stn
value != Null && value >= 0
value != Null && (value ==
‘S’ || ‘T’)
value != Null && value > 0
[T]
9(9)
grp_id
9(4)
seq_no
X(20)
stn_name
X
stn_type
999.99
bmwdth
[S]
sat_oper
9(9)
ntc_id
value != Null
S99.999
lat_fr
value != Null
S99.999
lat_to
value != Null
9(4)
nbr_op_sat
mask_lnk1
value != Null && value > = 0
9(9)
grp_id
9(9)
ntc_id
9(9)
mask_id
99
orb_id
99
sat_orb_id
mask_lnk2
value != Null && value > = 0
9(9)
grp_id
9(4)
seq_e_as
9(9)
ntc_id
9(4)
mask_id
99
orb_id
99
sat_orb_id
ITU-R S.1503-2
21
7B.9/7A.9
e_stn
9(9)
ntc_id
value != Null
X(20)
stn_name
value != Null
X(20)
sat_name
value != Null
S9(2).9(4)
lat_dec
value != Null
S9(2).9(4)
long_dec
S999.99
long_nom
value != Null
' '
' '
e_ant
value != Null
[R]
9(9)
ntc_id
X
emi_rcp
999.99
bmwdth
S99.9
gain
[E]
21
ITU-R S.1503-2
C
(pfd/e.i.r.p.)
1
pfd
pfd
2
1.2
pfd
1
X

4.4.6.D
L
4.4.6.D
X

2
5.4.6.D
5.4.6.D
ITU-R S.1503-2
GSO
22
pfd
X

epfd↓
2.2
epfd↑
0
0
X
X0
X
pfd
X
3
23
ITU-R S.1503-2
3
GSO arc projection line
T2
x
x
x
X
x
x
x
x
GSO
projection
zone
P
X
T1
x
x
x: beam turned off when edge within GSO projection zone
x
S.1503-03
pfd
pfd
pfd
dB 0,048
dB 3 +
dB 30-
𝑁𝑐𝑜
𝑁𝑐𝑟𝑜𝑠𝑠
𝑝𝑓𝑑 = 10 log (∑ 10𝑝𝑓𝑑_𝑐𝑜𝑖/10 + ∑ 10𝑝𝑓𝑑_𝑐𝑟𝑜𝑠𝑠𝑗/10 )
𝑖
𝑗
pfd
3.2
pfd
1.3.2
ITU-R S.1503-2
24
(dB(W/m2)
:pfd
:i
:Nco
(dB(W/m2))
pfd :pfd_coi
:j
:Ncross
pfd :pfd_crossj
2
(dB(W/m ))
𝑝𝑓𝑑_𝑐𝑜𝑖 = 𝑃𝑖 + 𝐺𝑖 − 10log10 (4 π 𝑑 2 )
(dB(W/BWref))
:Pi
i
(kHz)
(dBi)
i
:BWref
:Gi
:d
d
𝑝𝑓𝑑_𝑐𝑟𝑜𝑠𝑠𝑗 = 𝑃𝑗 + 𝐺_𝑐𝑟𝑜𝑠𝑠𝑗 − 10log10 (4 π 𝑑 2 )
:G_crossj
j
(dBi)
pfd/e.i.r.p.
2.3.2
i
M
: 
v  sin  sin  u  sin  cos  :v
B   sin  A   cos  :B
tan (Az)  tan  cos  sin (El)  sin  sin  :(Az, El)
25
ITU-R S.1503-2
B A
B A
4
4
BA
B
Cell i
M( a, b)
C(Ac, B c)
M
M
c
c
A
S.1503-04
(M, M)
(c, c)
B A
B A
(a , b )
(Ac, Bc)
M
i
C
M
M(a, b) C(Ac, Bc)
B A
M(a, b)
B A
P
5
{y1, y2,…}
y
{x1, x2, …}
x
ITU-R S.1503-2
26
5
y
y2
P12 = P (x1 , y2 )
P22 = P (x2 , y2 )
(x , y)
y1
P21 = P (x2 , y1 )
P11 = P ( x1 , y1 )
x
x1
x2
S.1503-05
(y, x)
P
𝑥 − 𝑥1
𝑥2 − 𝑥1
𝑦 − 𝑦1
λ𝑦 =
𝑦2 − 𝑦1
λ𝑥 =
P
P = (1 – λx)(1 – λy)P11 + λx (1 – λy)P21 + (1 – λx)λyP12 + λxλyP22
pfd
4.2
2
1
27
ITU-R S.1503-2
1


1.4.2
pfd
1
X
X

pfd
L

L
pfd
pfd
Ntotal
iso-
2

7 6
6
1
B
 = 0
Exclusion zone
1
M, long
=0
ïï < 0 degrees
 = –0
A
Cell i
S.1503-06
ITU-R S.1503-2
28
L
X
pfd
n
n
M,k
3

2 1 k
2 1 k
iso-
iso-
M,k n
M,k
L

pfd
i
M,k
M,k
4
pfd
pfd
Ntotal
Ncross
Nco
Ncross Nco
7
iso-
z
iso- line
O
y
longn o n - G S O
long
x
GSO arc
GSO satellite
S.1503-07
pfd
5
29
ITU-R S.1503-2
0
 0
iso-
0
iso-0
X
L
X0
X

pfd
6
pfd(, L)  maxk = 1, 2,...n(pfd(M,k))
pfd
iso-
7
pfd
pfd
8
2
pfd
pfd
2.4.2
ITU-R S.1503-2
31
8
2
Elevation
M(Az, E1)
Azimuth
Cell i
S.1503-08
pfd
Ntotal
M,k
pfd
M(Az, El)
pfd
1
2
MAz, El)
M,k
pfd
Ntotal
Ncross
Nco
Ncross Nco
pfd
3
31
ITU-R S.1503-2
0
  0
iso-
0
iso-0
X
X0
X
pfd
4
pfd
5
e.i.r.p.
3
e.i.r.p.
1.3
1.1.3
e.i.r.p.
e.i.r.p.
e.i.r.p.
2.1.3
2.2.C
epfd↑
3.1.3
e.i.r.p.
4.1.3
e.i.r.p.
ES_e.i.r.p(θ) = G(θ) + P
e.i.r.p.
1
ITU-R S.1503-2
32
(dB(W/BWref))
:ES_e.i.r.p.
:
(dBi)
:G()
(dB(W/BWraf))
:P
s (kHz)
:BWraf
2
ES_e.i.r.p.
e.i.r.p.
2.3
e.i.r.p.
e.i.r.p.
e.i.r.p.
e.i.r.p.
NGSO_SS_e.i.r.p.()  G()  P
(dB(W/BWref))
:NGSO_SS_ e.i.r.p.
 
(dBi)
:G()
(dB(W/BWrif))
:P
(kHz)
:BWrif
e.i.r.p. pfd
4
1.4
ITU-R S.1503
pfd
pfd (, long)
pfd
e.i.r.p. pfd
epfd
(
e.i.r.p.
epfd
e.i.r.p. ()
33
ITU-R S.1503-2
e.i.r.p.
epfd
e.i.r.p. ()

e.i.r.p.
pfd
1
e.i.r.p.
pfd
pfd
2
pfd (, long)
pfd
e.i.r.p. ()
e.i.r.p.
long 
long 
pfd
e.i.r.p.
long 
e.i.r.p.
pfd
e.i.r.p.
ITU-R S.1503-2
34
11
9
9
epfd
PFD mask
non-GSO satellite
pfd
Header
Table
Azimuth or long angle (degrees) Þ array
{Latitude, Table}
Elevation or  angle (degrees) Þ array
{Latitude, Table}
...
PFD (azimuth, elevation)
or
PFD ( ,  long)
...
S.1503-09
10
epfd
e.i.r.p. mask
non-GSO ES
pfd
Header
Off axis angle (degrees) Þ array
{Latitude, Table}
{Latitude, Table}
Table
e.i.r.p. at offaxis angle (dBW/Ref.BW) Þ array
...
...
S.1503-10
35
ITU-R S.1503-2
11
epfd
e.i.r.p. mask
non-GSO satellite
pfd
Header
Off axis angle (degrees) Þ array
{Latitude, Table}
Table
e.i.r.p. at offaxis angle (dBW/Ref.BW) Þ array
...
{Latitude, Table}
...
S.1503-11
XML
pfd
XML
<satellite_system>
</satellite_system>
<satellite_system ntc_id="NNNNNNN" sat_name="NAME">
[Header]
[Tables]
</satellite_system>
pfd
pfd
<pfd_mask mask_id="N" low_freq_mhz="F1" high_freq_mhz="F2" type="Type"
a_name="latitude" b_name="B" c_name="C">
2.4
ITU-R S.1503-2
36
5
5
pfd
3
10 000
–
mask_id
MHz
low_freq_mhz
MHz
high_freq_mhz
alpha_deltaLongitude
–
{alpha_deltaLongitude,
azimuth_elevation}
type
latitude
–
{latitude}
a_name
alpha
–
{alpha, azimuth}
b_name
deltaLongitude
–
{deltaLongitude, elevation}
c_name
c b a
<by_a a="N">
</by_a>
b
a=N
pfd
<pfd c="0">–140</pfd>
pfd
<satellite_system ntc_id="12345678" sat_name="MySatName">
<pfd_mask mask_id="3" low_freq_mhz="10000" high_freq_mhz="40000"
type="alpha_deltaLongitude" a_name="latitude" b_name="alpha"
c_name="deltaLongitude">
<by_a a="0">
<by_b b="–180">
<pfd c="–20">–150</pfd>
<pfd c="0">–140</pfd>
<pfd c="20">–150</pfd>
</by_b>
<by_b b="–8">
<pfd c="–20">–165</pfd>
<pfd c="0">–155</pfd>
<pfd c="20">–165</pfd>
</by_b>
<by_b b="–4">
<pfd c="–20">–170</pfd>
37
ITU-R S.1503-2
<pfd c="0">–160</pfd>
<pfd c="20">–170</pfd>
</by_b>
<by_b b="0">
<pfd c="–20">–180</pfd>
<pfd c="0">–170</pfd>
<pfd c="20">–180</pfd>
</by_b>
<by_b b="4">
<pfd c="–20">–170</pfd>
<pfd c="0">–160</pfd>
<pfd c="20">–170</pfd>
</by_b>
<by_b b="8">
<pfd c="–20">–165</pfd>
<pfd c="0">–155</pfd>
<pfd c="20">–165</pfd>
</by_b>
<by_b b="180">
<pfd c="–20">–150</pfd>
<pfd c="0">–140</pfd>
<pfd c="20">–150</pfd>
</by_b>
</by_a>
</pfd_mask>
</satellite_system>
epfd
e.i.r.p.
pfd
<eirp_mask_es mask_id="N" low_freq_mhz="F1" high_freq_mhz="F2" min_elev="E"
d_name="separation angle" ES_ID = “–1“>
3.4
ITU-R S.1503-2
38
6
6
e.i.r.p.
1
10 000
–
mask_id
MHz
low_freq_mhz
MHz
high_freq_mhz
10
min_elev
Separation angle
–
12345678
–
{separation angle}
d_name
ES_ID
–1 if non-specific
e.i.r.p.
<eirp d="0">30.0206</eirp>
pfd
<satellite_system ntc_id="12345678" sat_name="MySatName">
<eirp_mask_es mask_id="1" low_freq_mhz="10000" high_freq_mhz="40000"
min_elev="0" d_name="separation angle", ES_ID=–1>
<eirp d="0">30,0206</eirp>
<eirp d="1">20,0206</eirp>
<eirp d="2">12,49485</eirp>
<eirp d="3">8,092568</eirp>
<eirp d="4">4,9691</eirp>
<eirp d="5">2,54634976</eirp>
<eirp d="10">–4,9794</eirp>
<eirp d="15">–9,381681</eirp>
<eirp d="20">–12,50515</eirp>
<eirp d="30">–16,90743</eirp>
<eirp d="50">–18,9471149</eirp>
<eirp d="180">–18,9471149</eirp>
</eirp_mask_es>
</satellite_system>
39
ITU-R S.1503-2
epfd
e.i.r.p.
4.4
pfd
<eirp_mask_ss mask_id="N" low_freq_mhz="F1" high_freq_mhz="F2"
d_name="separation angle">
7
7
e.i.r.p.
1
10 000
Separation angle
–
mask_id
MHz
low_freq_mhz
MHz
high_freq_mhz
–
{separation angle}
d_name
e.i.r.p.
<eirp d="0">30.0206</eirp>
pfd
<satellite_system ntc_id="12345678" sat_name="MySatName">
<eirp_mask_ss mask_id="2" low_freq_mhz="10000" high_freq_mhz="40000"
d_name="separation angle">
<eirp d="0">30,0206</eirp>
<eirp d="1">20,0206</eirp>
<eirp d="2">12,49485</eirp>
<eirp d="3">8,092568</eirp>
<eirp d="4">4,9691</eirp>
<eirp d="5">2,54634976</eirp>
<eirp d="10">–4,9794</eirp>
<eirp d="15">–9,381681</eirp>
<eirp d="20">–12,50515</eirp>
<eirp d="30">–16,90743</eirp>
<eirp d="50">–18,9471149</eirp>
<eirp d="180">–18,9471149</eirp>
</eirp_mask_ss>
</satellite_system>
ITU-R S.1503-2
41
D
1
1.1
(SRD)
(epfd)
1
(1
(2
epfd
(3
2.1
epfd
pfd
pfd
epfd
epfd
GSO
epfd
e.i.r.p.
e.i.r.p.
epfd
epfd
e.i.r.p.
epfdis
epfdis
epfdis
GSO
3.1
2
3
4
41
ITU-R S.1503-2
epfd
5
epfd↓
1.5
epfd↑
2.5
epfdis
3.5
epfd
6
7
4.1
epfd
dB 0,1 = SB
epfd
3.1.7.D
dB 0,1
X 
4.4.6.D
1e-5
5.1
epfd
DLL
2
22
1.2
22
epfd
For all ES e.i.r.p. masks in non-GSO notice
{
Get frequency range of ES e.i.r.p. mask (fmin, fmax)
From LimitsAPI request all epfd(up) limits in range (fmin, fmax)
For all epfd(up) limits returned
{
Set FrequencyRun = max(fmin(mask), fmin(limits)) + RefBW/2
CreateRun:
Direction = Up
Frequency = FrequencyRun
Sat_Beamwidth = From Limits API
Sat_GainPattern = From Limits API
epfd_Threshold = From Limits API
Ref_BW = From Limits API
ITU-R S.1503-2
}
}
For all PFD masks in non-GSO notice
{
Get frequency range of pfd mask (fmin, fmax)
From LimitsAPI request all FSS epfd(down) limits in range (fmin, fmax)
For all epfd(down) limits returned
{
Set FrequencyRun = max(fmin(mask), fmin(limits)) + RefBW/2
CreateRun:
Direction = Down
Service = FSS
Frequency = FrequencyRun
ES_DishSize = From Limits API
ES_GainPattern = From Limits API
epfd_Threshold = From Limits API
Ref_BW = From Limits API
}
From LimitsAPI request all BSS epfd(down) limits in range (fmin, fmax)
For all epfd(down) limits returned
{
Set FrequencyRun = max(fmin(mask), fmin(limits)) + RefBW/2
CreateRun:
Direction = Down
Service = BSS
Frequency = FrequencyRun
ES_DishSize = From Limits API
ES_GainPattern = From Limits API
epfd_Threshold = From Limits API
Ref_BW = From Limits API
}
}
For all Satellite EIRP masks in non-GSO notice
{
Get frequency range of satellite EIRP mask (fmin, fmax)
From LimitsAPI request all epfd(is) limits in range (fmin, fmax)
For all epfd(is) limits returned
{
Set FrequencyRun = max(fmin(mask), fmin(limits)) + RefBW/2
CreateRun:
Direction = Intersatellite
Frequency = FrequencyRun
Sat_Beamwidth = From Limits API
Sat_GainPattern = From Limits API
epfd_Threshold = From Limits API
Ref_BW = From Limits API
}
}
42
43
ITU-R S.1503-2
7A.9
5
2.2
7A.9
If the selected earth station meets the criteria in Appendix 5
{
Get the frequency range of the selected ES(fmin, fmax)
Get all non-GSO networks in the SRS that overlap that frequency range
For each non-GSO network returned
{
For all pfd masks in non-GSO notice
{
Get frequency range of PFD mask Mask(fmin, fmax)
If there is overlap ES(fmin, fmax) with Mask(fmin, fmax)
{
Get RefBW from Appendix 5
Set FrequencyRun = max(ES_fmin, Mask_fmin) + RefBW/2
CreateRun:
Direction = Down
Frequency = FrequencyRun
ES_DishSize = From ES filing
ES_GainPattern = From ES filing
epfd_Threshold = From Appendix 5
Ref_BW = From Appendix 5
}
}
}
}
7B.9
5
7B.9
For all pfd masks in non-GSO notice
{
Get frequency range of pfd mask Mask(fmin, fmax)
Get all ES in the SRS that overlap that frequency range
For each ES returned
{
If the earth station meets the criteria in Appendix 5
{
Get the frequency range of the ES(fmin, fmax)
Get RefBW from Appendix 5
Set FrequencyRun = max(ES_fmin, Mask_fmin) + RefBW/2
CreateRun:
Direction = Down
Frequency = FrequencyRun
ES_DishSize = From ES filing
ES_GainPattern = From ES filing
epfd_Threshold = From Appendix 5
Ref_BW = From Appendix 5
}
}
}
}
3.2
ITU-R S.1503-2
44
3
epfd↓
1.3
1.1.3
pfd
pfd
:
:h
:
:i
:ES
2.1.3
epfd
(WCG)
pfd
(, φ)
0
+0 −0,0

+0

ITU-R S.1714
pfd
epfd
epfd
(dB 0,1)
epfd
–0
45
ITU-R S.1503-2
12
12
(, φ)
Elevation
 = + 0 line
 = 0 line
Search grid of ( , )
 = –0 line
Azimuth
Field of view of
non-GSO satellite
Sub-satellite point at nonGSO satellite latitude
Locations where elevation angle to
non-GSO = minimum operating
elevation angle
S.1503-12
WCGA_Down:
Set WorstEPFDBin = –9999
Set WorstAngularVelocity = +9999
For all satellites in the order listed in ITU DB
{
Determine PFD mask to use for this satellite
If this PFD mask has not been checked so far then
Call GetWCGA_Down
End if
Next satellite
GetWCGA_Down (PFD_Mask, 0, 0, ES):
StepSize = min(ES.Beamwidth, PFD_Mask_StepSize)/Nhits
If (i = 0)
{
CheckWCG_Down (latitude = 0)
}
Else
{
ITU-R S.1503-2
LatNumSteps = RoundUp(i / StepSize)
For n = 0 to LatNumSteps inclusive
{
latitude = i * n / LatNumSteps
CheckWCG_Down(latitude)
If (n > 0)
{
CheckWCG_Down(-latitude)
}
}
CheckExtremeWCG( = 0 &  = +/2}
CheckExtremeWCG( = 0 &  = -/2}
If (0 > 0)
{
CheckExtremeWCG( = 0 &  = +/2}
CheckExtremeWCG( = 0 &  = –/2}
CheckExtremeWCG( = +0 &  = +/2}
CheckExtremeWCG( = +0 &  = -/2}
}
}
CheckWCG_Down(latitude):
Locate non-GSO satellite at latitude
Calculate φ0 for elevation angle 0 and radius r
CheckCase(latitude,  = 0, φ = 0)
PhiSteps = RoundUp(φ0 / StepSize)
For φ = PhiStepSize to φ0 inclusive in PhiSteps steps
{
ThetaMin = /2
ThetaMax = +3/2
If the PFD mask is symmetric in DeltaLong or Azimuth
ThetaMax = /2
NumThetaSteps = RoundUp(2φ/PhiStepSize)
ThetaStepSize = (ThetaMax-ThetaMin)/NumThetaSteps
For ThetaStep = 0 to NumThetaSteps inclusive
{
 = ThetaMin + ThetaStep*ThetaStepSize
CheckCase(latitude, , φ)
}
If can calculate  that corresponds to  = 0
CheckCase(latitude, , φ)
If (0 > 0)
{
If can calculate  that corresponds to  = 0
CheckCase(latitude, , φ)
If can calculate  that corresponds to  = +0
CheckCase(latitude, , φ)
}
If mask is not symmetric then repeat for other hemisphere
}
46
47
ITU-R S.1503-2
CheckCase(latitude, , φ):
Convert (, φ) to (az, el)
Create line from non-GSO satellite N in direction (az, el)
Identify point P in which line intersects Earth
At point P calculate (, X, long) angles wrt point N
At point P calculate AngularVelocity using methodology below
Calculate PFD from mask, latitude & (az, el, , X, long)
Calculate Grel()
Calculate EPFDThreshold from latitude of point P
Calculate EPFDMargin = PFD + Grel() - EPFDThreshold
Calculate EPFDbin = EPFDMargin/BinSize
If WorstEPFDBin < EPFDBin
{
WorstEPFDBin = EPFDBin
Worst AngularVelocity = AngularVelocity
Store this (N, P)
}
Else if (WorstEPFDBin = EPFDBin &&
WorstAngularVelocity > AngularVelocity)
{
WorstAngularVelocity = AngularVelocity
Store this (N, P)
}
CheckExtremeWCG(,):
Iterate in true anomaly until find latitude for (, )
Calculate φ0 at latitude
CheckCase(latitude, , φ0)
3.1.3
(, φ)
1.3.1.3
cos(φ) = cos(az) cos(el)
sin(el) = sin(θ) sin(φ)
2.3.1.3

sin(ω + ) =
sin 𝑙𝑎𝑡
sin 𝑖
ITU-R S.1503-2
48
𝑟𝑠𝑎𝑡 = 𝑟𝑠𝑎𝑡 (cos  𝑃 + sin  𝑄)
𝜇
𝑠𝑎𝑡 = √ (– sin  𝑃 + (𝑒 + cos ) 𝑄)
𝜌
P
P, Q
a, e, 
𝑝
1 + 𝑒 cos 
p = a(1 – e2)
𝑟𝑠𝑎𝑡 =
PQW
i  
J2

φ
3.3.1.3
φ0

sin(φ0 ) =
𝑅𝑒
π
sin ( + ε)
𝑟𝑠𝑎𝑡
2
φ
4.3.1.3
φ0
13

49
ITU-R S.1503-2
13

Elevation
 = /2,  = 0
Constant  curve corresponding to
minimum operating elevation angle
Azimuth
Field of view of
non-GSO satellite
Sub-satellite point at nonGSO satellite latitude
 = –/2,  = 0
S.1503-13
(, φ)
Re
P

P
5.3.1.3
res
es
rsat
sat
r = rsat – res
 = sat – es
ITU-R S.1503-2
cos ψ =
θ=
51
𝑟∙
𝑟

sin ψ
𝑟
14
14
Vsat
y
V
rsat
r
VES
rES
S.1503-14
epfd
z y x
–𝑦
𝑒𝑠 = 𝑤𝑒 ( 𝑥 )
𝟎
we
 h 
6.3.1.3
 h 
/2
 

15
51
ITU-R S.1503-2
15

Elevation
 = +0
= 0
 = –0
Sub-satellite
point
Minimum
operating
elevation
= 0
 = –0
Elevation
Azimuth
Field of view of
non-GSO
satellite
Elevation
Sub-satellite
point
Sub-satellite
point
Minimum
operating
elevation
Highest latitude for  > 0
 = –0
Field of view of
non-GSO
satellite
Minimum
operating
elevation
Highest latitude for  = 0
Field of view of
non-GSO
satellite
Highest latitude for  < 0
S.1503-15


 h 
7.3.1.3
16
16

ES

g
Re
ES
 x
Re
p
q

dp
Non-GSO
satellite
Non-GSO
satellite
Re + h
g
Re + h
y
GSO Satellite
Rge o
S.1503-16
 R


y  arcsin  e sin      
2

 RGeo
p

y
2
ITU-R S.1503-2
52
 Re


g  arcsin 
sin     
2

 Re  h

g 
2
dp 
q  p  dp
 +   /2
 +  < /2
q

p
 h 
8.3.1.3
17
17

Non-GSO
satellite
ES




x
g
Re
Non-GSO
satellite
ES
x
dp
Re + h
g
Re
p
Re + h
y
q
GSO Satellite
R ge o
S.1503-17
 R


y  arcsin  e sin    
2

 RGeo
p

y
2
 Re


g  arcsin 
sin      

 Re  h  2
dp 

g 
2
53
ITU-R S.1503-2
q  p  dp
 +   /2
 +  < /2
q
 h 
 h 
p
, φ
9.3.1.3

18
18
 

Elevation
 = /2,  > 0
 line
Find  point using
binary chop

Sub-satellite point of
non-GSO satellite

Azimuth
Field of view of
non-GSO
satellite
 that corresponds to
minimum operating
elevation 
 = –/2,  < 0
S.1503-18
φ0
sin(φ0 ) =
𝑅𝑒
π
sin ( + ε)
𝑅𝑒 + ℎ
2
ITU-R S.1503-2
54
FindThetaPhiFromAlpha(lat, , h, ):
Configure Non-GSO satellite at latitude = lat
Phi0 = GetPhiZero(h, ) using equation above
Theta0 = /2
Theta1 = +/2
Alpha0 = GetAlpha(Theta0, Phi0)
Alpha1 = GetAlpha(Theta1, Phi0)
If Alpha0 <  then
{
Return fail with (Theta0, Phi0) as nearest angles
}
Else if Alpha1 > 
{
Return fail with (Theta1, Phi0) as nearest angles
}
While (Theta1 – Theta0 < 1e-6)
{
Theta2 = (Theta1 + Theta0)/2
Alpha2 = GetAlpha(Theta2, Phi0)
If (Alpha2 > )
{
Theta1 = Theta2
Alpha1 = Alpha2
}
Else
{
Theta0 = Theta2
Alpha0 = Alpha2
}
}
Return (Theta1, Phi0) and ok
GetAlpha(, φ):
Convert (, φ) to (az, el)
Create line in direction (az, el) from non-GSO satellite
Identify point P where line intersects Earth
At point P calculate 
Return 
epfd↑
2.3
1.2.3
e.i.r.p.
:ES_eirp
:θadB
:
:a,i,e, ,,
55
ITU-R S.1503-2
2.2.3
epfd
(WCG)
WCGA_UP:
Calculate φ0
From φ0 calculate LatBS
If single EIRP mask for all ES and ES from density
If orbit (e = 0, i > 0)
WCG(lat, long) = {LatBS, 0}
If orbit (e = 0, i = 0)
WCG(lat, long) = {0, LatBS}
If orbit (e > 0) and apogee in northern hemisphere
WCG(lat, long) = {LatBS, 0}
If orbit (e > 0) and apogee in southern hemisphere
WCG(lat, long) = {LatBS, 0}
Else
If ES from density
If (i = 0)
Call WCGA_UP_Equatorial_all
Else
Call WCGA_UP_General
Endif
Else
If non-GSO satellite repeats
Call WCGA_UP_SpecifcES_Repeating
Else
Call WCGA_UP_SpecifcES_NonRepeating
Endif
Endif
Endif
3.2.3
1.3.2.3
epfd
epfd
EPFD = EIRP(0) – 10log10(4πD2)
D
epfd
19
ITU-R S.1503-2
56
19
Elevation
 = /2,  = 0
Constant  curve corresponding to
minimum operating elevation angle
GSO
beamwidth
Azimuth
Field of view of
GSO satellite
GSO s ub-satellite point
S.1503-19
22
epfd
57
ITU-R S.1503-2
20
EOC = edge of
GSO coverage

Re
y
3dB /2
BS = boresight
of GSO beam
LatBS
EOC
GSO Satellite
Rge o
S.1503-20
sinφ𝐸𝑂𝐶 =
𝑅𝑒
π
sin ( + ε)
𝑅𝑔𝑒𝑜
2
φ𝐵𝑆 = φ𝐸𝑂𝐶 –
θa𝑑𝐵
2
/2
sin(π – ψ) =
y
𝑅𝑔𝑒𝑜
sin(φ𝐵𝑆 )
𝑅𝑒
LatBS = π – φBS – ψ
8
8
Ka
Ku
1,55
4
20
10
50,9
42,5
e.i.r.p.
e.i.r.p.
ITU-R S.1503-2
21
58
e.i.r.p.
21
Elevation
WCG for circular orbit global
coverage and elliptical systems with
apogee in northern hemisphere
GSO
beamwidth
WCG for equatorial orbit systems
Azimuth
Field of view of
GSO satellite
GSO s ub-satellite point
WCG for circular orbit global
coverage and elliptical systems with
apogee in northern hemisphere
S.1503-21
e.i.r.p.
1
2
e.i.r.p.
%0
%100
22
3
epfd
2.3.2.3
epfd
C
B A
22
59
ITU-R S.1503-2
22

y
Re
non-GSO
satellite

Rngso

i
Latmax
S.1503-22
a
(km)
e

i
ra = a(1 + e)
π
ψ= + ε
2
𝑅𝑒
φ𝑎 = sin–1 ( sin ψ)
𝑟𝑎
θa = π – (ψ + φa)
Latmax = i + θa
rp = a(1 – e)
(a)
(P)
Latmin = –i – θp
e=0
 = 270°
ITU-R S.1503-2
61

e>0
 = 90°
Latmax’ = –Latmin
Latmin’ = –Latmax
Latmax = θ
Latmin = –θ
e.i.r.p.
3.3.2.3
1.3.3.2.3
e.i.r.p.
23
23
Elevation
Test location on  line
Non-GSO satellite’s
path along equator
as seen by GSO
satellite
Satellite furthest
from GSO arc and
yet still usable
Satellite closer to
GSO arc and GSO
satellite beam
Azimuth
Field of view of
GSO satellite
GSO s ub-satellite point
S.1503-23
61
ITU-R S.1503-2

e.i.r.p.
epfd
EPFD = EIRP(θ) – 10log10(4πD2)

e.i.r.p.
e.i.r.p.
2.3.3.2.3
e.i.r.p.
𝑅𝑔𝑒𝑜
sin(φ𝐵𝑆 )
𝑅𝑒
θBS = π – φBS – ψBS
sin(π – ψ𝐵𝑆 ) =
24
24
EOC = edge of
GSO coverage

Re
y
3dB /2
BS = boresight
of GSO beam
BS
BS
EOC
GSO Satellite
Rge o
S.1503-24
cos θBS = cos latES cos ∆longES
ITU-R S.1503-2
cos ∆𝑙𝑜𝑛𝑔𝐸𝑆 =
𝑟𝐸𝑆
62
cos θ𝐵𝑆
cos 𝑙𝑎𝑡𝐸𝑆
cos 𝑙𝑎𝑡𝐸𝑆 cos ∆𝑙𝑜𝑛𝑔𝐸𝑆
= 𝑅𝑒 ( cos 𝑙𝑎𝑡𝐸𝑆 sin ∆𝑙𝑜𝑛𝑔𝐸𝑆 )
sin 𝑙𝑎𝑡𝐸𝑆
𝟏
𝑟𝐺𝑆𝑂 = 𝑅𝐺𝑆𝑂 (𝟎)
𝟎
2
𝐷2 = 𝑅𝑒2 + 𝑅𝑔𝑒𝑜
+ 2𝑅𝑒 𝑅𝑔𝑒𝑜 cos ∆𝑙𝑜𝑛𝑔𝐸𝑆
sin 𝐴𝑧𝑖𝑚𝑢𝑡ℎ =
sin(π – ψ𝑁𝐺𝑆𝑂 ) =
𝑅𝑒
sin ∆𝑙𝑜𝑛𝑔𝐸𝑆
𝐷
𝑅𝑔𝑒𝑜
sin(𝐴𝑧𝑖𝑚𝑢𝑡ℎ)
𝑅𝑁𝐺𝑆𝑂
∆𝑙𝑜𝑛𝑔𝑁𝐺𝑆𝑂 = π – 𝐴𝑧𝑖𝑚𝑢𝑡ℎ – ψ𝑁𝐺𝑆𝑂
cos ∆𝑙𝑜𝑛𝑔𝑁𝐺𝑆𝑂
𝑟𝑁𝐺𝑆𝑂 = 𝑅𝑒 ( sin ∆𝑙𝑜𝑛𝑔𝑁𝐺𝑆𝑂 )
𝟎
r1 = rGSO – rES
r2 = rNGSO – rES
r1
epfd
x = max(0, Angle(r1, r2))
epfd
EPFD = EIRP(x) – 10log10(4πr12)
epfd
63
ITU-R S.1503-2
WCGA_UP_Equatorial_Masks:
For all EIRP masks
Call WCGA_Up_Equatorial(max(LatMax, Mask start latitude))
Call WCGA_Up_Equatorial(min(+LatMax, Mask end latitude))
Next mask
e.i.r.p.
3.3.3.2.3
e.i.r.p.
e.i.r.p.
1
e.i.r.p.
WCGA_UP_Equatorial_all:
LatStepSize = min(1, StepSizeinEIRPMask)
Calculate LatMax from non-GSO orbit parameters
For latitude = 0 to LatMax
Get EIRP mask for this latitude
WCGA_Up_Equatorial(latitude)
Next latitude
e.i.r.p.
WCGA_Up_Equatorial(latitude):
Calculate the GSO satellite’s φBS
For this latitude, calculate the longitude
Calculate the ES and GSO satellite vectors
Calculate the longitude of the non-GSO satellite
Calculate the non-GSO satellite vector
Calculate offaxis angle at ES
Calculate EPFD
If this is the highest EPFD so far then store it
4.3.2.3
1.4.3.2.3

0  
epfd
ITU-R S.1503-2
64
25
25
Elevation
Maximum angle from GSO
sub-satellite point can point a
beam = 0
ES location as seen by GSO
satellite
GSO sub-satellite point

GSO adjusted boresight
position

Azimuth
Field of view of
GSO satellite
S.1503-25

 
o 
0 

65
ITU-R S.1503-2
WCGA_UP_SpecifcES_Repeating:
Set WorstEPFD = –999
For each ES
Get
Get
Use
Get
For
the EIRP mask for this ES
the beamwidth for this EIRP mask
the beamwidth to calculate the time step = t_step
t_repeat = the repeat period of the constellation
t = 0 to t_repeat with step size t_step
Update the position vector of this ES
For all non-GSO satellites
Update the position vector of this satellite
If this satellite is visible to the ES
Calculate α for this satellite, ES
Calculate elevation angle ε for this satellite
If α  α0 and ε > ε0 then
Calculate d = distance ES to α point on GSO arc
Calculate GSO boresight position and φ
Calculate EPFD = EIRP(α) + Grel(φ)
–10log10(4πd2)
If EPFD > WorstEPFD then
WorstEPFD = EPFD
Store this GSO(long, boresight) geometry
Endif
Endif
Endif
Next satellite
Next time step
Next ES
2.4.3.2.3
26
ITU-R S.1503-2
66
26
ES location
Re
y
d
ES
LatES
GSO satellite
Rgeo
S.1503-26
2
𝑑2 = 𝑅𝑒2 + 𝑅𝑔𝑒𝑜
– 2𝑅𝑒 𝑅𝑔𝑒𝑜 cos 𝑙𝑎𝑡𝐸𝑆

sin φ𝐸𝑆 =
𝑅𝑒
sin 𝑙𝑎𝑡𝐸𝑆
𝑑

φ0 φES

φ0 φES
EPFD = EIRP(0) + Grel(∆φ) – 10log10(4πd2)
epfd
epfd
e.i.r.p.
5.3.2.3
e.i.r.p.
epfd
EPFD = EIRP(0) + 10log10(4πd2)
epfd
epfd
67
ITU-R S.1503-2
27
Elevation
Test location on  line
Azimuth
Field of view of
GSO satellite
GSO sub-satellite point
S.1503-27
e.i.r.p.
(0) e.i.r.p.
θBS
cos θBS = cos latBS cos ∆longBS
𝑟𝐸𝑆
cos 𝑙𝑎𝑡𝐸𝑆 cos ∆𝑙𝑜𝑛𝑔𝐸𝑆
= 𝑅𝑒 ( cos 𝑙𝑎𝑡𝐸𝑆 sin ∆𝑙𝑜𝑛𝑔𝐸𝑆 )
sin 𝑙𝑎𝑡𝐸𝑆
𝑟𝐺𝑆𝑂
𝟏
= 𝑅𝐺𝑆𝑂 (𝟎)
𝟎
e.i.r.p.
ITU-R S.1503-2
68
𝑟 = 𝑝 + λ𝑞
p = rGSO
𝑞 = 𝑟𝐸𝑆 – 𝑟𝐺𝑆𝑂

2
λ2 𝑞 2 + 2λ𝑝 · 𝑞 + (𝑝2 – 𝑟𝑛𝑔𝑠𝑜
)=0
(longitude)
sin(ω + ) =
sin 𝑙𝑎𝑡
sin 𝑖

longGSO = longNGSO – ∆longitude

SetSatelliteElliptical:
Set LatIn1 = 0.00001
Set LatIn2 = LatBS
LatOut1 = CalcLatOut(LatIn1)
LatOut2 = CalcLatOut(LatIn2)
While (abs(LatIn1 – LatIn2) > 1e-6)
LatIn3 = (LatIn1 + LatIn2)/2
LatOut3 = CalcLatOut(LatIn3)
if (dLatIn3 > dLatOut3)
{
dLatIn2 = dLatIn3
dLatOut2 = dLatOut3
}
else
{
dLatIn1 = dLatIn3
dLatOut1 = dLatOut3
}
Wend
69
ITU-R S.1503-2
CalcLatOut(LatIn):
From LatIn calculate non-GSO (w + v) and hence v
Hence calculate r_ngso = p/(1 + e*cos(nu))
Solve line for point P where r = r_non
Calculate latitude of point P
Return latitude calculated
Hence:
WCGA_UP_General:
Set WorstEIRP = -999
Set MaxLat = 0
Calculate φ0
For each EIRP mask
Calculate ThisEIRP = max(EIRP( > α0), EIRP(α0))
If ThisEIRP > WorstEIRP
Set MaxLat = the largest absolute latitude for this mask
WorstEIRP = ThisEIRP
Endif
Next mask
From MaxLat and φ0 calculate the longitude
Calculate when first non-GSO satellite would be inline
Hence set WCG
epfdIS
3.3
1.3.3
e.i.r.p.
:SS_eirp
:θadB
:
:a,i,e, ,,
2.3.3
WCGA_IS:
From the EPFD limits get the gain pattern to use
From the EPFD limits get the GSO beamwidth θadB
From θadB calculate φ1, φ2
Using the gain pattern calculate Grel(φi) for i = 1,2
From φ1 calculate LatBS
If for all satellites i = 0 then
{
Worst Case Geometry:
BS.Latitude = 0
BS.Longitude = LatBS
GSO.Longitude = 0
}
Else
{
ITU-R S.1503-2
71
Set WorstEPFDBin = -9999
Set WorstAngularVelocity = +9999
For all satellites in the order listed in ITU DB
{
Determine EIRP mask to use for this satellite
If this EIRP mask has not been checked so far then
Call GetWCGA_IS(EIRP_mask, i)
End if
Next satellite
Rotate GSO, BS in longitude to ensure inline event
}
GetWCGA_IS(EIRP_Mask, i):
LatStep = i / RoundUp(i)
For lat=i to +i in LatStep steps
{
Set satellite at latitude to calculate r, v
If satellite is above minimum operating height
{
From r, φi calculate ψi
From φi, ψi calculate Di, θi
Try to calculate ∆longi
In the cases that the geometries are feasible
{
From the GSO gain pattern calculate Grel(φi)
From the EIRP mask calculate EIRP(ψi)
Calculate EPFDi
Calculate rgso, gso
Calculate θ of non-GSO satellite as seen by GSO
If EPFDi is higher than WorstEPFD
{
Store this geometry
WorstAngularVelocity = θ
WorstEPFD = EPFDi
}
Else if EPFDi is the same bin as WorstEPFD
{
If θ is lower than WorstAngularVelocity
{
Store this geometry
WorstAngularVelocity = θ
}
}
}
}
}
3.3.3
71
ITU-R S.1503-2
28
Non-GSO satellite
position 2
EOC = edge of
GSO coverage
BS = boresight
of GSO beam
Re

Non-GSO satellite
position 1
3dB /2
y
EOC
LatBS
GSO Satellite
R ge o
S.1503-28
e.i.r.p. ()
29
Non-GSO satellite
position 2
y2
D2
Non-GSO satellite
position 1
Rngso, 2
y1
2
1
D1
Rngso, 1
2
1
GSO Satellite
R ge o
S.1503-29
ITU-R S.1503-2
72
φ1 = φBS
𝑅𝑒
𝑅𝑔𝑠𝑜
sinφ2 =
sin ψ𝑖 =
𝑅𝑔𝑒𝑜
sin φ𝑖
𝑅𝑛𝑔𝑠𝑜,𝑖
π
2
π
y2
2
y1
2 1
θi = π – φi – ψi
𝐷𝑖 = 𝑅𝑛𝑔𝑠𝑜,𝑖
Rngso,i
sin θ𝑖
sin φ𝑖
epfd
𝐸𝑃𝐹𝐷𝑖 = 𝐸𝐼𝑅𝑃(ψ𝑖 ) + 𝐺𝑟𝑒𝑙,𝑖 – 10log10 (4π𝐷𝑖2 )
φ1
φ2 Grel
Grel,2 0
Grel,1
epfd
cos ∆𝑙𝑜𝑛𝑔𝑖 =
cos θ𝑖
cos 𝑙𝑎𝑡𝑖
epfd
𝑔𝑠𝑜
–𝑦
= 𝑤𝑒 ( 𝑥 )
𝟎
e.i.r.p.
epfd
3.2.3.C 3.1.3.C
i
73
ITU-R S.1503-2
4
1.4
2.4
t
pfd↓
tref
Nhit
tref 
(1)
t
Nhit
t
t
30
∆𝑡 =
(2)
φ=
2φ
ω
1
𝑅𝑒
1
θ3dB – arcsin [
sin ( θ3dB )]
2
𝑅𝑒 + ℎ
2
 
(3)
(3) (2)
 s
cos(i) – e 2  s sin (i)2
s 
0.071
( Re  h)
Re 1.5
:s
s
:e
:i
ITU-R S.1503-2
74
:3dB
dB 3
:Re
(km)
1
:h
(km)
h
1
30
epfd
GSO SS
non-GSO
SS
1 2
3
Nhits
3dB
GSO
ES

SS
SS: space station
ES: Earth station
ES
S.1503-30
Nhit
5.4.D
Nhit
16
Nhit
75
ITU-R S.1503-2
9
i
km
h
3dB
–
dB 3
Nhit
epfd↓
3.4
epfd↑
(2) (1)
Nhit
31
ITU-R S.1503-2
76
31
epfd
GSO SS
non-GSO
SS
1
2
3
Nhits
3dB
nonGSO
ES

SS
SS: space station
ES: Earth station
ES
S.1503-31
10
i
km
h
3dB
–
Nhit
dB 3
(epfd)
77
ITU-R S.1503-2
4.4
Nhit
epfdis
:R e
:h
:Rgeo
:3dB
 = –
32
32
GSO satellite
GSO satellite
3dB
1
D1
D1
2 D2
2
R ge o
D3
R ge o
Re + h
Re + h

3
Re
Non-GSO
satellite
Non-GSO
satellite
S.1503-32
ITU-R S.1503-2
78
 R
1  arcsin  e
R
 geo




Rgeo 


2  180 – arcsin  sin ( 1 )
Re  h 

3  180 – ( 1  2 )
D1   Re  h 
sin 3
sin 1
𝐷2 = 2𝐷1 sin (
θ3dB
)
2
D3  D2 cos (180 – 2 )
(4)
𝐷3 /2
φ = 2 arctan [
]
(𝑅𝑒 + ℎ) – (𝐷2 /2) sin(180 – θ2 )
(2)
Nhit
5.4
epfd
dB 0,1
epfd
Nhit
dB 0,05 = (0,1 dB)/2
33
79
ITU-R S.1503-2
33
Nhits
)( Gain ( )
Parabolic main
beam
3dB/ N hit
Offaxis
angle = 
3dB

S.1503-33
∆θ =
θ3dB
𝑁ℎ𝑖𝑡
𝐺𝑟𝑒𝑙 = 12 (
2
θ
θ3dB
)
dGrel
24


2
d
3dB
dB 0,05
Nhit
∆𝐺𝑟𝑒𝑙 = 0,05 = 24 ∙
θ
θ3dB
∙
∆θ
θ
1
= 24 ∙
∙
θ3dB
θ3dB 𝑁ℎ𝑖𝑡
𝑁ℎ𝑖𝑡 = 480 ∙

θ
θ3dB
1 3dB
2 N hit
ITU-R S.1503-2
N hit  RoundUp
81
 240  16
Ntrack = Nhit = 16
6.4
epfd↑ epfd↓
5.D
𝑇𝑟𝑢𝑛 =
2π
𝑤𝑠 – 𝑤𝑒
N steps  RoundDown
11
Trun
Tstep
2.D
we
ws
11
–
–
NS  10
Nmin  NS  100/(100 – (%100
22
))
%99,999
Nmin  1 000 000
81
ITU-R S.1503-2
1.6.4
3.6.D
34
34
S.1503-34
34
12
s
Prepeat
:Nmin
(s)
:Prepeat
(s)
5.4.D
16
:Tstep
:Ntracks
ITU-R S.1503-2
82
Nrepsteps  Prepeat/Tstep
′
𝑇𝑠𝑡𝑒𝑝
= 𝑇𝑠𝑡𝑒𝑝 (1 + 𝑁𝑟𝑒𝑝𝑠𝑡𝑒𝑝𝑠 )/ 𝑁𝑟𝑒𝑝𝑠𝑡𝑒𝑝𝑠
Tsig  Nmin · Tstep
Nrep  round (Tsig/Prepeat)
Ntracks
Nrep
Nrun  max (Nrep, Ntracks)
Trun = Nrun · Prepeat
Nsteps  round (Trun/Tstep)
2.6.4
Ntrack  Nhits
35
83
ITU-R S.1503-2
35
non-GSO satellite track
GSO ES beam
S.1503-35
35
13
i
km
a
3dB
–
(1)
dB 3
Ntracks
epfd↑
epfdis
epfd↓
(1)
e.i.r.p.

epfd↑

epfdis
(3)
(4)
Spass

Sreq
ITU-R S.1503-2
84
𝑛, Ω𝑟 , ω𝑟
2.3.6.D
1
𝑛, Ω𝑟 , ω𝑟
:
𝑃𝑛 =
2
3
360
𝑤𝑟 + 𝑛
S
4
0,250684 e
Spass  (e – r) Pn
Spass
Sreq
5
(3)
𝑆𝑟𝑒𝑞 =
2φ
𝑁𝑡𝑟𝑎𝑐𝑘𝑠
6
𝑁𝑜𝑟𝑏𝑖𝑡𝑠 =
180
𝑆𝑟𝑒𝑞
Norbits
7
8
Stotal  Norbits  Spass
0
𝑁360 = int (
9
𝑆𝑡𝑜𝑡𝑎𝑙
)
360
10
𝑆𝑎𝑐𝑡𝑢𝑎𝑙 =
360𝑁360
𝑁𝑜𝑟𝑏𝑖𝑡𝑠
11
Sartificial = Sactual – Spass
𝐷𝑎𝑟𝑡𝑖𝑓𝑖𝑐𝑖𝑎𝑙 =
𝑆𝑎𝑟𝑡𝑖𝑓𝑖𝑐𝑖𝑎𝑙
𝑇𝑝𝑒𝑟𝑖𝑜𝑑
degrees/orbit
degrees/s
85
ITU-R S.1503-2
D
12
:
Trun  Tperiod · Norbits
13
Nsteps  Round (Trun / Tstep)
7.4
epfd
0
X

X

1.7.4
36
36
GSO earth station
Exclusion zone for
non-GSO satellite
Track across
exclusion zone
GSO arc
GSO satellite
S.1503-36
GSO
coarse = 1,5
ITU-R S.1503-2
0

86
X GSO
r
GSO
100<D/
1 = r = 15,85(D/)–0,6
GSO
100>D/
1 = 95 /D
r
3,5
φFSR_1 = max (3,5, φ1)
 = 0
X = X0
φFSR_2 = φcoarse
(3dB) GSO
Ncoarse = Floor ((Nhits * φcoarse) / φ3dB)
floor
1,5
epfd
0

2.7.4
87
ITU-R S.1503-2
37
37
non-GSO earth station
Exclusion zone for
non-GSO satellite
Track across
exclusion zone
GSO arc
GSO satellite
S.1503-37
GSO
φcoarse = 1,5
(3dB)
Ncoarse = Floor ((Nhits * φcoarse) / φ3dB)
floor
1,5
epfd
5
epfd↓
1.5
epfd↓
pfd
pfd
epfd↓
epfd↓
ITU-R S.1503-2
88
38
38
epfd
S.1503-38
1.1.5
GHz
F_DOWN
GSO_LONG
GSO_ES_LAT
GSO_ES_LONG
m
GSO_ES_D_ANT
GSO_ES_PATTERN
5.6.D
kHz
REFBW
–
Nepfd_DOWN
dB(W/(m2 · BWref))
epfd_DOWN[I]
%
PC[I]
epfd↓
Nepfd_DOWN epfd↓
Nepfd_DOWN
89
ITU-R S.1503-2
2.1.5
1.3.B
C
pfd
–
Nsat
GHz
F_DOWNsat
(1)
Alpha or X
MIN_EXCLUDE
Nco[Latitude]
fsat
Wdelta
km
H_MIN
2.3.B
1.3.6.D
N-th
N-th
[N]
pfd [N]
pfd
pfd
pfd

pfd
–
pfd[N]
km
A[N]
–
E[N]
X
pfd
pfd
I[N]
O[N]
W[N]
V[N]
3.1.5
4.D
TSTEP

NSTEPS
ITU-R S.1503-2
91
4.1.5
MIN_OPERATING_HEIGHT
GSO
epfd
GSO
2.1.5.D
1
1.1.5.D
2
1.3.D
GSO
epfd
3
epfd↓
4
4.D
5
1.5
1
Tcoarse = Tfine * Ncoarse
22
Ncoarse
1.5
1.6
6
22
Tfine = Tstep
7
Tfine = Tstep
1.6
Ncoarse
2.6
FSR_1
X
Tfine = Tstep
X0

3.6
0
FSR_2
Tstep = Tcoarse
1.6.D
7
2.6.D
GSO
8
9
3.6.D
epfd↓
GSO
10
11
1.4.6.D
18
X
5.4.6.D
4.4.6.D

pfd
13
12
13
91
ITU-R S.1503-2

pfd
pfd
14
GSO
X
5.1.5.D
pfd
GSO

GSO
GSO
15
GRX()
dB
16
5.6.D
epfd↓
GSO
17
epfd↓i = pfd() + GRX() – Gmax 18
Gmax
epfd↓
epfd↓
Nco[lat]
19
21
20
Nco[lat]
GSO_ES
GSO
epfd↓i
epfd↓
(Tstep/Tfine)
epfd↓
21
epfd↓
22
epfd↓
23
2.1.7.D
1.7.D
epfd↓
24
3.7.D
25
pfd
pfd
5.1.5
pfd
ii+
i

pfd
X
pfd
pfd
C
pfd
ITU-R S.1503-2
92
6.1.5
dB(W/(m2 · BWref))
epfd_DOWN_CALC[I]
epfd↓
%
PC_CALC[I]
epfd_DOWN_CALC[I]
PC_CALC[I]
epfd↑
2.5
epfd↑
GSO
(1
1–
e.i.r.p.
ES_ID
e.i.r.p.
(2
epfd↑
e.i.r.p.
e.i.r.p.
GSO
epfd↑
39
GSO
GSO
93
ITU-R S.1503-2
39
epfd↑
S.1503-39
1.2.5
epfd↑
N
1.2.D
non-GSO
GHz
FREQ
FEND_UP
GSO
5.6.D
dBi
GSO_SAT_PEAKGAIN
GSO_SAT_BEAMWIDTH
kHz
RAFBW
–
Nepfd_UP
dB(W/(m2 · BWref))
epfd_UP[I]
%
PC_UP[I]
GSO
GSO
epfd↑
Nepfd_UP epfd↑
Nepfd_UP
ITU-R S.1503-2
94
epfd
2.3.D
GSO
2.2.5
epfd
3.2.5
4.D
4.2.5
1.4.2.5
2.4.2.5
1.3.B
–
Nsat
–
–
Wdelta
2.3.B
1.3.6.D
N
(N)
[N]
km
A[N]
–
E[N]
I[N]
O[N]
W[N]
V[N]
2.4.B
95
ITU-R S.1503-2
–
ES_TRACK
dB(W/BWref)
ES_EIRP[lat]
e.i.r.p.
ES_MINELEV
ES_MIN_GSO
2
km
ES_DENSITY
km
ES_DISTANCE
GSO
3.4.2.5
2.3.D
GSO_SAT_LONG
GSO
BS_LAT
GSO
BS_LONG
GSO
GSO_SAT_PATTERN
GSO
5.6.D
2.6.D 1.6.D
4.4.2.5
4.D
TSTEP

NSTEPS
5.2.5
1
NUM_ES = ES_DISTANCE * ES_DISTANCE * ES_DENSITY
e.i.r.p.
2
REP_e.i.r.p. = ES_e.i.r.p. + 10log10(NUM_ES)
dB 15
3
ES_DISTANCE
ES_DISTANCE
4
3
REP_e.i.r.p.
40
GSO
ITU-R S.1503-2
96
40
Align central line of
non-GSO
non-GSO
ES with
GSO boresight
GSO
GSO satellite
footprint
GSO
Maximum latitude of
non-GSOES
non-GSO
At each latitude
deploy east and west
of central line
Separation between
non-GSO ES should
be thenon-GSO
same distance
in both East/West
and North/South
directions
Boresight of
GSO
satellite
GSO
At each latitude
deploy east and west
of central line
Minimum latitude of
non-GSO ES
non-GSO
S.1503-40
∆𝑙𝑎𝑡 =
∆𝑙𝑜𝑛𝑔 =
𝑑
𝑅𝑒
𝑑
𝑅𝑒 cos 𝑙𝑎𝑡
6.2.5
epfd
GSO
2.4.2.5.D
1
3.4.2.5.D
GSO
2
97
ITU-R S.1503-2
epfd
GSO
3
2.3.D
4
5.2.5.D
epfd
5
4.D
1
6
Ncoarse
1.6
Tcoarse = Tfine * Ncoarse
1.6
24
22
8
7
1.7
Tfine = Tstep
1.7
Tfine = Tstep
Ncoarse
coarse
2.7

3.7
Tcoarse = Tstep
Tfine = Tstep
1.6.D
8
9
2.3.6
10
2.6.D
23
0 = epfd
11
13
12
13
1.4.6.D
23
15
GSO
14
23
(i-th)
16
15
16
GSO
23
18
17
ITU-R S.1503-2
98
(dB(W/BWraf) ES_EIRP [lat]
18
e.i.r.p.
C
3
REP_EIRP = ES_EIRP[lat] + 10log10 (NUM_ES)
GSO
(dB)
GRX
19
D
20
5.6.D
GSO
(km)
1.4.6.D
LFS = 10 log(4 D2) + 60
21
epfdi
22
epfdi  REP_EIRP – LFS + GRX – Gmax
epfd
epfd↑
:
.epfd↑
epfd↑
Tstep/Tfine
epfd↑
epfdi
23
epfd
24
1.24
epfd↑
25
2.1.7.D
1.7.D
epfd
2.7.D
26
27
7.2.5
NEPFD↑
dB(W/(m2 · BWref))
epfd_UP_CALC[I]
%
PC_CALC[I]
Nepfd_UP epfd↑
Nepfd_UP
epfd_UP_CALC[I]
PC_CALC[I]
epfdis
3.5
epfdis
epfdis
e.i.r.p.
epfdis
99
ITU-R S.1503-2
1.3.5
epfdis
(N)
1.2.D
GHz
FREQ
FEND_IS
GSO
5.5.D
dBi
GSO_SAT_PEAKGAIN
GSO
GSO_SAT_BEAMWIDTH
kHz
RIFBW
–
Nepfd_IS
2
dB(W/(m · BWrif))
epfd_IS[I]
%
PC_IS[I]
GSO
epfdis
Nepfd_IS epfdis
Nepfd_IS
epfd
3.3.D
2.3.5
GSO
3.3.5
4.D
4.3.5
1.4.3.5
1.2.B
–
Nsat
–
–
Wdelta
ITU-R S.1503-2
111
1.2.B
1.3.6.D
N-th
(N-th)
[N]
km
A[N]
E[N]
I[N]
O[N]
W[N]
V[N]
3.4.B
dB(W/BWrif)
non-GSO_SS_EIRP
GHz
e.i.r.p.
(1)
IS_F
(1)
e.i.r.p.
GSO
2.5.D
GSO
GSO_SAT_LONG
GSO
BS_LAT
GSO
BS_LONG
5.5.D
2.4.3.5
GSO
GSO_SAT_PATTERN
GSO
2.6.D
1.6.D
3.4.3.5
4.D
TSTEP
NSTEPS
Time step
Number of time steps
111
ITU-R S.1503-2
5.3.5
1
Ncoarse epfdis
epfdis
GSO
2.4.3.5.D
1
3.4.3.5.D
GSO
2
3.3.D
3
epfdis
4
4.D
1
5
Ncoarse
1.5
Tcoarse = Tfine * Ncoarse
1.5
19
17
7
6
1.6
Tfine = Tstep
Tfine = Tstep
1.6
Ncoarse
coarse
2.6

Tstep = Tcoarse
3.6
Tfine = Tstep
7
3.6.D
2.6.D
8
0 = epfdis
18
10
9
10
11
1.4.6.D
12
18
13
e.i.r.p. (dB(W/BWrif)
3.C
GSO
13
e.i.r.p.
(dB)
GRX
5.6.D
14
ITU-R S.1503-2
112
GSO
(km)
D
15
1.4.6.D
LFS = 10 log(4 D2) + 60
16
epfdisi
17
epfdisi = e.i.r.p. – LFS + GRX – Gmax
epfdisi
epfdis
Tstep/Tfine
epfdis
epfdis
epfdis
epfd is
epfdis
18
19
1.19
epfd is
20
2.1.7.D
1.7.D
epfdis
21
2.7.D
22
6.3.5
dB(W/(m2 · BWrif))
epfd_IS_CALC[I]
%
PC_CALC[I]
epfd_IS_CALC[I]
Nepfd_IS epfdis
Nepfd_IS
PC_CALC[I]
6
X
1.6
41
113
ITU-R S.1503-2
41
VectorZZ axis
Earth station
Re
XYXY plane
Vector
Latitude
Origin = O
O
S.1503-41
Z
Re = 2.2.A
Z
XY
2.2.A
XY
42
42
Earth station
+ve longitude
Positive
vector Z axis
Reference longitude = 0
S.1503-42
Y X
XY
e
ITU-R S.1503-2
114
𝑥
(5)
Long = arccos (
(6)
Long =– arccos (
√𝑥 2 +𝑦 2
)
if y  0
)
if y < 0
𝑥
√𝑥 2 +𝑦 2
𝑧
(7)
Lat = arctan (
(8)
x = Re cos(lat) cos(long)
(9)
y = Re cos(lat) sin(long)
(10)
z = Re sin(lat)
√𝑥 2 +𝑦2
)
(z y x)
long
lat
𝑅𝑒 cos(lat) cos(lon + Ω𝑒 𝑡)
𝑥
𝑦
[ ] = [ 𝑅𝑒 cos(lat) sin(lon + Ω𝑒 𝑡) ]
𝑧
𝑅𝑒 sin(lat)
(11)
lat
lon
t
e
2.6
2.2.A
Rgeo
43
Rgeo
XY
115
ITU-R S.1503-2
43
GSO
GSO
satellite
GSO
Z
Positive
vector Z axis
+ve longitude
Reference
longitude = 0
0
S.1503-43
3.6
1.3.6
44
ITU-R S.1503-2
116
44
Orbit plane
Z
Perigee
Orbit satellite
Equatorial plane
O

Y

i
Apogee
Line of the nodes
X
S.1503-44

i
45
117
ITU-R S.1503-2
45
non-GOS
non-GSO satellite
non-GOS
R
Apogee
0
Ra
Origin
=O
O
Rp

Perigee
Line of ascending node
a
Semi-major
axis = a
S.1503-45
(12)
a = (Ra + Rp)/2
(13)
e = (Ra – Rp) / (Ra + Rp)
a
e
Ra
Rp

v0

v0
(14)
0 =  + 0
(15)
p = a(1 – e2)
(16)
M = E – e sin E
(17)

1+𝑒
2
1–𝑒
tan = √
tan
𝐸
2
ITU-R S.1503-2
118
𝑝
(18)
𝑅=
(19)
𝑇 = 2π√𝑎3 /μ
1 +𝑒 cos()
P
E
M
T

R
5.D
2.3.6
(20)
𝑛 = 𝑛0 (1 +
3 𝐽2 𝑅𝑒2
3
(1 – 2 sin2 (𝑖)) (1 – 𝑒 2 )1/2 )
𝑝2
2
0,001082636 = J2
μ
√𝑎3 = 𝑛0
Ω𝑟 = –
(21)
(º90 < i)
3 𝐽2 𝑅𝑒2
2
𝑝2
𝑛 cos(𝑖)

(º90 > i)

(22)
ω𝑟 =
3 𝐽2 𝑅𝑒2
2
𝑝2
𝑛 (2 –
5
2
sin2 (𝑖))
180 = i 0 = i
i2 < i
i1 > i
116º 33' 54" = i2
i2 > i > i1
63º 26' 06" = i1
119
ITU-R S.1503-2
ω = ω 0 + ω rt
(23)
0
r
Ω = Ω0 + Ωrt
(24)
0
r
X
(25)
𝑅(cos( + ω) cos(Ω) – sin( + ω) sin(Ω) cos(𝑖))
𝑥
[𝑦] = [ 𝑅(cos( + ω) sin(Ω) + sin( + ω) cos(Ω) cos(𝑖)) ]
𝑧
𝑅 sin( + ω) sin(𝑖)
(26)
𝑀 = 𝑀0 + 𝑛𝑡
3.3.6
Wdelta
Wdelta
Wdelta
Z
4.3.6.D
ITU-R S.1503-2
111
4.3.6
J2
Z
𝑥′
cosθ – sinθ 0 𝑥
[𝑦 ′ ] = ( sinθ cosθ 0) [𝑦]
0
0 1 𝑧
𝑧′
(27)

1
5.3.6
46
46
non-GSO
(2)
(1)
J2
(3)
J2
S.1503-46
0=i
4.D
(1)
111
ITU-R S.1503-2
6.3.6
IFIC
ha = (km)
hp = (km)
INC =
RA =
LAN =
AP =
PA =
ℎ𝑎 + ℎ𝑝
2
ℎ𝑎 – ℎ𝑝
𝑒=
2𝑎
i = INC
𝑎 = 𝑅𝑒 +
 = LAN
 = AP

4
t=0
i
(i
5
(0° ≤ i < 360°)
47
4
ITU-R S.1503-2
112
47
non-GOS
r
0

ra
O=
rp
a
S.1503-47
0 = 𝑃𝐴 – ω
4.6
1.4.6
D
D
(z, y, x)
x1  x2 2   y1  y2 2  z1  z 2 2
2.4.6
R
𝐷ℎ = √𝑅2 – 𝑅𝑒2
3.4.6
1.6.D
4.4.6
X

48
113
ITU-R S.1503-2
48
X 
non-GOS
Earth
station
X
X
O=
TestPpoint
Pi
i
Pi
i

 = min (i)
Pi
Xi
X
X = min (Xi)
XY
X
GSO
RES
RNS
R  R ES   R EN
R EN  R NS  R ES
non-GSO

ITU-R S.1503-2
114
XY
R(z) = 0
λ𝑧=0 =
– 𝑅𝐸𝑆 (𝑧)
𝑅𝐸𝑁 (𝑧)
R z 0  R ES   z 0 R EN
X 
non-
()

Rgeo < Rz=0

Rgeo = Rz=0

Rgeo > Rz=0

X
49
X

GSO
GSO
49
()
z
O
y
Longnon-GSO
non-GOS
long
GSO arc
x
Point on
arc that
GSGSO
O
minimises
ai i
S.1503-49
115
ITU-R S.1503-2
Long = LongAlpha – LongNGSO
4.1.D
X

5.4.6
50
50
Z: (Az, El) = (–, + 90)
(Az, El) = (+ve, +ve)
Y: (Az, El) = (0.0)
El
X: (Az, El) = (90.0)
Az
S.1503-50
Z Y X
+ve
X
Y
+ve
Z
5.6
1.5.6
1.1.5.6
ITU-R S.1428
ITU-R S.1503-2
116
2.1.5.6
ITU-R BO.1443
2.5.6
22
ITU-R S 672
4
1,55
dBi 32,4
dBi 40,7
GHz 14-11
GHz 30-20
dB 20
dB 10
7
1.7
1.1.7
(PDF)
(CDF)
2.1.7
5.D
CDFi = 100 (1 – SUM (PDFmin: PDFi))
dB X
pdf
PDFx
PDFx
117
ITU-R S.1503-2
3.1.7
i
4 3 2
1
(Pi Ji)
Ji
dB 0,1
2
SB
Ji
3
dB 0,1
Pt
4
Ji
Pt > Pi
5
%100
Jmax
J100 > Jmax
J100
%100
J100  Jmax
4.1.7
2.7
3.7
1.3.7
D
4.1.7
ITU-R S.1503-2
118
2.3.7
14
14
pfd
Py
:
Py
P1
:
2
J1 dB(W/(m · BWref)
:
:
Pi
Ji dB(W/(m2 · BWref)
Pi Ji
Py
3.3.7
119
ITU-R S.1503-2
E
1
º180
epfd(↓/↑)
%100
2
epfd
%100
epfd
dB 0,X±
D
6
pfd
3
pfd
pfd
ITU-R S.1503-2
121
4
1.E
121
ITU-R S.1503-2
F
1
XP
2
(GIMS)
(SNS)
DVD
(GIBC)
8
epfd
3