mobile communications chapter 5: satellite systems · mobile station still in the footprint of the...
TRANSCRIPT
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f. D
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025.
1
Mo
bile
Co
mm
un
icat
ion
sC
hap
ter
5: S
atel
lite
Sys
tem
s
His
tory
Bas
ics
Loca
lizat
ion
Han
dove
rR
outin
gS
yste
ms
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025.
2
His
tory
of s
atel
lite
com
mun
icat
ion
1945
Art
hur
C. C
lark
e pu
blis
hes
an e
ssay
abo
ut „
Ext
ra
Ter
rest
rial R
elay
s“19
57
firs
t sat
ellit
e S
PU
TN
IK19
60fir
st r
efle
ctin
g co
mm
unic
atio
n sa
telli
te E
CH
O19
63
first
geo
stat
iona
ry s
atel
lite
SY
NC
OM
1965
fir
st c
omm
erci
al g
eost
atio
nary
sat
ellit
e S
atel
lit„E
arly
Bird
“ (I
NT
ELS
AT
I): 2
40 d
uple
x te
leph
one
chan
nels
or
1 T
V
chan
nel,
1.5
year
s lif
etim
e
1976
thre
e M
AR
ISA
T s
atel
lites
for
mar
itim
e co
mm
unic
atio
n19
82
first
mob
ile s
atel
lite
tele
phon
e sy
stem
INM
AR
SA
T-A
1988
fir
st s
atel
lite
syst
em fo
r m
obile
pho
nes
and
data
co
mm
unic
atio
n IN
MA
RS
AT
-C19
93fir
st d
igita
l sat
ellit
e te
leph
one
syst
em
1998
gl
obal
sat
ellit
e sy
stem
s fo
r sm
all m
obile
pho
nes
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3
App
licat
ions
Tra
ditio
nally
w
eath
er s
atel
lites
radi
o an
d T
V b
road
cast
sat
ellit
es
mili
tary
sat
ellit
es
sate
llite
s fo
r na
viga
tion
and
loca
lizat
ion
(e.g
., G
PS
)
Tel
ecom
mun
icat
ion
glob
al te
leph
one
conn
ectio
ns
back
bone
for
glob
al n
etw
orks
conn
ectio
ns fo
r co
mm
unic
atio
n in
rem
ote
plac
es o
r un
derd
evel
oped
area
s
glob
al m
obile
com
mun
icat
ion
sate
llite
sys
tem
s to
ext
end
cellu
lar
phon
e sy
stem
s (e
.g.,
GS
M o
rA
MP
S)
repl
aced
byfib
erop
tics
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4
base
stat
ion
orga
tew
ay
Cla
ssic
alsa
telli
tesy
stem
s
Inte
r S
atel
lite
Link
(I
SL)
Mob
ile U
ser
Link
(M
UL)
Gat
eway
Link
(G
WL)
foot
prin
t
smal
lcel
ls(s
potb
eam
s)
Use
r da
ta
PS
TN
ISD
NG
SM
GW
L
MU
L
PS
TN
: Pub
lic S
witc
hed
Tel
epho
ne N
etw
ork
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025.
5
Bas
ics
Sat
ellit
es in
circ
ular
orb
itsat
trac
tive
forc
e F
g=
m g
(R
/r)²
cent
rifug
al fo
rce
Fc
= m
r ω
²m
: mas
s of
the
sate
llite
R: r
adiu
s of
the
eart
h (R
= 6
370
km)
r: d
ista
nce
to th
e ce
nter
of t
he e
arth
g: a
ccel
erat
ion
of g
ravi
ty (
g =
9.8
1 m
/s²)
ω: a
ngul
ar v
eloc
ity (
ω=
2 π
f, f:
rota
tion
freq
uenc
y)
Sta
ble
orbi
tF
g=
Fc
32
2 )2(
f
gRr
π=
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6
Sat
ellit
e pe
riod
and
orbi
ts
1020
3040
x10
6m
24 20 16 12 8 4
radi
us
sate
llite
pe
riod
[h]
velo
city
[ x1
000
km/h
]
sync
hron
ous
dist
ance
35,7
86 k
m
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7
Bas
ics
ellip
tical
or
circ
ular
orb
itsco
mpl
ete
rota
tion
time
depe
nds
on d
ista
nce
sate
llite
-ear
thin
clin
atio
n: a
ngle
bet
wee
n or
bit a
nd e
quat
orel
evat
ion:
ang
le b
etw
een
sate
llite
and
hor
izon
LOS
(Li
ne o
f Sig
ht)
to th
e sa
telli
te n
eces
sary
for
conn
ectio
nhi
gh e
leva
tion
need
ed, l
ess
abso
rptio
n du
e to
e.g
. bui
ldin
gs
Upl
ink:
con
nect
ion
base
sta
tion
-sa
telli
teD
ownl
ink:
con
nect
ion
sate
llite
-ba
se s
tatio
nty
pica
lly s
epar
ated
freq
uenc
ies
for
uplin
k an
d do
wnl
ink
tran
spon
der
used
for
send
ing/
rece
ivin
g an
d sh
iftin
g of
freq
uenc
ies
tran
spar
ent t
rans
pond
er: o
nly
shift
of f
requ
enci
es
rege
nera
tive
tran
spon
der:
add
ition
ally
sig
nal r
egen
erat
ion
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8
Incl
inat
ion
incl
inat
ion
δ
δ
sate
llite
orbi
t
perig
ee
plan
e of
sat
ellit
eor
bit
equa
toria
lpla
ne
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9
Ele
vatio
n
Ele
vati
on
:an
gle
εbe
twee
n ce
nter
of s
atel
lite
beam
an
d su
rfac
e εm
inim
al e
leva
tio
n:
elev
atio
n ne
eded
at l
east
to c
omm
unic
ate
with
the
sate
llite
foot
prin
t
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10
Link
bud
get o
f sat
ellit
es
Par
amet
ers
like
atte
nuat
ion
or r
ecei
ved
pow
er d
eter
min
ed b
y fo
urpa
ram
eter
s:se
ndin
g po
wer
gain
of s
endi
ng a
nten
nadi
stan
ce b
etw
een
send
er
and
rece
iver
gain
of r
ecei
ving
ant
enna
Pro
blem
sva
ryin
g st
reng
th o
f rec
eive
d si
gnal
due
to m
ultip
ath
prop
agat
ion
inte
rrup
tions
due
to s
hado
win
g of
sig
nal (
no L
OS
)P
ossi
ble
solu
tions
Link
Mar
gin
to e
limin
ate
varia
tions
in s
igna
l str
engt
h sa
telli
te d
iver
sity
(us
age
of s
ever
al v
isib
le s
atel
lites
at t
he s
ame
time)
he
lps
to u
se le
ss s
endi
ng p
ower
24
=c
fr
Lπ
L: L
oss
f: ca
rrie
r fr
eque
ncy
r: d
ista
nce
c: s
peed
of l
ight
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11
Atm
osph
eric
atte
nuat
ion
Exa
mpl
e: s
atel
lite
syst
ems
at 4
-6 G
Hz
elev
atio
nof
the
sate
llite
5°10
°20
°30
°40
°50
°
Atte
nuat
ion
of
the
sign
alin
%
1020304050
rain
abso
rptio
n
fog
abso
rptio
n
atm
osph
eric
abso
rptio
n
ε
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12
Fou
r di
ffere
nt ty
pes
of s
atel
lite
orbi
ts c
an b
e id
entif
ied
depe
ndin
g on
the
shap
e an
d di
amet
er o
f the
orb
it:G
EO
: geo
stat
iona
ry o
rbit,
ca.
360
00 k
m a
bove
ear
th s
urfa
ce
LEO
(Lo
w E
arth
Orb
it): c
a. 5
00 -
1500
km
ME
O (
Med
ium
Ear
th O
rbit)
or
ICO
(In
term
edia
te C
ircul
ar O
rbit)
: ca
. 600
0 -
2000
0 km
HE
O (
Hig
hly
Elli
ptic
al O
rbit)
elli
ptic
al o
rbits
Orb
its I
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13
Orb
its II
eart
h
km35
768
1000
0
1000
LEO
(G
loba
lsta
r,Ir
dium
)
HE
O
inne
r an
d ou
ter
Van
Alle
n be
lts
ME
O (
ICO
)
GE
O (
Inm
arsa
t)
Van
-Alle
n-B
elts
:io
nize
d pa
rtic
les
2000
-60
00 k
m a
nd15
000
-30
000
kmab
ove
eart
h su
rfac
e
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14
Geo
stat
iona
rysa
telli
tes
Orb
it 35
.786
km
dis
tanc
e to
ear
th s
urfa
ce, o
rbit
in e
quat
oria
l pla
ne
(incl
inat
ion
0°)
com
plet
e ro
tatio
n ex
actly
one
day
, sat
ellit
e is
syn
chro
nous
to e
arth
ro
tatio
nfix
ant
enna
pos
ition
s, n
o ad
just
ing
nece
ssar
ysa
telli
tes
typi
cally
hav
e a
larg
e fo
otpr
int (
up to
34%
of e
arth
sur
face
!),
ther
efor
e di
fficu
lt to
reu
se fr
eque
ncie
s ba
d el
evat
ions
in a
reas
with
latit
ude
abov
e 60
° du
e to
fixe
d po
sitio
n ab
ove
the
equa
tor
high
tran
smit
pow
er n
eede
dhi
gh la
tenc
y du
e to
long
dis
tanc
e (c
a. 2
75 m
s)
not u
sefu
l for
glo
bal c
over
age
for
smal
l mob
ile p
hone
s an
d da
ta
tran
smis
sion
, typ
ical
ly u
sed
for
radi
o an
d T
V tr
ansm
issi
on
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15
LEO
sys
tem
s
Orb
it ca
. 500
-15
00 k
m a
bove
ear
th s
urfa
cevi
sibi
lity
of a
sat
ellit
e ca
. 10
-40
min
utes
glob
al r
adio
cov
erag
e po
ssib
le
late
ncy
com
para
ble
with
terr
estr
ial l
ong
dist
ance
co
nnec
tions
, ca.
5 -
10 m
ssm
alle
r fo
otpr
ints
, bet
ter
freq
uenc
y re
use
but n
ow h
ando
ver
nece
ssar
y fr
om o
ne s
atel
lite
to a
noth
er
man
y sa
telli
tes
nece
ssar
y fo
r gl
obal
cov
erag
e m
ore
com
plex
sys
tem
s du
e to
mov
ing
sate
llite
s
Exa
mpl
es:
Irid
ium
(st
art 1
998,
66
sate
llite
s)B
ankr
uptc
y in
200
0, d
eal w
ith U
S D
oD(f
ree
use,
sa
ving
from
“de
orbi
ting”
)
Glo
bals
tar
(sta
rt 1
999,
48
sate
llite
s)N
ot m
any
cust
omer
s (2
001:
440
00),
low
sta
nd-b
y tim
es fo
r m
obile
s
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16
ME
O s
yste
ms
Orb
it ca
. 500
0 -
1200
0 km
abo
ve e
arth
sur
face
com
paris
on w
ith L
EO
sys
tem
s:sl
ower
mov
ing
sate
llite
s le
ss s
atel
lites
nee
ded
sim
pler
sys
tem
des
ign
for
man
y co
nnec
tions
no
hand
-ove
r ne
eded
high
er la
tenc
y, c
a. 7
0 -
80 m
shi
gher
sen
ding
pow
er n
eede
dsp
ecia
l ant
enna
s fo
r sm
all f
ootp
rints
nee
ded
Exa
mpl
e:
ICO
(In
term
edia
te C
ircul
ar O
rbit,
Inm
arsa
t) s
tart
ca.
200
0B
ankr
uptc
y, p
lann
ed jo
int v
entu
res
with
Tel
edes
ic, E
llips
o–
canc
elle
d ag
ain,
sta
rt p
lann
ed fo
r 20
03
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17
Rou
ting
One
sol
utio
n: in
ter
sate
llite
link
s (I
SL)
redu
ced
num
ber
of g
atew
ays
need
ed
forw
ard
conn
ectio
ns o
r da
ta p
acke
ts w
ithin
the
sate
llite
net
wor
kas
long
as
pos
sibl
eon
ly o
ne u
plin
k an
d on
e do
wnl
ink
per
dire
ctio
n ne
eded
for
the
conn
ectio
n of
two
mob
ile p
hone
s P
robl
ems:
mor
e co
mpl
ex fo
cusi
ng o
f ant
enna
s be
twee
n sa
telli
tes
high
sys
tem
com
plex
ity d
ue to
mov
ing
rout
ers
high
er fu
el c
onsu
mpt
ion
thus
sho
rter
life
time
Irid
ium
and
Tel
edes
icpl
anne
d w
ith IS
LO
ther
sys
tem
s us
e ga
tew
ays
and
addi
tiona
lly te
rres
tria
l net
wor
ks
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18
Loca
lizat
ion
of m
obile
sta
tions
Mec
hani
sms
sim
ilar
to G
SM
Gat
eway
s m
aint
ain
regi
ster
s w
ith u
ser
data
HLR
(H
ome
Loca
tion
Reg
iste
r): s
tatic
use
r da
ta
VLR
(V
isito
r Lo
catio
n R
egis
ter)
: (la
st k
now
n) lo
catio
n of
the
mob
ile s
tatio
n
SU
MR
(S
atel
lite
Use
r M
appi
ng R
egis
ter)
: sa
telli
te a
ssig
ned
to a
mob
ile s
tatio
npo
sitio
ns o
f all
sate
llite
s
Reg
istr
atio
n of
mob
ile s
tatio
nsLo
caliz
atio
n of
the
mob
ile s
tatio
n vi
a th
e sa
telli
te’s
pos
ition
requ
estin
g us
er d
ata
from
HLR
upda
ting
VLR
and
SU
MR
Cal
ling
a m
obile
sta
tion
loca
lizat
ion
usin
g H
LR/V
LR s
imila
r to
GS
M
conn
ectio
n se
tup
usin
g th
e ap
prop
riate
sat
ellit
e
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19
Han
dove
rin
sat
ellit
esy
stem
s
Sev
eral
add
ition
al s
ituat
ions
for
hand
over
in s
atel
lite
syst
ems
com
pare
d to
cel
lula
r te
rres
tria
l mob
ile p
hone
net
wor
ks c
ause
d by
the
mov
emen
t of t
he s
atel
lites
Intr
a sa
telli
te h
ando
ver
hand
over
from
one
spo
t bea
m to
ano
ther
mob
ile s
tatio
n st
ill in
the
foot
prin
t of t
he s
atel
lite,
but
in a
noth
er c
ell
Inte
r sa
telli
te h
ando
ver
hand
over
from
one
sat
ellit
e to
ano
ther
sat
ellit
em
obile
sta
tion
leav
es th
e fo
otpr
int o
f one
sat
ellit
e
Gat
eway
han
dove
rH
ando
ver
from
one
gat
eway
to a
noth
erm
obile
sta
tion
still
in th
e fo
otpr
int o
f a s
atel
lite,
but
gat
eway
leav
es th
e fo
otpr
int
Inte
r sy
stem
han
dove
rH
ando
ver
from
the
sate
llite
net
wor
k to
a te
rres
tria
l cel
lula
r ne
twor
k
mob
ile s
tatio
n ca
n re
ach
a te
rres
tria
l net
wor
k ag
ain
whi
ch m
ight
be
chea
per,
has
a lo
wer
late
ncy
etc.
Pro
f. D
r.-I
ng. J
oche
nS
chill
er, h
ttp://
ww
w.jo
chen
schi
ller.
de/
MC
SS
025.
20
Ove
rvie
wof
LE
O/M
EO
sys
tem
s
Irid
ium
Glo
bal
star
ICO
Tel
edes
ic#
sate
llite
s66
+ 6
48 +
410
+ 2
288
alti
tud
e(k
m)
780
1414
1039
0ca
. 700
cove
rag
egl
obal
±70°
latit
ude
glob
algl
oba
lm
in.
elev
atio
n8°
20°
20°
40°
freq
uen
cies
[GH
z(c
irca
)]
1.6
MS
29.2
↑19
.5 ↓
23.3
ISL
1.6
MS
↑2.
5 M
S ↓
5.1
↑6.
9 ↓
2 M
S ↑
2.2
MS
↓5.
2 ↑
7 ↓
19 ↓
28.8
↑62
ISL
acce
ssm
eth
od
FD
MA
/TD
MA
CD
MA
FD
MA
/TD
MA
FD
MA
/TD
MA
ISL
yes
nono
yes
bit
rat
e2.
4 kb
it/s
9.6
kbit/
s4.
8 kb
it/s
64 M
bit/
s ↓
2/64
Mbi
t/s ↑
# ch
ann
els
4000
2700
4500
2500
Lif
etim
e[y
ears
]5-
87.
512
10
cost
esti
mat
ion
4.4
B$
2.9
B$
4.5
B$
9 B
$