ieee aess houston modified
TRANSCRIPT
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Global Navigation Satellite System (GNSS)- A vast System of Systems
Dr. S. Pal
Outstanding Scientist/Program Director,
Satellite Navigation Program
Chairman, GAGAN PMB
Deputy Director,
ISRO Satellite CentreBangalore
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HISTORY OF NAVIGATION
Navigation is the science of charting ones ownroute from point A to point B with respect to
known references both in spatial as well as in
temporal domain
Identifying and remembering objects and land markslike rocks, trees, rivers, marking on trees or leaving
stones/flags and looking at Sun and Moon, as points
of reference were the techniques and navigational
aids that the early man used to find his way in
jungles, deserts, mountains etc. Perhaps the time
reference was day/night or even could be seasons.
The situation changed drastically when man started
long voyages on oceans.
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HISTORY OF NAVIGATION
Phoenicians , Vikings and Greek were undertaking sea voyages andhad navigation skills even 3000 years back. Phoenicians claimed tohave circumnavigated Africa from Red sea, sailing via the Cape ofGood Hope.
Burning fire on mountain tops were used as light houses. Thelegendary Light House of Alexandria was an example.
Navigation word has perhaps its origin in Naoka- Nav boat + Gati-
velocity , in Sanskrit. Not much is written in the modern history about Navigation activities
in Asia-Pacific region. Chinese, Arabs etc., had under taken lot of seavoyages.
In Mohanjadaro ruins (Indian sub continent ) one clay tablet was foundwhich depicted a boat.
Sindhu or Indus valley civilization ruins ( parts of Pakistan, Gujarat ,Harayana ) do show that perhaps a successful business withRomans, Babylonians and Sumerian civilizations.
Out of 18 Tamil Sidhas, Sidha Bhoganathar went to China via searoute (even he is supposed to have designed an aeroplane) and livedin China as Lao-tzu, spread Taosim. He is attributed to have greatnavigational skills.
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History of NavigationThe great sanskrit scholar Kalidas (4th century A.D) was the first one toimagine above land navigation. In his famous Sanskrit Kavya`Meghdoot , Kalidass Yaksha instructs `Megha ,how to navigate fromRamagiri to Alkapuri. He used complete Bio-Sphere as NavigationalControl Points.
Soar up high and head North.Lift yourselves a little higher westward and keep moving. Relax for a while onthe top ofMount Amrakuta, whose burning woods you will have helped soak
As you lighten you will pick up speed and reach the rocky Vindhya Range.
.The wind there will be too weak to hoist you.
.The chataka birds will follow as you travel shedding rain catching the headyscent of flowers and charred wood charred summer fires
..when you reach Dashran, you will see garden hedges white with Ketakiflowers
..In the royal city of Vidisha you will be able to sip the sweet waters of theVetravati River. Go ahead and rest for a white on the low peaks ofNichais.
.Dont forget to detour a little and checkout the view ofUjjayinis white
mansions and savor..Along the way fill yourselves up at the nirvindhya River.
When you reach Awanti look forVishala, a city made in heaven.
There the cool morning breeze, fragrant from lotus blossoms on theShipra River,,,,,,,,,,,,
.Nurse the lotus flowers in the Manasa Lake with your water
There to the north ofKuberas estate is our house with a large rainbowlike gate and a Mandartree which is just like a.
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Archeological site at Lothal (Gujarat ,India) has got remains of
a port which indicated more than 4500 years back India had
advanced sea transport system. The dock is almost of the
same size as that of Visakhapatnam, modern port.
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Cross-staff
Astrolable
Traverse board
Position
ingduring
14-16c
entury
Sextant
Compass Rose
Radio Communication ( I & II World War)
Radar (Robert Watson Watt -1935)
Chronometer
George Harrison, 1764 A.D
Position
ingdur
ing17-20c
entury
Dead reckoning tools
Compass
Latitude
Speed
Direction
Longitud
e
RadioR
anging
VOR
LORAN
LandBasedR
adio
ositioning
TRANSITGPS
SpaceBa
sed
Positio
ning...
..
Egyptian Groma
20th Century
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FIRST RADIO-POSITIONG SYSTEM FOR
MARITIME APPLICATIONS
SERVICE FROM 30 CHAINS FOR WIDE
COVERAGE
PRINCIPLE OF RANGING FOR POSITION-FIX:
RADIO-PULSE TRANSMISSION FROM MASTER AND
SECONDARY STATIONS (OVER A GLOBAL NETWORK)
RECIEVER GETS BOTH PULSES AND TIME
DIFFERENCES (TD) FOR EACH PAIR OF MASTER-SECONDARY STATIONS IS COMPUTED
LOCUS OF POINTS HAVING THE SAME TD FROM A
SPECIFIC MASTER-SECONDARY PAIR IS A CURVED
LINE OF POSITION (LOP).
POSITION DETERMINED BY INTERSECTION OF 2 LOPs
TD IS USED WITH MAPS TO ESTIMATE LAT/LONG
PHASE MEASUREMENTS IMPROVES PRECISION
LORAN OPERATING RANGE : 90-110 KHZ
LIMITED COVERAGE: ~1000km RANGE
OBSTRUCTION/INTERFERENCE FROM GROUND
FEATURES
REFLECTION BY IONOSPHERE
POSITION ACCURACY: ~460m AT BEST
LAND BASED LORAN -C (LONG RANGE NAVIGATION)
x2,y2x1,y1
x3,y3x,y
21
2
1
2
1
2
2
2
2 )()()()( dyyxxyyxx =++
31
2
1
2
1
2
3
2
3 )()()()( dyyxxyyxx =++
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SATELLITE
NAVIGATION &
POSITION SYSTEMS
SECOR (Sequential Collation of Range)
SECOR was a U.S army satellite navigation and positioning system. Thirteen satellites
were launched between 1964 and 1969.
TIMATION
Developed in 1972 by the Naval Research Laboratory (NRL),TIMATION satellites were intended to provide time and frequencytransfer. The third satellite acted as a GPS technology
demonstrator.
TSIKADA
Russian four satellite civil navigation system
TSYKLON
First navigation satellite launched by soviet union in late 1967.
The satellite is based on doppler technique similar to
TRANSIT system.
TRANSIT
Operated in 100 MHz and 400 MHz frequency bands and allowed the user to determine
their position by measuring the Doppler shift of a radio signal transmitted bythe satellite.
When man moves from one place to another 3D positioning (latitude,
longitude & height) are required.
GPS (1978) &
GLONASS
SPUTNIK
First artificial Satellite launched from Russia. Operated using
Doppler frequency shift to obtain position.
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Navigation Satellites
2)uzs(z2)uys(y2)uxs(x0t ++=+ = ,timed
op
pl
er
Zenith
Elevation
Horizon
TRANSIT (US Navy satellite developed by John Hokins, AppliedPhysics Laboratory , 1960-1996). Based on doppler shift
measurements of a 400 MHz tone. TIMATION ( TIMe/navigATION) Programme. - 2 satellites (1967
& 1969) also called NCST ( Navy Centre for Space Technology)satellites carried quartz oscillator which were regularly updatedby master clocks.
NAVSTAR ( NAVigation Satellite Timing and Ranging) of US Air
force PROJECT621. used pseudorandom noise ranging signals. UnderTIMATION Program two more satellites viz., NTS-I( Navigation Technology Satellite) and NTS-II were launched in1974 and 1977 and carried Rubidium and cesium Atomic clocks.
In 1978, US Govt. Decided to bring all the above technologiesunder one head and made a joint program office under which
umbrella, GPS satellites were developed and first block 1satellites were launched during 1978-1985 and second blockduring 1989 to 1990. GPS constellation was completed by 1995.
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SATELLITE CONSTELLATION
DESIGN PARAMETER
ORBIT CHARACTERISTICS
ORBITAL HEIGHT >= 20,000
KM
LONGER VISIBILITY
ORBITAL PERIOD
PERTURBATIONS(MINIMUM)
SOLAR RADIATION PRESSURE
(IMPACTS ECCENTRICITY)LUNI SOLAR FORCES (IMPACTS
INCLINATION)
COMMUNICATION ANTENNA
ISO FLUX (MORE THAN EARTH DISC)
FREQUENCY - L BAND
MINIMUM BACKGROUND THERMAL
NOISE
MINIMUM PATHLOSS
MINIMAL IONOSPHERIC GROUP DELAY
MINIMAL ATTENUATION
3,
2
an
nT
==
)Re
Re(1cos
alt+
=
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SATELLITE CONSTELLATION DESIGN PARAMETER
1. ORBIT CHARACTERISTICS
ORBITAL HEIGHT >= 20,000 KM
LONGER VISIBILITY
ORBITAL PERIOD
PERTURBATIONS(MINIMUM)
SOLAR RADIATION PRESSURE
(IMPACTS ECCENTRICITY)
LUNI SOLAR FORCES (IMPACTSINCLINATION)
PLANES
LAUNCH CONSIDERATIONS
SPARE REQUIREMENT
INCLINATION
GLOBAL/HIGH LATITUDE COVERAGE
2. COMMUNICATION
ANTENNA ISO FLUX (MORE THAN EARTH DISC)
FREQUENCY - L BAND
MINIMUM BACKGROUND THERMAL NOISE
MINIMUM PATHLOSS
MINIMAL IONOSPHERIC GROUP DELAY
MINIMAL ATTENUATION
MODULATION - CDMA/FDMA
MODULATION OF BPSK & SPREAD
SPECTRUM
CDMA- SINGLE FREQUENCY FORMULTIPLE SATELLITE DOWNLINK
FDMA- MULTIPLE FREQUENCY JAMMING
DIFFICULT
3,
2
an
nT
==
)Re
Re(1cos
alt+
=
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REALTIME POSITION FIXING USING SATELLITES
1
2
3
4
(X,Y,Z, b)
(Un Known)
(XI,YI,ZI) REAL-TIME 3D POSITION FIXING:
1-WAY RANGING
ATOMIC CLOCK FOR PRECISERANGING
MIN OF 4 SATELLITES VISIBLE
ANYTIME
WORLD-WIDE TIME SYNCHRONISATION
2-FREQUENCY FOR IONOSPHERIC
CORRECTIONS SIMPLE USER-END EQUIPMENT
ACCURACY: FEW METRES
bZZYYXXP
bZZYYXXP
bZZYYXXP
bZZYYXXP
+++=
+++=
+++=
+++=
2
4
2
4
2
44
2
3
2
3
2
33
2
2
2
2
2
22
2
1
2
1
2
11
)()()()()()(
)()()(
)()()(
SOURCES OF ERROR
System Noise ~ 2m
Ephemeris ~ 5mSatellite clock ~ 1m
Receiver clock ~ 2m
Multi-path ~ 0.5m
Troposphere delay ~ 1m
Ionosphere delay ~10m
Ionospheric delay
Tropospheric delay
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ELEMENTS OF A SATELLITE POSITION FIXING
)]nm
((sinsin)mn
P
n
re
R
2n
n
1mnmJ(sin
nP
n
re
R
2nnJ[1
r
V
==
+
== )
MEASUREMENT (UHF, S-BAND, LASER)
MODELLING (Geo-Potential, Drag, SRP,
Luni-Solar) ESTIMATION (Least-Square, Kalman filter)
rrd
drag vvm
ACP )(
2
1=
uvm
A
PPdrag ))1( +=
)](2sinsinsin)sin(2sin[cos8
3 22
1jjjjj
j
iiiiydt
di+=
=
LEO (m/s2)
Atm drag 6*10-5
SRP 4.7*10-6
Sun 5.6*10-7
Moon 1.2*10-6
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DILUTION OF PRECISION AND IMPACT ON
POSITION ACCURACY
Range
1,4i
1i
uziz
i
uyiy
i
uxixAwhere,
1ATATraceDOP
==
=
=
1 2
2
1
DOP 1/volume
POSITION ERROR IS A FUNCTION
OF:
DILUTION OF PRECISION
MEASUREMENT ACCURACY
MEASUREMENT ERROR
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SATELLITE POSITIONING SYSTEM SEGMENTS
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GPS, GLONASS & GALILEO - Configuration
Constellation GPS GLONASS GALILEOTotal Satellites 24+3 24 (4 Opr) 27+3
Orbital Period 12 hrs 11hrs 15min 14Hrs 22minOrbital planes 6 3 3
Orbital height (km) 20200 19100 23616
Sat. In each plane 4 8 10
Inclination 55 deg 64.8 deg 56 deg
Plane Separation 60 deg 120 deg 120 deg
Frequency 1575.42MHz1227.6MHz
1246 - 1257 MHz1602 - 1616 MHz
1164 - 1300 MHz1559 - 1591 MHz
Modulation CDMA FDMA CDMA
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GLOBAL POSITIONING SYSTEM GPS is first one way (passive) ranging satellite
system The principal objective of the DOD is to offer USmilitary accurate estimates of Position, Velocity andTime (PVT) for a high dynamics platform (P 10m,velocity error 0.1 m/s and time error 100 ns all inrms)
Signal should have a measure of resistance tojamming and interference. That is why transmissionof signals on the same carrier is being done usingCDMA.
Provision to deny the use to US adversaries and atthe same time enhancing the accuracy over ageographical location on a limited time. (This wasdone in the Iraq war keeping high accuracy over aperiod of 2Hrs).
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Planned modernization of the GPS signalsCurrent frequency Plan Planned Frequency Capabilities
(additional)
------------------------------------------------------------------------------------------------------------------
Carrier frequencies Additional civilian frequency 6 dB higher powerrelative to L1
L1 : 1575.42 MHz L5 : 1176.45 MHz 20 MHz broadcastbandwidth
L2 : 1227.60 MHz (safety-of-life service frequency Improved signal cross
L2 C protection (ARNS-band)) correlation
Code frequencies ME code (L1/L2) M-code designed to
(pseudorandom) enhance system security
P-code: 10.23 MHZ (on L1/L2) to improve anti-jamming
Code frequencies (gold code) Dual freq. ionosphere
C/A-code:1.023MHz(onL1) C/A code on L2(1127.60MHz) correction (improved)
UERE and betteraccuracy)
Navigation message Ephemeris, SV clock parameters On L1, L2 and L5
ionospheric parameters, SV health
GLONASS
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GLONASSGLONASS
(GLObalnaya NAvigatsionnaya Sputnikovaya Sistema)(GLObalnaya NAvigatsionnaya Sputnikovaya Sistema)
Parallel constellation to GPS
Constellation was fully operational only in 1995 98 andfailed satellites were not replaced later on.
As of April 2006, 15 operational satellites available.
Minimum satellites required are 18 which will beavailable by 2007 end.
GLONASS is credited for providing precise universaltime coordinated transfer with better position accuracies
India will be helping in completion of the full constellationby launching M series and manufacturing K series
Note: Use of GLONASS in addition to GPS provides increasedsatellite signal observations, spatial distribution of visiblesatellites, reduced horizontal and vertical DOP and decreased
occupational times.
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GALILEO ServicesGALILEO Services (Planned)(Planned) Galileo envisages the provision of large variety of services based on
needs and market analysis.
satellite only, locally assisted, EGNOS Combined services
Galileo satellite only services: Open services,Safety of life, Commercial, Public regulated,
Search & Rescue
Open service Position and Timing Performance of : H : 15 meters, V : 35 meters (95% Single frequency) H : 4 meters, V : 8 meters (95% Dual frequency)
Integrity: No, Timing Accuracy: 39 ns (Three frequencies)
Safety of Life: Availability : 99.8%, Position accuracy : 4-6 m (95% Dual Frequency) Integrity: Yes, Certification/Liability: Yes
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GALILEO ServicesGALILEO Services (Planned)(Planned) Combined Services:
Availability : 99.8% (Global), Position Accuracy : 95% (Dual frequency) Integrity Value Added Services
Public Regulated Services: Availability : 99%, Position Accuracy: H-6.5m, V-12m(95% Dual
frequency), Timing Accurcy : 100 ns, Integrity: Yes
Search and Rescue Services: Capacity:150 beacons Galileo Locally Assisted Services:
Local Precision Navigation Service (1m, TTA 1s), Local High Precision Navigation Service (Position error < 10 cm) Local Assisted Navigation Services Local Augmented Availability Services (Pseudolite services)
Note: Total Project cost is 2.3 billion Euros and market as projected is10 billion Euros/Year and Growth rate is 25% and will reach 300
billion Euros in 2020 with 3 billion receivers in market.
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GPS GPSGPSGALILEO GLONASS GLONASS
1164.000MHz
1
188.000MHz
1
212.000MHz
1
215.000MHz
1
215.600MHz
1
260.000MHz
1
237.827MHz
1
239.600MHz
1
261.610MHz
GALILEO
1
300.000MHz
1
559.000MHz
1
592.952MHz
1
610.000MHz
1
620.610MHz
1
626.500MHz
1
587.420MHz
1
563.420MHz
GALILEO
5
010.000MHz
5
030.000MHz
Radioastronomy
1610.6 1613.6 MHz
GPS GLONASS & GALILEO
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GPS, GLONASS & GALILEO
Frequency Plans
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Thankfully borrowed from ICG Bangalore Meet
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Thankfully borrowed from ICG Bangalore Meet
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Comparison of SATNAV Systems
WGS-84ITREFPZ-90, ECEFWGS-84, ECEFCoordinate
system
IndiaNot yet knownMin. of DefenceDept. of
Defence, USAirforce
Controlled by
10 years>7 years5 years7.5 yearsSpacecraft life
CDMACDMAFDMA/CDMACDMA
Multiple access
< 8 meters with
GAGAN & < 20
meters with
IRNSS
8 meters10 meters10 metersAbsolute
position
accuracy
L1,L5 / L5 & S-
band
L-bandL-bandL-bandFrequency of
operation
36,000 Km23,616 Km19,100 Km20,200 KmAltitude
2 / 730 , GIOVE-A.14 now, 24 reqd24 (30)
No. of satellites
GAGAN / IRNSSGALILEOGLONASSGPSSystem
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LIMITATIONS OF GPS AND GLONASS
GPS stand alone, cannot satisfy the integrity,accuracy & availability requirements for allphases of flight, particularly for the morestringent precision approaches.
Integrity is not guaranteed, since all satellites
may not be satisfactorily working all times. Time to alarm could be from minutes to hours
and there is no indication of quality of service.
Accuracy is not sufficient even with S/A off, thevertical accuracy for 95%of the time is >10m.
For GPS & GLONASS stand alone systemsavailability & continuity are not assured.
All these calls for a special system addressing allthe above, which could be done by augmenting
the GNSS systems.
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REQUIREMENT OF ENHANCEMENT OF
ACCURACY, AVAILABILITY AND INTEGRITY
For the safety-critical applications it is essentialthat a user be assured that the system is
operating within design tolerances and the
position estimates derived from it can be trusted
to be within specifications This is the socalled integrity requirement.
Timely warning of a system anomaly (which may
be hazardous is called time to alarm.
30Sec En-route
6 Sec APV II (Approach with Vertical Guidance)
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AUGMENTATION OF GPS / GLONASSLIMITATIONS OF GPS:
SIGNAL NOT AVAILABLE INSIDE
TUNNEL & WATER NO ASSURANCE OF AVAILABILITY
AND INTEGRITY OF DATA
CRITICAL FOR AVIATION
APPLICATIONS
ACCURACY REQUIREMENTS
STRINGENT
SPACE BASED AUGMENTATION (SBAS)
WAAS, EGNOS, MSAS & GAGAN
GROUND BASED AUGMENTATION (GBAS) LAAS, PSUEDOLITE, DGPS
AIRCRAFT BASED AUGMENTATION (ABAS)
RAIM (RECEIVER AUTONOMOUS
INTEGRITY MONITORING TECHNIQUE)
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GPS Wide Area Augmentation SystemsGPS Wide Area Augmentation Systems
GAGAN
MSASEGNOS
C-WAAS
WAAS
*
***
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US WIDE AREA AUGMENTATION SYSTEM OF GPS
WAAS
24 Wide Area
Reference Stations
2 Wide Area Master
Stations 2 Navigation Land
Uplink Stations
2 GEOs AOR &POR
FAA presentation to ISRO
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EUROPEAN GEOSTATIONARY NAVIGATION
OVERLAY SERVICE - EGNOS
34 Range IntegrityMonitoring Stations Rims
4 Master Control Stations
2 Navigation Land UplinkStations
2 GEOs INMARSATAOR E & IOR andpresently working onARTEMIS
EGNOSS presentation to ISRO
Japanese S BAS System
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Japanese S-BAS System
(MSAS)
IbarakiIbaraki
MCSMCS
Sapporo GMSSapporo GMS
Fukuoka GMS
Naha GMSNaha GMS
UserUser
Australia MRSAustralia MRS
Hawaii MRSHawaii MRS
Kobe MCSKobe MCS
TokyoTokyo
GMSGMS
GPS ConstellationGPS ConstellationMTSATMTSAT
MCS Master Control StationMCS Master Control Station
MRS Monitor and Ranging StationMRS Monitor and Ranging Station
GMS Ground Monitor StationGMS Ground Monitor Station
KDD 128KbsKDD 128Kbs
NTT 64KbsNTT 64Kbs
MSAS is the Wide area Augmentation System of Japan like WAAS and is based on MTSAT.ICG 2007, Bangalore meet
QZSS Navigation System
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Function distributed in each institute
Timing management, WDGPScorrection, etc.
QZSS
SLR Site
GeonetGSI
Monitor Station NW
User Receiver
TT&CNAV
Message Uplink
Station
WDGPS CorrectionMessage, LEX NAV
L1-SAIF: 1575.42 MHzLEX: 1278.75 MHz
Laser Ranging
Navigation Signals
L1: 1575.42 MHzL2: 1227.60 MHzL5: 1176.45 MHzLEX: 1278.75 MHz
TWSTFTUp: 14.43453GHzDown: 12.30669GHz
Time Management
Station
SLR: Satellite Laser Ranging, TWSTFT: Two Way Satellite Time and Frequency Transfer
Master Control StationMCS)
TT&C, NAVMessage Upload**
**: Under trade-off study between S (Up: 2025-2110, Down: 2200-2290MHz)
and C (Up:5000-5010, Down:5010-5030MHz) band
QZSS Navigation System
Navigation System Architecture
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BEIDOU Chinese regional satellite Navigation System Beidou system consists of two geo-synchronous
satellites in space and a third used as back up, a
control centre located at Beijingand number ofmonitoring and calibration stations on grounddistributed through out China and the Beidoupositioning receivers.
Beidou system is fully operational in early 2004.
Similar to that of the Geostar regional navigationsystem. - Radio determination satellite service(RDSS)
Besides positioning, the system can perform two
way data communication. Users can determine their position and also transmit
messages to each other.
Accuracy (H about 100 meters,
T synch < 10 ms, Taccuracy < 100 ns)
New Chinese
Regional system
announced is
named asCOMPASS and may
consist of GEO, and
some MEO
components
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INDIAN SCENARIO IN GNSS
Satellite Positioning System (SPS) in IRS &
Scientific satellites & GAGAN
Participation in GALILEO & GLONASS
Having our own regional constellation (IRNSS)
Ionospheric & Tropospheric Studies and modeling
India may become biggest user of GNSS for GIS,mobile, survey, mining, fishing industry, aviation,
road, rail transport, etc.
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INSAT IRSLAUNCHVEHICLES
NATIONAL SPACE SYSTEMS
GNSS
GAGANIRNSS
Applications Science
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INDIAN AIRSPACE TO BE SERVICEDINDIAN AIRSPACE TO BE SERVICED
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40 50 60 70 80 90 100 110
-10
-5
0
5
10
15
20
25
30
35
40
INDIAN AIRSPACE TO BE SERVICEDINDIAN AIRSPACE TO BE SERVICED
C BAND
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INRESINRES
INMCC
BANGALORE INLUSBANGALORE
GEO
C BAND
L1 & L5
GAGAN USER
GPS L1 & L2GPS L1 & L2
GPS Nav Data GPS Nav Data
GEO D/L
in L1
GPS & GEO data
Correction
Messages
GPS & GEO data
D/L in C and L
U/L in C
GEO D/L
in L1
GPS and GEO
Broadcast Messages
GAGAN COVERAGE THROUGH INSAT
INDIAN S-BAS PROGRAM GAGAN
GPS AIDED GEO AUGMENTED
NAVIGATION
Indian Master Control Centre
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Indian Master Control Centre The INMCC has been established in
GAGAN AAI premises with all theinfrastructure and facilities atKundalahalli, Bangalore
Factory Acceptance and Site Acceptancetesting of INMCC subsystems havebeen completed
Preliminary System Acceptance Testing
(PSAT) of GAGAN subsystems has beensuccessfully carried out with SatelliteEmulation Subsystem.
GAGAN Master Control Facility
GAGAN Display System Service Monitoring Subsystem
Indian Land Uplinking Station
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Factory Acceptance and SiteAcceptance testing Indian
Land Uplinking Station(INLUS) subsystems havebeen completed
INLUS is co-located withINMCC, Kundalahalli.
A 11 meter C-band dishantenna has been installed. C-band feed is under integration.
KPA and INLUS-RF rack hasbeen integrated and installedat the site.
Indian Land Uplinking Station
GAGAN Uplinking Facility
GAGAN INLUS RF and Signal GenerationSubsystems
Indian Reference Stations
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All the eight Indian Reference Stations(INRES) have been established. FactoryAcceptance and Site Acceptance testingINRES have been completed. All theINRES stations have been linked toINMCC by Optical Fibre Links except forPort Blair.
The indigenously designed Navigationpayload bread-board testing has beencompleted and flight model fabrication is
under progress.
Indigenous development of Navigationsoftware is under development at ISAC.Algorithm for major S/W modules havebeen designed and being coded. Realtime data from INMCC is being archivedin the navigation Software Laboratory
The TEC data received from 18 TECstation is being archived at SAC,Ahmedabad. Iono/Tropo model activityis in progress. Scientists to whom studycontracts have been awarded submittedtheir report.
Indian Reference Stations
Reference Station Antenna
Reference Station Rack
Preliminary System Acceptance Test Results
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Preliminary System Acceptance Test Results
Achieved
position
accuracy inNorth, East
and Up
directions is
better than
the Exit
Criteria
PSAT Exit Criteria
PositionAccuracy better
than 7.5 Meters
GGTAGGTA
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GGTAGGTA
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Locations of GAGAN Reference Stations
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Locations of GAGAN Reference Stations
and
TEC stations
POSITION OF MAGNETIC EQUATOR AND
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POSITION OF MAGNETIC EQUATOR AND
SCINTILLATION REGIONS
INDIAN REGION EXPERIENCES UNPREDICTABLE
IONOSPHERIC DISTURBANCES
SUCCESS OF GAGAN IS DEPENDANT ON THE STUDY AND
MODEL THE IONOSPHERE OVER THE REGION.
GAGAN PERFORMANCE
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GAGAN PERFORMANCE
SPECIFICATIONS Accuracy Integrity Time-to-Alert Continuity Availability
En route
Terminal
Initial & Int
Approach,
NPA,
Departure
APV-I
APV-II
1-10-7 per hr
1-10-7 per hr
1-10-7 per hr
1-2x10-7 per
approach
1-2x10-7 per
approach
5 min
15 sec
10 sec
10 sec
6 sec
0.99 to
0.99999
0.999 to0.99999
0.99 to
0.99999
0.99 to
0.99999
0.99 to
0.99999
1-10-4/hr to
1-10-8/hr
1-10-4
/hr to1-10-8/hr
1-10-4/hr to
1-10-8/hr
1-8x10-6/hr in
any 15 sec
1-8x10-6/hr
in any 15 sec
3.7 km (H)
0.74 km (H)
220 m (H)
220 m (H)
20 m (V)
16 m (H)
8 m (V)
IMPACT AND APPLICATIONS OF GAGAN
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IMAGE CORRECTION/IMAGE CORRECTION/
MAP MAKINGMAP MAKING
NAVIGATION/NAVIGATION/
LANDINGLANDING
ROAD NAVIGATIONROAD NAVIGATION
SHIP ROUTINGSHIP ROUTING
NAVIGATION - AIR, SEA & LANDNAVIGATION - AIR, SEA & LANDPOSITIONING APPLICATIONS -POSITIONING APPLICATIONS -
SURVEYSURVEY
IMAGE CORRECTIONIMAGE CORRECTION
GISGIS
KINEMATIC SURVEYSKINEMATIC SURVEYS
SURVEILLENCE/FLEETSURVEILLENCE/FLEET
MONITORINGMONITORING
INTEGRATED RECIEVER SYSTEMS
PRECISE ORBIT DETERMINATION WAD CORRECTION
ATMOSPHERIC CORRECTION
INTEGRITY MONITORINGTHREAT MODELS & MONITORS SAFETY ISSUES
S-BAS MESSAGES, UPLINK &
SYNCHRONIZATION
TECHNOLOGY ISSUES
APPLICATIONSAPPLICATIONS
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340
550
830
1110
1320
IRNSS
INDIAN REGIONAL NAVIGATIONAL SATELLITE SYSTEM
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IRNSS Architecture
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IRNSS Architecture
Space Segment Seven satellite configuration, 3 SVs in Geo-Stationary orbit ( 34,
83 and 132 East), 4 SVs are in GEO Synchronous orbit placed atinclination of 29 (with Longitude crossing at 55 and 111 East)
The configuration takes care of continuity of service with a failureof one satellite.
The satellites are of 1 ton class with navigation payload of 102Kgs and power consumption of 676 Watts .
There will be two downlinks (L and S bands) providing dualfrequency operation with EIRP of 31.5 dBW at EOC. The payload will have 3 Rubidium clocks.
Ground Segment Master Control Center
IRNSS Ranging & Integrity Monitoring stations (IRIM) IRNSS Telemetry and Command stations Navigation Control Centre IRNSS Network Timing Centre
User Segment
Planned operationalization by 2011-2012
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HDOP & VDOP (99%) for theProposed Constellation
GEO 34,83,132
GSO 55(55,235), 111(111,291)
User Mask Angle 5deg
IRNSS Coverage Area
IRNSS Error Budget
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IRNSS Error Budget
6.5~9.9
Pos. Accu.-V(m)
4.3~9.9Pos. Accu.-H(m)
2.33.0VDOP
1.53.0HDOP
2.843.3UERE(m)
1.51.0Multipath0.60.6Rx. Noise
0.20.2Troposphere
0.51.2Ionosphere
1.82.0Clock
1.42.0EPH
(1 sigma)(1 sigma)Error
GPS(D)IRNSS(D)SYSTEM
IRNSS system provides the Dual frequency user with
a targeted position accuracy better than 10 metres
in the coverage area.
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NAVIGATION
SPACECRAFT
AIRCRAFT
SHIP
VEHICLE
GEOGRAPHIC DATA
COLLECTION
MAPPING
SURVEYING
ENGINEERING
SCIENTIFIC RESEARCH
ATMOSPHERIC STUDIES GEODYNAMICS
CRUSTAL MOVEMENTS
CRUSTAL DEFORMATIONS
MILITARY
NATURAL RESOURCE AND LAND
MANAGEMENT
GIS INGEST FOREST MENSURATION
TOWN PLANNING
FLEET MOVEMENT
ROUTING/ALIGNMENT
MONITORING THE HEALTH OF TALL
BUILDINGS/TOWERS, LONG BRIDGES
Power grid synchronization
AGRICULTURE
PRECISION FARMING
EMERGENCY RESPONSE
SEARCH AND RESCUE
BUSINESS SOLUTIONS
LOCATION BASED SERVICES
MOBILE
TOURISM
RETAILING/Banking
Assisted GNSS Applications
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Satellite positioning
systems (GPS, Galileo,
GLONASS)
Satellite positioning
augmentation systems
(EGNOS, WAAS)
Mobile
communications
signaling network(s)
Location server(s)Fixed
telecommunications
network nodes with
short-range wireless
data communications
equipment (Bluetooth,
WLAN)
Terrestrial positioningsystems (LORAN C)
Inertial navigation
sensors (implemented
into the rover itself:
accelerometer,
barometer)
ASSISTED-GNSS
POSITIONING
ALGORITHM
pp
AREAS OF RESEARCH & DEVELOPMENT IN
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POSITIONING AND TIMING SYSTEM
(GNSS)
SCIENCE
IONO-TROPO MODELLING IN THE
EQUATORIAL REGION IN L-BAND
RADIO OCCULTATION STUDIES
FOR NEAR EARTH
ATMOSPHERIC TEMPERATURE
PROFILE
REAL-TIME WEATHERFORECASTING
TECHNOLOGY
PRECISION ORBITS
TIME SYNCHRONISATION
DEVELOPMENT OF NAVIGATION
SOFTWARE
ATOMIC CLOCK RUBIDIUM, CESIUM,
HYDROGEN MASERS
ISOFLUX ANTENNAS FOR SPACECRAFT
DUAL RECEIVERS (GPS+GLONAAS,
GPS+GALILEO)
ACCURATE ESTIMATE OF PHASE DELAYS
ONBOARD SATELLITE
I l t d ith GNSS
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Issues related with GNSS
Interoperability refers to the ability of open globaland regional satellite navigation and timing servicesto be used together to provide better capabilities atthe user level than would be achieved by relying
solely on one service or signal.
Compatibility refers to the ability of space-basedpositioning, navigation, and timing services to be
used separately or together without interfering witheach individual service or signal.
I l t d ith GNSS
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Issues related with GNSS
Intentional and Unintentional Interferences
Multipath, Indoor and Urban Environment Over crowding of Frequency Spectra
Need for higher anti-jamming margins
Protection of RNSS and Radio Astronomy bands
Continuity of existing and planned constellations Ionospheric and Solar weather impact on GNSS signals
Standardization of Civilian Signals and Receivers
Universal Time and Reference Frames (Each
Constellation as of today has adopted different time andgeodetic reference frames)
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CONCLUSION
After all, we need measurements of space and time foralmost all our activities and GNSS provides these.
Hence, GNSS will influence our life more than any othertechnological advent.