بسم هللا الرحمن الرحيم SATELLITE COMMUNICATIONS - SERVICES AND 1 APPLICATIONS LECTURER : Dr. Lotfi Laadhar دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 I INTRODUCTION II SATCOM - PRINCIPLE III TVSAT & VSAT 2 IV LINK DESIGN – SatMaster Pro دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 SATELLITE COMMUNICATION SYSTEMS [1] - DENIS RODDY SATELLITE COMMUNICATIONS 1996 3 [2] – DONALD C. MEAD DIRECT BROADCAST SATELLITE COMMUNCATIONS 2000 [3] - TRI T. HA DIGITAL SATELLITE COMMUNICATIONS 1990 October'2003 HISTORY 1957 – LAUNCH THE FIRST SATELLITE SPUTNIC1 1961 – AT&T HAD LAUNCHED TELSTAR 4 1964 August 20 - International Telecommunications Satellite Organization (INTELSAT). دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 HISTORY CON’t 1976 – ARABSAT organization was created 1977- EUTELSAT was created 1979 - The International Maritime Organization 5 sponsored the establishment of the International Maritime Satellite Organization INMARSAT دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 HISTORY CON’t 1984–1985-1988 French satellites TELECOM had launched (I generation) 1995 – HOTBIRD I had lunched 1996 - II generation of ARABSAT was launched 6 1999 -Launching BADR-3 to the orbit of 26° East, the same orbit of Arabsat 2A. Feb.28 2006 - Proton rocket fails in ARABSAT 4A launch دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 INTELSAT FLEET 7 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 EUTELSAT FLEET Satellite Date Duration Eutelsat-1 F1,F2,F3,F4,F5 1981-1988 7 years Eutelsat-2 F1,F2,F3,F4,F5 1990-1994 10 years Hotbird1 1995 10 years Hotbird 2, 3, 4, 5 1996-1998 12 years Eutelsat W2, W3, W4, W5 (W1) 1998-2002 12 years Eutelsat-W1R 2000 12 years Atlantic Bird2 2001 12 years Eurobirdt-1(W1R) 2001 12 years 8 Atlantic Bird1 2002 15years Hotbird 6 2002 12 years Atlantic Bird3 (Stellat 5) 2002 15years Hotbird7 2002 12 years Eutelsat-W 3A 2002 12 years e-Bird 2003 10 years HOTBIRD 8 2006 15 years دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 ARABSAT FLEET ARABSAT 1A, 1B, 1C, 1D and 1E ARABSAT 2A, 2B, 2C, 2D (BADR 2) ARABSAT 3A (BADR3) 9 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 Arabsat 4-A (BADR1) will carry 24 active channels in C-band 16 active Ku-band channels Arabsat 4A was deorbited on 24.03.2006 over the pacific دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 Arabsat 4-B (BADR4) June’2006 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 Arabsat 4-C (BADR6) 2008 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 NILESAT FLEET NILESAT 101 NILESAT 102 Launch Information Launch Date 28 April 1998 17 August 2000 Launch Vehicle Arian 4 Launch Mass 1840 Kg 1827 Kg 13 Orbital Information MATRA MARCONI Satellite Manufacturer ASTRIUM SPACE Orbital Position 7 West Stabilization System 3-Axis System Power Consumption (Max) 3.02 kW 3.06 kW Expected Life Time 15 Years دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية NILESAT FLEET NILESAT 101 NILESAT 102 Payload Information EIRP (Max.) 50.1 dBW G/T (Max.) 1.5 dB/K Downlink Frequency Band (KU) 11.7 - 12.1 GHz 11.8 – 12.3 GHz Uplink Frequency Band (KU) 17.3 - 17.7 GHz 17.4 – 17.9 GHz No. of Transponders 12 14 Transponder Bandwidth 33 MHz Transponder Output Power 100 W TWTA Redundancy 16 for 12 in each satellite Polarization Linear Saturation Flux Density (FGM) * -76 to –94 dBW/m2 -76 to -96 dBW/m2 london Horn -72.5 to –90.5 dBW/m2 Operation Information Receiving Dish Diameter 50 cm to 75 cm within the coverage area. Operation Start Date 31 May 1998 12 September 2000 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية ORBITS AND LAUNCHING METHODS 15 October'2003 LUNCHING AN ARTIFICIAL SATELLITE دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 Earth orbits the sun دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 The Earth orbits the sun دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 KEPLER’S LAW 4 2M D F S 2 T 2 19 G M M F S E 1 D2 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية G M M 4 2M D F S E = F S 1 D2 2 T 2 G= 6.67.10-11 Nm2/Kg Universal Gravitation 24 ME = 6.10 Kg– Earth mass MS – Satellite mass D=(6378 + h ) Km دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 KEPLER’S LAW G M M 4 2M D S E F S F1 2 2 2 D T = T 2.G.M 21 D 3 E 4. 2 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية DIFFERENT KINDS OF ORBITS 1 – LOW EARTH ORBIT L E O IRIDIUM SPONSORED BY MOTOROLLA ALTITUDE 640 KM 22 6 ORBITAL PLANS 11 SATELLITES PER PLAN TOTAL 66 SATELLITES دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 IRIDIUM 23 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 2 – MEDIUM EARTH ORBIT M E O GLOBALSTAR ALTITUDE 1440 KM 24 8 ORBITAL PLANS 6 SATELLITES PER PLAN TOTAL 48 SATELLITES دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 3 – GEOSYCHRONOUS EARTH ORBIT G E O ALTITUDE 36000 KM ≈ 1000 SATELLITES 25 30 % ACTIVE دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 HISTORY 26 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 Features of different satellite constellations Type LEO MEO GEO Medium Earth Description Low Earth Orbit Geostationary Earth Orbit Orbit Height 00-1000 miles 6000-12000 miles 36000 KM Time in LOS 15 min 2-4 hrs 24 hrs 1) Lower launch 1) Covers as much as 42.2% 1) Moderate 27 costs. of the earth's surface. launch cost. Merits 2) Short round trip Ease of tracking. 2) Small round trip signal delay. 2) No problems due to delays. 3) Small path loss. doppler. 1) Larger 1) Shorter life, 5-8 1) Very large round trip delays. years. delays. Demerits 2) Greater path 2) Encounters 2) Expensive Earth Stations loss than radiation belts. due to weak signals. LEO's. دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية ELIPTIC ORBIT APOGE TELSTAR RELAY 28 MOLNYA دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 PERIGE I SATELLITE COMMUNICATION PRINCIPLE (POINT TO POINT) 29 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 POINT TO MULTIPOINT (BROADCASTING) 30 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 III FREQUENCY AND POLARIZATION 1) FREQUENCY FIXED SATELLITE SERVICE (FSS) BROADCAST SATELLITE SERVICE (BSS) 31 MOBILE SATELLITE SERVICES NAVIGATION SATELLITE SERVICES METEROLOGICAL SATELLITE SERVICES دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية KILO = x 103 MEGA = x 106 GIGA = x 109 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 BAND DESIGNATION UP-LINK DOWN-LINK GHz GHz S 4 2 C 6 4 X 8 7 33 Ku 14 11/12 K 24 18 Ka 40 24 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية POLARIZATION a ) V/H POLARIZATION b) RHC/LHC POLARIZATION 34 (CIRCULAR) دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية a ) V/H POLARIZATION 35 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 b) RHC/LHC POLARIZATION 36 دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 a ) V/H POLARIZATION E P H 37 H P E دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 b) RHC/LHC POLARIZATION Ey E EX Ey 38 E EX دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 SPACE SEGMENT 39 October'2003 THE PAYLOAD It refers to the equipment used to provide the service for which the satellite has been lunched THE BUS Refers to the various subsystems which provide the power, 40 attitude control, orbital control, thermal control, command and telemetry functions required to the service payload. TRANSPONDER Refers to the equipment which provide the connecting link between the satellite transmit and receive antennas دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 THE ATTITUDE CONTROL THE ATTITUDE CONTROL DEPENDS ON SATELLITE TYPE SPIN STABILZATION 41 • 3-AXIS STABILIZATION OR BODY STABILIZATION دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 SPIN STABILIZATION 42 • SPIN RATE IS TYPICALLY IN THE RANGE OF 50 ÷ 100 REV/min دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 SPIN AXIS 43 • THE SPIN AXIS IS ADJUSTED TO BE PARALLEL TO N-S AXIS OF THE EARTH دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 3-AXIS STABILIZATION 44 • BECAUSE THE BODY REMAIN FIXED RELATIVE TO THE EARTH, 3-AXIS SATBILIZATION IS ALSO KNOWN AS BODY STABILIZATION دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 ROLL PITCH and YAW AXIS 45 • THE THREE AXIS ARE ROLL, PITCH AND YAW دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 3-AXIS STABILIZATION ! 46 FOR COMMUNICATION SATELLITE, 3-AXIS STABILIZATION IS OFTEN USED دورة لمنسوبي الكلية SATCOM-Services $ Applications June’2006 THE POWER SUPPLY Primary Electrical Power supply provide from SOLAR CELLS ARRAYS of cells in series-parallel connection are required so that have high power The daily eclipse start approximately 23 days before EQUINOX And end approximately 23 days after. 47 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية EQUINOX 48 The EQUINOX for both the SPRING and AUTOMN can last Up to 72 min at the actual EQUINOX day. During ECLIPSE power is provided by a NICKEL-CADMIUM Ni-Cd or NICKEL-HYDROGEN (Ni-H2)Long life batteries. دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية TRANSPONDER TRANSPONDER – SERIES OF INTERCONNECTED UNITS WHICH FORMS A SINGLE COMMUNICATIONS CHANNEL BETWEEN THE RECEIVE AND TRANSMIT ANTENNAS IN A COMMUNICATION SATELLITE. 49 دورة لمنسوبي SATCOM-Services $ Applications June’2006 الكلية THE BANDWIDTH ALLOCATED FOR THE C-BAND SERVICE IS 500 MHz, THIS IS DEVIDED INTO SUBANDS ONE FOR 50 EACH TRANSPONDER