PRELIMINARY DESIGN of new antenna for NOAA AVHRR data reception station in Uzbekistan and IMPLEMENTATION plan for NOAA earth station. CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA 1 LOCAL GUIDE: Mr. K. K. Sood (Scientist/Engineer, Space Applications Centre) COUNTRY GUIDE: Mr. Botir Usmonov (Dean, Tashkent State Aviation Institute) SUBMITTED BY: Mr. Yunir Gataullin (Junior Research Assistant, Tashkent Research Institute of Space Engineering)

Started in 1978 Orbit: near circular, sun synchronous Inclination: 98 degrees Altitude: 800 to 900 km Orbital period: 98 to 102 minutes CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Earth Imaging Atmospheric Sounding Instruments Solar Backscatter Ultraviolet Radiometer Space Environment Monitor Search and Rescue Transponder Data Collection System 5

The Advanced Very High Resolution Radiometer (AVHRR) is a scanning radiometer, which makes calibrated measurement of upwelling radiation form small areas (pixels) that are scanned across the sub satellite track. CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 ROTATION SCAN MIRROR SECONDARY MIRROR PRIMARY MIRROR To optics and detectors Spacecraft velocity vector cm 5.06 cm Signal Dimensions Scanning and reflecting surfaces FROM EARTH 7

8 CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 CHARACTERISTICVALUE Line Rate360 lines/minute Data Channels5 transmitted, 6 available Image Resolution1.1 km Carrier ModulationDigital split phase, phase modulated Transmitter Frequency (MHz) or Transmitter Power6.35 W (38.03 dBm) EIRP39 dBm PolarizationRHCP

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 PARABOLIC DISH or ANTENNA ARRAY ? 9

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Parabolic dish normally has narrow beam. It demands a precise tracking It demands GPS receiver for tracking Complicated design It weights much and occupies more space Finally such a system costs more. 10

Wide beamwidth No need of tracking -no GPS is required Simpler design Low weight Low space is required It is cost-effective CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 SPECIFICATIONS AND REQUIREMENTS SELECTION OF CONFIGURATION ARRAY DESIGN RADIATION ELEMENTS DESIGN FEEDING NETWORK DESIGN DESIGN OPTIMIZATION 12

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, ParametersValue Operating frequency and MHz Gain (minimum)24 dBi Beam-width (minimum)25 degrees No. of elements8 PolarizationRHCP Mechanical requirements: Weight~12 kg Wind resistivity120 m/sec Temperature range -30 to + 50

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Ground plane Helical elements TOP VIEW SIDE VIEW 2x4 planar array 8 helical elements RHCP 14

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 This step is to decide two main parameters of the array: And then calculate the gain of the array: Number of elements for the array Spacing between elements 15

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 D - diameter of the helix; C – circumference of helix = D; S – spacing between turns - patch angle = arctan S/ D; L – length of one turn; n – number of turns; d – diameter of helix conductor A – axial length = nS AR – axial ratio ( ); d D S L S C=πD L α A 16

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Feeding point Ground plane Helical element 50-Ohm coaxial cable BACK VIEW SIDE VIEW 17

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Mechanical aspects of helix design; Mechanical aspects of helix design; Mechanical aspects of array design; Mechanical aspects of array design; Design of the mechanical support for the array element; Design of the mechanical support for the array element; Mechanical aspects in mount selection and design; Mechanical aspects in mount selection and design; Selection of suitable materials for the design; Selection of suitable materials for the design; Calculation of wind, weight and other acting forces; Calculation of wind, weight and other acting forces; Fabrication and optimization aspects. Fabrication and optimization aspects. 18

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, MEASUREMENTS - OPTIMIZATION - MEETING THE REQUIREMENTS

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

21 CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 The first aim of the project What is second? 22

Antenna LNBC Antenna control Unit Receiver and Demodulator Data acquisition and processing system CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 30, 2004 LNBC ANTENNA CONTROL UNIT Proposed NOAA HRPT Earth Station block diagram IF (70 MHz) DSP SERVER DATA BIT SYNCH- RONIZER 70 MHz RECEIVER Planar Array (2x4) G=24.15 dBW F =1698/1707 MHz METEOROLOGICAL APPLICATIONS AGRICULTURAL APPLICATIONS ECOLOGICAL APPLICATIONS L A N PM split phase DEMODULATOR PC 24

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 30, 2004 Orbit altitude 83319km, km Orbit inclination 98.8 Orbital period102 minutes Visibility from ground station3-5 minutes TRANSMISSION PARAMETERS NOAA transmitter EIRP39 dBm Transmitting frequency or MHz Data Rate664.5 kbps PolarizationRHCP, LHCP (redundancy) Bandwidth2.66 MHz 25

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 30, 2004 NOAA K, L, M ALTITUDE 850 KM INCLINATION 98 EIRP 9 dBW Path Loss = 158 dB Helical Array Antenna G/T = 4 dB/K =45 26

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 30, 2004 Link calculation. Link calculationsValueUnits Slant Range (at the elevation of 2) 3194,3km Slant Range (at the elevation of 45) 1157km Power Flux density-134.2dBW/m 2 Power received dBW Path loss158dB Link margin10dB Carrier to Noise Ratio C/N dBHz Bit Error Rate (BER)10 -6 En. per bit to noise dens. rat (E b /N 0 )25.42dB Ground station parameters Figure of Merit G/T4.02dB/K System noise temperature T sys 20.13dBK Cable attenuation1.01dB/15 meters Array Antenna parameters Antenna Gain24.15dB Antenna Effective Aperture1.076m Beamwidth (HPBW)12X30degrees 27

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Array design (electrical and mechanical considerations) Earth Station Implementation Plan Financial aspects and calculations 28

CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31, 2004 Wide beam helix array can receive NOAA HRPT data The antenna and Earth Station can be cost-effective Array antenna can be designed and implemented in developing countries 29

THANKS for attention CSSTEAP, SATCOM-IV SPACE APPLICATIONS CENTER, AHMEDABAD, INDIA August 1, 2003 – April 31,