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ION-SAT:Nano-satellite for
ionosphere monitoring
XV ISSS 2019
OUTLINE
2
Motivation Team Members Overview Problem to solve Mission Objective Mission Analysis PayLoad Specifications Subsystems Budget
Power Link Mass Cost
Conclusion
MOTIVATION
3
The International Summer Space School Samara (ISSS) is part of theSamara University's desire to establish cooperation between universities inthe field of space science and technology.
This 15th edition of the ISSS is part of a vision of international integration forthe involvement of young people in micro / nano satellite (NS) developmentprojects for the realization of experiments and space studies with a view to todevelop new fundamental knowledge in space science and technology.
We had the opportunity to share our ideas and experiences in new spacemissions with several young Russians and around the world to establishinteruniversity cooperation.
In the spirit of competitiveness; Our team developed a mission to monitor theionosphere in Polar Region using a 2U CubeSat in Low Earth Orbit
TEAM MEMBERS
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1. Alphonse Sibri Sandwidi (from University Norbert Zongo, Burkina Faso)2. Andrey Yu. Lavrov (from Samara University, Russian Federation)3. Hoda Awny El-Megharbel (Kyushu Institute of Technology of Japan / Egypt)4. Jayakamal Abeyesekera (from Arthur C Clerke institute for modern technologies, Sri Lanka)5. Liliana Lavrova (from Samara University, Russian Federation)6. Petter André Langstrand(from University of Oslo, Norway)
OVERVIEW: NANO-SATELLITES
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Satellites can be built small to reduce the large economic cost of launch vehicles andthe costs associated with construction also it enable missions that a larger satellitecould not accomplish, such as using formations to gather data from multiple points.
Miniature satellites, especially in large numbers, may be more useful than fewer,larger ones for some purposes – for example, gathering of scientific data and radiorelay.
Technical challenges in the construction of small satellites may include the lack ofsufficient power storage or of room for a propulsion system.
One rationale for miniaturizing satellites is to reduce the cost: heavier satellitesrequire larger rockets with greater thrust that also has greater cost to finance. Incontrast, smaller and lighter satellites require smaller and cheaper launch vehiclesand can sometimes be launched in multiples. They can also be launched 'piggyback',using excess capacity on larger launch vehicles.
PREVIOUS STUDIES
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Simulation of the Potential of a CubeSat Designed for Accurate Plasma
Measurement in LEO : LATMOS/CNRS, Jussieu, Paris, France; 500 km
The CuSPED Mission: CubeSat for GNSS Sounding of the Ionosphere-
Plasmasphere Electron Density; NASA ; 500 km
PROBLEM TO SOLVE?: PARTICULARITY OF POLAR REGION
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The polar regions are special areas of the ionosphere. First, the day–night cycle of solar illumination
has a strong seasonal dependence. In thewinter, it can be almost continuously dark,while in the summer, the sun radiates theatmosphere continuously.
Second, the close connection to the near-space environment due to the nearly verticalmagnetic field provides an additional ionizationsource with the aurora. At these high latitudes,the ionosphere is highly variable due to thechanging conditions in the solar wind, while atlower latitudes, the variation of the ionosphereis mostly dominated by the rotation of theEarth.
PROBLEM TO SOLVE?: CLIMATE CHANGE
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An illustration of the key interest ofmonitoring climate change BYIONOSPHERE STUDY withnanosatellite : Emerging pattern ofglobal change in the thermosphereand ionosphere,
Reference: J. Lastocicka etal.(Ann. Geophys., 26, 1255-1268,2008)
PROBLEM TO SOLVE: SECULAR VARIATIONS OF GEOMAGNETIC FIELD
9Secular variations of geomagnetic field
MISSION OBJECTIVE
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A nanosatellite designed to investigate F region ionospheric plasma inpolar regions.
The main goal is to use the NS for electron density (Ne) and electrontemperature (Te) measurement of the ionosphere.
Methodology: Instruments aboard CubeSat will sample in situ plasma density and
electron temperature at a rate of 10 Hz and 1.0 Hz, respectively. The choice of sampling rate provides for resolution of 2-10 km plasma
depletions, important since plasma anisotropies of this scale size areknown to disrupt Ultra High Frequency (UHF) radio transmissions.
A sensor, the Miniature Electrostatic Analyzer (MESA), will be used tomeasure plasma density and temperature with its heritage flight aboardCubeSat.
MISSION REQUIREMENTS
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ION-SAT shall collect the data for 1481seconds in orbit for the two polar zones
ION-SAT shall have period of 5554 In the sun-light for 3387 seconds In the shadow for 2167 seconds
ION-SAT shall charge the battery for 1196seconds
ION-SAT shall have a communicationwindow of 474 seconds with each GroundStation for receiving Commands andSending Data
ION-SAT shall downlink 4.34 Mbytes perpass.
MISSION ANALYSIS
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Calculation of the parameters of the orbit of a nanosatellite moving in the centralfield (Kepler's laws of planetary motion)
Constants (standard of GLONASS)Earth radius : RE = 6 378 kmStandard gravitational parameter : μ = 398 600 km3/sec2
Source dataOrbit height (apsis, periapsis) : Hp = Ha = 400 kmInclination : i0 90 deg = 1,571 radLongitude of ascending node : Ω0 = 0 deg = 0 radArgument of periapsis : ω0 = 0 deg = 0 radTrue anomaly : ʋ0 = 0 deg = 0 rad
MISSION ANALYSIS
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MISSION ANALYSIS
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ORBITAL PARAMETERS SIMULATION
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Semi-major axis variation during the orbital motion due to the effect ofaerodynamic impats
ORBITAL PARAMETERS SIMULATION
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Eccentricity of the orbit variation due to the effect of aerodynamic impats
ORBITAL PARAMETERS SIMULATION
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Inclination of the orbit, Anomaly of perigee and the longitude of ascending nodevariation during the orbital motion due to the effect of aerodynamic impats
ORBITAL PARAMETERS SIMULATION
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ION-SAT Orbit
GROUND STATIONS
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We will use two ground Stations for receiving data andtransmitting commands to the Nano-Satellite:
One of them – Plesetsk, Russia Geographic coordinates of Plesetsk,
Arkhangelsk Oblast, Russia Latitude: 62°42′28″ N Longitude: 40°17′29″ E Elevation above sea level: 130 m = 426 ft
The second of them - Cape Town, SouthAfrica The latitude of Cape Town, South Africa
is -33.918861, and the longitude is18.423300.
GPS coordinates of 33° 55' 7.8996'' Sand 18° 25' 23.8800'' E.
GROUND STATIONS: SETUP
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PAYLOAD SPECIFICATIONS
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MESA is used to investigate F regionionosphere plasma depletion. Plasma Density at a rate of 10 Hz Plasma Temperature at a rate of 1 Hz
Resolution: 2-10 Km Plasma depletion Data Collection: 10 spectra of electron flux per
second 16-bits data word 6 channels
Therefore, Data=16 bits x6 channels x10spectra=960 bits per second
SUBSYSTEMS: ON-BOARD COMPUTER
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Microcontroller 32-bit ARM Cortex-M3
Communication 2x I2C 2x UART 1x CAN 1x SPI
Memory and Storage 32 kb EEPROM 4 MB flash for code storage 2x 1 MB external SRAM for storage MicroSD socket
Operating voltage 3V3 Operating temperature -10 to 70 C
SUBSYSTEMS: ATTITUDE DETERMINATION AND CONTROL
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CubeControl
2x Ferrite core torquers 1x Air core coil 3x MEMS gyro rate sensors 10x Coarse Sun sensors 3x deployable magnetometer
ADCS computer
SUBSYSTEMS: ELECTRICAL POWER SUBSYSTEM
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BA0x High Energy Density Battery Array 8 cells 44.4 Whr / 12000 mAh, 3.7 V,
4x CubeSat solar panels 2U ideal power generation 4.6 W per panel
iEPS Electrical Power System 3.3V and 5 V operating temperature -20 to 60 C 20W power
STRUCTURE
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Payload envelope per 1U : 98.4 x 98.4 x 98.4 Thermal Range : 40 to +80
STRUCTURE: SCHEMATIC
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BUDGETS: POWER
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P(W) Duty time (%) Pcons/cycle (W) Name
OBC -0,200 100 -0,200 Cubecomputer
ADCS -0,450 100 -0,450 CubeADCS Magnetic
Rx -0,480 27 -0,128 UHF downlink /VHF uplink Full Duplex Transceiver
Tx -4,000 27 -1,067
Payload -0,750 73 -0,550 MESA
Consumption -5.880 - -2.395 -
Solar panels +8.053 73.345 +5.906 CubeSat solar panels 2U
Battery 44.4 Whr 26.655 BA0x High Energy Density Battery Array
BUDGETS: LINK
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Freequency RangeMHz
RF Power/Sensi
tivity
Modulation scheme
Data rate selectable(b
ps)
Data Link layer
protocol
Transmitter 145.8-146 23dBm BPSK 1200,2400.4800,9600
AX25 or HDLC
Receiver 435-438 -104dBm AFSK 1200 AX25 or HDLC
Path free los - -137.22 dB - - -
TX antenna >50MHz 0dB - - -
RX antenna >10MHz 0dB - - -
BUDGETS: MASS
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Mass (g) Volume (mm) Name
Structure 303 98.4 x 98.4 x 98.4 2U
Payload 750 81 x 81 x 10 MESA
Communication System 75 90 x 96 x 15 UHF downlink/VHF uplink Full Duplex Transceiver
ADCS 203 90 x 96 x 31 CubeADCS Magnetic
Onboard Computer System 70 90 x 96 x 10 Cubecomputer
Antenna 85 98x98x7 Deployable dipole antenna system
Battery 180 89x95x14 mm BA0x High Energy Density Battery Array
Solar Panels 4 x 150 CubeSat solar panels
iEPS Electrical Power System 189 96 x 92 x 26.45 iEPS Electrical Power System
Total Mass 2455
BUDGETS: COST
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Subsystem Cost(USD)
OBC 4500
ADCS 16000
Communication 8500
Payload 6000
EPS 8000
Solar panels 14000
Battery 6300
Structure 3150
Total 63300
CONCLUSION
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The ionosphere and atmosphere monitoring by using nanosatellite will be veryuseful for computing and big data instrumentation about understanding Solar-terrestrial interactions and so be able to understand how these inputs changeour living environment, weather and climate.
The total cost of developing this nanosatellite is about 80000 USD The comprehensive monitoring of the ionosphere at polar region should be
complemented by space observations monitoring all latitudes over restrictedlocal times by using a swarm of nanosatellite.
THANK YOU
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