ION-SAT:Nano-satellite for

ionosphere monitoring

XV ISSS 2019

OUTLINE

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Motivation Team Members Overview Problem to solve Mission Objective Mission Analysis PayLoad Specifications Subsystems Budget

Power Link Mass Cost

Conclusion

MOTIVATION

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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