DESIGN, BUILD AND TESTING OF A NANOSATELLITE Introduction to - - PowerPoint PPT Presentation

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DESIGN, BUILD AND TESTING OF A NANOSATELLITE Introduction to - - PowerPoint PPT Presentation

Feb 24, 2023 92 likes •422 views

EEE01A DESIGN, BUILD AND TESTING OF A NANOSATELLITE Introduction to CubeSats KEY POINTS Satellite Communication Characteristics of Satellite Orbits Background on Orbital Mechanics SCOOB-I 3U CubeSat Systems T ool Kit (STK) Results and

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SLIDE 1

DESIGN, BUILD AND TESTING OF A NANOSATELLITE

EEE01A

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SLIDE 2

KEY POINTS

Introduction to CubeSats Satellite Communication Characteristics of Satellite Orbits Background on Orbital Mechanics SCOOB-I 3U CubeSat Systems T

  • ol Kit (STK)

Results and Discussion Conclusion

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WHAT ARE CUBESATS?

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CUBESAT SUBSYSTEMS

  • Communications with the ground station [COMM]
  • On-Board Data Handling and Storage [OBDH]
  • Attitude Determination and Control System [ADCS]
  • Electrical Power System [EPS]
  • Mechanical Structure and Thermal Control System
  • Payload
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SLIDE 5

CUBESAT SUBSYSTEMS

MISSION DESIGN OF THE SATELLITE

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SATELLITE COMMUNICATION

Downlink

With ground contact, this would allow the ground station to send radio signals and command to the satellite while receiving data transmission for further analysis.

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SLIDE 7

CHARACTERISTICS OF SATELLITE ORBITS

THE 2 TYPES:

  • 1. Low-Earth Orbit (LEO)
  • 2. Equatorial Orbit
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SLIDE 8

LOW-EARTH ORBIT EQUATORIAL ORBIT

satellites orbit near the meridian line satellites are at the altitude of between 160 to 2,000km above Earth’s surface

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SLIDE 9

BACKGROUND ON ORBITAL MECHANICS

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ORBITAL ELEMENTS

  • i. Semi-major axis (a)
  • ii. Eccentricity (e)
  • iii. Inclination (i)
  • iv. Argument of Perigee (ω)
  • v. Right Ascension of the Ascending

Node (Ω)

  • vi. True Anomaly (ν)
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SLIDE 11

SCOOB-I SATELLITE

Mission Design of a 3U CubeSat

Scheduled for launch in 2020

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  • 1. To measure the solar irradiation in the infrared and visible

part of the solar spectrum

  • 2. To determine the ionization radiation at 400 km or above

in order to validate and verify first-principles aviation radiation models.

OBJECTIVES OF THE SATELLITE

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SLIDE 13

By applying the theory of orbital mechanics, fixed values of data such as orbit altitude are chosen. Additionally, an inclination range of 5° to 15° is used for comparison.

METHODOLOGY

Using the Systems Tool Kit (STK), orbit simulations are generated with the aforementioned values to find out parameters such as the solar intensity as well as the ground contact period. Analyses are made using the reports and graphs that are computed to determine which inclination is the most beneficial for the Singapore ground station.

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SLIDE 14

SYSTEMS TOOL KIT (STK)

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SLIDE 15
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STK SIMULATIONS

  • A simulation of the satellite orbit is created using

STK, which projects a satellite ground track.

  • Using STK, different graphs and reports can be

generated to find out the suitability of the inclination.

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SLIDE 17

RESULTS & DISCUSSION

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BETA ANGLE

Sun Vector Projection of Sun vector onto

  • rbital plane

Satellite’s

  • rbital plane
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SLIDE 19

Item 1 Item 2 Item 3 Item 4 40 30 20 10

BETA ANGLE

used for further calculations to determine the thermodynamic properties of the satellite in space.

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ACCESSIBILITY OF THE SATELLITE

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Item 1 Item 2 Item 3 Item 4 40 30 20 10

NUMBER OF CONTACTS

a contact occurs when the satellite passes directly

  • verhead the

Singapore ground station along the ground track.

Inclination Number of Contacts 5° 2550 10° 2550 15° 2549

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Item 1 Item 2 Item 3 Item 4 40 30 20 10

DURATION OF CONTACTS

used to calculate the communication window per day between the satellite and the Singapore ground station.

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Item 1 Item 2 Item 3 Item 4 40 30 20 10

DURATION OF CONTACTS

Inclination Average Contact Period per Day/s 5° 11400 10° 11000 15° 10300

used to calculate the communication window per day between the satellite and the Singapore ground station.

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SOLAR INTENSITY

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SLIDE 25

Item 1 Item 2 Item 3 Item 4 40 30 20 10

SOLAR INTENSITY

the percentage

  • f the solar disc

visible to the satellite.

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ECLIPSE DURATION

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Item 1 Item 2 Item 3 Item 4 40 30 20 10

ECLIPSE DURATION

eclipsing events are the start and end periods of penumbra and umbra.

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Item 1 Item 2 Item 3 Item 4 40 30 20 10

ECLIPSE DURATION

eclipsing events are the start and end periods of penumbra and umbra.

Inclination Average Eclipse Duration per Day/s 5° 2125 10° 2129 15° 2131

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CONCLUSION

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5° inclination for the SCOOB-I CubeSat is the most effective parameter for Singapore ground station because:

  • it has the longest communication period for more data

download.

  • it has the least eclipse duration, allowing for a shorter

period of power loss.

CONCLUSION

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SLIDE 31

Thank You for your kind attention!