The document presents an overview of the space debris removal system developed by the Department of Electronics and Communication Engineering at Krishna Institute of Engineering and Technology. It discusses the types of orbits, sources of debris, associated risks, tracking mechanisms, and potential mitigation strategies for space debris. The document concludes with ongoing research and development efforts, highlighting the importance of addressing the increasing threat of space debris to satellites and orbital operations.

1. Department of Electronics and
Communication Engineering (ECE)
SPACE DEBRIS REMOVAL
SYSTEM
Krishna Institute of Engineering
and Technology
Mohammad Shadab
University Roll No 1302931086
Presented By:- Presented To:
Shipra &Saumya MAM

2.  Introduction
 Types of orbits
 Sources of debris
 Tracking and Measurement
of Space Debris
 Mitigation of Space Debris
 Conclusion
Points of Discussion

3. Current Space Congestion

4. INTRODUCTION
Space Debris , also known as orbital debris , space junk and
space waste , is the collection of defunct objects in orbit around
Earth.
They can include anything from entire used rocket stages and out
of order satellites to explosion fragments, paint flakes, dust, slag
from solid rocket motors, coolant released by Upravlyaemy
Sputnik Aktivnyj (Russian: Управляемый Спутник
Активный),also known in the west as Radar Ocean
Reconnaissance Satellite or RORSAT other small particles from
equipments.
Debris poses a growing threat to satellites and could prevent the
use of valuable orbits in the future.

5. SPACE SURVEILLANCE NETWORK (SSN)
Debris Size 0.1-1cm 1-10cm >10cm
Total Number at all altitudes 150 million 780,000 23,000
Debris in Low-Earth Orbit 20 million 400,000 15,000
Estimated amount of Space Debris:
 Currently more than 15,000 objects are tracked and kept in catalogue by SSN
 Space debris number is much more than catalogued

6. Threat of this size?
• Category I (<1cm) - They can make significant
damage to vulnerable parts of a satellite.
• Category II (1-10cm) - They tend to seriously
damage or destroy a satellite in a collision.
• Category III (>10cm) – They may completely
destroy a satellite in a collision and can be
tracked easily.
Categorization:

7. Debris Distribution Graph

8.  Low Earth Orbit (LEO)
 Medium Earth Orbit (MEO)
 Geostationary Orbit
 Highly Elliptical Orbit
(HEO)
TYPES OF ORBITS

9.  Proximity
 Altitude Range
 Higher Velocity
 Energy
Low Earth Orbit

10. The International Space Station is in an LEO that
varies between 320 km (199 miles) and 400 km
(249 miles) above the Earth's surface.
Hubble Space Telescope
Earth's plates, remote sensing, spatial
investigation, meteorology.
Phone Satellites
Experiments and Installation
Features of LEO:

11. Presence of debris in LEO a function of altitude(h)
and declination(δ)

12. GRAPHIC EVOLUTION OF TRACKABLE LEO
ORBIT OBJECT:
Graphic evolution of total trackable Low-Earth Obit (LEO) object population since 1994
Source: Marshall H. Kaplan, Survey of Space Debris Reduction Methods, AIAA SPACE 2009 Conference & Exposition 14 - 17 September 2009, Pasadena,
California,AIAA 2009-6619
The number of space debris increases very quickly:

13. Hypervelocity accidents in space

14. Case of Iridium33 and Cosmos2251
 Fourth hypervelocity accident
 February 10 2009
 Collision velocity 11 km/s

15. Distribution of the collision Debris

16. Altitude -2000 km to 36,000 km
approx.
Common Use :Navigation , GPS
Communication ,MAPS and Space
and Environment science.
Orbital Period –Apogee ,Perigee
Medium Earth Orbit

17. Geostationary Earth Orbit
 Altitude - 35786 Km ,Precise and
Calculative.
 Television Broadcasting
 Weather Forecast-Storm
movements and developments.
 NATIONAL SECURITY

18. Highly Elliptical Orbit
 These satellites do not follow a circular orbit, but its orbit is elliptical.
 Its orbital period is of 8 to 24 hours.
 The perigee about 500 km and apogee of 50000 km.
Fig. HEO

19. The Inter-Agency Space Debris Coordination Committee (IADC)

21. Tracking of debris
RADAR
LIDAR
SPACE TELESCOPES
INTEGRATED SATGPS SYSTEMS

22. TOOLS
Electro dynamic tethers
 Laser brooms
 Solar sails
 Space nets and collectors

23. Electro-dynamic tethers
Simple
 Fleming’s Left Hand Rule

24. Laser brooms
Fast
Direct Impact
Drag by photon force
Technology is mature
• Could not be move freely in a huge range
• Threat- Space based weapon system

25. Ground based laser
Space based laser
Laser Brooms
Ground Based Space based

26. Solar sails
 Principle
 Outer Orbit Reach
 No propellant or engines
 Less maintenance
• Difficult to control
• Deployment
• Crashes

27. Space Nets and
Collector satellites
Space nets or umbrellas are
satellites which eject a huge net
that ‘fishes’ or collects the debris
and is later disposed off into a
graveyard orbit .
Uses momentum generated through
throwing for movement

28. Graveyard Orbit -
Conceptualization

29. Mathematics Involved

30. CONCLUSION
 Research and development
 Guidelines By IADC-
Inter Agency Space Debris Coordination Committee
 Implementation

31. Bullets Raining From The Sky