This document provides an overview of satellite systems. It discusses the main types of satellites including natural satellites like moons and artificial satellites launched by humans. The history of satellite development is summarized starting with Galileo's discovery of Jupiter's moons in 1610 and the first artificial satellites Sputnik 1 and satellites carrying animals. The document also briefly summarizes the typical sizes, masses and orbit types of different classes of satellites and provides some examples. Finally, it describes the basic mathematical principles governing satellite motion and orbits, and provides a high-level overview of the typical subsystems and structure of a satellite bus and payload.

1. Sattelite System
by Asim Khan (MS GNSS )

2. Contents
 Introduction
 Main Types
 History
 Types
Size
Mass
 Orbit Types
Altitude
Inclination
Eccentricity
 Mathematical Description
 Structure
Bus
Sub System
Payload

3. Introduction
• Satellite is an artificial or body placed in orbit round the earth or another planet in order to collect information or for
communication.

4. Main Types
• Natural Satellite
 A natural satellite is any
celestial body in space
that orbits around a larger
body. Moons are called
natural satellites because
they orbit planets
• Artificial Satellite
 Satellites that are made
by people and launched
into orbit using rockets
are called artificial
satellites. There are
thousands of artificial
satellites orbiting the
Earth

5. Natural (earth Moon ) And Artificial
Satellite (Tess )

6. History
 Galileo Galilei was first to
discover jupitor
satellites(Moon)on January
7, 1610
 First Artificial satellite
Sputnik 1 on 3 November
1957
 First Aniamal liaka (Dog )
orbit around Earth
 First Manned Satellite Salyut
1 in 1971
 Navstar 1, was launched
February 22, 1978 in GPS
system of Satellites
 1999 Mobile phone manufacturer
Benefon launched the first
commercially-available GPS
phone, a safety phone called the
Benefon Esc!

7. Types of Satellite
• Size and Mass
• CubeSats are built to standard dimensions (Units or “U”) of 10 cm x 10 cm
x 10 cm. They can be 1U, 2U, 3U, or 6U in size, and typically weigh less
than 1.33 kg (3 lbs) per U
Group name[1] Mass (kg) Size
Large satellite >1000 >1000 m³
Medium satellite 500 to 1000 500 m³
Mini satellite 100 to 500 100 m³
Micro satellite 10 to 100 50 m³
Nano satellite 1 to 10 10 cm³ to 100 cm³
Pico satellite 0.1 to 1 <10 cm³
Femto satellite <0.1 <5 cm³
2

8. Group name[1] Function Type
Large satellite  International space station(Laboratory )
 Skylab
Medium satellite Astronomicl Satellites and Communication
Mini satellite SSOT, Smart-1, Spirale(early warning system or
observing )
Micro satellite Astrid-1(Atmosphere Study )
Nano satellite : ExoCube (CP-10), ArduSat(Space Weather )
Pico satellite F-1 Sattelite (Educational )
Femto satellite Zero Gavity (Experiments)

9. Name Function
Astronomical satellites Observation of distant planets, galaxies, and
other outer space objects
Biosatellites To carry living organisms, generally for
scientific experimentation
Communication satellites Telecommunications
Earth observation satellites Environmental monitoring, meteorology, map
making etc
Navigational satellites Navigation Purposes (tracking )
Weather satellites To monitor Earth's weather and climate
Space stations Laboratory
Reconnaissance satellites Military or Intelligence applications
Recovery satellites Recovery of reconnaissance, biological, space-
production and other payloads from orbit to
Earth
Crewed spacecraft (spaceships) To put humans into (and beyond) an orbit, and

10. Orbits Types
Name Altitude
Low Earth orbit
(LEO)
180 km - 2,000 km
(1,200 mi)
Medium Earth orbit
(MEO)
2,000 km (1,200
mi) - 35,786 km
(22,236 mi)
Geosynchronous
orbit (GEO)
35,786 kilometres
(22,236 mi)
High Earth orbit
(HEO)
35,786 km (22,236
mi)
Name Inclination
Inclined orbit 1°to 89°
Poalr orbit 90 °
Polar sun
synchronous orbit
90°

11. Orbit Types
Name Eccentricity Perigee Apogee
Circular orbit e = 0 equal equal
Hohmann transfer
orbit
e = 0 equal equal
Elliptic orbit: e = 0.1 to 0.99 low earth orbit at Geosynchronous
Geosynchronous
transfer orbit
e = 0.1 to 0.99 low earh orbit at Geosynchronous
Geostationary
transfer orbit
e = 0.1 to 0.99 low earth orbit at Geosynchronous
Molniya orbit inclination = 63.4º low earth orbit at Geosynchronous
Tundra orbit inclination = 63.4º low earth orbit at Geosynchronous

12. Mathematical Description
Newton Laws
Every object will remian at rest or in
motion until a net force changes its
state .
Acceleration in a body is
a F∝ ÷m .
Every action has an reaction but opposite
in direction.
 Centripetal Force
F=mv² ÷ r.
Centripetal acceleration
a = v² ÷ r.
Gravitational Force
F=G m1×m 2 ∕ r².
Keplar laws
 All planets move about the Sun in
elliptical orbits, having the Sun as one
of the foci.
A radius vector joining any planet to
the Sun sweeps out equal areas in
equal lengths of time.
The squares of the sidereal periods
(of revolution) of the planets are
directly proportional to the cubes of
their mean distances from the Sun.
Orbital velocity
V= √Gm / r # r = R + h
Escape velocity
v = √2GR

13. Mathematical description
• Orbiting satellites acceleration
a = v² / r
Earth Gravity pull on satellite
g= 9.8 m/sec
• Raduis of Earth = 6.4× 10 6 m
 g= v² / r
 v = √gR
 v = √9.8×6.4 × 10 6 m
 v =7.9 km/sec
Critical orbital velocity for a satellite is
7.9 km/se
• Time Period for satellite
• T= 2R / v
T=5060 sec
π

14. Mathematical Description
• Orbital radius for Geo stationary satellite
r = (GMT²/4 π²)1/3
r =3600 km above from surface of Earth
• Orbital Parameters Of satellite
• a = semimajor axis =ra + rp/2
• b = semiminor axis
• e = ecentricity = ra - rp / ra + rp
• ra = apogee radius = a(1+ e )
• rp + perigee radius = a ( 1- e)
• p =semilatus rectum = a (1- e²)
• θ = true anomaly
• r = p /1+ecosθ

15. Structure
 Bus
The bus is the platform that supports the
payload and maintains
the satellite’s position in orbit.
Payload
 Command and Data Handling (C&DH)
System
Communications system and antennas
Electrical Power System (EPS)
Propulsion
Thermal control
Attitude Control System (ACS)
Guidance, navigation, and control (GNC)
System
Structures and trusses
Life support (for crewed missions)

16. Bus Sub system
Name Function
Structure Provides “real estate” for mounting all bus and
payload units and the interface with the launch
vehicle
Electrical Power Provides electrical power to the payload and
bus units
Attitude Determination and Control Provides the control for achieving and
maintaining orbit and pointing
Propulsion Provides the propulsive power for achieving
and maintaining orbit
Telemetry &
Command
Controls the spacecraft and monitors its health
Thermal Control
Subsystem
Maintains a benign operating environment
Mechanisms Provides the means for deploying appendages
which must be stored for launch, and the
means to adjust appendages

17. Typicsl 3-Axis Spacecraft

18. Refrences
• Slideshare.com
• Nasa.com
• wikipedia
•