The document summarizes India's Mars Orbiter Mission (MOM) launched in 2013. It describes the mission objectives of exploring Mars and advancing India's deep space capabilities. The mission profile involved three phases: reaching escape velocity from Earth, a 300-day cruise to Mars along a Hohmann transfer orbit, and Mars orbit insertion using a braking maneuver. MOM successfully entered Mars orbit in 2014 and began returning data on Mars' surface and atmosphere. The mission established India as the first Asian nation to reach Mars and the first nation to succeed on its first attempt.

1. 1RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT
Prepared by
Pramod M Khombare
(Source : ISRO) (Source : space.com)

2.  Introduction.
 Mission Objectives.
 Mission Profile.
 Earth-Mars Trajectory.
 Getting into Martian Orbit.
 References.
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Fig-1: Mangalyaan Satellite
(Source: ISRO)

4.  India’s first Interplanetary Mission by ISRO in its entire history of
44 years.
 Launched at Satish Dhawan Space Centre, Sriharikota,Andhra
Pradesh.
 By using Polar Satellite Launch Vehicle, C25 on 5 November 2013.
 ISRO is the 4th Space Agency in the world after NASA, RFSA and
ESA.
 Mangalyaan mission cost ~450 crores.
 Mars is about 670 million kilometers from the earth.
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5.  Cost - ~Rs.6.7 per kilometer.
 The orbiter weighs-1,350-kg.
 Spacecraft is cuboid in shape ~1.5 m across.
 Constructed of an aluminium and composite fibre reinforced plastic
sandwich construction.
 Electricity is generated by 3 solar array panels of 1.8 m × 1.4 m
each.
 Maximum power generation is 840 watts in Mars orbit.
 Manufacturing duration-15 months.
 Flyby time is 6 months.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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Fig-2 :PSLV-XL C25
(Source : ISRO)

7. A. Technological Objectives:
 Design and realisation of a Mars orbiter with a capability to
survive and perform Earth bound manoeuvres, cruise phase of
300 days, Mars orbit insertion / capture, and on-orbit phase
around Mars.
 Deep space communication, navigation, mission planning and
management.
 Incorporate autonomous features to handle contingency
situations.
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8. B. Scientific Objectives:
 Exploration of Mars surface features, morphology, mineralogy
and Martian atmosphere by indigenous scientific instruments.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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(Source:
Fig-3: Leading spacecraft into the large space simulation chamber for
Thermo-Vacuum test during the making of MOM.

10. The mission consists of following three phases:
1. Geo Centric Phase:
 The spacecraft is injected into an Elliptic Parking Orbit by the launcher.
 6 engine burns makes spacecraft to escape from earth’s Sphere of
Influence(SOI).
 Then spacecraft fallow hyperbolic trajectory.
 The SOI of earth ends at 918347 km from the surface of the earth.
 ISRO has used a method of travel called a Hohmann Transfer Orbit – or a
Minimum Energy Transfer Orbit.
 To send a spacecraft from Earth to Mars with the least amount of fuel
possible.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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(Source : ISRO)
Fig-4: Process 2: Trajectory of MOM.

12.  The spacecraft leaves Earth in a direction tangential to Earth’s orbit
encounters Mars tangentially to its orbit.
 The flight path is roughly one half of an ellipse around sun.
 It will intersect the orbit of Mars at the exact moment when Mars is there
too.
 This trajectory becomes possible with certain allowances when the
relative position of Earth, Mars and Sun form an angle of approximately
44o.
 This arrangement recur periodically at intervals of about 780 days.
 Minimum energy opportunities for Earth-Mars occur in November 2013,
January 2016, May2018 etc.
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13.  The spacecraft arrives at the Mars Sphere of Influence in a hyperbolic
trajectory.
 Mars Sphere of Influence is around 573473 km from the surface.
 At the time the spacecraft reaches the Periapsis of Mars, it is captured
into planned orbit around mars is called the Mars Orbit Insertion (MOI)
manoeuvre.
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(Source:http://www.isro.org/mars/mission-profile.aspx)
Fig-5:Earth-Mars Trajectory

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(Source: http://www.isro.org/mars/mission-profile.aspx)
Fig.6.Martian Orbit.

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(Courtsey : Doordarshan)
Video-1 : Process 1:Launching of Satellite.
MOM has greeted the RED PLANET on 24 September 2014.

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Fig-7: Trajectory Correction of MOM
(Source : ISRO)

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(Source: ISRO)
Video-2: Process 2: Trajectory Correction of MOM. The main
test engine had a perfect burn for 4 seconds.

19.  Speed of Satellite was 22 km/s.
 Satellite was carrying 1 large rocket motor and 8 small thrusters.
Plan A:
 Burning of a large engine to create thrust.
 The large engine has been functioning successfully since 1992 in
over 24 missions.
Plan B:
 Burning of 8 small engines to create thrust.
 Either Large engine or Small engines has to burn for 24 minutes.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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(Source :
ISRO)
Fig-8:Plan To Get Into Martian Orbit:

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Fig-9: MOM’s first image of Mars surface.
Taken from a height of 7300 km, with 376 m spatial resolution.
(Source : ISRO)

22. RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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Fig-10: Martian atmosphere as seen from an altitude of 8449
km. Image taken using Mars Color Camera on-board.
(Source: ISRO)

23. RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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THANK YOU
India makes a mark in Mars

24.  http://www.isro.org/mars/home.aspx
 http://www.space.com/27242-india-mars-
mission-arrival.html
 "Mars Orbiter Spacecraft completes Engine
Test, fine-tunes its Course". Spaceflight 101. 22
September 2014. Retrieved 2014-09-24.
 http://www.isro.org/pslv-c25/mission.aspx
 http://en.wikipedia.org/wiki/Mars_Orbiter_Mission
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