Mangalyaan Mission

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.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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.
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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)

18. RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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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
RS & GIS DIVISION, DEPT. OF CIVIL ENGG, NIT WARANGAL
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