The document summarizes India's Mars Orbiter Mission (MOM). It describes the objectives of studying Mars' climate, atmosphere and potential for life. MOM was launched in 2013 using the PSLV rocket and placed the spacecraft in Martian orbit in 2014. The orbiter carries instruments to analyze Mars' atmosphere and surface composition. It aims to demonstrate India's low-cost spaceflight capabilities and further scientific understanding of Mars on a smaller budget than other Mars missions. MOM has exceeded its original mission duration and continues to operate successfully from Martian orbit, collecting data to study the Red Planet.

1. MARS ORBITER MISSION
PRESENTED BY UNDER THE GUIDANCE OF
AAKASH JAIN DR. SHAHANAZ AYUB
1204331001
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2. CONTENTS
INTRODUCTION
OBJECTIVES
LAUNCH VEHICLE
SPACECRAFT
PAYLOADS
• LYMAN ALPHA PHOTOMETER(LAP)
• METHANE SENSOR(MS)
• MARS EXOSPHERIC NEUTRAL COMPOSITION
ANALYSER(MENCA)
•THERMAL INFRARED IMAGING
SPECROMETER(TIS)
•HIGH GAIN ANTENNA
TRACKING AND COMMAND
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3. INTRODUCTION
 ISRO launched the 1,350 kg Mars Orbiter Mission - Mangalyaan - from
Sriharikota using PSLV-C25 XL on November 5, 2013 at 14:38 hrs
 The launch was earlier scheduled for October 28, 2013,
 The Mars orbiter will be placed in an orbit of Mars on September 24, 2014.
 In 2009 the GOI sectioned money for project study.
 Total project cost is estimated about 450 crore which is lesser than other
mars mission.
 In 2012, the individual components of the orbiter began assembly before
the spacecraft came together in March 2013.
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4. OBJECTIVE
Scientific Objective
 Mars climate , mineralogy
 Effect of radiation in Martian atmosphere
 Existence of life
Technical Objective
 to showcase India's rocket launch systems
 deep-space communication;
 navigation, mission planning and management;
 Incorporate autonomous features
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5. LAUNCHERS
SLV ASLV PSLV GSLV LVM-3
WEIGHT
(TONNES)
17 40 320 414.75 640
HEIGHT
(m)
22 24 44 49.13 43.33
PAYLOAD
LOAD(kg)
40 150 1750 2500
APPROX
4000
FIRST
LAUNCH
1980 1988 1993 2001 NOT USED
PROPLLENT
TYPE
SOLID SOLID
SOLID &
LIQUID
LIQUID
SOLID &
LIQUID
STAGE
FOUR FIVE FOUR THREE THREE
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6. STAGE-1 STAGE-2 STAGE-3 STAGE-4
Propellant
Solid Liquid Solid Liquid
Propellant Mass
(Tonne)
138 42 7.6 2.5
Peak Thrust (kN)
4800 799 247 7.3 X 2
Burn Time (sec)
103 148 112 525
Diameter (m) 2.8 2.8 2.0 2.8
Length (m) 20 12.8 3.6 2.7
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7. SPACECRAFT
FLYBY LANDER
ROVER ORBITER
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8. ENERGY AND POWER
 Three solar array panels of 1.8 m× 1.4 m each.
 Maximum power generation is about 840 W.
 For night use, it stored energy in the battery whose capacity is
36ApH.
 It has two propellant system which stores 780 litre of
propellant.
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9. PAYLOADS
Atmospheric studies Lyman-
Alpha Photometer (LAP) —
— Measuring the
deuterium/hydrogen ratio will
allow to estimate the process
of water loss to outer space.
Methane Sensor For Mars
(MSM) to check for methane in
the atmosphere of Mars, if any,
and map its sources. 9

10. Mars Exospheric Neutral
Composition Analyzer (MENCA) — is
analyzing the neutral composition of
particles in the exosphere.
Weight about 4 kg
Surface imaging studies Thermal
Infrared Imaging Spectrometer (TIS) —
will measure the temperature and
emissivity of the Martian surface, this
can allow mapping surface composition
and mineralogy of Mars.
Weight about 4 kg 10

11. • 2.2-meter diameter High Gain Antenna .
•It Works on X-band.
• Data is stored in two 16Gb Solid State Recorders
Weighs about 1.4 Kilograms
Camera provides a wide field of view of 8,000
by 8,000 Kilometers.
It give images and information of Martian
surface. They are useful to monitor the dynamic
events and weather of Mars.
two satellites of Mars - Phobos and Deimos.
MARS COLOUR CAMERA
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12. LAUNCH SEQUENCE
First Burn
 At 01:17 AM IST on Nov 07, 2013.
 It was fired for 416 seconds raising the spacecraft to 28825 km.
Second Burn
 At 02:18:51 AM IST on November 08, 2013 for 570.6s.
 It was raised the spacecraft from 28814 km to 40186 km.
Third Burn
 At 02:10:43 hrs IST, on Nov 09, 2013 for 707s.
 It was raised the spacecraft from 40,186 km to 71,636 km.
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13. Fourth Burn
At 02:06 Hrs IST on 10 November failed to raise the MOM's orbit to the
planned 100,000 km.
It was raised from 71,636 km to 78,276 km.
Orbital velocity was 35m/s expected from 135m/s.
Supplementary Burn
A supplementary 303.8 s orbit raising liquid engine burn starting at 23:45
PM on November 11, 2013 successfully raised the spacecraft from 78,276-km
to to 1,186,42-km after.
Fifth Burn
At 01:27 AM IST, November 16,2013 and lasting 243.5 s
It raised the Spacecraft from 118642 km to 192874
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14. COMMUNICATION
 During launch, the MOM was tracked by ISRO ground stations
at Sriharikota, Port Blair, Brunei and Biak in Indonesia till
separation of stage 3.
 Following stage 4 ignition, the MOM was tracked by two
specially equipped Shipping Corporation of India ships -
'Yamuna' and 'Nalanda' - positioned in the South Pacific
Ocean.
 During its journey from Earth to Mars, MOM will be tracked
by ISTRAC (ISRO Telemetry, Tracking and Command
Network) using the Indian Deep Space Network (IDSN) at
Baylalu on the outskirts of Bangalore .
 ISRO will also get position data from NASA’s Deep Space
Network through its three stations located in Canberra,
Madrid and Goldstone on the U.S. West Coast.
 At the time of Mars capture in September 2014, tracking and
communication with MOM will be done using the 70-metre
antenna of Nasa's deep space network at Canberra in
Australia.
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15. MARS VS EARTH
 24 hrs,37 minute day
 687 Days Year
 Gravity=1/3 of Earth
 Planet similar to Earth
 Human Speculation
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16. REASONS FOR LOW COST
 Reuse Technologies
First placed in Earth orbit
Salary
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17. AWARDS
Won US-based National Space Society’s 2015
Space Pioneer Award in the science and
engineering category.
Government of India decide to give a
Padmasree awards to Dr S K Shivakumar
(Director, ISRO Satellite Centre) and Shri S
Arunan (Project Director, ISRO's Mars Orbiter
Mission ).
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18. PRESENT STATUS
Its life expected to complete on March 24, 2015
will have an extended life due to less fuel
consumption.
ISRO scientist said “Spacecraft consume only
one kg of fuel out of 40 kg after the insertion into
Martian orbit so its life become longer definitely.”
MOM needs a 20 kg of fuel for six months and it
have more than that. It is controlled by ground
stations but during solar eclipse the MOM will
goes on autonomous mode and there is no control
over it. 18

19. 1. K. Radhakrishan – Chairman, ISRO
2. A. S. Kiran Kumar – Director, SAC
3. Mylswamy Annadurai – Programme Director, MOM
4. B. S. Chandrashekar – Director, ISTRAC
5. P. Robert – Operations Director, MOM
6. Subbiah Arunan – Project Director, MOM
7. V. Kesavaraju – Post-Launch Mission Director, MOM
8. P. Ekambaram – Operations Director, MOM
9. P. Kunhikrishnan – Launch Mission Director, PSLV-XL
10. S. K. Shivkumar – Orbiting payload Director, ISAC
11. B. Jayakumar – Launch Vehicle Director, PSLV
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20. BIBLIOGRAPHY
 http://en.wikipedia.org/wiki/Mars_Orbiter_Mission
 http://isro.gov.in/pslv-c25-mars-orbiter-mission
 http://www.spaceflight101.com/mars-orbiter-mission.html
 http://space.io9.com/indian-becomes-4th-country-to-reach-
mars-with-mangalyaa-1637844562
 http://isp.justthe80.com/planetary-exploration/mars-obiter
 http://en.wikipedia.org/wiki/Rover_%28space_exploration%29
 http://en.wikipedia.org/wiki/Lander_%28spacecraft%29#Mars
 The Times of India published on Feb. 11, 2015
 https://www.facebook.com/isromom
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21. Thank
you
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