Mangalyaan india's first MOM at first attempt, so over view of MOM, and brief explanation of instruments used in payload spacecraft, and phases of orbital transformation

1. Journey of Mangalyaan
India's First (MOM) Mars Orbiter Mission
PRESENTED BY
CH.PURUSHOTHAM
Aero
SCIENCEOFAERONAUTICS
AND
ENGINEERINGEDUCATIONTECHNICS
Department ofAeronauticalEngg.
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2. CONTENTS
MARS INTRODUCTION
WHY THIS JOURNEY ?
MISSION PLAN
MISSION OBJECTIVES
-TECHNOLOGICAL OBJECTIVES
- SCIENTIFIC OBJECTIVES
LAUNCH
-PSLV XL C25
SPACECRAFT
PAYLOADS
-LYMAN ALPHA PHOTOMETER (LAP)
-METHANE SENSER FOR MARS (MSM)
-MARS EXOSPHERIC NEUTRAL COMPOSITION ANALYSER (MENCA)
-THERMAL INFRARED IMAGING SPECTROMETER (TIS)
-MARS COLOR CAMERA (MCC)
MISSION PHASES or TRAJECTORY
-GEOCENTRIC PHASES
-HELIOCENTRIC PHASES
-MARTIAN PHASES
14 BRAINS BEHIND THE SUCCESS
COST EFFECTIVENESS COMPARE WITH OTHERE MISSION
TRACKING AND COMMAND
-INDIAN DEEP SPACE NETWORK (IDSN)
-INTERNATIONAL GROUND STATIONS
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3. Mars Introduction
Mars is the fourth planet from the Sun and is commonly referred to as the Red Planet. The
rocks, soil and sky have a red or pink hue. The distinct red color was observed by stargazers
throughout history. It was given its name by the Romans in honor of their god of war
Mars is the fourth planet from the sun and the second smallest planet in the solar system,
after Mercury. Named after the Roman god of war, it is often described as the “Red Planet"
because the iron oxide prevalent on its surface gives it a reddish appearance
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4. • Mars is the fourth planet from the sun.
• Mars is the seventh largest planet in our solar system.
• Mars is referred to as the Red Planet, due to its red soil made up of iron oxide,
more commonly known as rust.
• Mars is named after the Roman god of war.
• The equatorial Diameter of Mars is 6,805 km.
• The polar diameter of Mars is 6,755 km.
• The Diameter of Mars is 6,794 km
• Martian day = 24 hours 34 minutes and 22 seconds.
• Martian year = 687 Earth days.
• The mass of Mars is 641,850,000,000,000,000,000,000 kg.
• Surface temperature on Mars can range from the maximum of 310 K to a
minimum of 150 K.
• Atmospheric components on Mars consists of 95.32% carbon dioxide, 2.7%
nitrogen, 1.6% argon, 0.13% oxygen.
• Average Surface Temperature:218K (-53º C)
• Average Distance from Sun:2.279 x 108 km
• Average Density:3934 kg/m3
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5. • Moons of Mars = 2
1. Phobos – Diameter 22 km, orbit 5981 km from the surface of Mars.
2. Deimos - Diameter 12 km, orbit 20,062 km form the surface of Mars.
• Mars atmospheric pressure at surface = 6.35 mbar; > 100th Earth’s atmospheric
pressure
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6. Earth/Mars Comparison
Distance from Sun 2.279 x 108 km 149.6 Million km
Diameter 6,794 km 12,742 km
Length of Year 687 Earth Days 365.25 Days
Length of Day
24 hours 34 minutes
and 22 sec
23 hours 56 minutes and 4.1
sec
Gravity 0.375 that of Earth 2.66 times that of Mars
Temperature 218K (-53º C) 14°C
Temperature Range -127 º C to 17º C -88 º C to 58 º C
Number of Moons 2 1
Mars Earth
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8. Why this Journey?
In an interview, with The Hindu, Radhakrishnan to a question on what’s the most interesting on
Mars, he replies saying Life. So, we talk about Methane...which is of biological origin or
geological origin. So, we have a methane sensor plus a thermal infrared spectrometer. These two
together should be able to give some information.
He went on to say that “We want to look at environment of Mars for various elements like
Deuterium-Hydrogen ratio. We also want to look at other constituents — neutral constituent
After the Earth
Its soil contains water to extract
It isn’t too cold or too hot
There is enough sunlight to use solar panels
Gravity 1/3 or 38% our Earth's, be sufficient for the human body to adapt
Human speculation
The day/night a Mars day is 24 hours, 39 minutes and 35 seconds
687 Days year
Planet similar to earth
extraterrestrial life
scientists to expect life on Mars
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9. The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical
Parking Orbit with a perigee of 250 km and an apogee of 23,500 km. With six
Liquid Engine firing, the spacecraft is gradually maneuvered into a hyperbolic
trajectory with which it escapes from the Earth’s Sphere of Influence (SOI) and
arrives at the Mars Sphere of Influence.
When spacecraft reaches nearest point
of Mars (Peri-apsis), it is maneuvered
in to an elliptical orbit around Mars by
firing the Liquid Engine. The spacecraft
then moves around the Mars in an orbit
with Peri-apsis of 366 km and Apo-apsis
of about 80000 km.
Mission Plan
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10. MISSION OBJECTIVES
ISRO website stated that, one of the main objectives of the first Indian mission to Mars is to
develop the technologies required for design, planning, management and operations of an
interplanetary mission.
A. Technological Objectives:
1. 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.
2. Deep space communication, navigation, mission planning and management and incorporate
autonomous features to handle contingency situations.
B. Scientific Objectives:
1. Exploration of Mars surface features,
2. morphology,
3. mineralogy
4. and Martian atmosphere by indigenous scientific instruments.
5. Existence of life
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11. LAUNCH
-PSLV C25 XL
• The Polar Satellite Launch Vehicle (PSLV),
is an expendable launch system developed
and operated by the Indian Space Research
Organization (ISRO). It was developed to
allow India to launch its Indian Remote
Sensing (IRS) satellites into sun synchronous
orbits
• PSLV include India's first lunar
probe Chandrayaan-1, India's first
interplanetary mission Mangalyaan (Mars
orbiter) and India's first space
observatory Astrosat.
• PSLV-XL is the upgrated version of Polar
Satellite Launch Vehicle in its standard
configuration boosted by more powerful,
stretched strap-on boosters.
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12. Mangalyan
( Mars Orbiter Mission)
Specifications
 Date Of Announcement : 15 August 2012
 Date Of Launch : 5 November 2013
 Place Of Launch : SDSC (Sriharikota)
 Type Of Rocket Used : PSLV XL-C25.
 Type Of A Mission : Mars Orbiter Mission.
 Capability : (i) 4 stage vehicle
(ii) Multi orbital Capability
 Spacecraft Weight At Lift Off : 1337 Kg.
 Propellant Loaded : 852 Kg.
 Scientific Payload Weight : 15 Kg.
 Overall height : 44 m
 Diameter : 2.8 m
 Type Of Fuel Used : Solid/Liquid/Cryo Propellant.
 Mission Cost : 450 Cr INR.

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14. Mass
The lift-off mass was 1,350 kg , including 852 kg
of propellant mass.
Dimensions
Cuboid in shape of approximately 1.5 m .
Power
Electric power is generated by three solar
array panels of 1.8 × 1.4 m each. Electricity is
stored in a 36 Ah Li-ion battery.
Propulsion
Liquid fuel engine of 440 N thrust is used for
orbit raising and insertion in Martian orbit, and 8
numbers of 22 N thrusters are used for attitude
control .
Communications
Two 230 W TWTAs and two coherent
transponders. The antenna array consists of
a low-gain antenna, a medium-gain antenna and
a high-gain antenna.
SPACECRAFT
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16. PAYLOADS
Atmospheric studies
•Lyman-Alpha Photometer (LAP)
•Methane Sensor For Mars
(MSM)
Particle environment studies
Mars Exospheric Neutral
Composition Analyser (MENCA)
Surface imaging studies
•Thermal Infrared Imaging
Spectrometer (TIS)
•Mars Color Camera (MCC)
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17. LAP Lyman-Alpha Photometer 1.97 kg
MSM Methane Sensor For Mars 2.94 kg
MENCA Mars Exospheric Neutral Composition Analyser 3.56 kg
TIS Thermal Infrared Imaging Spectrometer 3.20 kg
MCC Mars Colour Camera 1.27 kg
The 15 kg (33 lb) scientific payload consists of five instruments:
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18. LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an
absorption cell photometer. It measures the
relative abundance of deuterium and hydrogen
from lyman-alpha emission in the Martian
upper atmosphere (typically Exosphere and
exobase). Measurement of D/H (Deuterium to
Hydrogen abundance Ratio) allows us to
understand especially the loss process of water
from the planet.
The objectives of this instrument are as follows:
Estimation of D/H ratio
Estimation of escape flux of H2 corona
Generation of Hydrogen and Deuterium coronal profiles
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19. Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4)
in the Martian atmosphere with PPB accuracy
and map its sources. Data is acquired only over
illuminated scene as the sensor measures
reflected solar radiation. Methane
concentration in the Martian atmosphere
undergoes spatial and temporal variations.
Specific areas of interest:
1.Algorithm development for Methane detection in atmosphere of Mars
2.Mars reflectance changes due to dynamic atmosphere using MSM
3.Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM
spectrum
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20. Mars Exospheric Neutral Composition Analyser
(MENCA)
MENCA is a quadruple mass spectrometer
capable of analyzing the neutral composition in
the range of 1 to 300 amu(atomic mass unit) with
unit mass resolution.
Specific areas of interest:
1.Exopsheric composition of Mars
2.Atmospheric escape from Mars
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21. Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be
operated during both day and night. Temperature
and emissivity are the two basic physical
parameters estimated from thermal emission
measurement. Many minerals and soil types have
characteristic spectra in TIR region. TIS can map
surface composition and mineralogy of Mars.
Specific areas of interest:
1.Algorithm development for analysis of TIS data
2.Inversion of surface temperature of Mars using TIS data
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22. Specific areas of interest:
1.Geomorphology and morphometric analysis of martian volcanoes
2.Geomorphology and morphometric analysis of fluvial landforms
3.Aeolian processes on Mars
4.Dust storms
5.Dust devils
6.Wind streaks
7.Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)
This tri-color Mars color camera gives
images & information about the surface
features and composition of Martian
surface. They are useful to monitor the
dynamic events and weather of Mars. MCC
will also be used for probing the two
satellites of Mars-Phobos & Deimos. It also
provides the context information for other
science payloads.
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24. Mission Phases or Trajectory
Mars is to develop the technologies required for design, planning, management and
operations of an interplanetary mission.
A. Geocentric Phases
 The spacecraft is injected into Elliptical parking orbit by the launcher
 ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars
 Six main engines burns in this phase for six mid night maneuvers.
 At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI).
Earth SOI is 918347.
B. Heliocentric Phases
 Spacecraft enters into Mars tangential orbit
 This Phase depends on relative position of Earth, Mars and Sun
 Such relative arrangement recur periodically at interval of about 780 days.
C. Martian Phases
 The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars]
 At the time of spacecraft reaches the closest approach to Mars, It is captured into planed
orbit around Mars.
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25. Earth Parking Orbit
It would be extremely challenging to schedule launches so that they happened at
precisely the right time to launch a spacecraft directly from the pad into a
trajectory to an external body, like the ISS, the Moon, or Mars. It might even be
impossible for particular launch locations to do that.
So, instead, a spacecraft is launched into a stable orbit and the spacecraft then
goes around the Earth, in that orbit, until the timing and geometry are right to fire
its engine again, initiating a trajectory to its target. That temporary orbit is called
a parking orbit.
Perform checks of the following systems:
􀂾 Biomedical & safety equipment
􀂾 Environmental control system
􀂾 Comm & instrumentation system
􀂾 Electrical power system (EPS)
􀂾 Stabilization and control system (SCS)
􀂾 Crew equipment system
􀂾 SM propulsion system (SPS)
􀂾 SM reaction control system (RCS)
􀂾 Command Module Computer optics
􀂾 Entry monitoring system (EMS)
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27. In order to achieve the
velocity required to
escape the earth’s
gravity(escape
velocity), 6 orbit
raising manoeuvers
were performed on 6th,
7th, 8th, 10th, 11th and
15th November.
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 PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit )
 Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits )
 LEO Perigee : 240 Km LEO Apogee : 24000 Km
 Orbit increment was done when the satellite was at the perigee point
 It has undergone through Orbit Raising Maneuver 5 times
 Final Apogee : 193000 Km Corresponding Speed Of Satellite : ~ 11 Km/sec

28. With six Liquid Engine firing, the spacecraft is
gradually maneuvered into a hyperbolic trajectory
with which it escapes from the Earth’s Sphere of
Influence (SOI) and arrives at the Mars Sphere of
Influence.
The spacecraft then embarked on its 10-month,
670 million kms long journey towards Mars
On 30th November
2013, the engines
of MOM were
fired for 23
minutes.
The earth’s escape
velocity was
achieved by MOM
and the spacecraft
left the earth’s
orbit.
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29. The orbit of MOM around Mars is highly elliptical with periapsis ~370 km
and apoapsis ~80000 km, inclination 151 degree, and orbital period 3.15 sols.
The spacecraft mass is 1350 kg, with dry mass of 500 kg and science payload
mass of 14 kg 29

30. • launch will place from sriharikota and the Mars Orbiter will be placed into Earth
orbit, then six engine firings will raise that orbit to one with an apogee of 215,000
km and a perigee of 600 km, where it will remain for about 25 days.
• A final firing in 30 November 2013 will send MOM onto an interplanetary
trajectory.
• Mars orbit insertion is planned for 21 September 2014 and would allow the
spacecraft to enter a highly elliptical orbit of 422 km x 77,000 km around Mars.
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31. The government of India approved the project on 3 august 2012, after the Indian Space
Research Organization completed 125 crore of required studies for the orbiter. The total
project cost may be up to 454 crore . The satellite costs 153 crore and the rest of the budget
has been attributed to ground stations and relay upgrades that will be used for other ISRO
projects.
MISSION COST
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32. TRACKING AND COMMAND
-INDIAN DEEP SPACE NETWORK (IDSN)
-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry, Tracking and Command
Network(ISTTCN) performed navigation and tracking operations for the launch
with ground stations at Sriharikota, Port Blair, Brunei and Biak in Indonesia, and
after the spacecraft's apogee becomes more than 100,000 km, two large 18-metre and
32-metre diameter antennas of the Indian Deep Space Network will be utilised.
NASA's Deep Space Network will provide position data through its three stations
located in Canberra, Madrid and Goldstone on the U.S. West Coast during the non-
visible period of ISRO's network.
The South African National Space Agency's (SANSA) Harte beesthoek (HBK)
ground station is also providing satellite tracking, telemetry and command services.
Additional monitoring is provided by technicians on board two leased ships from the
Shipping Corporation of India, SCI Nalanda and SCI Yamuna which are currently in
position in the South Pacific.
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33. • The radio waves (to be more precise, in the case
microwaves) travelling at the speed of
light(300,000km/s) take 10minutes to travel from
Earth to a spacecraft orbiting Mars.
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34. Phobos, one of the two natural
satellites of Mars silhouetted against
the Martian surface
Taken using the Mars Colour Camera
from an altitude of 8449 km
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35. Regional dust storm activities over
Northern Hemisphere of Mars -captured
by MCC 35

36. 1. K. Radhakrishan – Chairman, ISRO
2. M. Annadurai – Programme Director, MOM
3. S Ramakrishnan - Director of Vikram Sarabhai Space Centre
4. S. K. Shivkumar – Orbiting payload Director, ISAC
5. V Adimurthy - Mission Concept Designer of Mars Orbiter Mission.
6. P. Kunhikrishnan – Launch Mission Director, PSLV-XL
7. Chandradathan - Director of the Propulsion Systems
8. A.S. Kiran Kumar – Director, SAC
9. MYS Prasad – Director, SDSC and chairman Launch Authorisation
Board
10. S. Arunan – Project Director, MOM
11. B. Jayakumar – Launch Vehicle Director, PSLV
12. MS. Pannirselvam - : The chief general manager of range operation
director
13. V. Kesavaraju – Post-Launch Mission Director, MOM
14. B. S. Chandrashekar – Director, ISTRAC
15. P. Robert – Operations Director, MOM
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37. K. Radhakrishan
Chairman, ISRO
M. Annadurai
Progr Director, MOM
S Ramakrishnan
Director,VSSC
S. K. Shivkumar
Orbiting payload Director,
ISAC
V Adimurthy
Mission Concept
Designer(MOM)
P. Kunhikrishnan
Launch Mission Director,
PSLV-XL
Madhavan Chandradathan
Director, Propulsion Systems
VSSC
A.S. Kiran Kumar
Director, SAC
S. Arunan
Project Director,
MOM
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38. CONCLUSION
 The success of Mangalyaan showed world nations
Indian and ISRO superiority in the space technology.
 The primary objective of the Mars Orbiter Mission is to
showcase India's rocket launch systems, spacecraft-
building and operations capabilities.
THANKYOU…
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