complete over view of MOM some additional point to add this documents

1. SCIENCE OF AERONAUTICS
AND
ENGINEERING EDUCATIONAL TECHNICS
CH. PURUSHOTHAM
AERONAUTICAL ENGG.
Journey of Mangalyaan
India's First (MOM) Mars Orbiter Mission
DEPARTMENT OF AERONAUTICAL ENGINEERING

2. CHAPTERS
1. MARS INTRODUCTION
1.1 ATMOSPHERE
1.2 TEMPERATUREAND PRESSURE
2. MARS SPECIFICATION
2.1 EARTH/MARS COMPARISON
2.2 INSIDE PLANET MARS
3. WHY THIS JOURNEY?
4. MISSION PLAN
5. MISSION OBJECTIVES
5.1 TECHNOLOGICAL OBJECTIVES
5.2 SCIENTIFIC OBJECTIVES
5.3 THE DEUTERIUM/HYDROGEN (D/H) RATIO
6. POLAR SATELLITE LAUNCH VEHICLE
6.1 PSLV-XL (Operational)
6.2 PSLV C25
6.3 TECHNICAL SPECIFICATIONS
6.4 DIFFERENT STAGES OF PSLV
7. SPACECRAFT
8. PAYLOADS
8.1 LYMAN ALPHA PHOTOMETER (LAP)
8.2 METHANE SENSER FOR MARS (MSM)
8.3 MARS EXOSPHERIC NEUTRAL
COMPOSITIONANALYSER (MENCA)
8.4 THERMAL INFRARED IMAGING SPECTROMETER
(TIS)
8.5 MARS COLOR CAMERA (MCC)
9. MISSION PHASES or TRAJECTORY
9.1 GEOCENTRIC PHASES
9.2 HELIOCENTRIC PHASES
9.3 MARTIAN PHASES
9(a) EARTH PARKING ORBIT
10. TRACKING AND COMMAND
11. COST COMPARE WITH OTHERE MISSION
12. 14 BRAINS BEHIND THE SUCCESS
13. CONALUSION
14. REFERENCE

3. ABSTRACT
India made history by becoming the first country in the world to enter the Martian orbit in its
maiden attempt. The Indian Space Research Organisation (ISRO) successfully inserted the
Mars Orbiter Mission (MOM) into mars orbit. MOM is the first interplanetary mission of
India launched by Indian Polar Satellite Launch Vehicle (PSLV-XL), it is the fifth in world
travel journey toward Mars or Red Planet. Interplanetary missions are susceptible to
gravitational and non-gravitational perturbing forces at every trajectory phase. These forces
are mainly due to planetary and solar-forcing-induced perturbations during geocentric,
heliocentric and Martian trajectories, and before orbit insertion. Mission Goal and Objectives
is to develop the technologies required for design, planning, management and operations of
an interplanetary mission.
The spacecraft carries five science payloads, namely: Methane Sensor for Mars (MSM), Mars
Colour Camera (MCC), Lyman Alpha Photometer (LAP), Mars Exospheric Neutral
Composition Analyzer (MENCA), TIR Imaging Spectrometer (TIS).
The knowledge is important for mission planning, design, implementation and situational
awareness. 14 brains behind Mangalyaan success. This paper will present the details of the
why this journey? Study the Martian atmosphere, instruments, observation plan, and expected
science.

4. 1. 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. Other
civilizations have had similar names. The ancient Egyptians named the planet Her
Descher meaning the red one.
Before space exploration, Mars was considered the best candidate for harboring
extraterrestrial life. Astronomers thought they saw straight lines crisscrossing its surface. This
led to the popular belief that irrigation canals on the planet had been constructed by
intelligent beings. In 1938, when Orson Welles broadcasted a radio drama based on the
science fiction classic War of the Worlds by H.G. Wells, enough people believed in the tale
of invading Martians to cause a near panic.
Fig 1: Solar system
Another reason for scientists to expect life on Mars had to do with the apparent seasonal color
changes on the planet's surface. This phenomenon led to speculation that conditions might
support a bloom of Martian vegetation during the warmer months and cause plant life to
become dormant during colder periods.
In July of 1965, Mariner 4, transmitted 22 close-up pictures of Mars. All that was revealed
was a surface containing many craters and naturally occurring channels but no evidence of
artificial canals or flowing water. Finally, in July and September 1976, Viking Landers 1 and
2 touched down on the surface of Mars. The three biology experiments aboard the landers
discovered unexpected and enigmatic chemical activity in the Martian soil, but provided no
clear evidence for the presence of living microorganisms in the soil near the landing sites.
According to mission biologists, Mars is self-sterilizing. They believe the combination of
solar ultraviolet radiation that saturates the surface, the extreme dryness of the soil and the
oxidizing nature of the soil chemistry prevent the formation of living organisms in the
Martian soil. The question of life on Mars at some time in the distant past remains open.

5. Other instruments found no sign of organic chemistry at either landing site, but they did
provide a precise and definitive analysis of the composition of the Martian atmosphere and
found previously undetected trace elements.
1.1Atmosphere
The atmosphere of Mars is quite different from that of Earth. It is composed primarily of
carbon dioxide with small amounts of other gases. The six most common components of the
atmosphere are:
 Carbon Dioxide (CO2): 95.32%
 Nitrogen (N2): 2.7%
 Argon (Ar): 1.6%
 Oxygen (O2): 0.13%
 Water (H2O): 0.03%
 Neon (Ne): 0.00025 %
Martian air contains only about 1/1,000 as much water as our air, but even this small amount
can condense out, forming clouds that ride high in the atmosphere or swirl around the slopes
of towering volcanoes. Local patches of early morning fog can form in valleys. At the Viking
Lander 2 site, a thin layer of water frost covered the ground each winter.
There is evidence that in the past a denser martian atmosphere may have allowed water to
flow on the planet. Physical features closely resembling shorelines, gorges, riverbeds and
islands suggest that great rivers once marked the planet.
1.2 Temperature and Pressure
The average recorded temperature on Mars is -63° C (-81° F) with a maximum temperature
of 20° C (68° F) and a minimum of -140° C (-220° F).
Barometric pressure varies at each landing site on a semiannual basis. Carbon dioxide, the
major constituent of the atmosphere, freezes out to form an immense polar cap, alternately at
each pole. The carbon dioxide forms a great cover of snow and then evaporates again with the
coming of spring in each hemisphere. When the southern cap was largest, the mean daily
pressure observed by Viking Lander 1 was as low as 6.8 millibars; at other times of the year it
was as high as 9.0 millibars. The pressures at the Viking Lander 2 site were 7.3 and 10.8
millibars. In comparison, the average pressure of the Earth is 1000 millibars.

6. 2. Mars Specification:
• 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
• Moons of Mars = 2
Phobos – Diameter 22 km, orbit 5981 km from the surface of Mars.
Deimos - Diameter 12 km, orbit 20,062 km from the surface of Mars.
• Mars atmospheric pressure at surface = 6.35 mbar; < 100th Earth’s atmospheric
pressure
Fig 2: Moons of Mars

7. Mars Statistics
Mass (kg) 6.421e+23
Mass (Earth = 1) 1.0745e-01
Equatorial radius (km) 3,397.2
Equatorial radius (Earth = 1) 5.3264e-01
Meandensity (gm/cm^3) 3.94
Meandistance from the Sun (km) 227,940,000
Meandistance from the Sun (Earth = 1) 1.5237
Rotational period (hours) 24.6229
Rotational period (days) 1.025957
Orbital period (days) 686.98
Meanorbital velocity (km/sec) 24.13
Orbital eccentricity 0.0934
Tilt of axis (degrees) 25.19
Orbital inclination (degrees) 1.850
Equatorial surface gravity (m/sec^2) 3.72
Equatorial escape velocity (km/sec) 5.02
Visual geometric albedo 0.15
Magnitude (Vo) -2.01
Minimum surface temperature -140°C
Meansurface temperature -63°C
Maximum surface temperature 20°C
Atmospheric pressure (bars) 0.007
Atmospheric composition
Carbon Dioxide (C02)
Nitrogen (N2)
Argon (Ar)
Oxygen (O2)
Carbon Monoxide (CO)
Water (H2O)
Neon (Ne)
Krypton (Kr)
Xenon (Xe)
Ozone (O3)
95.32%
2.7%
1.6%
0.13%
0.07%
0.03%
0.00025%
0.00003%
0.000008%
0.000003%
Table 1: Mars Statistics

8. 2.1 Earth/Mars Comparison
Mars Earth
In solarsystem 4th planet 3rd planet
Distance from sun 227,936,637 km 149,597,891 km
Diameter 6,794 km 12,742 km
Equatorial Radius 3,397 km 6,378 km
Mass 6.418 x 10^23 kg 5.972 × 10^24 kg
Length of Day 24 hours, 37 minutes and
22 seconds
23 hours 56 minute and 4.1 sec
Length of Year 687 Earth days 365 days
LargestVolcano Olympus Mons
26 km high
602 km in diameter
Mauna Loa(Hawaii)
10.1 km high
121 km in diameter
Gravity 0.375 that of Earth 2.66 times that of Mars
Tilt of Axis 25° 23.45°
Atmosphere
(Composition)
Carbon dioxide (95.32%)
Nitrogen (2.7%)
Argon (1.6%)
Oxygen (0.13%)
Water vapour (0.03%)
Nitric oxide (0.01%)
Carbon dioxide (0.038%)
Nitrogen (77%)
Argon (1%)
Oxygen (21%)
Water vapour (1%)
Atmosphere
(Pressure)
7.5 millibars
(average)
1,013 millibars
(at sea level)
Temperature 218 K(-63º C) 287 K (14°C)
Temperature Range -127°C to 17°C -88°C to 58°C
Number of Moons 2
(Phobos and Deimos)
1
(Moon)
PolarCaps Covered with a mixture
of carbon dioxide ice and
water ice
Permanently covered with
water ice
Average density 3.93 g/cm³ 5.51 g/cm³
Table 2: Earth/Mars Comparison

9. Fig 2.2: Inside Planet MARS
3. 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

10. 4. Mission Plan
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.
Fig 4: Mission Plan
5. 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.
5.1. 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.
5.2. Scientific Objectives:
1. Exploration of Mars surface features,
2. morphology,
3. mineralogy
4. and Martian atmosphere by indigenous scientific instruments.
5. Existence of life

11. 5.3 The deuterium/hydrogen ratio
One measurement of particular interest is the ratio of deuterium to hydrogen (D/H ratio) in
cometary water.
Fig 5.3(a): Hydrogen atom. Fig 3.5 (b): Deuterium atom.
Hydrogen is the simplest atom, with one electron in orbit around a nucleus of one proton.
Deuterium is an isotope of hydrogen, in which the nucleus also has one neutron. Chemical
compounds that contain hydrogen also come in versions made with deuterium.
Water that contains deuterium is known as "heavy water." Earth's oceans contain a
characteristic percentage of heavy water. So do comets, which are mostly water, and some of
the other planets and moons.
Knowing the D/H ratio of water and other substances is useful to scientists for two basic
reasons.
First, it acts as a fingerprint. By comparing the D/H ratios in Earth's water with that in
cometary water, for example, scientists can determine whether our planet's water could have
come from comets. The same determination can be made for other planets and moons in the
solar system.
Second, the D/H ratio in comets provides a clue to conditions at the beginning of the
Universe!
Scientists think the D/H ratio of pristine comets represents that of our original nebula, which
in turn is typical of the rest of the Universe. And all of the hydrogen and deuterium in the
Universe is thought to have formed during the first three minutes after the Big Bang (the
nuclei, that is - stable atoms didn't develop for another 300,000 years or so), so the D/H ratio
of the Universe was fixed in place at that time.

12. Knowing that ultimate D/H ratio would help scientists determine the conditions that could
have generated hydrogen and deuterium in that particular ratio, and therefore help them
deduce the nature of the Universe in its earliest stages.
Mars
Understanding the atmospheric chemistry of Mars is
important both for an understanding of Mars' history -
including the possibility that it was more like Earth in its
earlier days - and as a tool for comparing how atmospheres
differ on different planets. Such studies may provide insights
into the workings and possible future of our own atmosphere
here on Earth.
Herschel has explored the Martian atmosphere in the 200-670
micron range for the first time, enabling scientists to
determine the vertical profiles of water vapor and oxygen molecules. Monitoring water at
various times during the Martian year has revealed seasonal changes.
Herschel has also measured deuterium and carbon monoxide, and may detect other
compounds, such as hydrogen peroxide, that are predicted by models of Martian
photochemistry.
Finally, Herschel has obtained information about the composition and emissivity of minerals
covering Mars' surface.
Fig: Mars.

13. 6. Polar Satellite Launch Vehicle
The Polar Satellite Launch Vehicle (Hindi: ध्रुवीय उपग्रह प्रक्षेपण यान), commonly known by
its abbreviation PSLV, is an expendable launch system developed and operated by the Indian
Space Research Organisation (ISRO). It was developed to allow India to launch its Indian
Remote Sensing (IRS) satellites into Sun synchronous orbits(SSO), a service that was, until
the advent of the PSLV, commercially available only from Russia. PSLV can also launch
small size satellites into geostationary transfer orbit (GTO).
PSLV – The Polar Satellite Launch Vehicle is an Indian expendable launch system developed
and operated by the Indian Space Research Organisation. The launch vehicle is a medium lift
launcher that can reach a variety of orbits including Low Earth Orbit, Polar Sun Synchronous
Orbit and Geosynchronous Transfer Orbit. PSLV is operated from the Satish Dhawan Space
Center located in Sriharikota on India’s East coast.
PSLV is a four-stage rocket that uses a combination of liquid fueled and solid fueled rocket
stages. The vehicle can fly in three different configurations to adjust for mission
requirements.
The Polar Satellite Launch Vehicle features six Strap-on Solid Rocket Boosters clustered
around its first stage which itself is also solid-fueled. The second stage is liquid fueled while
the third stage is a solid rocket motor. The Upper Stage of the PSLV uses liquid Propellant.
The launcher stands 44.4 meters tall and has a diameter of 2.8 meters. Depending on the
launcher’s configuration, PSLV weighs 229,000, 296,000 or 320,000 Kilograms.
In addition to the ‘regular’ PSLV version, it can fly in its Core Alone configuration, without
the six Solid Rocket Boosters and less propellant in the tanks of its upper stage – a
configuration used for missions that feature small payloads.
PSLV can also fly in a XL Version that launches with additional propellant in its Solid
Rocket Boosters to increase payload capability.
Type PSLV
Versions Regular,Core Alone,XL
Height 44.5m
Diameter 2.8m
Launch Mass 229,000kg (CA) to 320,000kg (XL)
Mass to LEO 3,250kg
Mass to GTO 1,410kg
Mass to SSO 1,600kg – XL: 1,800kg – CA:1,100kg
In the year 2015 alone India successfully launched 17 foreign satellites belonging to Canada,
Indonesia, Singapore, the UK and the United States. Some notable payloads launched by
PSLV include India's first lunar probe Chandrayaan-1, India's first interplanetary
mission Mangalyaan (Mars orbiter) and India's first space observatory Astrosat.

14. 6.1 PSLV-XL (Operational)
PSLV-XL is the up rated version of Polar Satellite Launch Vehicle in its standard
configuration boosted by more powerful, stretched strap-on boosters. Weighing 320 tonnes at
lift-off, the vehicle uses larger strap-on motors (PSOM-XL) to achieve higher payload
capability. PSOM-XL uses larger 1-metre diameter, 13.5m length motors, and carries 12
tonnes of solid propellants instead of 9 tonnes used in the earlier configuration of PSLV. On
29 December 2005, ISRO successfully tested the improved version of strap-on booster for the
PSLV. The first version of PSLV-XL was the launch of Chandrayaan-1 by PSLV-C11. The
payload capability for this variant is 1800 kg compared to 1600 kg for the other
variants. Other launches include the RISAT Radar Imaging Satellite andGSAT-12
6.2 PSLV-C25
PSLV-C25, twenty fifth flight of PSLV will launch Mars Orbiter Mission Spacecraft from the
First Launch Pad at Satish Dhawan Space Centre SHAR, Sriharikota.
Fig 6.2: PSLV XL C25 Launch clip
The challenging PSLV-C25 mission is optimised for the launch of Mars Orbiter Mission
spacecraft into a highly elliptical Earth orbit with a perigee (nearest point to Earth) of 250 km
and an apogee (farthest point to Earth) of 23,500 km with an inclination of 19.2 degree with
respect to the equator.

15. PSLV- C25 Stages at a Glance
Propellant STAGE-1 PSOM-XL STAGE-2 STAGE-3 STAGE-4
Solid
(HTPB
Based)
Solid
(HTPB
Based)
Liquid
(UH25 + N2O4)
Solid
(HTPB Based)
Liquid
(MMH + MON-3)
Propellant Mass (Tonne) 138 12.2 42 7.6 2.5
Peak Thrust (kN) 4800 718 799 247 7.3 X 2
Burn Time (sec) 103 50 148 112 525
Diameter (m) 2.8 1 2.8 2.0 2.8
Length (m) 20 12 12.8 3.6 2.7
Table 6: PSLV-C25 Stages at a Glance
POLAR SATELLITE LAUNCH VEHICLE
About the Launch Vehicle
The PSLV is one of world's most reliable launch vehicles. It has been in service for over twenty years
and has launched various satellites for historic missions like Chandrayaan-1, Mars Orbiter Mission,
Space Capsule Recovery Experiment, Indian Regional Navigation Satellite System (IRNSS) etc.
PSLV remains a favourite among various organisations as a launch service provider and has launched
over 40 satellites for 19 countries. In 2008 it created a record for most number of satellites placed in
orbit in one launch by launching 10 satellites into various Low Earth Orbits.
Vehicle Specifications
Height : 44 m
Diameter : 2.8 m
Number of Stages : 4
Lift Off Mass : 320 tonnes (XL)
Variants : 3 (PSLV-G, PSLV - CA, PSLV - XL)
First Flight : September 20, 1993

16. 6.3 TECHNICAL SPECIFICATIONS
Payload to SSPO: 1,750 kg
PSLV earned its title 'the Workhorse of ISRO' through consistently delivering
various satellites to Low Earth Orbits, particularly the IRS series of satellites. It
can take up to 1,750 kg of payload to Sun-Synchronous Polar Orbits of 600 km
altitude.
Payload to Sub GTO: 1,425 kg
Due to its unmatched reliability, PSLV has also been used to launch various
satellites into Geosynchronous and Geostationary orbits, like satellites from the
IRNSS constellation.
Fourth Stage: PS4
The PS4 is the uppermost stage of PSLV, comprising of two Earth storable liquid
engines.
Engine : 2 x PS-4
Fuel : MMH + MON
Max. Thrust : 7.6 x 2 kN
Third Stage: PS3
The third stage of PSLV is a solid rocket motor that provides the upper stages high
thrust after the atmospheric phase of the launch.
Fuel : HTPB
Max. Thrust : 240 kN
Second Stage: PS2
PSLV uses an Earth storable liquid rocket engine for its second stage, know as the
Vikas engine, developed by Liquid Propulsion Systems Centre.
Engine : Vikas
Fuel : UDMH + N2O4
Max. Thrust : 799 kN
First Stage: PS1
PSLV uses the S139 solid rocket motor that is augmented by 6 solid strap-on
boosters.
Engine : S139
Fuel : HTPB
Max. Thrust : 4800 kN
Strap-on Motors
PSLV uses 6 solid rocket strap-on motors to augment the thrust provided by the first stage
in its PSLV-Gand PSLV-XL variants. However,strap-ons are not used in the core alone
version (PSLV-CA).
Fuel : HTPB
Max. Thrust : 719 kN

17. 6.4 DIFFERENT STAGES OF PSLV
The first stage uses a 2.8 meter diameter, 20 meter long, 472 ton thrust solid motor that burns
138 tons of propellant for 107 seconds. The first stage is augmented by six solid strap-on
boosters that produce 67.5 tons of thrust each for 45 seconds. Four of the strap-on boosters
ignite at liftoff. The two air-start strap-ons ignite 25 seconds after liftoff. The strap-on
boosters are jettisoned after burn-out. More powerful "XL" boosters carrying 12 tones of
propellant and producing up to 73.4 tones of thrust debuted in 2008. PSLV's 12.5 x 2.8 m PS-
2 second stage is powered by a 73.9 ton-thrust Viking 4 engine that burns unsymmetrical
dimethyl hydrazine fuel and nitrogen tetroxide ((N2O4) oxidizer for 162 seconds. Viking 4,
called "Vikas" by ISRO, was originally built by Europe's SEP for the Ariane 1 launch
vehicle. The third stage is another 2.8 meter diameter solid motor. It burns 7.6 tons of
propellant for 109 seconds, producing 33.5 tons of thrust. The fourth and final stage is a twin-
engine liquid propulsion system that is housed within the payload fairing below the satellite.
It burns 2.5 tons of mono-methyl hydrazine fuel and nitrogen tetroxide (N2O4) oxidizer. The
1.43 ton thrust stage can burn for up to 420 seconds
Fig 6.4: Important elements of PSLV

18. 7. SPACECRAFT
Mars Orbiter Mission is India's first interplanetary mission to planet Mars with an orbiter
craft designed to orbit Mars in an elliptical orbit. The Mission is primarily technological
mission considering the critical mission operations and stringent requirements on propulsion
and other bus systems of spacecraft. It has been configured to carry out observation of
physical features of mars and carry out limited study of Martian atmosphere with following
five payloads:
 Mars Colour Camera (MCC)
 Thermal Infrared Imaging Spectrometer (TIS)
 Methane Sensor for Mars (MSM)
 Mars Exospheric Neutral Composition Analyser (MENCA)
 Lyman Alpha Photometer (LAP)
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.
Fig 7: Spacecraft

19. Lift-off Mass 1337 kg
Structures Aluminum and Composite Fiber Reinforced Plastic (CFRP)
sandwich construction-modified I-1 K Bus
Mechanism Solar Panel Drive Mechanism (SPDM), Reflector & Solar panel
deployment
Propulsion Bi propellant system (MMH + N2O4) with additional safety and
redundancy features for MOI. Proplellant mass:852 kg
Thermal System Passive thermal control system
Power System Single Solar Array-1.8m X 1.4 m - 3 panels - 840 W Generation (in
Martian orbit), Battery:36AH Li-ion
Attitude and Orbit
Control System
AOCE (Attitude and Orbit Control Electronics): with MAR31750
Processor
Sensors: Star sensor (2Nos), Solar Panel Sun Sensor (1No), Coarse
Analogue Sun Sensor
Actuators: Reaction Wheels (4Nos), Thrusters (8Nos), 440N Liquid
Engine
Antennae: Low Gain Antenna (LGA), Mid Gain Antenna (MGA) and High
Gain Antenna (HGA)
Launch Date Nov 05, 2013
Launch Site SDSC SHAR Centre, Sriharikota, India
Launch Vehicle PSLV - C25
Table 7: Spacecraft
8. Payloads
The Mars Orbiter Mission carries five payloads to accomplish its scientific objectives. Three
electro-optical payloads operating in the visible and thermal infra-red spectral ranges and a
photometer to sense the Mars atmosphere & surface. One additional backup payload is
planned in case of non-availability of the identified payloads.
 Atmospheric studies
• Lyman-Alpha Photometer (LAP)
• Methane Sensor ForMars (MSM)
 Particle environment studies
• Mars Exospheric Neutral Composition Analyser(MENCA)
 Surface imaging studies
• Thermal Infrared Imaging Spectrometer (TIS)
• Mars Color Camera (MCC)
The 15 kg (33 lb) scientific payload consists of five instruments

20. 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
Fig 8: MOM Spacecraft Payload location
8.1 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 Fig 8.1: LAP
Specific areas of interest:
1. Atmospheric escape process addressing especially water loss mechanisms in Martian
exosphere.
2. Algorithm realization, code development and construction of a Far Ultra-violet
wavelength model of radiative transfer for the Mars exosphere from 250 km onwards.
3. Models addressing isotopic fractionation and enrichment of deuterium.
4. Assessment of Martian atmospheric escape process, especially water escape rate using
the measured Hydrogen, deuterium fluxes and estimated D/H ratio.
5. Combined analysis of LAP and MENCA data to assess the hydrogen atomic density
and distribution in Martian exosphere.
6. Integrated studies of LAP payload data with other international Mars missions.

21. 8.2 Methane Sensorfor 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. Hence global data is collected during
every orbit.
Specific areas of interest: Fig 8.2: MSM
1. Algorithm development for Methane detection in atmosphere of Mars
2. Mars reflectance changes due to dynamic atmosphere using MSM
3. Radiative transfer modeling in VNIR part of EM
spectrum
8.3 Mars Exospheric Neutral CompositionAnalyser
(MENCA)
MENCA is a quadruple mass spectrometer capable of analysing the
neutral composition in the range of 1 to 300 amu with unit mass
resolution. The heritage of this payload is from Chandra’s Altitudinal
Composition Explorer (CHANCE) payload aboard the Moon Impact
Probe (MIP) in Chandrayan-1 mission.
Specific areas of interest: Fig 8.3: MENCA
1. Exopsheric composition of Mars
2. Atmospheric escape from Mars.
8.4 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: Fig 8.4: TIS
1. Algorithm development for analysis of TIS data
2. Inversion of surface temperature of Mars using TIS data
8.5 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.

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
a. Study of genesis and direction of wind streaks on Mars
b. Dark streaks
c. Bright streaks
d. Other streaks
7. Dunes
a. Dune movement
b. Modeling Wind speeds and directions
8. Combined analysis of MCC and MSM data to study dust storms, dust devils, cloud
heights etc.
9. Understanding the process geomorphology of canyons, gullies and outflow channels
present on Mars
10. Photometric correction of MCC
11. Crater Size Frequency Distribution (CSFD) for surface age detection and geological
mapping
12. Surface change detection by comparative analysis of MCC data with international
datasets
13. International sensor data comparison and data merging for geomorphological and
mineralogical studies
14. Study of geomorphology of Mars with terrestrial analogues
9. Mission Phases or Trajectory
Mars is to develop the technologies required for design, planning, management and
operations of an interplanetary mission
9.1 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.
9.2 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.

23. 9.3 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
9(a) 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)
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.

24. Fig 9.1: Geocentric Phases
 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
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.

25. Fig 9.2: Heliocentric Phases
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
Fig 9.2.1 : six engine firing at the end of heliocentric phases

26. Fig 9.2.2: Mangalyaan Trajectrory
• 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
• 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

27. Fig 9.2.3: overall three phases
10. TRACKING AND COMMAND
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.
ISRO Telemetry Tracking and Command Network (ISTRAC) will be providing support of
the TTC ground stations, communications network between ground stations and control
center, Control center including computers, storage, data network and control room facilities,
and the support of Indian Space Science Data Center (ISSDC) for the mission. The ground
segment systems form an integrated system supporting both launch phase, and orbital phase
of the mission

28. The South African National Space Agency's (SANSA) Hartebeesthoek (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.
Fig 10.1: Shipping Corporation Fig 10.2: Indian DeepSpace networking
The radio waves (to be more precise, in the case microwaves) travelling at the
speedof light(300,000km/s) take 10minutes to travel from Earth to a spacecraft
orbiting Mars.

29. 11. MISSION COST
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.
Fig 11: Mission Cost
12. 14 Brains behind the success
We bring you the 14 brains behind Mangalyaan who helped put India in the elite club.
1. K Radhakrishnan: He is the chairman of
ISRO and secretary, department of space. The
65-year-old avionic engineer graduated in
engineering from Kerala University in 1970.
Radhakrishnan also has an MBA degree from
IIM-Bangalore and he also got a doctorate from
IIT-Kharagpur. Besides being a top space
scientist, Radhakrishnan is an enthusiast of
Kerala's classical art form Kathakali and a keen
music lover. He received a Padma Bhushan in
2014.

30. 2. M Annadurai: He is the
programme director of Mars Orbiter
Mission. Mylswamy Annadurai joined
Isro in 1982 and was the project director
for Chandrayaan I, Chandrayaan II,
ASTROSTAT, Aditya -I and the Mars
Obiter Mission. Annadurai and his
works are mentioned in the 10th
standard Science Text Book of Tamil
Nadu. Born in Kodhawady near Pollachi
in Coimbatore district of Tamil Nadu, Annadurai has been leading many Remote Sensing and
Science missions at ISRO.
3. S Ramakrishnan: Director of Vikram
Sarabhai Space Centre and Member Launch
Authorisation Board. A senior Isro scientist
has more than four decades of experience in
rocketry in the Indian space programme.
Joined ISRO in the August of 1972,
Ramakrishnan played a key role in the
development of PSLV which carried the
Mangalyaan into the space. He had said,
"From here to go to Mars we are going to
use only a fraction of what we did in getting to the (Earth) orbit." The challenge for him was
the launch of the rocket. He said the launch window was only five minutes. Ramakrishnan is
a mechanical engineer from the College of Engineering, Guindy, Chennai. He received his
M.Tech in Aerospace from IIT-Madras with the first rank.
4. SK Shivakumar: Director
of ISRO Satellite Centre,
Shivakumar joined ISRO in 1976.
He was part of the team that
developed the telemetry system
for Chandrayaan-I, India's first
lunar exploration mission. He
also developed satellite
technology and implemented
satellite systems for scientific,
technological and application
missions. He said, "Our baby is
up in the space. It was almost like
a caesarean."

31. 5. V Adimurthy: Born in Andhra Pradesh
and educated at IIT-Kanpur, Adimurthy joined
ISRO in 1973 and was the Mission Concept
Designer of Mars Orbiter Mission. He was
also awarded the Padma Shri in 2012.
6. P Kunhikrishnan: He is the Mission Director
for the launcher. From the Vikram Sarabhai Space
Centre in Thiruvananthapuram, Kunhikrishnan has
seven successful PSLV launches under his belt since
2009. He was appointed the mission director for the
ninth time. He was responsible for seeing the rocket
completes its mission successfully and that the satellite
is correctly injected in the designated orbit. The
challenge for him was that the orbital characteristic of
the Mars Mission is different from regular PSLV missions.
7. Chandradathan: Took over as the Director of the
Liquid Propulsion Systems Centre in 2013. He joined ISRO
in 1972. Initially, he worked for the SLV-3 project during
its design phase and later was involved in the development
of solid propellant formulations for SLV-3. Over three
decades, Chandradathan made contribution to the realisation
of solid motors for sounding rockets, SLV-3, ASLV and
PSLV.
8. AS Kiran Kumar: Joined ISRO in 1975, Kumar is the
Director of Satellite Application Centre. He was responsible
for designing and building three of the orbiter payloads - the
Mars Colour Camera, Methane Sensor and Thermal Infrared
Imaging Spectrometer. The challenge before him was
miniaturising the components as the satellite does not
provide much space.

32. 9. MYS Prasad: He is the director
of Satish Dhawan Space Centre and
chairman of the Launch Authorisation
Board. From 1975 to 1994, he worked
in the launch vehicle development
programmes of Isro. He was part of the
project Ttam of SLV-3, the first
indigenously developed launch vehicle
of India. As the launch was during
northeast monsoon season the
challenge was to enhance weather
forecasting capability to 10 days and simultaneously carrying out preparatory work for Mars
Mission while dismantling the GSLV rocket after the mission was aborted earlier this year.
10. S Arunan: He is the project director of
Mangalyaan. Arunan was responsible for leading
a team to build the spacecraft. The challenge for
him was to build a new communication system,
which would largely be autonomous so that it
could take decision and 'wake up' the orbiter
engine after 300 days.
11. B Jayakumar: The associate project director
of PSLV project, Jayakumar was responsible for the rocket systems, testing till the final lift-
off.
12. MS Pannirselvam: The chief general manager of range operation director at Sriharikota
Rocket port, Pannirselvam was responsible for maintaining launch schedules without any
slippages.
13. V Kesava Raju: He is the mission director of Mangalyaan. Raju and his team will track
the journey of the MOM in the outer space.
14. V Koteswara Rao: He is the Isro scientific secretary.

33. 13. CONCLUSION
India set for maiden Mars mission!!!!
India is inching closer to its maiden mission to Mars with just a day to go before the historic
launch.
During the countdown, the Polar Satellite Launch Vehicle (PSLV), the Indian Space
Research Organisations's workhorse launch vehicle that will carry Mangalyaan, will be
fuelled and its health checked. The giant 45-metre rocket will blast off from Sriharikota,
which is about 80 kilometres from Chennai.
The launch of Mangalyaan, which was scheduled for October 28 initially, was postponed due
to bad weather in the Pacific Ocean. Two Indian ships, SCI Yamuna and Nalanda, which will
monitor the health of the rocket and the satellite as it sails over the ocean after the launch, had
been delayed due to bad weather.
The launch window will remain open till November 19.
It is of critical importance for Mangalyaan to begin its over 200-million-kilometre journey on
its trans-Martian orbit by November 30; further delay could prove disastrous for the mission.
This will be the first-ever launch that ISRO will conduct in November at India's space port,
which is usually dogged by recurring cyclones at this time of the year.
The Mangalyaan mission will cost Rs 450 crores and will study the Martian atmosphere.
 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.

35. REFERENCES
1. isrohq.vssc.gov.in/isr0dem0v5a/index
2. http://en.wikipedia.org/wiki/polar_satellite_launch_vehicle
3. http://www.antrix.gov.in/pslv.html
4. www.isro.org/pslv-c25/Imagegallery
5. http://www.isro.gov.in