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CASE STUDY ON MANGALYAAN
ISRO (2014)
- Shradha Ghosh, Akash Patel
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University Of Petroleum And Energy Studies
Dehradun, Uttrakhand, India

2. Index
1. Introduction…………………………………………
2.Objectives of Mangalyaan………………………...
3.Interplanetary journey and Obstacles…………
4.Entry into Mars Orbit……………………………..
5.Unsuccessful Mars Missions…………………….
6.Geographical Factors………………………………
7.Political Conditions…………………………………
8.Economic Factors and Contribution…………...
9.Conclusion……………………………………………
10.Refrences…………………………………………….

3. Structure:
 Brief Introduction
 Cases
 Solution
 Brief conclusion
CASE STUDY: MANGALYAAN
By: Shradha Ghosh, Akash Patel
Introduction
Mars Orbiter or Mangalyaan, after 15 months of manufacturing at a cost of
Rs.454 crores using a Polar Satellite Launch Vehicle (PSLV) rocket C25 at
09:08 UTC on 5 November 2013 set out to cover the distance of 225 million km
by travelling 670 million kms between Mars and Earth. Successfully
undergoing India’s first interplanetary mission.
ISRO became the fourth space agency in the world after National Aeronautics
and Space Administration (NASA) of the US, Russian Federal Space Agency
(RFSA) and European Space Agency to have successfully undertaken a mission
to Mars. Costing only Rs.4 per Indian citizen!
 The study discusses the objective of Mangalyaan and distinguishes its
objectives from that of other missions of its kind.
 The study describes the interplanetary journey of Mangalyaan and its
obstacles in brief.
 The study analyses the Orbiter’s entry into Mars orbit and its phases,
 It walks through the technology used in propulsion and detecting
instruments and the reason for its cost effectiveness.
 The study discusses the common hurdles faced by 24 of previous
unsuccessful mars missions and how Mangalyaan overcame them.
 It explains the geographic, political and economic factors, that influenced
Mars Orbit Mission and its contribution to economy.
 It concludes with the outcomes of Mangalyaan.
This study is based on my research from the sources on internet and journals
that will be mentioned in the reference section.

4. Discussion#1 (Objective of Mangalyaan)
Mars Orbiter missions, is on a quest to fulfill dual objectives Technological
and Scientific.
Technological Objectives:
 Design and realization 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.
Scientific Objectives:
 Exploration of Mars surface features, morphology, mineralogy and
Martian atmosphere by indigenous scientific instruments.
In addition to Mangalyaan there are five other ongoing missions. They
are – Mars Odyssey(NASA), Mars Express(EU), MRO(NASA),
MAVEN(NASA), ExoMars Trace Gas(EU/RFSA).
Each mission has a slightly different objective, though all indicating
towards scientific exploration on the planet Mars in one form or another.
Mangalyaan however, has a broader objective of making interplanetary
explorations convenient for future in terms of Propulsion, navigation,
communication, payload and cost.
Below is a table comparing objectives of the above mentioned six
operational orbiters.

5. Comparison of MOM with other operational orbiters
Sno. Orbiter Agency Objective
1. Mangalyaan ISRO  Designing, planning, management and
operation of interplanetary mission.
 To explore Mars surface feature and
atmosphere.
2. Mars
Odyssey
NASA  Determining Mar’s habitability.
3. Mars
Express
EU  orbital (and originally in-situ) study of the
interior, subsurface, surface and
atmosphere, and environment of the planet
Mars
4. MRO NASA  to map the Martian landscape with its high-
resolution cameras in order to choose
landing sites for future surface missions.
5. MAVEN NASA  to find scientific proof that Mars once
sustained an atmosphere.
6. ExoMars
Trace Gas
Orbiter
EU/RFSA  Detection of Trace gasses on Mars surface.
Discussion#2 (Interplanetary Journey and
Obstacles)
How did going to mars take just as much fuel as going to moon, although its
100 times the distance of moon?
ISRO has used the method of Hohmann Transfer Orbit or Minimum energy
transfer orbit between Earth and Mars. When an object is moving in an orbit it
does not require additional energy. Hohmann demonstrated that the lowest
energy route between any two orbits is an elliptical "orbit" which forms

6. a tangent to the starting and destination orbits. The more elliptical the orbit
the higher is the speed of satellite.
The following describes the beginning and interplanetary part of
Mars Orbiter’s journey:
 The spacecraft is injected into an elliptical parking orbit by the launcher,
with pergee of 248km and apogee of 23,500km.
 According to the first principle the speed of the spacecraft is
highest at the perigee, so a little tangential force, could make it
cover a large distance. All the engine burns to raise the orbit were done
at the perigee.
 A total of six main engine burns were carried out for several seconds to
raise the orbiter through five orbits at apogee 28,825km, 40,000km,
71,650km, 100,000km, and 192,000km respectively.
 With a seventh prolonged burn of a 440 Newton engine, the orbiter
escapes earth’s sphere of influence and enters the sun- centered or
heliocentric orbit at a velocity of more than one lakh kilometer per hour.
 The orbit coasts around sun for nine months before being captured into
Martian orbit of influence.
 At the time the space craft reaches the closest approach to Mars, it is
captured into planned orbit around Mars.
Obstacles tackled during interplanetary flight
1. Failure of fourth orbital raising
According to ISRO, the fourth orbital raising attempt on 11 November failed
after a premature shut down of the main engine and the spacecraft’s back
up logic triggered thruster firings instead. The result was that the spacecraft’s
velocity increased 35m/s rather than the 130m/s expected and undershot its
planned for apogee (orbital high point) of 100,000km by nearly 22,000km.

7. Solution: an additional unscheduled burn was performed on 12 November
2013 that increased the apogee to 118,642 km (73,721 mi), a slightly higher
altitude than originally intended in the fourth maneuver.
2.Communication Black out
Although this glitch in the journey was anticipated, there was no telling
whether the Round-trip Light Time (RLT) from Earth to Mars can vary
anywhere between 6 to 43 minutes, it would be impractical to micromanage a
mission from Earth. Due to this communications delay, mission support
personnel on Earth cannot easily monitor and control all the spacecraft
systems in real-time basis.
Solution: The configuration includes the use of on-board autonomy to
automatically manage both the nominal and non-nominal scenarios on-board
the spacecraft.
3.Radiation
Once a vehicle leaves low Earth orbit and the protection of Earth's
magnetosphere, it enters the Van Allen radiation belt, a region of high
radiation. As a result of such effects, various physicochemical processes occur
in spacecraft materials and equipment components and lead to the
deterioration in their operating parameters.
Solution: The main frame bus elements and payloads are basically designed
for interplanetary missions capable of operating in Earth Burn Maneuvers
(EBN), Mars Transfer Trajectory (MTT) and Martian Orbit (MO) environments.

8. Discussion#3 (Entering into Mars Orbit)
Following are the phases encountered by MOM while entering Mars
Orbit:
 Reorienting the Spacecraft MOM is reoriented to align the thrust
vector- before firing the engines to reduce the velocity.
 In the shadow of Mars Because of the Mars-Sun-Earth geometry,
the orbit insertion is destined to happen while MOM is in ellipse.
MOM enters eclipse 5 minutes before Burn Start.
 Engine Firing The main liquid Engine and eight smaller thrusters
fire, imparting braking velocity of 1098.7 m/s.
 The communication blackout The radio link between MOM and
ground station blocked my Mars and MOM executes all operations
autonomously.
 Resuming Communication The burn is terminated when the
required braking velocity is achieved and MOM id in Martian Orbit.
The spacecraft is reoriented to point its Antenna towards Earth to
resume communication.
Factor’s considered before entering Mars Orbit:
 Thermal Environment
The Orbiter needed to cope with a wide range of thermal environment,
from Near Earth conditions with Sun and Earth contributions (hot case)
to Mars conditions where eventually eclipses and reduced solar flux give
rise to cold case issues.
The average solar flux at Mars orbit is 589 W/Sq.m, or about 42% of
what is experienced by an Earth-orbiting spacecraft. As a result of the
eccentricity of Mars orbit, however, the solar flux at Mars varies by +/-
19% over the Martian year, which is considerably more than the 3.5%
variation at Earth.

9.  Communication Systems
The communication systems for the Mars mission are responsible for
the challenging task of communication management up to a distance of
400 million km. It consists of Telemetry, Tracking and Commanding
(TTC) systems and Data transmission systems in S-band and a Delta
Differential One-way Ranging (Δ-DOR) Transmitter for ranging. The TTC
system comprises of coherent TTC Transponders, TWTAs (Travelling
Wave Tube Amplifiers), a near omni coverage antenna system, a High
Gain Antenna system, Medium Gain Antenna and corresponding feed
networks.
The High Gain Antenna system is based on a single 2.2 meter reflector
illuminated by a feed at S-band.
 Power System
One of the major challenges in the design of power system is due to the
larger distance of the satellite from the Sun. The power generation in
Mars orbit is reduced to nearly 50% to 35% compared to Earth’s orbit.
The power bus configuration comprises of a single wing of solar array
with 7.56 m2 area generating about 840 W during sunlit and normal
incidence in Martian orbit, and a 36 Ampere-Hour Lithium-Ion battery
supports the power load during launch phase, initial attitude
acquisition, eclipse, Earth burns, MOI, safe mode and data transmission
phases.
 Propulsion System
Propulsion System consists of one 440N Liquid Engine and 8 numbers
of 22N thrusters. The propellant tanks have combined storage capacity
up to 852 kg propellant. The 22N thrusters are used for attitude control
during the various activities of the mission like, orbit raising using
liquid engine, attitude maintenance, Martian orbit maintenance (if any)
and momentum dumping.
As the critical operation of Martian Orbit Insertion with Liquid Engine
burn occurs after 10 months of launch, suitable isolation techniques are
adopted to prevent fuel/ oxidizer migration issues.

10. Discussio#4(Unsuccessful Mars Mission: Causes of
Failure)
Out of the 29 failed missions, 11 never left the lower earth orbit, and 13
missions failed just before or immediately after entering Mars orbit.
The following table illustrates the failed missions and their reason for failure.
Space Crafts Reason
1M No.1,1M No.2,2MV-4 No.1, 2MV-3 No.1,Mariner
3,2M No.521 ,2M No.522 ,Mariner 8 ,Kosmos
419,(3MS No.170), Mars 96(M1 No.520)
Launch Failure
Mars 1(2MV-4 No.2), Zond 2(3MV-4A No.2), Mars 2
lander(SA 4M No.171), Prop-M Rover rover(SA 4M
No.172),Mars 4(3MS No.52S),Mars 5(3MS
No.53S),Mars 6(3MP No.50P),Mars (3MP No.51P),
Fobos 1(1F No.101),Fobos 2(1F No.102),Mars
Observer, Nozomi(PLANET-B),Mars Climate
Orbiter,Mars Polar Lander,Deep Space 2,Beagle
2,Fobos-Grunt,Yinghuo-1 .
System Failure
Mars 3(4M No.172),Mars 3 lander(SA 4M No.172) Other
The failure to orbit was mostly due to leakages, or early stage engine failure of
the inability of payload to detach. MOM solved this problem with a simpler
design, with light weight payload and a safe engine.
The second problem was the communication being lost, ISRO was already
prepared for it, by making all the systems post eclipse (when the orbiter looses
communication) autonomous. It also included a high gain antenna on the
Orbiter to keep communication strong. (see discussion 2)

11. Discussion#5(Geographical Factor)
The one geographical factor that influenced Mangalyaan the most is
the location of Shriharikota, it’s the second best spaceport in the
world next to Kennedy space center in U.S
 Sriharikota is ideal for eastward launches. SHAR’s location on the
east coast ensures that it gains an additional velocity of 0.4 km/s due
to Earth’s rotation to easily launch rockets.
 Being a coastal islandic area with no habitation proves advantageous
for Sriharikota because it is on National Highway (NH-5), 20 KM away
from nearest Railway Station, and 70 KM (Chennai) from nearest
International Ports by air & ships.
 Shriharikota has a safe distance for impact from the landing site.
Discussion#6 (Political Factors)
There are two types of political factors 1.Negative 2.Posititve, while the former
drives the Indian Space Research Organization (ISRO) to produce cheaper
missions the latter motivates it to increase the number of missions while
maintaining its authenticity.
These two factors are closely explored below:
1. Negative factor – Lack of Government Support
Although it might sound cliché at first the lack of government support has
caused slower execution of projects by the organization, between 2007 and
2012, Isro accomplished only about half of its planned 60 missions,
government data showed. The government cited "development complexity" as
the reason for the delay in some missions.
Between 2012 and 2017 the target is 58 missions. The agency has completed
17 missions so far, and ISRO did not say why the number remained low.

12. Some company executives and experts do not see that changing any time soon,
with the absence of heavy rocket launchers, too few launch facilities and
bureaucratic delays hampering growth.
2. Positive Factor- Competition with other Nations
Asian space race with china Japan and South Korea-
 With the many successes of the Chinese space program, through its
Shenzhou human spaceflight program and Chang’e robotic lunar
program, India has been left looking like one of several distant “also ran”
competitors in the Asian space race.
 Given that space exploration has traditionally carried with it significant
technology leadership implications India could not allow China’s regional space
leadership to go uncontested.
 Going to the Moon wouldn’t do it, but going to Mars would. China had
attempted a Mars mission with Yinghuo-1, launched in 2011 by Russia. But the
mission failed. That failure provided India with an open spot in the space record
books, and the geostrategic influence that accompanies those coveted spots.
Bureaucratic Politics-
 An agreement had been signed in 2007 between India and Russia for
Chandrayaan-2 to be a joint mission, with India supplying a lunar
orbiter and rover, and Russia the lander. In 2009, however, it began to
be clear that Russia was experiencing hardware development delays.
Russia cancelled its participation and India was left to complete the
mission on its own terms and its own time. And it left India with a
nearly completed Chandrayaan spacecraft in 2009-2010.
 However the contribution of K. Radhakrishnan(chair of ISRO in 2009)
for Chandrayaan-2 could not have been remembered as prominently as
that of his predecessor, G. Madhaven Nair for chandrayaan-1. Mars
Mission presented for Radhakrishnan an opportunity to create an even
bigger legacy.

13. Discussion#7(Economic Factors & Contribution)
How did Mangalyaan cost India just $76 million, and Maven cost
U.S $671 million, for more or less the same outcome?
There is a large cost difference between the two missions mainly because of the
different objectives, payloads, and expected operating lifespan
Factors that make Mangalyaan Economic yet accurate:
1. Objective: MAVEN is out to perform specialized research that involves
studying the atmosphere of Mars while MOM is a technology
demonstrator, more focused on taking the first step towards a successful
space program -- putting an orbiter successfully into Martian orbit and
perform maneuvers. This detail significantly reduces its cost of
manufacturing.
MAVEN is armed with eight scientific instruments whereas MOM has
five scientific instruments, one of them being methane sniffer.
2. Manufacturing: Two-thirds of Mangalyaan’s parts such as motor
casings and the antenna were manufactured by domestic firms such as
Godrej & Boyce and India's largest engineeringcompany, Larsen &
Toubro as oppose to international companies like companies like
lockheed martin, which substantially controlled costs.
3. Propulsion technique: Mangalyaan used a series of smaller engine
burns in place of one powerful burn like the heavy powerful upper stage l
Centaur in MAVEN, it used a smaller Liquid Apogee Motor (LAM) and the
relatively small amount of fuel it was able to carry to orbit. The reduced
payload and a simpler propulsion system efficiently minimized the costs.
4. Life Span: MAVEN is expected to function for 8.5 years while MOM is
expected to function for ten months. Hence the fuel content in both the
space crafts are filled accordingly, making MOM much cheaper and yet
functional.
5. Labor costs: Engineers cost much less in the India then they do in U.S.
The annual income for an aeronautical engineer in the United States is
$105,000.In India it is around $ 20,000 ,for equal or more work.

14. Economic Contribution of Mangalyaan
1. Attracting foreign investment: Mangalyaan has improved the
chances of foreign giants to launch satellites and work with ISRO.ISRO
has already launched them and has made huge profits.
Until now in 2014-15.
Through ISRO’s commercial arm Antrix by virtue of various activities
India has earned about $ 100 million launching 45 foreign satellites
till date and revenue from its commercial space missions is poised to
grow with another 28 foreign satellites planned to be put into orbit
between 2015 and 2017.
2. Growth of Domestic Firms: The success of Mangalyaan has opened
doors to other commercial opportunities for domestic companies like,
Godrej & Boyce and Larson & Turbo that manufactured two-third
components of Mangalyaan.
Godrej plans to shift focus from space technology to the aviation export
industry, catering to the likes of Boeing Co and Airbus and trimming
Isro's contribution to their aerospace business to 40 percent from 70
percent currently.
Conclusion
Mangalyaan has put India back in the space race with other countries. While
it’s a one of its kind opportunity, it has attracted a lot of attention and foreign
investment, which might help lifting India’s GDP in the near future. Along with
that it has the rare opportunity to test Mar’s atmospheric configuration with its
unparalled instruments.
MOM also shows that longer inter planetary space flights are possible in future
with lesser payload. It demonstrated innovative communication systems and
automation that was the major cause of failure of Mar’s missions in the past.
It did all this without hampering the country’s economy and overcame
obstacles that most agency couldn’t, with simpler mechanisms.
Although the scientific outcomes of the Orbiter including the methane content
has not yet been released, ISRO has released some pictures from the surface of
Mars that may lead in profound discoveries.

15. References
1. L. S. Novikov*, V. N. Mileev, E. N. Voronina, L. I. Galanina, A. A.
Makletsov, and V. V. Sinolits L. S. et.al Radiation effects of spacecraft
material (August 07 2008).
2. Zunhui Zhao, Haibin Shang, Pingyuan Cui, Xiangyu Huang, (2013)
"Solution space research for interplanetary trajectory", Aircraft
Engineering and Aerospace Technology, Vol. 85 Iss: 2, pp.150 – 16
3. Haibin Shang, Pingyuan Cui, Enjie Luan, (2008) "Design and
optimization of interplanetary low‐thrust trajectory with planetary
aerogravity‐assist maneuver", Aircraft Engineering and Aerospace
Technology, Vol. 80 Iss: 1, pp.18 – 26
4. http://www.isro.gov.in
5. http://www.planetary.org
6. http://www.emeraldinsight.com
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