The Mars Orbiter Mission (MOM) was India's first interplanetary mission, which successfully inserted an orbiter called Mangalyaan into orbit around Mars on September 24, 2014, making India the first nation to succeed on its first attempt. MOM was launched on November 5, 2013 aboard a Polar Satellite Launch Vehicle (PSLV) rocket and performed several orbit raising maneuvers to reach Mars after a 300 day cruise. The mission aims to develop technologies for designing and operating interplanetary missions while exploring Mars' surface features and atmosphere using scientific instruments.

1. Mars Orbiter Mission
( Mangalyaan )
Submitted To :
Prof. J K Thakur
HoD ( Department of Aerospace Engg. )
Amity University Gurgaon
( Haryana )
Aman Dhanda ( Aerospace Engg. ) November 17, 2014 1

2. Aman Dhanda ( Aerospace Engg. ) November 17, 2014 2

3. Introduction
The Mars Orbiter Mission (MOM), also
called Mangalyaan "Mars-craft"
(Sanskrit मंगल maṅgala "Mars" + यान yāna
"craft"),[ is a Mars orbiter launched
into Earth orbit on 5 November 2013 by
the Indian Space Research
Organisation (ISRO). It was successfully
inserted into Mars orbit on 24 September
2014, making India the first nation to send a
satellite into Mars orbit on its first attempt,
and the first Asian nation to do so.
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4. It is India's first interplanetary mission
and ISRO has become the fourth space
agency to reach Mars, after the Soviet
space program, NASA, and the European
Space Agency. The spacecraft is currently
being monitored from the Spacecraft
Control Centre at ISRO Telemetry, Tracking
and Command Network (ISTRAC)
in Bangalore with support from Indian Deep
Space Network (IDSN) antennae at Byalalu.
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5. Background of MOM
 The MOM mission concept began with a feasibility study in 2010,
after the launch of lunar satellite Chandrayaan-1 in 2008.
 The government of India approved the project on 3 August
2012, after the Indian Space Research Organisation completed
125 crore (US$21 million) of required studies for the orbiter. The
total project cost may be up to 454 crore ( US $74 million).
 The satellite costs 153 crore (US$25 million) and the rest of the
budget has been attributed to ground stations and relay upgrades
that will be used for other ISRO projects.
 The space agency had initially planned the launch on 28 October
2013 but was postponed to 5 November 2013 following the delay in
ISRO's spacecraft tracking ships to take up pre-determined
positions due to poor weather in the Pacific Ocean. Launch
opportunities for a fuel-saving Hohmann transfer orbit occur about
every 26 months, in this case, 2016 and 2018. The Mars Orbiter's
on-orbit mission life will be between six and ten months.
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6.  Assembly of the PSLV-XL launch vehicle, designated
C25, started on 5 August 2013.
 The satellite's development was fast-tracked and
completed in a record 15 months.
 Despite the US federal government shutdown, NASA
reaffirmed on 5 October 2013 it would provide
communications and navigation support to the
mission. ISRO chairman stated in November 2013
that if the MOM and NASA's orbiter MAVEN were
successful, they would complement each other in
findings and help understand Mars better.
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7. Objectives :
The primary objective of the Mars Orbiter Mission is to
showcase India's rocket launch systems, spacecraft-building
and operations capabilities. Specifically, the primary
objective is to develop the technologies required for design,
planning, management and operations of an interplanetary
m• isdseiosing,n c oanmdp rreisainlisga tthioen f oolfl oaw Minagrs m oarbjoitre tra wskitsh: a capability
to 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;
The secondary objective is to explore :
• Mars' surface
features, morphology, mineralogy and Martian
atmosphere using indigenous scientific instruments.
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8. Spacecraft specifications
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Mass :
The lift-off mass was 1,337 kg (2,948 lb), including 852 kg (1,878 lb)
of propellant.
Bus :
The spacecraft's bus is a modified I-1 K structure and propulsion
hardware configuration, similar to Chandrayaan 1, India's lunar orbiter that
operated from 2008 to 2009, with specific improvements and upgrades
needed for a Mars mission. The satellite structure is constructed of an
aluminium and composite fibre reinforced plastic (CFRP) sandwich
construction.
Power :
Electric power is generated by three solar array panels of 1.8 m
× 1.4 m (5 ft 11 in × 4 ft 7 in) each (7.56 m2 (81.4 sq ft) total), for a maximum
of 840 watts of power generation in Mars orbit. Electricity is stored in a
36 Ah Li-ion battery.

9. Propulsion :
A liquid fuel engine with a thrust of 440 newtons is used for
orbit raising and insertion into Mars orbit. The orbiter also has eight 22-
newton thrusters for attitude control. Its propellant mass is 852 kg.
Communications :
Communications are handled by two 230-
watt TWTAs and two coherent transponders. The antenna array consists of
a low-gain antenna, a medium-gain antenna and a high-gain antenna. The
high-gain antenna system is based on a single 2.2-metre (7 ft 3 in) reflector
illuminated by a feed at S-band. It is used to transmit and receive the
telemetry, tracking, commanding and data to and from the Indian Deep
Space Network.
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11. Payload :
The 15 kg (33 lb) scientific payload consists of five
Scientific instruments
Payload Primary Objective Weight (Kg)
Mars Colour Camera (MCC) Optical imaging 1.27
Thermal Infrared Imaging
Spectrometer(TIS) Map surface composition and mineralogy 3.2
Methane Sensor for Mars (MSM) Detection of Methane presence 2.94
Mars Enospheric Neutral
Composition Analyser
Study of the neutral composition of Martian
upper atmosphere 3.56
(MENCA)
Lyman Alpha Photometer (LAP) Study of Escape processes of Martian upper
atmosphere through Deuterium/Hydrogen 1.97
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instruments are :

12. The Indian Space Research Organisation Telemetry, Tracking and Command Network 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 became more than
100,000 km, an 18-metre and an 32 m diameter antenna of the Indian Deep Space Network were
utilised. The 18-metre dish-antenna was used for communication with the craft until April 2014,
after which the larger 32 m antenna was used. NASA's Deep Space Network is providing position
data through its three stations located in Canberra, Madrid and Goldstone on the US West Coast
during the non-visible period of ISRO's network. The South African National Space Agency's
(SANSA) Hartebeesthoek (HBK) ground station is also providing satellite tracking, telemetry and
command services.
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Telemetry and
command

13. Launch
:  ISRO would have launched MOM on its new Geosynchronous
Satellite Launch Vehicle (GSLV), but the GSLV has failed twice in
two space missions in 2010, ISRO is still sorting out issues with
its cryogenic engine, and it was not advisable to wait for the new
batch of rockets since that would have delayed the MOM project
for at least three years. ISRO had to make a choice between
delaying the Mars Orbiter Mission and switching to the less-powerful
PSLV. They opted for the latter. There is no way to launch
on a direct-to-Mars trajectory with the PSLV as it does not have the
power. Instead, ISRO launched it into Earth orbit first and slowly
boosted it into an interplanetary trajectory using multiple perigee
burns to maximize the Oberth effect.
 The orbiter's dry mass is 500 kg (1,100 lb), and it carries 852 kg
(1,878 lb) of fuel and oxidiser. Its main engine, which is a derivative
of the system used on India's communications satellites, uses the
bipropellant combination monomethylhydrazine and dinitrogen
tetroxide to achieve the thrust necessary for escape velocity from
Earth. It will also be used to slow down the probe for Mars orbit
insertion and subsequently, for orbit corrections.
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14. Orbit raising manoeuvres :
Orbit trajectory diagram (not to scale).
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15.  Several orbit raising operations were conducted
from the Spacecraft Control Centre (SCC) at
ISRO Telemetry, Tracking and Command
Network (ISTRAC) at Pena, Bangalore.
 The aim was to gradually build up the
necessary escape velocity (11.2 km/s) to break
free from Earth's gravitational pull while
minimising propellant use.
 A total of six burns were completed while the
spacecraft remained in Earth orbit, with a
seventh burn conducted on 30 November to
insert MOM into a heliocentric orbit for its transit
to Mars.
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16. Trans-Mars injection :
 On 30 November 2013 at 19:19 UTC, a
23-minute engine firing initiated
the transfer of MOM away from Earth orbit
and on heliocentric trajectory toward
Mars. The probe was travelling a distance
of 780,000,000 kilometres
(480,000,000 mi) to reach Mars.
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17. Trajectory correction manoeuvres
 Four trajectory corrections were originally planned, but only
three were carried out. The first trajectory correction
manoeuvre (TCM) was carried out on 11 December 2013,
01:00 UTC, by firing the 22 newtons thrusters for a duration
of 40.5 seconds. As observed in April 2014, MOM is
following the designed trajectory so closely that the
trajectory correction manoeuvre planned in April 2014 was
not required. The second trajectory correction manoeuvre
was performed on 11 June 2014, at 16:30 hrs IST by firing
the spacecraft's 22 newton thrusters for a duration of 16
seconds. The third planned trajectory correction manoeuvre
was postponed, due to the orbiter's trajectory closely
matching the planned trajectory. The third trajectory
correction was also a deceleration test 3.9 seconds long on
22 September 2014.
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18. Mars orbit insertion
 The plan was for an insertion into Mars orbit on 24
September 2014, approximately 2 days after the arrival of
NASA's MAVEN orbiter. The 440N liquid apogee motor was
successfully test fired at 09:00 UTC (14:30 IST) on 22
September for 3.968 seconds, about 41 hours before actual
orbit insertion.
 On 24 September 2014, at IST 04:17:32 satellite
communication changed over to the medium gain antenna.
At IST 06:56:32 forward rotation started and locked the
position to fire, at IST 07:14:32 an attitude
control manoeuvre took place with the help of thrusters after
eclipse started at IST 07:12:19 and LAM (Liquid Apogee
Motor) starts burning at IST 07:17:32 and ends at IST
07:41:46. After that reverse manoeuvre took place, the
spacecraft successfully enters Martian orbit.[68][85][86]
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19. Status :
MOM will be set on a highly elliptical orbit around Mars, with
a period of 3.2 days and a planned periapsis of 423 km
(263 mi) and apoapsis of 80,000 km
(50,000 mi). Commissioning and checkout operations are
planned over the coming weeks to prepare MOM's
instruments for science operations. On 24 September 2014,
the Spacecraft succesfully entered the Martian Orbit and
sent back the first pictures of Martian atmosphere.
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20. First Image taken by MOM
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21. Aman Dhanda ( Aerospace Engg. ) November 17, 2014 21