India's Mars Orbiter Mission (MOM), also known as Mangalyaan, is the cheapest Mars mission ever at a cost of about $74 million. It was developed and launched in just 15 months and involves sending an orbiter craft to orbit Mars and study its surface features and atmosphere. The mission aims to demonstrate India's technological capability to design, plan and manage deep space missions.

1. INDIAS MISSION TO
MARS
(MANGALYYAAN)

3. Interesting Facts
#1. Cheapest Mars Mission Ever.
India’s Mars mission – the Mars Orbiter Mission – or as
informally known: Mangalyaan - is built with a cost of
Rs. 454 crores (that is around Rs.4 per Indian, Rs. 12 per km). It is the cheapest
Mars mission, ever!
#2. Developed and deployed in just 15 months.
While ISRO has been researching for a Mars mission since
years, the project was only approved by the government in
August 2012. It took ISRO just a little over a year to put
together the spacecraft and the project.
#3. Launch a satellite = Gully Cricket;
Moon mission = Ranji Cricket;
Mars mission? International cricket.
#4. A trip to Mars = 73,791+ trips from Jammu to
Kanyakumari!
#5. It takes 14 minutes for a signal to reach Mars!

5. • Established in 1969
• Primary space agency of india.
• Amongst the largest government space agencies in the world.
• Primary objective is to advance space technology and use its applications
for national benefit.
• It built India's first satellite, Aryabhata, which was launched by the Soviet
Union on 19 April in 1975.

7. • It is known as the Mars Orbiter Mission (MOM), informally called
Mangalyaan.
• 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 MOM probe spent about a month in Earth orbit, where it made a series
of seven altitude-raising orbital manoeuvres before trans-Mars injection
• The mission is a "technology demonstrator”

8. • Travelling at a speed of 1.55 km per second, Mangalyan ,crossed half way
to Mars on 9 April 2014.
• The spacecraft is being currently 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.
Control station of Mangalyaan: Bangalore

10. A. Technological Objectives:
• 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.
• Deep space communication, navigation, mission planning and
management.
• B. Scientific Objectives:
Exploration of Mars surface features, morphology, mineralogy and
Martian atmosphere by indigenous scientific instruments.

12. PSLV(POLAR SATELLITE LAUNCH
VEHICLE)
• The Polar Satellite Launch Vehicle commonly
known by its abbreviation 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

14. TEAM
• Some of the scientists working on the Mars Orbiter Mission
project are:
• 1. K. Radhakrishan – Chairman, ISRO
• 2. A. S. Kiran Kumar – Director, SAC
• 3. Mylswamy Annadurai – Programme Director, MOM
• 4. B. S. Chandrashekar – Director, ISTRAC
• 5. P. Robert – Operations Director, MOM
• 6. Subbiah Arunan – Project Director, MOM
• 7. V. Kesavaraju – Post-Launch Mission Director, MOM
• 8. P. Ekambaram – Operations Director, MOM
• 9. P. Kunhikrishnan – Launch Mission Director, PSLV-XL
• 10. S. K. Shivkumar – Orbiting payload Director, ISAC
• 11. B. Jayakumar – Launch Vehicle Director, PSLV

15. SPACECRAFT ( BASIC DETAILS )
The lift-off mass was 1,350 kg (2,980 lb), including 852 kg
(1,878 lb) of propellant mass.
Cuboid in shape of approximately 1.5 m (4 feet 11 inches).

16. 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 W generation
in Martian orbit. Electricity is stored in a 36 Ah Li-ion battery.
Liquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian
orbit. The orbiter also has eight 22 N thrusters for attitude control or orientation.
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. The High-gain
antenna system is based on a single 2.2-metre 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.

21. Lyman-Alpha Photometer (LAP) – a photometer that measures the relative abundance
of deuterium and hydrogen from Lyman-alpha emissions in the upper atmosphere.
Measuring the deuterium/hydrogen ratio will allow an estimation of the amount of
water loss to outer space.
Methane Sensor For Mars (MSM) – will measure methane in the atmosphere of Mars,
if any, and map its sources. Particle environment studies.
Mars Exospheric Neutral Composition Analyser (MENCA) – is a quadruple mass
analyser capable of analysing the neutral composition of particles in the exosphere.
Surface imaging studies
Thermal Infrared Imaging Spectrometer (TIS) – will measure the temperature and
emissivity of the Martian surface, allowing for the mapping of surface composition and
mineralogy of Mars.
Mars Colour Camera (MCC) – will provide images in the visual spectrum, providing
context for the other instruments.

23. MSM (Methane Sensor For Mars )

28. Mars Orbiter Mission spacecraft being prepared for a prelaunch
test at Satish Dhawan Space Centre SHAR, Srihairkota.

29. Loading Spacecraft for Thermovacuum Test in Large Space
Simulation Chamber

30. First image of the Earth by Mars Color Camera (MCC) of Mars Orbiter Spacecraft taken on
Nov 19, 2013 at 13:50 hrs. (IST) from 67975 km altitude with a resolution of 3.53 km.

31. THANK YOU