Done by-Prateek Sharma (9C)

Established in 1969, ISRO superseded the erstwhile Indian National Committee for Space Research (INCOSPAR). Headquartered in Bangalore, ISRO is under the administrative control of the Department of Space, Government of India.Since its establishment, ISRO has achieved numerous milestones. It built India's first satellite, Aryabhata, which was launched by the Soviet Union on 19 April in 1975. In 1980, Rohini became the first satellite to be placed in orbit by an Indian-made launch vehicle, SLV-3. ISRO subsequently developed two other rockets: the Polar Satellite Launch Vehicle (PSLV) for launching satellites into polar orbits and the Geosynchronous Satellite Launch Vehicle (GSLV) for placing satellites into geostationary orbits.

These rockets have launched numerous

communications satellites and earth

observation satellite. On 22 October in 2008,

Chandrayaan-1, India sent its first mission to

the Moon. Over the years, ISRO has

conducted a variety of operations for both

Indian and foreign clients. ISRO's satellite

launch capability is mostly provided by

indigenous launch vehicles and launch sites.

In 2008, ISRO successfully launched its first

lunar probe, Chandrayaan-1, while future

plans include indigenous development of

GSLV, manned space missions, further lunar

exploration, mars exploration and

interplanetary probes. ISRO has several field

installations as assets, and cooperates with

the international community as a part of

several bilateral and multilateral agreements.

5 November 2013, ISRO launched its Mars

Orbiter Mission, which is currently en route to

Mars.

The Mars Orbiter Mission (MOM), informally called Mangalyaan (Sanskrit: मङ्गलयान, "Mars-Craft"), is a Mars orbiter launched into Earth

orbit on 5 November 2013 by the Indian Space Research Organisation

(ISRO). It is expected to enter orbit around Mars on 24 September 2014.

The mission is a

"technology

demonstrator" project

aiming to develop the

technologies required

for design, planning,

management, and

operations of an

interplanetary

mission.

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.

The Mars Orbiter Mission probe

lifted-off from the First Launch

Pad at Satish Dhawan Space

Centre SHAR, Sriharikota,

Andhra Pradesh, using a Polar

Satellite Launch Vehicle (PSLV)

rocket C25 at 09:08 UTC (2:38

PM IST) on 5 November 2013.

The launch window was

approximately 20 days long and

started on 28 October 2013. 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 on

30 November 2013 (UTC).

Travelling at a speed of 1.55 km per second, Mangalyan crossed half way

to Mars on 9 April 2014.

It is India's first interplanetary mission and, if successful, ISRO would

become the fourth space agency to reach Mars, after the Soviet space

program, NASA, and European Space Agency.

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.

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.

Following are the major objectives of the 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.

3. Incorporate autonomous features to handle contingency situations.

B. Scientific Objectives:

1. Exploration of Mars surface features, morphology, mineralogy and Martian

atmosphere by indigenous scientific instruments.

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 ₹1.25 billion

(US $21 million) of required studies for the orbiter. The total

project cost may be up to ₹4.54 billion (US $77 million). The

satellite costs ₹1.53 billion (US$26 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

inability of 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

Assembly of the PSLV-XL launch vehicle, designated C25,

started on 5 August 2013. The mounting of the five scientific

instruments was completed at ISRO Satellite Centre, Bangalore,

and the finished spacecraft was shipped to Sriharikota on 2

October 2013 for integration to the PSLV-XL launch vehicle.

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.

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

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).

The spacecraft's bus is a modified I-1 K structure and propulsion

hardware configurations similar to Chandrayaan 1, India's lunar orbiter

that operated from 2008 to 2009, with specific improvements and

upgrades needed for a Mars mission.[31] The satellite structure is of

aluminium and composite fibre reinforced plastic (CFRP) sandwich

construction.

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.

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:

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.

Nov 05, 2013

o PSLV-C25, in its twenty fifth flight successfully launches Mars Orbiter

Mission Spacecraft from SDSC SHAR.

o PSLV-C25 lifted off at 14:38 hrs.

o Automatic sequencing of launch initiated.

o Launch authorised by Mission Director for GO at 14:24 hrs.

o Mobile Service Tower (MST) withdrawal to final parking (150m)

completed. Countdown is normal.

o All vehicle systems are switched ON for the final eight and half hour

countdown starting at 6:08 hrs (IST).

o Second Stage (PS2) Propellant filling operations completed.

Nov 04, 2013

• Second Stage (PS2) Propellant filling commenced.

• Mobile Service Tower (MST) withdrawal up to 50m is completed.

• Mandatory Checks and Preparations for Propellant filling operations of

Second Stage (PS2) are in progress.

Nov 03, 2013

Propellant filling of PS4 stage and RCT completed.

Mixed Oxides of Nitrogen (MON) filling of PS4 completed at 17:00 hrs.

(IST).

Mixed Oxides of Nitrogen (MON) filling of PS4 under progress.

Mono Methyl Hydrazine (MMH) filling of Reaction Control Thrusters (RCT)

completed.

Mono Methyl Hydrazine (MMH) filling completed.

Propellant filling operations of Fourth Stage (PS4) are in progress.

The 56 hr. 30 min countdown of Mission commenced at 06:08 hrs. (IST).

Nov 02, 2013

All the pre-countdown activities have been completed

satisfactorily and the 56 and half hr. countdown of Mission will

commence tomorrow at 06:08 hrs. (IST).

Pre-count down activities of Mission commenced at 08:45 hrs.

Nov 01, 2013

Launch Authorisation Board has approved & cleared the PSLV-

C25/Mars Orbiter Mission launch on Nov 05, 2013 at 14:38

hrs. (IST)

56 and half hr. countdown for launch will begin on Nov 03,

2013 at 06:08 hrs. (IST)

Oct 31, 2013

Launch Rehearsal of PSLV-C25/Mars Orbiter Mission has

been completed successfully in the afternoon on Oct 31,

2013.

Launch Rehearsal of PSLV-C25/Mars Orbiter Mission

commenced at 06:08 hrs. (IST) on Oct 31, 2013 at First

Launch Pad, SDSC SHAR.

Vehicle systems powered and health is normal.

Oct 30, 2013

• Spacecraft & Launch Vehicle integrated level checks

completed.

• Preparations for Launch Rehearsal are under progress.

Oct 22, 2013

• Spacecraft Integration with the Launcher PSLV-C25

Completed.

The 18-metre diameter dish-antenna will be used for communication with craft till April 2014, after which the larger 32-metre antenna will be 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. 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 near Fiji.

PSLV-C25 carrying the Mars Orbiter Mission spacecraft was launched

from Sriharikota on 5 November 2013.

As originally conceived, 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 with

the help of gravity assist manoeuvres.

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 pointof 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 orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km.

1. Geo Centric Phase

The spacecraft is injected into an Elliptic Parking Orbit by the launcher. With

six main engine burns, the spacecraft is gradually maneuvered into a

departure hyperbolic trajectory with which it escapes from the Earth’s

Sphere of Influence (SOI) with Earth’s orbital velocity + V boost. The SOI of

earth ends at 918347 km from the surface of the earth beyond which the

perturbing force on the orbiter is mainly due to the Sun. One primary

concern is how to get the spacecraft to Mars, on the least amount of fuel.

ISRO uses a method of travel called a Hohmann Transfer Orbit – or a

Minimum Energy Transfer Orbit – to send a spacecraft from Earth to Mars

with the least amount of fuel possible.

2. Helio Centric Phase

The spacecraft leaves Earth in a direction tangential to Earth’s orbit and

encounters Mars tangentially to its orbit. The flight path is roughly one half

of an ellipse around sun. Eventually it will intersect the orbit of Mars at the

exact moment when Mars is there too. This trajectory becomes possible

with certain allowances when the relative position of Earth, Mars and Sun

form an angle of approximately 44o. Such an arrangement recur

periodically at intervals of about 780 days. Minimum energy opportunities

for Earth-Mars occur in November 2013, January 2016, May2018 etc.

3. Martian Phase

The spacecraft arrives at the Mars Sphere of Influence (around

573473 km from the surface of Mars) in a hyperbolic trajectory. At the

time the spacecraft reaches the closest approach to Mars (Periapsis),

it is captured into planned orbit around mars by imparting ∆V retro

which is called the Mars Orbit Insertion (MOI) manoeuvre. The Earth-

Mars trajectory is shown in the above figure. ISRO plans to launch the

Mars Orbiter Mission during the November 2013 window utilizing

minimum energy transfer opportunity.

Mars Orbiter Mission spacecraft being prepared for a

prelaunch test at Satish Dhawan Space Centre SHAR,

Srihairkota.

Loading Spacecraft for Thermovacuum Test in Large Space

Simulation Chamber

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.

The Polar Satellite Launch Vehicle, usually

known by its abbreviation PSLV is the first

operational launch vehicle of ISRO. PSLV is

capable of launching 1600 kg satellites in 620

km sun-synchronous polar orbit and 1050 kg

satellite in geo-synchronous transfer orbit. In

the standard configuration, it measures 44.4

m tall, with a lift off weight of 295 tonnes.

PSLV has four stages using solid and liquid

propulsion systems alternately. The first stage

is one of the largest solid propellant boosters

in the world and carries 139 tonnes of

propellant. A cluster of six strap-ones attached

to the first stage motor, four of which are

ignited on the ground and two are air-lit.

The reliability rate of PSLV has been superb. There had been

25 continuously successful flights of PSLV, till April 2014 .

With its variant configurations, PSLV has proved its multi-

payload, multi-mission capability in a single launch and its

geosynchronous launch capability. In the Chandrayaan-

mission, another variant of PSLV with an extended version of

strap-on motors, PSOM-XL, the payload haul was enhanced

to 1750 kg in 620 km SSPO. PSLV has rightfully earned the

status of workhorse launch vehicle of ISRO.

1. Lift-off weight 295 tonne

2. Pay Load 1600 kg in to 620 km Polar Orbit,

1060 kg in to Geosynchronous Transfer

Orbit (GTO)

3. Height 44 metre

Typical Parameters of PSLV