Mangalyan ( Mars Orbiter Mission)

© Atharva A. Dixit.

Mangalyan ( Mars Orbiter Mission)

Date Of Announcement : 15 August 2012

Date Of Launch : 5 November 2013

Place Of Launch : Satish Dhawan Space Centre ( Sriharikota )

Within 15 months from the announcement, ISRO developed own indigenous technology, tested different parts, assembled them and successfully launched as per plan

Mangalyan ( Mars Orbiter Mission)

Specifications

Mission Cost : 450 Crore INR.

Spacecraft Weight At Lift Off : 1337 Kg.

Propellant Loaded : 852 Kg.

Scientific Payload Weight : 13 Kg.

Type Of Rocket Used : PSLV XL-C25.

Type Of Fuel Used : Solid Propellant.

Type Of A Mission : Orbiter.

A Glance At The Trajectory Followed By

MOM

Transitions in orbit of Mom

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

Transfer orbit of MOM

Hohmaan transfer orbit: The elliptical heliocentric orbit that is used in interplanetary travel, with the use of least fuel

The elliptical transfer orbit’s apsides (the closest and farthest points) are tangential to both the departing planet’s orbit and the arriving planet’s orbit

For travel to outer planets, like Mars, the periapsis (closest point in the orbit) must coincide with Earth’s orbit, while apoapsis must coincide with Mars’ orbit

The Mars Orbiter Mission (MOM) by the Indian Space Research Organization which is expected to enter the orbit of the planet Mars soon, used this Hohmann transfer orbit as its trajectory to reach Mars

Transfer orbit of MOM

Since the satellite is in heliocentric trajectory, the fuel is not used in this travel

Fuel is used only to enter the Hohmann transfer orbit from earth and to exit the transfer orbit to enter martian orbit

This transfer orbit is thus highly fuel efficient compensating its long travel time

Different Sections Of The Orbiter

Payloads On The Orbiter & Their Functions LAP ( Lyman Alpha Photometer ): It’s an absorption cell photometer. It

measures the relative abundance of Dueterium & Hydrogen from Lyman-Alpha emission in the upper Martian atmosphere. Measurement of D/H allows us to understand the loss process of water from the planet.

MSM ( Methane Sensor For Mars ): Designed to measure Methane(CH4) in the Martian atmosphere with PPB accuracy and map its sources

MENCA ( Mars Exopheric Neutral Composition Analyser ): Quadruple mass spectrometer capable of analyzing the neutral composition in the of 1 to 300amu with unit mass resolution

MCC ( Mars Colour Camera ): A tri-colour camera used to take images of Martian surface. It will be used to take photographs of Phobos & Deimos.

TIS ( Thermal Infrared Imaging Spectrometer ): Measures the thermal emission and can be operated during both day & night. Many minerals and soil types have characteristic spectra in TIS region. It can map surface composition and mineralogy of Mars.

Images Taken By MOM

Shield Volcano Tharsis Tholus

MCC images

Ophir Chasma Terrain

Impact crater located SW of Huygens crater

Why is it so appreciable ?

Out of 51 only 21 Mars missions are successful

India is the first Asiatic Nation whose Mars Mission is successful

India is the first Nation in the world who has achieved this in the very first attempt only

Cheaper than any other mission to Mars

Heartiest Congratulations To Team ISRO

&

Thanks A Ton For Making Us Proud.