PRESENTATION ON

MARS ORBITAL MISSION(MOM)

GUIDED BY:- Mr. SANKET THAKOR PHYSICS

SUBMITTED BY:HIMANSHI GUPTA(140120119057) / ME / I1PRACHI SHARMA(140120119216) / ME / I1VIDISHA VYAS(140120119253) / ME / I1

(2110011)

GANDHINAGAR INSTITUTE OF TECHNOLOGY

MARS ORBITAL MISSION(MANGALYAN)

ABOUT ISRO

MISSION OBJECTIVES• 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 maneuvers, 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: Exploration of Mars surface features, morphology, mineralogy and Martian atmosphere by indigenous scientific instruments.

ABOUT LAUNCH VEHICLE(PSLV)• 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.

ABOUT MANGALYAN• 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 entered orbit around Mars on 24 September 2014. • Mars Orbiter Mission is India's first interplanetary

mission to planet Mars with an orbiter craft designed to orbit Mars in an elliptical orbit.

BASIC DETAILS

1. MASS: The lift-off mass was 1,350 kg, including 852 kg of propellant mass.

2. DIMENSIONS: Cuboid in shape of approximately 1.5 m (4 feet 11 inches).

3. 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 W generation in Martian orbit. Electricity is stored in a 36 Ah Li-ion battery.

4. PROPULSION: Liquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit.

5. COMMUNICATION: The antenna array consists of a low-gain antenna, a medium-gain antenna and a high-gain antenna. It is used to transmit and receive the telemetry, tracking, commanding and data to and from the Indian Deep Space Network.

PAYLOADS

METHANE SENSOR FOR MARS (MSM)

• MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources.

• Data is acquired only over illuminated scene as the sensor measures reflected solar radiation.

• Methane concentration in the Martian atmosphere undergoes spatial and temporal variations.

• Hence global data is collected during every orbit.

MARS COLOR CAMERA (MCC)

• This tri-color Mars Color camera gives images & information about the surface features and composition of Martian surface.

• They are useful to monitor the dynamic events and weather of Mars.

• MCC will also be used for probing the two satellites of Mars – Phobos & Deimos.

• It also provides the context information for other science payloads.

Mangalyaan carries a camera payload that acquires color images of planet Mars. The payload weighs about 1.4 Kilograms. MCC covers a spectral range of 400 to 700 nanometers – the visible spectrum.

LYMAN ALPHA PHOTOMETER (LAP)

• Lyman Alpha Photometer (LAP) is an absorption cell photometer.

• It measures the relative abundance of deuterium and hydrogen from Lyman-alpha emission in the Martian upper atmosphere.

• Measurement of D/H (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet.

The Lyman Alpha Photometer payload consists of an Ultraviolet Detector that is equipped with gas-filled pure molecular hydrogen and deuterium cells with tungsten filaments 

MARS EXOSPHERIC NEUTRAL COMPOSITION ANALYSER (MENCA)

• MENCA is a quadruple mass spectrometer capable of analysing the neutral composition in the range of 1 to 300 amu with unit mass resolution.

• The heritage of this payload is from Chandra’s Altitudinal Composition Explorer (CHANCE) payload aboard the Moon Impact Probe (MIP) in Chandrayan-1 mission.

• A Quadruple Mass Spectrometer consists of four parallel metal rods with opposing rods being connected electrically. A radio frequency voltage is applied between the two pairs of rods and a direct current voltage is then superimposed on the RF voltage.

Depending on their mass-to-charge ratio, ions either enter and collide with the rods or make it through to the detector. The m/z of ions reaching the detector is a function of the voltage setting which allows the operator to select an ion with a particular mass-to-charge ratio to measure its abundance or run the instrument through a range of voltages to scan for a number of species that might be present.

Ions are generated via electron ionization. Electrons are produced through thermionic emission. The electrons are accelerated in an electric field and focused into a beam by a trap electrode. The atoms and molecules enter the ion source perpendicular to the electron beam. As high-energy electrons pass by and collide with the particles, large fluctuations in the electric field around the neutral molecules are caused leading to ionization.

THERMAL INFRARED IMAGING SPECTROMETER (TIS)

• TIS measure the thermal emission and can be operated during both day and night.

• Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement.

• Many minerals and soil types have characteristic spectra in TIR region.

• TIS can map surface composition and mineralogy of mars.

The TIS instrument weighs 4 Kilograms and consists of a spectrometer that features a typical infrared grating spectrometer design. In the common design, radiation is directed through an entrance slit (available light energy depends on light intensity of the source as well as the dimensions of the slit and acceptance angle of the system).

The slit is placed at the effective focus of a collimator that directs collimated radiation (focused at infinity) to a diffraction grating that acts as dispersive element. Another mirror refocuses the dispersed radiation onto a detector.

As IR radiation strikes the detector, the absorbing material is heated and changes its electrical resistance which can be measured via electrodes and processed into an intensity read-out in order to create an IR spectrum. 

PHASES OF THE MISSION(1)GEO CENTRIC PHASE (2)HELIO CENTRIC PHASE (3)MARTIAN PHASE

MARS ORBITER MISSION SPACECRAFT BEING PREPARED FOR A PRELAUNCH TEST AT SATISH DHAWAN SPACE CENTRE SHAR, SRIHAIRKOTA.

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.