Yesterday, will be scripted in the India’s development
towards space. A day after Diwali rockets was fired in this part of the
country, "the big one" blasted off from the first launch pad in
Sriharikota on yesterday afternoon at 2:38 PM, firing the ambition of a nation, and
the imagination of many others.
1. Geo Centric Phase:
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| PSLV-C25 ROCKET AT SRIHARIKO |
I just want to update my readers about the MARS
MISSION. Before going to the mars mission, we have to know that India have
taken a giant leap in the area of space. Why this mission is a giant leap
because of all the planets in the solar system, Mars has sparked the greatest
human interest. The conditions in Mars are believed to be hospitable since the
planet is similar to Earth in many ways.
The Mars Orbiter Mission is the INDIA'S FIRST
INTERPLANETARY MISSION to planet. Mars with an orbiter craft is designed to
orbit the mars in an elliptical path.
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| LAUNCH SUCCESSFUL |
Firstly we have to know the objective of this
mission.
There are vastly two types of objectives
TECHNOLOGICAL OBJECTIVES:
- Design and realization 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.
- Incorporate autonomous features to handle contingency situations.
SCIENTIFIC
OBJECTIVES:
- Exploration of Mars surface features, morphology, mineralogy and Martian atmosphere by indigenous scientific instruments.
PAYLOADS:
Generally, the payloads consists of three categories
namely
- Atmospheric studies
In this it involves the use of LYMAN ALPHA PHOTOMETER (LAP) and METHANE SENSOR FOR MARS (MSM).
- Particle Environment Studies
This involves the usage of MARS EXOSPHERIC NEUTRAL COMPOSITION ANALYZER (MENCA).
- Surface Imaging Studies
In this area it involves the usage of MARS COLOR CAMERA (MCC) and THERMAL INFRARED IMAGING SPECTROMETER (TIS).
To know the elaborate details of each components
visit this link http://www.dnaindia.com/india/commentary-rs450-crore-indian-mars-orbiter-mission-expedition-seeks-to-find-if-there-is-methane-on-mars-1913946
MISSION
PROFILE:
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| TRAJECTORY DESIGN |
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 point of Mars , it is maneuvered in to
an elliptical orbit around Mars by firing the Liquid Engine.
The mission consists of following three phases:
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| MARTIAN ORBIT |
1. Geo Centric Phase:
In this phase, the
spacecraft is injected into an elliptic parking orbit by the launcher. There
are six main engines in the spacecraft when these burns the spacecraft will
gradually move carefully into a hyperbolic trajectory from where the spacecraft
escapes from the Earth’s surface of influence (SOI). 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 will leave 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 recurs 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 in a hyperbolic trajectory. At the time the spacecraft reaches the closest approach to Mars, it is captured into planned orbit around mars which is called the Mars Orbit Insertion (MOI) manoeuvre. The ISRO plans to launch the Mars Orbiter Mission during the November 2013 window utilizing minimum energy transfer opportunity.
The spacecraft will leave 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 recurs 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 in a hyperbolic trajectory. At the time the spacecraft reaches the closest approach to Mars, it is captured into planned orbit around mars which is called the Mars Orbit Insertion (MOI) manoeuvre. The ISRO plans to launch the Mars Orbiter Mission during the November 2013 window utilizing minimum energy transfer opportunity.
SPACECRAFT:
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| DISASSEMBLED SPACECRAFT |
The spacecraft configuration is a balanced mix of
design from flight proven IRS/INSAT/Chandrayaan-1 bus. Modifications required
for Mars mission are in the areas of Communication, Power, and Propulsion
systems.
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| SPACECRAFT |
The specifications of the space craft are:
- 390 liters capacity propellant tanks accommodate a maximum of 852 kg of propellant which is adequate with sufficient margins.
- A Liquid Engine of 440 N thrust is used for orbit raising and insertion in Martian Orbit.
- The spacecraft requires three solar panels (size 1800 X 1400 mm) to compensate for the lower solar irradiance.
- Antenna System consists of Low Gain Antenna (LGA), Medium Gain Antenna (MGA), and High Gain Antenna (HGA).
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