MOM IT WAS SENT BY ISRO ( indian space research organation ) it was sent in the year of 2013 from sriharikota , kerala a state of India the space center is (satish dhawan space center) a great astrophysicst of india . 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:
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.
Incorporate autonomous features to handle contingency situations.
B. Scientific Objectives:
Exploration of Mars surface features, morphology, mineralogy and Martian atmosphere by indigenous scientific instruments.
,Mars Orbiter Mission Profile
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 opport
ISRO Telemetry Tracking and Command Network (ISTRAC) will be providing support of the TTC ground stations, communications network between ground stations and control center, Control center including computers, storage, data network and control room facilities, and the support of Indian Space Science Data Center (ISSDC) for the mission. The ground segment systems form an integrated system supporting both launch phase, and orbital phase of the mission.
Launch Phase
- The launch vehicle is tracked during its flight from lift-off till spacecraft separation by a network of ground stations, which receive the telemetry data from the launch vehicle and transmit it in real time to the mission computer systems at Sriharikota, where it is processed.
- The ground stations at Sriharikota, Port Blair, Brunei provide continuous tracking of the PSLV-C25 from liftoff till burnout of third stage of PSLV-C25.
- Two ships carrying Ship Borne Terminals (SBT) are being deployed at suitable locations in the South Pacific Ocean, to support the tracking of the launch vehicle from PS4 ignition till spacecraft separation.
Orbital Phase
- After satellite separation from the launch vehicle, the Spacecraft operations are controlled from the Spacecraft Control Centre in Bangalore.
- To ensure the required coverage for carrying out the mission operations, the ground stations of ISTRAC at Bangalore, Mauritius, Brunei, and Biak are being supplemented by Alcantara and Cuiaba TTC stations of INPE, Brazil, Hartebeestoek TTC station of SANSA and the DSN network of JPL, NASA.
- See more at: http://www.isro.gov.in/pslv-c25-
M3tb.dpufunity.
PSLV-C25, twenty fifth flight of PSLV will launch Mars Orbiter Mission Spacecraft from the First Launch Pad at Satish Dhawan Space Centre SHAR, Sriharikota.
The challenging PSLV-C25 mission is optimised for the launch of Mars Orbiter Mission spacecraft into a highly elliptical Earth orbit with a perigee (nearest point to Earth) of 250 km and an apogee (farthest point to Earth) of 23,500 km with an inclination of 19.2 degree with respect to the equator.
| PSLV- C25 Stages at a Glance |
| |
STAGE-1 |
PSOM-XL |
STAGE-2 |
STAGE-3 |
STAGE-4 |
| Propellant |
Solid
(HTPB
Based) |
Solid
(HTPB
Based) |
Liquid
(UH25 + N2O4) |
Solid
(HTPB Based) |
Liquid
(MMH + MON-3) |
| Propellant Mass (Tonne) |
138 |
12.2 |
42 |
7.6 |
2.5 |
| Peak Thrust (kN) |
4800 |
718 |
799 |
247 |
7.3 X 2 |
| Burn Time (sec) |
103 |
50 |
148 |
112 |
525 |
| Diameter (m) |
2.8 |
1 |
2.8 |
2.0 |
2.8 |
| Length (m) |
20 |
12 |
12.8 |
3.6 |
2.7 |
