Mars Orbiter Mission

Mars Orbiter Mission ( MOM), unofficially in the media also Mangalyaan (Hindi: मंगलयान, Mars - traveler ') called, is a spacecraft of the Indian space agency ISRO, which was launched to Mars with a PSLV rocket.


The launch took place on November 5, 2013 at 9:08 UTC with a PSLV -XL rocket from Satish Dhawan Space Centre in Andhra Pradesh. First, she swung into orbit around the Earth. On November 30, 2013, it left then with a 22 -minute burn of the main engine orbit and headed to Mars. It is expected to reach Mars on 22 September 2014 and with 500 x Swivel there in a highly elliptical orbit 80,000 kilometers. The Indian ISRO would allow the fourth Space Agency, which would have sent a probe to Mars by the Soviet Union, the U.S. and Europe. The main task of the mission is to bring the probe successfully to Mars; special scientific results are not planned for this mission.


The structure of the Mars probe is based on the experience with IRS/INSAT/Chandrayaan-1 and was adjusted according to requirements. The central cylinder is made of aluminum and carbon fiber reinforced plastic ( CFRP ), the panels of metal honeycomb and CFRP. The structural components were manufactured by Hindustan Aeronautics (HAL ) in Bangalore, were assembled the basic structure and the subsystems of the Mars orbiter in ISRO Satellite Centre ( ISAC ) in Bangalore, where the installation of the scientific payload carried.

To the centrally mounted fuel tank and the main engine are grouped eight thrusters with 22 Newton thrust, four reaction wheels for attitude control, the three-part solar panels as well as one means profit (MGA ), high income ( HLA) and TT & C antenna ( HGA ). The HGA antenna with a 2.2 meter diameter reflector communicated in the S-band and is used for receiving and sending telemetry and TTC data to / from the Indian Deep Space Network ( IDSN ). The sensor is completed by each sensor a Star, Solar Panel Sun Sensor Coarse and Analogue Sun sensor. The systems are designed for autonomous operation. MAR31750 the processor forming the core of the control system Attitude and Orbit Control ( AOCE ).

The strong 440 Newton Hauptptriebwerk (Liquid Apogee Motor ) of the Mars probe is designed to be very robust: For fuel pressure from 0.9 to 2.0 MPa, fuel temperatures from 0 to 65 ° C, fuel - oxidizer mixture ratios of 1.2 to 2.0 and voltages from 28 to 42 volts. The engine can be fired several times, could be operated at full load and will be up and running again after a 10 -month journey to Mars for about an hour. Are driven main and capable engines with a mixture of MMH and N2O4, for which a fuel reserve of 852 kg or 390 liters are available.

The power supply is provided with three solar panels, each 1.8 m x 1.4 m, which are designed for an output of 840 watts in Mars orbit. A Li- ion cell stores 36 amp-hours.

The launch mass was 1337 kg; the time available for the scientific payload mass had to be reduced for reasons of weight to 14.5 kilograms.


The payload of 15 kg distributed on five instruments:

  • Mars Exospheric Neutral Composition Analyzer ( Menca ) - atmosphere analysis
  • Methane Sensor For Mars ( MSM) - atmosphere analysis
  • Mars Color Camera (MCC ) - color camera
  • Sample For Infrared Spectroscopy for Mars ( Prism ) - Infrared Camera
  • Lyman -alpha photometer - measuring atomic hydrogen in the Martian atmosphere