BHASKARA-I

The First Experimental Remote Sensing Satellite built in India. The onboard TV camera sent imageries which we reused in the field of Hydrology and Forestry. SAMIR sent rich scientific data which were used for oceanographic studies. Mission Experimental Remote Sensing Weight 442 kg onboard power 47 Watts Communication VHF band Stabilization Spin stabilized (spin axis controlled) Payload TVcameras, three band Microwave Radiometer (SAMIR) Launch date Jun 07,1979 Launch site Volgograd Launch Station (presently in Russia) Launch vehicle C-1Intercosmos Orbit 519 x 541 km Inclination 50.6 deg Mission life One year (nominal) Orbital Life About 10 years ( Re-entered in 1989 )

image by mangalyaan

Taken using the Mars Color Camera from an altitude of 8449 km, this image has a spatial resolution of 439 m and is centered around Lat: 20.01N, Lon:31.54E

Aryabhata

	Launch Date	19.04.1975
The First Indigenously built Indian Satellites
Mission Scientific/ Experimental Weight 360 kg On board power 46 Watts Communication VHF band Stabilization Spinstabilize Payload X-ray Astronomy Aeronomy & Solar Physics Launch date April 19,1975 Launch site Volgograd Launch Station (presently in Russia) Launch vehicle C-1 Intercosmos Orbit 563 x 619 km Inclination 50.7 deg Mission life 6 months(nominal), Spacecraft mainframe active till March,1981 Orbital Life Nearly seventeen years (Re-entered on February 10,1992)

image of Mars taken by Mangalyaan

Mars Orbiter Spacecraft captures its first image of Mars. Taken from a height of 7300 km; with 376 m spatial resolution. 

For High Resolution picture
Click
Download Hi-Res

BE PROUD GREAT SUCCESS

MANGALYAAN SUCCESSFULLY REACHED MARS ATMOSPHERE.  WE BE PROUD BE AN INDIAN ... BE AN ISRO INDIAN
GREAT SALUTE TO ISRO SCIENTISTS

COMPARISON OF MARS AND EARTH

MANGALYAAN - 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:

• 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.