MARS ORBITER MISSION PSLV-C25, twenty fifth flight of PSLV launched Mars Orbiter Mission Spacecraft from the First Launch Pad at Satish Dhawan Space Centre SHAR, Sriharikota Mars Orbiter Mission is India's first interplanetary mission to planet Mars with an orbiter craft designed to orbit Mars in an elliptical orbit It has been configured to carry out observation of physical features of mars and carry out limited study of Martian atmosphere with tollowing tive pavloads.
1. Mars Colour Camera (MCC) Spectrometer (TIS) (MSM) Composition Analyser Mars at Departure 2. Thermal Infrared Imaging Departure 01-12-13 3. Methane Sensor for Mars Earth at MOI 4. Mars Exospheric Neutral Vernal Equinox (MENCA) 5. Lyman Alpha Photometer (LAP) Mars Orbit Insertion(MOI) 24-09-14 Trajectory Design
BHUVAN Bhuvan is a Geo-portal. It is providing visualisation services and Earth observation data to users in public domain. Besides, the portal also services several users for their remote sensing application needs. BHOOSAMPADA Bhoosampada launched in 2009 .lt is an Information Portal of India Space Research Organisation(ISRO). Bhoosampada website provides the annual land use/Land Cover (LULC) assessent at national state and district level, The seasonal water body and snow cover distribution can also be visualized
Indian Regional Navigation Satellite System (IRNSS IRNSS is an independent regional navigation satellite system being developed by India India as well as the region extending up to 1500 km from its boundary Space Segment consists of seven satellites, three satellites in GEO stationary orbit (GEO) and four satellites in Geo Synchronous Orbit (GSO) Aditya - L1 (Future Mission) The Aditya-1 mission was conceived as a 400kg class satellite carrying one payload, the Visible Emission Line Coronagraph (VELC) and was planned to launch in a 800 km low earth orbit
PROPELLANT Liquid PROPELLANT Highly Refined kerosene used as fuel and liquid Oxigen used as Oxidizer. SOLID PROPELLANT Solid propellants are mainly used in rocket propulsion applications. They are very energetic and produce high temperature gaseous products on combustion. hydroxyl-terminated polybutadiene (HTPB) Cryogenic Engine Oxvgen liquifies at -183 deg C and Hydrogen at -253 deg C.
Cryogenic rocket stage is more efficient and provides more thrust for every kilogram of propellant it burns compared to solid and earth- storable liquid propellant rocket stages.
Upendra Kumar Singh
UPENDRA KUMAR SINGH MASTER IN COMPUTER APPLICATION APPEARED TWO TIMES IN UPSC CSE MAINS