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Launch Date:03.04.1999

INSAT-2E, the last of the five satellites in the INSAT-2 series is a multi-purpose satellite for telecommunication, television broadcasting and meteorological services.INSAT-2E, evolved as the forerunner of the future INSAT-3 bus and was launched successfully by Ariane-42P from Kourou, French Guiana on April 03, 1999. It carried seventeen C band including lower extended C band transponders providing zonal and global coverage with an Effective Isotropic Radiated Power (EIRP) of 36 dBW.

It also carried a Very High Resolution Radiometer (VHRR) with imaging capacity in the visible (0.55-0.75 μm), thermal infra-red (10.5-12.5 μm) and water vapour (5.7-7.1 μm) channels and provided 2 km x 2 km, 8 km x 8 km and 8 km x 8 km ground resolution respectively. In addition to the above two payloads it had a Charge Coupled Device (CCD) camera providing 1 km x 1 km ground resolution in the Visible (0.63-0.69 μm), Near Infra-red (0.77-0.86 μm) and Shortwave Infra-red (1.55-1.70 μm) bands.

Some of the new technologies used in the INSAT-2E spacecraft were corrugated central cylinder for housing propellant tanks, embedded heat pipe panels for spacecraft equipment mounting, GaAs/Ge solar cells for power generation, Nickel Hydrogen cells for battery realization, Shaped memory alloy principle - based solar flap for compensation in seasonal variations in solar radiation pressure, usage of ASICs in bus systems like telemetry,telecommand electronics and attitude and orbit control electronics, large scale usage of hybrid micro circuits, shaped beam dual gridded reflectors for communication payload operations, linear CCD array providing 1 km resolution imagery from geostationary altitude, modular tray designs for bus system package realization etc


Communication and Meteorology

Platform System


Spacecraft Power

Solar Array:2150 Watts Batteries: Ni-H2 (60 Ah)

Lift-off Mass

2550 kg


3-axis body stabilized using bipropellant thrusters,momentum wheels/ reaction Wheels & Magnetic torquers Sensors: earth sensors, digital sun sensors, coarse analog sun sensors, solar panel sun sensors


12 C band transponders, 5 extended C band
transponders, 1 Data relay transponder, 1 SAR
transponder, VHRR/CCD array

Launch date

03 April 1999

Launch site

French Guyana

Launch vehicle

Ariane – 42P


Geosynchronous (83 deg east longitude)

Orbital Life



1.Completed 13 years of successful Operation.
2. Design and development of new bus a fore runner of third generation satellite,employing ASICs, HMCs and new generation radiation hardened processors.
3. Heat pipe embedded panels for thermal design.
4. Electrical and Mechanical design techniques for all
designs of dual gridded antenna.
5. Provided satisfying service to the discerning
international service provider INTELSAT and also
Indian TV broadcasters in the private sector.

6. Interfacing, managing and handling of international
service providers like INTELSAT and private TV broadcasters.
7. Exploiting the design capability of controlling the
attitude of the satellite using gyros with reference
derived from VHRR, CCD camera and solar panel sun
sensor and signals from ground antennae located in
Russia and Sri Lanka, due to non-availability of earth
sensors for control, uniquely evolved new techniques.


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