EDUSAT will be launched by the third flight of ISRO’s Geosynchronous Satellite Launch Vehicle. Designated as GSLV-F01, this is the first operational flight of the vehicle. In its two developmental test flights conducted in April 2001 and May 2003 respectively, GSLV successfully launched GSAT-1 and GSAT-2 satellites into Geosynchronous Transfer Orbits (GTOs).

In the first developmental test flight (GSLV-D1), the vehicle placed 1530 kg GSAT-1 into GTO and in the second developmental test flight (GSLV-D2), it placed 1825 kg GSAT-2 into GTO. In its first operational flight (GSLV-F01), GSLV will launch the 1950 kg EDUSAT.

The 49 metre tall GSLV is a three stage vehicle. The first stage, GS1, comprises a core motor with 138 tonne of solid propellant and four strap-on motors each with 40 tonne of hypergolic liquid propellants (UH25 and N204). The second stage has 39 tonne of the same hypergolic liquid propellants. The third stage (GS3) is a cryogenic stage with 12.5 tonne of Liquid Oxygen and Liquid Hydrogen.

The Aluminum alloy GSLV payload fairing is 3.4 m in diameter and is 7.8 m long. GSLV employs various separation systems such as Flexible Linear Shaped Charge (FLSC) for the first stage, pyro actuated collet release mechanism for second stage and Merman band bolt cutter separation mechanism for the third stage. Spacecraft separation is by spring thrusters mounted at the separation interface. The three-axis attitude stabilisation of GSLV is achieved by autonomous control systems provided in each stage. Single plane Engine Gimbal Control (EGC) of the four strap-ons of the first stage are used for pitch, yaw and roll control. The second stage has Engine Gimbal Control (EGC) for pitch and yaw and hot gas Reaction Control System (RCS) for roll control. Two swivellable vernier engines using LH2 and LOX provide pitch, yaw and roll control for the third stage during thrust phase and cold gas system during coast phase. The Inertial Guidance System (IGS) in the Equipment Bay (EB) housed above the third stage guides the vehicle till spacecraft injection. The closed loop guidance scheme resident in the on-board computer ensures the required accuracy in the injection conditions.

Satish Dhawan Space Centre (SDSC) SHAR, the launch station for GSLV, is located at 80 km north of Chennai on the east coast of India.

The facilities at SDSC include:
• Mobile Service Tower, Umbilical Tower and Launch Pedestal
• Solid Motor Preparation Facility
• Subsystem Preparation Facility
• Hardware Storage Facility
• Liquid/Cryogenic Propellant Storage and Transfer Facility
• Stage Preparation Facility for Cryogenic Stage
• Automatic Checkout and Control for Propellant Filling
• Safety and Fire Fighting Systems
• Satellite Preparation Facility
• Launch Control Centre and Mission Control Centre
• Precision C-band Radars and S-band Radar for tracking
• Telecommand System
• Intercommunication, CCTV system, Data Links, Range Timing System, Real Time Systems and Specialist Display System, Meteorology and Technical Photography
• TM data receiving stations

The state-of-the-art Second Launch Pad (SLP) has been established at SDSC and it is awaiting its commissioning. SLP will help to increase the frequency of launches from SDSC and the new facility is designed to reduce the occupancy time for the integration and launch.