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Third
Stage
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The
third stage is 2.8 m in dia.and uses liquid hydrogen (LH2) and liquid oxygen
(LOX) in two separate tanks of aluminium alloy interconnected by an inter-stage
structure. Total propellant loading is 12.5 t. |
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PAYLOAD
FAIRING
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| GSLV payload fairing is made of aluminium alloy and is 3.4 m dia and 7.8 m long consisting of 2 halves. It protects the spacecraft from hostile flight environment during ascent phase. | |||||||||
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Stage
Separation Systems
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vehicle is provided with various separation systems such as Flexible Linear
Shaped Charge (FLSC) for first stage (GS1), pyro actuated collet release
mechanism for second stage (GS2) and Merman band bolt cutter separation
mechanism for third stage (GS3). GS1- spacecraft separation is by spring thrusters mounted at the separation interface. |
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Inertial
Navigation and Guidance
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| The
three-axis attitude stabilization of the vehicle is achieved by autonomous
control systems provided in each stage. Single plane Engine Gimbal Control
(EGC) of the four strapons 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. For the third
stage, two swivellable vernier engines, using LH2 and LOX, provide pitch,
yaw and roll control during thrusting 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. |
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