ISRO - ACTIVE LAUNCHER : Part -1

Rockets of ISRO

Why the launcher, why not the booster? Because when a system, machine, or any device is made to work with its full potential, its destination, now the working function of the booster, is completely different. This device increases force, power, pressure, or effectiveness.

A launch vehicle, or Launcher, is used to carry spacecraft to space in any space research organization worldwide. Likewise, the Indian Space Research Organization (ISRO) has three active operational launch vehicles: the Polar Satellite Launch Vehicle (PSLV), the Geosynchronous Satellite Launch Vehicle (GSLV), and the Geosynchronous Satellite Launch Vehicle Mk-III (LVM3).

Polar Satellite Launch Vehicle (PSLV):

Configuration of PSLV-XL:

Gross Weight - 320 tons

Gross Height - 44.4 meters

Diameter - 2.8 meters

Feature - 04 stage vehicle, multiple satellite launch capability, and multiple

orbits capability

Technical Specification:

Vehicle Specifications:

Height - 44 meters

Diameter - 2.8 meters

Number of stages - 4

Lift off Mass - 320 tonnes (XL)

Variants - 4 (PSLV, CA, DL, QL, XL)

First Flight - September 20, 1993

Payload Fairing

The PSLV can place multiple payloads into orbit; thus, in the payload fairing, multi-payload adaptors are used, resulting in the feat of launching 10 satellites in a single mission into different orbits in 2008. In 2016, eight satellites were launched successfully into two different orbits in a single mission from the First Launch Pad, and 103 co-passenger satellites and the Cartosat-2 series satellites were launched by the 39th flight of PSLV-C37. PSLV C52 launched EOS-04, INS-2TD & InspireSat-1 into their designated orbits successfully on 14th February.

First Stage: PSI

S139 solid rocket motor that is augmented by 6 solid strap-on boosters was used in PSLV.

Engine S139

Fuel HTPB

Max. Thrust 4

Secondary Injection Thrust Vector (SITVC) for PS1 Stage

Secondary Injection Thrust Vector Control (SITVC)

The dimension of the PS1 stage is defined as follows:

2.8 m diameter with 139 tonnes of Hydroxyl Terminated Poly Butadiene (HTPB) propellant and a composite nozzle of area ratio 8.

At 35% of the length of the nozzle throat to exit, injecting an aqueous solution of Strontium Perchlorate [Sr(ClO4)2]in the nozzle divergent allows the pitch and yaw control of PSLV during the thrust phase of the PS1 motor.

Specification of SITVC:

Propellant - Sr(ClO4)2

PS1 SITVC for pitch & yaw control (24 Valves):

Flow Rate 12 l/s

Side Thrust 20 t max.

Number of injectors 24 in quadrants of 6 each

PS0 SITVC for roll augmentation (2 valves/motor):

Flow Rate 3.7 l/s

Side Thrust 600 kg

Reaction Control System (RCS) for PS1 Stage:

Reaction Control Systems (RCS) for PS1 Stage

To meet the control requirements during the coasting phase of PS1, the RCS is designed. For PS1, RCS consists of two independent liquid engine packages mounted axially at 180° apart at the circumference of the base shroud.

Specification of PS1 RCS:

Thrust Main Engine 640 kgf

ACS Thrusters 150 kgf x 2

Propellants MMH / MON-3

Diameter 700 mm

Length 2.6 m

Subscribe for PSLV Stage -2.