ROCKET_LIQUID

Vikalp dongre

Liquid RocketVikalp Dongare

1MJ13MAE13

[email protected]

History

Rocket technology first became known to Europeans following their use by the Mongols Genghis Khan and Ögedei Khan, when they conquered parts of Russia, Eastern, and Central Europe --12th

gunpowder (75% of saltpeter, 15% of carbon and 10% of sulphur).

The name Rocket comes from the Italian Rocchetta (i.e. little fuse), a name of a small firecracker created by the Italian artificer Muratori in 1379.After that Korea 15th

Between 1529 and 1556 Conrad Haas wrote a book that described the concept of multi-stage rocketsindiaThe first iron cased and metal-cylinder rocket artillery made from iron tubes, were developed by the weapon suppliers of Tipu Sultan an Indian ruler of the Kingdom of Mysore

Vikalp dongre

Vikalp dongre

Vikalp dongre

Types

Vikalp dongre

Liquid

Vikalp dongre

Requirement

For long distance Variable thrust- the amount of fuel and rate of burn can be changed in

flight Liquid-fuel boosters are more easily re-usable Liquid-fueled rockets have higher specific impulse than solid rockets The primary performance advantage of liquid propellants is due to the

oxidizer. Several practical liquid oxidizers (liquid oxygen , nitrogen tetroxide, and hydrogen peroxide) are available which have better specific impulse than the ammonium perchlorate used in most solid rockets

liquid propellants are cheaper than solid propellants

Vikalp dongre

Vikalp dongre

Oxidizer liquid oxygen (LOX, O2)T-Stoff (80% hydrogen peroxid)nitric acid(HNO3)inhibited red fuming nitric acid

(IRFNA, HNO3 + N2O4)

nitric acid 73% with dinitrogen tetroxide 27% (=AK27)

Vikalp dongre

Fuelliquid hydrogen(LH2, H2) kerosene or RP-1alcohol (ethanol, C2H5OH)hydrazine(N2H4)Aerozine 50monomethylhydrazine(MMH,

(CH3)HN2H2)

Vikalp dongre

Propellant

LOX and liquid hydrogen, used in the Space Shuttle orbiter LOX and kerosene (RP-1). Used for the first stages of the Saturn

V, Atlas V and Falcon, the Russian Soyuz, Ukrainian Zenit Nitrogen tetroxide(N2O4) and hydrazine(N2H4), MMH, or UDMH.

Used in military, orbital, and deep space rockets because both liquids are storable for long periods at reasonable temperatures and pressure PSLV

hydrogen peroxide and kerosene hydrazine(N2H4) and red fuming nitric acid – Nike Ajax Antiaircraft

Rocket monomethylhydrazine (MMH, (CH3)HN2H2) and dinitrogen tetroxide

– Space Shuttle orbiter's Orbital maneuvering system (OMS) engines and Reaction control system (RCS) thrusters

Vikalp dongre

Combustion A liquid Rocket combustion chamber to designed to accommodate And allow to sufficient time for following jobs

Injection ,atomization ,vaporization and even mixing liquid fuel and oxidizer Thermal decomposition of oxidizer to enable chemical reaction with fuel Ignition and flame stabilization and combustion of fuel, oxidizer mixture

Vikalp dongre

Even dispersion of combustion products towards the nozzle The volume ,length and shape of combustion chamber needs to selected To all the steps. Various fuel and oxidizer combustion provides for characteristic lengthL* for rocket

L* =CC volume/throat aeraThe value of L* found experimently

Vikalp dongre

Desirable properties of liquid propellant

Low freezing point High specific gravity Good chemical stability during storage High specific heat and high thermal coundtivity , High thermal

decomposition Pumping property – flowablity (under cryogenic condition) Temperature stability of physical property (viscosity ,vapor pressure etc.)Under cryogenic condition.

Vikalp dongre

Vikalp dongre

Vikalp dongre

Vikalp dongre

Vikalp dongre

Currently, six governments have successfully developed and deployed cryogenic rocket engines

United States

European Space Agency

Russia

China

India CE-7.5 CE-20

Japan

Vikalp dongre

GSLV-D5 MK II, launched on January 5, 2014

Vikalp dongre

CE-7.5The CE-7.5 is a cryogenic rocket engine developed by India to power the upper stage of its GSLV Mk-2 launch vehicle

CE-7.5 is a regeneratively cooled, variable thrust, staged combustion cycle engine.

SpecificationsThe specifications of the engine:Operating Cycle - Staged combustionPropellant Combination - LOX / LH2Thrust Nominal (Vacuum) - 75 kNOperating Thrust Range - 73.55 kN to 93.1 kN (To be set at any fix values)Chamber Pressure (Nom) - 58 barEngine Mixture ratio (Oxidizer/Fuel by weight) - 5.05Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)Engine Burn Duration (Nom) - 720 secondsPropellant Mass - 12800 kg

Vikalp dongre

Vikalp dongre