2

Presented By: Pawan Rama Mali

CONTENTS

• What is CRYOGENICS

• Propellants used in CRE*

• Construction of CRE

• CRE around the world

• Challenges in CRE

• CONCLUSION

* CRE: Cryogenic Rocket Engine

PRINCIPLE OF ROCKET ENGINE

The basic principle driving a rocket engine are: Newton’s third law of motion

Law of conservation of momentum

Derives thrust like all other rocket engines by accelerating an impulse carrier to high speeds

Chemical energy Kinetic energy

CLASSIFICATION OF ROCKET PROPELLANTS

CRYOGENIC PROPELLENTS

What is Cryogenics ?

• Greek words “Kyros” - cold or freezing and“genes” - born or produced

• Cryonics is NOT the same as Cryogenics

• In physics, Cryogenics is the study of theoperations at very low temperature (below −150°C, −238 °F or 123 K) and the behaviour ofmaterials at these temperatures.

• Propulsion system

• Isp of different propulsion systems:

Solid propulsion = 265 sEarth-storable liquid propulsion = 285 sCryogenic propulsion = 450 s

ALSO, BECAUSE SATELLITES ARE BECOMING HEAVIER….

INSAT 1A [1982] –1150 kgINSAT 2A [1992] –1900 KgINSAT 3C [2002] –2750 KgINSAT 4A [2005] –3080 kg

IN ROCKET ENGINES

• Cryogenic technology involves the use of rocketpropellants at extremely low temperatures.

• Liquid Oxygen (LOX) & Liquid Hydrogen (LH2)

• Oxygen remains at liquid only at temperaturesbelow -183 ° C and hydrogen below - 253 ° C.

THE FIRST OPREATIONAL CRE

THE FIRST OPREATIONAL CRE

First successful flight in 1963 and is

still used on the Atlas V rocket.

The Japanese LE-5 engine flew in

1977

French HM-7 in 1979

Chinese YF-73 in 1984

The Soviet Union in 1987

(AMERICAN) - ATLAS V

CRYOGENIC PROPELLANTS

• Combination of Cryogenicfuel and oxidizer.

• Cryogenic fuel- Storage atextremely low temperaturein a liquid state such asLiquid Hydrogen.

• Storage of propellant isdifficult task.

Eg: LH2 and LOX

FACTORS FOR SELECTING THE PROPELLANT

• Ease of operation

• Cost

• Hazards

• Performance

CRYOGENIC FUEL- OXIDIZER COMBINATION

• Liquid hydrogen and Liquid oxygen

• Kerosene(RP-1) and Liquid oxygen

• Unsymmetrical dimethyl hydrazine and Nitrogen tetra oxide

• Hydrazine and Aerozine-50

DISADVANTAGES OF CRYOGENIC PROPELLANTS

• Difficult to store, so less desirable for usage.

• Liquid hydrogen has low density as compare to other liquid propellant.

• Kerosene is more damaging than hydrogen.

• Lithium and fluorine are both extremely corrosive and toxic.

PERFORMANCE OF PROPELLANTS

Propellant mix Vacuum Isp

(seconds)Effective exhaust

velocity (m/s)

Liquid hydrogen/ Liquid oxygen

455 4462

Kerosene(RP-1)/ Liquid oxygen

358 3510

Unsymmetrical dimethyl hydrazine/ Nitrogen tetra

oxide

333 3369

Hydrazine/ Aerozine-50 312 3126

CONSTRUCTION OF CRE

• Combustion chamber • Pyrotechnic igniters • Fuel injector • Fuel and Oxidizer Cryo-pumps • Gas turbine • Cryo-valves• Regulators • External fuel tanks • Nozzle

Combustion chamber

CONSTRUCTION OF CRE

Pyrotechnic igniters

CONSTRUCTION OF CRE

Fuel injector

External fuel tanks

Cryo-pumps

Axial-flow pump Centrifugal pump

Pre-burners and thrust control system

Schematic Diagram of CRE

Assembly animation

CRE AROUND THE WORLD

RL-10

First flight-27 November1962

Upper stage engine centaur

Thrust- 110 KN

Isp- 450 seconds

J-2

First flight-26 June 1966

Upper stage engine of AS-201

Thrust- 1033.1 KN

Isp- 421 seconds

UNITED STATES

RS-25

• First flight- 1981

• Space shuttle main engine

RS-68

• First flight- 1998

• First stage engine of delta 4 rocket

UNITED STATES

LE-7

• First flight- 1977

• H-2 satellite launch vehicle

• Thrust - 1078 KN

• Isp- 446 seconds

LE-5

• Thrust -102.9 KN

• Isp -450seconds

JAPAN

VULCAIN

First flight-1996

Main stage

Thrust- 1015 KN

Isp- 440 seconds

FRANCE

HM7

First flight-1979

Upper stage

Thrust- 64.8 KN

Isp- 446 seconds

YF-73

First flight- 1984

Long march

Thrust- 44.15 KN

Isp- 432 sec

YF-75

First flight- 1994

Thrust-78.45 KN

Isp- 437 sce

CHINA

RD-0146 First flight- 2001

Upper stage of booster

Thrust- 98100 KN

Isp- 463 sec

RD-0120

First flight- 1987

Expendable launch system

Thrust- 1961 KN

Isp- 455 sec

RUSSIA

C E 7.5

• The specifications and key characteristics of the engine are:

• Propellant Combination – LOX / LH2

• Maximum thrust (Vacuum) – 75 kN

• Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN

• Engine Specific Impulse - 454 seconds

• Steering during thrust: provided by two gimballed steering engines

C E 20

• Propellant Combination -LOX / LH2

• Thrust Nominal (Vacuum) -200 kN

• Operating Thrust Range -180 kN to 220 kN

• Engine Specific Impulse -443 seconds

DEVELOPMENTS IN ISRO

YEARS EVENTS

1986 Launch a program to develop 1 ton cryogenic engine

1987 Second generation INSAT- 2 series

1989 France offered 7 ton HM7

1990 India approved an offer with Soviet Union’s

1993 Soviet Union’s backed out of the deal with India

2001-2007 Development GSLV-D1 and cryogenic upper stage project speeded

up

YEARS EVENTS

2008 First indigenous cryogenic engine tested for 200 seconds

2009 GSLV-D3 successfully tested for 800 seconds

2010 Failure if GSLV-D3 with GSAT-4

2011 Fuel booster turbo pump modified

2012 ISRO test cryogenic engine under vacuum

2013 Assembly of GSLV-D5 started

2014 Successfully launch of GSLV-D5

DEVELOPMENTS IN ISRO

OTHER APPLICATIONS OF CRYOGENICS

► Cryosurgery

► Electric power transmission

► Frozen food

► Blood banks

► Infrared Sensors

► Electronics

CHALLENGES

Thermal contraction

Storage problems

High density

Highly reactive gases

Overall cost of propellants relatively high

CHALLENGES

Leakage problems

Boil off rate

Hydrogen embrittlement

Zero gravity conditions

FUTURE TRENDS OF CRYOGENIC MATERIALS

• Computationally designed materials and processing

• Unique nano-phase materials systems for new

applications at low temperatures

• Smart materials and systems based on new alloys

• Durability and performance

• Quality assurance and testing

CONCLUSION

Any Queries

Thank you