Cryogenics is the study of the operations at very low temperature (below −150 °C, −238 °F or 123 K) and the behaviour of materials at these temperatures.
This document summarizes the cryogenic engine used for India's first geo-synchronous satellite launch vehicle. The engine used liquid oxygen and liquid hydrogen propellants, providing an high specific impulse of 450 seconds for improved efficiency. Key specifications of the cryogenic engine are provided such as its thrust rating, chamber pressure, nozzle area ratio, and mass. While cryogenic engines offer benefits like non-toxic propellants and high performance, they also pose challenges including the need for complex low-temperature storage and transfer systems as well as ignition challenges. The launch discussed ultimately failed, but future success is hoped for to help launch increasingly heavier satellites.
This document discusses cryogenic rocket engines (CRE). It begins by defining cryogenics as the study of operations and behaviors of materials at temperatures below -150°C. It then discusses that CRE use cryogenic liquid propellants like liquid oxygen and liquid hydrogen, which must be stored at extremely low temperatures. The document outlines the various CRE developed around the world by countries like the US, Japan, France, China, Russia. It also discusses the challenges in developing CRE and India's indigenous developments like the CE7.5 and CE20 engines.
Cryogenic engines use cryogenic fuels that must be stored at extremely low temperatures in liquid form, such as liquid hydrogen at -253°C and liquid oxygen at -183°C. The basic principle is that the chemical energy from burning the cryogenic fuel in the thrust chamber is converted to kinetic energy through expansion in the rocket nozzle to produce thrust. Some key components of a cryogenic engine include the combustion chamber, fuel and oxidizer pumps, valves and regulators, fuel tanks, and rocket nozzle. Cryogenic engines provide high energy density but the low temperatures make storage and leakage challenges. They find applications in rocketry due to their performance and in other areas such as cooling and medical uses.
This document provides an overview of cryogenic rocket engines. It discusses that cryogenic fuels require storage at extremely low temperatures to remain liquid, and the most widely used combination is liquid hydrogen and liquid oxygen. The major components of cryogenic rocket engines are described, including the combustion chamber, injectors, pumps, valves and tanks. Advantages are high energy density and clean, non-toxic exhaust, while challenges include difficulties storing cryogenic liquids for long periods. Common applications are in rockets utilizing these high-performance fuels.
Cryogenics is the study of low temperatures and the production of low temperatures using liquefied gases like liquid nitrogen and liquid helium. Liquid rocket engines that use cryogenic fuels like liquid hydrogen and liquid oxygen provide some of the highest performance but also require bulky cryogenic fuel tanks and heavy insulation. There are two main types of liquid rocket engines - pressure-fed engines which use tank pressure to pump propellants and are simpler but provide lower performance, and pump-fed engines which use turbopumps to provide higher pressures and performance but are more complex. Cryogenic engines have been used successfully in applications like space shuttles and rockets where high performance outweighs the challenges of storing cryogenic fuels.
Cryogenic rocket engines use cryogenic (very cold) liquid fuels like liquid hydrogen and liquid oxygen that are stored at extremely low temperatures. They provide several advantages like high energy density and clean, non-polluting exhaust but also have challenges like boil-off losses and material compatibility issues. The document outlines the history, construction, power cycles like gas-generator and pressure-fed, combustion process in the thrust chamber, and advantages and disadvantages of cryogenic rocket engines.
Aerojet has nearly 50 years of experience with hydrocarbon propellants including engines for the Titan I and experience refurbishing and testing Russian NK-33 engines. The NK-33 was an oxygen-rich staged combustion cycle engine originally developed in the 1960s-70s for Russia's N1 moon rocket. Aerojet has worked to qualify the NK-33 for use on Orbital Sciences' Antares rocket, conducting tests of over 1,500 seconds total duration to demonstrate the engine can meet the rocket's duty cycle requirements. Oxygen-rich staged combustion engines provide higher performance than gas generator cycle engines and are more widely used internationally, while the U.S. has less experience with this engine cycle.
The advantages of different types of propellantsArya Ramaru
This document discusses and compares the four main types of chemical rocket propellants: solid, liquid, gas, and hybrid. Solid propellants are easier to store but have lower performance than liquids. Liquid propellants can be throttled and restarted but are more complex. Gas propellants have low density and hybrids combine solid fuel with liquid oxidizers for benefits like throttling. In conclusion, further research on current solid and liquid fuel technologies could help commercialize spaceflight.
This document summarizes the cryogenic engine used for India's first geo-synchronous satellite launch vehicle. The engine used liquid oxygen and liquid hydrogen propellants, providing an high specific impulse of 450 seconds for improved efficiency. Key specifications of the cryogenic engine are provided such as its thrust rating, chamber pressure, nozzle area ratio, and mass. While cryogenic engines offer benefits like non-toxic propellants and high performance, they also pose challenges including the need for complex low-temperature storage and transfer systems as well as ignition challenges. The launch discussed ultimately failed, but future success is hoped for to help launch increasingly heavier satellites.
This document discusses cryogenic rocket engines (CRE). It begins by defining cryogenics as the study of operations and behaviors of materials at temperatures below -150°C. It then discusses that CRE use cryogenic liquid propellants like liquid oxygen and liquid hydrogen, which must be stored at extremely low temperatures. The document outlines the various CRE developed around the world by countries like the US, Japan, France, China, Russia. It also discusses the challenges in developing CRE and India's indigenous developments like the CE7.5 and CE20 engines.
Cryogenic engines use cryogenic fuels that must be stored at extremely low temperatures in liquid form, such as liquid hydrogen at -253°C and liquid oxygen at -183°C. The basic principle is that the chemical energy from burning the cryogenic fuel in the thrust chamber is converted to kinetic energy through expansion in the rocket nozzle to produce thrust. Some key components of a cryogenic engine include the combustion chamber, fuel and oxidizer pumps, valves and regulators, fuel tanks, and rocket nozzle. Cryogenic engines provide high energy density but the low temperatures make storage and leakage challenges. They find applications in rocketry due to their performance and in other areas such as cooling and medical uses.
This document provides an overview of cryogenic rocket engines. It discusses that cryogenic fuels require storage at extremely low temperatures to remain liquid, and the most widely used combination is liquid hydrogen and liquid oxygen. The major components of cryogenic rocket engines are described, including the combustion chamber, injectors, pumps, valves and tanks. Advantages are high energy density and clean, non-toxic exhaust, while challenges include difficulties storing cryogenic liquids for long periods. Common applications are in rockets utilizing these high-performance fuels.
Cryogenics is the study of low temperatures and the production of low temperatures using liquefied gases like liquid nitrogen and liquid helium. Liquid rocket engines that use cryogenic fuels like liquid hydrogen and liquid oxygen provide some of the highest performance but also require bulky cryogenic fuel tanks and heavy insulation. There are two main types of liquid rocket engines - pressure-fed engines which use tank pressure to pump propellants and are simpler but provide lower performance, and pump-fed engines which use turbopumps to provide higher pressures and performance but are more complex. Cryogenic engines have been used successfully in applications like space shuttles and rockets where high performance outweighs the challenges of storing cryogenic fuels.
Cryogenic rocket engines use cryogenic (very cold) liquid fuels like liquid hydrogen and liquid oxygen that are stored at extremely low temperatures. They provide several advantages like high energy density and clean, non-polluting exhaust but also have challenges like boil-off losses and material compatibility issues. The document outlines the history, construction, power cycles like gas-generator and pressure-fed, combustion process in the thrust chamber, and advantages and disadvantages of cryogenic rocket engines.
Aerojet has nearly 50 years of experience with hydrocarbon propellants including engines for the Titan I and experience refurbishing and testing Russian NK-33 engines. The NK-33 was an oxygen-rich staged combustion cycle engine originally developed in the 1960s-70s for Russia's N1 moon rocket. Aerojet has worked to qualify the NK-33 for use on Orbital Sciences' Antares rocket, conducting tests of over 1,500 seconds total duration to demonstrate the engine can meet the rocket's duty cycle requirements. Oxygen-rich staged combustion engines provide higher performance than gas generator cycle engines and are more widely used internationally, while the U.S. has less experience with this engine cycle.
The advantages of different types of propellantsArya Ramaru
This document discusses and compares the four main types of chemical rocket propellants: solid, liquid, gas, and hybrid. Solid propellants are easier to store but have lower performance than liquids. Liquid propellants can be throttled and restarted but are more complex. Gas propellants have low density and hybrids combine solid fuel with liquid oxidizers for benefits like throttling. In conclusion, further research on current solid and liquid fuel technologies could help commercialize spaceflight.
NASA SLS Solid Rocket Booster - Complete ExplanationGokul Lakshmanan
The Space Launch System uses two solid rocket boosters that provide most of the thrust during launch. Each booster contains propellant made of ammonium perchlorate, aluminum, and binders that ignite and burn for 124 seconds. The boosters are jettisoned at an altitude of 45 km after which parachutes deploy to slow their descent into the ocean for recovery. A range safety system can destroy the boosters by remote command if needed for safety.
This document provides an introduction to rocket propulsion systems used in NASA's space shuttle. It first describes that rocket engines operate based on Newton's third law of motion. It then outlines the main components of rocket engines, including fuel, oxidizer, combustion chamber, and nozzle. Several types of fuels and engine cycles are described, such as cryogenic fuels, solid rocket boosters, monopropellants, and pressure-fed, gas generator, staged combustion, and expander cycles. Design parameters for rocket engines like specific impulse and thrust are also covered. The document concludes with an overview of challenges such as cooling and combustion instabilities, and alternatives like solar electric propulsion and ion thrusters.
This document discusses different types of rocket propulsion systems. It describes solid, liquid, gas, and hybrid rocket propellants. Solid propellant rockets have the fuel and oxidizer pre-mixed and stored in the rocket casing. Liquid propellant rockets store the fuel and oxidizer separately and pump them into the combustion chamber. Hybrid rockets combine aspects of solid and liquid rockets. The document also discusses factors to consider when selecting rocket fuels such as physical properties, performance, economic factors, and health and safety issues.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
Space tourism is emerging as private companies like SpaceX, Blue Origin, and Virgin Galactic are developing technologies to take tourists to space. SpaceX's Falcon 9 rocket and Dragon spacecraft have taken cargo and astronauts to the International Space Station. Blue Origin is developing the New Shepard rocket for suborbital space tourism flights. Virgin Galactic uses WhiteKnightTwo and SpaceShipTwo for suborbital space flights, providing passengers few minutes of weightlessness. As space technologies advance, companies aim to enable more affordable space tourism and eventually space colonization as Earth may become uninhabitable.
This slide contains information regarding one of the fourth generation reactor which is named as fast breeder reactor.As it is named as fast breeder reactor, this reactor does not contain any moderator as water rather contains sodium or molten salt as coolant.
Rocket engines produce thrust by accelerating and ejecting stored propellants at high speeds through a nozzle. They obtain high thrust-to-weight ratios but have the lowest fuel efficiency of all jet engines. Key components include the combustion chamber, where propellants combust at high pressures and temperatures, and the supersonic nozzle, which converts the hot gas energy into kinetic energy of the exhaust jet for propulsion. Rocket performance is optimized by maximizing exhaust velocity and specific impulse through high combustion temperatures, low-mass propellants, and nozzle designs that adapt to changing ambient pressures.
Rocket propellants can be either solid or liquid. Solid propellants store fuel and oxidizer together in a solid casing, while liquid propellants store fuel and oxidizer separately in tanks. Liquid propellants provide higher efficiency but require complex pumping systems, while solid propellants are simpler but provide lower efficiency. Rocket performance is measured by specific impulse, with higher values indicating more thrust per unit of propellant. Careful fuel measurement and propellant mixing ratios are required to achieve optimal rocket performance.
Natural gas is transported long distances as liquefied natural gas (LNG) via specialized carriers. Over the past 40 years, the size of LNG carriers has increased significantly to support growing demand. Early carriers held 0-36,000 cubic meters of LNG, while current largest carriers can hold over 220,000 cubic meters. Larger ships allow for more economical transport of LNG between countries without direct pipeline connections. Carrier designs have also evolved, with different containment systems developed to safely store larger volumes of cryogenic LNG cargo over long voyages.
This document provides an overview of different types of nuclear reactors, including pressurized water reactors, boiling water reactors, CANDU reactors, gas cooled reactors, and fast breeder reactors. It describes the basic design and functioning of each type of reactor, and highlights some of their key advantages and disadvantages. The document was prepared by an electrical engineering student as part of an active learning assignment on electrical power generation topics.
Rocket propulsion uses Newton's third law of motion and the conservation of momentum. Chemical energy from fuel is converted to kinetic energy through combustion in the thrust chamber and nozzle, producing thrust via reaction from ejected exhaust. Rocket engines differ from jet engines in that rockets are non-air breathing and can operate in a vacuum, do not rely on atmospheric conditions for oxygen, and carry both fuel and oxidizer onboard. Rockets use stored propellants that are pumped into a combustion chamber where they burn and expand through a nozzle, producing thrust. Solid propellant rockets burn a solid fuel/oxidizer block, while liquid propellant rockets mix and burn liquid fuel and oxidizer.
Fast breeder reactors can breed more fissile material than they consume, improving fuel utilization. They use liquid metal like sodium for cooling instead of water as moderators are not needed. India's first commercial fast breeder reactor, the 500 MWe Prototype Fast Breeder Reactor, is under construction and will go critical in 2014. Fast breeders and reprocessing of spent fuel can help reduce nuclear waste and allow uranium resources to last much longer than current light water reactors.
The document summarizes information about nuclear reactors presented in a seminar. It discusses how nuclear fission works and was discovered, the stages of the fission process, and controlled versus uncontrolled nuclear chain reactions. It then describes the key components of nuclear power plants, including the reactor core, coolant, control rods and safety systems. Different classifications of reactors are outlined based on the nuclear reaction, moderator, coolant, generation, and intended use. The history of nuclear energy programs in India and major nuclear accidents are also summarized.
Chemical reactors come in various sizes and designs depending on factors like the reactions taking place. The two main types are batch and continuous reactors. Batch reactors are used for laboratory reactions and involve mixing reactants together in a vessel then removing products. Continuous reactors constantly feed reactants and withdraw products at a controlled rate to produce large quantities of chemicals consistently. Common continuous reactor designs include tubular reactors where reactants flow through pipes, fixed bed reactors using a solid catalyst, and fluidized bed reactors where a fine catalyst acts like a fluid when mixed with gases.
This document discusses solid rocket propulsion. It describes the key components of a solid rocket motor, including the thermal insulation, nozzle, ignition system, and solid propellant grain. Solid propellant grains can be composite, containing an oxidizer like ammonium perchlorate and a fuel like aluminum powder held together by a binder. Performance criteria for rockets include thrust, specific impulse, total impulse, and effective exhaust velocity. Solid rockets provide high thrust but have low control and cannot easily be shut down or restarted.
The document discusses different types of breeder reactors, including liquid-metal cooled fast breeder reactors (LMFBRs), gas-cooled fast breeder reactors, molten salt breeder reactors, and light water breeder reactors. It provides details on the design and operation of each type of breeder reactor.
The document discusses nuclear rocket engines. It describes how nuclear rocket engines work by using heat from a nuclear reactor to heat liquid hydrogen propellant which is then expelled through a nozzle to create thrust. It discusses different types of nuclear rocket engines like solid core, liquid core, and gas core designs. Nuclear rocket engines offer benefits like very high specific impulse compared to chemical rockets, but also face challenges like high development costs and radiation shielding issues. Potential applications include rockets, submarines, and cars. Recent innovations include a proposed fusion rocket engine design.
The document discusses how rocket force works and compares two types of rocket fuel. It examines the third law of motion that for every action there is an equal and opposite reaction. The rocket fuel produces force by burning and the exhaust goes down, pushing the rocket up. A data table shows the effect of different fuels on speed and distance over time based on blows to a water rocket. The conclusion is that rocket force depends on the type of fuel and is related to the third law of motion.
For their senior rocket project, the students designed a solid rocket propellant that would accelerate the rocket to 100 feet per second without being unstable. They tested over a dozen mixtures using various catalysts and ultimately selected an iron oxide catalyst based on multi-scale testing results. The propellant was packed into tubes, cut into grains after setting, weighed, and paired in motors to keep mass equal for testing, which measured pressure values from a sensor using a DATAQ sampler and custom mounting rigs.
A rocket develops thrust through the rapid expulsion of propellant, which consists of fuel and an oxidizer. The major components of a rocket include the engine, propellant, frame to hold components, and a payload like a satellite. Thrust must exceed the rocket's weight to launch and continue accelerating the rocket against gravity in order to reach orbital velocity and altitude to place a satellite into orbit. Impulse, the product of thrust and firing duration, provides a measure of a rocket's performance - larger rockets like the Saturn V that powered the Apollo missions generated much greater thrust over longer periods than smaller rockets. Rockets work by enclosing gas produced from burning solid or liquid propellants under pressure, and thrust is generated as the gas
NASA SLS Solid Rocket Booster - Complete ExplanationGokul Lakshmanan
The Space Launch System uses two solid rocket boosters that provide most of the thrust during launch. Each booster contains propellant made of ammonium perchlorate, aluminum, and binders that ignite and burn for 124 seconds. The boosters are jettisoned at an altitude of 45 km after which parachutes deploy to slow their descent into the ocean for recovery. A range safety system can destroy the boosters by remote command if needed for safety.
This document provides an introduction to rocket propulsion systems used in NASA's space shuttle. It first describes that rocket engines operate based on Newton's third law of motion. It then outlines the main components of rocket engines, including fuel, oxidizer, combustion chamber, and nozzle. Several types of fuels and engine cycles are described, such as cryogenic fuels, solid rocket boosters, monopropellants, and pressure-fed, gas generator, staged combustion, and expander cycles. Design parameters for rocket engines like specific impulse and thrust are also covered. The document concludes with an overview of challenges such as cooling and combustion instabilities, and alternatives like solar electric propulsion and ion thrusters.
This document discusses different types of rocket propulsion systems. It describes solid, liquid, gas, and hybrid rocket propellants. Solid propellant rockets have the fuel and oxidizer pre-mixed and stored in the rocket casing. Liquid propellant rockets store the fuel and oxidizer separately and pump them into the combustion chamber. Hybrid rockets combine aspects of solid and liquid rockets. The document also discusses factors to consider when selecting rocket fuels such as physical properties, performance, economic factors, and health and safety issues.
This seminar gives idea about spacecraft propulsion i.e., actually what are different latest modes of propulsion are used in space agency and also the introduction of combustion of propellants.
Space tourism is emerging as private companies like SpaceX, Blue Origin, and Virgin Galactic are developing technologies to take tourists to space. SpaceX's Falcon 9 rocket and Dragon spacecraft have taken cargo and astronauts to the International Space Station. Blue Origin is developing the New Shepard rocket for suborbital space tourism flights. Virgin Galactic uses WhiteKnightTwo and SpaceShipTwo for suborbital space flights, providing passengers few minutes of weightlessness. As space technologies advance, companies aim to enable more affordable space tourism and eventually space colonization as Earth may become uninhabitable.
This slide contains information regarding one of the fourth generation reactor which is named as fast breeder reactor.As it is named as fast breeder reactor, this reactor does not contain any moderator as water rather contains sodium or molten salt as coolant.
Rocket engines produce thrust by accelerating and ejecting stored propellants at high speeds through a nozzle. They obtain high thrust-to-weight ratios but have the lowest fuel efficiency of all jet engines. Key components include the combustion chamber, where propellants combust at high pressures and temperatures, and the supersonic nozzle, which converts the hot gas energy into kinetic energy of the exhaust jet for propulsion. Rocket performance is optimized by maximizing exhaust velocity and specific impulse through high combustion temperatures, low-mass propellants, and nozzle designs that adapt to changing ambient pressures.
Rocket propellants can be either solid or liquid. Solid propellants store fuel and oxidizer together in a solid casing, while liquid propellants store fuel and oxidizer separately in tanks. Liquid propellants provide higher efficiency but require complex pumping systems, while solid propellants are simpler but provide lower efficiency. Rocket performance is measured by specific impulse, with higher values indicating more thrust per unit of propellant. Careful fuel measurement and propellant mixing ratios are required to achieve optimal rocket performance.
Natural gas is transported long distances as liquefied natural gas (LNG) via specialized carriers. Over the past 40 years, the size of LNG carriers has increased significantly to support growing demand. Early carriers held 0-36,000 cubic meters of LNG, while current largest carriers can hold over 220,000 cubic meters. Larger ships allow for more economical transport of LNG between countries without direct pipeline connections. Carrier designs have also evolved, with different containment systems developed to safely store larger volumes of cryogenic LNG cargo over long voyages.
This document provides an overview of different types of nuclear reactors, including pressurized water reactors, boiling water reactors, CANDU reactors, gas cooled reactors, and fast breeder reactors. It describes the basic design and functioning of each type of reactor, and highlights some of their key advantages and disadvantages. The document was prepared by an electrical engineering student as part of an active learning assignment on electrical power generation topics.
Rocket propulsion uses Newton's third law of motion and the conservation of momentum. Chemical energy from fuel is converted to kinetic energy through combustion in the thrust chamber and nozzle, producing thrust via reaction from ejected exhaust. Rocket engines differ from jet engines in that rockets are non-air breathing and can operate in a vacuum, do not rely on atmospheric conditions for oxygen, and carry both fuel and oxidizer onboard. Rockets use stored propellants that are pumped into a combustion chamber where they burn and expand through a nozzle, producing thrust. Solid propellant rockets burn a solid fuel/oxidizer block, while liquid propellant rockets mix and burn liquid fuel and oxidizer.
Fast breeder reactors can breed more fissile material than they consume, improving fuel utilization. They use liquid metal like sodium for cooling instead of water as moderators are not needed. India's first commercial fast breeder reactor, the 500 MWe Prototype Fast Breeder Reactor, is under construction and will go critical in 2014. Fast breeders and reprocessing of spent fuel can help reduce nuclear waste and allow uranium resources to last much longer than current light water reactors.
The document summarizes information about nuclear reactors presented in a seminar. It discusses how nuclear fission works and was discovered, the stages of the fission process, and controlled versus uncontrolled nuclear chain reactions. It then describes the key components of nuclear power plants, including the reactor core, coolant, control rods and safety systems. Different classifications of reactors are outlined based on the nuclear reaction, moderator, coolant, generation, and intended use. The history of nuclear energy programs in India and major nuclear accidents are also summarized.
Chemical reactors come in various sizes and designs depending on factors like the reactions taking place. The two main types are batch and continuous reactors. Batch reactors are used for laboratory reactions and involve mixing reactants together in a vessel then removing products. Continuous reactors constantly feed reactants and withdraw products at a controlled rate to produce large quantities of chemicals consistently. Common continuous reactor designs include tubular reactors where reactants flow through pipes, fixed bed reactors using a solid catalyst, and fluidized bed reactors where a fine catalyst acts like a fluid when mixed with gases.
This document discusses solid rocket propulsion. It describes the key components of a solid rocket motor, including the thermal insulation, nozzle, ignition system, and solid propellant grain. Solid propellant grains can be composite, containing an oxidizer like ammonium perchlorate and a fuel like aluminum powder held together by a binder. Performance criteria for rockets include thrust, specific impulse, total impulse, and effective exhaust velocity. Solid rockets provide high thrust but have low control and cannot easily be shut down or restarted.
The document discusses different types of breeder reactors, including liquid-metal cooled fast breeder reactors (LMFBRs), gas-cooled fast breeder reactors, molten salt breeder reactors, and light water breeder reactors. It provides details on the design and operation of each type of breeder reactor.
The document discusses nuclear rocket engines. It describes how nuclear rocket engines work by using heat from a nuclear reactor to heat liquid hydrogen propellant which is then expelled through a nozzle to create thrust. It discusses different types of nuclear rocket engines like solid core, liquid core, and gas core designs. Nuclear rocket engines offer benefits like very high specific impulse compared to chemical rockets, but also face challenges like high development costs and radiation shielding issues. Potential applications include rockets, submarines, and cars. Recent innovations include a proposed fusion rocket engine design.
The document discusses how rocket force works and compares two types of rocket fuel. It examines the third law of motion that for every action there is an equal and opposite reaction. The rocket fuel produces force by burning and the exhaust goes down, pushing the rocket up. A data table shows the effect of different fuels on speed and distance over time based on blows to a water rocket. The conclusion is that rocket force depends on the type of fuel and is related to the third law of motion.
For their senior rocket project, the students designed a solid rocket propellant that would accelerate the rocket to 100 feet per second without being unstable. They tested over a dozen mixtures using various catalysts and ultimately selected an iron oxide catalyst based on multi-scale testing results. The propellant was packed into tubes, cut into grains after setting, weighed, and paired in motors to keep mass equal for testing, which measured pressure values from a sensor using a DATAQ sampler and custom mounting rigs.
A rocket develops thrust through the rapid expulsion of propellant, which consists of fuel and an oxidizer. The major components of a rocket include the engine, propellant, frame to hold components, and a payload like a satellite. Thrust must exceed the rocket's weight to launch and continue accelerating the rocket against gravity in order to reach orbital velocity and altitude to place a satellite into orbit. Impulse, the product of thrust and firing duration, provides a measure of a rocket's performance - larger rockets like the Saturn V that powered the Apollo missions generated much greater thrust over longer periods than smaller rockets. Rockets work by enclosing gas produced from burning solid or liquid propellants under pressure, and thrust is generated as the gas
This document describes a study on developing and applying solid rocket ballistic models. It presents a combustion simulator that was created to overcome limits of existing models. The simulator links an internal ballistics model and regression model. It can handle anisotropic geometries. The 0D and 1D ballistics models are discussed. For complex geometries, the 1D model results were not as accurate due to interface issues and dynamic behavior. Future work includes improving remeshing, filtering noise, and modifying damping terms to better handle geometric perturbations from remeshing.
This document provides an introduction to solid rocket motors and hybrid rocket motors. It discusses the components and operation of solid rocket motors, including the types of solid propellants used, how thrust is controlled by grain configuration, ignition methods, and nozzle designs. It also covers scaling of solid rocket motors, engine cutoff methods, and some advantages and disadvantages of hybrid rocket motors that use a solid fuel and liquid oxidizer.
This document provides a basic introduction to rocketry. It explains that rockets work by ejecting pressurized gas through a nozzle, similar to how balloons work when the air inside is released. Rockets use solid or liquid propellants that are burned to produce the pressurized gases, unlike balloons which use compressed air. The document also outlines the main types of rockets and stages of rocket flight, and explains how rockets are able to move according to Newton's third law of motion.
1. Rockets work by gases being pushed out the bottom, exerting an equal force pushing the rocket upwards. Students will test amounts of vinegar to determine which makes the rocket fly highest.
2. They predict the rocket's momentum will carry it up initially and gravity will slow it down. Materials needed are film canisters, baking soda, vinegar, card and tape.
3. The challenge is to build rockets and find the amount of vinegar yielding the highest flight. Heights will be recorded and the winning rocket selected.
This document summarizes a rocket modeling project completed by four students and guided by Professor R.K. Bhagat. It describes the key forces acting on rockets, including lift, drag, weight, and thrust. It also covers topics such as center of gravity, center of pressure, terminal velocity, acceleration, stability, weathercocking, nose cone design, fin design, torpedo design, model rocket motors, and the students' attempts to fly their Phoenix and torpedo rockets.
The document summarizes a student rocketry project to design, build, and launch a high-powered rocket motor. The team chose a HyperTEK I310 hybrid rocket motor over a solid fuel motor for its smoother thrust curve and ability to reach a higher altitude. They designed a custom motor mount and successfully integrated the motor. However, on launch day the rocket crashed and the onboard data recorders were destroyed, preventing analysis of flight parameters. Based on video evidence, the team estimated the rocket reached the predicted altitude but no official data could be confirmed.
1) Elements can combine to form compounds through chemical bonding such as ionic and covalent bonding. Ionic bonds form between metals and nonmetals via electron transfer, while covalent bonds form between nonmetals via electron sharing.
2) Chemical formulas represent the composition of compounds and indicate the types and numbers of elements present. Empirical formulas show the simplest whole number ratio of elements in a compound.
3) Compounds are classified as ionic if formed between metals and nonmetals, or molecular if formed between nonmetals. Ionic compounds are composed of metal cations and nonmetal anions, while molecular compounds contain covalently bonded molecules.
Jet propulsion uses the velocity of air to produce thrust through a jet engine. A jet engine is made up of a fan, compressor, combustor, turbine, and nozzle. It works on Newton's third law - for every action, there is an equal and opposite reaction. Rocket propulsion works by ejecting exhaust produced from propellants carried within the rocket. Key challenges in rocket design include cooling combustion chambers, pumping fuel, controlling direction through thrust vectoring, and using lightweight materials. Electric propulsion systems provide a pollution-free alternative to rockets for outer space travel and include electrostatic, electrothermal, electromagnetic, and electrodynamic types.
The document discusses centre of mass and rocket propulsion. It defines centre of mass as the point where the entire mass of an object can be assumed to be concentrated and balances the distribution of mass. It provides examples of calculating the centre of mass for symmetrical shapes, uniform rods, triangles, circles, and cuboids. For a two-mass system, it gives the formula to find the centre of mass as a weighted average. Rocket propulsion is described as relying on conservation of momentum, where expelling mass in one direction causes the rocket to move in the opposite direction.
This document provides an overview of propulsion systems. It discusses different types of propulsion including liquid, solid, electric propulsion and others. It also covers key concepts in propulsion performance including specific impulse, thrust, nozzle design and equations. The document uses examples and diagrams to illustrate concepts in propulsion systems and their applications in launch vehicles and spacecraft.
Basics of Rocket Propulsion Part 2 The Thrust EquationZack Wanambwa
1) A rocket system can be modeled using Newton's Second Law of Motion. The thrust of a rocket is equal to the rate of change of momentum.
2) For a rocket of initial mass m drifting at velocity V0, the thrust is equal to the rate at which exhaust gases are ejected multiplied by the exhaust velocity.
3) The thrust equation relates the thrust of a rocket to the mass flow rate and exhaust velocity, where thrust equals the mass flow rate times exhaust velocity.
Gas dynamics and_jet_propulsion- questions & answesManoj Kumar
1. The document discusses compressible and incompressible fluid flow, defining key terms like Mach number and stagnation state. It also provides equations for adiabatic energy, stagnation pressure and temperature, and Prandtl-Meyer relation.
2. Various regions of compressible flow are defined based on the Mach number, including incompressible, subsonic, transonic, supersonic, and hypersonic. Normal and oblique shock waves are also discussed.
3. Examples of where Fanno flow occurs are given as gas ducts in aircraft engines and air conditioning ducts. Fanno flow is steady, one-dimensional flow with friction but no heat transfer.
This document provides an overview of rocketry concepts and history. It is divided into chapters that cover:
1) The history of rockets from ancient Greece and China to modern times, including key figures like Tsiolkovsky, Goddard, and von Braun.
2) Rocket principles like thrust, acceleration, and Newton's laws of motion.
3) The four major systems of rockets - airframe, guidance, control, and propulsion - and how they work.
4) Examples of American rockets like Redstone, Atlas, Titan, Saturn, Space Shuttle, and proposed Constellation rockets.
It outlines learning objectives for students and provides details on rocket science fundamentals and
The document discusses rocket propulsion, focusing on the launch phase of spaceflight. It describes how rockets use liquid or solid fuel engines to accelerate spacecraft to orbital velocity within 3 minutes. Liquid-fueled engines can control thrust by regulating fuel and oxidizer flow and can be stopped and restarted, while solid-fueled engines are simpler but cannot control thrust or be stopped once ignited. Common rocket fuels include liquid hydrogen and oxygen or kerosene and oxygen for liquid engines and aluminum powder for solid boosters.
Cryogenic rocket engines use cryogenic fuels such as liquid hydrogen and liquid oxygen that must be stored at extremely low temperatures to remain liquid. They work by accelerating these cryogenic propellants to high speeds through combustion in the thrust chamber and expansion through a nozzle to produce thrust according to Newton's third law of motion. Some key cryogenic rocket engines include the RL-10, CE 7.5, and CE-20. Cryogenic engines offer high energy density and clean, economical propellants but also present challenges like boil-off, reactivity, and leakage of the cryogenic fuels.
Cryogenic rocket engines use cryogenic fuels like liquid hydrogen and liquid oxygen that must be stored at extremely low temperatures to remain liquid. They have several advantages like high thrust and specific impulse but also disadvantages like complexity and cost. Common cryogenic engines include the RL-10, CE 7.5, and CE-20 which use liquid hydrogen and liquid oxygen and have specifications like thrust levels and specific impulse. Cryogenic engines require specialized construction elements to handle the extreme cold like fuel injectors, turbo-pumps, valves and tanks.
Cryogenics is the study of materials at very low temperatures below -150°C. Cryogenic rocket engines use cryogenic fuels like liquid oxygen and liquid hydrogen that must be stored at extremely cold temperatures to remain liquid. The first country to use a cryogenic engine was the USA in 1963, while Russia developed its own in 1983. India has successfully developed its own cryogenic upper stage powered by the CE-7.5 cryogenic engine. Cryogenic engines offer very high energy density and clean, economical propellants but also present challenges related to storage and handling of the cryogenic liquids.
Cryogenic rocket engines use cryogenic (extremely cold) liquid fuels like liquid hydrogen and liquid oxygen that provide high performance. They work by pumping the cryogenic liquids into a combustion chamber where they are burned, producing hot gas that is expelled through a nozzle to generate thrust. Some key advantages are high specific impulse (efficiency) and payload capacity, but they also have challenges with storing the cryogenic fuels. The document discusses the history, principles, components, propellants, and working of cryogenic rocket engines. It focuses on the Space Shuttle Main Engine as a prominent example.
Cryogenics is the study of production and behavior of materials at very low temperatures below -150°C. Some important cryogenic fluids include liquid hydrogen, helium, oxygen, nitrogen and air. Key applications of cryogenics include rocket propulsion, magnetic resonance imaging, superconductivity, frozen food storage and more. Cryogenic technology enables efficient rocket engines using liquid hydrogen and oxygen propellants. India has developed its own cryogenic engine GSLV Mk III to launch satellites using this technology. Future prospects include more efficient ion engines and alternative nuclear or solar thermal rocket concepts.
The document discusses cryogenic rocket engines. It begins with definitions of cryogenics and describes how cryogenic rocket engines use liquid oxygen and liquid hydrogen propellants at extremely low temperatures. It then covers the history, principles, major components like the combustion chamber and nozzle, operation, advantages like high energy density, and drawbacks such as boil off rates of cryogenic rocket engines. In conclusion, it discusses how cryogenic rocket engines are promising for future space exploration due to their high performance.
This document summarizes a seminar report on cryogenic rocket engines. It discusses how cryogenic rocket engines use liquid oxygen and hydrogen as fuel and oxidizer, which burn cleaner than hydrocarbon fuels. The report provides background on cryogenic technology, the history of cryogenic rocket engine development in the US and other countries in the 1960s. It describes the construction and working of cryogenic rocket engines, including components like the gas generator, turbo pumps, and thrust chamber. The report notes advantages of cryogenic fuels in providing high energy per unit mass and being clean-burning.
This document discusses cryogenic rocket engines. It begins with an introduction to cryogenics and cryogenic fuels that can be used for rocket engines. It then discusses the history of rocketry development by Russia and the US. Current rockets use liquid-fueled cryogenic engines, with the first being the RL10 in the 1960s. Cryogenic engines use supercooled liquid fuels like liquid oxygen and hydrogen that provide high energy density. Key components include the combustion chamber, injectors, pumps, valves and tanks. Cryogenic fuels allow for compact fuel storage on rockets. While powerful, cryogenic engines also present challenges like leakage and embrittlement issues. In conclusion, cryogenic rocketry is important for space exploration due to
This document discusses rocket propulsion and solid rocket motors. It defines propulsion as initiating or changing the motion of a body. Rocket propulsion works by ejecting propellant to create a reaction force and induce motion. Solid rocket motors use solid propellants composed of fuel, oxidizer, and binder. They provide high thrust but have low control and cannot be shut down and restarted. Performance is measured by parameters like specific impulse, total impulse, and effective exhaust velocity.
The document summarizes a presentation by Team 4 for a proposed orbital transfer vehicle (OTV) called Centurion. It introduces the team members and provides an overview of the mission, vehicle systems, and design process. Key aspects of the Centurion include transporting payloads to Lagrange points 1 and 2, using nuclear thermal propulsion, and having communication and tracking capabilities through NASA's Near Earth Network.
A cryogenic rocket engine is a rocket engine that uses a cryogenic fuel or oxidizer, that is, its fuel or oxidizer (or both) are gases liquefied and stored at very low temperatures. Notably, these engines were one of the main factors of NASA's success in reaching the Moon by the Saturn V rocket.
During World War II, when powerful rocket engines were first considered by the German, American and Soviet engineers independently, all discovered that rocket engines need high mass flow rate of both oxidizer and fuel to generate a sufficient thrust. At that time oxygen and low molecular weight hydrocarbons were used as oxidizer and fuel pair. At room temperature and pressure, both are in gaseous state. Hypothetically, if propellants had been stored as pressurized gases, the size and mass of fuel tanks themselves would severely decrease rocket efficiency. Therefore, to get the required mass flow rate, the only option was to cool the propellants down to cryogenic temperatures (below −183 °C [90 K], −253 °C [20 K]), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines.
Various cryogenic fuel-oxidizer combinations have been tried, but the combination of liquid hydrogen (LH2) fuel and the liquid oxygen (LOX) oxidizer is one of the most widely used. Both components are easily and cheaply available, and when burned have one of the highest enthalpy releases by combustion, producing specific impulse up to 450 s (effective exhaust velocity 4.4 km/s).
Cryogenic rocket engines use liquid oxygen and liquid hydrogen propellants that are stored at extremely low cryogenic temperatures. They provide several advantages like high energy density and clean, non-toxic exhaust but also have challenges like boil off rates and leakage of the reactive cryogenic fuels. The document traces the history of cryogenic engines from early US and Soviet designs to current engines used by various countries. It describes the key components and working of cryogenic engines and concludes by discussing future engine technologies still under development.
PRESENTATION ON CRYOGENIC ROCKET ENGINESelf-employed
This document provides information about a seminar on cryogenic rocket engines presented by Jaison Cyril. It discusses what cryogenics is, provides a history of cryogenic rocket engines including the RL10 engine, describes the construction and working principle of cryogenic engines including different power cycles, lists applications and advantages and disadvantages of cryogenic engines. It also summarizes the four phases of combustion in the thrust chamber and discusses potential next generation rocket engines.
The document describes a cryogenic rocket engine. Cryogenic engines use liquid oxygen and liquid hydrogen propellants, which must be stored at extremely low temperatures below -183°C and -253°C, respectively. The engine works on the principle of Newton's third law of motion - burning the cryogenic fuels in the combustion chamber and expanding the gases through a nozzle to generate thrust. Major components include the combustion chamber, injectors, turbo-pumps, and external fuel tanks. Cryogenic engines offer high energy efficiency due to the high energy density of liquid oxygen and hydrogen fuels.
This document provides an overview of nuclear reactors, including their classification, main components, the nuclear fission reaction, and different reactor types. It discusses reactors based on neutron energy, coolant used, moderator, and fuel enrichment. The main components of a nuclear reactor are described as the fuel, moderator, coolant, control rods, and shielding. Examples of reactor types are provided and compared such as BWR, PWR, PHWR, GCR, LWGR, and FBR. Current and planned nuclear reactor units in India are also listed.
The document discusses NASA's Space Launch System (SLS) heavy-lift launch vehicle. It describes the three proposed variations of the SLS (Block 1, 1B, and 2) with increasing payload capacity. Key specifications of the SLS include a diameter of 8.4 meters and use of cryogenic engines left over from the Space Shuttle program. The SLS will use two solid rocket boosters and the Orion Multi-Purpose Crew Vehicle to carry astronauts beyond low Earth orbit.
Cryogenic rocket engines use cryogenic fuels such as liquid hydrogen and liquid oxygen that are stored at very low temperatures. They provide high energy and are clean-burning but require complex engineering to handle the highly reactive cryogenic fuels. The document discusses the history and development of cryogenic rocket engines, how they work using a staged combustion cycle, their advantages of high energy and clean fuels, and disadvantages like leakage issues. It also covers India's achievements in developing its own cryogenic engines like the CE-7.5 and CE-20. Currently only a few nations including the US, Russia, China, France, Japan, and India have mastered cryogenic rocket engine technology.
This presentation is about cryogenic technology which includes working history and applications. tastefully added morph transition to add some aesthetic approach. Freely available to take reference from it don't copy directly make changes according to need
Submitted by sudarshan patil from D.N.Patel collage of engineering shahada
Cryogenic rocket engines use cryogenic fuels like liquid oxygen and liquid hydrogen that are stored at very low temperatures below -150°C. The United States first developed cryogenic rocket engines in 1963. Key components include the combustion chamber, injectors, turbo pumps, and nozzle. Cryogenic engines offer high energy density but present challenges like leakage and embrittlement. India successfully launched its first indigenous cryogenic upper stage in 2014. Future engine technologies being researched include ion engines and nuclear thermal rockets.
KuberTENes Birthday Bash Guadalajara - K8sGPT first impressionsVictor Morales
K8sGPT is a tool that analyzes and diagnoses Kubernetes clusters. This presentation was used to share the requirements and dependencies to deploy K8sGPT in a local environment.
Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapte...University of Maribor
Slides from talk presenting:
Aleš Zamuda: Presentation of IEEE Slovenia CIS (Computational Intelligence Society) Chapter and Networking.
Presentation at IcETRAN 2024 session:
"Inter-Society Networking Panel GRSS/MTT-S/CIS
Panel Session: Promoting Connection and Cooperation"
IEEE Slovenia GRSS
IEEE Serbia and Montenegro MTT-S
IEEE Slovenia CIS
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3-6 June 2024, Niš, Serbia
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Low power architecture of logic gates using adiabatic techniquesnooriasukmaningtyas
The growing significance of portable systems to limit power consumption in ultra-large-scale-integration chips of very high density, has recently led to rapid and inventive progresses in low-power design. The most effective technique is adiabatic logic circuit design in energy-efficient hardware. This paper presents two adiabatic approaches for the design of low power circuits, modified positive feedback adiabatic logic (modified PFAL) and the other is direct current diode based positive feedback adiabatic logic (DC-DB PFAL). Logic gates are the preliminary components in any digital circuit design. By improving the performance of basic gates, one can improvise the whole system performance. In this paper proposed circuit design of the low power architecture of OR/NOR, AND/NAND, and XOR/XNOR gates are presented using the said approaches and their results are analyzed for powerdissipation, delay, power-delay-product and rise time and compared with the other adiabatic techniques along with the conventional complementary metal oxide semiconductor (CMOS) designs reported in the literature. It has been found that the designs with DC-DB PFAL technique outperform with the percentage improvement of 65% for NOR gate and 7% for NAND gate and 34% for XNOR gate over the modified PFAL techniques at 10 MHz respectively.
Advanced control scheme of doubly fed induction generator for wind turbine us...IJECEIAES
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6th International Conference on Machine Learning & Applications (CMLA 2024)ClaraZara1
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politics, and conventional and nontraditional security are all explored and explained by the researcher.
Using Mackinder's Heartland, Spykman Rimland, and Hegemonic Stability theories, examines China's role
in Central Asia. This study adheres to the empirical epistemological method and has taken care of
objectivity. This study analyze primary and secondary research documents critically to elaborate role of
china’s geo economic outreach in central Asian countries and its future prospect. China is thriving in trade,
pipeline politics, and winning states, according to this study, thanks to important instruments like the
Shanghai Cooperation Organisation and the Belt and Road Economic Initiative. According to this study,
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governments. This success may be attributed to the effective utilisation of key tools such as the Shanghai
Cooperation Organisation and the Belt and Road Economic Initiative.
Introduction- e - waste – definition - sources of e-waste– hazardous substances in e-waste - effects of e-waste on environment and human health- need for e-waste management– e-waste handling rules - waste minimization techniques for managing e-waste – recycling of e-waste - disposal treatment methods of e- waste – mechanism of extraction of precious metal from leaching solution-global Scenario of E-waste – E-waste in India- case studies.
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ACEP Magazine edition 4th launched on 05.06.2024Rahul
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A SYSTEMATIC RISK ASSESSMENT APPROACH FOR SECURING THE SMART IRRIGATION SYSTEMSIJNSA Journal
The smart irrigation system represents an innovative approach to optimize water usage in agricultural and landscaping practices. The integration of cutting-edge technologies, including sensors, actuators, and data analysis, empowers this system to provide accurate monitoring and control of irrigation processes by leveraging real-time environmental conditions. The main objective of a smart irrigation system is to optimize water efficiency, minimize expenses, and foster the adoption of sustainable water management methods. This paper conducts a systematic risk assessment by exploring the key components/assets and their functionalities in the smart irrigation system. The crucial role of sensors in gathering data on soil moisture, weather patterns, and plant well-being is emphasized in this system. These sensors enable intelligent decision-making in irrigation scheduling and water distribution, leading to enhanced water efficiency and sustainable water management practices. Actuators enable automated control of irrigation devices, ensuring precise and targeted water delivery to plants. Additionally, the paper addresses the potential threat and vulnerabilities associated with smart irrigation systems. It discusses limitations of the system, such as power constraints and computational capabilities, and calculates the potential security risks. The paper suggests possible risk treatment methods for effective secure system operation. In conclusion, the paper emphasizes the significant benefits of implementing smart irrigation systems, including improved water conservation, increased crop yield, and reduced environmental impact. Additionally, based on the security analysis conducted, the paper recommends the implementation of countermeasures and security approaches to address vulnerabilities and ensure the integrity and reliability of the system. By incorporating these measures, smart irrigation technology can revolutionize water management practices in agriculture, promoting sustainability, resource efficiency, and safeguarding against potential security threats.
3. CONTENTS
• What is CRYOGENICS
• Propellants used in CRE*
• Construction of CRE
• CRE around the world
• Challenges in CRE
• CONCLUSION
* CRE: Cryogenic Rocket Engine
4. 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
6. 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 the
operations at very low temperature (below −150
°C, −238 °F or 123 K) and the behaviour of
materials at these temperatures.
7. • Propulsion system
• Isp of different propulsion systems:
Solid propulsion = 265 s
Earth-storable liquid propulsion = 285 s
Cryogenic propulsion = 450 s
8. ALSO, BECAUSE SATELLITES ARE BECOMING HEAVIER….
INSAT 1A [1982] –1150 kg
INSAT 2A [1992] –1900 Kg
INSAT 3C [2002] –2750 Kg
INSAT 4A [2005] –3080 kg
9. IN ROCKET ENGINES
• Cryogenic technology involves the use of rocket
propellants at extremely low temperatures.
• Liquid Oxygen (LOX) & Liquid Hydrogen (LH2)
• Oxygen remains at liquid only at temperatures
below -183 ° C and hydrogen below - 253 ° C.
11. 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
12. CRYOGENIC PROPELLANTS
• Combination of Cryogenic
fuel and oxidizer.
• Cryogenic fuel- Storage at
extremely low temperature
in a liquid state such as
Liquid Hydrogen.
• Storage of propellant is
difficult task.
Eg: LH2 and LOX
13. FACTORS FOR SELECTING THE PROPELLANT
• Ease of operation
• Cost
• Hazards
• Performance
14. 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
15. 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.
26. 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
27. RS-25
• First flight- 1981
• Space shuttle main engine
RS-68
• First flight- 1998
• First stage engine of delta 4 rocket
UNITED STATES
29. 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
30. 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
31. 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
32. 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
33. 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
34. 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
35. 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
36. OTHER APPLICATIONS OF CRYOGENICS
► Cryosurgery
► Electric power transmission
► Frozen food
► Blood banks
► Infrared Sensors
► Electronics
37. CHALLENGES
Thermal contraction
Storage problems
High density
Highly reactive gases
Overall cost of propellants
relatively high
39. 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
The basic principle driving a rocket engine are:
Newton third law of motion
Law of conservation of momentum(momentum are the product of the units of mass and velocity)
In principle, cryogenic rocket engine derives thrust like all other rocket engines by accelerating an impulse carrier to high speeds.
The chemical energy stored in the fuel is converted into kinetic energy by burning the fuel in the thrust chamber and subsequent expansion in the nozzle to produce thrust
Basically Rocket engines are Reaction engines.
Spacecraft propulsion is any method used to accelerate spacecraft and artificial satellites.
Rocket Engines
Interplanetary vehicles mostly use chemical rockets as well.
Cryogenics originated from two Greek words “Kyros” which means cold or freezing and “genes” which means born or produced
Cryonics (from Greek κρύος 'kryos-' meaning 'icy cold') is the low-temperature preservation of animals (including humans) who cannot be sustained by contemporary medicine, with the hope that healing may be possible in the future.
Cryogenics is the study of very low temperatures
In physics, Cryogenics is the study of the operations at very low temperature (below −150 °C, −238 °F or 123 K) and the behaviour of materials at these temperatures.
Propulsion system: The power Centre of a launcher and it increases the sp impulse of rocket
Specific Impulse (Isp): Index of efficiency of a propulsion system.
Isp= Thrust / Weight flow rate of propellants.
Traditionally expressed in seconds.
Isp of different propulsion systems (sea-level)
Solid propulsion –265 s
Earth-storable liquid propulsion –285 s
Cryogenic propulsion –450 s
Cryogenic technology involves the use of rocket propellants at extremely low temperatures.
The combination:- Liquid Oxygen (LOX) & Liquid Hydrogen (LH2) offers the highest energy efficiency for rocket engines.
Oxygen remains at liquid only at temperatures below -183 ° C and hydrogen below - 253 ° C.
American and Soviet engineers independently, all discovered that rocket engines need high mass flow rate of both oxidizer and fuel to generate a sufficient thrust.
At that time oxygen and low molecular weight hydrocarbons were used as oxidizer and fuel pair. At room temperature and pressure, both are in gaseous state. Hypothetically, if propellants had been stored as pressurized gases, the size and mass of fuel tanks themselves would severely decrease rocket efficiency.
Therefore, to get the required mass flow rate, the only option was to cool the propellants down to cryogenic temperatures (below −150 °C, −238 °F), converting them to liquid form. Hence, all cryogenic rocket engines are also, by definition, either liquid-propellant rocket engines or hybrid rocket engines
The first operational cryogenic rocket engine RL10 rocket engine.
The United States was the first country to develop cryogenic rocket engines.
with RL-10 engines, registered its first successful flight in 1963 and is still used on the Atlas V rocket.
Then The Japanese LE-5 engine flew in 1977 ,French HM-7 in 1979 , Chinese YF-73 in 1984 .
The Soviet Union, first country to put a satellite and later a human in space, successfully launched a rocket with a cryogenic engine only in 1987.
*In cre cryogenic propellant is a combination of cryogenic fuel and oxidizer which are in liquid forms.
*cryogenic fuels are fuels that require storage at extremely low temp. in order to maintain them in a liquid state.
cryogenic fuels often constitute liquifide gases such as liquid hydrogen.
To store prop. Onboard a rocket is very diff. task as they have low densities.
Thus by cooling and compressing the into liquids we can vastly increase their density and make it possible to store them in large quantity in small tanks.
The combination of LH2 and LOX is one of the most widely used.
When burned this combination have one of the highest enthalpy releases by combustion, producing specific impulse upto 455 sec.
It is the cleanest cryogenic fuel & oxidizer combination. When liquid hydrogen used with lox, by product is only water. This water is thrown out of nozzle in form of hot vapour.
It is economical. Lox costs less than gasoline.
Reaction time and storability are not too critical.
Bcs of low temp. cryogenic propellant are difficult to store over long period of time. For this reason they are less desirable for use in millatry rockets.
Even as a liqud, hydrogen has low density requiring large tanks, pumps and extreme cold requires tank insulation. Most rockets that use lh2 fuel use it in upper stage only.
In the case of kerosene launch pad fires due to spilled kerosene are more damaging than hydrogen fires.
Highest specific impulse ever test fired in rocket engine was li and f with hydrogen added to improve the exhaust thermodynamics. Isp= 542 sec in vaccume equivalent to exhaust vel. Of 5320 m/s.
But we don’t use this exotic prop. Bcs li and f are both extremely corrosive. Li ignites on contact with air. F ignites on contact with most fuels including hydrogen.
F and hf in the exhaust are very toxic. Which makes working around the launch pad difficult and damages the environment.
RL-10
CENTAUR IS USE AS UPPER STAGE
S-4 IS SECOND STAGE OF SATURN -1
DCSS –DELTA CRUOGENIC SECOND STAGE
J-2
AS-201- UNMANED TEST FIHHT OF APOLLLO SPACECRAFT
Saturn -2 stage & third stage
RS-83
LE-7A -FIRST SATGE OF H2 LAUNCH VEHICLE
VINCI- under development
Upperstage liquid rocket booster
China’s academy of launch vehicle technology
Long march 3- 3(chinese orbital carrier rocket)
YF-77-long march 5- heavy lift launch system
yf-50t under development
RD-0120 DESIGNETED AS 11D122
RD-0146- RUS-M LAUNCH VEHICLE TO CARRY FUTURE PPTS-PROPSPECTIVE PILOTED TRANSPORT SYSTEM
PARTIALLY REUSABLE CAPSULE MANNED SPACECRAFT
CE-7.5 IT REPLACED RUSSIAN KVD-1 ENGINE
NOMIAL THRUST OF 200KN
THE VALUE CAN FIXED BETWEEN THIS RANGR
1986- COST OF 12 CRORE TO LEARN HOW TO HANDLE CRYOGENIC FLUID
1987-INSAT-2 WEIGHING 2TONE- GTO- US OFFERED 800 MILLION DOLLER FOR 2 ENGINE
1989-HM7- 1200 MILLION DOLLER-2 7 TONE ENGINE, TRANSFER OF TECHNOLGY & SET UP OF MANUFAC FACILITIES IN INDIA
1990-8 SCIENTIST WENT TO MOSCOW- 15 MONTHS
2010- FAILURE OF GSLV-D3 WITH GSAT-4 – FAIL TO SUSTAIN IGNITION BCZ OF TURBO PUMP STOPPED
DECEMBER 2010- EXPLOSION DUE TECHNICAL SNAG FIRST STAGE
GSLV-D5 TARGETED TO BE LAUCHED IN JUNE ABORTED DUE LEAK IN THE FUEL TANK
05 JAN -2014-SATISH DHAWAN SPACE CENTRE SHAR, SRIHARIKOTA
Cryosurgery (also called cryo therapy) is the use of extreme cold produced by liquid to destroy abnormal tissue.
Cryosurgery is used to treat external tumors, such as those on the skin.
For internal tumors, liquid nitrogen is circulated through a hollow instrument called a cryoprobe.
Cryosurgery has been used for many years in the treatment of skin cancer
Frozen food When very large quantities of food must be transported to regions like war zones, earthquake hit regions, etc., they must be stored for a long time, so cryogenic food freezing is used.
Blood banking Certain rare blood groups are stored at low temperatures, such as -165 degrees C.
Forward looking infrared (FLIR) Many infra-red cameras require their detectors to be cryogenically cooled.
The super conducting electronic devices like SQUID (Super conducting quantum interference device) are used in sensitive digital magnetometers and voltmeters.
Zero friction bearings use magnetic field instead of oil or air, derived from the Meissner effect associated with super conductivity.
Super conducting electric motors are constructed approaching zero electric loses.
Low density of liquid Hydrogen –more structural mass Low temperature of propellants -Complex storage & transfer systems and operations
Hazards related to cryogens
High density requires larger tanks
Overall cost of propellants relatively high
Need for ignition system.
Cryogens are highly concentrated gases and have a very high reactivity. Liquid oxygen, which is used as an oxidizer, combines with most of the organic materials to form explosive compounds. So lots of care must be taken to ensure safety
One of the most major concerns is leakage. At cryogenic temperatures, which are roughly below 150 degrees Kelvin or equivalently (-190) degrees Fahrenheit, the seals of the container used for storing the propellants lose the ability to maintain a seal properly. Hydrogen, being the smallest element, has a tendency to leak past seals or materials.
The "Boil off rate" usually refers to the amount of liquid vaporized by heat leaking into the tank per unit time.
In a way it indicates that to maintain the same pressure in the tank you need to vent at least this amount of equivalent liquid or vapor. Less and you will build pressure, more will result in a drop in pressure in the tank, unless you have a vaporizer.
Hydrogen Embrittlement
It is the process by which various metals, most importantly high-strength steel, become brittle and fracture following exposure to hydrogen.
Need for ignition system.
Zero Gravity conditions
The condition of real or apparent weightlessness occurring when any gravitational forces acting on a body meet with no resistance sothe body is allowed to accelerate freely.
There are several trends today that can help us look into the future of cryogenics materials
Simulation of materials characteristics using this approach will include modeling of microstructure, defects, surface structure, interface properties, prediction of adhesion and bonding, thermodynamic properties, and general mechanical behaviour.
The future of cryogenics will be very exciting and dynamic. It will be driven by traditions, trends, costs, performance, legislation. Of these, the most critical issue is costs.
Logical, creative and innovative ideas will have little chance of success if the economics are not positive. Cryogenics materials will be part of the dynamic future. By considering the entire cryogenics materials, we are not limited to just one type of materials, but metal materials, composites and fluorinated polymers will remain the major materials for applications at very low temperatures.
We are no longer limited by shape, density, size, composition, we are only limited by our imagination and our knowledge and OUR understanding of how to achieve the highest level of performance from cryogenics materials. We must not only continue to make incremental improvements in present materials but develop whole new technologies of manufacturing and processing for to achieve the highest performance in THIS field.