gas dynamics-rocket propulsion
DESCRIPTION
Gas Dynamics and Propulsion / BY Dr.G.KUMARESAN, / PROFESSOR, / ANNA UNIVERSITYTRANSCRIPT
GDJP Anna University
Rocket
PROPULSION
Rocket Propulsion-Introduction
GDJP Anna University
Aircraft engine application is limited to altitudes of about
100,000 ft or less. But Rocket can function outside the
atmosphere
Rocket can operate in vacuum and achieve any altitude
The thrust of the rocket engines is independent of the flight
speed
Rocket works based on Newton’s law of motion
Rockets carry own oxidizer and fuel tank
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Newton’s First law - Applied to Rocket Liftoff
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Rocket Engine Thrust
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Forces on a Model Rocket
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Flight of a Model Rocket
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Forces at Liftoff
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Acceleration at Liftoff
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Forces in Powered Flight
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Forces in Coasting Flight
The rocket uses up all its fuel, the engine goes out and the thrust goes to zero
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Forces during Recovery
Rocket Propulsion-Introduction Cont..
GDJP Anna University
Terminal Velocity
Rocket Propulsion- Types
GDJP Anna University
Rockets can be classified by
A.Based on source of energy1. Chemical Rockets 2. Solar Rockets 3. Electrical Rockets
4. Nuclear Rockets
B.Based on propellant1. Liquid propellant 2. Solid propellant 3. Hybrid propellant
C.Based on application field1. Space rocket 2. Military rocket 3. Aircraft rocket 4. Booster rocket
D.Based on number stage 1. Single stage rocket 2. Multi stage rocket
E.Based on size and range1. Short range and small rocket 2. Long range and large rocket
Rocket Propulsion- Chemical Rocket Propellants
GDJP Anna University
Solid Propellant
Liquid Propellant
Propellant is a chemical mixture burned to produce thrust in rockets andconsists of a fuel and oxidizer
In a liquid system the fuel and oxidizer are separately stored and are sprayed under high pressure (20 to 60 bar) into the combustion chamber
In solid system, both fuel and oxidizer are contained in the propellant grain and the burning takes place on the surface of the propellant
Rocket Propulsion- Solid Propellant grains
GDJP Anna University
Well mixed fuel and oxidizer called as Propellant grain. Several grain configurations are employed to obtain burning at the desired rate.
Propellant cross section
Rocket Propulsion- Solid Propellants
GDJP Anna University
Exit velocity range1500 m/s to 3000 m/s
Star-grained solid rocket motor
Fuel : Plastic, Resin material
Oxidizer : Nitrates, Perchlorates
Rocket Propulsion- Hybrid Propellants
GDJP Anna University
Regulator
-
Liquidoxidizer
Oxidizer injector
Solid Fuel
Nozzle
Fuel : Solid type Oxidizer : Liquid type
Beryllium hydride(Be-H2 ) Fluorine(F2 )Lithium hydride (Li H) Chlorine Trifluoride(ClF3)Lithium hydride (Li H) Nitrogen tetroxide(N2O4 )Hydrocarbon(CH2)n Nitrogen tetroxide(N2O4 )
Special Type: Hypergolic propellants
Rocket Propulsion- Liquid Propellant Types
GDJP Anna University
Liquid Propellants
Monopropellant Bipropellant
Fuel and Oxidizer in a single chemical – MonopropellantsHydrogen peroxide (H2O2), Hydrazine (N2H4), Nitro methane (CH3NO2)
Fuel and Oxidizers are different in chemical - Bipropellants
Oxidizer Fuel mox/mf Combustion temperature (K)
Liquid Oxygen Gasoline, Hydrazine, UDMH, Ethanol
2.5, 0.92, 1.65, 1.8
3294, 34003600, 3422
Hydrogen Peroxide Hydrazine, UDMH
1.844.54
28172922
Nitric acid (RFNA) Aniline, Hydrazine
3.001.47
30453083
Rocket Propulsion- Propellant Properties
GDJP Anna University
Liquid Propellants1) Energy released during combustion should be high2) High density propellants are preferred3) Low freezing point propellants are preferred 4) Non-corrosive, chemically stable and should not absorb moisture5) Low values of vapor pressure and viscosity are preferred6) They should not be poisonous and hazardous7) It should be cheap and abundantly available
Solid Propellants1) Propellants should be easily available and safe to handle2) Physical and chemical properties should not change considerably during
processing as well as during time3) It should release large amount of heat energy during combustion4) They should be chemically inert before ignition5) Low molecular weight and high density of propellants are preferred6) Exhaust gases should be smokeless and colorless7) Propellants should not react with atmospheric air and moisture
Rocket Propulsion- Liquid Propellant feed system
GDJP Anna University
Liquid Propellant feed system - Cont..
GDJP Anna University
Liquid Propellant feed system - Cont..
GDJP Anna University
Pressure Fed system
Rocket Thrust
GDJP Anna University
Solid Motor
Liquid Motor
eAeceemm ..
Rocket Nozzle
GDJP Anna University
Rocket Nozzle- Function
GDJP Anna University
The function of the nozzle is to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy.
The nozzle converts the slow moving, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Since thrust is the product of mass and velocity, a very high gas velocity is desirable.
The nozzle is usually made long enough (or the exit area is great enough) such that the pressure in the combustion chamber is reduced at the nozzle exit to the pressure existing outside the nozzle.
It is under this condition, Pe=Po, where Pe is the pressure at the nozzle exit and Po is the outside ambient pressure, that thrust is maximum and thenozzle is said to be adapted, also called optimum or correct expansion.
When Pe is greater than Po, the nozzle is under-extended. When the opposite is true, it is over-extended.
Rocket Nozzle- Function
GDJP Anna University
The most efficient nozzle (1) is contoured to the exhaust stream, allowing the escaping gas to expand just enough to fill the nozzle.
A nozzle that lets the gas expand too much (2), or too little (3), wastes the energy and thrust potential of the exhaust system.
The most efficient nozzle (1) is contoured to the exhaust stream, allowing the escaping gas to expand just enough to fill the nozzle.
A nozzle that lets the gas expand too much (2), or too little (3), wastes the energy and thrust potential of the exhaust system.
C-D Nozzle
Rocket Propulsion – Combustion-Liquid Propellant
GDJP Anna University
Combustion process involves: injection, atomization, mixing, vaporization, ignition andexothermic chemical reaction between fuel and oxidizer
Propellant Injectors
Rocket Propulsion – Solid Fuel Geometry
GDJP Anna University
A solid fuel's geometry determines the area and contours of its exposed surfaces, and thus its burn pattern. There are two main types of solid fuel blocks used in the space industry. These are cylindrical blocks, with combustion at a front, or surface, and cylindrical blocks with internal combustion.
In the first case, the front of the flame travels in layers from the nozzle end of the block towards the top of the casing. This so-called end burner produces constant thrust throughout the burn.
In the second, more usual case, the combustion surface develops along the length of a central channel. Sometimes the channel has a star shaped, or other, geometry to moderate the growth of this surface.
Rocket Propulsion – Solid Fuel Geometry- Thrust profile
GDJP Anna University
Cylindrical Channel – Progressive burning
Cylindrical Channel with central cylinder- Neutral burning
Star Profile Cruciform Profile – Regressive burning
Rocket Propulsion – Solid Fuel Geometry- Thrust profile
GDJP Anna University
Double anchor profile
Cog profile
Rocket Propulsion- Solid motor- Combustion
GDJP Anna University
Linear burning rateThe burning rate of the propellant grain depends on the initial temperature of the grain before combustion, equilibrium combustion pressure and the ratio of grain surface area and the nozzle throat area.
The burning surface of a rocket propellant grain recedes in a direction perpendicular to this burning surface. The rate of regression, typically measured in millimeters per second (or inches per second), is termed burn rate.
The linear burning rate is given by, Saint-Roberts law (regression law)where r- burn rate ; a-burn rate coefficient ; Pc - combustor pressure
n-pressure exponent (range 0.2 to 0.8)a =f (chemical composition, initial temperature of the propellant grain )n =f( combustor pressure)
ncaPr
Combustion limitSolid propellant grain requires certain minimum value of the combustion pressure for stable combustion. This minimum value of the pressure is known as the combustion limit ( it depends on type of propellant employed)
Usually it lies between the range of 5 and 55 bar
Rocket Propulsion- Solid motor- Combustion
GDJP Anna University
Propellant consumption rate, cAncPacrAcm
.
.
Propellant flow rate, (1))(cm Vdt
dpm
. .
mass of gas in bore
mp
.
Equilibrium Combustion Pressure
Solid motor- Combustion Cont..
GDJP Anna University
Propellant area ratio
The ratio of the surface area available for burning of a propellant grain and the throat area of the exhaust nozzle is known as the propellant area ratio ( Kp)
*A
cApK r and Kp increase with the combustion pressure
Rocket Nozzle- Function
GDJP Anna University
The function of the nozzle is to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy.
The nozzle converts the slow moving, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Since thrust is the product of mass and velocity, a very high gas velocity is desirable.
The nozzle is usually made long enough (or the exit area is great enough) such that the pressure in the combustion chamber is reduced at the nozzle exit to the pressure existing outside the nozzle.
It is under this condition, Pe=Po, where Pe is the pressure at the nozzle exit and Po is the outside ambient pressure, that thrust is maximum and thenozzle is said to be adapted, also called optimum or correct expansion.
When Pe is greater than Po, the nozzle is under-extended. When the opposite is true, it is over-extended.