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By
V. Jagadish Babu(ME/SER/1016/09)
Advanced Propulsion Systems
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IntroductionPropulsion act of changing the motion of body
Jet propulsion
reaction force is imparted to a deviceby a momentum of ejected matter
Rocket propulsion
Duct propulsion
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Various Propulsion Devices
Chemical propulsion
Electric propulsion
Nuclear propulsion
Solar propulsion
Laser propulsion`
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Chemical Propulsion
o lid p ro p e llan t ro cket m o to r
Liquid propellant rocket engine
ybrid propellant rocket engines
Cryogenic engines
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Performance Parameters
Total impulse: It = Fdt Specific impulse: Is = It / mp g
Effective exhaust velocity: c = Is g
Mass ratio: MR = mf/ mo
Propellant mass fraction : = mp / mo
Impulse to weight ratio : It / wo = It /(mp + mf)g
Thrust to weight ratio : F/wo
Thrust : F = mc + (p2 p3 )A2 Characteristic velocity: c* = P1 At / m
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Solid Propellant Rocket Engine
Rocket motor that uses the
solid propellants (fuel/oxidizer).
Specific impulse of 265 sec.
It simple design, ready to operate.No leak, spill, slosh.
Stored for 5 to 25 yrs.
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Applications
Large booster and second stage motors.Tactical missiles(anti tank missiles ,ASM
,SSM AAM ).
Ballistic missiles
Gas generators
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Advanced research
Environmentally sensitive fuel formulationssuch as Alice propellant.
Ramjet with solid fuel.
Variable thrust design with variable nozzlegeometry.
Hybrid rockets that use solid fuel andthrottle able liquid or gaseous oxidizer
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Engine that uses propellant in liquidform.
High density(low volume).
Needs pump system(pressurization).
Higher specific impulse up to 380 sec.
Can be randomly throttled, stopped andrestarted.
Can have leaking, slosh, spilling(can be
hazardous).High thrust to weight ratio.
Combustion instabilities ,Minimum reliability.
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Applications
Anti aircraft rocketsUpper stage launch vehicle
Large missiles
Space craftssatellites.
Top stage of anti-ballistic missiles.
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yb rid P ro p e lla n t E n g in e
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Specific impulse is around 400 sec more thanliquid and solid propellant engines.
Safe and non toxic oxidizers such as liquidoxygen and nitrous oxide can be used.
More controllable-start/stop/restart andthrottling.
Needs feed system (pressurization).Low regression rate
y r rope an ng ne
Engine which uses two different types of propellants-onesolid and other liquid
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Cryogenic Rocket Engine
At atmospheric conditions, LOX and low molecularweight hydrocarbons are in gaseous state and to getrequired mass flow rate, the only option is to feed the
engine in liquid form.(below boiling point).
Specific impulse is more that 450 sec.LOX and LH2 are used as cryogenic
propellants.
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Electric Propulsion
electrically powering the propellant to high speed
.Types
electro static, electro thermal, electro magnetic
Resistojet Rocket
1.Specific impulse 200-350 sec2.Uses lot of power and low thrust..Arc jet Rocket
1.1600 sec specific impusle.2.Very low thrust and high power.
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Pulse Plasma Thruster
1.High specific can pulsed on and off forattitude control.
2.Low energetic efficiency.
VASMIR
1.Variable specific impulse,1000 to 10000sec.
2.Nuclear reactors are required.
A li ti
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Applications
Overcoming translational and rotationalperturbations in satellite orbits(forGEO,LEO,MEO.
Interplanetary travel and deep spaceprobes.
Flight velocity adjustments, flight pathcorrection.
De orbit , deep space, sun escape.Tactical missiles.
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http://en.wikipedia.org/wiki/File:Vasimr.png8/9/2019 Advance Propulsion System
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Nuclear fission reactors are devices used toconvert a nuclear fuel mass into energy E
according to
E = mc^2,where c is the speed of light.
Radioisotope rocket/poodle thruster Heat from radioactive decay is used
to heat hydrogen.
1.700 to 800 sec2.Low thrust/weight ratio.
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Nuclear thermal rocket Nuclear reactor is used
to heat the hydrogen to very high temperature.
1.Specific impulse is about 900 or more.2.Low thrust.
3.Gas core reactor rocket Nuclear reaction using a gaseous state
fission reactor in intimate contact withpropellant.
1.1500 to 3000 sec.2.Very high thrust.
3.
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Fission fragment rocket Fission products are directly exhausted
to give thrust.
Fission sail A sail material is coated with fissionable
materials one side.
Nuclear salt water rocket: Nuclear salt are held in solution caused to
react at nozzle.
1.Very high specific impulse. very high thrust.
2.Thermal issue in nozzle.
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Nuclear Pulse Propulsion Nuclear bombs are detonate behind
vehicle and blast caught by a pusher plate.
1.Very high impulse.
2.Very high thrust
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s
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-issio n frag m en t p ro p u lsio n co n cep t, ,fissio n a b le fila m e n ts b re vo lvin g d isks
,re a cto r co re d fra g m e n ts e xh a u st
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Laser Propulsion The laser propulsion system may
transfer momentum to a spacecraft in twodifferent ways.
1.Photon radiation pressure drives the momentum
transfer2.Using external devices.3.Ablative laser propulsion4.Pulse plasma propulsion.
5.CW plasma propulsion.6.Ram laser propulsion.7.Micro propulsion.
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Laser
b e a m
A cce le ra tio n
tube
p ro je ctile
B rea k
d o w n
Laser
a m la se r p ro p u lsio n
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la se r
p ro p e lla n t
a se r m icrop ro p u lsio n
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THANK YOU
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