Advance Propulsion System

8/9/2019 Advance Propulsion System

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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.png


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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

Advance Propulsion System

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