Animated And Amazing View Of Rocket Engines, Its Classification,And details

2. Content
Rockets Principles Of Working
Difference From Jet Engines
Design Of Rocket
Classification Of Rocket
Engines
•Solid Propellent Rockets
Its Advantages & Disadvantages
•Liquid Propellent Rockets
Its Advantages & Disadvantages
•Single Stage Rockets
•Multi Stage Rockets
Conclusion

7. Based On
Type Of Propellant
Solid
Propellant
Liquid
Propellant
Based On
Type Of
Application
Single
Stage Rocket
Multi-stage
Rocket

10. Fuels Used In Solid Propellents Rocket Engines :
1. Gun Powder:
Black powder(gunpowder) is
composed of charcoal(fuel), potassium
nitrate(oxidizer), and sulfur(fuel).
1. Candy Propellants:
Rocket candy propellants are an oxidizer
(typically potassium nitrate) and a sugar fuel (typically dextrose,
sorbitol, or sucrose)
1. DB Propellants:
Nitroglycerin is dissolved in a nitrocellulose gel and solidified
with additives.

14. Liquid oxygen ( LO2) and
liquid hydrogen
Liquid oxygen (LOX) and liquid
methane(CH4)
Liquid oxygen (LOX) and alcohol
(ethanol, C2H5OH)
Liquid oxygen (LOX)
and gasoline
Liquid oxygen (LOX) and carbon
monoxide

15. The main advantages of liquid propellants:
 High specific impulse
High thrust
 High thrust to weight ratio of the rockets
 Easy to control.
However,they also have certain disadvantages•
Complexity of the construction;•
It is impossible to achieve very high specific
Impulse.
They are difficult to scale,complexity grows
quickly with growing the thrust;•

16. The main reason for multi-stage rockets and boosters is that
once the fuel is exhausted, the space and structure which contained
it and the motors themselves are useless and only add weight to the
vehicle which slows down its future acceleration. By dropping the
stages which are no longer useful to the mission, the rocket
lightens itself. The thrust of future stages is able to
provide more acceleration than if the earlier stage were still
attached, or a single, large rocket would be capable of.
When a stage drops off, the rest of the rocket is still traveling
near the speed that the whole assembly reached at burn-out time.
This means that it needs less total fuel to reach a given velocity
and/or altitude.