This document summarizes an advanced rocket motors technical seminar. It discusses the principle of operation of rocket engines including components like propellant, combustion chamber, ignition system, and nozzle. It describes different types of rocket engines such as solid-propellant, liquid-propellant, and hybrid engines. Solid engines provide large thrust simply but cannot be throttled while liquid engines can be throttled and restarted but are more complex. Hybrid engines combine benefits of solid and liquid engines with a solid fuel and liquid oxidizer. The seminar discusses applications and advantages and disadvantages of each type.

1. TECHNICAL
SEMINAR
ADVANCED ROCKET MOTARS

2. AURORA'S TECHNOLOGICALAND RESEARCH INSTITUTE
DEPARTMENT OF MECHANICAL ENGINEERING
ADVANCED ROCKET MOTARS
Presented by :
PEDDI KRANTHI
20845A0347
Under the guidance OF: PHANI
Designation : Assistant Professor

3. Overview :
• ABSTRACT
• INTRODUCTION.
• PRINCIOLE OF OPERATION.
• COMPONENTS OF ROCKET ENGINE.
• ADVANCED CONCEPTS.
• ADVANTAGES
• DISADVANTAGES.
• CONCLUSION.
• REFERANCES.

4. Abstract:
• The rocket engine is the main and very important part of the space transportation system. In this
paper an attempt has been made about the history of Rocket Engine, types of Rocket Engines and
future scope in the technology of the Rocket Engines. Also, an attempt about physics behind the jets,
and advantages and disadvantages of every rocket engine is made in this review paper.

5. INTRODUCTION:
 Rocket engines may either work with solid or liquid
propellants or as a combination of both, hybrid propulsion
systems, such as the one for the SpaceShipOne project.
 Liquid rocket engines can be subdivided into mono-
propellant or bi-propellant systems.
 Typical bi-propellant engines use either earth storable
propellants, generally combinations of nitric acid or its
anhydride with derivates of hydrazine, i.e. asymmetric di-
methylhydrazine (UDMH) or mono-methyl-hydrazine
(MMH), mixtures of storable and cryogenic propellants,
liquid oxygen and kerosene or fully cryogenic, liquid oxygen
and liquid hydrogen.
 Rocket engines are energy conversions systems with a heat
release in the combustion chamber which exceed by far
typical values of nuclear power plants (~ 3-4 GW).

6. PRINCIPLE OF OPERATION
 Rocket thrust is caused by pressures acting in the
combustion chamber and nozzle. From Newton's
third law, equal and opposite pressures act on the
exhaust, and this accelerates it to high speeds.
 In a rocket engine , fuel and a source of oxygen, called
an oxidizer, are mixed and exploded in a combustion
chamber. The combustion produces hot exhaust which
is passed through a nozzle to accelerate the flow and
produce thrust.

7. COMPONENTS OF ROCKET ENGINE
PROPELLANT
A propellant is a mass that is expelled or expanded in such
a way as to create a thrust or other motive force in accordance
with Newton's third law of motion, and "propel" a vehicle, projectile,
or fluid payload. In vehicles, the engine that expels the propellant is
called a reaction engine.

8. COMBUSTION CHAMBER
A combustion chamber is part of an internal combustion engine in which
the fuel/air mix is burned. For steam engines, the term has also been used for
an extension of the firebox which is used to allow a more complete combustion
process.

9. IGNITION SYSTEM
An ignition system generates a spark or heats an electrode to a high temperature
to ignite a fuel-air mixture in spark ignition internal combustion engines, oil-fired and
gas-fired boilers, rocket engines, etc.

10. ROCKET ENGINE NOZZLE
A rocket engine nozzle is a propelling nozzle used in a rocket
engine to expand and accelerate combustion products to high supersonic velocities.

11. DE LAVAL NOZZLE
A de Laval nozzle is a tube which is
pinched in the middle, making a carefully
balanced, asymmetric hourglass shape.
It is used to accelerate a compressible
fluid to supersonic speeds in the axial
direction, by converting the thermal energy
of the flow into kinetic energy.

12. Advance rocker engine
The most powerful solid-propellant rocket, and the most powerful rocket motor ever constructed, is
the SLS Five-Segment Booster (also known as the Five Segment Reusable Solid Rocket Motor, or
RSRMV), built by Northrop Grumman (USA) for NASA's Space Launch System (SLS) super-heavy rocket

14. A solid-propellant rocket or solid rocket is a rocket with a rocket
engine that uses solid propellants. The earliest rockets were solid-
fuel rockets powered by gunpowder; they were used in warfare by
the Arabs, Chinese, Persians, Mongols, and Indians as early as the
13th century

16. Application of Solid rocket engine
Solid rocket engines are used on air-to-air and air-to-ground
missiles, on model rockets, and as boosters for satellite
launchers. In a solid rocket, the fuel and oxidizer are mixed
together into a solid propellant which is packed into a solid
cylinder. A hole through the cylinder serves as a combustion
chamber.

17. Advantages of solid rocket engine
Compared to liquid propellant rockets, the solid-propellant
motors SRMs have been capable of providing large amounts
of thrust with a relatively simple design. They provide
greater thrust without significant refrigeration and insulation
requirements, and produce large amounts of thrust for their
size.
Disadvantages of solid rocket engine
Explosion and fire potential is larger; failure can be
catastrophic; most cannot accept bullet impact or being dropped
onto a hard surface. Many require environmental permit and
safety features for transport on public conveyanced.

18. Liquid propellant rocket engines
Liquid rocket engines are used in a number of launch
vehicles worldwide. In these rocket engines, e.g. LE-7A
engine of H-2A, Space Shuttle Main Engine (SSME) and
Vulcain engine of ARIANE 5, liquid oxygen (LOX) and
gaseous hydrogen (GH2) are injected through coaxial
injectors (

19. Application of liquid rocket engine
Liquid rocket engines are used on the Space Shuttle to place
humans in orbit, on many un-manned missiles to place satellites in
orbit, and on several high-speed research aircraft following World
War2.
ADVNTAGES OF liquid rocket engine
Major advantages of liquid propellant rockets are that they
generally have higher specific impulses than solids, the thrust can
be throttled, the system can be restarted as often as designed, and
the flow of propellants can be monitored and regulated to precisely
control the magnitude of the thrust.
Disadvantages'of liquid rocket engine
once ignited, solid propellants cannot be throttled, turned off and
then restarted because they burn until all the propellant is used. The
surface area of the burning propellant is critical in determining the
amount of thrust being generated.

20. Hybrid propellant rocket engines
A hybrid propellant system has the fuel as a solid inside the
combustion chamber. The liquid oxidiser is stored in a separate
tank. The simplest hybrid system is to have the oxidiser under
pressure in its tank. When a valve is opened, this oxidiser is
released into the combustion chamber. It then reacts with the
solid fuel before being ejected.

21. Application of hybrid rocket engine
Hybrid rocket propulsion is being considered in several specific
areas of space transportation.
Those applications are: microsatelites (manoeuvring and orbit
transfer), lunar and planetary landers, suborbital and orbital
tourism vehicles.
ADVNTAGES OF HYBRID
ROCKET ENGINE
The Hybrid Rocket Motor (HRM), which uses liquid oxidizer
and solid fuel for power and has the advantages such as safety,
simplicity, reliability, thrust regulation, multiple restart
capability and low cost, is chosen as the power system of the
LV in this paper.
Quite simple, solid fuel is essentially inert without oxidiser, safer; cracks do not
escalate, throttleable and easy to switch off.