Analysis of Rocket Fuels: Types, Propulsion, Engine Design & Safety

This report provides an overview of rocket fuels and propulsion systems, detailing various types of propellants including solid, liquid, and hybrid fuels, as well as electromagnetic and solar engines. It discusses the characteristics, advantages, and disadvantages of each type, highlighting specific examples such as black powder, ammonium perchlorate, liquid oxygen, and hydrazine. The report also addresses critical design considerations such as thrust requirements, safety factors, and combustion rates, emphasizing the importance of these factors in determining the overall performance and efficiency of rocket engines. Furthermore, it touches upon emerging technologies like solar thermal rockets and electromagnetic propulsion, including ion thrusters, and their potential to revolutionize space travel. Concluding with the necessity of considering thrust, safety, and combustion rate in rocket fuel design, this document is a comprehensive resource available for students on Desklib, offering insights into the complex field of rocket propulsion.

Fuel for rocket

INTRODUCTION
• Rockets have seen constant development
since their inception.
• Rocket fuel/propellant is the substance used
to power the rocket.
• It is a reaction mass ejected at very high
speed to produce thrust which pushes the
rocket upwards.

Introduction
• Different rockets require different kinds of
propellants.
• Modern rockets are classified based on the
kind of fuel it uses to power its engine.
• These are:
 Solid propellant engine
 Liquid propellant engine

Solid propellant engine.
• This is the most common fuel.
• It is cheaper and easier to make and use. They
however have a lower specific impulse.
• It is made from powdered aluminum and an oxidizer
(Walker, 2015).
• Some of the solid rocket propellants include;
– Black powder
– Ammonium percolate
– Aluminum
– Magnesium

Liquid rocket propellants
• Liquid propellants are classified as cryogenic,
semi-cryogenic or hypergolic.
• The most used of these categories liquid
propellants is liquid oxygen and liquid hydrogen
both of which are cryogenic (Katona & Bell, 2017).
• Liquid oxygen and kerosene mixed together forms
a semi cryogenic propellant.
• Hydrazine and red fuming nitric acid are examples
of hypergolic propellants.

Hybrid propellants
• These are propellants which incorporate the
use of both liquid and solid propellants.
• If the fuel is in solid state the oxidizer is either
a liquid or gas
• The hybrid systems are able to apply both the
liquid and solid propellant.
• Nevertheless, the hybrid options of the
engines are not much common.

Hybrid
• When designed properly, the hybrid propellants
are much safe than the liquid and solid ones
(Borgdorff, Waslander & University of Waterloo,
2017).
• The three major hazards which has to be taken
care of on the hybrid fuel design include;
1. Pressure vessel failures
2. Blow back
3. Hard start

Electromagnetic and solar engines
• These are engines which rely on electrical
energy to change the speed of the space
velocity (Walker, 2015).
• The engines have high exhaust speed and
therefore tend to use less propellant.
• Nevertheless, low thrust has been a major
challenge when applying these engines in
rockets propellant design.

Electromagnetic and solar engines
• Additionally, these engines do9 not have the
nozzles like the common engines.
• The major classification of these engines
include;
1. Electrostatic
2. Electrotgermal
3. electromagnetic

Solid, fluid, solar and electromagnetic
• Gunpowder mixed with oxidant is one of the common
solid propellant used.
• Nevertheless, fluid fuels has been widely used to
propel the rocket engines to long.
• Solar thermal rocket is another key technology which
considers the solar energy as a source of heat reaction
mass to power the rockets.
• Concentrators and mirrors are the only elements
which will be needed in solar powered rockets for
taping the solar energy.

Solid fluid, solar and electromagnetic
• Electromagnets are currently being used by
NASA to provide thrust to the rockets.
• Ion thrusters are used in electromagnetic
through ionization of inert gases.
• They are used to direct plasma to provide the
required force to propel the rocket
• The plasma is usually a gas created consisting
of positive and negative ions.

Conclusion
• Rocket fuel design has to consider key factors
of the thrust force required.
• In addition, the safety factors of the fuel has
to be considered together with their
combustion rate.
• The fuel combustion rate dictate the amount
of energy the rocket will have.