This document discusses ignition methods for hybrid rocket motors. It describes hybrid rockets as using propellants in different physical states, with advantages over liquid and solid rockets in terms of simplicity, safety and cost. It then discusses various ignition methods for hybrid rockets such as pyro-grain ignition, high current ignition, and PIC ignition which involves wrapping pyrotechnic material around a plastic fuel tube. A hydrogen and oxygen torch igniter is also described, which uses a spark plug to ignite the gases and then inject them into the main combustion chamber. Advantages of hybrid rockets include use of energetic ingredients and safety, while disadvantages are low fuel regression rate and mixture ratio shifting.
The slides prepared to aid the engineering students to prepare the project presentation on topic of Rocket Fuels. The solid rocket propulsion system is explained in detail. We acknowledge the various sources from where the presentation has been made and without whom the presentation would not have been possible.
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Recycled waste material has recently become of interest because of the huge amount of
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Rocket propulsion is a class of jet propulsion that produces thrust by ejecting burned propellant. The thrust is generated on the basis of Newton's third law of motion. Rocket propulsion systems can be broadly classified according to the type of energy source (chemical, solar, electric, or nuclear).
The presentations helps us to understand about plastic welding and its different classifications. Further it gives a brief idea about the various industrial applications and latest developments in this field.
Theoretical Analysis for Energy Consumption of a Circulation-Type Superheate...IJMER
Recycled waste material has recently become of interest because of the huge amount of
natural resource consumption worldwide. It is necessary to introduce a material recycle system in
municipal and industrial waste management. Quality improvement of oily metal waste disposed from
metalworking factories as recycling materials is one of the issues. Here, the degreasing system plays an
important role. In this paper, energy consumption of a circulation-type superheated steam degreasing
system was applied to oily metal waste disposed from a metalworking factory. This system was
compared to a once-through type superheated steam degreasing system. Flow rates of materials
applicable to the degreasing system were estimated based on preliminary experiments, and heat and
energy balances from the system were theoretically evaluated and compared between once-through and
circulation type systems. As a result, a circulation-type superheated steam waste degreasing system
that can process oily metal waste provides a promising energy-saving waste metal recycle system.
i prepare some common knowlage about the self prepagating High temphrature method to obtain nanomaterials, this method is very cheap and need less heating energy, an exothermic method .
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1. BIRLA INSTITUTE OF TECHNOLOGY
IGNITERS FOR HYBRID ROCKETS
BY : FAZEEL AHMAD
(MT/ET/10003/18)
2. Hybrid Rockets
• A hybrid rocket is a rocket with a rocket motor which
uses propellants in two different states of matter - one solid and the
other either gas or liquid.
• Hybrid rockets exhibit advantages over both liquid rockets and solid
rockets especially in terms of simplicity, safety, and cost.
4. IGNITION METHODS FOR HYBRID ROCKET MOTORS
• Pyro-grain Ignition :-In the case of hybrid rocket motors using a
plastic fill tube, the plastic fill tube is run through the pyro-grain, so
when the pyro-grain ignites, it acts like a pyro-valve, thermally cutting
the plastic fill line as well as igniting the oxidizer and fuel.
• High Current Ignition :-High Current Ignition of hybrid rocket motors
involves passing a high current through a resistance wrapped around
a plastic fill tube, in an oxygen rich environment to ignite the fuel and
oxidiser.
5. IGNITION METHODS FOR HYBRID ROCKET MOTORS
• PIC Ignition :-In the PIC ignition method, a specific number of wraps of PIC
are made around a plastic fill tube at the injector end of a hybrid
combustion chamber, in hybrid rocket motors where the oxidizer tank is
filled by the plastic fill tube. An electrical igniter is attached to the PIC, and
the assembly is sealed with tape. When ignition is initiated, the PIC ignites,
cuts the plastic tube and ignites the oxidizer and the fuel.
• High Voltage Ignition :-The High Voltage Ignition method is used for hybrid
rocket motors where the oxidizer tank is filled via a metal fill tube. The High
Voltage ignition method involves injecting Gaseous Oxygen from a small
external Gaseous Oxygen tank into the combustion chamber, and then
initiating a high voltage electrical spark for ignition. In the oxygen rich
environment, this results in rapid ignition.
7. Hydrogen & Oxygen Torch Igniter
• Hydrogen and oxygen flow through separate ports into combustion
chamber in device, where they ignite by use of surface-gap spark
plug.
• Hot gases flow from this combustion chamber, through injector tube,
into larger combustion chamber containing fuel-oxidizer mixture to
be ignited.
8. Advantages of Hybrid Rockets
• Use of energetic propellant ingredients
• Handling
• Safety
• Reliability and Simplicity
• Low cost
9. Disadvantages of Hybrid Rockets
• Low fuel regression rate
• Low bulk density
• Mixture ratio shifting
10. REFERENCE
• "Hybrid Rocket Propulsion Overview“. Space Propulsion Group, Inc.
• "A Brief History of Hybrid Rocket Technology". Space Propulsion
Group, Inc.
• "Hybrid Rocket Engines Use Additive Manufacturing to Combine the
Advantages of Solid and Liquid Propellants". Stratasys.
Retrieved December 19, 2016.
