Development of a Hybrid Rocket to Achieve Precise Altitudes
Faculty Mentor Name
Elliot Bryner
Format Preference
Poster Presentation and Demonstration
Abstract
Hybrid rockets, employed by companies like space tourism provider Virgin Galactic, use propellants that are in different phases. Most commonly used is a solid fuel, such as Hydroxyl Terminated Polybutadiene (HTPB), paraffin, or acrylic, and a liquid oxidizer, such as liquid oxygen or nitrous oxide. The oxidizer is injected into the combustion chamber in vapor form, to prevent droplets of oxidizer impacting the fuel, resulting in localized detonations. When compared to liquid rocket engines, hybrid rocket engines can be designed and manufactured at a lower cost. When compared to solid rocket motors, hybrid rocket engines usually have higher impulse, and the ability to be throttled.
The purpose of this project is to fly a rocket using a hybrid propulsion system to a target altitude of 10 thousand feet as accurately as possible. The hybrid engine will use nitrous oxide as the oxidizer and HTPB as the fuel, with injector orifices less than 0.1 inch in diameter for vaporization. A small-scale hybrid engine prototype is being designed for static testing, to provide preliminary data on the design and to act as a proof of concept.
The flight vehicle, will carry an altitude prediction system that actively determines when the rocket will reach 10 thousand feet, if combustion shutdown were to occur instantaneously. It will then close the valve that controls oxidizer flow, shutting down combustion, allowing the rocket to coast to its desired altitude.
Location
AC1-ATRIUM
Start Date
3-31-2017 11:00 AM
End Date
3-31-2017 3:00 PM
Development of a Hybrid Rocket to Achieve Precise Altitudes
AC1-ATRIUM
Hybrid rockets, employed by companies like space tourism provider Virgin Galactic, use propellants that are in different phases. Most commonly used is a solid fuel, such as Hydroxyl Terminated Polybutadiene (HTPB), paraffin, or acrylic, and a liquid oxidizer, such as liquid oxygen or nitrous oxide. The oxidizer is injected into the combustion chamber in vapor form, to prevent droplets of oxidizer impacting the fuel, resulting in localized detonations. When compared to liquid rocket engines, hybrid rocket engines can be designed and manufactured at a lower cost. When compared to solid rocket motors, hybrid rocket engines usually have higher impulse, and the ability to be throttled.
The purpose of this project is to fly a rocket using a hybrid propulsion system to a target altitude of 10 thousand feet as accurately as possible. The hybrid engine will use nitrous oxide as the oxidizer and HTPB as the fuel, with injector orifices less than 0.1 inch in diameter for vaporization. A small-scale hybrid engine prototype is being designed for static testing, to provide preliminary data on the design and to act as a proof of concept.
The flight vehicle, will carry an altitude prediction system that actively determines when the rocket will reach 10 thousand feet, if combustion shutdown were to occur instantaneously. It will then close the valve that controls oxidizer flow, shutting down combustion, allowing the rocket to coast to its desired altitude.