Propulsion and Power Commons^™

A Pressure-Based Estimate Of Multi-Orifice Synthetic Jet Performance, Rhett Parry

Student Research Symposium

Synthetic Jets

• Zero-Net Mass Flux
• Wide voltage and frequency response
• Trends with physical and nondimensional parameters

Sunrise Propulsion Subsystem Leak Rate Measurement Methodology, Alex Kirkman, Brittany Woytko, Holly Walen, Bret Maughan

Space Dynamics Laboratory Publications

As part of the integration and testing for Sun Radio Interferometer Space Experiment (SunRISE), it was necessary to characterize the propellent leak rate of the fully assembled propulsion subsystem for each satellite to ensure compliance with performance requirements. SunRISE utilized a cold gas system for its propulsion subsystem, using R-236fa propellant inside a tank made from a monolithic 3D printed SLA material. It was not possible to accurately characterize the propellent leak rate via weight by measuring the mass loss from the tank. This is due to the SLA material having both a high absorbance rate of water in normal …

Sensitivity And Estimation Of Aerodynamic, Propulsion, And Inertial Parameters For Rudderless Aircraft Using Simulation, Jaden W. Thurgood

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

A technique known as system identification is often used in aircraft design and testing to understand and validate the mathematical parameters that describe the aircrafts stability and handling characteristics. System identification can be thought of as the inverse of simulation. In the world of system identification, we have a physical system that we seek to understand in more detail by monitoring the system with an array of sensors. In short, we conduct tests of an aircraft while recording the inputs and response outputs. Then we take the input and output data and run it through an algorithm that seeks to …

Reconstruction Of Attenuated Hybrid Rocket Motor Chamber Pressure Signals Using Maximum Likelihood Estimation And Optimal Deconvolution, Evan M. Zelesnik

All Graduate Plan B and other Reports, Spring 1920 to Spring 2023

Chamber pressure, as it develops during rocket combustion, strongly correlates with many of the internal motor ballistics, including combustion stability, fuel regression rate, and mass flow. Chamber pressure is also an essential measurement for calculating achieved thrust coefficient and characteristic velocity. Due to the combustion environment hostility, sensing chamber pressure with high-fidelity presents a difficult measurement problem, especially for solid and hybrid rocket systems where combustion by-products contain high amounts of carbon and other sooty materials. These contaminants tend to deposit within the pneumatic tubing used to transmit pressure oscillations from the thrust chamber to the sensing transducer. Partially clogged …

Additively-Manufactured Hybrid Rocket Consumable Structure For Cubesat Propulsion, Britany L. Chamberlain

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

Three-dimensional, additive printing has emerged as an exciting new technology for the design and manufacture of small spacecraft systems. Using 3-D printed thermoplastic materials, hybrid rocket fuel grains can be printed with nearly any cross-sectional shape, and embedded cavities are easily achieved. Applying this technology to print fuel materials directly into a CubeSat frame results in an efficient, cost-effective alternative to existing CubeSat propulsion systems. Different 3-D printed materials and geometries were evaluated for their performance as propellants and as structural elements. Prototype "thrust columns" with embedded fuel ports were printed from a combination of acrylonitrile utadiene styrene (ABS) and …

Enhancement Of Volumetric Specific Impulse In Htpb/Ammonium Nitrate Mixed Hybrid Rocket Systems, Jacob Ward Forsyth

All Graduate Plan B and other Reports, Spring 1920 to Spring 2023

Hybrid rocket systems are safer and have higher specific impulse than solid rockets. However, due to large oxidizer tanks and low regression rates, hybrid rockets have low volumetric efficiency and very long longitudinal profiles, which limit many of the applications for which hybrids can be used. This research investigates a method for increasing the volumetric efficiency and improving the form factor of hybrid rocket systems by a non-combustible load of solid oxidizer to the hybrid fuel grain. Including such oxidizers increases the regression rate of the fuel and lowers the amount of fluid oxidizer needed for optimal combustion. This type …

Catalytic Decomposition Of Nitrous Oxide Monopropellant For Hybrid Motor Ignition, Matthew D. Wilson

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

Nitrous oxide (N₂O), a commonly-used industrial gas, is also often used as a rocket motor oxidizer. It has been used in both hybrid rocket motors (using a solid fuel and a liquid oxidizer) and liquid rocket engines (using liquid fuel and oxidizer).

As a liquid form, nitrous oxide is highly stable, but in vapor form it can be decomposed, releasing large amounts of heat as it dissociates into nitrogen and oxygen. This project investigates using the energy from decomposing nitrous oxide to ignite a hybrid or liquid rocket. Such a system would be practical in rocket …