Propulsion and Power Commons^™

Wind Tunnel Modeling Of Small Electric Uav Power System Performance, Nathan R. Phelps

Aerospace Engineering

This report details the design and construction of a testing apparatus for characterization of small electric aircraft power systems designed for use in the California Polytechnic State University San Luis Obispo Aerospace Engineering department’s subsonic wind tunnel. This apparatus was constructed and implemented with the goal of determining system and component efficiencies of an entire power system using RC Aircraft components as an analog for systems currently in use in the current generation of small electric UAV’s in service with the US Armed Forces. The goal of these experiments was to determine where improvements in the system architecture can be …

Experimental Investigation Of A 2-D Air Augmented Rocket: Effects Of Nozzle Lip Thickness On Rocket Mixing And Entrainment, Trevor Allen Montre

Master's Theses

Cold-flow tests were performed using a simulated Air Augmented Rocket (AAR) operating as a mixer-ejector in order to investigate the effects of varied primary nozzle lip thickness on mixing and entrainment. The simulated primary rocket ejector was supplied with nitrogen at a maximum chamber stagnation pressure of 1712 psi, and maximum flow rate of 1.67 lb_m/s. Secondary air was entrained from a plenum, producing pressures as low as 6.8 psi and yielding maximum stagnation pressure ratios as high as 160. The primary ejector nozzles each had an area ratio of approximately 20, yielding average primary exit Mach numbers …

Comet: Constrained Optimization Of Multiple-Dimensions For Efficient Trajectories, Michael Curt Conrad

Master's Theses

The paper describes the background and concepts behind a master’s thesis platform known as COMET (Constrained Optimization of Multiple-dimensions for Efficient Trajectories) created for mission designers to determine and evaluate suitable interplanetary trajectories. This includes an examination of the improvements to the global optimization algorithm, Differential Evolution, through a cascading search space pruning method and decomposition of optimization parameters. Results are compared to those produced by the European Space Agency’s Advanced Concept Team’s Multiple Gravity Assist Program. It was found that while discrepancies in the calculation of ΔV’s for flyby maneuvers exist between the two programs, COMET showed a noticeable …

A Look At Near-Term Nuclear Fission And Fusion Rockets For Human Mars Missions, Douglass W. Casey

Von Braun Symposium Student Posters

No abstract provided.

Analysis Of Plasma Jet Driven Magneto-Inertial Fusion As Potential Primary Propulsion Driver For Project Icarus, Milos Stanic

Von Braun Symposium Student Posters

No abstract provided.

Magnetic Field Mapping In The Plasmoid Thruster Experiment (Ptx), Coby W. Mccolgin

Von Braun Symposium Student Posters

No abstract provided.

A Probabilistic Design Analysis Approach In Reducing The Overall Risk Of A Fusion Propulsion Spacecraft, Natalie Walker

Von Braun Symposium Student Posters

No abstract provided.

Plasma Jet Magneto Inertial Fusion Thruster Concept, Richard Hatcher

Von Braun Symposium Student Posters

No abstract provided.

Beamed Energy For Ablative Propulsion In Near Earth Space, Grant Bergstue

Von Braun Symposium Student Posters

No abstract provided.

Design And Development Of An Advanced Thermonuclear Fusion Propulsion R&D Facility At Uahuntsville, Ross J. Cortez

Von Braun Symposium Student Posters

No abstract provided.

Experimental Investigation And Cfd Simulation Of Active Damping Mechanism For Propellant Slosh In Spacecraft Launch Systems, Dhawal Leuva

Doctoral Dissertations and Master's Theses

Motion of propellant in the liquid propellant tanks due to inertial forces transferred from actions like stage separation and trajectory correction of the launch vehicle is known as propellant slosh. If unchecked, propellant slosh can reach resonance and lead to complete loss of the spacecraft stability, it can change the trajectory of the vehicle or increase consumption of propellant from the calculated requirements, thereby causing starvation of the latter stages of the vehicle. Predicting the magnitude of such slosh events is not trivial. Several passive mechanisms with limited operating range are currently used to mitigate the effects of slosh. An …

Innovative Double Bypass Engine For Increased Performance, Sanjivan Manoharan

Doctoral Dissertations and Master's Theses

Engines continue to grow in size to meet the current thrust requirements of the civil aerospace industry. Large engines pose significant transportation problems and require them to be split in order to be shipped. Thus, large amounts of time have been spent in researching methods to increase thrust capabilities while maintaining a reasonable engine size. Unfortunately, much of this research has been focused on increasing the performance and efficiencies of individual components while limited research has been done on innovative engine configurations. This thesis focuses on an innovative engine configuration, the High Double Bypass Engine, aimed at increasing fuel efficiency …

The Propulsive Design Aspects On The World’S First Direct Drive Hybrid Airplane, Ankit Nanda

Doctoral Dissertations and Master's Theses

The purpose of this thesis is to design a safe technology demonstrator by implementing a direct drive propulsion system for a gas-electric hybrid aircraft. This system was integrated on the Embry-Riddle Eco-Eagle for the Green Flight Challenge 2011. The aim of the system is to allow the pilot to use the electric motor as an independent power source to fly the aircraft once at cruise altitude, while having a gas engine to allow for higher power capability.

The system was designed to incorporate the motor and the motor control unit provided by Flight Design and Drivetek AG alongside a Rotax …

Mars Carbon Dioxide Propulsion, Christopher Cushman Perry

Mechanical & Aerospace Engineering Theses & Dissertations

An experimental investigation was conducted to characterize the performance of a small-scale supersonic propulsion system using supercritical CO₂ as a propellant intended for Mars surface applications. This research has focused on estimating the specific impulse behavior of high-pressure carbon dioxide propellant that can be produced by condensing dry ice out of Mars's atmosphere and heating it at constant volume to temperatures above its 31.1 ° C critical temperature. Since supercritical fluid was created by heating different dry ice-vapor mixtures to moderate temperatures, the nominal initial density and thermodynamic state within the pressure vessel could be controlled. The instrumented test …

Designing Propulsion Systems For Future Aerospace Applications, Nihad E. Daidzic

Aviation Department Publications

No abstract provided.

Vibration-Based Health Monitoring Of Multiple-Stage Gear Train And Differential Planetary Transmission Involving Teeth Damage And Backlash Nonlinearity, Andrew Patrick Sommer

Master's Theses

The objective of this thesis is to develop vibration-based fault detection strategies for on-line condition monitoring of gear transmission systems. The study divides the thesis into three sections. First of all, the local stresses created by a root fatigue crack on a pinion spur gear are analyzed using a quasi-static finite element model and non-linear contact mechanics simulation. Backlash between gear teeth which is essential to provide better lubrication on tooth surfaces and to eliminate interference is included as a defect and a necessary part of transmission design. The second section is dedicated to fixed axis power trains. Torsional vibration …

Comparison Of Best Economy And Best Power Mixture Settings In The Purdue University Training Fleet, Charles G. Chrisman

Purdue Polytechnic Directed Projects

Purdue University operates a fleet of Cirrus SR20s as training aircraft. Standard operating procedures for the cruise portion of cross country training flights call for 65% power with a best power mixture, also called rich of peak, as opposed to a best economy setting, also called lean of peak. Previous work demonstrated that fuel consumption rates, cylinder head temperatures, and true airspeeds are lower when best economy is employed compared to best power for the same power output. This study confirmed that best economy is associated with a lower fuel consumption rate and lower cylinder head temperatures but was unable …

Comparison Of Turbine Engine Test Cell Airborne Nanoparticle Count Versus Ambient Background Particle Count, Ryne Larowe

Purdue Polytechnic Directed Projects

With the establishment of the National Test Facility for Aerospace Fuels and Propulsion at Purdue University in October of 2009, new equipment has been acquired to measure and classify exhaust emissions. This facility utilizes the Honeywell F109 turbofan and Pratt & Whitney PT-6 turboprop engine test cells to analyze the emissions and engine operation of new alternative aviation fuels. This observational study investigates what, if any difference there is in the amount of ambient residual Particulate Matter (PM) in the turbofan engine test cell when compared to ambient particle count associated with the Purdue University Airport (KLAF) property. The project …

Analysis And Design Of A Propulsion System Trade Study Tool For A Boeing 376 Series Communications Satellite, Kevin Dunk

Aerospace Engineering

No abstract provided.

Design, Manufacturing And Testing Of An Environmentally-Green Bipropellant Thruster, Alex Bendoyro, Gabriel Sanchez, Erin Stearns, Phillip Takahashi

Aerospace Engineering

This project reviews the design, manufacturing and experimentation process of a green bi-propellant thruster designed to output 5 lbf. The goals were to successfully design, manufacture and test a thruster, while discovering the complications that arise through out the complete design process of a green thruster. The thruster was successfully designed using ideal rocket equations and the design was successfully confirmed using CFD and FEA. Manufacturing of the thruster was fully planned and revealed mild flaws in thruster design. For example some features were not manufacturable to the exact measurements desired. Testing of the engine gave results inconsistent with expected …

Electric Aircraft Propulsion Test Rig Design & Fabrication, Ryan Mayer, Brian Kubicki, Bradley Rodriguez, Austin Harris, David Caudle

Aerospace Engineering

An electric aircraft propulsion test rig was designed and fabricated to predict thrust, torque and battery discharge profiles for an electric aircraft. The original unit was purchased from ElectraFlyer and included the DC brushless motor, carbon fiber propeller, charger, electronic controller and lithium polymer batteries. Various components were constructed and purchased in order to fabricate the optimal test rig apparatus. This apparatus allows for simultaneous measurement of the torque and thrust of the system through the use of a biaxial sensor. The test rig also measures system voltage and current, which allows the user to determine the discharge profile of …

Hybrid Rocket Based Combined Cycle Test Rig Design, Construction, And Testing, Mark Costa, Matthew Handfelt

Aerospace Engineering

No abstract provided.

Imu Integration To The Cal Poly Spacecraft Attitude Dynamics Simulator Power System, Wayland Chan

Electrical Engineering

The Cal Poly Spacecraft Attitude Dynamics Simulator mimics the rotation dynamics of a spacecraft in orbit and acts as a test bed for spacecraft attitude control system development and demonstration. Prior to this project, the simulator measured its attitude dynamics from a total of seven sensors mounted on to the platform, including three micro-electromechanical system (MEMs) gyroscopes, and four motor encoders. This project entails the installation of an LN-200 high performance gyroscope, which will provide a greater measure of accuracy. The goal of this project is to design a power circuit that will integrate the LN-200 inertial measurement unit onto …

Airplane Landing Flare-The Last 5 Seconds, Nihad E. Daidzic

Aviation Department Publications

No abstract provided.

Electric Motor & Power Source Selection For Small Aircraft Propulsion, Jeremy Fehrenbacher, David L. Stanley, Mary E. Johnson Dr., Jeffrey Honchell

Purdue Polytechnic Directed Projects

The research conducted in this project is on electrical propulsion in aviation. A Cessna 172K aircraft with a Lycoming O-320-E2D piston engine serves as a baseline measurement. Investigation of the components required for electrical flight is performed, and components are selected based on market availability and operational performance criteria.

This research focuses on electrical propulsion in the aviation industry, and is tailored to aircraft within the General Aviation sector leading to the following research question: Can current electric motor and battery technologies conceptually support flight operations for a Cessna 172K in terms of aircraft performance criteria?

The results explore the …

Analysis Of Flow Migration In An Ultra-Compact Combustor, Brian T. Bohan

Theses and Dissertations

One of the major efforts for turbine engine research is to improve the thrust to weight of the system. One novel concept for accomplishing this is the use of an Ultra-Compact Combustor (UCC). The UCC attempts to shorten the overall combustion length (thereby reducing weight) by performing the combustion in the circumferential direction along the outside diameter of the core flowpath. One of the major benefits of this design is enhanced combustion due to the establishment of a high-g field in the circumferential cavity. AFIT and the Air Force Research Laboratory (AFRL) have been teamed for several years in understanding …

Compressor Performance Map Generation And Testing Per Sae J1723, Jeffrey Lee Freeman

Aerospace Engineering

A MATLAB program was written to plot compressor performance maps for a set of test data that was collected in accordance with SAE J1723 at Vortech Engineering, Inc. Paxton Automotive Corp.'s N2500 supercharger was used as a case example for the program, which was carried through from test stand installation to finalized compressor performance map. A sequence was also developed to interpolate the efficiency of the compressor for a given operational setting. The program was shown to be a great improvement from the previously applied technique for accomplishing the same tasks; it is more accurate in plotting the given data, …