Mechanical Engineering Commons^™

Estimating The Subsonic Aerodynamic Center And Moment Components For Swept Wings, W. F. Phillips, Doug F. Hunsaker, R. J. Niewoehner

Mechanical and Aerospace Engineering Faculty Publications

An improved method is presented for estimating the subsonic location of the semispan aerodynamic center of a swept wing and the aerodynamic moment components about that aerodynamic center. The method applies to wings with constant linear taper and constant quarter-chord sweep. The results of a computational fluid dynamics study for 236 wings show that the position of the semispan aerodynamic center of a wing depends primarily on aspect ratio, taper ratio, and quarter-chord sweep angle. Wing aspect ratio was varied from 4.0 to 20, taper ratios from 0.25 to 1.0 were investigated, quarter-chord sweep angles were varied from 0 to …

Photoelectric Charging By Ultraviolet Light Of A Lunar Dust Simulant In A Microgravity Environment, Microgravity Research Team 2008

Reports and Proposals

No abstract provided.

A Numerical Blade Element Approach To Estimating Propeller Flowfields, Doug F. Hunsaker

Mechanical and Aerospace Engineering Faculty Publications

A numerical method is presented as a low computational cost approach to modeling an induced propeller flowfield. This method uses blade element theory coupled with momentum equations to predict the axial and tangential velocities within the slipstream of the propeller, without the small angle approximation assumption common to most propeller models. The approach is of significant importance in the design of tail-sitter vertical takeoff and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow past the wings in some flight conditions. The algorithm is presented, the model is characterized, and the results (including the results …

The Effects Of Charging By Ultraviolet Light On Granular Lunar Simulant In A Microgravity Environment, Sydney J. Chamberlin, Troy Munro, Sarah Isert, Tracy Garin Savage

Reports and Proposals

No abstract provided.

A Lifting-Line Approach To Estimating Propeller/Wing Interactions, Doug F. Hunsaker, Deryl O. Snyder

Mechanical and Aerospace Engineering Faculty Publications

A combined wing and propeller model is presented as a low-cost approach to first-cut modeling of slipstream effects on a finite wing. The wing aerodynamic model employs a numerical lifting-line method utilizing the 3D vortex lifting law along with known 2D airfoil data to predict the lift distribution across a wing for a prescribed upstream flowfield. The propeller/slipstream model uses a blade element theory combined with momentum conservation equations. This model is expected to be of significant importance in the design of tail-sitter vertical take-off and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow …

Utilization Of Ultrasonic Consolidation In Fabricating Satellite Decking, Joshua L. George

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

A fundamental investigation of the use of ultrasonic consolidation (UC) to produce deck panels for small satellites was undertaken. Several fabrication methods for producing structural panels and decking were analyzed. Because of its ability to create aluminum objects in an additive fashion, and at near-room temperatures, UC was found to be a powerful solution for creating highly integrated and modular satellite panels. It also allowed a lightweight and stiff deck to be fabricated without the use of adhesives.

A series of experiments were performed to understand the issues associated with creating a sandwich-type structure using UC. The experiments used a …

Driveline For The Usu 2006 Mini Baja, Daniel Chase Swenson

Undergraduate Honors Capstone Projects

The Mini Baja project is part of an intercollegiate engineering design competition sponsored by SAE. For this competition senior engineering students at USU design and build a small off-road racecar. The design of the car is broken up into several different subassemblies. The driveline subassembly is responsible for transmitting the power from the transmission to the rear wheels. This is accomplished using several different components that have all been analyzed and designed. The completed driveline is able to accommodate sixteen inches of suspension travel, is lightweight, and was inexpensive to build. The driveline along with the rest of the car …

Design Of 'Iris', A Small Autonomous Surveillance Uav, Jennifer Boyce, Ryan Carr, Donovan Chipman, Greg Larson, Nathan Hopkins, Doug F. Hunsaker, W. Jerry Bowman

Mechanical and Aerospace Engineering Faculty Publications

This paper documents the design process used for a small autonomous surveillance UAV. The most significant requirements for the plane were size (man-packable), endurance (about 1 hour) and cost (essentially disposable). The plane that resulted, named "Iris", is a tailless plane with a 45 cm wing span and a total mass of less than 200g. During flight tests, it achieved an endurance of 52 minutes. The estimated cost to manufacture the planes was $343, excluding the autopilot.

Thermoacoustic Refrigerator, Nathan A. Hammond

Undergraduate Honors Capstone Projects

Thermoacoustic refrigerators have typically been designed to cool an isolated working fluid, necessitating a heat exchanging device to draw heat from the outside target fluid into the cooled working fluid. For example, a thermoacoustic refrigerator designed to chill air might utilize argon as an isolated working fluid, necessitating a heat exchanger to draw heat from the air to the argon. A second heat exchanger would be required to draw heat from the argon to a cold sink.

A design team at Utah State University has created a thermoacoustic refrigerator which uses air at atmospheric pressure as its working fluid. By …

The Wright Stuff: A Redesign Of The 1905 Wright Flyer, Adam Richards, Ben Case, Eric Peterson, Nathan Holman, Wayne Goodrich, Amy Hintze, Carson Esplin, David Christensen, Jonathan Holfeltz, Nick Filimoehala, Nicholas Alley

Mechanical and Aerospace Engineering Capstone Projects

No abstract provided.

Remote Freedom, Dominic M. Florin

Undergraduate Honors Capstone Projects

Increasing mobility is a key to ensuring that a disabled child feels accepted and as normal as possible. The object of Remote Freedom is to provide an inexpensive design that will modify a toy vehicle so that it can run remotely. The case that we designed for was a child with cerebral palsy. Originally the toy vehicle on the market needed major modifications both for the safety of the child and the addition of the remote control The main components that were added were a safety harness, a roll bar and motors to control steering and speed.

It was discovered …

Research And Design Of A High L/D Aircraft, Blake Ashby, Gregory Nielson

Undergraduate Honors Capstone Projects

This senior design team, consisting of Blake Ashby, Shelly Barlow, Greg Nielson, Deryl Snyder, and Chris Wright, designed, built, and flew an airplane that met the requirements of the Cessna/ONR Student Design/Build/Fly Competition sponsored by AIAA. This radio-controlled airplane was designed to fly the most laps around a course in seven minutes using only 2.5 pounds of NiCad batteries. A total of three senior design teams from Utah State University designed separate airplanes. Though all three teams designed, built, and tested complete airplanes, each emphasized a different aspect of a successful entry. This team emphasized theoretical and numerical analysis in …

Dual Adaptive Recumbent Trike, Jason V. Eastman

Undergraduate Honors Capstone Projects

The DART team's objective was to develop a tandem recumbent tricycle that would be economical, easy to build, and adaptable. This would involve designing, building and testing the tricycle.

Hydrogen On-Orbit Storage And Supply: A Spacecraft Bus Design, Roy Gladden

Undergraduate Honors Capstone Projects

Spacecraft designers have two options when developing spacecraft for a particular mission. The bus, which is the primary structure and support system for the spacecraft, can be designed from an existing layout or a new design may be developed to meet specific mission needs. In recent years, the trend in small satellite design has been to employ a previously designed spacecraft bus in order to reduce cost and development time. However, these structures sometimes provide greater capability than is required for smaller, simple missions at a higher price. Therefore, it may be preferable to custom design a bus to meet …

Design Of The Guidance, Navigation, And Control Subsystem For The Proposed Firebird Spacecraft, Erin Robinson

All Graduate Theses and Dissertations, Spring 1920 to Summer 2023

The Firebird spacecraft is a space mission to gather scientific and physical data on the effects of atmospheric deceleration, commonly called aerobraking. The objective of the Firebird mission is to measure specified aerobraking parameters over a range of reentry velocities to provide a database sufficient to construct and validate mathematical models of such aerobraking mission maneuvers. The Firebird senior design team designed the first spacecraft in the mission series to look at aerobraking at an altitude of 160 kilometers above the surface of the Earth. This paper looks specifically at the design of the subsystem that provides the guidance, navigation, …

Freezing Point Mobile Munitions Assessment Sytem: Thermal Chamber Redesign, Sara Gifford, Preston Harris

Undergraduate Honors Capstone Projects

The Army is actively investigating non-intrusive methods to identify six chemical weapons agents. The chemical munitions in question are often found scattered across military bases and other facilities. These non-stockpile munitions are specifically targeted for identification using the mobile munitions assessment system. This program is being administered by the Idaho National Engineering Laboratory.

Optimization Of Torquer Coil Design For Use With The Small Satellite Attitude Control Simulator, David Deloyd Anderson

Undergraduate Honors Capstone Projects

This paper presents a procedure used to optimize the performance of a ferromagnetic core magnetic torquer coil design for use on the Space Dynamics Laboratory (Logan, UT) Small Satellite Attitude Control Simulator. The items of optimization include the primary goal of maximizing the coil 's magnetic moment while reducing power consumption and system mass within given power, mass, and dimensional constraints. The optimization process makes use of several simple equations to determine a few starting points for design, after which an iterative approach based on experimentation is used to produce the final design. It is found that optimal magnetic moment …

Advanced Rover Chassis, Eric Alan Poulson, Collin Lewis, Todd Graves

Undergraduate Honors Capstone Projects

Background:

The six wheeled rover vehicle detailed in this design is intended as an upgrade test bed for the sensor array and autonomous navigation algorithms in use by Utah State University's Center for Self-Organizing and Intelligent Systems (CSOIS). The CSOIS's sensor suite can successfully detect and avoid unnavigable obstacles up to five vehicle lengths in front of the vehicle. The center presently uses a modified RC type chassis and only supports two wheel drive. This chassis was adequate to bring the CSOIS's algorithms to a proof-of-principles state, but in order to place the system in any practical application, a full …