Aeronautical Vehicles Commons^™

"Cap" Cornish, Indiana Pilot: Navigating The Century Of Flight, Ruth Ann Ingraham

Purdue University Press Books

Clarence "Cap" Cornish was an Indiana pilot whose life spanned all but five years of the Century of Flight. Born in Canada in 1898, Cornish grew up in Fort Wayne, Indiana. He began flying at the age of nineteen, piloting a "Jenny" aircraft during World War I, and continued to fly for the next seventy-eight years. In 1995, at the age of ninety-seven, he was recognized by Guinness World Records as the world's oldest actively flying pilot. The mid-1920s to the mid-1950s were Cornish's most active years in aviation. During that period, sod runways gave way to asphalt and concrete; …

The Differences Are Not So Great: High Altitude Balloon And Small Spacecraft Software Development, Jeremy Straub, Ronald Marsh

Jeremy Straub

Previous work discussed critical differences in planning, developing hardware for and executing a high altitude balloon (HAB) mission. One area where this difference is less pronounced is in software development, allowing HABs to be utilized as a ‘software testbed’ for many orbital missions. This paper provides an overview of the software development process for both orbital and HAB craft, highlighting differences between the two processes and the numerous similarities. It concludes by presenting a framework for analyzing the suitability of HAB testing for small satellite software.

Localization And System Identification Of A Quadcopter Uav, Kenneth Befus

Masters Theses

The research conducted explores the comparison of several trilateration algorithms as they apply to the localization of a quadcopter micro air vehicle (MAV). A localization system is developed employing a network of combined ultrasonic/radio frequency sensors used to wirelessly provide range (distance) measurements defining the location of the quadcopter in 3-dimensional space. A Monte Carlo simulation is conducted using the extrinsic parameters of the localization system to evaluate the adequacy of each trilateration method as it applies to this specific quadcopter application. The optimal position calculation method is determined.

Furthermore, flight testing is performed in which real range measurement data …

Lightweight Uav Launcher, Ben Miller, Christian Valoria, Corinne Warnock, Jake Coutlee

Mechanical Engineering

This report discusses the design, construction, and testing of a lightweight, portable UAV launcher. There is a current need for a small team of soldiers to launch a US Marine Tier II UAV in a remote location without transport. Research was conducted into existing UAV launcher designs and the pros and cons of each were recorded. This research served as a basis for concept generation during the initial design development stage. It was required that the design weigh less than 110 lbs, occupy a smaller volume than 48" x 24" 18" in its collapsed state, be portable by a single …

Flight Testing Small Uavs For Aerodynamic Parameter Estimation, Adam Thomas Chase

Master's Theses

A flight data acquisition system was developed to aid unmanned vehicle designers in verifying the vehicle's design performance. The system is reconfigurable and allows the designer to choose the correct combination of complexity, risk, and cost for a given flight test. The designer can also reconfigure the system to meet packaging and integration requirements. System functionality, repeatbility, and accuracy was validated by collecting data during multiple flights of a radio-controlled aircraft. Future work includes sensor fusion, thrust prediction methods, stability and control derivative estimation, and growing Cal Poly's small-scale component aerodynamic database.

2014 Sae Aero: Systems Engineering, Adam Herzog

Honors Theses

Union has participated in the annual SAE Aero Competition for the last 6 consecutive years. The aim of the competition involves the design and construction of an RC aircraft capable of carrying a maximum payload weight as consistently as possible. This report will summarize the methods used to determine shape and size of the final aircraft’s control surfaces, as well as include an analysis on the plane’s performance characteristics. The final design utilizes a 100 inch span main wing with a rear taper and an upright H-tail design. In addition, the horizontal tail has a stabilator in place of a …

The Role Of Unmanned Aircraft Systems (Uas) In Disaster Response And Recovery Efforts: Historical, Current And Future, Dennis Vincenzi, David C. Ison, Brent A. Terwilliger

Publications

A wide range of legislation has been proposed or put into place that restricts the use of unmanned systems. These actions by legislators and regulators will stifle the growth of this technology and the associated surrounding industry. The largest obstacle to the proliferation of UAS in the U.S. is the FAA. The FAA has designated the location of six test sites that are anticipated to allow for less restrictive and formative research to assess the technologies that the FAA has claimed need to exist in order to integrate UAS into the NAS. Further complicating the adoption of UAS for beneficent …

A Low-Cost Gps/Inertial Position Determination System For High Altitude Balloons, Spacecraft And Unmanned Aerial Systems, Tyler Leben, Jeremy Straub, Ronald Marsh

Jeremy Straub

A low-cost system is needed to determine precise position and predict future location in flight and low-Earth orbit. One method to accomplish this task is to utilize an onboard GPS receiver. GPS units receive data from the GPS NAVSTAR constellation of 24 satellites in the form of a 37 byte ASCII text sent at 4800 baud called NMEA sentences. The standard is 1 HZ, which is one sentence per second, but can be more. Ideally, from this data a PVT (position, velocity, time) and altitude can be determined. This data is then transferred from the GPS module to a separate …

The Path To Regulation Of Small Unmanned Aerial Vehicles In The United States, Jeremy Straub, Joe Vacek

Jeremy Straub

This poster presents an overview of proposed regulations that are presented in [1] related to a re-vised approach to small Unmanned Aerial Vehicles (UAV) regulation in the United States. Prospective strategies for enhancing UAV regulation are consid-ered as is the pathway to develop and implement these regulations. The benefits of changing the UAV regulatory regime are discussed, on both a user/prospective user and societal scale.

The Use Of Solar Balloons At Und As A Low-Cost Alternative To Helium Balloons For Small Spacecraft Testing And Stem Education, John Nordlie, Jeremy Straub, Chris Theisen, Ronald Marsh

Jeremy Straub

Helium-filled latex weather balloons have been utilized for many years to carry small satellite prototypes and subsystems into the stratosphere to allow testing in a “near space” (stratospheric) environment. A variety of environmental factors similar to the space environment can be found in this region, such as a rarified atmosphere, increased thermal stress including very low temperatures, increased solar radiation, the necessity of remote command and control, tracking, and telemetering of data. While this method of flight testing has been well-proven, a recent increase in the price of helium has driven the cost of such test programs to much higher …

The Use Of 3d Printing To Enable High Altitude Balloon Missions, Jeremy Straub

Jeremy Straub

The 3D printing technology allows the low-cost creation of structures based on user-defined configuration parameters. Unlike other plastic-forming technologies, there is no tooling cost related to the creation of a mold. Because of this, highly-customized structures can be created with a minimum production quantity of one, allowing adaptation to individual mission needs (for a single-HAB mission) or the change of the structure across a multi-unit run (e.g., to test various configurations or as part of a study requiring multiple payloads with different configurations).

This paper considers the mission possibilities enabled by the use of 3D printing for HAB structures. These …

Nasa Human Exploration Rover Challenge, Estelle Fortes, Aaron Taylor, Caitlin Talerico, Jessica Chow, Jessica Turcios, Johnnie Perry, Joshua Beck, Juana Cecilia Martin-Gonzalez, Lisa Ferguson, Michaela Branscomb, Mo Sabliny, Raeann Vansickle, Sarah Pearson, Sierra Dryer, Zach Henney, Brenda Haven

Aviation / Aeronautics / Aerospace International Research Conference

NASA's Great Moonbuggy Race, held annually in at the Marshall Space Flight Center in Huntsville, Alabama, is an engineering design challenge that asks teams of student engineers to design a human-­‐powered vehicle capable of traversing a simulated lunar surface. However, there is an interesCng sCpulaCon in the design of the moonbuggy: it must be able to be transported in a 4x4x4 foot cube, echoing the design constraint faced by the engineers who built the Lunar Roving Vehicles used by the astronauts of the later Apollo missions. The vehicle in this proposal, Ocelot, designed by the Society of Women Engineers at …

Investigation Of An Autonomous Landing Sensor For Unmanned Aerial Systems, A Ram (Bella) Kim

A Ram (Bella) Kim

Verification Of Video Frame Latency Telemetry For Uav Systems Using A Secondary Optical Method, Sam B. Siewert

Sam B. Siewert

This paper presents preliminary work and a prototype computer vision optical method for latency measurement for an UAS (Uninhabited Aerial System) digital video capture, encode, transport, decode, and presentation subsystem. Challenges in this type of latency measurement include a no-touch policy for the camera and encoder as well as the decoder and player because the methods developed must not interfere with the system under test. The goal is to measure the true latency of displayed frames compared to observed scenes (and targets in those scenes) and provide an indication of latency to operators that can be verified and compared to …

Solar Ballooning: A Low-Cost Alternative To Helium Balloons For Small Spacecraft Testing, John Nordlie, Jeremy Straub, Chris Theisen, Ronald Marsh

Jeremy Straub

Helium-filled latex weather balloons have been utilized to carry small satellite prototypes and subsystems into the stratosphere to allow testing in a “near space” environment. This provides a variety of environmental factors similar to the space environment, such as a rarified atmosphere, increased thermal stress, increased solar radiation, the necessity of remote command and control, tracking, and telemetering of data. While this method of flight testing has been well-proven, a recent spike in the price of helium has driven the cost of such test programs to much higher levels. In this poster, an alternative technology to provide the flight mechanism, …

Gust Mitigation Of Micro Air Vehicles Using Passive Articulated Wings, Adetunji Oduyela, Nathan Slegers

Faculty Publications - Biomedical, Mechanical, and Civil Engineering

Birds and insects naturally use passive flexing of their wings to augment their stability in uncertain aerodynamic environments. In a similar manner, micro air vehicle designers have been investigating using wing articulation to take advantage of this phenomenon. The result is a class of articulated micro air vehicles where artificial passive joints are designed into the lifting surfaces. In order to analyze how passive articulation affects performance of micro air vehicles in gusty environments, an efficient 8 degree-of-freedom model is developed. Experimental validation of the proposed mathematical model was accomplished using flight test data of an articulated micro air vehicle …

A Mobile Self-Leveling Landing Platform For Small-Scale Uavs, Stephen Austin Conyers

Electronic Theses and Dissertations

This thesis presents a semi-autonomous mobile self-leveling landing platform designed to launch, recover and re-launch VTOL UAVs without the need for human intervention. The landing platform is rugged, lightweight and inexpensive, making it ideal for civilian applications that require a base station from which a rotorcraft UAV can be launched and recovered on terrain that is normally unsuitable for UAV operations. This landing platform is capable of self-leveling on rough terrain and inclined slopes, and can autonomously operate in remote locations for extended periods of time using large onboard lithium batteries and wireless communication. This thesis discusses the unique design …

Rocket Flight Path, Jamie Waters

Undergraduate Journal of Mathematical Modeling: One + Two

This project uses Newton’s Second Law of Motion, Euler’s method, basic physics, and basic calculus to model the flight path of a rocket. From this, one can find the height and velocity at any point from launch to the maximum altitude, or apogee. This can then be compared to the actual values to see if the method of estimation is a plausible. The rocket used for this project is modeled after Bullistic-1 which was launched by the Society of Aeronautics and Rocketry at the University of South Florida.

Robust And Adaptive Nonlinear Control Of Limit Cycle Oscillations In Uavs Using Synthetic Jet Actuators, Natalie Ramos Pedroza

Doctoral Dissertations and Master's Theses

Limit cycle oscillations (LCO), also known as utter, cause significant challenges in fight control of unmanned aerial vehicles (UAVs), and could potentially lead to structural damage and catastrophic failures. LCO can be described as vibrational motions in the pitching and plunging displacements of an aircraft wing. Even in low Reynolds number (low-Re) fight regimes, LCO can exceed the limiting boundary for safe UAV fight. Further, as practical considerations motivate the design of smaller, lighter weight UAVs, there is a growing need for UAV systems that do not require heavy mechanical actuators (e.g., ailerons). To address this, the use of synthetic …

Filtered-Dynamic-Inversion Control For Fixed-Wing Unmanned Aerial Systems, Jon Mullen

Theses and Dissertations--Mechanical Engineering

Instrumented umanned aerial vehicles represent a new way of measuring turbulence in the atmospheric boundary layer. However, autonomous measurements require control methods with disturbance-rejection and altitude command-following capabilities. Filtered dynamic inversion is a control method with desirable disturbance-rejection and command-following properties, and this controller requires limited model information. We implement filtered dynamic inversion as the pitch controller in an altitude-hold autopilot. We design and numerically simulate the continuous-time and discrete-time filtered-dynamic-inversion controllers with anti-windup on a nonlinear aircraft model. Finally, we present results from a flight experiment comparing the filtered-dynamic-inversion controller to a classical proportional-integral controller. The experimental results show …