Theses/Dissertationshttp://hdl.handle.net/11141/2212019-03-21T15:48:18Z2019-03-21T15:48:18ZAerodynamic Model of the Piper Warrior II Based on Flight Test DataCasciola, Nicholashttp://hdl.handle.net/11141/27492019-03-21T07:00:58Z2018-12-01T00:00:00ZAerodynamic Model of the Piper Warrior II Based on Flight Test Data
Casciola, Nicholas
Aerodynamic modeling is an important part of aircraft design and of aircraft testing.
Generally, this is done through CFD models and Wind Tunnel tests prior to the aircrafts
first flight but building the models using flight test data is also very important. It is used to
verify theoretical models generated from the computer and wind tunnel tests. They are
also useful for building simulators, particularly those in modeling and analyzing airport
traffic patterns.
These tests used a Piper Pa-28-161 Warrior II owned by the Florida Tech Flight Test
Engineering program. It has a 160hp Lycoming engine. The test pilot was Dave Schwarz
with Nicholas Casciola and Gary Greeman acting as Flight Test Engineers. The tests took
place on April 27th, 2018 East of the Orlando-Melbourne International Airport (KMLB).
The stability and control parameters were estimated using least squares, equation error,
stepwise, and output-error regression methods. These parameters were not accurately
estimated here due to several reasons. The first being the lack of a filter on several sets of
input data. The next would be that no initial heading was recorded at the start of each
maneuver; this means that yaw angle could not be found. The final piece to improve the
models is to correct for the sensor locations in the aircraft. If the sensors are not over the
cg of the aircraft, then corrections need to be made to adjust for the inertial effects of the
moment arm caused by that distance.
Thesis (M.S.) - Florida Institute of Technology, 2018
2018-12-01T00:00:00ZDevelopment of Adaptable Human-Machine Interface for Teleoperation Over Time DelayChan, May Nyeinhttp://hdl.handle.net/11141/27482019-03-08T08:02:08Z2018-12-01T00:00:00ZDevelopment of Adaptable Human-Machine Interface for Teleoperation Over Time Delay
Chan, May Nyein
The Adaptable Human-Machine Interface (AHMI) was developed for the Orbital
Robotic Interaction, On-orbit servicing, and Navigation (ORION) Laboratory of the
Florida Institute of Technology. The primary project objective was to develop and test
a predictive display for mitigating the effects of time delay in teleoperation of space
robots and Unmanned Aerial Vehicles (UAV) using quadcopters as a test case.
Regardless of the increasing popularity of various autonomous systems, research and
development of teleoperating system should not be neglected since it is often utilized as
a back-up in most autonomous systems especially in systems for human spaceflight and
UAV operations in unpredicted conditions. This project serves as a pilot research
project for developing a Human-Machine-Interface (HMI) for teleoperating over time
delay, which can be adapted for different flight mechanics and/or systems. The interface
has been developed in the Unity3D game engine and implemented for a Parrot A.R.
Drone 2.0. Test results suggest that various elements of the head-up display will require
to be customized along with the system dynamics model to achieve an effective
predictive display. However, the interface software framework in Unity3D can be
utilized, adapted, or expanded for different flight mechanics.
Thesis (M.S.) - Florida Institute of Technology, 2018
2018-12-01T00:00:00ZEffect of Film Cooling Hole Size on a Turbine Rotor BladeMartis, Klinthttp://hdl.handle.net/11141/27472019-03-08T08:02:00Z2018-12-01T00:00:00ZEffect of Film Cooling Hole Size on a Turbine Rotor Blade
Martis, Klint
The objective of this study was to evaluate the effect of the cooling hole size on
the adiabatic film cooling effectiveness over a rotating turbine blade section. The
study was conducted using ANSYS FLUENT to determine the adiabatic wall
temperature over the blade surface. The geometry was created to be a single
section of a turbine rotating at 4000 rpm, and the blade increases in camber from
tip to hub. Cylindrical cooling holes were created and the diameters were varied
from 0.5 mm to 1.5 mm. The pitch-to-diameter ratio and the length-to-diameter
ratio were kept constant at a value of 3. An unstructured mesh was generated for
the geometry, and an inflation layer was created to capture the boundary layer
around the blade surface. The Shear-Stress Transport k-ω turbulent model was
used with the curvature correction and production limiter. The velocity
boundary condition for the flow entering the domain was set such that the angle
with respect to axial direction was the same as the angle-of-attack of the blade.
Therefore, the velocity components in the y−direction and the z−direction were
set to values of -128.56 m/s and 153.21 m/s, respectively, and the temperature
was set such that T The objective of this study was to evaluate the effect of the cooling hole size on
the adiabatic film cooling effectiveness over a rotating turbine blade section. The
study was conducted using ANSYS FLUENT to determine the adiabatic wall
temperature over the blade surface. The geometry was created to be a single
section of a turbine rotating at 4000 rpm, and the blade increases in camber from
tip to hub. Cylindrical cooling holes were created and the diameters were varied
from 0.5 mm to 1.5 mm. The pitch-to-diameter ratio and the length-to-diameter
ratio were kept constant at a value of 3. An unstructured mesh was generated for
the geometry, and an inflation layer was created to capture the boundary layer
around the blade surface. The Shear-Stress Transport k-ω turbulent model was
used with the curvature correction and production limiter. The velocity
boundary condition for the flow entering the domain was set such that the angle
with respect to axial direction was the same as the angle-of-attack of the blade.
Therefore, the velocity components in the y−direction and the z−direction were
set to values of -128.56 m/s and 153.21 m/s, respectively, and the temperature
was set such that T∞ = 1800 K. The velocity boundary conditions at the hole
inlets were calculated such that the mass flow rates on the suction and pressure
= 1800 K. The velocity boundary conditions at the hole
inlets were calculated such that the mass flow rates on the suction and pressure sides were 0.00384 kg/s and 0.01295 kg/s, respectively. The temperature
boundary condition at the hole inlets was calculated to be 973.86 K. A
quantitative analysis was performed using the exported temperature data, where
the laterally-averaged effectiveness was plotted against the non-dimensional
position, z/c. Qualitative analysis was also performed by observing the
temperature distributions on the blade surface, as well as the velocity streamlines
from the inlets of the film cooling holes. Streamlines colored by Mach number
were used to ensure flow remained subsonic. Based on the results, the increase in
the hole size improved the distribution of the effectiveness downstream from the
holes on the pressure side, but had minimal effect on the effectiveness on the
suction side. An increase in the cooling hole size caused an increase in the
spreading of the coolant from the cooling hole exits over the blade surface. On
the pressure side, the slope on the effectiveness plots for the larger angles show
that the amount of cooling remains almost the same along the blade’s axial
position.
Thesis (M.S.) - Florida Institute of Technology, 2018
2018-12-01T00:00:00ZTHREE DIMENSIONAL NONLINEAR SIMULATION OF QUENCH PHENOMENON IN SUPERCONDUCTING TAPES USING MESH-FREE MONTE-CARLO METHODBahadori, Rezahttp://hdl.handle.net/11141/27002019-03-06T08:00:49Z2018-12-01T00:00:00ZTHREE DIMENSIONAL NONLINEAR SIMULATION OF QUENCH PHENOMENON IN SUPERCONDUCTING TAPES USING MESH-FREE MONTE-CARLO METHOD
Bahadori, Reza
Performing quench propagation simulations of full size superconducting coils is a
challenging problem due to complex coil structures and internal arrangements of
superconducting wires. In addition, superconducting wires and cables themselves constitute
complex 3D arrangements comprised of superconductor, matrix, stabilizer, insulation and
other materials. Modelling quenches in complete coils is therefore a complex multi-scale
and multi-physics problem that is difficult to solve with conventional techniques like finite
element or finite difference methods. Monte-Carlo methods have been successfully used to
simulate various multi-scale and multi-physics problems, but to our knowledge have not
been applied to quench propagation simulations. In the first chapter, the application of the
Monte-Carlo method for quench propagation problems has been studied and first results are
presented. A mesh free Monte-Carlo method has been used that lends easily to
parallelization.
A novel mesh-free Monte-Carlo method for two-dimensional transient heat conduction in
composite media with temperature dependent thermal properties is presented in the second
chapter. The proposed approach is based on expressing the solution of the transient
conductive heat transfer equation, in domains with temperature-dependent material properties, as a combination of two solutions: Bessel functions and integrals of peripheral
temperature. The proposed approach is used to solve transient conduction in composite
layered materials with temperature dependent thermal diffusivity. Results are compared
against others obtained using a conventional finite element approach. Experimental results
for heat transfer in a non-homogeneous domain (composite layered material) are presented
to demonstrate the performance of the proposed approach.
A new solution for the three-dimensional transient heat conduction from a homogeneous
medium to a non-homogeneous multi-layered composite material with temperature
dependent thermal properties using a mesh-free Monte-Carlo method is proposed in chapter
three. The novel contributions include a new algorithm to account for the impact of thermal
diffusivities from source to sink in the calculation of the particles’ step length (particles are
represented as bundles of energy emitted from each source), and a derivation of the three-dimensional peripheral integration to account for the influence of material properties
around the sink on its temperature. Simulations developed using the proposed method are
compared against both experimental measurements and results from a finite element
simulation.
Finally, in chapter four, a state-of-the-art method is established to undertake the immense
and complex Multiphysics problems involving heat conduction, electrical current sharing
and joule heating. The innovative improvement includes an algorithm that eliminates the
requirement of particles scattering from conventional Monte-Carlo methods. This algorithm
encapsulate a volume around each point that the solution for the point is affected by in
corresponding time span. This volume consists of other points of geometry that can slightly
move to reconcile along the path of energy transfer. The proposed method benefits from high
parallelizability of Monte-Carlo method while its performance is escalated substantially by
dispose of interpolation steps. The accuracy and simulation time of the method is examined
and compared against Finite Element Method. The results are within strict margin of error
and the speed up performance is promising.
Thesis (Ph.D.) - Florida Institute of Technology, 2018
2018-12-01T00:00:00Z