BP-AE 2022 Symposium Virtual Poster Session
FAMU-FSU College of Engineering
This is the virtual poster session for the BP-AP symposium on August 11. It starts 1:30 pm until 2:45 pm. All presenters will be available for real-time, live Q/A (between 1:45 and 2:30 pm) via the ZOOM link right next to the poster. You can watch the pre-recorded video clip to get an overview of the project using the video link.
More info: https://
Filter displayed posters (33 keywords)
NASA (4)
FAMU (2)
FSU (2)
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AFRL Scholars (1)
BP -AE Summer Fellow (1)
BP-AE (1)
College of Engineering (1)
Deflected Forebody (1)
Design (1)
Engineering (1)
FlatSat (1)
GPDM (1)
GUI (1)
Innovation Initiatives (1)
Intern (1)
KSC (1)
Kennedy Space Center (1)
Lunar Flashlight (1)
MSFC intern (1)
MUREP (1)
Mechanisms (1)
Mechatronics (1)
NASA BP-AE Summer Fellow (1)
NASA KSC Intern (1)
NASA MSFC (1)
Research & Technology (1)
Robotics (1)
Software design (1)
Structures (1)
Supersonic (1)
data analysis tool (1)
post flight (1)
propulsion (1)
Show Posters:
Tracks
▼ 1. MSFC Projects Back to top
Cryogenic Thermodynamic Vent System Augmented Injector Coupled with Cryocooler to Demo Transfer and Liquefaction
Gabrielle Mayans
Abstract
Cryogenic fluid management is critical for in ground and space systems. Further advancements in cryogenic fluid management is necessary for space vehicles, especially for deep space, lunar and potential Martian missions. Current propellant transfer operations use a continuous vented chill/fill approach, this method is not preferred in space, the microgravity environment causes the gas and liquid to coalesce leading to potential loss of propellent when venting. The intended purpose of this modified injector coupled with a cryocooler is to condition the incoming liquid stream below its saturation condition, minimizing pressure spikes in the receiver tank and therefore reducing the need to vent. The injector will be tested in a vacuum chamber which mimics the low vacuum pressure of space and reduces the amount of heat transfer, limiting it to only conduction.
Presented by
Gabrielle Mayans
Institution
Florida State University
Other Affiliations
NASA Marshall Space Flight Center
Keywords
Flat Floor Robotics Laboratory Lunar Surface Simulations
Ebony Bland
Abstract
The Dynamic Overhead Robot is a robotic arm with unique capabilities. It will be used to validate the motion data of a Light Detection and Ranging sensor. However, the Overhead robot must first be automated using a Galil Motion Controller. I assisted in developing a testbed system to test the software features of the motion controller before using it on the robot. The testbed system has multiple axes of motion and hardware similar to the Overhead Robot. Using the testbed system, I evaluated a method to find optimal control law parameters to reduce position error. In addition, I interpreted the feedback provided by encoders into engineering units and found optimal amplifier settings. The progress I made on the testbed system will be in the future on the Overhead Robot.
Presented by
Ebony Bland
Institution
Florida State University
Other Affiliations
NASA
Keywords
NASA, Robotics, Mechatronics
Chat with Presenter
Available August 11th, 1-4 pm
Watch Presentation
Green Propellant Technology Development for SmallSat Propulsion Systems - GPDM FlatSat V.2
Solomon Andrews
Abstract
In the near future, permanent communities are planned for construction on the moon. This will require a demand for lots of water to be transported to and from the moon. To save large sums of time and money, the plan is to use a Lunar Flashlight to orbit the moon and pinpoint large ice deposits to use for water consumption. Our objective is to provide the capabilities to get the Lunar Flashlight mission into lunar orbit and maintain orbit for the duration of its flight mission.
A FlatSat propulsion system is the testing state of the propulsion system before it is on the Lunar Flashlight. It is completely open and accessible to any modifications necessary and to see how each piece of hardware reacts when it is operating. Our FlatSat design will be operating 5 thrusters inside a vacuum chamber. One 100mN blowdown thruster and four electrospray thrusters. The tube manufacturing for the propulsion system consists of various regulators, pressure transducers, flow meters, flight controllers, and etc. All will be used during test operations to verify the integrity of our designed solution. Test operations will evaluate the new flight controller, the 100mN thruster pulse, system response at various pressure levels, the electrosprays compact pressure regulating system, and much more. The manufacturing of the operational design is complete and we will begin running tests very soon.
A FlatSat propulsion system is the testing state of the propulsion system before it is on the Lunar Flashlight. It is completely open and accessible to any modifications necessary and to see how each piece of hardware reacts when it is operating. Our FlatSat design will be operating 5 thrusters inside a vacuum chamber. One 100mN blowdown thruster and four electrospray thrusters. The tube manufacturing for the propulsion system consists of various regulators, pressure transducers, flow meters, flight controllers, and etc. All will be used during test operations to verify the integrity of our designed solution. Test operations will evaluate the new flight controller, the 100mN thruster pulse, system response at various pressure levels, the electrosprays compact pressure regulating system, and much more. The manufacturing of the operational design is complete and we will begin running tests very soon.
Presented by
Solomon Andrews
Institution
Florida A & M University
Other Affiliations
NASA Marshall Space Flight Center
Keywords
NASA, NASA MSFC, MSFC intern, propulsion, FlatSat, GPDM, Lunar Flashlight, FAMU, FSU, Engineering, MUREP
▼ 2. KSC Projects Back to top
Automated Commercial Company Post Flight to Verify NASA Missions Requirements
Samuel Duval
Abstract
I worked with the NE-C6 team at NASA KSC this summer. The NE-C6 team (and some other branches) work as ground support for launch vehicles. To determine performance characteristics of each launch, they must graph telemetry from the launch vehicle, payload, and ground support structures.
Some members of the team use a NASA developed graphing tool called WinPlot. I was tasked with making a GUI to make the plotting for post flight analysis easier for members of the team, especially those with less experience in programming and script writing.
The GUI prompts the user for certain inputs, files, and output locations, then runs WinPlot to generate the appropriate telemetry plots.
Some functionality still needs to be added. The launch provider, Boeing, uses a different telemetry format which cannot be used in WinPlot. The plotting functionality for Boeing will be added in the Fall as I continue my internship. Some other plot customization options will also be added.
Special thanks to:
Dr. Chiang Shih, Dr. Carl Moore, my mentor Marina George, and NASA MUREP INCLUDES grant # 80NSSC21M0308 for having me
Special thanks to:
Dr. Chiang Shih, Dr. Carl Moore, my mentor Marina George, and NASA MUREP INCLUDES grant # 80NSSC21M0308 for having me
Presented by
Samuel Duval
Institution
Florida State University
Other Affiliations
Kennedy Space Center
Keywords
Software design, data analysis tool, GUI, post flight, Kennedy Space Center, NASA
Chat with Presenter
Available 3-3:45 pm EST
Watch Presentation
Research and Technology Innovation Initiatives at KSC
Tyler Ince-Ingram
Abstract
I worked as a NASA Internship (NIF) intern during the summer 2022 term, in the Research & Technology Management Office (UB-T), under the guidance of my mentor Hetal Miranda. My focus in this project consisted of; working with a cross-center team to develop a new edition of The Employee’s Guide on How to be Innovative at KSC (iGuide), aid in the facilitation of the Innovation Accelerator Initiative (IAI), and highlight Research and Technology projects and activities happening at KSC. This project will be used to enhance KSC's efforts to cultivate new ideas and technologies and will help take these efforts to the next level.
Quotes from this Summer:
Kelvin Ruiz (Deputy Chief Technologist): “The solution and templates created by Tyler will make it very simple to keep the video display up to date with the latest from the R&T community. This resource will help highlight R&T projects and activities to the rest of the KSC community.”
Hetal Miranda (Innovation Lead): “I enjoyed working with Tyler this summer! His attention to detail, organization, and communication skills were much appreciated in the development of the final report capturing the structure and results of this new initiative.”
Sean Dunne (Program Analyst): "Tyler was such a joy to work with. He brought so much enthusiasm to the table and was an integral part of all of us working together to complete the revision to the iGuide."
Quotes from this Summer:
Kelvin Ruiz (Deputy Chief Technologist): “The solution and templates created by Tyler will make it very simple to keep the video display up to date with the latest from the R&T community. This resource will help highlight R&T projects and activities to the rest of the KSC community.”
Hetal Miranda (Innovation Lead): “I enjoyed working with Tyler this summer! His attention to detail, organization, and communication skills were much appreciated in the development of the final report capturing the structure and results of this new initiative.”
Sean Dunne (Program Analyst): "Tyler was such a joy to work with. He brought so much enthusiasm to the table and was an integral part of all of us working together to complete the revision to the iGuide."
Presented by
Tyler Ince-Ingram
Institution
FAMU-FSU College of Engineering
Keywords
NASA KSC Intern, Innovation Initiatives, Research & Technology
Structures and Mechanisms Design
David Ramos
Abstract
I worked as a National Aeronautics and Space Administration (NASA) intern during the
summer 2022 term, in the NE-XD Branch, under my mentor, Cliff Manley. Our work focused on
mechanical ground support equipment. This includes the umbilical systems which transmit communication and power signals between the control room and the rocket before lift-off; primarily Quick Disconnects (QD); the mechanisms which release the umbilical systems from the rocket at or before time of launch. In addition to launch accessories, and landing and recovery equipment. My tasks for this internship were divided into three major projects which consisted of design work involving
Umbilical Hinge Brace kits, the Artemis Vehicle Stabilizer, and the Hollaender Fittings/
Guardrails Computer-Aided Design (CAD) library. These tasks are important to the rocket’s
transportation, control, and successful launch. The Umbilical Hinge Brace kits are used to
support the umbilical systems on the launch tower, holding them in place and during installation.
The Artemis Vehicle Stabilizer holds the rocket in place on the ground and releases as the rocket
launches. As for the CAD library, it holds the part and assembly files for guardrail fittings used
on the launch tower and other facilities throughout the space center. My responsibilities for these
projects centered around problem solving certain issues and inefficiencies through design.
Presented by
David Ramos
Institution
Florida A&M University
Other Affiliations
BP-AE MUREP
Keywords
NASA, KSC, Structures, Mechanisms, Design, Intern
Chat with Presenter
Available August 11; 1:30-3:00pm EST
Watch Presentation
▼ 3. AFRL Scholar Project Back to top
Experimental Testing Results of Deflected Forebody Airframes
Kevin Hernandez Lichtl and Zack Isriel
Abstract
The main objective of this study was to further the understanding of deflected nose cones and categorize the aerodynamic characteristics for varying nose deflections, angles of attack, and Mach numbers with a focus in minimizing uncertainties within the data. Our test runs utilized force and moment measurements to determine aerodynamic characteristics. This study sought to investigate and characterize the flow interactions that may lead to this loss of fin effectiveness. High-speed shadowgraphy and oil flow at Mach 2 and 4 were used to determine flow features around the model.
The force balance findings demonstrated that with increasing nose deflection, normal force and pitching moment coefficients grew when compared to an undefelcted baseline nose. Various CFD model data were shown to be valid as compared to the oil flow results, which showed near identical primary and secondary separation lines on the body and demonstrated no disturbance of the streamlines on or around the fins.
Presented by
Kevin Hernandez Lichtl, and Zack Isriel
Institution
FAMU-FSU College of Engineering
Keywords
Chat with Presenter
Available 1:45 - 2:30 pm
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High-Speed Weapon Aerodynamic Design & Flight Characterization
Robert Smith and Noah Moffeit
Abstract
In the ongoing effort to enhance the performance of modern projectiles, the articulated nose cone has been the subject of multiple studies due to its ability to impact the maneuverability and cruise performance of the projectile. Characterizing the effects of an articulated nose cone requires detailed experiments that build upon the aerodynamic database to help understand the complex flow physics involved with the unique concept. To ensure proper characterization of the impacts the articulated nose has, a detailed study involving experimental testing and computational analysis was performed.
Presented by
Robert Smith, Noah Moffeit
Institution
FAMU-FSU College of Engineering
Other Affiliations
AFRL, FCAAP
Keywords
AFRL Scholars, Deflected Forebody, Supersonic
▼ 4. BP-AE REU Projects Back to top
Implementing Adaptive Manufacturing in Development of ET Quadruped
Carl Moore III
Abstract
The NASA Big Ideas Project team is creating an extreme terrain robot capable of walking, swimming, and climbing. The goal is for a very similar robot to be put on the moon. I am on the motors, sensors, and systems integration groups.
Presented by
Carl Anthony Moore
Institution
Howard University
Keywords
BP-AE, FAMU, FSU, College of Engineering
Chat with Presenter
Available August 11: 1330 - 1445
Watch Presentation
Quantifying effects of expansion ratio on flow-field of rectangular jets
Jordan Wilkerson
Abstract
This research depicts how the flow field characteristics of supersonic jets change based on the relationship between ambient pressure and exhaust pressure. Significant factors were determined through the observation of contour plots of axial velocity, horizontal velocity, vertical velocity, density, and pressure. Plots of centerline pressure, centerline velocity, numerical shadowgraph, half-width, and velocity pressure gradient were also analyzed. I worked closely with my mentor, Anirudh, and faculty advisor, Dr. Nair. The initial two weeks began with reading literature/journals/papers relating to gas dynamics of turbulent flows. For the following three weeks after, I received mean flow field data of perfectly, under, and over expanded jets and compared the characteristics of their flow field. The last two weeks consisted of receiving the instantaneous data of all three jets and performing the same assessment, focusing on the vorticity of their flow field and comparing the instantaneous plots to the plots representing the mean data. Using a weekly-based roadmap, that involved reading literature, explaining essential details on computational fluid dynamics by my mentor, and overserving plots for mean and instantaneous data for over-, perfect-, and under- expanded jets, I developed an understanding of supersonic flows from a rectangular jet.
Presented by
Jordan Wilkerson
Institution
FAMU-FSU College of Engineering
Other Affiliations
AME Center
Keywords
BP -AE Summer Fellow
Chat with Presenter
Available April 11, 1:30-3 pm EST
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The Spread of Wildfires by Firebrands
Catherine Potts
Abstract
Wildfires generate heat and high winds that can carry flying embers, or firebrands, great distances, creating the possibility of igniting more fires. To better understand the behaviors of small particles in this turbulent air, I completed two experiments using a flume water channel, which allowed water to act in place of the air. One experiment used a laser and PIVLab analysis to reveal the velocities and turbulence of the background flow. The other deployed small particles of two different masses into the water, then used MATLAB to track their colors and positions. I conducted each experiment at flow speeds of 0.1, 0.2, and 0.3 m/s. Once the data is analyzed, future researchers may use it to corroborate numerical analysis and provide a more accurate simulation of wildfire spread
Presented by
Catherine Potts
Institution
FAMU-FSU College of Engineering
Other Affiliations
GFDI
Keywords
NASA BP-AE Summer Fellow
Chat with Presenter
Available August 11, 1:00PM - 4:00 PM EST
Watch Presentation
▼ 5. UCF Projects Back to top
Shock-Induced Breakup of Water Droplets
Anthony Aguilera, Sydney Briggs, Nicolas Berube, and Subith Vasu
Abstract
In our research we are trying to find whether water droplets cavitate when impacted by a shock wave. In our experiments we use our detonation tube to create a deflagration which then creates a shockwave. We then impact a water droplet with said shockwave with the goal of observing cavitation. Using a visible light detector and the high-speed camera we can determine if the impact caused cavitation. We are trying to collect the data necessary to better model impact in water droplets using simulation software. The main challenge is being able to hit the droplet with different shockwaves and being able to record the data with consistency.
Presented by
Anthony Aguilera
Institution
University of Central Florida
Keywords