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Systems Engineering and Multidisciplinary Design Optimization Commons

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Cubesat Astronomy Mission Modeling Using The Horizon Simulation Framework, Alexander W. Johnson 2019 California Polytechnic State University, San Luis Obispo

Cubesat Astronomy Mission Modeling Using The Horizon Simulation Framework, Alexander W. Johnson

Master's Theses and Project Reports

The CubeSat Astronomy Network is a proposed system of multiple CubeSat spacecraft capable of performing follow-up observations of astronomical targets of interest. The system is intended to serve as a space-borne platform that can complement existing systems utilized for astronomical research by undergraduate and high school students. Much research and development work has been performed to develop model-based system engineering methodologies and products for CubeSat missions, including the Horizon Simulation Framework. The Horizon Simulation Framework enables the development of system models using the Extended Markup Language (XML), and its simulation program can generate system simulations over model-specified timespans. System requirements ...


Satisfiability Checking For Mission-Time Ltl, Jianwen Li, Moshe Y. Vardi, Kristin Y. Rozier 2019 Iowa State University

Satisfiability Checking For Mission-Time Ltl, Jianwen Li, Moshe Y. Vardi, Kristin Y. Rozier

Kristin Yvonne Rozier

Mission-time LTL (MLTL) is a bounded variant of MTL over naturals designed to generically specify requirements for mission-based system operation common to aircraft, spacecraft, vehicles, and robots. Despite the utility of MLTL as a specification logic, major gaps remain in analyzing MLTL, e.g., for specification debugging or model checking, centering on the absence of any complete MLTL satisfiability checker. We prove that the MLTL satisfiability checking problem is NEXPTIME-complete and that satisfiability checking MLTL0 , the variant of MLTL where all intervals start at 0, is PSPACE-complete. We introduce translations for MLTL-to-LTL, MLTL-to-LTLf , MLTL-to-SMV, and MLTL-to-SMT, creating four ...


Satisfiability Checking For Mission-Time Ltl, Jianwen Li, Moshe Y. Vardi, Kristin Y. Rozier 2019 Iowa State University

Satisfiability Checking For Mission-Time Ltl, Jianwen Li, Moshe Y. Vardi, Kristin Y. Rozier

Aerospace Engineering Publications

Mission-time LTL (MLTL) is a bounded variant of MTL over naturals designed to generically specify requirements for mission-based system operation common to aircraft, spacecraft, vehicles, and robots. Despite the utility of MLTL as a specification logic, major gaps remain in analyzing MLTL, e.g., for specification debugging or model checking, centering on the absence of any complete MLTL satisfiability checker. We prove that the MLTL satisfiability checking problem is NEXPTIME-complete and that satisfiability checking MLTL0 , the variant of MLTL where all intervals start at 0, is PSPACE-complete. We introduce translations for MLTL-to-LTL, MLTL-to-LTLf , MLTL-to-SMV, and MLTL-to-SMT, creating four ...


R2u2: Monitoring And Diagnosis Of Security Threats For Unmanned Aerial Systems, Patrick Moosbrugger, Kristin Y. Rozier, Johann Schumann 2019 Vienna University of Technology

R2u2: Monitoring And Diagnosis Of Security Threats For Unmanned Aerial Systems, Patrick Moosbrugger, Kristin Y. Rozier, Johann Schumann

Kristin Yvonne Rozier

We present R2U2, a novel framework for runtime monitoring of security properties and diagnosing of security threats on-board Unmanned Aerial Systems (UAS). R2U2, implemented in FPGA hardware, is a real-time, Realizable, Responsive, Unobtrusive Unit for runtime system analysis, now including security threat detection. R2U2 is designed to continuously monitor inputs from on-board components such as the GPS, the ground control station, other sensor readings, actuator outputs, and flight software status. By simultaneously monitoring and performing statistical reasoning, attack patterns and post-attack discrepancies in the UAS behavior can be detected. R2U2 uses runtime observer pairs for Linear and Metric Temporal Logics ...


A Homegrown Dsmc-Pic Model For Electric Propulsion, Dominic Charles Lunde 2019 California Polytechnic State University, San Luis Obispo

A Homegrown Dsmc-Pic Model For Electric Propulsion, Dominic Charles Lunde

Master's Theses and Project Reports

Powering spacecraft with electric propulsion is becoming more common, especially in CubeSat-class satellites. On account of the risk of spacecraft interactions, it is important to have robust analysis and modeling tools of electric propulsion engines, particularly of the plasma plume. The Navier-Stokes equations used in classic continuum computational fluid dynamics do not apply to the rarefied plasma, and therefore another method must be used to model the flow. A good solution is to use the DSMC method, which uses a combination of particle modeling and statistical methods for modeling the simulated molecules. A DSMC simulation known as SINATRA has been ...


Innovative Schematic Concept Analysis For A Space Suit Portable Life Support Subsystem, M. Schuller, R. Kobrick, T. Lalk, L. Wiseman, F. Little, et al. 2019 Texas Engineering Experiment Station

Innovative Schematic Concept Analysis For A Space Suit Portable Life Support Subsystem, M. Schuller, R. Kobrick, T. Lalk, L. Wiseman, F. Little, Et Al.

Ryan L. Kobrick

Conceptual designs for a space suit Personal Life Support Subsystem (PLSS) were developed and assessed to determine if upgrading the system using new, emerging, or projected technologies to fulfill basic functions would result in mass, volume, or performance improvements. Technologies were identified to satisfy each of the functions of the PLSS in three environments (zero-g, Lunar, and Martian) and in three time frames (2006, 2010, and 2020). The viability of candidate technologies was evaluated using evaluation criteria such as safety, technology readiness, and reliability. System concepts (schematics) were developed for combinations of time frame and environment by assigning specific technologies ...


Defining An Abrasion Index For Lunar Surface Systems As A Function Of Dust Interaction Modes And Variable Concentration Zones, Ryan L. Kobrick, David M. Klaus, Kenneth W. Street Jr. 2019 University of Colorado Boulder

Defining An Abrasion Index For Lunar Surface Systems As A Function Of Dust Interaction Modes And Variable Concentration Zones, Ryan L. Kobrick, David M. Klaus, Kenneth W. Street Jr.

Ryan L. Kobrick

Unexpected issues were encountered during the Apollo era of lunar exploration due to detrimental abrasion of materials upon exposure to the fine-grained, irregular shaped dust on the surface of the Moon. For critical design features involving contact with the lunar surface and for astronaut safety concerns, operational concepts and dust tolerance must be considered in the early phases of mission planning. To systematically define material selection criteria, dust interaction can be characterized by two-body or three-body abrasion testing, and sub-categorically by physical interactions of compression, rolling, sliding and bending representing specific applications within the system. Two-body abrasion occurs when a ...


A Technology Survey Of Emergency Recovery And Flight Termination Systems For Uas, Richard Stansbury, Wesley Tanis, Timothy Wilson 2019 Embry-Riddle Aeronautical University

A Technology Survey Of Emergency Recovery And Flight Termination Systems For Uas, Richard Stansbury, Wesley Tanis, Timothy Wilson

Richard Stansbury

For safe flight in the National Airspace System (NAS), either under the current interim rules or under anticipated longer-term regulatory guidelines facilitating unmanned aircraft system (UAS) access to the NAS, the UAS must incorporate technologies and flight procedures to ensure that neither people nor property in the air, on the ground, or on or in the water are endangered by the failure of an onboard component, by inappropriate unmanned aircraft (UA) response to pilot commands, or by inadvertent entry by the UA into prohibited airspace. The aircraft must be equipped with emergency recovery (ER) procedures and technologies that ensure that ...


Comparison Of Induced And Parasitic Drag On Wings With Minimum Induced Drag, Sarah A. Abdel-Motaleb 2019 Utah State University

Comparison Of Induced And Parasitic Drag On Wings With Minimum Induced Drag, Sarah A. Abdel-Motaleb

All Graduate Plan B and other Reports

Minimizing the induced drag for steady level flight is a variational problem that requires solving for the optimum lift distribution given a set of design constraints. From lifting-line theory, minimizing the induced drag is, in part, achieved by varying the Fourier coefficients used to describe the section lift. The elliptic lift distribution minimizes the induced drag for a wing with fixed weight and wingspan by setting all but the first coefficient to zero. If wingspan is allowed to vary, a negative third Fourier coefficient is utilized to reach an optimum lift distribution that further reduces the induced drag for stress-limited ...


System Architecture Design And Development For A Reusable Lunar Lander, Chad Batten, Camille E. Bergin, Aaron Crigger, Darryl Harris, Gillian Suzanne McGlothin 2019 University of Tennessee, Knoxville

System Architecture Design And Development For A Reusable Lunar Lander, Chad Batten, Camille E. Bergin, Aaron Crigger, Darryl Harris, Gillian Suzanne Mcglothin

Chancellor’s Honors Program Projects

No abstract provided.


Extreme Altitude Search And Rescue Helicopter, Matthew J. De Sieno, Anthony Chavarria, David Stuver, Zach Boss 2019 Kennesaw State University

Extreme Altitude Search And Rescue Helicopter, Matthew J. De Sieno, Anthony Chavarria, David Stuver, Zach Boss

Senior Design Project For Engineers

The goal of this design was to develop an extreme altitude rescue helicopter capable of retrieving hikers stranded on top of Mount Everest. Using the Eurocopter AS350 as a baseline, a conceptual model was produced that is fully capable of hovering and delivering forward flight at the desired altitude of 8,848 meters. Combined blade element momentum theory, proper airfoil selection, and forward flight calculations were utilized in order to optimize the rotor for the given flight conditions on top of Mount Everest. Conceptual fluid dynamics and CAD modeling aided in the process of visually designing the fuselage and rotor ...


Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch 2019 Portland State University

Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch

Cameron Smith

Audiovisual records of a Project Mercury pilot’s activities during an orbital flight indicate that his visor was left open during reentry and descent to the sea surface, phases of flight during which cabin pressure loss was to be mitigated by suit pressurization; however, the suit could not have been pressurized with the visor open. Thus, for a presently unknown reason, a critical safety step—sealing the visor and making a pressure suit integrity test before reentry—was overlooked in this flight. Later, Space Shuttle flights were carried out with visors unsealed for much of the launch and landing phases ...


Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch 2019 Portland State University

Incidence Of An Astronaut Not Sealing The Pressure Garment Visor On Reentry, Cameron M. Smith, Trent Tresch

Journal of Human Performance in Extreme Environments

Audiovisual records of a Project Mercury pilot’s activities during an orbital flight indicate that his visor was left open during reentry and descent to the sea surface, phases of flight during which cabin pressure loss was to be mitigated by suit pressurization; however, the suit could not have been pressurized with the visor open. Thus, for a presently unknown reason, a critical safety step—sealing the visor and making a pressure suit integrity test before reentry—was overlooked in this flight. Later, Space Shuttle flights were carried out with visors unsealed for much of the launch and landing phases ...


Lasers For Communication And Coordination Control Of Spacecraft Swarms, Himangshu Kalita, Leonard Dean Vance, Vishnu Reddy, Jekan Thanga 2019 University of Arizona

Lasers For Communication And Coordination Control Of Spacecraft Swarms, Himangshu Kalita, Leonard Dean Vance, Vishnu Reddy, Jekan Thanga

Space Traffic Management Conference

Swarms of small spacecraft offer whole new capabilities in Earth observation, global positioning and communications compared to a large monolithic spacecraft. These small spacecraft can provide bigger apertures that increase gain in communication antennas, increase area coverage or effective resolution of distributed cameras and enable persistent observation of ground or space targets. However, there remain important challenges in operating large number of spacecrafts at once. Current methods would require a large number of ground operators monitor and actively control these spacecraft which poses challenges in terms of coordination and control which prevents the technology from scaled up in cost-effective manner ...


Project Atlas: A Mobile Universal Rocket Engine Test Stand, Collin Mickels, Conrad H. Wright, Noah Soderquist, Alona Prokofieva, Sattar Panahandehgar, Naveen Sri Uddanti, Alcuin Rajan 2019 Embry-Riddle Aeronautical University

Project Atlas: A Mobile Universal Rocket Engine Test Stand, Collin Mickels, Conrad H. Wright, Noah Soderquist, Alona Prokofieva, Sattar Panahandehgar, Naveen Sri Uddanti, Alcuin Rajan

Student Works

Project Atlas is a mobile, trailer-mounted, rocket engine test stand developed by Experimental Rocket Propulsion Lab (ERPL) at Embry-Riddle Aeronautical University’s Daytona Beach, Florida campus. The integrated test stand and automated data-acquisition and control system supports ERPL’s multitude of engine research projects, including bipropellant liquid and hybrid rocket engines. The need for an integrated universal mobile test stand stems from the inability to conduct frequent test fires on campus due to Class-3 airspace and liability issues. The test stand is designed as a horizontal thrust structure utilizing a dual flame duct to redirect and cancel reaction forces acting ...


Swat Operations Unmanned Vehicle, John K. Zelina, Tyler Meadows, Ryan Cook, Mathew Fellows 2019 The University of Akron

Swat Operations Unmanned Vehicle, John K. Zelina, Tyler Meadows, Ryan Cook, Mathew Fellows

Williams Honors College, Honors Research Projects

During SWAT operations, it is common to have a barricaded suspect who may be armed and a serious threat to SWAT team personnel. In these cases, sending a robot into harm's way to assess the situation as opposed to an operator has become the standard. The purpose of this of this research was to design and develop an unmanned system for the City of Akron's SWAT Team that can be injected into these scenarios to improve outcomes and mitigate risk to SWAT operators.


Improving The Delivered Specific Impulse Of Composite Rocket Propellant Through Alteration Of Chemical Composition: Methodology And Parameters For Characterization Of Propellant And Validation Of Simulation Software Common To The Amateur Rocketry Community, Isaac O'Brien, Austin Ryan 2019 The University of Akron

Improving The Delivered Specific Impulse Of Composite Rocket Propellant Through Alteration Of Chemical Composition: Methodology And Parameters For Characterization Of Propellant And Validation Of Simulation Software Common To The Amateur Rocketry Community, Isaac O'Brien, Austin Ryan

Williams Honors College, Honors Research Projects

In this study, two solid composite rocket propellants were designed utilizing ProPEP, a rocket propellant formulation software common in the amateur and hobby rocketry communities. The two propellants were designed to optimize specific impulse relative to a literature propellant designed by 1020 Research Labs. The literature propellant was also tested in order to validate the design of experiment as well as the mixing and testing procedures. All three propellants, which includes the literature propellant RCS-P, and the two novel propellants AKR-P1 and AKR-P2 were characterized with static tests. The results of the static tests provide data on propellant performance and ...


Space Dynamics Laboratory Payload Challenge: Autonomous Water Sampling Uav, Thomas Wheeler, Zachary Williams, Joseph Stack 2019 The University of Akron

Space Dynamics Laboratory Payload Challenge: Autonomous Water Sampling Uav, Thomas Wheeler, Zachary Williams, Joseph Stack

Williams Honors College, Honors Research Projects

The following report has been completed over the course of the Fall 2018 and Spring 2019 semesters at The University of Akron by Joseph P. Stack (Aerospace Systems Engineering), Thomas J. Wheeler (Mechanical Engineering) and Zachary M. Williams (Mechanical Engineering). The purpose of this project was to create a payload system for the Akronauts Rocket Design Team to use at the Intercollegiate Rocket Engineering Competition (IREC) Spaceport America Cup. The Competition as a challenge that is sponsored by Space Dynamics Laboratory specifically regarding payload systems. The challenge in very open-ended and allows student to identify their own scientific experiment and ...


A Systems And Cost Analysis Of Human Rated Mars Entry, Descent, And Landing Vehicles, Paul Daniel Friz 2019 Missouri University of Science and Technology

A Systems And Cost Analysis Of Human Rated Mars Entry, Descent, And Landing Vehicles, Paul Daniel Friz

Doctoral Dissertations

"Cost is one of the biggest obstacles to sending humans to Mars. However, spacecraft costs are typically not taken into consideration until after the preliminary vehicle and mission concepts have been designed. Once costs have been estimated, managers and project teams often lack confidence that the final cost of the mission will match the preliminary estimates. The present work provides a robust methodology for using cost as a valid metric early in the design phase of future human Mars Entry, Descent, and Landing (EDL) vehicles. This is done in three parts. First, state of the art parametric costing methods are ...


Landing-Gear Impact Response: A Non-Linear Finite Element Approach, Tuan H. Tran 2019 University of North Florida

Landing-Gear Impact Response: A Non-Linear Finite Element Approach, Tuan H. Tran

UNF Graduate Theses and Dissertations

The primary objective of this research is to formulate a methodology of assessing the maximum impact loading condition that will incur onto an aircraft’s landing gear system via Finite Element Analysis (FEA) and appropriately determining its corresponding structural and impact responses to minimize potential design failures during hard landing (abnormal impact) and shock absorption testing. Both static and dynamic loading condition were closely analyzed, compared, and derived through the Federal Aviation Administration’s (FAA) airworthiness regulations and empirical testing data.

In this research, a nonlinear transient dynamic analysis is developed and established via NASTRAN advanced nonlinear finite element model ...


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