Bigelow Expandable Activity Module (BEAM) ISS Year - One
Document ID: 20170006506NTRS Full-Text: Click to View [PDF Size: 1.10 MB]Author: Valle, Gerard; Wells, Nathan
Abstract: No abstract available
Publication Year: 2017Document Type: Oral/Visual PresentationReport/Patent Number: JSC-CN-39950Date Acquired: Jul 21, 2017
Impact of Coupled Radiation and Ablation on the Aerothermodynamics of Meteor Entries
Document ID: 20170006495NTRS Full-Text: Click to View [PDF Size: 1.4 MB]Author: Johnston, Christopher O.; Stern, Eric C.
Abstract: A high-fidelity approach for simulating the aerothermodynamic environments of meteor entries is
developed. Two primary components of this model are coupled radiation and coupled ablation. Coupled radiation accounts for the impact of radiation on the flow field energy equations, while coupled ablation explicitly models the injection of ablation products within the flow field and radiation simulations. For a meteoroid with a velocity of 20 km/s, coupled radiation reduces the stagnation point radiative heating by over 60%. For altitudes below 40 km, the impact of coupled radiation on the flow field structure is shown to be fundamentally different, as a result of the large optical thicknesses, than that seen for reentry vehicles, which do not reach such altitudes at velocities greater than 10 km/s. The impact of coupled ablation (with coupled radiation) is shown to provide at least a 70% reduction in the radiative heating relative to the coupled-radiation-only cases. This large reduction is partially the result of the low ionization energies, relative to air species, of ablation products. The low ionization energies of ablation products, such as Mg and Ca, provide strong photoionization and atomic line absorption in regions of the spectrum that air species do not. MgO and CaO are also shown to provide significant absorption. Turbulence is shown to impact the distribution of ablation products through the shock- layer, which results in up to a 100% increase in the radiative heating downstream of the stagnation point. To create a database of heat transfer coefficients the developed model was applied to a range of cases. This database considered velocities ranging from 14 to 20 km/s, altitudes ranging from 20 to 50 km, and nose radii ranging from 1 to 100 m. The heat transfer coefficients from these simulations are below 0.045 for the range of cases (with turbulence), which is significantly lower than the canonical value of 0.1.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: NF1676L-27230Date Acquired: Jul 21, 2017
Safety Critical Flight Software: Code Coverage Utilization
Document ID: 20170006507NTRS Full-Text: Click to View [PDF Size: 1.3 MB]Author: Uitenbroek, Nate
Abstract: No abstract available
Publication Year: 2017Document Type: Oral/Visual PresentationReport/Patent Number: JSC-CN-39933Date Acquired: Jul 21, 2017
Uncertainty Aware Structural Topology Optimization Via a Stochastic Reduced Order Model Approach
Document ID: 20170006496NTRS Full-Text: Click to View [PDF Size: 2.9 MB]Author: Aguilo, Miguel A.; Warner, James E.
Abstract: This work presents a stochastic reduced order modeling strategy for the quantification and
propagation of uncertainties in topology optimization. Uncertainty aware optimization problems can be computationally complex due to the substantial number of model evaluations that are necessary to accurately quantify and propagate uncertainties. This computational complexity is greatly magnified if a high-fidelity, physics-based numerical model is used for the topology optimization calculations. Stochastic reduced order model (SROM) methods are applied here to effectively 1) alleviate the prohibitive computational cost associated with an uncertainty aware topology optimization problem; and 2) quantify and propagate the inherent uncertainties due to design imperfections. A generic SROM framework that transforms the uncertainty aware, stochastic topology optimization problem into a deterministic optimization problem that relies only on independent calls to a deterministic numerical model is presented. This approach facilitates the use of existing optimization and modeling tools to accurately solve the uncertainty aware topology optimization problems in a fraction of the computational demand required by Monte Carlo methods. Finally, an example in structural topology optimization is presented to demonstrate the effectiveness of the proposed uncertainty aware structural topology optimization approach.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: NF1676L-27189Date Acquired: Jul 21, 2017
Expansion of Microbial Monitoring Capabilities on the International Space Station (ISS)
Document ID: 20170006508NTRS Full-Text: Click to View [PDF Size: 10 KB]Author: Khodadad, Christina L.; Castro, Victoria; Melendez, Orlando; Ott, C. Mark; Oubre, Cherie; Flint, Stephanie; Roman, Monsi
Abstract: Microbial monitoring is one of the tools that the National Aeronautics and Space Administration
(NASA) uses on the International Space Station (ISS) to help maintain crew health and safety. In combination with regular housekeeping and disinfection when needed, microbial monitoring provides important information to the crew about the quality of the environment. Rotation of astronauts, equipment, and cargo on the ISS can affect the microbial load in the air, surfaces, and water. The current ISS microbial monitoring methods are focused on culture-based enumeration during flight and require a significant amount of crew time as well as long incubation periods of up to 5 days there by proliferating potential pathogens. In addition, the samples require return to Earth for complete identification of the microorganisms cultivated. Although the current approach assess the quality of the ISS environment, molecular technology offers faster turn-around of information particularly beneficial in an off-nominal situation. In 2011, subject matter experts from industry and academia recommended implementation of molecular-based technologies such as quantitative real-time polymerase chain reaction (qPCR) for evaluation to replace current, culture-based technologies. The RAZOR EX (BioFire Defense, Inc, Salt Lake City, UT) a ruggedized, compact, COTS (commercial off the shelf) qPCR instrument was tested, evaluated and selected in the 2 X 2015 JSC rapid flight hardware demonstration initiative as part of the Water Monitoring Suite. RAZOR EX was launched to ISS on SpaceX-9 in July 2016 to evaluate the precision and accuracy of the hardware by testing various concentrations of DNA in microgravity compared to ground controls. Flight testing was completed between September 2016 and March 2017. Data presented will detail the hardware performance of flight testing results compared to ground controls. Future goals include additional operational ground-based testing and assay development to determine if this technology can meet spaceflight microbial monitoring requirements.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: JSC-CN-39930Date Acquired: Jul 21, 2017
Autonomous System Technologies for Resilient Airspace Operations
Document ID: 20170006497NTRS Full-Text: Click to View [PDF Size: 679 KB]Author: Le Vie, Lisa R.; Houston, Vincent E.
Abstract: Increasing autonomous systems within the aircraft cockpit begins with an effort to understand what
autonomy is and developing the technology that encompasses it. Autonomy allows an agent, human or machine, to act independently within a circumscribed set of goals; delegating responsibility to the agent(s) to achieve overall system objective(s). Increasingly Autonomous Systems (IAS) are the highly sophisticated progression of current automated systems toward full autonomy. Working in concert with humans, these types of technologies are expected to improve the safety, reliability, costs, and operational efficiency of aviation. IAS implementation is imminent, which makes the development and the proper performance of such technologies, with respect to cockpit operation efficiency, the management of air traffic and data communication information, vital. A prototype IAS agent that attempts to optimize the identification and distribution of "relevant" air traffic data to be utilized by human crews during complex airspace operations has been developed.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: NF1676L-27173Date Acquired: Jul 21, 2017
NASA ERA Integrated CFD for Wind Tunnel Testing of Hybrid Wing-Body Configuration
Document ID: 20170006533NTRS Full-Text: Click to View [PDF Size: 4.6 MB]Author: Schuh, Michael; Garcia, Joseph A.; Melton, John E.; James, Kevin D.; Vicroy, Dan D.; Deere, Karen A.; Luckring, James M.; Nikaido, Ben E.; Childs, Robert E.; Long, Kurt R.; Carter, Melissa B.; Flamm, Jeffrey D.; Stremel, Paul M.
Abstract: NASAs Environmentally Responsible Aviation (ERA) Project explores enabling technologies to reduce
aviations impact on the environment. One research challenge area for the project has been to study advanced airframe and engine integration concepts to reduce community noise and fuel burn. In order to achieve this, complex wind tunnel experiments at both the NASA Langley Research Centers (LaRC) 14x22 and the Ames Research Centers 40x80 low-speed wind tunnel facilities were conducted on a Boeing Hybrid Wing Body (HWB) configuration. These wind tunnel tests entailed various entries to evaluate the propulsion airframe interference effects including aerodynamic performance and aeroacoustics. In order to assist these tests in producing high quality data with minimal hardware interference, extensive Computational Fluid Dynamic (CFD) simulations were performed for everything from sting design and placement for both the wing body and powered ejector nacelle systems to the placement of aeroacoustic arrays to minimize its impact on the vehicles aerodynamics. This paper will provide a high level summary of the CFD simulations that NASA performed in support of the model integration hardware design as well as some simulation guideline development based on post-test aerodynamic data. In addition, the paper includes details on how multiple CFD codes (OVERFLOW, STAR-CCM+, USM3D, and FUN3D) were efficiently used to provide timely insight into the wind tunnel experimental setup and execution.
Publication Year: 2016Document Type: Oral/Visual PresentationReport/Patent Number: ARC-E-DAA-TN28678Date Acquired: Jul 21, 2017
Understanding the International Space Station Crew Perspective Following Long Duration Missions Through Data Analytics & Visualization of Crew Feedback
Document ID: 20170006509NTRS Full-Text: Click to View [PDF Size: 1.6 MB]Author: Bryant, Cody; Schuh, Susan; Schoenstein, Nicole
Abstract: No abstract available
Publication Year: 2017Document Type: Oral/Visual PresentationReport/Patent Number: JSC-CN-39921Date Acquired: Jul 21, 2017
Link!: Potential Field Guidance Algorithm for In-Flight Linking of Multi-Rotor Aircraft
Document ID: 20170006500NTRS Full-Text: Click to View [PDF Size: 722 KB]Author: Cooper, John R.; Rothhaar, Paul M.
Abstract: Link! is a multi-center NASA e ort to study the feasibility of multi-aircraft aerial docking
systems. In these systems, a group of vehicles physically link to each other during flight to form a larger ensemble vehicle with increased aerodynamic performance and mission utility. This paper presents a potential field guidance algorithm for a group of multi-rotor vehicles to link to each other during flight. The linking is done in pairs. Each vehicle first selects a mate. Then the potential field is constructed with three rules: move towards the mate, avoid collisions with non-mates, and stay close to the rest of the group. Once a pair links, they are then considered to be a single vehicle. After each pair is linked, the process repeats until there is only one vehicle left. The paper contains simulation results for a system of 16 vehicles.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: NF1676L-27073Date Acquired: Jul 21, 2017
A Method for Designing Conforming Folding Propellers
Document ID: 20170006489NTRS Full-Text: Click to View [PDF Size: 6.5 MB]Author: Patterson, Michael D.; Litherland, Brandon L.; Derlaga, Joseph M.; Borer, Nicholas K.
Abstract: As the aviation vehicle design environment expands due to the in flux of new technologies, new
methods of conceptual design and modeling are required in order to meet the customer's needs. In the case of distributed electric propulsion (DEP), the use of high-lift propellers upstream of the wing leading edge augments lift at low speeds enabling smaller wings with sufficient takeoff and landing performance. During cruise, however, these devices would normally contribute significant drag if left in a fixed or windmilling arrangement. Therefore, a design that stows the propeller blades is desirable. In this paper, we present a method for designing folding-blade configurations that conform to the nacelle surface when stowed. These folded designs maintain performance nearly identical to their straight, non-folding blade counterparts.
Publication Year: 2017Document Type: Conference PaperReport/Patent Number: NF1676L-27022Date Acquired: Jul 21, 2017
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