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Affordable Practical High-Efficiency Photovoltaic Concentrator Blanket Assembly for Ultra-Lightweight Solar Arrays Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:13:36.000ZDeployable Space Systems, Inc. (DSS) will focus the proposed NASA Phase 1 effort on the development of our innovative Functional Advanced Concentrator Technology (FACT). FACT is an affordable practical high-efficiency concentrator blanket assembly for ultra-lightweight solar arrays. FACT coupled to an ultra-lightweight solar array structural platform (such as DSS's ROSA) will provide game-changing performance metrics and unparalleled affordability for the end-user. FACT will enable emerging Solar Electric Propulsion (SEP) Space Science missions, and other NASA missions, through its ultra-affordability, high voltage operation capability, high/low temperature operation capability, high/low illumination operation capability, high radiation tolerance, ultra-lightweight, and ultra-compact stowage volume. Once completely optimized through the proposed Phase 1 and Phase 2 programs the FACT technology promises to provide NASA/industry a near-term and low-risk flexible blanket technology for advanced solar array systems that provides revolutionary performance in terms of high specific power / ultra-lightweight (>400-500 W/kg BOL at the array level & >1000 W/kg BOL at the blanket level, PV dependent), affordability (>50% cost savings at the array level), compact stowage volume (>80 kW/m3 BOL, 10X times better than current rigid panel arrays), high operation reliability, high radiation tolerance, high voltage operation capability (>150 VDC), scalability, and LILT & HIHT operation capability.
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Increasing NASA SSC Range Safety by Developing the Framework to Monitor Airspace and Enforce Restrictions Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:39:58.000Z<p>Engine testing at NASA SSC poses a significant risk to general aviation due to potential smoke and excessive turbulence. The airspace over Stennis has been designated as restricted from 0600 - 2300 at altitudes below 5000 feet. SSC has limited ability to detect aircraft that have breeched the restricted airspace. In order to protect lives and property, a systematic evaluation of the potential technologies was requested to identify and define options to monitor the airspace, warn aircraft of impending danger, warn NASA test operations, and if necessary provide NASA test operations data so that an informed, timely decision could be made on whether or not to interrupt engine tests. This project systematically evaluated potential technologies that could address the problem of unauthorized aircraft entering Restricted Airspace/R-4403; a primary focus of this activity was on protecting the SSC Fee and Buffer Zone during an engine test or other sensitive operation. The research began with the findings and technology identified in the SSC Facility Safety Assessment Report. In 2010, a Facility Safety Assessment was performed for SMA to identify hazards associated with the SSC multiuser test range. During this assessment, a top system level safety hazard concerning unauthorized aircraft entering the SSC Restricted Airspace during test range operations, as well as twelve other hazards that directly or indirectly relate to the top hazard, were identified. SSC has limited ability to detect aircraft that may have intentionally or unintentionally breached R-4403. Because the restricted airspace is controlled by Houston ARTCC, controllers at Gulfport-Biloxi International Airport (GPT) and Louis Armstrong New Orleans International Airport (MSY) are not required to monitor or alert aircraft to avoid R-4403.</p><p>The purpose of the project was to evaluate monitoring techniques to address the problem of aircraft entering R-4403, primarily focusing on access to the SSC Buffer Zone during an engine test or other sensitive operation. The objective was to provide a small set of cost effective solutions that enable appropriate personnel to make informed safety decisions in near-real time. A number of different existing and prototype technologies were considered against the monitoring requirements defined by NASA.</p><p>During this project, several different types of aircraft monitoring technologies were investigated. The project intended to prototype these potential technology solutions based on information and assessments performed. Potential software approaches to be prototyped included: phone apps, e-mail alerts, and desk top displays. Each was assessed against NASA&rsquo;s airspace monitoring requirements, which included the ability to monitor the entire buffer zone plus an additional 5 mile radius for both transponder and non-transponder equipped aircraft and, if possible, low-altitude UASs. Some technologies were eliminated because they are unable to track non-transponder equipped aircraft, while others are not capable of operating in all weather and illumination conditions. The remaining technologies represent potential solutions to monitoring the restricted airspace at SSC.&nbsp;Ultimately, the technologies investigated were not required and a refined notification procedure to follow in advance of test operations was implemented to insure NASA SSC Range Safety.</p><p>&nbsp;</p>
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Designer's Situation Awareness Toolbox (DeSAT) Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:22:49.000ZThis SBIR will develop a design decision support tool that will assist designers in providing a powerful, supportive work environment for aviation crews that support the maintenance of a high level of situation awareness in the flight environment. DeSAT will be developed as a design decision support system providing the capability to (1) analyze the situation awareness requirements associated with operational requirements (which could include ground based or flight based crew members), (2) compare situation awareness information requirements to system design features to identify potential situation awareness problems and deficiencies early in the design process, and (3) evaluate the degree to which design concepts support SA via the Situation Awareness Global Assessment Technique (SAGAT). DeSAT will be developed for analysis of SA for both individual crew stations and for distributed teams operating across flight and time. DeSAT will allow designers to modify design concepts early in the design process to ensure that they provide the needed situation awareness to system users.
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Predictive Situational Awareness Tool Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:09:28.000ZSituational Awareness is the key element of performing safe and effective operations, and the space vehicle operations carried out by NASA is by no means an exception to the rule. Astronauts and flight controllers need to maintain awareness of the situation in the space vehicles, robots, habitats, Mission Control Center, and other systems. NASA has devoted and continues to devote a significant amount of resources to software for displaying the current situation in order to maintain this awareness. However, astronauts and flight controllers need to predict the future state of the systems for themselves. What will happen next? Resources have now advanced to the point where it is possible to inform the astronauts and flight controllers of the expected situation in the near future, and also to warn them if the current situation does not match the expectations of the recent past?this will indicate a developing issue that requires attention. All of this will aid in reducing the cognitive load on the astronauts and flight controllers, and help them perform their work safely and effectively. S&K Aerospace, LLC (SKA) proposes to research and develop a system that will provide predictive situational awareness to flight controllers and astronauts, by bringing together information about the current state of the vehicles and other systems, the activities planned in the near future, and the expected state of the system in the future, as well as an indication if the current state of the system matches planned state. This system will be called the Predictive System Awareness Tool, or PSAT.
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Development of X-ray Computed Tomography (CT) Imaging Method for the Measurement of Complex 3D Ice Shapes Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:33:58.000ZWhen ice accretes on a wing or other aerodynamic surface, it can produce extremely complex shapes. These are comprised of well-known shapes such as horns and feathers but also include other shapes such as the scallops that are associated with swept wing icing. The development of the larger ice shapes is generally believed to be influenced or built up from smaller scale surface structures such as roughness elements which can grow into the precursors of feathers or scallops seen on larger swept wing ice accretions. Feathers and scallops are often comprised of complex interlocking geometries that can contain a large number of voids. Hence it is important to characterize the geometries of these ice shapes, not only to ensure an adequate representation of the geometry for subsequent aerodynamic effects studies but also to provide data to validate icing codes, understand the basic physics involved with the ice accretion, and provide a basis for modeling the ice accretion. To address the above issue, we propose to use an X-ray computed tomography (CT) imaging method to demonstrate that X-ray CT scanning can be used to measure 3D ice features of the form seen in aircraft ice accretions. We also propose to conduct a preliminary trade/design analysis to establish directions for a more detailed Phase II study that would address specific recommendations to integrate X-ray CT imaging with icing wind tunnels which can be used at NASA Glenn and commercial aerospace companies. It is anticipated that the proposed imaging method could provide a radically new way to visualize and characterize extremely complex 3D ice shapes.
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Flight Crew State Monitoring Metrics Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:15:06.000ZeSky will develop specific crew state metrics based on the timeliness, tempo and accuracy of pilot inputs required by the H-mode Flight Control System (HFCS). Specific scenarios will be developed which define required inputs by the pilot and metrics of timeliness, tempo and accuracy will be developed for each required input. An existing HFCS simulator will be enhanced to support the full scenarios and crew state metric capture. Human subject testing will validate the stability of the metrics in normal situations and the responsiveness of the metrics to crew state degradation due to high workload. Strategies for continuous real-time function allocation to crew and automation will be developed. At the end of phase 1 crew state monitoring metrics will be at TRL 4/5. In phase 2 we will incorporate these metrics and strategies into the HFCS simulator and evaluate the usability and validity of these metrics and strategies using both workload and hypoxia as means of controlled crew state degradation. At the end of phase 2 metric-based function reallocation will be implemented in a collaborative flight control system ready for incorporation into a full motion simulator at TRL 5.
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Ground Processing Optimization Using Artificial Intelligence Techniques Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:35:32.000ZThe ultimate goal is the automation of a large amount of KSC's planning, scheduling, and execution decision making. Phase II will result in a complete full-scale implementation of a general framework and its application to several problems at KSC to create several operational systems (e.g., for Ground Processing (GP) and the Cryogenic Test Bed (CTB)) and other systems targeting future, advanced applications (e.g., autonomous cryogenic operations). During Phase II, delivered applications will improve scheduling of SLS Processing and V&V activity, including reduced scheduler manpower, reduced turnaround time in response to changes and what-ifs, and more optimal schedules; improve CTB Planning and Scheduling; and complete the diagnosis, planning, scheduling, and execution closed loop system for more-automatic ground and autonomous space-based cryogenic operations. The KSC Engineering Development Lab has substantial development and testing efforts ongoing for automatically diagnosing faults in cryogenic operations. By interfacing our system to these applications, it effectively completes the closed loop system required for completely autonomous operations. Our Phase II system will participate in a number of demonstrations during Phase II to prove the capabilities for future advanced more-automatic ground and space-based operations. Letters of support are included in this proposal from the managers of the groups that would use the operational systems in Phase II and the manager of the project demonstrating future, advanced applications. This Phase II effort will also improve the ability of SMEs to customize intelligent scheduling systems, capture corporate knowledge, and implement the required interfaces to allow operational use and participation in cryogenic operations demonstrations.
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Advanced Manufacturing Technologies (AMT): Additive Manufactured Hot Fire Planning and Testing in GRC Cell 32 Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:37:51.000Z<p>GRC and AR have identified the following roles and responsibilities necessary to accomplish the hot fire objective of this task.&nbsp; AR will be responsible for delivering to GRC the additively manufactured thrust chamber components and injector, give input required for test plan documentation, participate in the test readiness review and give engineering support for hot fire testing.&nbsp; GRC will be responsible for preparing Cell 32 for testing, manufacturing all test support hardware, generating test plan documentation, conducting a test readiness review, conducting all hot fire operations and generating the final report.&nbsp;</p><p>&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; AR will use SLM to manufacture all of the thrust chamber components necessary to perform this task.&nbsp; The two water cooled thrust chamber barrels and one water cooled nozzle will be constructed from Cu-Cr which is an alloy of interest for several engines in the AR product line.&nbsp; Following fabrication and post processing AR will conduct pretest inspections on the thrust chamber components to verify the builds.&nbsp; The Inconel 625 injector that will be used in this investigation is the same injector that was used in the MIP.&nbsp; AR has already conducted post-test inspections on this component to verify that it can be used in this work.&nbsp;</p><p>&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; During the course of the MIP test campaign, AR working with GRC, identified several propellant feed system modifications necessary to be made to Cell 32.&nbsp; The modifications entail altering the feed system and main valve placement to facilitate easier engine operation.&nbsp; GRC facilities personnel have already coordinated with AR personnel to select components that can easily be integrated into the current test set-up in order to streamline the modification process.</p><p>&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; To support hot fire testing GRC will fabricate several igniters and one heat sink copper thrust chamber.&nbsp; The design work for these components was completed under the MIP and drawings are already available.&nbsp; The heat sink thrust chamber will be used in early hot fire tests to verify that Cell 32 feed system modifications had the desired effect on engine operation.&nbsp; This will minimize risk to the AR Cu-Cr thrust chamber components and also allows additional instrumentation to be integrated into the test set- up.&nbsp; Data from this additional instrumentation will also be used to better understand the performance of the thrust chamber assembly after the heat sink hardware has been replaced by the water cooled SLM components.</p><p>&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp;&nbsp; To prepare for hot fire testing GRC, with AR input, will generate a test requirements document (TRD) to capture all of facility and test requirements necessary to ensure successful completion of the hot fire objective of this task.&nbsp; This document will contain a preliminary test matrix that outlines plans and the number of tests required to increase hot fire test duration from short ignition tests (~ 0.5 seconds) to longer duration (~30) second tests with minimal hardware risk.&nbsp; The longer duration tests should allow the TCA to achieve thermal equilibrium and allow preliminary insight into the effect, if any, that longer duration testing has on SLM fabricated TCA components.&nbsp; AR will be a signatory on the document to capture concurrence with the GRC test approach.&nbsp; The information in the TRD will be used as a basis for a test readiness review t
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ATC Operations Analysis via Automatic Recognition of Clearances Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:08:05.000ZRecent advances in airport surface surveillance have motivated the creation of new tools for analysis of Air Traffic Control (ATC) operations, such as the Surface Operations Data Analysis and Adaptation (SODAA) tool, which is being used by NASA to conduct airport ATC operations analysis. What is missing from ATC operations analysis, however, is accessible and reliable data regarding the clearances issued by the controller and other communication conducted with the pilot that influences the behavior seen in the surveillance data. The reliance on voice communication in ATC operations presents challenges to the researcher who is trying to obtain data and conduct detailed analyses of ATC operations. During the Phase I effort, we designed and developed a prototype system to perform automatic speech recognition (ASR) of ATC clearances. We demonstrated the feasibility of recognizing ATC clearances from speech audio data and associating the clearance data with the flight that is the subject of the clearance. In the Phase II effort, we will create a complete prototype of the ATC speech recognition, processing and analysis capability in SODAA. In addition, we will integrate ATC speech recognition capabilities into a real-time application in the Surface Management System (SMS).
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Materials and Structures Optimization / Process Development for the Mega-ROSA / ROSA Solar Array Project
nasa-test-0.demo.socrata.com | Last Updated 2015-07-20T05:41:17.000ZDeployable Space Systems, Inc. (DSS), in collaboration with the University of California, Santa Barbara (UCSB), Department of Mechanical Engineering, will focus the proposed NASA STTR Phase 1 program on the materials optimization, structures optimization, and manufacturing process optimization/development for the Mega-ROSA/ROSA solar array. The ROSA technology (termed for: Roll-Out Solar Array) is a new/innovative mission-enabling solar array system that offers maximum performance in all key metrics and unparalleled affordability for NASA's Space Science & Exploration missions. ROSA will enable NASA's emerging Solar Electric Propulsion (SEP) Space Science & Exploration missions through its ultra-affordability, ultra-lightweight, ultra-compact stowage volume, high strength/stiffness, and its high voltage and high/low temperature operation capability within many environments. The ROSA technology will provide NASA/industry a near-term and low-risk solar array system that provides revolutionary performance in terms of high specific power (>200-500 W/kg BOL at the wing level, PV-blanket dependent), affordability (>25-50% projected cost savings at the array level, PV-blanket dependent), ultra-lightweight, high deployed stiffness (10X better than current rigid panel arrays), high deployed strength (10X better than current rigid panel arrays), compact stowage volume (>60-80 kW/m3 BOL, 10X times better than current rigid panel arrays), high deployment reliability and operation reliability, high radiation tolerance, high voltage operation capability (>200 VDC), scalability (500W to 100's of kW), and LILT & HIHT operation capability (LILT &#150; Low Intensity Low Temperature, HIHT &#150; High Intensity High Temperature).