Summary

Description

<p>Phased array ultrasonic testing (PAUT) instruments and array eddy current testing instruments were tested on hypervelocity impact damaged aluminum plates simulating the ISS pressure wall. Ultrasonic techniques were most successful in assessing the back side damage when a repair seal plate covers the damage. The ultrasonic instrument would be selected for implementation on ISS.</p>

Summary

Description

<p>Thermal modeling and Test plan to be carried out and developed by Goddard Space Flight Center. This project will be done in collaboration with partners at MIT and Draper Laboratory Basic Thermal Model, Oct. 1, 2011; Final Thermal Model, Mar. 1, 2012; Draft Test Plan, Mar. 1, 2012; Final Test Plan, July 1, 2012.</p>

Summary

Description

<p>Atmospheric confetti. Inchworm crawlers. Blankets of ground penetrating radar. These are some of the unique mission concepts which are enabled by a printable spacecraft. Flexible printed electronics is a wide-ranging technology that can enhance or even enable many engineering applications. Our concept is to utilize the commercial technology of printed electronics to design and fabricate an entire end to end functional spacecraft. The novel advancement (and therefore the technical challenge) of the concept is to apply printed electronics in a multi-functional platform by implementing every subsystem that a spacecraft might need from the scientific sensor through the data downlink and have it survive and function in a space environment. These requirements push the current state of the art for functionality as well as introduce design and manufacturing compatibility challenges among the functional subsystems. Current industry growth and commercial investment is expected to advance the functionality of available basic building blocks and components synergistically with NASA’s needs.</p>

Summary

Description

<p>The storage of cryogenic propellants is challenging because heat leaks into the cryogenic storage tanks no matter how good the insulation, resulting in a necessity to vent and maintain the propellant at the appropriate thermodynamic condition for engine operation and tank safety.  Although it is challenging to store LO2, it is even more difficult to store LH2 because of its lower boiling point.  There is therefore an increased focus for demonstrating LH2 storage in vent-free conditions.</p>

Summary

Description

<p>Inflatable structures will require low permeable bladder to metallic seal interface.  Cold flow of bladder materials over time is not acceptable for long term missions where materials cannot be easily inspected or replaced.  Reliable seal interfaces are required.<br /> Inflatable habitats can provide the volume necessary for space colonization at a lower cost than traditional habitats. Sealing bladder materials capable of deploying at cold temperatures is essential for deep space missions and likely LOE missions due to operational constraints</p>

Summary

Description

<p>In spite of our best efforts to minimize the amount of disposable supplies (and the associated packaging) used during space missions, the accumulation of solid wastes is an inevitable consequence of mission activity. That waste will occupy precious cargo or living space within the habitat unless it is properly managed. Converting solid wastes to an energy source presents a potential solution to this problem.</p>

Summary

Description

<p>The engineering design group upgraded the liquid nitrogen pump system at the HPGF. The pump system supports the site-wide liquid nitrogen supply and its operation is critical for supporting test activities. The new pumping facility was designed with the capability for adding diagnostic utilities to promote health management of the new cryogenic pump skids. This project provides the health management capability by embedding the AAMU into the system providing real-time diagnostic feedback to operators and scheduling preventive maintenance.  To accomplish this, LabView® software interface communicates between the TEAMS Product Suite’s remote diagnostic server and the pumping control system to display operational health events and suggested maintenance to the user.  </p>

Summary

Description

<p>The multi-core processor supports several operating systems including state of the art multiprocessing operating systems, such as Linux SMP, and use ANSI C/C++ allowing existing code to be easily integrated.</p><p>We will evaluate and implement existing techniques to streamline our data processing system.  We will perform benchmark tests (or timing tests) to evaluate our improvements in processing speed needed to solve the problem.</p><p>Our goal is to embed the processor in the on-board electronics, therefore, we must determine the smallest number of cores that provide sufficient processing capabilities compatible with the power resources of the balloon experiment and low earth orbiting satellite.</p>

Summary

Description

<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’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. 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> </p>

Summary

Description

<p>Absorbers for soft x-rays need to be made thinner and with larger area, to collect more photons, and with minimal number of support stems. However, the structure is then more challenging to fabricate and more subject to distortion or damage from internal or external stress. We will test multiple fabrication/design innovations.</p>

Summary

Description

<p> N/A</p>

Summary

Description

<p>A Hypervelocity Asteroid Intercept Vehicle (HAIV) mission architecture, which blends a hypervelocity kinetic impactor with a subsurface nuclear explosion for optimal fragmentation and dispersion of hazardous near-Earth objects (NEOs), has been developed through a 2011 NIAC Phase I study. Despite the uncertainties inherent to the nuclear disruption approach, disruption can become an effective strategy if most fragments disperse at speeds in excess of the escape velocity of an asteroid so that a very small number of fragments impacts the Earth. Thus, the proposed HAIV system will become essential for reliably mitigating the most probable impact threat: NEOs with warning times shorter than 10 years. It offers a potential breakthrough or great leap in mission capabilities for mitigating the impact threat of NEOs. The proposed Phase II study further develops the HAIV-based mission architecture and explores its potential infusion options within NASA and beyond.</p>

Summary

Description

<p>Subsurface caverns may be the best place on Mars to find life. They may be the best hope for safe havens and habitation on the Moon. They can provide a window into a planet’s geology, climate, and even biology. Skylights, formed by partial cave ceiling collapse, provide access to subsurface voids. Tunnel entrances have been conclusively shown to exist on Mars and the Moon. There is also evidence supporting their existence on other planetary bodies throughout the solar system. Despite astonishing discoveries of skylights and cave entrances, and their inevitable exploration, they do not yet appear in the decadal survey. Skylights and the voids below are so unknown that it is too risky to send astronauts to explore them without prior robotic reconnaissance and modeling. While robotic exploration of skylights and caves can seek out life, investigate geology and origins, and open the subsurface of other worlds to humankind, it is a daunting venture. Planetary voids present challenging terrain that requires innovative technologies for access, exploration, and modeling. The robots that venture into caves must leap, fly, or rappel into voids, traverse rubble, navigate safely in the dark, self-power, and explore autonomously with little or no communication to Earth. Exploiting these features necessitates a “leap” of technology from current planetary missions, which land with large error ellipses in statistically safe terrain, rove slowly and cautiously across the surface, depend on the sun for power and light, and rely heavily on human commands. Phase II develops the enabling technologies in the context of “Spelunker”, a prototype mission concept to explore a lunar skylight and cave. The Spelunker mission specifies safe landing on the rim of a skylight, tethered descent of a power and communications hub, and autonomous cave exploration by multiple hybrid driving/hopping robots. In this context, the Phase II study will expose and address major feasibility issues inherent in mission architecture for skylight access; robot configuration for in-cave mobility and subsurface sensing; terrain modeling in darkness from a lightweight, dynamic platform; and autonomy for exploring with hopping robots.</p>

Summary

Description

<p>Corrosion is a serious problem that has enormous costs for the nation (4.2% GDP in 2007) and worldwide. Kennedy Space Center is located in one of the most naturally corrosive areas in the world. Acidic exhaust from the solid rocket boosters aggravates these natural conditions. New space vehicles are likely to use the same solid rocket fuel used to launch the Space Shuttle. Launching facilities and ground support equipment will continue to need corrosion protection.</p><p>Current research is focused on encapsulating environmentally friendly corrosion inhibitors and incorporating them into commercially available coatings to test their effectiveness. Accelerated corrosion tests have shown that corrosion-activated release microcapsules and particles can be used as inhibitor delivery systems to improve the corrosion protection of several commercially available coatings. This work is being conducted in collaboration with several industry partners who are interested in the NASA-developed smart coating technology.</p>

Summary

Description

<p> <span style="font-family: "Lucida Grande";">The Plasma Magnetoshell is based on demonstrated experimental results and the successful implementation would dramatically decrease mission risk, launch cost, mass, and overall radiation exposure. The Plasma Magnetoshell is a high-Beta (the ratio of plasma to magnetic field energy density) dipole plasma configuration which would initially be populated with ambient atmospheric gases. This plasma is formed, sustained, and expanded with an electrodeless Rotating Magnetic Field (RMF), which has been shown in previous experiments to generate the required, fully ionized, high temperature magnetized plasma. RMF plasma formation induces large currents in the plasma that inflate and maintain the large-scale magnetic structure. The primary drag-inducing interaction between the magnetically confined plasma ions and the incoming neutral atmospheric particles is that of charge exchange, which has the largest cross section. After a charge exchange, the now magnetized atmospheric ion reacts its directional momentum (in the frame of the spacecraft) onto the magnet via field line bending and stretching.</span></p> <script id="dstb-id" language="javascript"> if(typeof(dstb)!= "undefined"){ dstb();}</script>

Summary

Description

<p>Photons weigh nothing. Why must even small space telescopes have high mass? Our team has demonstrated this is not the case using a completely novel approach to producing and correcting active optical primary mirrors to be used specifically for NASA’s future large space telescope missions. Unprecedented advances in nano-engineered meta-materials have produced a laser actuated liquid crystal elastomer (LCE) polymer substrate with controllable reversible bi-directional bending. Using our novel optically controlled molecular actuators allows substitution of optically induced control for rigidity and mass.</p>

Summary

Description

Tasks supported by LARS include those that seek to develop new analytical instrumentation or combinations of analytical instruments, or new components of analytical instruments, leading to significant improvements in the precision, resolution, or sensitivity of measurements compared to the existing state of the art. Also supported is the development of new analytical techniques for existing instrumentation that push the limits of current technology, for example, by the elimination of analytical interferences or contamination problems. Work that addresses the needs of current or selected missions have the highest priority. LARS supports the development of laboratory instrumentation and advanced analytical techniques, as well as the scientific analysis and analytical work on recently returned planetary samples. Based on analysis of active awards in FY12, the LARS R&A Lead estimates that $2.8M out of $8.1M, or 34% of LARS funds, will be spent on technology, developing new laboratory instrumentation and laboratory sample handling and preparation technologies. The amount of funding for technology in future years will depend upon the outcome of future ROSES solicitations, peer reviews, and selections.

Summary

Description

<p> <span style="font-family: "Lucida Grande";">We propose a new mission concept, called MAGNETOUR, that enables a spacecraft to orbit and travel between multiple moons of an outer planet, using very little or even no propellant. To achieve this free-lunch ‘Grand Tour’, we e</span>xploit the unexplored combination of magnetic and multi-body gravitational fields of planetary systems. This concept involves combining two main innovations:</p> <ol> <li> Design of a very low delta-v tour of planetary moons by considering the intrinsic multi-body gravitational dynamics of planetary systems, and</li> <li> Use of the electromagnetic Lorentz force as a revolutionary means for performing the required low delta-v maneuvers of our low-energy tour.</li> </ol> <p>  </p> <script id="dstb-id" language="javascript"> if(typeof(dstb)!= "undefined"){ dstb();}</script>

Summary

Description

<p> N/A</p>

Summary

Description

<p> N/A</p>

Summary

Description

<p> N/A</p>

Summary

Description

<p> <strong>Methodology used to answer science question:</strong></p> <p> The investigators propose to upgrade the successfully flown EUNIS EUV spectrograph, increasing its signal-to-noise ratio and replacing its 30-37 nm channel with a 52.4-63.0 nm channel to cover transition region lines.  They plan to fly the upgraded suborbital experiment, and analyze the results from this and the two previous EUNIS flights.</p>

Summary

Description

<p> N/A</p>

Summary

Description

<p> N/A</p>

Summary

Description

<p>Develop a well understood process for manufacturing visible quality SCSi mirrors. Areas of research include stress relief, figure, finish, and light weighting techniques.</p>