Datasets


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

In general, development and validation of diagnostic models for complex safety critical systems are time and cost intensive jobs. The proposed Phase-II effort will automate some vital processes essential in developing integrated diagnostic schemes and cost-effective revalidation of the integrated models. The automated processes, resulting from this effort will be incorporated as tools in TEAMS Design and Analytic Platform. For reducing the burden of testing diagnostic models, capability for automatically generating test cases, regression test suites along with the options for their playback will be developed under this effort. Additionally, an option for efficient diagnostics and troubleshooting in multi-mode systems will be introduced in TEAMS via this SBIR effort. To ensure the readiness of the TEAMS tools and options developed through this effort, those will be verified and validated with one or more NASA's ground support systems that are associated with the ARES or Constellation Program Ground Support. Collectively, these achievements will significantly reduce the time and cost in developing and better utilizing large scale fault diagnostic systems using TEAMS.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

The characterization of aircraft particulate matter (PM) emissions has benefited greatly by the Aerosol Mass Spectrometer (AMS) by providing size resolved compositional information. AMS data have been critical to much of our understanding of aircraft PM emissions, but it has limited utility in probing the smallest (<100 nm) particles in the exhaust. Also, to date the AMS has been able to detect only volatile PM and other instruments have been required to characterize the non-volatile (soot). We propose to improve greatly the capabilities of a novel version of the AMS to cover two important gaps in our understanding of gas turbine engine particle emissions: 1) size resolved composition of particles with diameters less than 50 nm; 2) size resolved mass and chemical composition (e.g., fullerenic composition) of black carbon soot. Specifically in Phase I, we aim to: 1) improve AMS detection of particles smaller than 100 nm by refining an existing computational fluid dynamics (CFD) model and use the CFD model to guide the design of new AMS particle focusing designs, and 2) evaluate for model soot characterization a newly developed instrument which combines a laser ablation system with AMS technology ? an instrument which we have termed the SP2-AMS.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Sn-SnSb Filled Carbon Fiber Anodes for High Energy Density Lithium Ion Batteries Project


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Organic Rubber Aerogel as Thermal Insulation and Radiation Shield Project


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

There is demand for vastly improved deep space satellite communications links. As data rates dramatically increase due to new sensor technologies and the desire to pack even more sensors on spacecraft, it is imperative that new solutions be compact in size, light in weight, be high speed, and highly power efficient. NASA has recognized optical links offer potential improvements in power and in size due to a substantially narrower beam and smaller components. An ideal technology for such links is a laser transmitter master oscillator power amplifier (MOPA) using pulse position modulation techniques. In Phase I, a design was developed for a laser transmitter MOPA with a wall-plug efficiency of up to 23% operating at 1560nm. Operating at longer wavelength offers a number of advantages including the use of numerous off-the-shelf components. This Phase II proposal will demonstrate a working prototype of the design at a Technology Readiness Level 4 by the end of the program.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

The Europa Jupiter System Mission (EJSM) will provide a better understanding as to how gas giant planets and their satellites form and evolve. The Jupiter Europa Orbiter (JEO) is the NASA element of the EJSM. JEO will be built to withstand the intense radiation in Europa orbit and the JEO payload includes a thermal instrument. The thermal instrument is based on thermopile detectors that are intrinsically radiation hard to at least 10 Mrad; however, the thermopile readout ASIC needs to be hardened to tolerate the radiation sources of the JEO mission. Black Forest Engineering proposes on Phase I to modify existing thermopile readout circuitry using radiation hardened by design techniques (RHBD) to tolerate the JEO mission radiation sources. The readout application specific integrated circuit (ASIC) when developed on Phase II and combined with JPL thermopiles will meet the thermal instrument requirements of the JEO.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Adiabatic Demagnetization Refrigerators (ADRs) are considered for operations in many space missions. At the heart of an ADR is a magnet that produces the background field necessary for demagnetization of a paramagnetic material. To achieve very low temperatures, all sources of heat need to be eliminated or minimized, making superconducting magnets an obvious choice. The size and power requirement of current cryocoolers that cool such superconducting magnets to about 4K make them unrealistic for space missions. ADR magnets that can operate at 30K-40K require simpler cooling systems and are more suited to space applications. This requires the coils to be fabricated from HTS wires. Phase I of this work aims to manufacture 0.2mm diameter Bi2212/Ag wires and fabricate a 1T 30mm dia. x 62mm long superconducting coil that can operate at 30-40K. Since 2002 our company has been the beneficiary of SBIR awards in the area of developing light-weight low-current ADR magnets operating at 10K by using Nb3Sn superconducting wires in manufacturing of ADR magnets, and successfully fabricated demonstration magnets that were provided to NASA Goddard Space Flight Center. All the developed techniques, procedures and the equipment will directly be applied to the aims of this proposal.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Aeroprobe proposes to design, construct and test an air-data probe with substantially higher frequency response than currently available. This fast-response atmospheric turbulence probe (FRAT probe) will be able to sample ambient air, and measure CO2 and other gases.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Improving Test Operations Through Scalable Video Processing on Computer Clusters Project


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

We are developing CAD tools, models and methodologies for electronics design for circuit operation in extreme environments with a focus on very low temperature and radiation effects. These new tools will help enable NASA to design next generation electronics especially for planetary projects including the Europa Jupiter System Mission. The new models and tools will be directly incorporated into industry standard CAD products to ensure their usability and extend their applicability to extreme environments. Such capabilities will significantly improve reliability, performance and lifetime of electronics that are used for space missions. This will be achieved through the development of novel compact and distributed device modeling capabilities for radiation-hard and extreme temperature instrument design, as well as techniques for circuit design that help to predict the vulnerability of circuits to degradation and upset from radiation. Research and development is indicating that standard bulk silicon CMOS and SOI processes operate well under these extreme conditions so that there is little need for NASA to commit to large expenditures for exotic materials. Models and CAD tools are relatively inexpensive as compared to fabrication costs; thus the results of this project should provide a very large return on investment.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

An aeroacoustic computational code based upon a numerical solution of the full Navier-Stokes equations will be developed to provide a deep understanding of the physical behavior of resonator liners exposed to intense sound and boundary-layer grazing flow. The code computes the entire flow and acoustic field inside the flow duct. The user has the option to choose the flow Mach number, boundary-layer thickness, duct mode of incoming sound, frequency and SPL. For broadband sound, the user has the option to specify an incident noise spectrum. The code is designed to operate at both standard temperatures and very high temperatures. A semi-empirical three-dimensional resonator liner impedance code will developed for resonators also exposed to intense sound and boundary-layer grazing flow. The liner empirical parameters will be calibrated with NASA furnished resonator test data. Because of its simplicity, it can be used to provide realistic liner geometries for sound propagation codes that are used in both NASA and industry to determine optimum wall impedances to control excessive sound generated in jet engines and other flow duct environments.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

The Mars Sample Return mission is being planned to return samples of Martian rock, regolith, and atmosphere to Earth for scientific analysis. The Martian sample size is directly affected by the propulsion capabilities of the Mars Ascent Vehicle (MAV) and innovations are sought to enhance propulsion capabilities of the MAV for functions including primary propulsion from the Mars surface, orbit insertion, and attitude control. The proposed constant-volume combustion rocket (CVC) propulsion technology will lead to 1) significant weight reduction and simplification; 2) reduced costs in the system components and ground servicing; 3) prolonged mission or systems lifetimes; 4) improved reliability; and 5) enhanced critical mission functions. The Constant Volume Combustion (CVC) engine is an innovative design that combines light weight, low pressure fuel tanks and operates at high chamber pressures. The CVC engine has nearly identical specific impulse as the constant pressure engine with the same mass flow and throat area, furthermore, the nozzle optimizes at the same area ratio. It has exceptional thrust-to-weight ratios, and the proposed bipropellant system meets Martian temperature requirements without heating or stirring. During Phase 1 we will demonstrate, through analysis, experimentation, and hot-fire testing, the feasibility of our proposed CVC engine as a credible candidate for Mars Ascent Propulsion. In Phase II, there will be an aggressive push towards flight-like hardware to ensure rapid maturation of the technology in order to meet the NASA mission goals.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Recovery of water from brine is critically important for future manned space exploration. Resupply of water is prohibitively costly for such extended missions. Water reclamation processes typically recover 90-95% of the water present in wastewater formed by combining urine, hygiene water, and humidity condensate with the remaining concentrated in brine. This concentrated brine contains a significant amount of water, potentially a very valuable resource. The proposed prototype development will recover virtually all of the remaining water using an ultrasonic brine dewatering system (UBDS). In the UBDS process, extremely small nebulized droplets of the brine are created ultrasonically at the brine?air interface. Small droplets enable quicker drying due to their high relative surface area. This is particularly important when drying brines that contain thermally labile materials, which require relatively low temperature drying. The UBDS prototype has no nozzles to become plugged, requires little power, is simple and small, requires minimal astronaut attention and is compatible with continuous, closed cycle operation that can be made gravity independent. The innovative Phase 2 prototype will fulfill the unmet need to significantly improve water loop closure during extended manned missions. The Phase 2 project will provide an automated UBDS prototype that will be delivered to NASA for further testing.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Motors used in rovers, cranes and instruments for use on lunar and Mars missions present unique design requirements. Weight reduction is critical, so motors with high power density and torque density are desirable. Also, the motors need to be designed to work over a wide temperature range: from 40 K to 403K. The proposed axial flux, coreless, brushless, Halbach array motor has been demonstrated to have the highest power density and the highest efficiency in land based applications. In this phase I effort, the motor will be developed for use in lunar and Mars missions in which the operating temperature range is from 40 K to 403K. This would be a significant technical advancement.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

NASA's plans for a lunar habitation outpost call out for process technologies to separate hydrogen sulfide and sulfur dioxide gases from regolith product gas streams. A low-pressure drop separation unit is needed to remove these sulfur compounds from regolith process streams that is compact and lightweight. To this end, Reactive Innovations, LLC proposes a Phase II SBIR program to continue the development of an electrochemical reactive-separation unit to selectively bind and remove the sulfur compounds into a separated stream of sulfur-based compounds. During the Phase I program, we developed and successfully demonstrated an electrochemical reactive-separation platform that binds sulfur compounds via a charge transfer process to a redox carrier that is subsequently transported across a membrane separator releasing the sulfur components. The Phase II program will continue to develop the membrane electrode assemble to improve the separation process as well as transition this technology to RIL's advanced reactor platform for more extensive testing. The Phase I effort has brought this lunar regolith reactive-separator unit to a Technology Readiness Level of 3. The Phase II program will deliver an operational prototype at a TRL of 4-5.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

We will design and formally verify a VLIW processor that is radiation-hardened, and where the VLIW instructions consist of predicated RISC instructions from the PowerPC 750 Instruction Set Architecture (ISA). The PowerPC 750 ISA is used in the radiation-hardened RAD750 flight-control computer that is utilized in many NASA space missions, including Deep Impact, the Mars Reconnaissance Orbiter, the Mars Rovers, and is planned to be used in the Crew Exploration Vehicle (CEV). The VLIW processor will have reconfigurable functional units and specialized instructions that will be optimized for Software Defined Radio applications. The radiation-hardening will be done at the microarchitectural level with a mechanism that will allow the detection and correction of all timing errors---caused not only by radiation, but also by variations in the voltage, frequency, manufacturing process, and aging of the chip. The binary-code compatibility of the resulting VLIW processors with the PowerPC 750 ISA will allow them to seamlessly execute legacy binary code from previous space missions. We have made critical contributions to the fields of formal verification of complex pipelined microprocessors, and Boolean Satisfiability (SAT), and have developed highly efficient Electronic Design Automation (EDA) tools that we will use.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

To address the NASA GSFC need for significant improvements in wide bandgap materials and detectors for UV applications, Physical Optics Corporation (POC) proposes to develop a new AlGaN nanowire photocathode for Silicon Microchannel Plate solar-blind photodetector fabricated directly on the MCP entrance plane. This innovative photocathode and the technology of its growth on the Si microchannel plate enables us to meet NASA requirements for windowless operation in the FUV range with high quantum efficiency, low noise, radiation-hardness, reliability, and potentially low cost. In Phase I, POC demonstrated the technology of GaN and AlN nanowire growth by Hydride Vapor Phase Epitaxy and investigated the properties of nanowire surfaces. In Phase II, POC will optimize this technology for fabrication of an AlGaN nanowire photocathode on a silicon MCP structure and demonstrate photodetector operation in the FUV range. This innovative, efficient, solar-blind, and radiation-hard UV photodetector with low background noise and a large sensing area will offer NASA capabilities to design new instrumentation with improved sensitivity and spatial or spectral resolution for FUV and UV instruments for several missions devoted to a better understanding of the origin of the Universe and its evolution to modern form.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

In terms of relevancy to piloted evaluation, there remains no substitute for actual flight tests even when considering the fidelity and effectiveness of modern ground-based simulators. In addition to real world cueing, flight test provides subtle but key intangibles that cannot be duplicated in a ground-based simulator. There is, however, a cost to be paid for the benefits of flight in terms of budget, mission complexity, and safety. New technologies and test procedures are therefore needed to maximize the investments and reduce some of the related costs associated with flight test. To address this need, Systems Technology, Inc. is developing a Fused Reality (FR) Flight system that allows a virtual environment to be integrated with the test aircraft so that tasks such as aerial refueling, formation flying, or approach and landing can be accomplished without additional aircraft or risk of operating in close proximity to the ground or other aircraft. Furthermore, for the first time, the dynamic motions of the simulated objects can be directly correlated with the responses of the test aircraft. The FR Flight system will allow real-time observation of and manual interaction with the cockpit environment that serves as a frame for the virtual out-the-window scene.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

We propose to investigate and develop an inexpensive system to determine: 1)VLBI antenna properties such as axis-offset, non-intersection of axis and antenna reference point; 2) Gravitational and/or Thermal deformation; 3) The eccentricity vector from the VLBI antenna to nearby GPS receivers. The proposed system involves using several GPS receivers in close proximity driven by a common clock. Because of their proximity, atmosphere and ionosphere errors are common, and vanish when we take the difference of measurements from different receivers to a common a satellite. Satellite clock errors also vanish in this difference. Since the receivers use a common clock, receiver clock error also vanishes. The remaining error source is GPS multipath which can be mitigated.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Based on successful space testing onboard the Midstar1 satellite, Eclipse Electrochromics have been identified by a number of organizations as well as NASA as a high interest technology. For nanosats, the critical design challenge is achieving autonomous control of the EclipseVEDs<SUP>TM</SUP> for spacecraft thermal self regulation without the need for human intervention. To achieve this goal, Eclipse employed EclipseVED<SUP>TM</SUP> technology and demonstrated the capacity to have automated control thermal systems capable of in-flight thermal regulation of a cubesat or other small satellite. In Phase II, Eclipse will build a complete multi-panel cubesat and work with NASA to lab test a completely functional prototype and review the capacity to utilize the ECDs concurrently with photovoltaics.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

SynGenics Corporation proposes a program that unites mathematical and statistical processes, Response Surface Methodology, and multicriterial optimization methods to design optimized, failsafe technologies to control shockwave-boundary-layer interactions and realize improvements in supersonic inlet performance and vehicle efficiency. The innovation described in this proposal is the development of SynGenics Optimization System (SynOptSys), a software product that will provide expert guidance to the user in the capture and documentation of response variables, identification of factors, and statistical design of experiments (DOE). Furthermore, the software system will assist the user in the analysis of DOE data, model building, diagnostics, and system optimization. The software will implement multicriteral optimization methods developed by SynGenics personnel, which will enable the simultaneous optimization of the flow-control (FC) system with respect to multiple, competing inlet-system requirements. SynOptSys will help designers and product developers overcome the barriers that prevent them from using powerful mathematical and statistical techniques to develop better products in a less costly manner. SynOptSys will implement the final task in a suite of methods developed by SynGenics to transform a need and candidate solution concepts to an affordable solution. Use of these powerful techniques enables the development of high-value systems. The significance of this program is that it will provide tools necessary to conduct multicriterial, inlet system-level-assessments and optimizations of enabling technologies, including, but not limited to flow-control technologies This program supports the Propulsion Efficiency key research area of the NASA Fundamental Aeronautics Supersonics Program by working to develop inlet FC technologies that will facilitate low TSFC of highly integrated supersonic inlets and improved overall cruise efficiency through reduced inlet drag.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Development of an improved water management membrane for a static vapor feed electrolyzer that produces sub-saturated H2 and O2 is proposed. This improved membrane can increase the performance and especially the durability of static vapor feed electrolyzers. Static vapor feed electrolyzers greatly simplify electrolyzer systems as they eliminate the need for water/gas phase separation, which is particularly challenging in a zero gravity environment. Maintaining water in the vapor phase greatly reduces membrane swelling which should increase durability. Finally, by keeping water in the vapor phase the MEA is not exposed to ion and other contaminants that are carried by a liquid water stream, further increasing durability and simplifying the system by reducing the need for ultra-pure water. The primary goal of this Phase I program then is to demonstrate the enhanced performance and durability of a static vapor feed electrolyzer utilizing an improved water management membrane.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Future X-ray telescopes require significant amounts of optical area. To accommodate this in a grazing incidence design, extremely thin mirrors are formed in concentric shell configurations. A slumping technique has been demonstrated with such thin, lightweight shells. However, the optical surface is found to contain a significant amount of mid-spatial frequency errors. Reactive Atom Plasma (RAP) is a figuring technique that does not impart mid-spatial frequencies to the optical substrate geometries and can additionally remove specific spectra from the figure error. RAP is a sub-aperture, atmospheric pressure, non-contact figuring technology that relies on a deterministic gas-phase etching of the optical surface with high material removal rates. Further, RAP has the ability to modulate tool footprint on the fly, allowing the removal of specific spatial frequencies from the error spectrum. RAP has already been demonstrated as a very credible approach for fabricating the lightweight wedges required for the assembly of such mirrors and is especially suitable for figuring extremely lightweight mirrors given the non-contact operation. In phase 1, we demonstrated the ability of the RAP process to impart minimal mid-spatial errors into the optical surface. A fully automated figuring platform with adjustable footprints is to be developed for phase 2.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

Robust, lightweight, power-efficient excavation robots are mission enablers for lunar outposts and surface systems. Lunar excavators of this type cost-effectively utilize native materials for both outpost preparation and in-situ resource utilization. They address the need for implements that dig, collect, transport, and dump lunar soil. Past prototypes, while providing valuable insights, have either been too large, too slow, or had too little pound-for pound regolith moving capacity (payload ratio) to be real options for a lunar outpost. Novel designs incorporating dump beds, high-speed driving, and composite materials are game changers, making lightweight excavation robots advantageous for lunar site and surface work. Performance of elemental actions such as digging or driving has been studied, but it is performance in achieving a site-level task like berm building that matters. This proposal team has identified payload ratio and driving speed as dominating parameters governing site work. This has been done by creating and applying a task-level simulator, REMOTE (Regolith Excavation, Mobility & Tooling Environment), for a prior NASA contract. Current excavation force models do not adequately address cohesion and soil-tool friction within a lunar-relevant regime, as this work proposes to do. Trade studies and prototypes of lunar excavators are informative, but direct controlled comparisons of configuration options (ex. loader or dozer) will yield the best means of choosing a real design. The Technology Readiness Level (TRL) at the beginning of the proposed Phase I work is 2. The anticipated results of Phase I include a prototype design as well as experimental data supporting the feasibility of the concept, bringing the TRL to 3. Phase II will result in a completed prototype that will be used to validate predictions of key parameters, bringing the TRL to 4.


Published By National Aeronautics and Space Administration

Issued over 9 years ago

US
beta

Summary

Type of release
a one-off release of a single dataset

Data Licence
Not Applicable

Content Licence
Creative Commons CCZero

Verification
automatically awarded

Description

In this proposed Phase I program, a multifunctional lightweight radiation shield composite will be developed and fabricated. This structural radiation shielding will be a high strength, syntactic polymeric where the polymer is filled with high strength low Z material. Specifically, this program will produce structural Polymeric aluminum alloy-LiBH4 composite materials layups. These structural composites are derived from similar structures Powdermet currently produces using hollow spheres (lightweight insulating structures), and more recently, energetic materials (such as KClO4). These materials serve to provide combined structural properties, thermal insulation, mass-efficient radiation shielding, and collision and micrometeroid impact energy adsorption.