Summary

Description

Self-assembled Dual-functionality Microspheres Project

Summary

Description

We propose to develop a "black carbon" (soot) monitor for measuring non-volatile particulate emissions from gas turbine engines employing a proprietary optical extinction measurement technique based on cavity attenuated phase shift spectroscopy (CAPS) operting in conjunction with a differential mobility analyzer. The singular aspect of the CAPS approach is that extinction is measured by determining shifts in the phase angle of a modulated light beam instead of changes in the intensity of the ransmitted light caused by the presence of particulates. This aspect makes the sensor immune to either abrupt or gradual changes in the intensity of the light caused by temperature or pressure fluctuations or light source deterioration. Furthermore, the sensor rarely needs to be calibrated ? i.e., its span value, a function of the optical properties of the particles themselves, remains virtually constant. This sensor does not rely on the deposition of particles on a filter and requires little maintenance. The monitor will be able to measure the size dependent particle mass concentration in the sub-micrograms per cubic meter with a sampling period of only 1 second.

Summary

Description

Differencing Electrostatic Optical Sensor (DEOS) Project

Summary

Description

Folded Structures Company (FSC) proposes the development of an innovative design approach for multi-laminate, primary and secondary structures for planetary habitats that integrates the dynamic deployment means with the static structural design using an advanced mathematical folding theory. The proposed approach holds the promise of a much simpler structure design that is both lightweight and compactable (low delivery volume) and yet capable of expanding into an expansive surface volume. FSC research indicates the possibility of a new class of deployable, space-based structures that utilize an advanced folding methodology as the primary engineering and assembly method combined with the use of multi-laminate sheet materials. The proprietary patterning algorithms design tessellations for planar sheets that articulate dynamically on the edges of the tessellation allowing for uniform deployment across the entire sheet. Previous to the development of these algorithms, there was no general system for generating doubly periodic folded structures. Based on results from a previous NASA SBIR project, FSC will apply its proprietary folding techniques to the broad topic of expandable habitat structures. The proposed project will essentially become the demonstration stage for the previous research effort, and thus, extend and provide continuity to the ongoing NASA interest in this area.

Summary

Description

A Long-Duration Commercial Microgravity Mouse Habitat: Waste/Odor Technologies Project

Summary

Description

Direct Write (DW) sensors deposited directly and precisely on to complex (3D) components are proposed. Sensors proposed include strain gages and thermocouples, intended as diagnostic elements of a larger health management (HM) scheme. The sensors are deposited using a high precision derivative of thermal spray, affording them the advantages of high temperature tolerance and compatibility with coatings. Strain gages will be deposited as patches onto a range of composites, and laser micromachined to produce their characteristic resistive elements. Signal routing may be via microwelding or DW lead-lines. Thermocouples will be deposited as conformal, parallel traces of paired thermoelements, overlapping to form a junction at the location whose temperature is to be measured. The sensors, having been deposited onto substrates representative of structures on upcoming NASA space vehicles (Orion, Ares, Altair), will then be exposed to conditions similar to those anticipated for said structures, such as low temperatures for fuel tanks, biaxial stress for other pressure vessels, and thermal cycling for on-orbit and lunar exposure. The sensors, having demonstrated their diagnostic capability and compatibility with existing DAQ and HM infrastructures, would form the cornerstone of a potential Phase II continuing application-specific sensor development while expanding to tackle HM integration issues.

Summary

Description

The overall objective of this proposal (Phases I and II) is to develop a robust and accurate solver for fluid-structure interaction computations capable of addressing multi-body flexible structures as well as rigid body motion. The fluid flow solution will be performed using our unstructured solution-adaptive flow solver TETHYS. We propose to develop a structural solver based on the Galerkin finite element method and to couple structure and fluid strongly using an immersed boundary method (IBM). We will employ operator overloading to perform automatic code differentiation so that sensitivity and adjoint analysis can be performed on the coupled code. We will couple to parameterized CAD geometry and to the state-of-the-art optimization modules in the DAKOTA toolkit to perform optimization of fluid-structure interaction problems. In Phase I, we will (i) establish the feasibility of the immersed boundary method across the range of Mach numbers, (ii) develop a tightly coupled algorithm for fluid and structure, and (iii) demonstrate that sensitivities and Jacobians may computed seamlessly and accurately for fluid-structure interaction. Though the focus of the proposal is on fluid-structure interaction problems of specific interest to NASA, the methodology will be applicable to a wide range of commercial CFD applications as well.

Summary

Description

Loop heat pipes (LHPs) can provide variable thermal conductance needed to maintain electronics and batteries on Lunar/Martian rovers/landers within desired temperature range. During lunar day, the LHP transfers the heat to the radiator for rejection. During the fourteen-day-long lunar night, the sink temperature drops, lowering LHP and WEB/battery temperatures. Without a variable thermal link, the LHP will continue to remove heat during the night, cooling the electronics/batteries to unacceptably low temperatures. For spacecraft applications, a small heater is typically attached to the LHP reservoir to shutoff the LHP, preventing excessive cooling of the WEB/battery temperatures. The battery mass penalty to shutoff the LHP through the 14-day-long lunar night is large and must be avoided. This project will develop a LHP incorporating a passive thermal control valve, eliminating the shut-off power requirements. The valve will be installed in the vapor line to selectively route vapor to the radiator during daytime and directly to the compensation chamber (bypassing the radiator) during night, thereby maintaining electronics/battery temperatures. Phase I will demonstrate the feasibility of utilizing the thermal control valve as a varying thermal link. Phase II will fabricate and test a LHP with a thermal control valve, bringing the technology to TRL 6.

Summary

Description

Deployable Space Systems, Inc. (DSS) will focus the proposed SBIR program on the development of a new highly-modularized and extremely-scalable solar array that provides immense power level range capability from 100kW to many Megawatts in size. The proposed ultra-high power solar array will enable extremely high power spacecraft, space-tug, power station applications, and large-scale Planetary and Lunar surface missions. The proposed technology's broad power level scalability is achieved while still retaining industry leading solar array performance metrics and mission enabling features for lightweight, high performance, compact stowage volume, and affordability. The proposed technology will enable future ultra-high power missions through low cost (25-50% cost savings depending on PV and blanket technology), lightweight, high specific power (>200 W/kg to 500 W/kg BOL at the wing level depending on PV and blanket technology), compact stowage volume (>80 kW/m3 for very large arrays), reliability, platform simplicity, high deployed strength/stiffness (10X stiffer and stronger than rigid panel arrays), radiation hardness, high voltage operation capability, scalability to ultra-high power (100kW to beyond Megawatts), and operability in unique environments (high/low illumination and high/low sun intensity).

Summary

Description

NASA is developing new platform systems that have the potential to benefit Earth science research activities, which include in situ instruments for atmospheric measurements for use on radiosondes, dropsondes, tethered balloons, kites, and unmanned aerial vehicles (UAVs). Aerosols influence global climate and human health and can affect local and regional weather processes. Despite of their importance, aerosols are the least-understood components of the climate system. There is a need in instrumentation capable of measuring the size distributions of aerosol particles and vertical distributions of aerosols in the atmosphere. Vista Photonics in collaboration with New Jersey Institute of Technology proposes an innovative and inexpensive, although rugged, self-contained, and intelligent optical aerosol measurement technology. The Phase I study will demonstrate the feasibility of the proposed technology and outline the design of the Phase II prototype instrument. The successful completion of this program will lead to a compact aerosol measurement instrument that can be used for UAV-, balloon-, radiosonde-, and dropsonde-based in situ measurements of aerosol size distribution, concentration, and aerosol vertical distribution in the atmosphere.

Summary

Description

Multi-band phased array antenna (PAA) can reduce the number of antennas on shipboard platforms while offering significantly improved performance. In order to steer wideband beams, photonic beamforming techniques must be invoked so that efficient elemental vector summation in the receiving mode or in the transmit mode is independent of frequency. Crystal Research, Inc. proposes to develop a multi-band photonic antenna based on a high-speed optical true-time-delay beamformer, capable of simultaneously steering multiple independent RF beams in less than 300 ns. Such a high steering speed is 3 orders of magnitude faster than any other existing optical beamformers. Unlike other approaches, the proposed technology uses a single controlling device per operation band, which eliminates the need for massive optical switches, laser diodes and fiber Bragg gratings. More importantly, only one beamformer is needed for all antenna elements. Advantages of the proposed multi-badn photonic phased array anttena includes wideband multibeam operation, high-speed steering, microwave delay compatible, small size, light weight, low power consumption, and immune to electro-magnetic interfere. We plan to develop a laboratory breadboard demonstration the proof-of-concept at the end of Phase I. In Phase II, we will design and fabricate a prototype that can be demonstrated in a representative environment.

Summary

Description

MATECH GSM (MG) proposes 1) to demonstrate a low-cost innovative Hi-Temp Si-doped in-situ BN fiber coating process for advanced ceramic matrix composites in order to eliminate performance barriers that prevent practical use of advanced future NASA aircraft by performing interfacial coating on single fiber tows and fiber preforms that are applicable to the shape and structural requirements of advanced SiC/SiC super- and hyper-sonic components, and 2) to examine and model environmental durability of the fiber coating constituent in various hot-section CMC components. The CVI coating process is costly and yields a porous non-uniform BN structure due to the low temperatures needed for diffusion and infiltration of the gaseous precursors. MG has discovered a faster, more economical and more versatile process for fiber interface coating formation, reactive-transformation-process (RTP), where the interface coating is formed from the ceramic fiber itself, a new innovative in-situ Si-doped BN-based fiber coating that is more stable during fabrication and service of Si-based CMC. The formation of an in-situ BN surface layer creates a more environmentally durable fiber surface not only because a more oxidation-resistant BN is formed, but also because this layer provides a physical barrier between contacting all single fibers with oxidation-prone SiC surface layers.

Summary

Description

We are proposing to develop high altitude CO2 analyzer technology that can be deployed on the research aircraft of NASA's Airborne Science Program (ASP). The ultimate scientific goal is the calibration/validation of CO2 observations made from spacecraft. Two forms of the analyzer are to be developed, pod for unmanned aircraft and rack for more general purpose platforms. The CO2 payloads are small and light enough to perform on all 15 platforms of NASA-ASP, some reaching altitudes of more than 65,000' ASL and capable of probing at least 95% of the atmospheric column. By prior work, we have built a prototype having the appropriate levels of sensitivity (0.10 ppmv), bias (<0.10 ppmv) and spatial/temporal resolution (1 Hz). Consequently, we can initiate our program with Technical Readiness Level (TRL) 5-6. Validation of the prototype was on a piloted aircraft by a second airborne AOS analyzer system of the same specifications and by flask samples analyzed by NOAA/GMD. Observations, some reaching altitudes of 26,000' ASL, were referred to the WMO scale of CO2 DMF by use of reference gases. As a result of prior technological and scientific work, our Phase I program can present a detailed plan for achievement of TRL 9.

Summary

Description

The Lunar Soil Particle Separator (LSPS) is an innovative method to beneficiate soil prior to in-situ resource utilization (ISRU). The LSPS improves ISRU oxygen yield by boosting the concentration of ilmenite or other iron-oxide bearing materials found in lunar soils. LSPS particle size separations can be performed to improve gas-solid interactions and reactor flow dynamics. LSPS mineral separations can be used to alter the sintering characteristics of lunar soil. The LSPS can eventually be used to separate and concentrate lunar minerals useful for manufacture of structural materials, glass, and chemicals. The LSPS integrates an initial centrifugal particle size separation with magnetic, gravity, and/or electrostatic separations. The LSPS centrifugal separation method overcomes the reduced efficiency of conventional particle sieving in reduced gravity. Feed conditioning, such as charge neutralization, can be incorporated into the LSPS to release and disperse surface fines prior to particle separations. The conceptual LSPS hardware design integrates many individual unit operations to reduce system mass and power requirements. The LSPS is applicable to ISRU feed processing as well as robotic prospecting to characterize soils over a wide region on the Moon. The LSPS is scalable and is amenable to testing and development under simulated lunar environmental conditions.

Summary

Description

The necessity of oxygen for consumption by human inhabitants on the lunar surface is readily apparent. NASA is pursuing several ways to generate oxygen from lunar regolith and reduce reliance on Earth for consumable re-supply. The most mature method is via hydrogen reduction. Paragon SDC proposes an innovative method for removing the problematic acidic contaminates from the water vapor compound released during the first stage of the hydrogen reduction process. This innovation also includes a subsequent high temperature water electrolysis technology that is insensitive to dissolved ions, should they persist beyond the acid scrubber. The final product of this system could essentially produce a source of oxygen using almost only in situ resources including lunar regolith (assumed to contain trace amounts of hydrogen) and sunlight. The process could be built to require very little crew interaction and is planned to be highly resistive to harsh chemical interactions. Further, the high temperature electrolysis proposed produces pure, dry oxygen making it a very appealing solution to the challenges facing ISRU programs in generating oxygen from lunar regolith.

Summary

Description

Virtual EM Inc. proposes a system that employs semi-passive RFID sensors with carbon nanotube inkjet-printed antenna and solar powered mesh-networked beacons. The tags will be powered by printed thin film batteries and/or via energy harvesting. Beacons will communicate among themselves and read the semi-active RFID tags worn by the astronauts. The location will be fixed via triangulation and this information will be beamed back to the astronauts.

Summary

Description

NASA has initiated a program to explore the upper troposphere/lower stratosphere (UT/LS) using the Global Hawk Unmanned Aerial System (UAS), which has a payload of over 1500 lb (680 kg), max ceiling of 65,000 ft (20 km) at a cruising speed of 335 kts and mission endurance of over 31 hours. These attributes make the Global Hawk UAS especially valuable as a tool for investigating subvisible cirrus (SVC) clouds, which are commonly found in the Tropical Tropospheric Layer (TTL) and are considered to have a significant potential impact on global climate change. The first of a series of NASA field programs, the UAS Aura Validation Experiment (UAS-AVE), is scheduled to take place in 2009 with the Global Hawk investigating aerosols and gas phase chemistry in the UT/LS. In ensuing years it is anticipated that follow-on field projects will utilize the Global Hawk to investigate properties of SVC clouds. Currently, there is no instrument available for installation on the Global Hawk that is capable of measuring particle size distributions and capturing high-resolution images of cloud particles in SVC. These measurements are essential for understanding the radiative effects that SVC has on the earth energy balance. In Phase I we propose to design and perform proof-of-concept laboratory tests of a state-of-the-art integrated instrument that measures cloud particle size distributions from 1 micron to about 3 mm, and provides three simultaneous digital images of cloud particles. The new probe will combine three instruments that SPEC sells commercially into a compact, aerodynamic package that runs autonomously. In addition, it will be totally compatible with the NASA Research Environment for Vehicle-Embedded Analysis on Linux (REVEAL) system, so that investigators on the ground can view data and control probe functions. In Phase II we propose to build a working prototype and fly it on the Global Hawk (or a Learjet research aircraft if the Global Hawk is not available).

Summary

Description

Southwest Sciences proposes development of gas filter correlation (GFC) spectroscopy using non-periodic gratings for spaceborne and airborne deployment. Our proposed technology will result in smaller, lighter weight, lower power, and more rugged instrumentation than is possible using established GFC spectrometers. The approach is based on the development of non-periodic diffraction gratings that replace the reference gas cells used in GFC spectrometers.

Summary

Description

Heat shield technology is a critical component of manned spaceflight. In particular, the new Crew Exploration Vehicle (CEV) requires thermal protection systems (TPS) beyond the current state of the art. While new TPS shields are under development, a key difficulty is the ability to diagnose TPS performance. In Phase-I SBIR research carried out by EDA and Penn State, we developed a low intrusive fiber optic plug insert for TPS materials that will enable spectrographic measurements of the reentry environment surrounding an ablating TPS. We propose to develop a ruggedized compact spectrometer suitable for coupling with this low-intrusive fiber optic insert. This resulting fiber-coupled spectrometer system plug enables the collection of benchmark data for fundamental flow, radiation, and materials modeling as well as operational correlations between vehicle reentry drag and radiation if implemented in a TPS flight test. The program proposed here will take the concept, originally encouraged at the request of researchers at NASA Ames, from concept to demonstration, through prototype, to a technology readiness level suitable for inclusion in the design of an ablation shield flight demonstrator mission.

Summary

Description

Los Gatos Research proposes to develop a photonic sensor instrumentation, capable of monitoring distributed load and acoustic emission (AE) for rapid inspection of damages in composite overwrapped pressure vessels (COPV). Our novel sensor technology offers a number of advantages including sensor compactness and lightweight with multiplexing capability for load and AE for monitoring and characterizing damages in advanced composite structures and components. We achieve this by employing Bragg grating sensor arrays and using a novel interrogation technique combined with state-of-the-art AE method to detect and pinpoint composite defects in these structures. In Phase I, we will demonstrate the sensor's capability to measure loads and acoustic emission in a composite structure in comparison with conventional piezoelectric type AE sensors. In addition, we will develop a damage grading methodology to predict the presence, location, severity of damages in the COPV. In Phase II, the grating sensors, interrogation system, and diagnostic software will be integrated into an automated system, capable of measuring and correlating the load history, acoustic emission activity, and determining the severity of damages and their location in the COPV.

Summary

Description

As an alternative material to aluminum-lithium, cryotanks developed from fiber reinforced composites can offer significant weight savings in applications for fuel containment of liquid oxygen and hydrogen. For composite materials to be accepted and utilized in these structures, they must be resistant to microcracking. It is the objective of this work to develop a matrix system for aerospace composites that alleviates all forms of microcracking from cryogenic cycling regardless of the lay-up and configuration. This will be accomplished by using a novel chemistry that provides the necessary inherent network and backbone structure for this environment combined with newly developed nano-modifiers. This technology and approach will result in a high performance matrix system that has low or no cure shrinkage combined with very low CTE and extremely high toughness. Such a matrix will be combined with carbon fibers to fabricate lightweight, high performance composites that are expected to have the microcrack and permeability resistance required for cryotank structures. It is expected that the Technology Readiness Level will be 3-4 at the end of this Phase I research.

Summary

Description

The proposed project is an antenna array whose beam is controlled digitally. The Phase 1 effort will assess the method needed to achieve the gain, bandwidth, and pattern (3 dB beam-width and scan field of view). This is based on the level of curvature and interference/geometry of the vehicle on which it is to be mounted. Phase 1 focuses on the fabrication and testing of one element and a sub-array of four elements on a similar surface such as a metallic or dielectric with some degree of curvature. Phase 1 also uses the LMS algorithm to adaptively perform beam shifting and correction for phase shift. Phase 2 will increase the number of elements in the array and allow for scanning in both planes. Also, Phase 2 will consider more complicated geometry as required to deliver a functioning antenna array mounted to the space vehicle.

Summary

Description

The objective of this Phase I project is to demonstrate InGaN materials are appropriate for high operating temperature single junction solar cells. Single junction InGaN test devices with bandgaps between 2.0 and 1.75 eV could provide power conversion in the 15-20% range while offering increased resistance to radiation damage. In this project, we will theoretically and experimentally optimize the doping profiles of p- and n-InGaN for high operating temperatures, fabricate test structures base on p-n junctions, and test the preliminary devices under concentrated sunlight and at temperatures from 100:C to 250:C. At the end of the Phase I, the technology will be at TRL 3.

Summary

Description

When solar energy is used in aerospace applications, the necessary shadowed parts of the spatial orbit require energy storage for the craft/equipment to continue in operation. Batteries are used for the purpose currently, but with increasing power requirements, more efficient charge storage devices have to be developed. Energy storage technologies are expected to have improved energy density, speed, efficiency, or wide-temperature operation (-125<SUP>o</SUP>C to over 450<SUP>o</SUP>C) with a high cycling stability. Supercapacitors or ultra-capacitors are known to exhibit high capacity and power storage characteristics but they suffer from low energy density compared to rechargeable battery systems. Newly developed "asymmetric" capacitors are hybrid charge-storage devices in which a Faradaic, rechargeable battery-type electrode is combined with a non-Faradaic, electrochemical, double-layer type of electrode. It is possible to reach very high working voltage and high energy density by the right choice of electrode material. Materials Modification Inc. proposes to develop a novel nanocomposite material to function as the high-specific capacitance electrode in an asymmetric capacitor. Phase I will involve fabricating the electrode material and testing its electrochemical properties by standard means. Phase II will involve fine tuning the technology to fabricate actual supercapacitors for field testing.

Summary

Description

The goal of this SBIR project is to develop an innovative, high fidelity computational tool for accurate prediction of aerothermal environment around space vehicles. This tool will be based on the Unified Flow Solver (UFS) developed at CFDRC for hybrid simulations of rarefied, transitional and continuum flows. In this project, UFS will be enhanced to include: Boltzmann/continuum solvers for vibrationally excited molecules, advanced non-equilibrium chemistry coupled to non-gray radiative transport with real gas effects, and charged particle transport and chemistry. The unique strengths of our proposal are: (i) smart software with self-aware physics and adaptive numerics for hypersonic flows with non-equilibrium chemistry, (ii) direct Boltzmann solvers for charged and neutral particles in rarefied regimes, and (iii) a high-fidelity multi-scale radiation transport model that can handle orders of magnitude variation in the medium optical thickness. Phase 1 will include evaluation of physical models, initial implementation and demonstration of new capabilities. In Phase 2, these capabilities will be fully developed, validated for selected benchmark problems, and applied to practical cases relevant to NASA. The proposed tool will significantly upgrade the modeling fidelity of high-speed flows of molecular gases, and enable computational investigation of innovative hypersonic flow and plasma technologies.