Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
One of the needs of NASA is the development of avionic systems and components that have the capability to operate in extreme radiation and temperature environments found in deep space, as well as the lunar and Martian surfaces. As a result, spacecraft electronics will be required to be hardened against radiation environment and temperature cycling. In fact, they should withstand a total ionizing dose (TID) of at least 100 krads (Si) and provide single-event latchup (SEL) immunity of at least 100 MeV cm2/mg. As part of these needs, NASA is interested in Field Programmable Gate Array (FPGA) technology with reliable reprogrammability and a degree of radiation hardness. We intend to answer NASA's need for FPGA technologies suitable for future exploration systems. In Phase I, we plan to focus on the integration of radiation hardening technologies involving both the structure of the FPGA and its sub-components, as well as use of an advanced foundry process and specialized circuits to mitigate radiation.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Lithium-ion (Li-ion) batteries are attractive candidates for use as power sources in aerospace applications because they have high specific energy (up to 200 Wh/kg), energy density (~ 500 Wh/L) and long cycle life (1,000 30,000 cycles depending on the depth of cycling). Yardney/Lithion, Inc. the leader in cutting edge Li-ion batteries is dedicated in research, development, design and manufacturer of high performing battery systems for aerospace, land and sea applications. At the present moment, two of the Lithion batteries are operating on the surface of Mars with great success. Future robotic and human exploration missions require advanced human-rated energy rechargeable batteries level metrics should have specific energy of 300 Wh/kg at C/2 discharge rate and 0<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Strict//EN" "http://www.w3.org/TR/xhtml1/DTD/xhtml1-strict.dtd"> <sup>o</sup> C, and energy density greater than 500 Wh/l, with a calendar life of 5 years. The cycle life of the cell is required at 100&#37; Depth of Discharge (DOD) in the range of 250 cycles. Yardney proposes to develop environmentally benign new electrode components and cell chemistries based on high capacity of 300mAh/g layered Li2MnO3 derivative cathode, composite silicon based anode with a capacity of over 600 mAh/g and suitable electrolyte.
Numerical and Physical Modeling of the Response of Resonator Liners to Intense Sound and High Speed Grazing Flow Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
An innovative research program is proposed that numerically and physically models the response of resonator liners to intense sound and high speed grazing flow. The research program is divided into two parts. Part 1 addresses the feasibility of performing direct numerical simulation (DNS) of the sound and flow fields of the following: (i) one-slit and two-slit resonators in a normal incidence impedance tube, (ii) adjust and modify the computational algorithm and mesh design to allow the code to perform high temperature simulations, and (iii) use the simulation codes to initiate a study of the performance of high temperature liners. Part 2 develops the following: (iv) a grazing flow multi-slit orifice resonator impedance model, (v) a grazing flow 1-dof multi-circular orifice resonator impedance model and (vi) a 2-dof non-grazing flow multi-circular orifice resonator impedance model. The research program was motivated, in part, by high oil prices that place ever greater demands upon the near-term need to provide aircraft engine acoustic engineers with reasonably accurate tools to design optimized liners and the long-term need to develop sophisticated computational codes to provide physical understanding of the interaction between incident intense sound and grazing flow on resonator liners
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Propulsion Design with Freeform Fabrication (PDFF) will develop and implement a novel design methodology that leverages the rapidly evolving Solid Freeform Fabrication (SFF) manufacturing techniques and materials in the advancement of spacecraft propulsion components development and production. This effort will engender otherwise unproducible designs that significantly improve performance, thermal management, power density, and stability, while reducing thruster development and production costs. The key feature of the SFF technique is the capability to form objects with any geometric complexity without the need for elaborate machine setup or final assembly. The application of SFF to propulsion components requires an evolution of design practice to harmonize material properties with functional efficiency. Using the expertise of propulsion industry analysis, design and development engineers, a new class of design approach will be developed for the enhancement of performance, combustion stability, weight reduction, and increased operating envelope as applied to liquid rocket injectors. The Phase I effort will establish material requirements specifications for dimension resolution, structural and thermal properties, and propellant compatibility. The various SFF techniques will be assessed to identify strengths and weakness as applied to propulsion component development and production. Assembly, inspection, and quality control requirements will be assessed. Novel approaches to component sensing and control will be investigated for the feasibility of embedded instrumentation and MEMS during production. The application of fluidics for rocket injection logic will be investigated. As a technology demonstration for Phase I, a novel, high performance, lightweight injector design for a pulsing attitude class thruster will be developed based on the project's investigation using the latest high-temperature SFF materials.
Lunar Navigator - A Miniature, Fully Autonomous, Lunar Navigation, Surveyor, and Range Finder System Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Microcosm proposes to design and develop a fully autonomous Lunar Navigator based on our MicroMak miniature star sensor and a gravity gradiometer similar to one on a ship-board celestial navigation system designed by Microcosm for the Navy. The new sensor will provide surface navigation on the Moon or Mars with accuracies comparable to state-of-the-art precision celestial navigation systems on Earth. The system can rapidly determine its location anywhere on the Moon or Mars where a large portion of the sky is visible, day or night. With the unique three field-of-view star sensor design, the sensor can also be used to provide precise surveying of surrounding terrain and, in either of two modes, can provide passive range-finding to artificial or natural objects. The entire package will be less than 10 cm on a side, weigh less than 1 kg, draw less than 10 W of power, and work in a wide range of temperature and illumination conditions. Phase I will focus on the system requirements, a preliminary navigator design, and initial performance estimate. Phase II will focus on fabricating and testing a functioning prototype of the Lunar Navigator, including ground testing with real stars at night.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
This proposal addresses the need for an antenna technology platform that meets the requirements of high-performance materials, exacting dimensional tolerances, and the geometrical design freedom to enable planar antenna array technologies for frequencies greater than 100GHz. The PolyStrata fabrication technology, being developed at Nuvotronics, LCC, Blacksburg, VA., is capable of meeting or exceeding all of the requirements outlined to be a solution for these frequencies. Air-filled copper rectangular coaxial transmission lines are fabricated using a photolithographically defined layer-by-layer process. The resulting transmission lines are extremely broadband, low-dispersion, high-isolation, and low loss compared to other forms of planar transmission lines. These lines are smaller than rectangular waveguides because the transverse cross-sections of the lines are not resonant. Phase I of this work includes designing a frequency-scanned antenna-array operating from 140-160GHz that would provide 116<SUP>o</SUP> beam steering with a beamwidth of 0.5<SUP>o</SUP> and 400MHz per beam bandwidth. An antenna array with this performance would require roughly a 24cm by 24cm aperture to fabricate. This is possible using 4 sub-arrays that each are fabricated on a single wafer and then tied together to achieve the overall system performance. The approach will offer a high-yield, cost effective product that will meet the NASA needs.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Autonomous and semi-autonomous robotic systems require information about their surroundings in order to navigate properly. A video camera machine vision system can supply position information of external objects, but no range information. Ideally, a system that, in one package, provides 3-dimensional relative information about external objects is needed. Existing laser range finding systems are expensive and consume large amounts of power. Additionally, they are sensitive to only a narrow solid angle, and must be scanned mechanically in order to provide more than a single dimension of depth information. Nanohmics proposes to design an electro-optical imaging device capable of autonomously determining the range to objects in a scene without the use of active emitters or multiple apertures. The novel, automated, low-power imaging system is based on a plenoptic camera design, and will be simple to implement, providing the range to selected objects in the field of view. Nanohmics will work towards presenting a 3D map of the field-of-view plus range ? to be used at a later time to interface with the autonomous vehicle for navigation and obstacle avoidance. The system will be designed so that it is inexpensive, easy to integrate with existing/planned planetary rovers, rugged, and low in maintenance. Nanohmics will develop a custom optical system along with embedded digital signal processing electronics and a unique opto-mechanical design; and develop firmware/software algorithms for determining range to objects within the system field-of-view. Optionally the processed image will be coupled with automatic detection, recognition, and avoidance algorithms.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Aurora Flight Sciences, along with its partner Vertigo Industries, proposes a novel approach to deployment of balloon-based payloads into the Martian atmosphere. Balloon-based Mars exploration has the capability to cover a larger portion of the Martian surface than is accessible via a rover and to provide better resolution than is available from satellites. Due to the low density of the Martian atmosphere, the balloon envelope for even a small payload is quite large (tens of meters in diameter); therefore, balloon deployment is a major challenge for a Mars balloon. A ground launched balloon, as compared to descent launched, allows a longer time constant for deployment, more control over the timing of the deployment, and, if coupled with a rover, also allows more control over the location of deployment. A challenge to ground deployment is the possibility of the envelope being damaged during deployment by winds, surrounding rocks, or parts of the associated lander. Aurora's Shielded Mars Balloon Launcher (SMBL) concept addresses this challenge by using inflatable structures to provide a safe environment for balloon inflation and deployment. The proposed SMBL system has a 15 kg mass and packed volume of 0.15 m^3, and is therefore feasible as a secondary payload on existing Mars exploration missions.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We propose a high-pressure, regeneratively-cooled combustion chamber that uses novel material selection for extreme reductions in mass. These materials are manufactured using proven processes, processes in which our two team members are expert. The combustion chamber liner will be made of a high-temperature-capable, low density material; the structural jacket will be made of a metal matrix composite material, with a tailored CTE close to that of the liner.
Hyperspectral Longwave Infrared Focal Plane Array and Camera Based on Quantum Well Infrared Photodetectors Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We propose to develop a hyperspectral focal plane array and camera imaging in a large number of sharp hyperspectral bands in the thermal infrared. The camera is particularly suitable for the multispectral thermal infrared (TIR) imager of NASA's HyspIRI Mission. In Phase 1, we will develop a crucial camera component: a 640x512 focal plane array (FPA) with 8 - 12 micron broadband longwave spectral response. In Phase 2, we will integrate the FPA with a linear variable filter in a dewar cooler assembly and package the resulting sensor engine with electronics and optics into a compact portable camera. A sample FPA will be delivered at the end of Phase 1. The camera, featuring digital and analog video outputs, will be delivered to NASA at the end of Phase 2 for field testing.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
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. It is proposed to demonstrate a sub-aperture figuring technique that does not impart mid-spatial frequencies to the optical substrate geometries planned for integration into next-generation X-ray telescopes. Reactive Atom Plasma (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. RAP has already been demonstrated as a very credible approach for fabricating the lightweight wedges required for the assembly of such mirrors. RAP is especially suitable for damage-free processing of extremely lightweight mirrors given the non-contact operation, and its ability to ameliorate sub-surface damage. The tool footprint is a Gaussian and hence has a limited capability to both impart mid-spatial errors, as well as to fix them. In phase 1, we plan on demonstrating the ability of the RAP process to impart minimal mid-spatial errors into the optical surface while a figuring demonstration using adjustable footprints is planned for phase 2.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Scramjet engine developers are working on advanced axisymmetric engine concepts that may not be feasible due to limitations of currently available manufacturing methods. The primary goal of this SBIR is to make available a new technology that will make it feasible to manufacture small diameter one-piece cooled axisymmetric scramjet combustors. The availability of the proposed technology will result in scramjet program cost savings and engine design improvements and a strong near term technology commercialization is likely. In fact, scramjet developers have expressed that there is no other known means of manufacturing some of the most desired axisymmetric combustor designs. Although Ormond, LLC currently manufactures scramjet engine panels using a novel abrasivejet machining process and software that is available nowhere else in industry, new engine developments have created the need for key technology advancements. A principal advantage of the proposed technology is that it can generate small high-aspect-ratio channels in nearly any material, and is now used to machine the complex cooling flow field patterns found in the Inconel scramjet heat exchanger circuits. There are technical and economic benefits over all of the existing manufacturing methods because it is a cold, non-chemical low-mechanical load process that has no affect on workpiece material crystal structure. Developments that will be made under this SBIR are: 1.) miniaturization of the specialized cutting head to fit in the axisymmetric combustor, 2.) development of a new numerical model and software needed to implement the process, and 3.) development of an appropriate long reach manipulator arm and control software to provide appropriate tool motion in the combustor cylinder. The Phase I program will initiate the development and demonstrate feasibility of the proposed technology.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Life on Earth is unique in many ways; one of its great mysteries is that all the biomolecules of Earth's life are chiral and one optical isomer of each amino acid or nucleic acid "building block" was selected by evolution. In our pursuit of finding life on Mars and beyond, it is likely that one of the clues to extant or extinct life could be the detection of non-racemic chiral molecules. This proposal describes the development of a highly miniaturized and ultrasensitive lab-on-a-chip polarimeter to measure the optical rotation of biomolecules such as amino acids, sugars, DNA, RNA in samples extracted from other planets or moons. The proposed polarimeter will be based on liquid crystal variable retarder (LCVR) technology. This technology offers a highly sensitive optical rotation measurement, from extremely small sample volumes, in a highly miniaturized format. This work is a joint collaboration between Intelligent Optical Systems, Professor Axel Scherer of the California Institute of Technology, and Meadowlark Optics. In Phase I, we propose to fabricate an LCVR polarimeter and demonstrate its ability to measure small angles of optical rotation. High sensitivity, low-power consumption, no moving parts, and potential for integration into future exploration missions are the attractive attributes of the proposed technology. In Phase II, we will optimize the performance, develop prototypes, and conduct extensive testing.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
NASA needs narrow linewidth lasers in the 1.5 or 2 micron wavelength regime for Lidar applications. The laser should be tunable by several nm and frequency modulated by 5GHz. Princeton Optronics has developed ultra-stable narrow linewidth diode pumped solid state lasers and developed high power Vertical Cavity Surface Emitting Laser (VCSEL) devices for fiber laser pumps as well as VCSEL pumped CW fiber lasers. In this SBIR, we propose to develop a fiber amplifier with a narrow line width seed laser for narrow wavelength output and the seed laser would be tunable and frequency modulated to a speed of 5GHz. By the end of the SBIR program we plan to deliver 10W level CW power fiber amplifiers with 10kHz linewidth in a small package. The package with the device would be space qualified and commercialized after development.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Lunar dust has been identified as a significant and present challenge in future exploration missions. The interlocking, angular nature of Lunar dust and its broad grain size distribution make it particularly detrimental to mechanisms with which it may come into contact. Honeybee Robotics Spacecraft Mechanisms Corporation (HRSMC) seeks to develop a dust-tolerant, autonomous connector to transmit data and power on Lunar surface systems. HRSMC has extensive heritage in developing mechanisms for extreme and dusty environments, including the development of a dust-tolerant electrical connector prototype and a dust-tolerant mechanical connector concept. There are many near-term applications of such a connector including: the utility and electrical connections that will be used on the next-generation Lunar EVA suit, cryogenic utility connections that will be used to pass liquid hydrogen and liquid oxygen during in-situ, resource utilization (ISRU) activities, and high-power electrical connectors capable of thousands of cycles for Lunar Surface Mobility Unit (LSMU) battery recharge and data transfer. As noted in current Lunar architectural options, human EVA's, long range Lunar rovers, and ISRU activities are on the mission horizon and are paramount to the establishment of a permanent human base on the Moon. In Phase I, HRSMC will baseline prior dust-tolerant connector work to develop a conceptual design for an autonomous, dust-tolerant, re-usable connector to enable electrical transfer between a LSMU and a central resource outpost or a deployed solar power unit. This connector would be easily adaptable to the needs of other Lunar surface system utility connectors required for EVA suits or other systems such as ISRU utility connections. This development path will result in an autonomous Lunar dust-tolerant electrical connector with a TRL level of 3-4 at the end of Phase 1 with a goal of at least TRL 6 at the end of Phase II.
On Orbit Immuno-Based, Label-Free, White Blood Cell Counting System with MicroElectroMechanical Sensor (MEMS) Technology (OILWBCS-MEMS) Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Aurora Flight Sciences Corporation and our partner, Draper Laboratory, propose to develop an on orbit immuno-based, label-free, white blood cell counting system for simultaneous counting of peripheral blood cell subpopulations, including total white blood cells, the five white blood cell differential subgroups, and various lymphocyte subtypes, such as CD4 and CD8 positive cells, using Draper's MicroElectroMechanical Sensor (MEMS) based microfabricated arrayable Adhesive Stress Electrostatic Sensor (ASES) technology. The proposed ASES sensor uses a capacitance read-out method to electronically measure the sensor membrane displacement due to the surface stress caused by molecular binding, (e.g., antibody-antigen binding). Antibodies specific to the white blood cell surface protein markers (antigens) are precoated on the ASES sensor membrane to recognize the specific white blood cell types with inherently high specificity and sensitivity. Our proposed cell counting system can meet NASA's requirements for a microgravity compatible, miniaturized, light weight peripheral blood cell counting instrument capable of on-orbit cell counting, without high energy lasers, requiring minimal sample volume or exogenous (sheath) fluid to operate, and generating minimal biohazardous waste. This ASES blood cell counting system, once developed, can stand alone for white blood cell differential and subtype count, or become a complimentary instrument to others available on-orbit.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Aero-assist technologies are used to control the velocity of exploration vehicles (EV) when entering earth or other planetary atmospheres. Since entry of EVs in planetary atmospheres results in significant heating, thermally stable aero-assist technologies are required to avoid the high heating rates while maintaining low mass.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
We are proposing to build a new technology, the photo-pneumatic analyzer. It is small, solid-state, inexpensive, and appropriate for observations of atmospheric carbon dioxide (CO2) from six of the seven robotic platforms being targeted by NASA in its solicitation. An inexpensive MEMS transducer is integrated into a miniature pair of gas cells to serve as the radiation sensitive element of the analyzer. Absorption by individual vibration-rotation transitions serves as the measure of CO2 Dry Mole Fraction of the sample. The analyzer has significant sensitivity, bandwidth and specificity to 12CO2 or 13CO2. Target sensitivity is 0.1 ppmv at 1 Hz for both isotopes. The analyzer may be modified to detect additional molecular species. The immediate objective is to develop an expendable CO2 analyzer that can be manufactured by machine and can be used to validate observations of CO2 column from spacecraft and can further serve as the basis of a new global monitoring network of climate change. The products targeted for Phase II are: (i) a substantial series of vertical profiles of CO2 that serve to prove the utility of the new technology as payload of the expendable balloon platform and (ii) the manufacturing plan for a commercially viable photo-pneumatic analyzer.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Problem: Ensuring that command execution scripts do not deviate from Standard Operating Procedures (SOPs) is time-consuming, costly, and error-prone. Deviations can be inefficient or hazardous. Solution: We propose to design and develop SAFE-P, an interactive tool to ensure conformance between command scripts and procedures, or guide users to clarify their rationale for deviations. Using semantic differencing and formal verification of bisimulation relations, SAFE-P will ensure that the scripts comply with SOPs and will highlight differences for the operators, so that they can double-check their work and confirm any deviations from standard procedures. SAFE-P's design will begin with relatively simple syntactic mechanisms to find differences between command sequences and textual procedures that can be applied directly to current flight control practices, including the use of SOPs captured in simple XML or PDF files and command scripts in ThinLayer. To reduce false error detection and assess the criticality of differences, we will incorporate knowledge of the space platform's architecture. For future missions, we will extend SAFE-P to richer languages (PRL, PLEXIL, SCL) and employ more complex verification of program-equivalence relationships (bisimulation) to ensure conformance between scripts and procedures.
Nonlinear Aerodynamic and Nonlinear Structures Interations (NANSI) Methodology for Ballute/Inflatable Aeroelasticity in Hypersonic Atmospheric Entry Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
ZONA proposes a phase II effort to fully develop a comprehensive methodology for aeroelastic predictions of the nonlinear aerodynamic/aerothermodynamic - structure interaction (NANSI) on ballutes during hypersonic atmospheric entry, including potential surface wrinkling. A time-accurate Boltzmann aerodynamic flow solver, called BGKX, will first be extended to 3D geometries for inviscid /viscous hypersonic flows. BGKX is a robust, unified-Mach-number, all-altitude, viscous flow solver; it provides pressure and heat flux solutions in one step. To handle the complex geometry of wrinkling ballutes, an advanced cartesian grid system, called gridless boundary condition cartesian (GBCC), will be implemented within BGKX. Next, generalized reduced order models (ROM) of the BGKX aerodynamics and nonlinear structures will be established to handle ballute wrinkling and the complex flow. In addition to Direct physical coupling of the aerodynamics and structures, an aerodynamic ROM - structures ROM coupling procedure will be fully developed for efficient aeroelastic applications to wrinkled ballutes. Lastly, we will evaluate the sensitivity of the ballute aeroelastic behavior in specific structural features: the pre-tensioning of the ballute, its inflation, and the existence of structural properties variations around its circumference. ZONA will work closely with the NASA monitor in phase II should an additional ballute configuration be considered.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The overall goal of this project is to design, develop, demonstrate, and deliver a miniature, variable speed control moment gyroscope (MVS CMG) for use on small satellites. Creare's MVS CMG has the potential to revolutionize the design and operation of small satellites (i.e., mass from less than 1 kg up to 500 kg). Currently available CMGs are too large and heavy, and miniature CMGs do not provide sufficient control authority for use on small satellites. This primarily results from the need to greatly increase the speed of rotation of the flywheel in order to reduce the flywheel size and mass. We will achieve this goal by making use of our unique, proprietary, space-qualified, high-speed (>100,000 RPM) motor technology to spin the flywheel at a speed 10 times faster than the only other known miniature CMG under development with comparable control authority. This will enable the fabrication of an MVS CMG with greatly improved performance and smaller size. Creare is particularly well qualified to lead this effort given our considerable and unique past experience in miniaturizing devices for use in important space missions, our firm's longevity, and the space-qualified fabrication facilities that we maintain.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
As manned missions to the moon and eventually Mars gain momentum, astronaut crews will be sent back to the deepest parts of space humans have ever traveled, and will continue deeper into space than ever before. Once outside the protection of the Earth's magnetic field, astronauts become fully exposed to an array of dangerous charged particles, both cosmic rays (CRs) and Solar Energetic Particles (SEPs). There exists a need to provide a comprehensive picture of the energetic charged particle environment within manned space vehicles to accurately measure and mitigate the crew's exposure to these hazardous radiations. Along with our partner, the University of New Hampshire (UNH), Aurora Flight Sciences proposes to develop a compact (low volume, mass and power) charged particle spectrometer for manned space vehicles based on heritage from similar spaceflight telescopes using Si solid state detectors and scintillators. The proposed instrument will be capable of detecting and identifying charged particles with single element resolution, performing on-board, real-time data reduction and providing rate and composition data over five to seven approximately logarithmically spaced energy intervals corresponding to ~10-200 MeV for protons, with integral measurements for higher energies.
A Super Cooled, Non-toxic, Non-flammable Phase Change Material Thermal Pack for Portable Life Support Systems Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The continuation of concept development and test of a water-based, advanced Phase Change Material (PCM) heat sink is proposed. Utilizing a novel material choice for both an expansion diaphragm and the PCM case itself, the PCM can accommodate both the expansion of the freezing water-based material and very low temperature of approximately -250F. The water-based PCM itself would be non-toxic and non-flammable, but additives will be included to preclude deterioration of wither the PCM container or the diaphragm material. The use of a water-based PCM gives the highest heat capacity for the mass. This is highly limited due to the needs for portability as required for an Extra-Vehicular Activity (EVA). The total heat capacity of an operational unit would be for 4 hour duration EVA use. Through a logical progression of tasks including concept of operation formulation, requirements formulation, concept design reviews and detail design reviews that include design and thermal analysis using Thermal Desktop<SUP>TM</SUP> models, this effort can progress from the TRL 3 achieved in Phase I to TRL 4-5. The team will continue development by designing a Variable Conductance Interface (VCI) for protecting water in the Liquid Cooling Garment (LCG) from freezing due to the temperature of the heat sink used by the PCM. The team will also develop system improvements identified during Phase I testing. The PCM will be tested to confirm heat input/temperature performance and cycling capability. The test bed will allow for accurate heat input knowledge, temperature monitoring and cycling capability. The results will be compared to the thermal model to ensure accurate prediction capability for the next phase unit and system implementation. The design description and test results would form the basis of the final report.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Space Micro proposes to build upon our existing space processing and hardening technologies and products e.g (Proton 200K), to research and develop reusable software for plug and play (PnP) for intelligent avionics and payload processing. This will leverage both AFRL and Space Micro R&amp;D to meet NASA's expanding reusable software needs. At the end of Phase 1 we will have demonstrated, both by analysis and limited lab testing of prototype PnP software, the technical feasibility.(TRL=3). In Phase 2 we will develop an engineering models of an avionics incorporating PnP reusable software, and demonstrate electrically and also in relevant ground-based test bed at NASA or AFRL.
High-Speed Scanning Interferometer Using CMOS Image Sensor and FPGA Based on Multi-Frequency Phase-Tracking Detection Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
In this SBIR, we propose a new type of laser interferometer engine for in-situ large optics inspection and metrology and supporting system platform. The proposed FPGA signal processing concept together with new generation high-speed CMOS image sensor enables high speed (> 1m/sec) and real-time continuous surface profiling with minimum local memory. This transforms the currently available laser interferometer into a sub-nanometer precision instrument with only minor modification while providing easy scalability for large optic surface testing and measurement capability simultaneously.