Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
NASA's Lunar and other future extraterrestrial outposts will be built for long duration missions that are likely to experience significant number of faults and degradations over its lifetime. Additionally, these systems will have a highly reconfigurable architecture and perform multimodal operation. Being a resource constrained environment, health management, troubleshooting, maintenance, and repair of the Lunar outpost poses formidable challenge. To address this challenge Qualtech Systems, Inc. proposes to automate a major part of the HM and recovery decision support systems through a TEAMS-based approach. The approach will provide the facility to develop on-the-fly reconfigurable diagnostic models that can be used to automatically update a TEAMS model upon configuration changes. Residual functional capability estimation techniques and automatic updating of diagnostic models based on current condition of components will be developed through this effort. Dynamic multiple fault diagnosis techniques will be used for enhancing the diagnostic accuracy obtained from TEAMS-based diagnosis. Such accuracy enhancement will greatly reduce the amount of human intervention required in troubleshooting of spurious faults, and faults that are isolated with a large ambiguity group. On the overall, the proposed effort will provide a solution for automating the HM related activities in highly reconfigurable systems with resource constraints.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The International X-Ray observatory (IXO) is due to be launched in 2021. The core of the instrument is a very large (3.2 meter diameter) Wolter I optic, to be assembled from approximately 13,000 individual elements. Each element will, in turn, be created by 'slumping' glass over a precision mandrel, of which there must be in excess of 700. In addition to the very large size of the mandrels (up to 1.6 meter radius), figure and size tolerances are exceedingly tight, ranging from 2 nanometers (axial figure) to 200 nanometers (radius variation). The combination of size, accuracies, production rate requirements and the number of individual component designs defy standard optical metrology techniques. While polishing equipment that can meet these tolerances exists, the polishers must be controlled by continuous or near continuous (process intermittent) feedback. In this effort we propose to develop a unique "point-defined" metrology instrument that can be incorporated into the polishing machine itself, to control the manufacturing process to the required levels of accuracy. In Phase 1 we will develop conceptual designs for both stand-alone and on-machine instrumentation. In Phase 2 we will develop a stand-alone metrology instrument, and in Phase 3 we will fully incorporate the technology onto a commercial polishing instrument.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Long-range optical telecommunications (LROT) impose challenging requirements on detector array sensitivity at 1064nm and arrays timing bandwidth. Large photonic arrays with integrated beam acquisition, tracking and/or communication capabilities, and smart pixel architecture should allow the implementation of more reliable and robust LROT systems. Integration of smart pixel technology for parallel data acquisition and processing is currently available in silicon. Current silicon photon-counting detector arrays benefit from a worldwide manufacturing and R&D infrastructure but their response at 1064nm is not suitable for LROT. In Phase I we proposed to verify the feasibility of increasing the responsivity of aPeak's silicon photon counting arrays at 1064nm by increasing their quantum absorption efficiency and demonstrating sub-nanosecond timing resolution. Phase I resulted in photon counting arrays with enhanced response at 1064 nm. Modules to be implemented into the readout IC (ROIC) have been fabricated in compact ASIC designs, suitable for integration into the smart pixel fabric they have demonstrated 100ps timing jitter and have exceeded the dynamic range requirements. Noise, timing resolution, and linearity requirements meet updated program requirements Phase II program builds upon Phase I results and previous smart pixel development at aPeak Inc with the aim to develop photon-counting arrays with enhanced 1064nm response and integrated counters at pixel level, capable of high - timing resolution and high counting rate. We propose to develop the photon counting detector arrays, associated ROIC arrays in ASIC, technology to assemble the detector and ROIC arrays, as well as in process ASIC mapping and maskless correction methods critical for the detector fabrication. Detector array design will be improved to meet the detection efficiency at 1064nm, while preserving or improving the detector noise, timing resolution, and linearity demonstrated in Phase I
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Spacecraft need accurate position and velocity estimates in order to control their orbits. Some missions require more accurate estimates than others, but nearly all missions need some type of orbit determination. IST-Rolla seeks to provide highly accurate algorithms that do not overpower the spacecraft's computer. Many new, powerful algorithms exist such as the particle filter and the unscented Kalman filter, but most of them involve integrating several state vectors, and those integrations devour the computing power available. IST-Rolla will implement the h-D technique, the cost based filter (CBF), and the neural network estimator for orbit determination(developed by IST-Rolla Engineers) and analyze the results. These filters are nonlinear and might provide better accuracy than the extended Kalman filter (EKF) which is widely used, without being computationally cumbersome as the particle filter and unscented Kalman filter. The theta-D technique approximates the solution to the filter-related Ricatti Equation. The CBF is an attempt to formulation of the filter under an 'optimal' framework. The neural network estimator works to estimate the modeling errors online so that the estimates become more accurate.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Effective methods for recovery and regeneration of cabin atmosphere to supply oxygen are critical to facilitate extended duration manned missions including expeditions to Mars or a return to the Moon. Currently, oxygen is recovered as water using the Sabatier reduction process. One of the by-products of this reaction is waste methane, which is vented into space. Lynntech proposes to reclaim the hydrogen from the methane by utilizing a low power, high efficiency, non-thermal plasma (NTP) process based on high frequency dielectric barrier discharge (HFDBD). The HFDBD is characterized by electrons and heavy particles being in thermodynamic non-equilibrium. The electron temperatures are near 10,000K, while the ions and neutrals species remain at ambient temperature. The high energy electrons have the potential to recover up to 75% of the hydrogen from methane. Since the majority of the electrical energy in the discharge is used to accelerate electrons rather than heat the plasma gas, Lynntech's process produces minimal soot. Hence, a complex filtration system to remove soot from the exhaust stream is not required. Recovery of hydrogen from methane minimizes the hydrogen resupply requirements and improves the efficiency of the Sabatier process by closing the mass loop of the reduction reaction.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The goal of this SBIR project is to develop a computational tool with unique predictive capabilities for the aerothermodynamic environment around ablation-cooled hypersonic re-entry vehicles. The framework for this tool will be developed such that all relevant models can be coupled to the LeMANS code for nonequilibrium hypersonic flows and the MOPAR code for ablation material response, both developed by the University of Michigan. In the proposed effort, the existing LeMANS-MOPAR framework will be enhanced by including innovative models for: (1) Non-equilibrium surface thermochemistry; (2) Non-equilibrium pyrolysis chemistry; (3) Radiation transfer in media with orders of magnitude variation in optical thickness; and (4) Spallation. The proposed tool is comprehensive and unique because all important phenomena will be modeled, with the software framework enabling coupling between the various components. The Phase I focus will be to: (1) Develop a module for the Modified Differential Approximation (MDA) to solve the radiative transfer equation; (2) Develop a framework for coupling the MDA module to LeMANS-MOPAR; and (3) Demonstrate the coupled framework for cases such as the Stardust re-entry. In Phase II, the tool will be made comprehensive by implementing important models identified above, including advanced non-equilibrium, non-gray radiation model. The tool will be validated and applied to re-entry ablation flows relevant to NASA. We will team with an ablative material OEM and a CFD software vendor to transition the technology to industry.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
NASA has been tasked to develop new and advanced capabilities to support both future manned and robotic missions to the lunar and Martian surfaces. It is the purpose of this program to develop advanced avionics, software, and information technologies for exploration missions. In particular, NASA is concerned with the extreme radiation present on the lunar surface, Martian surface, and in deep space. Spacecraft electronics will need to be radiation hardened against a TID of 100 krads (Si) or more and provide SEL immunity of 100 MeV cm2/mg or greater. Furthermore, electronics in these environments are also subjected to multiple thermal-cycling and wide temperature ranges. Our innovation provides solutions for the mitigation of radiation effects on reprogrammable SRAM-based FPGA processor elements through the use of an advanced foundry process combined with innovative and RHBD methods to mitigate total ionizing dose and provide SEL immunity, and SEU tolerance. These techniques will be utilized to develop a prototype of radiation hardened, reprogrammable FPGA that will be fabricated and tested, suitable for consideration in future NASA Flagship programs.
Small, Light-Weight Pump Technology for On-Board Pressurization of Propellants in a Mars Ascent Vehicle Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
To-date, the realization of high-performance liquid bipropellant rocket engines in the micro-scale has largely been hindered by the inability to obtain "on-board" pressurization through a light-weight and low-complexity pump. Ventions seeks to fulfill this critical need by proposing the development of a low-risk pump that can be batch fabricated in a low-cost manner to provide significant performance improvements for a Mars Ascent Vehicle and other spacecraft.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Lightweight, high performance thermal insulation is critical to NASA's next generation Exploration spacecraft. Zero or low cryogenic propellant boiloff is required during extended missions and lengthy on-orbit times. Heat flow through multilayer insulation is usually the largest heat leak in cryogenic systems, so improvements are desirable. Load Responsive Multi-Layer Insulation (LRMLI) is an innovative new technology using micro-molded polymer dynamic spacers that provide high performance insulation both in-atmosphere and on-orbit. LRMLI under atmospheric pressure compresses dynamic spacers to support an integrated, thin vacuum shell for high performance in-atmosphere operation, and disconnects the spacers during on-orbit/lunar surface operation to reduce heat leak and provide ultra-high performance thermal insulation. LRMLI was successfully proven feasible in Phase I work, reaching TRL4. A LRMLI prototype was built and tested and a 3-layer, 0.25" thick blanket demonstrated 7.1 W/m2 (0.19 mW/m-K) heat leak for on-orbit and 14.3 W/m2 (0.34 mW/m-K) for in-atmosphere operation. Equal heat leak on-orbit of a 0.25" LRMLI blanket (2.1 kg/m2) would require 16" of SOFI (15 kg/m2), with LRMLI having a 64X advantage in thickness and a 7X advantage in mass. LRMLI insulation can provide superior cryogen insulation during ground hold, launch and on-orbit/vacuum conditions without need for purge. Total heat gain into cryogenic systems could be substantially reduced. Terrestrial non-NASA applications include LH2 powered aircraft and cars in development. This proposal is to further develop LRMLI toward commercialization. Tasks proposed include a study of both NASA& non-NASA applications to select two for further optimization, next generation design of dynamic spacers and modular vacuum shells, and building and testing prototypes in realistic environments such as a 3' diameter cryotank similar to a selected use like NASA Altair or Boeing HALE tanks.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Typical communication satellites use traditional waveguide front-end architectures due to the excellent electrical performance and high reliability. While the systems offer excellent performance and reliability they are large and heavy due to incorporation of waveguide-based switches, diplexers, and waveguide packaged solid-state power amplifiers. Replacement of the waveguide components by micromachined parts that provide significant size, weight, and cost reduction without substantially affecting the electrical performance, can lead to a breakthrough in wireless communications. During the Phase I program, Nuvotronics utilized its proprietary PolyStrataTM metal micromachining process to create X and Ka band filters with state-of-the-art performance. During Phase II, tunable filters will be fabricated using the PolyStrata process and tuned using reliable and low actuation voltage MEMS devices. The filters will be designed and tested for space operation and have immediate applications in the Deep Space Network communications system. The PolyStrata process is capable of producing high Q, low weight and therefore compact filters. The PolyStrata process is a new multi-layer technology that creates high quality air loaded copper microdevices. High quality cavity resonator filters can be fabricated using this high precision micro-fabrication process, enabling very high Q filters while being compact, surface mountable and compatible with the integration of active chips.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
This Small Business Innovation Research (SBIR) Phase I project, which will conclude with a Technical Readiness Level of 3-4, will demonstrate the feasibility of the Componentized Models as a Service (CMaaS) system, a web-centric software service architecture that will dramatically improve the manner in which NASA's modeling assets are developed, deployed and used. Under this service architecture, models will be exposed as web services that are fully configurable and executable from a browser. Moreover, the software components from which models are comprised will be published as "pluggable" service modules that can be discovered and incorporated into a model at runtime via a novel dynamic build mechanism. Importantly, existing models and components will require little to no modification to be deployed on the service. The project will leverage technologies developed for the Frontier Dashboard, an extant browser interface to and supporting framework for Parabon's commercial grid computing service. Constructed with Google<SUP>TM</SUP> Web Toolkit (GWT) components, the Frontier Dashboard provides end users with a rich browser interface for managing large-scale computational jobs. Moreover, it provides developers pre-built mechanisms for user authentication and authorization, account management, and accounting, which greatly eases the burdens of creating web service applications.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
NextGen will require the development of novel solutions to shape the airspace of tomorrow. Along with the ability to generate new systems and technologies comes the need to rigorously evaluate, and eventually validate, the effectiveness of these concepts. However, it is often challenging to translate simulation data into useful, integrated, and contextually-based assessments. Many critical findings are not identified for this reason, which could otherwise guide researchers toward advancements with NextGen technologies. Aptima proposes to develop the Use-driven Testbed for Evaluating Systems and Technologies (U-TEST), a flexible toolset that helps NextGen researchers to efficiently extract findings on pilot performance in simulated flight environments. Three primary components are: (1) context-capturing software will guide researchers to key events and allow important contextual information to be gathered for analysis; (2) a data integration platform that will automate organization of data sources into a format conducive to analysis; and (3) context-based analysis software that will enable deep, focused analysis by combining a quick-look function, an algorithm for focusing analysis, and context-based playback of key events and trials. U-TEST will be an extensible toolset that can help NextGen researchers improve the amount and quality of findings across a range of studies.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Bear Engineering proposes to develop an innovative high torque, low speed, direct drive motor in order to meet NASA's requirements for such devices. Fundamentally, all electric motors basically work on the same electromagnetic principle: a tangential electromagnetic force attracts the rotor to the stator. Just when the rotor field is closest to the stator field and the electromagnetic attraction is greatest, the power is interrupted and another set of magnetic poles repeats the cycle. Furthermore, the two magnetically attracted elements never make contact, which would otherwise offer the highest force of attraction. The proposed novel motor design operates and behaves entirely differently from all other known electric motor designs and it will produce incredibly high, direct drive torques at low rotational speeds. Its operational performance is similar to that of a stepper motor with a 1000:1 gearhead attached, but the similarity ends there. The motor is configured such that its length to diameter aspect ratio is opposite that of traditional motors as it has a relatively large diameter and short axial length; this offers all new packaging opportunities. The proposed design also allows for a single, large diameter bearing pair to be used for the motor's output shaft which renders it stiff enough to directly mount the driven elements. The need for additional bearing supports and bearing mounting structure is thus eliminated. At the end of the proposed Phase 1 effort, the motor design will be at TRL 4 and by the end of a potential Phase 2, the system will be at TRL 6.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The Lunar Soil Particle Separator (LSPS) is an innovative method to beneficiate soil prior to in-situ resource utilization (ISRU). The LSPS can improve ISRU oxygen yield by boosting the concentration of ilmenite or other iron-oxide bearing materials found in lunar soils. This can substantially reduce hydrogen reduction reactor size and drastically decrease the power input required for soil heating. LSPS particle size separations can be performed to de-dust regolith and to improve ISRU reactor flow dynamics. LSPS mineral separations can be used to alter the sintering characteristics of lunar soil. The LSPS can also 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 electrostatic separations. The LSPS centrifugal separation method overcomes the reduced efficiency of conventional particle sieving in reduced gravity. The 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 wide regions on the Moon. The LSPS is scalable and is amenable to testing and development in vacuum and reduced gravity.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Future space telescopes such as the Super Nova Acceleration Probe (SNAP) require exceptionally reflective coatings applied to mirrors several meters in diameter. In 2007, Surface Optics Corporation (SOC) applied a protected silver coating to the Kepler Space telescope's 1.4-m primary mirror. Although SOC's coating design met the reflectance requirements for Kepler, the protective layers absorb too much energy in the UV and visible spectral regions to meet SNAP's science objectives. In this research, SOC will improve the spectra performance of its current protected silver coating, by modifying the protection chemistry, as well as, the deposition process. SOC's silver coating design is based on a protection recipe patented by Lawrence Livermore National Laboratory (LLNL). Recent SOC IRAD results showed that significant modifications to the basic LLNL protection scheme are possible, without sacrificing coating durability. In Phase I, a variety of protective compounds will be fabricated by an ion-assisted evaporation process and optimized for their protective properties, adhesion characteristics, and effect on coating reflectivity. In addition, SOC will create a more precise method to deposit protective NiCrNx atomic clusters, which are a critical element of LLNL's silver protection recipe. By modifying SOC's evaporation system and monitoring process, it is expected the necessary volume of these highly absorbing clusters may be reduced by a factor of 2, while still providing adequate engineering margin to insure durability. These modifications will significantly improve coating reflectance in the UV and visible spectral regions. In Phase II, scale-up issues will be addressed and the improved silver coating process will be applied to a 2.2-m mirror substrate in SOC's 3.3-meter vacuum coating chamber.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
While conventional injection seeding sources (such as DFB diode lasers and rare-earth doped solid-state microchip lasers) are available at 1.5 microns, these sources typically lack the ultra-narrow (<50 kHz), ultra-stable output spectrum required for use in applications such as Doppler shift measurements of the tropospheric winds. Furthermore, similar sources which operate at 2.0 microns (a preferred wavelength for space-based atmospheric measurements) are simply unavailable.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
As minimum cost will be required for a dedicated NanoSat Launch Vehicle, a series and parallel staged, highly modular vehicle architecture is proposed for design exploration. The principal advantage of a modular architecture on this size vehicle is a single propulsion development at a relatively small scale which drastically shortens development timelines and cost. A candidate launch vehicle could use 7 modules for the first stage, 4 for the second, 2 for the third, and 1 for the fourth. Whittinghill Aerospace proposes to investigate many modular designs for 3, 4, and 5 stage vehicles of different (solid, liquid, and hybrid) propellant types. Structural, aerodynamic, propulsion, and control configurations of vehicles will be optimized and "flown" with a trajectory tool to evaluate performance. After trades and analyses are completed and designs ranked, the resulting optimum module size will then be built and tested at an anticipated 1 to 3Klb thrust level. At the conclusion of Phase 1, the technology will be ready for flight development and will be at a TRL level of 5. At the end of Phase 2, a full-scale, 2-stage sub-orbital modular vehicle will have flown.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Silver coatings for optics greater than 2-meters in diameter are sought by NASA for future space telescope systems. In the Phase I research, Surface Optics Corporation (SOC) investigated several new coating systems for protecting silver. The new coating designs are derivations based on a patented coating design created at Lawrence Livermore National Laboratory (LLNL). The new designs improve the coating's reflectance performance, particularly in the UV region, while maintaining stability in humid and/or corrosive environments. In addition, SOC devised and installed a new piece of coating equipment, which improves the ability to apply exceptionally thin protective layers, by better monitoring the shape of the evaporation plume.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
In support of NASA Aeronautics Research Mission Directorate and Aviation Safety Mission, NanoSonic has developed a series of moisture and corrosion mitigating, ultra-hydrophobic, environmentally tunable, nanophase separating adhesive modifiers and complementary high performance, wide service temperature range (-60&#61616;C to 450&#61616;C) structural adhesives. The smart nanostructured modifiers represent a significant discovery as the adhesion strength of our novel and commercial-off-the-shelf aerospace adhesives was increased by > 40% with inclusion of such systems upon aging in 100% relative humidity (RH), ten days, 140&#61616;F. Of significant importance to manufacturability and dual-use commercialization, the novel modifying agents are inert, inorganic-organic, halogenated hybrid copolymers, and hence can be used with virtually any adhesive, paint or environmental aerospace materials systems. The inorganic poly(octahedral silsesquioxane) (POSS), fluorination and copolymer molecular weight can be synthetically engineered to complement any paste of film adhesive. The TRL of the novel adhesive system would be increased from 6-8 during Phase II.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
The early lunar network communications involves the use of a variety of communication channels and networks such as IEEE 802.16, Ka-Band and S-Band satellite data-links. The sophisticated environment casts a major challenge to provide a reliable network communications supporting the performance of lunar missions. In addition, the delivery of a higher Quality of Service (QoS) is not only stifled by the network segmentation but also greatly influenced by the potential data-link disruption. AGNC proposes the Reconfigurable Robust Routing for Mobile Outreach Network (R3MOON) implemented on its existing Service Oriented P2P Middleware. By adopting effective cross-layered network management strategies and routing algorithms in the underlying middleware, R3MOON greatly mitigates many network concerns and transforms the lunar communications from the maintenance of lower level data-link to the performance of higher level applications. Phase I is devoted to the R3MOON design validation and early prototype. Phase II will result in development of a fully functional prototype.
Integration of an Advanced Cryogenic Electric Propulsion System (ACEPS) to Aerodynamically Efficient Subsonic Transport Aircraft Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
This proposal defines innovative aerodynamic concepts and technology goals aimed at vehicle efficiency for future subsonic aircraft in the 2020 ? 2030 timeframe. Noise, emissions and fuel burn are all vehicle efficiency concerns which can be addressed by aerodynamic concepts either on the component, subsystem, or aircraft design system level. In line with the NASA, an assumption is made that by 2025, higher air traffic demand (2-3 times the 2004 level) will require a significant increase in airport throughput, improved air traffic control procedures, and a significant decrease in noise. Empirical Systems Aerospace (ESAero) has a design and analysis team to address high risk/high pay-off technologies on the aircraft aerodynamics concept level and airframe/propulsion integration to dramatically reduce noise, pollution, and fuel burn in the 2020-2030 timeframe. The key technology for these breakthroughs is the use of an advanced cryogenically-cooled electric propulsion system installed in advanced unconventional aircraft configurations. An important feature of this study is to understand and evaluate the impact of this propulsion system on the design and aerodynamic performance of the total aircraft. In addition, ESAero will examine the applicability of STOL performance to potential improvements in airport throughput using multiple configuration and aerodynamic performance concepts.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
AM Biotechnologies (AM) in partnership with Sandia National Laboratories will develop a Thioaptamer Diagnostic System (TDS) in response to Topic X10.01 Reusable Diagnostic Lab Technology. The TDS will quickly quantify clinically relevant biomarkers in flight using only microliters of virtually any complex sample. The system combines ambient-stable, long-shelf-life affinity agent assays with a handheld microfluidic gel electrophoresis affinity assay quantification technology. The system is easy to use, compatible with operation in microgravity, and designed to permit simultaneous quantification of 32 or more biomarkers from a single astronaut sample. Phase 1 of this project demonstrated that a thioaptamer assay used in the microfluidic instrument can quantify a specific biomarker in serum in the low nanomolar range. AM also successfully identified novel affinity agents to bone specific alkaline phosphatase (BAP) and demonstrated their use to detect BAP using the microfluidic instrument. Phase 2 will expand the number of ambient stable affinity agents and demonstrate a TDS prototype to NASA. AM anticipates that the TDS at the end of Phase 2 will be at TRL 4 to 5. In Phase 3, AM and Sandia will produce flight units for NASA research use on the International Space Station (ISS) as well as for diagnostic use on future long duration missions.
Algorithm Design and Validation for Adaptive Nonlinear Control Enhancement (ADVANCE) Technology Development for Resilient Flight Control Project
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
SSCI proposes to develop and test a framework referred to as the ADVANCE (Algorithm Design and Validation for Adaptive Nonlinear Control Enhancement), within which we plan to perform a comparison study of the state-of-the-art adaptive flight control algorithms on two challenging testbeds: (i) a small tailsitter unmanned aerial vehicle that is characterized by highly uncertain nonlinear dynamics, and (ii) F/A-18 aircraft under wing damage. The results of this study should give rise to a set of recommendations and guidelines regarding the use, tuning and implementation of different advanced nonlinear adaptive control algorithms to problems in flight control in the presence of large modeling uncertainties. Based on this study, we also propose to develop the ADVANCE algorithms and techniques as the most suitable combination of those that represent the state-of-the-art in nonlinear adaptive flight control. This combination will focus on retaining the most favorable features of the existing algorithms, while minimizing their disadvantages and unfavorable interactions. Specific Phase I tasks will include: (i) Problem formulation; (ii) Testbed modeling and simulation development; (iii) Simulation testing of flight control algorithms; (iv) Performance evaluation & trade study. Phase II will include further enhancement and development of the proposed ADVANCE algorithms and comprehensive testing of methods of interest through pilot-in-the-loop simulations of F/A-18 aircraft, and flight testing of the tailsitter UAV. Massachusetts Institute of Technology (Prof. Jonathan How) and Boeing Phantom Works (James Urnes, Sr.) will provide technical support under the project.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
Thin film Metal RubberTM sensor appliqus have the potential to reduce the time, complexity and cost of measuring air flow-induced skin friction during the development of rotary wing and fixed wing aircraft and related systems. Metal Rubber<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Strict//EN" "http://www.w3.org/TR/xhtml1/DTD/xhtml1-strict.dtd"> <sup>TM</sup> skin friction sensor appliqus allow near real-time detection 2D mapping of air flow conditions over surfaces of air vehicles. This is important for analysis of laminar to turbulent flow transitions, flow separation and reattachment mechanisms, and other instabilities, during rotor blade and fuselage design, blade tracking adjustments, and active flight control. The sensors act as mechano-electrical transducers to convert air flow-induced tangential surface forces into electrical output signals. They are thin and surface-mounted so cause minimal interaction with the flow, are easy to apply as an appliqu, and require no cavities or recesses other than holes to connect the sensor leads to data acquisition wiring. The material is resistant to normal aircraft fluids and solvents, can operate over a temperature range of -65 to +150C, and is capable of withstanding moderate rain and dust erosion. During Phase II, NanoSonic will Develop an improved understanding of the operation of thin film Metal RubberTM skin friction sensors, Standardize sensor design and sensor fabrication processes, Develop a method to calibrate sensor elements as part of manufacturing, Develop a means to compensate for cross-sensitivity effects, Develop and optimize means for data acquisition, Use developed sensors in cooperation with the NASA LaRC Subsonic Rotary Wing program to investigate rotorcraft research and development problems, and Use and demonstrate the sensors in cooperation industry and academic colleagues. The significance of the proposed NASA Phase II SBIR program is in transitioning these sensors from analytical and FEM modeling to commercial products for experimental use by NASA and industry.
Published By National Aeronautics and Space Administration
Issued over 9 years ago
Summary
Description
To address the NASA/ARC need for wireless networking technologies for small launch vehicles, Broadata Communications, Inc. proposes to develop a new Small Space Platform Internet Protocol (SSP-IP) Stack with Space-Enhanced TCP and devices to achieve high performance networking, despite typical space link problems and footprint constraints. BCI's approach incorporates advanced Space IP network measurements and their application in small embeddedable TCP. Our SSP-IP stack offers Internet-based protocols that provide seamless network command and control continuity between terrestrial and space-based platforms as well as networked operations of distributed ground stations. NASA will benefit from our SSP-IP by increasing simplicity of seamless network transmission and lowering cost. In Phase I BCI will demonstrate the feasibility of using SSP TCP to reliably transmit space imagery from a Nanosat launching vehicle by building, testing and integrating with hardware a preliminary version, which will demonstrate a TRL-level 3 by the end of Phase I. In Phase II, BCI plans to develop a fully functional prototype and demonstrate the low complexity and embeddability to NASA's platform with high performance. The demonstrated results will offer NASA capabilities to use our reliable SSP TCP in future ground and spacecraft operations, increasing efficiency and saving money.