PROTEUS-SN User Manual

DOE Office of Scientific and Technical Information (OSTI.GOV)

Shemon, Emily R.; Smith, Micheal A.; Lee, Changho

2016-02-16

PROTEUS-SN is a three-dimensional, highly scalable, high-fidelity neutron transport code developed at Argonne National Laboratory. The code is applicable to all spectrum reactor transport calculations, particularly those in which a high degree of fidelity is needed either to represent spatial detail or to resolve solution gradients. PROTEUS-SN solves the second order formulation of the transport equation using the continuous Galerkin finite element method in space, the discrete ordinates approximation in angle, and the multigroup approximation in energy. PROTEUS-SN’s parallel methodology permits the efficient decomposition of the problem by both space and angle, permitting large problems to run efficiently on hundredsmore » of thousands of cores. PROTEUS-SN can also be used in serial or on smaller compute clusters (10’s to 100’s of cores) for smaller homogenized problems, although it is generally more computationally expensive than traditional homogenized methodology codes. PROTEUS-SN has been used to model partially homogenized systems, where regions of interest are represented explicitly and other regions are homogenized to reduce the problem size and required computational resources. PROTEUS-SN solves forward and adjoint eigenvalue problems and permits both neutron upscattering and downscattering. An adiabatic kinetics option has recently been included for performing simple time-dependent calculations in addition to standard steady state calculations. PROTEUS-SN handles void and reflective boundary conditions. Multigroup cross sections can be generated externally using the MC2-3 fast reactor multigroup cross section generation code or internally using the cross section application programming interface (API) which can treat the subgroup or resonance table libraries. PROTEUS-SN is written in Fortran 90 and also includes C preprocessor definitions. The code links against the PETSc, METIS, HDF5, and MPICH libraries. It optionally links against the MOAB library and is a part of the SHARP multi-physics suite for coupled multi-physics analysis of nuclear reactors. This user manual describes how to set up a neutron transport simulation with the PROTEUS-SN code. A companion methodology manual describes the theory and algorithms within PROTEUS-SN.« less

An Update on Improvements to NiCE Support for PROTEUS

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bennett, Andrew; McCaskey, Alexander J.; Billings, Jay Jay

2015-09-01

The Department of Energy Office of Nuclear Energy's Nuclear Energy Advanced Modeling and Simulation (NEAMS) program has supported the development of the NEAMS Integrated Computational Environment (NiCE), a modeling and simulation workflow environment that provides services and plugins to facilitate tasks such as code execution, model input construction, visualization, and data analysis. This report details the development of workflows for the reactor core neutronics application, PROTEUS. This advanced neutronics application (primarily developed at Argonne National Laboratory) aims to improve nuclear reactor design and analysis by providing an extensible and massively parallel, finite-element solver for current and advanced reactor fuel neutronicsmore » modeling. The integration of PROTEUS-specific tools into NiCE is intended to make the advanced capabilities that PROTEUS provides more accessible to the nuclear energy research and development community. This report will detail the work done to improve existing PROTEUS workflow support in NiCE. We will demonstrate and discuss these improvements, including the development of flexible IO services, an improved interface for input generation, and the addition of advanced Fortran development tools natively in the platform.« less

Warthog: Coupling Status Update

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hart, Shane W. D.; Reardon, Bradley T.

The Warthog code was developed to couple codes that are developed in both the Multi-Physics Object-Oriented Simulation Environment (MOOSE) from Idaho National Laboratory (INL) and SHARP from Argonne National Laboratory (ANL). The initial phase of this work, focused on coupling the neutronics code PROTEUS with the fuel performance code BISON. The main technical challenge involves mapping the power density solution determined by PROTEUS to the fuel in BISON. This presents a challenge since PROTEUS uses the MOAB mesh format, but BISON, like all other MOOSE codes, uses the libMesh format. When coupling the different codes, one must consider that Warthogmore » is a light-weight MOOSE-based program that uses the Data Transfer Kit (DTK) to transfer data between the various mesh types. Users set up inputs for the codes they want to run, and then Warthog transfers the data between them. Currently Warthog supports XSProc from SCALE or the Sub-Group Application Programming Interface (SGAPI) in PROTEUS for generating cross sections. It supports arbitrary geometries using PROTEUS and BISON. DTK will transfer power densities and temperatures between the codes where the domains overlap. In the past fiscal year (FY), much work has gone into demonstrating two-way coupling for simple pin cells of various materials. XSProc was used to calculate the cross sections, which were then passed to PROTEUS in an external file. PROTEUS calculates the fission/power density, and Warthog uses DTK to pass this information to BISON, where it is used as the heat source. BISON then calculates the temperature profile of the pin cell and sends it back to XSProc to obtain the temperature corrected cross sections. This process is repeated until the convergence criteria (tolerance on BISON solve, or number of time steps) is reached. Models have been constructed and run for both uranium oxide and uranium silicide fuels. These models demonstrate a clear difference in power shape that is not accounted for in a stand-alone BISON run. Future work involves improving the user interface (UI), likely through integration with the Nuclear Energy Advanced Modeling and Simulation (NEAMS) Workbench. Furthermore, automating the input creation would ease the user experience. The next priority is to continue coupling the work with other codes in the SHARP package. Efforts on other projects include work to couple the Nek5000 thermo-hydraulics code to MOOSE, but this is in the preliminary stages.« less

Status Report on NEAMS PROTEUS/ORIGEN Integration

DOE Office of Scientific and Technical Information (OSTI.GOV)

Wieselquist, William A

2016-02-18

The US Department of Energy’s Nuclear Energy Advanced Modeling and Simulation (NEAMS) Program has contributed significantly to the development of the PROTEUS neutron transport code at Argonne National Laboratory and to the Oak Ridge Isotope Generation and Depletion Code (ORIGEN) depletion/decay code at Oak Ridge National Laboratory. PROTEUS’s key capability is the efficient and scalable (up to hundreds of thousands of cores) neutron transport solver on general, unstructured, three-dimensional finite-element-type meshes. The scalability and mesh generality enable the transfer of neutron and power distributions to other codes in the NEAMS toolkit for advanced multiphysics analysis. Recently, ORIGEN has received considerablemore » modernization to provide the high-performance depletion/decay capability within the NEAMS toolkit. This work presents a description of the initial integration of ORIGEN in PROTEUS, mainly performed during FY 2015, with minor updates in FY 2016.« less

Cooperative Collision Avoidance Technology Demonstration Data Analysis Report

NASA Technical Reports Server (NTRS)

2007-01-01

This report details the National Aeronautics and Space Administration (NASA) Access 5 Project Office Cooperative Collision Avoidance (CCA) Technology Demonstration for unmanned aircraft systems (UAS) conducted from 21 to 28 September 2005. The test platform chosen for the demonstration was the Proteus Optionally Piloted Vehicle operated by Scaled Composites, LLC, flown out of the Mojave Airport, Mojave, CA. A single intruder aircraft, a NASA Gulf stream III, was used during the demonstration to execute a series of near-collision encounter scenarios. Both aircraft were equipped with Traffic Alert and Collision Avoidance System-II (TCAS-II) and Automatic Dependent Surveillance Broadcast (ADS-B) systems. The objective of this demonstration was to collect flight data to support validation efforts for the Access 5 CCA Work Package Performance Simulation and Systems Integration Laboratory (SIL). Correlation of the flight data with results obtained from the performance simulation serves as the basis for the simulation validation. A similar effort uses the flight data to validate the SIL architecture that contains the same sensor hardware that was used during the flight demonstration.

HTR-PROTEUS PEBBLE BED EXPERIMENTAL PROGRAM CORE 4: RANDOM PACKING WITH A 1:1 MODERATOR-TO-FUEL PEBBLE RATIO

DOE Office of Scientific and Technical Information (OSTI.GOV)

John D. Bess; Leland M. Montierth

2013-03-01

In its deployment as a pebble bed reactor (PBR) critical facility from 1992 to 1996, the PROTEUS facility was designated as HTR-PROTEUS. This experimental program was performed as part of an International Atomic Energy Agency (IAEA) Coordinated Research Project (CRP) on the Validation of Safety Related Physics Calculations for Low Enriched HTGRs. Within this project, critical experiments were conducted for graphite moderated LEU systems to determine core reactivity, flux and power profiles, reaction-rate ratios, the worth of control rods, both in-core and reflector based, the worth of burnable poisons, kinetic parameters, and the effects of moisture ingress on these parameters.more » One benchmark experiment was evaluated in this report: Core 4. Core 4 represents the only configuration with random pebble packing in the HTR-PROTEUS series of experiments, and has a moderator-to-fuel pebble ratio of 1:1. Three random configurations were performed. The initial configuration, Core 4.1, was rejected because the method for pebble loading, separate delivery tubes for the moderator and fuel pebbles, may not have been completely random; this core loading was rejected by the experimenters. Cores 4.2 and 4.3 were loaded using a single delivery tube, eliminating the possibility for systematic ordering effects. The second and third cores differed slightly in the quantity of pebbles loaded (40 each of moderator and fuel pebbles), stacked height of the pebbles in the core cavity (0.02 m), withdrawn distance of the stainless steel control rods (20 mm), and withdrawn distance of the autorod (30 mm). The 34 coolant channels in the upper axial reflector and the 33 coolant channels in the lower axial reflector were open. Additionally, the axial graphite fillers used in all other HTR-PROTEUS configurations to create a 12-sided core cavity were not used in the randomly packed cores. Instead, graphite fillers were placed on the cavity floor, creating a funnel-like base, to discourage ordering effects during pebble loading. Core 4 was determined to be acceptable benchmark experiment.« less

HTR-proteus pebble bed experimental program core 4: random packing with a 1:1 moderator-to-fuel pebble ratio

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bess, John D.; Montierth, Leland M.; Sterbentz, James W.

2014-03-01

In its deployment as a pebble bed reactor (PBR) critical facility from 1992 to 1996, the PROTEUS facility was designated as HTR-PROTEUS. This experimental program was performed as part of an International Atomic Energy Agency (IAEA) Coordinated Research Project (CRP) on the Validation of Safety Related Physics Calculations for Low Enriched HTGRs. Within this project, critical experiments were conducted for graphite moderated LEU systems to determine core reactivity, flux and power profiles, reaction-rate ratios, the worth of control rods, both in-core and reflector based, the worth of burnable poisons, kinetic parameters, and the effects of moisture ingress on these parameters.more » One benchmark experiment was evaluated in this report: Core 4. Core 4 represents the only configuration with random pebble packing in the HTR-PROTEUS series of experiments, and has a moderator-to-fuel pebble ratio of 1:1. Three random configurations were performed. The initial configuration, Core 4.1, was rejected because the method for pebble loading, separate delivery tubes for the moderator and fuel pebbles, may not have been completely random; this core loading was rejected by the experimenters. Cores 4.2 and 4.3 were loaded using a single delivery tube, eliminating the possibility for systematic ordering effects. The second and third cores differed slightly in the quantity of pebbles loaded (40 each of moderator and fuel pebbles), stacked height of the pebbles in the core cavity (0.02 m), withdrawn distance of the stainless steel control rods (20 mm), and withdrawn distance of the autorod (30 mm). The 34 coolant channels in the upper axial reflector and the 33 coolant channels in the lower axial reflector were open. Additionally, the axial graphite fillers used in all other HTR-PROTEUS configurations to create a 12-sided core cavity were not used in the randomly packed cores. Instead, graphite fillers were placed on the cavity floor, creating a funnel-like base, to discourage ordering effects during pebble loading. Core 4 was determined to be acceptable benchmark experiment.« less

Use of MicroMaps for Satellite Validation and Potential UAV Applications

NASA Astrophysics Data System (ADS)

Connors, V. S.; Sachse, G. W.; Hopkins, P. E.; Morrow, W.; McMillan, W. W.

2005-12-01

The MicroMAPS instrument is a nadir-viewing, gas filter-correlated radiometer which operates in the 4.67 micrometer fundamental band of carbon monoxide. Originally designed and built for a space mission, this CO remote sensor is being flown in support of satellite validation and science instrument demonstrations for potential UAV applications. The MicroMAPS CO instrument was flown for the first time during the Summer-Fall 2004 on-board the Proteus aircraft, which is owned and operated by Scaled Composites, in Mojave, CA. The insturment system, flown on Proteus, was designed by a student team as a senior design project in the Aerospace Engineering Department, Virginia Tech, in Blacksburg, VA. This proposed design was reviewed and revised by Systems Engineers at NASA Langley; the final instrument system was integrated and tested at NASA LaRC in partnership with Scaled Composites and Virginia Space Grant Consortium, which supervised the fabrication of the nacelle which housed the instrument system on the right rear tail boom of Proteus. Full system integration and flight testing was performed at Scaled Composites, in Mojave, in June 2004. Its successful performance enabled participation in three international science missions: INTEX -NA over eastern North America in July 2004, ADRIEX over the Mediterranean region and EAQUATE over the United Kingdom region in September 2004, piggy-backing with the IPO-sponsored payload flown on Proteus. These flights resulted in nearly 100 hours of science measurements and in-flight calibrations. In parallel with the engineering devlopments, theoretical radiative transfer models were developed specifically for the MicroMAPS instrument system at the University of Virginia, Aerospace and Mechanical Engineering Department by a combined undergraduate and graduate student team. With techical support from Resonance Ltd. In June 2005, in Barrie, Canada, the MicroMAPS instrument was calibrated for the conditions underwhich the Summer-Fall 2004 flights occurred. The analyses of the calibration data, combined with the theoretical radiative transfer models, will provide the first data reduction for the science flights. These early results and comparisons with profile data from the NASA DC-8 and the coincident AIRS CO retrievals will be presented.

Proteus mirabilis RMS 203 as a new representative of the O13 Proteus serogroup.

PubMed

Palusiak, Agata; Siwińska, Małgorzata; Zabłotni, Agnieszka

2015-01-01

The unique feature of some Proteus O-polysaccharides is occurrence of an amide of galacturonic acid with N(ε)-[(S/R)-1-Carboxyethyl]-L-lysine, GalA6(2S,8S/R-AlaLys). The results of the serological studies presented here, with reference to known O-antigens structures suggest that GalA6(2S,8S/R-AlaLys) or 2S,8R-AlaLys contribute to cross-reactions of O13 Proteus antisera, and Proteeae LPSs. It was also revealed that the Proteus mirabilis RMS 203 strain can be classified into the O13 serogroup, represented so far by two strains: Proteus mirabilis 26/57 and Proteus vulgaris 8344. The O13 LPS is a serologically important antigen with a fragment common to LPSs of different species in the Proteeae tribe.

Reanalysis of the gas-cooled fast reactor experiments at the zero power facility proteus - Spectral indices

DOE Office of Scientific and Technical Information (OSTI.GOV)

Perret, G.; Pattupara, R. M.; Girardin, G.

2012-07-01

The gas-cooled fast reactor (GCFR) concept was investigated experimentally in the PROTEUS zero power facility at the Paul Scherrer Inst. during the 1970's. The experimental program was aimed at neutronics studies specific to the GCFR and at the validation of nuclear data in fast spectra. A significant part of the program used thorium oxide and thorium metal fuel either distributed quasi-homogeneously in the reference PuO{sub 2}/UO{sub 2} lattice or introduced in the form of radial and axial blanket zones. Experimental results obtained at the time are still of high relevance in view of the current consideration of the Gas-cooled Fastmore » Reactor (GFR) as a Generation-IV nuclear system, as also of the renewed interest in the thorium cycle. In this context, some of the experiments have been modeled with modern Monte Carlo codes to better account for the complex PROTEUS whole-reactor geometry and to allow validating recent continuous neutron cross-section libraries. As a first step, the MCNPX model was used to test the JEFF-3.1, JEFF-3.1.1, ENDF/B-VII.0 and JENDL-3.3 libraries against spectral indices, notably involving fission and capture of {sup 232}Th and {sup 237}Np, measured in GFR-like lattices. (authors)« less

Proteus: Mythology to modern times.

PubMed

Sellaturay, Senthy V; Nair, Raj; Dickinson, Ian K; Sriprasad, Seshadri

2012-10-01

It is common knowledge that proteus bacteria are associated with urinary tract infections and urinary stones. Far more interesting however, is the derivation of the word proteus. This study examines the origin of the word proteus, its mythological, historical and literary connections and evolution to present-day usage. A detailed search for primary and secondary sources was undertaken using the library and internet. Greek mythology describes Proteus as an early sea-god, noted for being versatile and capable of assuming many different forms. In the 8(th) century BC, the ancient Greek poet, Homer, famous for his epic poems the Iliad and Odyssey, describes Proteus as a prophetic old sea-god, and herdsman of the seals of Poseidon, God of the Sea. Shakespeare re-introduced Proteus into English literature, in the 15(th) century AD, in the comedy The Two Gentleman of Verona, as one of his main characters who is inconstant with his affections. The 'elephant man' was afflicted by a severely disfiguring disease, described as 'Proteus syndrome'. It is particularly difficult to distinguish from neurofibromatosis, due to its various forms in different individuals. The Oxford English Dictionary defines the word 'protean' as to mean changeable, variable, and existing in multiple forms. Proteus bacteria directly derive their name from the Sea God, due to their rapid swarming growth and motility on agar plates. They demonstrate versatility by secreting enzymes, which allow them to evade the host's defense systems. Thus proteus, true to its name, has had a myriad of connotations over the centuries.

Efficacy of some colloidal silver preparations and silver salts against Proteus bacteria, one possible cause of rheumatoid arthritis.

PubMed

Disaanayake, D M B T; Faoagali, Joan; Laroo, Hans; Hancock, Gerald; Whitehouse, Michael

2014-04-01

There has been increased interest in the role of anti-Proteus antibodies in the aetiology of rheumatoid arthritis (RA) and whether chemotherapeutic agents active against Proteus species might reduce the risk and/or exacerbations of RA. We examined the in vitro antibacterial effects of ten different silver preparations which were either ionic silver [Ag(I)] solutions or nanoparticulate silver (NPS) (Ag(0)) suspensions against ATCC and two wild (clinical) strains of Proteus. The data establish the low minimum inhibitory concentration and minimum bactericidal concentration of all the silver formulations tested against these four Proteus strains. In a pilot study, a potent NPS preparation ex vivo showed long-lasting anti-Proteus activity in a normal human volunteer.

Proteus: Mythology to modern times

PubMed Central

Sellaturay, Senthy V.; Nair, Raj; Dickinson, Ian K.; Sriprasad, Seshadri

2012-01-01

Aims: It is common knowledge that proteus bacteria are associated with urinary tract infections and urinary stones. Far more interesting however, is the derivation of the word proteus. This study examines the origin of the word proteus, its mythological, historical and literary connections and evolution to present-day usage. Materials and Methods: A detailed search for primary and secondary sources was undertaken using the library and internet. Results: Greek mythology describes Proteus as an early sea-god, noted for being versatile and capable of assuming many different forms. In the 8th century BC, the ancient Greek poet, Homer, famous for his epic poems the Iliad and Odyssey, describes Proteus as a prophetic old sea-god, and herdsman of the seals of Poseidon, God of the Sea. Shakespeare re-introduced Proteus into English literature, in the 15th century AD, in the comedy The Two Gentleman of Verona, as one of his main characters who is inconstant with his affections. The ‘elephant man’ was afflicted by a severely disfiguring disease, described as ‘Proteus syndrome’. It is particularly difficult to distinguish from neurofibromatosis, due to its various forms in different individuals. The Oxford English Dictionary defines the word ‘protean’ as to mean changeable, variable, and existing in multiple forms. Proteus bacteria directly derive their name from the Sea God, due to their rapid swarming growth and motility on agar plates. They demonstrate versatility by secreting enzymes, which allow them to evade the host's defense systems. Conclusions: Thus proteus, true to its name, has had a myriad of connotations over the centuries. PMID:23450503

Impact of Morphological Changes on the Motility of Amoeba proteus

NASA Astrophysics Data System (ADS)

Shroff N, Sunitha

2016-11-01

Bio-mechanical properties of cell membrane, actin and cytoskeleton have influence on the cell locomotion. To explore, morphological changes were induced in Amoeba proteus by depriving nutrition, also either through ATP mediated or through KCl mediated membrane depolarization. We observed that, membrane depolarization leads to complete loss/reduction of pseudopodia in a dose dependent manner, gradually A. proteus becomes globular. We also report that with depravation of its nutrition (Chilomonas) A. proteus transforms them into tube/filament like structure and this transformation is reversible with the supply of Chilomonas. Results indicate that the structural and locomotion variation of A. proteus through nucleotides may not be just a membrane phenomenon, but may involve signaling mechanisms. Further, we carried out immunostaining of A. proteus with P2X2 and P2Y2 antibodies to analyze their localization and the extent of expression. The result indicated that in normal A. proteus receptors are dispersed uniformly, whereas in filament shaped A. proteus P2X2-receptor was found to be localized, unlike P2Y2 receptor. As nucleotides are known to cause structural changes in the organism, we report corresponding changes in their locomotion. Assistant Professor, Department of Biotechnology. Mount Carmel College, Bangalore 560 052.

Warthog: A MOOSE-Based Application for the Direct Code Coupling of BISON and PROTEUS

DOE Office of Scientific and Technical Information (OSTI.GOV)

McCaskey, Alexander J.; Slattery, Stuart; Billings, Jay Jay

The Nuclear Energy Advanced Modeling and Simulation (NEAMS) program from the Department of Energy's Office of Nuclear Energy provides a robust toolkit for the modeling and simulation of current and future advanced nuclear reactor designs. This toolkit provides these technologies organized across product lines: two divisions targeted at fuels and end-to-end reactor modeling, and a third for integration, coupling, and high-level workflow management. The Fuels Product Line and the Reactor Product line provide advanced computational technologies that serve each respective field well, however, their current lack of integration presents a major impediment to future improvements of simulation solution fidelity. Theremore » is a desire for the capability to mix and match tools across Product Lines in an effort to utilize the best from both to improve NEAMS modeling and simulation technologies. This report details a new effort to provide this Product Line interoperability through the development of a new application called Warthog. This application couples the BISON Fuel Performance application from the Fuels Product Line and the PROTEUS Core Neutronics application from the Reactors Product Line in an effort to utilize the best from all parts of the NEAMS toolkit and improve overall solution fidelity of nuclear fuel simulations. To achieve this, Warthog leverages as much prior work from the NEAMS program as possible, and in doing so, enables interoperability between the disparate MOOSE and SHARP frameworks, and the libMesh and MOAB mesh data formats. This report describes this work in full. We begin with a detailed look at the individual NEAMS framework technologies used and developed in the various Product Lines, and the current status of their interoperability. We then introduce the Warthog application: its overall architecture and the ways it leverages the best existing tools from across the NEAMS toolkit to enable BISON-PROTEUS integration. Furthermore, we show how Warthog leverages a tool known as DataTransferKit to seamlessly enable the transfer for solution data between disparate frameworks and mesh formats. To end, we demonstrate tests for the direct software coupling of BISON and PROTEUS using Warthog, and discuss current impediments and solutions to the construction of physically realistic input models for this coupled BISON-PROTEUS system.« less

HTR-PROTEUS Pebble Bed Experimental Program Cores 1, 1A, 2, and 3: Hexagonal Close Packing with a 1:2 Moderator-to-Fuel Pebble Ratio

DOE Office of Scientific and Technical Information (OSTI.GOV)

John D. Bess; Barbara H. Dolphin; James W. Sterbentz

2013-03-01

In its deployment as a pebble bed reactor (PBR) critical facility from 1992 to 1996, the PROTEUS facility was designated as HTR-PROTEUS. This experimental program was performed as part of an International Atomic Energy Agency (IAEA) Coordinated Research Project (CRP) on the Validation of Safety Related Physics Calculations for Low Enriched HTGRs. Within this project, critical experiments were conducted for graphite moderated LEU systems to determine core reactivity, flux and power profiles, reaction-rate ratios, the worth of control rods, both in-core and reflector based, the worth of burnable poisons, kinetic parameters, and the effects of moisture ingress on these parameters.more » Four benchmark experiments were evaluated in this report: Cores 1, 1A, 2, and 3. These core configurations represent the hexagonal close packing (HCP) configurations of the HTR-PROTEUS experiment with a moderator-to-fuel pebble ratio of 1:2. Core 1 represents the only configuration utilizing ZEBRA control rods. Cores 1A, 2, and 3 use withdrawable, hollow, stainless steel control rods. Cores 1 and 1A are similar except for the use of different control rods; Core 1A also has one less layer of pebbles (21 layers instead of 22). Core 2 retains the first 16 layers of pebbles from Cores 1 and 1A and has 16 layers of moderator pebbles stacked above the fueled layers. Core 3 retains the first 17 layers of pebbles but has polyethylene rods inserted between pebbles to simulate water ingress. The additional partial pebble layer (layer 18) for Core 3 was not included as it was used for core operations and not the reported critical configuration. Cores 1, 1A, 2, and 3 were determined to be acceptable benchmark experiments.« less

HTR-PROTEUS Pebble Bed Experimental Program Cores 1, 1A, 2, and 3: Hexagonal Close Packing with a 1:2 Moderator-to-Fuel Pebble Ratio

DOE Office of Scientific and Technical Information (OSTI.GOV)

John D. Bess; Barbara H. Dolphin; James W. Sterbentz

2012-03-01

In its deployment as a pebble bed reactor (PBR) critical facility from 1992 to 1996, the PROTEUS facility was designated as HTR-PROTEUS. This experimental program was performed as part of an International Atomic Energy Agency (IAEA) Coordinated Research Project (CRP) on the Validation of Safety Related Physics Calculations for Low Enriched HTGRs. Within this project, critical experiments were conducted for graphite moderated LEU systems to determine core reactivity, flux and power profiles, reaction-rate ratios, the worth of control rods, both in-core and reflector based, the worth of burnable poisons, kinetic parameters, and the effects of moisture ingress on these parameters.more » Four benchmark experiments were evaluated in this report: Cores 1, 1A, 2, and 3. These core configurations represent the hexagonal close packing (HCP) configurations of the HTR-PROTEUS experiment with a moderator-to-fuel pebble ratio of 1:2. Core 1 represents the only configuration utilizing ZEBRA control rods. Cores 1A, 2, and 3 use withdrawable, hollow, stainless steel control rods. Cores 1 and 1A are similar except for the use of different control rods; Core 1A also has one less layer of pebbles (21 layers instead of 22). Core 2 retains the first 16 layers of pebbles from Cores 1 and 1A and has 16 layers of moderator pebbles stacked above the fueled layers. Core 3 retains the first 17 layers of pebbles but has polyethylene rods inserted between pebbles to simulate water ingress. The additional partial pebble layer (layer 18) for Core 3 was not included as it was used for core operations and not the reported critical configuration. Cores 1, 1A, 2, and 3 were determined to be acceptable benchmark experiments.« less

Immunochemical characterization of the O antigens of two Proteus strains, O8-related antigen of Proteus mirabilis 12 B-r and O2-related antigen of Proteus genomospecies 5/6 12 B-k, infecting a hospitalized patient in Poland.

PubMed

Drzewiecka, Dominika; Shashkov, Alexander S; Arbatsky, Nikolay P; Knirel, Yuriy A

2016-05-01

A hospitalized 73-year-old woman was infected with a Proteus mirabilis strain, 12 B-r, isolated from the place of injection of a blood catheter. Another strain, 12 B-k, recognized as Proteus genomospecies 5 or 6, was isolated from the patient's faeces, which was an example of a nosocomial infection rather than an auto-infection. Serological investigation using ELISA and Western blotting showed that strain 12 B-k from faeces belonged to the Proteus O2 serogroup. Strain 12 B-r from the wound displayed cross-reactions with several Proteus O serogroups due to common epitopes on the core or O-specific parts of the lipopolysaccharide. Studies of the isolated 12 B-r O-specific polysaccharide by NMR spectroscopy revealed its close structural similarity to that of Proteus O8. The only difference in 12 B-r was the presence of an additional GlcNAc-linked phosphoethanolamine residue, which creates a putative epitope responsible for the cross-reactivity with Pt. mirabilis O16. The new O-antigen form could appear as a result of adaptation of the bacterium to a changing environment. On the basis of the data obtained, we suggest division of the O8 serogroup into two subgroups: O8a for strains of various Proteus species that have been previously classified into the O8 serogroup, and O8a,b for Pt. mirabilis 12 B-r, where 'a' is a common epitope and 'b' is a phosphoethanolamine-associated epitope. These findings further confirm serological and structural heterogeneity of O antigens of Proteus strains isolated lately from patients in Poland.

Proteus in flight over Southern California

NASA Image and Video Library

2003-03-27

Scaled Composites' unique tandem-wing Proteus was the testbed for a series of UAV collision-avoidance flight demonstrations. An Amphitech 35GHz radar unit installed below Proteus' nose was the primary sensor for the Detect, See and Avoid tests.

Proteus front view in flight

NASA Image and Video Library

2003-03-27

Scaled Composites' unique tandem-wing Proteus was the testbed for a series of UAV collision-avoidance flight demonstrations. An Amphitech 35GHz radar unit installed below Proteus' nose was the primary sensor for the Detect, See and Avoid tests.

Proteus in flight over Rosamond Dry lakebed

NASA Image and Video Library

2003-03-27

Scaled Composites' unique tandem-wing Proteus was the testbed for a series of UAV collision-avoidance flight demonstrations. An Amphitech 35GHz radar unit installed below Proteus' nose was the primary sensor for the Detect, See and Avoid tests.

Development of Cross Section Library and Application Programming Interface (API)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lee, C. H.; Marin-Lafleche, A.; Smith, M. A.

2014-04-09

The goal of NEAMS neutronics is to develop a high-fidelity deterministic neutron transport code termed PROTEUS for use on all reactor types of interest, but focused primarily on sodium-cooled fast reactors. While PROTEUS-SN has demonstrated good accuracy for homogeneous fast reactor problems and partially heterogeneous fast reactor problems, the simulation results were not satisfactory when applied on fully heterogeneous thermal problems like the Advanced Test Reactor (ATR). This is mainly attributed to the quality of cross section data for heterogeneous geometries since the conventional cross section generation approach does not work accurately for such irregular and complex geometries. Therefore, onemore » of the NEAMS neutronics tasks since FY12 has been the development of a procedure to generate appropriate cross sections for a heterogeneous geometry core.« less

Design Considerations in Developing a Web-Based Mentor Network.

ERIC Educational Resources Information Center

Sumner, Todd

This paper describes a Web-based mentor network designed to pair students in rural independent schools with undergraduates at selected liberal arts colleges. It is one of nine central program elements that constitute the Proteus(TM) system, a multimedia technologies architecture that supports distributed collaborations and work undertaken in the…

Molecular analysis, biochemical characterization, antimicrobial activity and immunological analysis of proteus mirabilis isolated from broilers

USDA-ARS?s Scientific Manuscript database

Proteus mirabilis, a peritrichously flagellated Gram-negative bacterium, is ubiquitous in the environment and is the normal microflora in the human gastrointestinal tract. However, this bacterium is an opportunistic pathogen for human, often causing urinary tract infection. Moreover, Proteus has b...

Proteus syndrome: association with gingival hyperplasia.

PubMed

Arendorf, T M; Hanslo, B

1995-09-01

A 9-year old Black boy with gigantism of the hands and feet, and recurrent gingival hyperplasia, diagnosed as Proteus syndrome is presented. The oral manifestations of this syndrome are described. To the best of our knowledge, this is the first reported case of gingival hyperplasia associated with Proteus syndrome.

Professor Krystyna Kotełko and her contribution to the study of Proteus endotoxin.

PubMed

Różalski, Antoni W

2018-04-01

Professor Krystyna Kotełko was working as a microbiologist at the University of Łódź (Poland). Her main object of study was the LPS (endotoxin) of opportunistic urinary pathogens from the genus Proteus. She demonstrated, for the first time, the presence of uronic acids and amino acids, as well as two heptoses (L- glycero-D- manno-heptose and D- glycero-D- manno-heptose) and hexosamines in Proteus LPS, and developed a classification scheme of the Proteus LPS into chemotypes. Prof Kotełko also initiated studies on the chemical structure of Proteus O-specific polysaccharide and investigations on the serological specificity of this part of LPS, as well its core region. She also analysed the virulence factors of these bacteria, such as haemolysin and invasiveness.

[Dynamics of drug resistance in Proteus mirabilis cultures 1970-1985].

PubMed

Shvidenko, I G

1988-04-01

Resistance of 669 clinical strains of Proteus mirabilis to 18 chemotherapeutic drugs was studied in dynamics within 1970-1985. An increase in the number of cultures resistant to ampicillin and carbenicillin was noted while the number of cultures resistant to cephalosporines did not change. Within the period from 1970 to 1975 there was observed a marked increase in the number of Proteus strains resistant to aminoglycoside antibiotics. After that period their number gradually lowered and in 1985 reached the level of 1970. Beginning from 1973 there were observed a decrease in the number of Proteus chloramphenicol resistant strains and simultaneous occurrence of cultures sensitive to this antibiotic. The predominating number of the tested strains preserved during the whole observation period their resistance to tetracycline, doxycycline, rifampicin, novobiocin, furazolidone and furagin. No increase in the number of Proteus strains with multiple drug resistance including those resistant to 5-7 drugs was noted in the observation periods of 1970-1975, 1980 and 1985. The most frequent were Proteus strains resistant to 2-4 drugs. Among them cultures resistant to chloramphenicol and aminoglycoside antibiotics of the first generation predominated. Grouping of the strains by the same resistance spectra provided dividing the rested cultures of Proteus mirabilis into 69 variants.

User Manual for the PROTEUS Mesh Tools

DOE Office of Scientific and Technical Information (OSTI.GOV)

Smith, Micheal A.; Shemon, Emily R

2016-09-19

PROTEUS is built around a finite element representation of the geometry for visualization. In addition, the PROTEUS-SN solver was built to solve the even-parity transport equation on a finite element mesh provided as input. Similarly, PROTEUS-MOC and PROTEUS-NEMO were built to apply the method of characteristics on unstructured finite element meshes. Given the complexity of real world problems, experience has shown that using commercial mesh generator to create rather simple input geometries is overly complex and slow. As a consequence, significant effort has been put into place to create multiple codes that help assist in the mesh generation and manipulation.more » There are three input means to create a mesh in PROTEUS: UFMESH, GRID, and NEMESH. At present, the UFMESH is a simple way to generate two-dimensional Cartesian and hexagonal fuel assembly geometries. The UFmesh input allows for simple assembly mesh generation while the GRID input allows the generation of Cartesian, hexagonal, and regular triangular structured grid geometry options. The NEMESH is a way for the user to create their own mesh or convert another mesh file format into a PROTEUS input format. Given that one has an input mesh format acceptable for PROTEUS, we have constructed several tools which allow further mesh and geometry construction (i.e. mesh extrusion and merging). This report describes the various mesh tools that are provided with the PROTEUS code giving both descriptions of the input and output. In many cases the examples are provided with a regression test of the mesh tools. The most important mesh tools for any user to consider using are the MT_MeshToMesh.x and the MT_RadialLattice.x codes. The former allows the conversion between most mesh types handled by PROTEUS while the second allows the merging of multiple (assembly) meshes into a radial structured grid. Note that the mesh generation process is recursive in nature and that each input specific for a given mesh tool (such as .axial or .merge) can be used as “mesh” input for any of the mesh tools discussed in this manual.« less

Functional morphology of the inner ear and underwater audiograms of Proteus anguinus (Amphibia, Urodela).

PubMed

Bulog, B; Schlegel, P

2000-01-01

Octavolateral sensory organs (auditory and lateral line organs) of cave salamander Proteus anguinus are highly differentiated. In the saccular macula of the inner ear the complex pattern of hair cell orientation and the large otoconial mass enable particle displacement direction detection. Additionally, the same organ, through air cavities within the body, enables detection of underwater sound pressure changes thus acting as a hearing organ. The cavities in the lungs and mouth of Proteus are a resonators that transmit underwater sound pressure to the inner ear. Behaviourally determined audiograms indicate hearing sensitivity of 60 dB (rel. 1 microPa) at frequencies between 1 and 10 kHz. The hearing frequency range was between 10 Hz and 10 kHz. The hearing sensitivities of depigmented Proteus and black Proteus were compared. The highest sensitivities of the depigmented animals (N=4) were at frequencies 1.3-1.7 kHz and it was 2 kHz in black animals (N=1). Excellent underwater hearing abilities of Proteus are sensory adaptations to cave habitat.

[Joint action of aminoglycoside antibiotics and nitrofurans with bile on bacteria of the genus Proteus].

PubMed

Sytnik, I A; Puzakova, E V

1980-06-01

The combined effect of monomycin, kanamycin, neomycin and nitrofurans, such as furacillin, furagin, nitrofurantoin and furazolidone with bovine bile was studied on 36 strains of Proteus mirabilis and 14 strains of Proteus vulgaris. It was found that sub-bacteriostatic doses of the bile significantly increased the antiproteus activity of the aminoglycoside antibiotics and nitrofurans. The combinations of the bile with monomycin and kanamycin and the bile with furazolidone and nitrofurantoin proved to be most effective. Clinical trials of the drugs in treatment of inflammatory diseases of the biliferous system of the Proteus etiology are recommended.

Convergence acceleration of the Proteus computer code with multigrid methods

NASA Technical Reports Server (NTRS)

Demuren, A. O.; Ibraheem, S. O.

1992-01-01

Presented here is the first part of a study to implement convergence acceleration techniques based on the multigrid concept in the Proteus computer code. A review is given of previous studies on the implementation of multigrid methods in computer codes for compressible flow analysis. Also presented is a detailed stability analysis of upwind and central-difference based numerical schemes for solving the Euler and Navier-Stokes equations. Results are given of a convergence study of the Proteus code on computational grids of different sizes. The results presented here form the foundation for the implementation of multigrid methods in the Proteus code.

Proteus DSA control room in Mojave, CA

NASA Image and Video Library

2003-04-03

Proteus DSA control room in Mojave, CA (L to R) Jean-Pierre Soucy; Amphitech International Software engineer Craig Bomben; NASA Dryden Test Pilot Pete Siebold; (with headset, at computer controls) Scaled Composites pilot Bob Roehm; New Mexico State University (NMSU) UAV Technical Analysis Application Center (TAAC) Chuck Coleman; Scaled Composites Pilot Kari Sortland; NMSU TAAC Russell Wolfe; Modern Technology Solutions, Inc. Scaled Composites' unique tandem-wing Proteus was the testbed for a series of UAV collision-avoidance flight demonstrations. An Amphitech 35GHz radar unit installed below Proteus' nose was the primary sensor for the Detect, See and Avoid tests.

Evaluation of the Advanced Subsonic Technology Program Noise Reduction Benefits

NASA Technical Reports Server (NTRS)

Golub, Robert A.; Rawls, John W., Jr.; Russell, James W.

2005-01-01

This report presents a detailed evaluation of the aircraft noise reduction technology concepts developed during the course of the NASA/FAA Advanced Subsonic Technology (AST) Noise Reduction Program. In 1992, NASA and the FAA initiated a cosponsored, multi-year program with the U.S. aircraft industry focused on achieving significant advances in aircraft noise reduction. The program achieved success through a systematic development and validation of noise reduction technology. Using the NASA Aircraft Noise Prediction Program, the noise reduction benefit of the technologies that reached a NASA technology readiness level of 5 or 6 were applied to each of four classes of aircraft which included a large four engine aircraft, a large twin engine aircraft, a small twin engine aircraft and a business jet. Total aircraft noise reductions resulting from the implementation of the appropriate technologies for each class of aircraft are presented and compared to the AST program goals.

Remote Measurements of Carbon Monoxide over North America and Europe during Summer- Fall 2004 and Southern Hemisphere 2006

NASA Astrophysics Data System (ADS)

Connors, V. S.; Chen, G.; Pierce, B.; Hopkins, P. E.; Meriwether, T.; Reichle, H. G.; Sachse, Nia, G.; McMillan, W.; Sandy, M.; Companion, J.

2007-05-01

The MicroMAPS instrument is a nadir-viewing, gas filter-correlated radiometer which operating in the 4.67 micrometer fundamental band of carbon monoxide. Originally designed and built for a space mission, this CO remote sensor is being flown in support of satellite validation and science instrument demonstrations for potential UAV applications. The MicroMAPS instrument system was integrated and tested at NASA LaRC, in partnership with Scaled Composites and Virginia Space Grant Consortium (VSGC). Full system integration and flight testing was performed at Scaled Composites, in Mojave, in June 2004. Its successful performance enabled participation in four international science missions on Proteus: in 2004, INTEX -NA over eastern North America in July, ADRIEX over the Mediterranean region and EAQUATE over the United Kingdom region in September,and TWP-ICE over Darwin, Australia and the surrounding oceans in Jan-Feb 2006. These flights resulted in nearly 300 hours of data. In parallel with the engineering developments, theoretical radiative transfer models were developed specifically for the MicroMAPS instrument system at the University of Virginia, Mechanical Engineering Department by a combined undergraduate and graduate student team. With technical support from Resonance Ltd. in June 2005, the MicroMAPS instrument was calibrated for the conditions under which the Summer-Fall 2004 flights occurred. The analyses of the calibration data, combined with the theoretical radiative transfer models, provide the first data reduction for the science flights reported here. The influence on widespread fires in Alaska and Canada, coupled with the influence of stratospheric intrusions over the eastern portion of North America during Summer 2004, provides the opportunity to examine the evolution of the tropospheric column and to examine how the transport histories of the air resulted in the CO columns sampled from the Proteus aircraft. These early results and comparisons with profile data from the NASA DC-8, the coincident AIRS CO retrievals, and selected measurements from the MOZAIC program and RAQMS model runs will be presented. Preliminary retrievals for the TWP-ICE transit flights and comparison with the coincident AIRS CO retrievals will also be presented.

Defense function of pigment granules in the ciliate Blepharisma japonicum against two predatory protists, Amoeba proteus (Rhizopodea) and Climacostomum virens (Ciliata).

PubMed

Terazima, Masayo Noda; Harumoto, Terue

2004-08-01

The defense function of pigment granules in the red ciliate Blepharisma japonicum against two predatory protists, Amoeba proteus and Climacostomum virens, was investigated by (1) comparing normally-pigmented and albino mutant cells of B. japonicum as the prey of these predators and (2) comparing resistance of the predators to blepharismin, the toxic pigment contained in the pigment granules of B. japonicum. Normally pigmented cells which contained more blepharismin than albino cells were less vulnerable to A. proteus than albino cells, but not to C. virens. C. virens was more resistant than A. proteus to the lethal effect of blepharismin. The results indicate that pigment granules of B. japonicum function as defense organelles against A. proteus but not against C. virens and suggest that successful defense against a predator depends on the susceptibility of the predator to blepharismin.

FY16 Status Report on NEAMS Neutronics Activities

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lee, C. H.; Shemon, E. R.; Smith, M. A.

2016-09-30

The goal of the NEAMS neutronics effort is to develop a neutronics toolkit for use on sodium-cooled fast reactors (SFRs) which can be extended to other reactor types. The neutronics toolkit includes the high-fidelity deterministic neutron transport code PROTEUS and many supporting tools such as a cross section generation code MC 2-3, a cross section library generation code, alternative cross section generation tools, mesh generation and conversion utilities, and an automated regression test tool. The FY16 effort for NEAMS neutronics focused on supporting the release of the SHARP toolkit and existing and new users, continuing to develop PROTEUS functions necessarymore » for performance improvement as well as the SHARP release, verifying PROTEUS against available existing benchmark problems, and developing new benchmark problems as needed. The FY16 research effort was focused on further updates of PROTEUS-SN and PROTEUS-MOCEX and cross section generation capabilities as needed.« less

14 CFR 91.1109 - Aircraft maintenance: Inspection program.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Aircraft maintenance: Inspection program... Ownership Operations Program Management § 91.1109 Aircraft maintenance: Inspection program. Each program... conduct of inspections for the particular make and model aircraft, including necessary tests and checks...

14 CFR 91.1109 - Aircraft maintenance: Inspection program.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Aircraft maintenance: Inspection program... Ownership Operations Program Management § 91.1109 Aircraft maintenance: Inspection program. Each program... conduct of inspections for the particular make and model aircraft, including necessary tests and checks...

14 CFR 91.1109 - Aircraft maintenance: Inspection program.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Aircraft maintenance: Inspection program... Ownership Operations Program Management § 91.1109 Aircraft maintenance: Inspection program. Each program... conduct of inspections for the particular make and model aircraft, including necessary tests and checks...

The Proteus Cabinet, or "We Are Here but Not Here"

ERIC Educational Resources Information Center

Nield, Sophie

2008-01-01

In the early nineteenth century, there were three stage illusions in which a magician could cause a person to disappear. In one of these, the Proteus Cabinet, participants would enter a box, and simply vanish. As the designers of the Proteus Cabinet said of them, they were "Here, but not Here." My essay explores this concept in relation to…

Electron microscopy of the nuclear membrane of Amoeba proteus.

PubMed

FRAJOLA, W J; GREIDER, M H; KOSTIR, W J

1956-07-25

An electron microscope study of the nuclear membrane of Amoeba proteus by thin sectioning techniques has revealed an ultrastructure in the outer layer of the membrane that is homologous to the pores and annuli observed in the nuclear membranes of many other cell types studied by these techniques. An inner honeycombed layer apparently unique to Amoeba proteus is also described.

Evaluation of Proteus as a Tool for the Rapid Development of Models of Hydrologic Systems

NASA Astrophysics Data System (ADS)

Weigand, T. M.; Farthing, M. W.; Kees, C. E.; Miller, C. T.

2013-12-01

Models of modern hydrologic systems can be complex and involve a variety of operators with varying character. The goal is to implement approximations of such models that are both efficient for the developer and computationally efficient, which is a set of naturally competing objectives. Proteus is a Python-based toolbox that supports prototyping of model formulations as well as a wide variety of modern numerical methods and parallel computing. We used Proteus to develop numerical approximations for three models: Richards' equation, a brine flow model derived using the Thermodynamically Constrained Averaging Theory (TCAT), and a multiphase TCAT-based tumor growth model. For Richards' equation, we investigated discontinuous Galerkin solutions with higher order time integration based on the backward difference formulas. The TCAT brine flow model was implemented using Proteus and a variety of numerical methods were compared to hand coded solutions. Finally, an existing tumor growth model was implemented in Proteus to introduce more advanced numerics and allow the code to be run in parallel. From these three example models, Proteus was found to be an attractive open-source option for rapidly developing high quality code for solving existing and evolving computational science models.

Environmental DNA in subterranean biology: range extension and taxonomic implications for Proteus

NASA Astrophysics Data System (ADS)

Gorički, Špela; Stanković, David; Snoj, Aleš; Kuntner, Matjaž; Jeffery, William R.; Trontelj, Peter; Pavićević, Miloš; Grizelj, Zlatko; Năpăruş-Aljančič, Magdalena; Aljančič, Gregor

2017-03-01

Europe’s obligate cave-dwelling amphibian Proteus anguinus inhabits subterranean waters of the north-western Balkan Peninsula. Because only fragments of its habitat are accessible to humans, this endangered salamander’s exact distribution has been difficult to establish. Here we introduce a quantitative real time polymerase chain reaction-based environmental DNA (eDNA) approach to detect the presence of Proteus using water samples collected from karst springs, wells or caves. In a survey conducted along the southern limit of its known range, we established a likely presence of Proteus at seven new sites, extending its range to Montenegro. Next, using specific molecular probes to discriminate the rare black morph of Proteus from the closely related white morph, we detected its eDNA at five new sites, thus more than doubling the known number of sites. In one of these we found both black and white Proteus eDNA together. This finding suggests that the two morphs may live in contact with each other in the same body of groundwater and that they may be reproductively isolated species. Our results show that the eDNA approach is suitable and efficient in addressing questions in biogeography, evolution, taxonomy and conservation of the cryptic subterranean fauna.

High Spectral Resolution Infrared and Raman Lidar Observations for the ARM Program: Clear and Cloudy Sky Applications

DOE Office of Scientific and Technical Information (OSTI.GOV)

Revercomb, Henry; Tobin, David; Knuteson, Robert

2009-06-17

This grant began with the development of the Atmospheric Emitted Radiance Interferometer (AERI) for ARM. The AERI has provided highly accurate and reliable observations of downwelling spectral radiance (Knuteson et al. 2004a, 2004b) for application to radiative transfer, remote sensing of boundary layer temperature and water vapor, and cloud characterization. One of the major contributions of the ARM program has been its success in improving radiation calculation capabilities for models and remote sensing that evolved from the multi-year, clear-sky spectral radiance comparisons between AERI radiances and line-by-line calculations (Turner et al. 2004). This effort also spurred us to play amore » central role in improving the accuracy of water vapor measurements, again helping ARM lead the way in the community (Turner et al. 2003a, Revercomb et al. 2003). In order to add high-altitude downlooking AERI-like observations over the ARM sites, we began the development of an airborne AERI instrument that has become known as the Scanning High-resolution Interferometer Sounder (Scanning-HIS). This instrument has become an integral part of the ARM Unmanned Aerospace Vehicle (ARM-UAV) program. It provides both a cross-track mapping view of the earth and an uplooking view from the 12-15 km altitude of the Scaled Composites Proteus aircraft when flown over the ARM sites for IOPs. It has successfully participated in the first two legs of the “grand tour” of the ARM sites (SGP and NSA), resulting in a very good comparison with AIRS observations in 2002 and in an especially interesting data set from the arctic during the Mixed-Phase Cloud Experiment (M-PACE) in 2004.« less

FY 1978 aeronautics and space technology program summary

NASA Technical Reports Server (NTRS)

1977-01-01

Highlights of the aeronautics program include research on aircraft energy efficiency, supersonic cruise aircraft, vertical takeoff and landing aircraft, short haul/short takeoff and landing aircraft, and general aviation aircraft. The space technology program includes work on space structures, propulsion systems, power systems, materials, and electronics.

A new European small platform: Proteus and prospected optical application missions

NASA Astrophysics Data System (ADS)

Dubois, J.-B.; Paoli, F.

2018-04-01

Progress in technology in recent years and new industrial approaches now make it possible to design valuable optical missions using a small-class satellite, like the PROTEUS multi mission platform. Some future space optical missions using existing or planned instruments, combined with the PROTEUS platform, have been assessed by AEROSPATIALE / SPACE and DEFENSE and/or the CNES (French National Space Agency).

Program to compute the positions of the aircraft and of the aircraft sensor footprints

NASA Technical Reports Server (NTRS)

Paris, J. F. (Principal Investigator)

1982-01-01

The positions of the ground track of the aircraft and of the aircraft sensor footprints, in particular the metric camera and the radar scatterometer on the C-130 aircraft, are estimated by a program called ACTRK. The program uses the altitude, speed, and attitude informaton contained in the radar scatterometer data files to calculate the positions. The ACTRK program is documented.

NASA aeronautics

NASA Technical Reports Server (NTRS)

Anderton, D. A.

1982-01-01

Aeronautical research programs are discussed in relation to research methods and the status of the programs. The energy efficient aircraft, STOL aircraft and general aviation aircraft are considered. Aerodynamic concepts, rotary wing aircraft, aircraft safety, noise reduction, and aircraft configurations are among the topics included.

[Etiological and molecular characteristics of diarrhea caused Proteus mirabilis].

PubMed

Shi, Xiaolu; Hu, Qinghua; Lin, Yiman; Qiu, Yaqun; Li, Yinghui; Jiang, Min; Chen, Qiongcheng

2014-06-01

To analyze the etiological characteristics, virulence genes and plasmids that carrying diarrhea-causing Proteus mirabilis and to assess their relationship with drug resistance and pathogenicity. Proteus mirabilis coming from six different sources (food poisoning, external environment and healthy people) were analyzed biochemically, on related susceptibility and pulsed-field gel electrophoresis (PFGE). Virulence genes were detected by PCR. Plasmids were extracted and sequenced after gel electrophoresis purification. The biochemical characteristics of Proteus mirabilis from different sources seemed basically the same, and each of them showed having common virulence genes, as ureC, rsmA, hpmA and zapA. However, the PFGE patterns and susceptibility of these strains were different, so as the plasmids that they carried. Plasmid that presented in the sequenced strain showed that the 2 683 bp length plasmid encodes qnrD gene was associated with the quinolone resistance. Etiological characteristics and molecular characteristics of Proteus mirabilis gathered from different sources, were analyzed. Results indicated that traditional biochemical analysis and common virulence gene identification might be able to distinguish the strains with different sources. However, PFGE and plasmids analysis could distinguish the sources of strains and to identify those plasmids that commonly carried by the drug-resistant strains. These findings also provided theoretical basis for further study on the nature of resistance and pathogenicity in Proteus mirabilis.

Proteus vulgaris and Proteus mirabilis Decrease Candida albicans Biofilm Formation by Suppressing Morphological Transition to Its Hyphal Form.

PubMed

Lee, Kyoung Ho; Park, Su Jung; Choi, Sun Ju; Park, Joo Young

2017-11-01

Candida albicans (C. albicans) and Proteus species are causative agents in a variety of opportunistic nosocomial infections, and their ability to form biofilms is known to be a virulence factor. In this study, the influence of co-cultivation with Proteus vulgaris (P. vulgaris) and Proteus mirabilis (P. mirabilis) on C. albicans biofilm formation and its underlying mechanisms were examined. XTT reduction assays were adopted to measure biofilm formation, and viable colony counts were performed to quantify yeast growth. Real-time reverse transcriptase polymerase chain reaction was used to evaluate the expression of yeast-specific genes (rhd1 and rbe1), filament formation inhibiting genes (tup1 and nrg1), and hyphae-related genes (als3, ece1, hwp1, and sap5). Candida biofilm formation was markedly inhibited by treatment with either living or heat-killed P. vulgaris and P. mirabilis. Proteus-cultured supernatant also inhibited Candida biofilm formation. Likewise, treatment with live P. vulgaris or P. mirabilis or with Proteus-cultured supernatant decreased expression of hyphae-related C. albicans genes, while the expression of yeast-specific genes and the filament formation inhibiting genes of C. albicans were increased. Heat-killed P. vulgaris and P. mirabilis treatment, however, did not affect the expression of C. albicans morphology-related genes. These results suggest that secretory products from P. vulgaris and P. mirabilis regulate the expression of genes related to morphologic changes in C. albicans such that transition from the yeast form to the hyphal form can be inhibited. © Copyright: Yonsei University College of Medicine 2017

Experimental Proteus mirabilis Burn Surface Infection

DTIC Science & Technology

1982-02-01

Reprinted from the Achie of Surgery ECTE February 1982, Volume 117 Copyright 19 2. American Medical Association MAY 2 8 1982 V0A Experimental Proteus ... mirabilis Burn Surface Infection Albert T. McManus, PhD; Charles G. McLeod, Jr, DVM; Arthur D. Mason, Jr, MD * We established a human burn Isolate of... Proteus mirabills as have examined human burn isolates from the genera an experimental pathogen. Infliction of a nonfatal scald injury Enterobacter

Proteus two-dimensional Navier-Stokes computer code, version 2.0. Volume 3: Programmer's reference

NASA Technical Reports Server (NTRS)

Towne, Charles E.; Schwab, John R.; Bui, Trong T.

1993-01-01

A computer code called Proteus 2D was developed to solve the two-dimensional planar or axisymmetric, Reynolds-averaged, unsteady compressible Navier-Stokes equations in strong conservation law form. The objective in this effort was to develop a code for aerospace propulsion applications that is easy to use and easy to modify. Code readability, modularity, and documentation were emphasized. The governing equations are solved in generalized nonorthogonal body-fitted coordinates, by marching in time using a fully-coupled ADI solution procedure. The boundary conditions are treated implicitly. All terms, including the diffusion terms, are linearized using second-order Taylor series expansions. Turbulence is modeled using either an algebraic or two-equation eddy viscosity model. The thin-layer or Euler equations may also be solved. The energy equation may be eliminated by the assumption of constant total enthalpy. Explicit and implicit artificial viscosity may be used. Several time step options are available for convergence acceleration. The documentation is divided into three volumes. The Programmer's Reference contains detailed information useful when modifying the program. The program structure, the Fortran variables stored in common blocks, and the details of each subprogram are described.

Proteus three-dimensional Navier-Stokes computer code, version 1.0. Volume 3: Programmer's reference

NASA Technical Reports Server (NTRS)

Towne, Charles E.; Schwab, John R.; Bui, Trong T.

1993-01-01

A computer code called Proteus 3D was developed to solve the three-dimensional, Reynolds-averaged, unsteady compressible Navier-Stokes equations in strong conservation law form. The objective in this effort was to develop a code for aerospace propulsion applications that is easy to use and easy to modify. Code readability, modularity, and documentation were emphasized. The governing equations are solved in generalized nonorthogonal body fitted coordinates, by marching in time using a fully-coupled ADI solution procedure. The boundary conditions are treated implicitly. All terms, including the diffusion terms, are linearized using second-order Taylor series expansions. Turbulence is modeled using either an algebraic or two-equation eddy viscosity model. The thin-layer or Euler equations may also be solved. The energy equation may be eliminated by the assumption of constant total enthalpy. Explicit and implicit artificial viscosity may be used. Several time step options are available for convergence acceleration. The documentation is divided into three volumes. The Programmer's Reference contains detailed information useful when modifying the program. The program structure, the Fortran variables stored in common blocks, and the details of each subprogram are described.

Proteus three-dimensional Navier-Stokes computer code, version 1.0. Volume 2: User's guide

NASA Technical Reports Server (NTRS)

Towne, Charles E.; Schwab, John R.; Bui, Trong T.

1993-01-01

A computer code called Proteus 3D was developed to solve the three-dimensional, Reynolds-averaged, unsteady compressible Navier-Stokes equations in strong conservation law form. The objective in this effort was to develop a code for aerospace propulsion applications that is easy to use and easy to modify. Code readability, modularity, and documentation were emphasized. The governing equations are solved in generalized nonorthogonal body-fitted coordinates, by marching in time using a fully-coupled ADI solution procedure. The boundary conditions are treated implicitly. All terms, including the diffusion terms, are linearized using second-order Taylor series expansions. Turbulence is modeled using either an algebraic or two-equation eddy viscosity model. The thin-layer or Euler equations may also be solved. The energy equation may be eliminated by the assumption of constant total enthalpy. Explicit and implicit artificial viscosity may be used. Several time step options are available for convergence acceleration. The documentation is divided into three volumes. This User's Guide describes the program's features, the input and output, the procedure for setting up initial conditions, the computer resource requirements, the diagnostic messages that may be generated, the job control language used to run the program, and several test cases.

Proteus - A Free and Open Source Sensor Observation Service (SOS) Client

NASA Astrophysics Data System (ADS)

Henriksson, J.; Satapathy, G.; Bermudez, L. E.

2013-12-01

The Earth's 'electronic skin' is becoming ever more sophisticated with a growing number of sensors measuring everything from seawater salinity levels to atmospheric pressure. To further the scientific application of this data collection effort, it is important to make the data easily available to anyone who wants to use it. Making Earth Science data readily available will allow the data to be used in new and potentially groundbreaking ways. The US National Science and Technology Council made this clear in its most recent National Strategy for Civil Earth Observations report, when it remarked that Earth observations 'are often found to be useful for additional purposes not foreseen during the development of the observation system'. On the road to this goal the Open Geospatial Consortium (OGC) is defining uniform data formats and service interfaces to facilitate the discovery and access of sensor data. This is being done through the Sensor Web Enablement (SWE) stack of standards, which include the Sensor Observation Service (SOS), Sensor Model Language (SensorML), Observations & Measurements (O&M) and Catalog Service for the Web (CSW). End-users do not have to use these standards directly, but can use smart tools that leverage and implement them. We have developed such a tool named Proteus. Proteus is an open-source sensor data discovery client. The goal of Proteus is to be a general-purpose client that can be used by anyone for discovering and accessing sensor data via OGC-based services. Proteus is a desktop client and supports a straightforward workflow for finding sensor data. The workflow takes the user through the process of selecting appropriate services, bounding boxes, observed properties, time periods and other search facets. NASA World Wind is used to display the matching sensor offerings on a map. Data from any sensor offering can be previewed in a time series. The user can download data from a single sensor offering, or download data in bulk from all matching sensor offerings. Proteus leverages NASA World Wind's WMS capabilities and allow overlaying sensor offerings on top of any map. Specific search criteria (i.e. user discoveries) can be saved and later restored. Proteus is supports two user types: 1) the researcher/scientist interested in discovering and downloading specific sensor data as input to research processes, and 2) the data manager responsible for maintaining sensor data services (e.g. SOSs) and wants to ensure proper data and metadata delivery, verify sensor data, and receive sensor data alerts. Proteus has a Web-based companion product named the Community Hub that is used to generate sensor data alerts. Alerts can be received via an RSS feed, viewed in a Web browser or displayed directly in Proteus via a Web-based API. To advance the vision of making Earth Science data easily discoverable and accessible to end-users, professional or laymen, Proteus is available as open-source on GitHub (https://github.com/intelligentautomation/proteus).

14 CFR 135.419 - Approved aircraft inspection program.

Code of Federal Regulations, 2010 CFR

2010-01-01

... OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance, Preventive Maintenance, and Alterations § 135.419 Approved aircraft inspection program. (a... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Approved aircraft inspection program. 135...

14 CFR 135.419 - Approved aircraft inspection program.

Code of Federal Regulations, 2012 CFR

2012-01-01

... OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance, Preventive Maintenance, and Alterations § 135.419 Approved aircraft inspection program. (a... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Approved aircraft inspection program. 135...

14 CFR 135.419 - Approved aircraft inspection program.

Code of Federal Regulations, 2013 CFR

2013-01-01

... OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance, Preventive Maintenance, and Alterations § 135.419 Approved aircraft inspection program. (a... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Approved aircraft inspection program. 135...

14 CFR 135.419 - Approved aircraft inspection program.

Code of Federal Regulations, 2014 CFR

2014-01-01

... OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance, Preventive Maintenance, and Alterations § 135.419 Approved aircraft inspection program. (a... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Approved aircraft inspection program. 135...

14 CFR 135.419 - Approved aircraft inspection program.

Code of Federal Regulations, 2011 CFR

2011-01-01

... OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Maintenance, Preventive Maintenance, and Alterations § 135.419 Approved aircraft inspection program. (a... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Approved aircraft inspection program. 135...

Review of V/STOL lift/cruise fan technology

NASA Technical Reports Server (NTRS)

Rolls, L. S.; Quigley, H. C.; Perkins, R. G., Jr.

1976-01-01

This paper presents an overview of supporting technology programs conducted to reduce the risk in the joint NASA/Navy Lift/Cruise Fan Research and Technology Aircraft Program. The aeronautical community has endeavored to combine the low-speed and lifting capabilities of the helicopter with the high-speed capabilities of the jet aircraft; recent developments have indicated a lift/cruise fan propulsion system may provide these desired characteristics. NASA and the Navy have formulated a program that will provide a research and technology aircraft to furnish viability of the lift/cruise fan aircraft through flight experiences and obtain data on designs for future naval and civil V/STOL aircraft. The supporting technology programs discussed include: (1) design studies for operational aircraft, a research and technology aircraft, and associated propulsion systems; (2) wind-tunnel tests of several configurations; (3) propulsion-system thrust vectoring tests; and (4) simulation. These supporting technology programs have indicated that a satisfactory research and technology aircraft program can be accomplished within the current level of technology.

Status report on the land processes aircraft science management operations working group

NASA Technical Reports Server (NTRS)

Lawless, James G.; Mann, Lisa J.

1991-01-01

Since its inception three years ago, the Land Processes Aircraft Science Management Operations Working Group (MOWG) provided recommendations on the optimal use of the Agency's aircraft in support of the Land Processes Science Program. Recommendations covered topics such as aircraft and sensor usage, development of long-range plans, Multisensor Airborne Campaigns (MAC), program balance, aircraft sensor databases, new technology and sensor development, and increased University scientist participation in the program. Impacts of these recommendations improved the efficiency of various procedures including the flight request process, tracking of flight hours, and aircraft usage. The group also created a bibliography focused on publications produced by Land Processes scientists from the use of the aircraft program, surveyed NASA funded PI's on their participation in the aircraft program, and developed a planning template for multi-sensor airborne campaigns. Benefits from these activities are summarized.

SXT/R391 integrative and conjugative elements in Proteus species reveal abundant genetic diversity and multidrug resistance

PubMed Central

Li, Xinyue; Du, Yu; Du, Pengcheng; Dai, Hang; Fang, Yujie; Li, Zhenpeng; Lv, Na; Zhu, Baoli; Kan, Biao; Wang, Duochun

2016-01-01

SXT/R391 integrative and conjugative elements (ICEs) are self-transmissible mobile genetic elements that are found in most members of Enterobacteriaceae. Here, we determined fifteen SXT/R391 ICEs carried by Proteus isolates from food (4.2%) and diarrhoea patients (17.3%). BLASTn searches against GenBank showed that the fifteen SXT/R391 ICEs were closely related to that from different Enterobacteriaceae species, including Proteus mirabilis. Using core gene phylogenetic analysis, the fifteen SXT/R391 ICEs were grouped into six distinct clusters, including a dominant cluster and three clusters that have not been previously reported in Proteus isolates. The SXT/R391 ICEs shared a common structure with a set of conserved genes, five hotspots and two variable regions, which contained more foreign genes, including drug-resistance genes. Notably, a class A β-lactamase gene was identified in nine SXT/R391 ICEs. Collectively, the ICE-carrying isolates carried resistance genes for 20 tested drugs. Six isolates were resistant to chloramphenicol, kanamycin, streptomycin, trimethoprim-sulfamethoxazole, sulfisoxazole and tetracycline, which are drug resistances commonly encoded by ICEs. Our results demonstrate abundant genetic diversity and multidrug resistance of the SXT/R391 ICEs carried by Proteus isolates, which may have significance for public health. It is therefore necessary to continuously monitor the antimicrobial resistance and related mobile elements among Proteus isolates. PMID:27892525

Chaotic behavior in the locomotion of Amoeba proteus.

PubMed

Miyoshi, H; Kagawa, Y; Tsuchiya, Y

2001-01-01

The locomotion of Amoeba proteus has been investigated by algorithms evaluating correlation dimension and Lyapunov spectrum developed in the field of nonlinear science. It is presumed by these parameters whether the random behavior of the system is stochastic or deterministic. For the analysis of the nonlinear parameters, n-dimensional time-delayed vectors have been reconstructed from a time series of periphery and area of A. proteus images captured with a charge-coupled-device camera, which characterize its random motion. The correlation dimension analyzed has shown the random motion of A. proteus is subjected only to 3-4 macrovariables, though the system is a complex system composed of many degrees of freedom. Furthermore, the analysis of the Lyapunov spectrum has shown its largest exponent takes positive values. These results indicate the random behavior of A. proteus is chaotic and deterministic motion on an attractor with low dimension. It may be important for the elucidation of the cell locomotion to take account of nonlinear interactions among a small number of dynamics such as the sol-gel transformation, the cytoplasmic streaming, and the relating chemical reaction occurring in the cell.

Improvements to the adaptive maneuvering logic program

NASA Technical Reports Server (NTRS)

Burgin, George H.

1986-01-01

The Adaptive Maneuvering Logic (AML) computer program simulates close-in, one-on-one air-to-air combat between two fighter aircraft. Three important improvements are described. First, the previously available versions of AML were examined for their suitability as a baseline program. The selected program was then revised to eliminate some programming bugs which were uncovered over the years. A listing of this baseline program is included. Second, the equations governing the motion of the aircraft were completely revised. This resulted in a model with substantially higher fidelity than the original equations of motion provided. It also completely eliminated the over-the-top problem, which occurred in the older versions when the AML-driven aircraft attempted a vertical or near vertical loop. Third, the requirements for a versatile generic, yet realistic, aircraft model were studied and implemented in the program. The report contains detailed tables which make the generic aircraft to be either a modern, high performance aircraft, an older high performance aircraft, or a previous generation jet fighter.

The Proteus Navier-Stokes code

NASA Technical Reports Server (NTRS)

Towne, Charles E.; Bui, Trong T.; Cavicchi, Richard H.; Conley, Julianne M.; Molls, Frank B.; Schwab, John R.

1992-01-01

An effort is currently underway at NASA Lewis to develop two- and three-dimensional Navier-Stokes codes, called Proteus, for aerospace propulsion applications. The emphasis in the development of Proteus is not algorithm development or research on numerical methods, but rather the development of the code itself. The objective is to develop codes that are user-oriented, easily-modified, and well-documented. Well-proven, state-of-the-art solution algorithms are being used. Code readability, documentation (both internal and external), and validation are being emphasized. This paper is a status report on the Proteus development effort. The analysis and solution procedure are described briefly, and the various features in the code are summarized. The results from some of the validation cases that have been run are presented for both the two- and three-dimensional codes.

Benchmark Evaluation of HTR-PROTEUS Pebble Bed Experimental Program

DOE PAGES

Bess, John D.; Montierth, Leland; Köberl, Oliver; ...

2014-10-09

Benchmark models were developed to evaluate 11 critical core configurations of the HTR-PROTEUS pebble bed experimental program. Various additional reactor physics measurements were performed as part of this program; currently only a total of 37 absorber rod worth measurements have been evaluated as acceptable benchmark experiments for Cores 4, 9, and 10. Dominant uncertainties in the experimental keff for all core configurations come from uncertainties in the ²³⁵U enrichment of the fuel, impurities in the moderator pebbles, and the density and impurity content of the radial reflector. Calculations of k eff with MCNP5 and ENDF/B-VII.0 neutron nuclear data aremore » greater than the benchmark values but within 1% and also within the 3σ uncertainty, except for Core 4, which is the only randomly packed pebble configuration. Repeated calculations of k eff with MCNP6.1 and ENDF/B-VII.1 are lower than the benchmark values and within 1% (~3σ) except for Cores 5 and 9, which calculate lower than the benchmark eigenvalues within 4σ. The primary difference between the two nuclear data libraries is the adjustment of the absorption cross section of graphite. Simulations of the absorber rod worth measurements are within 3σ of the benchmark experiment values. The complete benchmark evaluation details are available in the 2014 edition of the International Handbook of Evaluated Reactor Physics Benchmark Experiments.« less

Update of aircraft profile data for the Integrated Noise Model computer program, vol. 3 : appendix B aircraft performance coefficients

DOT National Transportation Integrated Search

1992-03-01

This report provides aircraft takeoff and landing profiles, : aircraft aerodynamic performance coefficients and engine : performance coefficients for the aircraft data base : (Database 9) in the Integrated Noise Model (INM) computer : program. Flight...

Advanced turboprop testbed systems study. Volume 1: Testbed program objectives and priorities, drive system and aircraft design studies, evaluation and recommendations and wind tunnel test plans

NASA Technical Reports Server (NTRS)

Bradley, E. S.; Little, B. H.; Warnock, W.; Jenness, C. M.; Wilson, J. M.; Powell, C. W.; Shoaf, L.

1982-01-01

The establishment of propfan technology readiness was determined and candidate drive systems for propfan application were identified. Candidate testbed aircraft were investigated for testbed aircraft suitability and four aircraft selected as possible propfan testbed vehicles. An evaluation of the four candidates was performed and the Boeing KC-135A and the Gulfstream American Gulfstream II recommended as the most suitable aircraft for test application. Conceptual designs of the two recommended aircraft were performed and cost and schedule data for the entire testbed program were generated. The program total cost was estimated and a wind tunnel program cost and schedule is generated in support of the testbed program.

21 CFR 866.3410 - Proteus spp. (Weil-Felix) serological reagents.

Code of Federal Regulations, 2011 CFR

2011-04-01

... fluorescent dye (immunofluorescent reagents), derived from the bacterium Proteus vulgaris used in... (virus-like bacteria) in serum. Test results aid in the diagnosis of diseases caused by bacteria...

21 CFR 866.3410 - Proteus spp. (Weil-Felix) serological reagents.

Code of Federal Regulations, 2010 CFR

2010-04-01

... fluorescent dye (immunofluorescent reagents), derived from the bacterium Proteus vulgaris used in... (virus-like bacteria) in serum. Test results aid in the diagnosis of diseases caused by bacteria...

Update of aircraft profile data for the Integrated Noise Model computer program, vol. 2 : appendix A aircraft takeoff and landing profiles

DOT National Transportation Integrated Search

1992-03-01

This report provides aircraft takeoff and landing profiles, aircraft aerodynamic performance coefficients and engine performance coefficients for the aircraft data base (Database 9) in the Integrated Noise Model (INM) computer program. Flight profile...

[Proteus mirabilis septic arthritis].

PubMed

Sbiti, Mohammed; Bouhamidi, Bahia; Louzi, Lhoussaine

2017-01-01

Acute septic arthritis is rare. It is associated with poor prognosis in terms of mortality and morbidity. We report the case of a 61-year old patient with spontaneous Proteus mirabilis septic arthritis. He suffered from complicated diabetes associated with positive blood cultures and synovial fluid cultures. Patient's evolution was favorable thanks to early diagnosis and initiation of adequate antibiotic therapy. Proteus mirabilis septic arthritis is rare. On that basis we conducted a literature review of cases of Proteus mirabilis pyogenic arthritis to highlight the risk factors, pathogenesis, treatment and evolution of these diseases. Diagnosis is commonly based on microbiological analysis, early articular puncture biopsy is performed before the initiation of antibiotic treatment, direct examination, culture and antibiogram which are useful as guidance for antibiotic therapy. Septic arthritis is a diagnostic and therapeutic emergency; early management of this disease allows total healing without after-effects.

The Location GNSS Modules for the Components of Proteus System

NASA Astrophysics Data System (ADS)

Brzostowski, K.; Darakchiev, R.; Foks-Ryznar, A.; Sitek, P.

2012-01-01

The Proteus system - the Integrated Mobile System for Counterterrorism and Rescue Operations is a complex innovative project. To assure the best possible localization of mobile components of the system, many different Global Navigation Satellite System (GNSS) modules were taken into account. In order to chose the best solution many types of tests were done. Full results and conclusions are presented in this paper. The idea of measurements was to test modules in GPS Standard Positioning Service (SPS) with EGNOS system specification according to certain algorithms. The tests had to answer the question: what type of GNSS modules should be used on different components with respect to specific usage of Proteus system. The second goal of tests was to check the solution quality of integrated GNSS/INS (Inertial Navigation System) and its possible usage in some Proteus system components.

Characterisation of the Rac/PAK pathway in Amoeba proteus.

PubMed

Kłopocka, W; Moraczewska, J; Redowicz, M J

2005-04-01

Molecular mechanisms underlying the unique locomotion of the highly motile Amoeba proteus still remain poorly understood. Recently, we have shown that blocking the endogenous amoebal Rac-like protein(s) leads to distinct and irreversible changes in the appearance of these large migrating cells as well as to a significant inhibition of their locomotion. To elucidate the mechanism of the Rac pathway in Amoeba proteus, we tested the effects of blocking the endogenous myosin I heavy chain kinase (MIHCK), one of the Rac effectors in Acanthamoeba castellanii and Dictyostelium discoideum, with anti-MIHCK antibodies in migrating amoebae, as well as the effect of inhibiting Rac and MIHCK on the actin polymerisation process. Antibodies against A. castellanii MIHCK detected an A. proteus protein with a molecular mass (ca. 95 kDa) similar to the A. castellanii kinase. The cellular distribution of MIHCK in A. proteus was very similar to those of Rac-like protein in amoebae and MIHCK in A. castellanii. Amoebae microinjected with anti-MIHCK antibodies moved slower and protruded fewer wide pseudopodia (5-6) than the control cells (9-10), resembling to some extent the phenotype of cells microinjected with anti-Rac antibodies. The in vitro studies indicate that the A. proteus Rac-like protein, but not the MIHCK isoform, is engaged in the regulation of the nucleation step of the actin polymerisation process. These observations suggest that MIHCK may be one of the effectors for Rac in these extremely large cells.

Challenges for the aircraft structural integrity program

NASA Technical Reports Server (NTRS)

Lincoln, John W.

1994-01-01

Thirty-six years ago the United States Air Force established the USAF Aircraft Structural Integrity Program (ASIP) because flight safety had been degraded by fatigue failures of operational aircraft. This initial program evolved, but has been stable since the issuance of MIL-STD-1530A in 1975. Today, the program faces new challenges because of a need to maintain aircraft longer in an environment of reduced funding levels. Also, there is increased pressure to reduce cost of the acquisition of new aircraft. It is the purpose of this paper to discuss the challenges for the ASIP and identify the changes in the program that will meet these challenges in the future.

Taxonomic characterisation of Proteus terrae sp. nov., a N2O-producing, nitrate-ammonifying soil bacterium.

PubMed

Behrendt, Undine; Augustin, Jürgen; Spröer, Cathrin; Gelbrecht, Jörg; Schumann, Peter; Ulrich, Andreas

2015-12-01

In the context of studying the influence of N-fertilization on N2 and N2O flux rates in relation to the soil bacterial community composition in fen peat grassland, a group of bacterial strains was isolated that performed dissimilatory nitrate reduction to ammonium and concomitantly produced N2O. The amount of nitrous oxide produced was influenced by the C/N ratio of the medium. The potential to generate nitrous oxide was increased by higher availability of nitrate-N. Phylogenetic analysis based on the 16S rRNA and the rpoB gene sequences demonstrated that the investigated isolates belong to the genus Proteus, showing high similarity with the respective type strains of Proteus vulgaris and Proteus penneri. DNA-DNA hybridization studies revealed differences at the species level. These differences were substantiated by MALDI-TOF MS analysis and several distinct physiological characteristics. On the basis of these results, it was concluded that the soil isolates represent a novel species for which the name Proteus terrae sp. nov. (type strain N5/687(T) =DSM 29910(T) =LMG 28659(T)) is proposed.

[The etiology of urinary tract infections].

PubMed

Avio, C M; Ceccherini, M; Pierotti, R; Falcone, G

1977-01-01

The Authors have planned a program in order to file and elaborate with a computer the results of urine cultures. From 8.600 specimens, about 86% were negative or doubtful. The data obtained from 1201 positive cultures were processed in order to state the absolute and relative frequency of the bacterial species isolated and their distribution according to their genera, antibiotic resistence, month and sex. Among the most representative species the pattern of antibiotic resistence was surveyed. E. coli shows very high frequency (38%). The frequency of Pseudomonas increases while staphylococci frequency decreases as compared with the previous statements of various Authors. The analysis of the antibiotic sensitivity spectrum of 534 specimens shows that about 50% of E. coli strains are sensitive to 10, 11 and 12 antibiotics and their pattern of resistence involves no more than 9 antibiotics; on the contrary more than 60% of Pseudomonas and Proteus rettgeri are resistant to 10, 11 or 12 antibiotics and at any rate to no less than seven. Enterobacter and Proteus mirabilis present an intermediate pattern of resistence.

Vehicle Design Evaluation Program (VDEP). A computer program for weight sizing, economic, performance and mission analysis of fuel-conservative aircraft, multibodied aircraft and large cargo aircraft using both JP and alternative fuels

NASA Technical Reports Server (NTRS)

Oman, B. H.

1977-01-01

The NASA Langley Research Center vehicle design evaluation program (VDEP-2) was expanded by (1) incorporating into the program a capability to conduct preliminary design studies on subsonic commercial transport type aircraft using both JP and such alternate fuels as hydrogen and methane;(2) incorporating an aircraft detailed mission and performance analysis capability; and (3) developing and incorporating an external loads analysis capability. The resulting computer program (VDEP-3) provides a preliminary design tool that enables the user to perform integrated sizing, structural analysis, and cost studies on subsonic commercial transport aircraft. Both versions of the VDEP-3 Program which are designated preliminary Analysis VDEP-3 and detailed Analysis VDEP utilize the same vehicle sizing subprogram which includes a detailed mission analysis capability, as well as a geometry and weight analysis for multibodied configurations.

Viper Plague Project

DTIC Science & Technology

2009-07-01

labeled with the conjugated Proteus antibody, 40x………………………………………………………………………………………………………………………………………….……18 Figure 10i, 10j. Staphylococcus aureus ...Figure 10i, 10j. Staphylococcus aureus and Streptococcus pyogenes, (gram positive), labeled with the conjugated Proteus antibody, 40x...15 10. Proteus OX19 Aptamer

78 FR 12259 - Unmanned Aircraft System Test Site Program

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-22

...-0061] Unmanned Aircraft System Test Site Program AGENCY: Federal Aviation Administration (FAA), DOT... Defense, develop a test site program for the integration of unmanned aircraft systems in to the National Airspace System. The overall purpose of this test site program is to develop a body of data and operational...

Design and Development of the Aircraft Instrument Comprehension Program.

ERIC Educational Resources Information Center

Higgins, Norman C.

The Aircraft Instrument Comprehension (AIC) Program is a self-instructional program designed to teach undergraduate student pilots to read instruments that indicate the position of the aircraft in flight, based on sequential instructional stages of information, prompted practice, and unprompted practice. The program includes a 36-item multiple…

Quiet powered-lift propulsion

NASA Technical Reports Server (NTRS)

1979-01-01

Latest results of programs exploring new propulsion technology for powered-lift aircraft systems are presented. Topics discussed include results from the 'quiet clean short-haul experimental engine' program and progress reports on the 'quiet short-haul research aircraft' and 'tilt-rotor research aircraft' programs. In addition to these NASA programs, the Air Force AMST YC 14 and YC 15 programs were reviewed.

Antimicrobial activity Study of triclosan-loaded WBPU on Proteus mirabilis in vitro.

PubMed

Tian, Ye; Jian, Zhongyu; Wang, Jianzhong; He, Wei; Liu, Qinyu; Wang, Kunjie; Li, Hong; Tan, Hong

2017-04-01

To evaluate the antimicrobial activity study of triclosan-loaded waterborne polyurethanes (WBPU) on Proteus mirabilis in vitro. Inhibition zone assays on petri plates with triclosan-loaded WBPU samples were used to test its antimicrobial activity on Proteus mirabilis. Models of the catheterized bladder supplied with artificial urine infected with Proteus mirabilis were employed to confirm the antimicrobial activity of triclosan-loaded WBPU. Bacteria colony counting, pH of the residual urine at each time point and catheter blockage time were recorded. Confocal laser scanning microscopy, scanning electron microscopy and encrustation deposits dry weighing were used for evaluating the biofilm formation. Inhibition zones formed in the triclosan-loaded WBPU groups in a dose-response manner (the radius for samples with 1, 0.1 and 0.01 mg triclosan were 9.93 ± 1.08, 6.07 ± 0.54 and 2.47 ± 0.25 mm, P < 0.001). The bacterial growth in the triclosan group was markedly inhibited, which was almost undetectable after 12 h of bladder running. Residual urine pH in the control group increased significantly in comparison with the triclosan group (9.50 ± 0.04 vs. 6.17 ± 0.01 at 24 h, P < 0.001). The presence of triclosan-loaded WBPU decreased catheter encrustations and markedly postponed the catheter blockage time, as well as suppressed the Proteus mirabilis biofilm formation (33.9 ± 13.9 mg vs. 1.4 ± 1.5 mg, P = 0.016). Triclosan-loaded WBPU significantly inhibited Proteus mirabilis' growth and biofilm formation, indicating the promising antibacterial effects on Proteus mirabilis in vitro. Further efforts are under way that involves coating the material onto the urinary catheters and in vivo studies.

Update of aircraft profile data for the Integrated Noise Model computer program, vol 1: final report

DOT National Transportation Integrated Search

1992-03-01

This report provides aircraft takeoff and landing profiles, aircraft aerodynamic performance coefficients and engine performance coefficients for the aircraft data base (Database 9) in the Integrated Noise Model (INM) computer program. Flight profile...

Design definition study of NASA/Navy lift/cruise fan V/STOL aircraft

NASA Technical Reports Server (NTRS)

1975-01-01

Assessed are the risks associated with the lift/cruise fan technology V/STOL aircraft program. Three candidate concepts for the technology aircraft design approach are considered: the lowspeed only modification, the full performance modification, and the all new aircraft concepts. Survey results indicate that the lift/cruise fan technology aircraft program is feasible, from the standpoint of technical risk, with some evidence of uncertainty of meeting the planned schedule and relatively minor impact on estimated program costs.

Chemometric analysis of attenuated total reflectance infrared spectra of Proteus mirabilis strains with defined structures of LPS.

PubMed

Zarnowiec, Paulina; Mizera, Andrzej; Chrapek, Magdalena; Urbaniak, Mariusz; Kaca, Wieslaw

2016-07-01

Proteus spp. strains are some of the most important pathogens associated with complicated urinary tract infections and bacteremia affecting patients with immunodeficiency and long-term urinary catheterization. For epidemiological purposes, various molecular typing methods have been developed for this pathogen. However, these methods are labor intensive and time consuming. We evaluated a new method of differentiation between strains. A collection of Proteus spp. strains was analyzed by attenuated total reflectance Fourier transform infrared (ATR FT-IR) spectroscopy in the mid-infrared region. ATR FT-IR spectroscopy used in conjunction with a diamond ATR accessory directly produced the biochemical profile of the surface chemistry of bacteria. We conclude that a combination of ATR FT-IR spectroscopy and mathematical modeling provides a fast and reliable alternative for discrimination between Proteus isolates, contributing to epidemiological research. © The Author(s) 2016.

Effects of ceftazidime and ciprofloxacin on biofilm formation in Proteus mirabilis rods.

PubMed

Kwiecińska-Piróg, Joanna; Bogiel, Tomasz; Gospodarek, Eugenia

2013-10-01

Proteus mirabilis rods are one of the most commonly isolated species of the Proteus genus from human infections, mainly those from the urinary tract and wounds. They are often related to biofilm structure formation. The bacterial cells of the biofilm are less susceptible to routinely used antimicrobials, making the treatment more difficult. The aim of this study was to evaluate quantitatively the influence of ceftazidime and ciprofloxacin on biofilm formation on the polyvinyl chloride surface by 42 P. mirabilis strains isolated from urine, purulence, wound swab and bedsore samples. It has been shown that ceftazidime and ciprofloxacin at concentrations equal to 1/4, 1/2 and 1 times their MIC values for particular Proteus spp. strains decrease their ability to form biofilms. Moreover, ciprofloxacin at concentrations equal to 1/4, 1/2 and 1 times their MIC values for particular P. mirabilis strains reduces biofilm formation more efficiently than ceftazidime at the corresponding concentration values.

[Sensitivity of clinical Proteus strains to antibiotics and their combinations].

PubMed

Sheina, E P; Arutcheva, A A

1978-05-01

In 1976 isolation of Proteus from wounds of patients with various purulent processes amounted to 14.5 per cent. Serotypes 0-10, 0-3 and H-3 predominated among the isolates. Sensitivity of 35 clinical strains of Proteus to 10 antibiotics, furagin and nevigramone was studied by the method of serial dilutions in liquid media. All the isolates were highly resistant to the antibiotics except gentamicin, furagin and nevigramone, the MIC of which for most of the strains was 3.12, 1.6-3.12 and 6.25-12.5 gamma/ml, respectively. The effect of 14 combinations of chemotherapeutics was also studied. The combinations of gentamicin with carbenicillin, gentamicin with ampicillin and monomycin with ampicillin proved to be most effective against the Proteus strains tested. The following combinations may be of practical value: monomycin + carbenicillin, kanamycin + ampicillin, kanamycin + carbenicillin, ampicillin + furagin, gentamicin + nevigramone. The combinations of carbenicillin with furagin and gentamicin with furagin were also rational.

VASCOMP 2. The V/STOL aircraft sizing and performance computer program. Volume 6: User's manual, revision 3

NASA Technical Reports Server (NTRS)

Schoen, A. H.; Rosenstein, H.; Stanzione, K.; Wisniewski, J. S.

1980-01-01

This report describes the use of the V/STOL Aircraft Sizing and Performance Computer Program (VASCOMP II). The program is useful in performing aircraft parametric studies in a quick and cost efficient manner. Problem formulation and data development were performed by the Boeing Vertol Company and reflects the present preliminary design technology. The computer program, written in FORTRAN IV, has a broad range of input parameters, to enable investigation of a wide variety of aircraft. User oriented features of the program include minimized input requirements, diagnostic capabilities, and various options for program flexibility.

Giving Structure to Legacy Finding Aids before Conversion to EAD: The Case of the Archives Departementales des Pyrenees-Atlantiques, France

ERIC Educational Resources Information Center

Goulet, Anne; Maftei, Nicolas

2005-01-01

At the Archives Departementales des Pyrenees-Atlantiques, the encoding of more than forty legacy finding aids written between 1863 and 2000 is part of a program of digitization of the collections. Because of the size of the project, an external consultant, ArchProteus, has been brought in and specific management procedures have been put in place…

Proteus two-dimensional Navier-Stokes computer code, version 2.0. Volume 2: User's guide

NASA Technical Reports Server (NTRS)

Towne, Charles E.; Schwab, John R.; Bui, Trong T.

1993-01-01

A computer code called Proteus 2D was developed to solve the two-dimensional planar or axisymmetric, Reynolds-averaged, unsteady compressible Navier-Stokes equations in strong conservation law form. The objective in this effort was to develop a code for aerospace propulsion applications that is easy to use and easy to modify. Code readability, modularity, and documentation were emphasized. The governing equations are solved in generalized nonorthogonal body-fitted coordinates, by marching in time using a fully-coupled ADI solution procedure. The boundary conditions are treated implicitly. All terms, including the diffusion terms, are linearized using second-order Taylor series expansions. Turbulence is modeled using either an algebraic or two-equation eddy viscosity model. The thin-layer or Euler equations may also be solved. The energy equation may be eliminated by the assumption of constant total enthalpy. Explicit and implicit artificial viscosity may be used. Several time step options are available for convergence acceleration. The documentation is divided into three volumes. This is the User's Guide, and describes the program's features, the input and output, the procedure for setting up initial conditions, the computer resource requirements, the diagnostic messages that may be generated, the job control language used to run the program, and several test cases.

Proteus mirabilis inhibits cancer growth and pulmonary metastasis in a mouse breast cancer model

PubMed Central

Zhang, Hong; Diao, Hongxiu; Jia, Lixin; Yuan, Yujing; Thamm, Douglas H.; Wang, Huanan; Jin, Yipeng; Pei, Shimin; Zhou, Bin; Yu, Fang; Zhao, Linna; Cheng, Nan; Du, Hongchao; Huang, Ying; Lin, Degui

2017-01-01

A variety of bacteria have been used as agents and vectors for antineoplastic therapy. A series of mechanisms, including native bacterial toxicity, sensitization of the immune system and competition for nutrients, may contribute to antitumor effects. However, the antitumor effects of Proteus species have been minimally studied, and it is not clear if bacteria can alter tumor hypoxia as a component of their antineoplastic effect. In the present study, Proteus mirabilis bacteria were evaluated for the ability to proliferate and accumulate in murine tumors after intravenous injection. To further investigate the efficacy and safety of bacterial injection, mice bearing 4T1 tumors were treated with an intravenous dose of 5×107 CFU Proteus mirabilis bacteria via the tail vein weekly for three treatments. Histopathology, immunohistochemistry (IHC) and western analysis were then performed on excised tumors. The results suggested Proteus mirabilis localized preferentially to tumor tissues and remarkably suppressed the growth of primary breast cancer and pulmonary metastasis in murine 4T1 models. Results showed that the expression of NKp46 and CD11c was significantly increased after bacteria treatment. Furthermore, tumor expression of carbonic anhydrase IX (CA IX) and hypoxia inducible factor-1a (HIF-1a), surrogates for hypoxia, was significantly lower in the treated group than the control group mice as assessed by IHC and western analysis. These findings demonstrated that Proteus mirabilis may a promising bacterial strain for used against primary tumor growth and pulmonary metastasis, and the immune system and reduction of tumor hypoxia may contribute to the antineoplastic and antimetastatic effects observed. PMID:29206859

Proteus mirabilis inhibits cancer growth and pulmonary metastasis in a mouse breast cancer model.

PubMed

Zhang, Hong; Diao, Hongxiu; Jia, Lixin; Yuan, Yujing; Thamm, Douglas H; Wang, Huanan; Jin, Yipeng; Pei, Shimin; Zhou, Bin; Yu, Fang; Zhao, Linna; Cheng, Nan; Du, Hongchao; Huang, Ying; Zhang, Di; Lin, Degui

2017-01-01

A variety of bacteria have been used as agents and vectors for antineoplastic therapy. A series of mechanisms, including native bacterial toxicity, sensitization of the immune system and competition for nutrients, may contribute to antitumor effects. However, the antitumor effects of Proteus species have been minimally studied, and it is not clear if bacteria can alter tumor hypoxia as a component of their antineoplastic effect. In the present study, Proteus mirabilis bacteria were evaluated for the ability to proliferate and accumulate in murine tumors after intravenous injection. To further investigate the efficacy and safety of bacterial injection, mice bearing 4T1 tumors were treated with an intravenous dose of 5×107 CFU Proteus mirabilis bacteria via the tail vein weekly for three treatments. Histopathology, immunohistochemistry (IHC) and western analysis were then performed on excised tumors. The results suggested Proteus mirabilis localized preferentially to tumor tissues and remarkably suppressed the growth of primary breast cancer and pulmonary metastasis in murine 4T1 models. Results showed that the expression of NKp46 and CD11c was significantly increased after bacteria treatment. Furthermore, tumor expression of carbonic anhydrase IX (CA IX) and hypoxia inducible factor-1a (HIF-1a), surrogates for hypoxia, was significantly lower in the treated group than the control group mice as assessed by IHC and western analysis. These findings demonstrated that Proteus mirabilis may a promising bacterial strain for used against primary tumor growth and pulmonary metastasis, and the immune system and reduction of tumor hypoxia may contribute to the antineoplastic and antimetastatic effects observed.

49 CFR 1544.205 - Acceptance and screening of cargo.

Code of Federal Regulations, 2010 CFR

2010-10-01

...) Preventing or deterring the carriage of any explosive or incendiary. Each aircraft operator operating under a... operator operating under a full program or a full all-cargo program, or a twelve-five program in an all... program, before loading it on its aircraft. (c) Control. Each aircraft operator operating under a full...

14 CFR 119.49 - Contents of operations specifications.

Code of Federal Regulations, 2013 CFR

2013-01-01

... markings, and serial number of each aircraft that is subject to an airworthiness maintenance program..., and emergency equipment of aircraft that are subject to an airworthiness maintenance program required... Transportation, if required. (4) Type of aircraft, registration markings, and serial numbers of each aircraft...

14 CFR 119.49 - Contents of operations specifications.

Code of Federal Regulations, 2011 CFR

2011-01-01

... markings, and serial number of each aircraft that is subject to an airworthiness maintenance program..., and emergency equipment of aircraft that are subject to an airworthiness maintenance program required... Transportation, if required. (4) Type of aircraft, registration markings, and serial numbers of each aircraft...

14 CFR 119.49 - Contents of operations specifications.

Code of Federal Regulations, 2014 CFR

2014-01-01

... markings, and serial number of each aircraft that is subject to an airworthiness maintenance program..., and emergency equipment of aircraft that are subject to an airworthiness maintenance program required... Transportation, if required. (4) Type of aircraft, registration markings, and serial numbers of each aircraft...

14 CFR 119.49 - Contents of operations specifications.

Code of Federal Regulations, 2012 CFR

2012-01-01

... markings, and serial number of each aircraft that is subject to an airworthiness maintenance program..., and emergency equipment of aircraft that are subject to an airworthiness maintenance program required... Transportation, if required. (4) Type of aircraft, registration markings, and serial numbers of each aircraft...

Propeller aircraft interior noise model utilization study and validation

NASA Technical Reports Server (NTRS)

Pope, L. D.

1984-01-01

Utilization and validation of a computer program designed for aircraft interior noise prediction is considered. The program, entitled PAIN (an acronym for Propeller Aircraft Interior Noise), permits (in theory) predictions of sound levels inside propeller driven aircraft arising from sidewall transmission. The objective of the work reported was to determine the practicality of making predictions for various airplanes and the extent of the program's capabilities. The ultimate purpose was to discern the quality of predictions for tonal levels inside an aircraft occurring at the propeller blade passage frequency and its harmonics. The effort involved three tasks: (1) program validation through comparisons of predictions with scale-model test results; (2) development of utilization schemes for large (full scale) fuselages; and (3) validation through comparisons of predictions with measurements taken in flight tests on a turboprop aircraft. Findings should enable future users of the program to efficiently undertake and correctly interpret predictions.

Computer programs for estimating civil aircraft economics

NASA Technical Reports Server (NTRS)

Maddalon, D. V.; Molloy, J. K.; Neubawer, M. J.

1980-01-01

Computer programs for calculating airline direct operating cost, indirect operating cost, and return on investment were developed to provide a means for determining commercial aircraft life cycle cost and economic performance. A representative wide body subsonic jet aircraft was evaluated to illustrate use of the programs.

The NASA Aircraft Energy Efficiency program

NASA Technical Reports Server (NTRS)

Klineberg, J. M.

1979-01-01

A review is provided of the goals, objectives, and recent progress in each of six aircraft energy efficiency programs aimed at improved propulsive, aerodynamic and structural efficiency for future transport aircraft. Attention is given to engine component improvement, an energy efficient turbofan engine, advanced turboprops, revolutionary gains in aerodynamic efficiency for aircraft of the late 1990s, laminar flow control, and composite primary aircraft structures.

Proteus syndrome*

PubMed Central

Rocha, Ritha de Cássia Capelato; Estrella, Mariani Paulino Soriano; do Amaral, Danielle Mechereffe; Barbosa, Angela Marques; de Abreu, Marilda Aparecida Milanez Morgado

2017-01-01

Proteus syndrome is a rare syndrome characterized by disproportionate overgrowth of limbs, multiple hamartomas, and vascular malformations. The cerebriform connective tissue nevi, also called cerebriform plantar hyperplasia, are present in most patients, and is the main characteristic of the syndrome. If present, even alone, they can be considered as a pathognomonic sign. This article reports a classic case of Proteus syndrome in a 2-year-old male patient who began to show a discrete asymmetry of the right hemibody in relation to the left one after birth, which increased over the months. He also showed cerebriform plantar hyperplasia and Port-wine stains, among other alterations. PMID:29166516

Meeting the challenges with the Douglas Aircraft Company Aeroelastic Design Optimization Program (ADOP)

NASA Technical Reports Server (NTRS)

Rommel, Bruce A.

1989-01-01

An overview of the Aeroelastic Design Optimization Program (ADOP) at the Douglas Aircraft Company is given. A pilot test program involving the animation of mode shapes with solid rendering as well as wire frame displays, a complete aircraft model of a high-altitude hypersonic aircraft to test ADOP procedures, a flap model, and an aero-mesh modeler for doublet lattice aerodynamics are discussed.

United States Air Force Statistical Digest, Fiscal Year 1960. Fifteenth Edition

DTIC Science & Technology

1960-09-30

USAF CIVILIAN EMPLOYEES IN SALARIED AND WAGE BOARD GROUPS EMPLOYED UNDER MILITARY , ASSISTANCE PROGRAM (MAP), AT END OF QUARTER - FY � (Previous year...provide summary data on all aspects of the Mlli_ 165 tary Assistance program administered by the Air Force. The data were compiled from progress reports...Military Assistance . MAP AIRCRAFT - Aircraft in foreign countries provided by the USAF under Military Assistance Program . AIRCRAFT ATTRITION - Aircraft

A review of NASA's propulsion programs for aviation

NASA Technical Reports Server (NTRS)

Stewart, W. L.; Johnson, H. W.; Weber, R. J.

1978-01-01

A review of five NASA engine-oriented propulsion programs of major importance to civil aviation are presented and discussed. Included are programs directed at exploring propulsion system concepts for (1) energy conservation subsonic aircraft (improved current turbofans, advanced turbofans, and advanced turboprops); (2) supersonic cruise aircraft (variable cycle engines); (3) general aviation aircraft (improved reciprocating engines and small gas turbines); (4) powered lift aircraft (advanced turbofans); and (5) advanced rotorcraft.

The antigens contributing to the serological cross-reactions of Proteus antisera with Klebsiella representatives.

PubMed

Palusiak, Agata

2015-03-01

Proteus sp. and Klebsiella sp. mainly cause infections of the urinary and respiratory tracts or wounds in humans. The representatives of both genera produce virulence factors like lipopolysaccharide (LPS) or outer membrane proteins (OMPs) having much in common in the structures and/or functions. To check how far this similarity is revealed in the serological cross-reactivity, the bacterial masses of 24 tested Klebsiella sp. strains were tested in ELISA with polyclonal rabbit antisera specific to the representatives of 79 Proteus O serogroups. The strongest reacting systems were selected to Western blot, where the majority of Klebsiella masses reacted in a way characteristic for electrophoretic patterns of proteins. The strongest reactions were obtained for proteins of near 67 and 40 kDa and 12.5 kDa. Mass spectrometry analysis of the proteins samples of one Proteus sp. and one Klebsiella sp. strain showed the GroEL like protein of a sequence GI number 2980926 to be similar for both strains. In Western blot some Klebsiella sp. masses reacted similarly to the homologous Proteus LPSs. The LPS contribution in the observed reactions of the high molecular-mass LPS species was confirmed for Klebsiella oxytoca 0.062. Copyright © 2014 Elsevier Ltd. All rights reserved.

Histopathological features of Proteus syndrome.

PubMed

Hoey, S E H; Eastwood, D; Monsell, F; Kangesu, L; Harper, J I; Sebire, N J

2008-05-01

Proteus syndrome is a rare, sporadic overgrowth disorder for which the underlying genetic defect remains unknown. Although the clinical course is well-described there is no systematic histopathological description of the lesional pathology. To describe the histopathological features encountered in a series of patients with Proteus syndrome from a single centre. Patients with Proteus syndrome who had undergone therapeutic surgical resection or biopsy were identified from a database and the histopathological findings were reviewed, with particular regard to descriptive features of the underlying tissue abnormality. There were 18 surgical specimens from nine patients, median age 4 years (range 1-9), classified into four main categories: soft-tissue swellings (lipomatous lesions), vascular anomalies (vascular malformation and haemangioma), macrodactyly (hamartomatous overgrowth) and others (sebaceous naevus and nonspecific features). In all cases, the clinical features of overgrowth were due to increased amounts of disorganized tissue, indicating a hamartomatous-type defect in which normal tissue constituents were present, but with an abnormal distribution and architecture. Vascular malformations represented a prominent category of lesions, accounting for 50% of the specimens, predominantly comprising lymphatic and lymphovascular malformations. No malignancy or cytological atypia was identified in any case. The histopathological features of lesions resected from children with Proteus syndrome predominantly include hamartomatous mixed connective tissue lesions, benign neoplasms such as lipomata, and lymphatic-rich vascular malformations.

The NASA Aircraft Energy Efficiency Program

NASA Technical Reports Server (NTRS)

Klineberg, J. M.

1978-01-01

The objective of the NASA Aircraft Energy Efficiency Program is to accelerate the development of advanced technology for more energy-efficient subsonic transport aircraft. This program will have application to current transport derivatives in the early 1980s and to all-new aircraft of the late 1980s and early 1990s. Six major technology projects were defined that could result in fuel savings in commercial aircraft: (1) Engine Component Improvement, (2) Energy Efficient Engine, (3) Advanced Turboprops, (4) Energy Efficiency Transport (aerodynamically speaking), (5) Laminar Flow Control, and (6) Composite Primary Structures.

14 CFR 135.421 - Additional maintenance requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... programs, or a program approved by the Administrator, for each aircraft engine, propeller, rotor, and each... instructions set forth by the manufacturer as required by this chapter for the aircraft, aircraft engine, propeller, rotor or item of emergency equipment. (c) For each single engine aircraft to be used in passenger...

14 CFR 135.421 - Additional maintenance requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... programs, or a program approved by the Administrator, for each aircraft engine, propeller, rotor, and each... instructions set forth by the manufacturer as required by this chapter for the aircraft, aircraft engine, propeller, rotor or item of emergency equipment. (c) For each single engine aircraft to be used in passenger...

14 CFR 135.421 - Additional maintenance requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... programs, or a program approved by the Administrator, for each aircraft engine, propeller, rotor, and each... instructions set forth by the manufacturer as required by this chapter for the aircraft, aircraft engine, propeller, rotor or item of emergency equipment. (c) For each single engine aircraft to be used in passenger...

14 CFR 135.421 - Additional maintenance requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... programs, or a program approved by the Administrator, for each aircraft engine, propeller, rotor, and each... instructions set forth by the manufacturer as required by this chapter for the aircraft, aircraft engine, propeller, rotor or item of emergency equipment. (c) For each single engine aircraft to be used in passenger...

14 CFR 135.421 - Additional maintenance requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... programs, or a program approved by the Administrator, for each aircraft engine, propeller, rotor, and each... instructions set forth by the manufacturer as required by this chapter for the aircraft, aircraft engine, propeller, rotor or item of emergency equipment. (c) For each single engine aircraft to be used in passenger...

Small unmanned aircraft and the U.S. Forest Service : benefits, costs, and recommendations for using small unmanned aircraft in Forest Service operations

DOT National Transportation Integrated Search

2016-08-01

This paper provides information to Forest Service leadership about how the agency could use unmanned aircraft across different programs, especially in program areas where aircraft use is currently limited. It draws from published uses of unmanned air...

Host Defense against Opportunist Microorganisms Following Trauma

DTIC Science & Technology

1991-09-30

Proteus mirabills. No evidence was obtained supporting involvement of lipoxygenase metabolites L. the bactericidal defect of neutrophils or the...burn wound sepsis with P. aeruginosa and Proteus mirabills were investigated [16]. The bacteria were spread over the surface of the burn wound to

Characterization of Proteus mirabilis isolates from broilers

USDA-ARS?s Scientific Manuscript database

Background: Proteus mirabilis is ubiquitous in the environment and is regarded as a part of the normal flora in human gastrointestinal tract. However, this bacterium is also an opportunistic human pathogen that causes urinary tract infections. Recently, this microorganism has been isolated from m...

21 CFR 520.90d - Ampicillin trihydrate for oral suspension.

Code of Federal Regulations, 2011 CFR

2011-04-01

...., Staphylococcus spp., and Streptococcus spp., urinary tract infections (cystitis) due to E. coli, Staphylococcus spp., Streptococcus spp., and Proteus spp.; bacterial gastroenteritis due to E. coli; generalized... (bacterial pneumonia) due to Staphylococcus spp., Streptococcus spp., E. coli, and Proteus spp.; urinary...

21 CFR 520.90d - Ampicillin trihydrate for oral suspension.

Code of Federal Regulations, 2010 CFR

2010-04-01

...., Staphylococcus spp., and Streptococcus spp., urinary tract infections (cystitis) due to E. coli, Staphylococcus spp., Streptococcus spp., and Proteus spp.; bacterial gastroenteritis due to E. coli; generalized... (bacterial pneumonia) due to Staphylococcus spp., Streptococcus spp., E. coli, and Proteus spp.; urinary...

Analysis of the Effectiveness of F-15E Risk Management during Peacetime Operations

DTIC Science & Technology

2015-06-18

of aircraft or life . These results were compared with existing risk management programs in the form of unit worksheet assessments. This study found...Force risk management program across all fixed-wing aircraft. Rotary wing aircraft will have their own unique challenges . However, for all its...the loss of aircraft or life . These results were compared with existing risk management programs in the form of unit worksheet assessments. This

GASP- General Aviation Synthesis Program. Volume 1: Main program. Part 1: Theoretical development

NASA Technical Reports Server (NTRS)

Hague, D.

1978-01-01

The General Aviation synthesis program performs tasks generally associated with aircraft preliminary design and allows an analyst the capability of performing parametric studies in a rapid manner. GASP emphasizes small fixed-wing aircraft employing propulsion systems varying froma single piston engine with fixed pitch propeller through twin turboprop/ turbofan powered business or transport type aircraft. The program, which may be operated from a computer terminal in either the batch or interactive graphic mode, is comprised of modules representing the various technical disciplines integrated into a computational flow which ensures that the interacting effects of design variables are continuously accounted for in the aircraft sizing procedure. The model is a useful tool for comparing configurations, assessing aircraft performance and economics, performing tradeoff and sensitivity studies, and assessing the impact of advanced technologies on aircraft performance and economics.

NASA's program on icing research and technology

NASA Technical Reports Server (NTRS)

Reinmann, John J.; Shaw, Robert J.; Ranaudo, Richard J.

1989-01-01

NASA's program in aircraft icing research and technology is reviewed. The program relies heavily on computer codes and modern applied physics technology in seeking icing solutions on a finer scale than those offered in earlier programs. Three major goals of this program are to offer new approaches to ice protection, to improve our ability to model the response of an aircraft to an icing encounter, and to provide improved techniques and facilities for ground and flight testing. This paper reviews the following program elements: (1) new approaches to ice protection; (2) numerical codes for deicer analysis; (3) measurement and prediction of ice accretion and its effect on aircraft and aircraft components; (4) special wind tunnel test techniques for rotorcraft icing; (5) improvements of icing wind tunnels and research aircraft; (6) ground de-icing fluids used in winter operation; (7) fundamental studies in icing; and (8) droplet sizing instruments for icing clouds.

The Aircraft Morphing Program

NASA Technical Reports Server (NTRS)

Wlezien, R. W.; Horner, G. C.; McGowan, A. R.; Padula, S. L.; Scott, M. A.; Silcox, R. J.; Simpson, J. O.

1998-01-01

In the last decade smart technologies have become enablers that cut across traditional boundaries in materials science and engineering. Here we define smart to mean embedded actuation, sensing, and control logic in a tightly coupled feedback loop. While multiple successes have been achieved in the laboratory, we have yet to see the general applicability of smart devices to real aircraft systems. The NASA Aircraft Morphing program is an attempt to couple research across a wide range of disciplines to integrate smart technologies into high payoff aircraft applications. The program bridges research in seven individual disciplines and combines the effort into activities in three primary program thrusts. System studies are used to assess the highest- payoff program objectives, and specific research activities are defined to address the technologies required for development of smart aircraft systems. In this paper we address the overall program goals and programmatic structure, and discuss the challenges associated with bringing the technologies to fruition.

Thesaurus of DDC Descriptors

DTIC Science & Technology

1966-06-01

BIRDS BLASTOMYCES BLATTIDAE BOVINES CANDIDA CANNABIS CARNIVORA CATS CEPHALOPODA CEREALS CETACEA CHICKENS CHILDREN CHIMPANZEES CHLORELLA...POLIOMYELITIS VIRUS POX VIRUSES PROTEUS PROTEUS VULGAR1S PROTOZOA PSEUOOMONADACEAE PSEUUOMONADALES PSEUDOMONAS PSEUDOMONAS AEROGINOSA RABIES VIRUS...ISLANUS MARYLAND MASSACHUSETTS MASSACHUSETTS BAY MEDITERRANEAN SEA MEDITERRANEAN SEA ISLANDS MELANESIA MEXICO MEXICO GULF MICHIGAN MICRONESIA

Proteus mirabilis interkingdom swarming signals attract blow flies

USDA-ARS?s Scientific Manuscript database

Flies transport specific bacteria with their larvae which provides a wider range of nutrients for those bacteria. Our hypothesis was that this symbiotic interaction may depend on interkingdom signaling. We obtained Proteus mirabilis from the salivary glands of the blow fly Lucilia sericat. This s...

Isolation, characterization and immunological reaction of proteus mirabilis isolates from broilers

USDA-ARS?s Scientific Manuscript database

Introduction: Proteus mirabilis, which is ubiquitous in the environment, is an opportunistic human pathogen that causes urinary tract infections. Recently, this bacterium has been isolated from many food producing animals, including poultry and its products. Moreover, reports have shown P. mirabi...

Ureases as a target for the treatment of gastric and urinary infections.

PubMed

Follmer, C

2010-05-01

Urease is known to be a major contributor to pathologies induced by Helicobacter pylori and Proteus species. In H pylori, urease allows the bacteria to survive in an acidic gastric environment during colonisation, playing an important role in the pathogenesis of gastric and peptic ulcers. Ureolytic activity also results in the production of ammonia in close proximity to the gastric epithelium, causing cell damage and inflammation. In the case of Proteus species (notably Proteus mirabilis) infection, stones are formed due to the presence of ammonia and carbon dioxide released by urease action. In addition, the ammonia released is able to damage the glycosaminoglycan layer, which protects the urothelial surface against bacterial infection. In this context, the administration of urease inhibitors may be an effective therapy for urease-dependent pathogenic bacteria. This is a review of the role of ureases in H pylori and Proteus species infections, focussing on the biochemical and clinical aspects of the most promising and/or potent urease inhibitors for the treatment of gastric and urinary tract infections.

The surfaces of Larissa and Proteus

NASA Astrophysics Data System (ADS)

Stooke, Philip J.

1994-01-01

Topographic models of Neptune's small inner satellites Larissa and Proteus were derived from the shapes of limbs and terminators in Voyager images, modified locally to accomodate large craters and ridges. The models are presented here in tabular and graphic form, including the first map of Larissa and the first detailed relief map of Proteus. The shape of Larissa is approximated by a triaxial ellipsoid with axes of 208, 192 and 178 km, but is only weakly constrained by the single available view. The volume is estimated to be 3.5 +/- 1.0 x 106cu km. The surface is heavily cratered and may be crossed by one or two poorly seen linear ridges. Proteus is approximated by a triaxial ellipsoid with axes of 424, 390 and 396 km (the latter being the rotation axis dimension). The volume is estimated to be 3.4 +/- 0.4 x 107 cu km. Its surface appears to be very heavily cratered and extensive evidence for linear fractures is observed despite very low image quality.

A Historical Review of Training Requirements for Unmanned Aircraft Systems, Small Unmanned Aircraft Systems, and Manned Operations (1997-2014)

DOT National Transportation Integrated Search

2017-08-01

There are several mature Unmanned Aircraft System (UAS) and Small Unmanned Aircraft System (sUAS) training programs available for analysis. Many of these programs were developed by the various branches with the U.S. Department of Defense (DoD) in con...

STOVL aircraft simulation for integrated flight and propulsion control research

NASA Technical Reports Server (NTRS)

Mihaloew, James R.; Drummond, Colin K.

1989-01-01

The United States is in the initial stages of committing to a national program to develop a supersonic short takeoff and vertical landing (STOVL) aircraft. The goal of the propulsion community in this effort is to have the enabling propulsion technologies for this type aircraft in place to permit a low risk decision regarding the initiation of a research STOVL supersonic attack/fighter aircraft in the late mid-90's. This technology will effectively integrate, enhance, and extend the supersonic cruise, STOVL and fighter/attack programs to enable U.S. industry to develop a revolutionary supersonic short takeoff and vertical landing fighter/attack aircraft in the post-ATF period. A joint NASA Lewis and NASA Ames research program, with the objective of developing and validating technology for integrated-flight propulsion control design methodologies for short takeoff and vertical landing (STOVL) aircraft, was planned and is underway. This program, the NASA Supersonic STOVL Integrated Flight-Propulsion Controls Program, is a major element of the overall NASA-Lewis Supersonic STOVL Propulsion Technology Program. It uses an integrated approach to develop an integrated program to achieve integrated flight-propulsion control technology. Essential elements of the integrated controls research program are realtime simulations of the integrated aircraft and propulsion systems which will be used in integrated control concept development and evaluations. This paper describes pertinent parts of the research program leading up to the related realtime simulation development and remarks on the simulation structure to accommodate propulsion system hardware drop-in for real system evaluation.

78 FR 18932 - Public Meeting: Unmanned Aircraft Systems Test Site Program; Privacy Approach

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-28

... operation of the UAS Test Sites. They are not intended to pre-determine the long- term policy and regulatory...-0061] Public Meeting: Unmanned Aircraft Systems Test Site Program; Privacy Approach AGENCY: Federal... the unmanned aircraft systems (UAS) test site program. The FAA is seeking the views from the public...

Proteus syndrome: a case report.

PubMed

Pangkanon, S; Limpongsanurak, W; Sangtawesin, V

2001-05-01

Proteus syndrome is a rare genetic disorder, characterized by partial gigantism of the hands and/or feet, asymmetry of the limbs, plantar hyperplasia, multiple hamartomatous subcutaneous tumors, hyperostoses, and long bone overgrowth. A one day old Thai male infant is reported with macrosomia, hemihypertrophy of the left side of the face and left leg, large feet, macrodactyly of toes, plantar hyperplasia, large subcutaneous mass with a violet-red surface over the left side of the chest wall and a large port-wine stain involving the lateral aspect of the right chest wall. The clinical findings, diagnostic criteria, differential diagnosis, and management of the Proteus syndrome are reviewed.

Infective organisms in the cytoplasm of Amoeba proteus.

PubMed

ROTH, L E; DANIELS, E W

1961-02-01

Evidence from electron and phase microscopy is given which shows that infective organisms are present in the cytoplasm of Amoeba proteus. Vesicles containing living organisms have been observed after repeated washing and starvation of the amebae for a period of 2 weeks. Exposure to gamma-radiation in conjunction with starvation, repeated washing, isolation of single amebae, refeeding with contaminant-free Tetrahymena, and clone selection has produced clones with reduced cytoplasmic infection. These findings are discussed in regard to the autoradiographic studies of other investigators on Amoeba proteus. The controversies over whether DNA and RNA are synthesized in the cytoplasm may be resolved by the finding of cytoplasmic infection.

INFECTIVE ORGANISMS IN THE CYTOPLASM OF AMOEBA PROTEUS

PubMed Central

Roth, L. E.; Daniels, E. W.

1961-01-01

Evidence from electron and phase microscopy is given which shows that infective organisms are present in the cytoplasm of Amoeba proteus. Vesicles containing living organisms have been observed after repeated washing and starvation of the amebae for a period of 2 weeks. Exposure to γ-radiation in conjunction with starvation, repeated washing, isolation of single amebae, refeeding with contaminant-free Tetrahymena, and clone selection has produced clones with reduced cytoplasmic infection. These findings are discussed in regard to the autoradiographic studies of other investigators on Amoeba proteus. The controversies over whether DNA and RNA are synthesized in the cytoplasm may be resolved by the finding of cytoplasmic infection. PMID:13743844

Effectiveness evaluation of STOL transport operations (phase 2). [computer simulation program of commercial short haul aircraft operations

NASA Technical Reports Server (NTRS)

Welp, D. W.; Brown, R. A.; Ullman, D. G.; Kuhner, M. B.

1974-01-01

A computer simulation program which models a commercial short-haul aircraft operating in the civil air system was developed. The purpose of the program is to evaluate the effect of a given aircraft avionics capability on the ability of the aircraft to perform on-time carrier operations. The program outputs consist primarily of those quantities which can be used to determine direct operating costs. These include: (1) schedule reliability or delays, (2) repairs/replacements, (3) fuel consumption, and (4) cancellations. More comprehensive models of the terminal area environment were added and a simulation of an existing airline operation was conducted to obtain a form of model verification. The capability of the program to provide comparative results (sensitivity analysis) was then demonstrated by modifying the aircraft avionics capability for additional computer simulations.

Technology for reducing aircraft engine pollution

NASA Technical Reports Server (NTRS)

Rudey, R. A.; Kempke, E. E., Jr.

1975-01-01

Programs have been initiated by NASA to develop and demonstrate advanced technology for reducing aircraft gas turbine and piston engine pollutant emissions. These programs encompass engines currently in use for a wide variety of aircraft from widebody-jets to general aviation. Emission goals for these programs are consistent with the established EPA standards. Full-scale engine demonstrations of the most promising pollutant reduction techniques are planned within the next three years. Preliminary tests of advanced technology gas turbine engine combustors indicate that significant reductions in all major pollutant emissions should be attainable in present generation aircraft engines without adverse effects on fuel consumption. Fundamental-type programs are yielding results which indicate that future generation gas turbine aircraft engines may be able to utilize extremely low pollutant emission combustion systems.

Impact and promise of NASA aeropropulsion technology

NASA Technical Reports Server (NTRS)

Saunders, Neal T.; Bowditch, David N.

1987-01-01

The aeropropulsion industry in the United States has established an enviable record of leading the world in aeropropulsion for commercial and military aircraft. The NASA aeropropulsion propulsion program (primarily conducted through the Lewis Research Center) has significantly contributed to that success through research and technology advances and technology demonstrations such as the Refan, Engine Component Improvement, and the Energy Efficient Engine Programs. Some past NASA contributions to engines in current aircraft are reviewed, and technologies emerging from current research programs for the aircraft of the 1990's are described. Finally, current program thrusts toward improving propulsion systems in the 2000's for subsonic commercial aircraft and higher speed aircraft such as the High-Speed Civil Transport and the National Aerospace Plane (NASP) are discussed.

The atmospheric effects of stratospheric aircraft: A third program report

NASA Technical Reports Server (NTRS)

Stolarski, Richard S. (Editor); Wesoky, Howard L. (Editor)

1993-01-01

A third report from the Atmospheric Effects of Stratospheric Aircraft (AESA) component of NASA's High-Speed Research Program (HSRP) is presented. Market and technology considerations continue to provide an impetus for high-speed civil transport research. A recent United Nations Environment Program scientific assessment showed that considerable uncertainty still exists about the possible impact of aircraft on the atmosphere. The AESA was designed to develop the body of scientific knowledge necessary for the evaluation of the impact of stratospheric aircraft on the atmosphere. The first Program report presented the basic objectives and plans for AESA. This third report marks the midpoint of the program and presents the status of the ongoing research on the impact of stratospheric aircraft on the atmosphere as reported at the third annual AESA Program meeting in June 1993. The focus of the program is on predicted atmospheric changes resulting from projected HSCT emissions. Topics reported on cover how high-speed civil transports (HSCT) might affect stratospheric ozone, emissions scenarios and databases to assess potential atmospheric effects from HSCT's, calculated results from 2-D zonal mean models using emissions data, engine trace constituent measurements, and exhaust plume/aircraft wake vortex interactions.

Synthetic extreme environments: overlooked sources of potential biotechnologically relevant microorganisms.

PubMed

Sibanda, Timothy; Selvarajan, Ramganesh; Tekere, Memory

2017-05-01

Synthetic extreme environments like carwash effluent tanks and drains are potential sources of biotechnologically important microorganisms and molecules which have, however, remained unexplored. Using culture- and molecular-based methods, a total of 17 bacterial isolates belonging to the genera Shewanella, Proteus, Paenibacillus, Enterobacter and Citrobacter, Aeromonas, Pseudomonas and Pantoea were identified. Hydrocarbon utilization and enzyme production screening assays showed that Aeromonas sp. CAC11, Paenibacillus sp. CAC12 and Paenibacillus sp. CAC13 and Citrobacter sp. PCW7 were able to degrade benzanthracene, naphthalene and diesel oil, Paenibacillus sp. CAC12 and Paenibacillus sp. CAC13 could produce cellulase enzyme, while Proteus sp. BPS2, Pseudomonas sp. SAS8 and Proteus sp. CAL3 could produce lipase. GC-MS analysis of bacterial secondary metabolites resulted in identification of 107 different compounds produced by Proteus sp. BPS2, Paenibacillus sp. CAC12, Pseudomonas sp. SAS8, Proteus sp. CAL3 and Paenibacillus sp. CAC13. Most of the compounds identified by both GC-MS and LC-MS have previously been determined to have antibacterial, antifungal and/or anticancer properties. Further, microbial metabolites which have previously been known to be produced only by plants or microorganisms found in natural extreme environments were also identified in this study. This research has revealed the immense bioresource potential of microorganisms inhabiting synthetic extreme environments. © 2017 The Authors. Microbial Biotechnology published by John Wiley & Sons Ltd and Society for Applied Microbiology.

Analysis and calculation of lightning-induced voltages in aircraft electrical circuits

NASA Technical Reports Server (NTRS)

Plumer, J. A.

1974-01-01

Techniques to calculate the transfer functions relating lightning-induced voltages in aircraft electrical circuits to aircraft physical characteristics and lightning current parameters are discussed. The analytical work was carried out concurrently with an experimental program of measurements of lightning-induced voltages in the electrical circuits of an F89-J aircraft. A computer program, ETCAL, developed earlier to calculate resistive and inductive transfer functions is refined to account for skin effect, providing results more valid over a wider range of lightning waveshapes than formerly possible. A computer program, WING, is derived to calculate the resistive and inductive transfer functions between a basic aircraft wing and a circuit conductor inside it. Good agreement is obtained between transfer inductances calculated by WING and those reduced from measured data by ETCAL. This computer program shows promise of expansion to permit eventual calculation of potential lightning-induced voltages in electrical circuits of complete aircraft in the design stage.

Role of research aircraft in technology development

NASA Technical Reports Server (NTRS)

Szalai, K. J.

1984-01-01

The United States's aeronautical research program has been rich in the use of research aircraft to explore new flight regimes, develop individual aeronautical concepts, and investigate new vehicle classes and configurations. This paper reviews the NASA supercritical wing, digital fly-by-wire, HiMAT, and AD-1 oblique-wing flight research programs, and draws from these examples general conclusions regarding the role and impact of research aircraft in technology development. The impact of a flight program on spinoff technology is also addressed. The secondary, serendipitous results are often highly significant. Finally, future research aircraft programs are examined for technology trends and expected results.

A computer program for detailed analysis of the takeoff and approach performance capabilities of transport category aircraft

NASA Technical Reports Server (NTRS)

Foss, W. E., Jr.

1979-01-01

The takeoff and approach performance of an aircraft is calculated in accordance with the airworthiness standards of the Federal Aviation Regulations. The aircraft and flight constraints are represented in sufficient detail to permit realistic sensitivity studies in terms of either configuration modifications or changes in operational procedures. The program may be used to investigate advanced operational procedures for noise alleviation such as programmed throttle and flap controls. Extensive profile time history data are generated and are placed on an interface file which can be input directly to the NASA aircraft noise prediction program (ANOPP).

NASA Boeing 737 Aircraft Test Results from 1996 Joint Winter Runway Friction Measurement Program

NASA Technical Reports Server (NTRS)

Yager, Thomas J.

1996-01-01

A description of the joint test program objectives and scope is given together with the performance capability of the NASA Langley B-737 instrumented aircraft. The B-737 test run matrix conducted during the first 8 months of this 5-year program is discussed with a description of the different runway conditions evaluated. Some preliminary test results are discussed concerning the Electronic Recording Decelerometer (ERD) readings and a comparison of B-737 aircraft braking performance for different winter runway conditions. Detailed aircraft parameter time history records, analysis of ground vehicle friction measurements and harmonization with aircraft braking performance, assessment of induced aircraft contaminant drag, and evaluation of the effects of other factors on aircraft/ground vehicle friction performance will be documented in a NASA Technical Report which is being prepared for publication next year.

Integrated Research/Education University Aircraft Design Program Development

DTIC Science & Technology

2017-04-06

iterations and loop shaping compared to MIMO control methods. Despite the drawbacks, loop closure and classical methods are the design methods most commonly...AFRL-AFOSR-VA-TR-2017-0077 Integrated Research/Education University Aircraft Design Program Development Eli Livne UNIVERSITY OF WASHINGTON 4333...SUBTITLE Integrated Research/Education University Aircraft Design Program Development 5a.  CONTRACT NUMBER 5b.  GRANT NUMBER FA9550-14-1-0027 5c.  PROGRAM

21 CFR 866.3410 - Proteus spp. (Weil-Felix) serological reagents.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 21 Food and Drugs 8 2014-04-01 2014-04-01 false Proteus spp. (Weil-Felix) serological reagents. 866.3410 Section 866.3410 Food and Drugs FOOD AND DRUG ADMINISTRATION, DEPARTMENT OF HEALTH AND HUMAN SERVICES (CONTINUED) MEDICAL DEVICES IMMUNOLOGY AND MICROBIOLOGY DEVICES Serological Reagents § 866.3410...

21 CFR 866.3410 - Proteus spp. (Weil-Felix) serological reagents.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 21 Food and Drugs 8 2013-04-01 2013-04-01 false Proteus spp. (Weil-Felix) serological reagents. 866.3410 Section 866.3410 Food and Drugs FOOD AND DRUG ADMINISTRATION, DEPARTMENT OF HEALTH AND HUMAN SERVICES (CONTINUED) MEDICAL DEVICES IMMUNOLOGY AND MICROBIOLOGY DEVICES Serological Reagents § 866.3410...

21 CFR 866.3410 - Proteus spp. (Weil-Felix) serological reagents.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 21 Food and Drugs 8 2012-04-01 2012-04-01 false Proteus spp. (Weil-Felix) serological reagents. 866.3410 Section 866.3410 Food and Drugs FOOD AND DRUG ADMINISTRATION, DEPARTMENT OF HEALTH AND HUMAN SERVICES (CONTINUED) MEDICAL DEVICES IMMUNOLOGY AND MICROBIOLOGY DEVICES Serological Reagents § 866.3410...

Isolation and partial characterization of two plasmid deoxyribonucleic acids from endosymbiotic bacteria of Amoeba proteus.

PubMed Central

Han, J H; Jeon, K W

1980-01-01

Obligatory endosymbiotic bacteria in a strain of Amoeba proteus were found to harbor two distinct species of plasmid, pHJ11 and pHJ12. Their molecular weights were 39 x 10(6) and 14 x 10(6), respectively. Images PMID:7364732

NASA Aeronautics: Research and Technology Program Highlights

NASA Technical Reports Server (NTRS)

1990-01-01

This report contains numerous color illustrations to describe the NASA programs in aeronautics. The basic ideas involved are explained in brief paragraphs. The seven chapters deal with Subsonic aircraft, High-speed transport, High-performance military aircraft, Hypersonic/Transatmospheric vehicles, Critical disciplines, National facilities and Organizations & installations. Some individual aircraft discussed are : the SR-71 aircraft, aerospace planes, the high-speed civil transport (HSCT), the X-29 forward-swept wing research aircraft, and the X-31 aircraft. Critical disciplines discussed are numerical aerodynamic simulation, computational fluid dynamics, computational structural dynamics and new experimental testing techniques.

Aircraft noise source and computer programs - User's guide

NASA Technical Reports Server (NTRS)

Crowley, K. C.; Jaeger, M. A.; Meldrum, D. F.

1973-01-01

The application of computer programs for predicting the noise-time histories and noise contours for five types of aircraft is reported. The aircraft considered are: (1) turbojet, (2) turbofan, (3) turboprop, (4) V/STOL, and (5) helicopter. Three principle considerations incorporated in the design of the noise prediction program are core effectiveness, limited input, and variable output reporting.

Simulating a Direction-Finder Search for an ELT

NASA Technical Reports Server (NTRS)

Bream, Bruce

2005-01-01

A computer program simulates the operation of direction-finding equipment engaged in a search for an emergency locator transmitter (ELT) aboard an aircraft that has crashed. The simulated equipment is patterned after the equipment used by the Civil Air Patrol to search for missing aircraft. The program is designed to be used for training in radio direction-finding and/or searching for missing aircraft without incurring the expense and risk of using real aircraft and ground search resources. The program places a hidden ELT on a map and enables the user to search for the location of the ELT by moving a 14 NASA Tech Briefs, March 2005 small aircraft image around the map while observing signal-strength and direction readings on a simulated direction- finding locator instrument. As the simulated aircraft is turned and moved on the map, the program updates the readings on the direction-finding instrument to reflect the current position and heading of the aircraft relative to the location of the ELT. The software is distributed in a zip file that contains an installation program. The software runs on the Microsoft Windows 9x, NT, and XP operating systems.

Impact and promise of NASA aeropropulsion technology

NASA Technical Reports Server (NTRS)

Saunders, Neal T.; Bowditch, David N.

1990-01-01

The aeropropulsion industry in the U.S. has established an enviable record of leading the world in aeropropulsion for commercial and military aircraft. NASA's aeropropulsion program (primarily conducted through the Lewis Research Center) has significantly contributed to that success through research and technology advances and technology demonstration. Some past NASA contributions to engines in current aircraft are reviewed, and technologies emerging from current research programs for the aircraft of the 1990's are described. Finally, current program thrusts toward improving propulsion systems in the 2000's for subsonic commercial aircraft and higher speed aircraft such as the High-Speed Civil Transport and the National Aerospace Plane are discussed.

Quiet Short-Haul Research Aircraft Joint Navy/NASA Sea Trials

NASA Technical Reports Server (NTRS)

Queen, S.; Cochrane, J.

1982-01-01

The Quiet Short-Haul Research Aircraft (QSRA) is a flight facility which Ames Research Center is using to conduct a broad program of terminal area and low-speed, propulsive-life flight research. A joint Navy/NASA flight research program used the QSRA to investigate the application of advanced propulsive-lift technology to the naval aircraft-carrier environment. Flight performance of the QSRA is presented together with the results or the joint Navy/NASA flight program. During the joint program, the QSRA operated aboard the USS Kitty Hawk for 4 days, during which numerous unarrested landings and free deck takeoffs were accomplished. These operations demonstrated that a large aircraft incorporating upper-surface-blowing, propulsive-life technology can be operated in the aircraft-carrier environment without any unusual problems.

Airworthiness criteria development for powered-lift aircraft: A program summary

NASA Technical Reports Server (NTRS)

Heffley, R. K.; Stapleford, R. L.; Rumold, R. C.

1977-01-01

A four-year simulation program to develop airworthiness criteria for powered-lift aircraft is summarized. All flight phases affected by use of powered lift (approach, landing, takeoff) are treated with regard to airworthiness problem areas (limiting flight conditions and safety margins: stability, control, and performance; and systems failure). The general features of powered-lift aircraft are compared to conventional aircraft.

Computer program to predict noise of general aviation aircraft: User's guide

NASA Technical Reports Server (NTRS)

Mitchell, J. A.; Barton, C. K.; Kisner, L. S.; Lyon, C. A.

1982-01-01

Program NOISE predicts General Aviation Aircraft far-field noise levels at FAA FAR Part 36 certification conditions. It will also predict near-field and cabin noise levels for turboprop aircraft and static engine component far-field noise levels.

Studies of aircraft differential maneuvering. Report 75-27: Calculating of differential-turning barrier surfaces. Report 75-26: A user's guide to the aircraft energy-turn and tandem-motion computer programs. Report 75-7: A user's guide to the aircraft energy-turn hodograph program. [numerical analysis of tactics and aircraft maneuvers of supersonic attack aircraft

NASA Technical Reports Server (NTRS)

Kelley, H. J.; Lefton, L.

1976-01-01

The numerical analysis of composite differential-turn trajectory pairs was studied for 'fast-evader' and 'neutral-evader' attitude dynamics idealization for attack aircraft. Transversality and generalized corner conditions are examined and the joining of trajectory segments discussed. A criterion is given for the screening of 'tandem-motion' trajectory segments. Main focus is upon the computation of barrier surfaces. Fortunately, from a computational viewpoint, the trajectory pairs defining these surfaces need not be calculated completely, the final subarc of multiple-subarc pairs not being required. Some calculations for pairs of example aircraft are presented. A computer program used to perform the calculations is included.

Aircraft operations management manual

NASA Technical Reports Server (NTRS)

1992-01-01

The NASA aircraft operations program is a multifaceted, highly diverse entity that directly supports the agency mission in aeronautical research and development, space science and applications, space flight, astronaut readiness training, and related activities through research and development, program support, and mission management aircraft operations flights. Users of the program are interagency, inter-government, international, and the business community. This manual provides guidelines to establish policy for the management of NASA aircraft resources, aircraft operations, and related matters. This policy is an integral part of and must be followed when establishing field installation policy and procedures covering the management of NASA aircraft operations. Each operating location will develop appropriate local procedures that conform with the requirements of this handbook. This manual should be used in conjunction with other governing instructions, handbooks, and manuals.

First Earth-based observations of Neptune's satellite Proteus

NASA Astrophysics Data System (ADS)

Colas, F.; Buil, C.

1992-08-01

Proteus (Neptune III) was discovered from Voyager Spacecraft images in 1989 (Smith, 1989). It was never observed from ground-based observatories because of its magnitude (m = 20.3) and closeness to Neptune (maximum elongation = 6 arcsec). In October 1991, we used the 2.2 m telescope at the European Southern Observatory (La Silla, Chile) to look for it. The observation success is mainly due to the use of an anti blooming CCD and to good seeing conditions (less than 1 arcsec). We give the differential positions of Proteus referred to Neptune and we compare with theoretical positions issued from Voyager's data (Owen et al., 1991). We found that the rms orbital residual was about 0.1 arcsec.

Aeronautics research and technology program and specific objectives

NASA Technical Reports Server (NTRS)

1981-01-01

Aeronautics research and technology program objectives in fluid and thermal physics, materials and structures, controls and guidance, human factors, multidisciplinary activities, computer science and applications, propulsion, rotorcraft, high speed aircraft, subsonic aircraft, and rotorcraft and high speed aircraft systems technology are addressed.

Program on ground test of modified quiet, clean, JT3D and JT8D turbofan engines in their respective nacelles. [modification of Boeing 707, 727, and 737 aircraft for aircraft noise reduction

NASA Technical Reports Server (NTRS)

1973-01-01

A program to reduce the community noise levels of commercial jet aircraft is summarized. The program objective is the development of three acoustically treated nacelle configurations for the 707, 727, and 737 series aircraft to provide maximum noise reduction with minimum performance loss, modification requirements, and economic impact. The preliminary design, model testing, data analyses, and economic studies of proposed nacelle configurations are discussed.

Aircraft radial-belted tire evaluation

NASA Technical Reports Server (NTRS)

Yager, Thomas J.; Stubbs, Sandy M.; Davis, Pamela A.

1990-01-01

An overview is given of the ongoing joint NASA/FAA/Industry Surface Traction And Radial Tire (START) Program being conducted at NASA Langley's Aircraft Landing Dynamics Facility (ALDF). The START Program involves tests using three different tire sizes to evaluate tire rolling resistance, braking, and cornering performance throughout the aircraft ground operational speed range for both dry and wet runway surfaces. Preliminary results from recent 40 x 14 size bias-ply, radial-belted, and H-type aircraft tire tests are discussed. The paper concludes with a summary of the current program status and planned ALDF test schedule.

Genome sequence of a Proteus mirabilis strain isolated from the salivary glands of larval Lucilia sericata

USDA-ARS?s Scientific Manuscript database

We announced a draft genome sequence of a Proteus mirabilis strain derived from Lucilia sericata salivary glands. This strain is demonstrated to attract and induce oviposition by L. sericata, a common blow fly important to medicine, agriculture, and forensics. The genome will help to dissect inter...

Integration of the blaNDM-1 carbapenemase gene into Proteus genomic island 1 (PGI1-PmPEL) in a Proteus mirabilis clinical isolate.

PubMed

Girlich, Delphine; Dortet, Laurent; Poirel, Laurent; Nordmann, Patrice

2015-01-01

To decipher the mechanisms and their associated genetic determinants responsible for β-lactam resistance in a Proteus mirabilis clinical isolate. The entire genetic structure surrounding the β-lactam resistance genes was characterized by PCR, gene walking and DNA sequencing. Genes encoding the carbapenemase NDM-1 and the ESBL VEB-6 were located in a 38.5 kb MDR structure, which itself was inserted into a new variant of the Proteus genomic island 1 (PGI1). This new PGI1-PmPEL variant of 64.4 kb was chromosomally located, as an external circular form in the P. mirabilis isolate, suggesting potential mobility. This is the first known description of the bla(NDM-1) gene in a genomic island structure, which might further enhance the spread of the bla(NDM-1) carbapenemase gene among enteric pathogens. © The Author 2014. Published by Oxford University Press on behalf of the British Society for Antimicrobial Chemotherapy. All rights reserved. For Permissions, please e-mail: journals.permissions@oup.com.

Small transport aircraft technology

NASA Technical Reports Server (NTRS)

Williams, L. J.

1983-01-01

Information on commuter airline trends and aircraft developments is provided to upgrade the preliminary findings of a NASA-formed small transport aircraft technology (STAT) team, established to determine whether the agency's research and development programs could help commuter aircraft manufacturers solve technical problems related to passenger acceptance and use of 19- to 50-passenger aircraft. The results and conclusions of the full set of completed STAT studies are presented. These studies were performed by five airplane manufacturers, five engine manufacturers, and two propeller manufacturers. Those portions of NASA's overall aeronautics research and development programs which are applicable to commuter aircraft design are summarized. Areas of technology that might beneficially be expanded or initiated to aid the US commuter aircraft manufacturers in the evolution of improved aircraft for the market are suggested.

A summary of joint US-Canadian augmentor wing powered-lift STOL research programs at the Ames Research Center, NASA, 1975-1980

NASA Technical Reports Server (NTRS)

Hindson, W. S.; Hardy, G.

1980-01-01

Several different flight research programs carried out by NASA and the Canadian Government using the Augmentor Wing Jet STOL Research Aircraft to investigate the design, operational, and systems requirements for powered-lift STOL aircraft are summarized. Some of these programs considered handling qualities and certification criteria for this class of aircraft, and addressed pilot control techniques, control system design, and improved cockpit displays for the powered-lift STOL approach configuration. Other programs involved exploiting the potential of STOL aircraft for constrained terminal-area approaches within the context of present or future air traffic control environments. Both manual and automatic flight control investigations are discussed, and an extensive bibliography of the flight programs is included.

NASA's aircraft icing technology program

NASA Technical Reports Server (NTRS)

Reinmann, John J.

1991-01-01

NASA' Aircraft Icing Technology program is aimed at developing innovative technologies for safe and efficient flight into forecasted icing. The program addresses the needs of all aircraft classes and supports both commercial and military applications. The program is guided by three key strategic objectives: (1) numerically simulate an aircraft's response to an in-flight icing encounter, (2) provide improved experimental icing simulation facilities and testing techniques, and (3) offer innovative approaches to ice protection. Our research focuses on topics that directly support stated industry needs, and we work closely with industry to assure a rapid and smooth transfer of technology. This paper presents selected results that illustrate progress towards the three strategic objectives, and it provides a comprehensive list of references on the NASA icing program.

Highly integrated digital electronic control: Digital flight control, aircraft model identification, and adaptive engine control

NASA Technical Reports Server (NTRS)

Baer-Riedhart, Jennifer L.; Landy, Robert J.

1987-01-01

The highly integrated digital electronic control (HIDEC) program at NASA Ames Research Center, Dryden Flight Research Facility is a multiphase flight research program to quantify the benefits of promising integrated control systems. McDonnell Aircraft Company is the prime contractor, with United Technologies Pratt and Whitney Aircraft, and Lear Siegler Incorporated as major subcontractors. The NASA F-15A testbed aircraft was modified by the HIDEC program by installing a digital electronic flight control system (DEFCS) and replacing the standard F100 (Arab 3) engines with F100 engine model derivative (EMD) engines equipped with digital electronic engine controls (DEEC), and integrating the DEEC's and DEFCS. The modified aircraft provides the capability for testing many integrated control modes involving the flight controls, engine controls, and inlet controls. This paper focuses on the first two phases of the HIDEC program, which are the digital flight control system/aircraft model identification (DEFCS/AMI) phase and the adaptive engine control system (ADECS) phase.

A Program in Air Transportation Technology (Joint University Program)

NASA Technical Reports Server (NTRS)

Stengel, Robert F.

1996-01-01

The Joint University Program on Air Transportation Technology was conducted at Princeton University from 1971 to 1995. Our vision was to further understanding of the design and operation of transport aircraft, of the effects of atmospheric environment on aircraft flight, and of the development and utilization of the National Airspace System. As an adjunct, the program emphasized the independent research of both graduate and undergraduate students. Recent principal goals were to develop and verify new methods for design and analysis of intelligent flight control systems, aircraft guidance logic for recovery from wake vortex encounter, and robust flight control systems. Our research scope subsumed problems associated with multidisciplinary aircraft design synthesis and analysis based on flight physics, providing a theoretical basis for developing innovative control concepts that enhance aircraft performance and safety. Our research focus was of direct interest not only to NASA but to manufacturers of aircraft and their associated systems. Our approach, metrics, and future directions described in the remainder of the report.

Design of a proteus lattice representative of a burnt and fresh fuel interface at power conditions in light water reactors

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hursin, M.; Perret, G.

The research program LIFE (Large-scale Irradiated Fuel Experiment) between PSI and Swissnuclear has been started in 2006 to study the interaction between large sets of burnt and fresh fuel pins in conditions representative of power light water reactors. Reactor physics parameters such as flux ratios and reaction rate distributions ({sup 235}U and {sup 238}U fissions and {sup 238}U capture) are calculated to estimate an appropriate arrangement of burnt and fresh fuel pins within the central element of the test zone of the zero-power research reactor PROTEUS. The arrangement should minimize the number of burnt fuel pins to ease fuel handlingmore » and reduce costs, whilst guaranteeing that the neutron spectrum in both burnt and fresh fuel regions and at their interface is representative of a large uniform array of burnt and fresh pins in the same moderation conditions. First results are encouraging, showing that the burnt/fresh fuel interface is well represented with a 6 x 6 bundle of burnt pins. The second part of the project involves the use of TSUNAMI, CASMO-4E and DAKOTA to perform parametric and optimization studies on the PROTEUS lattice by varying its pitch (P) and fraction of D{sub 2}O in moderator (F{sub D2O}) to be as representative as possible of a power light water reactor core at hot full power conditions at beginning of cycle (BOC). The parameters P and F{sub D2O} that best represent a PWR at BOC are 1.36 cm and 5% respectively. (authors)« less

Guidebook for preparation of aircraft-system survivability requirements for procurement documents. Final report, October 1975-October 1976

DOE Office of Scientific and Technical Information (OSTI.GOV)

Morrow, J.J.; Burris, R.A.; Watson, D.J.

1977-05-01

This report is intended to provide guidelines for the preparation of procurements specifications for aircraft survivability enhancement equipment, for the survivability/vulnerability (S/V) tasks associated with the procurement of a total aircraft system or its relate subsystems, and also for the modification of current fleet aircraft to their related subsystems. It is intended that these S/V procurement guidelines be applied to the procurement of all military aircraft, aircraft subsystems, and aircraft componenets which can either lose their functional capability of have their performance degraded as a result of interactions with the damage mechanisms of threat weapons. The guidelines should be appliedmore » to preliminary design programs, to production programs, and to programs that will retrofit or modify existing systems. These guidelines include general requirements statements for the establishment of an S/V program, requirements statements for reducing the susceptibility of the system to the threat weapons, and requirements for the reduction of vulnerability to nonnuclear, nuclear, and laser weapon effects. Requirements for S/V assessments and the verification of vulnerability levels and survival enhancement features are also included. Although nuclear and laser weapon effects are included, the major emphasis is on the reduction of susceptibility and vulnerability to conventional weapons and the establishment of the S/V program.« less

DEKFIS user's guide: Discrete Extended Kalman Filter/Smoother program for aircraft and rotorcraft data consistency

NASA Technical Reports Server (NTRS)

1979-01-01

The computer program DEKFIS (discrete extended Kalman filter/smoother), formulated for aircraft and helicopter state estimation and data consistency, is described. DEKFIS is set up to pre-process raw test data by removing biases, correcting scale factor errors and providing consistency with the aircraft inertial kinematic equations. The program implements an extended Kalman filter/smoother using the Friedland-Duffy formulation.

Aircraft wake vortices : a state-of-the-art review of the United States R&D program

DOT National Transportation Integrated Search

1977-02-28

The report summarizes the current state-of-the-art understanding : of the aircraft wake vortex phenomenon and the results of the United : States program to minimize the restrictions caused by aircraft wake : vortices in the terminal environment. The ...

An overview of the quiet short-haul research aircraft program

NASA Technical Reports Server (NTRS)

Shovlin, M. D.; Cochrane, J. A.

1978-01-01

An overview of the Quiet Short Haul Research Aircraft (QSRA) Program is presented, with special emphasis on its propulsion and acoustic aspects. A description of the NASA technical participation in the program including wind tunnel testing, engine ground tests, and advanced aircraft simulation is given. The aircraft and its systems are described and, measured performance, where available, is compared to program goals. Preliminary data indicate that additional research and development are needed in some areas of which acoustics is an example. Some of these additional research areas and potential experiments using the QSRA to develop the technology are discussed. The concept of the QSRA as a national flight research facility is explained.

THE CONTENT AND RELATIVE BASE RATIOS OF RIBONUCLEIC ACID IN AMOEBA

PubMed Central

Iverson, Ray M.

1964-01-01

The amount and relative base ratios of ribonucleic acid (RNA) in the nucleus and cytoplasm of Amoeba proteus and A. dubia, and of homospecies cells obtained by nuclear transfer with A. proteus, have been determined by microelectrophoresis. In A. proteus the average amounts of RNA in the nucleus and the cytoplasm were 134. micromicrograms and 2520. micromicrograms; in A. dubia the averages for the nucleus and cytoplasm were 67. micromicrograms and 1427. micromicrograms. The relative base ratio of RNA of the nucleus is similar to that of the RNA of the cytoplasm within a species, but the two species differed in this respect. Homospecies nuclear transfer did not affect the relative base ratio or amount of RNA. PMID:14105213

Interior noise prediction methodology: ATDAC theory and validation

NASA Technical Reports Server (NTRS)

Mathur, Gopal P.; Gardner, Bryce K.

1992-01-01

The Acoustical Theory for Design of Aircraft Cabins (ATDAC) is a computer program developed to predict interior noise levels inside aircraft and to evaluate the effects of different aircraft configurations on the aircraft acoustical environment. The primary motivation for development of this program is the special interior noise problems associated with advanced turboprop (ATP) aircraft where there is a tonal, low frequency noise problem. Prediction of interior noise levels requires knowledge of the energy sources, the transmission paths, and the relationship between the energy variable and the sound pressure level. The energy sources include engine noise, both airborne and structure-borne; turbulent boundary layer noise; and interior noise sources such as air conditioner noise and auxiliary power unit noise. Since propeller and engine noise prediction programs are widely available, they are not included in ATDAC. Airborne engine noise from any prediction or measurement may be input to this program. This report describes the theory and equations implemented in the ATDAC program.

Interior noise prediction methodology: ATDAC theory and validation

NASA Astrophysics Data System (ADS)

Mathur, Gopal P.; Gardner, Bryce K.

1992-04-01

The Acoustical Theory for Design of Aircraft Cabins (ATDAC) is a computer program developed to predict interior noise levels inside aircraft and to evaluate the effects of different aircraft configurations on the aircraft acoustical environment. The primary motivation for development of this program is the special interior noise problems associated with advanced turboprop (ATP) aircraft where there is a tonal, low frequency noise problem. Prediction of interior noise levels requires knowledge of the energy sources, the transmission paths, and the relationship between the energy variable and the sound pressure level. The energy sources include engine noise, both airborne and structure-borne; turbulent boundary layer noise; and interior noise sources such as air conditioner noise and auxiliary power unit noise. Since propeller and engine noise prediction programs are widely available, they are not included in ATDAC. Airborne engine noise from any prediction or measurement may be input to this program. This report describes the theory and equations implemented in the ATDAC program.

14 CFR 91.1041 - Aircraft proving and validation tests.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Aircraft proving and validation tests. 91... Ownership Operations Program Management § 91.1041 Aircraft proving and validation tests. (a) No program... tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing...

14 CFR 91.1041 - Aircraft proving and validation tests.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Aircraft proving and validation tests. 91... Ownership Operations Program Management § 91.1041 Aircraft proving and validation tests. (a) No program... tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing...

14 CFR 91.1041 - Aircraft proving and validation tests.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Aircraft proving and validation tests. 91... Ownership Operations Program Management § 91.1041 Aircraft proving and validation tests. (a) No program... tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing...

14 CFR 91.1041 - Aircraft proving and validation tests.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Aircraft proving and validation tests. 91... Ownership Operations Program Management § 91.1041 Aircraft proving and validation tests. (a) No program... tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing...

14 CFR 91.1041 - Aircraft proving and validation tests.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Aircraft proving and validation tests. 91... Ownership Operations Program Management § 91.1041 Aircraft proving and validation tests. (a) No program... tests. However, pilot flight training may be conducted during the proving tests. (d) Validation testing...

A computer program to obtain time-correlated gust loads for nonlinear aircraft using the matched-filter-based method

NASA Technical Reports Server (NTRS)

Scott, Robert C.; Pototzky, Anthony S.; Perry, Boyd, III

1994-01-01

NASA Langley Research Center has, for several years, conducted research in the area of time-correlated gust loads for linear and nonlinear aircraft. The results of this work led NASA to recommend that the Matched-Filter-Based One-Dimensional Search Method be used for gust load analyses of nonlinear aircraft. This manual describes this method, describes a FORTRAN code which performs this method, and presents example calculations for a sample nonlinear aircraft model. The name of the code is MFD1DS (Matched-Filter-Based One-Dimensional Search). The program source code, the example aircraft equations of motion, a sample input file, and a sample program output are all listed in the appendices.

Composite components on commercial aircraft

NASA Technical Reports Server (NTRS)

Dexter, H. B.

1980-01-01

Commercial aircraft manufacturers are making production commitments to composite structure for future aircraft and modifications to current production aircraft. Flight service programs with advanced composites sponsored by NASA during the past 10 years are described. Approximately 2.5 million total composite component flight hours have been accumulated since 1970 on both commercial transports and helicopters. Design concepts with significant mass savings were developed, appropriate inspection and maintenance procedures were established, and satisfactory service was achieved for the various composite components. A major NASA/U.S. industry technology program to reduce fuel consumption of commercial transport aircraft through the use of advanced composites was undertaken. Ground and flight environmental effects on the composite materials used in the flight service programs supplement the flight service evaluation.

Advanced tow placement of composite fuselage structure

NASA Technical Reports Server (NTRS)

Anderson, Robert L.; Grant, Carroll G.

1992-01-01

The Hercules NASA ACT program was established to demonstrate and validate the low cost potential of the automated tow placement process for fabrication of aircraft primary structures. The program is currently being conducted as a cooperative program in collaboration with the Boeing ATCAS Program. The Hercules advanced tow placement process has been in development since 1982 and was developed specifically for composite aircraft structures. The second generation machine, now in operation at Hercules, is a production-ready machine that uses a low cost prepreg tow material form to produce structures with laminate properties equivalent to prepreg tape layup. Current program activities are focused on demonstration of the automated tow placement process for fabrication of subsonic transport aircraft fuselage crown quadrants. We are working with Boeing Commercial Aircraft and Douglas Aircraft during this phase of the program. The Douglas demonstration panels has co-cured skin/stringers, and the Boeing demonstration panel is an intricately bonded part with co-cured skin/stringers and co-bonded frames. Other aircraft structures that were evaluated for the automated tow placement process include engine nacelle components, fuselage pressure bulkheads, and fuselage tail cones. Because of the cylindrical shape of these structures, multiple parts can be fabricated on one two placement tool, thus reducing the cost per pound of the finished part.

Roles, uses, and benefits of general aviation aircraft in aerospace engineering education

NASA Technical Reports Server (NTRS)

Odonoghue, Dennis P.; Mcknight, Robert C.

1994-01-01

Many colleges and universities throughout the United States offer outstanding programs in aerospace engineering. In addition to the fundamentals of aerodynamics, propulsion, flight dynamics, and air vehicle design, many of the best programs have in the past provided students the opportunity to design and fly airborne experiments on board various types of aircraft. Sadly, however, the number of institutions offering such 'airborne laboratories' has dwindled in recent years. As a result, opportunities for students to apply their classroom knowledge, analytical skills, and engineering judgement to the development and management of flight experiments on an actual aircraft are indeed rare. One major reason for the elimination of flight programs by some institutions, particularly the smaller colleges, is the prohibitive cost of operating and maintaining an aircraft as a flying laboratory. The purpose of this paper is to discuss simple, low-cost, relevant flight experiments that can be performed using readily available general aviation aircraft. This paper examines flight experiments that have been successfully conducted on board the NASA Lewis Research Center's T-34B aircraft, as part of the NASA/AIAA/University Flight Experiment Program for Students (NAUFEPS) and discusses how similar experiments could be inexpensively performed on other general aviation aircraft.

The atmospheric effects of stratospheric aircraft

NASA Technical Reports Server (NTRS)

Stolarski, Richard S. (Editor); Wesoky, Howard L. (Editor)

1993-01-01

This document presents a second report from the Atmospheric Effects of Stratospheric Aircraft (AESA) component of NASA's High-Speed Research Program (HSRP). This document presents a second report from the Atmospheric Effects of Stratospheric Aircraft (AESA) component of NASA's High Speed Research Program (HSRP). Market and technology considerations continue to provide an impetus for high-speed civil transport research. A recent United Nations Environment Program scientific assessment has shown that considerable uncertainty still exists about the possible impact of aircraft on the atmosphere. The AESA was designed to develop the body of scientific knowledge necessary for the evaluation of the impact of stratospheric aircraft on the atmosphere. The first Program report presented the basic objectives and plans for AESA. This second report presents the status of the ongoing research as reported by the principal investigators at the second annual AESA Program meeting in May 1992: Laboratory studies are probing the mechanism responsible for many of the heterogeneous reactions that occur on stratospheric particles. Understanding how the atmosphere redistributes aircraft exhaust is critical to our knowing where the perturbed air will go and for how long it will remain in the stratosphere. The assessment of fleet effects is dependent on the ability to develop scenarios which correctly simulate fleet operations.

Environmental Assessment for Management of South End of Runway Wetlands, Moody AFB, Georgia

DTIC Science & Technology

2010-11-01

implement a management program for the wetlands at the south end of runway (EOR) at Moody AFB to reduce the bird/wildlife aircraft strike hazard (BASH) risk...because birds and other wildlife pose an increased bird/wildlife aircraft strike hazard (BASH) risk to aircraft utilizing the Moody AFB airfield. ln...support ofthe military mission, Moody AFB has implemented a BASH management program designed to minimize aircraft exposure to potentially hazardous

A Survey of Research Performed at NASA Langley Research Center's Impact Dynamics Research Facility

NASA Technical Reports Server (NTRS)

Jackson, K. E.; Fasanella, E. L.

2003-01-01

The Impact Dynamics Research Facility (IDRF) is a 240-ft-high gantry structure located at NASA Langley Research Center in Hampton, Virginia. The facility was originally built in 1963 as a lunar landing simulator, allowing the Apollo astronauts to practice lunar landings under realistic conditions. The IDRF was designated a National Historic Landmark in 1985 based on its significant contributions to the Apollo Program. In 1972, the facility was converted to a full-scale crash test facility for light aircraft and rotorcraft. Since that time, the IDRF has been used to perform a wide variety of impact tests on full-scale aircraft and structural components in support of the General Aviation (GA) aircraft industry, the US Department of Defense, the rotorcraft industry, and NASA in-house aeronautics and space research programs. The objective of this paper is to describe most of the major full-scale crash test programs that were performed at this unique, world-class facility since 1974. The past research is divided into six sub-topics: the civil GA aircraft test program, transport aircraft test program, military test programs, space test programs, basic research, and crash modeling and simulation.

THE BUREAU OF AERONAUTICS RESEARCH AND DEVELOPMENT PROGRAM FOR WATER-BASED AIRCRAFT,

DTIC Science & Technology

WATER BASED AIRCRAFT, BUDGETS), RESEARCH MANAGEMENT, FLIGHT TESTING, WIND TUNNEL MODELS, TABLES(DATA), AIRCRAFT, TEST VEHICLES, HYDRODYNAMICS, PIERS, FLOATING DOCKS, LOADS(FORCES), WATER , STABILITY, SPRAYS, NAVAL AIRCRAFT.

A FORTRAN program for determining aircraft stability and control derivatives from flight data

NASA Technical Reports Server (NTRS)

Maine, R. E.; Iliff, K. W.

1975-01-01

A digital computer program written in FORTRAN IV for the estimation of aircraft stability and control derivatives is presented. The program uses a maximum likelihood estimation method, and two associated programs for routine, related data handling are also included. The three programs form a package that can be used by relatively inexperienced personnel to process large amounts of data with a minimum of manpower. This package was used to successfully analyze 1500 maneuvers on 20 aircraft, and is designed to be used without modification on as many types of computers as feasible. Program listings and sample check cases are included.

Users Guide for NASA Lewis Research Center DC-9 Reduced-Gravity Aircraft Program

NASA Technical Reports Server (NTRS)

Yaniec, John S.

1995-01-01

The document provides guidelines and information for users of the DC-9 Reduced-Gravity Aircraft Program. It describes the facilities, requirements for test personnel, equipment design and installation, mission preparation, and in-flight procedures. Those who have used the KC-135 reduced-gravity aircraft will recognize that many of the procedures and guidelines are the same, to ensure a commonality between the DC-9 and KC-135 programs.

A computer program for fitting smooth surfaces to three-dimensional aircraft configurations

NASA Technical Reports Server (NTRS)

Craidon, C. B.; Smith, R. E., Jr.

1975-01-01

A computer program developed to fit smooth surfaces to the component parts of three-dimensional aircraft configurations was described. The resulting equation definition of an aircraft numerical model is useful in obtaining continuous two-dimensional cross section plots in arbitrarily defined planes, local tangents, enriched surface plots and other pertinent geometric information; the geometry organization used as input to the program has become known as the Harris Wave Drag Geometry.

The NASA aircraft icing research program

NASA Technical Reports Server (NTRS)

Shaw, Robert J.; Reinmann, John J.

1990-01-01

The objective of the NASA aircraft icing research program is to develop and make available to industry icing technology to support the needs and requirements for all-weather aircraft designs. Research is being done for both fixed wing and rotary wing applications. The NASA program emphasizes technology development in two areas, advanced ice protection concepts and icing simulation. Reviewed here are the computer code development/validation, icing wind tunnel testing, and icing flight testing efforts.

COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-C REPORT. HIGH STRENGTH STEEL EVALUATION FOR SUPERSONIC AIRCRAFT.

DTIC Science & Technology

JET TRANSPORT AIRCRAFT, *AIRFRAMES, SUPERSONIC AIRCRAFT, STEEL , STRUCTURAL PROPERTIES, FRACTURE(MECHANICS), FATIGUE(MECHANICS), STRESS CORROSION...MICROPHOTOGRAPHY, HIGH TEMPERATURE, NICKEL ALLOYS, COBALT ALLOYS, CARBON, BAINITE , COMMERCIAL AIRCRAFT.

The Enforcer Aircraft Program: A Lower-Cost Alternative Weapon System.

DTIC Science & Technology

1984-03-01

armoured striking forces. NATO’s air forces then, sns 1.select the optimum aircraft(s) to maximize the damage to the enemy while minimizing the cost to...the reascns Congress kept the Enforcer program alive was their inclination to support the underdog , an underdog with persuasiveness and tenacity. To

Process for Refining and Validating a Finite Element Model of an Experimental High-Altitude, Long-Endurance (HALE) Aircraft

DTIC Science & Technology

2011-06-01

7 Figure 4. Helios flying near the Hawaiian islands of Niihau and Lehua [15] ................... 8 Figure 5. Plan view of ERAST Program aircraft...Figure 4. Helios flying near the Hawaiian islands of Niihau and Lehua [15] 9 Figure 5. Plan view of ERAST Program aircraft

Status review of NASA programs for reducing aircraft gas turbine engine emissions

NASA Technical Reports Server (NTRS)

Rudey, R. A.

1976-01-01

The paper describes and discusses the results from some of the research and development programs for reducing aircraft gas turbine engine emissions. Although the paper concentrates on NASA programs only, work supported by other U.S. government agencies and industry has provided considerable data on low emission advanced technology for aircraft gas turbine engine combustors. The results from the two major NASA technology development programs, the ECCP (Experimental Clean Combustor Program) and the PRTP (Pollution Reduction Technology Program), are presented and compared with the requirements of the 1979 U.S. EPA standards. Emission reduction techniques currently being evaluated in these programs are described along with the results and a qualitative assessment of development difficulty.

A Sensor To Detect the Early Stages in the Development of Crystalline Proteus mirabilis Biofilm on Indwelling Bladder Catheters

PubMed Central

Stickler, D. J.; Jones, S. M.; Adusei, G. O.; Waters, M. G.

2006-01-01

A simple sensor has been developed to detect the early stages of urinary catheter encrustation and avoid the clinical crises induced by catheter blockage. In laboratory models of colonization by Proteus mirabilis, the sensor signaled encrustation at an average time of 43 h before catheters were blocked with crystalline biofilm. PMID:16597888

[Possibility of fortifying milk nutrient mixtures for children with lactoglobulin against E. coli and Proteus].

PubMed

Zlatnik, E Iu

1986-01-01

Sweet milk nutrient mixtures, biologically active additives (BAA) and lactic acid ferments, intended for child nutrition, were enriched with the immune preparation lactoglobulin against E. coli and Proteus. Serological and immunochemical investigations of hemagglutinating activity and other characteristics of lactoglobulin in the enriched milk mixtures and BAA evidenced that the preparation retained its full value during the technological process and in the period of storage. No signs of lactoglobulin degradation during the production of a test batch of the milk mixture and BAA were detected, and a high hemagglutinating activity with respect to enteropathogenic E. coli and Proteus was recorded. This permitted the author to recommend the lactoglobulin-enriched sweet mixtures for prevention of acute intestinal infections and dysbacteriosis in young children. The in vitro study of the lactoglobulin interaction with pure cultures of lactobacillus and bifidobacteria showed its inertness to eubacteria. Four strains studied retained their growth and acid-forming properties after combined incubation with lactoglobulin and did not inhibit its activity. A conclusion has been made on the possibility of enrichment of lactic acid products, intended for child nutrition, with lactoglobulin against E. coli and Proteus.

Development of a Phage Cocktail to Control Proteus mirabilis Catheter-associated Urinary Tract Infections

PubMed Central

Melo, Luís D. R.; Veiga, Patrícia; Cerca, Nuno; Kropinski, Andrew M.; Almeida, Carina; Azeredo, Joana; Sillankorva, Sanna

2016-01-01

Proteus mirabilis is an enterobacterium that causes catheter-associated urinary tract infections (CAUTIs) due to its ability to colonize and form crystalline biofilms on the catheters surface. CAUTIs are very difficult to treat, since biofilm structures are highly tolerant to antibiotics. Phages have been used widely to control a diversity of bacterial species, however, a limited number of phages for P. mirabilis have been isolated and studied. Here we report the isolation of two novel virulent phages, the podovirus vB_PmiP_5460 and the myovirus vB_PmiM_5461, which are able to target, respectively, 16 of the 26 and all the Proteus strains tested in this study. Both phages have been characterized thoroughly and sequencing data revealed no traces of genes associated with lysogeny. To further evaluate the phages’ ability to prevent catheter’s colonization by Proteus, the phages adherence to silicone surfaces was assessed. Further tests in phage-coated catheters using a dynamic biofilm model simulating CAUTIs, have shown a significant reduction of P. mirabilis biofilm formation up to 168 h of catheterization. These results highlight the potential usefulness of the two isolated phages for the prevention of surface colonization by this bacterium. PMID:27446059

Oriented thick and thin filaments in amoeba proteus

PubMed Central

Rinaldi, RA; Hrebenda, B

1975-01-01

Actin and myosin filaments as a foundation of contractile systems are well established from ameba to man (3). Wolpert et al. (19) isolated by differential centrifugation from Amoeba proteus a motile fraction composed of filaments which moved upon the addition of ATP. Actin filaments are found in amebas (1, 12, 13) which react with vertebrate heavy meromyosin (HMM), forming arrowhead complexes as vertebrate actin (3, 9), and are prominent within the ectoplasmic tube where some of them are attached to the plasmalemma (1, 12). Thick and thin filaments possessing the morphological characteristics of myosin and actin have been obtained from isolated ameba cytoplasm (18, 19). In addition, there are filaments exhibiting ATPase activity in amebas which react with actin (12, 16, 17). However, giant ameba (Chaos-proteus) shapes are difficult to preserve, and the excellent contributions referred to above are limited by visible distortions occurring in the amebas (rounding up, pseudopods disappearing, and cellular organelles swelling) upon fixation. Achievement of normal ameboid shape in recent glycerination work (15) led us to attempt other electron microscope fixation techniques, resulting in a surprising preservation of A. proteus with a unique orientation of thick and thin filaments in the ectoplasmic region. PMID:1141376

Oriented thick and thin filaments in Amoeba proteus.

PubMed

Rinaldi, R A; Hrebenda, B

1975-07-01

Actin and myosin filaments as a foundation of contractile systems are well established from ameba to man (3). Wolpert et al. (19) isolated by differential centrifugation from Amoeba proteus a motile fraction composed of filaments which moved upon the addition of ATP. Actin filaments are found in amebas (1, 12, 13) which react with vertebrate heavy meromyosin (HMM), forming arrowhead complexes as vertebrate actin (3, 9), and are prominent within the ectoplasmic tube where some of them are attached to the plasmalemma (1, 12). Thick and thin filaments possessing the morphological characteristics of myosin and actin have been obtained from isolated ameba cytoplasm (18, 19). In addition, there are filaments exhibiting ATPase activity in amebas which react with actin (12, 16, 17). However, giant ameba (Chaos-proteus) shapes are difficult to preserve, and the excellent contributions referred to above are limited by visible distortions occurring in the amebas (rounding up, pseudopods disappearing, and cellular organelles swelling) upon fixation. Achievement of normal ameboid shape in recent glycerination work (15) led us to attempt other electron microscope fixation techniques, resulting in a surprising preservation of A. proteus with a unique orientation of thick and thin filaments in the ectoplasmic region.

Status review of NASA programs for reducing aircraft gas turbine engine emissions

NASA Technical Reports Server (NTRS)

Rudey, R. A.

1976-01-01

Programs initiated by NASA to develop and demonstrate low emission advanced technology combustors for reducing aircraft gas turbine engine pollution are reviewed. Program goals are consistent with urban emission level requirements as specified by the U. S. Environmental Protection Agency and with upper atmosphere cruise emission levels as recommended by the U. S. Climatic Impact Assessment Program and National Research Council. Preliminary tests of advanced technology combustors indicate that significant reductions in all major pollutant emissions should be attainable in present generation aircraft gas turbine engines without adverse effects on fuel consumption. Preliminary test results from fundamental studies indicate that extremely low emission combustion systems may be possible for future generation jet aircraft. The emission reduction techniques currently being evaluated in these programs are described along with the results and a qualitative assessment of development difficulty.

Aircraft measurements and analysis of severe storms: 1975 field experiment

NASA Technical Reports Server (NTRS)

Sinclair, P. C.

1976-01-01

Three aircraft and instrumentation systems were acquired in support of the severe storm surveillance program. The data results indicate that the original concept of a highly mobile research aircraft capability for obtaining detailed measurements of wind, temperature, dew point, etc., near and within specifically designated severe storms is entirely feasible and has been demonstrated for the first time by this program. This program is unique in that it is designed to be highly mobile in order to move to and/or with the developing storm systems to obtain the necessary measurements. Previous programs have all been fixed to a particular location and therefore have had to wait for the storms to come within their network. The present research is designed around a highly mobile aircraft measurements group in order to maximize the storm cases during the field measurements program.

40 CFR 87.71 - Compliance with gaseous emission standards.

Code of Federal Regulations, 2010 CFR

2010-07-01

... PROGRAMS (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 87.71 Compliance with gaseous emission standards. Compliance with each gaseous emission standard by an aircraft engine shall be...

40 CFR 87.71 - Compliance with gaseous emission standards.

Code of Federal Regulations, 2011 CFR

2011-07-01

... PROGRAMS (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Exhaust Gaseous Emissions (Aircraft and Aircraft Gas Turbine Engines) § 87.71 Compliance with gaseous emission standards. Compliance with each gaseous emission standard by an aircraft engine shall be...

Computer program to perform cost and weight analysis of transport aircraft. Volume 2: Technical volume

NASA Technical Reports Server (NTRS)

1973-01-01

An improved method for estimating aircraft weight and cost using a unique and fundamental approach was developed. The results of this study were integrated into a comprehensive digital computer program, which is intended for use at the preliminary design stage of aircraft development. The program provides a means of computing absolute values for weight and cost, and enables the user to perform trade studies with a sensitivity to detail design and overall structural arrangement. Both batch and interactive graphics modes of program operation are available.

Protein side chain conformation predictions with an MMGBSA energy function.

PubMed

Gaillard, Thomas; Panel, Nicolas; Simonson, Thomas

2016-06-01

The prediction of protein side chain conformations from backbone coordinates is an important task in structural biology, with applications in structure prediction and protein design. It is a difficult problem due to its combinatorial nature. We study the performance of an "MMGBSA" energy function, implemented in our protein design program Proteus, which combines molecular mechanics terms, a Generalized Born and Surface Area (GBSA) solvent model, with approximations that make the model pairwise additive. Proteus is not a competitor to specialized side chain prediction programs due to its cost, but it allows protein design applications, where side chain prediction is an important step and MMGBSA an effective energy model. We predict the side chain conformations for 18 proteins. The side chains are first predicted individually, with the rest of the protein in its crystallographic conformation. Next, all side chains are predicted together. The contributions of individual energy terms are evaluated and various parameterizations are compared. We find that the GB and SA terms, with an appropriate choice of the dielectric constant and surface energy coefficients, are beneficial for single side chain predictions. For the prediction of all side chains, however, errors due to the pairwise additive approximation overcome the improvement brought by these terms. We also show the crucial contribution of side chain minimization to alleviate the rigid rotamer approximation. Even without GB and SA terms, we obtain accuracies comparable to SCWRL4, a specialized side chain prediction program. In particular, we obtain a better RMSD than SCWRL4 for core residues (at a higher cost), despite our simpler rotamer library. Proteins 2016; 84:803-819. © 2016 Wiley Periodicals, Inc. © 2016 Wiley Periodicals, Inc.

Multidisciplinary Techniques and Novel Aircraft Control Systems

NASA Technical Reports Server (NTRS)

Padula, Sharon L.; Rogers, James L.; Raney, David L.

2000-01-01

The Aircraft Morphing Program at NASA Langley Research Center explores opportunities to improve airframe designs with smart technologies. Two elements of this basic research program are multidisciplinary design optimization (MDO) and advanced flow control. This paper describes examples where MDO techniques such as sensitivity analysis, automatic differentiation, and genetic algorithms contribute to the design of novel control systems. In the test case, the design and use of distributed shape-change devices to provide low-rate maneuvering capability for a tailless aircraft is considered. The ability of MDO to add value to control system development is illustrated using results from several years of research funded by the Aircraft Morphing Program.

Multidisciplinary Techniques and Novel Aircraft Control Systems

NASA Technical Reports Server (NTRS)

Padula, Sharon L.; Rogers, James L.; Raney, David L.

2000-01-01

The Aircraft Morphing Program at NASA Langley Research Center explores opportunities to improve airframe designs with smart technologies. Two elements of this basic research program are multidisciplinary design optimization (MDO) and advanced flow control. This paper describes examples where MDO techniques such as sensitivity analysis, automatic differentiation, and genetic algorithms contribute to the design of novel control systems. In the test case, the design and use of distributed shapechange devices to provide low-rate maneuvering capability for a tailless aircraft is considered. The ability of MDO to add value to control system development is illustrated using results from several years of research funded by the Aircraft Morphing Program.

Airborne Science Program: Observing Platforms for Earth Science Investigations

NASA Technical Reports Server (NTRS)

Mace, Thomas H.

2009-01-01

This slide presentation reviews the Airborne Science Program and the platforms used for conducting investigations for the Earth System Science. Included is a chart that shows some of the aircraft and the operational altitude and the endurance of the aircraft, views of the Dryden Aircraft Operation Facility, and some of the current aircraft that the facility operates, and the varieties of missions that are flown and the type of instrumentation. Also included is a chart showing the attributes of the various aircraft (i.e., duration, weight for a payload, maximum altitude, airspeed and range) for comparison

Neonatal Meningoventriculitis Due to Proteus Mirabilis – A Case Report

PubMed Central

Juyal, Deepak; Rathaur, Vyas Kumar; Sharma, Neelam

2013-01-01

A five day old full term born baby was admitted to our Neonatal Intensive Care Unit with seizures, opisthotonous posture and was icteric upto thigh. Baby had a three day history of poor feeding, lethargy and abnormal body movements. Mother was a 29 years old primigravida and had a normal vaginal delivery at home. Sepsis profile of the patient was requested, lumbar puncture and ventricular tap was performed. Patient was put on third generation cephalosporins, aminoglycosides and phenobarbitone. Culture and sensitivity report of blood, Cerebro spinal fluid and ventricular fluid showed Proteus mirabilis. Computerized Tomography scan showed a large parenchymal lesion in the right frontal lobe and diffuse ependymal enhancement along both the lateral ventricles suggestive of meningoventriculitis. We hereby present a fatal case of neonatal meningoventriculitis due to Proteus mirabilis. PMID:23543669

User Manual for the PROTEUS Mesh Tools

DOE Office of Scientific and Technical Information (OSTI.GOV)

Smith, Micheal A.; Shemon, Emily R.

2015-06-01

This report describes the various mesh tools that are provided with the PROTEUS code giving both descriptions of the input and output. In many cases the examples are provided with a regression test of the mesh tools. The most important mesh tools for any user to consider using are the MT_MeshToMesh.x and the MT_RadialLattice.x codes. The former allows the conversion between most mesh types handled by PROTEUS while the second allows the merging of multiple (assembly) meshes into a radial structured grid. Note that the mesh generation process is recursive in nature and that each input specific for a givenmore » mesh tool (such as .axial or .merge) can be used as “mesh” input for any of the mesh tools discussed in this manual.« less

Novel polymer membrane process for pre-combustion CO{sub 2} capture from coal-fired syngas

DOE Office of Scientific and Technical Information (OSTI.GOV)

Merkel, Tim

2011-09-14

This final report describes work conducted for the Department of Energy (DOE NETL) on development of a novel polymer membrane process for pre-combustion CO{sub 2} capture from coalfired syngas (award number DE-FE0001124). The work was conducted by Membrane Technology and Research, Inc. (MTR) from September 15, 2009, through December 14, 2011. Tetramer Technologies, LLC (Tetramer) was our subcontract partner on this project. The National Carbon Capture Center (NCCC) at Wilsonville, AL, provided access to syngas gasifier test facilities. The main objective of this project was to develop a cost-effective membrane process that could be used in the relatively near-term tomore » capture CO{sub 2} from shifted syngas generated by a coal-fired Integrated Gasification Combined Cycle (IGCC) power plant. In this project, novel polymeric membranes (designated as Proteus™ membranes) with separation properties superior to conventional polymeric membranes were developed. Hydrogen permeance of up to 800 gpu and H{sub 2}/CO{sub 2} selectivity of >12 was achieved using a simulated syngas mixture at 150°C and 50 psig, which exceeds the original project targets of 200 gpu for hydrogen permeance and 10 for H{sub 2}/CO{sub 2} selectivity. Lab-scale Proteus membrane modules (with a membrane area of 0.13 m{sup 2}) were also developed using scaled-up Proteus membranes and high temperature stable module components identified during this project. A mixed-gas hydrogen permeance of about 160 gpu and H{sub 2}/CO{sub 2} selectivity of >12 was achieved using a simulated syngas mixture at 150°C and 100 psig. We believe that a significant improvement in the membrane and module performance is likely with additional development work. Both Proteus membranes and lab-scale Proteus membrane modules were further evaluated using coal-derived syngas streams at the National Carbon Capture Center (NCCC). The results indicate that all module components, including the Proteus membrane, were stable under the field conditions (feed pressures: 150-175 psig and feed temperatures: 120-135°C) for over 600 hours. The field performance of both Proteus membrane stamps and Proteus membrane modules is consistent with the results obtained in the lab, suggesting that the presence of sulfur-containing compounds (up to 780 ppm hydrogen sulfide), saturated water vapor, carbon monoxide and heavy hydrocarbons in the syngas feed stream has no adverse effect on the Proteus membrane or module performance. We also performed an economic analysis for a number of membrane process designs developed in this project (using hydrogen-selective membranes, alone or in the combination with CO{sub 2}- selective membranes). The current field performance for Proteus membranes was used in the design analysis. The study showed the current best design has the potential to reduce the increase in Levelized Cost of Electricity (LCOE) caused by 90% CO{sub 2} capture to about 15% if co-sequestration of H{sub 2}S is viable. This value is still higher than the DOE target for increase in LCOE (10%); however, compared to the base-case Selexol process that gives a 30% increase in LCOE at 90% CO2 capture, the membrane-based process appears promising. We believe future improvements in membrane performance have the potential to reach the DOE target.« less

Sensitivity Analysis of Linear Programming and Quadratic Programming Algorithms for Control Allocation

NASA Technical Reports Server (NTRS)

Frost, Susan A.; Bodson, Marc; Acosta, Diana M.

2009-01-01

The Next Generation (NextGen) transport aircraft configurations being investigated as part of the NASA Aeronautics Subsonic Fixed Wing Project have more control surfaces, or control effectors, than existing transport aircraft configurations. Conventional flight control is achieved through two symmetric elevators, two antisymmetric ailerons, and a rudder. The five effectors, reduced to three command variables, produce moments along the three main axes of the aircraft and enable the pilot to control the attitude and flight path of the aircraft. The NextGen aircraft will have additional redundant control effectors to control the three moments, creating a situation where the aircraft is over-actuated and where a simple relationship does not exist anymore between the required effector deflections and the desired moments. NextGen flight controllers will incorporate control allocation algorithms to determine the optimal effector commands and attain the desired moments, taking into account the effector limits. Approaches to solving the problem using linear programming and quadratic programming algorithms have been proposed and tested. It is of great interest to understand their relative advantages and disadvantages and how design parameters may affect their properties. In this paper, we investigate the sensitivity of the effector commands with respect to the desired moments and show on some examples that the solutions provided using the l2 norm of quadratic programming are less sensitive than those using the l1 norm of linear programming.

Power-by-Wire Development and Demonstration for Subsonic Civil Transport

NASA Technical Reports Server (NTRS)

1996-01-01

During the last decade, three significant studies by the Lockheed Martin Corporation, the NASA Lewis Research Center, and McDonnell Douglas Corporation have clearly shown operational, weight, and cost advantages for commercial subsonic transport aircraft that use all-electric or more-electric technologies in the secondary electric power systems. Even though these studies were completed on different aircraft, used different criteria, and applied a variety of technologies, all three have shown large benefits to the aircraft industry and to the nation's competitive position. The Power-by-Wire (PBW) program is part of the highly reliable Fly-By-Light/Power-By-Wire (FBL/PBW) Technology Program, whose goal is to develop the technology base for confident application of integrated FBL/PBW systems for transport aircraft. This program is part of the NASA aeronautics strategic thrust in subsonic aircraft/national airspace (Thrust 1) to "develop selected high-leverage technologies and explore new means to ensure the competitiveness of U.S. subsonic aircraft and to enhance the safety and productivity of the national aviation system" (The Aeronautics Strategic Plan). Specifically, this program is an initiative under Thrust 1, Key Objective 2, to "develop, in cooperation with U.S. industry, selected high-payoff technologies that can enable significant improvements in aircraft efficiency and cost."

Partners in Freedom: Contributions of the Langley Research Center to U.S. Military Aircraft of the 1990's

NASA Technical Reports Server (NTRS)

Chambers, Joseph R.

2000-01-01

Established in 1917 as the nation#s first civil aeronautics research laboratory under the National Advisory Commit-tee for Aeronautics (NACA), Langley was a small laboratory that solved the problems of flight for military and civil aviation. Throughout history, Langley has maintained a working partnership with the Department of Defense, U.S. industry, universities, and other government agencies to support the defense of the nation with research. During World War II, Langley directed virtually all of its workforce and facilities to research for military aircraft. Following the war, a balanced program of military and civil projects was undertaken. In some instances Langley research from one aircraft program helped solve a problem in another. At the conclusion of some programs, Langley obtained the research models for additional tests to learn more about previously unknown phenomena. The data also proved useful in later developmental programs. Many of the military aircraft in the U.S. inventory as of late 1999 were over 20 years old. Langley activities that contributed to the development of some of these aircraft began over 50 years prior. This publication documents the role, from early concept stages to problem solving for fleet aircraft, that Langley played in the military aircraft fleet of the United States for the 1990's.

An automated system for global atmospheric sampling using B-747 airliners

NASA Technical Reports Server (NTRS)

Lew, K. Q.; Gustafsson, U. R. C.; Johnson, R. E.

1981-01-01

The global air sampling program utilizes commercial aircrafts in scheduled service to measure atmospheric constituents. A fully automated system designed for the 747 aircraft is described. Airline operational constraints and data and control subsystems are treated. The overall program management, system monitoring, and data retrieval from four aircraft in global service is described.

Computer programs for producing single-event aircraft noise data for specific engine power and meteorological conditions for use with USAF (United States Air Force) community noise model (NOISEMAP)

NASA Astrophysics Data System (ADS)

Mohlman, H. T.

1983-04-01

The Air Force community noise prediction model (NOISEMAP) is used to describe the aircraft noise exposure around airbases and thereby aid airbase planners to minimize exposure and prevent community encroachment which could limit mission effectiveness of the installation. This report documents two computer programs (OMEGA 10 and OMEGA 11) which were developed to prepare aircraft flight and ground runup noise data for input to NOISEMAP. OMEGA 10 is for flight operations and OMEGA 11 is for aircraft ground runups. All routines in each program are documented at a level useful to a programmer working with the code or a reader interested in a general overview of what happens within a specific subroutine. Both programs input normalized, reference aircraft noise data; i.e., data at a standard reference distance from the aircraft, for several fixed engine power settings, a reference airspeed and standard day meteorological conditions. Both programs operate on these normalized, reference data in accordance with user-defined, non-reference conditions to derive single-event noise data for 22 distances (200 to 25,000 feet) in a variety of physical and psycho-acoustic metrics. These outputs are in formats ready for input to NOISEMAP.

Preliminary design of a high speed civil transport: The Opus 0-001

NASA Technical Reports Server (NTRS)

1992-01-01

Based on research into the technology and issues surrounding the design, development, and operation of a second generation High Speed Civil Transport, HSCT, the Opus 0-001 team completed the preliminary design of a sixty passenger, three engine aircraft. The design of this aircraft was performed using a computer program which the team wrote. This program automatically computed the geometric, aerodynamic, and performance characteristic of an aircraft whose preliminary geometry was specified. The Opus 0-001 aircraft was designed for a cruise Mach number of 2.2, a range of 4,700 nautical miles and its design was based in current or very near term technology. Its small size was a consequence of an emphasis on a profitable, low cost program, capable of delivering tomorrow's passengers in style and comfort at prices that make it an attractive competitor to both current and future subsonic transport aircraft. Several hundred thousand cases of Cruise Mach number, aircraft size and cost breakdown were investigated to obtain costs and revenues for which profit was calculated. The projected unit flyaway cost was $92.0 million per aircraft.

High Speed Research Noise Prediction Code (HSRNOISE) User's and Theoretical Manual

NASA Technical Reports Server (NTRS)

Golub, Robert (Technical Monitor); Rawls, John W., Jr.; Yeager, Jessie C.

2004-01-01

This report describes a computer program, HSRNOISE, that predicts noise levels for a supersonic aircraft powered by mixed flow turbofan engines with rectangular mixer-ejector nozzles. It fully documents the noise prediction algorithms, provides instructions for executing the HSRNOISE code, and provides predicted noise levels for the High Speed Research (HSR) program Technology Concept (TC) aircraft. The component source noise prediction algorithms were developed jointly by Boeing, General Electric Aircraft Engines (GEAE), NASA and Pratt & Whitney during the course of the NASA HSR program. Modern Technologies Corporation developed an alternative mixer ejector jet noise prediction method under contract to GEAE that has also been incorporated into the HSRNOISE prediction code. Algorithms for determining propagation effects and calculating noise metrics were taken from the NASA Aircraft Noise Prediction Program.

40 CFR 141.804 - Aircraft water system operations and maintenance plan.

Code of Federal Regulations, 2012 CFR

2012-07-01

... calendar quarter of initial operation of the aircraft. (e) Any changes to the aircraft water system... 40 Protection of Environment 24 2012-07-01 2012-07-01 false Aircraft water system operations and...) WATER PROGRAMS (CONTINUED) NATIONAL PRIMARY DRINKING WATER REGULATIONS Aircraft Drinking Water Rule...

40 CFR 141.804 - Aircraft water system operations and maintenance plan.

Code of Federal Regulations, 2011 CFR

2011-07-01

... calendar quarter of initial operation of the aircraft. (e) Any changes to the aircraft water system... 40 Protection of Environment 23 2011-07-01 2011-07-01 false Aircraft water system operations and...) WATER PROGRAMS (CONTINUED) NATIONAL PRIMARY DRINKING WATER REGULATIONS Aircraft Drinking Water Rule...

Host Defense against Opportunist Microorganisms Following Trauma.

DTIC Science & Technology

1988-06-30

aeruginosa and Proteus mirabilis . Drugs (10-20 ag/kg) or placebo were administered intramuscularly to thermally injured guinea pigs at 3 hr postburn and...and Proteus mirabilis were also investigated. Since certain NSAIDs have discrete inhibitory effects on PMNs that occur independently of the classic...25 in thermally injured animals treated with NSAIDs or placebo. Figure 7. Mortality from burn wound infection with P. mirabilis 26 in thermally

Detection of KPC-2 in a Clinical Isolate of Proteus mirabilis and First Reported Description of Carbapenemase Resistance Caused by a KPC Beta-Lactamase in P. mirabilis

USDA-ARS?s Scientific Manuscript database

An isolate of Proteus mirabilis recovered from bacterial cultures was shown to be resistant to imipenem, meropenem, and ertapenem by disk diffusion susceptibility testing. Amplification of whole cell and/or plasmid DNA recovered from the isolate using primers specific for the blaKPC carbapenemase g...

Remote lift fan study program, volume 4

NASA Technical Reports Server (NTRS)

1973-01-01

A study program to select and conduct preliminary design of advanced technology lift fan systems to meet low noise goals of future V/STOL transport aircraft is discussed. This volume contains results of additional studies conducted to support the main preliminary design effort done under the Remote Lift Fan Study Program (Contract NAS3-14406) and a companion effort, the Integral Lift Fan Study (NAS3-14404). These results cover engine emission study, a review of existing engines for research aircraft application and support data for aircraft studies.

Tire and runway surface research

NASA Technical Reports Server (NTRS)

Yager, Thomas J.

1986-01-01

The condition of aircraft tires and runway surfaces can be crucial in meeting the stringent demands of aircraft ground operations, particularly under adverse weather conditions. Gaining a better understanding of the factors influencing the tire/pavement interface is the aim of several ongoing NASA Langley research programs which are described in this paper. Results from several studies conducted at the Langley Aircraft Landing Dynamics Facility, tests with instrumented ground vehicles and aircraft, and some recent aircraft accident investigations are summarized to indicate effects of different tire and runway properties. The Joint FAA/NASA Runway Friction Program is described together with some preliminary test findings. The scope of future NASA Langley research directed towards solving aircraft ground operational problems related to the tire/pavement interface is given.

A novel functional class 2 integron in clinical Proteus mirabilis isolates.

PubMed

Wei, Quhao; Hu, Qingfeng; Li, Shanshan; Lu, Huoyang; Chen, Guoqiang; Shen, Beiqiong; Zhang, Ping; Zhou, Yonglie

2014-04-01

To describe a novel functional class 2 integron that was found in clinical Proteus mirabilis isolates. Class 1 and 2 integrons were screened by PCR in 153 clinical Proteus isolates. The variable regions of class 1 and 2 integrons were determined by restriction analysis and sequencing. The mutations of internal stop codons in class 2 integrons and their common promoters were also determined by sequencing. Enterobacterial repetitive intergenic consensus (ERIC)-PCR was used to analyse the phylogenetic relations of class 2 integron-positive P. mirabilis isolates. Class 1 integrons were detected in 96 (63%) of 153 Proteus isolates: eight different gene cassette arrays were detected, including dfrA32-ereA1-aadA2, which was detected for the first time in P. mirabilis. Class 2 integrons were detected in 101 (66%) of 153 Proteus isolates: four different gene cassette arrays were detected, including dfrA1-catB2-sat2-aadA1, which was detected for the first time in a class 2 integron. A novel functional class 2 integron was detected in 38 P. mirabilis isolates with a common promoter (-35 TTTAAT|16 bp|-10 TAAAGT). The variable region of this functional class 2 integron contained dfrA14 and three novel open reading frames with unknown functions. Very similar ERIC-PCR fingerprinting patterns were detected in these 38 P. mirabilis isolates and were different from other class 2 integron-positive isolates. A novel functional class 2 integron was found for the first time in P. mirabilis. These functional class 2 integron-harbouring P. mirabilis isolates were likely to be clonally spread in our hospital.

Experimental critical loadings and control rod worths in LWR-PROTEUS configurations compared with MCNPX results

DOE Office of Scientific and Technical Information (OSTI.GOV)

Plaschy, M.; Murphy, M.; Jatuff, F.

2006-07-01

The PROTEUS research reactor at the Paul Scherrer Inst. (PSI) has been operating since the sixties and has already permitted, due to its high flexibility, investigation of a large range of very different nuclear systems. Currently, the ongoing experimental programme is called LWR-PROTEUS. This programme was started in 1997 and concerns large-scale investigations of advanced light water reactors (LWR) fuels. Until now, the different LWR-PROTEUS phases have permitted to study more than fifteen different configurations, each of them having to be demonstrated to be operationally safe, in particular, for the Swiss safety authorities. In this context, recent developments of themore » PSI computer capabilities have made possible the use of full-scale SD-heterogeneous MCNPX models to calculate accurately different safety related parameters (e.g. the critical driver loading and the shutdown rod worth). The current paper presents the MCNPX predictions of these operational characteristics for seven different LWR-PROTEUS configurations using a large number of nuclear data libraries. More specifically, this significant benchmarking exercise is based on the ENDF/B6v2, ENDF/B6v8, JEF2.2, JEFF3.0, JENDL3.2, and JENDL3.3 libraries. The results highlight certain library specific trends in the prediction of the multiplication factor k{sub eff} (e.g. the systematically larger reactivity calculated with JEF2.2 and the smaller reactivity associated with JEFF3.0). They also confirm the satisfactory determination of reactivity variations by all calculational schemes, for instance, due to the introduction of a safety rod pair, these calculations having been compared with experiments. (authors)« less

AGFATL- ACTIVE GEAR FLEXIBLE AIRCRAFT TAKEOFF AND LANDING ANALYSIS

NASA Technical Reports Server (NTRS)

Mcgehee, J. R.

1994-01-01

The Active Gear, Flexible Aircraft Takeoff and Landing Analysis program, AGFATL, was developed to provide a complete simulation of the aircraft takeoff and landing dynamics problem. AGFATL can represent an airplane either as a rigid body with six degrees of freedom or as a flexible body with multiple degrees of freedom. The airframe flexibility is represented by the superposition of up to twenty free vibration modes on the rigid-body motions. The analysis includes maneuver logic and autopilots programmed to control the aircraft during glide slope, flare, landing, and takeoff. The program is modular so that performance of the aircraft in flight and during landing and ground maneuvers can be studied separately or in combination. A program restart capability is included in AGFATL. Effects simulated in the AGFATL program include: (1) flexible aircraft control and performance during glide slope, flare, landing roll, and takeoff roll under conditions of changing winds, engine failures, brake failures, control system failures, strut failures, restrictions due to runway length, and control variable limits and time lags; (2) landing gear loads and dynamics for up to five gears; (3) single and multiple engines (maximum of four) including selective engine reversing and failure; (4) drag chute and spoiler effects; (5) wheel braking (including skid-control) and selective brake failure; (6) aerodynamic ground effects; (7) aircraft carrier operations; (8) inclined runways and runway perturbations; (9) flexible or rigid airframes; 10) rudder and nose gear steering; and 11) actively controlled landing gear shock struts. Input to the AGFATL program includes data which describe runway roughness; vehicle geometry, flexibility and aerodynamic characteristics; landing gear(s); propulsion; and initial conditions such as attitude, attitude change rates, and velocities. AGFATL performs a time integration of the equations of motion and outputs comprehensive information on the airframe, state-of-maneuver logic, autopilots, control response, and aircraft loads from impact, runway roll-out, and ground operations. Flexible-body and total (elastic plus rigid-body) displacements, velocities, and accelerations are also output in the flexible-body option for up to twenty points on the aircraft. The AGFATL program is written in FORTRAN IV for batch execution and has been implemented on a CDC CYBER 170 series computer with an overlayed central memory requirement of approximately 141 (octal) of 60 bit words. The AGFATL program was last updated in 1984.

78 FR 68360 - Unmanned Aircraft System Test Site Program

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-14

...-0061] Unmanned Aircraft System Test Site Program AGENCY: Federal Aviation Administration (FAA), DOT...'') test site program; response to comments. SUMMARY: On February 22, 2013 the FAA published and requested public comment on the proposed privacy requirements (the ``Draft Privacy Requirements'') for UAS test...

Advanced supersonic technology and its implications for the future

NASA Technical Reports Server (NTRS)

Driver, C.

1979-01-01

A brief overview of the NASA Supersonic Cruise Research (SCR) program is presented. The SCR program has identified significant improvements in the areas of aerodynamics, structures, propulsion, noise reduction, takeoff and landing procedures, and advanced configuration concepts. These improvements tend to overcome most of the problems which led to the cancellation of the National SST program. They offer the promise of an advanced SST family of aircraft which are environmentally acceptable, have flexible range-payload capability, and are economically viable. The areas of technology addressed by the SCR program have direct application to advanced military aircraft and to supersonic executive aircraft.

Commercial jet transport crashworthiness

NASA Technical Reports Server (NTRS)

Widmayer, E.; Brende, O. B.

1982-01-01

The results of a study to identify areas of research and approaches that may result in improved occupant survivability and crashworthiness of transport aircraft are given. The study defines areas of structural crashworthiness for transport aircraft which might form the basis for a research program. A 10-year research and development program to improve the structural impact resistance of general aviation and commercial jet transport aircraft is planned. As part of this program parallel studies were conducted to review the accident experience of commercial transport aircraft, assess the accident performance of structural components and the status of impact resistance technology, and recommend areas of research and development for that 10-year plan. The results of that study are also given.

A mathematical model for Vertical Attitude Takeoff and Landing (VATOL) aircraft simulation. Volume 3: User's manual for VATOL simulation program

NASA Technical Reports Server (NTRS)

Fortenbaugh, R. L.

1980-01-01

Instructions for using Vertical Attitude Takeoff and Landing Aircraft Simulation (VATLAS), the digital simulation program for application to vertical attitude takeoff and landing (VATOL) aircraft developed for installation on the NASA Ames CDC 7600 computer system are described. The framework for VATLAS is the Off-Line Simulation (OLSIM) routine. The OLSIM routine provides a flexible framework and standardized modules which facilitate the development of off-line aircraft simulations. OLSIM runs under the control of VTOLTH, the main program, which calls the proper modules for executing user specified options. These options include trim, stability derivative calculation, time history generation, and various input-output options.

Time-based air traffic management using expert systems

NASA Technical Reports Server (NTRS)

Tobias, L.; Scoggins, J. L.

1986-01-01

A prototype expert system has been developed for the time scheduling of aircraft into the terminal area. The three functions of the air-traffic-control schedule advisor are as follows: (1) for each new arrival, it develops an admisible flight plan for that aircraft; (2) as the aircraft progresses through the terminal area, it monitors deviations from the aircraft's flight plan and provides advisories to return the aircraft to its assigned schedule; and (3) if major disruptions such as missed approaches occur, it develops a revised plan. The advisor is operational on a Symbolics 3600, and is programmed in MRS (a logic programming language), Lisp, and Fortran.

Alternate-fueled transport aircraft possibilities

NASA Technical Reports Server (NTRS)

Aiken, W. S.

1977-01-01

The paper is organized to describe: (1) NASA's cryogenically fueled aircraft program; (2) LH2 subsonic and supersonic transport design possibilities (3) the fuel system and ground side problems associated with LH2 distribution; (4) a comparison of LCH4 with LH2; (5) the design possibilities for LCH4 fueled aircraft; and (6) a summary of where NASA's cryogenically fueled programs are headed.

Aircraft noise prediction program validation

NASA Technical Reports Server (NTRS)

Shivashankara, B. N.

1980-01-01

A modular computer program (ANOPP) for predicting aircraft flyover and sideline noise was developed. A high quality flyover noise data base for aircraft that are representative of the U.S. commercial fleet was assembled. The accuracy of ANOPP with respect to the data base was determined. The data for source and propagation effects were analyzed and suggestions for improvements to the prediction methodology are given.

[Current resistence situation in a surgical and urological department].

PubMed

Wacha, H; Stix, H

1976-04-15

Spectrum and sensitivity of bacteria were studied at the Surgical (534 positive wound smears) and the Urological Clinics (7879 urine specimens). Krankenhaus Nordwest, Frankfurt/M., during the period of 1969-1971 and in 1973. The most common organisms identified in wound smears were E. coli, followed by Staph. areus, Aerobacter and Proteus species. E. coli were also predominant in urine, but followed by Enterococci, Proteus and Pseudomonas. E. coli, Proteus species and especially Pseudomonas increased in number whereas Enterococci decreased. There was no pronounced increase in resistance to 9 current antibiotics as well as to chemotherapeutics during the observation period which was particularly striking in the case of Ampicillin used on a large scale. The results of our study support the presently employed therapeutic method using bactericidal antibiotics of the penicillin group in strict indications.

Peptides as modifiers of Na+-induced pinocytosis in starved Amoeba proteus.

PubMed

Josefsson, J O; Johansson, P

1985-01-01

Low concentrations of six peptide hormones; glucagon, vasoactive intestinal peptide, substance P, angiotensin II, lysine-vasopressin, arginine-vasopressin, and the chemotactic peptide fMet-Leu-Phe, activated the capacity for pinocytosis in starved Amoeba proteus. Competitive inhibitors of the chemotactic peptide in leucocytes inhibited activation by fMet-Leu-Phe, suggesting that its action in the amoeba is mediated by specific receptors. The opioid peptides, beta-endorphin, dynorphin (1-13) and leu-enkephalin abolished through a naloxone-sensitive mechanism activation by hormones and several other activating agents. Also, low concentrations of beef and pork insulin inhibited activation by peptide hormones. An insulin analogue of low potency in mammalian cells was inactive in the amoeba. These results support the hypothesis that besides opioid receptors, there may be insulin receptors and possibly receptors for several other peptide hormones in Amoeba proteus.

Configuration aerodynamics

NASA Technical Reports Server (NTRS)

Polhamus, E. C.; Gloss, B. B.

1981-01-01

Static aerodynamic research related to aircraft configurations in their cruise or combat modes is discussed. Subsonic transport aircraft, transonic tactical aircraft, and slender wing aircraft are considered. The status and plans of Langley's NTF configuration research program are reviewed. Recommendations for near term configuration research are made.

Aerodynamic design and analysis system for supersonic aircraft. Part 3: Computer program description

NASA Technical Reports Server (NTRS)

Middleton, W. D.; Lundry, J. L.; Coleman, R. G.

1975-01-01

The computer program for the design and analysis of supersonic aircraft configurations is presented. The schematics of the program structure are provided. The individual overlays and subroutines are described. The system is useful in determining surface pressures and supersonic area rule concepts.

Fourier Transform Infrared Spectroscopy as a Tool in Analysis of Proteus mirabilis Endotoxins.

PubMed

Żarnowiec, Paulina; Czerwonka, Grzegorz; Kaca, Wiesław

2017-01-01

Fourier transform infrared spectroscopy (FT-IR) was used to scan whole bacterial cells as well as lipopolysaccharides (LPSs, endotoxins) isolated from them. Proteus mirabilis cells, with chemically defined LPSs, served as a model for the ATR FT-IR method. The paper focuses on three steps of infrared spectroscopy: (1) sample preparation, (2) IR scanning, and (3) multivariate analysis of IR data (principal component analysis, PCA).

Arthrite septique à Proteus mirabilis

PubMed Central

Sbiti, Mohammed; Bouhamidi, Bahia; Louzi, Lhoussaine

2017-01-01

L'arthrite septique aigue est une pathologie peu fréquente mais grevée d'un pronostic lourd en termes de mortalité et morbidité. Nous rapportons un cas d'arthrite septique à Proteus mirabilis survenue de façon spontanée chez un patient de 61 ansprésentant un diabète compliqué,associée à des hémoculturespositives et des cultures positives du liquide articulaire. L'évolution était favorable grâce au diagnostic précoce et à l'institution d'une antibiothérapie adéquate. L'arthrite septique à Proteus Mirabilis est rare, ce qui nous a incité à revoir dans la littérature des séries d'arthrites à pyogènes incluant Proteus mirabilis portant sur les facteurs de risque, la pathogénie, le traitement et l'évolution de ces pathologies. Le diagnostic est avant tout microbiologique, la ponction articulaire précoce est réalisée avant toute antibiothérapie, l'examen direct, la culture et l'antibiogramme qui va guider le choix d'une antibiothérapie. L'arthrite septique est une urgence diagnostique et thérapeutique, la prise en charge précoce de cette pathologie permet une guérison sans séquelles. PMID:28674590

Pathogenetic insights from quantification of the cerebriform connective tissue nevus in Proteus syndrome.

PubMed

Nathan, Neera R; Patel, Rachna; Crenshaw, Molly M; Lindhurst, Marjorie J; Olsen, Cara; Biesecker, Leslie G; Keppler-Noreuil, Kim M; Darling, Thomas N

2018-04-01

The plantar cerebriform connective tissue nevus (CCTN) is the most common and problematic cutaneous manifestation of Proteus syndrome. To gain insights into CCTN pathogenesis and natural history. The size and location of plantar CCTN was measured on 152 images from 22 individuals with Proteus syndrome by 2 independent, blinded reviewers. Average measures of plantar CCTN were transformed into a linear mixed model to estimate proportionate change in size with age. Median patient age was 6.9 years at study onset. The intraclass correlation coefficient between 2 blinded reviewers was 0.946 for CCTN single measures. The CCTN relative area increased with age in children (n = 18, P < .0001) by 5.6% per year. Confluent papules and nodules extending beyond the boundaries of CCTNs were gradually replaced by typical CCTN over time. The location of CCTN in different individuals overlapped near the ball of the foot. A positive relationship between CCTN growth rate and AKT1 mutant allele frequency was observed (0.62, P = .10, n = 8). This was a retrospective review using photographs. CCTN growth is affected by age and extent of the CCTN precursor lesion. Monitoring of CCTN size might prove useful for evaluating drug response in the treatment of Proteus syndrome. Published by Elsevier Inc.

The nuclear membrane-associated honeycomb structure of the unicellular organism Amoeba proteus: on the search for homologies with the nuclear lamina of metazoa.

PubMed

Schmidt, M; Grossmann, U; Krohne, G

1995-07-01

In the protozoon Amoeba proteus, a complex and highly organized structure with the morphology of a honeycomb is associated with the nucleoplasmic surface of the nuclear membrane. We have tested whether this structure exhibits similarity to the nuclear lamina of metazoic organisms. First, we have shown that the honeycomb layer is composed of 3 to 5 nm thick protein fibrils resistant to treatment with detergent, high salt, and digestion with nucleases, thus possessing properties typical for karyoskeletal elements. However, in contrast to the meshwork of lamin filaments in somatic cells of metazoic organisms, the honeycomb layer is not tightly anchored to the nucleoplasmic side of pore complexes, or to the inner nuclear membrane. Second, in microinjection experiments we investigated whether fluorescently labeled lamins of Xenopus laevis (lamins A and LI) and Drosophila melanogaster (lamin Dmo) were able to associate in vivo with the Amoeba proteus honeycomb structure. In microinjected amoeba these three lamins were efficiently transported into the nucleus, but did not associate with the nuclear envelope. Our results suggest that the Amoeba proteus nuclear envelope, including the honeycomb layer, does not contain proteins exhibiting high homologies to lamins of metazoan species thus preventing the localized assembly of microinjected lamins along the nuclear periphery.

Presence of aquaporin and V-ATPase on the contractile vacuole of Amoeba proteus.

PubMed

Nishihara, Eri; Yokota, Etsuo; Tazaki, Akira; Orii, Hidefumi; Katsuhara, Maki; Kataoka, Kensuke; Igarashi, Hisako; Moriyama, Yoshinori; Shimmen, Teruo; Sonobe, Seiji

2008-03-01

The results of water permeability measurements suggest the presence of an AQP (aquaporin) in the membrane of the CV (contractile vacuole) in Amoeba proteus [Nishihara, Shimmen and Sonobe (2004) Cell Struct. Funct. 29, 85-90]. In the present study, we cloned an AQP gene from A. proteus [ApAQP (A. proteus AQP)] that encodes a 295-amino-acid protein. The protein has six putative TMs (transmembrane domains) and two NPA (Asn-Pro-Ala) motifs, which are conserved among various AQPs and are thought to be involved in the formation of water channels that span the lipid bilayer. Using Xenopus oocytes, we have demonstrated that the ApAQP protein product can function as a water channel. Immunofluorescence microscopy with anti-ApAQP antibody revealed that ApAQP is detected on the CV membrane and on the vesicles around the CV. The presence of V-ATPase (vacuolar H+-ATPase) on the vesicle membrane around the CV was also detected. Our data on ApAQP allow us to provide the first informed explanation of the high water permeability of the CV membrane in amoeba. Moreover, the results suggest that vesicles possessing V-ATPase are involved in generating an osmotic gradient. Based on our findings, we propose a new hypothesis for the mechanism of CV function.

The Challenges Affecting Heavy Lift Aircraft Development to Support Sea Basing

DTIC Science & Technology

2005-06-17

effect timely development of heavy lift aircraft to support sea basing. 15. SUBJECT TERMS Aircraft Development, Aircraft Acquisition, Aircraft Program...bullet theory, vision, technology, and politics are the most prevalent factors, amongst many, that could potentially effect timely development of heavy...discussion will focus on some current examples of aircraft that will support sea basing and on factors effecting their development. 14 Secondary Questions

A computer program for fitting smooth surfaces to an aircraft configuration and other three dimensional geometries

NASA Technical Reports Server (NTRS)

Craidon, C. B.

1975-01-01

A computer program that uses a three-dimensional geometric technique for fitting a smooth surface to the component parts of an aircraft configuration is presented. The resulting surface equations are useful in performing various kinds of calculations in which a three-dimensional mathematical description is necessary. Programs options may be used to compute information for three-view and orthographic projections of the configuration as well as cross-section plots at any orientation through the configuration. The aircraft geometry input section of the program may be easily replaced with a surface point description in a different form so that the program could be of use for any three-dimensional surface equations.

Fiber Optic System Test Results In A Tactical Military Aircraft

NASA Astrophysics Data System (ADS)

Uhlhorn, Roger W.; Greenwell, Roger A.

1980-09-01

The YAV-8B Electromagnetic Immunity and Flight-Test Program was established to evaluate the susceptibility of wire and optical fiber signal transmission lines to electromagnetic interference when these lines are installed in a graphite/epoxy composite wing and to demonstrate the flightworthiness of fiber optics interconnects in the vertical/ short takeoff and landing aircraft environment. In response, two fiber optic systems were designed, fabricated, and flight tested by McDonnell Aircraft Co. (MCAIR), a division of the McDonnell Douglas Corporation, on the two YAV-8B V/STOL flight test aircraft. The program successfully demonstrated that fiber optics are compatible with the attack aircraft environment. As a result, the full scale development AV-8B will incorporate fiber optics in a point-to-point data link. We describe here the fiber optic systems designs, test equipment development, cabling and connection requirements, fabrication and installation experience, and flight test program results.

Remotely piloted aircraft in the civil environment

NASA Technical Reports Server (NTRS)

Gregory, T. J.; Nelms, W. P.; Karmarkar, J. S.

1977-01-01

Remotely piloted aircraft (RPA's) are of increasing interest to the military and others, as evidenced by a number of technology and development programs that are currently funded or planned. These programs have led to a number of test aircraft with significant capabilities, and future remotely piloted aircraft are forecast to become even more capable as the technology in a number of important subsystem areas is progressing at a rapid rate. As the size, weight and cost of RPA's is reduced, the prospect of using them for civilian applications becomes more likely.

Update of Aircraft Profile Data for the Integrated Noise Model Computer Program. Volume 2. Appendix A: Aircraft Takeoff and Landing Profiles

DTIC Science & Technology

1992-03-01

8 KT) 02- 10 -1992 09: 48 :32 AIRCRAFT ID AIRCRAFT AND ENGINE AIRCRAFT NUMBER NAMES CATEGORY ------------------- ------------------- -------- 003...MAX CLIMB 8 CLIMB ZErO MAX CLIMB 9 CLIMB ZERO MAX CLIMB A-21 TAKEOFF PROFILE DATA (HEADWIND = 8 KT) 02- 10 -1992 09: 48 :36 AIRCRAFT AIRCRAFT AND ENGINE...CLIMB ZERO USR SUPPL 34033 LB 10 CLIMB ZERO USR SUPPL 34798 LB A-194 TAKEOFF PROFILE DATA (HEADWIND = 8 KT) 06-24-1991 10 :33: 48 AIRCRAFT AIRCRAFT

In-situ Charge Determination for Vapor Cycle Systems in Aircraft (Postprint)

DTIC Science & Technology

2012-10-22

control and operation in support of the Energy Optimized Aircraft (EOA) initiative and the Integrated Vehicle ENergy Technology (INVENT) program...the Energy Optimized Aircraft (EOA) initiative and the Integrated Vehicle ENergy Technology (INVENT) program. Previous papers on ToTEMS have discussed...stationary chillers include a reduction in cooling capacity due to reduced availability of liquid for evaporation. In addition, the coefficient of

Overview of FIREMEN program at Ames Research Center

NASA Technical Reports Server (NTRS)

Kourtides, D. A.

1978-01-01

The Ames Firemen Program is described. The key elements of the program include: (1) the development and evaluation of aircraft interior composite panels; (2) the thermochemical and flammability characterization of thermoset and thermoplastic resins; and (3) the evolution of fire resist aircraft seat components. The first two elements are presented.

Aerospace Safety Advisory Panel

NASA Technical Reports Server (NTRS)

1985-01-01

The following areas of NASA's responsibilities are examined: (1) the Space Transportation System (STS) operations and evolving program elements; (2) establishment of the Space Station program organization and issuance of requests for proposals to the aerospace industry; and (3) NASA's aircraft operations, including research and development flight programs for two advanced X-type aircraft.

GASP- GENERAL AVIATION SYNTHESIS PROGRAM

NASA Technical Reports Server (NTRS)

Galloway, T. L.

1994-01-01

The General Aviation Synthesis Program, GASP, was developed to perform tasks generally associated with the preliminary phase of aircraft design. GASP gives the analyst the capability of performing parametric studies in a rapid manner during preliminary design efforts. During the development of GASP, emphasis was placed on small fixed-wing aircraft employing propulsion systems varying from a single piston engine with a fixed pitch propeller through twin turboprop/turbofan systems as employed in business or transport type aircraft. The program is comprised of modules representing the various technical disciplines of design, integrated into a computational flow which ensures that the interacting effects of design variables are continuously accounted for in the aircraft sizing procedures. GASP provides a useful tool for comparing configurations, assessing aircraft performance and economics, and performing tradeoff and sensitivity studies. By utilizing GASP, the impact of various aircraft requirements and design factors may be studied in a systematic manner, with benefits being measured in terms of overall aircraft performance and economics. The GASP program consists of a control module and six "technology" submodules which perform the various independent studies required in the design of general aviation or small transport type aircraft. The six technology modules include geometry, aerodynamics, propulsion, weight and balance, mission analysis, and economics. The geometry module calculates the dimensions of the synthesized aircraft components based on such input parameters as number of passengers, aspect ratio, taper ratio, sweep angles, and thickness of wing and tail surfaces. The aerodynamics module calculates the various lift and drag coefficients of the synthesized aircraft based on inputs concerning configuration geometry, flight conditions, and type of high lift device. The propulsion module determines the engine size and performance for the synthesized aircraft. Both cruise and take-off requirements for the aircraft may be specified. This module can currently simulate turbojet, turbofan, turboprop, and reciprocating or rotating combustion engines. The weight and balance module accepts as input gross weight, payload, aircraft geometry, and weight trend coefficients for use in calculating the size of tip tanks and wing location required such that the synthesized aircraft is in balance for center of gravity travel. In the mission analysis module, the taxi, take-off, climb, cruise, and landing segments of a specified mission are analyzed to compute the total range, and the aircraft size required to provide this range is determined. In the economic module both the flyaway and operating costs are determined from estimated resources and services cost. The six technology modules are integrated into a single synthesis system by the control module. This integrated approach ensures that the results from each module contain the effect of design interactions among all the modules. Starting from a set of simple input quantities concerning aircraft type, size, and performance, the synthesis is extended to the point where all of the important aircraft characteristics have been analyzed quantitatively. Together, the synthesis model and procedure develops aircraft configurations in a manner useful in parametric analysis and provides a useful step toward more detailed analytical and experimental studies. The GASP program is written in FORTRAN IV for batch execution and has been implemented on a CDC CYBER 170 series computer with a central memory requirement of approximately 200K(octal) of 60 bit words. The GASP program was developed in 1978.

40 CFR 141.804 - Aircraft water system operations and maintenance plan.

Code of Federal Regulations, 2010 CFR

2010-07-01

...) WATER PROGRAMS (CONTINUED) NATIONAL PRIMARY DRINKING WATER REGULATIONS Aircraft Drinking Water Rule... must include the following requirements for procedures for disinfection and flushing of aircraft water system. (i) The air carrier must conduct disinfection and flushing of the aircraft water system in...

Analysis and design of insulation systems for LH2-fueled aircraft

NASA Technical Reports Server (NTRS)

Cunnington, G. R., Jr.

1979-01-01

An analytical program was conducted to evaluate the performance of 15 potential insulations for the fuel tanks of a subsonic LH2-fueled transport aircraft intended for airline service in the 1990-1995 time period. As a result, two candidate insulation systems are proposed for subsonic transport aircraft applications. Both candidates are judged to be the optimum available and should meet the design requirements. However, because of the long-life cyclic nature of the application and the cost sensitivity of airline operations, an experimental tank/insulation development or proof-of-concept program is recommended. This program should be carried out with a nearly full-scale system which would be subjected to the cyclic thermal and mechanical inputs anticipated in aircraft service.

X-29 flight-research program

NASA Technical Reports Server (NTRS)

Putnam, T. W.

1984-01-01

The X-29A aircraft is the first manned, experimental high-performance aircraft to be fabricated and flown in many years. The approach for expanding the X-29 flight envelope and collecting research data is described including the methods for monitoring wind divergence, flutter, and aeroservoelastic coupling of the aerodynamic forces with the structure and the flight-control system. Examples of the type of flight data to be acquired are presented along with types of aircraft maneuvers that will be flown. A brief description of the program management structure is also presented and the program schedule is discussed.

Toward Mach 2: The Douglas D-558 Program

NASA Technical Reports Server (NTRS)

Hunley, J. D. (Editor)

1999-01-01

This monograph contains the edited transcript of a symposium marking the 50th anniversary of this aircraft's first flight in 1948. A sister aircraft to the more well-known rocket-powered X-1, the jet-powered D-558 gave NACA researchers many useful insights about the transonic speed range. Several of the original aircraft pilots present accounts of their involvement in the program. Appendices include design specifications for the Douglas D-558-1 and -2 as well as declassified documentation and memoranda (1949-1957) regarding the progress of the program.

ANOPP programmer's reference manual for the executive System. [aircraft noise prediction program

NASA Technical Reports Server (NTRS)

Gillian, R. E.; Brown, C. G.; Bartlett, R. W.; Baucom, P. H.

1977-01-01

Documentation for the Aircraft Noise Prediction Program as of release level 01/00/00 is presented in a manual designed for programmers having a need for understanding the internal design and logical concepts of the executive system software. Emphasis is placed on providing sufficient information to modify the system for enhancements or error correction. The ANOPP executive system includes software related to operating system interface, executive control, and data base management for the Aircraft Noise Prediction Program. It is written in Fortran IV for use on CDC Cyber series of computers.

Real-time Data Processing and Visualization for the Airborne Scanning High-resolution Interferometer Sounder (S-HIS)

NASA Astrophysics Data System (ADS)

Taylor, J. K.; Revercomb, H. E.; Hoese, D.; Garcia, R. K.; Smith, W. L.; Weisz, E.; Tobin, D. C.; Best, F. A.; Knuteson, R. O.; Sullivan, D. V.; Barnes, C. M.; Van Gilst, D. P.

2015-12-01

The Hurricane and Severe Storm Sentinel (HS3) is a five-year NASA mission targeted to enhance the understanding of the formation and evolution of hurricanes in the Atlantic basin. Measurements were made from two NASA Global Hawk Unmanned Aircraft Systems (UAS) during the 2012 through 2014 hurricane seasons, with flights conducted from the NASA Wallops Flight Facility. The Global Hawk aircraft are capable of high altitude flights with durations of up to 30 hours, which allow extensive observations over distant storms, not typically possible with manned aircraft. The two NASA Global Hawks were equipped with instrument suites to study the storm environment, and inner core structure and processes, respectively. The Scanning High-resolution Interferometer Sounder (S-HIS), designed and built by the University of Wisconsin (UW) Space Science and Engineering Center (SSEC), measures emitted thermal radiation at high spectral resolution between 3.3 and 18 microns. The radiance measurements are used to obtain temperature and water vapor profiles of the Earth's atmosphere. The S-HIS spatial resolution is 2 km at nadir, across a 40 km ground swath from a nominal altitude of 20 kilometers. Since 1998, the S-HIS has participated in 33 field campaigns and has proven to be extremely dependable, effective, and highly accurate. It has flown on the NASA ER-2, DC-8, Proteus, WB-57, and Global Hawk airborne platforms. The UW S-HIS infrared sounder instrument is equipped with a real-time ground data processing system capable of delivering atmospheric profiles, radiance data, and engineering status to mission support scientists - all within less than one minute from the time of observation. This ground data processing system was assembled by a small team using existing software and proven practical techniques similar to a satellite ground system architecture. This summary outlines the design overview for the system and illustrates the data path, content, and outcomes.

Development and validation of a general purpose linearization program for rigid aircraft models

NASA Technical Reports Server (NTRS)

Duke, E. L.; Antoniewicz, R. F.

1985-01-01

A FORTRAN program that provides the user with a powerful and flexible tool for the linearization of aircraft models is discussed. The program LINEAR numerically determines a linear systems model using nonlinear equations of motion and a user-supplied, nonlinear aerodynamic model. The system model determined by LINEAR consists of matrices for both the state and observation equations. The program has been designed to allow easy selection and definition of the state, control, and observation variables to be used in a particular model. Also, included in the report is a comparison of linear and nonlinear models for a high performance aircraft.

41 CFR 102-33.220 - What are the responsibilities of an agency's aviation program in justifying the use of a...

Code of Federal Regulations, 2013 CFR

2013-07-01

... responsibilities of an agency's aviation program in justifying the use of a Government aircraft to transport... Aircraft § 102-33.220 What are the responsibilities of an agency's aviation program in justifying the use... authority, the agency's aviation program must provide cost estimates to assist in determining whether or not...

41 CFR 102-33.220 - What are the responsibilities of an agency's aviation program in justifying the use of a...

Code of Federal Regulations, 2010 CFR

2010-07-01

... responsibilities of an agency's aviation program in justifying the use of a Government aircraft to transport... Aircraft § 102-33.220 What are the responsibilities of an agency's aviation program in justifying the use... authority, the agency's aviation program must provide cost estimates to assist in determining whether or not...

41 CFR 102-33.220 - What are the responsibilities of an agency's aviation program in justifying the use of a...

Code of Federal Regulations, 2014 CFR

2014-01-01

... responsibilities of an agency's aviation program in justifying the use of a Government aircraft to transport... Aircraft § 102-33.220 What are the responsibilities of an agency's aviation program in justifying the use... authority, the agency's aviation program must provide cost estimates to assist in determining whether or not...

41 CFR 102-33.220 - What are the responsibilities of an agency's aviation program in justifying the use of a...

Code of Federal Regulations, 2011 CFR

2011-01-01

... responsibilities of an agency's aviation program in justifying the use of a Government aircraft to transport... Aircraft § 102-33.220 What are the responsibilities of an agency's aviation program in justifying the use... authority, the agency's aviation program must provide cost estimates to assist in determining whether or not...

41 CFR 102-33.220 - What are the responsibilities of an agency's aviation program in justifying the use of a...

Code of Federal Regulations, 2012 CFR

2012-01-01

... responsibilities of an agency's aviation program in justifying the use of a Government aircraft to transport... Aircraft § 102-33.220 What are the responsibilities of an agency's aviation program in justifying the use... authority, the agency's aviation program must provide cost estimates to assist in determining whether or not...

Proteus Survey: Technical Manual and Codebook

DTIC Science & Technology

1992-06-01

Reserve Officer Training Corp, 20% from Officer Candidate School and Direct Commission) and by gender . Female officers were supposed to be oversampled...stratified by source of commission (40% USMA, 40% ROTC, 20% OCS and DC) and by gender , as in previous years. A total of approximately 7,000 surveys were...for the 1987 Proteus Survey and the population percentages from the OLRDB for each of the key strata ( gender and source of commission) reportedly used

Proteus mirabilis fimbriae- and urease-dependent clusters assemble in an extracellular niche to initiate bladder stone formation.

PubMed

Schaffer, Jessica N; Norsworthy, Allison N; Sun, Tung-Tien; Pearson, Melanie M

2016-04-19

The catheter-associated uropathogenProteus mirabilisfrequently causes urinary stones, but little has been known about the initial stages of bladder colonization and stone formation. We found thatP. mirabilisrapidly invades the bladder urothelium, but generally fails to establish an intracellular niche. Instead, it forms extracellular clusters in the bladder lumen, which form foci of mineral deposition consistent with development of urinary stones. These clusters elicit a robust neutrophil response, and we present evidence of neutrophil extracellular trap generation during experimental urinary tract infection. We identified two virulence factors required for cluster development: urease, which is required for urolithiasis, and mannose-resistantProteus-like fimbriae. The extracellular cluster formation byP. mirabilisstands in direct contrast to uropathogenicEscherichia coli, which readily formed intracellular bacterial communities but not luminal clusters or urinary stones. We propose that extracellular clusters are a key mechanism ofP. mirabilissurvival and virulence in the bladder.

Linear Cowden nevus: a new distinct epidermal nevus.

PubMed

Happle, Rudolf

2007-01-01

Within the group of epidermal nevi, a so far nameless disorder is described under the term "linear Cowden nevus". This non-organoid epidermal nevus is caused by loss of heterozygosity, occurring at an early developmental stage in an embryo with a germline PTEN mutation, giving rise to Cowden disease. Hence, linear Cowden nevus can be categorized as a characteristic feature of type 2 segmental Cowden disease. Until now, several authors had mistaken this epidermal nevus as a manifestation of Proteus syndrome. The concept of linear Cowden nevus implies that Proteus syndrome is by no means caused by PTEN mutations. As a clinical difference, linear Cowden nevus is markedly papillomatous and thick, whereas linear Proteus nevus tends to be rather flat. Moreover, the spectrum of possibly associated cutaneous or extracutaneous anomalies differs in the two types of nevi. In conclusion, linear Cowden nevus, that may also be called "linear PTEN nevus", represents a distinct clinicogenetic entity.

Intracellular pressure is a motive force for cell motion in Amoeba proteus.

PubMed

Yanai, M; Kenyon, C M; Butler, J P; Macklem, P T; Kelly, S M

1996-01-01

The cortical filament layer of free-living amoebae contains concentrated actomyosin, suggesting that it can contract and produce an internal hydrostatic pressure. We report here on direct and dynamic intracellular pressure (P(ic)) measurements in Amoeba proteus made using the servo-null technique. In resting apolar A. proteus, P(ic) increased while the cells remained immobile and at apparently constant volume. P(ic) then decreased approximately coincident with pseudopod formation. There was a positive correlation between P(ic) at the onset of movement and the rate of pseudopod formation. These results are the first direct evidence that hydrostatic pressure may be a motive force for cell motion. We postulate that contractile elements in the amoeba's cortical layer contract and increase P(ic) and that this P(ic) is utilized to overcome the viscous flow resistance of the intracellular contents during pseudopod formation.

CYTOPLASMIC DNA SYNTHESIS IN AMOEBA PROTEUS

PubMed Central

Rabinovitch, M.; Plaut, W.

1962-01-01

The incorporation of tritiated thymidine in Amoeba proteus was reinvestigated in order to see if it could be associated with microscopically detectable structures. Staining experiments with basic dyes, including the fluorochrome acridine orange, revealed the presence of large numbers of 0.3 to 0.5 µ particles in the cytoplasm of all cells studied. The effect of nuclease digestion on the dye affinity of the particles suggests that they contain DNA as well as RNA. Centrifugation of living cells at 10,000 g leads to the sedimentation of the particles in the centrifugal third of the ameba near the nucleus. Analysis of centrifuged cells which had been incubated with H3-thymidine showed a very high degree of correlation between the location of the nucleic acid-containing granules and that of acid-insoluble, deoxyribonuclease-sensitive labeled molecules and leads to the conclusion that cytoplasmic DNA synthesis in Amoeba proteus occurs in association with these particles. PMID:13972870

Elemental maps of Amoeba proteus by a scanning proton microprobe

NASA Astrophysics Data System (ADS)

Li, Minqian; Zhu, Jingde; Zhu, Jieqing; Zhou, Zheng; Huang, Zeqi; Zhou, Weiying; Cholewa, M.; Legge, G. J. F.

1991-03-01

Elemental maps for P, S, Cl, K, Ca and Zn of individual Amoeba proteus were obtained with the Melbourne scanning proton microprobe. The emphasis was put on the relationship of both distribution and concentration of Zn within the cell and the growth inhibitory effect of higher Zn concentrations in the culture medium. At a concentration of 0.04 mmol ZnCl 2, Amoeba growth was inhibited. But at a concentration of 0.0016 mmol, the Amoeba grew as well as a control grown without addition of Zn. We found that in the former (0.04 mmol) Zn concentrated three times more than in the latter (0.0016 mmol), and also that Zn was enriched much more in the nucleus and endoplasm (five to six times) than in other parts of the cell (two times). Future work along these lines may provide insight into the mechanism by which Zn affects the growth of Amoeba proteus and other cells.

[Regulation of cortical cytoskeleton dynamics during migration of free-living amoebae].

PubMed

Kłopocka, Wanda; Redowicz, Maria Jolanta; Wasik, Anna

2009-01-01

Amoeba proteus and smaller by an order of magnitude (and evolutionary younger) Acanthamoeba castellanii have been for many years model cells for studies of amoeboidal (crawling) type of movement, characteristic also for some of metazoan cells such as fibroblasts, granulocytes and macrophages. Amoeboidal migration is indispensable of organization and dynamics of actin-based cytoskeleton. While there is a number of data on molecular mechanisms of motility of A. castellanii, there is very little known about bases of migration of A. proteus. Noteworthy, a large A. proteus (length approximately 600 microm) have been from over a century an object for studies on biology and physiology of cellular migration. This review describes the current knowledge on molecular aspects of force generation required for migration of these two amoebae and attempts to compare the functioning and regulation of actin cytoskeleton in these free-living unicellular species.

System IDentification Programs for AirCraft (SIDPAC)

NASA Technical Reports Server (NTRS)

Morelli, Eugene A.

2002-01-01

A collection of computer programs for aircraft system identification is described and demonstrated. The programs, collectively called System IDentification Programs for AirCraft, or SIDPAC, were developed in MATLAB as m-file functions. SIDPAC has been used successfully at NASA Langley Research Center with data from many different flight test programs and wind tunnel experiments. SIDPAC includes routines for experiment design, data conditioning, data compatibility analysis, model structure determination, equation-error and output-error parameter estimation in both the time and frequency domains, real-time and recursive parameter estimation, low order equivalent system identification, estimated parameter error calculation, linear and nonlinear simulation, plotting, and 3-D visualization. An overview of SIDPAC capabilities is provided, along with a demonstration of the use of SIDPAC with real flight test data from the NASA Glenn Twin Otter aircraft. The SIDPAC software is available without charge to U.S. citizens by request to the author, contingent on the requestor completing a NASA software usage agreement.

A computer program for obtaining airplane configuration plots from digital Datcom input data

NASA Technical Reports Server (NTRS)

Roy, M. L.; Sliwa, S. M.

1983-01-01

A computer program is described which reads the input file for the Stability and Control Digital Datcom program and generates plots from the aircraft configuration data. These plots can be used to verify the geometric input data to the Digital Datcom program. The program described interfaces with utilities available for plotting aircraft configurations by creating a file from the Digital Datcom input data.

Preliminary analysis of long-range aircraft designs for future heavy airlift missions

NASA Technical Reports Server (NTRS)

Nelms, W. P., Jr.; Murphy, R.; Barlow, A.

1976-01-01

A computerized design study of very large cargo aircraft for the future heavy airlift mission was conducted using the Aircraft Synthesis program (ACSYNT). The study was requested by the Air Force under an agreement whereby Ames provides computerized design support to the Air Force Flight Dynamics Laboratory. This effort is part of an overall Air Force program to study advanced technology large aircraft systems. Included in the Air Force large aircraft program are investigations of missions such as heavy airlift, airborne missile launch, battle platform, command and control, and aerial tanker. The Ames studies concentrated on large cargo aircraft of conventional design with payloads from 250,000 to 350,000 lb. Range missions up to 6500 n.mi. and radius missions up to 3600 n.mi. have been considered. Takeoff and landing distances between 7,000 and 10,000 ft are important constraints on the configuration concepts. The results indicate that a configuration employing conventional technology in all disciplinary areas weighs approximately 2 million pounds to accomplish either a 6500-n.mi. range mission or a 3600-n.mi. radius mission with a 350,000-lb payload.

Aircraft and ground vehicle friction correlation test results obtained under winter runway conditions during joint FAA/NASA Runway Friction Program

NASA Technical Reports Server (NTRS)

Yager, Thomas J.; Vogler, William A.; Baldasare, Paul

1988-01-01

Aircraft and ground vehicle friction data collected during the Joint FAA/NASA Runway Friction Program under winter runway conditions are discussed and test results are summarized. The relationship between the different ground vehicle friction measurements obtained on compacted snow- and ice-covered conditions is defined together with the correlation to aircraft tire friction performance under similar runway conditions.

X-Wing Research Vehicle in Hangar

NASA Technical Reports Server (NTRS)

1987-01-01

One of the most unusual experimental flight vehicles appearing at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center) in the 1980s was the Rotor Systems Research Aircraft (RSRA) X-Wing aircraft, seen here on the ramp. The craft was developed originally and then modified by Sikorsky Aircraft for a joint NASA-Defense Advanced Research Projects Agency (DARPA) program and was rolled out 19 August 1986. Taxi tests and initial low-altitude flight tests without the main rotor attached were carried out at Dryden before the program was terminated in 1988. The unusual aircraft that resulted from the Ames Research Center/Army X-Wing Project was flown at the Ames-Dryden Flight Research Facility (now Dryden Flight Research Center), Edwards, California, beginning in the spring of 1984, with a follow-on program beginning in 1986. The program, was conceived to provide an efficient combination of the vertical lift characteristic of conventional helicopters and the high cruise speed of fixed-wing aircraft. It consisted of a hybrid vehicle called the NASA/Army Rotor Systems Research Aircraft (RSRA), which was equipped with advanced X-wing rotor systems. The program began in the early 1970s to investigate ways to increase the speed of rotor aircraft, as well as their performance, reliability, and safety . It also sought to reduce the noise, vibration, and maintenance costs of helicopters. Sikorsky Aircraft Division of United Technologies Laboratories built two RSRA aircraft. NASA's Langley Research Center, Hampton, Virginia, did some initial testing and transferred the program to Ames Research Center, Mountain View, California, for an extensive flight research program conducted by Ames and the Army. The purpose of the 1984 tests was to demonstrate the fixed-wing capability of the helicopter/airplane hybrid research vehicle and explore its flight envelope and flying qualities. These tests, flown by Ames pilot G. Warren Hall and Army Maj (soon promoted to Lt. Col.) Patrick Morris, began in May and continued until October 1984, when the RSRA vehicle returned to Ames. The project manager at Dryden for the flights was Wen Painter. These early tests were preparatory for a future X-Wing rotor flight test project to be sponsored by NASA, the Defense Advanced Research Projects Agency (DARPA), and Sikorsky Aircraft. A later derivative X-Wing flew in 1987. The modified RSRA was developed to provide a vehicle for in-flight investigation and verification of new helicopter rotor-system concepts and supporting technology. The RSRA could be configured to fly as an airplane with fixed wings, as a helicopter, or as a compound vehicle that could transition between the two configurations. NASA and DARPA selected Sikorsky in 1984 to convert one of the original RSRAs to the new demonstrator aircraft for the X-Wing concept. Developers of X-Wing technology did not view the X-Wing as a replacement for either helicopters (rotor aircraft) or fixed-wing aircraft. Instead, they envisioned it as an aircraft with special enhanced capabilities to perform missions that call for the low-speed efficiency and maneuverability of helicopters combined with the high cruise speed of fixed-wing aircraft. Some such missions include air-to-air and air-to-ground tactical operations, airborne early warning, electronic intelligence, antisubmarine warfare, and search and rescue. The follow-on X-Wing project was managed by James W. Lane, chief of the RSRA/X-Wing Project Office, Ames Research Center. Coordinating the Ames-Dryden flight effort in 1987 was Jack Kolf. The X-Wing project was a joint effort of NASA-Ames, DARPA, the U.S. Army, and Sikorsky Aircraft, Stratford, Connecticut. The modified X-Wing aircraft was delivered to Ames-Dryden by Sikorsky Aircraft on September 25, 1986. Following taxi tests, initial flights in the aircraft mode without main rotors attached took place at Dryden in December 1997. Ames research pilot G. Warren Hall and Sikorsky's W. Richard Faull were the pilots. The contract with Sikorsky ended that month, and the program ended in January 1988.

X-Wing Research Vehicle

NASA Technical Reports Server (NTRS)

1986-01-01

One of the most unusual experimental flight vehicles appearing at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center) in the 1980s was the Rotor Systems Research Aircraft (RSRA) X-Wing aircraft, seen here on the ramp. The craft was developed originally and then modified by Sikorsky Aircraft for a joint NASA-Defense Advanced Research Projects Agency (DARPA) program and was rolled out 19 August 1986. Taxi tests and initial low-altitude flight tests without the main rotor attached were carried out at Dryden before the program was terminated in 1988. The unusual aircraft that resulted from the Ames Research Center/Army X-Wing Project was flown at the Ames-Dryden Flight Research Facility (now Dryden Flight Research Center), Edwards, California, beginning in the spring of 1984, with a follow-on program beginning in 1986. The program, was conceived to provide an efficient combination of the vertical lift characteristic of conventional helicopters and the high cruise speed of fixed-wing aircraft. It consisted of a hybrid vehicle called the NASA/Army Rotor Systems Research Aircraft (RSRA), which was equipped with advanced X-wing rotor systems. The program began in the early 1970s to investigate ways to increase the speed of rotor aircraft, as well as their performance, reliability, and safety . It also sought to reduce the noise, vibration, and maintenance costs of helicopters. Sikorsky Aircraft Division of United Technologies Laboratories built two RSRA aircraft. NASA's Langley Research Center, Hampton, Virginia, did some initial testing and transferred the program to Ames Research Center, Mountain View, California, for an extensive flight research program conducted by Ames and the Army. The purpose of the 1984 tests was to demonstrate the fixed-wing capability of the helicopter/airplane hybrid research vehicle and explore its flight envelope and flying qualities. These tests, flown by Ames pilot G. Warren Hall and Army Maj (soon promoted to Lt. Col.) Patrick Morris, began in May and continued until October 1984, when the RSRA vehicle returned to Ames. The project manager at Dryden for the flights was Wen Painter. These early tests were preparatory for a future X-Wing rotor flight test project to be sponsored by NASA, the Defense Advanced Research Projects Agency (DARPA), and Sikorsky Aircraft. A later derivative X-Wing flew in 1987. The modified RSRA was developed to provide a vehicle for in-flight investigation and verification of new helicopter rotor-system concepts and supporting technology. The RSRA could be configured to fly as an airplane with fixed wings, as a helicopter, or as a compound vehicle that could transition between the two configurations. NASA and DARPA selected Sikorsky in 1984 to convert one of the original RSRAs to the new demonstrator aircraft for the X-Wing concept. Developers of X-Wing technology did not view the X-Wing as a replacement for either helicopters (rotor aircraft) or fixed-wing aircraft. Instead, they envisioned it as an aircraft with special enhanced capabilities to perform missions that call for the low-speed efficiency and maneuverability of helicopters combined with the high cruise speed of fixed-wing aircraft. Some such missions include air-to-air and air-to-ground tactical operations, airborne early warning, electronic intelligence, antisubmarine warfare, and search and rescue. The follow-on X-Wing project was managed by James W. Lane, chief of the RSRA/X-Wing Project Office, Ames Research Center. Coordinating the Ames-Dryden flight effort in 1987 was Jack Kolf. The X-Wing project was a joint effort of NASA-Ames, DARPA, the U.S. Army, and Sikorsky Aircraft, Stratford, Connecticut. The modified X-Wing aircraft was delivered to Ames-Dryden by Sikorsky Aircraft on 25 September 1986. Following taxi tests, initial flights in the aircraft mode without main rotors attached took place at Dryden in December 1997. Ames research pilot G. Warren Hall and Sikorsky's W. Richard Faull were the pilots. The contract with Sikorsky ended that month, and the program ended in January 1988.

MicroMAPS CO Measurements over North America and Europe during Summer-Fall 2004

NASA Astrophysics Data System (ADS)

Connors, V. S.; Hopkins, P. E.; Reichle, H. G.; Morrow, W. H.; McMillan, W. W.; Sandy, M.

2006-12-01

The MicroMAPS instrument is a nadir-viewing, gas filter-correlated radiometer which operating in the 4.67 micrometer fundamental band of carbon monoxide. Originally designed and built for a space mission, this CO remote sensor is being flown in support of satellite validation and science instrument demonstrations for potential UAV applications. The MicroMAPS instrument system, as flown on Proteus, was designed by a senior student design project in the Aerospace Engineering Department, Virginia Tech, in Blacksburg, VA. and then revised by Systems Engineers at NASA Langley. The final instrument system was integrated and tested at NASA LaRC, in partnership with Scaled Composites and Virginia Space Grant Consortium (VSGC). VSGC supervised the fabrication of the nacelle that houses the instrument system on the right rear tail boom of Proteus. Full system integration and flight testing was performed at Scaled Composites, in Mojave, in June 2004. Its successful performance enabled participation in four international science missions on Proteus: in 2004, INTEX -NA over eastern North America in July, ADRIEX over the Mediterranean region and EAQUATE over the United Kingdom region in September,and TWP-ICE over Darwin, Australia and the surrounding oceans in Jan-Feb 2006. These flights resulted in nearly 300 hours of data. In parallel with the engineering developments, theoretical radiative transfer models were developed specifically for the MicroMAPS instrument system at the University of Virginia, Mechanical Engineering Department by a combined undergraduate and graduate student team. With technical support from Resonance Ltd. in June 2005, the MicroMAPS instrument was calibrated for the conditions under which the Summer-Fall 2004 flights occurred. The analyses of the calibration data, combined with the theoretical radiative transfer models, provide the first data reduction for the science flights reported here. These early results and comparisons with profile data from the NASA DC-8, the coincident AIRS CO retrievals, and selected CO measurements from the MOZAIC program will be presented.

MicroMAPS CO Measurements over North America and Europe during Summer-Fall 2004

NASA Technical Reports Server (NTRS)

Connors, Vickie S.; Hopkins, Patrick E.; Reichle, Henry G., Jr.; Morrow, William H.; McMillan, Wallace; Sandy, Mary L.

2006-01-01

The MicroMAPS instrument is a nadir-viewing, gas filter-correlated radiometer which operating in the 4.67 micrometer fundamental band of carbon monoxide. Originally designed and built for a space mission, this CO remote sensor is being flown in support of satellite validation and science instrument demonstrations for potential UAV applications. The MicroMAPS instrument system, as flown on Proteus, was designed by a senior student design project in the Aerospace Engineering Department, Virginia Tech, in Blacksburg, VA. and then revised by Systems Engineers at NASA Langley. The final instrument system was integrated and tested at NASA LaRC, in partnership with Scaled Composites and Virginia Space Grant Consortium (VSGC). VSGC supervised the fabrication of the nacelle that houses the instrument system on the right rear tail boom of Proteus. Full system integration and flight testing was performed at Scaled Composites, in Mojave, in June 2004. Its successful performance enabled participation in four international science missions on Proteus: in 2004, INTEX -NA over eastern North America in July, ADRIEX over the Mediterranean region and EAQUATE over the United Kingdom region in September,and TWP-ICE over Darwin, Australia and the surrounding oceans in Jan-Feb 2006. These flights resulted in nearly 300 hours of data. In parallel with the engineering developments, theoretical radiative transfer models were developed specifically for the MicroMAPS instrument system at the University of Virginia, Mechanical Engineering Department by a combined undergraduate and graduate student team. With technical support from Resonance Ltd. in June 2005, the MicroMAPS instrument was calibrated for the conditions under which the Summer-Fall 2004 flights occurred. The analyses of the calibration data, combined with the theoretical radiative transfer models, provide the first data reduction for the science flights reported here. These early results and comparisons with profile data from the NASA DC-8, the coincident AIRS CO retrievals, and selected CO measurements from the MOZAIC program will be presented.

An Evaluation of an Analytical Simulation of an Airplane with Tailplane Icing by Comparison to Flight Data

NASA Technical Reports Server (NTRS)

Hiltner, Dale W.

2000-01-01

This report presents the assessment of an analytical tool developed as part of the NASA/FAA Tailplane Icing Program. The analytical tool is a specialized simulation program called TAILSM4 which was developed to model the effects of tailplane icing on the flight dynamics Twin Otter Icing Research Aircraft. This report compares the responses of the TAILSIM program directly to flight test data. The comparisons should be useful to potential users of TAILSIM. The comparisons show that the TAILSIM program qualitatively duplicates the flight test aircraft response during maneuvers with ice on the tailplane. TAILSIM is shown to be quantitatively "in the ballpark" in predicting when Ice Contaminated Tailplane Stall will occur during pushover and thrust transition maneuvers. As such, TAILSIM proved its usefulness to the flight test program by providing a general indication of the aircraft configuration and flight conditions of concern. The aircraft dynamics are shown to be modeled correctly by the equations of motion used in TAILSIM. However, the general accuracy of the TAILSIM responses is shown to be less than desired primarily due to inaccuracies in the aircraft database. The high sensitivity of the TAILSIM program responses to small changes in load factor command input is also shown to be a factor in the accuracy of the responses. A pilot model is shown to allow TAILSIM to produce more accurate responses and contribute significantly to the usefulness of the program. Suggestions to improve the accuracy of the TAILSIM responses are to further refine the database representation of the aircraft aerodynamics and tailplane flowfield and to explore a more realistic definition of the pilot model.

The NASA research program on propulsion for supersonic cruise aircraft

NASA Technical Reports Server (NTRS)

Weber, R. J.

1975-01-01

The objectives and status of the propulsion portion of a program aimed at advancing the technology and establishing a data base appropriate for the possible future development of supersonic cruise aircraft are reviewed. Research related to exhaust nozzles, combustors, and inlets that is covered by the noise, pollution, and dynamics programs is described.

Acoustic measurements of F-16 aircraft operating in hush house, NSN 4920-02-070-2721

NASA Astrophysics Data System (ADS)

Miller, V. R.; Plzak, G. A.; Chinn, J. M.

1981-09-01

The purpose of this test program was to measure the acoustic environment in the hush house facility located at Kelly Air Force Base, Texas, during operation of the F-16 aircraft to ensure that aircraft structural acoustic design limits were not exceeded. The acoustic measurements showed that no sonic fatigue problems are anticipated with the F-16 aircraft aft fuselage structure during operation in the hush house. The measured acoustic levels were less than those measured in an F-16 aircraft water cooled hush house at Hill AFB, but were increased over that measured during ground run up. It was recommended that the acoustic loads measured in this program should be specified in the structural design criteria for aircraft which will be subjected to hush house operation or defining requirements for associated equipment.

Assessing the Impact of Aircraft Emissions on the Stratosphere

NASA Technical Reports Server (NTRS)

Kawa, S. R.; Anderson, D. E.

1999-01-01

For the past decade, the NASA Atmospheric Effects of Aviation Project (AEAP) has been the U.S. focal point for research on aircraft effects. In conjunction with U.S. basic research programs, AEAP and concurrent European research programs have driven remarkable progress reports released in 1999 [IPCC, 1999; Kawa et al., 1999]. The former report primarily focuses on aircraft effects in the upper troposphere, with some discussion on stratospheric impacts. The latter report focuses entirely on the stratosphere. The current status of research regarding aviation effects on stratospheric ozone and climate, as embodied by the findings of these reports, is reviewed. The following topics are addressed: Aircraft Emissions, Pollution Transport, Atmospheric Chemistry, Polar Processes, Climate Impacts of Supersonic Aircraft, Subsonic Aircraft Effect on the Stratosphere, Calculations of the Supersonic Impact on Ozone and Sensitivity to Input Conditions.

Evaluation of a Hydrogen Fuel Cell Powered Blended-Wing-Body Aircraft Concept for Reduced Noise and Emissions

NASA Technical Reports Server (NTRS)

Guynn, Mark D.; Freh, Joshua E.; Olson, Erik D.

2004-01-01

This report describes the analytical modeling and evaluation of an unconventional commercial transport aircraft concept designed to address aircraft noise and emission issues. A blended-wing-body configuration with advanced technology hydrogen fuel cell electric propulsion is considered. Predicted noise and emission characteristics are compared to a current technology conventional configuration designed for the same mission. The significant technology issues which have to be addressed to make this concept a viable alternative to current aircraft designs are discussed. This concept is one of the "Quiet Green Transport" aircraft concepts studied as part of NASA's Revolutionary Aerospace Systems Concepts (RASC) Program. The RASC Program was initiated to develop revolutionary concepts that address strategic objectives of the NASA Enterprises, such as reducing aircraft noise and emissions, and to identify advanced technology requirements for the concepts.

Aircraft Survivability: UAVs and Manned Aircraft - Increasing Effectiveness and Survivability, Fall 2002

DTIC Science & Technology

2002-01-01

techniques that interface with the composite structure to attach opaque armor(s) to compos- ite aircraft structure. Over a period of four years...2002 2. REPORT TYPE 3. DATES COVERED 00-00-2002 to 00-00-2002 4. TITLE AND SUBTITLE Aircraft Survivability: UAVs and Manned Aircraft ...survivability concepts to UAV program offices and airframe manufacturers. 11 Aircraft Fire Protection Techniques—Application to UAVs by Ms. Ginger Bennett

Development of a computer technique for the prediction of transport aircraft flight profile sonic boom signatures. M.S. Thesis

NASA Technical Reports Server (NTRS)

Coen, Peter G.

1991-01-01

A new computer technique for the analysis of transport aircraft sonic boom signature characteristics was developed. This new technique, based on linear theory methods, combines the previously separate equivalent area and F function development with a signature propagation method using a single geometry description. The new technique was implemented in a stand-alone computer program and was incorporated into an aircraft performance analysis program. Through these implementations, both configuration designers and performance analysts are given new capabilities to rapidly analyze an aircraft's sonic boom characteristics throughout the flight envelope.

Research related to variable sweep aircraft development

NASA Technical Reports Server (NTRS)

Polhamus, E. C.; Toll, T. A.

1981-01-01

Development in high speed, variable sweep aircraft research is reviewed. The 1946 Langley wind tunnel studies related to variable oblique and variable sweep wings and results from the X-5 and the XF1OF variable sweep aircraft are discussed. A joint program with the British, evaluation of the British "Swallow", development of the outboard pivot wing/aft tail configuration concept by Langley, and the applied research program that followed and which provided the technology for the current, variable sweep military aircraft is outlined. The relative state of variable sweep as a design option is also covered.

Lightweight, low compression aircraft diesel engine. [converting a spark ignition engine to the diesel cycle

NASA Technical Reports Server (NTRS)

Gaynor, T. L.; Bottrell, M. S.; Eagle, C. D.; Bachle, C. F.

1977-01-01

The feasibility of converting a spark ignition aircraft engine to the diesel cycle was investigated. Procedures necessary for converting a single cylinder GTS10-520 are described as well as a single cylinder diesel engine test program. The modification of the engine for the hot port cooling concept is discussed. A digital computer graphics simulation of a twin engine aircraft incorporating the diesel engine and Hot Fort concept is presented showing some potential gains in aircraft performance. Sample results of the computer program used in the simulation are included.

A computer technique for detailed analysis of mission radius and maneuverability characteristics of fighter aircraft

NASA Technical Reports Server (NTRS)

Foss, W. E., Jr.

1981-01-01

A computer technique to determine the mission radius and maneuverability characteristics of combat aircraft was developed. The technique was used to determine critical operational requirements and the areas in which research programs would be expected to yield the most beneficial results. In turn, the results of research efforts were evaluated in terms of aircraft performance on selected mission segments and for complete mission profiles. Extensive use of the technique in evaluation studies indicates that the calculated performance is essentially the same as that obtained by the proprietary programs in use throughout the aircraft industry.

Price Determination of General Aviation, Helicopter, and Transport Aircraft

NASA Technical Reports Server (NTRS)

Anderson, Joseph L.

1978-01-01

The NASA must assess its aeronautical research program with economic as well as performance measures. It thus is interested in what price a new technology aircraft would carry to make it attractive to the buyer. But what price a given airplane or helicopter will carry is largely a reflection of the manufacturer's assessment of the competitive market into which the new aircraft will be introduced. The manufacturer must weigh any new aerodynamic or system technology innovation he would add to an aircraft by the impact of this innovation upon the aircraft's economic attractiveness and price. The intent of this paper is to give price standards against which new technologies and the NASA's research program can be assessed. Using reported prices for general aviation, helicopter, and transport aircraft, price estimating relations in terms of engine and airframe characteristics have been developed. The relations are given in terms of the aircraft type, its manufactured empty weight, engine weight, horsepower or thrust. Factors for the effects of inflation are included to aid in making predictions of future aircraft prices. There are discussions of aircraft price in terms of number of passenger seats, airplane size and research and development costs related to an aircraft model, and indirectly as to how new technologies, aircraft complexity and inflation have affected these.

Price-Weight Relationships of General Aviation, Helicopters, Transport Aircraft and Engines

NASA Technical Reports Server (NTRS)

Anderson, Joseph L.

1981-01-01

The NASA must assess its aeronautical research program with economic as well as performance measures. It thus is interested in what price a new technology aircraft would carry to make it attractive to the buyer. But what price a given airplane or helicopter will carry is largely a reflection of the manufacturer's assessment of the competitive market into which the new aircraft will be introduced. The manufacturer must weigh any new aerodynamic or system technology innovation he would add to an aircraft by the impact of this innovation upon the aircraft's cost to manufacture, economic attractiveness and price. The intent of this paper is to give price standards against which new technologies and the NASA's research program can be assessed. Using reported prices for sailplanes, general aviation, agriculture, helicopter, business and transport aircraft, price estimating relations in terms of engine and airframe characteristics have been developed. The relations are given in terms of the aircraft type, its manufactured empty weight, engine weight, horsepower or thrust. Factors for the effects of inflation are included to aid in making predictions of future aircraft prices. There are discussions of aircraft price in terms of number of passenger seats, airplane size and research and development costs related to an aircraft model, and indirectly how new technologies, aircraft complexity and inflation have affected these.

Advanced composites wing study program, volume 2

NASA Technical Reports Server (NTRS)

Harvey, S. T.; Michaelson, G. L.

1978-01-01

The study on utilization of advanced composites in commercial aircraft wing structures was conducted as a part of the NASA Aircraft Energy Efficiency Program to establish, by the mid-1980s, the technology for the design of a subsonic commercial transport aircraft leading to a 40% fuel savings. The study objective was to develop a plan to define the effort needed to support a production commitment for the extensive use of composite materials in wings of new generation aircraft that will enter service in the 1985-1990 time period. Identification and analysis of what was needed to meet the above plan requirements resulted in a program plan consisting of three key development areas: (1) technology development; (2) production capability development; and (3) integration and validation by designing, building, and testing major development hardware.

Dryden Test Pilots 1990 - Smolka, Fullerton, Schneider, Dana, Ishmael, Smith, and McMurtry

NASA Technical Reports Server (NTRS)

1990-01-01

It was a windy afternoon on Rogers Dry Lake as the research pilots of the National Aeronautics and Space Administration's Ames-Dryden Flight Research Facility gathered for a photo shoot. It was a special day too, the 30th anniversary of the first F-104 flight by research pilot Bill Dana. To celebrate, a fly over of Building 4800, in formation, was made with Bill in a Lockheed F-104 (826), Gordon Fullerton in a Northrop T-38, and Jim Smolka in a McDonnell Douglas F/A-18 (841) on March 23, 1990. The F-18 (841), standing on the NASA ramp is a backdrop for the photo of (Left to Right) James W. (Smoke) Smolka, C. Gordon Fullerton, Edward T. (Ed) Schneider, William H. (Bill) Dana, Stephen D. (Steve) Ishmael, Rogers E. Smith, and Thomas C. (Tom) McMurtry. Smolka joined NASA Ames-Dryden Flight Research Facility in September 1985. He has been the project pilot on the F-15 Advanced Control Technology for Integrated Vehicles (ACTIVE) research and F-15 Aeronautical Research Aircraft programs. He has also flown as a pilot on the NASA B-52 launch aircraft, as a co-project pilot on the F-16XL Supersonic Laminar Flow Control aircraft and the F-18 High Angle-of-Attack Research Vehicle (HARV) aircraft. Other aircraft he has flown in research programs are the F-16, F-111, F-104 and the T-38 as support. Fullerton, joined NASA's Ames-Dryden Flight Research Facility in November 1986. He was project pilot on the NASA/Convair 990 aircraft to test space shuttle landing gear components, project pilot on the F-18 Systems Research Aircraft, and project pilot on the B-52 launch aircraft, where he was involved in six air launches of the commercially developed Pegasus space launch vehicle. Other assignments include a variety of flight research and support activities in multi-engine and high performance aircraft such as, F-15, F-111, F-14, X-29, MD-11 and DC-8. Schneider arrived at the NASA Ames-Dryden Flight Research Facility on July 5, 1982, as a Navy Liaison Officer, becoming a NASA research pilot one year later. He has been project pilot for the F-18 High Angle-of-Attack program (HARV), project pilot for the F-15 aeronautical research aircraft, the NASA B-52 launch aircraft, and the SR-71 'Blackbird' aircraft. His past research work at Dryden has included participation in the F-8 Digital Fly-By-Wire, the FAA/NASA 720 Controlled Impact Demonstration, the F-14 Automatic Rudder Interconnect and Laminar Flow programs, and the F-104 Aeronautical Research and Microgravity programs. Dana joined the NASA's High-Speed Flight Station on October 1, 1958. As a research pilot, he was involved in some of the most significant aeronautical programs carried out at the Center. In the late 1960s and in the 1970s Dana was a project pilot on the lifting body program, flying the wingless M2-F1, HL-10, M2-F3, and the X-24B vehicles. He was a project pilot on the hypersonic X-15 research aircraft and flew the rocket-powered vehicle 16 times, reaching a speed of 3,897 mph and an altitude of 310,000 feet. Bill was the pilot on the final (199th) flight of the 10-year program. Other research and support programs Dana participated in were the F-15 Highly Integrated Digital Electronic Control (HIDEC), the F-18 High Angle-of-Attack Research Vehicle (HARV), YF-12, F-104, F-16, PA-30, and T-38. In 1993 Dana became Chief Engineer at NASA's Ames-Dryden Flight Research Facility (soon to be renamed the Dryden Flight Research Center). Ishmael was a research pilot at NASA's Dryden Flight Research Center from January 1977 until the spring of 1995, when he became manager of Dryden's Reusable Launch Vehicle (RLV) programs. In 1996 he became NASA's X-33 Deputy Manager for Flight Test and Operation. As a research pilot he served as the chief project pilot on two major aeronautical research programs, the SR-71 High Speed Research program and the F-16XL Laminar Flow Technology program. He took part in the X-29 Forward-Swept-Wing program, and gave support to other pilots' research flights in a T-38 and F-104 aircraft. Smith became a research pilot at NASA's Ames-Dryden Flight Research Facility in August 1982. In the spring of 1995 he became Chief of the Flight Crew Branch where currently there are 8 other NASA pilots and 2 flight engineers. Smith has also been a co-project pilot on two major aeronautical programs at Dryden. They are the integrated thrust vectoring F-15 ACTIVE and the SR-71 'Blackbird' Research programs. Other research programs that he has been associated with are the F-104 Zero 'G' tests, F-18 HARV, X-29 Forward-Swept-Wing, with support flights being flown in a T-38 and F-104. McMurtry has been a pilot at NASA's Dryden since joining the Flight Research Center in November 1967. In 1981, Tom became Chief Pilot a position he held until February 1986, when he was appointed Chief of the Research Aircraft Operations Division. McMurtry has been project pilot for the AD-1 Oblique Wing program, the F-15 Digital Electronic Engine Control (DEEC) project and the F-8 Supercritical Wing program. He was co- project pilot on the F-15 ACTIVE program, F-8 Digital Fly-By-Wire program and on several remotely piloted research vehicle programs such as the FAA/NASA 720 Controlled Impact Demonstration and the sub-scale F-15 spin research project. He has also been a co-project pilot on the NASA 747 Shuttle Carrier Aircraft.

Probing Emissions of Military Cargo Aircraft: Description of a Joint Field Measurement Program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cheng, Mengdawn; Corporan, E.; DeWitt, M.

2008-01-01

Direct emissions of NOx, volatile organic compounds, and particulate matter (PM) by aircraft contribute to the pollutant levels found in the atmosphere. Aircraft emissions can be injected at the ground level or directly at the high altitude in flight. Conversion of the precursor gases into secondary PM is one of the pathways for the increased atmospheric PM. Atmospheric PM interacts with solar radiation altering atmospheric radiation balance and potentially contributing to global and regional climate changes. Also, direct emissions of air toxics, ozone precursors and PM from aircraft in and around civilian airports and military air bases can worsen localmore » air quality in non-attainment and/or maintenance areas. These emissions need to be quantified. However, the current EPA methods for particle emission measurements from such sources, modified Method 5 and Conditional Test Method 039, are gravimetric-based, and it is anticipated that these methods will not be suitable for current and future generations of aircraft turbine engines, whose particle mass emissions are low. To evaluate measurement approaches for military aircraft emissions, two complementary projects were initiated in 2005. A joint field campaign between these two programs was executed during the first week of October 2005 at the Kentucky Air National Guard (KYANG) base in Louisville, KY. This campaign represented the first in a series of field studies for each program funded by the DoD Strategic Environmental Research and Development Program (SERDP) and provided the basis for cross-comparison of the sampling approaches and measurement techniques employed by the respective program teams. This paper describes the overall programmatic of the multi-year SERDP aircraft emissions research and presents a summary of the results from the joint field campaign.« less

Power management and distribution system for a More-Electric Aircraft (MADMEL) -- Program status

DOE Office of Scientific and Technical Information (OSTI.GOV)

Maldonado, M.A.; Shah, N.M.; Cleek, K.J.

1995-12-31

A number of technology breakthroughs in recent years have rekindled the concept of a more-electric aircraft. High-power solid-state switching devices, electrohydrostatic actuators (EHAs), electromechanical actuators (EMAs), and high-power generators are just a few examples of component developments that have made dramatic improvements in properties such as weight, size, power, and cost. However, these components cannot be applied piecemeal. A complete, and somewhat revolutionary, system design approach is needed to exploit the benefits that a more-electric aircraft can provide. A five-phase Power Management and Distribution System for a More-Electric Aircraft (MADMEL) program was awarded by the Air Force to the Northrop/Grumman,more » Military Aircraft Division team in September 1991. The objective of the program is to design, develop, and demonstrate an advanced electrical power generation and distribution system for a more-electric aircraft (MEA). The MEA emphasizes the use of electrical power in place of hydraulics, pneumatic, and mechanical power to optimize the performance and life cycle cost of the aircraft. This paper presents an overview of the MADMEL program and a top-level summary of the program results, development and testing of major components to date. In Phase 1 and Phase 2 studies, the electrical load requirements were established and the electrical power system architecture was defined for both near-term (NT-year 1996) and far-term (FT-year 2003) MEA application. The detailed design and specification for the electrical power system (EPS), its interface with the Vehicle Management System, and the test set-up were developed under the recently completed Phase 3. The subsystem level hardware fabrication and testing will be performed under the on-going Phase 4 activities. The overall system level integration and testing will be performed in Phase 5.« less

An airborne remote sensing platform of the Helsinki University of Technology

DOE Office of Scientific and Technical Information (OSTI.GOV)

Nikulainen, M.; Hallikainen, M.; Kemppinen, M.

1996-10-01

In 1994 Helsinki University of Technology acquired a Short SC7 Skyvan turboprop aircraft to be modified to carry remote sensing instruments. As the aircraft is originally designed to carry heavy and space consuming cargo, a modification program was implemented to make the aircraft feasible for remote sensing operations. The twelve-month long modification program had three design objectives: flexibility, accessibility and cost efficiency. The aircraft interior and electrical system were modified. Furthermore, the aircraft is equipped with DGPS-navigation system, multi-channel radiometer system and side looking airborne radar. Future projects include installation of local area network, attitude GPS system, imaging spectrometer andmore » 1.4 GHz radiometer. 6 refs., 5 figs., 1 tab.« less

State estimation applications in aircraft flight-data analysis: A user's manual for SMACK

NASA Technical Reports Server (NTRS)

Bach, Ralph E., Jr.

1991-01-01

The evolution in the use of state estimation is traced for the analysis of aircraft flight data. A unifying mathematical framework for state estimation is reviewed, and several examples are presented that illustrate a general approach for checking instrument accuracy and data consistency, and for estimating variables that are difficult to measure. Recent applications associated with research aircraft flight tests and airline turbulence upsets are described. A computer program for aircraft state estimation is discussed in some detail. This document is intended to serve as a user's manual for the program called SMACK (SMoothing for AirCraft Kinematics). The diversity of the applications described emphasizes the potential advantages in using SMACK for flight-data analysis.

An exploration of the accuracy of an invasive method for measuring the volume of specimens of Amoeba proteus.

PubMed

Whalen, T A; Demarco, A J

1999-10-01

A method is described for measuring the volume of individual specimens of Amoeba proteus which utilizes an easily constructed compressor to flatten the specimen to a known thickness. The microscopic image of the flattened specimen is captured on tape, digitized and analysed with the NIH Image software. The results from one specimen are given to illustrate the sources and magnitude of errors affecting these volume measurements.

Proteus Syndrome With a Cranial Intraosseous Lipoma.

PubMed

Wolfswinkel, Erik M; Imahiyerobo, Thomas A; McComb, J Gordon; Sanchez-Lara, Pedro A; Urata, Mark M

2017-11-01

Intraosseous lipomas are almost exclusively seen in the long bones. Presence in the craniofacial skeleton is extremely rare. A 7-year-old male is presented with a marked craniofacial deformation from a bony tumor containing an intraosseous lipoma. This finding established a clinical diagnosis of Proteus syndrome. Given the size of the tumor, producing an extensive deformity, three-dimensional modeling was used to generate a three-dimensional printed implant. The process to achieve a successful outcome is herein described.

[CHROMATIN ORGANIZATION IN CELL CYCLE OF AMOEBA PROTEUS ACCORDING TO OPTICAL TOMOGRAPHY DATA].

PubMed

Demin, S Yu; Berdieva, M A; Podlipaeva, Yu I; Yudin, A L; Goodkov, A V

2015-01-01

For the first time the nuclear cycle of large freshwater amoeba Amoeba proteus was studied by the method of optical tomography. The nuclei were fixed in situ in the cells of synchronized culture, stained by DAPI and examined by confocal laser scanning microscope. 3D-images of intranuclear chromatin were studied in details at different stages of nuclear cycle. The obtained data, together with literary ones allow represent the dynamics of structural organization of the nucleus in Amoeba proteus cell cycle in a new fashion. It was concluded that in this species the two-stage interphase takes place, as well as mitosis of peculiar type which does not correspond to any known type of mitosis according to classification existing now. It is presumed that in the course of nuclear cycle the chromosomes and/or their fragments are amplified, this presumption being in a good correspondence with the data about nuclear DNA hyperreplication in the cell cycle of A. proteus. As a result of chromosomes amplification their number may vary at different stages of cell cycle, and it allows to explain the contradictory data concerning the exact number of chromosomes in this species. The elimination of extra-DNA occurs mainly at the stage between prophase and prometaphase. We presume the majority of chromosomes, or may be even all of them to be referred to cholocentric type according to their behaviour during the mitosis.

Aircraft noise prediction program theoretical manual, part 1

NASA Technical Reports Server (NTRS)

Zorumski, W. E.

1982-01-01

Aircraft noise prediction theoretical methods are given. The prediction of data which affect noise generation and propagation is addressed. These data include the aircraft flight dynamics, the source noise parameters, and the propagation effects.

Coatings for aircraft gas turbine engines and space shuttle heat shields: A review of Lewis Research Center programs

NASA Technical Reports Server (NTRS)

Grisaffe, S. J.; Merutka, J. P.

1972-01-01

The status of several coating programs is reviewed. These include efforts on protecting aircraft gas turbine engine materials from oxidation/corrosion and on protecting refractory metal reentry heat shields from oxidation.

ACEE Composite Structures Technology: Review of selected NASA research on composite materials and structures

NASA Technical Reports Server (NTRS)

1984-01-01

The NASA Aircraft Energy Efficiency (ACEE) Composite Primary Aircraft Structures Program was designed to develop technology for advanced composites in commercial aircraft. Research on composite materials, aircraft structures, and aircraft design is presented herein. The following parameters of composite materials were addressed: residual strength, damage tolerance, toughness, tensile strength, impact resistance, buckling, and noise transmission within composite materials structures.

Development of pressure containment and damage tolerance technology for composite fuselage structures in large transport aircraft

NASA Technical Reports Server (NTRS)

Smith, P. J.; Thomson, L. W.; Wilson, R. D.

1986-01-01

NASA sponsored composites research and development programs were set in place to develop the critical engineering technologies in large transport aircraft structures. This NASA-Boeing program focused on the critical issues of damage tolerance and pressure containment generic to the fuselage structure of large pressurized aircraft. Skin-stringer and honeycomb sandwich composite fuselage shell designs were evaluated to resolve these issues. Analyses were developed to model the structural response of the fuselage shell designs, and a development test program evaluated the selected design configurations to appropriate load conditions.

Status of NASA aircraft engine emission reduction and upper atmosphere measurement programs

NASA Technical Reports Server (NTRS)

Rudey, R. A.; Lezberg, E. A.

1976-01-01

Advanced emission reduction techniques for five existing aircraft gas turbine engines are evaluated. Progress made toward meeting the 1979 EPA standards in rig tests of combustors for the five engines is reported. Results of fundamental combustion studies suggest the possibility of a new generation of jet engine combustor technology that would reduce oxides-of-nitrogen (NOx) emissions far below levels currently demonstrated in the engine-related programs. The Global Air Sampling Program (GAS) is now in full operation and is providing data on constituent measurements of ozone and other minor upper-atmosphere species related to aircraft emissions.

Selected topics from the structural acoustics program for the B-1 aircraft

NASA Technical Reports Server (NTRS)

Belcher, P. M.

1979-01-01

The major elements of the structural acoustics program for the B-1 aircraft are considered. Acoustic pressures measured at 280 sites on the surface of the vehicle were used to develop pressure models for a resizing of airframe components for aircraft No. 4 (A/C4). Acoustical fatigue design data for two dynamically complex structural configurations were acquired in laboratory programs, the conceptions for and executions of which detailed significant departures from the conventional. Design requirements for mechanical fasteners for configurations other than these two made use of analytical extensions of regrettably limited available information.

Lean, premixed, prevaporized combustion for aircraft gas turbine engines

NASA Technical Reports Server (NTRS)

Mularz, E. J.

1979-01-01

The application of lean, premixed, prevaporized combustion to aircraft turbine engine systems can result in benefits in terms of superior combustion performance, improved combustor and turbine durability, and environmentally acceptable pollutant emissions. Lean, premixed prevaporized combustion is particularly attractive for reducing the oxides of nitrogen emissions during high altitude cruise. The NASA stratospheric cruise emission reduction program will evolve and demonstrate lean, premixed, prevaporized combustion technology for aircraft engines. This multiphased program is described. In addition, the various elements of the fundamental studies phase of the program are reviewed, and results to date of many of these studies are summarized.

Variations of GHGs from the lower-troposphere to the UT/LS revealed by two Japanese regular aircraft observation programs

NASA Astrophysics Data System (ADS)

Niwa, Yosuke; Machida, Toshinobu; Sawa, Yousuke; Tsuboi, Kazuhiro; Matsueda, Hidekazu; Imasu, Ryoichi

2014-05-01

A Japan-centered observation network consisting of two regular aircraft programs have revealed the greenhouse gases variations from the lower-troposphere to the upper-troposphere/lower-stratosphere (UT/LS) regions. In the Comprehensive Observation Network for Trace gases by Airliner (CONTRAIL) project, in-situ continuous measurement equipment (CME) onboard commercial passenger aircraft world-widely observes CO2 profiles in vertical over tens of airports and in horizontal in the UT/LS regions. The CONTRAIL-CME has revealed three-dimensional structure of the global CO2 distribution and has exposed significant inter-hemispheric transport of CO2 through the upper-troposphere. In inverse modeling, the CME data have provided strong constraints on CO2 flux estimation especially for the Asian tropics. Automatic flask air sampling equipment (ASE) is also onboard the CONTRAIL aircraft and has been observing CO2 mixing ratios as well as those of methane, carbon monoxide, nitrous oxide and other trace species in the upper-troposphere between Japan and Australia. The observation period of the ASE has reached 20 years. In recent years, the ASE program has extended to the northern subarctic UT/LS region and has given an insight of transport mechanisms in the UT/LS by observing seasonal GHGs variations. In the other aircraft observation program by Japan Meteorological Agency, variations of GHGs have been observed by flask-sampling onboard a C-130H aircraft horizontally in the mid-troposphere over the western North Pacific as well as vertically over Minamitorishima-Island. The C-130H aircraft has persistently observed high mixing ratios of CH4 in the mid-troposphere, which seems to be originated from fossil fuel combustion throughout the year as well as from biogenic sources during summer in the Asian regions. Those above aircraft observation programs have a significant role for constraining GHGs flux estimates by filling the data gap of the existing surface measurement network specifically in the regions of Asia and the western North Pacific.

A Linear Programming Approach to the Development of Contrail Reduction Strategies Satisfying Operationally Feasible Constraints

NASA Technical Reports Server (NTRS)

Wei, Peng; Sridhar, Banavar; Chen, Neil Yi-Nan; Sun, Dengfent

2012-01-01

A class of strategies has been proposed to reduce contrail formation in the United States airspace. A 3D grid based on weather data and the cruising altitude level of aircraft is adjusted to avoid the persistent contrail potential area with the consideration to fuel-efficiency. In this paper, the authors introduce a contrail avoidance strategy on 3D grid by considering additional operationally feasible constraints from an air traffic controller's aspect. First, shifting too many aircraft to the same cruising level will make the miles-in-trail at this level smaller than the safety separation threshold. Furthermore, the high density of aircraft at one cruising level may exceed the workload for the traffic controller. Therefore, in our new model we restrict the number of total aircraft at each level. Second, the aircraft count variation for successive intervals cannot be too drastic since the workload to manage climbing/descending aircraft is much larger than managing cruising aircraft. The contrail reduction is formulated as an integer-programming problem and the problem is shown to have the property of total unimodularity. Solving the corresponding relaxed linear programming with the simplex method provides an optimal and integral solution to the problem. Simulation results are provided to illustrate the methodology.

Aircraft noise reduction technology. [to show impact on individuals and communities, component noise sources, and operational procedures to reduce impact

NASA Technical Reports Server (NTRS)

1973-01-01

Aircraft and airport noise reduction technology programs conducted by NASA are presented. The subjects discussed are: (1) effects of aircraft noise on individuals and communities, (2) status of aircraft source noise technology, (3) operational procedures to reduce the impact of aircraft noise, and (4) NASA relations with military services in aircraft noise problems. References to more detailed technical literature on the subjects discussed are included.

A computer program incorporating fatigue and fracture criteria in the preliminary design of transport aircraft: An evaluation

NASA Technical Reports Server (NTRS)

Berger, P. E.; Thornton, E. A.

1976-01-01

The APAS program a multistation structural synthesis procedure developed to evaluate material, geometry, and configuration with various design criteria usually considered for the primary structure of transport aircraft is described and evaluated. Recommendations to improve accuracy and extend the capabilities of the APAS program are given. Flow diagrams are included.

Programs at Wright-patterson Air Force Base

NASA Technical Reports Server (NTRS)

Dayton, Ron

1991-01-01

The Lubrication Branch has two active programs that are developing gas turbine engine mainshaft air/oil seals. Both of these programs, one of which is with General Electric Aircraft Engines and the other with Pratt & Whitney Aircraft, are addressing counter-rotating intershaft applications which involve very high rubbing velocities. The objectives and requirements of these efforts are briefly addressed.

Integration of structural health monitoring solutions onto commercial aircraft via the Federal Aviation Administration structural health monitoring research program

NASA Astrophysics Data System (ADS)

Swindell, Paul; Doyle, Jon; Roach, Dennis

2017-02-01

The Federal Aviation Administration (FAA) started a research program in structural health monitoring (SHM) in 2011. The program's goal was to understand the technical gaps of implementing SHM on commercial aircraft and the potential effects on FAA regulations and guidance. The program evolved into a demonstration program consisting of a team from Sandia National Labs Airworthiness Assurance NDI Center (AANC), the Boeing Corporation, Delta Air Lines, Structural Monitoring Systems (SMS), Anodyne Electronics Manufacturing Corp (AEM) and the FAA. This paper will discuss the program from the selection of the inspection problem, the SHM system (Comparative Vacuum Monitoring-CVM) that was selected as the inspection solution and the testing completed to provide sufficient data to gain the first approved use of an SHM system for routine maintenance on commercial US aircraft.

X-15 on Lakebed after Landing with B-52 Mothership Flyover

NASA Technical Reports Server (NTRS)

1961-01-01

As crew members secure the X-15 rocket-powered aircraft after a research flight, the B-52 mothership used for launching this unique aircraft does a low fly-by overhead. The X-15s made a total of 199 flights over a period of nearly 10 years -- 1959 to 1968 -- and set unofficial world speed and altitude records of 4,520 mph (Mach 6.7) and 354,200. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo piloted spaceflight programs, and also the Space Shuttle program. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet.. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

Recent progress in VSTOL technology

NASA Technical Reports Server (NTRS)

Roberts, L.; Deckert, W. R.

1982-01-01

Progress in vertical and short takeoff and landing (V/STOL) aircraft technology, in particular, during the 1970 to 1980 period at Ames Research Center is discussed. Although only two kinds of V/STOL aircraft (the helicopter and the British direct lift Harrier) have achieved operational maturity, understanding of the technology has vastly improved during this 10 year period. To pursue an aggressive R and D program at a reasonable cost, it was decided to conduct extensive large scale testing in wind tunnel and flight simulation facilities, to develop low cost research aircraft using modified airframes or engines, and to involve other agencies and industry contractors in joint technical and funding arrangements. The STOL investigations include exploring STOL performance using the rotating cylinder flap concept, the augmentor wing, upon initiation of the Quiet Short Haul Research Aircraft program, the upper surface blown flap concept. The VTOL investigations were conducted using a tilt rotor aircraft, resulting in the XV-15 tilt rotor research aircraft. Direct jet lift is now being considered for application to future supersonic fighter aircraft.

40 CFR 141.804 - Aircraft water system operations and maintenance plan.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 40 Protection of Environment 23 2014-07-01 2014-07-01 false Aircraft water system operations and maintenance plan. 141.804 Section 141.804 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) WATER PROGRAMS (CONTINUED) NATIONAL PRIMARY DRINKING WATER REGULATIONS Aircraft Drinking Water Rule § 141.804 Aircraft water system...

Navy Maintenance: The P-3 Aircraft Overhaul Program Can Be Improved.

DTIC Science & Technology

1987-06-01

Air Sys- tems Command’s Naval Aviation Logistics Center, we obtained data on aircraft turnaround times, mobilization requirements, and aircraft over...480 561 637 P-3 Workload as a Percent of 23 22 25 27 Total FINDING Z: Aplicability of Procedural Changes To Other Aircraft. The GAO observed that the

Evaluation of an Aircraft Concept With Over-Wing, Hydrogen-Fueled Engines for Reduced Noise and Emissions

NASA Technical Reports Server (NTRS)

Guynn, Mark D.; Olson, Erik D.

2002-01-01

This report describes the analytical modeling and evaluation of an unconventional commercial transport aircraft concept designed to address aircraft noise and emission issues. A strut-braced wing configuration with overwing, ultra-high bypass ratio, hydrogen fueled turbofan engines is considered. Estimated noise and emission characteristics are compared to a conventional configuration designed for the same mission and significant benefits are identified. The design challenges and technology issues which would have to be addressed to make the concept a viable alternative to current aircraft designs are discussed. This concept is one of the "Quiet Green Transport" aircraft concepts studied as part of NASA's Revolutionary Aerospace Systems Concepts (RASC) Program. The RASC Program seeks to develop revolutionary concepts that address strategic objectives of the NASA Enterprises, such as reducing aircraft noise and emissions, and to identify enabling advanced technology requirements for the concepts.

Aircraft stress sequence development: A complex engineering process made simple

NASA Technical Reports Server (NTRS)

Schrader, K. H.; Butts, D. G.; Sparks, W. A.

1994-01-01

Development of stress sequences for critical aircraft structure requires flight measured usage data, known aircraft loads, and established relationships between aircraft flight loads and structural stresses. Resulting cycle-by-cycle stress sequences can be directly usable for crack growth analysis and coupon spectra tests. Often, an expert in loads and spectra development manipulates the usage data into a typical sequence of representative flight conditions for which loads and stresses are calculated. For a fighter/trainer type aircraft, this effort is repeated many times for each of the fatigue critical locations (FCL) resulting in expenditure of numerous engineering hours. The Aircraft Stress Sequence Computer Program (ACSTRSEQ), developed by Southwest Research Institute under contract to San Antonio Air Logistics Center, presents a unique approach for making complex technical computations in a simple, easy to use method. The program is written in Microsoft Visual Basic for the Microsoft Windows environment.

STOL propulsion systems

NASA Technical Reports Server (NTRS)

Denington, R. J.; Koenig, R. W.; Vanco, M. R.; Sagerser, D. A.

1972-01-01

The selection and the characteristics of quiet, clean propulsion systems for STOL aircraft are discussed. Engines are evaluated for augmentor wing and externally blown flap STOL aircraft with the engines located both under and over the wings. Some supporting test data are presented. Optimum engines are selected based on achieving the performance, economic, acoustic, and pollution goals presently being considered for future STOL aircraft. The data and results presented were obtained from a number of contracted studies and some supporting NASA inhouse programs, most of which began in early 1972. The contracts include: (1) two aircraft and mission studies, (2) two propulsion system studies, (3) the experimental and analytic work on the augmentor wing, and (4) the experimental programs on Q-Fan. Engines are selected and discussed based on aircraft economics using the direct operating cost as the primary criterion. This cost includes the cost of the crew, fuel, aircraft, and engine maintenance and depreciation.

Mathematical model for lift/cruise fan V/STOL aircraft simulator programming data

NASA Technical Reports Server (NTRS)

Bland, M. P.; Fajfar, B.; Konsewicz, R. K.

1976-01-01

Simulation data are reported for the purpose of programming the flight simulator for advanced aircraft for tests of the lift/cruise fan V/STOL Research Technology Aircraft. These simulation tests are to provide insight into problem areas which are encountered in operational use of the aircraft. A mathematical model is defined in sufficient detail to represent all the necessary pertinent aircraft and system characteristics. The model includes the capability to simulate two basic versions of an aircraft propulsion system: (1) the gas coupled configuration which uses insulated air ducts to transmit power between gas generators and fans in the form of high energy engine exhaust and (2) the mechanically coupled power system which uses shafts, clutches, and gearboxes for power transmittal. Both configurations are modeled such that the simulation can include vertical as well as rolling takeoff and landing, hover, powered lift flight, aerodynamic flight, and the transition between powered lift and aerodynamic flight.

A review of advanced turboprop transport aircraft

NASA Astrophysics Data System (ADS)

Lange, Roy H.

The application of advanced technologies shows the potential for significant improvement in the fuel efficiency and operating costs of future transport aircraft envisioned for operation in the 1990s time period. One of the more promising advanced technologies is embodied in an advanced turboprop concept originated by Hamilton Standard and NASA and known as the propfan. The propfan concept features a highly loaded multibladed, variable pitch propeller geared to a high pressure ratio gas turbine engine. The blades have high sweepback and advanced airfoil sections to achieve 80 percent propulsive efficiency at M=0.80 cruise speed. Aircraft system studies have shown improvements in fuel efficiency of 15-20 percent for propfan advanced transport aircraft as compared to equivalent turbofan transports. Beginning with the Lockheed C-130 and Electra turboprop aircraft, this paper presents an overview of the evolution of propfan aircraft design concepts and system studies. These system studies include possible civil and military transport applications and data on the performance, community and far-field noise characteristics and operating costs of propfan aircraft design concepts. NASA Aircraft Energy Efficiency (ACEE) program propfan projects with industry are reviewed with respect to system studies of propfan aircraft and recommended flight development programs.

V/STOL tilt rotor aircraft study. Volume 5: Definition of stowed rotor research aircraft

NASA Technical Reports Server (NTRS)

Soule, V. A.

1973-01-01

The results of a study of folding tilt rotor (stowed rotor) aircraft are presented. The effects of design cruise speed on the gross weight of a conceptual design stowed rotor aircraft are shown and a comparison is made with a conventional (non-folding) tilt rotor aircraft. A flight research stowed rotor design is presented. The program plans, including costs and schedules, are shown for the research aircraft development and a wind tunnel plan is presented for a full scale test of the aircraft.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hess, J.W.

An aircraft battle-damage repair (BDR) program is described that provides for the assessment and repair of battle damage and the return of badly damaged aircraft to their home bases. The program methodology is based on the use of time-saving temporary repairs and associated training and materials provision. BDR is shown to require knowledge of damage mechanisms and specifications for the minimum effective requirements for BDR support, and the method can facilitate the return of 50 percent of damaged aircraft within 24 hours.

ANALYSIS OF AIRCRAFT MOTIONS

NASA Technical Reports Server (NTRS)

Wingrove, R. C.

1994-01-01

This program was developed by Ames Research Center, in cooperation with the National Transportation Safety Board, as a technique for deriving time histories of an aircraft's motion from Air Traffic Control (ATC) radar records. This technique uses the radar range and azimuth data, along with the downlinked altitude data, to derive an expanded set of data which includes airspeed, lift, attitude angles (pitch, roll, and heading), etc. This technique should prove useful as a source of data in the investigation of commercial airline accidents and in the analysis of accidents involving aircraft which do not have onboard data recorders (e.g., military, short-haul, and general aviation). The technique used to determine the aircraft motions involves smoothing of raw radar data. These smoothed results, in combination with other available information (wind profiles and aircraft performance data), are used to derive the expanded set of data. This program uses a cubic least-square fit to smooth the raw data. This moving-arc procedure provides a smoothed time history of the aircraft position, the inertial velocities, and accelerations. Using known winds, these inertial data are transformed to aircraft stability axes to provide true airspeed, thrust-drag, lift, and roll angle. Further derivation, based on aircraft dependent performance data, can determine the aircraft angle of attack, pitch, and heading angle. Results of experimental tests indicate that values derived from ATC radar records using this technique agree favorably with airborne measurements. This program is written in FORTRAN IV to be executed in the batch mode, and has been implemented on a CDC 6000 series computer with a central memory requirement of 64k (octal) of 60 bit words.

Environmental Assessment of the Reduce Bird Air Strike Hazards (BASH) Along East Tollgate Creek, Buckley Air Force Base, Colorado

DTIC Science & Technology

2011-03-22

Aircraft collisions with birds and other wildlife annually cause millions of dollars in aircraft damage and may result in loss of life and aircraft...collisions with birds and other wildlife annually cause millions of dollars in aircraft damage and may result in loss of life and aircraft. More...Action would support the BASH program and meet the AF goal of reducing the loss of life and of valuable aircraft and other resources. Figure 1-2

Designing for aircraft structural crashworthiness

NASA Technical Reports Server (NTRS)

Thomson, R. G.; Caiafa, C.

1981-01-01

This report describes structural aviation crash dynamics research activities being conducted on general aviation aircraft and transport aircraft. The report includes experimental and analytical correlations of load-limiting subfloor and seat configurations tested dynamically in vertical drop tests and in a horizontal sled deceleration facility. Computer predictions using a finite-element nonlinear computer program, DYCAST, of the acceleration time-histories of these innovative seat and subfloor structures are presented. Proposed application of these computer techniques, and the nonlinear lumped mass computer program KRASH, to transport aircraft crash dynamics is discussed. A proposed FAA full-scale crash test of a fully instrumented radio controlled transport airplane is also described.

Airborne antenna pattern calculations

NASA Technical Reports Server (NTRS)

Knerr, T. J.; Mielke, R. R.

1981-01-01

Progress on the development of modeling software, testing software against caclulated data from program VPAP and measured patterns, and calculating roll plane patterns for general aviation aircraft is reported. Major objectives are the continued development of computer software for aircraft modeling and use of this software and program OSUVOL to calculate principal plane and volumetric radiation patterns. The determination of proper placement of antennas on aircraft to meet the requirements of the Microwave Landing System is discussed. An overview of the performed work, and an example of a roll plane model for the Piper PA-31T Cheyenne aircraft and the resulting calculated roll plane radiation pattern are included.

Advanced prediction technique for the low speed aerodynamics of V/STOL aircraft. Volume 2: User's manual

NASA Technical Reports Server (NTRS)

Beatty, T. D.; Worthey, M. K.

1984-01-01

A computerized prediction method known as the Vought V/STOL Aircraft Propulsive Effects computer program (VAPE) for propulsive induced forces and moments in transition and Short TakeOff and Landing (STOL) flight is improved and evaluated. The VAPE program is capable of evaluating: (1) effects of relative wind about an aircraft, (2) effects of propulsive lift jet entrainment, vorticity and flow blockage, (3) effects of engine inlet flow on the aircraft flow field, (4) engine inlet forces and moments including inlet separation, (5) ground effects in the STOL region of flight, and (6) viscous effects on lifting surfaces.

A robust optimization methodology for preliminary aircraft design

NASA Astrophysics Data System (ADS)

Prigent, S.; Maréchal, P.; Rondepierre, A.; Druot, T.; Belleville, M.

2016-05-01

This article focuses on a robust optimization of an aircraft preliminary design under operational constraints. According to engineers' know-how, the aircraft preliminary design problem can be modelled as an uncertain optimization problem whose objective (the cost or the fuel consumption) is almost affine, and whose constraints are convex. It is shown that this uncertain optimization problem can be approximated in a conservative manner by an uncertain linear optimization program, which enables the use of the techniques of robust linear programming of Ben-Tal, El Ghaoui, and Nemirovski [Robust Optimization, Princeton University Press, 2009]. This methodology is then applied to two real cases of aircraft design and numerical results are presented.

Time-based air traffic management using expert systems

NASA Technical Reports Server (NTRS)

Tobias, L.; Scoggins, J. L.

1986-01-01

A prototype expert system was developed for the time scheduling of aircraft into the terminal area. The three functions of the air traffic control schedule advisor are as follows: first, for each new arrival, it develops an admissible flight plan for that aircraft. Second, as the aircraft progresses through the terminal area, it monitors deviations from the flight plan and provides advisories to return the aircraft to its assigned schedule. Third, if major disruptions such as missed approaches occur, it develops a revised plan. The advisor is operational on a Symbolics 3600, and is programed in MRS (a logic programming language), Lisp, and FORTRAN.

Verification of the proteus two-dimensional Navier-Stokes code for flat plate and pipe flows

NASA Technical Reports Server (NTRS)

Conley, Julianne M.; Zeman, Patrick L.

1991-01-01

The Proteus Navier-Stokes Code is evaluated for 2-D/axisymmetric, viscous, incompressible, internal, and external flows. The particular cases to be discussed are laminar and turbulent flows over a flat plate, laminar and turbulent developing pipe flows, and turbulent pipe flow with swirl. Results are compared with exact solutions, empirical correlations, and experimental data. A detailed description of the code set-up, including boundary conditions, initial conditions, grid size, and grid packing is given for each case.

The development of an intelligent interface to a computational fluid dynamics flow-solver code

NASA Technical Reports Server (NTRS)

Williams, Anthony D.

1988-01-01

Researchers at NASA Lewis are currently developing an 'intelligent' interface to aid in the development and use of large, computational fluid dynamics flow-solver codes for studying the internal fluid behavior of aerospace propulsion systems. This paper discusses the requirements, design, and implementation of an intelligent interface to Proteus, a general purpose, 3-D, Navier-Stokes flow solver. The interface is called PROTAIS to denote its introduction of artificial intelligence (AI) concepts to the Proteus code.

The development of an intelligent interface to a computational fluid dynamics flow-solver code

NASA Technical Reports Server (NTRS)

Williams, Anthony D.

1988-01-01

Researchers at NASA Lewis are currently developing an 'intelligent' interface to aid in the development and use of large, computational fluid dynamics flow-solver codes for studying the internal fluid behavior of aerospace propulsion systems. This paper discusses the requirements, design, and implementation of an intelligent interface to Proteus, a general purpose, three-dimensional, Navier-Stokes flow solver. The interface is called PROTAIS to denote its introduction of artificial intelligence (AI) concepts to the Proteus code.

Water quality bioassay using selected protozoa. I. [Paramecium candatum; Amoeba proteus; Euglena gracilis

DOE Office of Scientific and Technical Information (OSTI.GOV)

Mills, W.L.

1976-01-01

The suitability of certain species of protozoa as indicators of water quality has been determined. Experiments were conducted under laboratory conditions to standardize a bioassay procedure for water quality using either Paramecium caudatum, Amoeba proteus, or Euglena gracilis as the indicator organism. The bioassay, which consists of exposing the organisms to a known concentration of pollutant under laboratory conditions, followed by microscopic observation to establish the time of death, affords a reliable, convenient and inexpensive way to monitor for water quality.

IMP-27, a Unique Metallo-β-Lactamase Identified in Geographically Distinct Isolates of Proteus mirabilis.

PubMed

Dixon, Nyssa; Fowler, Randal C; Yoshizumi, A; Horiyama, Tsukasa; Ishii, Y; Harrison, Lucas; Geyer, Chelsie N; Moland, Ellen Smith; Thomson, Kenneth; Hanson, Nancy D

2016-10-01

A novel metallo-β-lactamase gene, blaIMP-27, was identified in unrelated Proteus mirabilis isolates from two geographically distinct locations in the United States. Both isolates harbor blaIMP-27 as part of the first gene cassette in a class 2 integron. Antimicrobial susceptibility testing indicated susceptibility to aztreonam, piperacillin-tazobactam, and ceftazidime but resistance to ertapenem. However, hydrolysis assays indicated that ceftazidime was a substrate for IMP-27. Copyright © 2016 Dixon et al.

Toward a Mathematical Theory of Counterterrorism (Proteus USA, Volume 1, Issue 2, December 2007)

DTIC Science & Technology

2007-12-01

Toward a MaTheMaTical Theory of counTerTerrorisM The Proteus Monograph Series Volume 1, Issue 2 December 2007 Report Documentation Page Form...COVERED 00-00-2007 to 00-00-2007 4. TITLE AND SUBTITLE Toward a Mathematical Theory of Counterterrorism 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c...Army War College,Center for Strategic Leadership ,650 Wright Avenue,Carlisle,PA,17013-5049 8. PERFORMING ORGANIZATION REPORT NUMBER 9. SPONSORING

Analyzing Future Complex National Security Challenges within the Joint, Interagency, Intergovernmental, and Multinational Environment. Proteus Futures Academic Workshop Held in Carlisle Barracks, Pennsylvania on 22-24 August 2006

DTIC Science & Technology

2006-08-01

AVAILABILITY STATEMENT Approved for public release; distribution unlimited 13. SUPPLEMENTARY NOTES 14. ABSTRACT 15. SUBJECT TERMS 16. SECURITY...threats, or financial insecurities. Yankee Going Home: The world of 2020 looks like a confused mess! Little is clear except that the world has... statements from Proteus: Insights from 2020 are highly releant when thinking about the current strategic picture in the context of Power: “When Power

Aircraft data summaries for the SURE intensives. Final report. [Sampling done July 1978 near Duncan Falls, Ohio and Scranton, Pennsylvania

DOE Office of Scientific and Technical Information (OSTI.GOV)

Keifer, W.S.; Blumenthal, D.L.; Tommerdahl, J.B.

1981-09-01

As part of the EPRI sulfate regional experiment (SURE), Meteorology Research, Inc., (MRI) and Research Triangle Institute (RTI) conducted six air quality sampling programs in the eastern United States using instrumented aircraft. This volume includes the air quality and meteorological data obtained during the July 1978 Intensive when MRI sampled near the Duncan Falls, Ohio, SURE Station and RTI sampled near the Scranton, Pennsylvania, SURE Station. During the last part of the July 1978 sampling period, both MRI and RTI aircraft participated in a large regional-scale sampling program with Brookhaven National Laboratory (BNL) and Pacific Northwest Laboratory (PNL). Only themore » data obtained by the MRI and RTI aircraft during this regional-scale sapling program are included in this volume.« less

Development and validation of a numerical acoustic analysis program for aircraft interior noise prediction

NASA Astrophysics Data System (ADS)

Garcea, Ralph; Leigh, Barry; Wong, R. L. M.

Reduction of interior noise in propeller-driven aircraft, to levels comparable with those obtained in jet transports, has become a leading factor in the early design stages of the new generation turboprops- and may be essential if these new designs are to succeed. The need for an analytical capability to predict interior noise is accepted throughout the turboprop aircraft industry. To this end, an analytical noise prediction program, which incorporates the SYSNOISE numerical acoustic analysis software, is under development at de Havilland. The discussion contained herein looks at the development program and how it was used in a design sensitivity analysis to optimize the structural design of the aircraft cabin for the purpose of reducing interior noise levels. This report also summarizes the validation of the SYSNOISE package using numerous classical cases from the literature.

X-31 in flight, Herbst maneuver

NASA Technical Reports Server (NTRS)

1990-01-01

Two X-31 Enhanced Fighter Maneuverability (EFM) demonstrators were flown at the Rockwell International Palmdale, California, facility and the NASA Dryden Flight Research Center, Edwards, California, to obtain data that may apply to the design of highly-maneuverable next-generation fighters. The program had its first flight on October 11, 1990, in Palmdale; it ended in June 1995. The X-31 program demonstrated the value of thrust vectoring (directing engine exhaust flow) coupled with advanced flight control systems, to provide controlled flight during close-in air combat at very high angles of attack. The result of this increased maneuverability is an aircraft with a significant advantage over conventional fighters. 'Angle-of-attack' (alpha) is an engineering term to describe the angle of an aircraft body and wings relative to its actual flight path. During maneuvers, pilots often fly at extreme angles of attack--with the nose pitched up while the aircraft continues in its original direction. This can lead to loss of control and result in the loss of the aircraft, or both. Three thrust-vectoring paddles made of graphite epoxy mounted on the X-31 aircraft exhaust nozzle directed the exhaust flow to provide control in pitch (up and down) and yaw (right and left) to improve control. The paddles can sustain heat of up to 1,500 degrees centigrade for extended periods of time. In addition the X-31 aircraft were configured with movable forward canards and fixed aft strakes. The canards were small wing-like structures set on the wing line between the nose and the leading edge of the wing. The strakes were set on the same line between the trailing edge of the wing and the engine exhaust. Both supplied additional control in tight maneuvering situations. The X-31 research program produced technical data at high angles of attack. This information is giving engineers and aircraft designers a better understanding of aerodynamics, effectiveness of flight controls and thrust vectoring, and airflow phenomena at high angles of attack. This is expected to lead to design methods that provide better maneuverability in future high performance aircraft and make them safer to fly. An international test organization of about 110 people, managed by the Advanced Research Projects Agency (ARPA), conducted the flight operations at NASA Dryden. The ARPA had requested flight research for the X-31 aircraft be moved there in February 1992. In addition to ARPA and NASA, the International Test Organization (ITO) included the U.S. Navy, the U.S. Air Force, Rockwell International, the Federal Republic of Germany, and Daimler-Benz Aerospace (formerly Messerschmitt-Bolkow-Blohm and Deutsche Aerospace). NASA was responsible for flight research operations, aircraft maintenance, and research engineering once the program moved to Dryden. The No. 1 X-31 aircraft was lost in an accident Jan. 19, 1995. The pilot, Karl Heinz-Lang, of the Federal Republic of Germany, ejected safely before the aircraft crashed in an unpopulated desert area just north of Edwards. The X-31 program logged an X-plane record of 580 flights during the program, including 555 research missions and 21 in Europe for the 1995 Paris Air Show. A total of 14 pilots representing all agencies of the ITO flew the aircraft. In this 40-second movie clip the X-31 aircraft is shown performing the 'Herbst maneuver,' which is a rapid, minimum-180-degree turn using a post-stall maneuver flying well beyond the aerodynamic limits of any conventional aircraft. Named after Wolfgang Herbst a proponent of using post-stall flight in air-to-air combat.

X-31 landing

NASA Technical Reports Server (NTRS)

1995-01-01

Two X-31 Enhanced Fighter Maneuverability (EFM) demonstrators were flown at the Rockwell International facility, Palmdale, California, and the NASA Dryden Flight Research Center, Edwards, California, to obtain data that may apply to the design of highly-maneuverable next-generation fighters. The program had its first flight on October 11, 1990, in Palmdale; it ended in June 1995. The X-31 program demonstrated the value of thrust vectoring (directing engine exhaust flow) coupled with advanced flight control systems, to provide controlled flight during close-in air combat at very high angles of attack. The result of this increased maneuverability is an airplane with a significant advantage over conventional fighters. 'Angle-of-attack' (alpha) is an engineering term to describe the angle of an aircraft's body and wings relative to its actual flight path. During maneuvers, pilots often fly at extreme angles of attack -- with the nose pitched up while the aircraft continues in its original direction. This can lead to loss of control and result in the loss of the aircraft, pilot or both. Three thrust vectoring paddles made of graphite epoxy mounted on the exhaust nozzle of the X-31 aircraft directed the exhaust flow to provide control in pitch (up and down) and yaw (right and left) to improve control. The paddles can sustain heat of up to 1,500 degrees centigrade for extended periods of time. In addition the X-31 aircraft were configured with movable forward canards and fixed aft strakes. The canards were small wing-like structures set on the wing line between the nose and the leading edge of the wing. The strakes were set on the same line between the trailing edge of the wing and the engine exhaust. Both supplied additional control in tight maneuvering situations. The X-31 research program produced technical data at high angles of attack. This information is giving engineers and aircraft designers a better understanding of aerodynamics, effectiveness of flight controls and thrust vectoring, and airflow phenomena at high angles of attack. This understanding is expected to lead to design methods that provide better maneuverability in future high performance aircraft and make them safer to fly. An international test organization of about 110 people, managed by the Advanced Research Projects Agency (ARPA), conducted the flight operations at NASA Dryden. The ARPA had requested flight research for the X-31 aircraft be moved there in February 1992. In addition to ARPA and NASA, the international test organization (ITO) included the U.S. Navy, the U.S. Air Force, Rockwell International, the Federal Republic of Germany, and Daimler-Benz Aerospace (formerly Messerschmitt-Bolkow-Blohm and Deutsche Aerospace). NASA was responsible for flight research operations, aircraft maintenance, and research engineering once the program moved to Dryden. The No. 1 X-31 aircraft was lost in an accident January 19, 1995. The pilot, Karl Heinz-Lang, of the Federal Republic of Germany, ejected safely before the aircraft crashed in an unpopulated desert area just north of Edwards. The X-31 program logged an X-plane record of 580 flights during the program, including 555 research missions and 21 in Europe for the 1995 Paris Air Show. A total of 14 pilots representing all agencies of the ITO flew the aircraft. The X-31 aircraft shown on approach with a high angle of attack, touches down with its speed brakes, which can be seen extended just above and behind the wing. The aircraft then begins to rotate the nosegear down to runway contact and deploys a braking parachute that assists in slowing the aircraft after landing.

NASA aviation safety program aircraft engine health management data mining tools roadmap

DOT National Transportation Integrated Search

2000-04-01

Aircraft Engine Health Management Data Mining Tools is a project led by NASA Glenn Research Center in support of the NASA Aviation Safety Program's Aviation System Monitoring and Modeling Thrust. The objective of the Glenn-led effort is to develop en...

A simplified analysis of propulsion installation losses for computerized aircraft design

NASA Technical Reports Server (NTRS)

Morris, S. J., Jr.; Nelms, W. P., Jr.; Bailey, R. O.

1976-01-01

A simplified method is presented for computing the installation losses of aircraft gas turbine propulsion systems. The method has been programmed for use in computer aided conceptual aircraft design studies that cover a broad range of Mach numbers and altitudes. The items computed are: inlet size, pressure recovery, additive drag, subsonic spillage drag, bleed and bypass drags, auxiliary air systems drag, boundary-layer diverter drag, nozzle boattail drag, and the interference drag on the region adjacent to multiple nozzle installations. The methods for computing each of these installation effects are described and computer codes for the calculation of these effects are furnished. The results of these methods are compared with selected data for the F-5A and other aircraft. The computer program can be used with uninstalled engine performance information which is currently supplied by a cycle analysis program. The program, including comments, is about 600 FORTRAN statements long, and uses both theoretical and empirical techniques.

Federal Aviation Administration aging aircraft nondestructive inspection research plan

NASA Technical Reports Server (NTRS)

Seher, Chris C.

1992-01-01

This paper highlights the accomplishments and plans of the Federal Aviation Administration (FAA) for the development of improved nondestructive evaluation (NDE) equipment, procedures, and training. The role of NDE in aircraft safety and the need for improvement are discussed. The FAA program participants, and coordination of activities within the program and with relevant organizations outside the program are also described.

Progress in supersonic cruise aircraft technology

NASA Technical Reports Server (NTRS)

Driver, C.

1978-01-01

The supersonic cruise aircraft research program identified significant improvements in the technology areas of propulsion, aerodynamics, structures, takeoff and landing procedures, and advanced configuration concepts. Application of these technology areas to a commercial aircraft is discussed. An advanced SST family of aircraft which may be environmentally acceptable, have flexible range-payload capability, and be economically viable is projected.

Modeling, Simulation, and Flight Test for Automatic Flight Control of the Condor Hybrid-Electric Remote Piloted Aircraft

DTIC Science & Technology

2012-03-01

comprehensive explanations (Yechout, 2003), (Nelson, 1998). Figure 9: USAFA/Brandt Jet5 Aircraft Modeling Program 18 2.5.1 Dynamic Aircraft...16 2.5.1 Dynamic Aircraft Stability Modes .......................................................... 18 2.5.2 State...12 Figure 7: Body-Fixed Reference Frame ........................................................................... 13 Figure 8: Static and Dynamic

Study on utilization of advanced composites in commercial aircraft wing structures, volume 2

NASA Technical Reports Server (NTRS)

Sakata, I. F.; Ostrom, R. B.

1978-01-01

A plan is defined for a composite wing development effort which will assist commercial transport manufacturers in reaching a level of technology readiness where the utilization of composite wing structure is a cost competitive option for a new aircraft production plan. The recommended development effort consists of two programs: a joint government/industry material development program and a wing structure development program. Both programs are described in detail.

A Case Study of an Aeronautical Systems Division System Program Office.

DTIC Science & Technology

1982-09-01

11111 -’.-- m 1 1.25 111111.4 1 1.6_ MICROCOPY RESOLUTION TEST CHART NATIONAL BUREAU OF STANDARDS-1963-A If. t 1’ I I( N 2> - .~.. * .~ .~-I ~ k~’ ~K ~r...office....assesses.................. 8 Section 11 The Standard Aircraft Sensor UnitProgram........ 32 Section III Terms and Defnition ...contracts with industry, (b) test programs with both industry and other DOD organizations, (c) aircraft production or modification programs with both

Development Cycle Time Simulation for Civil Aircraft

NASA Technical Reports Server (NTRS)

Spitz, William; Berardino, Frank; Golaszewski, Richard; Johnson, Jesse

2001-01-01

Cycle Time Reduction (CTR) will be one of the major factors affecting the future of the civil aerospace industry. This focus is the end reflection of the level of competition in the commercial large carrier aircraft industry. Aircraft manufacturer must minimize costs and pass a portion of those savings onto buyers. CTR is one strategy used to move the manufacturing firm down the cost curve. The current NASA Airframe Development Cycle Time Reduction Goal is 50% by year 2022. This goal is not achievable based on the program analysis done by the LMI/GRA team. This may mean that the current roster of NASA CTR programs needs to be reexamined or that the program technology progress factors, as determined by the NASA experts, were understated. Programs that duplicate the reductions of others should be replaced with non-duplicative programs. In addition, new programs targeting a specific part of the cycle can be developed.

A study on the utilization of advanced composites in commercial aircraft wing structure

NASA Technical Reports Server (NTRS)

Watts, D. J.

1978-01-01

A study was conducted to define the technology and data needed to support the introduction of advanced composite materials in the wing structure of future production aircraft. The study accomplished the following: (1) definition of acceptance factors, (2) identification of technology issues, (3) evaluation of six candidate wing structures, (4) evaluation of five program options, (5) definition of a composite wing technology development plan, (6) identification of full-scale tests, (7) estimation of program costs for the total development plan, (8) forecast of future utilization of composites in commercial transport aircraft and (9) identification of critical technologies for timely program planning.

Measurement of high altitude air quality using aircraft

NASA Technical Reports Server (NTRS)

Rudey, R. A.; Perkins, P. J.

1973-01-01

The minor atmospheric constituents associated with and affected by aircraft exhaust emissions at altitudes from 6 to 20 km will be monitored in flight programs presently being implemented. Preliminary in situ data are available from flight tests of dedicated instruments to be used in these programs. A Global Atmospheric Sampling Program using Boeing 747 airliners was determined to be feasible in studies conducted by airlines and airframe companies. Worldwide monitoring in the troposphere and the lower stratosphere is planned. Stratospheric air sampling on a more local basis will be done with a U2 aircraft. Measuring system evaluations and improvements have been required to detect the low background levels.

Measurement of high-altitude air quality using aircraft.

NASA Technical Reports Server (NTRS)

Rudey, R. A.; Perkins, P. J.

1973-01-01

The minor atmospheric constituents associated with and affected by aircraft exhaust emissions at altitudes from 6 to 20 km will be monitored in flight programs presently being implemented. Preliminary in situ data are available from flight tests of dedicated instruments to be used in these programs. A Global Atmospheric Sampling Program using Boeing 747 airliners was determined to be feasible in studies conducted by airlines and airframe companies. Worldwide monitoring in the troposphere and the lower stratosphere is planned. Stratospheric air sampling on a more local basis will be done with a U2 aircraft. Measuring system evaluations and improvements have been required to detect the low background levels.

The aircraft energy efficiency active controls technology program

NASA Technical Reports Server (NTRS)

Hood, R. V., Jr.

1977-01-01

Broad outlines of the NASA Aircraft Energy Efficiency Program for expediting the application of active controls technology to civil transport aircraft are presented. Advances in propulsion and airframe technology to cut down on fuel consumption and fuel costs, a program for an energy-efficient transport, and integrated analysis and design technology in aerodynamics, structures, and active controls are envisaged. Fault-tolerant computer systems and fault-tolerant flight control system architectures are under study. Contracts with leading manufacturers for research and development work on wing-tip extensions and winglets for the B-747, a wing load alleviation system, elastic mode suppression, maneuver-load control, and gust alleviation are mentioned.

Annual Industrial Capabilities Report to Congress

DTIC Science & Technology

2008-03-01

61 5.1 Aircraft Sector Industrial Summary...basis, key contractor workforce capabilities necessary for successful programs. Industry segment-level baseline assessments ( aircraft ; command, control...monitored representative individual corporate divisions for each major industry segment ( aircraft parts and components, water craft, ground vehicles

40 CFR 87.1 - Definitions.

Code of Federal Regulations, 2014 CFR

2014-07-01

... Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF AIR... turboprop engines. Class TF means all turbofan or turbojet aircraft engines or aircraft engines designed for... turbine engines employed for propulsion of aircraft designed to operate at supersonic flight speeds...

EGADS: A microcomputer program for estimating the aerodynamic performance of general aviation aircraft

NASA Technical Reports Server (NTRS)

Melton, John E.

1994-01-01

EGADS is a comprehensive preliminary design tool for estimating the performance of light, single-engine general aviation aircraft. The software runs on the Apple Macintosh series of personal computers and assists amateur designers and aeronautical engineering students in performing the many repetitive calculations required in the aircraft design process. The program makes full use of the mouse and standard Macintosh interface techniques to simplify the input of various design parameters. Extensive graphics, plotting, and text output capabilities are also included.

Navy’s Advanced Aircraft Armament System Program Concept Objectives

DTIC Science & Technology

1983-10-01

12-1 00 NAVY’S ADVANCED AIRCRAFT ARMAMENT SYSTEM PROGRAM CONCEPT OBJECTIVES T. M . Leese and J. F. Haney Naval Weapons Center Code 31403 China...STORE FLWNT LIFE RECONFIOURATION ♦ UWMST OMHTH ninoairv M — MANN HUCTHM ^♦■ SILECT ALTERNATE • STORE 0PTI0M ■ REOUCIO CK« W0RKL0A0 • . README...mOVEMENTS INÜTEO FUIWUTY MM AM tTATWM COMPLEX AUTOMATIC LACK OF OIT RESTRICTIVE MLNIRV M FLUWAITV IUCSMVI Figure 1. Carrier aircraft

Harrier Information Management System (HIMS): The system and the approach

NASA Astrophysics Data System (ADS)

Reynolds, D. J.

1990-01-01

The Harrier GR5 is to be fleet-fitted with an engine monitoring system. The ground station known as HIMS was developed to enable engineers to analyze parameter exceedance and component life count data collected from it. The HIMS and its development program are reviewed. Counts can vary from aircraft to aircraft for a given number of flying hours and lifting on this basis is expected to yield considerable savings. Aspects relevant to future aircraft health monitoring programs are considered.

Proteus mirabilis fimbriae- and urease-dependent clusters assemble in an extracellular niche to initiate bladder stone formation

PubMed Central

Schaffer, Jessica N.; Norsworthy, Allison N.; Sun, Tung-Tien

2016-01-01

The catheter-associated uropathogen Proteus mirabilis frequently causes urinary stones, but little has been known about the initial stages of bladder colonization and stone formation. We found that P. mirabilis rapidly invades the bladder urothelium, but generally fails to establish an intracellular niche. Instead, it forms extracellular clusters in the bladder lumen, which form foci of mineral deposition consistent with development of urinary stones. These clusters elicit a robust neutrophil response, and we present evidence of neutrophil extracellular trap generation during experimental urinary tract infection. We identified two virulence factors required for cluster development: urease, which is required for urolithiasis, and mannose-resistant Proteus-like fimbriae. The extracellular cluster formation by P. mirabilis stands in direct contrast to uropathogenic Escherichia coli, which readily formed intracellular bacterial communities but not luminal clusters or urinary stones. We propose that extracellular clusters are a key mechanism of P. mirabilis survival and virulence in the bladder. PMID:27044107

In Vitro Studies of Semisynthetic α- (Substituted-Ureido) Penicillins

PubMed Central

Bodey, Gerald P.; Stewart, Dorothy

1971-01-01

The activity of three α-(substituted-ureido) penicillins was evaluated in vitro against 599 clinical isolates of gram-negative bacilli, by use of the broth-dilution technique. At a concentration of 12.5 μg or less/ml, BL-P1597 inhibited 90% of isolates of Pseudomonas sp., 56% of Enterobacter sp., 67% of indole-positive Proteus spp., 72% of Escherichia coli, and 85% of Proteus mirabilis. BL-P1654 had similar activity, whereas BL-P1532 was much less active. At a concentration of 25 μg or less/ml, BL-P1597 also inhibited nearly 60% of isolates of Klebsiella sp. and nearly 40% of Serratia sp. BL-P1597 and BL-P1654 were as active as ampicillin and carbenicillin against E. coli and P. mirabilis. They were less active than carbenicillin against indole-positive Proteus spp. Both drugs were substantially more active than carbenicillin against Pseudomonas sp. A strain of Pseudomonas sp. which developed resistance to carbenicillin also developed resistance to the α-(substituted-ureido) penicillins simultaneously. PMID:4930281

Cytoplasmic DNA synthesis in Amoeba proteus. I. On the particulate nature of the DNA-containing elements.

PubMed

RABINOVITCH, M; PLAUT, W

1962-12-01

The incorporation of tritiated thymidine in Amoeba proteus was reinvestigated in order to see if it could be associated with microscopically detectable structures. Staining experiments with basic dyes, including the fluorochrome acridine orange, revealed the presence of large numbers of 0.3 to 0.5 micro particles in the cytoplasm of all cells studied. The effect of nuclease digestion on the dye affinity of the particles suggests that they contain DNA as well as RNA. Centrifugation of living cells at 10,000 g leads to the sedimentation of the particles in the centrifugal third of the ameba near the nucleus. Analysis of centrifuged cells which had been incubated with H(3)-thymidine showed a very high degree of correlation between the location of the nucleic acid-containing granules and that of acid-insoluble, deoxyribonuclease-sensitive labeled molecules and leads to the conclusion that cytoplasmic DNA synthesis in Amoeba proteus occurs in association with these particles.

The Role of Modern Control Theory in the Design of Controls for Aircraft Turbine Engines

NASA Technical Reports Server (NTRS)

Zeller, J.; Lehtinen, B.; Merrill, W.

1982-01-01

Accomplishments in applying Modern Control Theory to the design of controls for advanced aircraft turbine engines were reviewed. The results of successful research programs are discussed. Ongoing programs as well as planned or recommended future thrusts are also discussed.

Aircraft Mechanics: Scope and Sequence.

ERIC Educational Resources Information Center

Nashville - Davidson County Metropolitan Public Schools, TN.

This scope and sequence guide, developed for an aircraft mechanics vocational education program, represents an initial step in the development of a systemwide articulated curriculum sequence for all vocational programs within the Metropolitan Nashville Public School System. It was developed as a result of needs expressed by teachers, parents, and…

Airframe technology for aircraft energy efficiency. [economic factors

NASA Technical Reports Server (NTRS)

James, R. L., Jr.; Maddalon, D. V.

1984-01-01

The economic factors that resulted in the implementation of the aircraft energy efficiency program (ACEE) are reviewed and airframe technology elements including content, progress, applications, and future direction are discussed. The program includes the development of laminar flow systems, advanced aerodynamics, active controls, and composite structures.

High-Speed Jet Noise Reduction NASA Perspective

NASA Technical Reports Server (NTRS)

Huff, Dennis L.; Handy, J. (Technical Monitor)

2001-01-01

History shows that the problem of high-speed jet noise reduction is difficult to solve. the good news is that high performance military aircraft noise is dominated by a single source called 'jet noise' (commercial aircraft have several sources). The bad news is that this source has been the subject of research for the past 50 years and progress has been incremental. Major jet noise reduction has been achieved through changing the cycle of the engine to reduce the jet exit velocity. Smaller reductions have been achieved using suppression devices like mixing enhancement and acoustic liners. Significant jet noise reduction without any performance loss is probably not possible! Recent NASA Noise Reduction Research Programs include the High Speed Research Program, Advanced Subsonic Technology Noise Reduction Program, Aerospace Propulsion and Power Program - Fundamental Noise, and Quiet Aircraft Technology Program.

Detection of human antibodies binding with smooth and rough LPSs from Proteus mirabilis O3 strains S1959, R110, R45.

PubMed

Gleńska-Olender, J; Durlik, K; Konieczna, I; Kowalska, P; Gawęda, J; Kaca, W

2017-11-01

Bacteria of the genus Proteus of the family Enterobacteriaceae are facultative human pathogens responsible mainly for urinary tract and wound infections, bacteremia and the development of rheumatoid arthritis (RA). We have analyzed and compared by ELISA the titer of antibodies in plasmas of healthy individuals and in sera of rheumatoid arthritis patients recognizing a potential host cross-reactive epitope (lysine-galacturonic acid epitopes) present in Proteus lipopolysaccharide (LPS). In our experiments LPSs isolated from two mutants of smooth Proteus mirabilis 1959 (O3), i.e. strains R110 and R45, were used. R110 (Ra type mutant) is lacking the O-specific polysaccharide, but possesses a complete core oligosaccharide, while R45 (Re type) has a reduced core oligosaccharide and contains two 3-deoxy-D-manno-oct-2-ulosonic acid residues and one of 4-amino-4-deoxy-L-arabinopyranose residues. Titer of P. mirabilis S1959 LPS-specific-antibodies increased with the age of blood donors. RA and blood donors' sera contained antibodies against S and Ra and Re type of P. mirabilis O3 LPSs. Antibodies recognizing lysine-galacturonic acid epitopes of O3 LPS were detected by ELISA in some plasmas of healthy individuals and sera of rheumatoid arthritis patients. RA patients antibodies reacting with P. mirabilis S1959 S and R LPSs may indicate a potential role of anti-LPS antibodies in molecular mimicry in RA diseases.

Preliminary Analysis of the Transient Reactor Test Facility (TREAT) with PROTEUS

DOE Office of Scientific and Technical Information (OSTI.GOV)

Connaway, H. M.; Lee, C. H.

The neutron transport code PROTEUS has been used to perform preliminary simulations of the Transient Reactor Test Facility (TREAT). TREAT is an experimental reactor designed for the testing of nuclear fuels and other materials under transient conditions. It operated from 1959 to 1994, when it was placed on non-operational standby. The restart of TREAT to support the U.S. Department of Energy’s resumption of transient testing is currently underway. Both single assembly and assembly-homogenized full core models have been evaluated. Simulations were performed using a historic set of WIMS-ANL-generated cross-sections as well as a new set of Serpent-generated cross-sections. To supportmore » this work, further analyses were also performed using additional codes in order to investigate particular aspects of TREAT modeling. DIF3D and the Monte-Carlo codes MCNP and Serpent were utilized in these studies. MCNP and Serpent were used to evaluate the effect of geometry homogenization on the simulation results and to support code-to-code comparisons. New meshes for the PROTEUS simulations were created using the CUBIT toolkit, with additional meshes generated via conversion of selected DIF3D models to support code-to-code verifications. All current analyses have focused on code-to-code verifications, with additional verification and validation studies planned. The analysis of TREAT with PROTEUS-SN is an ongoing project. This report documents the studies that have been performed thus far, and highlights key challenges to address in future work.« less

Cytotoxicity of polyamines to Amoeba proteus: role of polyamine oxidase.

PubMed

Schenkel, E; Dubois, J G; Helson-Cambier, M; Hanocq, M

1996-02-01

It has been shown that oxidation of polyamines by polyamine oxidases can produce toxic compounds (H2O2, aldehydes, ammonia) and that the polyamine oxidase-polyamine system is implicated, in vitro, in the death of several parasites. Using Amoeba proteus as an in vitro model, we studied the cytotoxicity to these cells of spermine, spermidine, their acetyl derivatives, and their hypothetical precursors. Spermine and N1-acetylspermine were more toxic than emetine, an amoebicidal reference drug. Spermine presented a short-term toxicity, but a 48-h contact time was necessary for the high toxicity of spermidine. The uptake by Amoeba cells of the different polyamines tested was demonstrated. On the other hand, a high polyamine oxidase activity was identified in Amoeba proteus crude extract. Spermine (theoretical 100%) and N1-acetylspermine (64%) were the best substrates at pH 9.5, while spermidine, its acetyl derivatives, and putrescine were very poorly oxidized by this enzyme (3-20%). Spermine oxidase activity was inhibited by phenylhydrazine (nil) and isoniazid (approximately 50%). Mepacrine did not inhibit the enzyme activity at pH 8. Neither monoamine nor diamine oxidase activity (approximately 10%) was found. It must be emphasized that spermine, the best enzyme substrate, is the most toxic polyamine. This finding suggests that knowledge of polyamine oxidase specificity can be used to modulate the cytotoxicity of polyamine derivatives. Amoeba proteus was revealed as a simple model for investigation of the connection between cytotoxicity and enzyme activity.

Pinocytosis and locomotion of amoebae. XV. Visualization of Ca++-dynamics by chlorotetracycline (CTC) fluorescence during induced pinocytosis in living Amoeba proteus.

PubMed

Gawlitta, W; Stockem, W; Wehland, J; Weber, K

1980-01-01

The dynamics of Ca++ during induced pinocytosis were studied in Amoeba proteus using chlorotetracycline (CTC). The fluorescence of the Ca++ - CTC-complex was monitored by an image intensification system, which has certain advantages over standard equipment: (1) Living cells are not subjected to the damaging influence of intensive microscopic illumination, (2) fluorescent probes are not bleached during observation, and (3) the rapid dynamics of the Ca++ -fluxes can be recorded using short exposure times. The results demonstrate the existence of Ca++ bound to intracellular and extracellular sites of the cell membrane complex in normal locomoting and pinocytotic Amoeba proteus. The application of cations inducing pinocytosis causes a rapid decrease in the external CTC-fluorescence probably due to a release of Ca++ from the mucous layer. The degree of fluorescence intensity is correlated with the capacity of pinocytotic channel formation, i.e., the fluorescence decreases as the number of channels increases. During the phase of vesiculation a distinct fluorescence mainly restricted to the basal region of the channels is observed. Intracellular Ca++ was detected in close vicinity to the plasma membrane after both microinjection and external application of CTC. The internal CTC-fluorescence is slightly decreased during the induction phase of pinocytosis. The observations are in good agreement with previous results on the localization of Ca++ -binding sites at the plasma membrane of Amoeba proteus and demonstrate the important role of Ca++ -fluxes for the process of pinocytosis.

Review of the Rhein-Flugzeugbau Wankel powered aircraft program. [ducted fan engines

NASA Technical Reports Server (NTRS)

Riethmueller, M.

1978-01-01

The development of light aircraft with special emphasis on modern propulsion systems and production is discussed in terms of the application of rotary engines to aircraft. Emphasis is placed on the integrated ducted-fan propulsion system using rotary engines.

Statistical loads data for Cessna 172 aircraft using the Aircraft Cumulative Fatigue System (ACFS)

DOT National Transportation Integrated Search

2001-08-01

The purpose of this research and development program was to manufacture a small, lightweight, low-cost recorder for loads usage monitoring of general aviation and commuter type aircraft to support the Federal Aviation Administration (FAA) Operation L...

X-31 in flight - Mongoose Maneuver

NASA Technical Reports Server (NTRS)

1995-01-01

Two X-31 Enhanced Fighter Maneuverability (EFM) demonstrators were flown at the Rockwell International facility, Palmdale, California, and the NASA Dryden Flight Research Center, Edwards, California, to obtain data that may apply to the design of highly-maneuverable next-generation fighters. The program had its first flight on October 11, 1990, in Palmdale; it ended in June 1995. The X-31 program demonstrated the value of thrust vectoring (directing engine exhaust flow) coupled with advanced flight control systems, to provide controlled flight during close-in air combat at very high angles of attack. The result of this increased maneuverability is an aircraft with a significant advantage over conventional fighters. 'Angle-of-attack' (alpha) is an engineering term to describe the angle of an aircraft body and wings relative to its actual flight path. During maneuvers, pilots often fly at extreme angles of attack -- with the nose pitched up while the aircraft continues in its original direction. This can lead to loss of control and result in the loss of the aircraft, pilot or both. Three thrust-vectoring paddles made of graphite epoxy mounted on the exhaust nozzle of the X-31 aircraft directed the exhaust flow to provide control in pitch (up and down) and yaw (right and left) to improve control. The paddles can sustain heat of up to 1,500 degrees centigrade for extended periods of time. In addition the X-31 aircraft were configured with movable forward canards and fixed aft strakes. The canards were small wing-like structures set on the wing line between the nose and the leading edge of the wing. The strakes were set on the same line between the trailing edge of the wing and the engine exhaust. Both supplied additional control in tight maneuvering situations. The X-31 research program produced technical data at high angles of attack. This information is giving engineers and aircraft designers a better understanding of aerodynamics, effectiveness of flight controls and thrust vectoring, and airflow phenomena at high angles of attack. This understanding is expected to lead to design methods which provide better maneuverability in future high performance aircraft and make them safer to fly. An international test organization of about 110 people, managed by the Advanced Research Projects Agency (ARPA), conducted the flight operations at NASA Dryden. The ARPA had requested flight research for the X-31 aircraft be moved there in February 1992. In addition to ARPA and NASA, the international test organization (ITO) included the U.S. Navy, the U.S. Air Force, Rockwell International, the Federal Republic of Germany, and Daimler-Benz Aerospace (formerly Messerschmitt-Bolkow-Blohm and Deutsche Aerospace). NASA was responsible for flight research operations, aircraft maintenance, and research engineering once the program moved to Dryden. The No. 1 X-31 aircraft was lost in an accident January 19, 1995. The pilot, Karl Heinz-Lang, of the Federal Republic of Germany, ejected safely before the aircraft crashed in an unpopulated desert area just north of Edwards. The X-31 program logged an X-plane record of 580 flights during the program, including 555 research missions and 21 in Europe for the 1995 Paris Air Show. A total of 14 pilots representing all agencies of the ITO flew the aircraft. In this 36-second clip we see the X-31 performing the 'Mongoose maneuver,' beginning in a tight left hand turn, then pulling the aircraft into a high-angle-of-attack stall/tail-stand maneuver in which the aircraft remains in the vertical for several seconds, then pushes over to resume normal flight. This maneuver is in response to the Sukoi SU-27 'Flanker' test pilot Victor Georgievich Pugachev's 'Cobra maneuver' or 'Pugachev's cobra,' in which the aircraft, like the X-31, is stood on its tail to give the pilot a tactical advantage in air-to-air combat by essentially stopping and pointing the aircraft weapons toward the opponent.

78 FR 33357 - Takes of Marine Mammals Incidental to Specified Activities; Taking Marine Mammals Incidental to...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-06-04

...) Program. Multiple munitions (bombs, missiles, and gunner rounds) and aircraft would be used to meet the... with Munitions specific munitions) GBU-10 laser-guided Mk-84 bomb F-16C fighter aircraft. GBU-24 laser-guided Mk-84 bomb F-16C+ fighter aircraft. GBU-31 Joint Direct Attack Munition, F-15E fighter aircraft...

14 CFR 142.54 - Airline transport pilot certification training program.

Code of Federal Regulations, 2014 CFR

2014-01-01

... training in a flight simulation training device— (1) Holds an aircraft type rating for the aircraft represented by the flight simulation training device utilized in the training program and have received... will be demonstrated in the flight simulation training device; and (2) Satisfies the requirements of...

Aircraft: United States Air Force Child Care Program Activity Guide.

ERIC Educational Resources Information Center

Boggs, Juanita; Brant, Linda

General information about United States' aircraft is provided in this program activity guide for teachers and caregivers in Air Force preschools and day care centers. The guide includes basic information for teachers and caregivers, basic understandings, suggested teaching methods and group activities, vocabulary, ideas for interest centers, and…

78 FR 59974 - Centennial Challenges 2014 Unmanned Aircraft Systems (UAS) Airspace Operations Challenge (AOC)

Federal Register 2010, 2011, 2012, 2013, 2014

2013-09-30

... NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Centennial Challenges 2014 Unmanned Aircraft Systems... wish to compete may now register. Centennial Challenges is a program of prize competitions to stimulate...: http://www.uasaoc.org For general information on the NASA Centennial Challenges Program please visit...

X-31 in flight - Herbst Turn

NASA Technical Reports Server (NTRS)

1995-01-01

Two X-31 Enhanced Fighter Maneuverability (EFM) demonstrators were flown at the Rockwell International facility, Palmdale, California, and the NASA Dryden Flight Research Center, Edwards, California, to obtain data that may apply to the design of highly-maneuverable next-generation fighters. The program had its first flight on October 11, 1990, in Palmdale; it ended in June 1995. The X-31 program demonstrated the value of thrust vectoring (directing engine exhaust flow) coupled with advanced flight control systems, to provide controlled flight during close-in air combat at very high angles of attack. The result of this increased maneuverability is an airplane with a significant advantage over conventional fighters. 'Angle-of-attack' (alpha) is an engineering term to describe the angle of an aircraft body and wings relative to its actual flight path. During maneuvers, pilots often fly at extreme angles of attack -- with the nose pitched up while the aircraft continues in its original direction. This can lead to loss of control and result in the loss of the aircraft, pilot or both. Three thrust-vectoring paddles made of graphite epoxy mounted on the exhaust nozzle of the X-31 aircraft directed the exhaust flow to provide control in pitch (up and down) and yaw (right and left) to improve control. The paddles can sustain heat of up to 1,500 degrees centigrade for extended periods of time. In addition the X-31 aircraft were configured with movable forward canards and fixed aft strakes. The canards were small wing-like structures set on the wing line between the nose and the leading edge of the wing. The strakes were set on the same line between the trailing edge of the wing and the engine exhaust. Both supplied additional control in tight maneuvering situations. The X-31 research program produced technical data at high angles of attack. This information is giving engineers and aircraft designers a better understanding of aerodynamics, effectiveness of flight controls and thrust vectoring, and airflow phenomena at high angles of attack. This understanding is expected to lead to design methods that provide better maneuverability in future high performance aircraft and make them safer to fly. An international test organization of about 110 people, managed by the Advanced Research Projects Agency (ARPA), conducted the flight operations at NASA Dryden. The ARPA had requested flight research for the X-31 aircraft be moved there in February 1992. In addition to ARPA and NASA, the international test organization (ITO) included the U.S. Navy, the U.S. Air Force, Rockwell International, the Federal Republic of Germany, and Daimler-Benz Aerospace (formerly Messerschmitt-Bolkow-Blohm and Deutsche Aerospace). NASA was responsible for flight research operations, aircraft maintenance, and research engineering once the program moved to Dryden. The No. 1 X-31 aircraft was lost in an accident January 19, 1995. The pilot, Karl Heinz-Lang, of the Federal Republic of Germany, ejected safely before the aircraft crashed in an unpopulated desert area just north of Edwards. The X-31 program logged an X-plane record of 580 flights during the program, including 555 research missions and 21 in Europe for the 1995 Paris Air Show. A total of 14 pilots representing all agencies of the ITO flew the aircraft. This 32-second clip shows the aircraft at the top of a stall and then thrust vectoring itself around to attain a new heading, thereby allowing the aircraft to gain the advantage over a putative opponent in air-to-air combat. This maneuver is also known as a 'J turn.'

Program for narrow-band analysis of aircraft flyover noise using ensemble averaging techniques

NASA Technical Reports Server (NTRS)

Gridley, D.

1982-01-01

A package of computer programs was developed for analyzing acoustic data from an aircraft flyover. The package assumes the aircraft is flying at constant altitude and constant velocity in a fixed attitude over a linear array of ground microphones. Aircraft position is provided by radar and an option exists for including the effects of the aircraft's rigid-body attitude relative to the flight path. Time synchronization between radar and acoustic recording stations permits ensemble averaging techniques to be applied to the acoustic data thereby increasing the statistical accuracy of the acoustic results. Measured layered meteorological data obtained during the flyovers are used to compute propagation effects through the atmosphere. Final results are narrow-band spectra and directivities corrected for the flight environment to an equivalent static condition at a specified radius.

Technologies for Aircraft Noise Reduction

NASA Technical Reports Server (NTRS)

Huff, Dennis L.

2006-01-01

Technologies for aircraft noise reduction have been developed by NASA over the past 15 years through the Advanced Subsonic Technology (AST) Noise Reduction Program and the Quiet Aircraft Technology (QAT) project. This presentation summarizes highlights from these programs and anticipated noise reduction benefits for communities surrounding airports. Historical progress in noise reduction and technologies available for future aircraft/engine development are identified. Technologies address aircraft/engine components including fans, exhaust nozzles, landing gear, and flap systems. New "chevron" nozzles have been developed and implemented on several aircraft in production today that provide significant jet noise reduction. New engines using Ultra-High Bypass (UHB) ratios are projected to provide about 10 EPNdB (Effective Perceived Noise Level in decibels) engine noise reduction relative to the average fleet that was flying in 1997. Audio files are embedded in the presentation that estimate the sound levels for a 35,000 pound thrust engine for takeoff and approach power conditions. The predictions are based on actual model scale data that was obtained by NASA. Finally, conceptual pictures are shown that look toward future aircraft/propulsion systems that might be used to obtain further noise reduction.

Evaluation of two transport aircraft and several ground test vehicle friction measurements obtained for various runway surface types and conditions. A summary of test results from joint FAA/NASA Runway Friction Program

NASA Technical Reports Server (NTRS)

Yager, Thomas J.; Vogler, William A.; Baldasare, Paul

1990-01-01

Tests with specially instrumented NASA Boeing 737 and 727 aircraft together with several different ground friction measuring devices were conducted for a variety of runway surface types and conditions. These tests are part of joint FAA/NASA Aircraft/Ground Vehicle Runway Friction Program aimed at obtaining a better understanding of aircraft ground handling performance under adverse weather conditions and defining relationships between aircraft and ground vehicle tire friction measurements. Aircraft braking performance on dry, wet, snow and ice-covered runway conditions is discussed as well as ground vehicle friction data obtained under similar runway conditions. For a given contaminated runway surface condition, the correlation between ground vehicles and aircraft friction data is identified. The influence of major test parameters on friction measurements such as speed, test tire characteristics, type and amount of surface contaminant, and ambient temperature are discussed. The effect of surface type on wet friction levels is also evaluated from comparative data collected on grooved and ungrooved concrete and asphalt surfaces.

Application of the generalized reduced gradient method to conceptual aircraft design

NASA Technical Reports Server (NTRS)

Gabriele, G. A.

1984-01-01

The complete aircraft design process can be broken into three phases of increasing depth: conceptual design, preliminary design, and detail design. Conceptual design consists primarily of developing general arrangements and selecting the configuration that optimally satisfies all mission requirements. The result of the conceptual phase is a conceptual baseline configuration that serves as the starting point for the preliminary design phase. The conceptual design of an aircraft involves a complex trade-off of many independent variables that must be investigated before deciding upon the basic configuration. Some of these variables are discrete (number of engines), some represent different configurations (canard vs conventional tail) and some may represent incorporation of new technologies (aluminum vs composite materials). At Lockheed-Georgia, the sizing program is known as GASP (Generalized Aircraft Sizing Program). GASP is a large program containing analysis modules covering the many different disciplines involved fin defining the aricraft, such as aerodynamics, structures, stability and control, mission performance, and cost. These analysis modules provide first-level estimates the aircraft properties that are derived from handbook, experimental, and historical sources.

Automatic Dynamic Aircraft Modeler (ADAM) for the Computer Program NASTRAN

NASA Technical Reports Server (NTRS)

Griffis, H.

1985-01-01

Large general purpose finite element programs require users to develop large quantities of input data. General purpose pre-processors are used to decrease the effort required to develop structural models. Further reduction of effort can be achieved by specific application pre-processors. Automatic Dynamic Aircraft Modeler (ADAM) is one such application specific pre-processor. General purpose pre-processors use points, lines and surfaces to describe geometric shapes. Specifying that ADAM is used only for aircraft structures allows generic structural sections, wing boxes and bodies, to be pre-defined. Hence with only gross dimensions, thicknesses, material properties and pre-defined boundary conditions a complete model of an aircraft can be created.

U.S. aerospace industry opinion of the effect of computer-aided prediction-design technology on future wind-tunnel test requirements for aircraft development programs

NASA Technical Reports Server (NTRS)

Treon, S. L.

1979-01-01

A survey of the U.S. aerospace industry in late 1977 suggests that there will be an increasing use of computer-aided prediction-design technology (CPD Tech) in the aircraft development process but that, overall, only a modest reduction in wind-tunnel test requirements from the current level is expected in the period through 1995. Opinions were received from key spokesmen in 23 of the 26 solicited major companies or corporate divisions involved in the design and manufacture of nonrotary wing aircraft. Development programs for nine types of aircraft related to test phases and wind-tunnel size and speed range were considered.

A knowledge-based system design/information tool for aircraft flight control systems

NASA Technical Reports Server (NTRS)

Mackall, Dale A.; Allen, James G.

1991-01-01

Research aircraft have become increasingly dependent on advanced electronic control systems to accomplish program goals. These aircraft are integrating multiple disciplines to improve performance and satisfy research objective. This integration is being accomplished through electronic control systems. Systems design methods and information management have become essential to program success. The primary objective of the system design/information tool for aircraft flight control is to help transfer flight control system design knowledge to the flight test community. By providing all of the design information and covering multiple disciplines in a structured, graphical manner, flight control systems can more easily be understood by the test engineers. This will provide the engineers with the information needed to thoroughly ground test the system and thereby reduce the likelihood of serious design errors surfacing in flight. The secondary object is to apply structured design techniques to all of the design domains. By using the techniques in the top level system design down through the detailed hardware and software designs, it is hoped that fewer design anomalies will result. The flight test experiences are reviewed of three highly complex, integrated aircraft programs: the X-29 forward swept wing; the advanced fighter technology integration (AFTI) F-16; and the highly maneuverable aircraft technology (HiMAT) program. Significant operating technologies, and the design errors which cause them, is examined to help identify what functions a system design/informatin tool should provide to assist designers in avoiding errors.

Aircrew-aircraft integration: A summary of US Army research programs and plans

NASA Technical Reports Server (NTRS)

Key, D. L.; Aiken, E. W.

1984-01-01

A review of selected programs which illustrate the research efforts of the U.S. Army Aeromechanics Laboratory in the area of aircrew-aircraft integration is presented. Plans for research programs to support the development of future military rotorcraft are also described. The crew of a combat helicopter must, in general, perform two major functions during the conduct of a particular mission: flightpath control and mission management. Accordingly, the research programs described are being conducted in the same two major categories: (1) flightpath control, which encompasses the areas of handling qualities, stability and control, and displays for the pilot's control of the rotorcraft's flightpath, and (2) mission management, which includes human factors and cockpit integration research topics related to performance of navigation, communication, and aircraft systems management tasks.

40 CFR 141.806 - Reporting requirements.

Code of Federal Regulations, 2012 CFR

2012-07-01

... fleet; (ii) Change in status (active or inactive) of any aircraft as an aircraft water system as defined... to or removed from the water system. (iv) Change to whether the aircraft water system can be... Section 141.806 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) WATER PROGRAMS...

40 CFR 141.806 - Reporting requirements.

Code of Federal Regulations, 2011 CFR

2011-07-01

... fleet; (ii) Change in status (active or inactive) of any aircraft as an aircraft water system as defined... to or removed from the water system. (iv) Change to whether the aircraft water system can be... Section 141.806 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) WATER PROGRAMS...

Annual Industrial Capabilities Report to Congress

DTIC Science & Technology

2007-02-01

65 5.1 Aircraft Sector Industrial Summary ................................................................. 65 5.2 Command...industry partners to encourage long-term contractor workforce improvements. Industry segment-level baseline assessments ( aircraft ; command, control...For instance, within aircraft major defense acquisition programs (MDAPs), research, development, test, and evaluation (RDT&E) funding is steadily

14 CFR 35.4 - Instructions for Continued Airworthiness.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: PROPELLERS General § 35.4 Instructions for Continued Airworthiness. The... program exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standard certificate of airworthiness for an aircraft with the propeller...

14 CFR 35.4 - Instructions for Continued Airworthiness.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: PROPELLERS General § 35.4 Instructions for Continued Airworthiness. The... program exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standard certificate of airworthiness for an aircraft with the propeller...

14 CFR 35.4 - Instructions for Continued Airworthiness.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: PROPELLERS General § 35.4 Instructions for Continued Airworthiness. The... program exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standard certificate of airworthiness for an aircraft with the propeller...

14 CFR 35.4 - Instructions for Continued Airworthiness.

Code of Federal Regulations, 2012 CFR

2012-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: PROPELLERS General § 35.4 Instructions for Continued Airworthiness. The... program exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standard certificate of airworthiness for an aircraft with the propeller...

14 CFR 35.4 - Instructions for Continued Airworthiness.

Code of Federal Regulations, 2013 CFR

2013-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: PROPELLERS General § 35.4 Instructions for Continued Airworthiness. The... program exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standard certificate of airworthiness for an aircraft with the propeller...

Rubber airplane: Constraint-based component-modeling for knowledge representation in computer-aided conceptual design

NASA Technical Reports Server (NTRS)

Kolb, Mark A.

1990-01-01

Viewgraphs on Rubber Airplane: Constraint-based Component-Modeling for Knowledge Representation in Computer Aided Conceptual Design are presented. Topics covered include: computer aided design; object oriented programming; airfoil design; surveillance aircraft; commercial aircraft; aircraft design; and launch vehicles.

Advanced prediction technique for the low speed aerodynamics of V/STOL aircraft. Volume 1: Technical discussion

NASA Technical Reports Server (NTRS)

Beatty, T. D.; Worthey, M. K.

1984-01-01

The V/STOL Aircraft Propulsive Effects (VAPE) computerized prediction method is evaluated. The program analyzes viscous effects, various jet, inlet, and Short TakeOff and Landing (STOL) models, and examines the aerodynamic configurations of V/STOL aircraft.

Acoustic loads prediction on jet aircraft

NASA Technical Reports Server (NTRS)

Reddy, N. N.

1992-01-01

A nearfield aircraft noise prediction computer program is presented for the F-22 aircraft. The dominant sources of noise are jet turbulent mixing noise, jet broadband shock noise, and fluctuating pressure under the turbulent boundary layer. All results from this investigation are presented in viewgraph format.

Acoustic loads prediction on jet aircraft

NASA Astrophysics Data System (ADS)

Reddy, N. N.

1992-07-01

A nearfield aircraft noise prediction computer program is presented for the F-22 aircraft. The dominant sources of noise are jet turbulent mixing noise, jet broadband shock noise, and fluctuating pressure under the turbulent boundary layer. All results from this investigation are presented in viewgraph format.

Advanced rotorcraft transmission program

NASA Technical Reports Server (NTRS)

Bill, Robert C.

1990-01-01

The Advanced Rotorcraft Transmission (ART) program is an Army-funded, joint Army/NASA program to develop and demonstrate lightweight, quiet, durable drivetrain systems for next generation rotorcraft. ART addresses the drivetrain requirements of two distinct next generation aircraft classes: Future Air Attack Vehicle, a 10,000 to 20,000 lb. aircraft capable of undertaking tactical support and air-to-air missions; and Advanced Cargo Aircraft, a 60,000 to 80,000 lb. aircraft capable of heavy life field support operations. Both tiltrotor and more conventional helicopter configurations are included in the ART program. Specific objectives of ART include reduction of drivetrain weight by 25 percent compared to baseline state-of-the-art drive systems configured and sized for the next generation aircraft, reduction of noise level at the transmission source by 10 dB relative to a suitably sized and configured baseline, and attainment of at least a 5000 hr mean-time-between-removal. The technical approach for achieving the ART goals includes application of the latest available component, material, and lubrication technology to advanced concept drivetrains that utilize new ideas in gear configuration, transmission layout, and airframe/drivetrain integration. To date, candidate drivetrain systems were carried to a conceptual design stage, and tradeoff studies were conducted resulting in selection of an ART transmission configuration for each of the four contractors. The final selection was based on comparative weight, noise, and reliability studies. A description of each of the selected ART designs is included. Preliminary design of each of the four selected ART transmission was completed, as have mission impact studies wherein comparisons of aircraft mission performance and life cycle costs are undertaken for the next generation aircraft with ART and with the baseline transmission.

MD-11 PCA - View of aircraft on ramp

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 is taxiing to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - Closeup view of aircraft on ramp

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 has taxied to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

Auralization Architectures for NASA?s Next Generation Aircraft Noise Prediction Program

NASA Technical Reports Server (NTRS)

Rizzi, Stephen A.; Lopes, Leonard V.; Burley, Casey L.; Aumann, Aric R.

2013-01-01

Aircraft community noise is a significant concern due to continued growth in air traffic, increasingly stringent environmental goals, and operational limitations imposed by airport authorities. The assessment of human response to noise from future aircraft can only be afforded through laboratory testing using simulated flyover noise. Recent work by the authors demonstrated the ability to auralize predicted flyover noise for a state-of-the-art reference aircraft and a future hybrid wing body aircraft concept. This auralization used source noise predictions from NASA's Aircraft NOise Prediction Program (ANOPP) as input. The results from this process demonstrated that auralization based upon system noise predictions is consistent with, and complementary to, system noise predictions alone. To further develop and validate the auralization process, improvements to the interfaces between the synthesis capability and the system noise tools are required. This paper describes the key elements required for accurate noise synthesis and introduces auralization architectures for use with the next-generation ANOPP (ANOPP2). The architectures are built around a new auralization library and its associated Application Programming Interface (API) that utilize ANOPP2 APIs to access data required for auralization. The architectures are designed to make the process of auralizing flyover noise a common element of system noise prediction.

The development of turbojet aircraft in Germany, Britain, and the United States: A multi-national comparison of aeronautical engineering, 1935--1946

NASA Astrophysics Data System (ADS)

Pavelec, Sterling Michael

In the 1930s aeronautical engineering needed revision. A presumptive anomaly was envisaged as piston-engine aircraft flew higher and faster. Radical alternatives to piston engines were considered in the unending quest for speed. Concurrently, but unwittingly, two turbojet engine programs were undertaken in Europe. The air-breathing three-stage turbojet engine was based on previous turbine technology; the revolutionary idea was the gas turbine as a prime mover for aircraft. In Germany, Dr. Hans von Ohain was the first to complete a flight-worthy turbojet engine for aircraft. Installed in a Heinkel designed aircraft, the Germans began the jet age on 27 August 1939. The Germans led throughout the war and were the first to produce jet aircraft for combat operations. The principal limiting factor for the German jet program was a lack of reliable engines. The continuing myths that Hitler orders, too little fuel, or too few pilots hindered the program are false. In England, Frank Whittle, without substantial support, but with dogged determination, also developed a turbojet engine. The British came second in the jet race when the Whittle engine powered the Gloster Pioneer on 15 May 1941. The Whittle-Gloster relationship continued and produced the only Allied combat jet aircraft during the war, the Meteor, which was confined to Home Defense in Britain. The American turbojet program was built directly from the Whittle engine. General Electric copied the Whittle designs and Bell Aircraft was contracted to build the first American jet plane. The Americans began the jet age on 1 October 1942 with a lackluster performance from their first jet, the Airacomet. But the Americans forged ahead, and had numerous engine and airframe programs in development by the end of the war. But, the Germans did it right and did it first. Partly because of a predisposition towards excellent engineering and physics, partly out of necessity, the Germans were able to produce combat turbojet aircraft during the war. The Allies lagged from a lack of necessity, operational incompatibility, and stringent acceptance requirements. By the end of the war the Germans needed qualitative technological superiority to combat an overwhelming Allied quantitative advantage.

M2-F2 Lifting Body being Carried Aloft by B-52 Mothership

NASA Technical Reports Server (NTRS)

1966-01-01

The M2-F2 Lifting Body is shown here being carried aloft by the Air Force's B-52 (tail number 003) prior to a research launch. The success of Dryden's 'homebuilt' M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies--the M2-F2 and the HL-10, both built by the Northrop Corporation. The 'M' refers to 'manned' and 'F' refers to 'flight' version. 'HL' comes from 'horizontal landing.' The first flight of the M2-F2--which looked much like the 'F1'--was on July 12, 1966. Milt Thompson was the pilot. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During the X-15 and Lifting-Body programs, another B-52, tail number 003, also served as a launch aircraft. During those programs, both B-52s were operated by the Air Force, NASA's partner in both programs. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

ECN-3931

NASA Image and Video Library

1974-01-28

This photograph shows a modified General Dynamics TACT/F-111A Aardvaark with supercritical wings installed. The aircraft, with flaps and landing gear down, is in a decending turn over Rogers Dry Lakebed at Edwards Air Force Base. Starting in 1971 the NASA Flight Research Center and the Air Force undertook a major research and flight testing program, using F-111A (#63-9778), which would span almost 20 years before completion. Intense interest over the results coming from the NASA F-8 supercritical wing program spurred NASA and the Air Force to modify the General Dynamics-Convair F-111A to explore the application of supercritical wing technology to maneuverable military aircraft. This flight program was called Transonic Aircraft Technology (TACT).

Digital autopilots: Design considerations and simulator evaluations

NASA Technical Reports Server (NTRS)

Osder, S.; Neuman, F.; Foster, J.

1971-01-01

The development of a digital autopilot program for a transport aircraft and the evaluation of that system's performance on a transport aircraft simulator is discussed. The digital autopilot includes three axis attitude stabilization, automatic throttle control and flight path guidance functions with emphasis on the mode progression from descent into the terminal area through automatic landing. The study effort involved a sequence of tasks starting with the definition of detailed system block diagrams of control laws followed by a flow charting and programming phase and concluding with performance verification using the transport aircraft simulation. The autopilot control laws were programmed in FORTRAN 4 in order to isolate the design process from requirements peculiar to an individual computer.

Technology needs for high speed rotorcraft (3)

NASA Technical Reports Server (NTRS)

Detore, Jack; Conway, Scott

1991-01-01

The spectrum of vertical takeoff and landing (VTOL) type aircraft is examined to determine which aircraft are most likely to achieve high subsonic cruise speeds and have hover qualities similar to a helicopter. Two civil mission profiles are considered: a 600-n.mi. mission for a 15- and a 30-passenger payload. Applying current technology, only the 15- and 30-passenger tiltfold aircraft are capable of attaining the 450-knot design goal. The two tiltfold aircraft at 450 knots and a 30-passenger tiltrotor at 375 knots were further developed for the Task II technology analysis. A program called High-Speed Total Envelope Proprotor (HI-STEP) is recommended to meet several of these issues based on the tiltrotor concept. A program called Tiltfold System (TFS) is recommended based on the tiltrotor concept. A task is identified to resolve the best design speed from productivity and demand considerations based on the technology that emerges from the recommended programs. HI-STEP's goals are to investigate propulsive efficiency, maneuver loads, and aeroelastic stability. Programs currently in progress that may meet the other technology needs include the Integrated High Performance Turbine Engine Technology (IHPTET) (NASA Lewis) and the Advanced Structural Concepts Program funded through NASA Langley.

Small Aircraft Data Distribution System

NASA Technical Reports Server (NTRS)

Chazanoff, Seth L.; Dinardo, Steven J.

2012-01-01

The CARVE Small Aircraft Data Distribution System acquires the aircraft location and attitude data that is required by the various programs running on a distributed network. This system distributes the data it acquires to the data acquisition programs for inclusion in their data files. It uses UDP (User Datagram Protocol) to broadcast data over a LAN (Local Area Network) to any programs that might have a use for the data. The program is easily adaptable to acquire additional data and log that data to disk. The current version also drives displays using precision pitch and roll information to aid the pilot in maintaining a level-level attitude for radar/radiometer mapping beyond the degree available by flying visually or using a standard gyro-driven attitude indicator. The software is designed to acquire an array of data to help the mission manager make real-time decisions as to the effectiveness of the flight. This data is displayed for the mission manager and broadcast to the other experiments on the aircraft for inclusion in their data files. The program also drives real-time precision pitch and roll displays for the pilot and copilot to aid them in maintaining the desired attitude, when required, during data acquisition on mapping lines.

Cerebriform connective tissue nevus of lumbar.

PubMed

Chen, Jinbo; Chen, Liuqing; Duan, Yiqun; Li, Dongsheng; Dong, Bilin

2015-02-01

Connective tissue nevi represents a kind of hamartoma, and coalescence of the lesions in a cerebriform mode in the lumbar region without Proteus syndrome is rarely seen. Here, we report a 26-year-old woman presenting with nodules and plaques in her left lumbar region of 26 years in duration. Histopathological examination and Masson-trichrome stain showed increased dermal collagen bundles in a haphazard array. The diagnosis of connective tissue nevi was made. This is the first case report on cerebriform connective tissue nevi without Proteus syndrome in the lumbar region. © 2014 Japanese Dermatological Association.

Proteus syndrome: A rare cause of gigantic limb.

PubMed

Chakrabarti, Nandini; Chattopadhyay, Chandan; Bhuban, Majhi; Pal, Salil Kumar

2014-04-01

A congenital disorder with variable manifestations, including partial gigantism of the hands and feet with hypertrophy of soles, nevi, hemihypertrophy, gynecomastia, macrocephaly and other skull abnormalities, and abdominal lipomatosis. The cause is unknown, although a genetic origin, generally of autosomal-dominant transmission, has been conjectured. Symptoms can be treated, but there is no known cure. We present the case of a young male with grotesque overgrowth of the right lower limb, splenomegaly and multiple nevi. Angiography revealed venous malformation within the limb. The findings are in conformity to the criteria for the Proteus syndrome.

Collective motion in Proteus mirabilis swarms

NASA Astrophysics Data System (ADS)

Haoran, Xu

Proteus mirabilisis a Gram-negative, rod-shaped bacterium. It is widely distributed in soil and water, and it is well known for exhibiting swarming motility on nutrient agar surfaces. In our study, we focused on the collective motility of P. mirabilis and uncovered a range of interesting phenomena. Here we will present our efforts to understand these phenomena through experiments and simulation. Mailing address: Room 306 Science Centre North Block, The Chinese University of Hong Kong, Shatin, N.T. Hong Kong SAR. Phone: +852-3943-6354. Fax: +852-2603-5204. E-mail:xhrphx@gmail.com.

A Model for a Single Unmanned Aircraft Systems (UAS) Program Office Managing Joint ISR Capabilities

DTIC Science & Technology

2017-10-01

reduction in manning from the multiple program office structure to the new single program management model. Additional information regarding this...OFFICE MANAGING JOINT ISR CAPABILITIES by Angela E. Burris A Research Report Submitted to the Faculty In Partial Fulfillment of...research paper is to answer how a single management office could provide greater agility for unmanned aircraft systems (UAS); supporting Joint concepts

Automated predesign of aircraft

NASA Technical Reports Server (NTRS)

Poe, C. C., Jr.; Kruse, G. S.; Tanner, C. J.; Wilson, P. J.

1978-01-01

Program uses multistation structural-synthesis to size and design box-beam structures for transport aircraft. Program optimizes static strength and scales up to satisfy fatigue and fracture criteria. It has multimaterial capability and library of materials properties, including advanced composites. Program can be used to evaluate impact on weight of variables such as materials, types of construction, structural configurations, minimum gage limits, applied loads, fatigue lives, crack-growth lives, initial crack sizes, and residual strengths.

An overview of the Douglas Aircraft Company Aeroelastic Design Optimization Program (ADOP)

NASA Technical Reports Server (NTRS)

Dodd, Alan J.

1989-01-01

From a program manager's viewpoint, the history, scope and architecture of a major structural design program at Douglas Aircraft Company called Aeroelastic Design Optimization Program (ADOP) are described. ADOP was originally intended for the rapid, accurate, cost-effective evaluation of relatively small structural models at the advanced design level, resulting in improved proposal competitiveness and avoiding many costly changes later in the design cycle. Before release of the initial version in November 1987, however, the program was expanded to handle very large production-type analyses.

Aircraft cockpit vision: Math model

NASA Technical Reports Server (NTRS)

Bashir, J.; Singh, R. P.

1975-01-01

A mathematical model was developed to describe the field of vision of a pilot seated in an aircraft. Given the position and orientation of the aircraft, along with the geometrical configuration of its windows, and the location of an object, the model determines whether the object would be within the pilot's external vision envelope provided by the aircraft's windows. The computer program using this model was implemented and is described.

Applications of advanced V/STOL aircraft concepts to civil utility missions. Volume 2: Appendices

NASA Technical Reports Server (NTRS)

1977-01-01

The linear performance definition curves for the lift fan aircraft, tilt rotor aircraft, and advanced helicopter are given. The computer program written to perform the mission analysis for this study is also documented, and examples of its use are shown. Methods used to derive the performance coefficients for use in the mission analysis of the lift fan aircraft are described.

Concurrent airline fleet allocation and aircraft design with profit modeling for multiple airlines

NASA Astrophysics Data System (ADS)

Govindaraju, Parithi

A "System of Systems" (SoS) approach is particularly beneficial in analyzing complex large scale systems comprised of numerous independent systems -- each capable of independent operations in their own right -- that when brought in conjunction offer capabilities and performance beyond the constituents of the individual systems. The variable resource allocation problem is a type of SoS problem, which includes the allocation of "yet-to-be-designed" systems in addition to existing resources and systems. The methodology presented here expands upon earlier work that demonstrated a decomposition approach that sought to simultaneously design a new aircraft and allocate this new aircraft along with existing aircraft in an effort to meet passenger demand at minimum fleet level operating cost for a single airline. The result of this describes important characteristics of the new aircraft. The ticket price model developed and implemented here enables analysis of the system using profit maximization studies instead of cost minimization. A multiobjective problem formulation has been implemented to determine characteristics of a new aircraft that maximizes the profit of multiple airlines to recognize the fact that aircraft manufacturers sell their aircraft to multiple customers and seldom design aircraft customized to a single airline's operations. The route network characteristics of two simple airlines serve as the example problem for the initial studies. The resulting problem formulation is a mixed-integer nonlinear programming problem, which is typically difficult to solve. A sequential decomposition strategy is applied as a solution methodology by segregating the allocation (integer programming) and aircraft design (non-linear programming) subspaces. After solving a simple problem considering two airlines, the decomposition approach is then applied to two larger airline route networks representing actual airline operations in the year 2005. The decomposition strategy serves as a promising technique for future detailed analyses. Results from the profit maximization studies favor a smaller aircraft in terms of passenger capacity due to its higher yield generation capability on shorter routes while results from the cost minimization studies favor a larger aircraft due to its lower direct operating cost per seat mile.

Technology for aircraft energy efficiency

NASA Technical Reports Server (NTRS)

Klineberg, J. M.

1977-01-01

Six technology programs for reducing fuel use in U.S. commercial aviation are discussed. The six NASA programs are divided into three groups: Propulsion - engine component improvement, energy efficient engine, advanced turboprops; Aerodynamics - energy efficient transport, laminar flow control; and Structures - composite primary structures. Schedules, phases, and applications of these programs are considered, and it is suggested that program results will be applied to current transport derivatives in the early 1980s and to all-new aircraft of the late 1980s and early 1990s.

User's manual for LINEAR, a FORTRAN program to derive linear aircraft models

NASA Technical Reports Server (NTRS)

Duke, Eugene L.; Patterson, Brian P.; Antoniewicz, Robert F.

1987-01-01

This report documents a FORTRAN program that provides a powerful and flexible tool for the linearization of aircraft models. The program LINEAR numerically determines a linear system model using nonlinear equations of motion and a user-supplied nonlinear aerodynamic model. The system model determined by LINEAR consists of matrices for both state and observation equations. The program has been designed to allow easy selection and definition of the state, control, and observation variables to be used in a particular model.

Design definition study of NASA/Navy lift/cruise fan V/STOL aircraft. Volume 1: Summary report of Navy multimission aircraft

NASA Technical Reports Server (NTRS)

Cavage, R. L.

1975-01-01

Results are presented of a study of lift-cruise fan V/STOL aircraft for the 1980-1985 time period. Technical and operating characteristics and technology requirements for the ultimate development of this type aircraft are identified. Aircraft individually optimized to perform the antisubmarine warfare, carrier onboard delivery, combat search and rescue, and surveillance and surface attack missions are considered along with a multi-purpose aircraft concept capable of performing all five missions at minimum total program cost. It is shown that lighter and smaller aircraft could be obtained by optimizing the design and fan selection for specific missions.

14 CFR 43.15 - Additional performance rules for inspections.

Code of Federal Regulations, 2010 CFR

2010-01-01

... TRANSPORTATION AIRCRAFT MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION § 43.15 Additional..., or 135 of this chapter, shall— (1) Perform the inspection so as to determine whether the aircraft, or... accordance with the instructions and procedures set forth in the inspection program for the aircraft being...

14 CFR 43.15 - Additional performance rules for inspections.

Code of Federal Regulations, 2013 CFR

2013-01-01

... TRANSPORTATION AIRCRAFT MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION § 43.15 Additional..., or 135 of this chapter, shall— (1) Perform the inspection so as to determine whether the aircraft, or... accordance with the instructions and procedures set forth in the inspection program for the aircraft being...

14 CFR 91.1015 - Management specifications.

Code of Federal Regulations, 2011 CFR

2011-01-01

... of all fractional owners and types of aircraft, registration markings and serial numbers; (2) The... other procedures under which each class and size of aircraft is to be operated; (4) Authorization for an inspection program approved under § 91.1109, including the type of aircraft, the registration markings and...

14 CFR 91.1015 - Management specifications.

Code of Federal Regulations, 2012 CFR

2012-01-01

... of all fractional owners and types of aircraft, registration markings and serial numbers; (2) The... other procedures under which each class and size of aircraft is to be operated; (4) Authorization for an inspection program approved under § 91.1109, including the type of aircraft, the registration markings and...

14 CFR 43.15 - Additional performance rules for inspections.

Code of Federal Regulations, 2011 CFR

2011-01-01

... TRANSPORTATION AIRCRAFT MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION § 43.15 Additional..., or 135 of this chapter, shall— (1) Perform the inspection so as to determine whether the aircraft, or... accordance with the instructions and procedures set forth in the inspection program for the aircraft being...

14 CFR 91.1015 - Management specifications.

Code of Federal Regulations, 2013 CFR

2013-01-01

... of all fractional owners and types of aircraft, registration markings and serial numbers; (2) The... other procedures under which each class and size of aircraft is to be operated; (4) Authorization for an inspection program approved under § 91.1109, including the type of aircraft, the registration markings and...

14 CFR 43.15 - Additional performance rules for inspections.

Code of Federal Regulations, 2014 CFR

2014-01-01

... TRANSPORTATION AIRCRAFT MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION § 43.15 Additional..., or 135 of this chapter, shall— (1) Perform the inspection so as to determine whether the aircraft, or... accordance with the instructions and procedures set forth in the inspection program for the aircraft being...

14 CFR 91.1015 - Management specifications.

Code of Federal Regulations, 2014 CFR

2014-01-01

... of all fractional owners and types of aircraft, registration markings and serial numbers; (2) The... other procedures under which each class and size of aircraft is to be operated; (4) Authorization for an inspection program approved under § 91.1109, including the type of aircraft, the registration markings and...

14 CFR 43.15 - Additional performance rules for inspections.

Code of Federal Regulations, 2012 CFR

2012-01-01

... TRANSPORTATION AIRCRAFT MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND ALTERATION § 43.15 Additional..., or 135 of this chapter, shall— (1) Perform the inspection so as to determine whether the aircraft, or... accordance with the instructions and procedures set forth in the inspection program for the aircraft being...

40 CFR 87.89 - Compliance with smoke emission standards.

Code of Federal Regulations, 2011 CFR

2011-07-01

... PROGRAMS (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Smoke Emissions (Aircraft Gas Turbine Engines) § 87.89 Compliance with smoke emission standards... engine of the model being tested. An acceptable alternative to testing every engine is described in...

40 CFR 87.89 - Compliance with smoke emission standards.

Code of Federal Regulations, 2010 CFR

2010-07-01

... PROGRAMS (CONTINUED) CONTROL OF AIR POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES Test Procedures for Engine Smoke Emissions (Aircraft Gas Turbine Engines) § 87.89 Compliance with smoke emission standards... engine of the model being tested. An acceptable alternative to testing every engine is described in...

Preliminary sizing and performance of aircraft

NASA Technical Reports Server (NTRS)

Fetterman, D. E., Jr.

1985-01-01

The basic processes of a program that performs sizing operations on a baseline aircraft and determines their subsequent effects on aerodynamics, propulsion, weights, and mission performance are described. Input requirements are defined and output listings explained. Results obtained by applying the method to several types of aircraft are discussed.

Pathfinder aircraft in flight

NASA Image and Video Library

1995-07-27

The Pathfinder research aircraft's wing structure was clearly defined as it soared under a clear blue sky during a test flight July 27, 1995, from Dryden Flight Research Center, Edwards, California. The center section and outer wing panels of the aircraft had ribs constructed of thin plastic foam, while the ribs in the inner wing panels are fabricated from lightweight composite material. Developed by AeroVironment, Inc., the Pathfinder was one of several unmanned aircraft being evaluated under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) program.

Aircraft Rollout Iterative Energy Simulation

NASA Technical Reports Server (NTRS)

Kinoshita, L.

1986-01-01

Aircraft Rollout Iterative Energy Simulation (ARIES) program analyzes aircraft-brake performance during rollout. Simulates threedegree-of-freedom rollout after nose-gear touchdown. Amount of brake energy dissipated during aircraft landing determines life expectancy of brake pads. ARIES incorporates brake pressure, actual flight data, crosswinds, and runway characteristics to calculate following: brake energy during rollout for up to four independent brake systems; time profiles of rollout distance, velocity, deceleration, and lateral runway position; and all aerodynamic moments on aircraft. ARIES written in FORTRAN 77 for batch execution.

[Tail Plane Icing

NASA Technical Reports Server (NTRS)

1997-01-01

The Aviation Safety Program initiated by NASA in 1997 has put greater emphasis in safety related research activities. Ice-contaminated-tailplane stall (ICTS) has been identified by the NASA Lewis Icing Technology Branch as an important activity for aircraft safety related research. The ICTS phenomenon is characterized as a sudden, often uncontrollable aircraft nose- down pitching moment, which occurs due to increased angle-of-attack of the horizontal tailplane resulting in tailplane stall. Typically, this phenomenon occurs when lowering the flaps during final approach while operating in or recently departing from icing conditions. Ice formation on the tailplane leading edge can reduce tailplane angle-of-attack range and cause flow separation resulting in a significant reduction or complete loss of aircraft pitch control. In 1993, the Federal Aviation Authority (FAA) and NASA embarked upon a four-year research program to address the problem of tailplane stall and to quantify the effect of tailplane ice accretion on aircraft performance and handling characteristics. The goals of this program, which was completed in March 1998, were to collect aerodynamic data for an aircraft tail with and without ice contamination and to develop analytical methods for predicting the effects of tailplane ice contamination. Extensive dry air and icing tunnel tests which resulted in a database of the aerodynamic effects associated with tailplane ice contamination. Although the FAA/NASA tailplane icing program generated some answers regarding ice-contaminated-tailplane stall (ICTS) phenomena, NASA researchers have found many open questions that warrant further investigation into ICTS. In addition, several aircraft manufacturers have expressed interest in a second research program to expand the database to other tail configurations and to develop experimental and computational methodologies for evaluating the ICTS phenomenon. In 1998, the icing branch at NASA Lewis initiated a second multi-phase research program for tailplane icing (TIP II) to develop test methodologies and tailplane performance and handling qualities evaluation tools. The main objectives of this new NASA/Industry/Academia collaborative research programs were: (1) define and evaluate a sub-scale wind tunnel test methodology for determining tailplane performance degradation due to icing. (2) develop an experimental database of tailplane aerodynamic performance with and without ice contamination for a range of tailplane configurations. Wind tunnel tests were planned with representative general aviation aircraft, i.e., the Learjet 45, and a twin engine low speed aircraft. This report summarizes the research performed during the first year of the study, and outlines the work tasks for the second year.

Cost-efficient manufacturing of composite structures

NASA Technical Reports Server (NTRS)

Freeman, W. Tom; Davis, John G.; Johnston, Norman J.

1991-01-01

The Advanced Composites Technology (ACT) program is seeking research breakthroughs that will allow structures made of graphite epoxy materials to replace metals in the wings and fuselages of future aircrafts. NASA's goals are to reduce acquisition cost by 20 to 25 percent, structural weight for a resized aircraft by 40 to 50 percent, and the number of parts by half compared to current production aluminum aircraft. The innovative structural concepts, materials, and fabrication techniques emerging from the ACT program are described, and the relationship between aerospace developments and industrial, commercial, and sporting goods applications are discussed.

An Analysis of the Cost-Volume Relationships within the Aircraft Program of the Naval Air Rework Facility, Alameda, California.

DTIC Science & Technology

1986-06-01

INDIVIDUAL 22b TELEPHONE (include Area Code) 22c, OFFIcE YMBOI1. Thu . Lao(403) 646-255 1 o e DO FORM 1473,84 MAR 83 APR edition ray be used until...schedules are produced using projected direct labors hours available and established labor hour norms per aircraft. Since the actual workload is...and segment costs. (3) Use break-even analysis to compare revenues and costs and to evaluate relative profitability of the four aircraft program

Aircraft noise prediction program user's manual

NASA Technical Reports Server (NTRS)

Gillian, R. E.

1982-01-01

The Aircraft Noise Prediction Program (ANOPP) predicts aircraft noise with the best methods available. This manual is designed to give the user an understanding of the capabilities of ANOPP and to show how to formulate problems and obtain solutions by using these capabilities. Sections within the manual document basic ANOPP concepts, ANOPP usage, ANOPP functional modules, ANOPP control statement procedure library, and ANOPP permanent data base. appendixes to the manual include information on preparing job decks for the operating systems in use, error diagnostics and recovery techniques, and a glossary of ANOPP terms.

Long range view of materials research for civil transport aircraft

NASA Technical Reports Server (NTRS)

Ardema, M. D.; Waters, M. H.

1974-01-01

The impact of various material technology advancements on the economics of civil transport aircraft is investigated. Benefits of advances in both airframe and engine materials are considered. Benefits are measured primarily by improvements in return on investment for an operator. Materials research and development programs which lead to the greatest benefits are assessed with regards to cost, risk, and commonality with other programs. Emphasis of the paper is on advanced technology subsonic/transonic transports (ATT type aircraft) since these are likely to be the next generation of commercial transports.

Long range view of materials research for civil transport aircraft

NASA Technical Reports Server (NTRS)

Ardema, M. D.; Waters, M. H.

1973-01-01

The impact of various material technology advancements on the economics of civil transport aircraft is investigated. Benefits of advances in both airframe and engine materials are considered. Benefits are measured primarily by improvements in return on investment for an operator. Materials research and development programs which lead to the greatest benefits are assessed with regards to cost, risk, and commonality with other programs. Emphasis of the paper is on advanced technology subsonic/transonic transports (ATT type aircraft) since these are likely to be the next generation of commercial transports.

Aircraft engine pollution reduction

NASA Technical Reports Server (NTRS)

Rudey, R. A.

1972-01-01

The effect of engine operation on the types and levels of the major aircraft engine pollutants is described and the major factors governing the formation of these pollutants during the burning of hydrocarbon fuel are discussed. Methods which are being explored to reduce these pollutants are discussed and their application to several experimental research programs are pointed out. Results showing significant reductions in the levels of carbon monoxide, unburned hydrocarbons, and oxides of nitrogen obtained from experimental combustion research programs are presented and discussed to point out potential application to aircraft engines.

High heat flux actively cooled honeycomb sandwich structural panel for a hypersonic aircraft

NASA Technical Reports Server (NTRS)

Koch, L. C.; Pagel, L. L.

1978-01-01

The results of a program to design and fabricate an unshielded actively cooled structural panel for a hypersonic aircraft are presented. The design is an all-aluminum honeycomb sandwich with embedded cooling passages soldered to the inside of the outer moldline skin. The overall finding is that an actively cooled structure appears feasible for application on a hypersonic aircraft, but the fabrication process is complex and some material and manufacturing technology developments are required. Results from the program are summarized and supporting details are presented.

76 FR 60459 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-29

... Consideration for Purchase: continuation of a pilot training program and logistics support for F-16 aircraft at... program and logistics support for F-16 aircraft at Luke Air Force Base, Arizona to include flight training..., which will contribute to an acceptable military balance in the area. This proposed sale is consistent...

JSC reduced gravity program and 1992 highlights

NASA Technical Reports Server (NTRS)

Williams, R. K.; Billica, L. W.

1993-01-01

A review is presented of the aircraft parabolic flight program in the U.S. including the USAF and NASA participation from 1957 to the present. The parabolic flight profile to achieve microgravity levels and intermediate g-levels is discussed. The NASA reduced gravity aircraft is described including the service provisions for this reimbursable project.

An acceptable role for computers in the aircraft design process

NASA Technical Reports Server (NTRS)

Gregory, T. J.; Roberts, L.

1980-01-01

Some of the reasons why the computerization trend is not wholly accepted are explored for two typical cases: computer use in the technical specialties and computer use in aircraft synthesis. The factors that limit acceptance are traced in part, to the large resources needed to understand the details of computer programs, the inability to include measured data as input to many of the theoretical programs, and the presentation of final results without supporting intermediate answers. Other factors are due solely to technical issues such as limited detail in aircraft synthesis and major simplifying assumptions in the technical specialties. These factors and others can be influenced by the technical specialist and aircraft designer. Some of these factors may become less significant as the computerization process evolves, but some issues, such as understanding large integrated systems, may remain issues in the future. Suggestions for improved acceptance include publishing computer programs so that they may be reviewed, edited, and read. Other mechanisms include extensive modularization of programs and ways to include measured information as part of the input to theoretical approaches.

Dynamic Structural Fault Detection and Identification

NASA Technical Reports Server (NTRS)

Smith, Timothy; Reichenbach, Eric; Urnes, James M.

2009-01-01

Aircraft structures are designed to guarantee safety of flight in some required operational envelope. When the aircraft becomes structurally impaired, safety of flight may not be guaranteed within that previously safe operational envelope. In this case the safe operational envelope must be redefined in-flight and a means to prevent excursion from this new envelope must be implemented. A specific structural failure mode that may result in a reduced safe operating envelope, the exceedance of which could lead to catastrophic structural failure of the aircraft, will be addressed. The goal of the DFEAP program is the detection of this failure mode coupled with flight controls adaptation to limit critical loads in the damaged aircraft structure. The DFEAP program is working with an F/A-18 aircraft model. The composite wing skins are bonded to metallic spars in the wing substructure. Over time, it is possible that this bonding can deteriorate due to fatigue. In this case, the ability of the wing spar to transfer loading between the wing skins is reduced. This failure mode can translate to a reduced allowable compressive strain on the wing skin and could lead to catastrophic wing buckling if load limiting of the wing structure is not applied. The DFEAP program will make use of a simplified wing strain model for the healthy aircraft. The outputs of this model will be compared in real-time to onboard strain measurements at several locations on the aircraft wing. A damage condition is declared at a given location when the strain measurements differ sufficiently from the strain model. Parameter identification of the damaged structure wing strain parameters will be employed to provide load limiting control adaptation for the aircraft. This paper will discuss the simplified strain models used in the implementation and their interaction with the strain sensor measurements. Also discussed will be the damage detection and identification schemes employed and the means by which the damaged aircraft parameters will be used to provide load limiting that keeps the aircraft within the safe operational envelope.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 transport aircraft approaches its first landing under engine power only on Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 approaches the first landing ever of a transport aircraft under engine power only on Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when it normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

Propulsion integration for military aircraft

NASA Technical Reports Server (NTRS)

Henderson, William P.

1989-01-01

The transonic aerodynamic characteristics for high-performance aircraft are significantly affected by shock-induced flow interactions as well as other local flow interference effects which usually occur at transonic speeds. These adverse interactions can not only cause high drag, but can cause unusual aerodynamic loadings and/or severe stability and control problems. Many new programs are underway to develop methods for reducing the adverse effects, as well as to develop an understanding of the basic flow conditions which are the primary contributors. It is anticipated that these new programs will result in technologies which can reduce the aircraft cruise drag through improved integration as well as increased aircraft maneuverability throughh the application of thrust vectoring. This paper will identify some of the primary propulsion integration problems for high performance aircraft at transonic speeds, and demonstrate several methods for reducing or eliminating the undesirable characteristics, while enhancing configuration effectiveness.

Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration. Volume 2; Bibliography Appendices

NASA Technical Reports Server (NTRS)

Hodge, Kenneth E. (Compiler); Kellogg, Yvonne (Editor)

1996-01-01

A technical symposium, aircraft display dedication, and pilots' panel discussion were held on May 27, 1992. to commemorate the 20th anniversary of the first flights of the F-8 Digital Fly-By-Wire (DFBW) and Supercritical Wing (SCW) research aircraft. The symposium featured technical presentations by former key government and industry participants in the advocacy, design, aircraft modification, and flight research program activities. The DFBW and SCW technical contributions are cited. A dedication ceremony marked permanent display of both program aircraft. The panel discussion participants included eight of the eighteen research and test pilots who flew these experimental aircraft. Pilots' remarks include descriptions of their most memorable flight experiences. The report also includes a survey of the Gulf Air War, an after-dinner presentation by noted aerospace author and historian Dr. Richard Hallion.

Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration. Volume 1

NASA Technical Reports Server (NTRS)

Hodge, Kenneth E. (Compiler)

1996-01-01

A technical symposium, aircraft display dedication, and pilots' panel discussion were held on May 27, 1992, to commemorate the 20th anniversary of the first flights of the F-8 Digital Fly-By-Wire (DFBW) and Supercrit- ical Wing (SCW) research aircraft. The symposium featured technical presentations by former key government and industry participants in the advocacy, design, aircraft modification, and flight research program activities. The DFBW and SCW technical contributions are cited. A dedication ceremony marked permanent display of both program aircraft. The panel discussion participants included eight of the eighteen research and test pilots who flew these experimental aircraft. Pilots' remarks include descriptions of their most memorable flight experiences The report also includes a survey of the Gulf Air War, and an after-dinner presentation by noted aerospace author and historian Dr. Richard Hallion.

Factors affecting measured aircraft sound levels in the vicinity of start-of-takeoff roll

NASA Astrophysics Data System (ADS)

Richard, Horonjeff; Fleming, Gregg G.; Rickley, Edward J.; Connor, Thomas L.

This paper presents the findings of a recently conducted measurement and analysis program of jet transport aircraft sound levels in the vicinity of the star-of-takeoff roll. The purpose of the program was two-fold: (1) to evaluate the computational accuracy of the Federal Aviation Administration's Integrated Noise Model (INM) in the vicinity of start-of-takeoff roll with a recently updated database (INM 3.10), and (2) to provide guidance for future model improvements. Focusing on the second of these two goals, this paper examines several factors affecting Sound Exposure Levels (SELs) in the hemicircular area behind the aircraft brake release point at the start-of-takeoff. In addition to the aircraft type itself, these factors included the geometric relationship of the measurement site to the runway, the wind velocity (speed and direction), aircraft grow weight, and start-of-roll mode (static or rolling start).

Aircraft operability methods applied to space launch vehicles

NASA Astrophysics Data System (ADS)

Young, Douglas

1997-01-01

The commercial space launch market requirement for low vehicle operations costs necessitates the application of methods and technologies developed and proven for complex aircraft systems. The ``building in'' of reliability and maintainability, which is applied extensively in the aircraft industry, has yet to be applied to the maximum extent possible on launch vehicles. Use of vehicle system and structural health monitoring, automated ground systems and diagnostic design methods derived from aircraft applications support the goal of achieving low cost launch vehicle operations. Transforming these operability techniques to space applications where diagnostic effectiveness has significantly different metrics is critical to the success of future launch systems. These concepts will be discussed with reference to broad launch vehicle applicability. Lessons learned and techniques used in the adaptation of these methods will be outlined drawing from recent aircraft programs and implementation on phase 1 of the X-33/RLV technology development program.

Report of the Task Group on the Department of Energy Aviation Program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1992-02-01

The Department of Energy (DOE) owns or leases approximately 43 aircraft of which 17 are airplanes and 26 are helicopters. About two-thirds of these aircraft are used for activities related to defense programs; these are all government owned and contractor operated. The other third of DOE's aircraft is used by Bonneville Power Administration (BPA) and Western Area Power Administration (WAPA). These aircraft are primarily government owned and operated. In addition to transporting passengers, DOE aircraft are used for security operations, powerline and pipeline patrols, research and development activities, and aerial measurement and for the transport of hazardous materials. These operationsmore » are conducted at nine Field Offices under the organizational authority of eight DOE Program Secretarial Officers (PSOs). On July 24, 1991, a DOE-owned helicopter crashed at the Nevada Test Site resulting in the deaths of the five contractor employees on board. A DOE accident investigation board was convened, and an investigation into the causes of the crash was conducted. On November 19, 1991, a briefing of the preliminary results of the investigation was provided to the Assistant Secretary for Environment, Safety and Health (EH), the Assistant Secretary for Defense Programs (DP), and the Director, Office of Security Affairs (SA). On November 27, 1991, the Secretary of Energy directed the Assistant Secretary, EH, to convene and chair a Task Group with the PSOs to define the roles and responsibilities of DOE's aviation program. Task group recommendations are presented.« less

Report of the Task Group on the Department of Energy Aviation Program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1992-02-01

The Department of Energy (DOE) owns or leases approximately 43 aircraft of which 17 are airplanes and 26 are helicopters. About two-thirds of these aircraft are used for activities related to defense programs; these are all government owned and contractor operated. The other third of DOE`s aircraft is used by Bonneville Power Administration (BPA) and Western Area Power Administration (WAPA). These aircraft are primarily government owned and operated. In addition to transporting passengers, DOE aircraft are used for security operations, powerline and pipeline patrols, research and development activities, and aerial measurement and for the transport of hazardous materials. These operationsmore » are conducted at nine Field Offices under the organizational authority of eight DOE Program Secretarial Officers (PSOs). On July 24, 1991, a DOE-owned helicopter crashed at the Nevada Test Site resulting in the deaths of the five contractor employees on board. A DOE accident investigation board was convened, and an investigation into the causes of the crash was conducted. On November 19, 1991, a briefing of the preliminary results of the investigation was provided to the Assistant Secretary for Environment, Safety and Health (EH), the Assistant Secretary for Defense Programs (DP), and the Director, Office of Security Affairs (SA). On November 27, 1991, the Secretary of Energy directed the Assistant Secretary, EH, to convene and chair a Task Group with the PSOs to define the roles and responsibilities of DOE`s aviation program. Task group recommendations are presented.« less

Atmospheric electrical modeling in support of the NASA F106 Storm Hazards Project

NASA Technical Reports Server (NTRS)

Helsdon, J. H.

1986-01-01

With the use of composite (non-metallic) and microelectronics becoming more prevalent in the construction of both military and commercial aircraft, the control systems have become more susceptible to damage or failure from electromagnetic transients. One source of such transients is the lightning discharge. In order to study the effects of the lightning discharge on the vital components of an aircraft, NASA Langley Research Center has undertaken a Storm Hazards Program in which a specially instrumented F106B jet aircraft is flown into active thunderstorms with the intention of being struck by lightning. One of the specific purposes of the program is to quantify the environmental conditions which are conductive to aircraft lightning strikes.

Aircraft Engine Technology for Green Aviation to Reduce Fuel Burn

NASA Technical Reports Server (NTRS)

Hughes, Christopher E.; VanZante, Dale E.; Heidmann, James D.

2013-01-01

The NASA Fundamental Aeronautics Program Subsonic Fixed Wing Project and Integrated Systems Research Program Environmentally Responsible Aviation Project in the Aeronautics Research Mission Directorate are conducting research on advanced aircraft technology to address the environmental goals of reducing fuel burn, noise and NOx emissions for aircraft in 2020 and beyond. Both Projects, in collaborative partnerships with U.S. Industry, Academia, and other Government Agencies, have made significant progress toward reaching the N+2 (2020) and N+3 (beyond 2025) installed fuel burn goals by fundamental aircraft engine technology development, subscale component experimental investigations, full scale integrated systems validation testing, and development validation of state of the art computation design and analysis codes. Specific areas of propulsion technology research are discussed and progress to date.

14 CFR 91.1087 - Approval of aircraft simulators and other training devices.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Approval of aircraft simulators and other... OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Fractional Ownership Operations Program Management § 91.1087 Approval of aircraft simulators and...

14 CFR 91.1087 - Approval of aircraft simulators and other training devices.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Approval of aircraft simulators and other... OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Fractional Ownership Operations Program Management § 91.1087 Approval of aircraft simulators and...

14 CFR 91.1087 - Approval of aircraft simulators and other training devices.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Approval of aircraft simulators and other... OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Fractional Ownership Operations Program Management § 91.1087 Approval of aircraft simulators and...

14 CFR 91.1087 - Approval of aircraft simulators and other training devices.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Approval of aircraft simulators and other... OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Fractional Ownership Operations Program Management § 91.1087 Approval of aircraft simulators and...

Energy efficient engine flight propulsion system: Aircraft/engine integration evaluation

NASA Technical Reports Server (NTRS)

Patt, R. F.

1980-01-01

Results of aircraft/engine integration studies conducted on an advanced flight propulsion system are reported. Economic evaluations of the preliminary design are included and indicate that program goals will be met. Installed sfc, DOC, noise, and emissions were evaluated. Aircraft installation considerations and growth were reviewed.

Energy efficient engine flight propulsion system: Aircraft/engine integration evaluation

DOE Office of Scientific and Technical Information (OSTI.GOV)

Patt, R.F.

Results of aircraft/engine integration studies conducted on an advanced flight propulsion system are reported. Economic evaluations of the preliminary design are included and indicate that program goals will be met. Installed sfc, DOC, noise, and emissions were evaluated. Aircraft installation considerations and growth were reviewed.

Development of an intervention program to encourage shoulder harness use and aircraft retrofit in general aviation aircraft : phases I and II.

DOT National Transportation Integrated Search

1995-01-01

This report describes a study of shoulder harness installation and use rates in general aviation aircraft. Observations were made at six geographically separate areas to determine estimates of current installation and use rates. An expert panel was e...

Perspectives on Highly Adaptive or Morphing Aircraft

NASA Technical Reports Server (NTRS)

McGowan, Anna-Maria R.; Vicroy, Dan D.; Busan, Ronald C.; Hahn, Andrew S.

2009-01-01

The ability to adapt to different flight conditions has been fundamental to aircraft design since the Wright Brothers first flight. Over a hundred years later, unconventional aircraft adaptability, often called aircraft morphing has become a topic of considerable renewed interest. In the past two decades, this interest has been largely fuelled by advancements in multi-functional or smart materials and structures. However, highly adaptive or morphing aircraft is certainly a cross-discipline challenge that stimulates a wide range of design possibilities. This paper will review some of the history of morphing aircraft including recent research programs and discuss some perspectives on this work.

Investigations of simulated aircraft flight through thunderstorm outflows

NASA Technical Reports Server (NTRS)

Frost, W.; Crosby, B.

1978-01-01

The effects of wind shear on aircraft flying through thunderstorm gust fronts were investigated. A computer program was developed to solve the two dimensional, nonlinear equations of aircraft motion, including wind shear. The procedure described and documented accounts for spatial and temporal variations of the aircraft within the flow regime. Analysis of flight paths and control inputs necessary to maintain specified trajectories for aircraft having characteristics of DC-8, B-747, augmentor wing STOL, and DHC-6 aircraft was recorded. From the analysis an attempt was made to find criteria for reduction of the hazards associated with landing through thunderstorm gust fronts.

Initial Comparison of Direct and Legacy Modeling Approaches for Radial Core Expansion Analysis

DOE Office of Scientific and Technical Information (OSTI.GOV)

Shemon, Emily R.

2016-10-10

Radial core expansion in sodium-cooled fast reactors provides an important reactivity feedback effect. As the reactor power increases due to normal start up conditions or accident scenarios, the core and surrounding materials heat up, causing both grid plate expansion and bowing of the assembly ducts. When the core restraint system is designed correctly, the resulting structural deformations introduce negative reactivity which decreases the reactor power. Historically, an indirect procedure has been used to estimate the reactivity feedback due to structural deformation which relies upon perturbation theory and coupling legacy physics codes with limited geometry capabilities. With advancements in modeling andmore » simulation, radial core expansion phenomena can now be modeled directly, providing an assessment of the accuracy of the reactivity feedback coefficients generated by indirect legacy methods. Recently a new capability was added to the PROTEUS-SN unstructured geometry neutron transport solver to analyze deformed meshes quickly and directly. By supplying the deformed mesh in addition to the base configuration input files, PROTEUS-SN automatically processes material adjustments including calculation of region densities to conserve mass, calculation of isotopic densities according to material models (for example, sodium density as a function of temperature), and subsequent re-homogenization of materials. To verify the new capability of directly simulating deformed meshes, PROTEUS-SN was used to compute reactivity feedback for a series of contrived yet representative deformed configurations for the Advanced Burner Test Reactor design. The indirect legacy procedure was also performed to generate reactivity feedback coefficients for the same deformed configurations. Interestingly, the legacy procedure consistently overestimated reactivity feedbacks by 35% compared to direct simulations by PROTEUS-SN. This overestimation indicates that the legacy procedures are in fact not conservative and could be overestimating reactivity feedback effects that are closely tied to reactor safety. We conclude that there is indeed value in performing direct simulation of deformed meshes despite the increased computational expense. PROTEUS-SN is already part of the SHARP multi-physics toolkit where both thermal hydraulics and structural mechanical feedback modeling can be applied but this is the first comparison of direct simulation to legacy techniques for radial core expansion.« less

Mechanics and control of the cytoskeleton in Amoeba proteus.

PubMed Central

Dembo, M

1989-01-01

Many models of the cytoskeletal motility of Amoeba proteus can be formulated in terms of the theory of reactive interpenetrating flow (Dembo and Harlow, 1986). We have devised numerical methodology for testing such models against the phenomenon of steady axisymmetric fountain flow. The simplest workable scheme revealed by such tests (the minimal model) is the main preoccupation of this study. All parameters of the minimal model are determined from available data. Using these parameters the model quantitatively accounts for the self assembly of the cytoskeleton of A. proteus: for the formation and detailed morphology of the endoplasmic channel, the ectoplasmic tube, the uropod, the plasma gel sheet, and the hyaline cap. The model accounts for the kinematics of the cytoskeleton: the detailed velocity field of the forward flow of the endoplasm, the contraction of the ectoplasmic tube, and the inversion of the flow in the fountain zone. The model also gives a satisfactory account of measurements of pressure gradients, measurements of heat dissipation, and measurements of the output of useful work by amoeba. Finally, the model suggests a very promising (but still hypothetical) continuum formulation of the free boundary problem of amoeboid motion. by balancing normal forces on the plasma membrane as closely as possible, the minimal model is able to predict the turgor pressure and surface tension of A. proteus. Several dynamical factors are crucial to the success of the minimal model and are likely to be general features of cytoskeletal mechanics and control in amoeboid cells. These are: a constitutive law for the viscosity of the contractile network that includes an automatic process of gelation as the network density gets large; a very vigorous cycle of network polymerization and depolymerization (in the case of A. proteus, the time constant for this reaction is approximately 12 s); control of network contractility by a diffusible factor (probably calcium ion); and control of the adhesive interaction between the cytoskeleton and the inner surface of the plasma membrane. Images FIGURE 1 FIGURE 2 FIGURE 7 PMID:2765645

Analysis of plasmid-mediated quinolone resistance genes in clinical isolates of the tribe Proteeae from Argentina: First report of qnrD in the Americas.

PubMed

Albornoz, Ezequiel; Lucero, Celeste; Romero, Genara; Rapoport, Melina; Guerriero, Leonor; Andres, Patricia; Galas, Marcelo; Corso, Alejandra; Petroni, Alejandro

2014-12-01

To analyse the occurrence and prevalence of plasmid-mediated quinolone resistance (PMQR) genes in the tribe Proteeae, 81 isolates (65 Proteus spp., 12 Morganella morganii and 4 Providencia stuartii) consecutively collected in 66 hospitals belonging to the WHONET-Argentina Resistance Surveillance Network were studied. Of the 81 isolates, 50 (62%) were susceptible to quinolones [43/65 (66%) Proteus spp. and 7/12 (58%) M. morganii). The remaining 31 isolates (22 Proteus spp., 5 M. morganii and all P. stuartii) showed high-level resistance to nalidixic acid (NAL) and decreased susceptibility or resistance to ciprofloxacin. All NAL-resistant isolates harboured mutations associated with quinolone resistance (MAQRs) in both gyrA (S83I/R) and parC (S80I/R), and some also had MAQRs in gyrB (S464Y/F). The unique PMQR gene detected was qnrD, which was found in 2/81 isolates (Proteus mirabilis Q1084 and Proteus vulgaris Q5169), giving a prevalence of 2.5% in Proteeae. These two isolates were from different geographical regions and both harboured MAQRs in gyrA and parC. The qnrD genes were located on the related plasmids pEAD1-1 (2683bp) and pEAD1-2 (2669bp). Plasmid pEAD1-1 was 100% identical to pCGH15 and differed in only three nucleotides from pDIJ09-518a, which were previously found in clinical isolates of P. mirabilis (China) and Providencia rettgeri (France), respectively, whilst pEAD1-2 was not previously described. The extended-spectrum β-lactamase CTX-M-2 was found in 27% (22/81) of the isolates and was significantly associated with quinolone resistance but not with qnrD (only P. mirabilis Q1084 expressed CTX-M-2). This is the first report of qnrD in the Americas. Copyright © 2014 International Society for Chemotherapy of Infection and Cancer. Published by Elsevier Ltd. All rights reserved.

An assessment of the benefits of the use of NASA developed fuel conservative technology in the US commercial aircraft fleet

NASA Technical Reports Server (NTRS)

1975-01-01

Cost and benefits of a fuel conservative aircraft technology program proposed by NASA are estimated. NASA defined six separate technology elements for the proposed program: (a) engine component improvement (b) composite structures (c) turboprops (d) laminar flow control (e) fuel conservative engine and (f) fuel conservative transport. There were two levels postulated: The baseline program was estimated to cost $490 million over 10 years with peak funding in 1980. The level two program was estimated to cost an additional $180 million also over 10 years. Discussions with NASA and with representatives of the major commercial airframe manufacturers were held to estimate the combinations of the technology elements most likely to be implemented, the potential fuel savings from each combination, and reasonable dates for incorporation of these new aircraft into the fleet.

Examination of the costs, benefits and enery conservation aspects of the NASA aircraft fuel conservation technology program

NASA Technical Reports Server (NTRS)

1975-01-01

The costs and benefits of the NASA Aircraft Fuel Conservation Technology Program are discussed. Consideration is given to a present worth analysis of the planned program expenditures, an examination of the fuel savings to be obtained by the year 2005 and the worth of this fuel savings relative to the investment required, a comparison of the program funding with that planned by other Federal agencies for energy conservation, an examination of the private industry aeronautical research and technology financial posture for the period FY 76 - FY 85, and an assessment of the potential impacts on air and noise pollution. To aid in this analysis, a computerized fleet mix forecasting model was developed. This model enables the estimation of fuel consumption and present worth of fuel expenditures for selected commerical aircraft fleet mix scenarios.

Fuel Tank Non-Nuclear Vulnerability Test Program

DTIC Science & Technology

1975-02-01

configurations and structures , for all the threat velocities and obli~quities, alid for all the different fuel tank conditions. This is very unrealistic and can...of operational aircraft. It is, ot. course, imtpractical to simiul~ate all the potential conditions, threat variables, structural materials, and...simulate the structural members of the aircraft to which the aircraft skin and fuel tank walls are attached. The effect that paint, on the aircraft

Energy absorption studied to reduce aircraft crash forces

NASA Technical Reports Server (NTRS)

1981-01-01

The NASA/FAA aircraft safety reseach programs for general aviation aircraft are discussed. Energy absorption of aircraft subflooring and redesign of interior flooring are being studied. The testing of energy absorbing configurations is described. The three NASA advanced concepts performed at neary the maximum possible amount of energy absorption, and one of two minimum modifications concepts performed well. Planned full scale tests are described. Airplane seat concepts are being considered.

U-2 Aircraft at the Lewis Research Center

NASA Image and Video Library

1973-09-21

A National Aeronautics and Space Administration (NASA) Lockheed U-2 aircraft on display at the 1973 Inspection of the Lewis Research Center in Cleveland, Ohio. Lockheed developed the U-2 as a high-altitude reconnaissance aircraft in the early 1950s before satellites were available. The U-2 could cruise over enemy territory at 70,000 feet and remain impervious to ground fire, interceptor aircraft, and even radar. An advanced camera system was designed specifically for the aircraft. The pilot is required to use a pressure suit similar to those worn by astronauts. NASA’s Ames Research Center received two U-2 aircraft in April 1971 to conduct high-altitude research. They were used to study and monitor various Earth resources, celestial bodies, atmospheric chemistry, and oceanic processes. NASA replaced its U-2s with ER-2 aircraft in 1981 and 1989. The ER-2s were designed to carry up to 2600 pounds of scientific equipment. The ER-2 program was transferred to Dryden Flight Research Center in 1997. Since the inaugural flight for this program on August 31, 1971, NASA’s U-2 and ER-2 aircraft have flown more than 4500 data missions and test flights for NASA, other federal agencies, states, universities, and the private sector.

Persistence of antibiotic-resistant and -sensitive Proteus mirabilis strains in the digestive tract of the housefly (Musca domestica) and green bottle flies (Calliphoridae).

PubMed

Wei, Ting; Miyanaga, Kazuhiko; Tanji, Yasunori

2014-10-01

Synanthropic flies have been implicated in the rapid dissemination of antibiotic-resistant bacteria and resistance determinants in the biosphere. These flies stably harbor a considerable number of bacteria that exhibit resistance to various antibiotics, but the mechanisms underlying this phenomenon remain unclear. In this study, we investigated the persistence of antibiotic-resistant bacteria in the digestive tract of houseflies and green bottle flies, using Proteus mirabilis as a model microorganism. One resistant strain carried the blaTEM and aphA1 genes, and another carried a plasmid containing qnrD gene. Quantitative PCR and 454 pyrosequencing were used to monitor the relative abundance of the Proteus strains, as well as potential changes in the overall structure of the whole bacterial community incurred by the artificial induction of Proteus cultures. Both antibiotic-resistant and -sensitive P. mirabilis strains persisted in the fly digestive tract for at least 3 days, and there was no significant difference in the relative abundance of resistant and sensitive strains despite the lower growth rate of resistant strains when cultured in vitro. Therefore, conditions in the fly digestive tract may allow resistant strains to survive the competition with sensitive strains in the absence of antibiotic selective pressure. The composition of the fly-associated bacterial community changed over time, but the contribution of the artificially introduced P. mirabilis strains to these changes was not clear. In order to explain these changes, it will be necessary to obtain more information about bacterial interspecies antagonism in the fly digestive tract.

Phenotypic and molecular characterization of antimicrobial resistance in Proteus mirabilis isolates from dogs.

PubMed

Harada, Kazuki; Niina, Ayaka; Shimizu, Takae; Mukai, Yujiro; Kuwajima, Ken; Miyamoto, Tadashi; Kataoka, Yasushi

2014-11-01

Large-scale monitoring of resistance to 14 antimicrobial agents was performed using 103 Proteus mirabilis strains isolated from dogs in Japan. Resistant strains were analysed to identify their resistance mechanisms. Rates of resistance to chloramphenicol, streptomycin, enrofloxacin, trimethoprim/sulfamethoxazole, kanamycin, ampicillin, ciprofloxacin, cephalothin, gentamicin, cefoxitin and cefotaxime were 20.4, 15.5, 12.6, 10.7, 9.7, 8.7, 5.8, 2.9, 2.9, 1.9 and 1.9%, respectively. No resistance to ceftazidime, aztreonam or imipenem was found. Class 1 and 2 integrases were detected in 2.9 and 11.7% of isolates, respectively. Class 1 integrons contained aadB or aadB-catB-like-blaOXA10-aadA1, whereas those of class 2 contained sat-aadA1, dhfr1-sat-aadA1 or none of the anticipated resistance genes. Of five distinct plasmid-mediated quinolone-resistance (PMQR) genes, only qnrD gene was detected in 1.9% of isolates. Quinolone-resistance determining regions (QRDRs) of gyrA and parC from 13 enrofloxacin-intermediate and -resistant isolates were sequenced. Seven strains had double mutations and three had single mutations. Three of nine ampicillin-resistant isolates harboured AmpC-type β-lactamases (i.e. blaCMY-2, blaCMY-4 and blaDHA-1). These results suggest that canine Proteus mirabilis deserves continued surveillance as an important reservoir of antimicrobial resistance determinants. This is the first report, to our knowledge, describing integrons, PMQRs and QRDR mutations in Proteus mirabilis isolates from companion animals. © 2014 The Authors.

Operation REDWING. Technical Summary of Military Effects. Programs 1-9

DTIC Science & Technology

1981-05-15

study chorioretinal burns. The primary objective of the program on effects on aircraft structures was to ascer- tain the reliability of current weapons...other aircraft. In the program of tests on service equipment and studies of electromagnetic effects,I 4k. the emphasis was placed on studying long...range detection of nuclear explosions. An additional objective was the study of the effects of nuclear detonations on the ionosphere and microwave