Ignition of Hydrogen-Oxygen Rocket Combustor with Chlorine Trifluoride and Triethylaluminum

NASA Technical Reports Server (NTRS)

Gregory, John W.; Straight, David M.

1961-01-01

Ignition of a nominal-125-pound-thrust cold (2000 R) gaseous-hydrogen - liquid-oxygen rocket combustor with chlorine trifluoride (hypergolic with hydrogen) and triethylaluminum (hypergolic with oxygen) resulted in consistently smooth starting transients for a wide range of combustor operating conditions. The combustor exhaust nozzle discharged into air at ambient conditions. Each starting transient consisted of the following sequence of events: injection of the lead main propellant, injection of the igniter chemical, ignition of these two chemicals, injection of the second main propellant, ignition of the two main propellants, increase in chamber pressure to its terminal value, and cutoff of igniter-chemical flow. Smooth ignition was obtained with an ignition delay of less than 100 milliseconds for the reaction of the lead propellant with the igniter chemical using approximately 0.5 cubic inch (0-038 lb) of chlorine trifluoride or 1.0 cubic inch (0-031 lb) of triethylaluminum. These quantities of igniter chemical were sufficient to ignite a 20-percent-fuel hydrogen-oxygen mixture with a delay time of less than 15 milliseconds. Test results indicated that a simple, light weight chemical ignition system for hydrogen-oxygen rocket engines may be possible.

Hypergolic Propellants: The Handling Hazards and Lessons Learned from Use

NASA Technical Reports Server (NTRS)

Nufer, Brian

2010-01-01

Several unintentional hypergolic fluid related spills, fires, and explosions from the Apollo Program, the Space Shuttle Program, the Titan Program, and a few others have occurred over the past several decades. Spill sites include the following government facilities: Kennedy Space Center (KSC), Johnson Space Center (JSC), White Sands Test Facility (WSTF), Vandenberg Air Force Base (VAFB), Cape Canaveral Air Force Station (CCAFS), Edwards Air Force Base (EAFB), Little Rock AFB, and McConnell AFB. Until now, the only method of capturing the lessons learned from these incidents has been "word of mouth" or by studying each individual incident report. Through studying several dozen of these incidents, certain root cause themes are apparent. Scrutinizing these themes could prove to be highly beneficial to future hypergolic system testing, checkout, and operational use.

Computational analysis of liquid hypergolic propellant rocket engines

NASA Technical Reports Server (NTRS)

Krishnan, A.; Przekwas, A. J.; Gross, K. W.

1992-01-01

The combustion process in liquid rocket engines depends on a number of complex phenomena such as atomization, vaporization, spray dynamics, mixing, and reaction mechanisms. A computational tool to study their mutual interactions is developed to help analyze these processes with a view of improving existing designs and optimizing future designs of the thrust chamber. The focus of the article is on the analysis of the Variable Thrust Engine for the Orbit Maneuvering Vehicle. This engine uses a hypergolic liquid bipropellant combination of monomethyl hydrazine as fuel and nitrogen tetroxide as oxidizer.

Historical Evolution of NASA Standard Materials Testing with Hypergolic Propellants and Ammonia (NASA Standard 6001 Test 15)

NASA Technical Reports Server (NTRS)

Greene, Benjamin; McClure, Mark B.

2012-01-01

The NASA Johnson Space Center White Sands Test Facility (WSTF) has performed testing of hazardous and reactive aerospace fluids, including hypergolic propellants, with materials since the 1960s with the Apollo program. Amongst other test activities, Test 15 is a NASA standard test for evaluating the reactivity of materials with selected aerospace fluids, in particular hydrazine, monomethylhydrazine, uns-dimethylhydrazine, Aerozine 50, dinitrogen tetroxide oxidizers, and ammonia. This manuscript provides an overview of the history of Test 15 over a timeline ranging from prior to its development and first implementation as a NASA standard test in 1974 to its current refinement. Precursor documents to NASA standard tests, as they are currently known, are reviewed. A related supplementary test, international standardization, and enhancements to Test 15 are also discussed. Because WSTF was instrumental in the development and implementation of Test 15, WSTF experience and practices are referred to in this manuscript.

Update on Chemical Analysis of Recovered Hydrazine Family Fuels for Recycling

NASA Technical Reports Server (NTRS)

Davis, C. L.

1997-01-01

The National Aeronautics and Space Administration, Kennedy Space Center, has developed a program to re-use and/or recycle hypergolic propellants recovered from propellant systems. As part of this effort, new techniques were developed to analyze recovered propellants. At the 1996 PDCS, the paper 'Chemical Analysis of Recovered Hydrazine Family Fuels For Recycling' presented analytical techniques used in accordance with KSC specifications which define what recovered propellants are acceptable for recycling. This paper is a follow up to the 1996 paper. Lower detection limits and response linearity were examined for two gas chromatograph methods.

Lightweight, High Performance, Low Cost Propulsion Systems for Mars Exploration Missions to Maximize Science Payload

NASA Astrophysics Data System (ADS)

Trinh, H. P.

2012-06-01

Utilization of new cold hypergolic propellants and leverage Missile Defense Agency technology for propulsion systems on Mars explorations will provide an increase of science payload and have significant payoffs and benefits for NASA missions.

Hypergolic Propellant Destruction Evaluation Cost Benefit Analysis

NASA Technical Reports Server (NTRS)

Kessel, Kurt

2010-01-01

At space vehicle launch sites such as Vandenberg Air Force Base (VAFB), Cape Canaveral Air Force Station (CCAFS) and Kennedy Space Center (KSC), toxic vapors and hazardous liquid wastes result from the handling of commodities (hypergolic fuels and oxidizers), most notably from transfer operations where fuel and oxidizer are transferred from bulk storage tanks or transfer tankers to space launch vehicles. During commodity transfer at CCAFS and KSC, wet chemical scrubbers (typically containing four scrubbing towers) are used to neutralize fuel saturated vapors from vent systems on tanks and tanker trailers. For fuel vapors, a citric acid solution is used to scrub out most of the hydrazine. Operation of both the hypergolic fuel and oxidizer vapor scrubbers generates waste scrubber liquor. Currently, scrubber liquor from the fuel vapor scrubber is considered non-hazardous. The scrubber liquor is defined as spent citric acid scrubber solution; the solution contains complexed hydrazine I methylhydrazine and is used to neutralize nonspecification hypergolic fuel generated by CCAFS and KSC. This project is a collaborative effort between Air Force Space Command (AFSPC), Space and Missile Center (SMC), the CCAFS, and National Aeronautics and Space Administration (NASA) to evaluate microwave destruction technology for the treatment of non-specification hypergolic fuel generated at CCAFS and KSC. The project will capitalize on knowledge gained from microwave treatment work being accomplished by AFSPC and SMC at V AFB. This report focuses on the costs associated with the current non-specification hypergolic fuel neutralization process (Section 2.0) as well as the estimated costs of operating a mobile microwave unit to treat non-specification hypergolic fuel (Section 3.0), and compares the costs for each (Section 4.0).The purpose of this document is to assess the costs associated with waste hypergolic fuel. This document will report the costs associated with the current fuel neutralization process and also examine the costs of an alternative technology, microwave destruction of waste hypergolic fuel. The microwave destruction system is being designed as a mobile unit to treat non-specification hypergolic fuel at CCAFS and KSC.

Synthesis and testing of hypergolic ionic liquids for chemical propulsion

NASA Astrophysics Data System (ADS)

Stovbun, S. V.; Shchegolikhin, A. N.; Usachev, S. V.; Khomik, S. V.; Medvedev, S. P.

2017-06-01

Synthesis of new highly energetic ionic liquids (ILs) is described, and their hypergolic ignition properties are tested. The synthesized ILs combine the advantages of conventional rocket propellants with the energy characteristics of acetylene derivatives. To this end, N-alkylated imidazoles (alkyl = ethyl, butyl) have been synthesized and alkylated with propargyl bromide. The desired ionic liquids have been produced by metathesis using Ag dicyanamide. Modified hypergolic drop tests with white fuming nitric acid have been performed for N-ethyl (IL-1) and N-butyl propargylimidazolium (IL-2) ionic liquids. In the modified drop tests, high-speed shadowgraph imaging is used to visualize the process, and the temperature rise due to ignition is monitored with a two-color photodetector. It is shown that the ignition delay is shorter for IL-1 as compared to IL-2. The ignition of IL-1 occurs in two stages, whereas the combustion of IL-2 proceeds smoothly without secondary flashes.

Characterizing high-energy-density propellants for space propulsion applications

NASA Astrophysics Data System (ADS)

Kokan, Timothy

There exists wide ranging research interest in high-energy-density matter (HEDM) propellants as a potential replacement for existing industry standard fuels for liquid rocket engines. The U.S. Air Force Research Laboratory, the U.S. Army Research Lab, the NASA Marshall Space Flight Center, and the NASA Glenn Research Center each either recently concluded or currently has ongoing programs in the synthesis and development of these potential new propellants. In order to perform conceptual designs using these new propellants, most conceptual rocket engine powerhead design tools (e.g. NPSS, ROCETS, and REDTOP-2) require several thermophysical properties of a given propellant over a wide range of temperature and pressure. These properties include enthalpy, entropy, density, viscosity, and thermal conductivity. Very little thermophysical property data exists for most of these potential new HEDM propellants. Experimental testing of these properties is both expensive and time consuming and is impractical in a conceptual vehicle design environment. A new technique for determining these thermophysical properties of potential new rocket engine propellants is presented. The technique uses a combination of three different computational methods to determine these properties. Quantum mechanics and molecular dynamics are used to model new propellants at a molecular level in order to calculate density, enthalpy, and entropy. Additivity methods are used to calculate the kinematic viscosity and thermal conductivity of new propellants. This new technique is validated via a series of verification experiments of HEDM compounds. Results are provided for two HEDM propellants: quadricyclane and 2-azido-N,N-dimethylethanamine (DMAZ). In each case, the new technique does a better job than the best current computational methods at accurately matching the experimental data of the HEDM compounds of interest. A case study is provided to help quantify the vehicle level impacts of using HEDM propellants. The case study consists of the National Aeronautics and Space Administration's (NASA) Exploration Systems Architecture Study (ESAS) Lunar Surface Access Module (LSAM). The results of this study show that the use of HEDM propellants instead of hypergolic propellants can lower the gross weight of the LSAM and may be an attractive alternative to the current baseline hypergolic propellant choice.

Integrated hydrogen/oxygen technology applied to auxiliary propulsion systems

NASA Technical Reports Server (NTRS)

Gerhardt, David L.

1990-01-01

The purpose of the Integrated Hydrogen/Oxygen Technology (IHOT) study was to determine if the vehicle/mission needs and technology of the 1990's support development of an all cryogenic H2/O2 system. In order to accomplish this, IHOT adopted the approach of designing Integrated Auxiliary Propulsion Systems (IAPS) for a representative manned vehicle; the advanced manned launch system. The primary objectives were to develop IAPS concepts which appeared to offer viable alternatives to state-of-the-art (i.e., hypergolic, or earth-storable) APS approaches. The IHOT study resulted in the definition of three APS concepts; two cryogenic IAPS, and a third concept utilizing hypergolic propellants.

Kinetics Modeling of Hypergolic Propellants

DTIC Science & Technology

2013-07-01

comprehensive preconditioning and employs the line Gauss Seidel algorithm for the solution of the linear system. A multi-block unstructured mesh is...Explosives, Pyrotechnics, 33(3):209–212, 2008. 24Wei-Guang Liu, Shiqing Wang, Siddharth Dasgupta, Stefan T Thynell, William A Goddard III, Sergey Zybin

Propellant Analysis and Distillation Unit Design

NASA Technical Reports Server (NTRS)

Barragan, Michelle H.; Spangler, Cindy; Barrera, Louis K.

2007-01-01

The NASA White Sands Test Facility (WSTF) routinely operates hypergolic propulsion systems. Some of the onsite activities include performing long duration studies on the operational life of these systems. A few of them have been in use for over twenty years. During this span of time contamination has built up in the propellant and some of the distribution infrastructure. This study investigated the nature of this contamination, the pathology of its generation, and developed a process for removal of the contamination that was cost efficient with minimal waste generation.

MIT January Operational Internship Experience

NASA Technical Reports Server (NTRS)

Bosanac, Natasha; DeVivero, Charlie; James, Jillian; Perez-Martinez, Carla; Pino, Wendy; Wang, Andrew; Willett, Ezekiel; Williams, Kwami

2010-01-01

This viewgraph presentation describes the MIT January Operational Internship Experience (JOIE) program. The topics include: 1) Landing and Recovery; 2) Transportation; 3) Shuttle Processing; 4) Constellation Processing; 5) External Tank; 6) Launch Pad; 7) Ground Operations; 8) Hypergolic Propellants; 9) Environmental; 10) Logistics; 11) Six Sigma; 12) Systems Engineering; and 13) Human Factors.

Liquid and Gas Phase Chemistry of Hypergolic Reactions between MMH and NTO or RFNA

NASA Astrophysics Data System (ADS)

Black, Ariel

Hypergolic systems rely on fuel and oxidizer propellant combinations that spontaneously ignite upon contact. Monomethylhydrazine (MMH) fuel and nitrogen tetroxide (NTO) - based oxidizers embody the state of the art for hypergolic propellants, although the health and safety hazards associated with these propellants demand investigation into less-toxic, high performance alternatives. In order to replicate the combustion characteristics of these highly reactive propellants, a detailed understanding of the full reaction process is necessary. Current reaction mechanisms and hypergolic ignition models generally assume that gas-phase chemistry dominates the interaction since the liquid-phase reactions occur on the order of microseconds. However, condensed-phase reactions produce intermediates integral to gas-phase initiation and development. Additional insight into the physical and chemical processes that dictate this liquid-phase chemistry is therefore essential. Concurrently, further examination of the gas-phase reactions leading to and immediately following ignition is also needed. A method devoted to the determination of the liquid phase hypergolic reaction mechanism and kinematic rate parameters for MMH-NTO and MMH-red fuming nitric acid (RFNA) is presented in this study. MMH-RFNA reaction chemistry is better understood and documented in literature than MMH-NTO and is examined for comparison and validation. Drop on pool experiments at a range of temperatures were initially undertaken using MMH and RFNA and then modified to accommodate the high vapor pressure of NTO. Using a temperature and atmosphere controlled droplet contact chamber, the liquid phases of MMH-RFNA and MMH-NTO were studied by capturing impacts at frame rates from 100,000 to 500,000 fps. This footage allowed for the identification of time delays between droplet contact and initial gas formation, enabling calibration of the Arrhenius pre-exponential factors and activation energies for a global, one-step liquid phase chemical reaction model. These defining constants have never before been experimentally determined for MMH-NTO and can be employed to improve the accuracy of CFD combustion simulations. Induction delay times for MMH-RFNA ranged from 30 to 100 microseconds, agreeing with previously reported data, while MMH-NTO delays varied from 10 to 100 microseconds. Advanced ultraviolet and visible (UV-Vis) spectroscopic techniques were applied to conventional drop test analysis in order to study the emitting species in MMH-NTO and MMH-RFNA combustion reactions. A streak camera coupled with a spectrometer provided temporally resolved spectra for species emitting wavelengths from 250 to 950 nm within a one millimeter diameter point of interest above the reaction. The spectra were compared to known MMH-RFNA gas-phase reaction mechanisms and spectroscopic data reported in literature in an attempt to partially validate the proposed full and reduced MMH-RFNA reaction mechanisms and derive a connection to elementary reactions of MMH-NTO. MMH-NTO consistently produced brighter flames than MMH-RFNA and as such generally generated higher intensity signals for a given spectrometer setting. Both propellant combinations revealed conclusive evidence of OH and NH radicals and probable evidence of CN and/or CH radicals. In most tests OH* yielded the highest intensity signals with both RFNA and NTO. MMH-NTO revealed greater NH* intensity than MMH-RFNA. Additionally, species appeared later but peaked sooner relative to ignition for MMH-RFNA than for MMH-NTO. Efforts to draw correlations between these experimental results and existing reaction mechanisms proved to be challenging and are ongoing. A dominant, high intensity signal characteristic of sodium was an unexpected, but apparently not uncommon, observation, with varying opinions as to its origin.

High performance N2O4/amine elements: Blowapart

NASA Technical Reports Server (NTRS)

Lawver, B. R.

1977-01-01

The mechanisms controlling hypergolic propellant reactive stream separation (RRS) were studied and used to develop design criteria for injectors free from both steady state RSS and cyclic propellant stream separation. This was accomplished through the analysis of single element injectors using N204/MMH propellants; the injectors were representative of the space shuttle orbit maneuvering engine and space tug applications. A gas phase/surface reaction mechanism which controls RSS was identified. Injector design criteria were developed, which defined a critical chamber pressure for those operating conditions above which RSS occurs. It was found that the amount of interfacial surface area at impingement is controlled by injector hydraulics.

JANNAF 28th Propellant Development and Characterization Subcommittee and 17th Safety and Environmental Protection Subcommittee Joint Meeting. Volume 1

NASA Technical Reports Server (NTRS)

Cocchiaro, James E. (Editor); Mulder, Edwin J. (Editor); Gomez-Knight, Sylvia J. (Editor)

1999-01-01

This volume contains 37 unclassified/unlimited-distribution technical papers that were presented at the JANNAF 28th Propellant Development & Characterization Subcommittee (PDCS) and 17th Safety & Environmental Protection Subcommittee (S&EPS) Joint Meeting, held 26-30 April 1999 at the Town & Country Hotel and the Naval Submarine Base, San Diego, California. Volume II contains 29 unclassified/limited-distribution papers that were presented at the 28th PDCS and 17th S&EPS Joint Meeting. Volume III contains a classified paper that was presented at the 28th PDCS Meeting on 27 April 1999. Topics covered in PDCS sessions include: solid propellant rheology; solid propellant surveillance and aging; propellant process engineering; new solid propellant ingredients and formulation development; reduced toxicity liquid propellants; characterization of hypergolic propellants; and solid propellant chemical analysis methods. Topics covered in S&EPS sessions include: space launch range safety; liquid propellant hazards; vapor detection methods for toxic propellant vapors and other hazardous gases; toxicity of propellants, ingredients, and propellant combustion products; personal protective equipment for toxic liquid propellants; and demilitarization/treatment of energetic material wastes.

Experimental Study on an Unsteady Pressure Gain Combustion Hypergolic Rocket Engine Concept

NASA Astrophysics Data System (ADS)

Kan, Brandon K.

An experimental study is conducted to investigate pulsed combustion in a lab-scale bipropellant rocket engine using hypergolic propellants. The propellant combination is high concentration hydrogen peroxide and a catalyst-laced triglyme fuel. A total of 50 short duration firings have been conducted; the vast majority in an open-chamber configuration. High amplitude pulsations were evident in nearly all cases and have been assessed with high frequency pressure measurements. Both pintle and unlike impinging quadlet injector types have been evaluated although the bulk of the testing was with the latter configuration. Several firings were conducted with a transparent chamber in an attempt to gain understanding using a high-speed camera in the visible spectrum. Peak chamber pressures in excess of 5000 psi have been recorded with surface mounted high frequency gages with pulsation frequencies exceeding 600 Hz. A characterization of time-averaged performance is made for the unsteady system, where time-resolved thrust and pressure measurements were attempted. While prior literature describes this system as a pulse detonation rocket engine, the combustion appears to be more "constant volume" in nature.

A Discussion of Two Challenges of Non-cooperative Satellite Refueling

NASA Technical Reports Server (NTRS)

Coll, Gregory C.; Aranyos, Thomas; Nufer, Brian M.; Kandula, Max; Tomasic, David J.

2015-01-01

There is interest from government and commercial aerospace communities in advancing propellant transfer technology for in-orbit refueling of satellites. This paper introduces two challenges to a Propellant Transfer System (PTS) under development for demonstration of non-cooperative satellite refueling. The PTS is being developed to transfer storable propellant (heritage hypergolic fuels and oxidizers as well as xenon) safely and reliably from one servicer satellite to a non-cooperative typical existing client satellite. NASA is in the project evaluation planning stages for conducting a first time on-orbit demonstration to an existing government asset. The system manages pressure, flow rate totalization, temperature and other parameters to control the condition of the propellant being transferred to the client. It keeps the propellant isolated while performing leak checks of itself and the client interface before transferring propellant. A major challenge is to design a safe, reliable system with some new technologies while maintaining a reasonable cost.

A Discussion of Two Challenges of Non-Cooperative Satellite Refueling

NASA Technical Reports Server (NTRS)

Coll, Gregory T.; Aranyos, Thomas J.; Nufer, Brian M.; Tomasic, David; Kandula, Max

2015-01-01

There is interest from government and commercial aerospace communities in advancing propellant transfer technology for in-orbit refueling of satellites. This paper introduces two challenges to a Propellant Transfer System (PTS) under development for demonstration of non-cooperative satellite refueling. The PTS is being developed to transfer storable propellant (heritage hypergolic fuels and oxidizers as well as xenon) safely and reliably from one servicer satellite to a non-cooperative typical existing client satellite. NASA is in the project evaluation planning stages for conducting a first time on-orbit demonstration to an existing government asset. The system manages pressure, flow rate totalization, temperature and other parameters to control the condition of the propellant being transferred to the client. It keeps the propellant isolated while performing leak checks of itself and the client interface before transferring propellant. A major challenge is to design a safe, reliable system with some new technologies while maintaining a reasonable cost.

Theoretical and Experimental Investigations of Ignition, Combustion and Expansion Processes of Hypergolic Liquid Fuel Combinations at Gas Temperatures up to 3000 K. Thesis - Rhein-Westfalia Technical Coll., 1967

NASA Technical Reports Server (NTRS)

Schulz, Harry

1987-01-01

The ignition, combustion, and expansion characteristics of hypergolic liquid propellant mixtures in small rocket engines are studied theoretically and experimentally. It is shown by using the Bray approximation procedure that the reaction H + OH + M = H2O + M (where M is the molecular mass of the gas mixture) has a strong effect on the combustion efficiency. Increases in recombination energies ranging from 30 to 65% were obtained when the rate of this reaction was increased by a factor of 10 in gas mixtures containing 90% oxygen. The effect of aluminum additions and various injection techniques on the combustion process is investigated.

An Experimental Investigation of Hypergolic Ignition Delay of Hydrogen Peroxide with Fuel Mixtures

NASA Technical Reports Server (NTRS)

Blevins, John A.; Gostowski, Rudy; Chianese, Silvio

2003-01-01

An experimental investigation of hypergolicity and ignition delay of fuel mixtures with hydrogen peroxide is presented. Example results of high speed photography and schleiren from drop tests are shown. Also, a discussion of the sensitivity to experimental parameters such as drop size and subsequent uncertainty considerations of ignition delay results is presented. It is shown that using the described setup on the mixtures presented, the precision uncertainty is on the order of 6% of average ignition delay and 5% of average decomposition delay. This represents sufficient repeatability for first order discrimination of ignition delay for propellant development and screening. Two mixtures, each using commonly available amines and transition metal compounds, are presented as examples that result in ignition delays on the order of 10 milliseconds.

Human exposure limits to hypergolic fuels

NASA Technical Reports Server (NTRS)

Garcia, H. D.; James, J. T.; Limero, T. F.

1992-01-01

Over the past four decades, many studies have been conducted on the toxicities of the rocket propellants hydrazine (HZ) and monomethylhydrazine (MH). Numerous technical challenges have made it difficult to unambiguously interpret the results of these studies, and there is considerable divergence between results obtained by different investigators on the inhalation concentrations (MAC's) for each toxic effect inducible by exposure to hypergolic fuels in spacecraft atmospheres, NASA undertook a critical review of published and unpublished investigations on the toxicities of these compounds. The current state of the art practices for similar studies. While many questions remain unanswered, MAC's were determined using the best available data for a variety of toxic endpoints for potential continuous exposure durations ranging from 1 hour to 180 days. Spacecraft MAC's (SMAC's) were set for each compound based on the most sensitive toxic endpoint at each exposure duration.

Ignition characterization of the GOX/ethanol propellant combination

NASA Technical Reports Server (NTRS)

Lawver, B. R.; Rousar, D. C.; Boyd, W. C.

1984-01-01

This paper describes the results of a study to define the ignition characteristics and thruster pulse mode capabilities of the GOX/ethanol propellant combination. Ignition limits were defined in terms of mixture ratio and cold flow pressure using a spark initiated torch igniter. Igniter tests were run over a wide range of cold flow pressure, propellant temperature and mixture ratio. The product of cold flow pressure and igniter chamber diameter was used to correlate mixture ratio regimes of ignition and nonignition. Engine ignition reliability and pulse mode capability were demonstrated using a 620 lbF thruster with an integrated torch igniter. The nominal chamber pressure and mixture ratio were 150 psia and 1.8, respectively, thruster tests were run over a wide range of chamber pressures and mixture ratios. The feasibility of thruster pulse mode operation with the non-hypergolic GOX/ethanol propellant combination was demonstrated.

Hydrogen Peroxide - Material Compatibility Studied by Microcalorimetry

NASA Technical Reports Server (NTRS)

Homung, Steven D.; Davis, Dennis D.; Baker, David; Popp, Christopher G.

2003-01-01

Environmental and toxicity concerns with current hypergolic propellants have led to a renewed interest in propellant grade hydrogen peroxide (HP) for propellant applications. Storability and stability has always been an issue with HP. Contamination or contact of HP with metallic surfaces may cause decomposition, which can result in the evolution of heat and gas leading to increased pressure or thermal hazards. The NASA Johnson Space Center White Sands Test Facility has developed a technique to monitor the decompositions of hydrogen peroxide at temperatures ranging from 25 to 60 C. Using isothermal microcalorimetry we have measured decomposition rates at the picomole/s/g level showing the catalytic effects of materials of construction. In this paper we will present the results of testing with Class 1 and 2 materials in 90 percent hydrogen peroxide.

5. Credit USAF, ca. 1942. Original housed in the Photograph ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

5. Credit USAF, ca. 1942. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. View of Bell Aircraft XP-59A Airacomet in flight. This was the United States military's first jet propelled aircraft which was extensively flight tested in secrecy at the Muroc Flight Test Base (North Base). - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

The hard start phenomena in hypergolic engines. Volume 1: Bibliography

NASA Technical Reports Server (NTRS)

Miron, Y.; Perlee, H. E.

1974-01-01

A bibliography of reports pertaining to the hard start phenomenon in attitude control rocket engines on Apollo spacecraft is presented. Some of the subjects discussed are; (1) combustion of hydrazine, (2) one dimensional theory of liquid fuel rocket combustion, (3) preignition phenomena in small pulsed rocket engines, (4) experimental and theoretical investigation of the fluid dynamics of rocket combustion, and (5) nonequilibrium combustion and nozzle flow in propellant performance.

Computational analysis of Variable Thrust Engine (VTE) performance

NASA Technical Reports Server (NTRS)

Giridharan, M. G.; Krishnan, A.; Przekwas, A. J.

1993-01-01

The Variable Thrust Engine (VTE) of the Orbital Maneuvering Vehicle (OMV) uses a hypergolic propellant combination of Monomethyl Hydrazine (MMH) and Nitrogen Tetroxide (NTO) as fuel and oxidizer, respectively. The performance of the VTE depends on a number of complex interacting phenomena such as atomization, spray dynamics, vaporization, turbulent mixing, convective/radiative heat transfer, and hypergolic combustion. This study involved the development of a comprehensive numerical methodology to facilitate detailed analysis of the VTE. An existing Computational Fluid Dynamics (CFD) code was extensively modified to include the following models: a two-liquid, two-phase Eulerian-Lagrangian spray model; a chemical equilibrium model; and a discrete ordinate radiation heat transfer model. The modified code was used to conduct a series of simulations to assess the effects of various physical phenomena and boundary conditions on the VTE performance. The details of the models and the results of the simulations are presented.

Sample Diluter for Detecting Hypergolic Propellants and Other Toxic or Hazardous Gases

NASA Technical Reports Server (NTRS)

Barile, R. G.; Hodge, T. R.; Meneghelli, B. J.; Gursky, R.; Lueck, D. E.

1997-01-01

Hardware was developed to dilute vapor samples of purged hypergolic propellants (with air) into the range of existing instruments for detection of such toxic vapors. Since these detectors are normally used to monitor at the threshold limit value (TLV), most do not have quantitative capability at percent levels which relate to lower explosion limit (LEL) and fire hazards. For example, the upper limits of Energetic Sciences (ESI) 6000 series detectors used at KSC are 200 parts per million (ppm) for monomethyl hydrazine (MMH) and 500 ppm for nitrogen dioxide (NO2) arising from decomposition of nitrogen tetroxide (N2O4). Orbiter Processing Facility (OPF) personnel servicing Shuttle thrusters need to measure up to 250 ppm MMH and 7500 ppm NO2 with portable, intrinsically safe instruments. Our objective was to quickly fabricate a sample diluter out of existing materials as a temporary measure while other parallel efforts were conducted to provide a commercial or in-house-developed instrument to detect high propellant levels. A 3 to 1 diluter would bring 500 ppm MMH into the range of the existing fuel ESI, and a 30 to 1 diluter would do the same for NO2. In this way, familiar equipment already available would be used, resulting in minimal paperwork, safety, and training impacts and low cost. An MMH vapor sample-diluter was constructed from a 1/4-inch Kynar tee, along with specially designed lengths of sample and dilution tubing. The sample line was 3 feet of Bev-A-Line 4, 1/4 inch tube leading to the straight run of the tee. The side run of the tee had a 17-inch length of Bev-A-Line 4, 1/4-inch tube, for nominal 3 to 1 dilution. A gas sample bag was prepared and assayed at 113 ppm MMH, and diluted vapor sarnples were assayed at 39.5 ppm, or a measured dilution of 2.9 to 1. For NO2, a 316 stainless steel (SS) 1/8-inch tee with 49.5 inches of coiled, 1/8-inch outside diameter (OD) 316 SS tubing was used as the sarnpling end of the dilution system. The side run of the tee was open. The measured dilution ratio, based on the input value of 6,480 ppm NO2 and the average output value of 233 ppm, was 28 to 1. Thus, sample-diluters were successful in diluting concentrated hypergolic propellant vapors, both MMH and N2O4, into the ranges of existing TLV detectors.

Sample Diluter for Detecting Hypergolic Propellants and Other Toxic or Hazardous Gases

NASA Technical Reports Server (NTRS)

Barile, R. G.; Hodge, T. R.; Meneghelli, B. J.; Gursky, R.; Lueck, D. E.

1997-01-01

Hardware was developed to dilute vapor samples of purged hypergolic propellants (with air) into the range of existing instruments for detection of such toxic vapors. Since these detectors are normally used to monitor at the threshold limit value (TLV), most do not have quantitative capability at percent levels which relate to lower explosion limit (LEL) and fire hazards. For example, the upper limits of Energetic Sciences (ESI) 6000 series detectors used at KSC are 200 parts per million (ppm) for monomethyl hydrazine (MMH) and 500 ppm for nitrogen dioxide (NO2) arising from decomposition of nitrogen tetroxide (N2O4). Orbiter Processing Facility (OPF) personnel servicing Shuttle thrusters need to measure up to 250 ppm MMH and 7,500 ppm NO2 with portable, intrinsically safe instruments. Our objective was to quickly fabricate a sample diluter out of existing materials as a temporary measure while other parallel efforts were conducted to provide a commercial or in-house-developed instrument to detect high propellant levels. A 3 to 1 diluter would bring 500 ppm MMH into the range of the existing fuel ESI, and a 30 to 1 diluter would do the same for NO2. In this way, familiar equipment already available would be used, resulting in minimal paperwork, safety, and training impacts and low cost. An MMH vapor sample-diluter was constructed from a 1/4-inch Kynar tee, along with specially designed lengths of sample and dilution tubing. The sample line was 3 feet of Bev-A-Line 4, 1/4-inch tube leading to the straight run of the tee. The side run of the tee had a 17-inch length of Bev-A-Line 4, 1/4-inch tube, for nominal 3 to 1 dilution. A gas sample bag was prepared and assayed at 113 ppm ppm MMH, and diluted vapor samples were assayed at 39.5 ppm, or a measured dilution of 2.9 to 1. For NO2, a 316 stainless steel (SS) 1/8-inch tee with 49.5 inches of coiled, 1/8-inch outside diameter (OD) 316 SS tubing was used as the sampling end of the dilution system. The side run of the tee was open. The measured dilution ratio, based on the input value of 6,480 ppm NO2, and the average output value of 233 ppm, was 28 to 1. Thus, sample-diluters were successful in diluting concentrated hypergolic propellant vapors, both MMH and N2O4 into the ranges of existing TLV detectors.

The hard start phenomena in hypergolic engines. Volume 4: The chemistry of hydrazine fuels and nitrogen tetroxide propellant systems

NASA Technical Reports Server (NTRS)

Miron, Y.; Perlee, H. E.

1974-01-01

The various chemical reactions that occur and that could possibly occur in the RCS engines utilizing hydrazine-type fuel/nitrogen tetroxide propellant systems, prior to ignition (preignition), during combustion, and after combustion (postcombustion), and endeavors to relate the hard-start phenomenon to some of these reactions are discussed. The discussion is based on studies utilizing a variety of experimental techniques and apparatus as well as current theories of chemical reactions and reaction kinetics. The chemical reactions were studied in low pressure gas flow reactors, low temperature homogeneous- and heterogeneous-phase reactors, simulated two-dimensional (2-D) engines, and scaled and full size engines.

Boeing's CST-100 Launch Abort Engine Test

NASA Image and Video Library

2016-10-20

A launch abort engine built by Aerojet Rocketdyne is hot-fired during tests in the Mojave Desert in California. The engine produces up to 40,000 pounds of thrust and burns hypergolic propellants. The engines have been designed and built for use on Boeing’s CST-100 Starliner spacecraft in sets of four. In an emergency at the pad or during ascent, the engines would ignite to push the Starliner and its crew out of danger.

Boeing's CST-100 Launch Abort Engine Test

NASA Image and Video Library

2016-10-17

A launch abort engine built by Aerojet Rocketdyne is hot-fired during tests in the Mojave Desert in California. The engine produces up to 40,000 pounds of thrust and burns hypergolic propellants. The engines have been designed and built for use on Boeing’s CST-100 Starliner spacecraft in sets of four. In an emergency at the pad or during ascent, the engines would ignite to push the Starliner and its crew out of danger.

LOX/Methane Main Engine Igniter Tests and Modeling

NASA Technical Reports Server (NTRS)

Breisacher, Kevin J.; Ajmani, Kumund

2008-01-01

The LOX/methane propellant combination is being considered for the Lunar Surface Access Module ascent main engine propulsion system. The proposed switch from the hypergolic propellants used in the Apollo lunar ascent engine to LOX/methane propellants requires the development of igniters capable of highly reliable performance in a lunar surface environment. An ignition test program was conducted that used an in-house designed LOX/methane spark torch igniter. The testing occurred in Cell 21 of the Research Combustion Laboratory to utilize its altitude capability to simulate a space vacuum environment. Approximately 750 ignition test were performed to evaluate the effects of methane purity, igniter body temperature, spark energy level and frequency, mixture ratio, flowrate, and igniter geometry on the ability to obtain successful ignitions. Ignitions were obtained down to an igniter body temperature of approximately 260 R with a 10 torr back-pressure. The data obtained is also being used to anchor a CFD based igniter model.

Spray and Combustion of Gelled Hypergolic Propellants for Future Rocket and Missile Engines

DTIC Science & Technology

2014-08-13

Another aspect of the project was to develop cost- effective viscosity and surface tension determinations as a function of temperature up to 500 K. In...flow rates had an effect on the temperature observed in the stagnation zone with temperature trends from the numerical simulations being similar to...for the single step in the reaction mechanism was varied so as to provide information on the effect of reaction rates on the temperature 137 99

A Densified Liquid Methane Delivery System for the Altair Ascent Stage

NASA Technical Reports Server (NTRS)

Tomsik, Thomas M.; Johnson, Wesley L.; Smudde, Todd D.; Femminineo, Mark F.; Schnell, Andrew R.

2010-01-01

The Altair Lunar Lander is currently carrying options for both cryogenic and hypergolic ascent stage propulsion modules. The cryogenic option uses liquid methane and liquid oxygen to propel Altair from the lunar surface back to rendezvous with the Orion command module. Recent studies have determined that the liquid methane should be densified by subcooling it to 93 K in order to prevent over-pressurization of the propellant tanks during the 210 day stay on the lunar surface. A trade study has been conducted to determine the preferred method of producing; loading, and maintaining the subcooled, densified liquid methane onboard Altair from a ground operations perspective. The trade study took into account the limitations in mass for the launch vehicle and the mobile launch platform as well as the historical reliability of various components and their thermal efficiencies. Several unique problems were encountered, namely delivering a small amount of a cryogenic propellant to a flight tank that is positioned over 350 ft above the launch pad as well as generating the desired delivery temperature of the methane at 93 K which is only 2.3 K above the methane triple point of 90.7 K. Over 20 methods of subcooled liquid methane production and delivery along with the associated system architectures were investigated to determine the best solutions to the problem. The top four cryogenic processing solutions were selected for further evaluation and detailed thermal modeling. This paper describes the results of the preliminary trade analysis of the 20 plus methane densification methods considered. The results of the detailed analysis will be briefed to the Altair Project Office and their propulsion team as well as the Ground Operations Project Office before the down-select is made between cryogenic and hypergolic ascent stages in August 2010.

Functionalization and Passivation of Boron Nanoparticles with a Hypergolic Ionic Liquid (Pre-Print)

DTIC Science & Technology

2012-04-01

Department of Chemistry , University of Utah, 315 S 1400 E, Salt Lake City, UT 84112, USA Stefan Schneider3, Jerry Boatz4 and Tom Hawkins5 Propellants...USA Parker D. McCrary6, Preston A. Beasley6, Steven P. Kelley6 and Robin D. Rogers7 Center for Green Manufacturing and Department of Chemistry ... Chemistry , The University of Utah, 315 S. 1400 E., Rm. b107, Salt Lake City, UT 84112, USA. 2 Principal Investigator and Professor, Department of

Spray and Combustion of Gelled Hypergolic Propellants

DTIC Science & Technology

2014-10-20

Anderson Postdoc tlnu 2/09 Ast:I·ium Mau DeRidder Anderson Postdoc tlnu 5110 Spacex Chenzhou Lian Merkle Postdoc tlnu 8/10 IBM Watson Labs Changjin Yoon...Heister PhD, 1211 1 GE Global Research Center - 5 - - 6 - Erik Dambach Heister/Pourpoint PhD, 5/11 SpaceX Paulo Santos Campanella PhD, 8/11...Yair Solomon Anderson MS, 8/12 Technion Jordan Forness Heister/Pourpoint MS, 5/13 SpaceX Jennifer Mallory Sojka PhD, 5/12 Western New England

Research and Development of Energetic Ionic Liquids

DTIC Science & Technology

2012-03-01

Navy/ AF ) – USAF AF - M315E • Propellant uses ionic liquids to yield low vapor toxicity 22 – Sweden/ECAPS LMP-103S • Propellant uses ADN-based formulation...hydrazine replacement monopropellant objectives, relevant monopropellant properties, AF -M1028A monopropellant composition and physical properties...thruster tests of AF -M1028A, ionic liquids as explosives, predictive toxicology, predictive methods expected payoff. AFRL continues efforts in energetic

A Mixing Length Scale of Unlike Impinging Jets

NASA Astrophysics Data System (ADS)

Inoue, Chihiro; Fujii, Go; Daimon, Yu

2017-11-01

Bi-propellant thrusters in space propulsion systems often utilize unlike-doublet or triplet injectors. The impingement of hypergolic liquid jet streams of fuel and oxidizer involves the expanding sheet, droplet fragmentation, mixing, evaporation, and chemical reactions in liquid and gas phases, in which the rate controlling phenomenon is the mixing step. In this study, a defined length scale demonstrates the distribution of fuel and oxidizer, and therefore, represents their mixing states, allowing for providing a physical meaning of widely accepted practical indicator, so called Rupe factor, over half a century of injector design history. We concisely formulate the characteristic velocity in a consistent manner for doublet and triplet injectors as a function of propellant injection conditions. The validity of the present formulation is convinced by comparing with hot firing tests.

Analysis of a Hypergolic Propellant Explosion During Processing of Launch Vehicles in the VAB

NASA Technical Reports Server (NTRS)

Chrostowski, Jon D.; Gan Wenshui; Campbell, Michael D.

2010-01-01

NASA is developing launch vehicles to support missions to Low Earth Orbit (LEO), the moon and deep space. Whether manned or unmanned, the vehicle components will likely be integrated in the Vehicle Assembly Building (VAB) at Kennedy Space Center (KSC) and typically include a fueled spacecraft (SC) that sits on top of one or more stages. The processing of a fueled SC involves hazardous operations when it is brought into the VAB Transfer Aisle and lifted a significant height for mating with lower stages. Accidents resulting from these hazardous operations could impact unrelated personnel working in buildings adjacent to the VAB. Safe separation distances based on the DOD Explosives Standards Quantity-Distance (Q-D) approach result in large IBD arcs. This paper presents site-specific air blast and fragmentation hazard analyses for comparison with the Q-D arcs as well as consequence and risk analyses to provide added information for the decision maker. A new physics-based fragmentation model is presented that includes: a) the development of a primary fragment list (which defines the fragment characteristics) associated with a hypergolic propellant explosion, b) a description of a 3D fragment bounce model, c) the results of probabilistic Monte-Carlo simulations (that include uncertainties in the fragment characteristics) to determine: i) the hazardous fragment density distance, ii) the expected number of wall/roof impacts and penetrations to over 40 buildings adjacent to the VAB, and iii) the risk to building occupants.

Standards Development Activities at White Sands Test Facility

NASA Technical Reports Server (NTRS)

Baker, D. L.; Beeson, H. D.; Saulsberry, R. L.; Julien, H. L.; Woods, S. S.

2003-01-01

The development of standards and standard activities at the JSC White Sands Test Facility (WSTF) has been expanded to include the transfer of technology and standards to voluntary consensus organizations in five technical areas of importance to NASA. This effort is in direct response to the National Technology Transfer Act designed to accelerate transfer of technology to industry and promote government-industry partnerships. Technology transfer is especially important for WSTF, whose longterm mission has been to develop and provide vital propellant safety and hazards information to aerospace designers, operations personnel, and safety personnel. Meeting this mission is being accomplished through the preparation of consensus guidelines and standards, propellant hazards analysis protocols, and safety courses for the propellant use of hydrogen, oxygen, and hypergols, as well as the design and inspection of spacecraft pressure vessels and the use of pyrovalves in spacecraft propulsion systems. The overall WSTF technology transfer program is described and the current status of technology transfer activities are summarized.

Green hypergolic combination: Diethylenetriamine-based fuel and hydrogen peroxide

NASA Astrophysics Data System (ADS)

Kang, Hongjae; Kwon, Sejin

2017-08-01

The present research dealt with the concept of green hypergolic combination to replace the toxic hypergolic combinations. Hydrogen peroxide was selected as a green oxidizer. A novel recipe for the non-toxic hypergolic fuel (Stock 3) was suggested. Sodium borohydride was blended into the mixture of energetic hydrocarbon solvents as an ignition source for hypergolic ignition. The main ingredient of the mixture was diethylenetriamine. By mixing some amount of tetrahydrofuran with diethylenetriamine, the mixture became more flammable and volatile. The mixture of Stock 3 fuel remained stable for four months in the lab scale storability test. Through a simple drop test, the hypergolicity of the green hypergolic combination was verified. Comparing to the toxic hypergolic combination MMH/NTO as the reference, the theoretical performance of the green hypergolic combination would be achieved about 96.7% of the equilibrium specific impulse and about 105.7% of the density specific impulse. The applicability of the green hypergolic combination was successfully confirmed through the static hot-fire tests using 500 N scale hypergolic thruster.

4. Credit USAF, ca. 1945. Original housed in the Photograph ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

4. Credit USAF, ca. 1945. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. Low level oblique aerial view of Muroc Flight Test Base (North Base), looking southwest along flightline. HANG-P-A hangar (Building 4505) is in the right foreground. A Bell XP-59A Airacomet, the United States military's first jet propelled aircraft, is being towed on the apron toward the control tower. Other aircraft in the foreground include Douglas DC-3s, North American Aviation P-51 Mustangs, and Lockheed P-38 Lightnings. - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

Control of Propellant Lead/Lag to the LAE in the AXAF Propulsion System

NASA Technical Reports Server (NTRS)

Casillas, A. R.; Eninger, J.; Joseph, G.; Kenney, J.; Trinidad, M.

1998-01-01

Control of the rate at which hypergolic propellants are supplied to a rocket engine prior to ignition is critically important. Potentially damaging explosions may result from excessive lead of either propellant into the combustion chamber. Because the injector fill process is governed by the engine as well as the propellant feed system design, proper management of this issue must take both into consideration. This was recognized early in the development of TRW's Advanced Columbium-Liquid Apogee Engine (LAE), which was flight-qualified in 1996 to maneuver the Advanced X-Ray Astrophysics Facility (AXAF) spacecraft into orbit. The LAE runs on hydrazine and nitrogen tetroxide (MON-3) at a nominal mixture ratio of 1.0. This paper describes the comprehensive test program conducted to ensure reliable startup operation of the LAE in the AYAF propulsion system. The most significant factors affecting chamber fuel lead were found to be: (1) engine location, (2) propellant saturation level, (3) amount of undissolved gas in the lines, and (4) off- nominal tank pressures. Hot-fire tests at a chamber fuel lead range over and above that expected for the LAEs in AXAF demonstrated extremely tolerant behavior of the engine. AY-AF is scheduled for launch on NASA's STS-93 in December 1998.

Propulsion Risk Reduction Activities for Non-Toxic Cryogenic Propulsion

NASA Technical Reports Server (NTRS)

Smith, Timothy D.; Klem, Mark D.; Fisher, Kenneth

2010-01-01

The Propulsion and Cryogenics Advanced Development (PCAD) Project s primary objective is to develop propulsion system technologies for non-toxic or "green" propellants. The PCAD project focuses on the development of non-toxic propulsion technologies needed to provide necessary data and relevant experience to support informed decisions on implementation of non-toxic propellants for space missions. Implementation of non-toxic propellants in high performance propulsion systems offers NASA an opportunity to consider other options than current hypergolic propellants. The PCAD Project is emphasizing technology efforts in reaction control system (RCS) thruster designs, ascent main engines (AME), and descent main engines (DME). PCAD has a series of tasks and contracts to conduct risk reduction and/or retirement activities to demonstrate that non-toxic cryogenic propellants can be a feasible option for space missions. Work has focused on 1) reducing the risk of liquid oxygen/liquid methane ignition, demonstrating the key enabling technologies, and validating performance levels for reaction control engines for use on descent and ascent stages; 2) demonstrating the key enabling technologies and validating performance levels for liquid oxygen/liquid methane ascent engines; and 3) demonstrating the key enabling technologies and validating performance levels for deep throttling liquid oxygen/liquid hydrogen descent engines. The progress of these risk reduction and/or retirement activities will be presented.

Propulsion Risk Reduction Activities for Nontoxic Cryogenic Propulsion

NASA Technical Reports Server (NTRS)

Smith, Timothy D.; Klem, Mark D.; Fisher, Kenneth L.

2010-01-01

The Propulsion and Cryogenics Advanced Development (PCAD) Project s primary objective is to develop propulsion system technologies for nontoxic or "green" propellants. The PCAD project focuses on the development of nontoxic propulsion technologies needed to provide necessary data and relevant experience to support informed decisions on implementation of nontoxic propellants for space missions. Implementation of nontoxic propellants in high performance propulsion systems offers NASA an opportunity to consider other options than current hypergolic propellants. The PCAD Project is emphasizing technology efforts in reaction control system (RCS) thruster designs, ascent main engines (AME), and descent main engines (DME). PCAD has a series of tasks and contracts to conduct risk reduction and/or retirement activities to demonstrate that nontoxic cryogenic propellants can be a feasible option for space missions. Work has focused on 1) reducing the risk of liquid oxygen/liquid methane ignition, demonstrating the key enabling technologies, and validating performance levels for reaction control engines for use on descent and ascent stages; 2) demonstrating the key enabling technologies and validating performance levels for liquid oxygen/liquid methane ascent engines; and 3) demonstrating the key enabling technologies and validating performance levels for deep throttling liquid oxygen/liquid hydrogen descent engines. The progress of these risk reduction and/or retirement activities will be presented.

Green Application for Space Power

NASA Technical Reports Server (NTRS)

Robinson, Joel

2015-01-01

Most space vehicle auxiliary power units (APUs) use hydrazine propellant for generating power. Hydrazine is a toxic, hazardous fuel that requires special safety equipment and processes for handling and loading. In recent years, there has been development of two green propellants (less toxic) that could enable their use in APUs. The Swedish government, in concert with the Swedish Space Corporation, has developed a propellant based on ammonium dinitramide (LMP-103S) that was flown on the Prisma spacecraft in 2010. The United States Air Force (USAF) has been developing a propellant based on hydroxylammonium nitrate (AFM315E) that is scheduled to fly on the Green Propellant Infusion Mission in the spring of 2016 to demonstrate apogee and reaction control thrusters. However, no one else in the Agency is currently pursuing use of green propellants for application to the APUs. Per the TA-01 Launch Propulsion Roadmap, the Space Technology Mission Directorate had identified the need to have a green propellant APU by 2015. This is our motivation for continuing activities.

QuEST: Qualifying Environmentally Sustainable Technologies, Volume 5

NASA Technical Reports Server (NTRS)

Lewis, Pattie

2010-01-01

This edition of the QuEST newsletter contains brief articles that discuss the NASA Technology Evaluation for Environmental Risk Mitigation (TEERM) program, and the importance of collaboration, efforts in materials management and substitution for coatings for launch structures, Low volatile organic compound (VOC) Coatings Field Testing, Non-Chrome Coating Systems, Life Cycle Corrosion Testing, Lead-Free Electronics Testing and Corn Based Depainting and efforts in Pollution Control in the area of Hypergolic Propellant Destruction Evaluation, efforts in development of alternative energy in particular Hydrogen Sensors, Energy and Water Management, and efforts in remediation in the removal of Polychlorinated Biphenyl (PCB) contamination

KSC00pp0449

NASA Image and Video Library

2000-03-20

A recently installed fertilizer-producing system sits near Launch Pad 39A. Using a "scrubber," the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. Plans call for the resulting fertilizer to be used on the orange groves that KSC leases to outside companies

KSC-00pp0449

NASA Image and Video Library

2000-03-20

A recently installed fertilizer-producing system sits near Launch Pad 39A. Using a "scrubber," the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. Plans call for the resulting fertilizer to be used on the orange groves that KSC leases to outside companies

New fertilizer-producing system installed at Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

A recently installed fertilizer-producing system sits near Launch Pad 39A. Using a 'scrubber,' the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. Plans call for the resulting fertilizer to be used on the orange groves that KSC leases to outside companies.

Cis-Lunar Reusable In-Space Transportation Architecture for the Evolvable Mars Campaign

NASA Technical Reports Server (NTRS)

McVay, Eric S.; Jones, Christopher A.; Merrill, Raymond G.

2016-01-01

Human exploration missions to Mars or other destinations in the solar system require large quantities of propellant to enable the transportation of required elements from Earth's sphere of influence to Mars. Current and proposed launch vehicles are incapable of launching all of the requisite mass on a single vehicle; hence, multiple launches and in-space aggregation are required to perform a Mars mission. This study examines the potential of reusable chemical propulsion stages based in cis-lunar space to meet the transportation objectives of the Evolvable Mars Campaign and identifies cis-lunar propellant supply requirements. These stages could be supplied with fuel and oxidizer delivered to cis-lunar space, either launched from Earth or other inner solar system sources such as the Moon or near Earth asteroids. The effects of uncertainty in the model parameters are evaluated through sensitivity analysis of key parameters including the liquid propellant combination, inert mass fraction of the vehicle, change in velocity margin, and change in payload masses. The outcomes of this research include a description of the transportation elements, the architecture that they enable, and an option for a campaign that meets the objectives of the Evolvable Mars Campaign. This provides a more complete understanding of the propellant requirements, as a function of time, that must be delivered to cis-lunar space. Over the selected sensitivity ranges for the current payload and schedule requirements of the 2016 point of departure of the Evolvable Mars Campaign destination systems, the resulting propellant delivery quantities are between 34 and 61 tonnes per year of hydrogen and oxygen propellant, or between 53 and 76 tonnes per year of methane and oxygen propellant, or between 74 and 92 tonnes per year of hypergolic propellant. These estimates can guide future propellant manufacture and/or delivery architectural analysis.

CFD Analysis of Spray Combustion and Radiation in OMV Thrust Chamber

NASA Technical Reports Server (NTRS)

Giridharan, M. G.; Krishnan, A.; Przekwas, A. J.; Gross, K.

1993-01-01

The Variable Thrust Engine (VTE), developed by TRW, for the Orbit Maneuvering Vehicle (OMV) uses a hypergolic propellant combination of Monomethyl Hydrazine (MMH) and Nitrogen Tetroxide (NTO) as fuel and oxidizer, respectively. The propellants are pressure fed into the combustion chamber through a single pintle injection element. The performance of this engine is dependent on the pintle geometry and a number of complex physical phenomena and their mutual interactions. The most important among these are (1) atomization of the liquid jets into fine droplets; (2) the motion of these droplets in the gas field; (3) vaporization of the droplets (4) turbulent mixing of the fuel and oxidizer; and (5) hypergolic reaction between MMH and NTO. Each of the above phenomena by itself poses a considerable challenge to the technical community. In a reactive flow field of the kind occurring inside the VTE, the mutual interactions between these physical processes tend to further complicate the analysis. The objective of this work is to develop a comprehensive mathematical modeling methodology to analyze the flow field within the VTE. Using this model, the effect of flow parameters on various physical processes such as atomization, spray dynamics, combustion, and radiation is studied. This information can then be used to optimize design parameters and thus improve the performance of the engine. The REFLEQS CFD Code is used for solving the fluid dynamic equations. The spray dynamics is modeled using the Eulerian-Lagrangian approach. The discrete ordinate method with 12 ordinate directions is used to predict the radiative heat transfer in the OMV combustion chamber, nozzle, and the heat shield. The hypergolic reaction between MMH and NTO is predicted using an equilibrium chemistry model with 13 species. The results indicate that mixing and combustion is very sensitive to the droplet size. Smaller droplets evaporate faster than bigger droplets, leading to a well mixed zone in the combustion chamber. The radiative heat flux at combustion chamber and nozzle walls are an order of negligible less than the conductive heat flux. Simulations performed with the heat shield show that a negligible amount of fluid is entrained into the heat shield region. However, the heat shield is shown to be effective in protecting the OMV structure surrounding the engine from the radiated heat.

KSC00pp0511

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- Clyde Parrish, a NASA/KSC engineer, explains how the fertilizer scrubber control panel (center) works to turn nitrogen tetroxide vapor into fertilizer, potassium hydroxide. Parrish developed the system, which uses a "scrubber," to capture nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate. The resulting fertilizer will be used on the orange groves that KSC leases to outside companies

KSC00pp0510

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- A recently installed fertilizer-producing system sits near Launch Pad 39A (upper left background). Using a "scrubber," the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. The black tanker at left is collecting the potassium nitrate, which will be used on the orange groves that KSC leases to outside companies

KSC-00pp0510

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- A recently installed fertilizer-producing system sits near Launch Pad 39A (upper left background). Using a "scrubber," the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. The black tanker at left is collecting the potassium nitrate, which will be used on the orange groves that KSC leases to outside companies

KSC-00pp0511

NASA Image and Video Library

2000-04-07

KENNEDY SPACE CENTER, FLA. -- Clyde Parrish, a NASA/KSC engineer, explains how the fertilizer scrubber control panel (center) works to turn nitrogen tetroxide vapor into fertilizer, potassium hydroxide. Parrish developed the system, which uses a "scrubber," to capture nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate. The resulting fertilizer will be used on the orange groves that KSC leases to outside companies

The new fertilizer-producing facility near Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

A recently installed fertilizer-producing system sits near Launch Pad 39A (upper left background). Using a 'scrubber,' the system captures nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate, a commercial fertilizer. The black tanker at left is collecting the potassium nitrate, which will be used on the orange groves that KSC leases to outside companies.

Propellant Feed Subsystem for a 26 kW flight arcjet propulsion system

NASA Astrophysics Data System (ADS)

Vaughan, C. E.; Morris, J. P.

1993-06-01

The USAF arcjet ATTD program demanded the development of a low-cost ammonia Propellant Feed Subsystem (PFS). A flow rate of 240 +/- 5 mg/sec during a total of ten 15-min ammonia outflows was required for the flight mission. The precision of the flow tolerance required a departure from the design of previous ammonia propellant feed systems. Since a propellant management device was not used, thermocapillary forces were explored as a means to limit outflow of liquid phase ammonia. A high energy density feedline heater with an internal wick was developed to guarantee that only gas phase propellant would reach the arcjet. A digital control algorithm was developed to implement bang-bang control of mass flow rate metered by a sonic venturi. Development tests of this system have been completed. The system is capable of continuous gas phase outflows regardless of orientation. Integrated tests with the arcjet and power conditioning unit have also been successfully completed.

Thermodynamic Vent System for an On-Orbit Cryogenic Reaction Control Engine

NASA Technical Reports Server (NTRS)

Hurlbert, Eric A.; Romig, Kris A.; Jimenez, Rafael; Flores, Sam

2012-01-01

A report discusses a cryogenic reaction control system (RCS) that integrates a Joule-Thompson (JT) device (expansion valve) and thermodynamic vent system (TVS) with a cryogenic distribution system to allow fine control of the propellant quality (subcooled liquid) during operation of the device. It enables zero-venting when coupled with an RCS engine. The proper attachment locations and sizing of the orifice are required with the propellant distribution line to facilitate line conditioning. During operations, system instrumentation was strategically installed along the distribution/TVS line assembly, and temperature control bands were identified. A sub-scale run tank, full-scale distribution line, open-loop TVS, and a combination of procured and custom-fabricated cryogenic components were used in the cryogenic RCS build-up. Simulated on-orbit activation and thruster firing profiles were performed to quantify system heat gain and evaluate the TVS s capability to maintain the required propellant conditions at the inlet to the engine valves. Test data determined that a small control valve, such as a piezoelectric, is optimal to provide continuously the required thermal control. The data obtained from testing has also assisted with the development of fluid and thermal models of an RCS to refine integrated cryogenic propulsion system designs. This system allows a liquid oxygenbased main propulsion and reaction control system for a spacecraft, which improves performance, safety, and cost over conventional hypergolic systems due to higher performance, use of nontoxic propellants, potential for integration with life support and power subsystems, and compatibility with in-situ produced propellants.

Green Applications for Space Power Project

NASA Technical Reports Server (NTRS)

Robinson, Joel (Principal Investigator)

2014-01-01

Spacecraft propulsion and power for many decades has relied on Hydrazine monopropellant technology for auxiliary power units (APU), orbital circularization, orbit raising/lowering and attitude control. However, Hydrazine is toxic and therefore requires special ground handling procedures to ensure launch crew safety. The Swedish Company ECAPS has developed a technology based upon the propellant Ammonium Dinitramide (ADN) that offers higher performance, higher density and reduced ground handling support than Hydrazine. This blended propellant is called LMP-103S. Currently, the United States Air Force (USAF) is pursuing a technology based on Hydroxyl Ammonium Nitrate (HAN, otherwise known as AF-M315E) with industry partners Aerojet and Moog. Based on the advantages offered by these propellants, MSFC should explore powering APU's with these propellants. Due to the availability of space hardware, the principal investigator has found a collection of USAF hardware, that will act as a surrogate, which operates on a Hydrazine derivative. The F-16 fighter jet uses H-70 or 30% diluted Hydrazine for an Emergency Power Unit (EPU) which supplies power to the plane. The PI has acquired two EPU's from planes slated for destruction at the Davis Monthan AFB. This CIF will include a partnership with 2 other NASA Centers who are individually seeking seed funds from their respective organizations: Kennedy Space Center (KSC) and Dryden Flight Research Center (DFRC). KSC is preparing for future flights from their launch pads that will utilize green propellants and desire a low-cost testbed in which to test and calibrate new leak detection sensors. DFRC has access to F-16's which can be used by MSFC & KSC to perform a ground test that demonstrates emergency power supplied to the jet. Neither of the green propellant alternatives have been considered nor evaluated for an APU application. Work has already been accomplished to characterize and obtain the properties of these 2 propellants. However, the spacecraft are using existing leak detection sensors that are typically used for Hydrazine. Using these green propellants for the APU application requires decrementing their TRL down to 3. This task would aim to establish a TRL of 4 at conclusion by showing a proof of concept with a KSC-instrumented EPU asset at the MSFC Component Development Area (CDA). The task to accomplish this is called Green Application for Space Power or GRASP.

Electronic nose for space program applications

NASA Technical Reports Server (NTRS)

Young, Rebecca C.; Buttner, William J.; Linnell, Bruce R.; Ramesham, Rajeshuni

2003-01-01

The ability to monitor air contaminants in the shuttle and the International Space Station is important to ensure the health and safety of astronauts, and equipment integrity. Three specific space applications have been identified that would benefit from a chemical monitor: (a) organic contaminants in space cabin air; (b) hypergolic propellant contaminants in the shuttle airlock; (c) pre-combustion signature vapors from electrical fires. NASA at Kennedy Space Center (KSC) is assessing several commercial and developing electronic noses (E-noses) for these applications. A short series of tests identified those E-noses that exhibited sufficient sensitivity to the vapors of interest. Only two E-noses exhibited sufficient sensitivity for hypergolic fuels at the required levels, while several commercial E-noses showed sufficient sensitivity of common organic vapors. These E-noses were subjected to further tests to assess their ability to identify vapors. Development and testing of E-nose models using vendor supplied software packages correctly identified vapors with an accuracy of 70-90%. In-house software improvements increased the identification rates between 90 and 100%. Further software enhancements are under development. Details on the experimental setup, test protocols, and results on E-nose performance are presented in this paper along with special emphasis on specific software enhancements. c2003 Elsevier Science B.V. All rights reserved.

Incorporation of Chemochromic Pigment into a Variety of Articles as an Indicator for the Presence of Hypergolic Fuels

NASA Technical Reports Server (NTRS)

Captain, Janine E. (Inventor); Santiago-Maldonado, Edgardo (Inventor); Roberson, Luke B. (Inventor); DeVor, Robert W. (Inventor)

2014-01-01

A chemochromic indicator is provided that includes a hypergolic fuel sensing chemochromic pigment that change from a first color to a second color in the presence of a hypergolic fuel. In a first embodiment, a chemochromic indicator is provided for detecting the presence of a hypergolic fuel such that the irreversible hypergolic fuel sensing chemochromic pigment includes potassium tetrachloroaurate (KAuCl.sub.4). There are several types of chemochromic indicators, for example, the article used to form the chemochromic indicators include, but are not limited to, wipe materials, silicone/TEFLON tape, manufactured parts, fabrics, extruded parts, and paints.

On-Board Chemical Propulsion

NASA Technical Reports Server (NTRS)

Schneider, Steven J.

1997-01-01

NASA Lewis Research Center's On-Board Propulsion program (OBP) is developing low-thrust chemical propulsion technologies for both satellite and vehicle reaction control applications. There is a vigorous international competition to develop new, highperformance bipropellant engines. High-leverage bipropellant systems are critical to both commercial competitiveness in the international communications market and to cost-effective mission design in government sectors. To significantly improve bipropellant engine performance, we must increase the thermal margin of the chamber materials. Iridium-coated rhenium (Ir/Re) engines, developed and demonstrated under OBP programs, can operate at temperatures well above the constraints of state-of-practice systems, providing a sufficient margin to maximize performance with the hypergolic propellants used in most satellite propulsion systems.

The hard start phenomena in hypergolic engines. Volume 5: RCS engine deformation and destruct tests

NASA Technical Reports Server (NTRS)

Miron, Y.; Perlee, H. E.

1974-01-01

Tests were conducted to determine the causes of Apollo Reaction Control (RCS) engine failures. Stainless steel engines constructed for use in the destructive tests are described. The tests conducted during the three phase investigation are discussed. It was determined that the explosive reaction that destroys the RCS engines occurs at the time of engine ignition and is apparently due to either the detonation of the heterogeneous constituents of the rocket engine, consisting primarily of unreacted propellant droplets and vapors, and/or the detonation of explosive materials accumulated on the engine walls from previous pulses. Photographs of the effects of explosions on the simulated RCS engines are provided.

Apollo 15 main-parachute failure

NASA Technical Reports Server (NTRS)

Arabian, D. D.; Mechelay, J. E.

1972-01-01

In the investigation of the failure of one of the three main parachutes of the Apollo 15 spacecraft, which collapsed at approximately 1825 meters after operating properly from deployment at 3050 meters, three conditions considered to be possible causes of the failure were produced. The suspect conditions were the proximity of the forward heat shield that passed the spacecraft at approximately 1825 meters, the dumping of the reaction control system hypergolic propellants at approximately 1825 meters, and the failing of a riser link found on a recovered parachute. (The failed parachute was not recovered). The remaining two parachutes functioned as planned and averted a catastrophic failure. The conclusions concerning the cause of the failure are discussed.

CATIA V5 Virtual Environment Support for Constellation Ground Operations

NASA Technical Reports Server (NTRS)

Kelley, Andrew

2009-01-01

This summer internship primarily involved using CATIA V5 modeling software to design and model parts to support ground operations for the Constellation program. I learned several new CATIA features, including the Imagine and Shape workbench and the Tubing Design workbench, and presented brief workbench lessons to my co-workers. Most modeling tasks involved visualizing design options for Launch Pad 39B operations, including Mobile Launcher Platform (MLP) access and internal access to the Ares I rocket. Other ground support equipment, including a hydrazine servicing cart, a mobile fuel vapor scrubber, a hypergolic propellant tank cart, and a SCAPE (Self Contained Atmospheric Protective Ensemble) suit, was created to aid in the visualization of pad operations.

A KSC engineer describes the new fertilizer-producing facility near Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

Clyde Parrish, a NASA/KSC engineer, explains how the fertilizer scrubber control panel (center) works to turn nitrogen tetroxide vapor into fertilizer, potassium hydroxide. Parrish developed the system, which uses a 'scrubber,' to capture nitrogen tetroxide vapor that develops as a by-product when it is transferred from ground storage tanks into the Shuttle storage tanks. Nitrogen tetroxide is used as the oxidizer for the hypergolic propellant in the Shuttle's on-orbit reaction control system. The scrubber then uses hydrogen peroxide to produce nitric acid, which, after adding potassium hydroxide, converts to potassium nitrate. The resulting fertilizer will be used on the orange groves that KSC leases to outside companies.

Occupational hazards of missile operations with special regard to the hydrazine propellants.

PubMed

Back, K C; Carter, V L; Thomas, A A

1978-04-01

The second generation of ballistic missiles and boosters, characterized by increased range and quick reaction capability, required the development of new high-energy storage propellants. This exploration led to the introduction of hydrazine (Hz), monomethylhydrazine (MMH), and 1,1-dimethylhydrazine (UDMH) into the USAF inventory. These compounds are all storable, noncryogenic, high-energy fuels which may be used alone or in combination as mixed amine fuels. Early toxicology experiments were to produce data on acute and subacute effects of the propellants in order to set standards for test and operational procedures to protect propellant handlers. The early work indicated that, despite similar chemical characteristics, there were marked differences between the compounds in terms of toxicological mechanisms. Since the propellant systems have been used for some 15 years, recent emphasis on toxicology has been centered on the more chronic effects and on an increasing body of evidence from animal experiments that the compounds may possess oncogenic potential as well as chronic systemic effects. This paper addresses itself to data leading up to current occupational standards.

LADEE Propulsion System Cold Flow Test

NASA Technical Reports Server (NTRS)

Williams, Jonathan Hunter; Chapman, Jack M.; Trinh, Hau, P.; Bell, James H.

2013-01-01

Lunar Atmosphere and Dust Environment Explorer (LADEE) is a NASA mission that will orbit the Moon. Its main objective is to characterize the atmosphere and lunar dust environment. The spacecraft development is being led by NASA Ames Research Center and scheduled for launch in 2013. The LADEE spacecraft will be operated with a bi-propellant hypergolic propulsion system using MMH and NTO as the fuel and oxidizer, respectively. The propulsion system utilizes flight-proven hardware on major components. The propulsion layout is composed of one 100-lbf main thruster and four 5-lbf RCS thrusters. The propellants are stored in four tanks (two parallel-connected tanks per propellant component). The propellants will be pressurized by regulated helium. A simulated propulsion system has been built for conducting cold flow test series to characterize the transient fluid flow of the propulsion system feed lines and to verify the critical operation modes, such as system priming, waterhammer, and crucial mission duty cycles. Propellant drainage differential between propellant tanks will also be assessed. Since the oxidizer feed line system has a higher flow demand than the fuel system does, the cold flow test focuses on the oxidizer system. The objective of the cold flow test is to simulate the LADEE propulsion fluid flow operation through water cold flow test and to obtain data for anchoring analytical models. The models will be used to predict the transient and steady state flow behaviors in the actual flight operations. The test activities, including the simulated propulsion test article, cold flow test, and analytical modeling, are being performed at NASA Marshall Space Flight Center. At the time of the abstract submission, the test article checkout is being performed. The test series will be completed by November, 2012

Color-Changing Sensors for Detecting the Presence of Hypergolic Fuels

NASA Technical Reports Server (NTRS)

Roberson, Luke; Captain, Janine; Santiago-Maldonado, Edgardo; Starr, Stanley; DeVor, Robert

2013-01-01

Hypergolic fuel sensors were designed to incorporate novel chemochromic pigments into substrates for use in various methods of leak detection. There are several embodiments to this invention that would provide specific visual indication of hypergols used during and after transfer. The ability to incorporate these pigments into various polymer matrices provides a unique opportunity to manufacture nearly any type of sensor shape that is required. The vibrant color change from yellow to black instantaneously shows the worker the presence of hypergols in the area.

Electrical Pressurization Concept for the Orion MPCV European Service Module Propulsion System

NASA Technical Reports Server (NTRS)

Meiss, Jan-Hendrik; Weber, Jorg; Ierardo, Nicola; Quinn, Frank D.; Paisley, Jonathan

2015-01-01

The paper presents the design of the pressurization system of the European Service Module (ESM) of the Orion Multi-Purpose Crew Vehicle (MPCV). Being part of the propulsion subsystem, an electrical pressurization concept is implemented to condition propellants according to the engine needs via a bang-bang regulation system. Separate pressurization for the oxidizer and the fuel tank permits mixture ratio adjustments and prevents vapor mixing of the two hypergolic propellants during nominal operation. In case of loss of pressurization capability of a single side, the system can be converted into a common pressurization system. The regulation concept is based on evaluation of a set of tank pressure sensors and according activation of regulation valves, based on a single-failure tolerant weighting of three pressure signals. While regulation is performed on ESM level, commanding of regulation parameters as well as failure detection, isolation and recovery is performed from within the Crew Module, developed by Lockheed Martin Space System Company. The overall design and development maturity presented is post Preliminary Design Review (PDR) and reflects the current status of the MPCV ESM pressurization system.

The NASA/USAF arcjet research and technology program

NASA Technical Reports Server (NTRS)

Stone, James R.; Huston, Edward S.

1987-01-01

Direct current arcjets have the potential to provide specific impulses greater than 500 sec with storable propellants, and greater than 1000 sec with hydrogen. This level of performance can provide significant benefits for such applications as orbit transfer, station keeping, orbit change, and maneuvering. The simplicity of the arcjet system and its elements of commonality with state-of-the-art resistojet systems offer a relatively low risk transition to these enhanced levels of performance for low power (0.5 to 1.5 kW) station keeping applications. Arcjets at power levels of 10 to 30 kW are potentially applicable to orbit transfer missions. Furthermore, with the anticipated development of space nuclear power systems, arcjets at greater than 100 kW may become attractive. This paper describes the ongoing NASA/USAF program and describes major recent accomplishments.

Liquid Oxygen/Liquid Methane Test Summary of the RS-18 Lunar Ascent Engine at Simulated Altitude Conditions at NASA White Sands Test Facility

NASA Technical Reports Server (NTRS)

Melcher, John C., IV; Allred, Jennifer K.

2009-01-01

Tests were conducted with the RS18 rocket engine using liquid oxygen (LO2) and liquid methane (LCH4) propellants under simulated altitude conditions at NASA Johnson Space Center White Sands Test Facility (WSTF). This project is part of NASA s Propulsion and Cryogenics Advanced Development (PCAD) project. "Green" propellants, such as LO2/LCH4, offer savings in both performance and safety over equivalently sized hypergolic propellant systems in spacecraft applications such as ascent engines or service module engines. Altitude simulation was achieved using the WSTF Large Altitude Simulation System, which provided altitude conditions equivalent up to approx.120,000 ft (approx.37 km). For specific impulse calculations, engine thrust and propellant mass flow rates were measured. Propellant flow rate was measured using a coriolis-style mass-flow meter and compared with a serial turbine-style flow meter. Results showed a significant performance measurement difference during ignition startup. LO2 flow ranged from 5.9-9.5 lbm/sec (2.7-4.3 kg/sec), and LCH4 flow varied from 3.0-4.4 lbm/sec (1.4-2.0 kg/sec) during the RS-18 hot-fire test series. Thrust was measured using three load cells in parallel. Ignition was demonstrated using a gaseous oxygen/methane spark torch igniter. Data was obtained at multiple chamber pressures, and calculations were performed for specific impulse, C* combustion efficiency, and thrust vector alignment. Test objectives for the RS-18 project are 1) conduct a shakedown of the test stand for LO2/methane lunar ascent engines, 2) obtain vacuum ignition data for the torch and pyrotechnic igniters, and 3) obtain nozzle kinetics data to anchor two-dimensional kinetics codes.

Spark Ignition Characteristics of a L02/LCH4 Engine at Altitude Conditions

NASA Technical Reports Server (NTRS)

Kleinhenz, Julie; Sarmiento, Charles; Marshall, William

2012-01-01

The use of non-toxic propellants in future exploration vehicles would enable safer, more cost effective mission scenarios. One promising "green" alternative to existing hypergols is liquid methane/liquid oxygen. To demonstrate performance and prove feasibility of this propellant combination, a 100lbf LO2/LCH4 engine was developed and tested under the NASA Propulsion and Cryogenic Advanced Development (PCAD) project. Since high ignition energy is a perceived drawback of this propellant combination, a test program was performed to explore ignition performance and reliability versus delivered spark energy. The sensitivity of ignition to spark timing and repetition rate was also examined. Three different exciter units were used with the engine s augmented (torch) igniter. Propellant temperature was also varied within the liquid range. Captured waveforms indicated spark behavior in hot fire conditions was inconsistent compared to the well-behaved dry sparks (in quiescent, room air). The escalating pressure and flow environment increases spark impedance and may at some point compromise an exciter s ability to deliver a spark. Reduced spark energies of these sparks result in more erratic ignitions and adversely affect ignition probability. The timing of the sparks relative to the pressure/flow conditions also impacted the probability of ignition. Sparks occurring early in the flow could trigger ignition with energies as low as 1-6mJ, though multiple, similarly timed sparks of 55-75mJ were required for reliable ignition. An optimum time interval for spark application and ignition coincided with propellant introduction to the igniter and engine. Shifts of ignition timing were manifested by changes in the characteristics of the resulting ignition.

Spark Ignition Characteristics of a LO2/LCH4 Engine at Altitude Conditions

NASA Technical Reports Server (NTRS)

Kleinhenz, Julie; Sarmiento, Charles; Marshall, William

2012-01-01

The use of non-toxic propellants in future exploration vehicles would enable safer, more cost effective mission scenarios. One promising "green" alternative to existing hypergols is liquid methane/liquid oxygen. To demonstrate performance and prove feasibility of this propellant combination, a 100lbf LO2/LCH4 engine was developed and tested under the NASA Propulsion and Cryogenic Advanced Development (PCAD) project. Since high ignition energy is a perceived drawback of this propellant combination, a test program was performed to explore ignition performance and reliability versus delivered spark energy. The sensitivity of ignition to spark timing and repetition rate was also examined. Three different exciter units were used with the engine's augmented (torch) igniter. Propellant temperature was also varied within the liquid range. Captured waveforms indicated spark behavior in hot fire conditions was inconsistent compared to the well-behaved dry sparks (in quiescent, room air). The escalating pressure and flow environment increases spark impedance and may at some point compromise an exciter.s ability to deliver a spark. Reduced spark energies of these sparks result in more erratic ignitions and adversely affect ignition probability. The timing of the sparks relative to the pressure/flow conditions also impacted the probability of ignition. Sparks occurring early in the flow could trigger ignition with energies as low as 1-6mJ, though multiple, similarly timed sparks of 55-75mJ were required for reliable ignition. An optimum time interval for spark application and ignition coincided with propellant introduction to the igniter and engine. Shifts of ignition timing were manifested by changes in the characteristics of the resulting ignition.

Prototype Chemiluminescent Analyzer for Measurement of Hydrazines and Nitrogen Dioxide.

DTIC Science & Technology

1983-10-01

propellants, mono- methyihydrazine ( MMI ), 1,1-dimethy1hydrazine (UOMH), and hydrazine (Hz), as well as nitrogen dioxide (NO2 ). Preliminary studies at the USAF...large background readings, which consisted mainly of red and infrared (ir) radiation, were obtained in these instruments (2-5), optical filters were...used. This choice eliminated both the need for optical filters and the need to cool the PMTs (since bialkali tubes have much lower dark currents than

Kinetic Studies of Reactions in Solution Using Fast Mass Spectrometry

DTIC Science & Technology

2013-08-13

dicyanamide ionic liquids Hypergolic fuels, or hypergols, can be ignited by exposure to an oxidizing agent under ambient conditions and are a common...DCA) based ionic liquids are a less volatile alternative that are less viscous than most ionic liquids ; however, ignition of these compounds...Condensates upon Hypergolic Ignition of Dicyanamide Ionic Liquids ," Angew. Chem. Int. Ed. 50, 8634–8637 (2011). (7) R. H. Perry, D. I. Bellovin, E

Method for Predicting Hypergolic Mixture Flammability Limits

DTIC Science & Technology

2017-02-01

liquid phase, in the gas phase, at the liquid / liquid interface and at the gas / liquid interface during hypergolic ignition and the interactions...of what happens in the liquid phase, in the gas phase, at the liquid / liquid interface and at the gas / liquid interface during hypergolic ignition...and the interactions of all these phases. The ignition happens in the gas -phase but products formed here and there (in the liquid phase or at

USAF Propellant Handbooks. Nitric Acid/Nitrogen Tetroxide Oxidizers. Volume II.

DTIC Science & Technology

1977-02-01

Report . MCR -64-88, Martin Marietta Corpora 32. Lukens, S.C.: Sterilizable Liquid PropulSion tion, Denver, Colorado. November 1964. System, Part I1...the Air Force Project Engineer. Mr. A. C. Wright was the Martin Marietta Program Manager. This report has been reviewed by the Information Office/DOZ...lated from test data reported by the Martin Marietta 2C2 H6 + 3NO2----- 2C6 H5 NO 2 + NO + H2 0 Company (11), Test values were obtained at four

Fast Ignition and Sustained Combustion of Ionic Liquids

NASA Technical Reports Server (NTRS)

Joshi, Prakash B. (Inventor); Piper, Lawrence G. (Inventor); Oakes, David B. (Inventor); Sabourin, Justin L. (Inventor); Hicks, Adam J. (Inventor); Green, B. David (Inventor); Tsinberg, Anait (Inventor); Dokhan, Allan (Inventor)

2016-01-01

A catalyst free method of igniting an ionic liquid is provided. The method can include mixing a liquid hypergol with a HAN (Hydroxylammonium nitrate)-based ionic liquid to ignite the HAN-based ionic liquid in the absence of a catalyst. The HAN-based ionic liquid and the liquid hypergol can be injected into a combustion chamber. The HAN-based ionic liquid and the liquid hypergol can impinge upon a stagnation plate positioned at top portion of the combustion chamber.

Low flow vortex shedding flowmeter for hypergolics/all media

NASA Technical Reports Server (NTRS)

Thinh, Ngo

1990-01-01

A family of vortex shedding flowmeters for flow measurement of hypergols that requires a long term operation without removal from system lines was further developed. A family of vortex shedding flowmeters without moving parts was designed. The test loop to evaluate the meters for the Freon flow, which simulates the hypergolic fluids, was modified and reconstructed. Preliminary results were obtained on the output frequency characteristics of an 1/2 inch flowmeter as a function of the flow rate.

Disposal of hypergolic propellants, phase 6 task 4. Disposal pond products

NASA Technical Reports Server (NTRS)

Cohenour, B. C.; Wiederhold, C. N.

1977-01-01

Waste monomethyl hydrazine scrubber liquor, consisting of aqueous solutions containing small amounts of CH4, Cl2, CH3Cl, CH2Cl2, and CHCl3 as well as large amounts of CH3OH is scheduled to be dumped in stabilization ponds along with nitrate and nitrite salt solutions obtained as waste liquors from the N2O4 scrubbers. The wastes are investigated as to the hazardous materials generated by such combinations of items as described as well as the finite lifetime of such materials in the stabilization ponds. The gas liquid chromatograph was used in the investigation. A series of experiments designed to convert nitrate and nitrite salts to the environmentally innocuous N2O and N2 using solar energy is reported. Results indicate that this solar conversion is feasible.

Green Propellant Demonstration with Hydrazine Catalyst of F-16 Emergency Power Unit

NASA Technical Reports Server (NTRS)

Robinson, Joel W.; Brechbill, Shawn

2015-01-01

Some space vehicle and aircraft Auxiliary Power Units (APUs) use hydrazine propellant for generating power. Hydrazine is a toxic, hazardous fuel which requires special safety equipment and processes for handling and loading. In recent years, there has been development of two green propellants that could enable their use in APU's: the Swedish LMP-103S and the Air Force Research Laboratory (AFRL) AF-M315E. While there has been work on development of these propellants for thruster applications (Prisma and Green Propulsion Infusion Mission, respectively), there has been less focus on the application to power units. Beginning in 2012, an effort was started by the Marshall Space Flight Center (MSFC) on the APU application. The MSFC plan was to demonstrate green propellants with residual Space Shuttle hardware. The principal investigator was able to acquire a Solid Rocket Booster gas generator and an Orbiter APU. Since these test assets were limited in number, an Air Force equivalent asset was identified: the F-16 Emergency Power Unit (EPU). In June 2013, two EPU's were acquired from retired aircraft located at Davis Monthan Air Force Base. A gas generator from one of these EPU's was taken out of an assembly and configured for testing with a version of the USAF propellant with a higher water content (AF-M315EM) to reduce decomposition temperatures. Testing in November 2014 has shown that this green propellant is reactive with the Hydrazine catalyst (Shell 405) generating 300 psi of pressure with the existing F-16 EPU configuration. This paper will highlight the results of MSFC testing in collaboration with AFRL.

Combustion and flow modelling applied to the OMV VTE

NASA Technical Reports Server (NTRS)

Larosiliere, Louis M.; Jeng, San-Mou

1990-01-01

A predictive tool for hypergolic bipropellant spray combustion and flow evolution in the OMV VTE (orbital maneuvering vehicle variable thrust engine) is described. It encompasses a computational technique for the gas phase governing equations, a discrete particle method for liquid bipropellant sprays, and constitutive models for combustion chemistry, interphase exchanges, and unlike impinging liquid hypergolic stream interactions. Emphasis is placed on the phenomenological modelling of the hypergolic liquid bipropellant gasification processes. An application to the OMV VTE combustion chamber is given in order to show some of the capabilities and inadequacies of this tool.

Theoretical Investigation of the Reactivity of Sodium Dicyanamide with Nitric Acid.

PubMed

Vogelhuber, Kristen M; Booth, Ryan S; Annesley, Christopher J

2018-03-01

There is a need to replace current hydrazine fuels with safer propellants, and dicyanamide (DCA - )-based systems have emerged as promising alternatives because they autoignite when mixed with some oxidizers. Previous studies of the hypergolic reaction mechanism have focused on the reaction between DCA - and the oxidizer HNO 3 ; here, we compare the calculated pathway of DCA - + HNO 3 with the reaction coordinate of the ion pair sodium dicyanamide with nitric acid, Na[DCA] + HNO 3 . Enthalpies and free energies are calculated in the gas phase and in solution using a quantum mechanical continuum solvation model, SMD-GIL. The barriers to the Na[DCA] + HNO 3 reaction are dramatically lowered relative to those of the reaction with the bare anion, and an exothermic exit channel to produce NaNO 3 and the reactive intermediate HDCA appears. These results suggest that Na[DCA] may accelerate the ignition reaction.

Chemochromic Indicators for the Detection of Hypergolic Fuels

NASA Technical Reports Server (NTRS)

Santiago-Maldonado, E.; Captian, J.; Devor, R.

2010-01-01

The toxicity and hazard level associated with the use of hypergolic fuels necessitates the development of technology capable of detecting the presence of such fuels in a variety of different environments and conditions. The most commonly used sensors for the detection of hypergolic fuels are electrochemical in nature, which have serious limitations when used as area monitoring devices. Recent collaborative work between Kennedy Space Center and ASRC Aerospace has led to the development of indicators which exhibit a color change upon exposure to hydrazine under different conditions. The indicators under investigation on this developmental effort are para-dimethylaminobenzaldehyde (PDAB), various formulations of universal pH indicators, and potassium tetrachloroaurate (KAuCl4). These chemochromic indicators have been tested for the detection of hydrazine under various conditions: pure liquid fuel, aqueous fuel solution, saline aqueous fuel solutions, vapor fuel, and 3-month shelf life study, which included UV protection, thermal extremes, and normal storage conditions. The hypergolic fuel indicator test was conducted with the indicator impregnated into a wipe material to test the applicability of the indicator to be used to capture (absorb) and indicate the presence of hypergolic fuels. Each of the indicators performed well, with the universal pH indicator being the best candidate because of the visible response color change and the indicator stability after the shelf life study.

The hard start phenomena in hypergolic engines. Volume 3: Physical and combustion characteristics of engine residuals

NASA Technical Reports Server (NTRS)

Miron, Y.; Perlee, H. E.

1974-01-01

An investigation was conducted to determine the cause of starting problems in the hypergolic rocket engines of the Apollo reaction control (RCS) engines. The scope of the investigation was as follows: (1) to establish that chemical reactions occurred during the preignition and post combustion periods, (2) to identify the chemical species of the products of preignition and post combustion reaction, and (3) to determine the explosive nature of the identified species. The methods used in identifying the chemical products are described species. The infrared spectra, X-ray spectra, and other signatures of the compounds are presented. The physical and explosion characteristics of various hypergolic agents are reported.

Failure Investigation of an Intra-Manifold Explosion in a Horizontally-Mounted 870 lbf Reaction Control Thruster

NASA Technical Reports Server (NTRS)

Durning, Joseph G., III; Westover, Shayne C.; Cone, Darren M.

2011-01-01

In June 2010, an 870 lbf Space Shuttle Orbiter Reaction Control System Primary Thruster experienced an unintended shutdown during a test being performed at the NASA White Sands Test Facility. Subsequent removal and inspection of the thruster revealed permanent deformation and misalignment of the thruster valve mounting plate. Destructive evaluation determined that after three nominal firing sequences, the thruster had experienced an energetic event within the fuel (monomethylhydrazine) manifold at the start of the fourth firing sequence. The current understanding of the phenomenon of intra-manifold explosions in hypergolic bipropellant thrusters is documented in literature where it is colloquially referred to as a ZOT. The typical ZOT scenario involves operation of a thruster in a gravitational field with environmental pressures above the triple point pressure of the propellants. Post-firing, when the thruster valves are commanded closed, there remains a residual quantity of propellant in both the fuel and oxidizer (nitrogen tetroxide) injector manifolds known as the "dribble volume". In an ambient ground test configuration, these propellant volumes will drain from the injector manifolds but are impeded by the local atmospheric pressure. The evacuation of propellants from the thruster injector manifolds relies on the fluids vapor pressure to expel the liquid. The higher vapor pressure oxidizer will evacuate from the manifold before the lower vapor pressure fuel. The localized cooling resulting from the oxidizer boiling during manifold draining can result in fuel vapor migration and condensation in the oxidizer passage. The liquid fuel will then react with the oxidizer that enters the manifold during the next firing and may produce a localized high pressure reaction or explosion within the confines of the oxidizer injector manifold. The typical ZOT scenario was considered during this failure investigation, but was ultimately ruled out as a cause of the explosion. Converse to the typical ZOT failure mechanism, the failure of this particular thruster was determined to be the result of liquid oxidizer being present within the fuel manifold.

Resources Available for Hazards Analysis of Aerospace Fluids

NASA Technical Reports Server (NTRS)

Woods, S. S.; Stewart, W. F.; Baker, D. L.

2001-01-01

In recent years, the legislative and executive branches of the federal government have pushed to make government more efficient and responsive to the needs of the marketplace. One of these initiatives, Public Law 104-113, also known as the National Technology Transfer and Advancement Act of 1995 (NTTAA), is designed to accelerate technology transfer to industry and promote government-industry partnership. Summarized, NTTAA states that '... all Federal agencies and departments shall use technical standards that are developed or adopted by voluntary consensus standards bodies, using such technical standards as a means to carry out policy objectives or activities determined by the agencies and departments. Government agencies must now determine if their in-house requirement-setting activities are sufficiently unique that no public interest is served by having them adopted by a voluntary consensus organization (VCO), or if not, to use or develop voluntary consensus standards. The Office of Management and Budget (OMB) is chartered by the law to monitor federal agency progress and report the results to Congress. In response to NTTAA, agency-wide oxygen and hydrogen safety standards sponsored by the NASA Headquarters (HQ) Office of Safety and Mission Assurance (OSMA) were obvious choices for early adoption by VCOs. In 1996, HQ sought assistance from the Johnson Space Center (JSC) White Sands Test Facility (WSTF), the technical lead for development of these safety standards, to evaluate their adoption by VCOs. At that time, WSTF-developed propellant hazards manuals were likewise identified for possible VCO adoption. Subsequently, WSTF was asked to represent NASA for development of an international ISO safety standard for hydrogen use. Concurrent with these WSTF standards activities are related efforts to develop and publish propellant hazards analysis protocols and safety courses for the industrial, propellant use of oxygen, hydrogen, and hypergols. This paper reports on these efforts and describes WSTF's overall voluntary consensus standards program to coordinate the interchange of NASA's propellant hazards and safety information with industry.

Space Technology: Game Changing Development Deep Space Engine (DSE) 100 lbf and 5 lbf Thruster Development and Qualification

NASA Technical Reports Server (NTRS)

Barnett, Gregory

2017-01-01

Science mission studies require spacecraft propulsion systems that are high-performance, lightweight, and compact. Highly matured technology and low-cost, short development time of the propulsion system are also very desirable. The Deep Space Engine (DSE) 100-lbf thruster is being developed to meet these needs. The overall goal of this game changing technology project is to qualify the DSE thrusters along with 5-lbf attitude control thrusters for space flight and for inclusion in science and exploration missions. The aim is to perform qualification tests representative of mission duty cycles. Most exploration missions are constrained by mass, power and cost. As major propulsion components, thrusters are identified as high-risk, long-lead development items. NASA spacecraft primarily rely on 1960s' heritage in-space thruster designs and opportunities exist for reducing size, weight, power, and cost through the utilization of modern materials and advanced manufacturing techniques. Advancements in MON-25/MMH hypergolic bipropellant thrusters represent a promising avenue for addressing these deficiencies with tremendous mission enhancing benefits. DSE is much lighter and costs less than currently available thrusters in comparable thrust classes. Because MON-25 propellants operate at lower temperatures, less power is needed for propellant conditioning for in-space propulsion applications, especially long duration and/or deep-space missions. Reduced power results in reduced mass for batteries and solar panels. DSE is capable of operating at a wide propellant temperature range (between -22 F and 122 F) while a similar existing thruster operates between 45 F and 70 F. Such a capability offers robust propulsion operation as well as flexibility in design. NASA's Marshall Space Flight Center evaluated available operational Missile Defense Agency heritage thrusters suitable for the science and lunar lander propulsion systems.

Experimental Investigation of Augmented Spark Ignition of a LO2/LCH4 Reaction Control Engine at Altitude Conditions

NASA Technical Reports Server (NTRS)

Kleinhenz, Julie; Sarmiento, Charles; Marshall, William

2012-01-01

The use of nontoxic propellants in future exploration vehicles would enable safer, more cost-effective mission scenarios. One promising green alternative to existing hypergols is liquid methane (LCH4) with liquid oxygen (LO2). A 100 lbf LO2/LCH4 engine was developed under the NASA Propulsion and Cryogenic Advanced Development project and tested at the NASA Glenn Research Center Altitude Combustion Stand in a low pressure environment. High ignition energy is a perceived drawback of this propellant combination; so this ignition margin test program examined ignition performance versus delivered spark energy. Sensitivity of ignition to spark timing and repetition rate was also explored. Three different exciter units were used with the engine s augmented (torch) igniter. Captured waveforms indicated spark behavior in hot fire conditions was inconsistent compared to the well-behaved dry sparks. This suggests that rising pressure and flow rate increase spark impedance and may at some point compromise an exciter s ability to complete each spark. The reduced spark energies of such quenched deliveries resulted in more erratic ignitions, decreasing ignition probability. The timing of the sparks relative to the pressure/flow conditions also impacted the probability of ignition. Sparks occurring early in the flow could trigger ignition with energies as low as 1 to 6 mJ, though multiple, similarly timed sparks of 55 to 75 mJ were required for reliable ignition. Delayed spark application and reduced spark repetition rate both correlated with late and occasional failed ignitions. An optimum time interval for spark application and ignition therefore coincides with propellant introduction to the igniter.

Low Flow Vortex Shedding Flow Meter for Hypergolics/all Media

NASA Technical Reports Server (NTRS)

Thinh, Ngo Dinh

1991-01-01

A family of vortex shedding flow meters, for measurement of hypergol flows, was designed and fabricated. The test loops to evaluate the flow meters for water flow, as well as Freon -113 flow which simulates the hypergolic fluids, were modified and constructed to utilize a pump system which has an output capacity of 200 gpm. Test runs were conducted on the small 1/2 inch model with Freon 113 and on the larger models with water. Results showed that the linearity between the frequency of the vortices and the flow rate of the fluids was very close to that of the turbine flow meter. It is suggested that the vortex shedding flow meter is a possible replacement for the existing turbine type.

Regeneratively Cooled Liquid Oxygen/Methane Technology Development

NASA Technical Reports Server (NTRS)

Robinson, Joel W.; Greene, Christopher B.; Stout, Jeffrey

2012-01-01

The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LOX)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon exploration studies. The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. NASA-Marshall Space Flight Center (MSFC) in concert with industry partner Pratt & Whitney Rocketdyne (PWR) utilized a Space Act Agreement to test an oxygen/methane engine system in the Summer of 2010. PWR provided a 5,500 lbf (24,465 N) LOX/LCH4 regenerative cycle engine to demonstrate advanced thrust chamber assembly hardware and to evaluate the performance characteristics of the system. The chamber designs offered alternatives to traditional regenerative engine designs with improvements in cost and/or performance. MSFC provided the test stand, consumables and test personnel. The hot fire testing explored the effective cooling of one of the thrust chamber designs along with determining the combustion efficiency with variations of pressure and mixture ratio. The paper will summarize the status of these efforts.

Quality assurance and control in the production and static tests of the solid rocket boosters for the Space Shuttle

NASA Technical Reports Server (NTRS)

Cerny, O. F.

1979-01-01

The paper surveys the various aspects of design and overhaul of the solid rocket boosters. It is noted that quality control is an integral part of the design specifications. Attention is given to the production process which is optimized towards highest quality. Also discussed is the role of the DCA (Defense Contract Administration) in inspecting the products of subcontractors, noting that the USAF performs this role for prime contractors. Fabrication and construction of the booster is detailed with attention given to the lining of the booster cylinder and the mixing of the propellant and the subsequent X-ray inspection.

Oxygen/Alcohol Dual Thrust RCS Engines

NASA Technical Reports Server (NTRS)

Angstadt, Tara; Hurlbert, Eric

1999-01-01

A non-toxic dual thrust RCS engine offers significant operational, safety, and performance advantages to the space shuttle and the next generation RLVs. In this concept, a single engine produces two thrust levels of 25 and 870 lbf. The low thrust level is provided by the spark torch igniter, which, with the addition of 2 extra valves, can also be made to function as a vernier. A dual thrust RCS engine allows 38 verniers to be packaged more efficiently on a vehicle. These 38 vemiers improve translation and reduce cross coupling, thereby providing more pure roll, pitch, and yaw maneuvers of the vehicle. Compared to the 6 vemiers currently on the shuttle, the 38 dual thrust engines would be 25 to 40% more efficient for the same maneuvers and attitude control. The vernier thrust level also reduces plume impingement and contamination concerns. Redundancy is also improved, thereby improving mission success reliability. Oxygen and ethanol are benign propellants which do not create explosive reaction products or contamination, as compared to hypergolic propellants. These characteristics make dual-thrust engines simpler to implement on a non-toxic reaction control system. Tests at WSTF in August 1999 demonstrated a dual-thrust concept that is successful with oxygen and ethanol. Over a variety of inlet pressures and mixture ratios at 22:1 area ratio, the engine produced between 230 and 297 sec Isp, and thrust levels from 8 lbf. to 50 lbf. This paper describes the benefits of dual-thrust engines and the recent results from tests at WSTF.

Development of an in-line filter to prevent intrusion of NO2 toxic vapors into A/C systems

NASA Technical Reports Server (NTRS)

Meneghelli, Barry; Mcnulty, R. J.; Springer, Mike; Lueck, Dale E.

1995-01-01

The hypergolic propellant nitrogen tetroxide (N2O4 or NTO) is routinely used in spacecraft launched at Kennedy Space Center (KSC) and Cape Canaveral Air Station (CCAS). In the case of a catastrophic failure of the spacecraft, there would be a release of the unspent propellant in the form of a toxic cloud. Inhalation of this material at downwind concentrations which may be as high as 20 parts per million (ppm) for 30 minutes in duration, may produce irritation to the eyes, nose and respiratory tract. Studies at both KSC and CCAS have shown that the indoor concentrations of N2O4 during a toxic release may range from 1 to 15 ppm and depend on the air change rate (ACR) for a particular building and whether or not the air conditioning (A/C) system has been shut down or left in an operating mode. This project was initiated in order to assess how current A/C systems could be easily modified to prevent personnel from being exposed to toxic vapors. A sample system has been constructed to test the ability of several types of filter material to capture the N2O4 vapors prior to their infiltration into the A/C system. Test results will be presented which compare the efficiencies of standard A/C filters, water wash systems, and chemically impregnated filter material in taking toxic vapors out of the incoming air stream.

Liquid Oxygen/Liquid Methane Test Results of the RS-18 Lunar Ascent Engine at Simulated Altitude Conditions at NASA White Sands Test Facility

NASA Technical Reports Server (NTRS)

Melcher, John C., IV; Allred, Jennifer K.

2009-01-01

Tests were conducted with the RS-18 rocket engine using liquid oxygen (LO2) and liquid methane (LCH4) propellants under simulated altitude conditions at NASA Johnson Space Center White Sands Test Facility (WSTF). This project is part of NASA's Propulsion and Cryogenics Advanced Development (PCAD) project. "Green" propellants, such as LO2/LCH4, offer savings in both performance and safety over equivalently sized hypergolic propulsion systems in spacecraft applications such as ascent engines or service module engines. Altitude simulation was achieved using the WSTF Large Altitude Simulation System, which provided altitude conditions equivalent up to 122,000 ft (37 km). For specific impulse calculations, engine thrust and propellant mass flow rates were measured. LO2 flow ranged from 5.9 - 9.5 lbm/sec (2.7 - 4.3 kg/sec), and LCH4 flow varied from 3.0 - 4.4 lbm/sec (1.4 - 2.0 kg/sec) during the RS-18 hot-fire test series. Propellant flow rate was measured using a coriolis mass-flow meter and compared with a serial turbine-style flow meter. Results showed a significant performance measurement difference during ignition startup due to two-phase flow effects. Subsequent cold-flow testing demonstrated that the propellant manifolds must be adequately flushed in order for the coriolis flow meters to give accurate data. The coriolis flow meters were later shown to provide accurate steady-state data, but the turbine flow meter data should be used in transient phases of operation. Thrust was measured using three load cells in parallel, which also provides the capability to calculate thrust vector alignment. Ignition was demonstrated using a gaseous oxygen/methane spark torch igniter. Test objectives for the RS-18 project are 1) conduct a shakedown of the test stand for LO2/methane lunar ascent engines, 2) obtain vacuum ignition data for the torch and pyrotechnic igniters, and 3) obtain nozzle kinetics data to anchor two-dimensional kinetics codes. All of these objectives were met with the RS-18 data and additional testing data from subsequent LO2/methane test programs in 2009 which included the first simulated-altitude pyrotechnic ignition demonstration of LO2/methane.

Compatibility Studies of Hydrogen Peroxide and a New Hypergolic Fuel Blend

NASA Technical Reports Server (NTRS)

Baldridge, Jennifer; Villegas, Yvonne

2002-01-01

Several preliminary materials compatibility studies have been conducted to determine the practicality of a new hypergolic fuel system. Hypergolic fuel ignites spontaneously as the oxidizer decomposes and releases energy in the presence of the fuel. The bipropellant system tested consists of high-test hydrogen peroxide (HTP) and a liquid fuel blend consisting of a hydrocarbon fuel, an ignition enhancer and a transition metal catalyst. In order for further testing of the new fuel blend to take place, some basic materials compatibility and HTP decomposition studies must be accomplished. The thermal decomposition rate of HTP was tested using gas evolution and isothermal microcalorimetry (IMC). Materials were analyzed for compatibility with hydrogen peroxide including a study of the affect welding has on stainless steel elemental composition and its relation to HTP decomposition. Compatibility studies of valve materials in the fuel blend were performed to determine the corrosion resistance of the materials.

Defense Acquisition Research Journal. Volume 22, Number 1, Issue 72.

DTIC Science & Technology

2015-01-01

Capt Allen J. DeNeve, USAF, Lt Col Erin T. Ryan , USAF, Lt Col Jonathan D. Ritschel, USAF, and Christine Schubert Kabban The Effects of System...USAF, Lt Col Erin T. Ryan , USAF, Lt Col Jonathan D. Ritschel, USAF, and Christine Schubert Kabban A regression technique is used to predict cost...practices. Capt Allen J. DeNeve, USAF, Lt Col Erin T. Ryan , USAF, Lt Col Jonathan D. Ritschel, USAF, and Christine Schubert Kabban, in “Taming the

Liquid Oxygen/Liquid Methane Ascent Main Engine Technology Development

NASA Technical Reports Server (NTRS)

Robinson, Joel W.; Stephenson, David D.

2008-01-01

The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LO2)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon the Exploration Systems Architecture Study (ESAS). The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. The current application considering this technology is the lunar ascent main engine (AME). AME is anticipated to be an expendable, pressure-fed engine to provide ascent from the moon at the completion of a 210 day lunar stay. The engine is expected to produce 5,500 lbf (24,465 N) thrust with variable inlet temperatures due to the cryogenic nature of the fuel and oxidizer. The primary technology risks include establishing reliable and robust ignition in vacuum conditions, maximizing specific impulse, developing rapid start capability for the descent abort, providing the capability for two starts and producing a total engine bum time over 500 seconds. This paper will highlight the efforts of the Marshall Space Flight Center (MSFC) in addressing risk reduction activities for this technology.

Regeneratively Cooled Liquid Oxygen/Methane Technology Development Between NASA MSFC and PWR

NASA Technical Reports Server (NTRS)

Robinson, Joel W.; Greene, Christopher B.; Stout, Jeffrey B.

2012-01-01

The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LOX)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon exploration studies. The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. NASA-Marshall Space Flight Center (MSFC) in concert with industry partner Pratt & Whitney Rocketdyne (PWR) utilized a Space Act Agreement to test an oxygen/methane engine system in the Summer of 2010. PWR provided a 5,500 lbf (24,465 N) LOX/LCH4 regenerative cycle engine to demonstrate advanced thrust chamber assembly hardware and to evaluate the performance characteristics of the system. The chamber designs offered alternatives to traditional regenerative engine designs with improvements in cost and/or performance. MSFC provided the test stand, consumables and test personnel. The hot fire testing explored the effective cooling of one of the thrust chamber designs along with determining the combustion efficiency with variations of pressure and mixture ratio. The paper will summarize the status of these efforts.

Molecular Orbital Based Design Guidelines for Hypergolic Energetic Ionic Liquids

DTIC Science & Technology

2015-01-01

energy content of the anion must also be taken into account in the design strategy ; substitution should be carried out in such a way that does not...substitution strategy . So far in the litera- ture, HP (with energy gap similar to DCA) is the lowest DHf anion (661.9 kJmol1) for which EIL hypergolicity...T. Nakajima, Y. Honda , O. Kitao, H. Nakai, M. Klene, X. Li, J. E. Knox, H. P. Hratchian, J. B. Cross, V. Bakken, C. Adamo, J. Jaramillo, R. Gomperts

Low flow vortex shedding flowmeter

NASA Technical Reports Server (NTRS)

Waugaman, Charles J.

1989-01-01

The purpose was to continue a development project on a no moving parts vortex shedding flowmeter used for flow measurement of hypergols. The project involved the design and construction of a test loop to evaluate the meter for flow of Freon which simulates the hypergol fluids. Results were obtained on the output frequency characteristics of the flow meter as a function of flow rate. A family of flow meters for larger size lines and ranges of flow was sized based on the results of the tested meter.

Shuttle Primary Reaction Control Subsystem Thruster Fuel Valve Pilot Seal Extrusion: A Failure Correlation

NASA Technical Reports Server (NTRS)

Waller, Jess; Saulsberry, Regor L.

2003-01-01

Pilot operated valves (POVs) are used to control the flow of hypergolic propellants monomethylhydrazine (fuel) and nitrogen tetroxide (oxidizer) to the Shuttle orbiter Primary Reaction Control Subsystem (PRCS) thrusters. The POV incorporates a two-stage design: a solenoid-actuated pilot stage, which in turn controls a pressure-actuated main stage. Isolation of propellant supply from the thruster chamber is accomplished in part by a captive polytetrafluoroethylene (PTFE) pilot seal retained inside a Custom 455.1 stainless steel cavity. Extrusion of the pilot seal restricts the flow of fuel around the pilot poppet, thus impeding or preventing the main valve stage from opening. It can also prevent the main stage from staying open with adequate force margin, particularly if there is gas in the main stage actuation cavity. During thruster operation on-orbit, fuel valve pilot seal extrusion is commonly indicated by low or erratic chamber pressure or failure of the thruster to fire upon command (Fail-Off). During ground turnaround, pilot seal extrusion is commonly indicated by slow gaseous nitrogen (GN2) main valve opening times (greater than 38 ms) or slow water main valve opening response times (greater than 33 ms). Poppet lift tests and visual inspection can also detect pilot seal extrusion during ground servicing; however, direct metrology on the pilot seat assembly provides the most quantitative and accurate means of identifying extrusion. Minimizing PRCS fuel valve pilot seal extrusion has become an important issue in the effort to improve PRCS reliability and reduce associated life cycle costs.

In-Space Engine (ISE-100) Development - Design Verification Test

NASA Technical Reports Server (NTRS)

Trinh, Huu P.; Popp, Chris; Bullard, Brad

2017-01-01

In the past decade, NASA has formulated science mission concepts with an anticipation of landing spacecraft on the lunar surface, meteoroids, and other planets. Advancing thruster technology for spacecraft propulsion systems has been considered for maximizing science payload. Starting in 2010, development of In-Space Engine (designated as ISE-100) has been carried out. ISE-100 thruster is designed based on heritage Missile Defense Agency (MDA) technology aimed for a lightweight and efficient system in terms volume and packaging. It runs with a hypergolic bi-propellant system: MON-25 (nitrogen tetroxide, N2O4, with 25% of nitric oxide, NO) and MMH (monomethylhydrazine, CH6N2) for NASA spacecraft applications. The utilization of this propellant system will provide a propulsion system capable of operating at wide range of temperatures, from 50 C (122 F) down to -30 C (-22 F) to drastically reduce heater power. The thruster is designed to deliver 100 lb(sub f) of thrust with the capability of a pulse mode operation for a wide range of mission duty cycles (MDCs). Two thrusters were fabricated. As part of the engine development, this test campaign is dedicated for the design verification of the thruster. This presentation will report the efforts of the design verification hot-fire test program of the ISE-100 thruster in collaboration between NASA Marshall Space Flight Center (MSFC) and Aerojet Rocketdyne (AR) test teams. The hot-fire tests were conducted at Advance Mobile Propulsion Test (AMPT) facility in Durango, Colorado, from May 13 to June 10, 2016. This presentation will also provide a summary of key points from the test results.

Study to optimize gellant polymer-water systems for the control of hypergolic spills and fires

NASA Technical Reports Server (NTRS)

Jennings, R. R.; Macwilliams, D. C.; Foshee, W. C.; Katzer, M. F.

1973-01-01

A system of buffered gelled water was developed to prevent and control fires from small spills of nitrogen tetroxide-(N2O4)-Aerozine 50-hypergolic fuel. Laboratory studies on various alkalis, buffers, and seavengers for the fuel components are described. Chilling and sodium acetate-acetic acid buffer was found to be the best additives to the gelled water. Field tests and a delivery system (airborne) for the extinguishant are described. A short movie showing the field testing is available upon request.

Technology Challenges for Deep-Throttle Cryogenic Engines for Space Exploration

NASA Technical Reports Server (NTRS)

Brown, Kendall K.; Nelson, Karl W.

2005-01-01

Historically, cryogenic rocket engines have not been used for in-space applications due to their additional complexity, the mission need for high reliability, and the challenges of propellant boil-off. While the mission and vehicle architectures are not yet defined for the lunar and Martian robotic and human exploration objectives, cryogenic rocket engines offer the potential for higher performance and greater architecture/mission flexibility. In-situ cryogenic propellant production could enable a more robust exploration program by significantly reducing the propellant mass delivered to low earth orbit, thus warranting the evaluation of cryogenic rocket engines versus the hypergolic bi-propellant engines used in the Apollo program. A multi-use engine. one which can provide the functionality that separate engines provided in the Apollo mission architecture, is desirable for lunar and Mars exploration missions because it increases overall architecture effectiveness through commonality and modularity. The engine requirement derivation process must address each unique mission application and each unique phase within each mission. The resulting requirements, such as thrust level, performance, packaging, bum duration, number of operations; required impulses for each trajectory phase; operation after extended space or surface exposure; availability for inspection and maintenance; throttle range for planetary descent, ascent, acceleration limits and many more must be addressed. Within engine system studies, the system and component technology, capability, and risks must be evaluated and a balance between the appropriate amount of technology-push and technology-pull must be addressed. This paper will summarize many of the key technology challenges associated with using high-performance cryogenic liquid propellant rocket engine systems and components in the exploration program architectures. The paper is divided into two areas. The first area describes how the mission requirements affect the engine system requirements and create system level technology challenges. An engine system architecture for multiple applications or a family of engines based upon a set of core technologies, design, and fabrication approaches may reduce overall programmatic cost and risk. The engine system discussion will also address the characterization of engine cycle figures of merit, configurations, and design approaches for some in-space vehicle alternatives under consideration. The second area evaluates the component-level technology challenges induced from the system requirements. Component technology issues are discussed addressing injector, thrust chamber, ignition system, turbopump assembly, and valve design for the challenging requirements of high reliability, robustness, fault tolerance, deep throttling, reasonable performance (with respect to weight and specific impulse).

Hypergol Systems: Design, Buildup, and Operation

NASA Technical Reports Server (NTRS)

Baker, David; Rathgeber, Kurt

2006-01-01

This course was developed by personnel at the NASA JSC White Sands Test Facility in conjunction with the NASA Safety Training Center (NSTC). The NSTC was established in May 1991 by the NASA Headquarters Safety Directorate to provide up-to-date, high-quality, NASA specific safety training on location at NASA centers, or simultaneously to multiple centers over the Video Teleconferencing System (ViTS). Our desire is to establish and maintain a strong, long-lasting relationship with all NASA centers in order to fulfill your safety training needs on a cost-effective basis. Our ultimate goal is to provide a positive contribution to safe operations at NASA. NSTC Course 055 is a 2-day course discussing the safe usage of hypergols (hydrazine fuels and nitrogen tetroxide). During the course we will identify the hazards associated with hypergols including toxicity, reactivity, fire, and explosion. Management of risk is discussed in terms of the primary engineering controls design, buildup, and operation; and secondary controls personal protective equipment and detectors/monitors. The emphasis is on the design and buildup of compatible systems and the safe operation of these systems by technicians and engineers.

A Tailored Systems Engineering Framework for Science and Technology Projects

DTIC Science & Technology

2009-03-01

PROJECTS THESIS Stephen M. Behm Major, USAF J . Bradford Pitzer Major, USAF Jane F. White Civilian, US AFIT/GSE/ENV/09-M02 DEPARTMENT OF THE...Engineering Stephen M. Behm, Major, USAF J . Bradford Pitzer, Major, USAF Jane F. White, Civilian, US March 2009 APPROVED FOR PUBLIC...Stephen M. Behm, Major, USAF J . Bradford Pitzer, Major, USAF Jane F. White, Civilian, US Approved: iv AFIT/GSE/ENV

Hypergolic ignitor

NASA Technical Reports Server (NTRS)

Taylor, Eric S. (Inventor); Myers, W. Neill (Inventor); Martin, Michael A. (Inventor)

2005-01-01

An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture disc to rupture and hypergolic fluid contained within the cartridge is discharged out the ignitor outlet.

Air and Space Power Journal. Volume 17, Number 4, Winter 2003

DTIC Science & Technology

2003-01-01

Van Nederveen, USAF, Retired Gradual Failure: The Air War over North Vietnam, 1965–1966 . . . . . . . . . . . . . . . . . . . . . . . . . . . 99...Jacob Van Staaveren Reviewer: Maj Paul G. Niesen, USAF Flankers: The New Generation...Operations Directorate Headquarters USAF Brig Gen Phillip D. Caine, USAF, Retired Monument, Colorado Dr. Don D. Chipman USAF Squadron Officer College

KSC-04pd1373

NASA Image and Video Library

2004-06-28

KENNEDY SPACE CENTER, FLA. - At Astrotech in Titusville, Fla., technicians with The Johns Hopkins University Applied Physics Laboratory (APL) prepare to cover the MESSESNGER spacecraft for a move to a hazardous processing facility in preparation for loading the spacecraft’s complement of hypergolic propellants. MESSENGER is scheduled to launch Aug. 2 aboard a Boeing Delta II rocket from Pad 17-B, Cape Canaveral Air Force Station, Fla., on a journey to Mercury. It will return to Earth for a gravity boost in July 2005, then fly past Venus twice, in October 2006 and June 2007. The spacecraft uses the tug of Venus’ gravity to resize and rotate its trajectory closer to Mercury’s orbit. Three Mercury flybys, each followed about two months later by a course-correction maneuver, put MESSENGER in position to enter Mercury orbit in March 2011. During the flybys, MESSENGER will map nearly the entire planet in color, image most of the areas unseen by Mariner 10, and measure the composition of the surface, atmosphere and magnetosphere. It will be the first new data from Mercury in more than 30 years - and invaluable for planning MESSENGER’s year-long orbital mission. MESSENGER was built for NASA by APL in Laurel, Md.

KSC-04pd1372

NASA Image and Video Library

2004-06-28

KENNEDY SPACE CENTER, FLA. - At Astrotech in Titusville, Fla., technicians with The Johns Hopkins University Applied Physics Laboratory (APL) prepare the MESSESNGER spacecraft for a move to a hazardous processing facility in preparation for loading the spacecraft’s complement of hypergolic propellants. MESSENGER is scheduled to launch Aug. 2 aboard a Boeing Delta II rocket from Pad 17-B, Cape Canaveral Air Force Station, Fla., on a journey to Mercury. It will return to Earth for a gravity boost in July 2005, then fly past Venus twice, in October 2006 and June 2007. The spacecraft uses the tug of Venus’ gravity to resize and rotate its trajectory closer to Mercury’s orbit. Three Mercury flybys, each followed about two months later by a course-correction maneuver, put MESSENGER in position to enter Mercury orbit in March 2011. During the flybys, MESSENGER will map nearly the entire planet in color, image most of the areas unseen by Mariner 10, and measure the composition of the surface, atmosphere and magnetosphere. It will be the first new data from Mercury in more than 30 years - and invaluable for planning MESSENGER’s year-long orbital mission. MESSENGER was built for NASA by APL in Laurel, Md.

Max Launch Abort System (MLAS) Pad Abort Test Vehicle (PATV) II Attitude Control System (ACS) Integration and Pressurization Subsystem Dynamic Random Vibration Analysis

NASA Technical Reports Server (NTRS)

Ekrami, Yasamin; Cook, Joseph S.

2011-01-01

In order to mitigate catastrophic failures on future generation space vehicles, engineers at the National Aeronautics and Space Administration have begun to integrate a novel crew abort systems that could pull a crew module away in case of an emergency at the launch pad or during ascent. The Max Launch Abort System (MLAS) is a recent test vehicle that was designed as an alternative to the baseline Orion Launch Abort System (LAS) to demonstrate the performance of a "tower-less" LAS configuration under abort conditions. The MLAS II test vehicle will execute a propulsive coast stabilization maneuver during abort to control the vehicles trajectory and thrust. To accomplish this, the spacecraft will integrate an Attitude Control System (ACS) with eight hypergolic monomethyl hydrazine liquid propulsion engines that are capable of operating in a quick pulsing mode. Two main elements of the ACS include a propellant distribution subsystem and a pressurization subsystem to regulate the flow of pressurized gas to the propellant tanks and the engines. The CAD assembly of the Attitude Control System (ACS) was configured and integrated into the Launch Abort Vehicle (LAV) design. A dynamic random vibration analysis was conducted on the Main Propulsion System (MPS) helium pressurization panels to assess the response of the panel and its components under increased gravitational acceleration loads during flight. The results indicated that the panels fundamental and natural frequencies were farther from the maximum Acceleration Spectral Density (ASD) vibrations which were in the range of 150-300 Hz. These values will direct how the components will be packaged in the vehicle to reduce the effects high gravitational loads.

Analysis of Possible Explosions at Kennedy Space Center Due to Spontaneous Ignition of Hypergolic Propellants

NASA Technical Reports Server (NTRS)

Brown, Stephen

2010-01-01

NASA's Constellation Program plan currently calls for the replacement of the Space Shuttle with the ARES I & V spacecraft and booster vehicles to send astronauts to the moon and beyond. Part of the ARES spacecraft is the Orion Crew Exploration Vehicle (CEV), which includes the Crew Module (CM) and Service Module (SM). The Orion CM's main propulsion system and supplies are provided by the SM. The SM is to be processed off line and moved to the Vehicle Assembly Building (V AB) for stacking to the first stage booster motors prior to ARES move to the launch pad. The new Constellation Program philosophy to process in this manner has created a major task for the KSC infrastructure in that conventional QD calculations are no longer viable because of the location of surrounding facilities near the VAB and the Multi Purpose Processing Facility (MPPF), where the SM will be serviced with nearly 18,000 pounds of hypergolic propellants. The Multi-Payload Processing Facility (MPPF) complex, constructed by NASA in 1994, is located just off E Avenue south of the Operations and Checkout (O&C) building in the Kennedy Space Center industrial area. The MPPF includes a high bay and a low bay. The MPPF high bay is 40.2 m (132 ft) long x 18.9 m (60 ft) wide with a ceiling height of 18.9 m (62 ft). The low bay is a 10.4 m (34 ft) long x 10.4 m (34 ft) wide processing area and has a ceiling height of6.1 m (20 ft). The MPPF is currently used to process non-hazardous payloads. Engineering Analysis Inc. (EAI), under contract with ASRC Aerospace, Inc. in conjunction with the Explosive Safety Office, NASA, Kennedy Space Center (KSC), has carried out an analysis of the effects of explosions at KSC in or near various facilities produced by the spontaneous ignition ofhypergolic fuel stored in the CEV SM. The facilities considered included (1) Vehicle Assembly Building (VAB) (2) Multi-Payload Processing Facility (MPPF) (3) Canister Rotation Facility (CRF) Subsequent discussion deals with the MPPF analysis. Figure 1 provides a view of the MPPF from the northwest. An interior view ofthe facility is shown in Figure 2. The study was concerned with both blast hazards and hazardous fragments which exceed existing safety standards, as described in Section 2.0. The analysis included both blast and fragmentation effects and was divided into three parts as follows: (1) blast (2) primary fragmentation (3) secondary fragmentation Blast effects are summarized in Section 3.0, primary fragmentation in Section 4.0, and secondary fragmentation (internal and external) in Section 5.0. Conclusions are provided in Section 6.0, while references cited are included in Section 7.0. A more detailed description of the entire study is available in a separate document.

Liquid Rocket Booster Study. Volume 2, Book 1

NASA Technical Reports Server (NTRS)

1989-01-01

The recommended Liquid Rocket Booster (LRB) concept is shown which uses a common main engine with the Advanced Launch System (ALS) which burns LO2 and LH2. The central rationale is based on the belief that the U.S. can only afford one big new rocket engine development in the 1990's. A LO2/LH2 engine in the half million pound thrust class could satisfy STS LRB, ALS, and Shuttle C (instead of SSMEs). Development costs and higher production rates can be shared by NASA and USAF. If the ALS program does not occur, the LO2/RP-1 propellants would produce slight lower costs for and STS LRB. When the planned Booster Engine portion of the Civil Space Transportation Initiatives has provided data on large pressure fed LO2/RP-1 engines, then the choice should be reevaluated.

Guidance, navigation, and control trades for an Electric Orbit Transfer Vehicle

NASA Astrophysics Data System (ADS)

Zondervan, K. P.; Bauer, T. A.; Jenkin, A. B.; Metzler, R. A.; Shieh, R. A.

The USAF Space Division initiated the Electric Insertion Transfer Experiment (ELITE) in the fall of 1988. The ELITE space mission is planned for the mid 1990s and will demonstrate technological readiness for the development of operational solar-powered electric orbit transfer vehicles (EOTVs). To minimize the cost of ground operations, autonomous flight is desirable. Thus, the guidance, navigation, and control (GNC) functions of an EOTV should reside on board. In order to define GNC requirements for ELITE, parametric trades must be performed for an operational solar-powered EOTV so that a clearer understanding of the performance aspects is obtained. Parametric trades for the GNC subsystems have provided insight into the relationship between pointing accuracy, transfer time, and propellant utilization. Additional trades need to be performed, taking into account weight, cost, and degree of autonomy.

Acquisition Review Quarterly (ARQ): Volume 10, Number 3, Summer 2003

DTIC Science & Technology

2003-01-01

PROJECT NUMBER Lt Col Robert L. Waller, USAF, (Ret), Robert Graham, Maj David R. King, USAF, Lt Col John D. Driessnack, USAF, LTC Michael D. Proctor...High-Technology Industries Implications for Industrial Policy Maj David R. King, USAF Lt Col John D. Driessnack, USAF Why the "T" in SMART A...Business School William H . Reed Director Michael Wynne Defense Contract Audit Agency Acting Under Secretary of Defense (Acquisition, Technology, and

1977 Annual Typhoon Report

DTIC Science & Technology

1995-01-01

George T. McKaige, USN *CAPT Frederick P. Milwer, USAF CAPT Alan W. Hassebrock, USAF CAPT Charles P. Guard , USAF CAPT”John D. Shewchuk, USAF ENS Edward...Det 1, lWW - USAF 1977 ANNUAL TYPHOON REPORT *Departed during 1977 season FRONTCOVER: ln&a.tedphoztogzaphof a - tmJ -A.toZmb.iaZatAn o.ulh a M dtig -&A...ships provide day and night coverage in the JTWC area of responsibility. Interpretation of this satellite imagery pro- vides cyclone positions, and for

Hypergol Maintenance Facility Hazardous Waste South Staging Areas, SWMU 070 Corrective Measures Implementation

NASA Technical Reports Server (NTRS)

Miller, Ralinda R.

2016-01-01

This document presents the Corrective Measures Implementation (CMI) Year 10 Annual Report for implementation of corrective measures at the Hypergol Maintenance Facility (HMF) Hazardous Waste South Staging Areas at Kennedy Space Center, Florida. The work is being performed by Tetra Tech, Inc., for the National Aeronautics and Space Administration (NASA) under Indefinite Delivery Indefinite Quantity (IDIQ) NNK12CA15B, Task Order (TO) 07. Mr. Harry Plaza, P.E., of NASA's Environmental Assurance Branch is the Remediation Project Manager for John F. Kennedy Space Center. The Tetra Tech Program Manager is Mr. Mark Speranza, P.E., and the Tetra Tech Project Manager is Robert Simcik, P.E.

1991 Annual Tropical Cyclone Report

DTIC Science & Technology

1995-01-01

CAPT * CAPT lLT * MSGT MSGT...TSGT * TSGT TSGT TSGT TSGT * SSGT * SSGT SSGT * SSGT SSGT SSGT CAPT MR SGT SGT * SOT DR NICHOLASD.GURAL USN LESTERE.CARRrIII USN ROBEmL.BEARD USN...ANNR.GOETZ USAF BRUCEW.THOMPSON USAF ELIZABETHB.BORELLI USAF STEPHENC.HALLJN USAF DAVIDJ.STREMLER USN STACYR.STEWART USNR RICHARDA.JEFFRIES USN THOMAS

Technology Challenges for Deep-Throttle Cryogenic Engines for Space Exploration

NASA Astrophysics Data System (ADS)

Brown, Kendall K.; Nelson, Karl W.

2005-02-01

Historically, cryogenic rocket engines have not been used for in-space applications due to their additional complexity, the mission need for high reliability, and the challenges of propellant boil-off. While the mission and vehicle architectures are not yet defined for the lunar and Martian robotic and human exploration objectives, cryogenic rocket engines offer the potential for higher performance and greater architecture/mission flexibility. In-situ cryogenic propellant production could enable a more robust exploration program by significantly reducing the propellant mass delivered to low earth orbit, thus warranting the evaluation of cryogenic rocket engines versus the hypergolic bipropellant engines used in the Apollo program. A multi-use engine, one which can provide the functionality that separate engines provided in the Apollo mission architecture, is desirable for lunar and Mars exploration missions because it increases overall architecture effectiveness through commonality and modularity. The engine requirement derivation process must address each unique mission application and each unique phase within each mission. The resulting requirements, such as thrust level, performance, packaging, burn duration, number of operations; required impulses for each trajectory phase; operation after extended space or surface exposure; availability for inspection and maintenance; throttle range for planetary descent, ascent, acceleration limits and many more must be addressed. Within engine system studies, the system and component technology, capability, and risks must be evaluated and a balance between the appropriate amount of technology-push and technology-pull must be addressed. This paper will summarize many of the key technology challenges associated with using high-performance cryogenic liquid propellant rocket engine systems and components in the exploration program architectures. The paper is divided into two areas. The first area describes how the mission requirements affect the engine system requirements and create system level technology challenges. An engine system architecture for multiple applications or a family of engines based upon a set of core technologies, design, and fabrication approaches may reduce overall programmatic cost and risk. The engine system discussion will also address the characterization of engine cycle figures of merit, configurations, and design approaches for some in-space vehicle alternatives under consideration. The second area evaluates the component-level technology challenges induced from the system requirements. Component technology issues are discussed addressing injector, thrust chamber, ignition system, turbopump assembly, and valve design for the challenging requirements of high reliability, robustness, fault tolerance, deep throttling, reasonable performance (with respect to weight and specific impulse).

Bioenvironmental Engineering Career Ladder AFSC 907X0

DTIC Science & Technology

1991-05-01

TTA 1 1 HQ USAF/DPPE 1 HQ USAF/SGPA ( BOLLING AFB DC 20332-6188) 1 1 HQ USAFE/DPAT 3 3 HQ USAFE/TTA 1 1 HSD/SOSP 1 1 NODAC 1 USAFOMS/OMDQ 1 USAFOMS...this report are available for use by operations and training officials. Mr Roberto Salinas developed the survey instrument, Ms Becky Hernandez provided

An Overview of the Concept of Operations for Assembly, Integration, Testing and Ground Servicing Develoed for the MPCV-ESM Propulsion System

NASA Technical Reports Server (NTRS)

Bielozer, M.; VanLear, Benjamin S.; Kindred, N.; Monien, G.; Schulte, U.

2014-01-01

A concept of operations for the Assembly, Integration and Testing (AIT) and the Ground Systems Development Operations (GSDO) of the European Service Module (ESM) propulsion system has been developed. The AIT concept of operations covers all fabrication, integration and testing activities in both Europe and in the United States. The GSDO Program develops the facilities, equipment, and procedures for the loading of hypergolic propellants, the filling of high-pressure gases, and contingency de-servicing operations for the ESM. NASA and ESA along with the Lockheed Martin and Airbus Space and Defense are currently working together for the EM-1 and EM-2 missions in which the ESM will be flown as part of the Orion Multi-Purpose Crew Vehicle (MPCV). The NASA/ESA SM propulsion team is collaborating with the AIT personnel from ESA/Airbus and NASA/Lockheed Martin to ensure successful integration of the European designed Service Module propulsion system, the Lockheed Martin designed Crew Module Adapter and the heritage Space Shuttle Orbital Maneuvering System Engines (OMS-E) being provided as Government Furnished Equipment (GFE). This paper will provide an overview of the current AIT and GSDO concept of operations for the ESM propulsion system.

An Overview of the Concept of Operations for Assembly, Integration, Testing and Ground Servicing Developed for the MPCV-ESM Propulsion System

NASA Technical Reports Server (NTRS)

Bielozer, Matthew C.

2014-01-01

A concept of operations for the Assembly, Integration and Testing (AIT) and the Ground Systems Development Operations (GSDO) of the European Service Module (ESM) propulsion system has been developed. The AIT concept of operations covers all fabrication, integration and testing activities in both Europe and in the United States. The GSDO Program develops the facilities, equipment, and procedures for the loading of hypergolic propellants, the filling of high-pressure gases, and contingency de-servicing operations for the ESM. NASA and ESA along with the Lockheed Martin and Airbus Space and Defense are currently working together for the EM-1 and EM-2 missions in which the ESM will be flown as part of the Orion Multi-Purpose Crew Vehicle (MPCV). The NASA/ESA SM propulsion team is collaborating with the AIT personnel from ESA/Airbus and NASA/Lockheed Martin to ensure successful integration of the European designed Service Module propulsion system, the Lockheed Martin designed Crew Module Adapter and the heritage Space Shuttle Orbital Maneuvering System Engines (OMS-E) being provided as Government Furnished Equipment (GFE). This paper will provide an overview of the current AIT and GSDO concept of operations for the ESM propulsion system.

KSC-04pd1371

NASA Image and Video Library

2004-06-28

KENNEDY SPACE CENTER, FLA. - - After the deployment test of two solar panels at Astrotech in Titusville, Fla., technicians with The Johns Hopkins University Applied Physics Laboratory (APL) prepare the MESSESNGER spacecraft for a move to a hazardous processing facility in preparation for loading the spacecraft’s complement of hypergolic propellants. The solar arrays will provide MESSENGER’s power on its journey to Mercury. MESSENGER is scheduled to launch Aug. 2 aboard a Boeing Delta II rocket from Pad 17-B, Cape Canaveral Air Force Station, Fla. It will return to Earth for a gravity boost in July 2005, then fly past Venus twice, in October 2006 and June 2007. The spacecraft uses the tug of Venus’ gravity to resize and rotate its trajectory closer to Mercury’s orbit. Three Mercury flybys, each followed about two months later by a course-correction maneuver, put MESSENGER in position to enter Mercury orbit in March 2011. During the flybys, MESSENGER will map nearly the entire planet in color, image most of the areas unseen by Mariner 10, and measure the composition of the surface, atmosphere and magnetosphere. It will be the first new data from Mercury in more than 30 years - and invaluable for planning MESSENGER’s year-long orbital mission. MESSENGER was built for NASA by APL in Laurel, Md.

Dental Diamond Rotary Instruments. Test and Evaluation

DTIC Science & Technology

1983-09-01

Gov’t. agencies only; Critical Technology; Test and Evaluation; 19 NOV 1982. Other requests shall be referred to Dental Investigation Service, School of... DENTAL DIAMOND ROTARY INSTRUMENTS Test and Evaluation Cad D. Foster, Major, USAF, DC Joseph M. Powell, Colonel, USAF, DC John M. Young, Colonel, USAF...19 November 1982. Other requests for this document must be referred to the Dental Investig tion Service, USAF School of Aerospace Medicine. SUBJECT TO

Technology Support for Combat Casualty Related Medical Infrared Imaging

DTIC Science & Technology

2011-08-10

LtCol. David Trant USAF as On-site PI, and the Duke Medical IR group (Drs. Pearlstein and Guenther) serving as Co-PI’s, was approved in January 2009...patient outcome. COLLABORATORS: LtCol. Kenneth Egerstrom, USAF; LtCol. David Trant, USAF; Dr. Larry Katz, Department of Emergency Medicine...University of North Carolina Hospitals; Col. Byron Funke, USAF; Dr. David Randall, USArmy Night Vision Laboratories (Ft. Belvoir); Mr. Wayne Antesberger

Rational Design and Facile Synthesis of Boranophosphate Ionic Liquids as Hypergolic Rocket Fuels.

PubMed

Liu, Tianlin; Qi, Xiujuan; Wang, Binshen; Jin, Yunhe; Yan, Chao; Wang, Yi; Zhang, Qinghua

2018-05-14

The design and synthesis of new hypergolic ionic liquids (HILs) as replacements for toxic hydrazine derivatives have been the focus of current academic research in the field of liquid bipropellant fuels. In most cases, however, the requirements of excellent ignition performances, good hydrolytic stabilities, and low synthetic costs are often contradictory, which makes the development of high-performance HILs an enormous challenge. Here, we show how a fuel-rich boranophosphate ion was rationally designed and used to synthesize a series of high-performance HILs with excellent comprehensive properties. In the design strategy, we introduced the {BH 3 } moiety into the boranophosphate ion for improving the self-ignition property, whereas the complexation of boron and phosphite was used to improve the hydrolytic activity of the borohydride species. As a result, these boranophosphate HILs exhibited wide liquid operating ranges (>220 °C), high densities (1.00-1.10 g cm -3 ), good hydrolytic stabilities, and short ignition delay times (2.3-9.7 milliseconds) with white fuming nitric acid (WFNA) as the oxidizer. More importantly, these boranophosphate HILs could be readily prepared in high yields from commercial phosphite esters, avoiding complex and time-consuming synthetic routes. This work offers an effective strategy of designing boranophosphate HILs towards safer and greener hypergolic fuels for liquid bipropellant applications. © 2018 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim.

Simplified Key Management for Digital Access Control of Information Objects

DTIC Science & Technology

2016-07-02

0001, Task BC-5-2283, “Architecture, Design of Services for Air Force Wide Distributed Systems,” for USAF HQ USAF SAF/CIO A6. The views, opinions...Challenges for Cloud Computing,” Lecture Notes in Engineering and Computer Science: Proceedings World Congress on Engineering and Computer Science 2011...P. Konieczny USAF HQ USAF SAF/CIO A6 11. SPONSOR’S / MONITOR’S REPORT NUMBER(S) 12. DISTRIBUTION / AVAILABILITY STATEMENT Approved for public

Gravitational Lens: Deep Space Probe Design

DTIC Science & Technology

2012-03-01

Lieutenant, USAF Approved: Timothy Lawrence, Col, USAF (Chairman) Date Carl Hartsfield, Lt Col, USAF (Member) Date Marc G. Millis (Member) Date Abstract A...23 RTG Radioisotope Thermoelectric Generators . . . . . . . . . . . . . . . . . 26 EOL End of Life...26 ASRG Advanced Stirling Radioisotope Generator . . . . . . . . . . . . . . . . 26 GPHS

United States Air Force Statistical Digest, Fiscal Year 1956. Eleventh Edition

DTIC Science & Technology

1956-09-30

340 •••••••••••••••••• USAF Dental Health Activitiea at USAF In.tallations, Worldwide - FY 1956 ••• USAF Veterinary Animal Origin Food ...Inspection Service Incident to Pro- curement - FY 1956 ••••••••••••••••••••••••• Summary - USAF Veterinary Non-Animal Origin Food Inspection Service Incident...to Procurement - FY 1956 •••••.•••••••• USAF Veterinary Animal Origin Food Inspection Service Incident to Surveillance - FY 1956

Development of an advanced rocket propellant handler's suit.

PubMed

Doerr, D F

2001-01-01

Most launch vehicles and satellites in the US inventory rely upon the use of hypergolic rocket propellants, many of which are toxic to humans. These fuels and oxidizers, such as hydrazine and nitrogen tetroxide have threshold limit values as low as 0.01 PPM. It is essential to provide space workers handling these agents whole body protection as they are universally hazardous not only to the respiratory system, but the skin as well. This paper describes a new method for powering a whole body protective garment to assure the safety of ground servicing crews. A new technology has been developed through the small business innovative research program at the Kennedy Space Center. Currently, liquid air is used in the environmental control unit (ECU) that powers the propellant handlers suit (PHE). However, liquid air exhibits problems with attitude dependence, oxygen enrichment, and difficulty with reliable quantity measurement. The new technology employs the storage of the supply air as a supercritical gas. This method of air storage overcomes all of three problems above while maintaining high density storage at relatively low vessel pressures (<7000 kPa or approximately 1000 psi). A one hour prototype ECU was developed and tested to prove the feasibility of this concept. This was upgraded by the design of a larger supercritical dewar capable of holding 7 Kg of air, a supply which provides a 2 hour duration to the PHE. A third version is being developed to test the feasibility of replacing existing air cooling methodology with a liquid cooled garment for relief of heat stress in this warm Florida environment. Testing of the first one hour prototype yielded data comparable to the liquid air powered predecessor, but enjoyed advantages of attitude independence and oxygen level stability. Thermal data revealed heat stress relief at least as good as liquid air supplied units. The application of supercritical air technology to this whole body protective ensemble marked an advancement in the state-of-the-art in personal protective equipment. Not only was long duration environmental control provided, but it was done without a high pressure vessel. The unit met human performance needs for attitude independence, oxygen stability and relief of heat stress. This supercritical air (and oxygen) technology is suggested for microgravity applications in life support such as the Extravehicular Mobility Unit. c 2001. Elsevier Science Ltd. All rights reserved.

Development of an advanced rocket propellant handler's suit

NASA Technical Reports Server (NTRS)

Doerr, D. F.

2001-01-01

Most launch vehicles and satellites in the US inventory rely upon the use of hypergolic rocket propellants, many of which are toxic to humans. These fuels and oxidizers, such as hydrazine and nitrogen tetroxide have threshold limit values as low as 0.01 PPM. It is essential to provide space workers handling these agents whole body protection as they are universally hazardous not only to the respiratory system, but the skin as well. This paper describes a new method for powering a whole body protective garment to assure the safety of ground servicing crews. A new technology has been developed through the small business innovative research program at the Kennedy Space Center. Currently, liquid air is used in the environmental control unit (ECU) that powers the propellant handlers suit (PHE). However, liquid air exhibits problems with attitude dependence, oxygen enrichment, and difficulty with reliable quantity measurement. The new technology employs the storage of the supply air as a supercritical gas. This method of air storage overcomes all of three problems above while maintaining high density storage at relatively low vessel pressures (<7000 kPa or approximately 1000 psi). A one hour prototype ECU was developed and tested to prove the feasibility of this concept. This was upgraded by the design of a larger supercritical dewar capable of holding 7 Kg of air, a supply which provides a 2 hour duration to the PHE. A third version is being developed to test the feasibility of replacing existing air cooling methodology with a liquid cooled garment for relief of heat stress in this warm Florida environment. Testing of the first one hour prototype yielded data comparable to the liquid air powered predecessor, but enjoyed advantages of attitude independence and oxygen level stability. Thermal data revealed heat stress relief at least as good as liquid air supplied units. The application of supercritical air technology to this whole body protective ensemble marked an advancement in the state-of-the-art in personal protective equipment. Not only was long duration environmental control provided, but it was done without a high pressure vessel. The unit met human performance needs for attitude independence, oxygen stability and relief of heat stress. This supercritical air (and oxygen) technology is suggested for microgravity applications in life support such as the Extravehicular Mobility Unit. c 2001. Elsevier Science Ltd. All rights reserved.

Evaluation and Characterization Study of Dual Pulse Laser-Induced Spark (DPLIS) for Rocket Engine Ignition System Application

NASA Technical Reports Server (NTRS)

Osborne, Robin; Wehrmeyer, Joseph; Trinh, Huu; Early, James

2003-01-01

This paper addresses the progress of technology development of a laser ignition system at NASA Marshall Space Flight Center (MSFC). Laser ignition has been used at MSFC in recent test series to successfully ignite RP1/GOX propellants in a subscale rocket chamber, and other past studies by NASA GRC have demonstrated the use of laser ignition for rocket engines. Despite the progress made in the study of this ignition method, the logistics of depositing laser sparks inside a rocket chamber have prohibited its use. However, recent advances in laser designs, the use of fiber optics, and studies of multi-pulse laser formats3 have renewed the interest of rocket designers in this state-of the-art technology which offers the potential elimination of torch igniter systems and their associated mechanical parts, as well as toxic hypergolic ignition systems. In support of this interest to develop an alternative ignition system that meets the risk-reduction demands of Next Generation Launch Technology (NGLT), characterization studies of a dual pulse laser format for laser-induced spark ignition are underway at MSFC. Results obtained at MSFC indicate that a dual pulse format can produce plasmas that absorb the laser energy as efficiently as a single pulse format, yet provide a longer plasma lifetime. In an experiments with lean H2/air propellants, the dual pulse laser format, containing the same total energy of a single laser pulse, produced a spark that was superior in its ability to provide sustained ignition of fuel-lean H2/air propellants. The results from these experiments are being used to optimize a dual pulse laser format for future subscale rocket chamber tests. Besides the ignition enhancement, the dual pulse technique provides a practical way to distribute and deliver laser light to the combustion chamber, an important consideration given the limitation of peak power that can be delivered through optical fibers. With this knowledge, scientists and engineers at Los Alamos National Laboratory and CFD Research Corporation have designed and fabricated a miniaturized, first-generation optical prototype of a laser ignition system that could be the basis for a laser ignition system for rocket applications. This prototype will be tested at MSFC in future subscale rocket ignition tests.

Development of an advanced rocket propellant handler's suit

NASA Astrophysics Data System (ADS)

Doerr, DonaldF.

2001-08-01

Most launch vehicles and satellites in the US inventory rely upon the use of hypergolic rocket propellants, many of which are toxic to humans. These fuels and oxidizers, such as hydrazine and nitrogen tetroxide have threshold limit values as low as 0.01 PPM. It is essential to provide space workers handling these agents whole body protection as they are universally hazardous not only to the respiratory system, but the skin as well. This paper describes a new method for powering a whole body protective garment to assure the safety of ground servicing crews. A new technology has been developed through the small business innovative research program at the Kennedy Space Center. Currently, liquid air is used in the environmental control unit (ECU) that powers the propellant handlers suit (PHE). However, liquid air exhibits problems with attitude dependence, oxygen enrichment, and difficulty with reliable quantity measurement. The new technology employs the storage of the supply air as a supercritical gas. This method of air storage overcomes all of three problems above while maintaining high density storage at relatively low vessel pressures (<7000 kPa or ˜1000 psi). A one hour prototype ECU was developed and tested to prove the feasibility of this concept. This was upgraded by the design of a larger supercritical dewar capable of holding 7 Kg of air, a supply which provides a 2 hour duration to the PHE. A third version is being developed to test the feasibility of replacing existing air cooling methodology with a liquid cooled garment for relief of heat stress in this warm Florida environment. Testing of the first one hour prototype yielded data comprobable to the liquid air powered predecessor, but enjoyed advantages of attitude independence and oxygen level stability. Thermal data revealed heat stress relief at least as good as liquid air supplied units. The application of supercritical air technology to this whole body protective ensemble marked an advancement in the state-of-the-art in personal protective equipment. Not only was long duration environmental control provided, but it was done without a high pressure vessel. The unit met human performance needs for attitude independence, oxygen stability, and relief of heat stress. This supercritical air (and oxygen) technology is suggested for microgravity applications in life support such as the Extravehicular Mobility Unit.

Design Evolution of a Fighter Training Scheduling Decision Support System.

DTIC Science & Technology

1987-03-01

SYSTEM THESIS Paul E. Trapp Jeffrey W. Grechanik Captain, USAF Captain, USAF AFIT/GST/ENS/87M-8 MAY 191987 " Approved for public release; distribution...E. Trapp, B.S., M.A. Jeffrey W. Grechanik, B.S. Captain, USAF Captain, USAF March 87 Approved for public release; distribution unlimited This work...DNIF, TDY, and other disruptions. Therefore, cycli- cal scheduling will not be used (3:1-18). ProgAMming. Arthur and Ravindran proposed a goal

T-38C Optimal Landing Technique Determination (Project Talon Spot)

DTIC Science & Technology

2010-05-01

USAF TPS, Class 09B. All objectives of the test were met. 15. SUBJECT TERMS T-38 Aircraft , T-38C Aircraft , J85-GE-5 engine, landing performance... aircraft crossed the threshold. The requesting agency was Headquarters AETC/A3FV, through the USAF TPS. The responsible test organization was the 412...13197 (Figure 1) instrumented test aircraft were flown. The USAF TPS personnel performed all testing at USAF Plant 42 in Palmdale, CA and Edwards

Research and technology at the Kennedy Space Center

NASA Technical Reports Server (NTRS)

1983-01-01

Cryogenic engineering, hypergolic engineering, hazardous warning, structures and mechanics, computer sciences, communications, meteorology, technology applications, safety engineering, materials analysis, biomedicine, and engineering management and training aids research are reviewed.

A Parametric Regression of the Cost of Base Realignment Action (COBRA) Model

DTIC Science & Technology

1993-09-20

Douglas D. Hardman , Captain, USAF Michael S. Nelson, Captain, USAF AFIT/GEE/ENS/93S-03 93 P’ 8 143 Approved for public release, distribution unlimited 93... Hardman CLASS: GEE 93S Captain Michael Nelson TITLE: A Parametric Regression of the Cost of Base Realignment Action (COBRA) Model DEFENSE DATE: 20...Science in Engineering and Environmental Management Douglas D. Hardman , B.S.E.E. Michael S. Nelson, B.S.C.E Captain, USAF Captain, USAF September 1993

Beyond the Horizon: Developing Future Airpower Strategy

DTIC Science & Technology

2014-01-01

is or becomes more capable, then it is further evidence the USAF failed to proactively usher in these emerging and vital airpower capabilities...USAF airpower. 9. USAF chief of staff, Gen Norton Schwartz, 2009, offered in numerous speeches. 10. Carl H. Builder, The Icarus Syndrome : The Role of

Neural Network Back-Propagation Algorithm for Sensing Hypergols

NASA Technical Reports Server (NTRS)

Perotti, Jose; Lewis, Mark; Medelius, Pedro; Bastin, Gary

2013-01-01

Fast, continuous detection of a wide range of hazardous substances simultaneously is needed to achieve improved safety for personnel working with hypergolic fuels and oxidizers, as well as other hazardous substances, with a requirement for such detection systems to warn personnel immediately upon the sudden advent of hazardous conditions, with a high probability of detection and a low false alarm rate. The primary purpose of this software is to read the voltage outputs from voltage dividers containing carbon nano - tube sensors as a variable resistance leg, and to recognize quickly when a leak has occurred through recognizing that a generalized pattern change in resistivity of a carbon nanotube sensor has occurred upon exposure to dangerous substances, and, further, to identify quickly just what substance is present through detailed pattern recognition of the shape of the response provided by the carbon nanotube sensor.

Incorporation of alpha-Ketoglutaric Acid as a Fixed Bed Scrubber Media for the Neutralization of Hydrazine Family Hypergolic Fuels

NASA Technical Reports Server (NTRS)

DeVor, R. W.; Santiago-Maldonado, E.; Parkerson, J. K.

2010-01-01

A candidate scrubber media, alpha-ketoglutaric acid (aKGA) adsorbed onto a silica-based substrate was examined as a potential alternative to the hydrazine-family hypergolic fuel neutralization techniques currently utilized at NASA/Kennedy Space Center (KSC). Helvenson et. al. has indicated that aKGA will react with hydrazines to produce non-hazardous, possibly biodegradable products. Furthermore, the authors have previously tested and demonstrated the use of aKGA aqueous solutions as a replacement neutralizing agent for citric acid, which is currently used as a scrubbing agent in liquid scrubbers at KSC. Specific properties examined include reaction efficiency, the loading capacity of aKGA onto various silica substrates, and the comparison of aKGA media performance to that of the citric acid vapor scrubber systems at KSC and a commercial vapor scrubber media. Preliminary investigations showed hydrophobic aerogel particles to be an ideal substrate for the deposition of the aKGA. Current studies have shown that the laboratory produced aKGA-Aerogel absorbent media are more efficient and cost effective than a commercially available fixed bed scrubber media, although much less cost effective than liquid-based citric acid scrubbers (although possibly safer and less labor intensive). A comparison of all three alternative scrubber technologies (liquid aKGA, solid-phase aKGA, and commercially available sorbent materials) is given considering both hypergolic neutralization capabilities and relative costs (as compared to the current citric acid scrubbing technology in use at NASA/KSC).

A Condition Based Maintenance Approach to Forecasting B-1 Aircraft Parts

DTIC Science & Technology

2017-03-23

1 Problem Statement...aimed at making the USAF aware of CBM methods, and recommending which techniques to consider for implementation. Problem Statement The USAF relies on... problem , this research will seek to highlight common CBM forecasting methods that are well established and evaluate its suitability with current USAF

76 FR 59116 - Procurement List; Additions

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-23

... NSN: AF110--Shirt, Class A/Primary Duty, USAF, Men's, Long Sleeve, Dark Navy Blue, Numerous Sizes. NSN: AF111--Shirt, Class A/Primary Duty, USAF, Women's, Long Sleeve, Dark Navy Blue, Numerous Sizes. NSN: AF120--Shirt, Class A/Primary Duty, USAF, Men's, Short Sleeve, Dark Navy Blue, Numerous Sizes. NSN...

Gulf Cooperation Council: Arabian Gulf Cooperation Continues Defense Forces (Peninsula Shield Force)

DTIC Science & Technology

2015-05-23

Lieutenant Colonel Rhett Champagne , USAF, “The Case for a Gulf Cooperation Council Peninsula Shield Force,” The FAOA Journal of International Affairs...Anthony J. Mastalir USAF, Lieutenant Colonel Jim Keating USA, and Lieutenant Colonel Rhett Champagne , USAF. “The Case for a Gulf Cooperation Council

Low Yield Nuclear Experiments: Should They Be Permitted Within a Comprehensive Test Ban Treaty?

DTIC Science & Technology

1996-10-01

GRAVITY BOMB 83 AF A W87 ICBM REENTRY VEHICLE 86 AF A W88 SLBM REENTRY VEHICLE 89 NAVY C SAFETY FEATURES: A--(ENDS, IHE, FRP) B--(ENDS, IHE) C--(ENDS) o...NUCLEAR WEAPON DELIVERY PLATFORMS (NUCLEAR POSTURE REVIEW) STRATEGIC DELIVERY VEHICLES 20 B-2 BOMBERS USAF 66 B-52 BOMBERS USAF 500/450 MINUTEMAN III...ICBMs USAF 14 TRIBENT SUBMARINES USN W/ 24 D-5 MISSILES EACH TACTICAL DELIVERY VEHICLES DUAL CAPABLE AIRCRAFT USAF/USN SEA-LAUNCH CRUISE MISSILES USN

Design optimization of space launch vehicles using a genetic algorithm

NASA Astrophysics Data System (ADS)

Bayley, Douglas James

The United States Air Force (USAF) continues to have a need for assured access to space. In addition to flexible and responsive spacelift, a reduction in the cost per launch of space launch vehicles is also desirable. For this purpose, an investigation of the design optimization of space launch vehicles has been conducted. Using a suite of custom codes, the performance aspects of an entire space launch vehicle were analyzed. A genetic algorithm (GA) was employed to optimize the design of the space launch vehicle. A cost model was incorporated into the optimization process with the goal of minimizing the overall vehicle cost. The other goals of the design optimization included obtaining the proper altitude and velocity to achieve a low-Earth orbit. Specific mission parameters that are particular to USAF space endeavors were specified at the start of the design optimization process. Solid propellant motors, liquid fueled rockets, and air-launched systems in various configurations provided the propulsion systems for two, three and four-stage launch vehicles. Mass properties models, an aerodynamics model, and a six-degree-of-freedom (6DOF) flight dynamics simulator were all used to model the system. The results show the feasibility of this method in designing launch vehicles that meet mission requirements. Comparisons to existing real world systems provide the validation for the physical system models. However, the ability to obtain a truly minimized cost was elusive. The cost model uses an industry standard approach, however, validation of this portion of the model was challenging due to the proprietary nature of cost figures and due to the dependence of many existing systems on surplus hardware.

Development of Advanced Hydrocarbon Fuels at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Bai, S. D.; Dumbacher, P.; Cole, J. W.

2002-01-01

This was a small-scale, hot-fire test series to make initial measurements of performance differences of five new liquid fuels relative to rocket propellant-1 (RP-1). The program was part of a high-energy-density materials development at Marshall Space Flight Center (MSFC), and the fuels tested were quadricyclane, 1-7 octodiyne, AFRL-1, biclopropylidene, and competitive impulse noncarcinogenic hypergol (CINCH) (di-methyl-aminoethyl-azide). All tests were conducted at MSFC. The first four fuels were provided by the U.S. Air Force Research Laboratory (AFRL), Edwards Air Force Base, CA. The U.S. Army, Redstone Arsenal, Huntsville, AL, provided the CINCH. The data recorded in all hot-fire tests were used to calculate specific impulse and characteristic exhaust velocity for each fuel, then compared to RP-1 at the same conditions. This was not an exhaustive study, comparing each fuel to RP-1 at an array of mixture ratios, nor did it include important fuel parameters, such as fuel handling or long-term storage. The test hardware was designed for liquid oxygen (lox)/RP-1, then modified for gaseous oxygen/RP-1 to avoid two-phase lox at very small flow rates. All fuels were tested using the same thruster/injector combination designed for RP-1. The results of this test will be used to determine which fuels will be tested in future test programs.

USAF/SCEEE Graduate Student Summer Research Program (1984). Program Management Report. Volume 1.

DTIC Science & Technology

1984-10-01

AFRL -TN-87, Air Force . Weapons Laboratory , Kirtland Air Foce...Mexico Research Location: Air Force Weapons Laboratory , NTATT, Kirtland Air Force Base, Albuquerque, NM 87117 .. USAF Research Contact: Dr. Carl E. Baum...Albuquerque, NM 87131 ... Research Location: Air Force Weapons Laboratory Kirtland Air Force Base Albuquerque, New Mexico 87117 USAF

Unintended Consequences: Potential Downsides of the Air Force’s Conversion to Biofuels

DTIC Science & Technology

2011-01-01

Mark N. Goltz , PhD, USAF, Retired Dr. Charles A. Bleckmann Dr. Douglas M. Mackay Maj Khai Vuong, USAF Capt Jerrod P. McComb, USAF* *Lieutenant...Colonel Goltz and Dr. Bleckmann are faculty members in the environmental engineering and science program at the Air Force Institute of Technology (AFIT

MANTECH project book

NASA Astrophysics Data System (ADS)

The effective integration of processes, systems, and procedures used in the production of aerospace systems using computer technology is managed by the Integration Technology Division (MTI). Under its auspices are the Information Management Branch, which is actively involved with information management, information sciences and integration, and the Implementation Branch, whose technology areas include computer integrated manufacturing, engineering design, operations research, and material handling and assembly. The Integration Technology Division combines design, manufacturing, and supportability functions within the same organization. The Processing and Fabrication Division manages programs to improve structural and nonstructural materials processing and fabrication. Within this division, the Metals Branch directs the manufacturing methods program for metals and metal matrix composites processing and fabrication. The Nonmetals Branch directs the manufacturing methods programs, which include all manufacturing processes for producing and utilizing propellants, plastics, resins, fibers, composites, fluid elastomers, ceramics, glasses, and coatings. The objective of the Industrial Base Analysis Division is to act as focal point for the USAF industrial base program for productivity, responsiveness, and preparedness planning.

Tubing For Sampling Hydrazine Vapor

NASA Technical Reports Server (NTRS)

Travis, Josh; Taffe, Patricia S.; Rose-Pehrsson, Susan L.; Wyatt, Jeffrey R.

1993-01-01

Report evaluates flexible tubing used for transporting such hypergolic vapors as those of hydrazines for quantitative analysis. Describes experiments in which variety of tubing materials, chosen for their known compatibility with hydrazine, flexibility, and resistance to heat.

Wipes, Coatings, and Patches for Detecting Hydrazines

NASA Technical Reports Server (NTRS)

Young, Rebecca; Buttner, William

2005-01-01

Three color-indicating devices have been conceived as simple, rapid, inexpensive means of detecting hazardous liquid and gaseous substances in settings in which safety is of paramount concern and it would be too time-consuming or otherwise impractical to perform detection by use of such instruments as mass spectrometers. More specifically, these devices are designed for detecting hypergolic fuels (in particular, hydrazines) and hypergolic oxidizers in spacecraft settings, where occasional leakage of these substances in liquid or vapor form occurs and it is imperative to take early corrective action to minimize adverse health effects. With suitable redesign, including reformulation of their color indicator chemicals, these devices could be adapted to detection of other hazardous substances in terrestrial settings (e.g., industrial and military ones). One of the devices is a pad of a commercially available absorbent material doped with a color indicator. The absorbent material is made from 70 percent polyester and 30 percent nylon and can absorb about eight times its own weight of liquid. The color indicator is a mixture of conventional pH color indicator chemicals. Hydrazine and monomethyl hydrazine, which are basic, cause the color indicator to turn green. In the original intended application, the pad is wiped on a space suit that is suspected of having been exposed to leaking monomethyl hydrazine during a space walk, before the wearer returns to the interior of the spacecraft. If the wiped surface is contaminated with hydrazine, the pad turns green. In addition, the pad absorbs hydrazine from the wiped surface, thereby reducing or eliminating the hazard. Used pads, including ones that show contamination by hydrazine, can be stored in a sealed plastic bag for subsequent disposal. The second device, which has been proposed but not yet developed, would comprise a color indicator material in the form of either a coating on a space suit (or other protective garment) or a coating on a sheet that could be easily attached to and detached from the protective garment. The coating material would be a hydrogel doped with a suitable pH indicator. The hydrogel would also serve to maintain a level of moisture needed to support the chemical reaction mentioned in the next sentence. In addition to changing color to indicate the presence of any hypergolic fuel (which is basic) or hypergolic oxidizer (which is acidic) that might splash on the space suit, the pH indicator would also react with the hypergolic fuel or oxidizer and thereby bind it. The third device is a color dosimeter for detecting hydrazine liquid or vapor coming from microscopic leaks. This device is designed to satisfy several requirements specific to its original intended use in the auxiliary power unit of the space shuttle. These requirements include stability under vacuum, stability at moderate temperature, fast and irreversible change in color upon exposure to hydrazine, and visibility of the color change through polyimide tape.

Experimental and Theoretical Studies of the Reactivity and Thermochemistry of Dicyanamide: N(CN)(2)(-).

PubMed

Nichols, Charles M; Wang, Zhe-Chen; Yang, Zhibo; Lineberger, W Carl; Bierbaum, Veronica M

2016-02-25

Dicyanamide [N(CN)2(-)] is a common anionic component of ionic liquids, several of which have shown hypergolic reactivity upon mixing with white-fuming nitric acid. In this study, we explore the thermochemistry of dicyanamide and its reactivity with nitric acid and other molecules to gain insight into the initial stages of the hypergolic phenomenon. We have developed and utilized an electrospray ion source for our selected ion flow tube (SIFT) to generate the dicyanamide anion. We have explored the general reactivity of this ion with several neutral molecules and atoms. Dicyanamide does not show reactivity with O2, H2SO4, H2O2, DBr, HCl, NH3, N2O, SO2, COS, CO2, CH3OH, H2O, CH4, N2, CF4, or SF6 (k < 1 × 10(-12) cm(3)/s); moreover, dicyanamide does not react with N atom, O atom, or electronically excited molecular oxygen (k < 5 × 10(-12) cm(3)/s), and our previous studies showed no reactivity with H atom. However, at 0.45 Torr helium, we observe the adduct of dicyanamide with nitric acid with an effective bimolecular rate constant of 2.7 × 10(-10) cm(3)/s. Intrinsically, dicyanamide is a very stable anion in the gas phase, as illustrated by its lack of reactivity, high electron-binding energy, and low proton affinity. The lack of reactivity of dicyanamide with H2SO4 gives an upper limit for the gas-phase deprotonation enthalpy of the parent compound (HNCNCN; <310 ± 3 kcal/mol). This limit is in agreement with theoretical calculations at the MP2/6-311++G(d,p) level of theory, finding that ΔH298 K(HNCNCN) = 308.5 kcal/mol. Dicyanamide has two different proton acceptor sites. Experimental and computational results indicate that it is lower in energy to protonate the terminal nitrile nitrogen than the central nitrogen. Although proton transfer to dicyanamide was not observed for any of the acidic molecules investigated here, the calculations on dicyanamide with one to three nitric acid molecules reveal that higher-order solvation can favor exothermic proton transfer. Furthermore, the formation of 1,5-dinitrobiuret, proposed to be the key intermediate during the hypergolic ignition of dicyanamide ionic liquids with nitric acid, is investigated by calculation of the reaction coordinate. Our results suggest that solvation dynamics of dicyanamide with nitric acid play an important role in hypergolic ignition and the interactions at the droplet/condensed-phase surface between the two hypergolic liquids are very important. Moreover, dicyanamide exists in the atmosphere of Saturn's moon, Titan; the intrinsic stability of dicyanamide strongly suggests that it may exist in molecular clouds of the interstellar medium, especially in regions where other stable carbon-nitrogen anions have been detected.

Research and technology, 1984 report

NASA Technical Reports Server (NTRS)

1984-01-01

Research and technology projects in the following areas are described: cryogenic engineering, hypergolic engineering, hazardous warning instrumentation, structures and mechanics, sensors and controls, computer sciences, communications, material analysis, biomedicine, meteorology, engineering management, logistics, training and maintenance aids, and technology applications.

John F. Kennedy Space Center's Chemochromic Hypergol Sensors

NASA Technical Reports Server (NTRS)

Nichols, James D.

2012-01-01

The National Aeronautics and Space Administration (NASA) seeks partne rs interested in the commercial application of the Chemochromic Hyper gol Sensors technology. NASA's Kennedy Space Center (KSC) is soliciti ng licensees for this innovative technology. The Chemochromic Hypergo l Sensors technology consists of chemochromic pigments incorporated i nto various matrices (e.g., tapes, sheets, injection molded parts, fi bers). When placed near strategic locations such as piping and contai ner valves, seams, and joints, these sensors provide an instantaneous , distinct color change from yellow to black indicating the presence of hypergols at the leak location. The chemochromic pigments can be incorporated into fibers used to make fabrics for personal protective equipment as well as into badge holders for use as a point leak detector. These affordable, easily replaceable sensors provide the capabil ity to visually monitor leak-prone locations and personnel working i n those areas on a continuous basis for the presence of dangerous hyp ergols.

USAF/SCEEE Graduate Student Summer Support Program (1982). Management and Technical Report.

DTIC Science & Technology

1982-10-01

AD-A130 767 USAF/SCEEE GRADUATE STUDENT SUMMER SUPPORT PROGRAM (1982) MANAGEMENT AND..(U) SOUTHEASTERN CENTER FORELECTRICAL ENGINEERING EDUCATION INC...SUMMER SUPPORT PROGRAM Conducted by Southeastern Center for Electrical Engineering Education under USAF Contract Number F49620-82-C-0035 MANAGEMENT ...UNITED STATES AIR FORCE GRADUATE STUDENT SL24MER SUPPORT PROGRAM 1982 PROGRAM MANAGEMENT AND TECHNICAL REPORT SOUTHEASTERN CENTER FOR ELECTRICAL

The Relationship between Physical Activity and Productivity

DTIC Science & Technology

1984-04-01

suggestions as our advisor. Captain Jeffrey S. Austin, USAF, of the Leadership and Management Development Center (LMDC) served unofficially yet willingly as...youthful and healthy population. It is recommended that the USAF: (1) develop fitness standards based on wartime requirements for skills requiring high...encouraged its military personnel to develop and maintain physical fitness. In the USAF’s view, regular physical conditioning and a balanced diet

Incidence of Testicular Cancer in U.S. Air Force Officer Aviators: 1998-2008

DTIC Science & Technology

2011-06-01

DAVID B. RHODES, Col, USAF, MC ROBERT E. CARROLL , Col, USAF, MC, CFS This... S ) Christopher Walker 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME( S ) AND ADDRESS(ES) USAF...REPORT NUMBER AFRL-SA-WP-SR-2012-0001 9. SPONSORING / MONITORING AGENCY NAME( S ) AND ADDRESS(ES) 10. SPONSORING/MONITOR’S ACRONYM( S

Leadership Competencies for the USAF Acquisition Community

DTIC Science & Technology

2002-04-01

RAND National Defense Fellow writing on leadership for the 21st USAF) labeled “the intellectual progeny of Burn’s transformational theory .”21 In 1999...1) a historical perspective of leadership and management in academic theory , (2) challenges facing the USAF that suggest a new leadership paradigm...the question at hand. Her research reflects a more studied academic understanding of leadership and management theory than does the work of Brolin

Air and Space Power Journal. Volume 30, Number 2, Summer 2016

DTIC Science & Technology

2016-01-01

Nicholas J. Thomas, USAF, PE Features Thinking beyond the Books ❙ 15 Sociological Biases of Our Military Institutions Ben Zweibelson Institutional ...Retired Editor, Strategic Studies Quarterly Air Force Research Institute Dr. Grant T. Hammond USAF Center for Strategy and Technology Dr. Dale L...Hayden Air Force Research Institute Col S. Clinton Hinote Military Fellow Council on Foreign Relations Dr. Thomas Hughes USAF School of Advanced Air and

A Cost Analysis of Dining Facilities: Should the Air Force Continue to Operate Dining Facilities

DTIC Science & Technology

2009-03-01

accounted for. After receiving estimates from both WPAFB ( Burkholder , 2008) and Travis AFB (Yu, 2008) and comparing those estimates with actual...doc=GetTRDoc.pdf Brinker, Steven D. MSgt, USAF, FSS/FSVF, Peterson AFB, CO. Personal Correspondence. 25 August 2008. Burkholder , Dave E. Civilian...USAF, CEMM/AFMC, Wright Patterson AFB, OH. Personal Correspondence. 3 September 2008. Coats, John N. Captain, USAF, SAF/FMFF, Washington DC

3,700 USAF Junior Acquisition Officers! Rebalance USAF Manning Priorities Now

DTIC Science & Technology

2017-04-06

duties because they represent basically “no-cost” manpower to the headquarters and base -level leaders. The USAF pays for their military salary and...Colonel, United States Air Force A Research Report Submitted to the Faculty In Partial Fulfillment of the Graduation Requirements Advisor: Colonel...academic research paper are those of the author and do not reflect the official policy or position of the US government, the Department of Defense

Joint Force Quarterly. Number 19, Summer 1998

DTIC Science & Technology

1998-08-01

Shelton, USA Publisher ADVISORY COMMITTEE LTG Richard A. Chilcoat, USA ■ National Defense University Chairman BG David A. Armstrong, USA (Ret.) ■ Office of...College Maj Gen Richard L. Engel, USAF ■ Industrial College of the Armed Forces Maj Gen Timothy A. Kinnan, USAF ■ Air War College Col David M. Lumsden...BOARD Hans Binnendijk ■ National Defense University Chairman Richard K. Betts ■ Columbia University Col J. Lee Blank, USAF ■ National War College Col

Liquid Oxygen/Liquid Methane Component Technology Development at MSFC

NASA Technical Reports Server (NTRS)

Robinson, Joel W.

2010-01-01

The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LOX)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon exploration studies. The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. Besides existing in-house risk reduction activities, NASA has solicited from industry their participation on component technologies based on the potential application to the lunar ascent main engine (AME). Contracted and NASA efforts have ranged from valve technologies to engine system testbeds. The application for the AME is anticipated to be an expendable, pressure-fed engine for ascent from the moon at completion of its lunar stay. Additionally, the hardware is expected to provide an abort capability prior to landing, in the event that descent systems malfunction. For the past 4 years, MSFC has been working with the Glenn Research Center and the Johnson Space Center on methane technology development. This paper will focus on efforts specific to MSFC in pursuing ignition, injector performance, chamber material assessments and cryogenic valve technologies. Ignition studies have examined characteristics for torch, spark and microwave systems. Injector testing has yielded insight into combustion performance for shear, swirl and impinging type injectors. The majority of chamber testing has been conducted with ablative and radiatively cooled chambers with planned activities for regenerative and transpiration cooled chambers. Lastly, an effort is underway to examine the long duration exposure issues of cryogenic valve internal components. The paper will summarize the status of these efforts.

Viscosity, conductivity, and electrochemical property of dicyanamide ionic liquids

NASA Astrophysics Data System (ADS)

Yuan, Wen-Li; Yang, Xiao; He, Ling; Xue, Ying; Qin, Song; Tao, Guo-Hong

2018-03-01

The instructive structure-property relationships of ionic liquids (ILs) can be put to task-specific design of new functionalized ILs. The dicyanamide (DCA) ILs are typical CHN type ILs which are halogen free, chemical stable, low-viscous and fuel-rich. The transport properties of DCA ionic liquids are significant for their applications as solvents, electrolytes and hypergolic propellants. This work systematically investigates several important transport properties of four DCA ILs ([C4mim][N(CN)2], [C4m2im][N(CN)2], N4442[N(CN)2], and N8444[N(CN)2]) including viscosity, conductivity, and electrochemical property at different temperatures. The melting points, temperature-dependent viscosities and conductivities reveal the structure-activity relationship of four DCA ILs. From the Walden plots, the imidazolium cations exhibit stronger cation–anion attraction than the ammonium cations. DCA ILs have relatively high values of electrochemical windows (EWs), which indicates that the DCA ILs are potential candidates for electrolytes in electrochemical applications. The cyclic voltammograms of Eu(III) in these DCA ILs at GC working electrode at various temperatures 303–333 K consists of quasi-reversible waves. The electrochemical properties of the DCA ILs are also dominated by the cationic structures. The current intensity (ip), the diffusion coefficients (Do), the charge transfer rate constants (ks) of Eu(III) in DCA ILs all increased with the molar conductivities increased. The cationic structure-transport property relationships of DCA ILs were constructed for designing novel functionalized ILs to fulfill specific demands.

Viscosity, Conductivity, and Electrochemical Property of Dicyanamide Ionic Liquids

PubMed Central

Yuan, Wen-Li; Yang, Xiao; He, Ling; Xue, Ying; Qin, Song; Tao, Guo-Hong

2018-01-01

The instructive structure-property relationships of ionic liquids (ILs) can be put to task-specific design of new functionalized ILs. The dicyanamide (DCA) ILs are typical CHN type ILs which are halogen free, chemical stable, low-viscous, and fuel-rich. The transport properties of DCA ionic liquids are significant for their applications as solvents, electrolytes, and hypergolic propellants. This work systematically investigates several important transport properties of four DCA ILs ([C4mim][N(CN)2], [C4m2im][N(CN)2], N4442[N(CN)2], and N8444[N(CN)2]) including viscosity, conductivity, and electrochemical property at different temperatures. The melting points, temperature-dependent viscosities and conductivities reveal the structure-activity relationship of four DCA ILs. From the Walden plots, the imidazolium cations exhibit stronger cation–anion attraction than the ammonium cations. DCA ILs have relatively high values of electrochemical windows (EWs), which indicates that the DCA ILs are potential candidates for electrolytes in electrochemical applications. The cyclic voltammograms of Eu(III) in these DCA ILs at GC working electrode at various temperatures 303–333 K consists of quasi-reversible waves. The electrochemical properties of the DCA ILs are also dominated by the cationic structures. The current intensity (ip), the diffusion coefficients (Do), the charge transfer rate constants (ks) of Eu(III) in DCA ILs all increased with the molar conductivities increased. The cationic structure-transport property relationships of DCA ILs were constructed for designing novel functionalized ILs to fulfill specific demands. PMID:29600245

Sampling and Data Gathering Strategies for Future USAF Anthropometry

DTIC Science & Technology

1976-02-01

of USAF body size data. The approach we suggest would be less costly and more responsive to the needs of the USAF than periodic massive surveys...has been that many of these photographs were taken primarily for somatotyping rather than for measure- ment. Another source of difficulty has been...goals and we have recently i j accepted responsibility under an AMRL research contract to demonstrate that this is so. V Of all the non-standard

The Effect of Values on System Development Project Outcomes

DTIC Science & Technology

2009-03-01

before me and upon whose broad shoulders I stand. Men like Col John Boyd (USAF, ret), Col Chet Richards (USAF, ret), Col James Burton (USAF, ret), Chuck...with new homes that could have housed more than 8,000 people. - President Dwight D. Eisenhower, April 19, 1953 I. Introduction This research...Boyne, 2007 RUBRIC SCORE: 30 F-Score:10 I-Score: 5 S-Score:10 T-Score:5 OUTCOME: A SAMPLE STATEMENTS: FAST “The Navy men liked everything

The Military Casualty with Combat Related Acute Post Traumatic Stress Disorder

DTIC Science & Technology

1984-05-01

explored. A researcher designed "Combat Fatigue Questionnaire" was mailed to 600 USAF nurses selected randomly. Three hundred sixty one USAF nurses...psychiatry noted: "Exhaustion was selected because it best described the appearance of most psychia- tric casualties" (p. xvii). Ernie Pyle, a World War II...Haber & Runyon, PL 1977), 600 (13.3% of the total USAF nurse population) names were selected . The "Combat Fatigue Questionnaire" was mailed between

Pullout of a Rigid Insert Adhesively Bonded to an Elastic Half Plane.

DTIC Science & Technology

1983-12-01

COMMAND UNITED STATES AIR FORCE C-= °84 02 13 071. C,, W % d 6 This document was prepared by the Department of Engineering Mechanics, USAF Academy Faculty...THOMAS E. KULLGREN, Lt Col, USAF Project Engineer /Scientist Professor and Acting Head, Department of Engineering Mechanics KENNETH E. SIEGETH Lt Col...Department of Engineering (Ifapphicable) Mechanics USAFA/DFEM 6c. ADDRESS (City. State and ZIP Code) 7b. ADDRESS (City, Slate and ZIP Code) USAF Academy

32 CFR 842.12 - HQ USAF claims responsibility.

Code of Federal Regulations, 2010 CFR

2010-07-01

... Administrative Management Program (CAMP) reviews. (2) Implements claims and tort litigation policies, issues... LITIGATION ADMINISTRATIVE CLAIMS Functions and Responsibilities § 842.12 HQ USAF claims responsibility. (a...

The F-16 Onboard Oxygen Generating System: Performance Evaluation and Man Rating

DTIC Science & Technology

1983-08-01

OXYGEN GENERATING , YSTEM: PERFORMANCE EVALUATION AND MAN RATING Thomas C. Horch , Captain, USAF Richard L. Miller, Ph.D. John B. Bomar, Jr...C. Horch , Capt, USAF; R. L. Miller, 8. CONTRACT OR GRANT NUMBER(i) Ph.D.; J. B. Bomar, Jr., Lt Col, IJSAF, BSC; J. B. Tedor, Maj, USAF, BSC; R. D...limitation (as of 1983); however, the information may no longer need protection since it is 14 years. At the time of its publication, Capt Thomas Horch

Space Resilience and the Contested, Degraded, and Operationally Limited Environment: The Gaps in Tactical Space Operations

DTIC Science & Technology

2014-12-01

Operationally Limited Environment The Gaps in Tactical Space Operations Capt Bryan M. Bell , USAF 2d Lt Even T. Rogers, USAF The ability of space...David S. Fadok, “John Boyd and John Warden: Airpower’s Quest for Strategic Paralysis ,” in The Paths of Heaven: The Evolution of Airpower Theory, ed...Warden,” 365. Capt Bryan M. Bell , USAF Captain Bell (BS, University of Florida; MS, Air Force Institute of Technology) is assistant operations officer and

Project CHECO Southeast Asia Report. USAF Tactics Against Air & Ground Defenses in SEA, November 1968 - May 1970

DTIC Science & Technology

1970-09-25

EB-66 Orbits for Drone Flight .......................... 50 16. ( EB-66 Orbits in Support of B-52 Mission ................ 50I 3 ix I~WI ’CNON.11...outmaneuver it. During the period of this report, while SAMs were fired at several USAF aircraft and shot down several drones , the USAF lost no manned...Oblique camaras had beendesigned to allow photography from a safe distance, but the heavy tree cover in Laos usually required vertical photography for

49 CFR 173.52 - Classification codes and compatibility groups of explosives.

Code of Federal Regulations, 2011 CFR

2011-10-01

... one containing white phosphorus, phosphide or flammable liquid or gel or hypergolic liquid) G 1.1G1.2G 1.3G 1.4G Article containing both an explosive substance and white phosphorus H 1.2H1.3H Article...

49 CFR 173.52 - Classification codes and compatibility groups of explosives.

Code of Federal Regulations, 2010 CFR

2010-10-01

... one containing white phosphorus, phosphide or flammable liquid or gel or hypergolic liquid) G 1.1G1.2G 1.3G 1.4G Article containing both an explosive substance and white phosphorus H 1.2H1.3H Article...

Atmospheric Dispersion of Hypergolic Liquid Rocket Fuels. Volume 1

DTIC Science & Technology

1984-11-01

hydrazlnes by nitrosonium ton (NO+), formed from the ionization of nitrogen tetroxide which is promoted by donor solvents such as aminen and hydrazines. 10... ion ). C. CALCULATION OF FIREBALL SIZE AND QUANTIFICATION OF HEAT FLUX Mie fireball size and heat flux calculations presented here are based on the

Proceedings of the NASA/Florida Institute of Technology Environmental Engineering Conference on Nitrogen Tetroxide. [with emphasis on space shuttle

NASA Technical Reports Server (NTRS)

Rhodes, E. L.

1978-01-01

Methods of reducing the user hazards of nitrogen tetroxide, a hypergolic oxidizer are discussed. Kennedy Space Center developments in N2O4 control for the space shuttle are featured. Other areas covered are life support equipment and transportation.

Three Orbital Burns to Molniya Orbit Via Shuttle_Centaur G Upper Stage

NASA Technical Reports Server (NTRS)

Williams, Craig H.

2015-01-01

An unclassified analytical trajectory design, performance, and mission study was done for the 1982 to 1986 joint National Aeronautics and Space Administration (NASA)-United States Air Force (USAF) Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37 deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57 deg inclined orbit: 9,545 versus 9,552 lb of separated spacecraft weight, respectively. There was a significant reduction in the need for propellant launch time reserve for a 1 hr window: only 78 lb for the three burn transfer versus 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three versus two burn transfer (12 vs. 1-1/4 hr), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

Three Orbital Burns to Molniya Orbit via Shuttle Centaur G Upper Stage

NASA Technical Reports Server (NTRS)

Williams, Craig H.

2014-01-01

An unclassified analytical trajectory design, performance, and mission study was done for the 1982-86 joint NASA-USAF Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57deg inclined orbit: 9,545 lb vs. 9,552 lb of separated spacecraft weight respectively. There was a significant reduction in the need for propellant launch time reserve for a one hour window: only 78 lb for the three burn transfer vs. 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three vs. two burn transfer (12 vs. 11/4 hrs), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

USAF Bioenvironmental Noise Data Handbook. Volume 156. HH-1N In-flight Crew Noise

NASA Astrophysics Data System (ADS)

Hille, H. K.

1982-11-01

The HH-IN is a USAF multi-purpose utility helicopter providing support for various USAF missions. This report provides measured data defining the bioacoustic environments at flight crew locations inside this helicopter during normal flight operations. Data are reported for two locations in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors. Refer to Volume 1 of this handbook, USAF Bioenvironmental Noise Data Handbook, Vol. 1: Organization, Content and Application, AMRL-TR-75-50(1) 1975, for discussion of the objective and design of the handbook, the types of data presented, measurement procedures, instrumentation, data processing, definitions of quantities, symbols, equations, applications, limitations, etc.

Thruster residues on returned Mir solar panel

NASA Astrophysics Data System (ADS)

Harvey, Gale A.

2000-09-01

A solar panel with more than ten years space exposure was returned to Earth in January 1998. Several types of residues were deposited or transported onto the solar cell coverglasses during the space exposure. Self-contamination of SiOx films from the silicone potting compound was a major contamination of the coverglasses. A second type of contamination was thick, detergent-like residues of the order of a millimeter diameter on many, but not most of the coverglasses. A third, prevalent type of contamination was very thin irregular shaped films or patterns of a millimeter size which are readily visible in brilliant colors when the coverglasses are viewed with a 50x brightfield microscope. These prolific, overlapping, and almost ubiquitous patterns strongly suggest wetting on the surface. The probably cause of most of the wetted patterns on the returned Mir solar cell coverglasses is trace hydrazine nitrate in condensed water droplets produced as reaction products from Mir's and the Orbiters' hypergolic thrusters. This paper presents some of the wetted patterns, information regarding hypergolic reaction products, and type of thrusters associated with Mir operations.

Material selection and evaluation of new encapsulation compounds for electric cables for launch support system

NASA Technical Reports Server (NTRS)

Ray, Asit K.

1992-01-01

Eight urethane compounds were evaluated as possible replacement for the existing encapsulating compoounds for electrical cables for the Launch Support System at Kennedy Space Center (KSC). The existing encapsulating compound, PR-1535, contains the curative MOCA 4-4'-Methylene-BIS (2-chloroaniline), which is a suspect carcinogen and hence may be the subject of further restrictions of its use by the Occupational Safety and Health Administration (OSHA). The samples made in the configuration of cable joints and in the form of disks were evaluated for flammability and hypergolic compatibility. These also underwent accelerated weatherability tests that measured the residual hardness of the exposed samples. Three candidates and the existing compound passed the hardness test. Of these, only one candidate and the existing compound passed the flammability test. The thermal and hydrolytic stability (weatherability) of these samples was studied using thermogravimetric analysis (DSC) techniques. The TMA and DSC data correlated with the residual hardness data; whereas, the TGA data showed no correlation. A hypergolic compatibility test will be conducted on the compound V-356-HE80, which passed both the flammability and accelerated weatherability tests.

An Assessment of the USAFE School Board Test Program

DTIC Science & Technology

2002-07-01

2000. USAFE Strategic Plan on Dependent Education, Headquarters, USAFE, October 1998. Vajont ES, http://www.vajo-es.eu.odedodea.edu/ Vogelweh ES...Pordenone ES K–6 109 2/2/0 Vajont ES K–6 157 2/2/0 Aviano AB 4 1,365 11/11/1 4/4/1 10/0 Incirlik ES K–6 475 3/3/0 Incirlik HS 7–12 217...Aviano) K–6 109 AF SB VAJONT ES (Aviano) K–6 157 AVIANO ES K–6 629 AVIANO HS 7–12 470 VICENZA ES K–6 480 A IAC VICENZA HS 7–12 251

Air-to-Air Encounters in Southeast Asia. Volume I. Account of F-4 and F-8 Events Prior to 1 March 1967

DTIC Science & Technology

1967-10-01

Project of the following Air ) Force pilots is acknowledged: Thomas H. Curtis, Maj., USAF Leslie C . Long, Capt., USAF Robert S. Maxwell , Capt., USAF R. P...maneuvering combat. Aircrew of two valid in GC1 envlronment c Di. Dlstracting in v4 ual engagement, because must think about back seat. Coordinatuc 2-Jficult...EVENTS PRIOR TO MARCH 1967(U) John S. Atrincilo. Project Leader Reproduced From Best Available Copy October !967 /I L U J %r. ,-~i ’, *J * . oc,,,11C

2001 Industry Studies: Munitions

DTIC Science & Technology

2001-01-01

Lt Col Michael P. Howe, USAF Lt Col William E . MacLure, USAF Mr. Terrence K. May, Dept of the Air Force LTC Paul M. McQuain, USA CDR David L. Prater...USN CAPT Steven K. Tucker, USN Lt Col Richard L. Wojick , Jr., USAF Mr. Michael J. Yurina, Dept of the Navy Dr. Thomas C. Hone, faculty CAPT Ralph...FY98 FY99 FY00 FY01 FY02 FY03 FY04 FY05 FY 00 $ BI LL IO N RDT& E - S&T (Far-Term) RDT& E - Development (Near- and Mid-Term) Procurement (Near-Term) 6 As

Program Office Guide to Ada. Edition 1

DTIC Science & Technology

1986-09-17

publication. MARK V. ZIEMBA , 2Lt, USAF Project Officer, Software Engineering Tools & Methods ARTHUR G. DECELLES, Capt, USAF Program Manager, Computer...UNLIMITED G3 SAME AS RPT D DTIC USERS 21 ABSTRACT SECURITY CLASSIFICATION UNCLASSIFIED 22a. NAME OF RESPONSIBLE INDIVIDUAL M.V. Ziemba

Lightning Launch Commit Criteria for America's Space Program

NASA Technical Reports Server (NTRS)

Roeder, W. P.; Sardonia, J. E.; Jacobs, S. C.; Hinson, M. S.; Harms, D. E.; Madura, J. T.; DeSordi, S. P.

1999-01-01

The danger of natural and triggered lightning significantly impacts space launch operations supported by the USAF. The lightning Launch Commit Criteria (LCC) are used by the USAF to avoid these lightning threats to space launches. This paper presents a brief overview of the LCC.

Aircraft Control Using Engine Thrust: A History of Learning TOC Real-Time

NASA Technical Reports Server (NTRS)

Cole, Jennifer H.; Batteas, Frank; Fullerton, Gordon

2006-01-01

A history of learning the operation of Throttles Only Control (TOC) to control an aircraft in real time using engine thrust is shown. The topics include: 1) Past TOC Accidents/Incidents; 2) 1972: DC-10 American Airlines; 3) May 1974: USAF B-52H; 4) April 1975: USAF C-5A; 5) April 1975: USAF C-5A; 6) 1981: USAF B-52G; 7) August 1985: JAL 123 B-747; 8) JAL 123 Survivor Story; 9) JAL 123 Investigation Findings; 10) July 1989: UAL 232 DC-10; 11) UAL 232 DC-10; 12) Eastwind 517 B-737; 13) November 2003: DHL A-300; 14) Historically, TOC has saved lives; 15) Automated Throttles-Only Control; 16) PCA Project; 17) Propulsion-Controlled Aircraft; 18) MD-11 PCA System and Flight Test Envelope; 19) MD-11 Simulation, PCA ILS-Soupled Landing Dispersion; 20) Throttles-Only Pitch and Roll Control Power; 21) PCA in Commercial Fleet; 22) Fall 2005: PCAR Project; 23) PCAR Background - TOC; and 24) PCAR Background - TOC.

Epidemiology of HIV among US Air Force Military Personnel, 1996–2011

PubMed Central

Hakre, Shilpa; Mydlarz, Dariusz G.; Dawson, Peter; Danaher, Patrick J.; Gould, Philip L.; Witkop, Catherine T.; Michael, Nelson L.; Peel, Sheila A.; Scott, Paul T.; Okulicz, Jason F.

2015-01-01

Objective The objectives of this study were to describe the epidemiology of HIV in the United States Air Force (USAF) from 1996 through 2011 and to assess whether socio-demographic characteristics and service-related mobility, including military deployments, were associated with HIV infection. Methods We conducted a retrospective cohort analysis of USAF personnel who were HIV-infected during the study period January 1, 1996 through December 31, 2011 and a matched case-control study. Cases were USAF personnel newly-diagnosed with HIV during the study period. Five randomly-selected HIV-uninfected controls were matched to each case by age, length of service, sex, race, service, component, and HIV test collection date. Socio-demographic and service-related mobility factors and HIV diagnosis were assessed using conditional logistic regression. Results During the study period, the USAF had 541 newly diagnosed HIV-infected cases. HIV incidence rate (per 100,000 person-years) among 473 active duty members was highest in 2007 (16.78), among black/ African-American USAF members (26.60) and those aged 25 to 29 years (10.84). In unadjusted analysis restricted to personnel on active duty, 10 characteristics were identified and considered for final multivariate analysis. Of these single (adjusted odds ratio [aOR], 8.15, 95% confidence interval [CI] 5.71–11.6) or other marital status (aOR 4.60, 95% CI 2.72–7.75), communications/ intelligence (aOR 2.57, 95% CI 1.84–3.60) or healthcare (aOR 2.07, 95% CI 1.28–3.35) occupations, and having no deployment in the past 2 years before diagnosis (aOR 2.02, 95% CI 1.47–2.78) conferred higher odds of HIV infection in adjusted analysis. Conclusion The highest risk of HIV infection in the USAF was among young unmarried deployment-naïve males, especially those in higher risk occupation groups. In an era when worldwide military operations have increased, these analyses identified potential areas where targeted HIV prevention efforts may be beneficial in reducing HIV incidence in the USAF military population. PMID:25961564

QDR 2001: Strategy-Driven Choices for America’s Security

DTIC Science & Technology

2001-04-01

McKenzie, Jr., USMC; Lieutenant Colonel Philip M. Ruhlman , USAF; Lieutenant Colonel John J. Spinelli, USA; and Captain Sam J. Tangredi, USN. Their...one chosen by their service: Lieutenant Colonel Frank McKenzie, USMC; Lieutenant Colonel Philip Ruhlman , USAF; Lieutenant Colonel John Spinelli, USA

Special Features of the Air to Space Neutron Transport Problem

DTIC Science & Technology

2017-09-14

Fig. 5 from (NOAA, NASA , USAF, 1976, p. 13). .......................................................... 194 Atmospheric density as a function of...75 Physical constants for 1976 U.S. Standard Atmosphere. (NOAA, NASA ... NASA , USAF, 1976, p. 3), and computed base temperatures and pressures from the surface to 86 geometric kilometers

Continuous Hypergolic Monitor Network for Shipboard Applications

DTIC Science & Technology

2005-08-30

PEI Oxidizers MON-25 Polyamines and Polycarbonyls Ethanol SXFA Acetone PEO Octane Poly(ethylene-co-vinyl acetate) ( PEVA ), Polyisobutylene...polyvinylacetate ( PEVA ). These tests were performed under variable humidity and temperature (Figure 13) and under low humidity at ambient temperature...Test of Chemoselective Polymers Against Interferents with Variable Temperature and Humidity. Key: PEVA black; PEI red; SXFA blue; NmA yellow

Plasma Propulsion Testing Capabilities at Arnold Engineering Development Center

NASA Technical Reports Server (NTRS)

Polzin, Kurt A.; Dawbarn, Albert; Moeller, Trevor

2007-01-01

This paper describes the results of a series of experiments aimed at quantifying the plasma propulsion testing capabilities of a 12-ft diameter vacuum facility (12V) at USAF-Arnold Engineering Development Center (AEDC). Vacuum is maintained in the 12V facility by cryogenic panels lining the interior of the chamber. The pumping capability of these panels was shown to be great enough to support plasma thrusters operating at input electrical power >20 kW. In addition, a series of plasma diagnostics inside the chamber allowed for measurement of plasma parameters at different spatial locations, providing information regarding the chamber's effect on the global plasma thruster flowfield. The plasma source used in this experiment was Hall thruster manufactured by Busek Co. The thruster was operated at up to 20 kW steady-state power in both a lower current and higher current mode. The vacuum level in the chamber never rose above 9 x 10(exp -6) torr during the course of testing. Langmuir probes, ion flux probes, and Faraday cups were used to quantify the plasma parameters in the chamber. We present the results of these measurements and estimates of pumping speed based on the background pressure level and thruster propellant mass flow rate.

Air and Space Power Joumal. Volume 25, Number 3, Fall 2011

DTIC Science & Technology

2011-01-01

Navarre, Florida Mr. Charles Tustin Kamps USAF Air Command and Staff College Dr. Tom Keaney Johns Hopkins University Col Merrick E. Krause , USAF, Retired...fighter pilots such as Wolfgang Falck, Hajo Herrmann, and Hans-Joachim Jabs. In this aspect, Heaton (a professor at the American Military University

2001 Industry Studies: Aircraft

DTIC Science & Technology

2001-01-01

Air Force Mr Bill Craft, Dept of State LTC Conway Ellers, USA Col Bob D’Amico, USAF Mr Dave Hersh, Dept of Navy Mr John Krieger , Dept of Treasury Mr...the Navy), John Krieger (Department of Treasury), and Colonel James Solinski (USAF) 34 The world has changed significantly since the end of the Cold War

Situational Leadership Theory to the USAF Officer Training School.

DTIC Science & Technology

1988-04-01

Commanders Develop Leadership Styles ................... 4 FeedbacK Systems .............................................. 5 Conclusion...7 Leadership Styles ....................... . ..................... 9 CHAPTER THREE--THE SITUATIONAL LEADERSHIP THEORY AND OTS The USAF Officer...53 . 6 P N 5p* LIST OF ILLUSTRATIONS a- I" TABLES TABLE P-I-- Leadership Styles Matched With Maturity Levels

78 FR 41042 - Proposed Collection; Comment Request

Federal Register 2010, 2011, 2012, 2013, 2014

2013-07-09

... DEPARTMENT OF DEFENSE Department of the Air Force [Docket ID: USAF-2013-0030] Proposed Collection; Comment Request AGENCY: Air Force Chief of Chaplains Office (DOD/USAF/HQ AF/HC), Department of the Air Force, Department of Defense. ACTION: Notice. In compliance with Section 3506(c)(2)(A) of the Paperwork...

Using Nanotechnology to Detect Nerve Agents

DTIC Science & Technology

2011-01-01

56 | Air & Space Power Journal Air Force Institute of Technology Using Nanotechnology to Detect Nerve Agents Lt Col Mark N. Goltz , PhD, USAF...Retired Dr. Dong Shik Kim Maj LeeAnn Racz, PhD, USAF* *Lieutenant Colonel Goltz and Major Racz are faculty members in the Department of Systems and

Resource Prospector Propulsion System Cold Flow Testing

NASA Technical Reports Server (NTRS)

Williams, Hunter; Holt, Kim; Addona, Brad; Trinh, Huu

2015-01-01

Resource Prospector (RP) is a NASA mission being led by NASA Ames Research Center with current plans to deliver a scientific payload package aboard a rover to the lunar surface. As part of an early risk reduction activity, Marshall Space Flight Center (MSFC) and Johnson Space Flight Center (JSC) have jointly developed a government-version concept of a lunar lander for the mission. The spacecraft consists of two parts, the lander and the rover which carries the scientific instruments. The lander holds the rover during launch, cruise, and landing on the surface. Following terminal descent and landing the lander portion of the spacecraft become dormant after the rover embarks on the science mission. The lander will be equipped with a propulsion system for lunar descent and landing, as well as trajectory correction and attitude control maneuvers during transit to the moon. Hypergolic propellants monomethyl hydrazine and nitrogen tetroxide will be used to fuel sixteen 70-lbf descent thrusters and twelve 5-lbf attitude control thrusters. A total of four metal-diaphragm tanks, two per propellant, will be used along with a high-pressure composite-overwrapped pressure vessel for the helium pressurant gas. Many of the major propulsion system components are heritage missile hardware obtained by NASA from the Air Force. In parallel with the flight system design activities, a simulated propulsion system based on flight drawings was built for conducting a series of water flow tests to characterize the transient fluid flow of the propulsion system feed lines and to verify the critical operation modes such as system priming, waterhammer, and crucial mission duty cycles. The primary objective of the cold flow testing was to simulate the RP propulsion system fluid flow operation through water flow testing and to obtain data for anchoring analytical models. The models will be used to predict the transient and steady state flow behaviors in the actual flight operations. All design and build efforts, including the analytical modeling, have been performed. The cold flow testing of the propulsion system was set up and conducted at a NASA MSFC test facility. All testing was completed in the summer of 2014, and this paper documents the results of that testing and the associated fluid system modeling efforts.

Air and Space Power Journal. Volume 25, Number 3, Fall 2011

DTIC Science & Technology

2011-01-01

Charles Tustin Kamps USAF Air Command and Staff College Dr. Tom Keaney Johns Hopkins University Col Merrick E. Krause , USAF, Retired Department of Homeland...conducted face-to-face interviews with many of the air war leaders and noble night-fighter pilots such as Wolfgang Falck, Hajo Herrmann, and Hans

Heritage, Image and Identity: The Evolution of USAF Leadership

DTIC Science & Technology

2011-02-16

up-in-coming “ Generation Z ” (also known as the “Net or Digital Generation”), which is the most connected and high-tech generation ever seen. 40...for future RPA warrior leaders. 43 The USAF has already set the ground work to position “ Generation Z ” RPA pilots for future senior leadership

77 FR 43816 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2012-07-26

... DEPARTMENT OF DEFENSE Department of the Air Force [Docket ID: USAF-2012-0012] Privacy Act of 1974; System of Records AGENCY: Department of the Air Force, DoD. ACTION: Notice to alter a system of records... OSD Federal Register Liaison Officer, Department of Defense. F033 AFCA C SYSTEM NAME: USAF Information...

13. DETAIL OF CENTER OF CENTRAL CONTROL CONSOLE IN SLC3W ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

13. DETAIL OF CENTER OF CENTRAL CONTROL CONSOLE IN SLC-3W CONTROL ROOM SHOWING USAF LAUNCH CONTROLLER AND ASSISTANT USAF LAUNCH CONTROLLER PANELS. CONSOLES AND CHAIRS NEAR NORTH WALL IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

76 FR 15231 - Proposed Amendment of Class D and E Airspace; Palmdale, CA

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-21

... Palmdale Regional Airport/USAF Plant 42. This action would enhance the safety and management of aircraft operations at Palmdale Regional Airport/USAF Plant 42. This action would also correct the name of the airport..., economic, environmental, and energy-related aspects of the proposal. Communications should identify both...

Army Fixed-Wing Ground Attack Aircraft: A Historical Precedent and Contemporary Rationale

DTIC Science & Technology

2015-06-12

platforms at the tactical level. Fielding such aircraft would free the Air Force to focus on its broader missions while enhancing the capabilities of...ground forces. In fact, an Army attack aircraft would reduce, but not eliminate, the requirement for USAF CAS, freeing the USAF to focus on its

32 CFR 989.22 - Mitigation.

Code of Federal Regulations, 2010 CFR

2010-07-01

... EPF informed of the mitigation status. The EPF reports its status, through the MAJCOM, to HQ USAF/A7CI when requested. Upon request, the EPF must also provide the results of relevant mitigation monitoring... forwarded, through the MAJCOM EPF to HQ USAF/A7CI for review within 90 days from the date of signature of...

32 CFR Appendix A to Part 989 - Glossary of References, Abbreviations, Acronyms, and Terms

Code of Federal Regulations, 2010 CFR

2010-07-01

... Engineering and the Environment AFCEE/TDB AFCEE Technical Directorate, Built Infrastructure Division (AFCEE... Materiel Command HQ USAF Headquarters, United States Air Force HQ USAF/A7C The Air Force Civil Engineer.../AQR Deputy Assistant Secretary of the Air Force (Science, Technology, and Engineering) SAF/GC Air...

USAF (United States Air Force) bioenvironmental noise data handbook. Volume 2: Index

NASA Astrophysics Data System (ADS)

Cole, J. N.; Peachey, N. J.

1983-03-01

This report is an index which identifies the individual volumes published during the 1975-1982 period by the Air Force Aerospace Medical Research Laboratory (AFAMRL) as a multi-volume report, ""USAF Bioenvironmental Noise Data Handbook'', AMRL-TR-75-50 and lists those aircraft, ground equipment and other systems reported there in.

Command Structure for Theater Warfare: The Quest for Unity of Command

DTIC Science & Technology

1984-09-01

that trryfari tail forth thr htst from iti—Btturki Major General« Pern M Smith. USAF. and Hark) A Hughe«. USAF. contributed more to the rndertaking...an air. ground, and sea component. These arc generic commands which control all combat operations in the media of the air. ground, and sea. There

British Naval Aviation and the Anti-Submarine Campaign, 1917-18

DTIC Science & Technology

2004-01-01

me. Also, I extend my gratitude to Col Phil Meilinger, USAF (Ret.) and Lt Col Roy Houchin, USAF, for reading some of my earlier chapter drafts and...Revolution, 1912-1918. London: Frank Cass, 1999. Barker, Ralph. A Brief History of the Royal Flying Corps in World War I. London: Robinson, 2002. Beckett

Toward the Implementation of Augmented Reality Training

ERIC Educational Resources Information Center

Mayberry, Charles R.

2013-01-01

The United States Air Force (USAF) trains C-130H Loadmaster students at Little Rock Air Force Base (AFB) through a civilian contract. The Aircrew Training System (ATS) contractor utilizes a Fuselage Trainer (FuT) to provide scenarios for the Loadmaster students to practice loading and unloading a simulated aircraft. The problem was the USAF does…

Ionic Liquid Fuels for Chemical Propulsion

DTIC Science & Technology

2014-11-20

researchers seeking hypergolic fuels have limited themselves to the extremely toxic and corrosive nitric acid solutions. While important questions remain...storable oxidizer (N204 , nitric acid ) have been synthesized and demonstrated. The bipropellant fuels are based upon salts containing dicyanamide or...20-30% nanoparticle loading but decreases between 10-20%, perhaps indicating an optimal loading concentration for these nanoparticles between 10-20

An Experimental Investigation of Hypergolic Ignition Delay of Hydrogen Peroxide with Fuel Mixtures

NASA Technical Reports Server (NTRS)

Blevins, John A.; Gostowski, Rudy; Chianese, Silvio

2003-01-01

An experimental evaluation of decomposition and ignition delay of hydrogen peroxide at concentrations of 80% to 98% with combinations of hydrocarbon fuels, tertiary amines and transition metal chelates will be presented in the proposed paper. The results will be compared to hydrazine ignition delays with hydrogen peroxide and nitric acid mixtures using the same test apparatus.

Integration Of Launch Vehicle Simulation/Analysis Tools And Lunar Cargo Lander Design. Part 2/2

NASA Technical Reports Server (NTRS)

DeJean, George Brian; Shiue, Yeu-Sheng Paul; King, Jeffrey

2005-01-01

Part 2, which will be discussed in this report, will discuss the development of a Lunar Cargo Lander (unmanned launch vehicle) that will transport usable payload from Trans- Lunar Injection to the moon. The Delta IV-Heavy was originally used to transport the Lunar Cargo Lander to TLI, but other launch vehicles have been studied. In order to uncover how much payload is possible to land on the moon, research was needed in order to design the sub-systems of the spacecraft. The report will discuss and compare the use of a hypergolic and cryogenic system for its main propulsion system. The guidance, navigation, control, telecommunications, thermal, propulsion, structure, mechanisms, landing gear, command, data handling, and electrical power sub-systems were designed by scaling off other flown orbiters and moon landers. Once all data was collected, an excel spreadsheet was created to accurately calculate the usable payload that will land on the moon along with detailed mass and volume estimating relations. As designed, The Lunar Cargo Lander can plant 5,400 lbm of usable payload on the moon using a hypergolic system and 7,400 lbm of usable payload on the moon using a cryogenic system.

A Study to Compare the Failure Rates of Current Space Shuttle Ground Support Equipment with the New Pathfinder Equipment and Investigate the Effect that the Proposed GSE Infrastructure Upgrade Might Have to Reduce GSE Infrastructure Failures

NASA Technical Reports Server (NTRS)

Kennedy, Barbara J.

2004-01-01

The purposes of this study are to compare the current Space Shuttle Ground Support Equipment (GSE) infrastructure with the proposed GSE infrastructure upgrade modification. The methodology will include analyzing the first prototype installation equipment at Launch PAD B called the "Pathfinder". This study will begin by comparing the failure rate of the current components associated with the "Hardware interface module (HIM)" at the Kennedy Space Center to the failure rate of the neW Pathfinder components. Quantitative data will be gathered specifically on HIM components and the PAD B Hypergolic Fuel facility and Hypergolic Oxidizer facility areas which has the upgraded pathfinder equipment installed. The proposed upgrades include utilizing industrial controlled modules, software, and a fiber optic network. The results of this study provide evidence that there is a significant difference in the failure rates of the two studied infrastructure equipment components. There is also evidence that the support staff for each infrastructure system is not equal. A recommendation to continue with future upgrades is based on a significant reduction of failures in the new' installed ground system components.

Anesthesia Provider’s Use of the Precordial or Esophageal Stethoscope: Is Anyone Still Listening to the Patient

DTIC Science & Technology

1996-06-01

USAF, NC and Dr. Maura McAuliffe, Lt. Col. , USAF, NC. Dr. Hall served as my qualitative data advisor. Her assi stance ensured an accurate...esophageal stethoscope, Anesthesiology, 65 (5), 534-536. Prielipp, R. c., Kelly , J. S., & Roy, R. C. (1995, August). Use of esophageal or

Evaluating the Impacts of Technology Education on Military Maintenance Students

ERIC Educational Resources Information Center

Jordan, Jeremy D.; Curtis, Christopher

2010-01-01

The United States Air Force (USAF) provides career and technical education (CTE) to a wide variety of specialty career fields. Training airmen to carry out the mission while honoring the USAF core values of integrity first, service before self, and excellence in all we do is the top priority of military leaders and trainers. Vehicle maintenance is…

Cyberspace Human Capital: Building a Cadre Today to Win Tomorrows War

DTIC Science & Technology

2016-04-28

sustainable and flexible framework that manages and develops a cyberspace cadre, today and into the future. This professional paper examines USAF and DoD...future conflicts, USAF leadership must develop a sustainable and flexible framework that manages and develops cyberspace cadre...international security and stability. CYBERSPACE FORCE MANAGEMENT ACCESSIONS RETENTION INSTITUTIONAL STRUCTURE FORCE DEVELOPMENT EDUCATION TRAINING

JANNAF "Test and Evaluation Guidelines for Liquid Rocket Engines": Status and Application

NASA Technical Reports Server (NTRS)

Parkinson, Douglas; VanLerberghe, Wayne M.; Rahman, Shamim A.

2017-01-01

For many decades, the U.S. rocket propulsion industrial base has performed remarkably in developing complex liquid rocket engines that can propel critical payloads into service for the nation, as well as transport people and hardware for missions that open the frontiers of space exploration for humanity. This has been possible only at considerable expense given the lack of detailed guidance that captures the essence of successful practices and knowledge accumulated over five decades of liquid rocket engine development. In an effort to provide benchmarks and guidance for the next generation of rocket engineers, the Joint Army Navy NASA Air Force (JANNAF) Interagency Propulsion Committee published a liquid rocket engine (LRE) test and evaluation (T&E) guideline document in 2012 focusing on the development challenges and test verification considerations for liquid rocket engine systems. This document has been well received and applied by many current LRE developers as a benchmark and guidance tool, both for government-driven applications as well as for fully commercial ventures. The USAF Space and Missile Systems Center (SMC) has taken an additional near-term step and is directing activity to adapt and augment the content from the JANNAF LRE T&E guideline into a standard for potential application to future USAF requests for proposals for LRE development initiatives and launch vehicles for national security missions. A draft of this standard was already sent out for review and comment, and is intended to be formally approved and released towards the end of 2017. The acceptance and use of the LRE T&E guideline is possible through broad government and industry participation in the JANNAF liquid propulsion committee and associated panels. The sponsoring JANNAF community is expanding upon this initial baseline version and delving into further critical development aspects of liquid rocket propulsion testing at the integrated stage level as well as engine component level, in order to advance the state of the practice. The full participation of the entire U.S. rocket propulsion industrial base is invited and expected at this opportune moment in the continuing advancement of spaceflight technology.

A Heat Transfer Investigation of Liquid and Two-Phase Methane

NASA Technical Reports Server (NTRS)

VanNoord, Jonathan

2010-01-01

A heat transfer investigation was conducted for liquid and two-phase methane. The tests were conducted at the NASA Glenn Research Center Heated Tube Facility (HTF) using resistively heated tube sections to simulate conditions encountered in regeneratively cooled rocket engines. This testing is part of NASA s Propulsion and Cryogenics Advanced Development (PCAD) project. Nontoxic propellants, such as liquid oxygen/liquid methane (LO2/LCH4), offer potential benefits in both performance and safety over equivalently sized hypergolic propulsion systems in spacecraft applications. Regeneratively cooled thrust chambers are one solution for high performance, robust LO2/LCH4 engines, but cooling data on methane is limited. Several test runs were conducted using three different diameter Inconel 600 tubes, with nominal inner diameters of 0.0225-, 0.054-, and 0.075-in. The mass flow rate was varied from 0.005 to 0.07 lbm/sec. As the current focus of the PCAD project is on pressure fed engines for LO2/LCH4, the average test section outlet pressures were targeted to be 200 psia or 500 psia. The heat flux was incrementally increased for each test condition while the test section wall temperatures were monitored. A maximum average heat flux of 6.2 Btu/in.2 sec was achieved and, at times, the temperatures of the test sections reached in excess of 1800 R. The primary objective of the tests was to produce heat transfer correlations for methane in the liquid and two-phase regime. For two-phase flow testing, the critical heat flux values were determined where the fluid transitions from nucleate boiling to film boiling. A secondary goal of the testing was to measure system pressure drops in the two-phase regime.

Combustion Diagnostics and Flow Visualization of Hypergolic Combustion and Gelled Mixing Behavior

DTIC Science & Technology

1997-12-19

difference. Also, Exciplex Flourescence imaging has been implented to visualize diffusion layers which form at the contact interface of mixing...have been implemented and developed as a result of this effort. Among these techniques the most noteworthy involves a unique application of Exciplex ...fluorescence for visualization of diffusion layers formed between mixing liquids. Time resolved images of Exciplex fluorescence have been obtained

Chemical Kinetics Interpretation of Hypergolicity of Ionic Liquid-Based Systems

DTIC Science & Technology

2009-04-01

acid (WFNA) mixtures 6 4. Thermochemistry of imidazoles, triazoles and tetrazoles 8 5. Thermochemistry of compounds formed...reactivity of gaseous mixtures formed above ionic liquids (ILs) when mixed with white fuming nitric acid (WFNA). After a general introduction on the...replacement for NTO is also of interest but probably less crucial. For instance, NTO could be replaced by nitric acid (or by any other suitable

Design and Development of Functionally Operative and Visually Appealing Remote Firing Room Displays

NASA Technical Reports Server (NTRS)

Quaranto, Kristy

2014-01-01

This internship provided an opportunity for an intern to work with NASA's Ground Support Equipment (GSE) for the Spaceport Command and Control System (SCCS) at Kennedy Space Center as a remote display developer, under NASA mentor Kurt Leucht. The main focus was on creating remote displays for the hypergolic and high pressure helium subsystem team to help control the filling of the respective tanks. As a remote display developer for the GSE hypergolic and high pressure helium subsystem team the intern was responsible for creating and testing graphical remote displays to be used in the Launch Control Center (LCC) on the Firing Room's computer monitors. To become more familiar with the subsystem, the individual attended multiple project meetings and acquired their specific requirements regarding what needed to be included in the remote displays. After receiving the requirements, the next step was to create a display that had both visual appeal and logical order using the Display Editor, on the Virtual Machine (VM). In doing so, all Compact Unique Identifiers (CUI), which are associated with specific components within the subsystem, will need to be included in each respective display for the system to run properly. Then, once the display was created it needed to be tested to ensure that the display runs as intended by using the Test Driver, also found on the VM. This Test Driver is a specific application that checks to make sure all the CUIs in the display are running properly and returning the correct form of information. After creating and locally testing the display it will need to go through further testing and evaluation before deemed suitable for actual use. By the end of the semester long experience at NASA's Kennedy Space Center, the individual should have gained great knowledge and experience in various areas of display development and testing. They were able to demonstrate this new knowledge obtained by creating multiple successful remote displays that will one day be used by the hypergolic and high pressure helium subsystem team in one of the LCC's firing rooms to fill the new Orion spacecraft.

1958 NASA/USAF Space Probes (ABLE-1). Volume 3; Vehicles, Trajectories, and Flight Histories

NASA Technical Reports Server (NTRS)

1959-01-01

The three NASA/USAF lunar probes of August 17, October 13, and November 8, 1958 are described. Details of the program, the vehicles, the payloads, the firings, the tracking, and the results are presented. Principal result was the first experimental verification of a confined radiation zone of the type postulated by Van Allen and others.

Will Empowerment of USAF Program Managers Mitigate the Acquisitions Crisis

DTIC Science & Technology

2016-06-10

FAR Federal Acquisition Regulations GAO Government Accountability Office MDAP Major Defense Acquisition Program USAF United States Air Force ix...actually run the project. The Government Accountability Office (GAO),2 along with many other organizations, including Congress in their 2016 National...1 Government Accountability Office (GAO), GAO-06-110, Best Practices: Better Support of Weapons Systems Program Managers Needed to

Clinging to the Past: The Air Force’s War on Dual-Career Families

DTIC Science & Technology

2014-06-01

combines existing research on stress and work-family conflict with new primary research on current USAF dual-career families in the form of a case...incompatibilities between the Air Force family schema (conceptions of, and practices relating to, USAF families). The study combines existing research on stress ... Stress Pathways ..................................................... 74 Figure 5, Civilian Dual-Career Stress Pathways

Tropical Cyclone Report, 1986.

DTIC Science & Technology

1986-01-01

Gunzelman, USN CAPT Robert F. Crosby, USAF LT Harry S. Gatanis, USN *AG2 Kristopher W. Buttermore, USN TSGT Marguritta H. Smith, USAF *AG2 Kevin L. Cobb...dollars~ wuyur~v to a ’ U~se- rx nif, or est ,A te city. of’ ~ was seotrong nn5xa rttengsiv Iaag dito, n n.. N wAer ~z lins fr prted names. iedn eatthan

Current Barriers to Successful Implementation of FIST Principles

DTIC Science & Technology

2013-07-01

risks will surface during development that could not have been predicted. Managing a thin budget with no schedule slack for these unknown-unknowns is...Fleischer » Keywords: Fast, Inexpensive, Simple, Tiny (FIST); Program Management ; Heuristics; Innovation; Oversight Current Barriers to Successful...Implementation of FIST Principles Capt Brandon Keller, USAF, and Lt Col J. Robert Wirthlin, USAF The Fast, Inexpensive, Simple, and Tiny (FIST

Time Critical Conventional Strike from Strategic Standoff

DTIC Science & Technology

2009-03-01

Competitor with Emerging Counter-Space Capability has Destroyed U.S. Leo Satellite...destroyed a U.S. Low Earth Orbit ( LEO ) satellite. The U.S. desires to prevent future damage to other satellites in the constellation, but with...Precision from ISR Assets January 18 – 19 2007 Col Paul Gydesen USAF USAF ICBM, Ballistic Missile – Prompt Global Strike Dr. Barry Hannah Navy

32 CFR 842.121 - Referring a claim to the US Attorney.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 6 2011-07-01 2011-07-01 false Referring a claim to the US Attorney. 842.121... to the US Attorney. Only HQ USAF/JACC authorizes referral of a claim to the US Attorney. The base SJA...-case basis, HQ USAF/JACC will authorize referral of a case to the US Attorney by telephone. ...

Establishing and Maintaining Trust for an Airborne Network. Search and Rescue Enterprise: Security Assessment Report

DTIC Science & Technology

2014-12-01

Area Code) (937) 528-8142 Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std. Z39-18 1 MITCHELL, LOLITA V CIV USAF AFMC AFRL/RYOX To...MITCHELL, LOLITA V CIV USAF AFMC AFRL/RYOX Subject: FW: Final Report Change - Search and Rescue Security Assessment From: J M Schlesselman [mailto:joe

Upper Stage Engine Composite Nozzle Extensions

NASA Technical Reports Server (NTRS)

Valentine, Peter G.; Allen, Lee R.; Gradl, Paul R.; Greene, Sandra E.; Sullivan, Brian J.; Weller, Leslie J.; Koenig, John R.; Cuneo, Jacques C.; Thompson, James; Brown, Aaron;

RS-34 (Peacekeeper Post Boost Propulsion System) Orbital Debris Application Concept Study

NASA Technical Reports Server (NTRS)

Esther, Elizabeth A.; Burnside, Christopher G.

2013-01-01

The Advanced Concepts Office (ACO) at the NASA Marshall Space Flight Center (MSFC) lead a study to evaluate the Rocketdyne produced RS-34 propulsion system as it applies to an orbital debris removal design reference mission. The existing RS-34 propulsion system is a remaining asset from the de-commissioned United States Air Force Peacekeeper ICBM program; specifically the pressure-fed storable bi-propellant Stage IV Post Boost Propulsion System. MSFC gained experience with the RS-34 propulsion system on the successful Ares I-X flight test program flown in the Ares I-X Roll control system (RoCS). The heritage hardware proved extremely robust and reliable and sparked interest for further utilization on other potential in-space applications. Subsequently, MSFC is working closely with the USAF to obtain all the remaining RS-34 stages for re-use opportunities. Prior to pursuit of securing the hardware, MSFC commissioned the Advanced Concepts Office to understand the capability and potential applications for the RS-34 Phoenix stage as it benefits NASA, DoD, and commercial industry. Originally designed, the RS-34 Phoenix provided in-space six-degrees-of freedom operational maneuvering to deploy multiple payloads at various orbital locations. The RS-34 Concept Study, preceded by a utilization study to understand how the unique capabilities of the RS-34 Phoenix and its application to six candidate missions, sought to further understand application for an orbital debris design reference mission as the orbital debris removal mission was found to closely mimic the heritage RS-34 mission. The RS-34 Orbital Debris Application Concept Study sought to identify multiple configurations varying the degree of modification to trade for dry mass optimization and propellant load for overall capability and evaluation of several candidate missions. The results of the RS-34 Phoenix Utilization Study show that the system is technically sufficient to successfully support all of the missions analyzed. The results and benefits of the RS-34 Orbital Debris Application Concept Study are presented in this paper.

Report of Evaluation of Decompression Sickness, Beale AFB, 10-14 Aug 2009

DTIC Science & Technology

2009-09-01

MICHAELSON, Col, USAF, MC, SFS Chief, Hyperbaric Medicine Branch //SIGNED// JAMES W. WEISSMANN, Col, USAF, BSC Chief, Aerospace Medicine...Robert S Michaelson (Chief of Hyperbaric Medicine at USAFSAM), Dr. Andy Pilmanis (Consultant), and Dr. Tom Morgan (711 HPW/HPS). BACKGROUND The...without consent of originator’s office. MP = Mission Pilot HBOT = Hyperbaric Oxygen Treatment CNS = Central Nervous System HA = headache BAFB = Beale

Air Force Flight Screening: Evolutionary Changes, 1917-2003

DTIC Science & Technology

2004-12-01

US), FFA (Switzerland), Siai Marchetti (Italy), SAAB (Sweden), Slingsby (United Kingdom), Glassair (US), Piper (US), American General (US), and...Jumper, USAF/CC, [Academy Flight Screening program], 10 Apr 03, 3) BBP , 557 FTS/CC, “USAF 66 As the...Academy Flight Screening (AFS) Program,” 4 Feb 03, 4) BBP , 557 FTS/CC, “AFS Funding,” 22 Jan 03, 5) Position Paper, 557 FTS/CC

High Accuracy Attitude Control of a Spacecraft Using Feedback Linearization

DTIC Science & Technology

1992-05-01

High Accuracy Attitude Control of a Spacecraft Using Feedback Linearization A Thesis Presented by Louis Joseph PoehIman, Captain, USAF B.S., U.S. Air...High Accuracy Attitude Control of a Spacecraft Using Feedback Linearization by Louis Joseph Poehlman, Captain, USAF Submitted to the Department of...31 2-4 Attitude Determination and Control System Architecture ................. 33 3-1 Exact Linearization Using Nonlinear Feedback

Multi-Objective Optimization for Speed and Stability of a Sony AIBO Gait

DTIC Science & Technology

2007-09-01

MULTI-OBJECTIVE OPTIMIZATION FOR SPEED AND STABILITY OF A SONY AIBO GAIT THESIS Christopher A. Patterson, Second Lieutenant, USAF AFIT/GCS...07-17 MULTI-OBJECTIVE OPTIMIZATION FOR SPEED AND STABILITY OF A SONY AIBO GAIT THESIS Presented to the Faculty Department of...MULTI-OBJECTIVE OPTIMIZATION FOR SPEED AND STABILITY OF A SONY AIBO GAIT Christopher A. Patterson, BS Second Lieutenant, USAF

Project CHECO Southeast Asia Report. USAF Control of Airstrikes in Support of Indigenous Lao Ground Forces

DTIC Science & Technology

1972-07-19

a low pass over the "airstrip" to clear the area of vehicles, children , and animals, and then return and land before the locals 287/ had a chance...II I • • • - SECit!T NO PORN - validating authority not given to other USAF FACs in Laos. The X-Ray per- sonnel were selected by local Lao

United States Air Force F-35A Operational Basing Environmental Impact Statement. Appendix E: Comments

DTIC Science & Technology

2013-09-01

Germanos, Nicholas M Civ USAF HQ ACC/A7NS From: Sent: To: Subject: Dear Mr. Germanos, Ginger Hobbs Monday, July 15, 2013 9:45PM Germanos...considerat ion of all t he facts. Thank you, Ginger Hobbs 1 E-757 Germanos, Nicholas M Civ USAF HQ ACC/A7NS From: Sent: To: Subject: Kara Schwartz

BH3-Amine and B(CH3)3-Amine Adducts as Additives for Liquid/Gel Hypergols and Solid Hybrid Rocket Motor Fuels: Property and Performance Predictions

DTIC Science & Technology

2013-12-01

and Thermolysis of Lithium, Magnesium Calcium and Strontium Tetraborate Complex Compounds With Triethylenediamine-Crystal Structure of 2BH3•C6H12N2...of Closed-Shell Atoms and Hydrides of the 1st-Row Elements. Journal of Chemical Physics 1988, 89 , 2193-2218. Petersson, G. A.; Tensfeldt, T

Atmospheric Dispersion of Hypergolic Liquid Rocket Fuels. Volume 2

DTIC Science & Technology

1984-11-01

time tI required for the initial concentration of nitr- gen dioxide [NO 2]0 to decay to I ppm yields the expression [NO2 ]O - I ppm t - ( 2 (3-16)k3 [H2[0...19S1 ACCIDENT TINE IS 1015 EST 12 NOV 1931 TINE OF EXECUTION IS 2140 EST 9 PFE 1984 PEAK CLOUD CLOUD fANCE IEANING CONCEN- ARRIVAL 01PAITOOE FROM SITE

Evaluating Ionic Liquids as Hypergolic Fuels: Exploring Reactivity from Molecular Structure

DTIC Science & Technology

2014-01-27

obtained , some caution is required since 14 of these exhibited no observable melting or glass transitions which might be a result of the hygroscopic...Fuels 01-27-14 23 short ignition delays and lower viscosities ( alkene ) or higher densities (N-N) should be considered further. The development of...Experimental Materials and Methods . 1-methylimidazole, 3-picoline, pyridine, 1-chlorobutane, 1- bromobutane, allyl chloride, and 1-chloro-2

Hypergolic fuel detection using individual single walled carbon nanotube networks

NASA Astrophysics Data System (ADS)

Desai, S. C.; Willitsford, A. H.; Sumanasekera, G. U.; Yu, M.; Tian, W. Q.; Jayanthi, C. S.; Wu, S. Y.

2010-06-01

Accurate and reliable detection of hypergolic fuels such as hydrazine (N2H4) and its derivatives is vital to missile defense, aviation, homeland security, and the chemical industry. More importantly these sensors need to be capable of operation at low temperatures (below room temperature) as most of the widely used chemical sensors operate at high temperatures (above 300 °C). In this research a simple and highly sensitive single walled carbon nanotube (SWNT) network sensor was developed for real time monitoring of hydrazine leaks to concentrations at parts per million levels. Upon exposure to hydrazine vapor, the resistance of the air exposed nanotubes (p-type) is observed to increase rapidly while that of the vacuum-degassed nanotubes (n-type) is observed to decrease. It was found that the resistance of the sample can be recovered through vacuum pumping and exposure to ultraviolet light. The experimental results support the electrochemical charge transfer mechanism between the oxygen redox couple of the ambient and the Fermi level of the SWNT. Theoretical results of the hydrazine-SWNT interaction are compared with the experimental observations. It was found that a monolayer of water molecules on the SWNT is necessary to induce strong interactions between hydrazine and the SWNT by way of introducing new occupied states near the bottom of the conduction band of the SWNT.

A decade of U.S. Air Force bat strikes

USGS Publications Warehouse

Peurach, Suzanne C.; Dove, Carla J.; Stepko, Laura

2009-01-01

From 1997 through 2007, 821 bat strikes were reported to the U.S. Air Force (USAF) Safety Center by aircraft personnel or ground crew and sent to the National Museum of Natural History, Smithsonian Institution, for identification. Many samples were identified by macroscopic and or microscopic comparisons with bat specimens housed in the museum and augmented during the last 2 years by DNA analysis. Bat remains from USAF strikes during this period were received at the museum from 40 states in the United States and from 20 countries. We confirmed that 46% of the strikes were caused by bats, but we did not identify them further; we identified 5% only to the family or genus level, and 49% to the species level. Fifty-five of the 101 bat-strike samples submitted for DNA analysis have been identified to the species level. Twenty-five bat species have been recorded striking USAF planes worldwide. The Brazilian free-tailed bat (Tadarida brasiliensis; n = 173) is the species most commonly identified in USAF strike impacts, followed by the red bat (Lasiurus borealis; n = 83). Bat strikes peak during the spring and fall, with >57% occurring from August through October; 82% of the reports that included time of strike were recorded between 2100 and 0900 hours. More than 12% of the bat strikes were reported at >300 m above ground level (AGL). Although <1% of the bat-strike reports indicated damage to USAF aircraft, cumulative damage for 1997 through 2007 totaled >$825,000 and >50% of this sum was attributable to 5 bat-strike incidents. Only 5 bats from the 10 most damaging bat strikes were identified to the species level, either because we did not receive remains with the reports or the sample was insufficient for identification.

Design and Testing of Non-Toxic RCS Thrusters for Second Generation Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Calvignac, Jacky; Tramel, Terri

2003-01-01

The current NASA Space Shuttle auxiliary propulsion system utilizes nitrogen tetroxide (NTO) and monomethylhydrazine (MMH), hypergolic propellants. This use of these propellants has resulted in high levels of maintenance and precautions that contribute to costly launch operations. By employing alternate propellant combinations, those less toxic to humans, the hazards and time required between missions can be significantly reduced. Use of alternate propellants can thereby increase the efficiency and lower the cost in launch operations. In support of NASA's Space Launch Initiative (SLI), TRW proposed a three-phase project structured to significantly increase the technology readiness of a high-performance reaction control subsystem (RCS) thruster using non-toxic propellant for an operationally efficient and reusable auxiliary propulsion system (APS). The project enables the development of an integrated primary/vernier thruster capable of providing dual-thrust levels of both 1000-lbf class thrust and 25-lbf thrust. The intent of the project is to reduce the risk associated with the development of an improved RCS flight design that meets the primary NASA objectives of improved safety and reliability while reducing systems operations and maintenance costs. TRW proposed two non-toxic auxiliary propulsion engine designs, one using liquid oxygen and liquid hydrogen and the other using liquid oxygen and liquid ethanol, as candidates to meet the goals of reliability and affordability at the RCS level. Both of these propellant combinations offer the advantage of a safe environment for maintenance, while at the same time providing adequate to excellent performance for a conventional liquid propulsion systems. The key enabling technology incorporated in both TRW thrusters is the coaxial liquid on liquid pintle injector. This paper will concentrate on only the design and testing of one of the thrusters, the liquid oxygen (LOX) and liquid hydrogen (LH2) thruster. The LOX/LH2 thruster design includes a LOX-centered pintle injector, consisting of two rows of slots that create a radial spoke spray pattern in the combustion chamber. The main fuel injector creates a continuous sheet of LH2 originating upstream of the LOX pintle injector. The two propellants impinge at the pintle slots, where the resulting momentum ratio and spray pattern determines the combustion efficiency and thermal effects on the hardware. Another enabling technology used in the design of this thruster is fuel film cooling through a duct, lining the inner wall of the combustion chamber barrel section. The duct is also acts as a secondary fuel injection point. The variation in the amount of LH2 used for the duct allows for adjustments in the cooling capacity for the thruster. The Non-Toxic LOX-LH2 RCS Workhorse Thruster was tested at the NASA Marshall Space Flight Center's Test Stand 500. Hot-fire tests were conducted between March 08, 2002 and April 05, 2002. All testing during the program base period were performed at sea-level conditions. During the test program, 7 configurations were tested, including 2 combustion chambers, 3 LOX injector pintle tips, and 4 LH2 injector stroke settings. The operating conditions that were surveyed varied thrust levels, mixture ratio and LH2 duct cooling flow. The copper heat sink chamber was used for 16 burns, each burn lasting from 0.4 to 10 seconds, totaling 51.4 seconds, followed by Haynes chamber testing ranging from 0.9 to 120 seconds, totaling 300.9 seconds. The total accumulated burn time for the test program is 352.3 seconds. C* efficiency was calculated and found to be within expectable limits for most operating conditions. The temperature on the Haynes combustion chamber remained below established material limits, with the exception of one localized hot spot. The test results demonstrate that both the coaxial liquid-on-liquid pintle injector design and fuel duct concepts are viable for the intended application. The thruster head-e design maintained cryogenic injection temperatures while firing, which validates the concept for minimal heat soak back. By injecting fuel into the duct, the throat temperatures were manageable, yet the split of fuel through the cooling duct does not compromise the overall combustion efficiency, which indicates that, provided proper design refinement, such a concept can be applied to a high-performance version of the thruster. These hot fire tests demonstrate the robustness of the duct design concept and good capability to withstand off-nominal operating conditions without adversely impacting the thermal response of the engine, a key design feature for a cryogenic thruster.

GSOSTATS Database: USAF Synchronous Satellite Catalog Data Conversion Software. User's Guide and Software Maintenance Manual, Version 2.1

NASA Technical Reports Server (NTRS)

Mallasch, Paul G.; Babic, Slavoljub

1994-01-01

The United States Air Force (USAF) provides NASA Lewis Research Center with monthly reports containing the Synchronous Satellite Catalog and the associated Two Line Mean Element Sets. The USAF Synchronous Satellite Catalog supplies satellite orbital parameters collected by an automated monitoring system and provided to Lewis Research Center as text files on magnetic tape. Software was developed to facilitate automated formatting, data normalization, cross-referencing, and error correction of Synchronous Satellite Catalog files before loading into the NASA Geosynchronous Satellite Orbital Statistics Database System (GSOSTATS). This document contains the User's Guide and Software Maintenance Manual with information necessary for installation, initialization, start-up, operation, error recovery, and termination of the software application. It also contains implementation details, modification aids, and software source code adaptations for use in future revisions.

USAF shale oil program status

NASA Technical Reports Server (NTRS)

Delaney, C. L.

1984-01-01

The test and evaluation program on shale derived fuel being conducted by the Air Force is intended to accomplish the minimum amount of testing necessary to assure both the safe use of shale oil derived turbine fuels in operational USAF aircraft and its compatibility with USAF handling systems. This program, which was designed to take advantage of existing R&D testing programs, began in 1981. However, due to a problem in acquiring the necessary fuel, the testing program was suspended until July 1983 when an additional sample of shale derived fuel was received. Tentatively, the Air Force is planning to make three relatively minor revisions to the procurement specifications requirements for the production shale derived fuel. These are: (1) Aromatic Contest (min) - 9% (by volume); (2) Nitrogen (max - 20 ppm by weight); and (3) Antioxidants - 9.1 g/100 gal (U.S.)

USAF Bioenvironmental Noise Data Handbook. Volume 155. CH-3 in-flight crew noise

NASA Astrophysics Data System (ADS)

Hille, H. K.

1982-09-01

The CH-3 is a USAF tactical combat transport helicopter. This report provides measured data defining the bioacoustic environments at flight crew/passenger locations inside this helicopter during normal flight operations. Data are reported for nine locations in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C weighted and A weighted sound levels, preferred speech interference level, perceived noise levels and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors. Refer to Volume 1 of this handbook, USAF Bioenvironmental Noise Data handbook, Vol. 1: Organization, Content and Application, AMRL-TR-75-50(1) 1975, for discussion of the objective and design of the handbook, the types of data presented, measurement procedures, instrumentation, data processing, definitions of quantities, symbols, equations, applications, limitations, etc.

USAF Environmental Noise Data Handbook. Volume 150: C-140 in-flight crew noise

NASA Astrophysics Data System (ADS)

Hille, H. K.

1982-09-01

The C-140 is a USAF transport aircraft used for operational support. This report provides measured data defining the bioacoustic environments at flight crew/passenger locations inside this aircraft during normal flight operations. Date are reported for seven locations in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors. Refer to Volume 1 of this handbook, USAF Bioenvironmental Noise Data Handbook, Vol. 1: Organization, Content and Application, AMRL-TR-75-50(1) 1975, for discussion of the objective and design of the handbook, the types of data presented, measurement procedures, instrumentation, data processing, definitions of quantities, symbols, equations, applications, limitations, etc.

Behavioral Profiling of Scada Network Traffic Using Machine Learning Algorithms

DTIC Science & Technology

2014-03-27

BEHAVIORAL PROFILING OF SCADA NETWORK TRAFFIC USING MACHINE LEARNING ALGORITHMS THESIS Jessica R. Werling, Captain, USAF AFIT-ENG-14-M-81 DEPARTMENT...subject to copyright protection in the United States. AFIT-ENG-14-M-81 BEHAVIORAL PROFILING OF SCADA NETWORK TRAFFIC USING MACHINE LEARNING ...AFIT-ENG-14-M-81 BEHAVIORAL PROFILING OF SCADA NETWORK TRAFFIC USING MACHINE LEARNING ALGORITHMS Jessica R. Werling, B.S.C.S. Captain, USAF Approved

Environmental Assessment: Hurlburt Field Soundside Boathouse and Restroom Facility Construction

DTIC Science & Technology

2007-08-01

seq., and Air Force Instruction (AFI) 32-7061, The Environmental Impact Analysis Process, the USAF concludes that the Proposed Action will have no...U.S.C.) §4321, et seq., and Air Force Instruction (AFI) 32-7061, The Environmental Impact Analysis Process, the USAF concludes that the Proposed...et seq. • AFI 32-7061, The Environmental Impact Analysis Process These regulations require federal agencies to analyze the potential environmental

Evaluation of Inventory Reduction Strategies: Balad Air Base Case Study

DTIC Science & Technology

2012-03-01

produced by conducting individual simulations using a unique random seed generated by the default Anylogic © random number generator. The...develops an agent-based simulation model of the sustainment supply chain supporting Balad AB during its closure using the software AnyLogic ®. The...research. The goal of USAF Stockage Policy is to maximize customer support while minimizing inventory costs (DAF, 2011:1). USAF stocking decisions

Fall of the Fighter Generals: The Future of USAF Leadership

DTIC Science & Technology

2001-06-01

World War II, Colonel S . F. Giffen argued that one of the great lessons to be...Generals: The Future of USAF Leadership Contract Number Grant Number Program Element Number Author( s ) Danskine, Wm. Bruce Project Number Task...results of World War II led to the separation of part of the Army to form an independent Air Force. Or the transition can be smooth, such as when the

The USAF Academy Honor System.

DTIC Science & Technology

1988-04-01

Dec 1986, p. H- 8 . 3. Hosmer, Clark, Colonel (Retired), USAF. Personal Interview, 29 September 1987. 4 . Maus, Steven A. Cadet Wing Honor Education...the basic procedures of the Honor System. A. Strongly Agree 8 % B. Agree 53% C. Neutral 21% D. Disagree 14% E. Strongly Disagree 4 % 28. It is possible...DISTRIBUTION/AVAILABILITY OF REPORT STATEMENT "A" 2b. DECLASSIFICATION/DOWNGRADING SCHEDULE Approved for public release; Distribution is unlimited. 4

Supplier Development: A Long-Term Supportability Option For USAF Engines

DTIC Science & Technology

2012-02-01

Supply Chain Management Practices..................8 AF and DoD Regulations "Limitation or Hoax" Can USAF Develop Suppliers...integrated supply chain management (SCM) process providing engines and parts, aiding in the ability of the depots to meet the warfighter‟s needs. The... supply chain has struggled in the past to support the warfighter with enough engines to accomplish the mission. The engine supply chain management

Case Report: Rhabdomyolysis in Service Member Following SERE Physical Training

DTIC Science & Technology

2017-09-19

Member following SERE physical training. Sb. GRANT NUMBER Sc. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER Capt Matthew A Pombo Se. TASK...NOTES 14. ABSTRACT Case Report: Rhabdomyolysis in Service Member following SERE physical training. Authors: Matthew A. Pombo, DO (Capt, USAF...in Service Member following SERE physical training. Authors: Matthew A. Pombo, DO (Capt, USAF); Dwaipayan Chakraborti, MD (MAJ, USA); Joseph Marcus

Combat Medical Modernization: Posturing Low Supply And High Demand Assets To Meet Emerging And Future Capability Requirements

DTIC Science & Technology

2015-07-01

OFFICE OF THE AIR FORCE SURGEON GENERAL FELLOWSHIP PAPER COMBAT MEDICAL MODERNIZATION: POSTURING LOW SUPPLY AND HIGH DEMAND ASSETS TO...Maj, USAF, MSC Scott A. Baker, Capt, USAF, MSC A Research Report Submitted to HQ AF/SG35X In Partial Fulfillment of Medical Plans Fellowship...i TABLE OF FIGURES 3 I. INTRODUCTION 5 II. CURRENT MEDICAL EN-ROUTE CARE CAPABILITY

Application of a Micro Computer-Based Management Information System to Improve the USAF Service Reporting Process

DTIC Science & Technology

1990-09-01

I. Introduction .......................................... 1 General Issue .................................. 1 Specific Research Problem...viii APPLICATION OF A MICRO COMPUTER-BASED MANAGEMENT INFORMATION SYSTEM TO IMPROVE THE USAF SERVICE REPORTING PROCESS I. Introduction General Issue...continued Transfer MIP Responsibility ,KNT WETSS0GEFORM UNCLASSIFIED 904 JAUG 19: iRR iRRl UUUUI HOWE271652_ D- FF:MCH INFO: NONE E. iUCH DATA DEF: NONE F

Assessment of USAFs Hiring Potential of Civilian Scientists and Engineers of the Millennial Generation

DTIC Science & Technology

2016-02-12

AIR WAR COLLEGE AIR UNIVERSITY ASSESSMENT OF USAF’S HIRING POTENTIAL OF CIVILIAN SCIENTISTS AND ENGINEERS OF THE MILLENNIAL GENERATION...government organizations. iv Abstract The Millennial Generation (individuals born 1981-2000) is entering the workforce in large numbers and...of Millennials and what they view as important in their work and social lives revealed policy approaches that could ensure the USAF maximizes it

CAD/CAM Preparation Design Effects on Endodontically Treated and Restored Molars

DTIC Science & Technology

2016-05-24

ii APPROVED: Col Drew W . Fallis Dean, Air Force Postgraduate Dental School iii Acknowledgements Special thanks to Col Howard Roberts, Maj...excerpts, is with the permission of the copyright owner. Signature AARON T. DANCB. MAJ. USAF, DC v Printed Name USAF Postgraduate Dental School Keesler...internal amalgam-dentin 3 interface. Preparations were accomplished by one operator using a high speed electric dental hand piece (EA-SlLT, Adee

Multidimensional Aptitude Battery-Second Edition Intelligence Testing of Remotely Piloted Aircraft Training Candidates Compared with Manned Airframe Training Candidates

DTIC Science & Technology

2015-03-01

assessing the general intelligence and neuropsychological aptitudes of USAF RPA pilot training candidates. Chappelle et al. obtained comprehensive...computer-based intelligence testing (Multidimensional Aptitude Battery-Second Edition [MAB-II]) and neuropsychological screening (MicroCog) on USAF MQ-1... schizophrenia , attention deficit hyperactivity disorder, and autism spectrum disorders) and not on very high functioning populations such as aviators

Military Air Cargo Containerization.

DTIC Science & Technology

1996-05-01

MILITARY AIR CARGO CONTAINERIZATION GRADUATE RESEARCH PAPER Joseph W. Mancy, Major, USAF AFIT/ GMO /LAL/96J-4 : ."•" ’* ■- ’ DEPARTMENT OF...Approved to public release; Distribution UnHmlted ? DTIC QUALITY INSPECTED 1 AFIT/ GMO /LAL/96J-4 MILITARY AIR CARGO CONTAINERIZATION GRADUATE RESEARCH...PAPER Joseph W. Mancy, Major, USAF AFIT/ GMO /LAL/96J-4 19960617 134 Approved for public release; distribution unlimited The views expressed in this

USAF Hearing Conservation Program, DOEHRS-HC Data Repository Annual Report: CY15

DTIC Science & Technology

2017-05-31

AFRL-SA-WP-SR-2017-0014 USAF Hearing Conservation Program, DOEHRS-HC Data Repository Annual Report: CY15 Daniel A. Williams...Conservation Program, DOEHRS-HC Data Repository Annual Report: CY15 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR...Health Readiness System-Hearing Conservation Data Repository (DOEHRS-HC DR). Major command- and installation-level reports are available quarterly

Characterization of Construction Material Properties through Gamma Spectroscopy, X-ray Fluorescence, and Hyper-spectral Imagery for Background Correction Applications in Nuclear Detection

DTIC Science & Technology

2014-03-27

14 Mar 2014 David J. Bunker, Ph.D. (Chairman) Date ____________//signed//_________________ 14 Mar 2014 Tay W. Johannes, Ph.D...Lt Col, USAF (Member) Date ____________//signed//_________________ 12 Mar 2014 Benjamin R. Kowash, Ph.D., Maj, USAF (Member) Date AFIT-ENP...by Test Date ........................ 28 Figure 3: Comparison of background spectra from 6 October (blue) and 16 September (green

4. Credit USAF, ca. 1945. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

4. Credit USAF, ca. 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Photographic copy of photograph captioned "Hangar No. 2 Hydraulics Room." Location within Building 4402 not determined. - Edwards Air Force Base, North Base, Hangar No. 2, First & A Streets, Boron, Kern County, CA

Copper Doping of Zinc Oxide by Nuclear Transmutation

DTIC Science & Technology

2014-03-27

Copper Doping of Zinc Oxide by Nuclear Transmutation THESIS Matthew C. Recker, Captain, USAF AFIT-ENP-14-M-30 DEPARTMENT OF THE AIR FORCE AIR...NUCLEAR TRANSMUTATION THESIS Presented to the Faculty Department of Engineering Physics Graduate School of Engineering and Management Air Force...COPPER DOPING OF ZINC OXIDE BY NUCLEAR TRANSMUTATION Matthew C. Recker, BS Captain, USAF Approved: //signed// 27 February 2014 John W. McClory, PhD

Religious Accommodation for Military Members in the Twenty-First Century

DTIC Science & Technology

2012-02-01

order and discipline is speculative. He presented a scenario where a female Airman had permission to wear her hijab indoors. When she transferred to the...Lieutenant Colonel, USAF A Research Report Submitted to the Faculty In Partial Fulfillment of the Graduation Requirements Advisor: Dr. Stefan Eisen, Jr...Colonel, USAF (Retired) Maxwell Air Force Base, Alabama February 2012 DISTRIBUTION A . Approved for public release: distribution unlimited 2

Semantic Interpretation of An Artificial Neural Network

DTIC Science & Technology

1995-12-01

ARTIFICIAL NEURAL NETWORK .7,’ THESIS Stanley Dale Kinderknecht Captain, USAF 770 DEAT7ET77,’H IR O C 7... ARTIFICIAL NEURAL NETWORK THESIS Stanley Dale Kinderknecht Captain, USAF AFIT/GCS/ENG/95D-07 Approved for public release; distribution unlimited The views...Government. AFIT/GCS/ENG/95D-07 SEMANTIC INTERPRETATION OF AN ARTIFICIAL NEURAL NETWORK THESIS Presented to the Faculty of the School of Engineering of

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

Moderating Effects of Perceived Organizational Support on the Relationship between Job Satisfaction and Turnover Intentions for Recently Retrained USAF Enlisted Members

DTIC Science & Technology

2006-03-01

career in the service. The turnover body of knowledge was furthered because POS was eliminated as a moderator in the relationship of job satisfaction and...MODERATING EFFECTS OF PERCEIVED ORGANIZATIONAL SUPPORT ON THE RELATIONSHIP BETWEEN JOB SATISFACTION ...EFFECTS OF PERCEIVED ORGANIZATIONAL SUPPORT ON THE RELATIONSHIP BETWEEN JOB SATISFACTION AND TURNOVER INTENTIONS FOR RECENTLY RETRAINED USAF ENLISTED

Senior Leader Perspective on the Air Force Nuclear Enterprise: Todays Issues and the Future

DTIC Science & Technology

2016-09-15

SENIOR LEADER PERSPECTIVE ON THE AIR FORCE NUCLEAR ENTERPRISE: TODAY’S ISSUES AND THE FUTURE GRADUATE RESEARCH PAPER Matthew D. Boone...States. AFIT-ENS-MS-16-S-028 SENIOR LEADER PERSPECTIVE ON THE AIR FORCE NUCLEAR ENTERPRISE: TODAY’S ISSUES AND THE FUTURE GRADUATE... ISSUES AND THE FUTURE Matthew D. Boone, BS, MA Major, USAF Committee Membership: Robert E. Overstreet, Lt Col, USAF, PhD

National Positioning, Navigation, and Timing Architecture Study

DTIC Science & Technology

2008-09-01

Ballooning • Trip Planning Environment • Tide / Current Measures • BLM Tract Management • Oil Spill Containment • Hazardous Waste Remediation...SMC/GPSW (Aerospace) Adde, Barbara GOVT NASA Alexander, Dexter LTC USA SMDC Alexander, Ken GOVT FAA Rep to NCO Allen, Leonard GOVT FRA...Shawn Lt Col USAF NSSO/PNT Brewer, Mike Col USAF OASD/NII Space Programs Brodsky, Beryl CTR NASA (Overlook) Broussard, Robert CTR AFSPC/A5

Security Verification of Secure MANET Routing Protocols

DTIC Science & Technology

2012-03-22

SECURITY VERIFICATION OF SECURE MANET ROUTING PROTOCOLS THESIS Matthew F. Steele, Captain, USAF AFIT/GCS/ ENG /12-03 DEPARTMENT OF THE AIR FORCE AIR...States AFIT/GCS/ ENG /12-03 SECURITY VERIFICATION OF SECURE MANET ROUTING PROTOCOLS THESIS Presented to the Faculty Department of Electrical and Computer...DISTRIBUTION UNLIMITED AFIT/GCS/ ENG /12-03 SECURITY VERIFICATION OF SECURE MANET ROUTING PROTOCOLS Matthew F. Steele, B.S.E.E. Captain, USAF

A B-52H, tail number 61-0025, arrives at NASA's Dryden Flight Research Center after landing July 30,

NASA Technical Reports Server (NTRS)

2001-01-01

NASA Dryden Flight Research Center, Edwards, California, received an 'H' model B-52 Stratofortress aircraft on July 30, 2001. The B-52H will be used as an air-launch aircraft supporting NASA's flight research and advanced technology demonstration efforts. Dryden received the B-52H from the U.S. Air Force's (USAF) 23rd Bomb Squadron, 5th Bombardment Wing (Air Combat Command), located at Minot AFB, N.D. A USAF crew flew the aircraft to Dryden. The aircraft, USAF tail number 61-0025, will be loaned initially, then later transferred from the USAF to NASA. The B-52H is scheduled to leave Dryden Aug. 2 for de-militarization and Programmed Depot Maintenance (PDM) at Tinker Air Force Base (AFB), Oklahoma. The depot-level maintenance is scheduled to last about six months and includes a thorough maintenance and inspection process. The newly arrived B-52H is slated to replace Dryden's famous B-52B '008,' in the 2003-2004 timeframe. It will take about one year for the B-52H to be ready for flight research duties. This time includes PDM, construction of the new pylon, installation of the flight research instrumentation equipment, and aircraft envelope clearance flights.

Training for the Air Force fitness assessment: the experience of postpartum women.

PubMed

Armitage, Nicole H; Severtsen, Billie M; Vandermause, Roxanne; Smart, Denise A

2014-07-01

Active duty personnel in the U.S. Air Force (USAF) are required to pass periodic fitness assessments in order to facilitate and evaluate physical readiness. Pregnant women are exempt from testing but must take the fitness test 6 months after childbirth. However, evidence from prior research indicates that in the first 6 months postpartum, women may not achieve prepregnancy fitness levels and may be more vulnerable to mental and physical health problems. It is important for health care clinicians to understand how training for the USAF fitness test after childbirth may impact health and well-being. The purpose of this study was to develop a deep understanding of the experiences of postpartum USAF women as they train for their fitness assessment. Understanding was sought through a phenomenological study by interpreting the meaning of the lived experiences of 17 active duty women at two USAF bases. Two overarching patterns emerged from this analysis: "Striving to Perform under Pressure through Profound Life Transitions of Childbirth" and "Seeking Understanding from Others." These results provide insight into the challenges postpartum women encounter while training for their fitness assessments, and they can inform practices that facilitate efforts of women in returning to optimal fitness and well-being. Reprint & Copyright © 2014 Association of Military Surgeons of the U.S.

A B-52H, on loan to NASA's Dryden Flight Research Center, makes a pass down the runway prior to land

NASA Technical Reports Server (NTRS)

2001-01-01

NASA Dryden Flight Research Center, Edwards, California, received an 'H' model B-52 Stratofortress aircraft on July 30, 2001. The B-52H will be used as an air-launch aircraft supporting NASA's flight research and advanced technology demonstration efforts. Dryden received the B-52H from the U.S. Air Force's (USAF) 23rd Bomb Squadron, 5th Bombardment Wing (Air Combat Command), located at Minot AFB, N.D. A USAF crew flew the aircraft to Dryden. The aircraft, USAF tail number 61-0025, will be loaned initially, then later transferred from the USAF to NASA. The B-52H is scheduled to leave Dryden Aug. 2 for de-militarization and Programmed Depot Maintenance (PDM) at Tinker Air Force Base (AFB), Oklahoma. The depot-level maintenance is scheduled to last about six months and includes a thorough maintenance and inspection process. The newly arrived B-52H is slated to replace Dryden's famous B-52B '008,' in the 2003-2004 timeframe. It will take about one year for the B-52H to be ready for flight research duties. This time includes PDM, construction of the new pylon, installation of the flight research instrumentation equipment, and aircraft envelope clearance flights.

An Environmental Evaluation of Acid Scrubbers; Building 628, McClellan AFB CA

DTIC Science & Technology

1975-08-01

found collection efficiencies ranging from 42 to 80% for 1 pm particles in low energy scrubbers . High energy scrubbers , venturi and wet dynamic, had...collection elliciency ctyi be obtained but not with low energy wet scrubbers . High energy wet scrubbers ( venturi , wet dynamic, wet fabric nitrations, etc...ENVIRONMENTAL EVALUATION OF ACID SCRUBBERS Building 628. McClellan AFB CA Jerry W. Jackson. Capt, USAF, BSC William £. Normington. Capt, USAF August 1975

A Case for Air Force Reorganization

DTIC Science & Technology

2013-04-01

overstaffing problem exists, sev- eral theories lend insight into why and how this overgrowth occurs. Noted German sociologist Max Weber discusses...USAF Almanac, 1980,” May 1980; “2010 USAF Almanac”; and “Air Force Strength from FY 1948–2012.” 9. Max Weber , On Charisma and Institution Building...MA: Belknap Press of Harvard University Press, 1957), 67. 22. Max Weber , The Theory of Social and Economic Organization, trans. A. M. Henderson and

Development and Employment of Fixed-Wing Gunships 1962-1972

DTIC Science & Technology

1982-01-01

Carl Berger. Mr. Eugene P. Sagstetter, Mary F. Loughlin, and Vanessa D. Allen edited, proofread, and purged the manuscript of the typographical...General Coun.el. USAF Dr. Forrest C. Pogue Lt. General Charles G. Cleveland Smithsonian Institution USAF Commander. Air University. ATC Dr. Edward L...GiUNSHIP I (AC-47) Major Interdiction Areas (Southeast Asia) A NORTH VIETNAM Bar 1 LAOS Steel Tiger THAILAND ’ * Tiger Hound *~ ~T39 VAN DEVELOPMENT OF FIXED

Pulse Coupled Neural Networks for the Segmentation of Magnetic Resonance Brain Images.

DTIC Science & Technology

1996-12-01

PULSE COUPLED NEURAL NETWORKS FOR THE SEGMENTATION OF MAGNETIC RESONANCE BRAIN IMAGES THESIS Shane Lee Abrahamson First Lieutenant, USAF AFIT/GCS/ENG...COUPLED NEURAL NETWORKS FOR THE SEGMENTATION OF MAGNETIC RESONANCE BRAIN IMAGES THESIS Shane Lee Abrahamson First Lieutenant, USAF AFIT/GCS/ENG/96D-01...research develops an automated method for segmenting Magnetic Resonance (MR) brain images based on Pulse Coupled Neural Networks (PCNN). MR brain image

Consideration of USAF (United States Air Force) Logistics Doctrine Principles in a Decision Making Framework.

DTIC Science & Technology

1987-09-01

Henry Fayu.l: planning, organizing, commanding, coordinating, and controlling (Donnelly, Gibson, and Ivancevich , 1984:88). In 2 their text, Donnelly (et...al) describe the management function as "planning, organizing, and controlling (Donnelly, Gibson, and Ivancevich , 1984:5)." 3. Logistics Management...Air Force Weapon Systems. Washington DC: HQ USAF, 1 February 1985. Donnelly, James H., James L. Gibson, John M. Ivancevich , Fundamentals of Management

Air-Sea Battle through Joint Training: Power Projection Sustainability

DTIC Science & Technology

2014-05-15

9 generate our decisive advantage.” 39 An example of cross-domain operations employed by the USN and USAF was the release of an AGM-154C Joint...and Herzegovina. While employing a USAF GBU -15 “electro-optically guided” bomb within close range of a USN AGM-84 SLAM-ER, “electronic... 39 U.S. Office of the Chairman, Joint Chiefs of Staff. Capstone Concept for Joint Operations: Joint Force 2020

Business Process Improvement Applied to Written Temporary Duty Travel Orders within the United States Air Force

DTIC Science & Technology

1993-12-01

Generally Accepted Process While neither DoD Directives nor USAF Regulations specify exact mandatory TDY order processing methods, most USAF units...functional input. Finally, TDY order processing functional experts at Hanscom, Los Angeles and McClellan AFBs provided inputs based on their experiences...current electronic auditing capabilities. 81 DTPS Initiative. This DFAS-initiated action to standardize TDY order processing throughout DoD is currently

Solar Cycle Effects on the Near-Earth Space Systems

DTIC Science & Technology

1990-08-06

foreign nationals. This technical report has been reviewed and is approved for publication. Publication of this report does not constitute Air Force...approval of the report’s findings or conclusions. It is published only for the exchange and stimulation of ideas. RAFAEL A. RIVIERE, Capt, USAF ONATHAN...M. EMHES , MAJ, USAF MOIE Project Officer MOIE Project Manager SSD/CNL AFSTC/WCO OL-AB UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAGE REPORT

Credit USAF. Original housed in the Muroc Flight Test Base, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View captioned as "7 Sept 1945, BH-5 Base Ordinance Motor Repair Shop" with gas station and gasoline pump. View looks roughly northwest - Edwards Air Force Base, North Base, Motor Repair Shop T-16, Third & C Streets, Boron, Kern County, CA

Credit USAF, 7 September 1945. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF, 7 September 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View of the mess hall, looking to the north. Sign over door reads "MFTB Muroc Flight Test Base Base Mess." - Edwards Air Force Base, North Base, Base Mess Hall T-27, Third Street, Boron, Kern County, CA

7. Credit USAF, 1945. Original housed in the Muroc Flight ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

7. Credit USAF, 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Interior view in shop wing on south side of hangar. Original caption reads "7 Sept. 1945, BH-10, Hangar No. 4 4505 Machine Shop." - Edwards Air Force Base, North Base, Hangar, End of North Base Road, Boron, Kern County, CA

PLC Hardware Discrimination using RF-DNA fingerprinting

DTIC Science & Technology

2014-06-19

PLC HARDWARE DISCRIMINATION USING RF-DNA FINGERPRINTING THESIS Bradley C. Wright, Civilian, USAF AFIT-ENG-T-14-J-12 DEPARTMENT OF THE AIR FORCE AIR...protection in the United States. AFIT-ENG-T-14-J-12 PLC HARDWARE DISCRIMINATION USING RF-DNA FINGERPRINTING THESIS Presented to the Faculty Department...DISCRIMINATION USING RF-DNA FINGERPRINTING Bradley C. Wright, B.S.E.E. Civilian, USAF Approved: /signed/ Maj Samuel J. Stone, PhD (Chairman) /signed/ Michael A

Experimental and Theoretical Basis for a Closed-Form Spectral BRDF Model

DTIC Science & Technology

2015-09-17

EXPERIMENTAL AND THEORETICAL BASIS FOR A CLOSED-FORM SPECTRAL BRDF MODEL DISSERTATION Samuel D. Butler, Major, USAF AFIT-ENP-DS-15-S-021 DEPARTMENT...SPECTRAL BRDF MODEL DISSERTATION Presented to the Faculty Graduate School of Engineering and Management Air Force Institute of Technology Air University Air...FOR A CLOSED-FORM SPECTRAL BRDF MODEL DISSERTATION Samuel D. Butler, BS, MS Major, USAF Committee Membership: Michael A. Marciniak, PhD Chairman Kevin

United States Air Force Statistical Digest, Fiscal Year 1965, Twentieth Edition

DTIC Science & Technology

1965-09-30

prOVided by the USAF under Military Assistance Program . MAP EMPLOYEES - Category of civilian personnel engaged in activities reqUired in carrying out the...92 - USAF CIVIUAN EMPLOYEES IN SALARIED AND WAGE BOARD GROUPS EMPLOYED UNDER MILITARY ASSISTANCE PROGRAM (MAP), WORLO-WIDE, AT END OF QUARTER - FY...statistical material for tary Assistance Program (MAP), and re- the digest. AFCHO will furnish a chronology lated studies and historical events. of

A Study of Benefits Resulting from the AFIT (Air Force Institute of Technology) Education with Industry Program

DTIC Science & Technology

1989-09-01

A STUDY OF BENEFITS RESULTING FROM THE AFIT EDUCATION WITH INDUSTRY PROGRAM THESIS Ed R. Hernandez Captain, USAF AFIT/G SM/LSR/ 8 9S- 18_...RESULTING FROM THE AFIT EDUCATION WITH INDUSTRY PROGRAM THESIS Ed R. Hernandez Captain, USAF AFIT/GSM/LSR/89S-18 Approved for public release...5 Discussion .. ............. ........ 6 Education versus Training .. .. ............. 7 Concept of Learning .. .. ............... 10 Active Learning

Airborne Operations in World War II, European Theater

DTIC Science & Technology

1956-09-01

GARDEN Gee Hamilcar HANDS UP Formation usually composed of two or more elements and roughly equivalent to a squadron Forward Visual Control Post Ground...USAF HISTORICAL STUDIES: NO. 97 AIRBORNE OPERATIONS IN WORLD WAR II, EUROPEAN THEATER By Dr. John C. Warren USAF Historical Division Research Studies...OMB control number. 1. REPORT DATE SEP 1956 2. REPORT TYPE 3. DATES COVERED - 4. TITLE AND SUBTITLE Airborne Operations in World War II 5a

USAF Flight Surgeon Survey: Aircrew Mental Health Referrals and Satisfaction with Local Mental Health Providers Response

DTIC Science & Technology

2008-05-01

Autogenic training exercise; A treatment for airsickness in military pilots. International Journal of Aviation Psychology, 2005; 15(4): 395-412...flying during training , humanitarian, and operational missions can be extremely taxing. Flight surgeons often observe or hear of changes in the...health care is to ease and resolve the emotional or behavioral difficulties of an aviator while attempting to preserve a highly trained USAF asset

Missions and Mobility Configurations for RED HORSE

DTIC Science & Technology

1988-04-01

use in other research reports or educational pursuits contingent upon the following stipulations: - Reproduction rights do not extend to any copyrighted...MOBILITY CONFIGURATIONS FOR RED HORSE AUTHOR(S) MAJOR JAMES T. RYBURN, USAF FACULTY ADVISOR LT COL ROBERT L. PETERS, ACSC/3823 STUS SPONSOR COL ROBERT J...Classification) MISSIONS AND MOBILITY CONFIGURATIONS FOR RED HORSE 12. PERSONAL AUTHOR(S) Ryburn, James T., Maj or, USAF 13a. TYPE OF REPORT J13b. TIME

Fibrinogen Recovery in Two Methods of Cryoprecipitate Preparation

DTIC Science & Technology

1989-08-01

ERNEST A. HAYGOOD, 1st Lt, USAF Executive Officer, Civilian Institution Programs 17. COSATI CODES 18. SUBJECT TERMS (Continue on reverse if necessary...NAME OF RESPONSIBLE INDIVIDUAL 22b. TELEPHONE (Include Area Code) 22c. OFFICE SYMBOL ERNEST A. HAYGOOD, 1st Lt, USAF (513) 255-2259 AFIT/CI DDForm...u I iv ACKNOWLEDGEMENTS I would like to extend sincerest appreciation to Dr. Lloyd Lippert , my research advisor. Without his continued guidance

Corrective lens use and refractive error among United States Air Force aircrew.

PubMed

Wright, Steve T; Ivan, Douglas J; Clark, Patrick J; Gooch, John M; Thompson, William

2010-03-01

Corrective lens use by military aviators is an important consideration in the design of head-mounted equipment. The United States Air Force (USAF) has periodically monitored lens use by aviators; however, it has been over a decade since the last study. We provide an update on the prevalence of corrective lenses and refractive error among USAF aircrew based on eyeglass orders processed through the Spectacle Request Transmission System (SRTS). Currently, 41% of active duty USAF pilots and 54% of other aircrew require corrective lenses to perform flight duties. Refractive errors are characterized by low to moderate levels of myopia with a mean spherical equivalent power of -1.01 diopters (D) for pilots and -1.68 D for others. Contact lenses, and more recently refractive surgery, reduce the number of aircrew that must rely on spectacles when flying; however, spectacle compatibility remains an important consideration in the cockpit.

USAF bioenvironmental noise data handbook. Volume 157: KC-10A in-flight crew noise

NASA Astrophysics Data System (ADS)

Hille, H. K.

1982-09-01

The KC-10A is a standard USAF tanker-transport aircraft with high-speed, high altitude refueling and long range transport capability. This report provides measured data defining the bioacoustic environments at flight crew/passenger locations inside this helicopter during normal flight operations. Data are reported for 24 locations in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors. Refer to Volume 1 of this handbook, USAF Bioenvironmental Noise Data Handbook, Vol. 1: Organization, Content and Application, AMRL-TR-75-50(1) 1975, for discussion of the objective and design of the handbook, the types of data presented, measurement procedures, instrumentation, data processing, definitions of quantities, symbols, equations, applications, limitations, etc.

Evaluation of Corrective Action Team (CAT) Leader Training in Aeronautical Systems Division

DTIC Science & Technology

1991-09-01

00A DI EVALUATION OF CORRECTIVE ACTION TEAM ( CAT ) LEADER TRAINING IN AERONAUTICAL SYSTEMS DIVISION CA THESIS Kirk J. Streitrater, Captain, USAF AFIT...EVALUATION OF CORRECTIVE ACTION TEAM ( CAT ) LEADER TRAINING IN AERONAUTICAL SYSTEMS DIVISION THESIS Kirk J. Streitmater, Captain, USAF AFIT/GSM/LSR/91S-25...8217, , C- s :C AFIT/GSM/LSR/91S-25 EVALUATION OF CORRECTIVE ACTION TEAM ( CAT ) LEADER TRAINING IN AERONAUTICAL SYSTEMS DIVISION THESIS Presented to the

Proceedings of the USAF Logistics Capability Assessment Symposium LOGCAS 82 Held at USAF Academy, Colorado on 15-19 March 1982

DTIC Science & Technology

1982-05-01

Ohio. General Merkling , fZ" and graduated from Hamilton High School, Los Angeles. He has a bachelor of science degree in mechanical engineering...navigation, navigation radar and doppler radar systems on bomber, cargo , fighter, and drone aircraft. He also performed duties as maintenance debriefer...measure supply support for those items. ihe model will also project future performance and provide a cost/support relationship. 11-13

Dental Electric Handengines: Test and Evaluation.

DTIC Science & Technology

1985-04-01

ADRD5 066 A DENTAL ELECTRIC HANDENGINES: TEST AND EVALUATION(U) j/ij SCHOOL OF AEROSPACE MEDICINE BROOKS AFB TX C D FOSTER ET AL. APR 85 USAFSAM-TR... DENTAL ELECTRIC HANDENGINES o Test and Evaluation In -- I Cad D. Foster, Major, USAF, DC Paul M. Callison, Master Sergeant, USAF Gerald F. McKinley...AFSC) Brooks Air Force Base, TX 78235-5301 85 7 15 057 NOTICES This final report was submitted by personnel of the Dental Investigation Service

Dollar Summary of Federal Supply Classification and Service Category by Company, FY83, Part 4 (AA92-N063).

DTIC Science & Technology

1983-01-01

INTEGRATED SYSTEMS ANALYSTS INC VIRGINIA NAVY RDTE/ELECTRONICS AND COMMUNICATION EQUIP 964 INTERACTIVE SYSTEMS INC MICHIGAN USAF ROTE/ELECTRONICS AND...HARD GOODS INTERACTIVE SYSTEMS INC COLORADO ARMY RDTE/MISCELLANEOUS HARD GOODS LITTON SYSTEMS INC NEW JERSEY NAVY RDTE/MISCELLANEOUS HARD GOODS I...DEFENSE 88 INTELLIGENT SY STATE TOTAL 114 INTERACTIVE TE CO CALIFORNIA ARMY RDTE/OTHER DEFENSE 201 INTERNATIONAL I NAVY ROTE/OTHER DEFENSE 778 USAF RDTE

Experimental Validation Techniques for the Heleeos Off-Axis Laser Propagation Model

DTIC Science & Technology

2010-03-01

EXPERIMENTAL VALIDATION TECHNIQUES FOR THE HELEEOS OFF-AXIS LASER PROPAGATION MODEL THESIS John Haiducek, 1st Lt, USAF AFIT/GAP/ENP/10-M07 DEPARTMENT...Department of Defense, or the United States Government. AFIT/GAP/ENP/10-M07 EXPERIMENTAL VALIDATION TECHNIQUES FOR THE HELEEOS OFF-AXIS LASER ...BS, Physics 1st Lt, USAF March 2010 APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED. AFIT/GAP/ENP/10-M07 Abstract The High Energy Laser End-to-End

The United States Air Force in Korea: A Chronology, 1950-1953

DTIC Science & Technology

2000-01-01

War , the U.S. Air Force (USAF) Historian commissioned the Research Division, Air Force His- torical Research Agency (AFHRA), Maxwell Air Force Base...and aces. Finally, it attempts to summarize those USAF events in Korea that best illustrate the air war and the application of air power in the...sources, usually to confirm the most signifi- cant events of the air war in Korea. AFHRA historians or archivists who researched and wrote the monthly and

Leadership in Crisis: Service Chiefs in the Post-Vietnam World

DTIC Science & Technology

2012-06-01

the Korean War offered numerous lessons for the Army and USAF based on the effectiveness of interdiction and the need to coordinate with the ground ...roles and missions.100 Attack capability in this discussion is a platform’s ability to attack targets on the ground . Both USAF and Army leaders had...States Government; Record Group 11; National Archives , 7 August 1964). AU/SAASS/MILLS/AY12 72 of war.8 Soon after Johnson signed the resolution

Golden Legacy, Boundless Future: Essays on the United States Air Force and the Rise of Aerospace Power

DTIC Science & Technology

2000-01-01

tactical support, and, to a lesser extent, bom- bardment. The American Army had to digest quickly the crucial lesson already absorbed by the...2. United States Air Force Statistical Digest , 1947, Director of Statistical Services, Comptroller, HQ USAF, Washington, D.C., 1948, 15-16, 72, 132...Statistical Digest , Director of Statistical Services, Deputy Chief of Staff, Comptroller, HQ USAF, Washington, D.C., Nov 1952, 162-164. 6. Sarah A

United States Air Force Summer Research Program -- 1993 Summer Research Program Final Reports. Volume 12. Armstrong Laboratory

DTIC Science & Technology

1993-01-01

Panasonic TLD . Panasonic Industrial Company; Secaucus, New Jersey. 5. Thurlow, Ronald M. "Neutron Dosimetry Using a Panasonic Thermoluminescent Dosimeter." A...steps 8-12. 29-15 THE BUILDING OF THE USAF PANASONIC UD-809AS ALGORITHM Katherine M. Arnold Research Associate Radiation Dosimetry Branch Brooks Air...Research August 1993 30-1 THE BUILDING OF THE USAF PANASONIC UD-809AS ALGORITHM Katherine M. Arnold Research Associate Radiation Dosimetry Branch

Book Analysis: Challenger: A Major Malfunction.

DTIC Science & Technology

1988-04-01

REPORT NUMBER 88-113S TITLE BOOK ANALYSIS: CHALLENGER : A MAJOR MALFUNCTION AUTHOR(S) MAJOR THOMAS M. HALL, USAF FACULTY ADVISOR LT COL JOhN R. GRELLMAN... CHALLENGER : A MAJOR MALFUNCTION 12. PERSONAL AUTHOR(S) Hall, Thomas M., Major, USAF 13a. TYPE OF REPORT 13b. TIME COVERED 14. DATE OF REPORT (Year, Month...identify by block number) FIELD GROUP SUB-GROUP 19. ABSTRACT Continue on reverse if necessary and identify by block number) This report analyzes Challenger

Developing Cyberspace Data Understanding: Using CRISP-DM for Host-based IDS Feature Mining

DTIC Science & Technology

2010-03-01

Developing Cyberspace Data Understanding: Using CRISP - DM for Host-based IDS Feature Mining THESIS Joseph R. Erskine, Captain, USAF AFIT/GCS/ENG/10-01...Air Force, Department of Defense, or the United States Government. AFIT/GCS/ENG/10-01 Developing Cyberspace Data Understanding: Using CRISP - DM for...Developing Cyberspace Data Understanding: Using CRISP - DM for Host-based IDS Feature Mining Joseph R. Erskine, B.S.C.S. Captain, USAF Approved: /signed/ 12

A Graphics Environment Supporting the Rapid Prototyping of Pictorial Cockpit Displays

DTIC Science & Technology

1986-12-01

0 - niDi cO 3 FIL .OF I A GRAPHICS ENVIRONMENT SUPPORTING THE RAPID PROTOTYPING OF PICTORIAL COCKPIT DISPLAYS THESIS Alan J. Braaten Captain, USAF...COCKPIT DISPLAYS THESIS Alan J. Braaten Captain, USAF AFIT/GCS/IA/86D- 1 Appram:ed for public release; distribution unlimited AFIT/GCS/MA/80- 1 A...GRAPHICS ENVIROWNT SUPPORTING THE RAPID PROTOTYPING OF PICTORIAL COCKPIT DISPLAYS THESIS Preented to the Faculty Of the School of Engineering of the Air

An Analysis of Factors Influencing the Turnover of United States Air Force Pilots in the Six to Eleven Year Group

DTIC Science & Technology

1980-06-01

1979. 16. Donnelly, James H., Jr., James L. Gibson, and JohnM. Ivancevich . Organizations--Structure, Processes, Behavior. Dallas TX: Business...Publications, Inc., 1973. 17. Ivancevich , John M., Andrew D. Szilagyi, Jr., and Marc J. Wallace, Jr. Organizational Behavior and Performance. Santa Monica CA...215. 102 Lyons , Colonel Billy S., USAF, and Colonel KZjnald L. Marks, USAF. "An Alternate Pilot Management Pro- gram for Future Strategic Weapon

MAKING THE WEASELS WILD AGAIN: ENSURING FUTURE AIR DOMINANCE THROUGH EFFECTIVE SEAD TRAINING

DTIC Science & Technology

2016-06-01

both multi-mission design series (MMDS) and joint SEAD training as well as improve the capabilities of its electronic warfare (EW) ranges in order...USAF units to train for multi-mission design series (MMDS) SEAD operations.14 MMDS training includes the use of multiple USAF airborne platforms...not provided SEAD aircrews with either the quantity or quality of training required to conduct effective operations.2 At that time , Major Jon Norman

An Assessment of Software Safety as Applied to the Department of Defense Software Development Process

DTIC Science & Technology

1992-12-01

provide program 5 managers some level of confidence that their software will operate at an acceptable level of risk. A number of structured safety...safety within the constraints of operational effectiveness, schedule, and cost through timely application of system safety management and engineering...Master of Science in Software Systems Management Peter W. Colan, B.S.E. Robert W. Prouhet, B.S. Captain, USAF Captain, USAF December 1992 Approved for

Centralized Contractor Operated Initial Flight Screening Program at Pueblo, Colorado

DTIC Science & Technology

2006-03-23

TAXI = Private/Corporate Jets Source:USAF IFT Preliminary Noise Impact Assessment, 22 July 2005 Current activity at the private airfield at Fowler...Airport Land use Source:USAF IFT Preliminary Noise Impact Assessment, 22 July 2005 3.8 Transportation Pueblo Memorial Airport is served by United...pumpage per day in 2003: 23.567 million gallons per day • All time record Peak Day: 62,930,000 on July 16th, 1997 • Treatment plant capacity: 84

Band Gap Transition Studies of U:ThO2 Using Cathodoluminescence

DTIC Science & Technology

2014-03-27

BAND GAP TRANSITION STUDIES OF U:THO2 USING CATHODOLUMINESCENCE THESIS Joshua D. Reding , Second Lieutenant, USAF AFIT-ENP-14-M-31 DEPARTMENT OF THE...Education and Training Command in Partial Fulfillment of the Requirements for the Degree of Master of Science in Applied Physics Joshua D. Reding , B.S...STUDIES OF U:THO2 USING CATHODOLUMINESCENCE Joshua D. Reding , B.S. Second Lieutenant, USAF Approved: //signed// Robert L. Hengehold, PhD (Chair) //signed

Credit USAF, ca. 1943. Original housed in the Muroc Flight ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF, ca. 1943. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Historic view looking north across southwest end of swimming pool as army personnel work on finishing the pool bottom. View looks towards Mess Hall (T-10) on Second Street - Edwards Air Force Base, North Base, Swimming Pool, Second Street, Boron, Kern County, CA

USAF Dental Service Mercury Hygiene Report, Calendar Year 1980.

DTIC Science & Technology

1981-12-01

the floor. Mercury Vapor Analyzer Used No. calibration No. of clinics Percent reported MV2 - Bacharach 81 67.5 14 Hopcalite tubes 8 6.7 Jerome model...instruments which could determine TWA: hopcalite tubes (8), Jerome with dosimeter coils (5), and 3M monitor (3). All 16 of these surveys showed mercury...vapor levels. This quantification requires sampling using the Jerome with a dosimeter coil, hopcalite tubes, or the 3M monitor. The USAF Occupational

Installation Restoration Program. Phase 2. Confirmation Quantification. Stage 2 for MacDill Air Force Base, Florida. Volume 2

DTIC Science & Technology

1988-07-22

Inc. of Savannah, Georgia and Tallahassee, Florida provided analytical services. Michael Newberry, Captain USAF, and Jeff Mason, 2d LT., USAF, from...2803-19 AG AP6 ST;- ES Ci eit 2803-20 A? APC S -2 ES 23033-23 AG .AF6 SD-S 2803-22 AC AP6 SD-4 E.> PARAMIETER 280u- .y 2&u r 23-2: 2803-22 Bezo (g.h.1

Legal Issues for the Commander,

DTIC Science & Technology

1983-01-01

Frederick T. Kiley, USAF Deputy Director, Plans and Programs Major William A. Buckingham, Jr., USAF Deputy Director, Administration Lieutenant (Junior...Writer-Editors Editorial Clerks Evelyn Lakes Pat Williams , Janis L. Hietala Lead Clerk Rebecca W. Miller Dorothy M. Mack Albert C. Helder Carol Valentine...9 M.J. 575 (A.F.C.M.R. 1980). 41 AL .. ~ ~. .~ ~ i 42 References 28. United States v. Poundstone , 22 U.S.C.M.A. 277, 46 C.M.R. 277 (1973). 29. United

Epidemoligic Investigation of Health Effects in Air Force Personnel Following Exposure to Herbicides: Baseline Questionnaires

DTIC Science & Technology

1982-11-01

19M I Prepared for: The Surgeon General ~, United States Air Force Washington, D.C. 20314 USAF SCHOOL OF AEROSPACE MEDICINE Brooks Air Force Base...School of Aerospace Medicine , Aerospace Medical Division, AFSC, Brooks Air Force Base, Texas, under job order 2767-00-01. la When Government drawings...Wolfe. Ljeujenant; Colonel, USAF. M C S F. IlFONMING ORGANIZATION NAMS AND AODRESS 10. PROGRAM ELEMENT. PROJECT, TASKUSAF School of Aerospace Medicine

What’s Wrong with the Survivor Benefit Plan?

DTIC Science & Technology

1986-04-01

Found aspects of the program confusing. Most often mentioned were the benefit adjustment mechanism and the special tax advantage Features. Not...WHAT’S WRONG WITH THE SURVIVOR BENEFIT PLAN? AUTHOR(S) MAJOR RALPH A. BLA1ELOCK, USAF FACULTY ADVISOR MAJOR MACK FOSTER, ACSC/EDCM SPONSOR LT COLONEL...Include.ecurslty Ckwaaicationl WHAT’S WRONG WITH THE SURVIVOR BENEFIT , PERSONAL AUTHORST Blakelock, ph A., Major, USAF 13a. TYPE OF REPORT 13t. TIME

Student Modeling in an Intelligent Tutoring System

DTIC Science & Technology

1996-12-17

Multi-Agent Architecture." Advances in Artificial Intelligence : Proceedings of the 12 th Brazilian Symposium on Aritificial Intelligence , edited by...STUDENT MODELING IN AN INTELLIGENT TUTORING SYSTEM THESIS Jeremy E. Thompson Captain, USAF AFIT/GCS/ENG/96D-27 DIMTVMON* fCKAJWINT A Appr"v*d t=i...Air Force Base, Ohio AFIT/GCS/ENG/96D-27 STUDENT MODELING IN AN INTELLIGENT TUTORING SYSTEM THESIS Jeremy E. Thompson Captain, USAF AFIT/GCS/ENG/96D

Air Force Basing Strategies in the Western Pacific in Response to Chinese Military Buildup during Fiscal Austerity

DTIC Science & Technology

2016-02-01

CHINESE MILITARY BUILDUP DURING FISCAL AUSTERITY by Timothy M. Swierzbin, Major, USAF A Research Report Submitted to the Faculty In Partial...future of USAF operations in the Asia-Pacific such as drastic military budget austerity and the state of Chinese aggression in the region...around the world to impart various levels of austerity to tackle their national debts. The U.S. was also susceptible to the crisis and the Government

Acoustic Evaluation and Recommended Controls for Runway Supervisory Units, Laughlin AFB, Texas.

DTIC Science & Technology

1980-02-01

NR ), given in Table 2 and shown in Figures 8 through 12 , are the arithmetic differences between exterior and interior noise levels. No difference...ORG. REPORT MUM4MR , ,IT]VPARINACCI, Capt, USAF- BSC Consultant, Acoustics Evaluation Engr CAROLYN M. JONES, 2LT USAF, BSC Consultant, Industria ...Documents.,") Block 12 . Report Date. Enter here the day, month, and year or month and year as shown on the cover, Block 13. Number of Pages. Enter

Distributed Localization of Active Transmitters in a Wireless Sensor Network

DTIC Science & Technology

2012-03-01

Distributed Localization of Active Transmitters in a Wireless Sensor Network THESIS Oba L. Vincent, 2nd Lieutenant, USAF AFIT/GE/ENG/12-41 DEPARTMENT...protection in the United States. AFIT/GE/ENG/12-41 Distributed Localization of Active Transmitters in a Wireless Sensor Network THESIS Presented to the...Transmitters in a Wireless Sensor Network Oba L. Vincent, B.S.E.E. 2nd Lieutenant, USAF Approved: /signed/ 29 Feb 2012 Maj. Mark D. Silvius, Ph.D. (Chairman

Flow-Tube Investigations of Hypergolic Reactions of a Dicyanamide Ionic Liquid Via Tunable Vacuum Ultraviolet Aerosol Mass Spectrometry.

PubMed

Chambreau, Steven D; Koh, Christine J; Popolan-Vaida, Denisia M; Gallegos, Christopher J; Hooper, Justin B; Bedrov, Dmitry; Vaghjiani, Ghanshyam L; Leone, Stephen R

2016-10-07

The unusually high heats of vaporization of room-temperature ionic liquids (RTILs) complicate the utilization of thermal evaporation to study ionic liquid reactivity. Although effusion of RTILs into a reaction flow-tube or mass spectrometer is possible, competition between vaporization and thermal decomposition of the RTIL can greatly increase the complexity of the observed reaction products. In order to investigate the reaction kinetics of a hypergolic RTIL, 1-butyl-3-methylimidazolium dicyanamide (BMIM + DCA - ) was aerosolized and reacted with gaseous nitric acid, and the products were monitored via tunable vacuum ultraviolet photoionization time-of-flight mass spectrometry at the Chemical Dynamics Beamline 9.0.2 at the Advanced Light Source. Reaction product formation at m/z 42, 43, 44, 67, 85, 126, and higher masses was observed as a function of HNO 3 exposure. The identities of the product species were assigned to the masses on the basis of their ionization energies. The observed exposure profile of the m/z 67 signal suggests that the excess gaseous HNO 3 initiates rapid reactions near the surface of the RTIL aerosol. Nonreactive molecular dynamics simulations support this observation, suggesting that diffusion within the particle may be a limiting step. The mechanism is consistent with previous reports that nitric acid forms protonated dicyanamide species in the first step of the reaction.

The United States Air Force and the Culture of Innovation, 1945-1965

DTIC Science & Technology

2002-01-01

US Dept of Transportation; typically they hover between 85 and 95 percent. 16. Kent C. Redmond and Thomas M. Smith, Project Whirlwind: A Case Histo...Washing- ton, D.C.: AF Hist and Museums Prog, 1994). 14. Thomas A . Sturm, The USAF SAB: Its First Twenty Years 1944–1964 (Washington, D.C.: USAF...allegations at Ramo-Wooldridge and the Air Force’s approach. Schriever answered them in a letter to Lt. Gen. Thomas Power, the commander of ARDC, in

The Death of Superman: The Case Against Specialized Tanker Aircraft in the USAF

DTIC Science & Technology

2002-06-01

tanker and receiver aircraft were de Havilland DH -4Bs. The DH -4B was a single engine biplane with a gross weight of 3,557 pounds. Its cruising speed...including transport, air ambulance, photographic plane, trainer, target tug, forest fire patroller, and air racer. “De Havilland DH -4: Air Service... Havilland DH -4: Air Service Workhorse.” USAF Museum, WPAFB. On-line. Internet, 6 June 2002. Available from http://www.wpafb.af.mil/ museum

Status Report on Medical Materiel Items Tested and Evaluated for Use in the USAF Aeromedical Evacuation System

DTIC Science & Technology

1990-12-01

Volumetric Infusion Pump is conditionally acceptable for use. The Air -In- Line detector does not sense air bubbles 0.95 cm (3/8 inch) or smaller...been fitted with an improved brushless air circulation motor, Brailsford model T- 2NFR. Using the new motor, the 185 passed EMI and is acceptable for...USAF School of Aerospace Medicine, Human Systems Division, Air Force Systems Command, Brooks Air Force Base, Texas, under job order 7930-16- 12. This

An Annotated Bibliography of Hypobaric Decompression Sickness Research Conducted at the Crew Technology Division, USAF School of Aerospace Medicine, Brooks AFB, Texas from 1983 to 1988

DTIC Science & Technology

1990-06-01

AN ANNOTATED BIBLIOGRAPHY OF HYPOBARIC DECOMPRESSION SICKNESS RESEARCH CONDUCTED AT THE CREW TECHNOLOGY DIVISION, USAF SCHOOL OF AEROSPACE MEDICINE...190 man-flights to four selected altitudes (30000, 27500, 25000, and 22500 ft pressure equivalent) in a hypobaric chamber. The subjects’ ages ranged...conditions and two of these developed delayed sy~rtcms. Three of these five subjects underwent hyperbaric oxygen treatment. Conclusion. Female subjects

Report of the Defense Science Board Task Force on Tactical Battlefield Communications,

DTIC Science & Technology

2000-02-01

Communications, in and Intelligence (ASD/C3I); and LTG John Woodward, J6. The Task Force comprised fourteen experts from government, industry, and academe. The...O’Berry (USAF-Retired) Col Bobby Smart (USAF) Professor Stewart Personick Mr. Mark Rich Mr. Peter D. Steensma DSB Staff Assistant Mr. John ...were: The Honorable Dr. Jacques Gansler, USD/AT&L, the Honorable Art Money, ASD/C3I and LTG John Woodward, JCS-J6. The Task Force membership (Figure

6. Credit USAF, ca. 1947. Original housed in the Photograph ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

6. Credit USAF, ca. 1947. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. Interior of Building 4401 (or possibly 4402) looking east at hangar doors with a North American Aviation XB-45 Tornado jet aircraft in the foreground. This view illustrates why the series of sliding doors and wide, high interior clearances were necessary to accommodate large aircraft. Note configuration of wooden trusses supporting the roof. - Edwards Air Force Base, North Base, Hangar No. 1, First & B Streets, Boron, Kern County, CA

Development and Implementation of a Comprehensive Risk Management Program at the USAF Academy Hospital, USAF Academy, Colorado

DTIC Science & Technology

1980-04-01

injuries annually of which some 700,000 appeared to involve some form of medically negligent conduct. 6 Similarly, the number of malpractice claims brought...only three (3) claims of medical malpractice were filed against the Air Force. That same year, a total of $12(!) was paid by the Air Force in...1976.26 The department of Health, Education and Welfare’s Commission on Medical Malpractice estimated that 12,000 medical malpractice claims 27 were filed

Total Quality Management in the Department of Defense

DTIC Science & Technology

1989-09-01

DTI ELECT SDu TOTAL QUALITY MANAGEMENT IN THE DEPARTMENT OF DEFENSE THESIS BRUCE E. SPRINGS, B.S. CAPTAIN, USAF AFIT/GLN/LSR/ 89S -57 I1- DEPARTMENT...13 0 3 AFIT/GLM/LSR/89S-57 TOTAL QUALITY MANAGEMENT IN THE DEPARTMENT OF DEFENSE THESIS BRUCE E. SPRINGS, B.S. CAPTAIN, USAF AFIT/GLH/LSR/89S-57...Defense. # AFIT/GLM/LSR/89S-57 TOTAL QUALITY MANAGEMENT IN THE DEPARTMENT OF DEFENSE THESIS Presented to the Faculty of the School of Systems and Logistics

Project CHECO Southeast Asia Report. Forward Airfields for Tactical Airlift in SEA

DTIC Science & Technology

1970-06-15

publications, this is an authen- tic s-sment of the effectiveness of USAF airpower in PACOM. ef /o a , Major General, USAF I/ m i ii l UNCLASSIFIED...Australian Air Force (RAAF) crews were airborne 35,569 times in 1969, with cargo that ranged from troops to chickens, cement , rice, ammunition, cattle...Runway surfaces--clay, laterite , limestone, light steel matting (M8Al), or sod, depending on the aircraft involved-- were expected to sustain 700 traffic

Randolph AFB, San Antonio, Texas. Revised Uniform Summary of Surface Weather Observations (RUSSWO)

DTIC Science & Technology

1976-03-19

FoRM ARE oUsoIII ’, " ’ . . . " " -,, ’:,,,:t."," *4 -- ".°" "- . . . " ’ * "- : ; Ir , ( DATA PROCESSING BRANCH EtAC/USAF SURFACE WINDS AIR" WATHER ...FORM ARI OS$Oitlt_ ___ _zT z __ __ ___......- ___ _ _ _ .4. .. . II DATA PROCESSIN G BRASFCH FTAC/USAF SURFACE WINDS AiR WATHER SERVICE/MAC PERCENTAGE...SURFACE WINDS 1 A/R WATHER SERVICE/MAC PERCENTAGE FREQUENCY OF WIND DIRECTION AND SPEED (FROM HOURLY OBSERVATIONS) ( 12911- RANDOLPH AFBJTEXAS/SAN

Engineering Test and Evaluation During High G. Volume III, Anti-G Suits.

DTIC Science & Technology

1978-06-01

items are: 3 inservice units from USAF and IJSN; an RAF unit; and 2 experimental units (lower body full pressure, and capstan). The study of the capstan...inspections are performed by life-support techni- cians whose training and expertise best enable them to evaluate the anti-G suit condition. The TEHG...of testing in one minute." At some installations this test has been waived by USAF Air Training Command (ATC) to "l psig drop from 5 psig in 20 sec

Development and Implementation of a Comprehensive Risk Management Program at the USAF Academy Hospital.

DTIC Science & Technology

1980-04-01

much less con - cerned about malpractice problems. As a result of the program, they began to view the risk management program as their own and to recog...that con - tributes to better patient care. 131 Implementing Risk Management According to Donovan and Bader, an action plan for the systems approach might...Al87 344 DEVELOPMENT AND IMPLEMENTATION OF A COMPREHENSIVE RISK 1 MANAGEMENT PROGRAM AT THE USAF ACADEMY HOSPITAL(U) ARMY HEALTH CARE STUDIES AND

A Study to Determine Patient Waiting Time at the Outpatient Pharmacy at Wilford Hall USAF Medical Center

DTIC Science & Technology

1988-06-01

at Wilford Hall USAF Medical Center significantly reduced the patient wait time at the main outpatient pharmacy. Satellite pharmacies have been ).’l...PRESENTING TO WINDOW 1, 19 MAR 88. 47 C:. A’.’E-:A: -ESCRIRTIONS PER PATIENT ...........48 H. WILFORD HALL MEDICAL CENTER OUTPATIENT QUESTIONNAIRE...that wait times at tne outpatient pharmacy were excessive. It was this concern that motivated the Medical Center Administrator to request that patient

The ’Irreversibility’ of Israel’s Annexation of the West Bank and Gaza Strip: A Critical Evaluation.

DTIC Science & Technology

1985-10-01

to the West Bank - 22 - and Gaza Strip warrant the conclusion that political initiatives based on the presumption that Israeli withdrawal is feasible...with the possible and important exception of East Jerusalem, the second, psycho-cultural threshold, has not yet been crossed. An ingrained presumption ...HQ USAF/IN Washington, D.C. 20330 AFSAC/ INOC Fort Belvoir, VA 22060-5788 Commandant USAF Academy Colorado Springs, CO 80914 AFIS/DPT Fort Belvoir, VA

Retaining U.S. Air Force Pilots When the Civilian Demand for Pilots Is Growing

DTIC Science & Technology

2016-01-01

pilot retention and determine the changes in ARP and AP that could offset those effects. It also simulates the effects of eliminating AP for pilots...array of compensation policies for pilots, thereby providing the USAF with an empirically based analytical platform to determine the special and...greatly from the input and support of our project monitor, Maj Ryan Theiss, Chief, Rated Force Policy-Mobility Forces (HQ USAF/A1PPR), as well as Lt

Refrigeration and Cryogenics Career Ladder, AFSc 54530, 54550, and 54570.

DTIC Science & Technology

1983-07-01

STATES AIR FORCE D cl e 00l REFRIGERATION AND CRYOGENICS CAREER LADDER AFSCs 54530, 54550, AND 54570 AFPT 90-545-461 JULY 1983 ,-. 71983 - OCCUPATIONAL...been reviewed and is approved. PAUL T. RINGENBACH, Colonel, USAF WALTER E . DRISKILL, Ph.D. Commander Chief, Occupational Analysis Branch USAF...ASSIGNED SAMPLE AIRMAN 35 35 E -4 22 23 E -5 27 26 E -6 11 12 E -7 5 4 E -8 * E -9 * TOTALS 100 100 DENOTES LESS THAN ONE PERCENT TABLE 3 TAFHS

9. Credit USAF, ca. 1945. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

9. Credit USAF, ca. 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View of concrete base and brackets of jet engine rotor balancing machine. Location where photograph was taken not determined, but presumed to be in shops of Building 4505. - Edwards Air Force Base, North Base, Hangar, End of North Base Road, Boron, Kern County, CA

8. Credit USAF, ca. 1945. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

8. Credit USAF, ca. 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View of concrete base for jet engine rotor balancing machine. Location where photograph was taken not determined, but presumed to be in shops of Building 4505 which had a sizeable machine shop. - Edwards Air Force Base, North Base, Hangar, End of North Base Road, Boron, Kern County, CA

Analysis of Minuteman Missile Crew Member Attitudes Toward Present Minuteman Education Program and Possible Alternatives.

DTIC Science & Technology

1980-06-01

TO0WARD PRESLT NUE N - DUCATION PROGRADF AND T0SMBLE 6. PERFORMING GIG. 0114:00RT NUMneRt 11. CONTRACT ORt GRANT NuUSERf(s1 t~ Donald L. i emp Captain...USAF, M4SC *Andrew T.//Rybacr Captain, USAF 9. PERFORMING ORGANIZATION NAME AND AOORES~r10 PROGRAM ELEMENT. PROJECT. TASK School of Systems and...106 38. MMEP IMPROVES DUTY PERFORMANCE (X2 One Sample Test) .. .......... . 107 39. MMEP IMPROVES DUTY PERFORMANCE (Questionnaire Data

Is the USAF Officer Corps a Fighting Force?

DTIC Science & Technology

1988-05-01

quottin)j analysis, and operational audit . Following work moasurent and 14 computAtions, th., standards 4uro staffed and approved by NQ USAF *rnl...occupation group in the Air Force. 9 Most recently# Senator John Glenn has asked the GAO to conduct an audit of pilot requirements.1 9 This information...AlIocdtion System," Air Force Times, 14 September 1987, p. 6. 9. Pat )alton, " Audit Pilot Requirements, Glenn Asks GAO," Air Forte Times, 18 January 1988

Mission Emphasis and the Determination of Needs for New Weapon Systems

DTIC Science & Technology

2009-05-01

Loveland, CO: Prosci, 2006). 61. Richard R. Nelson and Sidney G. Winter, An Evolutionary Theory of Economic Change (Cambridge, MA: The Belknap Press...of Gen Hunter Harris, USAF, (Ret.), by Col John E. Van Duyn and Maj Richard B. Clement, 7 July 1971. Typed transcript p. 32, K239.0512-403 Iris No...C. Jones, USAF, (Ret.) by Dr. Lt Col Maurice Maryanow and Dr. Richard H. Kohn, 5 August, 15-17 October 1985; 20-21 January, 13-14 March 1986

Practical Applications of Math and Science in Junior High Schools

DTIC Science & Technology

1984-04-01

APPLICATIONS OF MATH AND SCIENCE IN JUNIOR HIGH SCHOOLS AUTHOR(S) MAJOR LAWRENCE N. HYLAND, USAF FACULTY ADVISOR mAJoR JAMM WILSON, ACSC/EDDP SPONSOR LT COL...JUNIOR HIGH SCHOOLS 6 PERFORMING O1G. REPORT NUMBER "ś, Au THORrs) 8. CON’RACT OR GRANT NUMBER(.,) Lawrence N. Hyland, Major, USAF 9. PERFORMING...materials aimed at the jumior high school level. Material exposes target group to the mathematical and scientific skills required of Air Force

Investigation of Pseudo Bi-Polar Nickel Cadmium Batteries as Filter Elements for Pulsed Power Loads.

DTIC Science & Technology

1984-12-01

FOR PULSED POWER LOADS THESIS Michael B. Cimino Gregory M. Gearing Major, USAF Captain, USAF AFIT/GE/ENG/84D-1B DTIC SECETE D~rR~fl"N STATEMENT A...LOADS THESIS Presented to the Faculty of the School of Engineering of the Air Force Institute of Technology Air University In Partial Fulfillment of...with the intent to make batteries capable of out performing capacitors as power supply filters. Purpose This thesis investigated the use of nickel

Desert Express: An Analysis on Improved Customer Service

DTIC Science & Technology

1991-09-01

Nt MARQ 3,199 Of. DESERT EXPRESS: AN ANALYSIS ON IMPROVED CUSTOMER SERVICE THESIS Thomas C Thaiheim, Majo-,r USAF AFTT/GLM/LSM,/91S-64 ?Z; W...Astq vt.: tyc a l AFIT/GLM/,LSM/91S-64 DESERT EXPRESS: AN ANALYSIS ON IMPROVED CUSTOMER SERVICE THESIS Thomas C. Thalheim, Major, USAF AFIT/GLM/LSM...91S-64 Approved for public release; distribution unlimited AFIT/GLM/LSM/91S-64 DESERT EXPRESS: AN ANALYSIS ON IMPROVED CUSTOMER SERVICE THESIS

USAF Support to Low Intensity Conflict: Three Case Studies From the 1980s

DTIC Science & Technology

1994-06-01

included armed reconnaissance provided by AC- 130H gunships, and an airdrop of USAF Combat Control Teams and Army Rangers . The main body for the...performance of elite units such as Delta Force, SEALS, Rangers , etc. did not justify the money spent or their claims of eliteness. AU Library Document M-43828...48Adkin, 132. 23 Figure 1 Task Organization for Joint Task Force 120. CJTF 120 Carribean Peacekeeping Force CTF 121 Airborne CTF 123 Rangers

Air & Space Power Journal. Volume 22, Number 1, Spring 2008

DTIC Science & Technology

2008-01-01

Braganca, USAF Naval Air Station Patuxent River, Maryland Dr. Kendall K. Brown NASA Marshall Space Flight Center Col Steven D. Carey, USAF...bunch of ‘Bs’ I’ve ever heard of.” At first there was no reaction to my remarks, but then the entire room erupted in shouts and cheers! All I had...present itself. Being in Our Profession Is All about Service to Others I am reminded of the photograph of the chief master sergeant stationed in Iraq

Effect of Prior Exposure at Elevated Temperatures on Tensile Properties and Stress-Strain Behavior of Three Oxide/Oxide Ceramic Matrix Composites

DTIC Science & Technology

2015-03-26

OF THREE OXIDE/OXIDE CERAMIC MATRIX COMPOSITES THESIS Christopher J. Hull, Captain, USAF AFIT- ENY -MS-15-M-228 DEPARTMENT OF THE AIR FORCE...Government and is not subject to copyright protection in the United States. AFIT- ENY -MS-15-M-228 EFFECT OF PRIOR EXPOSURE AT ELEVATED TEMPERATURES ON...BS Captain, USAF March 2015 DISTRIBUTION STATEMENT A: APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED AFIT- ENY - MS-15-M-228 EFFECT OF

Fatigue and Workload in Four-Man C-5A Cockpit Crews (Volant Galaxy).

DTIC Science & Technology

1980-08-01

AD-AO91. 1.9 SCI400L OF AEROSPACE MEDICINE BROOKS AFB TX F/6 S/9 FATIGUE AND WORKLOAD ZN FOUR-NAN C-SA COCKPIT CREWS (VOLANT *AL--ETC(U$ AUG 80 W F...release; distribution unlimited. USAF SCHOOL OF ALROSPACE MEDICINE Aerospace Medical Division (AFSC) Brooks Air Force Base, Texas 78235 81 2 NOTICES...This final report was submitted by personnel of the Crew Performance Branch, Crew Technology Division, USAF School of Aerospace Medicine , Aerospace

Project CHECO Southeast Asia Report. USAF Search and Rescue in Southeast Asia, 1 July 1969 - 31 December 1970

DTIC Science & Technology

1971-04-23

airpower to meet a multitude of requirements. The varied applications of airpower have involved the full spectrum of USAF aerospace vehicles, support...shield of the sky proper, a sphere azure , rimmed and gridded or, superimposed in the southwest areas of the sphere a cross and three lightning bolt...Plan 69-1 to provide two full squadrons of HH-53 Super Jolly Greens or BUFFs as they were known in SEA--for Big Ugly Friendly Fellows, as one

Practical question-and-answer guide on VDTS (video display terminals) for BEES (base bioenvironmental engineer). Final report

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

Olson, B.M.

1985-01-01

The USAF OEHL conducted an extensive literature review of Video Display Terminals (VDTs) and the health problems commonly associated with them. The report is presented in a question-and-answer format in an attempt to paraphrase the most commonly asked questions about VDTs that are forwarded to USAF OEHL/RZN. The questions and answers have been divided into several topic areas: Ionizing Radiation; Nonionizing Radiation; Optical Radiation; Ultrasound; Static Electricity; Health Complaints/Ergonomics; Pregnancy.

Project CHECO Southeast Asia Report. USAF Civic Action in Thailand

DTIC Science & Technology

1969-03-22

SECOND CLASS HEALTH CENTERS MIDWIFERY CENTER MOBILE MEDICAL TEAMS , I SPECIAL 7AF/l3AF FORCES I I I I t I i ! L------·-. 56 ACW -t I i 1 I i...direct treatment of patients by U.S. personnel and the wide variety of drugs offered by the Americans were considered to be contrary to the stated...while diminishing the sophistication 10/ of drugs .-- The variety of drugs supplied by the USAF created a dual problem: (1) Thai resources were

Demographic Shifts in the United States Air Force: 1994-2007

DTIC Science & Technology

2008-02-15

experience includes F-15C, F-15E, A-10, F-16, RC-135, RQ-4 “Global Hawk”, MQ-9 “Predator” and U-2. He is married to the former Deanna Pacansky of...manpower is relied upon to keep this operational tempo, the retention of personnel in whom the USAF invested heavily through training and equipping will...continue to examine the demographics of both the US and USAF population to be alert to possible changes as they affect recruitment, retention , and

Defense AT&L (Volume 36, Number 2, March-April 2007)

DTIC Science & Technology

2007-04-01

87 28 The Pursuit of Courage, Judg- ment, and Luck Maj. Dan Ward, USAF Maj. Chris Quaid, USAF Conventional wisdom states that a closed risk is a good...example) that could be as much as 50 percent dirt. Many agencies were buying adobe bricks that were not kiln -fired, so within two or three seasons of...all too many PMs think a good risk management process simply identifies and mitigates the bad things that can happen. Conventional risk manage- ment

Testing and Evaluation of the Bear Medical Systems, Inc. Bear 33 Volume Ventilator System

DTIC Science & Technology

1990-12-01

approved for publication. RICHARD J. KNECHT, Lt Col, USAF, NC ROGER L STORK , Col, USAF, BSC Project Scientist Chief, Crew Systems Branch EORCHENDER...no problems. After the vibration tests, a visual inspection of the humidifier revealed that a screw and metal clip from a terminal on the incoming...hexagonal J-bolt nuts, which secure the sled to the litter, with larger wing nuts. This modification will allow the sled to be adequately secured by

Testing and Evaluation of the International Biomedical Inc. Neonatal Transport System.

DTIC Science & Technology

1990-12-01

nationals. This report has been reviewed and is approved for publication. RICHARD J. KNECHT, Lt Col, USAF, NC ROGER L. STORK , Colonel, USAF, BSC Project...required by the 375th Aeromedical Airlift Wing surgeon (375 AAW/SG); a process that can consume precious time. (NOTE: The 375 AAW was later redesignated...the 375th Military Airlift Wing , and the SG components were integrated with HQ MAC/SG.) The life and death nature of most newborn referrals to Level

Project CHECO Southeast Asia Report. USAF Civic Action in Republic of Vietnam

DTIC Science & Technology

1968-04-01

peace in SEA." 1 The Commander, 7AF, told his staff the "capabilities and energies of the USAF would be used to implement a positive Civic Action...Civic Action Division took the position that Community Relations was not a function of a Military Civic Action Program and properly belonged in the...considered an assignment of convenience, since the position more properly called for a Special Air Warfare Officer, AFSC 0316. Efforts were being made to

The rate of adverse events during IV conscious sedation.

PubMed

Schwamburger, Nathan T; Hancock, Raymond H; Chong, Chol H; Hartup, Grant R; Vandewalle, Kraig S

2012-01-01

Conscious sedation has become an integral part of dentistry; it is often used to reduce anxiety or fear in some patients during oral surgery, periodontal surgery, implant placement, and general dentistry procedures. The purpose of this study was to evaluate the frequency of adverse events during IV conscious sedation provided by credentialed general dentists and periodontists in the United States Air Force (USAF). Sedation clinical records (Air Force Form 1417) from calendar year 2009 were requested from all USAF bases. A total of 1,468 records were reviewed and 19 adverse events were noted in 17 patients. IV complication (infiltration) was the most common adverse event. The overall adverse event rate was 1.3 per 100 patients treated. The results of this study show that moderate sedation provided by general dentists and periodontists in the USAF has a low incidence of adverse events, and conscious sedation remains a viable option for providers for the reduction of anxiety in select patients.

An analysis of post-traumatic stress symptoms in United States Air Force drone operators.

PubMed

Chappelle, Wayne; Goodman, Tanya; Reardon, Laura; Thompson, William

2014-06-01

Remotely piloted aircraft (RPA), commonly referred to as "drones," have emerged over the past decade as an innovative warfighting tool. Given there is a paucity of empirical research assessing drone operators, the purpose of this study was to assess for the prevalence of PTSD symptoms among this cohort. Of the 1084 United States Air Force (USAF) drone operators that participated, a total of 4.3% endorsed a pattern of symptoms of moderate to extreme level of severity meeting criteria outlined in the Diagnostic and Statistical Manual of Mental Disorders-4th edition. The incidence of PTSD among USAF drone operators in this study was lower than rates of PTSD (10-18%) among military personnel returning from deployment but higher than incidence rates (less than 1%) of USAF drone operators reported in electronic medical records. Although low PTSD rates may be promising, limitations to this study are discussed. Copyright © 2014 Elsevier Ltd. All rights reserved.

NASA Experience with Pogo in Human Spaceflight Vehicles

NASA Technical Reports Server (NTRS)

Larsen, Curtis E.

2008-01-01

An overview of more than 45 years of NASA human spaceflight experience is presented with respect to the thrust axis vibration response of liquid fueled rockets known as pogo. A coupled structure and propulsion system instability, pogo can result in the impairment of the astronaut crew, an unplanned engine shutdown, loss of mission, or structural failure. The NASA history begins with the Gemini Program and adaptation of the USAF Titan II ballistic missile as a spacecraft launch vehicle. It continues with the pogo experienced on several Apollo-Saturn flights in both the first and second stages of flight. The defining moment for NASA s subsequent treatment of pogo occurred with the near failure of the second stage on the ascent of the Apollo 13 mission. Since that time NASA has had a strict "no pogo" philosophy that was applied to the development of the Space Shuttle. The "no pogo" philosophy lead to the first vehicle designed to be pogo-free from the beginning and the first development of an engine with an integral pogo suppression system. Now, more than 30 years later, NASA is developing two new launch vehicles, the Ares I crew launch vehicle propelling the Orion crew excursion vehicle, and the Ares V cargo launch vehicle. A new generation of engineers must again exercise NASA s system engineering method for pogo mitigation during design, development and verification.

Mechanisms of slow-pitch softball injuries reported to the HQ Air Force Safety Center a 10-year descriptive study, 1993-2002.

PubMed

Burnham, Bruce R; Copley, G Bruce; Shim, Matthew J; Kemp, Philip A; Jones, Bruce H

2010-01-01

Softball is a popular sport in civilian and military populations and results in a large number of lost-workday injuries. The purpose of this study is to describe the mechanisms associated with softball injuries occurring among active duty U.S. Air Force (USAF) personnel to better identify potentially effective countermeasures. Data derived from safety reports were obtained from the USAF Ground Safety Automated System in 2003. Softball injuries for the years 1993-2002 that resulted in at least one lost workday were included in the study. Narrative data were systematically reviewed and coded in order to categorize and summarize mechanisms associated with these injuries. This report documents a total of 1181 softball-related mishap reports, involving 1171 active duty USAF members who sustained one lost-workday injury while playing softball. Eight independent mechanisms were identified. Three specific scenarios (sliding, being hit by a ball, and colliding with a player) accounted for 60% of reported softball injuries. Mechanisms of injury for activities such as playing softball, necessary for prevention planning, can be identified using the detailed information found in safety reports. This information should also be used to develop better sports injury coding systems. Within the USAF and U.S. softball community, interventions to reduce injuries related to the most common mechanisms (sliding, being hit by a ball, and colliding with a player) should be developed, implemented, and evaluated. Published by Elsevier Inc.

Hypergolic Combustion Demonstration in a Reciprocating Internal Combustion Engine

DTIC Science & Technology

1984-05-01

deposit problem encountered with Pearl Kerosene. Specifications and properties data for JP-7 fuel are in Table 5-2. 5.5.3. Methanol. Methanol ( CH OH...methylphenol, 0./1,000 bbls. 8.4 max. 8.4 PWA536, PPM 200-250 225 27 ’, •X TABLE 5-3. Typical Properties for Methanol(8) Formula CH 0,i Molecular weight 32.&2...46_ LIST OF REFERENCES (1) Hopple, L. 0. "Pyrophoric Combustion in Internal Combustion Engines," Eaton Technical Report No. 7845 , 1978. (2) Hoppie

49 CFR 173.52 - Classification codes and compatibility groups of explosives.

Code of Federal Regulations, 2012 CFR

2012-10-01

... or hypergolic liquid) E 1.1E1.2E 1.4E Article containing a secondary detonating explosive substance...-S 1.1 1.1A 1.1B 1.1C 1.1D 1.1E 1.1F 1.1G 1.1J 1.1L 9 1.2 1.2B 1.2C 1.2D 1.2E 1.2F 1.2G 1.2H 1.2J 1...

49 CFR 173.52 - Classification codes and compatibility groups of explosives.

Code of Federal Regulations, 2013 CFR

2013-10-01

... or hypergolic liquid) E 1.1E1.2E 1.4E Article containing a secondary detonating explosive substance....1E 1.1F 1.1G 1.1J 1.1L 9 1.2 1.2B 1.2C 1.2D 1.2E 1.2F 1.2G 1.2H 1.2J 1.2K 1.2L 10 1.3 1.3C 1.3F 1.3G...

A study for hypergolic vapor sensor development

NASA Technical Reports Server (NTRS)

Stetter, J. R.; Tellefsen, K.

1977-01-01

In summary, the following tasks were completed within the scope of this work: (1) a portable Monomethylhydrazine analyzer was developed, designed, fabricated and tested. (2) A portable NO2 analyzer was developed, designed, fabricated and tested. (3) Sampling probes and accessories were designed and fabricated for this instrumentation. (4) Improvements and modifications were made to the model 7630 Ecolyzer in preparation for field testing. (5) Instrument calibration procedures and hydrazine handling techniques necessary to the successful application of this hardware were developed.

Relationships Between Molecular Structure and Chemical Reactivity in Hypergolic Ionic Liquids: Progress Toward Designing Green Fuels for Bipropellant Applications

DTIC Science & Technology

2012-05-01

molten salts can be employed over a wide range of applications, which include solvents, 7 electrolytes , 8 pharmaceuticals and therapeutics,9 and...waxy, hygroscopic solid at room temperature, where the additional products in the HP series exist as liquids at room 9 temperature. In general...compressed aluminum pans. Melting and decomposition points for solids were measured by DSC from 40 to 400 oC at a scan rate of 5 ºC/min. IR spectra

Fire Suppression Testing of Hypergolic Vapor Control Foams

DTIC Science & Technology

1990-11-01

tests is given in Table 4. The obstruction test is plotted in Figure 11. c. MIL - F - 24385 -C Tests The low-expansion test utilized in certifying foams for...nozzle, and foam application in accordance with MIL - F -24385C. Extinguishment times were obtained for different application rates. The data were plotted...additional fire tests on the MMH curve. c. MIL - F -24385C Tests A second test (Test A-1B) of this type was conducted with the acrylic-modified foam using

Center Director Bridges addresses guests at ribbon cutting for the new Checkout & Launch Control

NASA Technical Reports Server (NTRS)

2000-01-01

KSC Director Roy Bridges addresses attendees at a ribbon cutting for the new Checkout and Launch Control System (CLCS) at the Hypergolic Maintenance Facility (HMF). The CLCS was declared operational in a ribbon cutting ceremony earlier. The new control room will be used to process the Orbital Maneuvering System pods and Forward Reaction Control System modules at the HMF. This hardware is removed from Space Shuttle orbiters and routinely taken to the HMF for checkout and servicing.

NASA Associate Administrator for Space Flight Rothenberg addresses guests at ribbon cutting for the

NASA Technical Reports Server (NTRS)

2000-01-01

NASA Associate Administrator for Space Flight Joseph Rothenberg addresses attendees at a ribbon cutting for the new Checkout and Launch Control System (CLCS) at the Hypergolic Maintenance Facility (HMF). The CLCS was declared operational in a ribbon cutting ceremony earlier. The new control room will be used to process the Orbital Maneuvering System pods and Forward Reaction Control System modules at the HMF. This hardware is removed from Space Shuttle orbiters and routinely taken to the HMF for checkout and servicing.

Developing Ionic Liquid Know-How for the Design of Modular Functionality, Versatile Platforms, and New Synthetic Methodologies for Energetic Materials

DTIC Science & Technology

2013-12-05

Protocol for the Synthesis of Alkylated Imidazolium Salt Derivatives 1,3-Dimethylimidazolium chloride (1,3-diMe-IM][Cl]) (19c) and 1,2,3...C5’). A8. Hypergolic Ionic Liquids to Mill, Suspend, and Ignite Boron Nanoparticles Synthesis of 1-Butyl-3-methylimidazolium chloride ([1-Bu...3-methylimidazolium chloride , 5[Cl] D5. Zinc-assisted synthesis of imidazolium-tetrazolate bi-heterocyclic zwitterions with variable alkyl

Space shuttle hypergolic bipropellant RCS engine design study, Bell model 8701

NASA Technical Reports Server (NTRS)

1974-01-01

A research program was conducted to define the level of the current technology base for reaction control system rocket engines suitable for space shuttle applications. The project consisted of engine analyses, design, fabrication, and tests. The specific objectives are: (1) extrapolating current engine design experience to design of an RCS engine with required safety, reliability, performance, and operational capability, (2) demonstration of multiple reuse capability, and (3) identification of current design and technology deficiencies and critical areas for future effort.

A New Solid/Liquid Hypergolic System: 3-amino-1,2,4-triazine and Nitric Acid

DTIC Science & Technology

2016-04-01

PROGRAM ELEMENT NUMBER 6. AUTHOR(S) William M Sherrill, William M Sickels, Eric J Bukowski, Eric C Johnson, and Joseph E Banning 5d. PROJECT ...on an Anasazi Instruments 90 MHz NMR. Dimethyl sulfoxide (DMSO)-D6 was obtained from Sigma -Aldrich and used as received. All NMR chemical shifts...were obtained from Sigma -Aldrich and were used as received. Approved for public release; distribution is unlimited. 7 5.2 Synthesis of 3-amino

United States Air Force Summary (Consolidation of Statistical Digest and USAF Summary), Ninth Edition

DTIC Science & Technology

1983-01-01

MARIANA ISLS ,..•o 8 GUAM .. o ANDERSEN AFB ,. BONIN ISLSo o o I) . o • ... .... t gO 6 ~,... ()0 KAitENA AB i"r o EAST CHINA SEA • ~. USAF MAJOR... Dave (OK) Hertel, Denni s M. (MI) Price, Melvin (IL) Bennett, Charles E. (FL) Military Personnel & Compensation Mitche 11 , Donal d J. (NY) Holt...Schroeder, Patricia (CO) Stump, Bob (AZ) Skelton, Ike (MO) Leath, James M. (TX) McCurdy, Dave (OK) Smith, Joseph F. (PA) TABLE 81 (Cont I d

Myrtle Beach AFB South Carolina. Revised Uniform Summary of Surface Weather Observations. Parts A-F

DTIC Science & Technology

1975-07-03

DATA PROCESSING BRNCm2 TAC/USAF SURFACE WINDS AIP wATHER SERVIC/?AL PERCENTAGE FREQUENCY OF WIND DIRECTION AND SPEED (FROM HOURLY OBSERVATIONS...TRANS MONI, ALL WATHER 1200-1400 CLAM MUES (L.$,t.) ( CONDITION SPEED MEAN (KNTS) i’ 4-6 7. 10 11. 16 17.21 22 .27 28 . 33 34.40 41 .47 48 • !5 ;t56...PRUCESSING BRANCH 2ETAC/USAF SURFACE WINDSAIR wATHER SERVICE/MAC PERCENTAGE FREQUENCY OF WIND DIRECTION AND SPEED (FROM HOURLY OBSERVATIONS) 13717

A Qualitative Study of the European Trucking Industry and Logistics Strategies Using the United States Motor Carrier Industry as a Guide

DTIC Science & Technology

1992-09-01

UNITED STATES MOTOR CARRIER INDUSTRY AS A GUIDE THESIS David W. Butler Andrew P. Wilhelm Captain, USAF Captain, USAF AFIT/GLM/LSM/92S-7 Approved for...UNITED STATES MOTOR CARRIER INDUSTRY AS A GUIDE THESIS Presented to the Faculty of the School of Systems and Logistics of the Air Force Institute of...THE EUROPEAN TRUCKING INDUSTRY AND LOGISTICS STRATEGIES USING THE UNITED STATES MOTOR CARRIER INDUSTRY AS A GUIDE I. Introduction General Issue The

1. Credit USAF, 1943. Original housed in the Photograph Files, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

1. Credit USAF, 1943. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. View west showing eastern elevation of wooden hangar while under construction. Building 4401 was also historically designated Hangar No. 1. The north side of the Unicon Portable Hangar (Building 4305) appears at the extreme left of the view. Concrete apron is under construction in the foreground. Building 4402 is same design and construction as Building 4401. - Edwards Air Force Base, North Base, Hangar No. 1, First & B Streets, Boron, Kern County, CA

Credit USAF, 7 September 1945. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF, 7 September 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Photo captioned "Oblique view of Recreation Hall/Chapel Bldg. T73." Movies on marquee were "Why Girls Leave Home" and "Blazing the Western Trail." View looks west from camera position across E Street - Edwards Air Force Base, North Base, Recreation Hall & Chapel T-73, E Street near North Base Road, Boron, Kern County, CA

Credit USAF, ca. 1945. Original housed in the Muroc Flight ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF, ca. 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View looks north at a hutment typical of several structures erected at the Muroc Flight Test Base (North Base) ca. 1943-1945. Similar structures, Buildings T-61, T-62 and T-63, lie in the distance behind T-40 - Edwards Air Force Base, North Base, Barracks T-40, Second & A Streets, Boron, Kern County, CA

Credit USAF, ca. 1943. Original housed in the Muroc Flight ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Credit USAF, ca. 1943. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Historic view looking northeast along southeast edge of swimming pool during construction. The wavy edge of the pool visible here remains as a ground surface feature in 1995. Building in the background is the second Bachelor Officers' Quarters (T-15) built in 1943 - Edwards Air Force Base, North Base, Swimming Pool, Second Street, Boron, Kern County, CA

USAF bioenvironmental noise data handbook. Volume 148. T-37B in-flight crew noise

NASA Astrophysics Data System (ADS)

Hille, H. K.

1981-11-01

The T-37B is a USAF two-seat primary trainer aircraft. This report provides measured data defining the bioacoustic environments at flight crew/passenger locations inside this aircraft during normal flight operations. Data are reported at one location for 19 different flight conditions and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors.

8. Credit USAF, ca. 1952. Original housed in the Photograph ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

8. Credit USAF, ca. 1952. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. Oblique low-level aerial view of North Base looking northeast. Based on positions and types of aircraft and automobiles, this photo taken same day as HAER photo CA-170-7. Most temporary structures in this view have been demolished with the exception of the hangars. The concrete foundations remain of many structures, while no trace was found of others. - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

A Study of the Relationship between Years of Commissioned Service and the Perceived Importance of the Military Compensation Package to Air Force Officers.

DTIC Science & Technology

1984-09-01

OF’ COMMISSIONED SERVICE AND THE PERCEIVED IMPORTANCE OF THE MILITARY COMPENSATION PACKAGE TO AIR FORCE OFFICERS THESIS Daniel A. Ovelbar Captain, USAF... THESIS Daniel A. Cvelbar Captain, USAF AFI T/GSM/LSY/84S-8 DTICSLECTE3 Approved for public release; distribution unlimited The contents of the document...OF THE MILITARY COMPENSATION PACKAGE TO AIR FORCE OFFICERS THESIS Presented to the Faculty of the School of Systems and Logistics of the Air Force

A Study to Demonstrate the Application of a Graphical Method to Determine an Optimal Maintenance Task Interval for an Item in Air Force Inventory.

DTIC Science & Technology

1982-09-01

SCHOOL OF SYST.. U14CLASSIFIED D C BECKWITH ET AL. SEP 82 AFIT-LSSR- 60 -82 F/ 5/1 NLI IIIIIIIIIIIIIIlfflfflf IIIIIIIIIIIIIIfllfllf IIIIIIIIIIIIIIl...Beckwith, Captain, USAF Anthony R. Roclevitch, Captain, USAF LSSR 60 -82 j1 -’~ The contents of the document are technically accurate, and no sensitive...Force, or the Department of Defense. II AFIT Control Number LSSR 60 -82 AFIT RESEARCH ASSESSMENT The purpose of this questionnaire is to determine the

The Continued Need for USAF Light Attack post OEF/OIF: A Survey of West African Infrastructure to Support Tactical Air Operations

DTIC Science & Technology

2013-04-01

Mauritania’s two main airfields, at Nouakchott and Atar , have 9,800 foot runways that A-10s could operate from. In addition to those airfields...running road passes through Atar , Zouerat and Bir Moghrein on the way to Algeria. Without the use of the bases at Zouerat and Bir Moghrein the highway...runs almost 400 miles beyond extended duration air support from Atar . With the legacy platforms currently available, the USAF could provide air

A New Facility Design and Work Method for the Quantitative Fit Testing Laboratory

DTIC Science & Technology

1989-05-01

AtRV=’Uk kUB C RELEASEIW R190 I ERNEST A. HAYGOOD, 1st Lt, USAF Executive Officer, Civilian Institution Proarams 17. COSATI CODES 18. SUBJECT TERMS...22. NAME O RESPONSIBLE INDIVIDUAL 22b. TELEPHONE (Mdud. e Cd) 22c. OFFICE SYMBOL ERNEST A. HAYGOOD, lst Lt, USAF (513) 255-2259 A AFIT/CI DO Form 1473...Morgan et al. C1963) define a link as "any connection between a man and a machine or between one man and another" (p. 322). Lippert [1971) studied the

Flag and Footprints Mission Mars: Preliminary Design Review Two

NASA Astrophysics Data System (ADS)

1998-01-01

SMI has developed a preliminary guideline for a flag and footprints manned mission to Mars. The manned mission is a split mission where the return and ground supplies will be sent on a cargo spacecraft. The crew spacecraft will leave on a high-energy trajectory once the cargo spacecraft has arrived in the prescribed orbit about Mars. The trajectory will be approximately 150-day from Low Earth Orbit (LEO) to the prescribed rendezvous orbit. The crew spacecraft will then dock with the orbiting cargo spacecraft for refuel and resupply. In addition, once safely docked, the crew members will transfer to the Mars Excursion Vehicle (MEV) for transport to the Martian surface. Each vehicle will be equipped with all necessary subsystems. To facilitate the transport of a large payload from Earth to Mars, the cargo spacecraft will utilize Ion propulsion. The Ion propulsion is ideal due to the high Isp characteristics. The crew spacecraft will be propelled with high-thrust RL-10 engines. Due to the smaller mass of the crew spacecraft, the spacecraft will utilize a 150-day high-energy trajectory. The MEV propulsion will be hypergolic. This choice of fuel is due to the reliability and simplicity of use. The crew members will stay on the surface of Mars for 30-days. During the 30-days, the crew will perform a series of scientific and exploratory experiments. To broaden the astronauts range of exploration, the astronauts will have access to three Unmanned Aerial Vehicles (UAV) and one rover while on the surface. The scientific experiments will consist of several soil and rock analyses as well as atmospheric study. Upon completion of the 30-day ground phase, the astronauts will return to the orbiting crew ship for return to Earth. SMI's flag and footprints mission outlines the fundamental systems and general requirements for these systems. SMI feels that with the fulfillment of these fundamental systems, this mission will be a highly desirable and potential candidate for development by NASA.

Increased flight surgeon role in military aeromedical evacuation.

PubMed

Lyons, T J; Connor, S B

1995-10-01

Physicians were involved in the development of aeromedical evacuation (medevac) and flight surgeons flew as crewmembers on the first U.S. military medevac flights. However, since World War II flight surgeons have not been routinely assigned to operational medevac units. The aeromedical literature addressing the role of physicians in medevac is controversial. Recent contingencies involving the U.S. Air Force (USAF) have required the augmentation of medevac units with flight surgeons. Beginning in 1992, the United States Air Forces Europe (USAFE) assigned three flight surgeons to the medevac squadron. Between 2 February 1993 and 24 March 1994 USAFE moved 241 patients on 29 missions out of the former Yugoslavia--most of these missions had a flight surgeon on the crew. Because advance medical information on the status of these patients is often nonexistent, the presence of a physician on the crew proved life-saving in some instances. In peacetime operations, there has been a recent trend in the European theater for the USAF to move more unstable patients. Dedicated medevac flight surgeons have proven to have the specific experience and training to perform effectively in the role of in-flight medical attendant. In addition, they are effective in negotiating with referring physicians about the urgency of movement, required equipment, the need for medical attendants, etc. These flight surgeons also provide medical coverage of transiting patients in the Aeromedical Staging Flight (ASF), thus providing needed continuity in the medevac system. Dedicated medevac flight surgeons fill a unique and valuable role in medevac systems. Agencies with medevac units should consider assigning flight surgeons to these units.

Twenty-Seven-Year Follow-Up of Vietnam Air War USAF POWs and Matched Controls Not Captured: A Qualitative Study.

PubMed

Sledge, William; Rozanova, Julia; Dorset, Julianne

2018-01-01

To provide a follow up of a 1976 study of the impact of captivity on U.S. Air Force (USAF) POWs and USAF Controls matched for time in Southeast Asia, military rank and aircraft crew position. Qualitative study of replies to open ended questions of positive and negative changes due to their captivity/combat experiences made by participants (POWs and Controls) who replied in both 1976 and in 2003. Both groups acknowledged positive and negative effects of the experiences in 1976. In 1976 and 2003 the POWs mainly reported negative effects on career and family domains but positive effects of individual development and growth. Controls reported mild negative effects on family in 1976, and benefits to their careers and sense of self in both 1976 and 2003. Captivity during the Vietnam War for USAF included two types of extreme duress which were the incarceration itself; and the repatriation experience which entailed re-assimilation despite loss of occupation and disrupted families. Despite these obstacles, POWs exhibited substantial resilience in achieving self-growth and how they regarded themselves psychologically in comparison to their matched control fellow aviators who while also suffering a lesser separation from family, tended to prosper in their careers and were proud of their accomplishments. Long term separation from work, family and friends and the inability to return to their families and careers with the effectiveness demanded by their ambition were a more devastating ongoing consequence of their captivity than the immediate suffering of their imprisonment.

Mechanisms of flag-football injuries reported to the HQ Air Force Safety Center a 10-year descriptive study, 1993-2002.

PubMed

Burnham, Bruce R; Copley, G Bruce; Shim, Matthew J; Kemp, Philip A; Jones, Bruce H

2010-01-01

Flag (touch or intramural) football is a popular sport among the U.S. Air Force (USAF) active duty population and causes a substantial number of lost-workday injuries. The purpose of this study is to describe the mechanisms of flag-football injuries to better identify effective countermeasures. The data were derived from safety reports obtained from the USAF Ground Safety Automated System. Flag-football injuries for the years 1993-2002 that resulted in at least one lost workday were included in the study conducted in 2003. Narrative data were systematically reviewed for 32,812 USAF mishap reports; these were then coded in order to categorize and summarize mechanisms associated with flag football and other sports and occupational injuries. Nine hundred and forty-four mishap reports involving active duty USAF members playing flag football met the criteria for inclusion into this study. Eight mechanisms of injury were identified. The eight mechanisms accounted for 90% of all flag-football injuries. One scenario (contact with another player) accounted for 42% of all flag-football injuries. The most common mechanisms of injury caused by playing flag football can be identified using the detailed information found in safety reports. These scenarios are essential to developing evidence-based countermeasures. Results for flag football suggest that interventions that prevent player contact injuries deserve further research and evaluation. The broader implications of this study are that military safety data can be used to identify potentially modifiable mechanisms of injury for specific activities such as flag football. Published by Elsevier Inc.

Urinary Polycyclic Aromatic Hydrocarbon (OH-PAH) Metabolite Concentrations and the Effect of GST Polymorphisms Among US Air Force Personnel Exposed to Jet Fuel

PubMed Central

Rodrigues, Ema G.; Smith, Kristen; Maule, Alexis L.; Sjodin, Andreas; Li, Zheng; Romanoff, Lovisa; Kelsey, Karl; Proctor, Susan; McClean, Michael D.

2016-01-01

Objective To evaluate the association between inhalation exposure to jet propulsion fuel 8 (JP-8) and urinary metabolites among US Air Force (USAF) personnel, and investigate the role of glutathione S-transferase polymorphisms. Methods Personal air samples were collected from 37 full-time USAF personnel during 4 consecutive workdays and analyzed for JP-8 constituents and total hydrocarbons. Pre- and postshift urine samples were collected each day and analyzed for polycyclic aromatic hydrocarbon urinary metabolites. Results Work shift exposure to total hydrocarbons was significantly associated with postshift urinary 1-naphthol (β = 0.17; P = <0.0001), 2-naphthol (β = 0.09; P = 0.005), and 2-hydroxyfluorene concentrations (β = 0.08; P = 0.006), and a significant gene-environment interaction was observed with glutathione S-transferase mu-1. Conclusions USAF personnel experience inhalation exposure to JP-8, which is associated with absorption of JP-8 constituents while performing typical job-related tasks, and in our data the glutathione S-transferase mu-1 polymorphism was associated with differential metabolism of naphthalene. PMID:24806557

Urinary polycyclic aromatic hydrocarbon (OH-PAH) metabolite concentrations and the effect of GST polymorphisms among US Air Force personnel exposed to jet fuel.

PubMed

Rodrigues, Ema G; Smith, Kristen; Maule, Alexis L; Sjodin, Andreas; Li, Zheng; Romanoff, Lovisa; Kelsey, Karl; Proctor, Susan; McClean, Michael D

2014-05-01

To evaluate the association between inhalation exposure to jet propulsion fuel 8 (JP-8) and urinary metabolites among US Air Force (USAF) personnel, and investigate the role of glutathione S-transferase polymorphisms. Personal air samples were collected from 37 full-time USAF personnel during 4 consecutive workdays and analyzed for JP-8 constituents and total hydrocarbons. Pre- and postshift urine samples were collected each day and analyzed for polycyclic aromatic hydrocarbon urinary metabolites. Work shift exposure to total hydrocarbons was significantly associated with postshift urinary 1-naphthol (β = 0.17; P = <0.0001), 2-naphthol (β = 0.09; P = 0.005), and 2-hydroxyfluorene concentrations (β = 0.08; P = 0.006), and a significant gene-environment interaction was observed with glutathione S-transferase mu-1. USAF personnel experience inhalation exposure to JP-8, which is associated with absorption of JP-8 constituents while performing typical job-related tasks, and in our data the glutathione S-transferase mu-1 polymorphism was associated with differential metabolism of naphthalene.

Women in Combat Pros and Cons

DTIC Science & Technology

1988-04-01

and Cons . Major Thomas H. Cecil 88-0490 "--"insights into tomorrou,"’ ..v- A A 0 PtY-i f(.> i’I,-:::x:’~ --pcr~ j.~ ~~* --. -- iiV • DISCLAIMER The...k. r- r,’ I’. REPORT NUMBER 88-0490 TITLE WOMEN IN COMBAT-PROS AND CONS AUTHOR(S) MAJOR THOMAS H. CEC-IL, USAF -% FACULTY ADVISOR CH, LT COL DAVID W...NUMBERS 11 TITLE (include Security Classification) WOMEN IN COMBAT--PROS AND CONS 12. PERSON4AL AUTHOR(S) Cecil, Thomas H1., Major, USAF 9a YýOF REPORT

Anthropometric accommodation in USAF cockpits

NASA Technical Reports Server (NTRS)

Zehner, Gregory F.

1994-01-01

Over the past three years, a new set of methodologies has been developed to specify and evaluate anthropometric accommodation in USAF crewstation designs. These techniques are used to improve the ability of the pilot to reach controls, to safely escape the aircraft, to achieve adequate mobility and comfort, and to assure full access to the visual field both inside and outside the aircraft. This paper summarized commonly encountered aircraft accommodation problems, explains the failure of the traditional 'percentile man' design concept to resolve these difficulties, and suggests an alternative approach for improving cockpit design to better accommodate today's more heterogeneous flying population.

10. Credit USAF, 1945. Original housed in the Muroc Flight ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

10. Credit USAF, 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View of jet engine rotor balancing machine with engine rotor in place for balancing operations. Original caption reads "Balancing bucket wheel of jet engine, Muroc Flight Test Base, Oct. 1945"; personnel not identified. Location where photograph was taken not determined, but presumed to be in shops of Building 4505. - Edwards Air Force Base, North Base, Hangar, End of North Base Road, Boron, Kern County, CA

United States Air Force F-35A Operational Basing Environmental Impact Statement. Appendix E: Comments

DTIC Science & Technology

2013-09-01

Germanos, Nicholas M Civ USAF HQ ACC/A7NS From: Sent: To: Subject: Hi Leo Ioannou Wednesday, July 10, 2013 11:28 AM Germanos, Nicholas M Civ USAF HQ...we have them here . And the F35s, even if they are louder, I would not mind them either. Remember . Keep the F35s coming. SOUND OF FREEDOM Leo ...34 Explaining further, Reuters reported that: uThose a re the dates that Loc kheed Martin’s F-35 will achieve <http://articles.chicagotribune.com/2013-05

Advanced propulsion for LEO and GEO platforms

NASA Technical Reports Server (NTRS)

Sovey, James S.; Pidgeon, David J.

1990-01-01

Mission requirements and mass savings applicable to specific low earth orbit and geostationary earth orbit platforms using three highly developed propulsion systems are described. Advanced hypergolic bipropellant thrusters and hydrazine arcjets can provide about 11 percent additional instrument payload to 14,000 kg LEO platforms. By using electric propulsion on a 8,000 kg class GEO platform, mass savings in excess of 15 percent of the beginning-of-life platform mass are obtained. Effects of large, advanced technology solar arrays and antennas on platform propulsion requirements are also discussed.

Condition Based vs. Time Based Maintenance: Case Study on Hypergolic Pumps

NASA Technical Reports Server (NTRS)

Gibson, Lewis J.

2007-01-01

Two Pad 39B Ox pumps were monitored with the Baker Instruments Explorer Motor tester. Using the torque spectrum it was determined that Ox pump #2 had a significant peak at a frequency, which indicated lubricant fluid whirl. Similar testing on Ox pump #1 didn't indicate this peak, an indication that this pump was in good mechanical condition. Subsequent disassembly of both motors validated these findings. Ox pump #2 rear bearing showed significant wear, the front bearing showed little wear. Ox pump #1 was still within manufacturers tolerances.

Recent Developments in the Field of Energetic Ionic Liquids

DTIC Science & Technology

2014-10-07

tetranitroaniline RDX 14,18,19,21 1,3,5-trinitro-1,3,5- triazacyclohexane PETN 14,15,21 [3-nitrooxy-2,2-bis(nitro oxymethyl) propyl ] nitrate CL20 21-25...was then proved to play a vital role since the chloride precursor (2a) was also found to be hypergolic. Therefore, the 45 anion is not solely... Synthesis , 1977, 1, 1. 91 C. D. Hurd, L. F. Audrieth and L. A. Nalefski, Inorganic Syntheses, ed. H. S. Booth, McGraw-Hill Book Company Inc., New York

A study for hypergolic vapor sensor development

NASA Technical Reports Server (NTRS)

Stetter, J. R.

1977-01-01

The use of an electrochemical technique for MMH and N02 measurement was investigated. Specific MMH and N02 electrochemical sensors were developed. Experimental techniques for preparation, handling, and analysis of hydrazine's vapor mixtures at ppb and ppm levels were developed. Two approaches to N02 instrument design were evaluated including specific adsorption and specific electrochemical reduction. Two approaches to hydrazines monitoring were evaluated including catalytic conversion to N0 with subsequent N0 detection and direct specific electrochemical oxidation. Two engineering prototype MMH/N02 monitors were designed and constructed.

Hypergol Maintenance Facility Hazardous Waste South Staging Areas, SWMU 070

NASA Technical Reports Server (NTRS)

Wilson, Deborah M.; Miller, Ralinda R.

2015-01-01

The purpose of this CMI Year 9 AGWMR is to present the actions taken and results obtained during the ninth year of implementation of Corrective Measures (CM) at HMF. Groundwater monitoring activities were conducted in accordance with the CMI Work Plan (Tetra Tech, 2005a) and CMI Site-Specific Safety and Health Plan (Tetra Tech, 2005b). Groundwater monitoring activities detailed in this Year 9 report include pre-startup sampling in February 2014(prior to restarting the air sparging system) and quarterly performance monitoring in March, July, and September 2014.

Demographic, Lifestyle Factors, and Reasons for Use of Dietary Supplements by Air Force Personnel.

PubMed

Austin, Krista G; Price, Lori Lyn; McGraw, Susan M; Leahy, Guy; Lieberman, Harris R

2016-07-01

Dietary supplement (DS) use is common among U.S. Army personnel to purportedly improve health, provide energy, and increase strength. However, a comprehensive analysis of DS use among U.S. Air Force (USAF) personnel has not been conducted using the same survey instrument, which would permit direct comparisons to DS use by Army personnel. A standardized questionnaire was used to assess DS use, demographic factors, and reasons for use of DS by USAF personnel (N = 1750). Logistic regression models adjusted for age, sex, and rank were used to determine relationships among categories of DS (multivitamin and multimineral, individual vitamins and minerals, protein/amino acid supplements, combination products, herbal supplements, purported steroid analogs, and other) and demographic factors. Findings were compared to reports from other military services and civilian populations. DS were used by 68% of USAF personnel: 35% used 1-2 DS ≥ 1 time/wk, 13% 3-4 DS ≥ 1 time/wk, and 20% ≥ 5 DS ≥ 1 time/wk. There were 45% of personnel who used a multivitamin and mineral, 33% protein supplements, 22% individual vitamins/minerals, 22% combination products, and 7% herbals. Logistic regression demonstrated aerobic exercise duration and strength training were associated with increased DS use. Individuals who previously deployed were more likely to use DS. Like Army personnel, college students and athletes, USAF personnel use more DS than the general population and are more likely to use purported performance enhancing DS, such as protein supplements, and concurrently consume multiple DS. Austin KG, Price LL, McGraw SM, Leahy G, Lieberman HR. Demographic, lifestyle factors, and reasons for use of dietary supplements by Air Force personnel. Aerosp Med Hum Perform. 2016; 87(7):628-637.

Using the Freiburg Acuity and Contrast Test to measure visual performance in USAF personnel after PRK.

PubMed

Dennis, Richard J; Beer, Jeremy M A; Baldwin, J Bruce; Ivan, Douglas J; Lorusso, Frank J; Thompson, William T

2004-07-01

Photorefractive keratectomy (PRK) may be an alternative to spectacle and contact lens wear for United States Air Force (USAF) aircrew and may offer some distinct advantages in operational situations. However, any residual corneal haze or scar formation from PRK could exacerbate the disabling effects of a bright glare source on a complex visual task. The USAF recently completed a longitudinal clinical evaluation of the long-term effects of PRK on visual performance, including the experiment described herein. After baseline data were collected, 20 nonflying active duty USAF personnel underwent PRK. Visual performance was then measured at 6, 12, and 24 months after PRK. Visual acuity (VA) and contrast sensitivity (CS) data were collected by using the Freiburg Acuity and Contrast Test (FrACT), with the subject viewing half of the runs through a polycarbonate windscreen. Experimental runs were completed under 3 glare conditions: no glare source and with either a broadband or a green laser (532-nm) glare annulus (luminance approximately 6090 cd/m) surrounding the Landolt C stimulus. Systematic effects of PRK on VA relative to baseline were not identified. However, VA was almost 2 full Snellen lines worse with the laser glare source in place versus the broadband glare source. A significant drop-off was observed in CS performance after PRK under conditions of no glare and broadband glare; this was the case both with and without the windscreen. As with VA, laser glare disrupted CS performance significantly and more than broadband glare did. PRK does not appear to have affected VA, but the changes in CS might represent a true decline in visual performance. The greater disruptive effects from laser versus broadband glare may be a result of increased masking from coherent spatial noise (speckle) surrounding the laser stimulus.

X-43C Flight Demonstrator Project Overview

NASA Technical Reports Server (NTRS)

Moses, Paul L.

2003-01-01

The X-43C Flight Demonstrator Project is a joint NASA-USAF hypersonic propulsion technology flight demonstration project that will expand the hypersonic flight envelope for air-breathing engines. The Project will demonstrate sustained accelerating flight through three flights of expendable X-43C Demonstrator Vehicles (DVs). The approximately 16-foot long X-43C DV will be boosted to the starting test conditions, separate from the booster, and accelerate from Mach 5 to Mach 7 under its own power and autonomous control. The DVs will be powered by a liquid hydrocarbon-fueled, fuel-cooled, dual-mode, airframe integrated scramjet engine system developed under the USAF HyTech Program. The Project is managed by NASA Langley Research Center as part of NASA's Next Generation Launch Technology Program. Flight tests will be conducted by NASA Dryden Flight Research Center off the coast of California over water in the Pacific Test Range. The NASA/USAF/industry project is a natural extension of the Hyper-X Program (X-43A), which will demonstrate short duration (approximately 10 seconds) gaseous hydrogen-fueled scramjet powered flight at Mach 7 and Mach 10 using a heavy-weight, largely heat sink construction, experimental engine. The X-43C Project will demonstrate sustained accelerating flight from Mach 5 to Mach 7 (approximately 4 minutes) using a flight-weight, fuel-cooled, scramjet engine powered by much denser liquid hydrocarbon fuel. The X-43C DV design flows from integrating USAF HyTech developed engine technologies with a NASA Air-Breathing Launch Vehicle accelerator-class configuration and Hyper-X heritage vehicle systems designs. This paper describes the X-43C Project and provides the background for NASA's current hypersonic flight demonstration efforts.

Asymptomatic Wolff-Parkinson-White Pattern ECG in USAF Aviators.

PubMed

Davenport, Eddie D; Rupp, Karen A N; Palileo, Edwin; Haynes, Jared

2017-01-01

Wolff-Parkinson-White (WPW) pattern is occasionally found in asymptomatic aviators during routine ECGs. Aeromedical concerns regarding WPW pattern include risk of dysrhythmia or sudden cardiac death (SCD), thus affecting the safety of flight. The purpose of this study was to determine the prevalence and outcomes of aviators with asymptomatic WPW pattern and assess for risk factors that contribute to progression to dysrhythmia or symptoms. The U.S. Air Force (USAF) ECG library database containing over 1.2 million ECGs collected over the past 68 yr was used to identify 638 individual aviators with WPW pattern. Demographic, medical history, and outcome data were obtained by medical record review. Aviators who developed high risk features defined as symptoms, arrhythmia, or ablation of a high risk pathway, were compared to those who remained asymptomatic. Prevalence of WPW pattern was 0.30% among all USAF aviators. Of the 638 individuals, 64 (10%) progressed to the combined endpoint of SCD, arrhythmia, and/or ablation of a high risk pathway over 6868 patient years, with average follow-up of 10.5 yr. There were two sudden cardiac deaths (0.3%). Annual risk of possible sudden incapacitation was 0.95% and of SCD 0.03%. Those that progressed to high risk were significantly younger, had lower diastolic blood pressure, lower total cholesterol, and better physical fitness testing scores. WPW pattern on ECG found in asymptomatic aviators confers < 1% annual risk of arrhythmia or incapacitating events with the highest risk in the younger, healthier, and most fit populations.Davenport ED, Rupp KAN, Palileo E, Haynes J. Asymptomatic Wolff-Parkinson-White pattern ECG in USAF aviators. Aerosp Med Hum Perform. 2017; 88(1):56-60.

Seventh Annual Workshop on Space Operations Applications and Research (SOAR 1993), volume 2

NASA Technical Reports Server (NTRS)

Krishen, Kumar (Editor)

1994-01-01

This document contains papers presented at the Space Operations, Applications and Research Symposium (SOAR) Symposium hosted by NASA/Johnson Space Center (JSC) and cosponsored by NASA/JSC and U.S. Air Force Materiel Command. SOAR included NASA and USAF programmatic overviews, plenary session, panel discussions, panel sessions, and exhibits. It invited technical papers in support of U.S. Army, U.S. Navy, Department of Energy, NASA, and USAF programs in the following areas: robotics and telepresence, automation and intelligent systems, human factors, life support, and space maintenance and servicing. SOAR was concerned with Government-sponsored research and development relevant to aerospace operations.

United States Air Force Statistical Digest, Fiscal Year 1964, Nineteenth Edition

DTIC Science & Technology

1964-09-30

opera- tions, materiel, personnel, training, medical serv- ices, finance, security and law enforcement, fa- cilities, transportation , Military...RTER. AND HOUR. FI..OWN DURING QU"’RTER. By COMM"’ND, WORL.D-WIOE - FY 1964 AGE (IN MONTHlJ) D,.TRIBUTION 0.- USAF A,RCR...FT By MI •• ION, DE . ION. AHD...WOfl ....D_wIOE - 30 JUN 1964 • • • • • • • • • • • • • • • • • • • • • •••••• USAF AND COMPONENT A,RCR.....T G...,NS AND LoasEs By MI •• roN. DES

TRASANA. Force Stratification System User Handbook.

DTIC Science & Technology

1977-09-01

n - 4 u m W CL a 0-C C COCOc:11 7 k., 0 =. t.4 c-Ac( ~ lqa . U~ ~~~~~ p. c A? W 0=0 ’. 0 a - 0 - EO U=ON~.S4’ o S .0 p. . 0 0 0 ’ ft 0 LO Cl O.CCL. . k...ADGRU, USAF Institute of Technology I Chief, ADGRU, US Naval War College 1 Chief, US Elm, USAF Air-Ground Operations School 1 USA Rep, USMC Educ Cen...Marine Corps Dev and Educ Command I USA Rep, Comb Svc Spt Prog School, Atlantic I Commandant, USA Element, School of Music 1 Liaison Offices/Officers

5. Credit USAF, ca. 1944. Original housed in the Muroc ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

5. Credit USAF, ca. 1944. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. Interior view of hangar, looking north northwest. Note exposed wooden construction. Two jet engines lie partially concealed by tarpaulins in the background, along with a combustion chamber assembly (horizontal cylinders in a circular array). On the workbench in the foreground lie an engine rotor hub and what appears to be an engine fuel line assembly. - Edwards Air Force Base, North Base, Hangar No. 1, First & B Streets, Boron, Kern County, CA

7. Credit USAF, ca. 1952. Original housed in the Photograph ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

7. Credit USAF, ca. 1952. Original housed in the Photograph Files, AFFTC/HO, Edwards AFB, California. Oblique aerial view of North Base AFFTC (Air Force Flight Test Center) looking west northwest. The flight line at the edge of Rogers Dry Lake appears in the foreground, served by the facility's four hangars. Temporary structures beyond the hangars were demolished later in the 1950s. The fence that formerly surrounded the swimming pool in earlier photos has been taken down. In the distance lies the Jet Propulsion Laboratory Edwards Test Station, in its pre-1953 configuration. - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

Sixth Annual Workshop on Space Operations Applications and Research (SOAR 1992), volume 2

NASA Technical Reports Server (NTRS)

Krishen, Kumar (Editor)

1993-01-01

This document contains papers presented at the Space Operations, Applications, and Research Symposium (SOAR) hosted by the U.S. Air Force (USAF) on 4-6 Aug. 1992. The symposium was cosponsored by the Air Force Material Command and by NASA/JSC. Key technical areas covered during the symposium were robotics and telepresence, automation and intelligent systems, human factors, life sciences, and space maintenance and servicing. The SOAR differed from most other conferences in that it was concerned with Government-sponsored research and development relevant to aerospace operations. Symposium proceedings include papers covering various disciplines presented by experts from NASA, the USAF, universities, and industry.

X-15 test pilots - in a lighter mood

NASA Technical Reports Server (NTRS)

1966-01-01

The X-15 pilots clown around in front of the #2 aircraft.From left to right: USAF Capt. Joseph Engle, USAF Maj. Robert Rushworth, NASA test pilot John 'Jack' McKay, USAF Maj. William 'Pete' Knight, NASA test pilot Milton Thompson, and NASA test pilot William Dana. First flown in 1959 from the NASA High Speed Flight Station (later renamed the Dryden Flight Research Center), the rocket powered X-15 was developed to provide data on aerodynamics, structures, flight controls and the physiological aspects of high speed, high altitude flight. Three were built by North American Aviation for NASA and the U.S. Air Force. They made a total of 199 flights during a highly successful research program lasting almost ten years, following which its speed and altitude records for winged aircraft remained unbroken until the Space Shuttle first returned from earth orbit in 1981. The X-15's main rocket engine provided thrust for the first 80 to 120 seconds of a 10 to 11 minute flight; the aircraft then glided to a 200 mph landing. The X-15 reached altitudes of 354,200 feet (67.08 miles) and a speed of 4,520 mph (Mach 6.7).

Aircraft and related factors in crashes involving spatial disorientation: 15 years of U.S. Air Force data.

PubMed

Lyons, Terence J; Ercoline, William; O'Toole, Kevin; Grayson, Kevin

2006-07-01

Previous studies have determined that spatial disorientation (SD) causes 0.5-23% of aircraft crashes, but SD-related crash and fatality rates in different aircraft types have not been systematically studied. SD crashes for the fiscal years 1990 to 2004 and aircraft sortie numbers for all U.S. Air Force (USAF) aircraft were obtained from the USAF Safety Center. Contingency table analysis and Chi-squared tests were used to evaluate differences in SD rates. SD accounted for 11% of USAF crashes with an overall rate of 2.9 per million sorties and a crash fatality rate of 69%. The SD rate was higher in fighter/attack aircraft and helicopters than in training and transport aircraft. The risk of SD was increased at night with 23% of night crashes being caused by SD. But the SD rate and crash fatality rate were not higher in single-crewmember aircraft. SD risk is significantly increased in helicopters and fighter/attack aircraft and at night. The data suggest that a second crewmember does not protect against SD. Further study of specific SD scenarios could lead to focused interventions for SD prevention.

USAF Bioenvironmental Noise Data Handbook. Volume 160: KC-10A aircraft, near and far-field noise

NASA Astrophysics Data System (ADS)

Powell, R. G.

1982-09-01

The USAF KC-10A aircraft is an advanced tanker/cargo aircraft powered by three CF6-50C2 turbofan engines. This report provides measured and extrapolated data defining the bioacoustic environments produced by this aircraft operating on a concrete runup pad for eight engine/power configurations. Near-field data are reported for one location in a wide variety of physical and psychoacoustic measures: overall and band sound pressure levels, C-weighted and A-weighted sound levels, preferred speech interference levels, perceived noise levels, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors. Far-field data measured at 15 locations are normalized to standard meteorological conditions and extrapolated from 75-8000 meters to derive sets of equal-value contours for these same seven acoustic measures as functions of angle and distance from the source. Refer to Volume 1 of this handbook, USAF Bioenvironmental Noise Data Handbook, Vol 1: Organization, Content and Application, AMRL-TR-75-50(1) 1975, for discussion of the objective and design of the handbook, the types of data presented, measurement procedures, instrumentation, data processing, definitions of quantities, symbols, equations, applications, limitations, etc.

Reassessment of psychological distress and post-traumatic stress disorder in United States Air Force Distributed Common Ground System operators.

PubMed

Prince, Lillian; Chappelle, Wayne L; McDonald, Kent D; Goodman, Tanya; Cowper, Sara; Thompson, William

2015-03-01

The goal of this study was to assess for the main sources of occupational stress, as well as self-reported symptoms of distress and post-traumatic stress disorder among U.S. Air Force (USAF) Distributed Common Ground System (DCGS) intelligence exploitation and support personnel. DCGS intelligence operators (n=1091) and nonintelligence personnel (n = 447) assigned to a USAF Intelligence, Surveillance, and Reconnaissance Wing responded to the web-based survey. The overall survey response rate was 31%. Study results revealed the most problematic stressors among DCGS intelligence personnel included high workload, low manning, as well as organizational leadership and shift work issues. Results also revealed 14.35% of DCGS intelligence operators' self-reported high levels of psychological distress (twice the rate of DCGS nonintelligence support personnel). Furthermore, 2.0% to 2.5% self-reported high levels of post-traumatic stress disorder symptoms, with no significant difference between groups. The implications of these findings are discussed along with recommendations for USAF medical and mental health providers, as well as operational leadership. Reprint & Copyright © 2015 Association of Military Surgeons of the U.S.

14 CFR 45.13 - Identification data.

Code of Federal Regulations, 2014 CFR

2014-01-01

... any aircraft, aircraft engine, propeller, propeller blade, or propeller hub, without the approval of... paragraph (a) of this section on any aircraft, aircraft engine, propeller, propeller blade, or propeller hub... this section on any aircraft, aircraft engine, propeller, propeller blade, or propeller hub other than...

14 CFR 45.13 - Identification data.

Code of Federal Regulations, 2013 CFR

2013-01-01

... any aircraft, aircraft engine, propeller, propeller blade, or propeller hub, without the approval of... paragraph (a) of this section on any aircraft, aircraft engine, propeller, propeller blade, or propeller hub... this section on any aircraft, aircraft engine, propeller, propeller blade, or propeller hub other than...

Going Paperless

NASA Technical Reports Server (NTRS)

1999-01-01

Sentel Corporation has commercialized NASA's Electronic Portable Information Collection (EPIC) System, which stemmed from a NASA Kennedy Space Center SBIR contract. NASA and Sentel designed, built, and tested work authorization procedures used as a paperless procedures system for Space Shuttle and International Space Station payload processing operations. EPIC is now being applied to various markets including; airplane maintenance, aerospace system data management, shipbuilding industries, shipping industries, law enforcement agencies, and public utilities. KSC is planning a pilot program to use EPIC at the Hypergol Maintenance Facility. In addition, Ames Research Center and KSC are working together to apply EPIC to the area of wireless communication.

Development and Testing of Functionally Operative and Visually Appealing Remote Firing Room Displays and Applications

NASA Technical Reports Server (NTRS)

Quaranto, Kristy

2014-01-01

This internship provided an opportunity for an intern to work with NASA's Ground Support Equipment (GSE) for the Spaceport Command and Control System (SCCS) at Kennedy Space Center as a remote display developer, under NASA technical mentor Kurt Leucht. The main focus was on creating remote displays and applications for the hypergolic and high pressure helium subsystem team to help control the filling of the respective tanks. As a remote display and application developer for the GSE hypergolic and high pressure helium subsystem team the intern was responsible for creating and testing graphical remote displays and applications to be used in the Launch Control Center (LCC) on the Firing Room's computers. To become more familiar with the subsystem, the individual attended multiple project meetings and acquired their specific requirements regarding what needed to be included in the software. After receiving the requirements for the displays, the next step was to create displays that had both visual appeal and logical order using the Display Editor, on the Virtual Machine (VM). In doing so, all Compact Unique Identifiers (CUI), which are associated with specific components within the subsystem, were need to be included in each respective display for the system to run properly. Then, once the display was created it was to be tested to ensure that the display runs as intended by using the Test Driver, also found on the VM. This Test Driver is a specific application that checks to make sure all the CUIs in the display are running properly and returning the correct form of information. After creating and locally testing the display it needed to go through further testing and evaluation before deemed suitable for actual use. For the remote applications the intern was responsible for creating a project that focused on channelizing each component included in each display. The core of the application code was created by setting up spreadsheets and having an auto test generator, generate the complete code structure. This application code was then loaded and ran on a testing environment set to ensure the code runs as anticipated. By the end of the semester-long experience at NASA's Kennedy Space Center, the individual should have gained great knowledge and experience in various areas of both display and application development and testing. They were able to demonstrate this new knowledge obtained by creating multiple successful remote displays that will one day be used by the hypergolic and high pressure helium subsystem team in the LCC's firing rooms to service the new Orion spacecraft. The completed display channelization application will be used to receive verification from NASA quality engineers.

Advanced U.S. military aircraft battery systems

NASA Astrophysics Data System (ADS)

Flake, Richard A.; Eskra, Michael D.

1990-04-01

While most USAF aircraft currently use vented Ni-Cd for dc electrical power and emergency power, as well as the powering of lights and instruments prior to engine starting, these batteries have high maintenance requirements, low reliability, and no built-in testing capability with which to check battery health prior to flight. The USAF Wright R&D Center accordingly initiated its Advanced Maintenance-Free NiCd Battery System development program in 1986, in order to develop a sealed Ni-Cd battery which would remain maintenance-free over a period of three years. Attention is being given to a high power bipolar battery design in which there are no individual cell cases or cell interconnects.

Injuries and Illnesses of Vietnam War POWs Revisited. 5. Combined Service Group Risk Factors

DTIC Science & Technology

2017-11-08

provide the decision was made report both the standard F test using the Tukey post-hoc test, as well as the Welch test using the Games -Howell test for...USAF USN - USA USAF - USA Torture Mann-Whitney U < 0.001 < 0.001 0.170 Tukey HSD < 0.001 < 0.001 0.325 Games -Howell < 0.001 < 0.001 0.270 LOC months...Mann-Whitney U 0.185 < 0.001 < 0.001 Tukey HSD 0.015 0.013 0.578 Games -Howell 0.013 < 0.001 0.390 LOS weeks Mann-Whitney U < 0.001 < 0.001 0.541 Tukey

A Study of the Perceptions of Roles, Responsibilities, and Problem Areas during Facility Transition in the Military Construction Program.

DTIC Science & Technology

1987-09-01

priority based on the r sul-s of the rank order analysis of the combined USAF/COE Sa a jrouo n1 or :v.e USA’ dana qrouo. The COE data group sablisn...between the Resident Engineer and the DEEC is needed. O&M Manuals. The USAF conmnents anI concerns a bo,1t -ie &M M4ani’L3 4ere: 1. Som etnes g-ttinj the...teR-2sidJent Engineer- .ini tn- Chieff oDf Contract Man age-!n-enit ( DEEC is needed. Along the same line , onie COE comnmen t statedI that thne

3. Credit USAF, ca. 1945. Original housed in the Records ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

3. Credit USAF, ca. 1945. Original housed in the Records of the Defense Intelligence Agency. Record Group 373. National Archives. Cartographic and Architectural Branch. Washington, D.C. Aerial orthophoto map 16PS5M79-IV23 of Muroc Flight Test Base (North Base), north faces up with runway at the top and Rogers Dry Lake at the lower right. Ammunition huts (not extant in 1995) appear in a cluster just south of the west end of the runway. Note runway markings on lakebed. Linear feature at very top of image is rocket sled test track designed and built 1944-1945. - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

The Sixth Annual Workshop on Space Operations Applications and Research (SOAR 1992)

NASA Technical Reports Server (NTRS)

Krishen, Kumar (Editor)

1993-01-01

This document contains papers presented at the Space Operations, Applications, and Research Symposium (SOAR) hosted by the U.S. Air Force (USAF) on 4-6 Aug. 1992 and held at the JSC Gilruth Recreation Center. The symposium was cosponsored by the Air Force Material Command and by NASA/JSC. Key technical areas covered during the symposium were robotic and telepresence, automation and intelligent systems, human factors, life sciences, and space maintenance and servicing. The SOAR differed from most other conferences in that it was concerned with Government-sponsored research and development relevant to aerospace operations. The symposium's proceedings include papers covering various disciplines presented by experts from NASA, the USAF, universities, and industry.

6. Credit USAF, April, 1945. Original in the possession of ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

6. Credit USAF, April, 1945. Original in the possession of Ken G. Oldfield, Laguna Hills, California. View looking west across North Base flightline of XP-80s Shooting Stars undergoing accelerated service tests. HANG-N-A hangars No. 1 (Building 4401) and No. 2 (Building 4402) appear at left of view, with runway control tower (T-65, or Building 4500) at far right. Flight operations offices were in T-42 (Building 4502) at base of control tower; this structure was not extant in 1995. In the background between the control tower and Building 4402 lies T-15, officer's quarters. - Edwards Air Force Base, North Base, North Base Road, Boron, Kern County, CA

Fuel property effects on USAF gas turbine engine combustors and afterburners

NASA Technical Reports Server (NTRS)

Reeves, C. M.

1984-01-01

Since the early 1970s, the cost and availability of aircraft fuel have changed drastically. These problems prompted a program to evaluate the effects of broadened specification fuels on current and future aircraft engine combustors employed by the USAF. Phase 1 of this program was to test a set of fuels having a broad range of chemical and physical properties in a select group of gas turbine engine combustors currently in use by the USAF. The fuels ranged from JP4 to Diesel Fuel number two (DF2) with hydrogen content ranging from 14.5 percent down to 12 percent by weight, density ranging from 752 kg/sq m to 837 kg/sq m, and viscosity ranging from 0.830 sq mm/s to 3.245 sq mm/s. In addition, there was a broad range of aromatic content and physical properties attained by using Gulf Mineral Seal Oil, Xylene Bottoms, and 2040 Solvent as blending agents in JP4, JP5, JP8, and DF2. The objective of Phase 2 was to develop simple correlations and models of fuel effects on combustor performance and durability. The major variables of concern were fuel chemical and physical properties, combustor design factors, and combustor operating conditions.

Characterization of microbial contamination in United States Air Force aviation fuel tanks.

PubMed

Rauch, Michelle E; Graef, Harold W; Rozenzhak, Sophie M; Jones, Sharon E; Bleckmann, Charles A; Kruger, Randell L; Naik, Rajesh R; Stone, Morley O

2006-01-01

Bacteria and fungi, isolated from United States Air Force (USAF) aviation fuel samples, were identified by gas chromatograph fatty acid methyl ester (GC-FAME) profiling and 16S or 18S rRNA gene sequencing. Thirty-six samples from 11 geographically separated USAF bases were collected. At each base, an above-ground storage tank, a refueling truck, and an aircraft wing tank were sampled at the lowest sample point, or sump, to investigate microbial diversity and dispersion within the fuel distribution chain. Twelve genera, including four Bacillus species and two Staphylococcus species, were isolated and identified. Bacillus licheniformis, the most prevalent organism isolated, was found at seven of the 11 bases. Of the organisms identified, Bacillus sp., Micrococcus luteus, Sphinogmonas sp., Staphylococcus sp., and the fungus Aureobasidium pullulans have previously been isolated from aviation fuel samples. The bacteria Pantoea ananatis, Arthrobacter sp., Alcaligenes sp., Kocuria rhizophilia, Leucobacter komagatae, Dietza sp., and the fungus Discophaerina fagi have not been previously reported in USAF aviation fuel. Only at two bases were the same organisms isolated from all three sample points in the fuel supply distribution chain. Isolation of previously undocumented organisms suggests either, changes in aviation fuel microbial community in response to changes in aviation fuel composition, additives and biocide use, or simply, improvements in isolation and identification techniques.

Aeroacoustic wind-tunnel tests of a light twin-boom general-aviation airplane with free or shrouded-pusher propellers. [in the Langley full-scale tunnel

NASA Technical Reports Server (NTRS)

Mclemore, H. C.; Pegg, R. J.

1980-01-01

Tests were conducted in the Langley full-scale tunnel to determine the aerodynamic performance and acoustic characteristics of four different pusher-propeller configurations on a twin boom, general aviation airplane. The propellers included a 2-blade free propeller, two 3-blade shrouded propellers, and a 5-blade shrouded propeller. The tests were conducted for a range of airplane angles of attack from about 0 deg to 16 deg for test speeds from 0 to about 36 m/sec and for a range of propeller blade angles and rotation speeds. The free propeller provided the best aerodynamic propulsive performance. For forward flight conditions, the free propeller noise levels were lower than those of the shrouded propellers. In the static conditions the free propeller noise levels were as low as those for the shrouded propellers, except for the propeller in-plane noise where the shrouded propeller noise levels were lower.

RS-34 Phoenix In-Space Propulsion System Applied to Active Debris Removal Mission

NASA Technical Reports Server (NTRS)

Esther, Elizabeth A.; Burnside, Christopher G.

2014-01-01

In-space propulsion is a high percentage of the cost when considering Active Debris Removal mission. For this reason it is desired to research if existing designs with slight modification would meet mission requirements to aid in reducing cost of the overall mission. Such a system capable of rendezvous, close proximity operations, and de-orbit of Envisat class resident space objects has been identified in the existing RS-34 Phoenix. RS-34 propulsion system is a remaining asset from the de-commissioned United States Air Force Peacekeeper program; specifically the pressure-fed storable bi-propellant Stage IV Post Boost Propulsion System. The National Aeronautics and Space Administration (NASA) Marshall Space Flight Center (MSFC) gained experience with the RS-34 propulsion system on the successful Ares I-X flight test program flown in the Ares I-X Roll control system (RoCS). The heritage hardware proved extremely robust and reliable and sparked interest for further utilization on other potential in-space applications. Subsequently, MSFC has obtained permission from the USAF to obtain all the remaining RS-34 stages for re-use opportunities. The MSFC Advanced Concepts Office (ACO) was commissioned to lead a study for evaluation of the Rocketdyne produced RS-34 propulsion system as it applies to an active debris removal design reference mission for resident space object targets including Envisat. Originally designed, the RS-34 Phoenix provided in-space six-degrees-of freedom operational maneuvering to deploy payloads at multiple orbital locations. The RS-34 Concept Study lead by sought to further understand application for a similar orbital debris design reference mission to provide propulsive capability for rendezvous, close proximity operations to support the capture phase of the mission, and deorbit of single or multiple large class resident space objects. Multiple configurations varying the degree of modification were identified to trade for dry mass optimization and propellant load. The results of the RS-34 Phoenix Concept Study show that the system is technically sufficient to successfully support all of the missions to rendezvous, capture, and de-orbit targets including Envisat and Hubble Space Telescope. The results and benefits of the RS-34 Orbital Debris Application Concept Study are presented in this paper.

Resilience, Stress, Stigma, and Barriers to Mental Healthcare in U.S. Air Force Nursing Personnel.

PubMed

Hernandez, Stephen H A; Morgan, Brenda J; Parshall, Mark B

Stigma may deter military service members from seeking mental health (MH) services. Previously, substantial proportions of U.S. Air Force (USAF) registered nurses and medical technicians reported concerns about stigma with accessing MH services; in particular, that unit members might lose confidence in them or perceive them as weak, unit leadership might treat them differently, or accessing care might affect career advancement. This study assessed the extent to which stigma and barriers to accessing MH services as perceived by USAF nursing personnel are associated with resilience, stress, previous deployment, or demographic characteristics. An anonymous, online survey was administered to active-duty USAF registered nurses and medical technicians at three locations (N = 250). The survey included demographic items, the Stigma and Barriers to Care scales, Conner-Davidson Resilience Scale, and Perceived Stress Questionnaire. Mean resilience was high, and perceived stress was moderate. About half of participants agreed that unit members might have less confidence in me (54%) or unit leadership might treat me differently (58%). Many also had concerns that it would harm my career (47%), I would be seen as weak (47%), or there would be difficulty getting time off work for treatment (45%). Stigma was positively correlated with perceived stress (r = .40, p < .01) and negatively correlated with resilience (r = -.24, p < .01). Officers had significantly higher stigma and resilience scores and lower stress scores compared with enlisted personnel, but those differences were small. This study validated previous findings that substantial percentages of USAF nursing personnel have concerns that accessing MH services may adversely affect their careers and how they are viewed by unit leaders and peers. In addition, higher levels of concern about stigma were associated with higher levels of stress and lower levels of resilience. Limitations included a low response rate (18%) and self-selection biases.

X-43C Plans and Status

NASA Technical Reports Server (NTRS)

Moses, Paul L.

2003-01-01

X-43C Project is a hypersonic flight demonstration being executed as a collaboration between the National Aeronautics and Space Administration (NASA) and the United States Air Force (USAF). X-43C will expand the hypersonic flight envelope for air breathing engines beyond the history making efforts of the Hyper-X Program (X-43A). X-43C will demonstrate sustained accelerating flight during three flight tests of expendable X-43C Demonstrator Vehicles (DVs). The approximately 16-foot long X-43C DV will be boosted to the starting test conditions, separate from the booster, and accelerate from Mach 5 to Mach 7 under its own power and autonomous control. The DVs are to be powered by a liquid hydrocarbon-fueled, fuel-cooled, dual-mode, airframe integrated scramjet engine system developed under the USAF HyTech Program. The Project is managed by NASA Langley Research Center as part of NASA s Next Generation Launch Technology Program. Flight tests will be conducted by NASA Dryden Flight Research Center over water off the coast of California in the Pacific Test Range. The NASA/USAF/industry project is a natural extension of the Hyper-X Program (X-43A), which will demonstrate short duration ( 10 seconds) gaseous hydrogen-fueled scramjet powered flight at Mach 7 and Mach 10 using a heavyweight, largely heat sink construction, experimental engine. The X-43C Project will demonstrate sustained accelerating flight from Mach 5 to Mach 7 ( 4 minutes) using a flight-weight, fuel-cooled, scramjet engine powered by much denser liquid hydrocarbon fuel. The X-43C DV design flows from integrating USAF HyTech developed engine technologies with a NASA Air Breathing Launch Vehicle accelerator-class configuration and Hyper-X heritage vehicle systems designs. This paper describes the X-43C Project and provides background for NASA s current hypersonic flight demonstration efforts.

Ranking the risk of wildlife species hazardous to military aircraft

USGS Publications Warehouse

Zakrajsek, E.J.; Bissonette, J.A.

2005-01-01

Collisions between birds and aircraft (birdstrikes) pose a major threat to aviation safety. Different species pose different levels of threat; thus, identification of the most hazardous species can help managers identify the level of hazard and prioritize mitigation efforts. Dolbeer et al. (2000) assessed the hazard posed by birds to civilian aircraft by analyzing data from the Federal Aviation Administration's (FAA) Wildlife Strike Database to rank the hazardous species and species groups. A similar analysis has not been done for the military but would be useful and necessary. Military flight characteristics differ from those of civilian flights. During the period 1985-1998, birdstrikes cost the United States Air Force (USAF) an average of $35 million/year in damage. Using the USAF Birdstrike Database, we selected and evaluated each species or species group by the number of strikes recorded in each of 3 damage categories. We weighted damage categories to reflect extent and cost of damage. The USAF Birdstrike Database contained 25,519 records of wildlife strikes in the United States. During the period 1985-1998, 22 (mean = 1.6/year) Class-A birdstrikes (>$1,000,000 damage, loss of aircraft, loss of life, or permanent total disability) were sustained, accounting for 80% of total monetary losses caused by birds. Vultures (Cathartes aura, Coragyps atratus, Caracara cheriway) were ranked the most hazardous species group (Hazard Index Rank [HIR] = 127) to USAF aircraft, followed by geese (Branta canadensis, Chen caerulescens, HIR = 76), pelicans (Pelecanus erythrorhynchos, P. occidentalis, HIR = 47), and buteos (Buteo sp., HIR = 30). Of the smaller flocking birds, blackbirds and starlings (mostly Agelaius phoeniceus, Euphagus cyanocephalus, Molothrus ater, Sturnus vulgaris, HIR = 46), horned larks (Eremophila alpestris, HIR = 24), and swallows (Families Hirundinidae, Apodidae, HIR = 23) were species groups ranked highest. Coupling these results with local bird census data to adjust hazard rank indices to specific locations can facilitate hazard management and lead to meaningful reductions in hazards and costs associated with birdstrikes.

Propellant Readiness Level: A Methodological Approach to Propellant Characterization

NASA Technical Reports Server (NTRS)

Bossard, John A.; Rhys, Noah O.

2010-01-01

A methodological approach to defining propellant characterization is presented. The method is based on the well-established Technology Readiness Level nomenclature. This approach establishes the Propellant Readiness Level as a metric for ascertaining the readiness of a propellant or a propellant combination by evaluating the following set of propellant characteristics: thermodynamic data, toxicity, applications, combustion data, heat transfer data, material compatibility, analytical prediction modeling, injector/chamber geometry, pressurization, ignition, combustion stability, system storability, qualification testing, and flight capability. The methodology is meant to be applicable to all propellants or propellant combinations; liquid, solid, and gaseous propellants as well as monopropellants and propellant combinations are equally served. The functionality of the proposed approach is tested through the evaluation and comparison of an example set of hydrocarbon fuels.

Research into the propeller strut for high speed outboard motor

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

Shimizu, Takashi; Sunayama, Yoshihiko

1995-12-31

For better performance of outboard motors for high speed craft, improvement in the performance of the propeller strut located ahead of the propeller is indispensable in addition to ameliorating the performance of the screw propeller itself. Thus, it is extremely important to reduce the drag of the propeller strut, which accounts for the predominant portion of the submerged parts of the motor and hull when the craft is running at high speed and to improve the propeller efficiency in the wake of the propeller strut. This paper, taking up two different shapes of the propeller strut, compares the performances ofmore » the propeller placed in the wake of the propeller strut in tank tests, and discusses the drag of the propeller strut. The two propeller strut shapes are that of a 70% scaled down model of the propeller strut Suzuki`s 200 PS outboard motor and its improved version. The propeller used in the experiment is one having super cavitating blades with the Pseudo-Kirchhoff nose, whose performance the authors have been analyzing systematically. Detailed comparison was further made of the drags of the differently shaped propeller struts by means of computational fluid dynamics.« less

The 1997 JANNAF Propellant Development and Characterization Subcommittee and Safety and Environmental Protection Subcommittee Joint Meeting

NASA Technical Reports Server (NTRS)

Cocchiaro, James E. (Editor); Filliben, Jeff D. (Editor); Watson, Anne H. (Editor)

1997-01-01

In the Propellant Development and Characterization Subcommittee (PDCS) meeting, topics included: the analysis, characterization, and processing of propellants and propellant ingredients; chemical reactivity; liquid propellants; test methods; rheology; surveillance and aging; and process engineering. In the Safety and Environmental Protection Subcommittee (S&EPS) meeting, topics covered included: hydrazine propellant vapor detection methods; toxicity of propellants and propellants; explosives safety; atmospheric modeling and risk assessment of toxic releases; reclamation, disposal, and demilitarization methods; and remediation of explosives or propellant contaminated sites.

75 FR 7934 - Airworthiness Directives; McCauley Propeller Systems 1A103/TCM Series Propellers

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-23

... with cracks that do not meet acceptable limits, and rework of propellers with cracks that meet..., replacement of propellers with cracks that do not meet acceptable limits, and rework of propellers with cracks... propeller hub, removal from service of propellers with cracks that do not meet acceptable limits, and rework...

Variable Pitch Propellers

NASA Technical Reports Server (NTRS)

1920-01-01

In this report are described four different types of propellers which appeared at widely separated dates, but which were exhibited together at the last Salon de l'Aeronautique. The four propellers are the Chaviere variable pitch propeller, the variable pitch propeller used on the Clement Bayard dirigible, the variable pitch propeller used on Italian dirigibles, and the Levasseur variable pitch propeller.

10. Credit USAF, 7 September 1945. Original housed in the ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

10. Credit USAF, 7 September 1945. Original housed in the Muroc Flight Test Base, Unit History, 1 September 1942 - 30 June 1945. Alfred F. Simpson Historical Research Agency. United States Air Force. Maxwell AFB, Alabama. View looks northwest into jet engine test cell located on aircraft apron southeast of Building 4305. In background of photo can be seen doors of Unicon Portable Hangar on left, and southeast end of Building T-l Bachelor Officers' Quarters ("Desert Rat Hotel"). This view emphasizes the hangar's role as a test facility for developing and testing aircraft and aircraft systems, not simply as a "garage" for aircraft. - Edwards Air Force Base, North Base, Unicon Portable Hangar, First & C Streets, Boron, Kern County, CA

Application Of Optical Techniques To Command, Control, And Communications (C3) Systems

NASA Astrophysics Data System (ADS)

Weinberg, M.; Steensma, P. D.

1981-02-01

This paper identifies and discusses specific applications of the optical transmission technology to various Command Control and Communications (C3) systems. Candidate C3 systems will first be identified and discussed briefly. These will include: 407L/485L Tactical Air Defense Systems (USAF) TAOC-85 Tactical Air Operations Central (USMC) SACDIN Strategic Air Command Digital Integrated Network (USAF) MX-C3 Missile "X" Command Control Communications Network The first tr are classified as tactical C3 systems while the latter two are classified as strategic C systems. Potential optical applications will be identified along with the benefits derived. Each application will be discussed with key parameters, cost performance benefits, potential problem areas, time frame for development identified.

Circulation control propellers for general aviation, including a BASIC computer program

NASA Technical Reports Server (NTRS)

Taback, I.; Braslow, A. L.; Butterfield, A. J.

1983-01-01

The feasibility of replacing variable pitch propeller mechanisms with circulation control (Coanada effect) propellers on general aviation airplanes was examined. The study used a specially developed computer program written in BASIC which could compare the aerodynamic performance of circulation control propellers with conventional propellers. The comparison of aerodynamic performance for circulation control, fixed pitch and variable pitch propellers is based upon the requirements for a 1600 kg (3600 lb) single engine general aviation aircraft. A circulation control propeller using a supercritical airfoil was shown feasible over a representative range of design conditions. At a design condition for high speed cruise, all three types of propellers showed approximately the same performance. At low speed, the performance of the circulation control propeller exceeded the performance for a fixed pitch propeller, but did not match the performance available from a variable pitch propeller. It appears feasible to consider circulation control propellers for single engine aircraft or multiengine aircraft which have their propellers on a common axis (tractor pusher). The economics of the replacement requires a study for each specific airplane application.

14 CFR 45.13 - Identification data.

Code of Federal Regulations, 2012 CFR

2012-01-01

... paragraph (a) of this section, on any aircraft, aircraft engine, propeller, propeller blade, or propeller... identification information required by paragraph (a) of this section on any aircraft, aircraft engine, propeller... with paragraph (d)(2) of this section on any aircraft, aircraft engine, propeller, propeller blade, or...

A Historical Analysis of Crane Mishaps at Kennedy Space Center

NASA Technical Reports Server (NTRS)

Wolfe, Crystal

2014-01-01

Cranes and hoists are widely used in many areas. Crane accidents and handling mishaps are responsible for injuries, costly equipment damage, and program delays. Most crane accidents are caused by preventable factors. Understanding these factors is critical when designing cranes and preparing lift plans. Analysis of previous accidents provides insight into current recommendations for crane safety. Cranes and hoists are used throughout Kennedy Space Center to lift everything from machine components to critical flight hardware. Unless they are trained crane operators, most NASA employees and contractors do not need to undergo specialized crane training and may not understand the safety issues surrounding the use of cranes and hoists. A single accident with a crane or hoist can injure or kill people, cause severe equipment damage, and delay or terminate a program. Handling mishaps can also have a significant impact on the program. Simple mistakes like bouncing or jarring a load, or moving the crane down when it should go up, can damage fragile flight hardware and cause major delays in processing. Hazardous commodities (high pressure gas, hypergolic propellants, and solid rocket motors) can cause life safety concerns for the workers performing the lifting operations. Most crane accidents are preventable with the correct training and understanding of potential hazards. Designing the crane with human factors taken into account can prevent many accidents. Engineers are also responsible for preparing lift plans where understanding the safety issues can prevent or mitigate potential accidents. Cranes are widely used across many areas of KSC. Failure of these cranes often leads to injury, high damage costs, and significant delays in program objectives. Following a basic set of principles and procedures during design, fabrication, testing, regular use, and maintenance can significantly minimize many of these failures. As the accident analysis shows, load drops are often caused or influenced by human factors. Therefore, proper training and understanding of crane safety throughout the workforce is critical. It is important that the engineers designing the cranes, lift planners preparing the lift plans, operators performing the lifts, and training officers conducting the operator training all understand the problems that can happen with cranes and how to ensure the safety of the workforce and equipment being lifted.

KSC-2011-2423

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Crews in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida remove space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2425

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Crews in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida remove space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2427

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit, is removed in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2431

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit, is moved to a transporter in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2433

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit, is atop a transporter in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2430

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit, is moved to a transporter in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

KSC-2011-2426

NASA Image and Video Library

2011-03-22

CAPE CANAVERAL, Fla. - Crews in Orbiter Processing Facility-2 at NASA's Kennedy Space Center in Florida remove space shuttle Discovery's forward reaction control system (FRCS), which helped steer the shuttle in orbit. To maneuver, the FRCS used hypergolic fuel and oxidizer, which were purged from Discovery after its final spaceflight, STS-133. Next, the FRCS will be shipped to a maintenance facility at White Sands Space Harbor in New Mexico, where additional inspections will be performed and its components made safe to go on public display. The transition and retirement processing is expected to help rocket designers build next-generation spacecraft and prepare the shuttle for display. Photo credit: NASA/Jim Grossmann

Experimental Studies of Liquefaction and Densification of Liquid Oxygen

NASA Technical Reports Server (NTRS)

Partridge, Jonathan Koert

2010-01-01

The propellant combination that offers optimum performance is very reactive with a low average molecular weight of the resulting combustion products. Propellant combinations such as oxygen and hydrogen meet the above criteria, however, the propellants in gaseous form require large propellant tanks due to the low density of gas. Thus, rocketry employs cryogenic refrigeration to provide a more dense propellant stored as a liquid. In addition to propellant liquefaction, cryogenic refrigeration can also conserve propellant and provide propellant subcooling and propellant densification. Previous studies analyzed vapor conditioning of a cryogenic propellant, with the vapor conditioning by either a heat exchanger position in the vapor or by using the vapor in a refrigeration cycle as the working fluid. This study analyzes the effects of refrigeration heat exchanger located in the liquid of the common propellant oxidizer, liquid oxygen. This study predicted and determined the mass condensation rate and heat transfer coefficient for liquid oxygen.

The Aerodynamic Characteristics of Full-Scale Propellers Having 2, 3, and 4 Blades of Clark Y and R.A.F. 6 Airfoil Sections

NASA Technical Reports Server (NTRS)

Hartman, Edwin P; Biermann, David

1938-01-01

Aerodynamic tests were made of seven full-scale 10-foot-diameter propellers of recent design comprising three groups. The first group was composed of three propellers having Clark y airfoil sections and the second group was composed of three propellers having R.A.F. 6 airfoil sections, the propellers of each group having 2, 3, and 4 blades. The third group was composed of two propellers, the 2-blade propeller taken from the second group and another propeller having the same airfoil section and number of blades but with the width and thickness 50 percent greater. The tests of these propellers reveal the effect of changes in solidity resulting either from increasing the number of blades or from increasing the blade width propeller design charts and methods of computing propeller thrust are included.

Propeller torque load and propeller shaft torque response correlation during ice-propeller interaction

NASA Astrophysics Data System (ADS)

Polić, Dražen; Ehlers, Sören; Æsøy, Vilmar

2017-03-01

Ships use propulsion machinery systems to create directional thrust. Sailing in ice-covered waters involves the breaking of ice pieces and their submergence as the ship hull advances. Sometimes, submerged ice pieces interact with the propeller and cause irregular fluctuations of the torque load. As a result, the propeller and engine dynamics become imbalanced, and energy propagates through the propulsion machinery system until equilibrium is reached. In such imbalanced situations, the measured propeller shaft torque response is not equal to the propeller torque. Therefore, in this work, the overall system response is simulated under the ice-related torque load using the Bond graph model. The energy difference between the propeller and propeller shaft is estimated and related to their corresponding mechanical energy. Additionally, the mechanical energy is distributed among modes. Based on the distribution, kinetic and potential energy are important for the correlation between propeller torque and propeller shaft response.

14 CFR 23.905 - Propellers.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Propellers. (a) Each propeller must have a type certificate. (b) Engine power and propeller shaft rotational... tests, that the propeller is capable of continuous safe operation. (h) All engine cowling, access doors... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Propellers. 23.905 Section 23.905...

14 CFR 23.905 - Propellers.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Propellers. (a) Each propeller must have a type certificate. (b) Engine power and propeller shaft rotational... tests, that the propeller is capable of continuous safe operation. (h) All engine cowling, access doors... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Propellers. 23.905 Section 23.905...

14 CFR 23.905 - Propellers.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Propellers. (a) Each propeller must have a type certificate. (b) Engine power and propeller shaft rotational... tests, that the propeller is capable of continuous safe operation. (h) All engine cowling, access doors... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Propellers. 23.905 Section 23.905...

14 CFR 23.905 - Propellers.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Propellers. (a) Each propeller must have a type certificate. (b) Engine power and propeller shaft rotational... tests, that the propeller is capable of continuous safe operation. (h) All engine cowling, access doors... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Propellers. 23.905 Section 23.905...

14 CFR 23.905 - Propellers.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Propellers. (a) Each propeller must have a type certificate. (b) Engine power and propeller shaft rotational... tests, that the propeller is capable of continuous safe operation. (h) All engine cowling, access doors... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Propellers. 23.905 Section 23.905...

14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

Code of Federal Regulations, 2013 CFR

2013-01-01

... airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL... AIRWORTHINESS CERTIFICATION General § 36.9 Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. For propeller-driven small airplanes in the primary, normal, utility...

14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

Code of Federal Regulations, 2012 CFR

2012-01-01

... airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL... AIRWORTHINESS CERTIFICATION General § 36.9 Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. For propeller-driven small airplanes in the primary, normal, utility...

14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

Code of Federal Regulations, 2011 CFR

2011-01-01

... airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL... AIRWORTHINESS CERTIFICATION General § 36.9 Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. For propeller-driven small airplanes in the primary, normal, utility...

14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

Code of Federal Regulations, 2014 CFR

2014-01-01

... airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL... AIRWORTHINESS CERTIFICATION General § 36.9 Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. For propeller-driven small airplanes in the primary, normal, utility...

14 CFR 36.9 - Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category...

Code of Federal Regulations, 2010 CFR

2010-01-01

... airplanes and propeller-driven commuter category airplanes. 36.9 Section 36.9 Aeronautics and Space FEDERAL... AIRWORTHINESS CERTIFICATION General § 36.9 Acoustical change: Propeller-driven small airplanes and propeller-driven commuter category airplanes. For propeller-driven small airplanes in the primary, normal, utility...

Propeller Study. Part 2: the Design of Propellers for Minimum Noise

NASA Technical Reports Server (NTRS)

Ormsbee, A. I.; Woan, C. J.

1977-01-01

The design of propellers which are efficient and yet produce minimum noise requires accurate determinations of both the flow over the propeller. Topics discussed in relating aerodynamic propeller design and propeller acoustics include the necessary approximations and assumptions involved, the coordinate systems and their transformations, the geometry of the propeller blade, and the problem formulations including the induced velocity, required in the determination of mean lines of blade sections, and the optimization of propeller noise. The numerical formulation for the lifting-line model are given. Some applications and numerical results are included.

Operational Space Weather in USAF Education

NASA Astrophysics Data System (ADS)

Smithtro, C.; Quigley, S.

2006-12-01

Most education programs offering space weather courses are understandably and traditionally heavily weighted with theoretical space physics that is the basis for most of what is researched and modeled. While understanding the theory is a good and necessary grounding for anyone working the field of space weather, few military or commercial jobs employ such theory in real-time operations. The operations sites/centers are much more geared toward use of applied theory-resultant models, tools and products. To ensure its operations centers personnel, commanders, real-time system operators and other customers affected by the space environment are educated on available and soon-to-be operational space weather models and products, the USAF has developed applicable course/lecture material taught at various institutions to include the Air Force Institute of Technology (AFIT) and the Joint Weather Training Complex (335th/TRS/OUA). Less frequent training of operational space weather is available via other venues that will be discussed, and associated course material is also being developed for potential use at the National Security Space Institute (NSSI). This presentation provides an overview of the programs, locations, courses and material developed and/or taught by or for USAF personnel dealing with operational space weather. It also provides general information on student research project results that may be used in operational support, along with observations regarding logistical and professional benefits of teaching such non-theoretical/non-traditional material.

Standard of care of erectile dysfunction in U.S. Air Force aircrew and active duty not on flying status.

PubMed

Nast, Justin B

2014-11-01

In 2011, over 3,000 active duty U.S. Air Force (USAF) members were prescribed a phosphodiesterase inhibitor (PDEI). PDEIs are first-line therapy for treating erectile dysfunction and can have significant side effects that could impact aircrew performance. In total, 200 eligible subject records were randomly sampled from the active duty USAF population of those males filling a prescription for a PDEI in June 2011; 100 of those records were from aviators. The electronic records were reviewed and scored to determine if USAF aeromedical standards for prescribing PDEIs were followed, with a minimum score of 0 for no standards met and a maximum of 3 for all standards met. The average score for both groups was 1, with no significant difference between the group scores. A proper aeromedical disposition was documented in 67% of the aviator records. Although there was no significant difference in standard of care for aviators and nonaviators, the overall documented standard of care was poor. Lack of documentation was the primary reason for the low scores and the low percentage of properly rendered aeromedical dispositions. Proper medical record documentation is important for evaluating quality of care and ensuring compliance with regulations in an Air Force aviator population. Reprint & Copyright © 2014 Association of Military Surgeons of the U.S.

Ecological risk assessment for Mather Air Force Base, California: Phase 1, screening assessment

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

Meyers-Schoene, L.; Fischer, N.T.; Rabe, J.J.

Mather Air Force Base (AFB) is among the numerous facilities scheduled for closure under the US Air Force (USAF) Installation Restoration Program (IRP). A component of the Mather AFB IRP is to prepare risk assessments for each of the chemically contaminated sites. Because no previous ecological risk related studies have been conducted on Mather AFB, the authors proposed a phased approach to assessing ecological risks at the base. Phase 1 consisted of baseline ecological surveys that collected data over a 12-month period. In addition, benchmark screening criteria were used in conjunction with modeling results that utilized measured concentrations of chemicalmore » analytes in abiotic samples. Phase 2 may consist of the collection of more site-specific data and toxicity testing, if warranted by the Phase 1 screening analysis. This approach was in agreement with the USAF`s ecological risk assessment guidance and met the approval of the Air Force and USEPA Region 9. The authors found the use of established and derived screening values to effectively aid in the focusing of the ecological risk assessment on those chemicals most likely to be hazardous to ecological receptors at the base. Disadvantages in the use of screening values include the uncertainties associated with the conservative assumptions inherent in the derivation of benchmark values and the difficulty in extrapolating from laboratory determined benchmark values to impacts in the field.« less

14 CFR 23.1149 - Propeller speed and pitch controls.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Propeller speed and pitch controls. 23.1149... Powerplant Controls and Accessories § 23.1149 Propeller speed and pitch controls. (a) If there are propeller... propeller; and (2) Simultaneous control of all propellers. (b) The controls must allow ready synchronization...

14 CFR 23.1149 - Propeller speed and pitch controls.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Propeller speed and pitch controls. 23.1149... Powerplant Controls and Accessories § 23.1149 Propeller speed and pitch controls. (a) If there are propeller... propeller; and (2) Simultaneous control of all propellers. (b) The controls must allow ready synchronization...

14 CFR 23.1149 - Propeller speed and pitch controls.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Propeller speed and pitch controls. 23.1149... Powerplant Controls and Accessories § 23.1149 Propeller speed and pitch controls. (a) If there are propeller... propeller; and (2) Simultaneous control of all propellers. (b) The controls must allow ready synchronization...

Noise reduction for model counterrotation propeller at cruise by reducing aft-propeller diameter

NASA Technical Reports Server (NTRS)

Dittmar, James H.; Stang, David B.

1987-01-01

The forward propeller of a model counterrotation propeller was tested with its original aft propeller and with a reduced diameter aft propeller. Noise reductions with the reduced diameter aft propeller were measured at simulated cruise conditions. Reductions were as large as 7.5 dB for the aft-propeller passing tone and 15 dB in the harmonics at specific angles. The interaction tones, mostly the first, were reduced probably because the reduced-diameter aft-propeller blades no longer interacted with the forward propeller tip vortex. The total noise (sum of primary and interaction noise) at each harmonic was significantly reduced. The chief noise reduction at each harmonic came from reduced aft-propeller-alone noise, with the interaction tones contributing little to the totals at cruise. Total cruise noise reductions were as much as 3 dB at given angles for the blade passing tone and 10 dB for some of the harmonics. These reductions would measurably improve the fuselage interior noise levels and represent a definite cruise noise benefit from using a reduced diameter aft propeller.

32 CFR 806.1 - Summary of revisions.

Code of Federal Regulations, 2010 CFR

2010-07-01

... Headquarters United States Air Force (HQ USAF/SC) and Headquarters Air Force Communications and Information Center/Corporate Information Division (HQ AFCIC/ITC); contains significant changes and additions to...

32 CFR 644.26 - Required clearances.

Code of Federal Regulations, 2010 CFR

2010-07-01

... Director of Engineering and Services (AF/PRE) and the Director of Planning, Programming and Analysis (AF/RDXI), as to industrial installations, of Headquarters, USAF, are responsible for initiating all...

32 CFR 644.26 - Required clearances.

Code of Federal Regulations, 2012 CFR

2012-07-01

... Director of Engineering and Services (AF/PRE) and the Director of Planning, Programming and Analysis (AF/RDXI), as to industrial installations, of Headquarters, USAF, are responsible for initiating all...