Sample records for system engine firings

  1. A Combined Water-Bromotrifluoromethane Crash-Fire Protection System for a T-56 Turbopropeller Engine

    NASA Technical Reports Server (NTRS)

    Campbell, John A.; Busch, Arthur M.

    1959-01-01

    A crash-fire protection system is described which will suppress the ignition of crash-spilled fuel that may be ingested by a T-56 turbo-propeller engine. This system includes means for rapidly extinguishing the combustor flame, means for cooling and inerting with water the hot engine parts likely to ignite engine ingested fuel, and means for blanketing with bromotrifluoromethane massive metal parts that may reheat after the engine stops rotating. Combustion-chamber flames were rapidly extinguished at the engine fuel nozzles by a fuel shutoff and drain valve. Hot engine parts were inerted and cooled by 42 pounds of water discharged at seven engine stations. Massive metal parts that could reheat were inerted with 10 pounds of bromotrifluoromethane discharged at two engine stations. Performance trials of the crash-fire protection system were conducted by bringing the engine up to takeoff temperature, actuating the crash-fire protection system, and then spraying fuel into the engine to simulate crash-ingested fuel. No fires occurred during these trials, although fuel was sprayed into the engine from 0.3 second to 15 minutes after actuating the crash-fire protection system.

  2. Crash-Fire Protection System for T-56 Turbopropeller Engine Using Water as Cooling and Inerting Agent

    NASA Technical Reports Server (NTRS)

    Busch, Arthur M.; Campbell, John A.

    1959-01-01

    A crash-fire protection system to suppress the ignition of crash-spilled fuel that may be ingested by a T-56 turbopropeller engine is described. This system includes means for rapidly extinguishing the combustor flame and means for cooling and inerting with water the hot engine parts likely to ignite engine-ingested fuel. Combustion-chamber flames were extinguished in 0.07 second at the engine fuel manifold. Hot engine parts were inerted and cooled by 52 pounds of water discharged at ten engine stations. Performance trials of the crash-fire prevention system were conducted by bringing the engine up to takeoff temperature, stopping the normal fuel flow to the engine, starting the water discharge, and then spraying fuel into the engine to simulate crash-ingested fuel. No fires occurred during these trials, although fuel was sprayed into the engine from 0.3 second to 15 minutes after actuating the crash-fire protection system.

  3. 36 CFR 1234.12 - What are the fire safety requirements that apply to records storage facilities?

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... records storage facilities? (a) The fire detection and protection systems must be designed or reviewed by a licensed fire protection engineer. If the system was not designed by a licensed fire protection... engineer that describes the design intent of the fire detection and suppression system, detailing the...

  4. 36 CFR 1234.12 - What are the fire safety requirements that apply to records storage facilities?

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... records storage facilities? (a) The fire detection and protection systems must be designed or reviewed by a licensed fire protection engineer. If the system was not designed by a licensed fire protection... engineer that describes the design intent of the fire detection and suppression system, detailing the...

  5. 36 CFR § 1234.12 - What are the fire safety requirements that apply to records storage facilities?

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... records storage facilities? (a) The fire detection and protection systems must be designed or reviewed by a licensed fire protection engineer. If the system was not designed by a licensed fire protection... engineer that describes the design intent of the fire detection and suppression system, detailing the...

  6. 14 CFR 23.1201 - Fire extinguishing systems materials.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Fire extinguishing systems materials. 23... Powerplant Powerplant Fire Protection § 23.1201 Fire extinguishing systems materials. For all airplanes with engine(s) embedded in the fuselage or in pylons on the aft fuselage the following applies: (a) No...

  7. 14 CFR 23.1201 - Fire extinguishing systems materials.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Fire extinguishing systems materials. 23... Powerplant Powerplant Fire Protection § 23.1201 Fire extinguishing systems materials. For all airplanes with engine(s) embedded in the fuselage or in pylons on the aft fuselage the following applies: (a) No...

  8. 46 CFR 27.203 - What are the requirements for fire detection on towing vessels?

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... detection on towing vessels? You must have a fire-detection system installed on your vessel to detect engine... use an existing engine-room-monitoring system (with fire-detection capability) instead of a fire-detection system, if the monitoring system is operable and complies with this section. You must ensure that...

  9. 14 CFR 23.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ..., and the discharge distribution must be adequate to extinguish fires. An individual “one shot” system... to extinguish fires. An individual “one shot” system may be used, except for engine(s) embedded in the fuselage, where a “two shot” system is required. ...

  10. 78 FR 58960 - Airworthiness Directives; BAE SYSTEMS (OPERATIONS) LIMITED Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-25

    ... inspection of certain engine and auxiliary power unit (APU) fire extinguishers to determine if the fire... system to extinguish fires in the engine or APU fire zones, possibly resulting in damage to the airplane... Unit (APU) fire zones, possibly resulting in damage to the aeroplane and injury to the occupants. For...

  11. Wildland fire management. Volume 1: Prevention methods and analysis. [systems engineering approach to California fire problems

    NASA Technical Reports Server (NTRS)

    Weissenberger, S. (Editor)

    1973-01-01

    A systems engineering approach is reported for the problem of reducing the number and severity of California's wildlife fires. Prevention methodologies are reviewed and cost benefit models are developed for making preignition decisions.

  12. Aviation Engine Test Facilities (AETF) fire protection study

    NASA Astrophysics Data System (ADS)

    Beller, R. C.; Burns, R. E.; Leonard, J. T.

    1989-07-01

    An analysis is presented to the effectiveness of various types of fire fighting agents in extinguishing the kinds of fires anticipated in Aviation Engine Test Facilities (AETF), otherwise known as Hush Houses. The agents considered include Aqueous Film-Forming Foam, Halon 1301, Halon 1211 and water. Previous test work has shown the rapidity with which aircraft, especially high performance aircraft, can be damaged by fire. Based on this, tentative criteria for this evaluation included a maximum time of 20 s from fire detection to extinguishment and a period of 30 min in which the agent would prevent reignition. Other issues examined included: toxicity, corrosivity, ease of personnel egress, system reliability, and cost effectiveness. The agents were evaluated for their performance in several fire scenarios, including: under frame fire, major engine fire, engine disintegration fire, high-volume pool fire with simultaneous spill fire, internal electrical fire, and runaway engine fire.

  13. 46 CFR 162.161-1 - Scope.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-1 Scope. (a) This subpart applies to each engineered fixed fire extinguishing system using a halocarbon or an inert gas as an agent. It does not apply to pre-engineered systems. (b) Each system must be designed for...

  14. 46 CFR 162.161-1 - Scope.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-1 Scope. (a) This subpart applies to each engineered fixed fire extinguishing system using a halocarbon or an inert gas as an agent. It does not apply to pre-engineered systems. (b) Each system must be designed for...

  15. 46 CFR 162.161-1 - Scope.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-1 Scope. (a) This subpart applies to each engineered fixed fire extinguishing system using a halocarbon or an inert gas as an agent. It does not apply to pre-engineered systems. (b) Each system must be designed for...

  16. 14 CFR 25.857 - Cargo compartment classification.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

  17. 14 CFR 25.857 - Cargo compartment classification.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

  18. 14 CFR 25.857 - Cargo compartment classification.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

  19. 14 CFR 25.857 - Cargo compartment classification.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

  20. 14 CFR 25.857 - Cargo compartment classification.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

  1. Systems Engineering Approach To Ground Combat Vehicle Survivability In Urban Operations

    DTIC Science & Technology

    2016-09-01

    extinguishing system (AFES), which uses fire wires to detect the presence of fires. The detection of fire automatically triggers the activation of the fire...corresponding wires and connection points also means that it can be more difficult for engineers to integrate distributed architecture systems onto...command signals to the missile via wires trailing behind the missile or via RF signals. See Figure 29 for an illustration of CLOS guidance. Since CLOS

  2. 14 CFR 23.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ..., and the discharge distribution must be adequate to extinguish fires. An individual “one shot” system may be used, except for engine(s) embedded in the fuselage, where a “two shot” system is required. (3...

  3. 14 CFR 23.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ..., and the discharge distribution must be adequate to extinguish fires. An individual “one shot” system may be used, except for engine(s) embedded in the fuselage, where a “two shot” system is required. (3...

  4. Reliability study of an emerging fire suppression system

    DOE PAGES

    Miller, David A.; Rossati, Lyric M.; Fritz, Nathan K.; ...

    2015-11-01

    Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Plutonium gloveboxes are known to present harsh environmental conditions for polymer materials, these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. The primary component of interest in self-contained fire extinguishers is the nylon 6-6 machined tube that comprises the main body of the system.Thermo-mechanical modeling and characterization of nylon 6-6 for use in plutonium glovebox applications has been carried out. Data has been generated regarding property degradation leading to poor, or reduced, engineering performancemore » of nylon 6-6 components. In this study, nylon 6-6 tensile specimens conforming to the casing of self-contained fire extinguisher systems have been exposed to hydrochloric, nitric, and sulfuric acids. This information was used to predict the performance of a load bearing engineering component comprised of nylon 6-6 and designed to operate in a consistent manner over a specified time period. The study provides a fundamental understanding of the engineering performance of the fire suppression system and the effects of environmental degradation due to acid exposure on engineering performance. Data generated help identify the limitations of self-contained fire extinguishers. No critical areas of concern for plutonium glovebox applications of nylon 6-6 have been identified when considering exposure to mineral acid.« less

  5. Reliability study of an emerging fire suppression system

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

    Miller, David A.; Rossati, Lyric M.; Fritz, Nathan K.

    Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Plutonium gloveboxes are known to present harsh environmental conditions for polymer materials, these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. The primary component of interest in self-contained fire extinguishers is the nylon 6-6 machined tube that comprises the main body of the system.Thermo-mechanical modeling and characterization of nylon 6-6 for use in plutonium glovebox applications has been carried out. Data has been generated regarding property degradation leading to poor, or reduced, engineering performancemore » of nylon 6-6 components. In this study, nylon 6-6 tensile specimens conforming to the casing of self-contained fire extinguisher systems have been exposed to hydrochloric, nitric, and sulfuric acids. This information was used to predict the performance of a load bearing engineering component comprised of nylon 6-6 and designed to operate in a consistent manner over a specified time period. The study provides a fundamental understanding of the engineering performance of the fire suppression system and the effects of environmental degradation due to acid exposure on engineering performance. Data generated help identify the limitations of self-contained fire extinguishers. No critical areas of concern for plutonium glovebox applications of nylon 6-6 have been identified when considering exposure to mineral acid.« less

  6. 46 CFR 193.05-10 - Fixed fire extinguishing systems.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ....05-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH... provided for internal combustion engine installations in accordance with the following: (1) Enclosed spaces containing gasoline engines shall have fixed carbon dioxide systems. (2) If a fire extinguishing system is...

  7. 46 CFR 193.05-10 - Fixed fire extinguishing systems.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ....05-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH... provided for internal combustion engine installations in accordance with the following: (1) Enclosed spaces containing gasoline engines shall have fixed carbon dioxide systems. (2) If a fire extinguishing system is...

  8. 30 CFR 250.1629 - Additional production and fuel gas system requirements.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... operating range. (2) Engine exhaust. You must equip engine exhausts to comply with the insulation and... structure. (4) Fire- and gas-detection system. (i) Fire (flame, heat, or smoke) sensors shall be installed...

  9. 75 FR 20516 - Special Conditions: Cirrus Design Corporation, Model SF50; Fire Extinguishing for Upper Aft...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-20

    ...; Special Conditions No. 23-245-SC] Special Conditions: Cirrus Design Corporation, Model SF50; Fire... protect such installed engines from fires, were not envisioned in the development of the part 23 normal... condition for the fire extinguishing system for the engine on the model SF50 is required. Regulations...

  10. Applying Open Source Game Engine for Building Visual Simulation Training System of Fire Fighting

    NASA Astrophysics Data System (ADS)

    Yuan, Diping; Jin, Xuesheng; Zhang, Jin; Han, Dong

    There's a growing need for fire departments to adopt a safe and fair method of training to ensure that the firefighting commander is in a position to manage a fire incident. Visual simulation training systems, with their ability to replicate and interact with virtual fire scenarios through the use of computer graphics or VR, become an effective and efficient method for fire ground education. This paper describes the system architecture and functions of a visual simulated training system of fire fighting on oil storage, which adopting Delat3D, a open source game and simulation engine, to provide realistic 3D views. It presents that using open source technology provides not only the commercial-level 3D effects but also a great reduction of cost.

  11. 14 CFR 25.903 - Engines.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... chapter. (2) Each turbine engine must comply with one of the following: (i) Sections 33.76, 33.77 and 33... any engine individually in flight, except that, for turbine engine installations, the means for... might be exposed to fire must be at least fire-resistant. If hydraulic propeller feathering systems are...

  12. Development and Evaluation of a Prototype Wheeled Ultra-High Pressure Extinguisher System with Novec 1230

    DTIC Science & Technology

    2016-01-01

    Fire Tests Pool fire tests were conducted as outlined below, and consisted of a pretest phase, in which the F-100 engine nacelle was first...the nacelle during the test phase. Pretest Phase  Determine and record extinguisher full weight.  Initiate flow of jet fuel through the...extinguisher after test. 3.4.2. Rear Engine Fire Tests Rear engine fire tests were conducted as outlined below, and consisted of a pretest phase

  13. Video File - NASA Conducts 2nd RS-25 Engine Hot Fire of 2018 - 2018-02-01

    NASA Image and Video Library

    2018-02-01

    NASA Conducts 2nd RS-25 Engine Hot Fire of 2018. A 365-second hot fire test on Feb. 1, 2018, at NASA’s Stennis Space Center in Mississippi marks the completion of “green run” testing, or flight certification, for all new RS-25 engine flight controllers slated for Exploration Mission-2, the first Space Launch System mission with astronauts on board. In addition to the flight controller, the Feb. 1 hot fire also marked the third test of a 3D printed pogo accumulator assembly for the RS-25 engine.

  14. Engine Data Interpretation System (EDIS)

    NASA Technical Reports Server (NTRS)

    Cost, Thomas L.; Hofmann, Martin O.

    1990-01-01

    A prototype of an expert system was developed which applies qualitative or model-based reasoning to the task of post-test analysis and diagnosis of data resulting from a rocket engine firing. A combined component-based and process theory approach is adopted as the basis for system modeling. Such an approach provides a framework for explaining both normal and deviant system behavior in terms of individual component functionality. The diagnosis function is applied to digitized sensor time-histories generated during engine firings. The generic system is applicable to any liquid rocket engine but was adapted specifically in this work to the Space Shuttle Main Engine (SSME). The system is applied to idealized data resulting from turbomachinery malfunction in the SSME.

  15. 14 CFR 23.1197 - Fire extinguishing agents.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Protection § 23.1197 Fire extinguishing agents. For all airplanes with engine(s) embedded in the fuselage or... extinguishing system; and (2) Have thermal stability over the temperature range likely to be experienced in the... personnel compartment, even though a defect may exist in the extinguishing system. This must be shown by...

  16. 14 CFR 23.1197 - Fire extinguishing agents.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... Protection § 23.1197 Fire extinguishing agents. For all airplanes with engine(s) embedded in the fuselage or... extinguishing system; and (2) Have thermal stability over the temperature range likely to be experienced in the... personnel compartment, even though a defect may exist in the extinguishing system. This must be shown by...

  17. 14 CFR 29.1203 - Fire detector systems.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... detector systems. (a) For each turbine engine powered rotorcraft and Category A reciprocating engine... fire zones and in the combustor, turbine, and tailpipe sections of turbine installations (whether or... affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow...

  18. 14 CFR 29.1203 - Fire detector systems.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... detector systems. (a) For each turbine engine powered rotorcraft and Category A reciprocating engine... fire zones and in the combustor, turbine, and tailpipe sections of turbine installations (whether or... affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow...

  19. 14 CFR 29.1203 - Fire detector systems.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... detector systems. (a) For each turbine engine powered rotorcraft and Category A reciprocating engine... fire zones and in the combustor, turbine, and tailpipe sections of turbine installations (whether or... affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow...

  20. 14 CFR 29.1203 - Fire detector systems.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... detector systems. (a) For each turbine engine powered rotorcraft and Category A reciprocating engine... fire zones and in the combustor, turbine, and tailpipe sections of turbine installations (whether or... affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow...

  1. 14 CFR 29.1203 - Fire detector systems.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... detector systems. (a) For each turbine engine powered rotorcraft and Category A reciprocating engine... fire zones and in the combustor, turbine, and tailpipe sections of turbine installations (whether or... affected by any oil, water, other fluids, or fumes that might be present. (d) There must be means to allow...

  2. Development of life prediction capabilities for liquid propellant rocket engines. Post-fire diagnostic system for the SSME system architecture study

    NASA Technical Reports Server (NTRS)

    Gage, Mark; Dehoff, Ronald

    1991-01-01

    This system architecture task (1) analyzed the current process used to make an assessment of engine and component health after each test or flight firing of an SSME, (2) developed an approach and a specific set of objectives and requirements for automated diagnostics during post fire health assessment, and (3) listed and described the software applications required to implement this system. The diagnostic system described is a distributed system with a database management system to store diagnostic information and test data, a CAE package for visual data analysis and preparation of plots of hot-fire data, a set of procedural applications for routine anomaly detection, and an expert system for the advanced anomaly detection and evaluation.

  3. 46 CFR 62.35-15 - Fire safety.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 2 2011-10-01 2011-10-01 false Fire safety. 62.35-15 Section 62.35-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING VITAL SYSTEM AUTOMATION Requirements for Specific Types of Automated Vital Systems § 62.35-15 Fire safety. (a) All required fire pump...

  4. 46 CFR 62.35-15 - Fire safety.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 2 2010-10-01 2010-10-01 false Fire safety. 62.35-15 Section 62.35-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING VITAL SYSTEM AUTOMATION Requirements for Specific Types of Automated Vital Systems § 62.35-15 Fire safety. (a) All required fire pump...

  5. 46 CFR 189.55-5 - Plans and specifications required for new construction.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., the arrangement of the alarm and extinguishing systems, the fire extinguishers, means of access to... other fire control features. (3) Details of alarm systems. (4) Details of extinguishing systems, including fire mains, carbon dioxide, clean agent, foam, and sprinkling systems. (e) Marine engineering. For...

  6. 46 CFR 189.55-5 - Plans and specifications required for new construction.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., the arrangement of the alarm and extinguishing systems, the fire extinguishers, means of access to... other fire control features. (3) Details of alarm systems. (4) Details of extinguishing systems, including fire mains, carbon dioxide, clean agent, foam, and sprinkling systems. (e) Marine engineering. For...

  7. 14 CFR 27.1195 - Fire detector systems.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Fire detector systems. 27.1195 Section 27.1195 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... detector systems. Each turbine engine powered rotorcraft must have approved quick-acting fire detectors in...

  8. 14 CFR 27.1195 - Fire detector systems.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Fire detector systems. 27.1195 Section 27.1195 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... detector systems. Each turbine engine powered rotorcraft must have approved quick-acting fire detectors in...

  9. 14 CFR 27.1195 - Fire detector systems.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Fire detector systems. 27.1195 Section 27.1195 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... detector systems. Each turbine engine powered rotorcraft must have approved quick-acting fire detectors in...

  10. 14 CFR 27.1195 - Fire detector systems.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Fire detector systems. 27.1195 Section 27.1195 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... detector systems. Each turbine engine powered rotorcraft must have approved quick-acting fire detectors in...

  11. 14 CFR 27.1195 - Fire detector systems.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Fire detector systems. 27.1195 Section 27.1195 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT... detector systems. Each turbine engine powered rotorcraft must have approved quick-acting fire detectors in...

  12. Development and testing of dry chemicals in advanced extinguishing systems for jet engine nacelle fires

    NASA Technical Reports Server (NTRS)

    Altman, R. L.; Ling, A. C. (Editor); Mayer, L. A.; Myronik, D. J.

    1979-01-01

    The effectiveness of dry chemical in extinguishing and delaying reignition of fires resulting from hydrocarbon fuel leaking onto heated surfaces such as can occur in jet engine nacelles is studied. The commercial fire extinguishant dry chemical tried are sodium and potassium bicarbonate, carbonate, chloride, carbamate (Monnex), metal halogen, and metal hydroxycarbonate compounds. Synthetic and preparative procedures for new materials developed, a new concept of fire control by dry chemical agents, descriptions of experiment assemblages to test dry chemical fire extinguishant efficiencies in controlling fuel fires initiated by hot surfaces, comparative testing data for more than 25 chemical systems in a 'static' assemblage with no air flow across the heated surface, and similar comparative data for more than ten compounds in a dynamic system with air flows up to 350 ft/sec are presented.

  13. Defense Acquisitions: Assessments of Selected Weapon Programs

    DTIC Science & Technology

    2017-03-01

    PAC-3 MSE) 81 Warfighter Information Network-Tactical (WIN-T) Increment 2 83 Improved Turbine Engine Program (ITEP) 85 Long Range Precision Fires...Unmanned Air System 05/2018 —- O  Joint Surveillance Target Attack Radar System Recapitalization 10/2017 —- O  Improved Turbine Engine Program TBD...Network-Tactical (WIN-T) Increment 2 83 1-page assessments Improved Turbine Engine Program (ITEP) 85 Long Range Precision Fires (LRPF) 86

  14. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant Conceptual Design Engineering Report (CDER)

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The reference conceptual design of the magnetohydrodynamic (MHD) Engineering Test Facility (ETF), a prototype 200 MWe coal-fired electric generating plant designed to demonstrate the commercial feasibility of open cycle MHD, is summarized. Main elements of the design, systems, and plant facilities are illustrated. System design descriptions are included for closed cycle cooling water, industrial gas systems, fuel oil, boiler flue gas, coal management, seed management, slag management, plant industrial waste, fire service water, oxidant supply, MHD power ventilating

  15. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant Conceptual Design Engineering Report (CDER)

    NASA Astrophysics Data System (ADS)

    1981-09-01

    The reference conceptual design of the magnetohydrodynamic (MHD) Engineering Test Facility (ETF), a prototype 200 MWe coal-fired electric generating plant designed to demonstrate the commercial feasibility of open cycle MHD, is summarized. Main elements of the design, systems, and plant facilities are illustrated. System design descriptions are included for closed cycle cooling water, industrial gas systems, fuel oil, boiler flue gas, coal management, seed management, slag management, plant industrial waste, fire service water, oxidant supply, MHD power ventilating

  16. Automated Propulsion Data Screening demonstration system

    NASA Technical Reports Server (NTRS)

    Hoyt, W. Andes; Choate, Timothy D.; Whitehead, Bruce A.

    1995-01-01

    A fully-instrumented firing of a propulsion system typically generates a very large quantity of data. In the case of the Space Shuttle Main Engine (SSME), data analysis from ground tests and flights is currently a labor-intensive process. Human experts spend a great deal of time examining the large volume of sensor data generated by each engine firing. These experts look for any anomalies in the data which might indicate engine conditions warranting further investigation. The contract effort was to develop a 'first-cut' screening system for application to SSME engine firings that would identify the relatively small volume of data which is unusual or anomalous in some way. With such a system, limited and expensive human resources could focus on this small volume of unusual data for thorough analysis. The overall project objective was to develop a fully operational Automated Propulsion Data Screening (APDS) system with the capability of detecting significant trends and anomalies in transient and steady-state data. However, the effort limited screening of transient data to ground test data for throttle-down cases typical of the 3-g acceleration, and for engine throttling required to reach the maximum dynamic pressure limits imposed on the Space Shuttle. This APDS is based on neural networks designed to detect anomalies in propulsion system data that are not part of the data used for neural network training. The delivered system allows engineers to build their own screening sets for application to completed or planned firings of the SSME. ERC developers also built some generic screening sets that NASA engineers could apply immediately to their data analysis efforts.

  17. 46 CFR 161.002-9 - Automatic fire detecting system, power supply.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... system must meet the requirements of § 113.10-9 of subchapter J (Electrical Engineering Regulations) of... 46 Shipping 6 2013-10-01 2013-10-01 false Automatic fire detecting system, power supply. 161.002-9..., CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL ELECTRICAL EQUIPMENT Fire-Protective Systems § 161.002...

  18. 46 CFR 161.002-9 - Automatic fire detecting system, power supply.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... system must meet the requirements of § 113.10-9 of subchapter J (Electrical Engineering Regulations) of... 46 Shipping 6 2014-10-01 2014-10-01 false Automatic fire detecting system, power supply. 161.002-9..., CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL ELECTRICAL EQUIPMENT Fire-Protective Systems § 161.002...

  19. 46 CFR 161.002-9 - Automatic fire detecting system, power supply.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... system must meet the requirements of § 113.10-9 of subchapter J (Electrical Engineering Regulations) of... 46 Shipping 6 2012-10-01 2012-10-01 false Automatic fire detecting system, power supply. 161.002-9..., CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL ELECTRICAL EQUIPMENT Fire-Protective Systems § 161.002...

  20. NASA Conducts 2nd RS-25 Engine Hot Fire of 2018

    NASA Image and Video Library

    2018-02-01

    A 365-second hot fire test on Feb. 1, 2018, at NASA’s Stennis Space Center in Mississippi marks the completion of “green run” testing, or flight certification, for all new RS-25 engine flight controllers slated for Exploration Mission-2, the first Space Launch System mission with astronauts on board. In addition to the flight controller, the Feb. 1 hot fire also marked the third test of a 3D printed pogo accumulator assembly for the RS-25 engine.

  1. Aircraft Instrument, Fire Protection, Warning, Communication, Navigation and Cabin Atmosphere Control System (Course Outline), Aviation Mechanics 3 (Air Frame): 9067.04.

    ERIC Educational Resources Information Center

    Dade County Public Schools, Miami, FL.

    This document presents an outline for a 135-hour course designed to familiarize the student with manipulative skills and theoretical knowledge concerning aircraft instrument systems like major flight and engine instruments; fire protection and fire fighting systems; warning systems and navigation systems; aircraft cabin control systems, such as…

  2. Video File - NASA on a Roll Testing Space Launch System Flight Engines

    NASA Image and Video Library

    2017-08-09

    Just two weeks after conducting another in a series of tests on new RS-25 rocket engine flight controllers for NASA’s Space Launch System (SLS) rocket, engineers at NASA’s Stennis Space Center in Mississippi completed one more hot-fire test of a flight controller on August 9, 2017. With the hot fire, NASA has moved a step closer in completing testing on the four RS-25 engines which will power the first integrated flight of the SLS rocket and Orion capsule known as Exploration Mission 1.

  3. 76 FR 3566 - Airworthiness Directives; The Boeing Company Model 777-200 and -300 Series Airplanes Equipped...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-20

    ... hydraulic fluid contamination, which can cause cracking of titanium parts in the system disconnect assembly, resulting in compromise of the engine firewall. A cracked firewall can allow fire in the engine area to enter the strut and can lead to an uncontained engine strut fire if flammable fluid is present. Cracking...

  4. KSC-2010-5768

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket awaits a static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station, in which all nine Merlin engines will fire at once. The engines use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Rusty Backer

  5. Digital Image Correlation Techniques Applied to Large Scale Rocket Engine Testing

    NASA Technical Reports Server (NTRS)

    Gradl, Paul R.

    2016-01-01

    Rocket engine hot-fire ground testing is necessary to understand component performance, reliability and engine system interactions during development. The J-2X upper stage engine completed a series of developmental hot-fire tests that derived performance of the engine and components, validated analytical models and provided the necessary data to identify where design changes, process improvements and technology development were needed. The J-2X development engines were heavily instrumented to provide the data necessary to support these activities which enabled the team to investigate any anomalies experienced during the test program. This paper describes the development of an optical digital image correlation technique to augment the data provided by traditional strain gauges which are prone to debonding at elevated temperatures and limited to localized measurements. The feasibility of this optical measurement system was demonstrated during full scale hot-fire testing of J-2X, during which a digital image correlation system, incorporating a pair of high speed cameras to measure three-dimensional, real-time displacements and strains was installed and operated under the extreme environments present on the test stand. The camera and facility setup, pre-test calibrations, data collection, hot-fire test data collection and post-test analysis and results are presented in this paper.

  6. 75 FR 68245 - Airworthiness Directives; McDonnell Douglas Corporation Model MD-90-30 Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-05

    ... shutoff system wiring. This proposed AD was prompted by a possible latent failure in the fire handle... engine fuel fire shutoff handle is activated. Separating the fire handle shutoff system wiring will... handle shutoff system wiring. FAA's Determination We are proposing this AD because we evaluated all the...

  7. Aircraft Alerting Systems Standardization Study. Volume I. Candidate System Validation and Time-Critical Display Evaluation.

    DTIC Science & Technology

    1981-01-01

    SELCAL FLT ALT ATNI AUO ALT BRK CANSELCAL OVSO CALL CONTRL ALRT _ I7CT be SPLR b 0 11CALL Figure 5.4.4-1 Pilot’s Response Panel Figure 5.4.4-2 Flight...Galley bus off 27 GLY BUS OFF A RP ELEC CYCLE SWITCH Utility bus off 28 UTIL BUS OFF A RP ELEC CYCLE SWITCH Right engine 29 R ENG HYD PUMP A RP HYD...CYCLE SWITCH hydraulic pump Left engine 30 L ENG FIRE DET A RP FIRE RP FIRE fire detector Left brake overheat 31 L BRAKE OVHT A RP BRK RP BRK Right

  8. Unified Facilities Criteria (UFC) Design: Fire Protection Engineering for Facilities

    DTIC Science & Technology

    2003-08-20

    following provisions: • Ceiling sprinkler design area must be increased by 10 percent. ESFR sprinklers must increase the required number to be...Control System ESFR Early Suppression Fast-Response Sprinklers ETL Engineering Technical Letters FAAA Fire Administration Authorization Act FM

  9. Aerospike Engine Post-Test Diagnostic System Delivered to Rocketdyne

    NASA Technical Reports Server (NTRS)

    Meyer, Claudia M.

    2000-01-01

    The NASA Glenn Research Center at Lewis Field, in cooperation with Rocketdyne, has designed, developed, and implemented an automated Post-Test Diagnostic System (PTDS) for the X-33 linear aerospike engine. The PTDS was developed to reduce analysis time and to increase the accuracy and repeatability of rocket engine ground test fire and flight data analysis. This diagnostic system provides a fast, consistent, first-pass data analysis, thereby aiding engineers who are responsible for detecting and diagnosing engine anomalies from sensor data. It uses analytical methods modeled after the analysis strategies used by engineers. Glenn delivered the first version of PTDS in September of 1998 to support testing of the engine s power pack assembly. The system was used to analyze all 17 power pack tests and assisted Rocketdyne engineers in troubleshooting both data acquisition and test article anomalies. The engine version of PTDS, which was delivered in June of 1999, will support all single-engine, dual-engine, and flight firings of the aerospike engine.

  10. 14 CFR 23.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... systems must be installed and compliance shown with the following: (1) Except for combustor, turbine, and tailpipe sections of turbine-engine installations that contain lines or components carrying flammable fluids or gases for which a fire originating in these sections is shown to be controllable, a fire...

  11. 14 CFR 25.1203 - Fire detector system.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... fire zone, and in the combustion, turbine, and tailpipe sections of turbine engine installations, in... short circuit. (c) No fire or overheat detector may be affected by any oil, water, other fluids or fumes...

  12. 14 CFR 25.1203 - Fire detector system.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... fire zone, and in the combustion, turbine, and tailpipe sections of turbine engine installations, in... short circuit. (c) No fire or overheat detector may be affected by any oil, water, other fluids or fumes...

  13. 14 CFR 25.1203 - Fire detector system.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... fire zone, and in the combustion, turbine, and tailpipe sections of turbine engine installations, in... short circuit. (c) No fire or overheat detector may be affected by any oil, water, other fluids or fumes...

  14. 14 CFR 25.1203 - Fire detector system.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... fire zone, and in the combustion, turbine, and tailpipe sections of turbine engine installations, in... short circuit. (c) No fire or overheat detector may be affected by any oil, water, other fluids or fumes...

  15. Preparing to Test

    NASA Image and Video Library

    2015-03-26

    Stennis Space Center employees install a 96-inch valve during a recent upgrade of the high-pressure industrial water system that serves the site’s large rocket engine test stands. The upgraded system has a capacity to flow 335,000 gallons of water a minute, which is a critical element for testing. At Stennis, engines are anchored in place on large test stands and fired just as they are during an actual space flight. The fire and exhaust from the test is redirected out of the stand by a large flame trench. A water deluge system directs thousands of gallons of water needed to cool the exhaust. Water also must be available for fire suppression in the event of a mishap. The new system supports RS-25 engine testing on the A-1 Test Stand, as well as testing of the core stage of NASA’s new Space Launch System on the B-2 Test Stand at Stennis.

  16. Fire Effects Information System: New engine, remodeled interior, added options

    Treesearch

    Jane Kapler Smith

    2010-01-01

    Some of today's firefighters weren't even born when the Fire Effects Information System (FEIS) (Web site ) "hit the streets" in 1986. Managers might remember using a dial-up connection in the early 1990s to access information on biology, ecology, and fire offered by FEIS.

  17. Final RS-25 Engine Test of the Summer

    NASA Image and Video Library

    2017-08-30

    On Aug. 30, engineers at our Stennis Space Center wrapped up a summer of hot fire testing for flight controllers on RS-25 engines that will help power the new Space Launch System rocket being built to carry astronauts to deep-space destinations, including Mars. The 500-second hot fire of a flight controller or “brain” of the engine marked another step toward the nation’s return to human deep-space exploration missions. Four RS-25 engines, equipped with flight-worthy controllers will help power the first integrated flight of our Space Launch System rocket with our Orion spacecraft, known as Exploration Mission One.

  18. 14 CFR 27.1189 - Shutoff means.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ...— (1) Lines, fittings, and components forming an intergral part of an engine; (2) For oil systems for which all components of the system, including oil tanks, are fireproof or located in areas not subject to engine fire conditions; and (3) For reciprocating engine installations only, engine oil system...

  19. KSC-2010-5772

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket awaits a static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station, in which all nine Merlin engines will fire at once. The engines use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  20. KSC-2010-5774

    NASA Image and Video Library

    2010-12-04

    CAPE CANAVERAL, Fla. -- During a static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station, all nine Merlin engines of the SpaceX Falcon 9 rocket fire at once. The engines use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust. After the test, SpaceX began to conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which ended after the engines fired at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  1. KSC-2010-5775

    NASA Image and Video Library

    2010-12-04

    CAPE CANAVERAL, Fla. -- During a static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station, all nine Merlin engines of the SpaceX Falcon 9 rocket fire at once. The engines use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust. After the test, SpaceX began to conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which ended after the engines fired at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  2. KSC-2010-5776

    NASA Image and Video Library

    2010-12-04

    CAPE CANAVERAL, Fla. -- During a static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station, all nine Merlin engines of the SpaceX Falcon 9 rocket fire at once. The engines use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust. After the test, SpaceX began to conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which ended after the engines fired at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  3. 14 CFR 25.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... extinguishing systems. (a) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire...

  4. 14 CFR 25.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... extinguishing systems. (a) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire...

  5. 14 CFR 25.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... extinguishing systems. (a) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire...

  6. 14 CFR 25.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... extinguishing systems. (a) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire...

  7. 14 CFR 25.1195 - Fire extinguishing systems.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... extinguishing systems. (a) Except for combustor, turbine, and tail pipe sections of turbine engine installations that contain lines or components carrying flammable fluids or gases for which it is shown that a fire...

  8. Simultaneously firing two cylinders of an even firing camless engine

    DOEpatents

    Brennan, Daniel G

    2014-03-11

    A valve control system includes an engine speed control module that determines an engine speed and a desired engine stop position. A piston position module determines a desired stopping position of a first piston based on the desired engine stop position. A valve control module receives the desired stopping position, commands a set of valves to close at the desired stopping position if the engine speed is less than a predetermined shutdown threshold, and commands the set of valves to reduce the engine speed if the engine speed is greater than the predetermined shutdown threshold.

  9. Oxygen Compatibility Assessment of Components and Systems

    NASA Technical Reports Server (NTRS)

    Stoltzfus, Joel; Sparks, Kyle

    2010-01-01

    Fire hazards are inherent in oxygen systems and a storied history of fires in rocket engine propulsion components exists. To detect and mitigate these fire hazards requires careful, detailed, and thorough analyses applied during the design process. The oxygen compatibility assessment (OCA) process designed by NASA Johnson Space Center (JSC) White Sands Test Facility (WSTF) can be used to determine the presence of fire hazards in oxygen systems and the likelihood of a fire. This process may be used as both a design guide and during the approval process to ensure proper design features and material selection. The procedure for performing an OCA is a structured step-by-step process to determine the most severe operating conditions; assess the flammability of the system materials at the use conditions; evaluate the presence and efficacy of ignition mechanisms; assess the potential for a fire to breach the system; and determine the reaction effect (the potential loss of life, mission, and system functionality as the result of a fire). This process should be performed for each component in a system. The results of each component assessment, and the overall system assessment, should be recorded in a report that can be used in the short term to communicate hazards and their mitigation and to aid in system/component development and, in the long term, to solve anomalies that occur during engine testing and operation.

  10. KSC-2010-5769

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station was aborted at T minus 1.1 seconds due to high engine chamber pressure. During the test, all nine Merlin engines, which use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust, are expected to fire at once. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Rusty Backer

  11. Mass Analyzers Facilitate Research on Addiction

    NASA Technical Reports Server (NTRS)

    2012-01-01

    The famous go/no go command for Space Shuttle launches comes from a place called the Firing Room. Located at Kennedy Space Center in the Launch Control Center (LCC), there are actually four Firing Rooms that take up most of the third floor of the LCC. These rooms comprise the nerve center for Space Shuttle launch and processing. Test engineers in the Firing Rooms operate the Launch Processing System (LPS), which is a highly automated, computer-controlled system for assembly, checkout, and launch of the Space Shuttle. LPS monitors thousands of measurements on the Space Shuttle and its ground support equipment, compares them to predefined tolerance levels, and then displays values that are out of tolerance. Firing Room operators view the data and send commands about everything from propellant levels inside the external tank to temperatures inside the crew compartment. In many cases, LPS will automatically react to abnormal conditions and perform related functions without test engineer intervention; however, firing room engineers continue to look at each and every happening to ensure a safe launch. Some of the systems monitored during launch operations include electrical, cooling, communications, and computers. One of the thousands of measurements derived from these systems is the amount of hydrogen and oxygen inside the shuttle during launch.

  12. A study of the durability of beryllium rocket engines. [space shuttle reaction control system

    NASA Technical Reports Server (NTRS)

    Paster, R. D.; French, G. C.

    1974-01-01

    An experimental test program was performed to demonstrate the durability of a beryllium INTEREGEN rocket engine when operating under conditions simulating the space shuttle reaction control system. A vibration simulator was exposed to the equivalent of 100 missions of X, Y, and Z axes random vibration to demonstrate the integrity of the recently developed injector-to-chamber braze joint. An off-limits engine was hot fired under extreme conditions of mixture ratio, chamber pressure, and orifice plugging. A durability engine was exposed to six environmental cycles interspersed with hot-fire tests without intermediate cleaning, service, or maintenance. Results from this program indicate the ability of the beryllium INTEREGEN engine concept to meet the operational requirements of the space shuttle reaction control system.

  13. Video File - RS-25 Engine Test 2017-08-30

    NASA Image and Video Library

    2017-08-30

    NASA engineers closed a summer of hot fire testing Aug. 30 for flight controllers on RS-25 engines that will help power the new Space Launch System (SLS) rocket being built to carry astronauts to deep-space destinations, including Mars. The 500-second hot fire an RS-25 engine flight controller unit on the A-1 Test Stand at Stennis Space Center near Bay St. Louis, Mississippi marked another step toward the nation’s return to human deep-space exploration missions.

  14. 46 CFR 56.01-10 - Plan approval.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...) Fire extinguishing systems including fire main and sprinkler piping, inert gas and foam. (vi) Bilge and..., I-L, and II-L systems. (ii) All Class II firemain, foam, sprinkler, bilge and ballast, vent sounding... GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND APPURTENANCES...

  15. 46 CFR 56.01-10 - Plan approval.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...) Fire extinguishing systems including fire main and sprinkler piping, inert gas and foam. (vi) Bilge and..., I-L, and II-L systems. (ii) All Class II firemain, foam, sprinkler, bilge and ballast, vent sounding... GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND APPURTENANCES...

  16. 46 CFR 56.01-10 - Plan approval.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...) Fire extinguishing systems including fire main and sprinkler piping, inert gas and foam. (vi) Bilge and..., I-L, and II-L systems. (ii) All Class II firemain, foam, sprinkler, bilge and ballast, vent sounding... GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND APPURTENANCES...

  17. 46 CFR 56.01-10 - Plan approval.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...) Fire extinguishing systems including fire main and sprinkler piping, inert gas and foam. (vi) Bilge and..., I-L, and II-L systems. (ii) All Class II firemain, foam, sprinkler, bilge and ballast, vent sounding... GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING PIPING SYSTEMS AND APPURTENANCES...

  18. 5. DETAIL VIEW OF OLD, PUNCHTYPE MASTER FIRE ALARM SYSTEM, ...

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

    5. DETAIL VIEW OF OLD, PUNCH-TYPE MASTER FIRE ALARM SYSTEM, LOCATED ON S WALL OF ENGINE STORAGE ROOM; LOOKING S. (Ceronie and Ryan) - Watervliet Arsenal, Building No. 22, Westervelt Avenue & Buffington Street, Watervliet, Albany County, NY

  19. 14 CFR Appendix D to Part 147 - Powerplant Curriculum Subjects

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... (CONTINUED) SCHOOLS AND OTHER CERTIFICATED AGENCIES AVIATION MAINTENANCE TECHNICIAN SCHOOLS Pt. 147, App. D... engine temperature, pressure, and r.p.m. indicating systems. b. engine fire protection systems (3) 11... repair heat exchangers, superchargers, and turbine engine airflow and temperature control systems. (3) 28...

  20. Fire safety practices in the Shuttle and the Space Station Freedom

    NASA Technical Reports Server (NTRS)

    Friedman, Robert

    1993-01-01

    The Shuttle reinforces its policy of fire-preventive measures with onboard smoke detectors and Halon 1301 fire extinguishers. The forthcoming Space Station Freedom will have expanded fire protection with photoelectric smoke detectors, radiation flame detectors, and both fixed and portable carbon dioxide fire extinguishers. Many design and operational issues remain to be resolved for Freedom. In particular, the fire-suppression designs must consider the problems of gas leakage in toxic concentrations, alternative systems for single-failure redundancy, and commonality with the corresponding systems of the Freedom international partners. While physical and engineering requirements remain the primary driving forces for spacecraft fire-safety technology, there are, nevertheless, needs and opportunities for the application of microgravity combustion knowledge to improve and optimize the fire-protective systems.

  1. KSC-2010-5773

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station was aborted at T minus 1.1 seconds due to high engine chamber pressure. During the test, all nine Merlin engines, which use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust, are expected to fire at once. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  2. KSC-2010-5770

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station was aborted at T minus 1.1 seconds due to high engine chamber pressure. During the test, all nine Merlin engines, which use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust, are expected to fire at once. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  3. KSC-2010-5771

    NASA Image and Video Library

    2010-12-03

    CAPE CANAVERAL, Fla. -- The SpaceX Falcon 9 rocket static fire test on Space Launch Complex-40 at Cape Canaveral Air Force Station was aborted at T minus 1.1 seconds due to high engine chamber pressure. During the test, all nine Merlin engines, which use rocket-grade kerosene and liquid oxygen to produce 1 million pounds of thrust, are expected to fire at once. After the test, SpaceX will conduct a thorough review of all data as engineers make final preparations for the first launch of the Commercial Orbital Transportation Services (COTS) Dragon spacecraft to low Earth orbit atop the Falcon 9. This first stage firing is part of a full launch dress rehearsal, which will end after the engines fire at full power for two seconds, with only the hold-down system restraining the rocket from flight. Photo credit: NASA/Tony Gray and Kevin O'Connell

  4. Fastrac Nozzle Design, Performance and Development

    NASA Technical Reports Server (NTRS)

    Peters, Warren; Rogers, Pat; Lawrence, Tim; Davis, Darrell; DAgostino, Mark; Brown, Andy

    2000-01-01

    With the goal of lowering the cost of payload to orbit, NASA/MSFC (Marshall Space Flight Center) researched ways to decrease the complexity and cost of an engine system and its components for a small two-stage booster vehicle. The composite nozzle for this Fastrac Engine was designed, built and tested by MSFC with fabrication support and engineering from Thiokol-SEHO (Science and Engineering Huntsville Operation). The Fastrac nozzle uses materials, fabrication processes and design features that are inexpensive, simple and easily manufactured. As the low cost nozzle (and injector) design matured through the subscale tests and into full scale hot fire testing, X-34 chose the Fastrac engine for the propulsion plant for the X-34. Modifications were made to nozzle design in order to meet the new flight requirements. The nozzle design has evolved through subscale testing and manufacturing demonstrations to full CFD (Computational Fluid Dynamics), thermal, thermomechanical and dynamic analysis and the required component and engine system tests to validate the design. The Fastrac nozzle is now in final development hot fire testing and has successfully accumulated 66 hot fire tests and 1804 seconds on 18 different nozzles.

  5. Saturn Apollo Program

    NASA Image and Video Library

    1966-09-15

    This vintage photograph shows the 138-foot long first stage of the Saturn V being lowered to the ground following a successful static test firing at Marshall Space flight Center's S-1C test stand. The firing provided NASA engineers information on the booster's systems. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

  6. Quick look test report: MPT static firing no. 2 test MPT-S2

    NASA Technical Reports Server (NTRS)

    1978-01-01

    The three engine cluster was fired at 70 percent power level for a nominal 15 seconds to evaluate the integrated performance of the main propulsion system. Engine ignition occurred at approximately 1403 with the planned mainstage duration achieved for all three engines. Operation of all systems was as expected with the exception of the recirculation pumps. The pumps were started while the propellant loading was in fast fill, but they cavitated and lost head at the termination of fast fill. The pumps were subsequently restarted after pressurizing the tank and draining back propellant to get good quality. Post test inspection of the engines revealed some discoloration on the inside of the thrust chamber and distorted drain lines for engine #2.

  7. A simulation and optimisation procedure to model daily suppression resource transfers during a fire season in Colorado

    Treesearch

    Yu Wei; Erin J. Belval; Matthew P. Thompson; Dave E. Calkin; Crystal S. Stonesifer

    2016-01-01

    Sharing fire engines and crews between fire suppression dispatch zones may help improve the utilisation of fire suppression resources. Using the Resource Ordering and Status System, the Predictive Services’ Fire Potential Outlooks and the Rocky Mountain Region Preparedness Levels from 2010 to 2013, we tested a simulation and optimisation procedure to transfer crews and...

  8. Computational Pollutant Environment Assessment from Propulsion-System Testing

    NASA Technical Reports Server (NTRS)

    Wang, Ten-See; McConnaughey, Paul; Chen, Yen-Sen; Warsi, Saif

    1996-01-01

    An asymptotic plume growth method based on a time-accurate three-dimensional computational fluid dynamics formulation has been developed to assess the exhaust-plume pollutant environment from a simulated RD-170 engine hot-fire test on the F1 Test Stand at Marshall Space Flight Center. Researchers have long known that rocket-engine hot firing has the potential for forming thermal nitric oxides, as well as producing carbon monoxide when hydrocarbon fuels are used. Because of the complex physics involved, most attempts to predict the pollutant emissions from ground-based engine testing have used simplified methods, which may grossly underpredict and/or overpredict the pollutant formations in a test environment. The objective of this work has been to develop a computational fluid dynamics-based methodology that replicates the underlying test-stand flow physics to accurately and efficiently assess pollutant emissions from ground-based rocket-engine testing. A nominal RD-170 engine hot-fire test was computed, and pertinent test-stand flow physics was captured. The predicted total emission rates compared reasonably well with those of the existing hydrocarbon engine hot-firing test data.

  9. 14 CFR 23.903 - Engines.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... engine compartment) of any system that can affect an engine (other than a fuel tank if only one fuel tank...) Starting and stopping (piston engine). (1) The design of the installation must be such that risk of fire or...

  10. 14 CFR 23.903 - Engines.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... engine compartment) of any system that can affect an engine (other than a fuel tank if only one fuel tank...) Starting and stopping (piston engine). (1) The design of the installation must be such that risk of fire or...

  11. Hot-Fire Test Results of Liquid Oxygen/RP-2 Multi-Element Oxidizer-Rich Preburners

    NASA Technical Reports Server (NTRS)

    Protz, C. S.; Garcia, C. P.; Casiano, M. J.; Parton, J. A.; Hulka, J. R.

    2016-01-01

    As part of the Combustion Stability Tool Development project funded by the Air Force Space and Missile Systems Center, the NASA Marshall Space Flight Center was contracted to assemble and hot-fire test a multi-element integrated test article demonstrating combustion characteristics of an oxygen/hydrocarbon propellant oxidizer-rich staged-combustion engine thrust chamber. Such a test article simulates flow through the main injectors of oxygen/kerosene oxidizer-rich staged combustion engines such as the Russian RD-180 or NK-33 engines, or future U.S.-built engine systems such as the Aerojet-Rocketdyne AR-1 engine or the Hydrocarbon Boost program demonstration engine. To supply the oxidizer-rich combustion products to the main injector of the integrated test article, existing subscale preburner injectors from a previous NASA-funded oxidizer-rich staged combustion engine development program were utilized. For the integrated test article, existing and newly designed and fabricated inter-connecting hot gas duct hardware were used to supply the oxidizer-rich combustion products to the oxidizer circuit of the main injector of the thrust chamber. However, before one of the preburners was used in the integrated test article, it was first hot-fire tested at length to prove it could provide the hot exhaust gas mean temperature, thermal uniformity and combustion stability necessary to perform in the integrated test article experiment. This paper presents results from hot-fire testing of several preburner injectors in a representative combustion chamber with a sonic throat. Hydraulic, combustion performance, exhaust gas thermal uniformity, and combustion stability data are presented. Results from combustion stability modeling of these test results are described in a companion paper at this JANNAF conference, while hot-fire test results of the preburner injector in the integrated test article are described in another companion paper.

  12. 14 CFR 23.1203 - Fire detector system.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... in— (1) An engine compartment of— (i) Multiengine turbine powered airplanes; (ii) Multiengine... may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids...

  13. 14 CFR 23.1203 - Fire detector system.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... in— (1) An engine compartment of— (i) Multiengine turbine powered airplanes; (ii) Multiengine... may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids...

  14. 14 CFR 23.1203 - Fire detector system.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... in— (1) An engine compartment of— (i) Multiengine turbine powered airplanes; (ii) Multiengine... may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids...

  15. 14 CFR 23.1203 - Fire detector system.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... in— (1) An engine compartment of— (i) Multiengine turbine powered airplanes; (ii) Multiengine... may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids...

  16. 14 CFR 23.1203 - Fire detector system.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... in— (1) An engine compartment of— (i) Multiengine turbine powered airplanes; (ii) Multiengine... may be subjected in operation. (c) No fire detector may be affected by any oil, water, other fluids...

  17. An investigation of enhanced capability thermal barrier coating systems for diesel engine components

    NASA Technical Reports Server (NTRS)

    Holtzman, R. L.; Layne, J. L.; Schechter, B.

    1984-01-01

    Material systems and processes for the development of effective and durable thermal barriers for heavy duty diesel engines were investigated. Seven coating systems were evaluated for thermal conductivity, erosion resistance, corrosion/oxidation resistance, and thermal shock resistance. An advanced coating system based on plasma sprayed particle yttria stabilized zirconia (PS/HYSZ) was judged superior in these tests. The measured thermal conductivity of the selected coating was 0.893 W/m C at 371 C. The PS/HYSZ coating system was applied to the piston crown, fire deck and valves of a single cylinder low heat rejection diesel engine. The coated engine components were tested for 24 hr at power levels from 0.83 MPa to 1.17 MPa brake mean effective pressure. The component coatings survived the engine tests with a minimum of distress. The measured fire deck temperatures decreased 86 C (155 F) on the intake side and 42 C (75 F) on the exhaust side with the coating applied.

  18. NASA Conducts First RS-25 Rocket Engine Test of 2015

    NASA Image and Video Library

    2015-01-09

    From the Press Release: The new year is off to a hot start for NASA's Space Launch System (SLS). The engine that will drive America's next great rocket to deep space blazed through its first successful test Jan. 9 at the agency's Stennis Space Center near Bay St. Louis, Mississippi. The RS-25, formerly the space shuttle main engine, fired up for 500 seconds on the A-1 test stand at Stennis, providing NASA engineers critical data on the engine controller unit and inlet pressure conditions. This is the first hot fire of an RS-25 engine since the end of space shuttle main engine testing in 2009. Four RS-25 engines will power SLS on future missions, including to an asteroid and Mars. "We’ve made modifications to the RS-25 to meet SLS specifications and will analyze and test a variety of conditions during the hot fire series,” said Steve Wofford, manager of the SLS Liquid Engines Office at NASA's Marshall Space Flight Center in Huntsville, Alabama, where the SLS Program is managed. "The engines for SLS will encounter colder liquid oxygen temperatures than shuttle; greater inlet pressure due to the taller core stage liquid oxygen tank and higher vehicle acceleration; and more nozzle heating due to the four-engine configuration and their position in-plane with the SLS booster exhaust nozzles.” The engine controller unit, the "brain" of the engine, allows communication between the vehicle and the engine, relaying commands to the engine and transmitting data back to the vehicle. The controller also provides closed-loop management of the engine by regulating the thrust and fuel mixture ratio while monitoring the engine's health and status. The new controller will use updated hardware and software configured to operate with the new SLS avionics architecture. "This first hot-fire test of the RS-25 engine represents a significant effort on behalf of Stennis Space Center’s A-1 test team," said Ronald Rigney, RS-25 project manager at Stennis. "Our technicians and engineers have been working diligently to design, modify and activate an extremely complex and capable facility in support of RS-25 engine testing." Testing will resume in April after upgrades are completed on the high pressure industrial water system, which provides cool water for the test facility during a hot fire test. Eight tests, totaling 3,500 seconds, are planned for the current development engine. Another development engine later will undergo 10 tests, totaling 4,500 seconds. The second test series includes the first test of new flight controllers, known as green running. The first flight test of the SLS will feature a configuration for a 70-metric-ton (77-ton) lift capacity and carry an uncrewed Orion spacecraft beyond low-Earth orbit to test the performance of the integrated system. As the SLS is upgraded, it will provide an unprecedented lift capability of 130 metric tons (143 tons) to enable missions even farther into our solar system.

  19. 14 CFR 25.1203 - Fire detector system.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... fire zone, and in the combustion, turbine, and tailpipe sections of turbine engine installations, in... the sensor or associated wiring within a designated fire zone is severed at one point, unless the... means to warn the crew in the event of a short circuit in the sensor or associated wiring within a...

  20. 46 CFR 27.203 - What are the requirements for fire detection on towing vessels?

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...— (a) Each detector, each control panel, and each fire alarm are approved under 46 CFR subpart 161.002...; (c) The system is arranged and installed so a fire in the engine room automatically sets off alarms... light; (2) Both an audible alarm to notify crew at the operating station of fire and visible alarms to...

  1. 46 CFR 27.203 - What are the requirements for fire detection on towing vessels?

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...— (a) Each detector, each control panel, and each fire alarm are approved under 46 CFR subpart 161.002...; (c) The system is arranged and installed so a fire in the engine room automatically sets off alarms... light; (2) Both an audible alarm to notify crew at the operating station of fire and visible alarms to...

  2. 46 CFR 27.203 - What are the requirements for fire detection on towing vessels?

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...— (a) Each detector, each control panel, and each fire alarm are approved under 46 CFR subpart 161.002...; (c) The system is arranged and installed so a fire in the engine room automatically sets off alarms... light; (2) Both an audible alarm to notify crew at the operating station of fire and visible alarms to...

  3. 46 CFR 27.203 - What are the requirements for fire detection on towing vessels?

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...— (a) Each detector, each control panel, and each fire alarm are approved under 46 CFR subpart 161.002...; (c) The system is arranged and installed so a fire in the engine room automatically sets off alarms... light; (2) Both an audible alarm to notify crew at the operating station of fire and visible alarms to...

  4. Wallace L. Fons: fire research pioneer

    Treesearch

    David R. Weise; Ted R. Fons

    2014-01-01

    During his 30-year career with the U.S. Forest Service, Wally Fons laid the foundation for much of the understanding we have today of forest fire's many properties by applying his mechanical engineering background. He left a legacy of research that formed the basis for the fire behavior and danger systems still used in the United States. In addition to fire...

  5. Self-Contained AFFF Sprinkler System,

    DTIC Science & Technology

    1982-05-01

    aqueous film forming foam ( AFFF ). Such systems are...supply. Extinguishing Agents All fire tests were run with a pre-mixed solution of 6% aqueous film forming foam ( AFFF ) agent in accordance with MIL-F...Applying Aqueous Film Forming Foam on Large-Scale Fires", Civil and Environmental Engineering Development Office (Air Force Systems Command) Report

  6. NASA Concludes Summer of RS-25 Testing

    NASA Image and Video Library

    2017-08-30

    NASA engineers closed a summer of hot fire testing Aug. 30 for flight controllers on RS-25 engines that will help power the new Space Launch System (SLS) rocket being built to carry astronauts to deep-space destinations, including Mars. The 500-second hot fire an RS-25 engine flight controller unit on the A-1 Test Stand at Stennis Space Center near Bay St. Louis, Mississippi marked another step toward the nation’s return to human deep-space exploration missions.

  7. Saturn V First Stage Lowered to the Ground After Static Test

    NASA Technical Reports Server (NTRS)

    1966-01-01

    This vintage photograph shows the 138-foot long first stage of the Saturn V being lowered to the ground following a successful static test firing at Marshall Space flight Center's S-1C test stand. The firing provided NASA engineers information on the booster's systems. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

  8. 46 CFR 111.99-1 - Applicability.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Applicability. 111.99-1 Section 111.99-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-1 Applicability. This subpart applies to fire door...

  9. 46 CFR 111.99-1 - Applicability.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Applicability. 111.99-1 Section 111.99-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-1 Applicability. This subpart applies to fire door...

  10. 46 CFR 111.99-1 - Applicability.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Applicability. 111.99-1 Section 111.99-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-1 Applicability. This subpart applies to fire door...

  11. 46 CFR 111.99-1 - Applicability.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Applicability. 111.99-1 Section 111.99-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-1 Applicability. This subpart applies to fire door...

  12. 46 CFR 111.99-1 - Applicability.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Applicability. 111.99-1 Section 111.99-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-1 Applicability. This subpart applies to fire door...

  13. 14 CFR 29.1189 - Shutoff means.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... engine; (2) For oil systems for turbine engine installations in which all components of the system, including oil tanks, are fireproof or located in areas not subject to engine fire conditions; or (3) For...) There must be means to shut off or otherwise prevent hazardous quantities of fuel, oil, de-icing fluid...

  14. 14 CFR 23.903 - Engines.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... compartment) of any system that can affect an engine (other than a fuel tank if only one fuel tank is... stopping (piston engine). (1) The design of the installation must be such that risk of fire or mechanical...

  15. Testing of Twin Linear Aerospike XRS-2200 Engine

    NASA Technical Reports Server (NTRS)

    2001-01-01

    The test of twin Linear Aerospike XRS-2200 engines, originally built for the X-33 program, was performed on August 6, 2001 at NASA's Sternis Space Center, Mississippi. The engines were fired for the planned 90 seconds and reached a planned maximum power of 85 percent. NASA's Second Generation Reusable Launch Vehicle Program , also known as the Space Launch Initiative (SLI), is making advances in propulsion technology with this third and final successful engine hot fire, designed to test electro-mechanical actuators. Information learned from this hot fire test series about new electro-mechanical actuator technology, which controls the flow of propellants in rocket engines, could provide key advancements for the propulsion systems for future spacecraft. The Second Generation Reusable Launch Vehicle Program, led by NASA's Marshall Space Flight Center in Huntsville, Alabama, is a technology development program designed to increase safety and reliability while reducing costs for space travel. The X-33 program was cancelled in March 2001.

  16. Space shuttle main engine anomaly data and inductive knowledge based systems: Automated corporate expertise

    NASA Technical Reports Server (NTRS)

    Modesitt, Kenneth L.

    1987-01-01

    Progress is reported on the development of SCOTTY, an expert knowledge-based system to automate the analysis procedure following test firings of the Space Shuttle Main Engine (SSME). The integration of a large-scale relational data base system, a computer graphics interface for experts and end-user engineers, potential extension of the system to flight engines, application of the system for training of newly-hired engineers, technology transfer to other engines, and the essential qualities of good software engineering practices for building expert knowledge-based systems are among the topics discussed.

  17. Heat Transfer Principles in Thermal Calculation of Structures in Fire

    PubMed Central

    Zhang, Chao; Usmani, Asif

    2016-01-01

    Structural fire engineering (SFE) is a relatively new interdisciplinary subject, which requires a comprehensive knowledge of heat transfer, fire dynamics and structural analysis. It is predominantly the community of structural engineers who currently carry out most of the structural fire engineering research and design work. The structural engineering curriculum in universities and colleges do not usually include courses in heat transfer and fire dynamics. In some institutions of higher education, there are graduate courses for fire resistant design which focus on the design approaches in codes. As a result, structural engineers who are responsible for structural fire safety and are competent to do their jobs by following the rules specified in prescriptive codes may find it difficult to move toward performance-based fire safety design which requires a deep understanding of both fire and heat. Fire safety engineers, on the other hand, are usually focused on fire development and smoke control, and may not be familiar with the heat transfer principles used in structural fire analysis, or structural failure analysis. This paper discusses the fundamental heat transfer principles in thermal calculation of structures in fire, which might serve as an educational guide for students, engineers and researchers. Insights on problems which are commonly ignored in performance based fire safety design are also presented. PMID:26783379

  18. NASA Tests RS-25 Flight Engine for Space Launch System

    NASA Image and Video Library

    2017-10-19

    Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans.

  19. 46 CFR 181.400 - Where required.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 7 2010-10-01 2010-10-01 false Where required. 181.400 Section 181.400 Shipping COAST... PROTECTION EQUIPMENT Fixed Fire Extinguishing and Detecting Systems § 181.400 Where required. (a) The... cubic meters (6,000 cubic feet); (2) A pre-engineered fixed gas fire extinguishing system must be in...

  20. 46 CFR 34.01-15 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... Systems, IBR approved for § 34.30-1 (“NFPA 13-1996”). (2) NFPA 2001, Standard on Clean Agent Fire... Headquarters. Contact Commandant (CG-ENG), Attn: Office of Design and Engineering Systems, U.S. Coast Guard... F1121-87 (Reapproved 2010), Standard Specification for International Shore Connections for Marine Fire...

  1. 46 CFR 34.01-15 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... Systems, IBR approved for § 34.30-1 (“NFPA 13-1996”). (2) NFPA 2001, Standard on Clean Agent Fire... Headquarters. Contact Commandant (CG-ENG), Attn: Office of Design and Engineering Systems, U.S. Coast Guard... F1121-87 (Reapproved 2010), Standard Specification for International Shore Connections for Marine Fire...

  2. Smoke and fire Rocket-engine ablaze on This Week @NASA – August 14, 2015

    NASA Image and Video Library

    2015-08-14

    On Aug. 13, NASA conducted a test firing of the RS-25 rocket engine at Stennis Space Center. The 535 second test was the sixth in the current series of seven developmental tests of the former space shuttle main engine. Four RS-25 engines will power the core stage of the new Space Launch System (SLS) rocket, which will carry humans deeper into space than ever before, including to an asteroid and Mars. Also, Veggies in space, Russian spacewalk, Supply ship undocks from ISS, Smallest giant black hole, 10th anniversary of MRO launch and more!

  3. 46 CFR 27.209 - What are the requirements for training crews to respond to fires?

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... the engine room and effectively seal all natural openings to the space to prevent leakage of the.... (3) Reporting inoperative alarm systems and fire-detection systems. (4) Putting on a fireman's outfit...) Testing of all alarm and detection systems; and (4) Putting on protective clothing (by at least one person...

  4. Study of aircraft crashworthiness for fire protection

    NASA Technical Reports Server (NTRS)

    Cominsky, A.

    1981-01-01

    Impact-survivable postcrash fire accidents were surveyed. The data base developed includes foreign and domestic accidents involving airlines and jet aircraft. The emphasis was placed on domestic accidents, airlines, and jet aircraft due principally to availability of information. Only transport category aircraft in commercial service designed under FAR Part 25 were considered. A matrix was prepared to show the relationships between the accident characteristics and the fire fatalities. Typical postcrash fire scenaries were identified. Safety concepts were developed for three engineering categories: cabin interiors - cabin subsystems; power plant - engines and fuel systems; and structural mechanics - primary and secondary structures. The parameters identified for concept evaluation are cost, effectiveness, and societal concerns. Three concepts were selected for design definition and cost and effectiveness analysis: improved fire-resistant seat materials; anti-misting kerosene; and additional cabin emergency exits.

  5. Engine System Loads Analysis Compared to Hot-Fire Data

    NASA Technical Reports Server (NTRS)

    Frady, Gregory P.; Jennings, John M.; Mims, Katherine; Brunty, Joseph; Christensen, Eric R.; McConnaughey, Paul R. (Technical Monitor)

    2002-01-01

    Early implementation of structural dynamics finite element analyses for calculation of design loads is considered common design practice for high volume manufacturing industries such as automotive and aeronautical industries. However with the rarity of rocket engine development programs starts, these tools are relatively new to the design of rocket engines. In the NASA MC-1 engine program, the focus was to reduce the cost-to-weight ratio. The techniques for structural dynamics analysis practices, were tailored in this program to meet both production and structural design goals. Perturbation of rocket engine design parameters resulted in a number of MC-1 load cycles necessary to characterize the impact due to mass and stiffness changes. Evolution of loads and load extraction methodologies, parametric considerations and a discussion of load path sensitivities are important during the design and integration of a new engine system. During the final stages of development, it is important to verify the results of an engine system model to determine the validity of the results. During the final stages of the MC-1 program, hot-fire test results were obtained and compared to the structural design loads calculated by the engine system model. These comparisons are presented in this paper.

  6. Impingement effect of service module reaction control system engine plumes. Results of service module reaction control system plume model force field application to an inflight Skylab mission proximity operation situation with the inflight Skylab response

    NASA Technical Reports Server (NTRS)

    Lobb, J. D., Jr.

    1978-01-01

    Plume impingement effects of the service module reaction control system thruster firings were studied to determine if previous flight experience would support the current plume impingement model for the orbiter reaction control system engines. The orbiter reaction control system is used for rotational and translational maneuvers such as those required during rendezvous, braking, docking, and station keeping. Therefore, an understanding of the characteristics and effects of the plume force fields generated by the reaction control system thruster firings were examined to develop the procedures for orbiter/payload proximity operations.

  7. 46 CFR 28.330 - Galley hood and other fire protection equipment.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... Stage of Construction on or After or Which Undergo a Major Conversion Completed on or After September 15... pre-engineered dry or wet chemical fire extinguishing system meeting the applicable sections of NFPA...

  8. Investigation of Altitude Starting and Acceleration Characteristics of J47 Turbojet Engine

    NASA Technical Reports Server (NTRS)

    Golladay, Richard L; Bloomer, Harry E

    1951-01-01

    An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approximately 6200 rpm could be made at a preset constant throttle position. The use of a variable-area nozzle reduced acceleration time.

  9. 41 CFR 102-80.135 - Who is a qualified fire protection engineer?

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... protection engineer? 102-80.135 Section 102-80.135 Public Contracts and Property Management Federal Property... qualified fire protection engineer? A qualified fire protection engineer is defined as an individual with a thorough knowledge and understanding of the principles of physics and chemistry governing fire growth...

  10. Fuel supply system and method for coal-fired prime mover

    DOEpatents

    Smith, William C.; Paulson, Leland E.

    1995-01-01

    A coal-fired gas turbine engine is provided with an on-site coal preparation and engine feeding arrangement. With this arrangement, relatively large dry particles of coal from an on-site coal supply are micro-pulverized and the resulting dry, micron-sized, coal particulates are conveyed by steam or air into the combustion chamber of the engine. Thermal energy introduced into the coal particulates during the micro-pulverizing step is substantially recovered since the so-heated coal particulates are fed directly from the micro-pulverizer into the combustion chamber.

  11. Application of High Speed Digital Image Correlation in Rocket Engine Hot Fire Testing

    NASA Technical Reports Server (NTRS)

    Gradl, Paul R.; Schmidt, Tim

    2016-01-01

    Hot fire testing of rocket engine components and rocket engine systems is a critical aspect of the development process to understand performance, reliability and system interactions. Ground testing provides the opportunity for highly instrumented development testing to validate analytical model predictions and determine necessary design changes and process improvements. To properly obtain discrete measurements for model validation, instrumentation must survive in the highly dynamic and extreme temperature application of hot fire testing. Digital Image Correlation has been investigated and being evaluated as a technique to augment traditional instrumentation during component and engine testing providing further data for additional performance improvements and cost savings. The feasibility of digital image correlation techniques were demonstrated in subscale and full scale hotfire testing. This incorporated a pair of high speed cameras to measure three-dimensional, real-time displacements and strains installed and operated under the extreme environments present on the test stand. The development process, setup and calibrations, data collection, hotfire test data collection and post-test analysis and results are presented in this paper.

  12. 14 CFR 25.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Design and Construction Fire Protection § 25.865 Fire protection of flight controls, engine mounts, and other flight structure. Essential flight controls, engine mounts, and other flight structures located in... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Fire protection of flight controls, engine...

  13. 14 CFR 25.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Design and Construction Fire Protection § 25.865 Fire protection of flight controls, engine mounts, and other flight structure. Essential flight controls, engine mounts, and other flight structures located in... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Fire protection of flight controls, engine...

  14. 14 CFR 25.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Design and Construction Fire Protection § 25.865 Fire protection of flight controls, engine mounts, and other flight structure. Essential flight controls, engine mounts, and other flight structures located in... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Fire protection of flight controls, engine...

  15. 14 CFR 25.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Design and Construction Fire Protection § 25.865 Fire protection of flight controls, engine mounts, and other flight structure. Essential flight controls, engine mounts, and other flight structures located in... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Fire protection of flight controls, engine...

  16. 14 CFR 25.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... Design and Construction Fire Protection § 25.865 Fire protection of flight controls, engine mounts, and other flight structure. Essential flight controls, engine mounts, and other flight structures located in... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Fire protection of flight controls, engine...

  17. Propulsion and Energetics Panel Working Group 11 on Aircraft Fire Safety. Volume 2. Main Report

    DTIC Science & Technology

    1979-11-01

    which make burning metal particles a potent igni- tion source and extinguishment of bulk metal fires a difficult task. In the latter case, the difficulty...aircraft to fires induced by uncon- tained engine failures and internal engine metal fires . With respect to the uncontained engine failure current engine

  18. Firefighters Integrated Response Equipment System

    NASA Technical Reports Server (NTRS)

    Kaplan, H.; Abeles, F.

    1978-01-01

    The Firefighters Integrated Response Equipment System (Project FIRES) is a joint National Fire Prevention and Control Administration (NFPCA)/National Aeronautics and Space Administration (NASA) program for the development of an 'ultimate' firefighter's protective ensemble. The overall aim of Project FIRES is to improve firefighter protection against hazards, such as heat, flame, smoke, toxic fumes, moisture, impact penetration, and electricity and, at the same time, improve firefighter performance by increasing maneuverability, lowering weight, and improving human engineering design of his protective ensemble.

  19. Advanced Reciprocating Engine Systems (ARES) Research at Argonne National Laboratory. A Report

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

    Gupta, Sreenath; Biruduganti, Muni; Bihari, Bipin

    The goals of these experiments were to determine the potential of employing spectral measurements to deduce combustion metrics such as HRR, combustion temperatures, and equivalence ratios in a natural gas-fired reciprocating engine. A laser-ignited, natural gas-fired single-cylinder research engine was operated at various equivalence ratios between 0.6 and 1.0, while varying the EGR levels between 0% and maximum to thereby ensure steady combustion. Crank angle-resolved spectral signatures were collected over 266-795 nm, encompassing chemiluminescence emissions from OH*, CH*, and predominantly by CO2* species. Further, laser-induced gas breakdown spectra were recorded under various engine operating conditions.

  20. Research Technology

    NASA Image and Video Library

    2001-08-06

    The test of twin Linear Aerospike XRS-2200 engines, originally built for the X-33 program, was performed on August 6, 2001 at NASA's Sternis Space Center, Mississippi. The engines were fired for the planned 90 seconds and reached a planned maximum power of 85 percent. NASA's Second Generation Reusable Launch Vehicle Program , also known as the Space Launch Initiative (SLI), is making advances in propulsion technology with this third and final successful engine hot fire, designed to test electro-mechanical actuators. Information learned from this hot fire test series about new electro-mechanical actuator technology, which controls the flow of propellants in rocket engines, could provide key advancements for the propulsion systems for future spacecraft. The Second Generation Reusable Launch Vehicle Program, led by NASA's Marshall Space Flight Center in Huntsville, Alabama, is a technology development program designed to increase safety and reliability while reducing costs for space travel. The X-33 program was cancelled in March 2001.

  1. Coil-On-Plug Ignition for Oxygen/Methane Liquid Rocket Engines in Thermal-Vacuum Environments

    NASA Technical Reports Server (NTRS)

    Melcher, John C.; Atwell, Matthew J.; Morehead, Robert L.; Hurlbert, Eric A.; Bugarin, Luz; Chaidez, Mariana

    2017-01-01

    A coil-on-plug ignition system has been developed and tested for Liquid Oxygen (LOX)/liquid methane (LCH4) rocket engines operating in thermal vacuum conditions. The igniters were developed and tested as part of the Integrated Cryogenic Propulsion Test Article (ICPTA), previously tested as part of the Project Morpheus test vehicle. The ICPTA uses an integrated, pressure-fed, cryogenic LOX/LCH4 propulsion system including a reaction control system (RCS) and a main engine. The ICPTA was tested at NASA Glenn Research Center's Plum Brook Station in the Spacecraft Propulsion Research Facility (B-2) under vacuum and thermal vacuum conditions. A coil-on-plug ignition system has been developed to successfully demonstrate ignition reliability at these conditions while preventing corona discharge issues. The ICPTA uses spark plug ignition for both the main engine igniter and the RCS. The coil-on-plug configuration eliminates the conventional high-voltage spark plug cable by combining the coil and the spark plug into a single component. Prior to ICPTA testing at Plum Brook, component-level reaction control engine (RCE) and main engine igniter testing was conducted at NASA Johnson Space Center (JSC), which demonstrated successful hot-fire ignition using the coil-on-plug from sea-level ambient conditions down to 10(exp -2) torr. Integrated vehicle hot-fire testing at JSC demonstrated electrical and command/data system performance. Lastly, hot-fire testing at Plum Brook demonstrated successful ignitions at simulated altitude conditions at 30 torr and cold thermal-vacuum conditions at 6 torr. The test campaign successfully proved that coil-on-plug technology will enable integrated LOX/LCH4 propulsion systems in future spacecraft.

  2. Forest Fire Mapping

    NASA Technical Reports Server (NTRS)

    1990-01-01

    The Fire Logistics Airborne Mapping Equipment (FLAME) system, mounted in a twin-engine and airplane operated by the U.S. Forest Service (USFS) of the U.S. Department of Agriculture (USDA), is an airborne instrument for detecting and pinpointing forest fires that might escape ground detection. The FLAME equipment rack includes the operator interface, a video monitor, the system's control panel and film output. FLAME's fire detection sensor is an infrared line scanner system that identifies fire boundaries. Sensor's information is correlated with the aircraft's position and altitude at the time the infrared imagery is acquired to fix the fire's location on a map. System can be sent to a fire locale anywhere in the U.S. at the request of a regional forester. USFS felt a need for a more advanced system to deliver timely fire information to fire management personnel in the decade of the 1990s. The Jet Propulsion Laboratory (JPL) conducted a study, jointly sponsored by NASA and USDA, on what advanced technologies might be employed to produce an end-to-end thermal infrared fire detection and mapping system. That led to initiation of the Firefly system, currently in development at JPL and targeted for operational service beginning in 1992. Firefly will employ satellite-reference position fixing and provide performance superior to FLAME.

  3. Utilization of geoinformation tools for the development of forest fire hazard mapping system: example of Pekan fire, Malaysia

    NASA Astrophysics Data System (ADS)

    Mahmud, Ahmad Rodzi; Setiawan, Iwan; Mansor, Shattri; Shariff, Abdul Rashid Mohamed; Pradhan, Biswajeet; Nuruddin, Ahmed

    2009-12-01

    A study in modeling fire hazard assessment will be essential in establishing an effective forest fire management system especially in controlling and preventing peat fire. In this paper, we have used geographic information system (GIS), in combination with other geoinformation technologies such as remote sensing and computer modeling, for all aspects of wild land fire management. Identifying areas that have a high probability of burning is an important component of fire management planning. The development of spatially explicit GIS models has greatly facilitated this process by allowing managers to map and analyze variables contributing to fire occurrence across large, unique geographic units. Using the model and its associated software engine, the fire hazard map was produced. Extensive avenue programming scripts were written to provide additional capabilities in the development of these interfaces to meet the full complement of operational software considering various users requirements. The system developed not only possesses user friendly step by step operations to deliver the fire vulnerability mapping but also allows authorized users to edit, add or modify parameters whenever necessary. Results from the model can support fire hazard mapping in the forest and enhance alert system function by simulating and visualizing forest fire and helps for contingency planning.

  4. 14 CFR 25.1181 - Designated fire zones; regions included.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... engines; and (7) Combustor, turbine, and tailpipe sections of turbine engine installations that contain... Protection § 25.1181 Designated fire zones; regions included. (a) Designated fire zones are— (1) The engine power section; (2) The engine accessory section; (3) Except for reciprocating engines, any complete...

  5. 14 CFR 25.1181 - Designated fire zones; regions included.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... engines; and (7) Combustor, turbine, and tailpipe sections of turbine engine installations that contain... Protection § 25.1181 Designated fire zones; regions included. (a) Designated fire zones are— (1) The engine power section; (2) The engine accessory section; (3) Except for reciprocating engines, any complete...

  6. 14 CFR 25.1181 - Designated fire zones; regions included.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... engines; and (7) Combustor, turbine, and tailpipe sections of turbine engine installations that contain... Protection § 25.1181 Designated fire zones; regions included. (a) Designated fire zones are— (1) The engine power section; (2) The engine accessory section; (3) Except for reciprocating engines, any complete...

  7. 14 CFR 25.1181 - Designated fire zones; regions included.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... engines; and (7) Combustor, turbine, and tailpipe sections of turbine engine installations that contain... Protection § 25.1181 Designated fire zones; regions included. (a) Designated fire zones are— (1) The engine power section; (2) The engine accessory section; (3) Except for reciprocating engines, any complete...

  8. 14 CFR 25.1181 - Designated fire zones; regions included.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... engines; and (7) Combustor, turbine, and tailpipe sections of turbine engine installations that contain... Protection § 25.1181 Designated fire zones; regions included. (a) Designated fire zones are— (1) The engine power section; (2) The engine accessory section; (3) Except for reciprocating engines, any complete...

  9. NASA Tests 2nd RS-25 Flight Engine for Space Launch System

    NASA Image and Video Library

    2017-10-19

    Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

  10. NASA Tests 2nd RS-25 Flight Engine For Space Launch System

    NASA Image and Video Library

    2017-10-19

    Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

  11. Video File - NASA Tests 2nd RS-25 Flight Engine for Space Launch System

    NASA Image and Video Library

    2017-10-19

    Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

  12. PBF Control Building auxiliary features, including fire hose house and ...

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

    PBF Control Building auxiliary features, including fire hose house and sewage system. Ebasco Services 1205 PER/PER-A-4. INEEL undex no. 760-0619-00-205-123024 - Idaho National Engineering Laboratory, SPERT-I & Power Burst Facility Area, Scoville, Butte County, ID

  13. Firing Room Remote Application Software Development

    NASA Technical Reports Server (NTRS)

    Liu, Kan

    2014-01-01

    The Engineering and Technology Directorate (NE) at National Aeronautics and Space Administration (NASA) Kennedy Space Center (KSC) is designing a new command and control system for the checkout and launch of Space Launch System (SLS) and future rockets. The purposes of the semester long internship as a remote application software developer include the design, development, integration, and verification of the software and hardware in the firing rooms, in particular with the Mobile Launcher (ML) Launch Accessories subsystem. In addition, a Conversion Fusion project was created to show specific approved checkout and launch engineering data for public-friendly display purposes.

  14. 41 CFR 102-80.135 - Who is a qualified fire protection engineer?

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... protection engineer? 102-80.135 Section 102-80.135 Public Contracts and Property Management Federal Property... qualified fire protection engineer? A qualified fire protection engineer is defined as an individual with a..., spread, and suppression, meeting one of the following criteria: (a) An engineer having an undergraduate...

  15. 41 CFR 102-80.135 - Who is a qualified fire protection engineer?

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... protection engineer? 102-80.135 Section 102-80.135 Public Contracts and Property Management Federal Property... qualified fire protection engineer? A qualified fire protection engineer is defined as an individual with a..., spread, and suppression, meeting one of the following criteria: (a) An engineer having an undergraduate...

  16. 41 CFR 102-80.135 - Who is a qualified fire protection engineer?

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... protection engineer? 102-80.135 Section 102-80.135 Public Contracts and Property Management Federal Property... qualified fire protection engineer? A qualified fire protection engineer is defined as an individual with a..., spread, and suppression, meeting one of the following criteria: (a) An engineer having an undergraduate...

  17. 41 CFR 102-80.135 - Who is a qualified fire protection engineer?

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... protection engineer? 102-80.135 Section 102-80.135 Public Contracts and Property Management Federal Property... qualified fire protection engineer? A qualified fire protection engineer is defined as an individual with a..., spread, and suppression, meeting one of the following criteria: (a) An engineer having an undergraduate...

  18. Analytical concepts for health management systems of liquid rocket engines

    NASA Technical Reports Server (NTRS)

    Williams, Richard; Tulpule, Sharayu; Hawman, Michael

    1990-01-01

    Substantial improvement in health management systems performance can be realized by implementing advanced analytical methods of processing existing liquid rocket engine sensor data. In this paper, such techniques ranging from time series analysis to multisensor pattern recognition to expert systems to fault isolation models are examined and contrasted. The performance of several of these methods is evaluated using data from test firings of the Space Shuttle main engines.

  19. 33 CFR 149.409 - How many fire extinguishers are needed?

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... turbine engines B-II One for each engine. 2 (6) Open electric motors and generators C-II One for each of... fixed system is installed. 2 If the engine is installed on a weather deck or is open to the atmosphere... fans, are exempt. 4 Not required if a fixed foam system is installed in accordance with 46 CFR 108.489. ...

  20. 33 CFR 149.409 - How many fire extinguishers are needed?

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... turbine engines B-II One for each engine. 2 (6) Open electric motors and generators C-II One for each of... fixed system is installed. 2 If the engine is installed on a weather deck or is open to the atmosphere... fans, are exempt. 4 Not required if a fixed foam system is installed in accordance with 46 CFR 108.489...

  1. 33 CFR 149.409 - How many fire extinguishers are needed?

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... turbine engines B-II One for each engine. 2 (6) Open electric motors and generators C-II One for each of... fixed system is installed. 2 If the engine is installed on a weather deck or is open to the atmosphere... fans, are exempt. 4 Not required if a fixed foam system is installed in accordance with 46 CFR 108.489. ...

  2. 33 CFR 149.409 - How many fire extinguishers are needed?

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... turbine engines B-II One for each engine. 2 (6) Open electric motors and generators C-II One for each of... fixed system is installed. 2 If the engine is installed on a weather deck or is open to the atmosphere... fans, are exempt. 4 Not required if a fixed foam system is installed in accordance with 46 CFR 108.489...

  3. 33 CFR 149.409 - How many fire extinguishers are needed?

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... turbine engines B-II One for each engine. 2 (6) Open electric motors and generators C-II One for each of... fixed system is installed. 2 If the engine is installed on a weather deck or is open to the atmosphere... fans, are exempt. 4 Not required if a fixed foam system is installed in accordance with 46 CFR 108.489. ...

  4. Powerful lineup

    NASA Image and Video Library

    2012-10-11

    Two J-2X engines and a powerpack, developed for NASA by Pratt and Whitney Rocketdyne, sit side-by-side Oct. 11 at Stennis Space Center as work continues on the Space Launch System. Engine 10001 (far left) has been removed from the A-2 Test Stand after being hot-fire tested 21 times, for a total of 2,697 seconds. The engine is now undergoing a series of post-test inspections. A J-2X powerpack (center) has been removed from the A-1 Test Stand to receive additional instrumentation. So far, the powerpack been hot-fire tested 10 times, for a total of 4,162 seconds. Meanwhile, assembly on the second J-2X engine, known as Engine 10002 and located to the far right, has begun in earnest, with engine completion scheduled for this November. Engine 10002 is about 15 percent complete.

  5. Battleship tank firing test of H-II launch vehicle - First stage

    NASA Astrophysics Data System (ADS)

    Watanabe, Atsutaro; Endo, Mamoru; Yamazaki, Isao; Maemura, Takashi; Namikawa, Tatsuo

    1991-06-01

    The H-II launch vehicle capable of placing 2-ton-class payloads on geostationary orbits is outlined, and focus is placed on its propulsion system. The development status of the project, including component development, preliminary battleship tank firing test (BFT-1), battleship tank firing test (BFT-2), and flight-type tank firing test (CFT) is discussed. The configuration and schematic diagram of BFT-2 are presented, and the firing test results of BFT-2 first series are analyzed, including engine performance, interface compatibility, and pressurization of subsystems.

  6. PYRONES: pyro-modeling and evacuation simulation system

    NASA Astrophysics Data System (ADS)

    Kanellos, Tassos; Doulgerakis, Adam; Georgiou, Eftichia; Kountouriotis, Vassilios I.; Paterakis, Manolis; Thomopoulos, Stelios C. A.; Pappou, Theodora; Vrahliotis, Socrates I.; Rekouniotis, Thrasos; Protopsaltis, Byron; Rozenberg, Ofir; Livneh, Ofer

    2016-05-01

    Structural fires continue to pose a great threat towards human life and property. Due to the complexity and non-deterministic characteristics of a building fire disaster, it is not a straightforward task to assess the effectiveness of fire protection measures embedded in the building design, planned evacuation strategies and potential modes of response for mitigating the fire's consequences. Additionally, there is a lack of means that realistically and accurately recreate the conditions of building fire disasters for the purpose of training personnel in order to be sufficiently prepared when vis-a-vis with such an environment. The propagation of fire within a building, the diffusion of its volatile products, the behavior of the occupants and the sustained injuries not only exhibit non-linear behaviors as individual phenomena, but are also intertwined in a web of co-dependencies. The PYRONES system has been developed to address all these aspects through a comprehensive approach that relies on accurate and realistic computer simulations of the individual phenomena and their interactions. PYRONES offers innovative tools and services to strategically targeted niches in two market domains. In the domain of building design and engineering, PYRONES is seamlessly integrated within existing engineering Building Information Modelling (BIM) workflows and serves as a building performance assessment platform, able to evaluate fire protection systems. On another front, PYRONES penetrates the building security management market, serving as a holistic training platform for specialists in evacuation strategy planning, firefighters and first responders, both at a Command and Control and at an individual trainee level.

  7. Guidelines of the Design of Electropyrotechnic Firing Circuit for Unmanned Flight and Ground Test Projects

    NASA Technical Reports Server (NTRS)

    Gonzalez, Guillermo A.; Lucy, Melvin H.; Massie, Jeffrey J.

    2013-01-01

    The NASA Langley Research Center, Engineering Directorate, Electronic System Branch, is responsible for providing pyrotechnic support capabilities to Langley Research Center unmanned flight and ground test projects. These capabilities include device selection, procurement, testing, problem solving, firing system design, fabrication and testing; ground support equipment design, fabrication and testing; checkout procedures and procedure?s training to pyro technicians. This technical memorandum will serve as a guideline for the design, fabrication and testing of electropyrotechnic firing systems. The guidelines will discuss the entire process beginning with requirements definition and ending with development and execution.

  8. Chemical research projects office functions accomplishments programs. [applied research in the fields of polymer chemistry and polymeric composites with emphasis on fire safety

    NASA Technical Reports Server (NTRS)

    Heimbuch, A. H.; Parker, J. A.

    1975-01-01

    Basic and applied research in the fields of polymer chemistry, polymeric composites, chemical engineering, and biophysical chemistry is summarized. Emphasis is placed on fire safety and human survivability as they relate to commercial and military aircraft, high-rise buildings, mines and rapid transit transportation. Materials systems and other fire control systems developed for aerospace applications and applied to national domestic needs are described along with bench-scale and full-scale tests conducted to demonstrate the improvements in performance obtained through the utilization of these materials and fire control measures.

  9. Numerical modeling of water spray suppression of conveyor belt fires in a large-scale tunnel.

    PubMed

    Yuan, Liming; Smith, Alex C

    2015-05-01

    Conveyor belt fires in an underground mine pose a serious life threat to miners. Water sprinkler systems are usually used to extinguish underground conveyor belt fires, but because of the complex interaction between conveyor belt fires and mine ventilation airflow, more effective engineering designs are needed for the installation of water sprinkler systems. A computational fluid dynamics (CFD) model was developed to simulate the interaction between the ventilation airflow, the belt flame spread, and the water spray system in a mine entry. The CFD model was calibrated using test results from a large-scale conveyor belt fire suppression experiment. Simulations were conducted using the calibrated CFD model to investigate the effects of sprinkler location, water flow rate, and sprinkler activation temperature on the suppression of conveyor belt fires. The sprinkler location and the activation temperature were found to have a major effect on the suppression of the belt fire, while the water flow rate had a minor effect.

  10. Numerical modeling of water spray suppression of conveyor belt fires in a large-scale tunnel

    PubMed Central

    Yuan, Liming; Smith, Alex C.

    2015-01-01

    Conveyor belt fires in an underground mine pose a serious life threat to miners. Water sprinkler systems are usually used to extinguish underground conveyor belt fires, but because of the complex interaction between conveyor belt fires and mine ventilation airflow, more effective engineering designs are needed for the installation of water sprinkler systems. A computational fluid dynamics (CFD) model was developed to simulate the interaction between the ventilation airflow, the belt flame spread, and the water spray system in a mine entry. The CFD model was calibrated using test results from a large-scale conveyor belt fire suppression experiment. Simulations were conducted using the calibrated CFD model to investigate the effects of sprinkler location, water flow rate, and sprinkler activation temperature on the suppression of conveyor belt fires. The sprinkler location and the activation temperature were found to have a major effect on the suppression of the belt fire, while the water flow rate had a minor effect. PMID:26190905

  11. Wet countdown demonstration and flight readiness firing

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The prelaunch tests for the Space Transportation System 1 flight are briefly described. Testing is divided into two major sections: the wet countdown demonstration test/flight readiness firing, which includes a 20 second test firing of the orbiter's three main engines, and a mission verification test, which is centered on flight and landing operations. The functions of the countdown sequence are listed and end of mission and mission abort exercises are described.

  12. Temperature Dependent Modal Test/Analysis Correlation of X-34 Fastrac Composite Rocket Nozzle

    NASA Technical Reports Server (NTRS)

    Brown, Andrew M.; Brunty, Joseph A. (Technical Monitor)

    2001-01-01

    A unique high temperature modal test and model correlation/update program has been performed on the composite nozzle of the FASTRAC engine for the NASA X-34 Reusable Launch Vehicle. The program was required to provide an accurate high temperature model of the nozzle for incorporation into the engine system structural dynamics model for loads calculation; this model is significantly different from the ambient case due to the large decrease in composite stiffness properties due to heating. The high-temperature modal test was performed during a hot-fire test of the nozzle. Previously, a series of high fidelity modal tests and finite element model correlation of the nozzle in a free-free configuration had been performed. This model was then attached to a modal-test verified model of the engine hot-fire test stand and the ambient system mode shapes were identified. A reduced set of accelerometers was then attached to the nozzle, the engine fired full-duration, and the frequency peaks corresponding to the ambient nozzle modes individually isolated and tracked as they decreased during the test. To update the finite-element model of the nozzle to these frequency curves, the percentage differences of the anisotropic composite moduli due to temperature variation from ambient, which had been used in the initial modeling and which were obtained by small sample coupon testing, were multiplied by an iteratively determined constant factor. These new properties were used to create high-temperature nozzle models corresponding to 10 second engine operation increments and tied into the engine system model for loads determination.

  13. 46 CFR 28.320 - Fixed gas fire extinguishing systems.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... only in a normally unoccupied machinery space, paint locker, or space containing flammable liquid... spaces: (1) A space containing an internal combustion engine of more than 50 horsepower; (2) A space containing an oil fired boiler; (3) An incinerator and; (4) A space containing a gasoline storage tank. (b...

  14. 46 CFR 28.320 - Fixed gas fire extinguishing systems.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... only in a normally unoccupied machinery space, paint locker, or space containing flammable liquid... spaces: (1) A space containing an internal combustion engine of more than 50 horsepower; (2) A space containing an oil fired boiler; (3) An incinerator and; (4) A space containing a gasoline storage tank. (b...

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

    Sommer, T.; Melick, T.; Morrison, D.

    The objective of this DOE sponsored project was to successfully fire coal-water slurry in a fire-tube boiler that was designed for oil/gas firing and establish a data base that will be relevant to a large number of existing installations. Firing slurry in a fire-tube configuration is a very demanding application because of the extremely high heat release rates and the correspondingly low furnace volume where combustion can be completed. Recognizing that combustion efficiency is the major obstacle when firing slurry in a fire-tube boiler, the program was focused on innovative approaches for improving carbon burnout without major modifications to themore » boiler. The boiler system was successfully designed and operated to fire coal-water slurry for extended periods of time with few slurry related operational problems. The host facility was a 3.8 million Btu/hr Cleaver-Brooks fire-tube boiler located on the University of Alabama Campus. A slurry atomizer was designed that provided outstanding atomization and was not susceptible to pluggage. The boiler was operated for over 1000 hours and 12 shipments of slurry were delivered. The new equipment engineered for the coal-water slurry system consisted of the following: combustion air and slurry heaters; cyclone; baghouse; fly ash reinjection system; new control system; air compressor; CWS/gas burner and gas valve train; and storage tank and slurry handling system.« less

  16. n/a

    NASA Image and Video Library

    1961-01-01

    The static firing of a Saturn F-1 engine at the Marshall Space Flight Center's Static Test Stand. The F-1 engine is a single-start, 1,5000,000 Lb fixed-thrust, bipropellant rocket system. The engine uses liquid oxygen as the oxidizer and RP-1 (kerosene) as fuel. The five-engine cluster used on the first stage of the Saturn V produces 7,500,000 lbs of thrust.

  17. Capability and flight record of the versatile space shuttle OMS engine

    NASA Astrophysics Data System (ADS)

    Judd, D. Craig

    The development contract for Aerojet's Orbital Manuevering Subsystem (OMS) engine was awarded in February 1974. This paper provides a description of the OMS subcomponents along with a summary of the OMS development program and subsequent flight record. The major subcomponents include the platelet injector, regeneratively cooled chamber, radiation cooled nozzle extension, bipropellant valve, thrust mount, gimbal actuator assembly, and propellant feedlines. The OMS engine underwent an extensive development program between 1974 and 1978 that included approximately 3680 tests performed on 21 separate engines on components for a total duration of more than 19,000 seconds. This was followed with qualification testing of two engines with another 521 tests and 18,504 seconds of hot fire testing. The Space Shuttle system has completed 45 orbital flights with the OMS engines having fired a total of 356 times with a cumulative duration of 38,094 seconds. In all cases, the OMS engine has performed as required because of its maturity, simplicity, and built-in redundancy. Also described are the results of studies performed to increase the performance of the OMS engine either by using LOX/hydrocarbon propellants or by converting to a pump fed system to increase chamber pressure and area ratio.

  18. Advanced Concept

    NASA Image and Video Library

    2003-12-01

    This photo gives an overhead look at an RS-88 development rocket engine being test fired at NASA's Marshall Space Flight Center in Huntsville, Alabama, in support of the Pad Abort Demonstration (PAD) test flights for NASA's Orbital Space Plane (OSP). The tests could be instrumental in developing the first crew launch escape system in almost 30 years. Paving the way for a series of integrated PAD test flights, the engine tests support development of a system that could pull a crew safely away from danger during liftoff. A series of 16 hot fire tests of a 50,000-pound thrust RS-88 rocket engine were conducted, resulting in a total of 55 seconds of successful engine operation. The engine is being developed by the Rocketdyne Propulsion and Power unit of the Boeing Company. Integrated launch abort demonstration tests in 2005 will use four RS-88 engines to separate a test vehicle from a test platform, simulating pulling a crewed vehicle away from an aborted launch. Four 156-foot parachutes will deploy and carry the vehicle to landing. Lockheed Martin is building the vehicles for the PAD tests. Seven integrated tests are plarned for 2005 and 2006.

  19. Advanced Concept

    NASA Image and Video Library

    2003-12-01

    In this photo, an RS-88 development rocket engine is being test fired at NASA's Marshall Space Flight Center in Huntsville, Alabama, in support of the Pad Abort Demonstration (PAD) test flights for NASA's Orbital Space Plane (OSP). The tests could be instrumental in developing the first crew launch escape system in almost 30 years. Paving the way for a series of integrated PAD test flights, the engine tests support development of a system that could pull a crew safely away from danger during liftoff. A series of 16 hot fire tests of a 50,000-pound thrust RS-88 rocket engine were conducted, resulting in a total of 55 seconds of successful engine operation. The engine is being developed by the Rocketdyne Propulsion and Power unit of the Boeing Company. Integrated launch abort demonstration tests in 2005 will use four RS-88 engines to separate a test vehicle from a test platform, simulating pulling a crewed vehicle away from an aborted launch. Four 156-foot parachutes will deploy and carry the vehicle to landing. Lockheed Martin is building the vehicles for the PAD tests. Seven integrated tests are plarned for 2005 and 2006.

  20. 46 CFR 193.05-10 - Fixed fire extinguishing systems.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ....05-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH... combustion engine installations; (2) Gas turbine installations; (3) Enclosed spaces containing gasoline engines; (4) Chemical storerooms; (5) Any space containing auxiliaries with an aggregate power of 1,000...

  1. 46 CFR 193.05-10 - Fixed fire extinguishing systems.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ....05-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH... combustion engine installations; (2) Gas turbine installations; (3) Enclosed spaces containing gasoline engines; (4) Chemical storerooms; (5) Any space containing auxiliaries with an aggregate power of 1,000...

  2. 46 CFR 193.05-10 - Fixed fire extinguishing systems.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ....05-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH... combustion engine installations; (2) Gas turbine installations; (3) Enclosed spaces containing gasoline engines; (4) Chemical storerooms; (5) Any space containing auxiliaries with an aggregate power of 1,000...

  3. Additively Manufactured Combustion Devices Components for LOX/Methane Applications

    NASA Technical Reports Server (NTRS)

    Greene, Sandra Elam; Protz, Christopher; Garcia, Chance; Goodman, Dwight; Baker, Kevin

    2016-01-01

    Marshall Space Flight Center (MSFC) has designed, fabricated, and hot-fire tested a variety of successful injectors, chambers, and igniters for potential liquid oxygen (LOX) and methane (CH4) systems since 2005. The most recent efforts have focused on components with additive manufacturing (AM) to include unique design features, minimize joints, and reduce final machining efforts. Inconel and copper alloys have been used with AM processes to produce a swirl coaxial injector and multiple methane cooled thrust chambers. The initial chambers included unique thermocouple ports for measuring local coolant channel temperatures along the length of the chamber. Results from hot-fire testing were used to anchor thermal models and generate a regeneratively cooled thruster for a 4,000 lbf LOX/CH4 engine. The completed thruster will be hot-fire tested in the summer of 2016 at MSFC. The thruster design can also be easily scaled and used on a 25,000 lbf engine. To further support the larger engine design, an AM gas generator injector has been designed. Hot-fire testing on this injector is planned for the summer of 2016 at MSFC.

  4. Fire protection for launch facilities using machine vision fire detection

    NASA Astrophysics Data System (ADS)

    Schwartz, Douglas B.

    1993-02-01

    Fire protection of critical space assets, including launch and fueling facilities and manned flight hardware, demands automatic sensors for continuous monitoring, and in certain high-threat areas, fast-reacting automatic suppression systems. Perhaps the most essential characteristic for these fire detection and suppression systems is high reliability; in other words, fire detectors should alarm only on actual fires and not be falsely activated by extraneous sources. Existing types of fire detectors have been greatly improved in the past decade; however, fundamental limitations of their method of operation leaves open a significant possibility of false alarms and restricts their usefulness. At the Civil Engineering Laboratory at Tyndall Air Force Base in Florida, a new type of fire detector is under development which 'sees' a fire visually, like a human being, and makes a reliable decision based on known visual characteristics of flames. Hardware prototypes of the Machine Vision (MV) Fire Detection System have undergone live fire tests and demonstrated extremely high accuracy in discriminating actual fires from false alarm sources. In fact, this technology promises to virtually eliminate false activations. This detector could be used to monitor fueling facilities, launch towers, clean rooms, and other high-value and high-risk areas. Applications can extend to space station and in-flight shuttle operations as well; fiber optics and remote camera heads enable the system to see around obstructed areas and crew compartments. The capability of the technology to distinguish fires means that fire detection can be provided even during maintenance operations, such as welding.

  5. Fire protection for launch facilities using machine vision fire detection

    NASA Technical Reports Server (NTRS)

    Schwartz, Douglas B.

    1993-01-01

    Fire protection of critical space assets, including launch and fueling facilities and manned flight hardware, demands automatic sensors for continuous monitoring, and in certain high-threat areas, fast-reacting automatic suppression systems. Perhaps the most essential characteristic for these fire detection and suppression systems is high reliability; in other words, fire detectors should alarm only on actual fires and not be falsely activated by extraneous sources. Existing types of fire detectors have been greatly improved in the past decade; however, fundamental limitations of their method of operation leaves open a significant possibility of false alarms and restricts their usefulness. At the Civil Engineering Laboratory at Tyndall Air Force Base in Florida, a new type of fire detector is under development which 'sees' a fire visually, like a human being, and makes a reliable decision based on known visual characteristics of flames. Hardware prototypes of the Machine Vision (MV) Fire Detection System have undergone live fire tests and demonstrated extremely high accuracy in discriminating actual fires from false alarm sources. In fact, this technology promises to virtually eliminate false activations. This detector could be used to monitor fueling facilities, launch towers, clean rooms, and other high-value and high-risk areas. Applications can extend to space station and in-flight shuttle operations as well; fiber optics and remote camera heads enable the system to see around obstructed areas and crew compartments. The capability of the technology to distinguish fires means that fire detection can be provided even during maintenance operations, such as welding.

  6. Vulnerability Methodology and Protective Measures for Aircraft Fire and Explosion Hazards. Volume 2. Aircraft Engine Nacelle Fire Test Programs. Part 1. Fire Detection, Fire Extinguishment and Surface Ignition Studies

    DTIC Science & Technology

    1986-01-01

    by sensors in the test cell and sampled, digitized, averaged, and calibrated by the facility computer system. The data included flowrates calculated ...before the next test could be started. This required about 2 minutes. 6.4 Combat Damage Testing Appendix C contains calculations and analysis...were comparable (Figure 7-5). Agent quantities required per MIL-E-22285 were again calculated using the equations noted in paragraph 7.1.1. The

  7. Space Launch System Base Heating Test: Sub-Scale Rocket Engine/Motor Design, Development and Performance Analysis

    NASA Technical Reports Server (NTRS)

    Mehta, Manish; Seaford, Mark; Kovarik, Brian; Dufrene, Aaron; Solly, Nathan; Kirchner, Robert; Engel, Carl D.

    2014-01-01

    The Space Launch System (SLS) base heating test is broken down into two test programs: (1) Pathfinder and (2) Main Test. The Pathfinder Test Program focuses on the design, development, hot-fire test and performance analyses of the 2% sub-scale SLS core-stage and booster element propulsion systems. The core-stage propulsion system is composed of four gaseous oxygen/hydrogen RS-25D model engines and the booster element is composed of two aluminum-based model solid rocket motors (SRMs). The first section of the paper discusses the motivation and test facility specifications for the test program. The second section briefly investigates the internal flow path of the design. The third section briefly shows the performance of the model RS-25D engines and SRMs for the conducted short duration hot-fire tests. Good agreement is observed based on design prediction analysis and test data. This program is a challenging research and development effort that has not been attempted in 40+ years for a NASA vehicle.

  8. 41 CFR 102-80.90 - Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 41 Public Contracts and Property Management 3 2011-01-01 2011-01-01 false Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? 102-80.90... Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? Yes, the Fire...

  9. 41 CFR 102-80.90 - Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 41 Public Contracts and Property Management 3 2010-07-01 2010-07-01 false Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? 102-80.90... Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? Yes, the Fire...

  10. 41 CFR 102-80.90 - Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 41 Public Contracts and Property Management 3 2012-01-01 2012-01-01 false Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? 102-80.90... Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? Yes, the Fire...

  11. 41 CFR 102-80.90 - Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire...

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... 41 Public Contracts and Property Management 3 2013-07-01 2013-07-01 false Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? 102-80.90... Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? Yes, the Fire...

  12. 41 CFR 102-80.90 - Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 41 Public Contracts and Property Management 3 2014-01-01 2014-01-01 false Is the Fire Administration Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? 102-80.90... Authorization Act of 1992 (Public Law 102-522) relevant to fire protection engineering? Yes, the Fire...

  13. 46 CFR 167.45-45 - Carbon dioxide fire-extinguishing system requirements.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... SCHOOLS PUBLIC NAUTICAL SCHOOL SHIPS Special Firefighting and Fire Prevention Requirements § 167.45-45... school ship propelled by internal combustion engines, the quantity of carbon dioxide required may be... arrangement of the piping shall be such as to give a general and fairly uniform distribution over the entire...

  14. 46 CFR 167.45-45 - Carbon dioxide fire-extinguishing system requirements.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... SCHOOLS PUBLIC NAUTICAL SCHOOL SHIPS Special Firefighting and Fire Prevention Requirements § 167.45-45... school ship propelled by internal combustion engines, the quantity of carbon dioxide required may be... arrangement of the piping shall be such as to give a general and fairly uniform distribution over the entire...

  15. 46 CFR 181.400 - Where required.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... following spaces must be equipped with a fixed gas fire extinguishing system, in compliance with § 181.410... allowed by paragraph (b) of this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 37.3 kW (50 hp); (3) A space containing an oil fired...

  16. 46 CFR 181.400 - Where required.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... following spaces must be equipped with a fixed gas fire extinguishing system, in compliance with § 181.410... allowed by paragraph (b) of this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 37.3 kW (50 hp); (3) A space containing an oil fired...

  17. 46 CFR 181.400 - Where required.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... following spaces must be equipped with a fixed gas fire extinguishing system, in compliance with § 181.410... allowed by paragraph (b) of this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 37.3 kW (50 hp); (3) A space containing an oil fired...

  18. 46 CFR 181.400 - Where required.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... following spaces must be equipped with a fixed gas fire extinguishing system, in compliance with § 181.410... allowed by paragraph (b) of this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 37.3 kW (50 hp); (3) A space containing an oil fired...

  19. 46 CFR 162.161-2 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire Protection...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... from the sources listed below. It is also available for inspection at the National Archives and Records...

  20. 46 CFR 162.161-2 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire Protection...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... from the sources listed below. It is also available for inspection at the National Archives and Records...

  1. 46 CFR 162.161-2 - Incorporation by reference.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    .../Circ. 848) (June 4, 2008), (“MSC.1/Circ. 1267”), IBR approved for § 162.161-6. (c) National Fire...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-2... is available from the sources listed below. It is also available for inspection at the National...

  2. Ignition study of a petrol/CNG single cylinder engine

    NASA Astrophysics Data System (ADS)

    Khan, N.; Saleem, Z.; Mirza, A. A.

    2005-11-01

    Benefits of laser ignition over the electrical ignition system for Compressed Natural Gas (CNG) engines have fuelled automobile industry and led to an extensive research on basic characteristics to switch over to the emerging technologies. This study was undertaken to determine the electrical and physical characteristics of the electric spark ignition of single cylinder petrol/CNG engine to determine minimum ignition requirements and timeline of ignition events to use in subsequent laser ignition study. This communication briefly reviews the ongoing research activities and reports the results of this experimental study. The premixed petrol and CNG mixtures were tested for variation of current and voltage characteristics of the spark with speed of engine. The current magnitude of discharge circuit was found to vary linearly over a wide range of speed but the stroke to stroke fire time was found to vary nonlinearly. The DC voltage profiles were observed to fluctuate randomly during ignition process and staying constant in rest of the combustion cycle. Fire to fire peaks of current amplitudes fluctuated up to 10% of the peak values at constant speed but increased almost linearly with increase in speed. Technical barriers of laser ignition related to threshold minimum ignition energy, inter-pulse durations and firing sequence are discussed. Present findings provide a basic initiative and background information for designing suitable timeline algorithms for laser ignited leaner direct injected CNG engines.

  3. Engine Data Interpretation System (EDIS), phase 2

    NASA Technical Reports Server (NTRS)

    Cost, Thomas L.; Hofmann, Martin O.

    1991-01-01

    A prototype of an expert system was developed which applies qualitative constraint-based reasoning to the task of post-test analysis of data resulting from a rocket engine firing. Data anomalies are detected and corresponding faults are diagnosed. Engine behavior is reconstructed using measured data and knowledge about engine behavior. Knowledge about common faults guides but does not restrict the search for the best explanation in terms of hypothesized faults. The system contains domain knowledge about the behavior of common rocket engine components and was configured for use with the Space Shuttle Main Engine (SSME). A graphical user interface allows an expert user to intimately interact with the system during diagnosis. The system was applied to data taken during actual SSME tests where data anomalies were observed.

  4. CFD assessment of the pollutant environment from RD-170 propulsion system testing

    NASA Technical Reports Server (NTRS)

    Wang, Ten-See; Mcconnaughey, Paul; Warsi, Saif; Chen, Yen-Sen

    1995-01-01

    Computational Fluid Dynamics (CFD) technology has been used to assess the exhaust plume pollutant environment of the RD-170 engine hot-firing on the F1 Test Stand at Marshall Space Flight Center. Researchers know that rocket engine hot-firing has the potential for forming thermal nitric oxides (NO(x)), as well as producing carbon monoxide (CO) when hydrocarbon fuels are used. Because of the complicated physics involved, however, little attempt has been made to predict the pollutant emissions from ground-based engine testing, except for simplified methods which can grossly underpredict and/or overpredict the pollutant formations in a test environment. The objective of this work, therefore, has been to develop a technology using CFD to describe the underlying pollutant emission physics from ground-based rocket engine testing. This resultant technology is based on a three-dimensional (3D), viscous flow, pressure-based CFD formulation, where wet CO and thermal NO finite-rate chemistry mechanisms are solved with a Penalty Function method. A nominal hot-firing of a RD-170 engine on the F1 stand has been computed. Pertinent test stand flow physics such as the multiple-nozzle clustered engine plume interaction, air aspiration from base and aspirator, plume mixing with entrained air that resulted in contaminant dilution and afterburning, counter-afterburning due to flame bucket water-quenching, plume impingement on the flame bucket, and restricted multiple-plume expansion and turning have been captured. The predicted total emission rates compared reasonably well with those of the existing hydrocarbon engine hot-firing test data.

  5. Mean composite fire severity metrics computed with Google Earth engine offer improved accuracy and expanded mapping potential

    Treesearch

    Sean A. Parks; Lisa M. Holsinger; Morgan A. Voss; Rachel A. Loehman; Nathaniel P. Robinson

    2018-01-01

    Landsat-based fire severity datasets are an invaluable resource for monitoring and research purposes. These gridded fire severity datasets are generally produced with pre- and post-fire imagery to estimate the degree of fire-induced ecological change. Here, we introduce methods to produce three Landsat-based fire severity metrics using the Google Earth Engine (GEE)...

  6. Direct fired reciprocating engine and bottoming high temperature fuel cell hybrid

    DOEpatents

    Geisbrecht, Rodney A [New Alexandria, PA; Holcombe, Norman T [McMurray, PA

    2006-02-07

    A system of a fuel cell bottoming an internal combustion engine. The engine exhaust gas may be combined in varying degrees with air and fed as input to a fuel cell. Reformer and oxidizers may be combined with heat exchangers to accommodate rich and lean burn conditions in the engine in peaking and base load conditions without producing high concentrations of harmful emissions.

  7. Directory of workers in the fire field

    NASA Technical Reports Server (NTRS)

    Kuvshinoff, B. W.; Mcleod, S. B.; Katz, R. G.

    1973-01-01

    A directory was compiled to provide a list of workers engaged in fire research, their addresses and affiliations, and their principal fields of activity. The initial criteria for the selection of names for the directory are recent contributions to fire literature, teaching of subjects relevant to fire science, or participation in or support of fire research programs. With some exceptions, fire service personnel and fire protection engineers were excluded because directories already exist for these professionals. Also excluded are investigators engaged principally in studies of propulsion, combustion, and explosion phenomena, because these areas of study are somewhat aside from the main focus of fire research. For purposes of the directory, fire science is taken to be the body of knowledge, art, and skill related to the investigation, analysis, and interpretation of the phenomena of unwanted fires and the evaluation of materials methods, systems, and equipment related to fire safety, prevention, detection, and suppression.

  8. Design Definition Study Report. Full Crew Interaction Simulator-Laboratory Model (FCIS-LM) (Device X17B7). Volume I. Problem Analysis.

    DTIC Science & Technology

    1978-06-01

    and Sound Levels. Tank sound characteris- tics can be categorized by four areas of tank operation. These are: engine starting and running, mobility or...the use of the ballistic computer system. The indirect sighting and fire control system consists of the elevation quadrant M13A3, a control light source...in low ambient 2-22 temperatures. No controls or indicators are provided for the engine air intake system. The exhaust system has four engine

  9. A common sense approach to sprinklers.

    PubMed

    Passingham, Andy

    2010-03-01

    As debate continues over the importance of incorporating automatic sprinkler systems into healthcare facilities, Andy Passingham, associate director at Arup Fire, considers how Arup, the multi-disciplinary engineers for two high profile new Welsh hospitals under construction in Ebbw Vale and Caerphilly, addressed fire safety on both projects. He highlights how the installation of sprinklers should not only improve fire safety, but has also contributed to a number of wider design elements which should enhance the patient, staff, and visitor experience.

  10. Impact of Fire Resistant Fuel Blends on Compression Ignition Engine Performance

    DTIC Science & Technology

    2011-07-01

    EFFECTS ON ENGINE PERFORMANCE FRF blends were tested in the CAT C7 and GEP 6.5L(T) engines to determine the effects of FRF on engine ...impact on efficiency of the Stanadyne rotary injection pump used in the GEP 6.5L(T) engine , thus largely effecting its power output when varying... exhaust backpressure .  Emissions are sampled from an exhaust probe installed between the engine and exhaust system butterfly valve. 

  11. A Model for Training Range Planning Data.

    DTIC Science & Technology

    1984-04-01

    firing over flank avoided; reduced accuracy Thermal Imaging System: For day and night target acLquisition and aiming Digital Ballistic Computer...ATTN: NGB-DAP US Army Engineer Districts USACC ATTN: DAAATTN Libary 41)WASH DC 20314 ATTN. Library (41) ATTN: Facilities Engineer (2) A C Chief

  12. NASA Conducts Final RS-25 Rocket Engine Test of 2017

    NASA Image and Video Library

    2017-12-13

    NASA engineers at Stennis Space Center capped a year of Space Launch System testing with a final RS-25 rocket engine hot fire on Dec. 13. The 470-second test on the A-1 Test Stand was a “green run” test of an RS-25 flight controller. The engine tested also included a large 3-D-printed part, a pogo accumulator assembly, scheduled for use on future RS-25 flight engines.

  13. 46 CFR 162.161-7 - Inspections at production.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-7... Coast Guard to take samples of systems for tests prescribed by this subpart; and (4) Conduct a leakage...

  14. 46 CFR 162.161-7 - Inspections at production.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-7... Coast Guard to take samples of systems for tests prescribed by this subpart; and (4) Conduct a leakage...

  15. 46 CFR 162.161-7 - Inspections at production.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-7... Coast Guard to take samples of systems for tests prescribed by this subpart; and (4) Conduct a leakage...

  16. 33 CFR 145.10 - Locations and number of fire extinguishers required.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... vicinity of exits, either inside or outside of spaces. machinery spaces Gas-fired boilers B-II (CO2 or dry chemical) 2 required. Gas-fired boilers B-V 1 required. 1 Oil-fired boilers B-II 2 required. Oil-fired boilers B-V 2 required. 1 Internal combustion or gas turbine engines B-II 1 for each engine. 2 Electric...

  17. 33 CFR 145.10 - Locations and number of fire extinguishers required.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... vicinity of exits, either inside or outside of spaces. machinery spaces Gas-fired boilers B-II (CO2 or dry chemical) 2 required. Gas-fired boilers B-V 1 required. 1 Oil-fired boilers B-II 2 required. Oil-fired boilers B-V 2 required. 1 Internal combustion or gas turbine engines B-II 1 for each engine. 2 Electric...

  18. 33 CFR 145.10 - Locations and number of fire extinguishers required.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... vicinity of exits, either inside or outside of spaces. machinery spaces Gas-fired boilers B-II (CO2 or dry chemical) 2 required. Gas-fired boilers B-V 1 required. 1 Oil-fired boilers B-II 2 required. Oil-fired boilers B-V 2 required. 1 Internal combustion or gas turbine engines B-II 1 for each engine. 2 Electric...

  19. 33 CFR 145.10 - Locations and number of fire extinguishers required.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... vicinity of exits, either inside or outside of spaces. machinery spaces Gas-fired boilers B-II (CO2 or dry chemical) 2 required. Gas-fired boilers B-V 1 required. 1 Oil-fired boilers B-II 2 required. Oil-fired boilers B-V 2 required. 1 Internal combustion or gas turbine engines B-II 1 for each engine. 2 Electric...

  20. 33 CFR 145.10 - Locations and number of fire extinguishers required.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... vicinity of exits, either inside or outside of spaces. machinery spaces Gas-fired boilers B-II (CO2 or dry chemical) 2 required. Gas-fired boilers B-V 1 required. 1 Oil-fired boilers B-II 2 required. Oil-fired boilers B-V 2 required. 1 Internal combustion or gas turbine engines B-II 1 for each engine. 2 Electric...

  1. Test Plan to Assess Fire Effects on the Function of an Engineered Surface Barrier

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

    Ward, Anderson L.; Berlin, Gregory T.; Cammann, Jerry W.

    2008-09-29

    Wildfire is a frequent perturbation in shrub steppe ecosystems, altering the flora, fauna, atmosphere, and soil of these systems. Research on the fire effects has focused mostly on natural ecosystems with essentially no attention on engineered systems like surface barriers. The scope of the project is to use a simulated wildfire to induce changes in an engineered surface barrier and document the effects on barrier performance. The main objective is to quantify the effects of burning and the resulting post-fire conditions on alterations in soil physical properties; hydrologic response, particularly the water balance; geochemical properties; and biological properties. A secondarymore » objective is to use the lessons learned to maximize fire protection in the design of long-term monitoring systems based on electronic sensors. A simulated wildfire will be initiated, controlled and monitored at the 200-BP-1 barrier in collaboration with the Hanford Fire Department during the fall of 2008. The north half of the barrier will be divided into nine 12 x 12 m plots, each of which will be randomly assigned a fuel load of 2 kg m-2 or 4 kg m-2. Each plot will be ignited around the perimeter and flames allowed to carry to the centre. Any remaining unburned vegetation will be manually burned off using a drip torch. Progress of the fire and its effects will be monitored using point measurements of thermal, hydrologic, and biotic variables. Three measures of fire intensity will be used to characterize fire behavior: (1) flame height, (2) the maximum temperature at three vertical profile levels, and (3) total duration of elevated temperature at these levels. Pre-burn plant information, including species diversity, plant height, and canopy diameter will be measured on shrubs from the plots to be burned and from control plots at the McGee ranch. General assessments of shrub survival, recovery, and recruitment will be made after the fire. Near-surface soil samples will be collected pre- and post-burn to determine changes in the gravel content of the surface layer so as to quantify inflationary or deflationary responses to fire and to reveal the ability of the surface to resist post-fire erosive stresses. Measures of bulk density, water repellency, water retention, and hydraulic conductivity will be used to characterize changes in infiltration rates and water storage capacity following the fire. Samples will also be analyzed to quantify geochemical changes including changes in soil pH, cation exchange capacity, specific surface area, and the concentration of macro nutrients (e.g. N, P, K) and other elements such as Na, Mg, Ca, that are critical to the post-fire recovery revegetation. Soil CO2 emissions will be measured monthly for one year following the burn to document post-fire stimulation of carbon turnover and soil biogenic emissions. Surface and subsurface temperature measurements at and near monitoring installations will be used to document fire effects on electronic equipment. The results of this study will be used to bridge the gaps in knowledge on the effects of fire on engineered ecosystems (e.g. surface barriers), particularly the hydrologic and biotic characteristics that govern the water and energy balance. These results will also support the development of practical fire management techniques for barriers that are compatible with wildfire suppression strategies. Furthermore, lessons learned will be use to develop installation strategies needed to protect electronic monitoring equipment from the intense heat of fire and the potential damaging effects of smoke and fire extinguishing agents. Such information is needed to better understand long-term barrier performance under extreme conditions, especially if site maintenance and operational funding is lost for activities such as barrier revegetation.« less

  2. Fire Protection Jacket

    NASA Technical Reports Server (NTRS)

    1991-01-01

    NERAC, Inc., Tolland, CT, aided Paul Monroe Engineering, Orange, CA, in the development of their PC1200 Series Fire Protection Jacket that protects the oil conduit system on an offshore drilling platform from the intense hydrocarbon fires that cause buckling and could cause structural failure of the platform. The flame-proof jacketing, which can withstand temperatures of 2000 degrees Fahrenheit for four hours or more, was developed from a combination of ceramic cloth (similar to the ceramic in Space Shuttle tiles), and laminates used in space suits.

  3. Engine performance with a hydrogenated safety fuel

    NASA Technical Reports Server (NTRS)

    Schey, Oscar W; Young, Alfred W

    1933-01-01

    This report presents the results of an investigation to determine the engine performance obtained with a hydrogenated safety fuel developed to eliminate fire hazard. The tests were made on a single-cylinder universal test engine at compression ratios of 5.0, 5.5, and 6.0. Most of the tests were made with a fuel-injection system, although one set of runs was made with a carburetor when using gasoline to establish comparative performance. The tests show that the b.m.e.p. obtained with safety fuel when using a fuel-injection system is slightly higher than that obtained with gasoline when using a carburetor, although the fuel consumption with safety fuel is higher. When the fuel-injection system is used with each fuel and with normal engine temperatures the b.m.e.p. with safety fuel is from 2 to 4 percent lower than with gasoline and the fuel consumption about 25 to 30 percent higher. However, a few tests at an engine coolant temperature of 250 F have shown a specific fuel consumption approximating that obtained with gasoline with only a slight reduction in power. The idling of the test engine was satisfactory with the safety fuel. Starting was difficult with a cold engine but could be readily accomplished when the jacket water was hot. It is believed that the use of the safety fuel would practically eliminate crash fires.

  4. J-2X engine test

    NASA Image and Video Library

    2011-12-01

    NASA conducted a key stability test firing of the J-2X rocket engine on the A-2 Test Stand at Stennis Space Center on Dec. 1, marking another step forward in development of the upper-stage engine that will carry humans deeper into space than ever before. The J-2X will provide upper-stage power for NASA's new Space Launch System.

  5. 46 CFR 27.102 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... Street, Suite 10, Annapolis, MD 21403 H-25-1986—Portable Fuel Systems for Flammable Liquids 27.211 H-33... Clean Agent Fire Extinguishing Systems, 2000 edition 27.101 Society of Automotive Engineers (SAE), 400...

  6. 46 CFR 27.102 - Incorporation by reference.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... Street, Suite 10, Annapolis, MD 21403 H-25-1986—Portable Fuel Systems for Flammable Liquids 27.211 H-33... Clean Agent Fire Extinguishing Systems, 2000 edition 27.101 Society of Automotive Engineers (SAE), 400...

  7. 46 CFR 27.102 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... Street, Suite 10, Annapolis, MD 21403 H-25-1986—Portable Fuel Systems for Flammable Liquids 27.211 H-33... Clean Agent Fire Extinguishing Systems, 2000 edition 27.101 Society of Automotive Engineers (SAE), 400...

  8. 46 CFR 27.102 - Incorporation by reference.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Street, Suite 10, Annapolis, MD 21403 H-25-1986—Portable Fuel Systems for Flammable Liquids 27.211 H-33... Clean Agent Fire Extinguishing Systems, 2000 edition 27.101 Society of Automotive Engineers (SAE), 400...

  9. Hydrogen Sensors Boost Hybrids; Today's Models Losing Gas?

    NASA Technical Reports Server (NTRS)

    2005-01-01

    Advanced chemical sensors are used in aeronautic and space applications to provide safety monitoring, emission monitoring, and fire detection. In order to fully do their jobs, these sensors must be able to operate in a range of environments. NASA has developed sensor technologies addressing these needs with the intent of improving safety, optimizing combustion efficiencies, and controlling emissions. On the ground, the chemical sensors were developed by NASA engineers to detect potential hydrogen leaks during Space Shuttle launch operations. The Space Shuttle uses a combination of hydrogen and oxygen as fuel for its main engines. Liquid hydrogen is pumped to the external tank from a storage tank located several hundred feet away. Any hydrogen leak could potentially result in a hydrogen fire, which is invisible to the naked eye. It is important to detect the presence of a hydrogen fire in order to prevent a major accident. In the air, the same hydrogen-leak dangers are present. Stress and temperature changes can cause tiny cracks or holes to form in the tubes that line the Space Shuttle s main engine nozzle. Such defects could allow the hydrogen that is pumped through the nozzle during firing to escape. Responding to the challenges associated with pinpointing hydrogen leaks, NASA endeavored to improve propellant leak-detection capabilities during assembly, pre-launch operations, and flight. The objective was to reduce the operational cost of assembling and maintaining hydrogen delivery systems with automated detection systems. In particular, efforts have been focused on developing an automated hydrogen leak-detection system using multiple, networked hydrogen sensors that are operable in harsh conditions.

  10. Video File - NASA Conducts Final RS-25 Rocket Engine Test of 2017

    NASA Image and Video Library

    2017-12-13

    NASA engineers at Stennis Space Center capped a year of Space Launch System testing with a final RS-25 rocket engine hot fire on Dec. 13. The 470-second test on the A-1 Test Stand was a “green run” test of an RS-25 flight controller. The engine tested also included a large 3-D-printed part, a pogo accumulator assembly, scheduled for use on future RS-25 flight engines.

  11. Idaho National Engineering and Environmental Laboratory Wildland Fire Management Environmental Assessment - April 2003

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

    Irving, J.S.

    DOE prepared an environmental assessment (EA)for wildland fire management activities on the Idaho National Engineering and Environmental Laboratory (INEEL) (DOE/EA-1372). The EA was developed to evaluate wildland fire management options for pre-fire, fire suppression, and post fire activities. Those activities have an important role in minimizing the conversion of the native sagebrush steppe ecosystem found on the INEEL to non-native weeds. Four alternative management approaches were analyzed: Alternative 1 - maximum fire protection; Alternative 2 - balanced fire protection; Alternative 2 - balanced fire protection; Alternative 3 - protect infrastructure and personnel; and Alternative 4 - no action/traditional fire protection.

  12. Idaho National Engineering and Environmental Laboratory Wildland Fire Management Environmental Assessment

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

    Irving, John S

    DOE prepared an environmental assessment (EA)for wildland fire management activities on the Idaho National Engineering and Environmental Laboratory (INEEL) (DOE/EA-1372). The EA was developed to evaluate wildland fire management options for pre-fire, fire suppression, and post fire activities. Those activities have an important role in minimizing the conversion of the native sagebrush steppe ecosystem found on the INEEL to non-native weeds. Four alternative management approaches were analyzed: Alternative 1 - maximum fire protection; Alternative 2 - balanced fire protection; Alternative 2 - balanced fire protection; Alternative 3 - protect infrastructure and personnel; and Alternative 4 - no action/traditional fire protection.

  13. Exodus - Distributed artificial intelligence for Shuttle firing rooms

    NASA Technical Reports Server (NTRS)

    Heard, Astrid E.

    1990-01-01

    This paper describes the Expert System for Operations Distributed Users (EXODUS), a knowledge-based artificial intelligence system developed for the four Firing Rooms at the Kennedy Space Center. EXODUS is used by the Shuttle engineers and test conductors to monitor and control the sequence of tasks required for processing and launching Shuttle vehicles. In this paper, attention is given to the goals and the design of EXODUS, the operational requirements, and the extensibility of the technology.

  14. ENVIRONMENTAL TECHNOLOGY VERIFICATION REPORT ANR PIPELINE COMPANY PARAMETRIC EMISSIONS MONITORING SYSTEM (PEMS)

    EPA Science Inventory

    The Environmental Technology Verification report discusses the technology and performance of a gaseous-emissions monitoring system for large, natural-gas-fired internal combustion engines. The device tested is the Parametric Emissions Monitoring System (PEMS) manufactured by ANR ...

  15. Research in fire prevention.

    PubMed

    Pearce, N

    1985-10-01

    This paper describes in broad terms, the fire testing programme we carried out on whole bed assemblies in 1984. It should be clear that the tests were carried out in a thoroughly rigorous scientific manner. As always there is more to be done. The immediate task of finding the so called 'safe' bed assembly is proceeding with the search this year for safer pillows. Softer barrier foams are now being produced and it may be that the NHS could use full depth foam mattresses rather than a barrier foam wrap. On the engineering side I have explained the false alarm problem, and I have reviewed some of the research we are doing to see that new technology is used to give us better systems in future. Life safety sprinkler systems give the possibility of truly active fire protection in patient areas. They will enhance fire safety but at the moment no trade-offs can be offered in other areas of fire protection--either active or passive. My final point is that although I have considered the Department's fire research by looking separately at specific projects, the fire safety of a hospital must always be considered as a total package. To be effective, individual components of fire safety must not be considered in isolation but as part of the overall fire safety system.

  16. Robot Contest as a Laboratory for Experiential Engineering Education

    ERIC Educational Resources Information Center

    Verner, Igor M.; Ahlgren, David J.

    2004-01-01

    By designing, building, and operating autonomous robots students learn key engineering subjects and develop systems-thinking, problem-solving, and teamwork skills. Such events as the Trinity College Fire-Fighting Home Robot Contest (TCFFHRC) offer rich opportunities for students to apply their skills by requiring design, and implementation of…

  17. SSME Post Test Diagnostic System: Systems Section

    NASA Technical Reports Server (NTRS)

    Bickmore, Timothy

    1995-01-01

    An assessment of engine and component health is routinely made after each test firing or flight firing of a Space Shuttle Main Engine (SSME). Currently, this health assessment is done by teams of engineers who manually review sensor data, performance data, and engine and component operating histories. Based on review of information from these various sources, an evaluation is made as to the health of each component of the SSME and the preparedness of the engine for another test or flight. The objective of this project - the SSME Post Test Diagnostic System (PTDS) - is to develop a computer program which automates the analysis of test data from the SSME in order to detect and diagnose anomalies. This report primarily covers work on the Systems Section of the PTDS, which automates the analyses performed by the systems/performance group at the Propulsion Branch of NASA Marshall Space Flight Center (MSFC). This group is responsible for assessing the overall health and performance of the engine, and detecting and diagnosing anomalies which involve multiple components (other groups are responsible for analyzing the behavior of specific components). The PTDS utilizes several advanced software technologies to perform its analyses. Raw test data is analyzed using signal processing routines which detect features in the data, such as spikes, shifts, peaks, and drifts. Component analyses are performed by expert systems, which use 'rules-of-thumb' obtained from interviews with the MSFC data analysts to detect and diagnose anomalies. The systems analysis is performed using case-based reasoning. Results of all analyses are stored in a relational database and displayed via an X-window-based graphical user interface which provides ranked lists of anomalies and observations by engine component, along with supporting data plots for each.

  18. Non-Toxic Orbital Maneuvering System Engine Development

    NASA Technical Reports Server (NTRS)

    Green, Christopher; Claflin, Scott; Maeding, Chris; Butas, John

    1999-01-01

    Recent results using the Aestus engine operated with LOx/ethanol propellant are presented. An experimental program at Rocketdyne Propulsion and Power is underway to adapt this engine for the Boeing Reusable Space Systems Division non-toxic Orbital Maneuvering System/Reaction control System (OMS/RCS) system. Daimler-Chrysler Aerospace designed the Aestus as an nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) upper-stage engine for the Ariane 5. The non-toxic OMS/RCS system's preliminary design requires a LOx/ethanol (O2/C2H5OH) engine that operates with a mixture ratio of 1.8, a specific impulse of 323 seconds, and fits within the original OMS design envelope. This paper describes current efforts to meet these requirements including, investigating engine performance using LOx/ethanol, developing the en-ine system sizing package, and meeting the vehicle operation parameters. Data from hot-fire testing are also presented and discussed.

  19. Department of the Air Force. FY 1995 Budget Estimates. Military Construction and Family Housing

    DTIC Science & Technology

    1994-02-01

    monorail lift systems and provide AFFF fire protection system, and elevators. Renovate engineering and work areas; provide new air make-up unit and...135,0U0 SY 1,200 880-212 AFFF FIRE SUPPRESSION SYSTEM LS 800 FOR FUEL CELL TOTAL: 10,450 9b. Future Projects: Typical Planned Next Three Years: 111...PROTECT 2 EA 3,600 PH II & AFFF PUMPS/RESERVOIR TOTAL: 27,900 9b. Future Projects: Typical Planned Next Three Years: 442-758 WAREHOUSE 107,000 SF

  20. Inductive knowledge acquisition experience with commercial tools for space shuttle main engine testing

    NASA Technical Reports Server (NTRS)

    Modesitt, Kenneth L.

    1990-01-01

    Since 1984, an effort has been underway at Rocketdyne, manufacturer of the Space Shuttle Main Engine (SSME), to automate much of the analysis procedure conducted after engine test firings. Previously published articles at national and international conferences have contained the context of and justification for this effort. Here, progress is reported in building the full system, including the extensions of integrating large databases with the system, known as Scotty. Inductive knowledge acquisition has proven itself to be a key factor in the success of Scotty. The combination of a powerful inductive expert system building tool (ExTran), a relational data base management system (Reliance), and software engineering principles and Computer-Assisted Software Engineering (CASE) tools makes for a practical, useful and state-of-the-art application of an expert system.

  1. The KSC Simulation Team practices for contingencies in Firing Room 1

    NASA Technical Reports Server (NTRS)

    1998-01-01

    In Firing Room 1 at KSC, Shuttle launch team members put the Shuttle system through an integrated simulation. The control room is set up with software used to simulate flight and ground systems in the launch configuration. A Simulation Team, comprised of KSC engineers, introduce 12 or more major problems to prepare the launch team for worst-case scenarios. Such tests and simulations keep the Shuttle launch team sharp and ready for liftoff. The next liftoff is targeted for Oct. 29.

  2. AJ26 rocket engine test

    NASA Image and Video Library

    2010-11-10

    Fire and steam signal a successful test firing of Orbital Sciences Corporation's Aerojet AJ26 rocket engine at John C. Stennis Space Center. AJ26 engines will be used to power Orbital's Taurus II space vehicle on commercial cargo flights to the International Space Station. On Nov. 10, operators at Stennis' E-1 Test Stand conducted a 10-second test fire of the engine, the first of a series of three verification tests. Orbital has partnered with NASA to provide eight missions to the ISS by 2015.

  3. B-1 and B-3 Test Stands at NASA’s Plum Brook Station

    NASA Image and Video Library

    1966-09-21

    Operation of the High Energy Rocket Engine Research Facility (B-1), left, and Nuclear Rocket Dynamics and Control Facility (B-3) at the National Aeronautics and Space Administration’s (NASA) Plum Brook Station in Sandusky, Ohio. The test stands were constructed in the early 1960s to test full-scale liquid hydrogen fuel systems in simulated altitude conditions. Over the next decade each stand was used for two major series of liquid hydrogen rocket tests: the Nuclear Engine for Rocket Vehicle Application (NERVA) and the Centaur second-stage rocket program. The different components of these rocket engines could be studied under flight conditions and adjusted without having to fire the engine. Once the preliminary studies were complete, the entire engine could be fired in larger facilities. The test stands were vertical towers with cryogenic fuel and steam ejector systems. B-1 was 135 feet tall, and B-3 was 210 feet tall. Each test stand had several levels, a test section, and ground floor shop areas. The test stands relied on an array of support buildings to conduct their tests, including a control building, steam exhaust system, and fuel storage and pumping facilities. A large steam-powered altitude exhaust system reduced the pressure at the exhaust nozzle exit of each test stand. This allowed B-1 and B-3 to test turbopump performance in conditions that matched the altitudes of space.

  4. Fire tests to evaluate the potential fire threat and its effects on HEPA filter integrity in cell ventilation at the Oak Ridge National Laboratory, Building 7920

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

    Hasegawa, H.K.; Staggs, K.J.; Doughty, S.M.

    1992-12-01

    As a result of a DOE (Tiger Team) Technical Safety Appraisal (November 1990) of the Radiochemical Engineering Development Center (REDC), ORNL Building 7920, a number of fire protection concerns were identified. The primary concern was the perceived loss of ventilation system containment due to the thermal destruction and/or breaching of the prefilters and/or high-efficiency particulate air filters (HEPA `s) and the resultant radioactive release to the external environment. The following report describes the results of an extensive fire test program performed by the Fire Research Discipline (FRD) of the Special Projects Division of Lawrence Livermore National Lab (LLNL) and fundedmore » by ORNL to address these concerns. Full scale mock-ups of a REDC hot cell tank pit, adjacent cubicle pit, and associated ventilation system were constructed at LLNL and 13 fire experiments were conducted to specifically answer the questions raised by the Tiger Team. Our primary test plan was to characterize the burning of a catastrophic solvent spill (kerosene) of 40 liters and its effect on the containment ventilation system prefilters and HEPA filters. In conjunction with ORNL and Lockwood Greene we developed a test matrix that assessed the fire performance of the prefilters and HEPA filters; evaluated the fire response of the fiber reinforced plastic (FRP) epoxy ventilation duct work; the response and effectiveness of the fire protection system, the effect of fire in a cubicle on the vessel off-gas (VOG) elbow, and other fire safety questions.« less

  5. Engineering support for magnetohydrodynamic power plant analysis and design studies

    NASA Technical Reports Server (NTRS)

    Carlson, A. W.; Chait, I. L.; Marchmont, G.; Rogali, R.; Shikar, D.

    1980-01-01

    The major factors which influence the economic engineering selection of stack inlet temperatures in combined cycle MHD powerplants are identified and the range of suitable stack inlet temperatures under typical operating conditions is indicated. Engineering data and cost estimates are provided for four separately fired high temperature air heater (HTAH) system designs for HTAH system thermal capacity levels of 100, 250, 500 and 1000 MWt. An engineering survey of coal drying and pulverizing equipment for MHD powerplant application is presented as well as capital and operating cost estimates for varying degrees of coal pulverization.

  6. 36 CFR 200.1 - Central organization.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ..., engineering, lands, aviation, and computer systems. The National Forest System includes: 155 Proclaimed or... other environmental concerns, forest insects and disease, forest fire and atmospheric science. Plans and...-wide management of systems and computer applications. [41 FR 24350, June 16, 1976, as amended at 42 FR...

  7. 36 CFR 200.1 - Central organization.

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ..., engineering, lands, aviation, and computer systems. The National Forest System includes: 155 Proclaimed or... other environmental concerns, forest insects and disease, forest fire and atmospheric science. Plans and...-wide management of systems and computer applications. [41 FR 24350, June 16, 1976, as amended at 42 FR...

  8. 36 CFR 200.1 - Central organization.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ..., engineering, lands, aviation, and computer systems. The National Forest System includes: 155 Proclaimed or... other environmental concerns, forest insects and disease, forest fire and atmospheric science. Plans and...-wide management of systems and computer applications. [41 FR 24350, June 16, 1976, as amended at 42 FR...

  9. 36 CFR 200.1 - Central organization.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ..., engineering, lands, aviation, and computer systems. The National Forest System includes: 155 Proclaimed or... other environmental concerns, forest insects and disease, forest fire and atmospheric science. Plans and...-wide management of systems and computer applications. [41 FR 24350, June 16, 1976, as amended at 42 FR...

  10. Test Report for NASA MSFC Support of the Linear Aerospike SR-71 Experiment (LASRE)

    NASA Technical Reports Server (NTRS)

    Elam, S. K.

    2000-01-01

    The Linear Aerospike SR-71 Experiment (LASRE) was performed in support of the Reusable Launch Vehicle (RLV) program to help develop a linear aerospike engine. The objective of this program was to operate a small aerospike engine at various speeds and altitudes to determine how slipstreams affect the engine's performance. The joint program between government and industry included NASA!s Dryden Flight Research Center, The Air Force's Phillips Laboratory, NASA's Marshall Space Flight Center, Lockheed Martin Skunkworks, Lockheed-Martin Astronautics, and Rocketdyne Division of Boeing North American. Ground testing of the LASRE engine produced two successful hot-fire tests, along with numerous cold flows to verify sequencing and operation before mounting the assembly on the SR-71. Once installed on the aircraft, flight testing performed several cold flows on the engine system at altitudes ranging from 30,000 to 50,000 feet and Mach numbers ranging from 0.9 to 1.5. The program was terminated before conducting hot-fires in flight because excessive leaks in the propellant supply systems could not be fixed to meet required safety levels without significant program cost and schedule impacts.

  11. System Detects Vibrational Instabilities

    NASA Technical Reports Server (NTRS)

    Bozeman, Richard J., Jr.

    1990-01-01

    Sustained vibrations at two critical frequencies trigger diagnostic response or shutdown. Vibration-analyzing electronic system detects instabilities of combustion in rocket engine. Controls pulse-mode firing of engine and identifies vibrations above threshold amplitude at 5.9 and/or 12kHz. Adapted to other detection and/or control schemes involving simultaneous real-time detection of signals above or below preset amplitudes at two or more specified frequencies. Potential applications include rotating machinery and encoders and decoders in security systems.

  12. Using Innovative Technologies for Manufacturing Rocket Engine Hardware

    NASA Technical Reports Server (NTRS)

    Betts, E. M.; Eddleman, D. E.; Reynolds, D. C.; Hardin, N. A.

    2011-01-01

    Many of the manufacturing techniques that are currently used for rocket engine component production are traditional methods that have been proven through years of experience and historical precedence. As the United States enters into the next space age where new launch vehicles are being designed and propulsion systems are being improved upon, it is sometimes necessary to adopt innovative techniques for manufacturing hardware. With a heavy emphasis on cost reduction and improvements in manufacturing time, rapid manufacturing techniques such as Direct Metal Laser Sintering (DMLS) are being adopted and evaluated for their use on NASA s Space Launch System (SLS) upper stage engine, J-2X, with hopes of employing this technology on a wide variety of future projects. DMLS has the potential to significantly reduce the processing time and cost of engine hardware, while achieving desirable material properties by using a layered powder metal manufacturing process in order to produce complex part geometries. Marshall Space Flight Center (MSFC) has recently hot-fire tested a J-2X gas generator (GG) discharge duct that was manufactured using DMLS. The duct was inspected and proof tested prior to the hot-fire test. Using a workhorse gas generator (WHGG) test fixture at MSFC's East Test Area, the duct was subjected to extreme J-2X hot gas environments during 7 tests for a total of 537 seconds of hot-fire time. The duct underwent extensive post-test evaluation and showed no signs of degradation. DMLS manufacturing has proven to be a viable option for manufacturing rocket engine hardware, and further development and use of this manufacturing method is recommended.

  13. Internal combustion engine cylinder-to-cylinder balancing with balanced air-fuel ratios

    DOEpatents

    Harris, Ralph E.; Bourn, Gary D.; Smalley, Anthony J.

    2006-01-03

    A method of balancing combustion among cylinders of an internal combustion engine. For each cylinder, a normalized peak firing pressure is calculated as the ratio of its peak firing pressure to its combustion pressure. Each cylinder's normalized peak firing pressure is compared to a target value for normalized peak firing pressure. The fuel flow is adjusted to any cylinder whose normalized peak firing pressure is not substantially equal to the target value.

  14. The Elimination of Fire Hazard Due to Back Fires

    NASA Technical Reports Server (NTRS)

    Theodorsen, Theodore; Freeman, Ira M

    1933-01-01

    A critical study was made of the operation of a type of back-fire arrester used to reduce the fire hazard of aircraft engines. A flame arrester consisting of a pack or plug of alternate flat and corrugated plates of thin metal was installed in the intake pipe of a gasoline engines; an auxiliary spark plug inserted in the intake manifold permitted the production of artificial back fires at will. It was found possible to design a plug which prevented all back fires from reaching the carburetor.

  15. 76 FR 47092 - Approval and Promulgation of Implementation Plans; Reasonably Available Control Technology for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-04

    ... oxides of nitrogen from the stationary reciprocating, diesel fuel fired, internal combustion engines..., diesel fuel fired, internal combustion engines--one existing and one new engine. B. Why is EPA proposing... both engines. In addition, the Conditions of Approval specify the NO X emissions limits, combustion...

  16. 40 CFR Table 6 to Subpart IIIi of... - Optional 3-Mode Test Cycle for Stationary Fire Pump Engines

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 40 Protection of Environment 6 2010-07-01 2010-07-01 false Optional 3-Mode Test Cycle for.... IIII, Table 6 Table 6 to Subpart IIII of Part 60—Optional 3-Mode Test Cycle for Stationary Fire Pump Engines [As stated in § 60.4210(g), manufacturers of fire pump engines may use the following test cycle...

  17. Defense Acquisitions: Assessments of Selected Weapon Programs

    DTIC Science & Technology

    2016-03-01

    Increment 3 81 Indirect Fire Protection Capability Increment 2-Intercept Block 1 (IFPC Inc 2-I Block 1) 83 Improved Turbine Engine Program (ITEP...ITEP Improved Turbine Engine Program JAGM Joint Air-to-Ground Missile JLTV Joint Light Tactical Vehicle JSTARS Recap Joint Surveillance Target...Attack Radar System Recap 09/2017 —-   Improved Turbine Engine Program 06/2018 O O O Amphibious Ship Replacement 09/2018 O O Advanced Pilot

  18. FAA Rotorcraft Research, Engineering, and Development Bibliography, 1962-1988. Supplement

    DTIC Science & Technology

    1989-03-01

    fires, the aircraft engine was the major fire origin for twin- and single- engine air - craft. Only in single- engine aircraft was the instrument panel a...Certification Issues. The topics of Operational Requirements, Procedures, Air - worthiness and Engineering Capabilities are discussed. Volume II presents the...Issues. The topics of Operational Requirements, Procedures, Air - worthiness and Engineering Capabilities are discussed. Volume II presents the operator

  19. 7. COMPLETE X15 VEHICLE TEST STAND AFTER AN ENGINE FIRE ...

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

    7. COMPLETE X-15 VEHICLE TEST STAND AFTER AN ENGINE FIRE OR EXPLOSION. Wreckage of engine is still fixed in its clamp; X-15 vehicle lies on the ground detached from engine. - Edwards Air Force Base, X-15 Engine Test Complex, Rocket Engine & Complete X-15 Vehicle Test Stands, Rogers Dry Lake, east of runway between North Base & South Base, Boron, Kern County, CA

  20. INTEGRATED AIR POLLUTION CONTROL SYSTEM, VERSION 4.0 - VOLUME 1: USER'S GUIDE

    EPA Science Inventory

    The Integrated Air Pollution Control System (IAPCS) was developed for the U.S. EPA's Air and Energy Engineering Research Laboratory to estimate costs and performance for emission control systems applied to coal-fired utility boilers. The model can project a material balance, and ...

  1. 46 CFR 195.05-1 - Installation and details.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 7 2012-10-01 2012-10-01 false Installation and details. 195.05-1 Section 195.05-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS VESSEL... Systems. Fire Detecting and Alarm Systems. Sound Powered Telephone and Voice Tube Systems. Engine Order...

  2. 46 CFR 195.05-1 - Installation and details.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 7 2014-10-01 2014-10-01 false Installation and details. 195.05-1 Section 195.05-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS VESSEL... Systems. Fire Detecting and Alarm Systems. Sound Powered Telephone and Voice Tube Systems. Engine Order...

  3. 46 CFR 195.05-1 - Installation and details.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 7 2011-10-01 2011-10-01 false Installation and details. 195.05-1 Section 195.05-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS VESSEL... Systems. Fire Detecting and Alarm Systems. Sound Powered Telephone and Voice Tube Systems. Engine Order...

  4. 46 CFR 195.05-1 - Installation and details.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 7 2013-10-01 2013-10-01 false Installation and details. 195.05-1 Section 195.05-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS VESSEL... Systems. Fire Detecting and Alarm Systems. Sound Powered Telephone and Voice Tube Systems. Engine Order...

  5. Performance of the Spacecraft Propulsion Research Facility During Altitude Firing Tests of the Delta 3 Upper Stage

    NASA Technical Reports Server (NTRS)

    Meyer, Michael L.; Dickens, Kevin W.; Skaff, Tony F.; Cmar, Mark D.; VanMeter, Matthew J.; Haberbusch, Mark S.

    1998-01-01

    The Spacecraft Propulsion Research Facility at the NASA Lewis Research Center's Plum Brook Station was reactivated in order to conduct flight simulation ground tests of the Delta 3 cryogenic upper stage. The tests were a cooperative effort between The Boeing Company, Pratt and Whitney, and NASA. They included demonstration of tanking and detanking of liquid hydrogen, liquid oxygen and helium pressurant gas as well as 12 engine firings simulating first, second, and third burns at altitude conditions. A key to the success of these tests was the performance of the primary facility systems and their interfaces with the vehicle. These systems included the structural support of the vehicle, propellant supplies, data acquisition, facility control systems, and the altitude exhaust system. While the facility connections to the vehicle umbilical panel simulated the performance of the launch pad systems, additional purge and electrical connections were also required which were unique to ground testing of the vehicle. The altitude exhaust system permitted an approximate simulation of the boost-phase pressure profile by rapidly pumping the test chamber from 13 psia to 0.5 psia as well as maintaining altitude conditions during extended steady-state firings. The performance of the steam driven ejector exhaust system has been correlated with variations in cooling water temperature during these tests. This correlation and comparisons to limited data available from Centaur tests conducted in the facility from 1969-1971 provided insight into optimizing the operation of the exhaust system for future tests. Overall, the facility proved to be robust and flexible for vehicle space simulation engine firings and enabled all test objectives to be successfully completed within the planned schedule.

  6. Defining pyromes and global syndromes of fire regimes.

    PubMed

    Archibald, Sally; Lehmann, Caroline E R; Gómez-Dans, Jose L; Bradstock, Ross A

    2013-04-16

    Fire is a ubiquitous component of the Earth system that is poorly understood. To date, a global-scale understanding of fire is largely limited to the annual extent of burning as detected by satellites. This is problematic because fire is multidimensional, and focus on a single metric belies its complexity and importance within the Earth system. To address this, we identified five key characteristics of fire regimes--size, frequency, intensity, season, and extent--and combined new and existing global datasets to represent each. We assessed how these global fire regime characteristics are related to patterns of climate, vegetation (biomes), and human activity. Cross-correlations demonstrate that only certain combinations of fire characteristics are possible, reflecting fundamental constraints in the types of fire regimes that can exist. A Bayesian clustering algorithm identified five global syndromes of fire regimes, or pyromes. Four pyromes represent distinctions between crown, litter, and grass-fueled fires, and the relationship of these to biomes and climate are not deterministic. Pyromes were partially discriminated on the basis of available moisture and rainfall seasonality. Human impacts also affected pyromes and are globally apparent as the driver of a fifth and unique pyrome that represents human-engineered modifications to fire characteristics. Differing biomes and climates may be represented within the same pyrome, implying that pathways of change in future fire regimes in response to changes in climate and human activity may be difficult to predict.

  7. Defining pyromes and global syndromes of fire regimes

    PubMed Central

    Archibald, Sally; Lehmann, Caroline E. R.; Gómez-Dans, Jose L.; Bradstock, Ross A.

    2013-01-01

    Fire is a ubiquitous component of the Earth system that is poorly understood. To date, a global-scale understanding of fire is largely limited to the annual extent of burning as detected by satellites. This is problematic because fire is multidimensional, and focus on a single metric belies its complexity and importance within the Earth system. To address this, we identified five key characteristics of fire regimes—size, frequency, intensity, season, and extent—and combined new and existing global datasets to represent each. We assessed how these global fire regime characteristics are related to patterns of climate, vegetation (biomes), and human activity. Cross-correlations demonstrate that only certain combinations of fire characteristics are possible, reflecting fundamental constraints in the types of fire regimes that can exist. A Bayesian clustering algorithm identified five global syndromes of fire regimes, or pyromes. Four pyromes represent distinctions between crown, litter, and grass-fueled fires, and the relationship of these to biomes and climate are not deterministic. Pyromes were partially discriminated on the basis of available moisture and rainfall seasonality. Human impacts also affected pyromes and are globally apparent as the driver of a fifth and unique pyrome that represents human-engineered modifications to fire characteristics. Differing biomes and climates may be represented within the same pyrome, implying that pathways of change in future fire regimes in response to changes in climate and human activity may be difficult to predict. PMID:23559374

  8. Spaceflight 101: Explorer 1

    NASA Image and Video Library

    2018-05-09

    Aerospace pioneers who worked on the launch of Explorer 1 participate in a panel discussion with NASA Kennedy Space Center Director Bob Cabana at the center's Training Auditorium on Wednesday, May 9, 2018. Panelists, from left are William "Curly" Chandler, firing room engineer; Lionel (Ed) Fannin, mechanical and propulsion systems; Terry Greenfield, blockhouse engineer; Carl Jones, measuring branch engineer; and Ike Rigell, electrical networks systems chief. Explorer 1 was the first satellite launched by the U.S. It was launched by the Army Ballistic Missile Agency on Jan. 31, 1958 on a Juno I rocket from Launch Complex-26.

  9. On-line structural health and fire monitoring of a composite personal aircraft using an FBG sensing system

    NASA Astrophysics Data System (ADS)

    Chandler, K.; Ferguson, S.; Graver, T.; Csipkes, A.; Mendez, A.

    2008-03-01

    We report in this paper on the design and development of a novel on-line structural health monitoring and fire detection system based on an array of optical fiber Bragg grating (FBG) sensors and interrogation system installed on a new, precommercial compact aircraft. A combined total of 17 FBG sensors - strain, temperature and high-temperature - were installed at critical locations in an around the wings, fuselage and engine compartment of a prototype, Comp Air CA 12 all-composite, ten-passenger personal airplane powered by a 1,650 hp turbine engine. The sensors are interrogated online and in real time by a swept laser FBG interrogator (Micron Optics sm125-700) mounted on board the plane. Sensors readings are then combined with the plane's avionics system and displayed on the pilot's aviation control panel. This system represents the first of its kind in commercial, small frame, airplanes and a first for optical fiber sensors.

  10. 14 CFR 23.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... controls, engine mounts, and other flight structure. Flight controls, engine mounts, and other flight... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false Fire protection of flight controls, engine mounts, and other flight structure. 23.865 Section 23.865 Aeronautics and Space FEDERAL AVIATION...

  11. 14 CFR 23.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... controls, engine mounts, and other flight structure. Flight controls, engine mounts, and other flight... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Fire protection of flight controls, engine mounts, and other flight structure. 23.865 Section 23.865 Aeronautics and Space FEDERAL AVIATION...

  12. 14 CFR 23.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... controls, engine mounts, and other flight structure. Flight controls, engine mounts, and other flight... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Fire protection of flight controls, engine mounts, and other flight structure. 23.865 Section 23.865 Aeronautics and Space FEDERAL AVIATION...

  13. 14 CFR 23.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... controls, engine mounts, and other flight structure. Flight controls, engine mounts, and other flight... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Fire protection of flight controls, engine mounts, and other flight structure. 23.865 Section 23.865 Aeronautics and Space FEDERAL AVIATION...

  14. 14 CFR 23.865 - Fire protection of flight controls, engine mounts, and other flight structure.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... controls, engine mounts, and other flight structure. Flight controls, engine mounts, and other flight... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Fire protection of flight controls, engine mounts, and other flight structure. 23.865 Section 23.865 Aeronautics and Space FEDERAL AVIATION...

  15. EM-1 Countdown Simulation with Charlie Blackwell-Thompson

    NASA Image and Video Library

    2018-03-29

    Liquid Oxygen Systems Engineer Quinten Jones, left and Liquid Oxygen Systems Engineer Andrew "Kody" Smitherman, both of Jacobs, monitor operation from his position in Firing Room 1 at the Kennedy Space Center's Launch Control Center during a countdown simulation for Exploration Mission 1. It was the agency's first simulation of a portion of the countdown for the first launch of a Space Launch System rocket and Orion spacecraft that will eventually take astronauts beyond low-Earth orbit to destinations such as the Moon and Mars.

  16. Ways to Improve Russian Coal-Fired Power Plants

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

    Tumanovskii, A. G., E-mail: vti@vti.ru; Olkhovsky, G. G.

    Coal is an important fuel for the electric power industry of Russia, especially in Ural and the eastern part of the country. It is fired in boilers of large (200 – 800 MW) condensing power units and in many cogeneration power plants with units rated at 50 – 180 MW. Many coal-fired power plants have been operated for more than 40 – 50 years. Though serviceable, their equipment is obsolete and does not comply with the current efficiency, environmental, staffing, and availability standards. It is urgent to retrofit and upgrade such power plants using advanced equipment, engineering and business ideas.more » Russian power-plant engineering companies have designed such advanced power units and their equipment such as boilers, turbines, auxiliaries, process and environmental control systems similar to those produced by the world’s leading manufacturers. Their performance and ways of implementation are discussed.« less

  17. 46 CFR 95.01-2 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...) NFPA 13-1996, Standard for the Installation of Sprinkler Systems, incorporation by reference approved... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) CARGO AND MISCELLANEOUS VESSELS FIRE... and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  18. 46 CFR 95.01-2 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...) NFPA 13-1996, Standard for the Installation of Sprinkler Systems, incorporation by reference approved... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) CARGO AND MISCELLANEOUS VESSELS FIRE... and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  19. 14. Site D57C, Improved NIKEHercules System, Grading Plan, U.S. Army ...

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

    14. Site D-57-C, Improved NIKE-Hercules System, Grading Plan, U.S. Army Corps of Engineers, 18 January 1962. - Newport NIKE Missile Battery D-57/58, Integrated Fire Control Area, Newport Road, Carleton, Monroe County, MI

  20. Coil-On-Plug Ignition for LOX/Methane Liquid Rocket Engines in Thermal Vacuum Environments

    NASA Technical Reports Server (NTRS)

    Melcher, John C.; Atwell, Matthew J.; Morehead, Robert L.; Hurlbert, Eric A.; Bugarin, Luz; Chaidez, Mariana

    2017-01-01

    A coil-on-plug ignition system has been developed and tested for Liquid Oxygen (LOX) / liquid methane rocket engines operating in thermal vacuum conditions. The igniters were developed and tested as part of the Integrated Cryogenic Propulsion Test Article (ICPTA), previously tested as part of the Project Morpheus test vehicle. The ICPTA uses an integrated, pressure-fed, cryogenic LOX/methane propulsion system including a reaction control system (RCS) and a main engine. The ICPTA was tested at NASA Glenn Research Center's Plum Brook Station in the Spacecraft Propulsion Research Facility (B-2) under vacuum and thermal vacuum conditions. In order to successfully demonstrate ignition reliability in the vacuum conditions and eliminate corona discharge issues, a coil-on-plug ignition system has been developed. The ICPTA uses spark-plug ignition for both the main engine igniter and the RCS. The coil-on-plug configuration eliminates the conventional high-voltage spark plug cable by combining the coil and the spark-plug into a single component. Prior to ICPTA testing at Plum Brook, component-level reaction control engine (RCE) and main engine igniter testing was conducted at NASA Johnson Space Center (JSC), which demonstrated successful hot-fire ignition using the coil-on-plug from sea-level ambient conditions down to 10(exp.-2) torr. Integrated vehicle hot-fire testing at JSC demonstrated electrical and command/data system performance. Lastly, Plum Brook testing demonstrated successful ignitions at simulated altitude conditions at 30 torr and cold thermal-vacuum conditions at 6 torr. The test campaign successfully proved that coil-on-plug technology will enable integrated LOX/methane propulsion systems in future spacecraft.

  1. INTEGRATED AIR POLLUTION CONTROL SYSTEM, VERSION 4.0 - VOLUME 3: PROGRAMMER'S MAINTENACE MANUAL

    EPA Science Inventory

    The Integrated Air Pollution Control System (IAPCS) was developed for the U.S. EPA's Air and Energy Engineering Research Laboratory to estimate costs and performance for emission control systems applied to coal-fired utility boilers. The model can project a material balance, and ...

  2. INTEGRATED AIR POLLUTION CONTROL SYSTEM, VERSION 4.0 - VOLUME 2: TECHNICAL DOCUMENTATION MANUAL

    EPA Science Inventory

    The Integrated Air Pollution Control System (IAPCS) was developed for the U.S. EPA's Air and Energy Engineering Research Laboratory to estimate costs and performance for emission control systems applied to coal-fired utility boilers. The model can project a material balance, and ...

  3. 46 CFR 62.25-30 - Environmental design standards.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...-30 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING VITAL SYSTEM AUTOMATION General Requirements for All Automated Vital Systems § 62.25-30 Environmental design standards. (a... inclination requirements for fire and flooding safety systems are described in 46 CFR 112.05-5(c). (2) Ambient...

  4. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant. Conceptual Design Engineering Report (CDER). Volume 4: Supplementary engineering data

    NASA Astrophysics Data System (ADS)

    1981-09-01

    The reference conceptual design of the Magnetohydrodynamic Engineering Test Facility (ETF), a prototype 200 MWe coal-fired electric generating plant designed to demonstrate the commercial feasibility of open cycle MHD is summarized. Main elements of the design are identified and explained, and the rationale behind them is reviewed. Major systems and plant facilities are listed and discussed. Construction cost and schedule estimates, and identification of engineering issues that should be reexamined are also given. The latest (1980-1981) information from the MHD technology program are integrated with the elements of a conventional steam power electric generating plant. Supplementary Engineering Data (Issues, Background, Performance Assurance Plan, Design Details, System Design Descriptions and Related Drawings) is presented.

  5. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant. Conceptual Design Engineering Report (CDER). Volume 4: Supplementary engineering data

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The reference conceptual design of the Magnetohydrodynamic Engineering Test Facility (ETF), a prototype 200 MWe coal-fired electric generating plant designed to demonstrate the commercial feasibility of open cycle MHD is summarized. Main elements of the design are identified and explained, and the rationale behind them is reviewed. Major systems and plant facilities are listed and discussed. Construction cost and schedule estimates, and identification of engineering issues that should be reexamined are also given. The latest (1980-1981) information from the MHD technology program are integrated with the elements of a conventional steam power electric generating plant. Supplementary Engineering Data (Issues, Background, Performance Assurance Plan, Design Details, System Design Descriptions and Related Drawings) is presented.

  6. Conceptual design of the MHD Engineering Test Facility

    NASA Technical Reports Server (NTRS)

    Bents, D. J.; Bercaw, R. W.; Burkhart, J. A.; Mroz, T. S.; Rigo, H. S.; Pearson, C. V.; Warinner, D. K.; Hatch, A. M.; Borden, M.; Giza, D. A.

    1981-01-01

    The reference conceptual design of the MHD engineering test facility, a prototype 200 MWe coal-fired electric generating plant designed to demonstrate the commerical feasibility of open cycle MHD is summarized. Main elements of the design are identified and explained, and the rationale behind them is reviewed. Major systems and plant facilities are listed and discussed. Construction cost and schedule estimates are included and the engineering issues that should be reexamined are identified.

  7. Safety engineering in handling fuels and lubricants in civil aviation

    NASA Astrophysics Data System (ADS)

    Protoereiskii, Aleksandr Stepanovich

    The book is concerned with methods of improving working conditions, work hygiene, safety engineering, and fire and explosion prevention during the storage and handling of petroleum products at fuel and lubricant storage facilities. The discussion covers methods of protection against static and atmospheric discharges, lightning protection, safety engineering in fuel and lubricant laboratories, and methods of fire prevention and fire extinction. Attention is also given to methods for administering first aid in case of accidents and poisoning.

  8. Facility Activation and Characterization for IPD Workhorse Preburner and Oxidizer Turbopump Hot-Fire Testing at NASA Stennis Space Center

    NASA Technical Reports Server (NTRS)

    Sass, J. P.; Raines, N. G.; Ryan, H. M.

    2004-01-01

    The Integrated Powerhead Demonstrator (IPD) is a 250K lbf (1.1 MN) thrust cryogenic hydrogen/oxygen engine technology demonstrator that utilizes a full flow staged combustion engine cycle. The Integrated Powerhead Demonstrator (IPD) is part of NASA's Next Generation Launch Technology (NGLT) program, which seeks to provide safe, dependable, cost-cutting technologies for future space launch systems. The project also is part of the Department of Defense's Integrated High Payoff Rocket Propulsion Technology (IHPRPT) program, which seeks to increase the performance and capability of today s state-of-the-art rocket propulsion systems while decreasing costs associated with military and commercial access to space. The primary industry participants include Boeing-Rocketdyne and GenCorp Aerojet. The intended full flow engine cycle is a key component in achieving all of the aforementioned goals. The IPD Program recently achieved a major milestone with the successful completion of the IPD Oxidizer Turbopump (OTP) hot-fire test project at the NASA John C. Stennis Space Center (SSC) E-1 test facility in June 2003. A total of nine IPD Workhorse Preburner tests were completed, and subsequently 12 IPD OTP hot-fire tests were completed. The next phase of development involves IPD integrated engine system testing also at the NASA SSC E-1 test facility scheduled to begin in late 2004. Following an overview of the NASA SSC E-1 test facility, this paper addresses the facility aspects pertaining to the activation and testing of the IPD Workhorse Preburner and the IPD Oxidizer Turbopump. In addition, some of the facility challenges encountered during the test project shall be addressed.

  9. 14 CFR 29.1121 - General.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... vapors outside the shroud. (h) If significant traps exist, each turbine engine exhaust system must have... exhaust gases without fire hazard or carbon monoxide contamination in any personnel compartment. (b) Each... exhaust system. (c) Each component upon which hot exhaust gases could impinge, or that could be subjected...

  10. 14 CFR 29.1121 - General.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... vapors outside the shroud. (h) If significant traps exist, each turbine engine exhaust system must have... exhaust gases without fire hazard or carbon monoxide contamination in any personnel compartment. (b) Each... exhaust system. (c) Each component upon which hot exhaust gases could impinge, or that could be subjected...

  11. 14 CFR 29.1121 - General.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... vapors outside the shroud. (h) If significant traps exist, each turbine engine exhaust system must have... exhaust gases without fire hazard or carbon monoxide contamination in any personnel compartment. (b) Each... exhaust system. (c) Each component upon which hot exhaust gases could impinge, or that could be subjected...

  12. 14 CFR 29.1121 - General.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... vapors outside the shroud. (h) If significant traps exist, each turbine engine exhaust system must have... exhaust gases without fire hazard or carbon monoxide contamination in any personnel compartment. (b) Each... exhaust system. (c) Each component upon which hot exhaust gases could impinge, or that could be subjected...

  13. 46 CFR 162.161-4 - Construction.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-4... mechanical or pneumatic means. (d) Automatically actuated systems must be released by pneumatic or fusible... actuation and have a remote backup manual mechanical actuator. (f) Each container charged with nitrogen must...

  14. 46 CFR 162.161-4 - Construction.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-4... mechanical or pneumatic means. (d) Automatically actuated systems must be released by pneumatic or fusible... actuation and have a remote backup manual mechanical actuator. (f) Each container charged with nitrogen must...

  15. 46 CFR 162.161-4 - Construction.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-4... mechanical or pneumatic means. (d) Automatically actuated systems must be released by pneumatic or fusible... actuation and have a remote backup manual mechanical actuator. (f) Each container charged with nitrogen must...

  16. 46 CFR 76.01-2 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...) NFPA 13-1996, Standard for the Installation of Sprinkler Systems (“NFPA 13”), incorporation by... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) PASSENGER VESSELS FIRE PROTECTION... and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  17. 46 CFR 76.01-2 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...) NFPA 13-1996, Standard for the Installation of Sprinkler Systems (“NFPA 13”), incorporation by... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) PASSENGER VESSELS FIRE PROTECTION... and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  18. History of Fire Events in the U.S. Commercial Nuclear Industry

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

    Bijan Najafi; Joglar-Biloch, Francisco; Kassawara, Robert P.

    2002-07-01

    Over the past decade, interest in performance-based fire protection has increased within the nuclear industry. In support of this growing interest, in 1997 the Electric Power Research Institute (EPRI) developed a long-range plan to develop/improve data and tools needed to support Risk-Informed/Performance-Based fire protection. This plan calls for continued improvement in collection and use of information obtained from fire events at nuclear plants. The data collection process has the objectives of improving the insights gained from such data and reducing the uncertainty in fire risk and fire modeling methods in order to make them a more reliable basis for performancemore » based fire protection programs. In keeping with these objectives, EPRI continues to collect, review and analyze fire events in support of the nuclear industry. EPRI collects these records in cooperation with the Nuclear Electric Insurance Limited (NEIL), by compiling public fire event reports and by direct solicitation of U.S. nuclear facilities. EPRI fire data collection project is based on the principle that the understanding of history is one of the cornerstones of improving fire protection technology and practice. Therefore, the goal has been to develop and maintain a comprehensive database of fire events with flexibility to support various aspects of fire protection engineering. With more than 1850 fire records over a period of three decades and 2400 reactor years, this is the most comprehensive database of nuclear power industry fire events in existence today. In general, the frequency of fires in the U.S. commercial nuclear industry remains constant. In few cases, e.g., transient fires and fires in BWR offgas/recombiner systems, where either increasing or decreasing trends are observed, these trends tend to slow after 1980. The key issues in improving quality of the data remain to be consistency of the recording and reporting of fire events and difficulties in collection of records. EPRI has made significant progress towards improving the quality of the fire events data through use of multiple collection methods as well as its review and verification. To date EPRI has used this data to develop a generic fire ignition frequency model for U.S. nuclear power industry (Ref. 1, 4 and 5) as well as to support other models in support of EPRI Fire Risk Methods such as a cable fire manual suppression model. EPRI will continue its effort to collect and analyze operating data to support risk informed/performance based fire safety engineering, including collection and analysis of impairment data for fire protection systems and features. This paper provides details on the collection and application of fire events to risk informed/performance based fire protection. The paper also provides valuable insights into improving both collection and use of fire events data. (authors)« less

  19. Guide for Oxygen Compatibility Assessments on Oxygen Components and Systems

    NASA Technical Reports Server (NTRS)

    Rosales, Keisa R.; Shoffstall, Michael S.; Stoltzfus, Joel M.

    2007-01-01

    Understanding and preventing fire hazards is necessary when designing, maintaining, and operating oxygen systems. Ignition risks can be minimized by controlling heat sources and using materials that will not ignite or will not support burning in the end-use environment. Because certain materials are more susceptible to ignition in oxygen-enriched environments, a compatibility assessment should be performed before the component is introduced into an oxygen system. This document provides an overview of oxygen fire hazards and procedures that are consistent with the latest versions of American Society for Testing and Materials (ASTM) Standards G63 (1999) and G94 (2005) to address fire hazards associated with oxygen systems. This document supersedes the previous edition, NASA Technical Memorandum 104823, Guide for Oxygen Hazards Analyses on Components and Systems (1996). The step-by-step oxygen compatibility assessment method described herein (see Section 4) enables oxygen-system designers, system engineers, and facility managers to determine areas of concern with respect to oxygen compatibility and, ultimately, prevent damage to a system or injury to personnel.

  20. Passive fire protection--a vital safety role.

    PubMed

    MacInnes, Callum; Rankin, Richard

    2012-06-01

    Callum Maclnnes BSc (Hons), AIFireE, an engineer at WSP UK--part of a global design engineering and management consultancy group specialising in property, transport and infrastructure, industry and environment projects--and his colleague, senior engineer, Richard Rankin CEng MEng (Hons) MIFireE, discuss the importance of passive fire protection in healthcare premises at a time when, due particularly to the difficult financial climate, many hospitals are undergoing upgrading and refurbishment, potentially affording an ideal opportunity to ensure that proper fire compartmentation measures are in place.

  1. Verification study of an emerging fire suppression system

    DOE PAGES

    Cournoyer, Michael E.; Waked, R. Ryan; Granzow, Howard N.; ...

    2016-01-01

    Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Moreover, plutonium gloveboxes present harsh environmental conditions for polymer materials; these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. Several studies have been conducted to determine the robustness of selfcontained fire extinguishers in plutonium gloveboxes in a nuclear facility, verification tests must be performed. These tests include activation and mass loss calorimeter tests. In addition, compatibility issues with chemical components of the self-contained fire extinguishers need to be addressed. Our study presents activation andmore » mass loss calorimeter test results. After extensive studies, no critical areas of concern have been identified for the plutonium glovebox application of Fire Foe™, except for glovebox operations that use large quantities of bulk plutonium or uranium metal such as metal casting and pyro-chemistry operations.« less

  2. Verification study of an emerging fire suppression system

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

    Cournoyer, Michael E.; Waked, R. Ryan; Granzow, Howard N.

    Self-contained fire extinguishers are a robust, reliable and minimally invasive means of fire suppression for gloveboxes. Moreover, plutonium gloveboxes present harsh environmental conditions for polymer materials; these include radiation damage and chemical exposure, both of which tend to degrade the lifetime of engineered polymer components. Several studies have been conducted to determine the robustness of selfcontained fire extinguishers in plutonium gloveboxes in a nuclear facility, verification tests must be performed. These tests include activation and mass loss calorimeter tests. In addition, compatibility issues with chemical components of the self-contained fire extinguishers need to be addressed. Our study presents activation andmore » mass loss calorimeter test results. After extensive studies, no critical areas of concern have been identified for the plutonium glovebox application of Fire Foe™, except for glovebox operations that use large quantities of bulk plutonium or uranium metal such as metal casting and pyro-chemistry operations.« less

  3. Demonstrated survivability of a high temperature optical fiber cable on a 1500 pound thrust rocket chamber

    NASA Technical Reports Server (NTRS)

    Sovie, Amy L.

    1992-01-01

    A demonstration of the ability of an existing optical fiber cable to survive the harsh environment of a rocket engine was performed at the NASA Lewis Research Center. The intent of this demonstration was to prove the feasibility of applying fiber optic technology to rocket engine instrumentation systems. Extreme thermal transient tests were achieved by wrapping a high temperature optical fiber, which was cablized for mechanical robustness, around the combustion chamber outside wall of a 1500 lb Hydrogen-Oxygen rocket engine. Additionally, the fiber was wrapped around coolant inlet pipes which were subject to near liquid hydrogen temperatures. Light from an LED was sent through the multimode fiber, and output power was monitored as a function of time while the engine was fired. The fiber showed no mechanical damage after 419 firings during which it was subject to transients from 30 K to 350 K, and total exposure time to near liquid hydrogen temperatures in excess of 990 seconds. These extreme temperatures did cause attenuation greater than 3 dB, but the signal was fully recovered at room temperature. This experiment demonstrates that commercially available optical fiber cables can survive the environment seen by a typical rocket engine instrumentation system, and disclose a temperature-dependent attenuation observed during exposure to near liquid hydrogen temperatures.

  4. 14 CFR 33.17 - Fire protection.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... STANDARDS: AIRCRAFT ENGINES Design and Construction; General § 33.17 Fire protection. (a) The design and... addition, the design and construction of turbine engines must minimize the probability of the occurrence of...

  5. Hot-Fire Test Results of an Oxygen/RP-2 Multi-Element Oxidizer-Rich Staged-Combustion Integrated Test Article

    NASA Technical Reports Server (NTRS)

    Hulka, J. R.; Protz, C. S.; Garcia, C. P.; Casiano, M. J.; Parton, J. A.

    2016-01-01

    As part of the Combustion Stability Tool Development project funded by the Air Force Space and Missile Systems Center, the NASA Marshall Space Flight Center was contracted to assemble and hot-fire test a multi-element integrated test article demonstrating combustion characteristics of an oxygen/hydrocarbon propellant oxidizer-rich staged-combustion engine thrust chamber. Such a test article simulates flow through the main injectors of oxygen/kerosene oxidizer-rich staged combustion engines such as the Russian RD-180 or NK-33 engines, or future U.S.-built engine systems such as the Aerojet-Rocketdyne AR-1 engine or the Hydrocarbon Boost program demonstration engine. For the thrust chamber assembly of the test article, several configurations of new main injectors, using relatively conventional gas-centered swirl coaxial injector elements, were designed and fabricated. The design and fabrication of these main injectors are described in a companion paper at this JANNAF meeting. New ablative combustion chambers were fabricated based on hardware previously used at NASA for testing at similar size and pressure. An existing oxygen/RP-1 oxidizer-rich subscale preburner injector from a previous NASA-funded program, along with existing and new inter-connecting hot gas duct hardware, were used to supply the oxidizer-rich combustion products to the oxidizer circuit of the main injector of the thrust chamber. Results from independent hot-fire tests of the preburner injector in a combustion chamber with a sonic throat are described in companion papers at this JANNAF conference. The resulting integrated test article - which includes the preburner, inter-connecting hot gas duct, main injector, and ablative combustion chamber - was assembled at Test Stand 116 at the East Test Area of the NASA Marshall Space Flight Center. The test article was well instrumented with static and dynamic pressure, temperature, and acceleration sensors to allow the collected data to be used for combustion analysis model development. Hot-fire testing was conducted with main combustion chamber pressures ranging from 1400 to 2100 psia, and main combustion chamber mixture ratios ranging from 2.4 to 2.9. Different levels of fuel film cooling injected from the injector face were examined ranging from none to about 12% of the total fuel flow. This paper presents the hot-fire test results of the integrated test article. Combustion performance, stability, thermal, and compatibility characteristics of both the preburner and the thrust chamber are described. Another companion paper at this JANNAF meeting includes additional and more detailed test data regarding the combustion dynamics and stability characteristics.

  6. 46 CFR 193.01-3 - Incorporation by reference.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., Standard for the Installation of Sprinkler Systems, incorporation by reference approved for § 193.30-1. (2... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS FIRE... Design and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  7. 46 CFR 193.01-3 - Incorporation by reference.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., Standard for the Installation of Sprinkler Systems, incorporation by reference approved for § 193.30-1. (2... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) OCEANOGRAPHIC RESEARCH VESSELS FIRE... Design and Engineering Systems, U.S. Coast Guard Stop 7509, 2703 Martin Luther King Jr. Avenue SE...

  8. 46 CFR 111.99-3 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Definitions. 111.99-3 Section 111.99-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING ELECTRIC SYSTEMS-GENERAL REQUIREMENTS Fire Door Holding and Release Systems § 111.99-3 Definitions. As used in this subpart— Central...

  9. B-29 Superfortress Engine in the Altitude Wind Tunnel

    NASA Image and Video Library

    1944-07-21

    The resolution of the Boeing B-29 Superfortress’ engine cooling problems was one of the Aircraft Engine Research Laboratory’s (AERL) key contributions to the World War II effort. The B-29 leapfrogged previous bombers in size, speed, and altitude capabilities. The B–29 was intended to soar above anti-aircraft fire and make pinpoint bomb drops onto strategic targets. Four Wright Aeronautical R-3350 engines powered the massive aircraft. The engines, however, frequently strained and overheated due to payload overloading. This resulted in a growing number of engine fires that often resulted in crashes. The military asked the NACA to tackle the overheating issue. Full-scale engine tests on a R–3350 engine in the Prop House demonstrated that a NACA-designed impeller increased the fuel injection system’s flow rate. Single-cylinder studies resolved a valve failure problem by a slight extension of the cylinder head, and researchers in the Engine Research Building combated uneven heating with a new fuel injection system. Investigations during the summer of 1944 in the Altitude Wind Tunnel, which could simulate flight conditions at high altitudes, led to reduction of drag and improved air flow by reshaping the cowling inlet and outlet. The NACA modifications were then flight tested on a B-29 bomber that was brought to the AERL.

  10. Identification of Noise Sources During Rocket Engine Test Firings and a Rocket Launch Using a Microphone Phased-Array

    NASA Technical Reports Server (NTRS)

    Panda, Jayanta; Mosher, Robert N.; Porter, Barry J.

    2013-01-01

    A 70 microphone, 10-foot by 10-foot, microphone phased array was built for use in the harsh environment of rocket launches. The array was setup at NASA Wallops launch pad 0A during a static test firing of Orbital Sciences' Antares engines, and again during the first launch of the Antares vehicle. It was placed 400 feet away from the pad, and was hoisted on a scissor lift 40 feet above ground. The data sets provided unprecedented insight into rocket noise sources. The duct exit was found to be the primary source during the static test firing; the large amount of water injected beneath the nozzle exit and inside the plume duct quenched all other sources. The maps of the noise sources during launch were found to be time-dependent. As the engines came to full power and became louder, the primary source switched from the duct inlet to the duct exit. Further elevation of the vehicle caused spilling of the hot plume, resulting in a distributed noise map covering most of the pad. As the entire plume emerged from the duct, and the ondeck water system came to full power, the plume itself became the loudest noise source. These maps of the noise sources provide vital insight for optimization of sound suppression systems for future Antares launches.

  11. 16 CFR 1101.32 - Reasonable steps to assure information is accurate.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ..., an electrical engineer, or an attending physician) conducts an investigation or an inspection which... fire marshal, a fire investigator, an electrical engineer, an ambulance attendant, or an attending...

  12. 16 CFR 1101.32 - Reasonable steps to assure information is accurate.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ..., an electrical engineer, or an attending physician) conducts an investigation or an inspection which... fire marshal, a fire investigator, an electrical engineer, an ambulance attendant, or an attending...

  13. 16 CFR 1101.32 - Reasonable steps to assure information is accurate.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ..., an electrical engineer, or an attending physician) conducts an investigation or an inspection which... fire marshal, a fire investigator, an electrical engineer, an ambulance attendant, or an attending...

  14. 16 CFR 1101.32 - Reasonable steps to assure information is accurate.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ..., an electrical engineer, or an attending physician) conducts an investigation or an inspection which... fire marshal, a fire investigator, an electrical engineer, an ambulance attendant, or an attending...

  15. Spaceflight 101: Explorer 1

    NASA Image and Video Library

    2018-05-09

    Aerospace pioneers who worked on the launch of Explorer 1 participate in a panel discussion with NASA Kennedy Space Center Director Bob Cabana, at far left, at the center's Training Auditorium on Wednesday, May 9, 2018. Panelists, from left are William "Curly" Chandler, firing room engineer; Lionel (Ed) Fannin, mechanical and propulsion systems; Terry Greenfield, blockhouse engineer; Carl Jones, measuring branch engineer; and Ike Rigell, electrical networks systems chief. Explorer 1 was the first satellite launched by the U.S. It was launched by the Army Ballistic Missile Agency on Jan. 31, 1958 on a Juno I rocket from Launch Complex-26.

  16. Fire and Rescue Technology. Resources in Technology.

    ERIC Educational Resources Information Center

    Valesey, Brigitte G.

    1997-01-01

    Provides occupational information about fire and rescue operations personnel, such as fire science, fire protection engineering, emergency medical technicians, and firefighters. Provides information about organizations in these fields. (JOW)

  17. Development of unified propulsion system for geostationary satellite

    NASA Astrophysics Data System (ADS)

    Murayama, S.; Kobayashi, H.; Masuda, I.; Kameishi, M.; Miyoshi, K.; Takahashi, M.

    Japan's first Liquid Apogee Propulsion System (LAPS) has been developed for ETS-VI (Engineering Test Satellite - VI) 2-ton class geostationary satellite. The next largest (2-ton class) geostationary satellite, COMETS (Communication and Broadcasting Engineering Test Satellite), requires a more compact apogee propulsion system in order to increase the space for mission instruments. The study for such a propulsion system concluded with a Unified Propulsion System (UPS), which uses a common N2H4 propellant tank for both bipropellant apogee engines and monopropellant Reaction Control System (RCS) thrusters. This type of propulsion system has several significant advantages compared with popular nitrogen tetroxide/monomethyl hydrazine (NTO/MMH) bipropellant satellite propulsion systems: The NTO/N2H4 apogee engine has a high specific impulse, and N2H4 thrusters have high reliability. Residual of N2H4 caused by propellant utilization of apogee engine firing (AEF) can be consumed by N2H4 monopropellant thrusters; that means a considerably prolonged satellite life.

  18. 16 CFR § 1101.32 - Reasonable steps to assure information is accurate.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ..., an electrical engineer, or an attending physician) conducts an investigation or an inspection which... fire marshal, a fire investigator, an electrical engineer, an ambulance attendant, or an attending...

  19. 46 CFR 12.602 - Basic training.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...) Swimming while wearing a lifejacket. (v) Keeping afloat without a lifejacket. (2) Fire prevention and... extinguishers. (ii) Extinguishing smaller fires. e.g., electrical fires, oil fires, and propane fires. (iii... firefighting agent in an accommodation room or simulated engine room with fire and heavy smoke. (vii...

  20. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant. Conceptual Design Engineering Report (CDER). Volume 2: Engineering. Volume 3: Costs and schedules

    NASA Astrophysics Data System (ADS)

    1981-09-01

    Engineering design details for the principal systems, system operating modes, site facilities, and structures of an engineering test facility (ETF) of a 200 MWE power plant are presented. The ETF resembles a coal-fired steam power plant in many ways. It is analogous to a conventional plant which has had the coal combustor replaced with the MHD power train. Most of the ETF components are conventional. They can, however, be sized or configured differently or perform additional functions from those in a conventional coal power plant. The boiler not only generates steam, but also performs the functions of heating the MHD oxidant, recovering seed, and controlling emissions.

  1. NASA Tests 2nd RS-25 Flight Engine for Space Launch System

    NASA Image and Video Library

    2018-01-16

    On Jan. 16, 2018, engineers at NASA’s Stennis Space Center in Mississippi conducted a certification test of another RS-25 engine flight controller on the A-1 Test Stand at Stennis Space Center. The 365-second, full-duration test came a month after the space agency capped a year of RS-25 testing with a flight controller test in mid-December. For the “green run” test the flight controller was installed on RS-25 developmental engine E0528 and fired just as during an actual launch. Once certified, the flight controller will be removed and installed on a flight engine for use by NASA’s new deep-space rocket, the Space Launch System (SLS).

  2. Magnetohydrodynamics (MHD) Engineering Test Facility (ETF) 200 MWe power plant. Conceptual Design Engineering Report (CDER). Volume 2: Engineering. Volume 3: Costs and schedules

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Engineering design details for the principal systems, system operating modes, site facilities, and structures of an engineering test facility (ETF) of a 200 MWE power plant are presented. The ETF resembles a coal-fired steam power plant in many ways. It is analogous to a conventional plant which has had the coal combustor replaced with the MHD power train. Most of the ETF components are conventional. They can, however, be sized or configured differently or perform additional functions from those in a conventional coal power plant. The boiler not only generates steam, but also performs the functions of heating the MHD oxidant, recovering seed, and controlling emissions.

  3. System for Anomaly and Failure Detection (SAFD) system development

    NASA Technical Reports Server (NTRS)

    Oreilly, D.

    1992-01-01

    This task specified developing the hardware and software necessary to implement the System for Anomaly and Failure Detection (SAFD) algorithm, developed under Technology Test Bed (TTB) Task 21, on the TTB engine stand. This effort involved building two units; one unit to be installed in the Block II Space Shuttle Main Engine (SSME) Hardware Simulation Lab (HSL) at Marshall Space Flight Center (MSFC), and one unit to be installed at the TTB engine stand. Rocketdyne personnel from the HSL performed the task. The SAFD algorithm was developed as an improvement over the current redline system used in the Space Shuttle Main Engine Controller (SSMEC). Simulation tests and execution against previous hot fire tests demonstrated that the SAFD algorithm can detect engine failure as much as tens of seconds before the redline system recognized the failure. Although the current algorithm only operates during steady state conditions (engine not throttling), work is underway to expand the algorithm to work during transient condition.

  4. Propulsion system tests on a full scale Centaur vehicle to investigate 3-burn mission capability of the D-lT configuration

    NASA Technical Reports Server (NTRS)

    Groesbeck, W. A.; Baud, K. M.; Lacovic, R. F.; Tabata, W. K.; Szabo, S. V., Jr.

    1974-01-01

    Propulsion system tests were conducted on a full scale Centaur vehicle to investigate system capability of the proposed D-lT configuration for a three-burn mission. This particular mission profile requires that the engines be capable of restarting and firing for a final maneuver after a 5-1/2-hour coast to synchronous orbit. The thermal conditioning requirements of the engine and propellant feed system components for engine start under these conditions were investigated. Performance data were also obtained on the D-lT type computer controlled propellant tank pressurization system. The test results demonstrated that the RL-10 engines on the Centaur vehicle could be started and run reliably after being thermally conditioned to predicted engine start conditions for a one, two and three burn mission. Investigation of the thermal margins also indicated that engine starts could be accomplished at the maximum predicted component temperature conditions with prestart durations less than planned for flight.

  5. Saturn Apollo Program

    NASA Image and Video Library

    1967-09-09

    This photograph depicts the F-1 engine firing in the Marshall Space Flight Center’s F-1 Engine Static Test Stand. Construction of the S-IC Static test stand complex began in 1961 in the west test area of MSFC, and was completed in 1964. It is a vertical engine firing test stand, 239 feet in elevation and 4,600 square feet in area at the base, designed to assist in the development of the F-1 Engine. Capability is provided for static firing of 1.5 million pounds of thrust using liquid oxygen and kerosene. The foundation of the stand is keyed into the bedrock approximately 40 feet below grade.

  6. Russian Rocket Engine Test

    NASA Technical Reports Server (NTRS)

    1998-01-01

    NASA engineers successfully tested a Russian-built rocket engine on November 4, 1998 at the Marshall Space Flight Center (MSFC) Advanced Engine Test Facility, which had been used for testing the Saturn V F-1 engines and Space Shuttle Main engines. The MSFC was under a Space Act Agreement with Lockheed Martin Astronautics of Denver to provide a series of test firings of the Atlas III propulsion system configured with the Russian-designed RD-180 engine. The tests were designed to measure the performance of the Atlas III propulsion system, which included avionics and propellant tanks and lines, and how these components interacted with the RD-180 engine. The RD-180 is powered by kerosene and liquid oxygen, the same fuel mix used in Saturn rockets. The RD-180, the most powerful rocket engine tested at the MSFC since Saturn rocket tests in the 1960s, generated 860,000 pounds of thrust.

  7. Electric ants: A cross-disciplinary approach to understanding insect behavior

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

    Slowik, T.J.; Thorvilson, H.G.; Green, B.L.

    1996-12-31

    The response and attraction of the red imported fire ant, Solenopsis invicta, to electrical equipment was examined using an interdisciplinary approach. Entomologists specializing in fire ant behavior combined expertise with electrical engineers to investigate the economically damaging interaction of fire ants with electrical circuitry. Knowledge from the realms of physics, engineering, and biology were integrated in experimentation to test for a fire ant response to electric fields and magnetic fields associated with electrical equipment. It was determined that fire ants react to electrified conductive material and the alternating-current magnetic fields associated with electricity.

  8. Burnout control at the Albright coal-waste-bank fire. Rept. of investigations/1991

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

    Chaiken, R.F.; Bayles, L.G.

    1991-01-01

    Burnout Control is a process developed by the U.S. Bureau of Mines for accelerating the burning of wasted coal fires in situ, while at the same time controlling the heat and fumes produced. The Albright fire project is a first field trial of Burnout Control as applied to a coal waste bank. An exhaust ventilation system was designed and constructed and then operated over a 1-year period at the site of an existing abandoned mine land fire near the town of Albright, W.V. While predicted exhaust gas temperatures of 900 C and thermal power levels of 5 MW were achievedmore » at 20- to 30-in H2O vacuum levels, problems were encountered with engineering designs, equipment breakdown, and fuel-rich combustion that curtailed the time period of satisfactory operation. Effective afterburning of the exhaust gases (as they were drawn from the bank) corrected the problems associated with combustion stoichiometry and led to high thermal outputs. It is believed that with (1) improvements in engineering design and construction, (2) better control of the afterburning process, and (3) the use of conventional stack gas air-pollution controls, Burnout Control can be applied successfully to a coal waste bank fire.« less

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

    Vinnikov, B.; NRC Kurchatov Inst.

    According to Scientific and Technical Cooperation between the USA and Russia in the field of nuclear engineering the Idaho National Laboratory has transferred to the possession of the National Research Center ' Kurchatov Inst. ' the SAPHIRE software without any fee. With the help of the software Kurchatov Inst. developed a Pilot Living PSA- Model of Leningrad NPP Unit 1. Computations of core damage frequencies were carried out for additional Initiating Events. In the submitted paper such additional Initiating Events are fires in various compartments of the NPP. During the computations of each fire, structure of the PSA - Modelmore » was not changed, but Fault Trees for the appropriate systems, which are removed from service during the fire, were changed. It follows from the computations, that for ten fires Core Damaged Frequencies (CDF) are not changed. Other six fires will cause additional core damage. On the basis of the calculated results it is possible to determine a degree of importance of these fires and to establish sequence of performance of fire-prevention measures in various places of the NPP. (authors)« less

  10. Overview of safety research

    NASA Technical Reports Server (NTRS)

    Enders, J. H.

    1978-01-01

    Aircraft safety is reviewed by first establishing a perspective of air transportation accidents as a function of calendar year, geographic area, and phase of flight, and then by describing the threats to safety and NASA research underway in the three representative areas of engine operational problems, meteorological phenomena, and fire. Engine rotor burst protection, aircraft nacelle fire extinguishment, the aircraft-weather interface, severe weather wind shears and turbulence, clear air turbulence, and lightning are among the topics covered. Fire impact management through fire resistant materials technology development is emphasized.

  11. 46 CFR 113.10-5 - Common return.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Common return. 113.10-5 Section 113.10-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-5 Common return. A conductor...

  12. 46 CFR 113.10-5 - Common return.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Common return. 113.10-5 Section 113.10-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-5 Common return. A conductor...

  13. 46 CFR 113.10-7 - Connection boxes.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Connection boxes. 113.10-7 Section 113.10-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-7 Connection boxes. Each...

  14. 46 CFR 113.10-1 - Approved equipment.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Approved equipment. 113.10-1 Section 113.10-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-1 Approved equipment. Each alarm...

  15. 46 CFR 113.10-7 - Connection boxes.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Connection boxes. 113.10-7 Section 113.10-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-7 Connection boxes. Each...

  16. 46 CFR 113.10-5 - Common return.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Common return. 113.10-5 Section 113.10-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-5 Common return. A conductor...

  17. 46 CFR 113.10-1 - Approved equipment.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Approved equipment. 113.10-1 Section 113.10-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-1 Approved equipment. Each alarm...

  18. 46 CFR 113.10-1 - Approved equipment.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Approved equipment. 113.10-1 Section 113.10-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-1 Approved equipment. Each alarm...

  19. 46 CFR 113.10-3 - Cable runs.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Cable runs. 113.10-3 Section 113.10-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-3 Cable runs. Cable runs between...

  20. 46 CFR 113.10-5 - Common return.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Common return. 113.10-5 Section 113.10-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-5 Common return. A conductor...

  1. 46 CFR 113.10-7 - Connection boxes.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Connection boxes. 113.10-7 Section 113.10-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-7 Connection boxes. Each...

  2. 46 CFR 113.10-7 - Connection boxes.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Connection boxes. 113.10-7 Section 113.10-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-7 Connection boxes. Each...

  3. 46 CFR 113.10-3 - Cable runs.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 4 2011-10-01 2011-10-01 false Cable runs. 113.10-3 Section 113.10-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-3 Cable runs. Cable runs between...

  4. 46 CFR 113.10-3 - Cable runs.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Cable runs. 113.10-3 Section 113.10-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-3 Cable runs. Cable runs between...

  5. 46 CFR 113.10-3 - Cable runs.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Cable runs. 113.10-3 Section 113.10-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-3 Cable runs. Cable runs between...

  6. 46 CFR 113.10-5 - Common return.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Common return. 113.10-5 Section 113.10-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-5 Common return. A conductor...

  7. 46 CFR 113.10-1 - Approved equipment.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 4 2014-10-01 2014-10-01 false Approved equipment. 113.10-1 Section 113.10-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-1 Approved equipment. Each alarm...

  8. 46 CFR 113.10-7 - Connection boxes.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 4 2013-10-01 2013-10-01 false Connection boxes. 113.10-7 Section 113.10-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-7 Connection boxes. Each...

  9. 46 CFR 113.10-1 - Approved equipment.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 4 2012-10-01 2012-10-01 false Approved equipment. 113.10-1 Section 113.10-1 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-1 Approved equipment. Each alarm...

  10. 46 CFR 113.10-3 - Cable runs.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Cable runs. 113.10-3 Section 113.10-3 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) ELECTRICAL ENGINEERING COMMUNICATION AND ALARM SYSTEMS AND EQUIPMENT Fire and Smoke Detecting and Alarm Systems § 113.10-3 Cable runs. Cable runs between...

  11. 75 FR 32142 - Combustible Dust

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-07

    .... Contact Mat Chibbaro, P.E., Fire Protection Engineer, Office of Safety Systems, OSHA Directorate of..., and metals (such as aluminum and magnesium). Industries that may have combustible dust hazards include..., chemical manufacturing, textile manufacturing, furniture manufacturing, metal processing, fabricated metal...

  12. 46 CFR 132.120 - Fire pumps.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... with one self-priming power-driven fire pump capable of delivering a single stream of water from the..., the pump required by paragraph (a) of this section may be driven by one of the engines. If only one propulsion engine is installed, the pump must be driven by a source of power independent of the engine. (e...

  13. 46 CFR 132.120 - Fire pumps.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... vessel must be equipped with one self-priming power-driven fire pump capable of delivering a single... propulsion engines are installed, the pump required by paragraph (a) of this section may be driven by one of the engines. If only one propulsion engine is installed, the pump must be driven by a source of power...

  14. 46 CFR 132.120 - Fire pumps.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... vessel must be equipped with one self-priming power-driven fire pump capable of delivering a single... propulsion engines are installed, the pump required by paragraph (a) of this section may be driven by one of the engines. If only one propulsion engine is installed, the pump must be driven by a source of power...

  15. 46 CFR 132.120 - Fire pumps.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... vessel must be equipped with one self-priming power-driven fire pump capable of delivering a single... propulsion engines are installed, the pump required by paragraph (a) of this section may be driven by one of the engines. If only one propulsion engine is installed, the pump must be driven by a source of power...

  16. 40 CFR Table 4 to Subpart IIIi of... - Emission Standards for Stationary Fire Pump Engines

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 40 Protection of Environment 6 2010-07-01 2010-07-01 false Emission Standards for Stationary Fire Pump Engines 4 Table 4 to Subpart IIII of Part 60 Protection of Environment ENVIRONMENTAL PROTECTION... of Performance for Stationary Compression Ignition Internal Combustion Engines Part 60, Subpt. IIII...

  17. 40 CFR Table 3 to Subpart IIIi of... - Certification Requirements for Stationary Fire Pump Engines

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 40 Protection of Environment 6 2010-07-01 2010-07-01 false Certification Requirements for Stationary Fire Pump Engines 3 Table 3 to Subpart IIII of Part 60 Protection of Environment ENVIRONMENTAL... Standards of Performance for Stationary Compression Ignition Internal Combustion Engines Part 60, Subpt...

  18. 78 FR 23698 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-22

    ... fire extinguisher discharge tube (No. 1 engine tube). This proposed AD is prompted by the discovery that the No. 1 engine tube installed on the helicopters is too long to ensure that a fire could be effectively extinguished on a helicopter. The proposed actions are intended to ensure the No. 1 engine tube...

  19. 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.

  20. Gas-Centered Swirl Coaxial Liquid Injector Evaluations

    NASA Technical Reports Server (NTRS)

    Cohn, A. K.; Strakey, P. A.; Talley, D. G.

    2005-01-01

    Development of Liquid Rocket Engines is expensive. Extensive testing at large scales usually required. In order to verify engine lifetime, large number of tests required. Limited Resources available for development. Sub-scale cold-flow and hot-fire testing is extremely cost effective. Could be a necessary (but not sufficient) condition for long engine lifetime. Reduces overall costs and risk of large scale testing. Goal: Determine knowledge that can be gained from sub-scale cold-flow and hot-fire evaluations of LRE injectors. Determine relationships between cold-flow and hot-fire data.

  1. Firing Room Remote Application Software Development

    NASA Technical Reports Server (NTRS)

    Liu, Kan

    2015-01-01

    The Engineering and Technology Directorate (NE) at National Aeronautics and Space Administration (NASA) Kennedy Space Center (KSC) is designing a new command and control system for the checkout and launch of Space Launch System (SLS) and future rockets. The purposes of the semester long internship as a remote application software developer include the design, development, integration, and verification of the software and hardware in the firing rooms, in particular with the Mobile Launcher (ML) Launch Accessories (LACC) subsystem. In addition, a software test verification procedure document was created to verify and checkout LACC software for Launch Equipment Test Facility (LETF) testing.

  2. The NASA/Baltimore Applications Project (BAP). Computer aided dispatch and communications system for the Baltimore Fire Department: A case study of urban technology application

    NASA Technical Reports Server (NTRS)

    Levine, A. L.

    1981-01-01

    An engineer and a computer expert from Goddard Space Flight Center were assigned to provide technical assistance in the design and installation of a computer assisted system for dispatching and communicating with fire department personnel and equipment in Baltimore City. Primary contributions were in decision making and management processes. The project is analyzed from four perspectives: (1) fire service; (2) technology transfer; (3) public administration; and (5) innovation. The city benefitted substantially from the approach and competence of the NASA personnel. Given the proper conditions, there are distinct advantages in having a nearby Federal laboratory provide assistance to a city on a continuing basis, as is done in the Baltimore Applications Project.

  3. Evaluation of NDI compressed air foam system (cafs) applied as a retrofit. Final report

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

    Duncan, S.

    1994-08-01

    Army Engineer Firefighting Detachments require increased firefighting capability to compensate for deficiencies in structural, brush, or wildland and large petroleum storage site fires. Additionally, Army fire departments responsible for protection and prevention on posts, camps and stations have difficulty accessing new or emerging technology do not possess state-of-the-art equipment. The results of this evaluation and subsequent projects, will be reported throughout the Army in an attempt to mitigate operational deficiencies and widen the scope of knowledge in the Army fire service. The evaluation of non-developmental retrofitted compressed air foam systems show an efficiency of suppressive capabilities of water superseded bymore » water alone. Retrofitting the equipment was not easy or inexpensive but it was very successful.« less

  4. A data base and analysis program for shuttle main engine dynamic pressure measurements. Appendix F: Data base plots for SSME tests 750-120 through 750-200

    NASA Technical Reports Server (NTRS)

    Coffin, T.

    1986-01-01

    A dynamic pressure data base and data base management system developed to characterize the Space Shuttle Main Engine (SSME) dynamic pressure environment is presented. The data base represents dynamic pressure measurements obtained during single engine hot firing tests of the SSME. Software is provided to permit statistical evaluation of selected measurements under specified operating conditions. An interpolation scheme is also included to estimate spectral trends with SSME power level.

  5. Development of Life Prediction Capabilities for Liquid Propellant Rocket Engines. Task 4. Post-Fire Diagnostic System for the SSME System Architecture Study.

    DTIC Science & Technology

    1991-07-31

    90 START MCC LN CAV PR 3 UNDERSHOOT ABOVE THRESHOLD YES MI A2-492 2/13/90 MAINSTAGE HPOT DS TMP CHANNEL A/B DIVERGENCE NO MI A2-492 2/13/90 MAINSTAGE ...System for the SSME System Architecture Study Y, , Contract NAS 3 -25883 JUL 31󈧣 CR-187112 Prepared for: National Aeronautics and Space...Liquid Propellant Rocket Engines Contract No. NAS 3 -25883 Eli Ki ,,, July 31, 1991 BY Dist Prepared By.: Mr. Mark Gage Aerojet Propulsion Division Box

  6. Centaur space vehicle pressurized propellant feed system tests

    NASA Technical Reports Server (NTRS)

    1972-01-01

    Engine firing tests, using a full-scale flight-weight vehicle, were performed to evaluate a pressurized propellant feed system for the Centaur. The pressurant gases used were helium and hydrogen. The system was designed to replace the boost pumps currently used on Centaur. Two liquid oxygen tank pressurization modes were studied: (1) directly into the ullage and (2) below the propellant surface. Test results showed the two Centaur RL10 engines could be started and run over the range of expected flight variables. No system instabilities were encountered. Measured pressurization gas quantities agreed well with analytically predicted values.

  7. Around Marshall

    NASA Image and Video Library

    1998-11-04

    NASA engineers successfully tested a Russian-built rocket engine on November 4, 1998 at the Marshall Space Flight Center (MSFC) Advanced Engine Test Facility, which had been used for testing the Saturn V F-1 engines and Space Shuttle Main engines. The MSFC was under a Space Act Agreement with Lockheed Martin Astronautics of Denver to provide a series of test firings of the Atlas III propulsion system configured with the Russian-designed RD-180 engine. The tests were designed to measure the performance of the Atlas III propulsion system, which included avionics and propellant tanks and lines, and how these components interacted with the RD-180 engine. The RD-180 is powered by kerosene and liquid oxygen, the same fuel mix used in Saturn rockets. The RD-180, the most powerful rocket engine tested at the MSFC since Saturn rocket tests in the 1960s, generated 860,000 pounds of thrust.

  8. Vehicle fires and fire safety in tunnels

    DOT National Transportation Integrated Search

    2002-09-20

    Tunnels present what is arguably the most hazardous environment, from the point of view of fire safety, that members of the public ever experience. The fire safety design of tunnels is carried out by tunnel engineers on the basis of a potential fire ...

  9. Enhancing fire safety at Hydro plants with dry transformers

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

    Clemen, D.M.

    Hydroelectric plant owners and engineers can use dry-type transformers to reduce fire hazards in auxiliary power systems. The decision to replace a liquid-immersed transformer with a dry-type product has a price: higher unit cost and a need to be more vigilant in detailing transformer specifications. But, whether the change affects only one failed transformer or is part of a plant rehabilitation project, the benefits in safety can be worth it. Voltages on hydroelectric plant auxiliary power systems can range from a 20 kV medium-voltage system to the normal 480-208/120 V low-voltage system. Dry transformers typically are used in such systemsmore » to reduce the fire hazard present with liquid-filled transformers. For a hydro plant owner or engineer seeking alternatives to liquid-filled transformers, there are two main kinds of dry-type transformers to consider: vacuum pressure impregnated (VPI) and cast coil epoxy resin. VPI transformers normally are manufactured in sizes up to 6,000 kVA with primary voltage ratings up to 20 kV. Cast coil transformers can be made in sizes from 75 to 10,000 kVA, with primary voltage ratings up to 34,500 V. Although the same transformer theory applies to dry transformers as to liquid-filled units, the cooling medium, air, required different temperature rise ratings, dielectric tests, and construction techniques to ensure reliability. Consequently, the factory and field tests for dry units are established by a separate set of American National Standards Institute (ANSI)/Institute of Electrical and Electronics Engineers (IEEE) standards. Cast coil transformers have several important advantages over VPI units.« less

  10. Sample Delivery and Computer Control Systems for Detecting Leaks in the Main Engines of the Space Shuttle

    NASA Technical Reports Server (NTRS)

    Griffin, Timothy P.; Naylor, Guy R.; Hritz, Richard J.; Barrett, Carolyn A.

    1997-01-01

    The main engines of the Space Shuttle use hydrogen and oxygen as the fuel and oxidant. The explosive and fire hazards associated with these two components pose a serious danger to personnel and equipment. Therefore prior to use the main engines undergo extensive leak tests. Instead of using hazardous gases there tests utilize helium as the tracer element. This results in a need to monitor helium in the ppm level continuously for hours. The major challenge in developing such a low level gas monitor is the sample delivery system. This paper discuss a system developed to meet the requirements while also being mobile. Also shown is the calibration technique, stability, and accuracy results for the system.

  11. Developing a byproduct materials information system for the Kentucky Transportation Cabinet.

    DOT National Transportation Integrated Search

    2007-09-01

    Kentucky has numerous coal-fired, electric generating facilities and, as a result, there are abundant byproduct materials being produced from these facilities that have environmental, engineering, and economic potential as materials for use in common...

  12. 49 CFR 176.905 - Motor vehicles or mechanical equipment powered by internal combustion engines.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... of ignition. A motor vehicle or mechanical equipment showing any signs of leakage or electrical fault... smoke or fire detection system capable of alerting personnel on the bridge. (h) All electrical equipment...

  13. Boeing's CST-100 Launch Abort Engine Test

    NASA Image and Video Library

    2016-10-10

    Boeing and Aerojet Rocketdyne have begun a series of developmental hot-fire tests with two launch abort engines similar to the ones that will be part of Boeing’s CST-100 Starliner service module, in the Mojave Desert in California. The engines, designed to maximize thrust build-up, while minimizing overshoot during start up, will be fired between half a second and 3 seconds each during the test campaign. If the Starliner’s four launch abort engines were used during an abort scenario, they would fire between 3 and 5.5. seconds, with enough thrust to get the spacecraft and its crew away from the rocket, before splashing down in the ocean under parachutes.

  14. Ballistic impact velocity response of carbon fibre reinforced aluminium alloy laminates for aero-engine

    NASA Astrophysics Data System (ADS)

    Mohammed, I.; Abu Talib, A. R.; Sultan, M. T. H.; Saadon, S.

    2017-12-01

    Aerospace and other industries use fibre metal laminate composites extensively due to their high specific strength, stiffness and fire resistance, in addition to their capability to be tailored into different forms for specific purposes. The behaviours of such composites under impact loading is another factor to be considered due to the impacts that occur in take-off, landing, during maintenance and operations. The aim of the study is to determine the specific perforation energy and impact strength of the fibre metal laminates of different layering pattern of carbon fibre reinforced aluminium alloy and hybrid laminate composites of carbon fibre and natural fibres (kenaf and flax). The composites are fabricated using the hand lay-up method in a mould with high bonding polymer matrix and compressed by a compression machine, cured at room temperature for one day and post cure in an oven for three hours. The impact tests are conducted using a gun tunnel system with a flat cylindrical bullet fired using a helium gas at a distance of 14 inches to the target. Impact and residual velocity of the projectile are recorded by high speed video camera. Specific perforation energy of carbon fibre reinforced aluminium alloy (CF+AA) for both before and after fire test are higher than the specific perforation energy of the other composites considered before and after fire test respectively. CF +AA before fire test is 55.18% greater than after. The same thing applies to impact strength of the composites where CF +AA before the fire test has the highest percentage of 11.7%, 50.0% and 32.98% as respectively compared to carbon fibre reinforced aluminium alloy (CARALL), carbon fibre reinforced flax aluminium alloy (CAFRALL) and carbon fibre reinforced kenaf aluminium alloy (CAKRALL), and likewise for the composites after fire test. The considered composites in this test can be used in the designated fire zone of an aircraft engine to protect external debris from penetrating the engine shield due to higher values of impact strength and specific perforation energy as highlighted by the test results.

  15. CECE: Expanding the Envelope of Deep Throttling Technology in Liquid Oxygen/Liquid Hydrogen Rocket Engines for NASA Exploration Missions

    NASA Technical Reports Server (NTRS)

    Giuliano, Victor J.; Leonard, Timothy G.; Lyda, Randy T.; Kim, Tony S.

    2010-01-01

    As one of the first technology development programs awarded by NASA under the Vision for Space Exploration, the Pratt & Whitney Rocketdyne (PWR) Deep Throttling, Common Extensible Cryogenic Engine (CECE) program was selected by NASA in November 2004 to begin technology development and demonstration toward a deep throttling, cryogenic engine supporting ongoing trade studies for NASA s Lunar Lander descent stage. The CECE program leverages the maturity and previous investment of a flight-proven hydrogen/oxygen expander cycle engine, the PWR RL10, to develop and demonstrate an unprecedented combination of reliability, safety, durability, throttlability, and restart capabilities in high-energy, cryogenic, in-space propulsion. The testbed selected for the deep throttling demonstration phases of this program was a minimally modified RL10 engine, allowing for maximum current production engine commonality and extensibility with minimum program cost. Four series of demonstrator engine tests have been successfully completed between April 2006 and April 2010, accumulating 7,436 seconds of hot fire time over 47 separate tests. While the first two test series explored low power combustion (chug) and system instabilities, the third test series investigated and was ultimately successful in demonstrating several mitigating technologies for these instabilities and achieved a stable throttling ratio of 13:1. The fourth test series significantly expanded the engine s operability envelope by successfully demonstrating a closed-loop control system and extensive transient modeling to enable lower power engine starting, faster throttle ramp rates, and mission-specific ignition testing. The final hot fire test demonstrated a chug-free, minimum power level of 5.9%, corresponding to an overall 17.6:1 throttling ratio achieved. In total, these tests have provided an early technology demonstration of an enabling cryogenic propulsion concept with invaluable system-level technology data acquisition toward design and development risk mitigation for future lander descent main engines.

  16. Next-Generation RS-25 Engines for the NASA Space Launch System

    NASA Technical Reports Server (NTRS)

    Ballard, Richard O.

    2017-01-01

    The utilization of heritage RS-25 engines, also known as the Space Shuttle Main Engine (SSME), has enabled rapid progress in the development and certification of the NASA Space Launch System (SLS) toward operational flight status. The RS-25 brings design maturity and extensive experience gained through 135 missions, 3000+ ground tests, and over 1 million seconds total accumulated hot-fire time. In addition, there were also 16 flight engines and 2 development engines remaining from the Space Shuttle program that could be leveraged to support the first four flights. Beyond these initial SLS flights, NASA must have a renewed supply of RS-25 engines that must reflect program affordability imperatives as well as technical requirements imposed by the SLS Block-1B vehicle (i.e., 111% RPL power level, reduced service life). Recognizing the long lead times needed for the fabrication, assembly and acceptance testing of flight engines, design activities are underway to improve system affordability and eliminate obsolescence concerns. These key objectives are enabled largely by utilizing modern materials and fabrication technologies, but also by innovations in systems engineering and integration (SE&I) practices.

  17. 11. PHOTOCOPY OF DRAWING 99S1, FIRE ENGINE HOUSE, FOUNDATION PLAN, ...

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

    11. PHOTOCOPY OF DRAWING 99-S-1, FIRE ENGINE HOUSE, FOUNDATION PLAN, MARCH 1900. NOTE THAT THIS PHOTOCOPY IS OF A MICROFILM ENLARGEMENT, ORIGINAL DRAWING LOST. - Mare Island Naval Shipyard, Firehouse, Vallejo, Solano County, CA

  18. Fire, Fuel, and Smoke Science Program 2015 Research Accomplishments

    Treesearch

    Faith Ann Heinsch; Charles W. McHugh; Colin C. Hardy

    2016-01-01

    The Fire, Fuel, and Smoke Science Program (FFS) of the U.S. Forest Service, Rocky Mountain Research Station focuses on fundamental and applied research in wildland fire, from fire physics and fire ecology to fuels management and smoke emissions. Located at the Missoula Fire Sciences Laboratory in Montana, the scientists, engineers, technicians, and support...

  19. KSC-2011-7004

    NASA Image and Video Library

    2011-09-16

    CAPE CANAVERAL, Fla. – At the newly remodeled Launch Control Center's Young-Crippen Firing Room at NASA's Kennedy Space Center in Florida, engineering directorate personnel demonstrate the recently added Space Command & Control System which will be used for launches of future human spaceflight vehicles. Known as Firing Room 1 in the Apollo era, it was re-named as a tribute to the Space Shuttle Program's first crewed mission, STS-1, which was flown by Commander John W. Young and Pilot Robert L. Crippen in April 1981. Photo credit: NASA/Jim Grossmann

  20. KSC-2011-7001

    NASA Image and Video Library

    2011-09-16

    CAPE CANAVERAL, Fla. – At the newly remodeled Launch Control Center's Young-Crippen Firing Room at NASA's Kennedy Space Center in Florida, engineering directorate personnel demonstrate the recently added Space Command & Control System which will be used for launches of future human spaceflight vehicles. Known as Firing Room 1 in the Apollo era, it was re-named as a tribute to the Space Shuttle Program's first crewed mission, STS-1, which was flown by Commander John W. Young and Pilot Robert L. Crippen in April 1981. Photo credit: NASA/Jim Grossmann

  1. KSC-2011-7003

    NASA Image and Video Library

    2011-09-16

    CAPE CANAVERAL, Fla. – At the newly remodeled Launch Control Center's Young-Crippen Firing Room at NASA's Kennedy Space Center in Florida, engineering directorate personnel demonstrate the recently added Space Command & Control System which will be used for launches of future human spaceflight vehicles. Known as Firing Room 1 in the Apollo era, it was re-named as a tribute to the Space Shuttle Program's first crewed mission, STS-1, which was flown by Commander John W. Young and Pilot Robert L. Crippen in April 1981. Photo credit: NASA/Jim Grossmann

  2. KSC-2011-7002

    NASA Image and Video Library

    2011-09-16

    CAPE CANAVERAL, Fla. – At the newly remodeled Launch Control Center's Young-Crippen Firing Room at NASA's Kennedy Space Center in Florida, engineering directorate personnel demonstrate the recently added Space Command & Control System which will be used for launches of future human spaceflight vehicles. Known as Firing Room 1 in the Apollo era, it was re-named as a tribute to the Space Shuttle Program's first crewed mission, STS-1, which was flown by Commander John W. Young and Pilot Robert L. Crippen in April 1981. Photo credit: NASA/Jim Grossmann

  3. Engineering and Design: Fire Protection for Helicopter Hangars

    DTIC Science & Technology

    1997-10-15

    B-5 4.5 ESFR Sprinkler Systems Design Requirements...Early Suppression Fast Response ( ESFR ) sprinklers operating at a minimum discharge pressure of 345 kPa (50 psi). 3.13.2 Conventional automatic sprinkler...using ESFR sprinklers. 4.1.3 Although foam-water sprinkler systems using AFFF generally provide optimum effectiveness in combating a combustible or

  4. 24. SATURN V Fl ENGINE TEST FIRING ON TEST STAND ...

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

    24. SATURN V F-l ENGINE TEST FIRING ON TEST STAND 1A. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Test Stand 1-A, Test Area 1-120, north end of Jupiter Boulevard, Boron, Kern County, CA

  5. Fire prevention on aircraft

    NASA Technical Reports Server (NTRS)

    Kuhn, Fritz

    1931-01-01

    The following discussion is at first restricted to the light-oil engines now in use. We shall consider how far it is possible to reduce fire hazards by changes in the design of the engines and carburetors and in the arrangement of the fuel pipes.

  6. Subscale Carbon-Carbon Nozzle Extension Development and Hot Fire Testing in Support of Upper Stage Liquid Rocket Engines

    NASA Technical Reports Server (NTRS)

    Gradl, Paul; Valentine, Peter; Crisanti, Matthew; Greene, Sandy Elam

    2016-01-01

    Upper stage and in-space liquid rocket engines are optimized for performance through the use of high area ratio nozzles to fully expand combustion gases to low exit pressures increasing exhaust velocities. Due to the large size of such nozzles and the related engine performance requirements, carbon-carbon (C/C) composite nozzle extensions are being considered for use in order to reduce weight impacts. NASA and industry partner Carbon-Carbon Advanced Technologies (C-CAT) are working towards advancing the technology readiness level of large-scale, domestically-fabricated, C/C nozzle extensions. These C/C extensions have the ability to reduce the overall costs of extensions relative to heritage metallic and composite extensions and to decrease weight by 50%. Material process and coating developments have advanced over the last several years, but hot fire testing to fully evaluate C/C nozzle extensions in relevant environments has been very limited. NASA and C-CAT have designed, fabricated and hot fire tested multiple subscale nozzle extension test articles of various C/C material systems, with the goal of assessing and advancing the manufacturability of these domestically producible materials as well as characterizing their performance when subjected to the typical environments found in a variety of liquid rocket and scramjet engines. Testing at the MSFC Test Stand 115 evaluated heritage and state-of-the-art C/C materials and coatings, demonstrating the capabilities of the high temperature materials and their fabrication methods. This paper discusses the design and fabrication of the 1.2k-lbf sized carbon-carbon nozzle extensions, provides an overview of the test campaign, presents results of the hot fire testing, and discusses potential follow-on development work.

  7. Occupational burns from oxygen resuscitator fires: the hazard of aluminum regulators.

    PubMed

    Hodous, Thomas K; Washenitz, Frank; Newton, Barry

    2002-07-01

    There have been over 30 incidents of oxygen resuscitator fires over the last 6 years, causing severe burns to a number of fire fighters, emergency medical service personnel, health care workers, and patients. The National Institute for Occupational Safety and Health (NIOSH) was requested to investigate three such incidents. NIOSH conducted site investigations of the incidents, and the requesters also sent the involved oxygen resuscitators to a forensic engineering company for a causal analysis. The investigated fires were associated with aluminum regulators, all from one manufacturer, on compressed pure oxygen cylinders. The investigations indicated that the cause of the fires was an initial small ignition in the high-pressure area of the aluminum regulator, which then consumed itself in a massive burnout. Aluminum regulators used with high-pressure oxygen systems are subject to rare, but potentially catastrophic combustion in normal use. Replacement of such regulators with those made of more fire-resistant materials or designs, as well as education and improved safety practices are needed to reduce this hazard.

  8. Component qualification and initial build of the AGT 100 advanced automotive gas turbine

    NASA Technical Reports Server (NTRS)

    Johnson, R. A.

    1983-01-01

    In advance of initial dynamometer testing of the AGT 100 engine, all prime components and subsystems were bench/rig tested. Included were compressor, combustor, turbines, regenerator, ceramic components, and electronic control system. Results are briefly reviewed. Initial engine buildup was completed and rolled-out for test cell installation in July 1982. Shakedown testing included motoring and sequential firing of the combustor's three fuel nozzles.

  9. The Development of a Thermally Enhanced Emergency Fire Shelter

    NASA Technical Reports Server (NTRS)

    Fody, Joshua M.; Calomino, Anthony M.; Daryabeigi, Kamran; Bruce III, Walter E.; Wells, John M.; Wusk, Mary E.; Miller, Stephen D.

    2017-01-01

    Since its founding in 1905, the U.S. Forest Service has been responsible for maintaining public lands. The Forest Service and other public lands agencies respond to an average of 73,000 wildfires per year, and responding firefighters are required to carry a number of safety gear items, including the M2002 emergency fire shelter. The emergency fire shelter is intended to serve as a last resort means of protection in case a firefighter's escape route has been compromised in the face of an approaching flame front. No fire shelter deployment tragedy has been more costly than the 2013 Yarnell Hill fire in Arizona, where 19 members of the Granite Mountain Hotshots perished. After the tragedy at Yarnell Hill, the Forest Service decided to expedite the next redesign cycle of the fire shelter in order to improve its ability to withstand direct contact with flames. Engineers at NASA Langley Research Center have spent the better part of a decade developing flexible thermal materials for use in inflatable aerodynamic decelerators and have demonstrated their performance in the IRVE-2 and IRVE-3 flight programs (Inflatable Reentry Vehicle Experiment). NASA engineers recognized an opportunity to leverage their experience and knowledge with flexible thermal protection systems to potentially improve the fire shelter's resistance to direct flame contact, and have been working directly with the U.S. Forest Service to achieve this goal. They launched the CHIEFS project (Convective Heating Improvement for Emergency Fire Shelters) in 2014. Over the past three years, CHIEFS has screened over 270 unique material layups, and tested over 30 unique full scale shelter concepts in an effort to achieve a game changing improvement to the thermal protection of the fire shelter, while maintaining minimal mass and volume. This paper will discuss CHIEFS' 1st and 2nd generation fire shelter development efforts and test results.

  10. The selection of flying roller as an effort to increase the power of scooter-matic as the main power of centrifugal pump for fire fighter motor cycle

    NASA Astrophysics Data System (ADS)

    Hadi Sutrisno, Himawan

    2018-03-01

    In densely populated settlements, fires often occur and cause losses. In some instances, the process of the occurrence of fires takes place so quickly that to reduce and avoid the occurrence of a fire disaster effort is required in accordance with the existing environmental condition. Fire fighter motorcycle by using motorcycle scooter-matic is considered suitable as one alternative to combating fire hazard in densely populated residential settlements. The use of motorcycle engines as the driving force of the pump often leads to unstable and not optimum power. Thus, the water spray on the centrifugal pump also becomes not maximum. To increase the engine power at scooter-matic engine idle rotation (700-2000 rpm), then the flying roller replacement with certain mass weight becomes an option. By selecting a 10 to 14 gram flying roller mass, the power analysis using a dynotest engine produces several variations. Of the calculation, the mass of a 14 gram flying roller provides a significant increase in motor power on the upper rotation. Meanwhile, on the lower power rotation using a flying roller with a mass of 10 grams provides an increase in power compared to a standard flying roller on a scooter matic motor engine. As a reference to the use of scooter-matic motor power as the pump power, the result of use of the flying roller with a mass of 10 grams becomes the best option.

  11. 40 CFR 60.4235 - What fuel requirements must I meet if I am an owner or operator of a stationary SI gasoline fired...

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... am an owner or operator of a stationary SI gasoline fired internal combustion engine subject to this... Stationary Spark Ignition Internal Combustion Engines Other Requirements for Owners and Operators § 60.4235... internal combustion engine subject to this subpart? Owners and operators of stationary SI ICE subject to...

  12. 40 CFR 60.4235 - What fuel requirements must I meet if I am an owner or operator of a stationary SI gasoline fired...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... am an owner or operator of a stationary SI gasoline fired internal combustion engine subject to this... Stationary Spark Ignition Internal Combustion Engines Other Requirements for Owners and Operators § 60.4235... internal combustion engine subject to this subpart? Owners and operators of stationary SI ICE subject to...

  13. 40 CFR 60.4235 - What fuel requirements must I meet if I am an owner or operator of a stationary SI gasoline fired...

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... am an owner or operator of a stationary SI gasoline fired internal combustion engine subject to this... Stationary Spark Ignition Internal Combustion Engines Other Requirements for Owners and Operators § 60.4235... internal combustion engine subject to this subpart? Owners and operators of stationary SI ICE subject to...

  14. 40 CFR 60.4235 - What fuel requirements must I meet if I am an owner or operator of a stationary SI gasoline fired...

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... am an owner or operator of a stationary SI gasoline fired internal combustion engine subject to this... Stationary Spark Ignition Internal Combustion Engines Other Requirements for Owners and Operators § 60.4235... internal combustion engine subject to this subpart? Owners and operators of stationary SI ICE subject to...

  15. 40 CFR 60.4235 - What fuel requirements must I meet if I am an owner or operator of a stationary SI gasoline fired...

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... am an owner or operator of a stationary SI gasoline fired internal combustion engine subject to this... Stationary Spark Ignition Internal Combustion Engines Other Requirements for Owners and Operators § 60.4235... internal combustion engine subject to this subpart? Owners and operators of stationary SI ICE subject to...

  16. A data base and analysis program for shuttle main engine dynamic pressure measurements. Appendix B: Data base plots for SSME tests 901-290 through 901-414

    NASA Technical Reports Server (NTRS)

    Coffin, T.

    1986-01-01

    A dynamic pressure data base and data base management system developed to characterize the Space Shuttle Main Engine (SSME) dynamic pressure environment is described. The data base represents dynamic pressure measurements obtained during single engine hot firing tesets of the SSME. Software is provided to permit statistical evaluation of selected measurements under specified operating conditions. An interpolation scheme is also included to estimate spectral trends with SSME power level. Flow dynamic environments in high performance rocket engines are discussed.

  17. A data base and analysis program for shuttle main engine dynamic pressure measurements. Appendix C: Data base plots for SSME tests 902-214 through 902-314

    NASA Technical Reports Server (NTRS)

    Coffin, T.

    1986-01-01

    A dynamic pressure data base and data base management system developed to characterize the Space Shuttle Main Engine (SSME) dynamic pressure environment is reported. The data base represents dynamic pressure measurements obtained during single engine hot firing tests of the SSME. Software is provided to permit statistical evaluation of selected measurements under specified operating conditions. An interpolation scheme is included to estimate spectral trends with SSME power level. Flow Dynamic Environments in High Performance Rocket Engines are described.

  18. Russian Rocket Engine Test

    NASA Technical Reports Server (NTRS)

    1998-01-01

    NASA engineers successfully tested a Russian-built rocket engine on November 4, 1998 at the Marshall Space Flight Center (MSFC) Advanced Engine Test Facility, which had been used for testing the Saturn V F-1 engines and Space Shuttle Main engines. The MSFC was under a Space Act Agreement with Lockheed Martin Astronautics of Denver to provide a series of test firings of the Atlas III propulsion system configured with the Russian-designed RD-180 engine. The tests were designed to measure the performance of the Atlas III propulsion system, which included avionics and propellant tanks and lines, and how these components interacted with the RD-180 engine. The RD-180 is powered by kerosene and liquid oxygen, the same fuel mix used in Saturn rockets. The RD-180, the most powerful rocket engine tested at the MSFC since Saturn rocket tests in the 1960s, generated 860,000 pounds of thrust. The test was the first test ever anywhere outside Russia of a Russian designed and built engine.

  19. 36 CFR 331.15 - Fires.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 36 Parks, Forests, and Public Property 3 2010-07-01 2010-07-01 false Fires. 331.15 Section 331.15... INDIANA § 331.15 Fires. Open fires are prohibited unless confined to fireplaces, grills, or other facilities designed for this purpose as designated by the District Engineer. Fires shall not be left...

  20. 14 CFR 33.17 - Fire protection.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Fire protection. 33.17 Section 33.17... STANDARDS: AIRCRAFT ENGINES Design and Construction; General § 33.17 Fire protection. (a) The design and... fire during normal operation and failure conditions, and must minimize the effect of such a fire. In...

  1. Fire, Fuel, and Smoke Program: 2014 Research Accomplishments

    Treesearch

    Faith Ann Heinsch; Robin J. Innes; Colin C. Hardy; Kristine M. Lee

    2015-01-01

    The Fire, Fuel, and Smoke Science Program (FFS) of the U.S. Forest Service, Rocky Mountain Research Station focuses on fundamental and applied research in wildland fire, from fire physics and fire ecology to fuels management and smoke emissions. Located at the Missoula Fire Sciences Laboratory in Montana, the scientists, engineers, technicians, and support staff in FFS...

  2. Fire, Fuel, and Smoke Science Program: 2013 Research accomplishments

    Treesearch

    Faith Ann Heinsch; Robin J. Innes; Colin C. Hardy; Kristine M. Lee

    2014-01-01

    The Fire, Fuel, and Smoke Science Program (FFS) of the U.S. Forest Service, Rocky Mountain Research Station, focuses on fundamental and applied research in wildland fire, from fire physics and fire ecology to fuels management and smoke emissions. Located at the Missoula Fire Sciences Laboratory in Montana, the scientists, engineers, technicians, and support staff in...

  3. Shift in fire-ecosystems and weather changes

    Treesearch

    Bongani Finiza

    2013-01-01

    During recent decades too much focus fell on fire suppression and fire engineering methods. Little attention has been given to understanding the shift in the changing fire weather resulting from the global change in weather patterns. Weather change have gradually changed the way vegetation cover respond to fire occurrence and brought about changes in fire behavior and...

  4. CECE: Expanding the Envelope of Deep Throttling in Liquid Oxygen/Liquid Hydrogen Rocket Engines For NASA Exploration Missions

    NASA Technical Reports Server (NTRS)

    Giuliano, Victor J.; Leonard, Timothy G.; Lyda, Randy T.; Kim, Tony S.

    2010-01-01

    As one of the first technology development programs awarded by NASA under the Vision for Space Exploration, the Pratt & Whitney Rocketdyne (PWR) Deep Throttling, Common Extensible Cryogenic Engine (CECE) program was selected by NASA in November 2004 to begin technology development and demonstration toward a deep throttling, cryogenic engine supporting ongoing trade studies for NASA s Lunar Lander descent stage. The CECE program leverages the maturity and previous investment of a flight-proven hydrogen/oxygen expander cycle engine, the PWR RL10, to develop technology and demonstrate an unprecedented combination of reliability, safety, durability, throttlability, and restart capabilities in a high-energy cryogenic engine. The testbed selected for the deep throttling demonstration phases of this program was a minimally modified RL10 engine, allowing for maximum current production engine commonality and extensibility with minimum program cost. Three series of demonstrator engine tests, the first in April-May 2006, the second in March-April 2007 and the third in November-December 2008, have demonstrated up to 13:1 throttling (104% to 8% thrust range) of the hydrogen/oxygen expander cycle engine. The first two test series explored a propellant feed system instability ("chug") environment at low throttled power levels. Lessons learned from these two tests were successfully applied to the third test series, resulting in stable operation throughout the 13:1 throttling range. The first three tests have provided an early demonstration of an enabling cryogenic propulsion concept, accumulating over 5,000 seconds of hot fire time over 27 hot fire tests, and have provided invaluable system-level technology data toward design and development risk mitigation for the NASA Altair and future lander propulsion system applications. This paper describes the results obtained from the highly successful third test series as well as the test objectives and early results obtained from a fourth test series conducted over March-May 2010

  5. Elastic resistance change and action potential generation of non-faradaic Pt/TiO2/Pt capacitors.

    PubMed

    Lim, Hyungkwang; Jang, Ho Won; Lee, Doh-Kwon; Kim, Inho; Hwang, Cheol Seong; Jeong, Doo Seok

    2013-07-21

    Electric current in the mixed ionic-electronic conductor TiO2 is hysteretic, i.e. history-dependent, and its use is versatile in electronic devices. Nowadays, biologically inspired, analogue-type computing systems, known as neuromorphic systems, are being actively investigated owing to their new and intriguing physical concepts. The realization of artificial synapses is important for constructing neuromorphic systems. In mammalians' brains, the plasticity of synapses between neighbouring nerve cells arises from action potential firing. Emulating action potential firing via inorganic systems has therefore become important in neuromorphic engineering. In this work, the current-voltage hysteresis of TiO2-based non-faradaic capacitors is investigated to primarily focus on the correlation between the blocking contact and the elasticity, i.e. non-plasticity, of the capacitors' resistance change, in experimental and theoretical methods. The similarity between the action potential firing behaviour in nerve cells and the elasticity of the non-faradaic capacitors is addressed.

  6. Dilution-based emissions sampling from stationary sources: Part 2--Gas-fired combustors compared with other fuel-fired systems.

    PubMed

    England, Glenn C; Watson, John G; Chow, Judith C; Zielinska, Barbara; Chang, M C Oliver; Loos, Karl R; Hidy, George M

    2007-01-01

    With the recent focus on fine particle matter (PM2.5), new, self-consistent data are needed to characterize emissions from combustion sources. Such data are necessary for health assessment and air quality modeling. To address this need, emissions data for gas-fired combustors are presented here, using dilution sampling as the reference. The dilution method allows for collection of emitted particles under conditions simulating cooling and dilution during entry from the stack into the air. The sampling and analysis of the collected particles in the presence of precursor gases, SO2 nitrogen oxide, volatile organic compound, and NH3 is discussed; the results include data from eight gas fired units, including a dual-fuel institutional boiler and a diesel engine powered electricity generator. These data are compared with results in the literature for heavy-duty diesel vehicles and stationary sources using coal or wood as fuels. The results show that the gas-fired combustors have very low PM2.5 mass emission rates in the range of approximately 10(-4) lb/million Btu (MMBTU) compared with the diesel backup generator with particle filter, with approximately 5 x 10(-3) lb/MMBTU. Even higher mass emission rates are found in coal-fired systems, with rates of approximately 0.07 lb/MMBTU for a bag-filter-controlled pilot unit burning eastern bituminous coal. The characterization of PM2.5 chemical composition from the gas-fired units indicates that much of the measured primary particle mass in PM2.5 samples is organic or elemental carbon and, to a much less extent, sulfate. Metal emissions are quite low compared with the diesel engines and the coal- or wood-fueled combustors. The metals found in the gas-fired combustor particles are low in concentration, similar in concentration to ambient particles. The interpretation of the particulate carbon emissions is complicated by the fact that an approximately equal amount of particulate carbon (mainly organic carbon) is found on the particle collector and a backup filter. It is likely that measurement artifacts, mostly adsorption of volatile organic compounds on quartz filters, are positively biasing "true" particulate carbon emission results.

  7. Aircraft engine sump-fire studies

    NASA Technical Reports Server (NTRS)

    Loomis, W. R.

    1976-01-01

    Results of ongoing experimental studies are reported in which a 125-millimeter-diameter-advanced-bearing test rig simulating an engine sump is being used to find the critical range of conditions for fires to occur. Design, material, and operating concepts and techniques are being studied with the objective of minimizing the problem. It has been found that the vapor temperature near a spark ignitor is most important in determining ignition potential. At temperatures producing oil vapor pressures below or much above the calculated flammability limits, fires have not been ignited. But fires have been routinely started within the theoretical flammability range. This indicates that generalizing the sump-fire problem may make it amenable to analysis, with the potential for realistic solutions.

  8. Explosion and/or fire risk assessment methodology: a common approach, structured for underground coalmine environments / Metoda szacowania ryzyka wybuchu i pożarów: podejście ogólne, dostosowane do środowiska kopalni podziemnej

    NASA Astrophysics Data System (ADS)

    Cioca, Ionel-Lucian; Moraru, Roland Iosif

    2012-10-01

    In order to meet statutory requirements concerning the workers health and safety, it is necessary for mine managers within Valea Jiului coal basin in Romania to address the potential for underground fires and explosions and their impact on the workforce and the mine ventilation systems. Highlighting the need for a unified and systematic approach of the specific risks, the authors are developing a general framework for fire/explosion risk assessment in gassy mines, based on the quantification of the likelihood of occurrence and gravity of the consequences of such undesired events and employing Root-Cause analysis method. It is emphasized that even a small fire should be regarded as being a major hazard from the point of view of explosion initiation, should a combustible atmosphere arise. The developed methodology, for the assessment of underground fire and explosion risks, is based on the known underground explosion hazards, fire engineering principles and fire test criteria for potentially combustible materials employed in mines.

  9. Development of a Maintenance Advisor Expert System for the MK 92 MOD 2 Fire Control System: FC-1 Designation - Time, Range, Bearing FC-1 Acquisition, FC-1 Track - Range, Bearing, and FC-2 Designation - Time, Range, Bearing, FC-2 Acquisition, FC-2 Track - Range, Bearing, and FC-4 and FC-5

    DTIC Science & Technology

    1993-09-01

    is not present at output of the power amplifier- THEN replace train drive motor ELSE continue troubleshooting procedures. 30 Rules offer several...Type Body Type Tires Tires Engine Type Engine Type Battery Type Battery Type Figure 5-2 KOWLEDGE ACCESS BY FRAME AND SLOT 33 B. SEMANTIC NETWORKS A

  10. Pressure-Fed LOX/LCH4 Reaction Control System for Spacecraft: Transient Modeling and Thermal Vacuum Hotfire Test Results

    NASA Technical Reports Server (NTRS)

    Atwell, Matthew J.; Hurlbert, Eric A.; Melcher, J. C.; Morehead, Robert L.

    2017-01-01

    An integrated cryogenic liquid oxygen, liquid methane (LOX/LCH4) reaction control system (RCS) was tested at NASA Glenn Research Center's Plum Brook Station in the Spacecraft Propulsion Research Facility (B-2) under vacuum and thermal vacuum conditions. The RCS is a subsystem of the Integrated Cryogenic Propulsion Test Article (ICPTA), a pressure-fed LOX/LCH4 propulsion system composed of a single 2,800 lbf main engine, two 28 lbf RCS engines, and two 7 lbf RCS engines. Propellants are stored in four 48 inch diameter 5083 aluminum tanks that feed both the main engine and RCS engines in parallel. Helium stored cryogenically in a composite overwrapped pressure vessel (COPV) flows through a heat exchanger on the main engine before being used to pressurize the propellant tanks to a design operating pressure of 325 psi. The ICPTA is capable of simultaneous main engine and RCS operation. The RCS engines utilize a coil-on-plug (COP) ignition system designed for operation in a vacuum environment, eliminating corona discharge issues associated with a high voltage lead. There are two RCS pods on the ICPTA, with two engines on each pod. One of these two engines is a heritage flight engine from Project Morpheus. Its sea level nozzle was removed and replaced by an 85:1 nozzle machined using Inconel 718, resulting in a maximum thrust of 28 lbf under altitude conditions. The other engine is a scaled down version of the 28 lbf engine, designed to match the core and overall mixture ratios as well as other injector characteristics. This engine can produce a maximum thrust of 7 lbf with an 85:1 nozzle that was additively manufactured using Inconel 718. Both engines are film-cooled and capable of limited duration gas-gas and gas-liquid operation, as well as steady-state liquid-liquid operation. Each pod contains one of each version, such that two engines of the same thrust level can be fired as a couple on opposite pods. The RCS feed system is composed of symmetrical 3/8 inch lines that tap off of the main propellant manifold to send LOX and LCH4 outboard to the RCS pods. A Thermodynamic Vent System (TVS) is used to condition propellants at each pod by venting through an orifice and then routing the cold expansion products back through tubing that is welded along a large portion of the main RCS feed lines. Prior to final installation on the ICPTA, the RCS engines were tested in a small vacuum chamber at the Johnson Space Center (JSC) Energy Systems Test Area (ESTA) to verify functionality of the new COP ignition system and check out operation of the vacuum nozzles. After engine-level testing, the RCS engines were installed on the vehicle and a series of integrated hot-fire tests were performed at JSC consisting of various pulsing and steady-state firings as well as integrated main engine/RCS operation. The ICPTA was then integrated into the Plum Brook B-2 facility for vacuum and thermal/vacuum testing. Testing in the B-2 facility was composed of multiple thermal and pressure environments. The first set of tests were performed under ambient temperature and altitude pressure conditions. These tests consisted of a range of minimum impulse bit (MIB) pulsing sequences with low duty cycle, analogous to a coast phase in which the RCS is primarily used for station keeping. The primary goal of this sequence is to understand how propellant conditions were effected without an active TVS. In this scenario, consistent gas-gas operation is desirable since it results in a smaller MIB and more efficient propellant consumption. Multiple skin thermocouples are mounted on the feedlines, in addition to a submerged thermocouple on each commodity, in order to gather thermal data on the system. Higher duty cycle pulsing tests were then performed, analogous to an ascent or landing mission phase. The primary goal of this sequence was to examine how well the engines self-conditioned without active TVS when starting from a quiescent state. The TVS was then activated during some tests to demonstrate the capability to quickly condition the engines for higher pulsing demand scenarios. A thermocouple at the TVS outlet allows for the calculation of energy absorbed by the vented propellant. Lastly, tests with longer pulses and multiple engines firing either in sequence or simultaneously were run in order to gather transient system response data on waterhammer. Six total high-speed pressure transducers are installed on the RCS system, one sensor at the end of each propellant manifold line on the pods, and one at the tap-off location for each commodity. This will allow for the accurate characterization of waterhammer in the system under various propellant conditions and firing sequences. Other instrumentation for this test series includes nozzle throat thermocouples, chamber pressure measurement, heat soakback measurement, and tank wall plume impingement temperature measurement. The next set of tests were performed to demonstrate simultaneous main engine and RCS operation. Data from this test will be used to examine if there is any change to nominal operation of the RCS as a result of feed system interaction or other phenomenon. Some of these tests began under high vacuum conditions (target ambient pressure less than 1x10(exp -3) torr) and others began at altitude conditions. The last set of tests were performed with the B-2 cold wall active. Under these tests, many of the same low duty cycle MIB tests were repeated in order to characterize how propellant conditions changed with the lower heat leak. In this scenario the RCS manifold experiences much less heat leak, resulting in a change to how well the engines self-condition. As a result, an increase in maximum waterhammer pressures and a change in natural frequency of the system was expected due to higher density propellants. The lower heat leak should also result in a change to the MIB pulse profile, and data will be examined to understand how MIB repeatability is affected in the different operating environments. Parallel to the test efforts, a set of transient model development efforts were made to predict RCS performance. The primary effort was aimed at producing a SINDA/FLUINT model to predict propellant conditioning up to the engine inlet as a function of different environmental and operating parameters, with the goal of predicting chamber pressure, TVS performance, and propellant consumption over time. Preliminary results for this effort will be presented in comparison with test data. Additional modeling efforts were made using SINDA/FLUINT to predict waterhammer in the system since the software is capable of handling multiphase transient fluid dynamics. These results will be compared with the high-speed pressure transducer test data for validation purposes.

  11. 8. TEST STAND 15, INVERTED ENGINE FIRING TEST, CIRCA 1963. ...

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

    8. TEST STAND 1-5, INVERTED ENGINE FIRING TEST, CIRCA 1963. Original is a color print. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Test Stand 1-5, Test Area 1-115, northwest end of Saturn Boulevard, Boron, Kern County, CA

  12. A reliability as an independent variable (RAIV) methodology for optimizing test planning for liquid rocket engines

    NASA Astrophysics Data System (ADS)

    Strunz, Richard; Herrmann, Jeffrey W.

    2011-12-01

    The hot fire test strategy for liquid rocket engines has always been a concern of space industry and agency alike because no recognized standard exists. Previous hot fire test plans focused on the verification of performance requirements but did not explicitly include reliability as a dimensioning variable. The stakeholders are, however, concerned about a hot fire test strategy that balances reliability, schedule, and affordability. A multiple criteria test planning model is presented that provides a framework to optimize the hot fire test strategy with respect to stakeholder concerns. The Staged Combustion Rocket Engine Demonstrator, a program of the European Space Agency, is used as example to provide the quantitative answer to the claim that a reduced thrust scale demonstrator is cost beneficial for a subsequent flight engine development. Scalability aspects of major subsystems are considered in the prior information definition inside the Bayesian framework. The model is also applied to assess the impact of an increase of the demonstrated reliability level on schedule and affordability.

  13. 46 CFR 162.028-5 - Independent laboratories: Listing.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... MATERIALS: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Extinguishers, Fire, Portable, Marine Type... or tests of portable fire extinguishers: (a) For dry chemical, CO2, water and foam type portable fire...

  14. 46 CFR 162.028-5 - Independent laboratories: Listing.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... MATERIALS: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Extinguishers, Fire, Portable, Marine Type... or tests of portable fire extinguishers: (a) For dry chemical, CO2, water and foam type portable fire...

  15. 46 CFR 162.028-5 - Independent laboratories: Listing.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... MATERIALS: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Extinguishers, Fire, Portable, Marine Type... or tests of portable fire extinguishers: (a) For dry chemical, CO2, water and foam type portable fire...

  16. 46 CFR 162.028-5 - Independent laboratories: Listing.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... MATERIALS: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Extinguishers, Fire, Portable, Marine Type... or tests of portable fire extinguishers: (a) For dry chemical, CO2, water and foam type portable fire...

  17. 46 CFR 162.028-5 - Independent laboratories: Listing.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... MATERIALS: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Extinguishers, Fire, Portable, Marine Type... or tests of portable fire extinguishers: (a) For dry chemical, CO2, water and foam type portable fire...

  18. IPD 100% Power Test

    NASA Image and Video Library

    2006-07-12

    The Integrated Powerhead Demonstration engine was fired at 100 percent power for the first time July 12, 2006 at NASA Stennis Space Center's E Test Complex. The IPD, which can generate about 250,000 pounds of thrust, is a reusable engine system whose technologies could one day help Americans return to the moon, and travel to Mars and beyond. The IPD engine has been designed, developed and tested through the combined efforts of Pratt & Whitney Rocketdyne and Aerojet, under the direction of the Air Force Research Laboratory and NASA's Marshall Space Flight Center.

  19. Evaluation of fire hazard inspection procedures in Butte County, California

    Treesearch

    William S. Folkman

    1967-01-01

    To assess effectiveness of fire hazard inspection procedures in securing compliance with fire safety requirements, effects of different types and combinations of contacts and timing were determined, and the production capacity of inspectors measured. It was demonstrated that fire law inspection is as much fire prevention education and engineering as it is law...

  20. 46 CFR 130.470 - Fire alarms.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... fire detector and control unit must be of a type specifically approved by the Commandant (CG-ENG). (b) No fire-alarm circuit for the engine room may contain a fire detector for any other space. (c) The number and placement of fire detectors must be approved by the cognizant OCMI. [CGD 82-004 and CGD 86-074...

  1. 46 CFR 130.470 - Fire alarms.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... fire detector and control unit must be of a type specifically approved by the Commandant (CG-521). (b) No fire-alarm circuit for the engine room may contain a fire detector for any other space. (c) The number and placement of fire detectors must be approved by the cognizant OCMI. [CGD 82-004 and CGD 86-074...

  2. 46 CFR 130.470 - Fire alarms.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... fire detector and control unit must be of a type specifically approved by the Commandant (CG-521). (b) No fire-alarm circuit for the engine room may contain a fire detector for any other space. (c) The number and placement of fire detectors must be approved by the cognizant OCMI. [CGD 82-004 and CGD 86-074...

  3. 46 CFR 130.470 - Fire alarms.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... fire detector and control unit must be of a type specifically approved by the Commandant (CG-ENG). (b) No fire-alarm circuit for the engine room may contain a fire detector for any other space. (c) The number and placement of fire detectors must be approved by the cognizant OCMI. [CGD 82-004 and CGD 86-074...

  4. 46 CFR 130.470 - Fire alarms.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... fire detector and control unit must be of a type specifically approved by the Commandant (CG-ENG). (b) No fire-alarm circuit for the engine room may contain a fire detector for any other space. (c) The number and placement of fire detectors must be approved by the cognizant OCMI. [CGD 82-004 and CGD 86-074...

  5. Fault tree analysis of fire and explosion accidents for dual fuel (diesel/natural gas) ship engine rooms

    NASA Astrophysics Data System (ADS)

    Guan, Yifeng; Zhao, Jie; Shi, Tengfei; Zhu, Peipei

    2016-09-01

    In recent years, China's increased interest in environmental protection has led to a promotion of energy-efficient dual fuel (diesel/natural gas) ships in Chinese inland rivers. A natural gas as ship fuel may pose dangers of fire and explosion if a gas leak occurs. If explosions or fires occur in the engine rooms of a ship, heavy damage and losses will be incurred. In this paper, a fault tree model is presented that considers both fires and explosions in a dual fuel ship; in this model, dual fuel engine rooms are the top events. All the basic events along with the minimum cut sets are obtained through the analysis. The primary factors that affect accidents involving fires and explosions are determined by calculating the degree of structure importance of the basic events. According to these results, corresponding measures are proposed to ensure and improve the safety and reliability of Chinese inland dual fuel ships.

  6. Technologies for Future Precision Strike Missile Systems (les Technologies des futurs systemes de missiles pour frappe de precision)

    DTIC Science & Technology

    2001-07-01

    hardware - in - loop (HWL) simulation is also developed...Firings / Engine Tests Structure Test Hardware In - Loop Simulation Subsystem Test Lab Tests Seeker Actuators Sensors Electronics Propulsion Model Aero Model...Structure Test Hardware In - Loop Simulation Subsystem Test Lab Tests Seeker Actuators Sensors Electronics Propulsion Model Aero Model Model

  7. NASA Fastrac Engine Gas Generator Component Test Program and Results

    NASA Technical Reports Server (NTRS)

    Dennis, Henry J., Jr.; Sanders, T.

    2000-01-01

    Low cost access to space has been a long-time goal of the National Aeronautics and Space Administration (NASA). The Fastrac engine program was begun at NASA's Marshall Space Flight Center to develop a 60,000-pound (60K) thrust, liquid oxygen/hydrocarbon (LOX/RP), gas generator-cycle booster engine for a fraction of the cost of similar engines in existence. To achieve this goal, off-the-shelf components and readily available materials and processes would have to be used. This paper will present the Fastrac gas generator (GG) design and the component level hot-fire test program and results. The Fastrac GG is a simple, 4-piece design that uses well-defined materials and processes for fabrication. Thirty-seven component level hot-fire tests were conducted at MSFC's component test stand #116 (TS116) during 1997 and 1998. The GG was operated at all expected operating ranges of the Fastrac engine. Some minor design changes were required to successfully complete the test program as development issues arose during the testing. The test program data results and conclusions determined that the Fastrac GG design was well on the way to meeting the requirements of NASA's X-34 Pathfinder Program that chose the Fastrac engine as its main propulsion system.

  8. Wildfire simulation using LES with synthetic-velocity SGS models

    NASA Astrophysics Data System (ADS)

    McDonough, J. M.; Tang, Tingting

    2016-11-01

    Wildland fires are becoming more prevalent and intense worldwide as climate change leads to warmer, drier conditions; and large-eddy simulation (LES) is receiving increasing attention for fire spread predictions as computing power continues to improve (see, e.g.,). We report results from wildfire simulations over general terrain employing implicit LES for solution of the incompressible Navier-Stokes (N.-S.) and thermal energy equations with Boussinesq approximation, altered with Darcy, Forchheimer and Brinkman extensions, to represent forested regions as porous media with varying (in both space and time) porosity and permeability. We focus on subgrid-scale (SGS) behaviors computed with a synthetic-velocity model, a discrete dynamical system, based on the poor man's N.-S. equations and investigate the ability of this model to produce fire whirls (tornadoes of fire) at the (unresolved) SGS level. Professor, Mechanical Engineering and Mathematics.

  9. SSME environment database development

    NASA Technical Reports Server (NTRS)

    Reardon, John

    1987-01-01

    The internal environment of the Space Shuttle Main Engine (SSME) is being determined from hot firings of the prototype engines and from model tests using either air or water as the test fluid. The objectives are to develop a database system to facilitate management and analysis of test measurements and results, to enter available data into the the database, and to analyze available data to establish conventions and procedures to provide consistency in data normalization and configuration geometry references.

  10. Propulsion System Advances that Enable a Reusable Liquid Fly Back Booster (LFBB)

    NASA Technical Reports Server (NTRS)

    Keith, Edward L.; Rothschild, William J.

    1998-01-01

    This paper provides an overview of the booster propulsion system for the Liquid Fly Back Booster (LFBB). This includes, system requirements, design approach, concept of operations, reliability, safety and cost assumptions. The paper summarizes the findings of the Boeing propulsion team that has been studying the LFBB feasibility as a booster replacement for the Space Shuttle. This paper will discuss recent advances including a new generation of kerosene and oxygen rich pre-burner staged combustion cycle main rocket engines. The engine reliability and safety is expected to be much higher than current standards by adding extra operating margins into the design and normally operating the engines at 75% of engine rated power. This allows for engine out capability. The new generation of main engines operates at significantly higher chamber pressure than the prior generation of gas generator cycle engines. The oxygen rich pre-burner engine cycle, unlike the fuel rich gas generator cycle, results in internally self-cleaning firings which facilitates reusability. Maintenance is further enhanced with integrated health monitoring to improve safety and turn-around efficiency. The maintainability of the LFBB LOX / kerosene engines is being improved by designing the vehicle/engine interfaces for easy access to key engine components.

  11. Propulsion system advances that enable a reusable Liquid Fly Back Booster (LFBB)

    NASA Technical Reports Server (NTRS)

    Keith, E. L.; Rothschild, W. J.

    1998-01-01

    This paper provides an overview of the booster propulsion system for the Liquid Fly Back Booster (LFBB). This includes, system requirements, design approach, concept of operations, reliability, safety and cost assumptions. The paper summarizes the findings of the Boeing propulsion team that has been studying the LFBB feasibility as a booster replacement for the Space Shuttle. This paper will discuss recent advances including a new generation of kerosene and oxygen rich pre-burner staged combustion cycle main rocket engines. The engine reliability and safety is expected to be much higher than current standards by adding extra operating margins into the design and normally operating the engines at 75% of engine rated power. This allows for engine out capability. The new generation of main engines operates at significantly higher chamber pressure than the prior generation of gas generator cycle engines. The oxygen rich pre-burner engine cycle, unlike the fuel rich gas generator cycle, results in internally self-cleaning firings which facilitates reusability. Maintenance is further enhanced with integrated health monitoring to improve safety and turn-around efficiency. The maintainability of the LFBB LOX/kerosene engines is being improved by designing the vehicle/engine interfaces for easy access to key engine components.

  12. Spring 2014 Internship Diffuser Data Analysis

    NASA Technical Reports Server (NTRS)

    Laigaie, Robert T.; Ryan, Harry M.

    2014-01-01

    J-2X engine testing on the A-2 test stand at the NASA John C. Stennis Space Center (SSC) has recently concluded. As part of that test campaign, the engine was operated at lower power levels in support of expanding the use of J-2X to other missions. However, the A-2 diffuser was not designed for engine testing at the proposed low power levels. To evaluate the risk of damage to the diffuser, computer simulations were created of the rocket engine exhaust plume inside the 50ft long, water-cooled, altitude-simulating diffuser. The simulations predicted that low power level testing would cause the plume to oscillate in the lower sections of the diffuser. This can possibly cause excessive vibrations, stress, and heat transfer from the plume to the diffuser walls. To understand and assess the performance of the diffuser during low power level engine testing, nine accelerometers and four strain gages were installed around the outer surface of the diffuser. The added instrumentation also allowed for the verification of the rocket exhaust plume computational model. Prior to engine hot-fire testing, a diffuser water-flow test was conducted to verify the proper operation of the newly installed instrumentation. Subsequently, two J-2X engine hot-fire tests were completed. Hot-Fire Test 1 was 11.5 seconds in duration, and accelerometer and strain data verified that the rocket engine plume oscillated in the lower sections of the diffuser. The accelerometers showed very different results dependent upon location. The diffuser consists of four sections, with Section 1 being closest to the engine nozzle and Section 4 being farthest from the engine nozzle. Section 1 accelerometers showed increased amplitudes at startup and shutdown, but low amplitudes while the diffuser was started. Section 3 accelerometers showed the opposite results with near zero G amplitudes prior to and after diffuser start and peak amplitudes to +/- 100G while the diffuser was started. Hot-Fire Test 1 strain gages showed different data dependent on section. Section 1 strains were small, and were in the range of 50 to 150 microstrain, which would result in stresses from 1.45 to 4.35 ksi. The yield stress of the material, A-285 Grade C Steel, is 29.7 ksi. Section 4 strain gages showed much higher values with strains peaking at 1600 microstrain. This strain corresponds to a stress of 46.41 ksi, which is in excess of the yield stress, but below the ultimate stress of 55 to 75 ksi. The decreased accelerations and strain in Section 1, and the increased accelerations and strain in Sections 3 and 4 verified the computer simulation prediction of increased plume oscillations in the lower sections of the diffuser. Hot-Fire Test 2 ran for a duration of 125 seconds. The engine operated at a slightly higher power level than Hot-Fire Test 1 for the initial 35 seconds of the test. After 35 seconds the power level was lowered to Hot-Fire Test 1 levels. The acceleration and strain data for Hot-Fire Test 2 was similar during the initial part of the test. However, just prior to the engine being lowered to the Hot-Fire Test 1 power level, the strain gage data in Section 4 showed a large decrease to strains near zero microstrain from their peak at 1500 microstrain. Future work includes further strain and acceleration data analysis and evaluation.

  13. Mission Impact Through Neuro-Inspired Design (MIND) Laboratory: Design Principles and Performance Characteristics

    DTIC Science & Technology

    2013-09-01

    sprinkler , fire alarm, and mass-notification systems ). Piping required for the sprinkler system uses dielectric couplers at each penetration of the...environment for neuroscience research designed for studying Soldier- system interactions in support of the U.S. Army Research Laboratory’s (ARL’s...Engineers, of Towson, MD, —designed the heating, ventilation, and air conditioning and electrical systems ; Hi-Tech Services, Inc., of Ferndale, WA

  14. 40 CFR 60.4205 - What emission standards must I meet for emergency engines if I am an owner or operator of a...

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ... with a displacement of less than 10 liters per cylinder that are not fire pump engines must comply with... emergency stationary CI ICE with a displacement of greater than or equal to 10 liters per cylinder and less... with a displacement of less than 30 liters per cylinder that are not fire pump engines must comply with...

  15. 40 CFR 60.4205 - What emission standards must I meet for emergency engines if I am an owner or operator of a...

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... with a displacement of less than 10 liters per cylinder that are not fire pump engines must comply with...-emergency stationary CI ICE with a displacement of greater than or equal to 10 liters per cylinder and less... with a displacement of less than 30 liters per cylinder that are not fire pump engines must comply with...

  16. 40 CFR 60.4205 - What emission standards must I meet for emergency engines if I am an owner or operator of a...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... with a displacement of less than 10 liters per cylinder that are not fire pump engines must comply with...-emergency stationary CI ICE with a displacement of greater than or equal to 10 liters per cylinder and less... with a displacement of less than 30 liters per cylinder that are not fire pump engines must comply with...

  17. 40 CFR 60.4205 - What emission standards must I meet for emergency engines if I am an owner or operator of a...

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... with a displacement of less than 10 liters per cylinder that are not fire pump engines must comply with... emergency stationary CI ICE with a displacement of greater than or equal to 10 liters per cylinder and less... with a displacement of less than 30 liters per cylinder that are not fire pump engines must comply with...

  18. 40 CFR 60.4205 - What emission standards must I meet for emergency engines if I am an owner or operator of a...

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... with a displacement of less than 10 liters per cylinder that are not fire pump engines must comply with... emergency stationary CI ICE with a displacement of greater than or equal to 10 liters per cylinder and less... with a displacement of less than 30 liters per cylinder that are not fire pump engines must comply with...

  19. First Stage Acceptance Test

    NASA Technical Reports Server (NTRS)

    1960-01-01

    This photograph shows the intense smoke and fire created by the five F-1 engines from a test firing of the Saturn V first stage (S-1C) in the S-1C test stand at the Marshall Space Flight Center. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

  20. 33 CFR 154.735 - Safety requirements.

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... engines used on the facility— (1) Does not constitute a fire hazard; and (2) Has a fire extinguisher... internal combustion engine is not refueled on a pier, wharf, or other similar structure. (o) There are no... approval for that use by— (1) Underwriters Laboratories; (2) Factory Mutual Research Corporation; or (3...

  1. 33 CFR 154.735 - Safety requirements.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... engines used on the facility— (1) Does not constitute a fire hazard; and (2) Has a fire extinguisher... internal combustion engine is not refueled on a pier, wharf, or other similar structure. (o) There are no... approval for that use by— (1) Underwriters Laboratories; (2) Factory Mutual Research Corporation; or (3...

  2. 33 CFR 154.735 - Safety requirements.

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ... engines used on the facility— (1) Does not constitute a fire hazard; and (2) Has a fire extinguisher... internal combustion engine is not refueled on a pier, wharf, or other similar structure. (o) There are no... approval for that use by— (1) Underwriters Laboratories; (2) Factory Mutual Research Corporation; or (3...

  3. 78 FR 72550 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-03

    ... (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire. DATES: This AD... brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire. (f) Compliance Comply with... 3532, dated January 12, 2012. (1) Do either a general visual inspection or ultrasonic non- destructive...

  4. 77 FR 7518 - Airworthiness Directives; The Boeing Company Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-02-13

    ... report that the top 3 inches of the aero/fire seals of the blocker doors on the thrust reverser torque... aero/fire seals of the blocker doors on the thrust reverser torque boxes on the engines, and replacing affected aero/fire seals with new, improved aero/fire seals. We are issuing this AD to prevent a fire in...

  5. Econometric analysis of fire suppression production functions for large wildland fires

    Treesearch

    Thomas P. Holmes; David E. Calkin

    2013-01-01

    In this paper, we use operational data collected for large wildland fires to estimate the parameters of economic production functions that relate the rate of fireline construction with the level of fire suppression inputs (handcrews, dozers, engines and helicopters). These parameter estimates are then used to evaluate whether the productivity of fire suppression inputs...

  6. Studying interregional wildland fire engine assignments for large fire suppression

    Treesearch

    Erin J. Belval; Yu Wei; David E. Calkin; Crystal S. Stonesifer; Matthew P. Thompson; John R. Tipton

    2017-01-01

    One crucial component of large fire response in the United States (US) is the sharing of wildland firefighting resources between regions: resources from regions experiencing low fire activity supplement resources in regions experiencing high fire activity. An important step towards improving the efficiency of resource sharing and related policies is to develop a better...

  7. Design and operation of a medium speed 12-cylinder coal-fueled diesel engine. Phase 2: Improvements

    NASA Astrophysics Data System (ADS)

    Confer, G. L.; Hsu, B. D.; McDowell, R. E.; Gal, E.; Vankleunen, W.; Kaldor, S.; Mengel, M.

    Under the sponsorship of the US Department of Energy, General Electric has been pioneering the development of a coal fired diesel engine to power a locomotive. The feasibility of using a coal water slurry (CWS) mixture as a fuel in a medium speed diesel engine has been demonstrated with the first successful locomotive systems test in 1991 on the GE Transportation Systems test track in Erie, PA. Phase 2 of the development process incorporates the results of the programs research in durable engine parts, improved combustion efficiency, and emissions reduction. A GE 7FDL12 engine has been built using diamond insert injector nozzles, tungsten carbide coated piston rings, and tungsten carbide coated liners to overcome power assembly wear. Electronic controlled fuel injection for both diesel pilot and main CWS injector were incorporated to control injection timing. An envelop filter and copper oxide sorbent system were used to cleanup engine emissions. The system is capable of removing over 99% of the particulates, 90% of the SO2, and 85% of NO(x).

  8. Definition, technology readiness, and development cost of the orbit transfer vehicle engine integrated control and health monitoring system elements

    NASA Technical Reports Server (NTRS)

    Cannon, I.; Balcer, S.; Cochran, M.; Klop, J.; Peterson, S.

    1991-01-01

    An Integrated Control and Health Monitoring (ICHM) system was conceived for use on a 20 Klb thrust baseline Orbit Transfer Vehicle (OTV) engine. Considered for space used, the ICHM was defined for reusability requirements for an OTV engine service free life of 20 missions, with 100 starts and a total engine operational time of 4 hours. Functions were derived by flowing down requirements from NASA guidelines, previous OTV engine or ICHM documents, and related contracts. The elements of an ICHM were identified and listed, and these elements were described in sufficient detail to allow estimation of their technology readiness levels. These elements were assessed in terms of technology readiness level, and supporting rationale for these assessments presented. The remaining cost for development of a minimal ICHM system to technology readiness level 6 was estimated. The estimates are within an accuracy range of minus/plus 20 percent. The cost estimates cover what is needed to prepare an ICHM system for use on a focussed testbed for an expander cycle engine, excluding support to the actual test firings.

  9. Linear Aerospike SR-71 Experiment (LASRE): Aerospace Propulsion Hazard Mitigation Systems

    NASA Technical Reports Server (NTRS)

    Mizukami, Masashi; Corpening, Griffin P.; Ray, Ronald J.; Hass, Neal; Ennix, Kimberly A.; Lazaroff, Scott M.

    1998-01-01

    A major hazard posed by the propulsion system of hypersonic and space vehicles is the possibility of fire or explosion in the vehicle environment. The hazard is mitigated by minimizing or detecting, in the vehicle environment, the three ingredients essential to producing fire: fuel, oxidizer, and an ignition source. The Linear Aerospike SR-71 Experiment (LASRE) consisted of a linear aerospike rocket engine integrated into one-half of an X-33-like lifting body shape, carried on top of an SR-71 aircraft. Gaseous hydrogen and liquid oxygen were used as propellants. Although LASRE is a one-of-a-kind experimental system, it must be rated for piloted flight, so this test presented a unique challenge. To help meet safety requirements, the following propulsion hazard mitigation systems were incorporated into the experiment: pod inert purge, oxygen sensors, a hydrogen leak detection algorithm, hydrogen sensors, fire detection and pod temperature thermocouples, water misting, and control room displays. These systems are described, and their development discussed. Analyses, ground test, and flight test results are presented, as are findings and lessons learned.

  10. Experimental study on the thrust modulation performance of powdered magnesium and CO2 bipropellant engine

    NASA Astrophysics Data System (ADS)

    Li, Chao; Hu, Chunbo; Zhu, Xiaofei; Hu, Jiaming; Li, Yue; Hu, Xu

    2018-06-01

    Powdered Mg and CO2 bipropellant engine providing a practical demonstration of in situ resource utilization (ISRU) for Mars Sample Return (MSR) mission seems to be feasible by current investigations. However, essential functions of the engine to satisfy the complicated ballistics requirements such as thrust modulation and multiple pulse have not been established yet. The aim of this experimental study is to evaluate the engine's thrust modulation feasibility and to investigate its thrust modulation characteristics. A powdered Mg and CO2 bipropellant engine construction aiming to achieve thrust modulation ability was proposed. A mass flow rate calibration experiment to evaluate the gas-solid mass flow rate regulating performance was conducted before fire tests. Fire test result shows that the engine achieved successful ignition as well as self-sustaining combustion; Thrust modulation of the engine is feasible, detail thrust estimating result of the test shows that maximum thrust is 135.91 N and the minimum is 5.65 N with a 22.11 thrust modulation ratio, moreover, the transportation period is quick and the thrust modulation ratio is adjustable. At the same time, the powder feed system reaches a two-step flow rate regulating with a modulation ratio of 4.5-5. What' more, caused by the uneven engine working conditions, there is an obvious difference in combustion efficiency value, maximum combustion efficiency of the powdered Mg and CO2 bipropellant engine is 80.20%.

  11. Cassidy conducts BASS Experiment Test Operations

    NASA Image and Video Library

    2013-04-05

    ISS035-E-015081 (5 April 2013) --- Astronaut Chris Cassidy, Expedition 35 flight engineer, conducts a session of the Burning and Suppression of Solids (BASS) experiment onboard the Earth-orbiting International Space Station. Following a series of preparations, Cassidy conducted a run of the experiment, which examined the burning and extinction characteristics of a wide variety of fuel samples in microgravity and will guide strategies for extinguishing fires in microgravity. BASS results contribute to the combustion computational models used in the design of fire detection and suppression systems in microgravity and on Earth.

  12. Apollo 16, LM-11 ascent propulsion system final flight evaluation

    NASA Technical Reports Server (NTRS)

    Griffin, W. G.

    1974-01-01

    The duty cycle for the LM-11 APS consisted of two firings, an ascent stage liftoff from the lunar surface, and the terminal phase initiation (TPI) burn. APS performance for the first firing was evaluated and found to be satisfactory. No propulsion data were received from the second APS burn; however, all indications were that the burn was nominal. Engine ignition for the APS lunar liftoff burn occured at the Apollo elapsed time (AET) of 175:31:47.9 (hours:minutes:seconds). Burn duration was 427.7 seconds.

  13. Extended temperature range ACPS thruster investigation

    NASA Technical Reports Server (NTRS)

    Blubaugh, A. L.; Schoenman, L.

    1974-01-01

    The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydrogen/liquid oxygen attitude control propulsion system thruster is described. The test was the result of research to develop a simple, lightweight, and high performance reaction control system without the traditional requirements for extensive periods of engine thermal conditioning, or the use of complex equipment to convert both liquid propellants to gas prior to delivery to the engine. Significant departures from conventional injector design practice were employed to achieve an operable design. The work discussed includes thermal and injector manifold priming analyses, subscale injector chilldown tests, and 168 full scale and 550 N (1250 lbF) rocket engine tests. Ignition experiments, at propellant temperatures ranging from cryogenic to ambient, led to the generation of a universal spark ignition system which can reliably ignite an engine when supplied with liquid, two phase, or gaseous propellants. Electrical power requirements for spark igniter are very low.

  14. Main propulsion system test requirements for the two-engine Shuttle-C

    NASA Technical Reports Server (NTRS)

    Lynn, E. E.; Platt, G. K.

    1989-01-01

    The Shuttle-C is an unmanned cargo carrying derivative of the space shuttle with optional two or three space shuttle main engines (SSME's), whereas the shuttle has three SSME's. Design and operational differences between the Shuttle-C and shuttle were assessed to determine requirements for additional main propulsion system (MPS) verification testing. Also, reviews were made of the shuttle main propulsion test program objectives and test results and shuttle flight experience. It was concluded that, if significant MPS modifications are not made beyond those currently planned, then main propulsion system verification can be concluded with an on-pad flight readiness firing.

  15. Design of structures against fire. Civil engineering/buildings, architecture

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

    Anchor, R.D.; Malhotra, H.L.; Purkiss, J.A.

    1986-01-01

    The book covers structural design criteria, along with background theory on fire protection methods for structures from a variety of materials, including timber, steel, and concrete. Research on the behavior of structural materials in the presence of fire is highlighted, and the need for fire-resistant materials is addressed.

  16. Parabolic dish systems at work - Applying the concepts

    NASA Technical Reports Server (NTRS)

    Marriott, A. T.

    1981-01-01

    An overview is given of parabolic dish solar concentrator application experiments being conducted by the U.S. Department of Energy. The 'engineering experiments' comprise the testing of (1) a small-community powerplant system, in conjunction with a grid-connected utility; (2) stand-alone applications at remote sites such as military installations, radar stations and villages; and (3) dish modules that can deliver heat for direct use in industrial processes. Applicability projections are based on a dish and receiver that use a Brayton engine with an engine/generator efficiency of 25% and a production level of up to 25,000 units per year. Analyses indicate that parabolic-dish power systems can potentially replace small, oil-fired power plants in all regions of the U.S. between 1985 and 1991.

  17. Space Shuttle Projects

    NASA Image and Video Library

    1989-06-03

    The Marshall Space Flight Center (MSFC) engineers test fired a 26-foot long, 100,000-pound-thrust solid rocket motor for 30 seconds at the MSFC east test area, the first test firing of the Modified NASA Motor (M-NASA Motor). The M-NASA Motor was fired in a newly constructed stand. The motor is 48-inches in diameter and was loaded with two propellant cartridges weighing a total of approximately 12,000 pounds. The purpose of the test was to learn more about solid rocket motor insulation and nozzle materials and to provide young engineers additional hands-on expertise in solid rocket motor technology. The test is a part of NASA's Solid Propulsion Integrity Program, that is to provide NASA engineers with the techniques, engineering tools, and computer programs to be able to better design, build, and verify solid rocket motors.

  18. 78 FR 60656 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-02

    ... firewall center fire extinguisher discharge tube (No. 1 engine tube) and inspecting the outboard discharge tube to determine if it is correctly positioned. This AD was prompted by the discovery that the No. 1 engine tube installed on the helicopters is too long to ensure that a fire could be effectively...

  19. Aircraft Engine Sump Fire Mitigation

    NASA Technical Reports Server (NTRS)

    Rosenlieb, J. W.

    1973-01-01

    An investigation was performed of the conditions in which fires can result and be controlled within the bearing sump simulating that of a gas turbine engine; Esso 4040 Turbo Oil, Mobil Jet 2, and Monsanto MCS-2931 lubricants were used. Control variables include the oil inlet temperature, bearing temperature, oil inlet and scavenge rates, hot air inlet temperature and flow rate, and internal sump baffling. In addition to attempting spontaneous combustion, an electric spark and a rub (friction) mechanism were employed to ignite fires. Spontaneous combustion was not obtained; however, fires were readily ignited with the electric spark while using each of the three test lubricants. Fires were also ignited using the rub mechanism with the only test lubricant evaluated, Esso 4040. Major parameters controlling ignitions were: Sump configuration; Bearing and oil temperatures, hot air temperature and flow and bearing speed. Rubbing between stationary parts and rotating parts (eg. labyrinth seal and mating rub strip) is a very potent fire source suggesting that observed accidental fires in gas turbine sumps may well arise from this cause.

  20. Next-Generation RS-25 Engines for the NASA Space Launch System

    NASA Technical Reports Server (NTRS)

    Ballard, Richard O.

    2017-01-01

    The utilization of heritage RS-25 engine, also known as the Space Shuttle Main Engine (SSME), has enabled rapid progress in the development and certification of the NASA Space Launch System (SLS) toward operational flight status. The RS-25 brings design maturity and extensive experience gained through 135 missions, 3000+ ground tests, and over a million seconds total accumulated hot-fire time. In addition, there were also over a dozen functional flight assets remaining from the Space Shuttle program that could be leveraged to support the first four flights. Beyond these initial SLS flights, NASA must have a renewed supply of RS-25 engines that must reflect program affordability imperatives as well as technical requirements imposed by the SLS Block-1B vehicle (i.e., 111% RPL power level, reduced service life). Recognizing the long lead times needed for the fabrication, assembly and acceptance testing of flight engines, design activities are underway at NASA and the RS-25 engine provider, Aerojet Rocketdyne, to improve system affordability and eliminate obsolescence concerns. This paper describes how the achievement of these key objectives are enabled largely by utilizing modern materials and fabrication technologies, but also by innovations in systems engineering and integration (SE&I) practices.

  1. Flight Testing the Linear Aerospike SR-71 Experiment (LASRE)

    NASA Technical Reports Server (NTRS)

    Corda, Stephen; Neal, Bradford A.; Moes, Timothy R.; Cox, Timothy H.; Monaghan, Richard C.; Voelker, Leonard S.; Corpening, Griffin P.; Larson, Richard R.; Powers, Bruce G.

    1998-01-01

    The design of the next generation of space access vehicles has led to a unique flight test that blends the space and flight research worlds. The new space vehicle designs, such as the X-33 vehicle and Reusable Launch Vehicle (RLV), are powered by linear aerospike rocket engines. Conceived of in the 1960's, these aerospike engines have yet to be flown, and many questions remain regarding aerospike engine performance and efficiency in flight. To provide some of these data before flying on the X-33 vehicle and the RLV, a spacecraft rocket engine has been flight-tested atop the NASA SR-71 aircraft as the Linear Aerospike SR-71 Experiment (LASRE). A 20 percent-scale, semispan model of the X-33 vehicle, the aerospike engine, and all the required fuel and oxidizer tanks and propellant feed systems have been mounted atop the SR-71 airplane for this experiment. A major technical objective of the LASRE flight test is to obtain installed-engine performance flight data for comparison to wind-tunnel results and for the development of computational fluid dynamics-based design methodologies. The ultimate goal of firing the aerospike rocket engine in flight is still forthcoming. An extensive design and development phase of the experiment hardware has been completed, including approximately 40 ground tests. Five flights of the LASRE and firing the rocket engine using inert liquid nitrogen and helium in place of liquid oxygen and hydrogen have been successfully completed.

  2. Development of a Prototype Human Resources Data Handbook for Systems Engineering: An Application to Fire Control Systems. Final Report for Period October 1971-June 1975.

    ERIC Educational Resources Information Center

    Reed, Lawrence E.; And Others

    The methods and problems encountered in the development of a prototype human resources data handbook are discussed. The goal of the research was to determine whether it was feasible to consolidate, in a single comprehensive handbook, human resources data applicable to system design and development. Selected for this purpose were data on the…

  3. Systems Engineering Approach for Conceptual Design of Frigate

    DTIC Science & Technology

    2015-09-01

    ejection area. Topside designers should also take note of the gun maintenance required area (e.g., barrel swabbing area), which requires significant...Figure 9. Range-to-Target Plot (BlueIntercept Missile vs. RedFire) ........................34 Figure 10. Range-to-Target Plot (Main Gun System vs...and the secondary anti-air weapon will be the main gun system. The frigates shall also be equipped with an area terminal type defense (ATTD

  4. Design for Maintainability with Modified Petri Nets (MPNs): Shipboard Propulsion System Application.

    DTIC Science & Technology

    1984-11-01

    hazard (in acco- Fance with current environmental protection requirements). P20 YES T20 T2 1 EOOW report to 000, "Fire hazards removed from No engine room...8217-..! AARCA: GAS TURBINE MAIN ENGINE - GENERATOR Room NO 2 , .’ .- " SE7 NO. 2 \\ N 2 GEN MRGA GTM ,RZT 4o i .. .E rAF- _....Pr AJ*~ IAMR...GA Z0GYM GEN "-- ~ ~ P LL-L GIM. I I - GT MAIN ENGINE/ \\ t I . ROOM NO. I GAS 7RBINE ALIX MCHRY AUX MCHRY O OROO NO OOM NO. GENEU.ATOF ROOM NO 2 R

  5. 46 CFR 162.161-3 - Materials.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-3... § 162.161-2) and be made of metal, except for bushings, o-rings, and gaskets. Aluminum or aluminum..., or if galvanically incompatible, be separated by a bushing, o-ring, gasket, or similar device. (c...

  6. 46 CFR 162.161-3 - Materials.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-3... § 162.161-2) and be made of metal, except for bushings, o-rings, and gaskets. Aluminum or aluminum..., or if galvanically incompatible, be separated by a bushing, o-ring, gasket, or similar device. (c...

  7. 46 CFR 162.161-3 - Materials.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ...: SPECIFICATIONS AND APPROVAL ENGINEERING EQUIPMENT Fixed Clean Agent Fire Extinguishing Systems § 162.161-3... § 162.161-2) and be made of metal, except for bushings, o-rings, and gaskets. Aluminum or aluminum..., or if galvanically incompatible, be separated by a bushing, o-ring, gasket, or similar device. (c...

  8. Celestial Triple Treat on This Week @NASA – February 2, 2018

    NASA Image and Video Library

    2018-02-02

    Super Blue Blood Moon – a rare triple treat up in the sky, celebrating America’s first explorer in space, and smoke and fire – another Space Launch System engine test … a few of the stories to tell you about – This Week at NASA!

  9. 46 CFR 118.400 - Where required.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... Extinguishing and Detecting Systems § 118.400 Where required. (a) The following spaces must be equipped with a... this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 50 hp; (3) A space containing an oil fired boiler; (4) A space containing...

  10. 46 CFR 118.400 - Where required.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... Extinguishing and Detecting Systems § 118.400 Where required. (a) The following spaces must be equipped with a... this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 50 hp; (3) A space containing an oil fired boiler; (4) A space containing...

  11. 46 CFR 118.400 - Where required.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... Extinguishing and Detecting Systems § 118.400 Where required. (a) The following spaces must be equipped with a... this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 50 hp; (3) A space containing an oil fired boiler; (4) A space containing...

  12. 46 CFR 118.400 - Where required.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... Extinguishing and Detecting Systems § 118.400 Where required. (a) The following spaces must be equipped with a... this section: (1) A space containing propulsion machinery; (2) A space containing an internal combustion engine of more than 50 hp; (3) A space containing an oil fired boiler; (4) A space containing...

  13. 46 CFR 52.25-15 - Fired thermal fluid heaters.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 2 2014-10-01 2014-10-01 false Fired thermal fluid heaters. 52.25-15 Section 52.25-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING POWER BOILERS Other Boiler Types § 52.25-15 Fired thermal fluid heaters. (a) Fired thermal fluid heaters shall be designed...

  14. 46 CFR 52.25-15 - Fired thermal fluid heaters.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 2 2013-10-01 2013-10-01 false Fired thermal fluid heaters. 52.25-15 Section 52.25-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING POWER BOILERS Other Boiler Types § 52.25-15 Fired thermal fluid heaters. (a) Fired thermal fluid heaters shall be designed...

  15. 46 CFR 52.25-15 - Fired thermal fluid heaters.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 2 2012-10-01 2012-10-01 false Fired thermal fluid heaters. 52.25-15 Section 52.25-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING POWER BOILERS Other Boiler Types § 52.25-15 Fired thermal fluid heaters. (a) Fired thermal fluid heaters shall be designed...

  16. Demonstration of natural gas reburn for NO{sub x} emissions reduction at Ohio Edison Company`s cyclone-fired Niles Plant Unit Number 1

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

    Borio, R.W.; Lewis, R.D.; Koucky, R.W.

    1996-04-01

    Electric utility power plants account for about one-third of the NO{sub x} and two-thirds of the SO{sub 2} emissions in the US cyclone-fired boilers, while representing about 9% of the US coal-fired generating capacity, emit about 14% of the NO{sub x} produced by coal-fired utility boilers. Given this background, the Environmental Protection Agency, the Gas Research Institute, the Electric Power Research Institute, the Pittsburgh Energy Technology Center, and the Ohio Coal Development Office sponsored a program led by ABB Combustion Engineering, Inc. (ABB-CE) to demonstrate reburning on a cyclone-fired boiler. Ohio Edison provided Unit No. 1 at their Niles Stationmore » for the reburn demonstration along with financial assistance. The Niles Unit No. 1 reburn system was started up in September 1990. This reburn program was the first full-scale reburn system demonstration in the US. This report describes work performed during the program. The work included a review of reburn technology, aerodynamic flow model testing of reburn system design concepts, design and construction of the reburn system, parametric performance testing, long-term load dispatch testing, and boiler tube wall thickness monitoring. The report also contains a description of the Niles No. 1 host unit, a discussion of conclusions and recommendations derived from the program, tabulation of data from parametric and long-term tests, and appendices which contain additional tabulated test results.« less

  17. Ultrafine and respirable particle exposure during vehicle fire suppression

    PubMed Central

    Fent, Kenneth W.

    2015-01-01

    Vehicle fires are a common occurrence, yet few studies have reported exposures associated with burning vehicles. This article presents an assessment of firefighters’ potential for ultrafine and respirable particle exposure during vehicle fire suppression training. Fires were initiated within the engine compartment and passenger cabins of three salvaged vehicles, with subsequent water suppression by fire crews. Firefighter exposures were monitored with an array of direct reading particle and air quality instruments. A flexible metallic duct and blower drew contaminants to the instrument array, positioned at a safe distance from the burning vehicles, with the duct inlet positioned at the nozzle operator’s shoulder. The instruments measured the particle number, active surface area, respirable particle mass, photoelectric response, aerodynamic particle size distributions, and air quality parameters. Although vehicle fires were suppressed quickly (<10 minutes), firefighters may be exposed to short duration, high particle concentration episodes during fire suppression, which are orders of magnitude greater than the ambient background concentration. A maximum transient particle concentration of 1.21 × 107 particles per cm3, 170 mg m−3 respirable particle mass, 4700 μm2 cm−3 active surface area and 1400 (arbitrary units) in photoelectric response were attained throughout the series of six fires. Expressed as fifteen minute time-weighted averages, engine compartment fires averaged 5.4 × 104 particles per cm3, 0.36 mg m−3 respirable particle mass, 92 μm2 cm−3 active particle surface area and 29 (arbitrary units) in photoelectric response. Similarly, passenger cabin fires averaged 2.04 × 105 particles per cm3, 2.7 mg m−3 respirable particle mass, 320 μm2 cm−3 active particle surface area, and 34 (arbitrary units) in photoelectric response. Passenger cabin fires were a greater potential source of exposure than engine compartment fires. The wind direction and the relative position of the fire crew to the stationary burning vehicle played a primary role in fire crews’ potential for exposure. We recommend that firefighters wear self-contained breathing apparatus during all phases of the vehicle fire response to significantly reduce their potential for particulate, vapor, and gaseous exposures. PMID:26308547

  18. Ultrafine and respirable particle exposure during vehicle fire suppression.

    PubMed

    Evans, Douglas E; Fent, Kenneth W

    2015-10-01

    Vehicle fires are a common occurrence, yet few studies have reported exposures associated with burning vehicles. This article presents an assessment of firefighters' potential for ultrafine and respirable particle exposure during vehicle fire suppression training. Fires were initiated within the engine compartment and passenger cabins of three salvaged vehicles, with subsequent water suppression by fire crews. Firefighter exposures were monitored with an array of direct reading particle and air quality instruments. A flexible metallic duct and blower drew contaminants to the instrument array, positioned at a safe distance from the burning vehicles, with the duct inlet positioned at the nozzle operator's shoulder. The instruments measured the particle number, active surface area, respirable particle mass, photoelectric response, aerodynamic particle size distributions, and air quality parameters. Although vehicle fires were suppressed quickly (<10 minutes), firefighters may be exposed to short duration, high particle concentration episodes during fire suppression, which are orders of magnitude greater than the ambient background concentration. A maximum transient particle concentration of 1.21 × 10(7) particles per cm(3), 170 mg m(-3) respirable particle mass, 4700 μm(2) cm(-3) active surface area and 1400 (arbitrary units) in photoelectric response were attained throughout the series of six fires. Expressed as fifteen minute time-weighted averages, engine compartment fires averaged 5.4 × 10(4) particles per cm(3), 0.36 mg m(-3) respirable particle mass, 92 μm(2) cm(-3) active particle surface area and 29 (arbitrary units) in photoelectric response. Similarly, passenger cabin fires averaged 2.04 × 10(5) particles per cm(3), 2.7 mg m(-3) respirable particle mass, 320 μm(2) cm(-3) active particle surface area, and 34 (arbitrary units) in photoelectric response. Passenger cabin fires were a greater potential source of exposure than engine compartment fires. The wind direction and the relative position of the fire crew to the stationary burning vehicle played a primary role in fire crews' potential for exposure. We recommend that firefighters wear self-contained breathing apparatus during all phases of the vehicle fire response to significantly reduce their potential for particulate, vapor, and gaseous exposures.

  19. Unexpected Control Structure Interaction on International Space Station

    NASA Technical Reports Server (NTRS)

    Gomez, Susan F.; Platonov, Valery; Medina, Elizabeth A.; Borisenko, Alexander; Bogachev, Alexey

    2017-01-01

    On June 23, 2011, the International Space Station (ISS) was performing a routine 180 degree yaw maneuver in support of a Russian vehicle docking when the on board Russian Segment (RS) software unexpectedly declared two attitude thrusters failed and switched thruster configurations in response to unanticipated ISS dynamic motion. Flight data analysis after the maneuver indicated that higher than predicted structural loads had been induced at various locations on the United States (U.S.) segment of the ISS. Further analysis revealed that the attitude control system was firing thrusters in response to both structural flex and rigid body rates, which resonated the structure and caused high loads and fatigue cycles. It was later determined that the thruster themselves were healthy. The RS software logic, which was intended to react to thruster failures, had instead been heavily influenced by interaction between the control system and structural flex. This paper will discuss the technical aspects of the control structure interaction problem that led to the RS control system firing thrusters in response to structural flex, the factors that led to insufficient preflight analysis of the thruster firings, and the ramifications the event had on the ISS. An immediate consequence included limiting which thrusters could be used for attitude control. This complicated the planning of on-orbit thruster events and necessitated the use of suboptimal thruster configurations that increased propellant usage and caused thruster lifetime usage concerns. In addition to the technical aspects of the problem, the team dynamics and communication shortcomings that led to such an event happening in an environment where extensive analysis is performed in support of human space flight will also be examined. Finally, the technical solution will be presented, which required a multidisciplinary effort between the U.S. and Russian control system engineers and loads and dynamics structural engineers to develop and implement an extensive modification in the RS software logic for ISS attitude control thruster firings.

  20. Fire resistance of engineered wood rim board products.

    Treesearch

    Robert H. White

    2003-01-01

    Engineered wood products, such as oriented strandboard, laminated veneer lumber, and other composite wood products, are being used more often in construction. This includes use as rim boards, which are the components around the perimeter of a floor assembly. This situation has increased the need for information about the fire resistance of these products. In this study...

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