Sample records for pyrotechnics

  1. 16 CFR 1507.5 - Pyrotechnic leakage.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 16 Commercial Practices 2 2010-01-01 2010-01-01 false Pyrotechnic leakage. 1507.5 Section 1507.5... FIREWORKS DEVICES § 1507.5 Pyrotechnic leakage. The pyrotechnic chamber in fireworks devices shall be sealed in a manner that prevents leakage of the pyrotechnic composition during shipping, handling, and...

  2. 16 CFR 1507.5 - Pyrotechnic leakage.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 16 Commercial Practices 2 2011-01-01 2011-01-01 false Pyrotechnic leakage. 1507.5 Section 1507.5... FIREWORKS DEVICES § 1507.5 Pyrotechnic leakage. The pyrotechnic chamber in fireworks devices shall be sealed in a manner that prevents leakage of the pyrotechnic composition during shipping, handling, and...

  3. 46 CFR 160.066-12 - Operational tests.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160... the pyrotechnic candle; (2) Color; (3) Whether the pyrotechnic candle burns out above, at, or below... pyrotechnic candle fails to ignite, (3) The pyrotechnic candle continues to burn after it falls back to the...

  4. Integration of pyrotechnics into aerospace systems

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.; Schimmel, Morry L.

    1993-01-01

    The application of pyrotechnics to aerospace systems has been resisted because normal engineering methods cannot be used in design and evaluation. Commonly used approaches for energy sources, such as electrical, hydraulic and pneumatic, do not apply to explosive and pyrotechnic devices. This paper introduces the unique characteristics of pyrotechnic devices, describes how functional evaluations can be conducted, and demonstrates an engineering approach for pyrotechnic integration. Logic is presented that allows evaluation of two basic types of pyrotechnic systems to demonstrate functional margin.

  5. NASA pyrotechnically actuated systems program

    NASA Technical Reports Server (NTRS)

    Schulze, Norman R.

    1993-01-01

    The Office of Safety and Mission Quality initiated a Pyrotechnically Actuated Systems (PAS) Program in FY-92 to address problems experienced with pyrotechnically actuated systems and devices used both on the ground and in flight. The PAS Program will provide the technical basis for NASA's projects to incorporate new technological developments in operational systems. The program will accomplish that objective by developing/testing current and new hardware designs for flight applications and by providing a pyrotechnic data base. This marks the first applied pyrotechnic technology program funded by NASA to address pyrotechnic issues. The PAS Program has been structured to address the results of a survey of pyrotechnic device and system problems with the goal of alleviating or minimizing their risks. Major program initiatives include the development of a Laser Initiated Ordnance System, a pyrotechnic systems data base, NASA Standard Initiator model, a NASA Standard Linear Separation System and a NASA Standard Gas Generator. The PAS Program sponsors annual aerospace pyrotechnic systems workshops.

  6. Low-Shock Pyrotechnic Actuator

    NASA Technical Reports Server (NTRS)

    Lucy, M. H.

    1984-01-01

    Miniature 1-ampere, 1-watt pyrotechnic actuator enclosed in flexible metal bellows. Bellows confines outgassing products, and pyrotechnic shock reduction achieved by action of bellows, gas cushion within device, and minimum use of pyrotechnic material. Actuator inexpensive, compact, and lightweight.

  7. Pyrotechnic whistle technology enhancements to law enforcement applications

    NASA Astrophysics Data System (ADS)

    Domanico, Joseph A.; Thomas, Terry E.

    1998-12-01

    In the past several years, there has been increasing interest in acoustic technology for less-than-lethal applications. Pyrotechnic whistles have been under study at the Edgewood Research, Development and engineering Center for several years for similar applications. Improvements in safety and handling, combined with increased levels of acoustic output, make the properly designed pyrotechnic whistle a valuable addition (read augmentation) to some current device designs. Either alone or in combination with other distraction effects, such as multiple concussion, strobing pyrotechnic, or microstarts, the pyrotechnic whistle family of devices provide a high level of target reaction with a minimum of collateral damage. This paper will summarize the recent research and development efforts in pyrotechnic whistle compositions, and the capabilities for the application of pyrotechnic whistles for typical law enforcement applications.

  8. 27 CFR 555.221 - Requirements for display fireworks, pyrotechnic compositions, and explosive materials used in...

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... fireworks, pyrotechnic compositions, and explosive materials used in assembling fireworks or articles pyrotechnic. 555.221 Section 555.221 Alcohol, Tobacco Products, and Firearms BUREAU OF ALCOHOL, TOBACCO... Requirements for display fireworks, pyrotechnic compositions, and explosive materials used in assembling...

  9. 46 CFR 169.553 - Pyrotechnic distress signals.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 7 2010-10-01 2010-10-01 false Pyrotechnic distress signals. 169.553 Section 169.553... Lifesaving and Firefighting Equipment Additional Lifesaving Equipment § 169.553 Pyrotechnic distress signals. (a) All pyrotechnic distress signals must be of an approved type. (b) Replacement must be made no...

  10. 46 CFR 169.553 - Pyrotechnic distress signals.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 7 2011-10-01 2011-10-01 false Pyrotechnic distress signals. 169.553 Section 169.553... Lifesaving and Firefighting Equipment Additional Lifesaving Equipment § 169.553 Pyrotechnic distress signals. (a) All pyrotechnic distress signals must be of an approved type. (b) Replacement must be made no...

  11. 27 CFR 555.221 - Requirements for display fireworks, pyrotechnic compositions, and explosive materials used in...

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... fireworks, pyrotechnic compositions, and explosive materials used in assembling fireworks or articles pyrotechnic. 555.221 Section 555.221 Alcohol, Tobacco Products, and Firearms BUREAU OF ALCOHOL, TOBACCO... Requirements for display fireworks, pyrotechnic compositions, and explosive materials used in assembling...

  12. 46 CFR 169.553 - Pyrotechnic distress signals.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 7 2014-10-01 2014-10-01 false Pyrotechnic distress signals. 169.553 Section 169.553... Lifesaving and Firefighting Equipment Additional Lifesaving Equipment § 169.553 Pyrotechnic distress signals. (a) All pyrotechnic distress signals must be of an approved type. (b) Replacement must be made no...

  13. 46 CFR 169.553 - Pyrotechnic distress signals.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 7 2013-10-01 2013-10-01 false Pyrotechnic distress signals. 169.553 Section 169.553... Lifesaving and Firefighting Equipment Additional Lifesaving Equipment § 169.553 Pyrotechnic distress signals. (a) All pyrotechnic distress signals must be of an approved type. (b) Replacement must be made no...

  14. 46 CFR 169.553 - Pyrotechnic distress signals.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 7 2012-10-01 2012-10-01 false Pyrotechnic distress signals. 169.553 Section 169.553... Lifesaving and Firefighting Equipment Additional Lifesaving Equipment § 169.553 Pyrotechnic distress signals. (a) All pyrotechnic distress signals must be of an approved type. (b) Replacement must be made no...

  15. Pyrotechnic hazards classification and evaluation program. Run-up reaction testing in pyrotechnic dust suspensions

    NASA Technical Reports Server (NTRS)

    1971-01-01

    A preliminary investigation of the parameters included in run-up dust reactions is presented. Two types of tests were conducted: (1) ignition criteria of large bulk pyrotechnic dusts, and (2) optimal run-up conditions of large bulk pyrotechnic dusts. These tests were used to evaluate the order of magnitude and gross scale requirements needed to induce run-up reactions in pyrotechnic dusts and to simulate at reduced scale an accident that occurred in a manufacturing installation. Test results showed that propagation of pyrotechnic dust clouds resulted in a fireball of relatively long duration and large size. In addition, a plane wave front was observed to travel down the length of the gallery.

  16. Ultimately Reliable Pyrotechnic Systems

    NASA Technical Reports Server (NTRS)

    Scott, John H.; Hinkel, Todd

    2015-01-01

    This paper presents the methods by which NASA has designed, built, tested, and certified pyrotechnic devices for high reliability operation in extreme environments and illustrates the potential applications in the oil and gas industry. NASA's extremely successful application of pyrotechnics is built upon documented procedures and test methods that have been maintained and developed since the Apollo Program. Standards are managed and rigorously enforced for performance margins, redundancy, lot sampling, and personnel safety. The pyrotechnics utilized in spacecraft include such devices as small initiators and detonators with the power of a shotgun shell, detonating cord systems for explosive energy transfer across many feet, precision linear shaped charges for breaking structural membranes, and booster charges to actuate valves and pistons. NASA's pyrotechnics program is one of the more successful in the history of Human Spaceflight. No pyrotechnic device developed in accordance with NASA's Human Spaceflight standards has ever failed in flight use. NASA's pyrotechnic initiators work reliably in temperatures as low as -420 F. Each of the 135 Space Shuttle flights fired 102 of these initiators, some setting off multiple pyrotechnic devices, with never a failure. The recent landing on Mars of the Opportunity rover fired 174 of NASA's pyrotechnic initiators to complete the famous '7 minutes of terror.' Even after traveling through extreme radiation and thermal environments on the way to Mars, every one of them worked. These initiators have fired on the surface of Titan. NASA's design controls, procedures, and processes produce the most reliable pyrotechnics in the world. Application of pyrotechnics designed and procured in this manner could enable the energy industry's emergency equipment, such as shutoff valves and deep-sea blowout preventers, to be left in place for years in extreme environments and still be relied upon to function when needed, thus greatly enhancing safety and operational availability.

  17. Pyrotechnic hazards classification and evaluation program test report. Heat flux study of deflagrating pyrotechnic munitions

    NASA Technical Reports Server (NTRS)

    Fassnacht, P. O.

    1971-01-01

    A heat flux study of deflagrating pyrotechnic munitions is presented. Three tests were authorized to investigate whether heat flux measurements may be used as effective hazards evaluation criteria to determine safe quantity distances for pyrotechnics. A passive sensor study was conducted simultaneously to investigate their usefulness in recording events and conditions. It was concluded that heat flux measurements can effectively be used to evaluate hazards criteria and that passive sensors are an inexpensive tool to record certain events in the vicinity of deflagrating pyrotechnic stacks.

  18. Pyrotechnic filled molding powder

    DOEpatents

    Hartzel, Lawrence W.; Kettling, George E.

    1978-01-01

    The disclosure relates to thermosetting molding compounds and more particularly to a pyrotechnic filled thermosetting compound comprising a blend of unfilled diallyl phthalate molding powder and a pyrotechnic mixture.

  19. 2. SOUTH FACE OF PYROTECHNIC SHED (BLDG. 757) SHOWING SIGN ...

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

    2. SOUTH FACE OF PYROTECHNIC SHED (BLDG. 757) SHOWING SIGN HOLDER ON LEFT AND ENTRANCE TO TEST CELL. METEOROLOGICAL TOWER AND METEOROLOGICAL SHED (BLDG. 756) IN BACKGROUND ON LEFT; SOUTHEAST CORNER OF GPS AZIMUTH STATION (BLDG. 775) IN BACKGROUND BEHIND AND RIGHT OF PYROTECHNIC SHED. - Vandenberg Air Force Base, Space Launch Complex 3, Pyrotechnic Shed, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  20. A study of the role of pyrotechnic systems on the space shuttle program

    NASA Technical Reports Server (NTRS)

    Lake, E. R.; Thompson, S. J.; Drexelius, V. W.

    1973-01-01

    Pyrotechnic systems, high burn rate propellant and explosive-actuated mechanisms, have been used extensively in aerospace vehicles to perform a variety of work functions, including crew escape, staging, deployment and destruction. Pyrotechnic system principles are described in this report along with their applications on typical military fighter aircraft, Mercury, Gemini, Apollo, and a representative unmanned spacecraft. To consider the possible pyrotechnic applications on the space shuttle the mechanical functions on a large commercial aircraft, similar in scale to the shuttle orbiter, were reviewed. Many potential applications exist for pyrotechnic system on the space shuttle, both in conventional short-duration functions and in longer duration and/or repetitive type gas generators.

  1. 5. PERSONNEL ROOM ON WEST SIDE OF PYROTECHNIC SHED (BLDG. ...

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

    5. PERSONNEL ROOM ON WEST SIDE OF PYROTECHNIC SHED (BLDG. 757) STORAGE LOCKER ON EAST WALL; PADDED TABLE ON SOUTH WALL. - Vandenberg Air Force Base, Space Launch Complex 3, Pyrotechnic Shed, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  2. 78 FR 29669 - Airworthiness Directives; DASSAULT AVIATION Airplanes

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-21

    ... Maintenance Procedure 26-20-2, ``Removal of Pyrotechnical Cartridge for Check/Replacement,'' dated October... Maintenance Procedure 26-20-2, ``Removal of Pyrotechnical Cartridge for Check/ Replacement,'' dated October... Maintenance Procedure 26-20-2, ``Removal of Pyrotechnical Cartridge for Check/Replacement,'' dated October...

  3. A manual for pyrotechnic design, development and qualification

    NASA Astrophysics Data System (ADS)

    Bement, Laurence J.; Schimmel, Morry L.

    1995-06-01

    Although pyrotechnic devices have been singularly responsible for the success of many of the critical mechanical functions in aerospace programs for over 30 years, ground and in-flight failures continue to occur. Subsequent investigations reveal that little or no quantitative information is available on measuring the effects on performance of system variables or on determining functional margins. Pyrotechnics are considered to be readily available and, therefore, can be managed by any subsystem in which they are applied, such as structure, propulsion, electric power, or life support. The primary purpose of this manual is to alter the concept that the use of pyrotechnics is an art and refute 'justifications' that applications do not need to be understood by providing information on pyrotechnic design, development, and qualification on an engineering basis. Included are approaches to demonstrate functional reliability with less than 10 units, how to manage pyrotechnic-unique requirements, and methods to assure that the system is properly assembled and will perform the required tasks.

  4. A manual for pyrotechnic design, development and qualification

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.; Schimmel, Morry L.

    1995-01-01

    Although pyrotechnic devices have been singularly responsible for the success of many of the critical mechanical functions in aerospace programs for over 30 years, ground and in-flight failures continue to occur. Subsequent investigations reveal that little or no quantitative information is available on measuring the effects on performance of system variables or on determining functional margins. Pyrotechnics are considered to be readily available and, therefore, can be managed by any subsystem in which they are applied, such as structure, propulsion, electric power, or life support. The primary purpose of this manual is to alter the concept that the use of pyrotechnics is an art and refute 'justifications' that applications do not need to be understood by providing information on pyrotechnic design, development, and qualification on an engineering basis. Included are approaches to demonstrate functional reliability with less than 10 units, how to manage pyrotechnic-unique requirements, and methods to assure that the system is properly assembled and will perform the required tasks.

  5. 76 FR 37643 - Safety Zone; Delta Independence Day Foundation Celebration, Mandeville Island, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... with the pyrotechnics. Unauthorized persons or vessels are prohibited from entering into, transiting... the dangers posed by the pyrotechnics used in this fireworks display, the safety zone is necessary to... fireworks launch site during loading of the pyrotechnics, and during the fireworks display. This restricted...

  6. 77 FR 43517 - Safety Zone; Flying Magazine Air Show, Lake Winnebago, Oshkosh, WI

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-07-25

    ... the hazards associated with an air show and associated pyrotechnics, which are discussed further below... associated pyrotechnics will be held over Lake Winnebago in Oshkosh WI. The Captain of the Port, Sector Lake Michigan, has determined that an aircraft executing acrobatic maneuvers with associated pyrotechnics...

  7. 33 CFR 175.130 - Visual distress signals accepted.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    .... One is required to meet the day only requirement. (3) Pyrotechnics meeting the standards noted in....130—Pyrotechnic Signal Devices Approval number under 46 CFR Device description Meets requirement for....066 Distress Signal for Boats, Red Aerial Pyrotechnic Flare Day and Night 2 3 1 These signals require...

  8. 46 CFR 160.066-13 - Technical tests.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160... signal, or; (iii) Two or more of the signals fail to project and ignite the pyrotechnic candle. (c) The... in the following manner: (1) Remove the pyrotechnic candle from the remaining three signals. (2...

  9. 75 FR 59963 - Safety Zone: Monte Foundation Firework Display, Monterey, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-29

    ... and spectators from the dangers associated with the pyrotechnics. Unauthorized persons and vessels are... be completed. Because of the dangers posed by the pyrotechnics used in this fireworks display, the... fireworks launch site during loading of the pyrotechnics, and during the fireworks display. This restricted...

  10. 76 FR 61259 - Safety Zone; Monte Foundation Fireworks Extravaganza, Aptos, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-04

    ... from the dangers associated with the pyrotechnics. Unauthorized persons or vessels are prohibited from... be completed. Because of the dangers posed by the pyrotechnics used in this fireworks display, the... the hazards associated with the pyrotechnics. The Coast Guard has granted the event sponsor a marine...

  11. 75 FR 34376 - Safety Zone; City of Pittsburg Independence Day Celebration, Pittsburg, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-17

    ... associated with the pyrotechnics. Unauthorized persons or vessels are prohibited from entering into... of the dangers posed by the pyrotechnics used in this fireworks display, the safety zone is necessary... restricted area on the waters surrounding the fireworks launch site during loading of the pyrotechnics, and...

  12. 75 FR 67618 - Safety Zone: Richardson Ash Scattering by Fireworks, San Francisco, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-11-03

    ... participants and spectators from the dangers associated with the pyrotechnics. Unauthorized persons and vessels... before the rulemaking process would be completed. Because of the dangers posed by the pyrotechnics used... restricted area on the waters surrounding the fireworks launch site during loading of the pyrotechnics, and...

  13. 75 FR 33694 - Safety Zone; Delta Independence Day Foundation Celebration, Mandeville Island, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-15

    ... safety of participants and spectators from the dangers associated with the pyrotechnics. Unauthorized... completed. Because of the immediate dangers posed by the pyrotechnics used in this fireworks display, the... pyrotechnics, during the transit of the barge to the display location, and during the fireworks display. This...

  14. 75 FR 25111 - Safety Zone; KFOG Kaboom, Fireworks Display, San Francisco, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-07

    ... associated with the pyrotechnics. Unauthorized persons or vessels are prohibited from entering into... posed by the pyrotechnics used in these fireworks displays, the safety zones are necessary to provide... effective date of this rule would expose mariners to the dangers posed by the pyrotechnics used in the...

  15. Do pyrotechnics contain radium?

    NASA Astrophysics Data System (ADS)

    Steinhauser, Georg; Musilek, Andreas

    2009-07-01

    Many pyrotechnic devices contain barium nitrate which is used as an oxidizer and colouring agent primarily for green-coloured fireworks. Similarly, strontium nitrate is used for red-coloured pyrotechnic effects. Due to their chemical similarities to radium, barium and strontium ores can accumulate radium, causing a remarkable activity in these minerals. Radium in such contaminated raw materials can be processed together with the barium or strontium, unless extensive purification of the ores was undertaken. For example, the utilization of 'radiobarite' for the production of pyrotechnic ingredients can therefore cause atmospheric pollution with radium aerosols when the firework is displayed, resulting in negative health effects upon inhalation of these aerosols. In this study, we investigated the occurrence of gamma-photon-emitting radionuclides in several pyrotechnic devices. The highest specific activities were due to K-40 (up to 20 Bq g-1, average value 14 Bq g-1). Radium-226 activities were in the range of 16-260 mBq g-1 (average value 81 mBq g-1). Since no uranium was found in any of the samples, indeed, a slight enrichment of Ra-226 in coloured pyrotechnics can be observed. Radioactive impurities stemming from the Th-232 decay chain were found in many samples as well. In the course of novel developments aiming at the 'greening' of pyrotechnics, the potential radioactive hazard should be considered as well.

  16. 76 FR 30232 - Hours of Service (HOS) of Drivers; Application of American Pyrotechnics Association (APA) for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-05-24

    ...-28043] Hours of Service (HOS) of Drivers; Application of American Pyrotechnics Association (APA) for... American Pyrotechnics Association (APA) has applied for a limited exemption from FMCSA's regulation that... exemption would apply solely to the operation of CMVs by 9 designated APA-member motor carriers in...

  17. 76 FR 37880 - Hours of Service (HOS) of Drivers; Granting of Exemption; American Pyrotechnics Association (APA)

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ...-28043] Hours of Service (HOS) of Drivers; Granting of Exemption; American Pyrotechnics Association (APA... exemption from the American Pyrotechnics Association (APA) on behalf of 9 member motor carriers seeking... such exemption'' (49 U.S.C. 31315(b)(1)). The initial APA application for waiver or exemption relief...

  18. 76 FR 37876 - Hours of Service (HOS) of Drivers; Renewal of American Pyrotechnics Association (APA) Exemption...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ...-28043] Hours of Service (HOS) of Drivers; Renewal of American Pyrotechnics Association (APA) Exemption... announces the renewal of the exemption of specified members of the American Pyrotechnics Association (APA... of this exemption in effect, designated APA-member motor carriers will maintain a level of safety...

  19. 77 FR 38378 - Hours of Service (HOS) of Drivers; Revision of Exemption; American Pyrotechnics Association (APA)

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-27

    ...-28043] Hours of Service (HOS) of Drivers; Revision of Exemption; American Pyrotechnics Association (APA... Pyrotechnics Association (APA) that were granted an exemption from FMCSA's prohibition on driving commercial...-July 8, inclusive, in 2011 and 2012. The exemption covered renewal of 53 APA-member motor carriers and...

  20. 76 FR 37012 - Safety Zone; Independence Day Fireworks Celebration for the City of Richmond, Richmond, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-24

    ... associated with the pyrotechnics. Unauthorized persons or vessels are prohibited from entering into... before the rulemaking process would be completed. Because of the dangers posed by the pyrotechnics used... expose mariners to the dangers posed by the pyrotechnics used in the fireworks display. Background and...

  1. 75 FR 19882 - Safety Zone; Benchmark Destination Corporate Party, Fireworks Display, San Francisco, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-16

    ... participants and spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels... by the pyrotechnics used in these fireworks displays, it would be contrary to the public interest to... delay in the effective date of this rule would expose mariners to the dangers posed by the pyrotechnics...

  2. 27 CFR 555.223 - Table of distances between fireworks process buildings and other specified areas.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... Consumer Fireworks and Articles Pyrotechnic, Magazines and Fireworks Shipping Buildings, and Inhabited... permitted. 1 Net weight is the weight of all pyrotechnic compositions, and exposive materials and fuse only. 2 While consumer fireworks or articles pyrotechnic in a finished state are not subject to regulation...

  3. 76 FR 33641 - Safety Zone; The Pacific Grove Feast of Lanterns, Fireworks Display, Pacific Grove, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-09

    ... ensure the safety of participants and spectators from the dangers associated with the pyrotechnics... completed. Because of the dangers posed by the pyrotechnics used in these fireworks displays, the safety... property from the hazards associated with the pyrotechnics over the water. The Coast Guard has granted the...

  4. 76 FR 37009 - Safety Zone; Jameson Beach Fourth of July Fireworks Display

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-24

    ... pyrotechnics. Unauthorized persons or vessels are prohibited from entering into, transiting through, or.... Because of the dangers posed by the pyrotechnics used in this fireworks display, the safety zone is... effective date of this rule would expose mariners to the dangers posed by the pyrotechnics used in the...

  5. 76 FR 37653 - Safety Zone; Independence Day Fireworks Celebration for the City of Martinez, Martinez, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-28

    ... the pyrotechnics. Unauthorized persons or vessels are prohibited from entering into, transiting... be completed. Because of the dangers posed by the pyrotechnics used in these fireworks displays, the... by the pyrotechnics used in the fireworks display. Basis and Purpose The City of Martinez will...

  6. 27 CFR 555.223 - Table of distances between fireworks process buildings and other specified areas.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... Consumer Fireworks and Articles Pyrotechnic, Magazines and Fireworks Shipping Buildings, and Inhabited... permitted. 1 Net weight is the weight of all pyrotechnic compositions, and exposive materials and fuse only. 2 While consumer fireworks or articles pyrotechnic in a finished state are not subject to regulation...

  7. 75 FR 29658 - Safety Zone; America's Discount Tire 50th Anniversary, Fireworks Display, South Lake Tahoe, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-27

    ... participants and spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels... process before the event occurs. Because of the dangers posed by the pyrotechnics used in these fireworks... fireworks launch site during loading of the pyrotechnics, and during the fireworks displays. This restricted...

  8. 77 FR 50919 - Safety Zone: Wedding Reception Fireworks at Pier 24, San Francisco, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-08-23

    ... mariners and spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels... could be completed. Because of the dangers posed by the pyrotechnics used in this fireworks display, the... property from the hazards associated with the pyrotechnics. C. Discussion of the Final Rule The Coast Guard...

  9. 75 FR 25879 - Notice of Proposed Supplementary Rules Concerning Fireworks on Public Land in Colorado

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-05-10

    ... thirty milligrams of explosive material, aerial shells containing more than forty grams of pyrotechnic..., total pyrotechnic composition not to exceed seventy-five grams each for a single tube or, when more than... grams; (II) Cone fountains, total pyrotechnic composition not to exceed fifty grams each for a single...

  10. Apollo Spacecraft and Saturn V Launch Vehicle Pyrotechnics/Explosive Devices

    NASA Technical Reports Server (NTRS)

    Interbartolo, Michael

    2009-01-01

    The Apollo Mission employs more than 210 pyrotechnic devices per mission.These devices are either automatic of commanded from the Apollo spacecraft systems. All devices require high reliability and safety and most are classified as either crew safety critical or mission critical. Pyrotechnic devices have a wide variety of applications including: launch escape tower separation, separation rocket ignition, parachute deployment and release and electrical circuit opening and closing. This viewgraph presentation identifies critical performance, design requirements and safety measures used to ensure quality, reliability and performance of Apollo pyrotechnic/explosive devices. The major components and functions of a typical Apollo pyrotechnic/explosive device are listed and described (initiators, cartridge assemblies, detonators, core charges). The presentation also identifies the major locations and uses for the devices on: the Command and Service Module, Lunar Module and all stages of the launch vehicle.

  11. Pyrotechnic hazards classification and evaluation program. Phase 3, segments 1-4: Investigation of sensitivity test methods and procedures for pyrotechnic hazards evaluation and classification, part A

    NASA Technical Reports Server (NTRS)

    1971-01-01

    The findings, conclusions, and recommendations relative to the investigations conducted to evaluate tests for classifying pyrotechnic materials and end items as to their hazard potential are presented. Information required to establish an applicable means of determining the potential hazards of pyrotechnics is described. Hazard evaluations are based on the peak overpressure or impulse resulting from the explosion as a function of distance from the source. Other hazard classification tests include dust ignition sensitivity, impact ignition sensitivity, spark ignition sensitivity, and differential thermal analysis.

  12. 77 FR 67797 - Takes of Marine Mammals Incidental to Specified Activities; Taking Marine Mammals Incidental to...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-14

    ... averaged units rather than by peak pressures. The use of biosonics, pyrotechnics, and zon guns may result... still preventing birds from settling on the island. Biosonics, pyrotechnics, and zon guns will be... personnel are available, the USFWS will also monitor sound levels of biosonics, pyrotechnics, and zon guns...

  13. 27 CFR 555.222 - Table of distances between fireworks process buildings and between fireworks process and...

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... weight is the weight of all pyrotechnic compositions, and explosive materials and fuse only. 2 The..., the distances must be doubled. 3 While consumer fireworks or articles pyrotechnic in a finished state... pyrotechnic are being processed shall meet these requirements. 4 A maximum of 500 pounds of in-process...

  14. 78 FR 38830 - Safety Zone; Execpro Services Fireworks Display, Lake Tahoe, Incline Village, NV

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-28

    ... spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels are prohibited... pyrotechnics used in this fireworks display, the safety zone is necessary to provide for the safety of event... loading, transit and arrival of the pyrotechnics from the loading site to the launch site and until the...

  15. 76 FR 37007 - Safety Zone; Stockton Ports Baseball Club Fourth of July Fireworks Display, Stockton, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-24

    ... and spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels are... the dangers posed by the pyrotechnics used in this fireworks display, the safety zone is necessary to... in the effective date of this rule would expose mariners to the dangers posed by the pyrotechnics...

  16. 75 FR 81854 - Safety Zone; New Year's Celebration for the City of San Francisco, Fireworks Display, San...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-29

    ... the loading, transit, and arrival of the pyrotechnics, and will extend 1,000 feet from the nearest... participants and spectators from the dangers associated with the pyrotechnics. Unauthorized persons or vessels... process would be completed. Because of the dangers posed by the pyrotechnics used in these fireworks...

  17. 27 CFR 555.222 - Table of distances between fireworks process buildings and between fireworks process and...

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... weight is the weight of all pyrotechnic compositions, and explosive materials and fuse only. 2 The..., the distances must be doubled. 3 While consumer fireworks or articles pyrotechnic in a finished state... pyrotechnic are being processed shall meet these requirements. 4 A maximum of 500 pounds of in-process...

  18. 78 FR 60766 - Clarification on Fireworks Policy Regarding Approvals or Certifications for Specialty Fireworks...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-10-02

    ... fireworks device is a fire truck with 10 tubes, 2 grams per tube, for a total pyrotechnic weight of 20 grams... fusing; 3. May not exceed 10 fiberboard or plastic tubes per device; 4. May not contain more than 2 grams of pyrotechnic composition per tube, and not more than 20 grams pyrotechnic composition in the...

  19. A study of the feasibility of directly applying gas generator systems to space shuttle mechanical functions

    NASA Technical Reports Server (NTRS)

    Lake, E. R.

    1974-01-01

    This study examined the current status and potential application of pyrotechnic gas generators and energy convertors for the space shuttle program. While most pyrotechnic devices utilize some form of linear actuation, only limited use of rotary actuators has been observed. This latter form of energy conversion, using a vane-type actuator as optimum, offers considerable potential in the area of servo, as well as non-servo systems, and capitalizes on a means of providing prolonged operating times. Pyrotechnic devices can often be shown to provide the optimum means of attaining a truly redundant back-up to a primary, non-pyrotechnic system.

  20. Development of low-shock pyrotechnic separation nuts. [design performance of flight type nuts

    NASA Technical Reports Server (NTRS)

    Bement, L. J.; Neubert, V. H.

    1973-01-01

    Performance demonstrations and comparisons were made on six flight type pyrotechnic separation nut designs, two of which are standard designs in current use, and four of which were designed to produce low shock on actuation. Although the shock performances of the four low shock designs are considerably lower than the standard designs, some penalties may be incurred in increased volume, weight, or complexity. These nuts, and how they are installed, can significantly influence the pyrotechnic shock created in spacecraft structures. A high response monitoring system has been developed and demonstrated to provide accurate performance comparisons for pyrotechnic separation nuts.

  1. Metal-Element Compounds of Titanium, Zirconium, and Hafnium as Pyrotechnic Fuels

    DTIC Science & Technology

    2015-05-04

    including ceramic materials in this role has been far less common. Following the development of boron carbide-based pyrotechnics in our laboratories, we...ameliorate these problems. Commercially available group 4 compounds containing hydrogen, boron , carbon, nitrogen, silicon, and phosphorus were obtained for...predicted behavior suggests that these compounds may be useful for a variety of pyrotechnic applications. 1. INTRODUCTION The recent use of boron

  2. Survey of Military Pyrotechnics

    DTIC Science & Technology

    1991-05-24

    ignition of pyrotechnics. Both diode and gas lasers are being evaluated to initiate combustion of compositions such as zirconium-potassium perchlorate...Research on and simulation of the combustion process is being conducted. An air-gun is described which is used to ground test the performance of flares...an acceptable level. Magnesium Powder - Magnesium is one of the most common fuels used in pyrotechnic compositions. Although it has a high combustion

  3. Pyrotechnic system failures: Causes and prevention

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.

    1988-01-01

    Although pyrotechnics have successfully accomplished many critical mechanical spacecraft functions, such as ignition, severance, jettisoning and valving (excluding propulsion), failures continue to occur. Provided is a listing of 84 failures of pyrotechnic hardware with completed design over a 23-year period, compiled informally by experts from every NASA Center, as well as the Air Force Space Division and the Naval Surface Warfare Center. Analyses are presented as to when and where these failures occurred, their technical source or cause, followed by the reasons why and how these kinds of failures persist. The major contributor is a fundamental lack of understanding of the functional mechanisms of pyrotechnic devices and systems, followed by not recognizing pyrotechnics as an engineering technology, insufficient manpower with hands-on experience, too few test facilities, and inadequate guidelines and specifications for design, development, qualification and acceptance. Recommendations are made on both a managerial and technical basis to prevent failures, increase reliability, improve existing and future designs, and develop the technology to meet future requirements.

  4. 27 CFR 555.201 - General.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... fireworks, pyrotechnic compositions, and explosive materials used in assembling fireworks and articles pyrotechnic. (e) The provisions of § 555.202(a) classifying flash powder and bulk salutes as high explosives...

  5. 27 CFR 555.201 - General.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... fireworks, pyrotechnic compositions, and explosive materials used in assembling fireworks and articles pyrotechnic. (e) The provisions of § 555.202(a) classifying flash powder and bulk salutes as high explosives...

  6. 49 CFR 175.9 - Special aircraft operations.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... similar devices carried during a parachute operation. (3) Smoke grenades, flares, and pyrotechnic devices... installation accommodating the smoke grenades, flares, or pyrotechnic devices on the aircraft must be approved...

  7. Penetration of pyrotechnic effects with SWIR laser gated viewing in comparison to VIS and thermal IR bands

    NASA Astrophysics Data System (ADS)

    Göhler, Benjamin; Lutzmann, Peter

    2016-10-01

    In this paper, the potential capability of short-wavelength infrared laser gated-viewing for penetrating the pyrotechnic effects smoke and light/heat has been investigated by evaluating data from conducted field trials. The potential of thermal infrared cameras for this purpose has also been considered and the results have been compared to conventional visible cameras as benchmark. The application area is the use in soccer stadiums where pyrotechnics are illegally burned in dense crowds of people obstructing visibility of stadium safety staff and police forces into the involved section of the stadium. Quantitative analyses have been carried out to identify sensor performances. Further, qualitative image comparisons have been presented to give impressions of image quality during the disruptive effects of burning pyrotechnics.

  8. 46 CFR 160.066-11 - Approval procedures.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-11 Approval procedures. (a) Red aerial pyrotechnic flare distress signals are approved under the...

  9. 46 CFR 160.066-9 - Labeling.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...: (1) The manufacturer's name, (2) The designed burning time of the pyrotechnic candle(s), (3) The...

  10. 46 CFR 160.066-11 - Approval procedures.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-11 Approval procedures. (a) Red aerial pyrotechnic flare distress signals are approved under the...

  11. 46 CFR 160.066-9 - Labeling.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...: (1) The manufacturer's name, (2) The designed burning time of the pyrotechnic candle(s), (3) The...

  12. Problem Definition Studies on Potential Environmental Pollutants. 6. Preliminary Assessment of Environmental Effects of Seven Substances Used in Pyrotechnic Compositions at Pine Bluff Arsenal

    DTIC Science & Technology

    1979-11-01

    on reveryo if nec.,ary and identify by block number) FIELD GROUP SUB-GROUP Benzanthrone, 1-Methylaminoanthraquinone, Pyrotechnics 24 03 .uramine, 1,4...necessary and identify by block number) Procurement data for the period 1965-1975 are used to estimate soil contaminatior by pyrotechnic and smoke...Project Manager for Chemical Demilitarization and Installation Restoration, has identified an initial list of substances (Table 1) requiring assessment

  13. Pyrotechnic shock: A literature survey of the Linear Shaped Charge (LSC)

    NASA Technical Reports Server (NTRS)

    Smith, J. L.

    1984-01-01

    Linear shaped charge (LSC) literature for the past 20 years is reviewed. The following topics are discussed: (1) LSC configuration; (2) LSC usage; (3) LSC induced pyroshock; (4) simulated pyrotechnic testing; (5) actual pyrotechnic testing; (6) data collection methods; (7) data analysis techniques; (8) shock reduction methods; and (9) design criteria. Although no new discoveries have been made in LSC research, charge shapes are improved to allow better cutting performance, testing instrumentation is refined, and some new explosives, for use in LSC, are formulated.

  14. 46 CFR 160.066-1 - Type.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-1 Type. (a) Red aerial pyrotechnic distress signals specified by this subpart must be either self-contained or...

  15. 14 CFR 25.1199 - Extinguishing agent containers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... discharge. (e) If a pyrotechnic capsule is used to discharge the extinguishing agent, each container must be installed so that temperature conditions will not cause hazardous deterioration of the pyrotechnic capsule...

  16. 14 CFR 25.1199 - Extinguishing agent containers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... discharge. (e) If a pyrotechnic capsule is used to discharge the extinguishing agent, each container must be installed so that temperature conditions will not cause hazardous deterioration of the pyrotechnic capsule...

  17. 48 CFR 252.223-7002 - Safety precautions for ammunition and explosives.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... propellants and explosives, pyrotechnics, incendiaries and smokes in the following forms: (i) Bulk, (ii... components containing no explosives, propellants, or pyrotechnics; (ii) Flammable liquids; (iii) Acids; (iv...

  18. 48 CFR 252.223-7002 - Safety precautions for ammunition and explosives.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... propellants and explosives, pyrotechnics, incendiaries and smokes in the following forms: (i) Bulk, (ii... components containing no explosives, propellants, or pyrotechnics; (ii) Flammable liquids; (iii) Acids; (iv...

  19. 46 CFR 160.066-1 - Type.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-1 Type. (a) Red aerial pyrotechnic distress signals specified by this subpart must be either self-contained or...

  20. 14 CFR 23.1199 - Extinguishing agent containers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... pyrotechnic capsule is used to discharge the extinguishing agent, each container must be installed so that temperature conditions will not cause hazardous deterioration of the pyrotechnic capsule. [Amdt. 23-34, 52 FR...

  1. 14 CFR 23.1199 - Extinguishing agent containers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... pyrotechnic capsule is used to discharge the extinguishing agent, each container must be installed so that temperature conditions will not cause hazardous deterioration of the pyrotechnic capsule. [Amdt. 23-34, 52 FR...

  2. 49 CFR 175.9 - Exceptions for special aircraft operations.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... parachute operation. (c) Smoke grenades, flares, and pyrotechnic devices affixed to aircraft during any... the smoke grenades, flares, or pyrotechnic devices on the aircraft must be approved for its intended...

  3. Functional Performance of Pyrovalves

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.

    1996-01-01

    Following several flight and ground test failures of spacecraft systems using single-shot, 'normally closed' pyrotechnically actuated valves (pyrovalves), a government/industry cooperative program was initiated to assess the functional performance of five qualified designs. The goal of the program was to improve performance-based requirements for the procurement of pyrovalves. Specific objectives included the demonstration of performance test methods, the measurement of 'blowby' (the passage of gases from the pyrotechnic energy source around the activating piston into the valve's fluid path), and the quantification of functional margins for each design. Experiments were conducted in-house at NASA on several units each of the five valve designs. The test methods used for this program measured the forces and energies required to actuate the valves, as well as the energies and the pressures (where possible) delivered by the pyrotechnic sources. Functional performance ranged widely among the designs. Blowby cannot be prevented by o-ring seals; metal-to-metal seals were effective. Functional margin was determined by dividing the energy delivered by the pyrotechnic sources in excess to that required to accomplish the function by the energy required for that function. All but two designs had adequate functional margins with the pyrotechnic cartridges evaluated.

  4. The First NASA Aerospace Pyrotechnic Systems Workshop

    NASA Technical Reports Server (NTRS)

    St.cyr, William W. (Compiler)

    1993-01-01

    Papers from the conference proceedings are presented, and they are grouped by the following sessions: pyrotechnically actuated systems, laser initiation, and modeling and analysis. A fourth session, a panel discussion and open forum, concluded the workshop.

  5. Hazard-Free Pyrotechnic Simulator

    NASA Technical Reports Server (NTRS)

    Mcalister, William B., Jr.

    1988-01-01

    Simulator evaluates performance of firing circuits for electroexplosive devices (EED's) safely and inexpensively. Tests circuits realistically when pyrotechnic squibs not connected and eliminates risks of explosions. Used to test such devices as batteries where test conditions might otherwise degrade them.

  6. 76 FR 37002 - Safety Zone; Central Astoria Independence Celebration Fireworks Event, Wards Island, NY

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-24

    ... the fireworks display. Due to the dangers posed by the pyrotechnics used in this fireworks display... and would expose spectators, vessels, and other property to the hazards associated with pyrotechnics...

  7. Pyrotechnic modeling for the NSI and pin puller

    NASA Technical Reports Server (NTRS)

    Powers, Joseph M.; Gonthier, Keith A.

    1993-01-01

    A discussion concerning the modeling of pyrotechnically driven actuators is presented in viewgraph format. The following topics are discussed: literature search, constitutive data for full-scale model, simple deterministic model, observed phenomena, and results from simple model.

  8. Pyrotechnic hazards classification and evaluation program. Phase 2, segment 3: Test plan for determining hazards associated with pyrotechnic manufacturing processes

    NASA Technical Reports Server (NTRS)

    1971-01-01

    A comprehensive test plan for determining the hazards associated with pyrotechnic manufacturing processes is presented. The rationale for each test is based on a systematic analysis of historical accounts of accidents and a detailed study of the characteristics of each manufacturing process. The most hazardous manufacturing operations have been determined to be pressing, mixing, reaming, and filling. The hazard potential of a given situation is evaluated in terms of the probabilities of initiation, communication, and transition to detonation (ICT). The characteristics which affect the ICT probabilities include the ignition mechanisms which are present either in normal or abnormal operation, the condition and properties of the pyrotechnic material, and the configuration of the processing equipment. Analytic expressions are derived which describe the physical conditions of the system, thus permitting a variety of processes to be evaluated in terms of a small number of experiments.

  9. 75 FR 39163 - Safety Zone; Illinois River, Mile 119.7 to 120.3

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-07-08

    ... completed. Because of the dangers posed by the pyrotechnics used in this fireworks display, the safety zone... the dangers posed by the pyrotechnics used in this fireworks display, the safety zone is necessary to...

  10. 76 FR 46753 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to Coastal Commercial...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-08-03

    ... the sanctuary. The MBNMS has determined that debris fallout (i.e., spent pyrotechnic materials) from... permitted by MBNMS may be found in MBNMS' application, in MBNMS' Assessment of Pyrotechnic Displays and...

  11. Pyrotechnic device provides one-shot heat source

    NASA Technical Reports Server (NTRS)

    Haller, H. C.; Lalli, V. R.

    1968-01-01

    Pyrotechnic heater provides a one-shot heat source capable of creating a predetermined temperature around sealed packages. It is composed of a blend of an active chemical element and another compound which reacts exothermically when ignited and produces fixed quantities of heat.

  12. Functional performance of pyrovalves

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.

    1996-01-01

    Following several flight and ground test failures of spacecraft systems using single-shot, 'normally closed' pyrotechnically actuated valves (pyrovalves), a Government/Industry cooperative program was initiated to assess the functional performance of five qualified designs. The goal of the program was to provide information on functional performance of pyrovalves to allow users the opportunity to improve procurement requirements. Specific objectives included the demonstration of performance test methods, the seating; these gases/particles entered the fluid path of measurement of 'blowby' (the passage of gases from the pyrotechnic energy source around the activating piston into the valve's fluid path), and the quantification of functional margins for each design. Experiments were conducted at NASA's Langley Research Center on several units for each of the five valve designs. The test methods used for this program measured the forces and energies required to actuate the valves, as well as the energies and the pressures (where possible) delivered by the pyrotechnic sources. Functional performance ranged widely among the designs. Blowby cannot be prevented by o-ring seals; metal-to-metal seals were effective. Functional margin was determined by dividing the energy delivered by the pyrotechnic sources in excess to that required to accomplish the function by the energy required for that function. Two of the five designs had inadequate functional margins with the pyrotechnic cartridges evaluated.

  13. WSTF Propulsion and Pyrotechnics Corrective Action Test Program Status-2000

    NASA Technical Reports Server (NTRS)

    Saulsberry, R.; Ramirez, J.; Julien, H. L.; Hart, M.; Smith, W.; Bement, L.; Meagher, N. E.

    2000-01-01

    Extensive propulsion and pyrotechnic testing has been in progress at the NASA Johnson Space Center White Sands Test Facility (WSTF) since 1995. This started with the Mars Observer Propulsion and Pyrotechnics Corrective Action Test Program (MOCATP). The MOCATP has concluded, but extensive pyrovalve testing and research and development has continued at WSTF. The capability to accurately analyze and measure pyrovalve combustion product blow-by, evaluate propellant explosions initiated by blow-by, and characterize pyrovalve operation continues to be used and improved. This paper contains an overview of testing since MOCATP inception, but focuses on accomplishments since the status was last reported at the 35th Joint Propulsion Conference, June, 1999. This new activity includes evaluation of 3/8 inch Conax pyrovalves; development and testing of advanced pyrovalve technologies; investigation of nondestructive evaluation techniques to inspect pyrotechnically induced hydrazine explosions both through testing and modeling. Data from this collection of projects are now being formatted into a pyrovalve applications and testing handbook and consensus standard to benefit pyrovalve users and spacecraft designers. The handbook is briefly described here and in more detail in a separate paper. To increase project benefit, pyrovalve manufacturers are encouraged to provide additional valves for testing and consideration, and feedback is encouraged in all aspects of the pyrotechnic projects.

  14. 78 FR 34577 - Safety Zone; Ad Club's 100th Anniversary Gala Fireworks Display, Boston Inner Harbor, Boston, MA.

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-10

    ... posed by the pyrotechnics used in this fireworks display, the safety zone is necessary to provide for... would expose spectators, vessels and other property to the hazards associated with pyrotechnics used in...

  15. Fully redundant mechanical release actuator

    NASA Technical Reports Server (NTRS)

    Lucy, Melvin H. (Inventor)

    1987-01-01

    A system is described for performing a mechanical release function exhibiting low shock. This system includes two pyrotechnic detents fixed mounted in opposing axial alignment within a cylindrical housing having two mechanical bellows. Two mechanical bellow assemblies, each having one end hermetically bonded to the housing and the other to the respective actuator pin extending from either end of the housing, ensure that all outgassing and contamination from the operation of the pyrotechnic devices will be contained within the housing and bellows. The pin on one end of the assembly is fixed mounted and supported, via a bolt or ball-and-socket joint so that when the charge corresponding to that pin ignites, the entire assembly will exhibit rectilinear movement, including the opposing pin providing the unlatching motion. The release detent pin is supported by a linear bearing and when its corresponding pyrotechnic charge ignites the pin is retracted within the housing producing the same unlatching motion without movement of the entire assembly, thus providing complete mechanical, electrical and pyrotechnic redundancy for the unlatching pin.

  16. Autoignition Chamber for Remote Testing of Pyrotechnic Devices

    NASA Technical Reports Server (NTRS)

    Harrington, Maureen L.; Steward, Gerald R.; Dartez, Toby W.

    2009-01-01

    The autoignition chamber (AIC) performs by remotely heating pyrotechnic devices that can fit the inner diameter of the tube furnace. Two methods, a cold start or a hot start, can be used with this device in autoignition testing of pyrotechnics. A cold start means extending a pyrotechnic device into the cold autoignition chamber and then heating the device until autoignition occurs. A hot start means heating the autoignition chamber to a specified temperature, and then extending the device into a hot autoignition chamber until autoignition occurs. Personnel are remote from the chamber during the extension into the hot chamber. The autoignition chamber, a commercially produced tubular furnace, has a 230-V, single-phase, 60-Hz electrical supply, with a total power output of 2,400 W. It has a 6-in. (15.2-cm) inner diameter, a 12-in. (30.4-cm) outer diameter and a 12-in.- long (30.4-cm), single-zone, solid tubular furnace (element) capable of heating to temperatures up to 2,012 F (1,100 C) in air.

  17. Heavy metals from pyrotechnics in New Years Eve snow

    NASA Astrophysics Data System (ADS)

    Steinhauser, Georg; Sterba, Johannes H.; Foster, Michaela; Grass, Friedrich; Bichler, Max

    Pyrotechnics and fireworks cause pollution with barium aerosols, which is a result of the utilization of barium nitrate as a combined pyrotechnic oxidizer and coloring agent. In this study, the washing-out of barium-rich aerosols by snowflakes during the New Years Eve celebrations in an Austrian village in the Alps has been investigated. It could be shown that the fireworks caused an increase in the barium concentration in snow of up to a factor of 580 compared to the blank value. An increase of the concentrations of strontium and occasionally arsenic in snow was also observed. The geographic distribution of the pyrotechnic combustion products on this snowy evening was restricted to a relatively small area and even in a very local scale, the variations in the concentrations were remarkable. Post-firework snow from the summits of nearby located mountains was found to be as clean as pre-firework snow. However, snow that was visibly contaminated with smoke residues contained exorbitant concentrations of Ba, K, Sr, and Fe.

  18. Tethered Pyrotechnic Apparatus for Acquiring a Ground Sample

    NASA Technical Reports Server (NTRS)

    Jones, Jack; Zimmerman, Wayne; Wu, Jiunn Jenq; Badescu, Mircea; Sherrit, Stewart

    2009-01-01

    A proposed alternative design for the balloon-borne ground-sampling system described in the immediately preceding article would not rely on free fall to drive a harpoonlike sample-collecting device into the ground. Instead, the harpoon-like sample-collecting device would be a pyrotechnically driven, tethered projectile. The apparatus would include a tripod that would be tethered to the gondola. A gun for shooting the projectile into the ground would be mounted at the apex of the tripod. The gun would include an electronic trigger circuit, a chamber at the breech end containing a pyrotechnic charge, and a barrel. A sabot would be placed in the barrel just below the pyrotechnic charge, and the tethered projectile would be placed in the barrel just below the sabot. The tripod feet would be equipped with contact sensors connected to the trigger circuit. In operation, the tripod would be lowered to the ground on its tether. Once contact with the ground was detected by the sensors on all three tripod feet, the trigger circuit would fire the pyrotechnic charge to drive the projectile into the ground. (Requiring contact among all three tripod feet and the ground would ensure that the projectile would be fired into the ground, rather than up toward the gondola or the balloon.) The tethered projectile would then be reeled back up to the gondola for analysis of the sample.

  19. A pilot study using a novel pyrotechnically driven prototype applicator for epidermal powder immunization in piglets.

    PubMed

    Engert, Julia; Anamur, Cihad; Engelke, Laura; Fellner, Christian; Lell, Peter; Henke, Stefan; Stadler, Julia; Zöls, Susanne; Ritzmann, Mathias; Winter, Gerhard

    2018-04-20

    Epidermal powder immunization (EPI) is an alternative technique to the classical immunization route using needle and syringe. In this work, we present the results of an in vivo pilot study in piglets using a dried influenza model vaccine which was applied by EPI using a novel pyrotechnically driven applicator. A liquid influenza vaccine (Pandemrix ® ) was first concentrated by tangential flow filtration and hemagglutinin content was determined by RP-HPLC. The liquid formulation was then transformed into a dry powder by collapse freeze-drying and subsequent cryo-milling. The vaccine powder was attached to a membrane of a novel pyrotechnical applicator using oily adjuvant components. Upon actuation of the applicator, particles were accelerated to high speed as determined by a high-speed camera setup. Piglets were immunized twice using either the novel pyrotechnical applicator or classical intramuscular injection. Blood samples of the animals were collected at various time points and analyzed by enzyme-linked immunosorbent assay. Our pilot study shows that acceleration of a dried vaccine powder to supersonic speed using the pyrotechnical applicator is possible and that the speed and impact of the particles is sufficient to breach the stratum corneum of piglet skin. Importantly, the administration of the dry vaccine powder resulted in measurable anti-H1N1 antibody titres in vivo. Copyright © 2018 Elsevier B.V. All rights reserved.

  20. Pyrotechnic hazards classification and evaluation program. Electrostatic vulnerability of the E8 and XM15/XM165 clusters, phase 1

    NASA Technical Reports Server (NTRS)

    1970-01-01

    A survey of the electrostatic vulnerability of explosive manufacturing plants and recommendations for reducing the vulnerability are discussed. During the course of the investigations, the XM15/XM165 and the E8 launcher were shown to be susceptible to electrostatic ignition. The pyrotechnic hazard of prime concern associated with electrostatics is that of the spark which can be generated. The heat, shock, and ionization produced by the spark can cause ignition of pyrotechnics. However, as a result of the initial ignition tests (XM15 fuse train), changes have been incorporated to make the fusing system relatively safe from premature electrostatic activation.

  1. A High-efficiency, Small, Solid-state Laser for Pyrotechnic Ignition

    NASA Technical Reports Server (NTRS)

    Yang, L. C.; Menichelli, V. J.

    1973-01-01

    A completely self-contained, small, neodymium laser has been designed and demonstrated for use in a pyrotechnic ignition system. A nominal 16 J of laser energy (1.06 micron wavelength, 1-ms duration) was achieved in a rectangular 10.5-X 15.1-X 25.4-cm package weighting 5.14 kg. This high energy-to-weight ratio is encouraging for laser applications in which specific energy efficiency (energy per unit weight or volume) is important. The laser design concepts are described, and some results on pyrotechnic ignition are given. Some details on a laser currently under construction, which will be 1/8 the size of the above laser, are included.

  2. PERSPECTIVE: Fireworks and radioactivity

    NASA Astrophysics Data System (ADS)

    Breitenecker, Katharina

    2009-09-01

    Katharina Breitenecker Fireworks, the one and only amongst all other pyrotechnic applications, have pleased the hearts and minds of billions of people all over the world for almost 1000 years. Even though pyrotechnics were originally developed in order to fulfil the needs of military purposes, fireworks began to form a unique part of the cultural heritage of many countries, presumably starting in ancient China during the Song Dynasty (960-1280 AD). Festivities like New Year's Eve, national holidays or activities like music festivals and parish fairs are crowned by a firework display. Fireworks have traditionally been associated with Independence Day celebrations, like 4 July in the United States, Guy Fawkes' Night (5 November) in Britain, or Bastille Day (14 July) in France. Much of Chinese culture is associated with the use of firecrackers to celebrate the New Year and other important occasions. The fascination of fireworks and firecrackers is due to the brilliant colours and booming noises, which have a universal appeal to our basic senses [1]. The basic components of any traditional civil firework is black powder, a mixture of about 75% potassium nitrate, 15% charcoal, and about 10% sulfur [2]. Without the addition of a colouring agent, the fuel would provide an almost white light. Therefore, several metal salts can be added to cause colourful luminescence upon combustion. In general barium is used to obtain a green coloured flame, strontium for red, copper for blue and sodium for yellow [2, 3]. The use of pyrotechnics has raised issues pertaining to health concerns. The health aspects are not only restricted to injuries by accidental ignition of certain devices. Moreover, several recent works identified fireworks and pyrotechnics as causing environmental pollution, which might result in a potential hazard concerning health aspects. The fundamental problem in this respect is that all chemicals used are dispersed in the environment by combustion. This includes both reaction products and unburnt constituents of a pyrotechnic mixture. One major environmental concern in pyrotechnics focuses on the emission of heavy metals. This is the topic discussed in the article by Georg Steinhauser and Andreas Musilek in this issue [4]. A possible interrelationship between respiratory effects and fireworks emissions of barium-rich aerosols was also raised last year [5]. In recent years the potential hazard of naturally occurring radioactive material has become of importance to the scientific community. Naturally occurring radionuclides can be of terrestrial or cosmological origin. Terrestrial radionuclides were present in the presolar cloud that later contracted in order to build our solar system. These radionuclides—mainly heavy metals—and their non-radioactive isotopes are nowadays fixed in the matrix of the Earth's structure. Usually, their percentage is quite small compared to their respective stable isotopes—though there are exceptions like in the case of radium. The problem with environmental pollution due to naturally occurring radioactive material begins when this material is concentrated due to mining and milling, and later further processed [6]. Environmental pollution due to radioactive material goes back as far as the Copper and Iron Ages, when the first mines were erected in order to mine ores (gold, silver, copper, iron, etc), resulting in naturally occurring radioactive material being set free with other dusts into the atmosphere. So where is the link between pyrotechnics and radioactivity? In this article presented by Georg Steinhauser and Andreas Musilek [4], the pyrotechnic ingredients barium nitrate and strontium nitrate are explored with respect to their chemical similarities to radium. The fundamental question, therefore, was whether radium can be processed together with barium and strontium. If so, the production and ignition of these pyrotechnic ingredients could cause atmospheric pollution with radium aerosols, resulting in potential negative health effects, unless an extensive purification of the ores is undertaken. From the environmental and toxicological point of view, the formation of barium-rich aerosols following the display of fireworks is a problem. The barium compounds released are mainly in a bioavailable form. Considering the chemical similarities of barium and strontium to radium, the potential hazard of fireworks due to liberated radionuclides might be of interest. Ores and compounds used for pyrotechnic devices are usually purified only to the grade that is necessary for the intended effect. Thus, fireworks can contain traces of heavy metals which do not have a pyrotechnic function [5, 7, 8]. The incorporation, and thus, the inhalation of α-emitters (such as 226Ra) is a major health issue in human radiation protection. In order to examine the potential hazard Georg Steinhauser and Andreas Musilek investigated this topic. Although the specific radium activities were relatively low in the investigated samples, Steinhauser and Musilek showed that radium is significantly enriched in pyrotechnics. This fact gives no reason why people should not attend firework displays or should not set off their own fireworks on New Year's Eve. Rather, it is now the authorities' turn to take care of this topic. What if highly active radiobarite was used as a raw material for the production of pyrotechnic indoor devices? This would definitely cause unexpected health issues. Now that the problem is identified, the authorities have to ensure that the exemption limits are not exceeded. Today, public opinion is going more and more in the direction of using eco-friendly products. A lot of products have been shown to have potential negative health effects and are therefore now produced in safer and more eco-friendly forms than they used to be a few years ago. Thus, Georg Steinhauser and Andreas Musilek demonstrated that pyrotechnics do contain a certain amount of radioactive material—so why not make pyrotechnics safer, more eco-friendly and 'greener'? References [1] Plimpton G 1984 Fireworks: A History and Celebration (New York: Doubleday) [2] Russell M S 2000 The Chemistry of Fireworks (Cambridge: Royal Society of Chemistry) [3] Steinhauser G and Klapötke T M 2008 'Green' pyrotechnics: a chemist's challenge Angew. Chem. Int. Ed. 47 3330-47 [4] Steinhauser G and Musilek A 2009 Do pyrotechnics contain radium? Environ. Res. Lett. 4 034006 [5] Steinhauser G, Sterba J H, Foster M, Grass F and Bichler M 2008 Heavy metals from pyrotechnics in New Year's Eve snow Atmos. Environ. 42 8616-22 [6] Cooper J R, Randle K and Sokhi R S 2003 Radioactive Releases in the Environment—Impact and Assessment (Chichester: Wiley) [7] Smith R M and Dinh V-D 1975 Changes in forced expiration flow due to air pollution from fireworks Environ. Res. 9 321-31 [8] Bach W, Dickinson L, Weiner B and Costello G 1972 Some adverse health effects due to air pollution from fireworks Hawaii Med. J. 31 459-65

  3. 78 FR 26690 - Hours of Service (HOS) of Drivers; Application for Renewal and Expansion of American Pyrotechnics...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-07

    ... Association (APA) Exemption From the 14-Hour Rule During Independence Day Celebrations AGENCY: Federal Motor... exemption; request for comments. SUMMARY: The American Pyrotechnics Association (APA) has requested a renewal of its exemption for 48 APA member-companies from FMCSA's regulation that drivers of commercial...

  4. A chamber investigation of the IR and visible wavelength obscuration properties of pyrotechnically generated smokes

    NASA Astrophysics Data System (ADS)

    Hanley, J. T.; Mack, E. J.

    1985-05-01

    The overall objective of the program is the development of an effective screening agent to both visible and IR wavelengths utilizing pyrotechnically-generated hygroscopic aerosol. In pursuit of an effective IR wavelength screen and an increased understanding of the particle formation mechanisms and resultant size distribution, the primary objective of this year's effort was to evaluate the influence of an energetic binder (GAP) on the performance of two pyrotechnics, one which produced a KCL aerosol, the other a mixed aerosol, the other a mixed aerosol of MgCl2 and carbon. Comparison tests were run, in Calspan's 600 cu m test chamber, in which the performance of the energetic vs. non-energetic pyrotechnics was compared in terms of mass yield, payload mass extinction coefficient, aerosol decay rate and size distribution. A secondary objective of limited scope was to investigate the potential of using IR absorbing surface active agents to coat the smoke aerosol so as to enhance the smoke's IR wavelength absorption as well as inhibit subsequent aerosol evaporation upon exposure to decreasing humidity.

  5. Determining Functional Reliability of Pyrotechnic Mechanical Devices

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.; Multhaup, Herbert A.

    1997-01-01

    This paper describes a new approach for evaluating mechanical performance and predicting the mechanical functional reliability of pyrotechnic devices. Not included are other possible failure modes, such as the initiation of the pyrotechnic energy source. The requirement of hundreds or thousands of consecutive, successful tests on identical components for reliability predictions, using the generally accepted go/no-go statistical approach routinely ignores physics of failure. The approach described in this paper begins with measuring, understanding and controlling mechanical performance variables. Then, the energy required to accomplish the function is compared to that delivered by the pyrotechnic energy source to determine mechanical functional margin. Finally, the data collected in establishing functional margin is analyzed to predict mechanical functional reliability, using small-sample statistics. A careful application of this approach can provide considerable cost improvements and understanding over that of go/no-go statistics. Performance and the effects of variables can be defined, and reliability predictions can be made by evaluating 20 or fewer units. The application of this approach to a pin puller used on a successful NASA mission is provided as an example.

  6. Piezoelectrically Initiated Pyrotechnic Igniter

    NASA Technical Reports Server (NTRS)

    Quince, Asia; Dutton, Maureen; Hicks, Robert; Burnham, Karen

    2013-01-01

    This innovation consists of a pyrotechnic initiator and piezoelectric initiation system. The device will be capable of being initiated mechanically; resisting initiation by EMF, RF, and EMI (electromagnetic field, radio frequency, and electromagnetic interference, respectively); and initiating in water environments and space environments. Current devices of this nature are initiated by the mechanical action of a firing pin against a primer. Primers historically are prone to failure. These failures are commonly known as misfires or hang-fires. In many cases, the primer shows the dent where the firing pin struck the primer, but the primer failed to fire. In devices such as "T" handles, which are commonly used to initiate the blowout of canopies, loss of function of the device may result in loss of crew. In devices such as flares or smoke generators, failure can result in failure to spot a downed pilot. The piezoelectrically initiated ignition system consists of a pyrotechnic device that plugs into a mechanical system (activator), which on activation, generates a high-voltage spark. The activator, when released, will strike a stack of electrically linked piezo crystals, generating a high-voltage, low-amperage current that is then conducted to the pyro-initiator. Within the initiator, an electrode releases a spark that passes through a pyrotechnic first-fire mixture, causing it to combust. The combustion of the first-fire initiates a primary pyrotechnic or explosive powder. If used in a "T" handle, the primary would ramp the speed of burn up to the speed of sound, generating a shock wave that would cause a high explosive to go "high order." In a flare or smoke generator, the secondary would produce the heat necessary to ignite the pyrotechnic mixture. The piezo activator subsystem is redundant in that a second stack of crystals would be struck at the same time with the same activation force, doubling the probability of a first strike spark generation. If the first activation fails to ignite, the device is capable of multiple attempts. Another unique aspect is in the design of the pyrotechnic device. There is an electrode that aids the generation of a directed spark and the use of a conductive matrix to support the first-fire material so that the spark will penetrate to the second electrode.

  7. Stochastic shock response spectrum decomposition method based on probabilistic definitions of temporal peak acceleration, spectral energy, and phase lag distributions of mechanical impact pyrotechnic shock test data

    NASA Astrophysics Data System (ADS)

    Hwang, James Ho-Jin; Duran, Adam

    2016-08-01

    Most of the times pyrotechnic shock design and test requirements for space systems are provided in Shock Response Spectrum (SRS) without the input time history. Since the SRS does not describe the input or the environment, a decomposition method is used to obtain the source time history. The main objective of this paper is to develop a decomposition method producing input time histories that can satisfy the SRS requirement based on the pyrotechnic shock test data measured from a mechanical impact test apparatus. At the heart of this decomposition method is the statistical representation of the pyrotechnic shock test data measured from the MIT Lincoln Laboratory (LL) designed Universal Pyrotechnic Shock Simulator (UPSS). Each pyrotechnic shock test data measured at the interface of a test unit has been analyzed to produce the temporal peak acceleration, Root Mean Square (RMS) acceleration, and the phase lag at each band center frequency. Maximum SRS of each filtered time history has been calculated to produce a relationship between the input and the response. Two new definitions are proposed as a result. The Peak Ratio (PR) is defined as the ratio between the maximum SRS and the temporal peak acceleration at each band center frequency. The ratio between the maximum SRS and the RMS acceleration is defined as the Energy Ratio (ER) at each band center frequency. Phase lag is estimated based on the time delay between the temporal peak acceleration at each band center frequency and the peak acceleration at the lowest band center frequency. This stochastic process has been applied to more than one hundred pyrotechnic shock test data to produce probabilistic definitions of the PR, ER, and the phase lag. The SRS is decomposed at each band center frequency using damped sinusoids with the PR and the decays obtained by matching the ER of the damped sinusoids to the ER of the test data. The final step in this stochastic SRS decomposition process is the Monte Carlo (MC) simulation. The MC simulation identifies combinations of the PR and decays that can meet the SRS requirement at each band center frequency. Decomposed input time histories are produced by summing the converged damped sinusoids with the MC simulation of the phase lag distribution.

  8. Pyrotechnically Generated and Disseminated Aerosol for Bioagent Defeat

    DTIC Science & Technology

    2016-12-01

    Chemical Biological Center [ECBC]; Aberdeen Proving Ground, MD);  Mark Hull ( Engineering Directorate, ECBC); and  Christine Franklin (Leidos, Inc...with the metal fuel/iodine pentoxide reactions . These results show a strong biocidal action against the tested biological targets, suggesting use...for these reactions in bioagent defeat applications. 15. SUBJECT TERMS Iodine Bioagent Pyrotechnic Antimicrobial Iodine pentoxide 16. SECURITY

  9. Pyrotechnic Tubing Connector

    NASA Technical Reports Server (NTRS)

    Graves, Thomas J.; Yang, Robert A.

    1988-01-01

    Tool forms mechanical seal at joint without levers or hydraulic apparatus. Proposed tool intended for use in outer space used on Earth by heavily garbed workers to join tubing in difficult environments. Called Pyrotool, used with Lokring (or equivalent) fittings. Piston slides in cylinder when pushed by gas from detonating pyrotechnic charge. Impulse of piston compresses fittings, sealing around butting ends of tubes.

  10. Independent Orbiter Assessment (IOA): Analysis of the pyrotechnics subsystem

    NASA Technical Reports Server (NTRS)

    Robinson, W. W.

    1988-01-01

    The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results corresponding to the Orbiter Pyrotechnics hardware. The IOA analysis process utilized available pyrotechnics hardware drawings and schematics for defining hardware assemblies, components, and hardware items. Each level of hardware was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode.

  11. Chlorine-Free Red-Burning Pyrotechnics.

    PubMed

    Sabatini, Jesse J; Koch, Ernst-Christian; Poret, Jay C; Moretti, Jared D; Harbol, Seth M

    2015-09-07

    The development of a red, chlorine-free pyrotechnic illuminant of high luminosity and spectral purity was investigated. Red-light emission based solely on transient SrOH(g) has been achieved by using either 5-amino-1H-tetrazole or hexamine to deoxidize the combustion flame of a Mg/Sr(NO3 )2 /Epon-binder composition and reduce the amount of both condensed and gaseous SrO, which emits undesirable orange-red light. The new formulations were found to possess high thermal onset temperatures. Avoiding chlorine in these formulations eliminates the risk of the formation of PCBs, PCDDs, and PCDFs. This finding, hence, will have a great impact on both military pyrotechnics and commercial firework sectors. © 2015 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

  12. High-nitrogen-based pyrotechnics: longer- and brighter-burning, perchlorate-free, red-light illuminants for military and civilian applications.

    PubMed

    Sabatini, Jesse J; Nagori, Amita V; Chen, Gary; Chu, Phillip; Damavarapu, Reddy; Klapötke, Thomas M

    2012-01-09

    The full-up prototype testing of perchlorate-free, hand-held, signal illuminants for the US Army's M126A1 red star parachute hand-held signal is described. Compared to the perchlorate-containing control, the disclosed illuminants yielded excellent stabilities toward various ignition stimuli while offering superior pyrotechnic performance. Militarily, the illuminants provided further evidence that development of smaller hand-held signal items in an environmentally conscious way is a realistic and obtainable goal. The results are also important from the perspective of civilian fireworks, as the development of brighter, longer-burning, and environmentally compatible red-light-emitting pyrotechnics is now possible. Copyright © 2012 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

  13. Symposium on Explosives and Pyrotechnics, 13th, Hilton Head Island, SC, Dec. 2-4, 1986, Proceedings

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

    Not Available

    1987-01-01

    The present conference on explosive and pyrotechnic technologies discusses the shock-sensitivity of RDX, the thermodynamic properties of RDX, TNT, nitroglycerine, and HMX energetic molecules, the dynamic resistivity of exploding conductors, the decomposition of azides, the critical shock-initiation energy of emulsion explosives, actuator valve optimization, pyrotechnic aerosolization from novel imbibed liquid matrices, tetrazole initiators, and polymeric binders for red phosphorus pellets. Also discussed are channel-effect studies, the dynamic desensitization of coal mine explosives, the electromagnetic and electrostatic protection of explosives, the reliability of fuze explosive trains, the hazardous properties of explosive chemicals, the emulsification of an explosive with a chemical foamingmore » agent, and low energy ignition of HMX using a foil bridge.« less

  14. Using the Chemistry of Fireworks to Engage Students in Learning Basic Chemical Principles: A Lesson in Eco-Friendly Pyrotechnics

    ERIC Educational Resources Information Center

    Steinhauser, Georg; Klapotke, Thomas M.

    2010-01-01

    Fascination with fireworks and pyrotechnics can be used for educational purposes. Several aspects of pyrochemistry such as redox reactions, flame colors, or the theory of combustion can be incorporated in the curriculum to illustrate some basic chemical principles, guaranteeing a lesson that will be engaging and memorable. Beyond classic…

  15. Miniature laser ignited bellows motor

    NASA Technical Reports Server (NTRS)

    Renfro, Steven L.; Beckman, Tom M.

    1994-01-01

    A miniature optically ignited actuation device has been demonstrated using a laser diode as an ignition source. This pyrotechnic driven motor provides between 4 and 6 lbs of linear force across a 0.090 inch diameter surface. The physical envelope of the device is 1/2 inch long and 1/8 inch diameter. This unique application of optical energy can be used as a mechanical link in optical arming systems or other applications where low shock actuation is desired and space is limited. An analysis was performed to determine pyrotechnic materials suitable to actuate a bellows device constructed of aluminum or stainless steel. The aluminum bellows was chosen for further development and several candidate pyrotechnics were evaluated. The velocity profile and delivered force were quantified using an non-intrusive optical motion sensor.

  16. Versatile Boron Carbide-Based Visual Obscurant Compositions for Smoke Munitions

    DTIC Science & Technology

    2015-04-17

    Versatile Boron Carbide-Based Visual Obscurant Compositions for Smoke Munitions Anthony P. Shaw,*,† Giancarlo Diviacchi,‡ Ernest L. Black,‡ Jared D...have been demonstrated to produce thick white smoke clouds upon combustion. These compositions use powdered boron carbide (B4C) as a pyrotechnic...ignition and are safe to handle. KEYWORDS: Smoke, Obscurants, Pyrotechnics, Boron carbide, Sustainable chemistry ■ INTRODUCTION Visible obscuration

  17. Shape Memory Actuation and Release Devices.

    DTIC Science & Technology

    1996-10-01

    shelf devices such as pyrotechnics, gas-discharge systems, paraffin wax actuators, and other electro-mechanical devices may not be able to meet...shelf devices such as pyrotechnics, gas-discharge systems, paraffin wax actuators, and other electro-mechanical devices may not be able to meet future...shard mounts. They do have wide utility as pin-pullers and single point release devices for a variety of spacecraft appendages. Parrafin based mechanisms

  18. Demonstration of a Pyrotechnic Bolt-Retractor System

    NASA Technical Reports Server (NTRS)

    Johnston, Nick; Ahmed, Rafiq; Garrison, Craig; Gaines, Joseph; Waggoner, Jason

    2004-01-01

    A paper describes a demonstration of the X-38 bolt-retractor system (BRS) on a spacecraft-simulating apparatus, called the Large Mobility Base, in NASA's Flight Robotics Laboratory (FRL). The BRS design was proven safe by testing in NASA's Pyrotechnic Shock Facility (PSF) before being demonstrated in the FRL. The paper describes the BRS, FRL, PSF, and interface hardware. Information on the bolt-retraction time and spacecraft-simulator acceleration, and an analysis of forces, are presented. The purpose of the demonstration was to show the capability of the FRL for testing of the use of pyrotechnics to separate stages of a spacecraft. Although a formal test was not performed because of schedule and budget constraints, the data in the report show that the BRS is a successful design concept and the FRL is suitable for future separation tests.

  19. Pyrotechnic hazards classification and evaluation program. Phase 2, segment 1: Records and experience analysis

    NASA Technical Reports Server (NTRS)

    1970-01-01

    A comprehensive search review and analysis was made of various technical documents relating to both pyrotechnics and high explosives testing, handling, storage, manufacturing, physical and chemical characteristics and accidents and incidents. Of approximately 5000 technical abstracts reviewed, 300 applicable documents were analyzed in detail. These 300 documents were then converted to a subject matrix so that they may be readily referenced for application to the current programs. It was generally concluded that information in several important categories was lacking. Two of the more important categories were in pyrotechnics sensitivity testing and TNT equivalency testing. A general recommendation resulting from this study was that this activity continue and a comprehensive data bank be generated that would allow immediate access to a large volume of pertinent information in a relatively short period of time.

  20. Titanium subhydride potassium perchlorate (TiH1.65/KClO4) burn rates from hybrid closed bomb-strand burner experiments.

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

    Cooper, Marcia A.; Oliver, Michael S.

    2012-08-01

    A hybrid closed bomb-strand burner is used to measure the burning behavior of the titanium subhydride potassium perchlorate pyrotechnic with an equivalent hydrogen concentration of 1.65. This experimental facility allows for simultaneous measurement of the closed bomb pressure rise and pyrotechnic burn rate as detected by electrical break wires over a range of pressures. Strands were formed by pressing the pyrotechnic powders to bulk densities between 60% and 90% theoretical maximum density. The burn rate dependance on initial density and vessel pressure are measured. At all initial strand densities, the burn is observed to transition from conductive to convective burningmore » within the strand. The measured vessel pressure history is further analyzed following the closed bomb analysis methods developed for solid propellants.« less

  1. Alternatives to Pyrotechnic Distress Signals; Supplemental Report

    DTIC Science & Technology

    2015-08-01

    distribution of an incandescent lamp as compared to a specific white LED . ...................... 3  Figure 3. Spectral distribution of a “cool” white LED ...of common lamps2. Figure 2 shows the spectral distribution of an incandescent lamp as compared to a “cool” white LED . Note the LED peak intensity in...project effort that developed a specification for a light-emitting diode ( LED ) signal characteristic as an alternative to pyrotechnic, maritime

  2. 2007 Armaments Technology Seminar and Exhibition - Joint Munitions and Lethality Life Cycle Management Command

    DTIC Science & Technology

    2007-06-13

    MTOP APS LOS-KE TBX Ceramic Barrel Novel Energetic Materials for the Future Force Multimode HPM and Laser Induced Plasma Channel Technology T Force...in one item • Enhanced incendiary device • Replacement of environmentally unfriendly materials • Insensitive munitions compliance 12 Pyrotechnics...simulators • Pocket sized hand held signals • Replacement of environmentally unfriendly materials • Improve pyrotechnic characteristics with nanotechnologies

  3. Development and Performance of Boron Carbide-Based Smoke Compositions

    DTIC Science & Technology

    2013-03-06

    DOI: 10.1002/prep.201200166 Development and Performance of Boron Carbide -Based Smoke Compositions Anthony P. Shaw,*[a] Jay C. Poret,[a] Robert A...volatilized and recondense to give smoke. Boron carbide was recognized as a pyrotechnic fuel many years ago, but it has since been overlooked. A 1961...Abstract : Pyrotechnic smoke compositions for visual ob- scuration containing boron carbide , potassium nitrate, po- tassium chloride, and various lubricants

  4. The Shock and Vibration Bulletin. Part 3. Invited Papers, Pyrotechnic Shock, Pyrotechnic Shock Workshop

    DTIC Science & Technology

    1986-08-01

    Technology Laboratory, Watertown, MA AIR FORCE BASIC RESEARCH IN DYNAMICS AND CONTROL OF LARGE SPACE STRUCTURES Anthony K. Amos, Boiling Air Force Base...Engineering, Watchun$, NJ TEMPERATURE SHIFT CONSIDERATIONS FOR DAMPING MATERIALS L. Rogers, Air Force Wright Aeronautictl Laboratories, Wright...INDUCED CAVITY ACOUSTICS L.L. Shaw,. Air Force Wr4ht Aeroaauical Laborawrics, Wri•ht-Paucswon AFB. OH i 4i SESSION CHAIRMEN AND COCHAIRMEN 56th Shock and

  5. Under-Body Blast Mitigation: Stand-Alone Seat Safety Activation System

    DTIC Science & Technology

    2014-04-01

    Restraints, Airbags or other protection systems) to mitigate injury to the occupant during the onset of the event. Injuries may occur as soon as 2.5 ms...cost-effective sensor to accurately and consistently deploy airbags and other pyrotechnic restraint systems based on accelerometers and other...Circuitry are critically important in order to activate the initiators of air bags and pyrotechnic restraint system such as airbags at the very first

  6. Structural and mechanical design challenges of space shuttle solid rocket boosters separation and recovery subsystems

    NASA Technical Reports Server (NTRS)

    Woodis, W. R.; Runkle, R. E.

    1985-01-01

    The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique and challenging design considerations. The separation of the SRBs from the cluster (orbiter and external tank) at 150,000 ft when the orbiter engines are running at full thrust meant the two SRBs had to have positive separation forces pushing them away. At the same instant, the large attachments that had reacted launch loads of 7.5 million pounds thrust had to be servered. These design considerations dictated the design requirements for the pyrotechnics and separation rocket motors. The recovery and reuse of the two SRBs meant they had to be safely lowered to the ocean, remain afloat, and be owed back to shore. In general, both the pyrotechnic and recovery subsystems have met or exceeded design requirements. In twelve vehicles, there has only been one instance where the pyrotechnic system has failed to function properly.

  7. Pyrotechnic shock measurement and data analysis requirements

    NASA Technical Reports Server (NTRS)

    Albers, L.

    1975-01-01

    A study of laboratory measurement and analysis of pyrotechnic shock prompted by a discrepancy in preliminary Mariner Jupiter/Saturn shock test data is reported. It is shown that before generating shock response plots from any recorded pyrotechnic event, a complete review of each instrumentation and analysis system must be made. In addition, the frequency response capability of the tape recorder used should be as high as possible; the discrepancies in the above data were due to inadequate frequency response in the FM tape recorders. The slew rate of all conditioning amplifiers and input converters must be high enough to prevent signal distortion at maximum input voltage; amplifier ranges should be selected so that the input pulse is approximately 50% of full scale; the Bessel response type should be chosen for digital shock analysis if antialiasing filters are employed; and transducer selection must consider maximum acceleration limit, mounted resonance frequency, flat clean mounting surfaces, base bending sensitivity, and proper torque.

  8. Environmental Health Assessment for Pyrotechnic Perchlorate Elimination/Mitigation Program for M118/M119 Simulators

    DTIC Science & Technology

    2009-09-11

    evaluated. When toxicity data were not available, criteria were modeled using QSAR approaches. 3 Toxicology Report No. 87-XE-074Z-09C g. Potential...Environmental Health Assessment for Work Unit PYRO 06-08, Pyrotechnic Perchlorate Elimination/Mitigation Program for M118/M119 Simulators, Toxicology ...Directorate of Toxicology , Health Effects Research Program. He may be contacted at DSN (312) 584-7159 or commercial (410) 436-7159. FOR THE COMMANDER

  9. Pyrotechnic shock at the orbiter/external tank forward attachment

    NASA Technical Reports Server (NTRS)

    Rogers, W. F.; Grissom, D. S.; Rhodes, L. R.

    1980-01-01

    During the initial certification test of the forward structural attachment of the space shuttle orbiter to the external tank, pyrotechnic shock from actuation of the separation device resulted in structural failure of the thermal protection tiles surrounding the attachment. Because of the high shock associated with the separation bolt, the development of alternative low shock separation designs was initiated. Two concepts that incorporate a 5.08 centimeter frangible nut as the release device were developed and tested.

  10. High-Nitrogen-Based Pyrotechnics: Longer- and Brighter-Burning, Perchlorate-Free, Red-Light Illuminants for Military and Civilian Applications

    DTIC Science & Technology

    2011-01-01

    combustion of these materials. To address the aforementioned perchlorate issues, an effort was initiated by ARDEC to remove potassium per- chlorate ...with acceptable burn times for pyrotechnic applications by using potassium nitrate– amorphous boron–crystalline boron/boron carbide–epoxy binder mixtures...3,4] Moreover, it was discovered by ARDEC that a potassium nitrate–boron carbide–epoxy binder mix- ture alone was able to generate suitable green

  11. The 2nd NASA Aerospace Pyrotechnic Systems Workshop

    NASA Technical Reports Server (NTRS)

    St.Cyr, William W. (Compiler)

    1994-01-01

    This NASA Conference Publication contains the proceedings of the Second NASA Aerospace Pyrotechnics Systems Workshop held at Sandia National Laboratories, Albuquerque, New Mexico, February 8-9, 1994. The papers are grouped by sessions: (1) Session 1 - Laser Initiation and Laser Systems; (2) Session 2 - Electric Initiation; (3) Session 3 - Mechanisms & Explosively Actuated Devices; (4) Session 4 - Analytical Methods and Studies; and (5) Session 5 - Miscellaneous. A sixth session, a panel discussion and open forum, concluded the workshop.

  12. Comparison of Separation Shock for Explosive and Nonexplosive Release Actuators on a Small Spacecraft Panel

    NASA Technical Reports Server (NTRS)

    Lucy, M. H.; Buehrle, R. D.; Woolley, J. P.

    1996-01-01

    Functional shock, safety, overall system costs, and emergence of new technologies, have raised concerns regarding continued use of pyrotechnics on spacecraft. NASA Headquarters-Office of Chief Engineer requested Langley Research Center (LaRC) study pyrotechnic alternatives using non-explosive actuators (NEA's), and LARC participated with Lockheed Martin Missile and Space Co. (LMMSC)-Sunnyvale, CA in objectively evaluating applicability of some NEA mechanisms to reduce small spacecraft and booster separation event shock. Comparative tests were conducted on a structural simulator using five different separation nut mechanisms, consisting of three pyrotechnics from OEA-Aerospace and Hi-Shear Technology and two NEA's from G&H Technology and Lockheed Martin Astronautics (LMA)-Denver, CO. Multiple actuations were performed with preloads up to 7000 pounds, 7000 being the comparison standard. All devices except LMA's NEA rotary flywheel-nut concept were available units with no added provisions to attenuate shock. Accelerometer measurements were recorded, reviewed, processed into Shock Response Spectra (SRS), and comparisons performed. For the standard preload, pyrotechnics produced the most severe and the G&H NEA the least severe functional shock levels. Comparing all results, the LMA concept produced the lowest levels, with preload limited to approximately 4200 pounds. Testing this concept over a range of 3000 to 4200 pounds indicated no effect of preload on shock response levels. This report presents data from these tests and the comparative results.

  13. Development of an ultra-low-shock separation nut

    NASA Technical Reports Server (NTRS)

    Woebkenberg, W.; Matteo, D. N.; Williams, V. D.

    1982-01-01

    The technical problems encountered in the development of an advanced separation nut design are described. The nut is capable of sustaining a large preload and releasing that load with a low level of induced pyrotechnic shock, while demonstrating a tolerance for extremely high shock imposed by other pyrotechnic devices. The analysis of the separation nut was performed to acquire additional understanding of the phenomena affecting operation of the nut and to provide quantitative evaluation of design modification for aerospace applications.

  14. Normally-Closed Zero-Leak Valve with Magnetostrictive Actuator

    NASA Technical Reports Server (NTRS)

    Ramspacher, Daniel J. (Inventor); Richard, James A. (Inventor)

    2017-01-01

    A non-pyrotechnic, normally-closed, zero-leak valve is a replacement for the pyrovalve used for both in-space and launch vehicle applications. The valve utilizes a magnetostrictive alloy for actuation, rather than pyrotechnic charges. The alloy, such as Terfenol-D, experiences magnetostriction, i.e. a gross elongation, when exposed to a magnetic field. This elongation fractures a parent metal seal, allowing fluid flow through the valve. The required magnetic field is generated by redundant coils that are isolated from the working fluid.

  15. DSIS Consolidated ARMX 83 Briefing Notes.

    DTIC Science & Technology

    1983-07-08

    PRAhISIONGERATEERK GUNNERY SIMULLATOR ,07$3")j j711 U.K. OFFICE FOR ARMOUR FIGHTING MOIUNTBATTEN HOUSE VEICLES TACTICAL AND VICTORIA STREET GUNNERY TRAINER...FOR WINDSOR BERKS AfI-TNLK CUIDED SL4 HE WEAPONS TOW SI.UI.ATOR ANTI ARMOUR HELICOPTER SYSTEM ASTIRA PYROTECHNICS SAMPLES OF . REED LIM PYROTECHNIC...he engir’e mounts ir efo -irg -’,c t-ers i ’* : evimale t-e %.1113 Armoured Personeel Car-iar 15 .Vet e ’ -- z - ere ’rav nave to te a reallocation of

  16. The Shock Vibration Bulletin. Part 1. Welcome, Keynote Address, Invited Papers, Nondevelopment Items Workshop, and Pyrotechnic Shock Workshop (From 56th Shock and Vibration Symposium)

    DTIC Science & Technology

    1987-01-01

    PREDICTION OF PYROTECHNIC SHOCK FROM PIN-PULLERS AND SEPARATION JOINTS M. J. Evans and V. H. Neubert , The Pennsylvania State University, University...A.M. Shock and Vibration Information Center, Naval Research , Laboratory, Washington, DC k% Wednesday Nondevelopment Mr. James W. Daniel, Mr. Paul ...FL Wednesday Structural Mr. Stanley Barrett, Mr. W. Paul Dunn, 15 October, A.M. Dynamics I Martin Marietta The Aerospace Denver Aerospace, Corporation

  17. Explosively activated egress area

    NASA Technical Reports Server (NTRS)

    Bement, L. J.; Bailey, J. W. (Inventor)

    1983-01-01

    A lightweight, add on structure which employs linear shaped pyrotechnic charges to smoothly cut an airframe along an egress area periphery is provided. It compromises reaction surfaces attached to the exterior surface of the airframe's skin and is designed to restrict the skin deflection. That portion of the airframe within the egress area periphery is jettisoned. Retention surfaces and sealing walls are attached to the interior surface of the airframe's skin and are designed to shield the interior of the aircraft during detonation of the pyrotechnic charges.

  18. Random Vibrations

    NASA Technical Reports Server (NTRS)

    Messaro. Semma; Harrison, Phillip

    2010-01-01

    Ares I Zonal Random vibration environments due to acoustic impingement and combustion processes are develop for liftoff, ascent and reentry. Random Vibration test criteria for Ares I Upper Stage pyrotechnic components are developed by enveloping the applicable zonal environments where each component is located. Random vibration tests will be conducted to assure that these components will survive and function appropriately after exposure to the expected vibration environments. Methodology: Random Vibration test criteria for Ares I Upper Stage pyrotechnic components were desired that would envelope all the applicable environments where each component was located. Applicable Ares I Vehicle drawings and design information needed to be assessed to determine the location(s) for each component on the Ares I Upper Stage. Design and test criteria needed to be developed by plotting and enveloping the applicable environments using Microsoft Excel Spreadsheet Software and documenting them in a report Using Microsoft Word Processing Software. Conclusion: Random vibration liftoff, ascent, and green run design & test criteria for the Upper Stage Pyrotechnic Components were developed by using Microsoft Excel to envelope zonal environments applicable to each component. Results were transferred from Excel into a report using Microsoft Word. After the report is reviewed and edited by my mentor it will be submitted for publication as an attachment to a memorandum. Pyrotechnic component designers will extract criteria from my report for incorporation into the design and test specifications for components. Eventually the hardware will be tested to the environments I developed to assure that the components will survive and function appropriately after exposure to the expected vibration environments.

  19. Organic Coatings to Improve the Storageability and Safety of Pyrotechnic Compositions.

    DTIC Science & Technology

    1987-11-01

    TERMS (CONTINUE ON REVERSE IF NECESSARY AND IDENTIFY BY BLOCK NUMBER) FIELD GROUP sue-oRouP Organic coatings Pyrotechnic compositions Magnesium coatings...Storageability Hydrogen gassing \\ ABSTRACT (CONTINUE ON REVERSE IF NECESSARY AND IDENTIFY BY BLOCK NUMBER) study was conducted to find organic...composition 52% KC10 3, 31% S2S31 17% dextrin Impact = (14 cm Coated with 5% Elvax-360 Impact = 16 cm in Ln cn- -T 01 LA 1C) -l4 -t, 0 14-1 0 toJ 0 0 110

  20. Effects of variables upon pyrotechnically induced shock response spectra, part 2

    NASA Technical Reports Server (NTRS)

    Smith, James Lee

    1988-01-01

    Throughout the aerospace industry, large variations of 50 percent (6 dB) or more in shock response spectra (SRS) derived from pyrotechnic separation events continue to be reported from actual spaceflight data and from laboratory tests. As a result of these variations, NASA funded a research program for 1984 through 1986. The purpose of the 1984 through 1986 project was to analyze variations in pyrotechnically induced SRS and to determine if and to what degree manufacturing and assembly variables and tolerances, distance from the shock source, data acquisition instrumentation, and shock energy propagation affect the SRS. Sixty-four free-free boundary plate tests were performed. NASA funded an additional study for 1987 through 1988. This paper is a summary of the additional study. The purpose was to evaluate shock dissipation through various spacecraft structural joint types, to evaluate shock variation for various manufacturing and assembly variables on clamped boundary test plates, and to verify data correction techniques. Five clamped boundary plate tests investigated manufacturing and assembly variables and mass loading effects. Six free-free boundary plate tests investigated shock dissipation across spacecraft joint structures.

  1. Cartridge output testing - Methods to overcome closed-bomb shortcomings

    NASA Technical Reports Server (NTRS)

    Bement, Laurence J.; Schimmel, Morry L.

    1991-01-01

    Although the closed-bomb test has achieved virtually universal acceptance for measuring the output performance of pyrotechnic cartridges, there are serious shortcomings in its ability to quantify the performance of cartridges used as energy sources for pyrotechnic-activated mechanical devices. This paper presents several examples of cartridges (including the NASA Standard Initiator NSI) that successfully met closed-bomb performance requirements, but resulted in functional failures in mechanisms. To resolve these failures, test methods were developed to demonstrate a functional margin, based on comparing energy required to accomplish the function to energy deliverable by the cartridge.

  2. X-38 Bolt Retractor Subsystem Separation Demonstration

    NASA Technical Reports Server (NTRS)

    Rugless, Fedoria (Editor); Johnston, A. S.; Ahmed, R.; Garrison, J. C.; Gaines, J. L.; Waggoner, J. D.

    2002-01-01

    The Flight Robotics Laboratory FRL successfully demonstrated the X-38 bolt retractor subsystem (BRS). The BRS design was proven safe by testing in the Pyrotechnic Shock Facility (PSI) before being demonstrated in the FRL. This Technical Memorandum describes the BRS, FRL, PSF, and interface hardware. Bolt retraction time, spacecraft simulator acceleration, and a force analysis are also presented. The purpose of the demonstration was to show the FRL capability for spacecraft separation testing using pyrotechnics. Although a formal test was not performed due to schedule and budget constraints, the data will show that the BRS is a successful design concept and the FRL is suitable for future separation tests.

  3. Four-terminal connector for measuring resistance of a pyrotechnic initiator

    NASA Technical Reports Server (NTRS)

    Robinson, Robert L. (Inventor); Graves, Thomas J. (Inventor); Hoffman, III, William C. (Inventor)

    1989-01-01

    A four-terminal electrical connector device (40) for testing and measuring unknown resistances of initiators (11) used for starting pyrotechnic events aboard a Space Transportation System. The testing device minimizes contact resistance degradation effects and so improves the reliability of resistance measurement taken with the device. Separate and independent voltage sensing (19) and current supply (20) circuits each includes a pair of socket contacts (13-16) for mating engagement with the pins (17,18) of the initiator. The unknown resistance that is measured by the device is the resistance of the bridgewire (23) of the initiator which is required to be between 0.95 and 1.15 ohms.

  4. Development of a high force thermal latch

    NASA Technical Reports Server (NTRS)

    Nygren, William D.

    1995-01-01

    This paper describes the preliminary development of a high force thermal latch (HFTL). The HFTL has one moving part which is restrained in the latched position by a low melting temperature or fusible metal alloy. When heated the fusible alloy flows to a receiving chamber and in so doing at first releases the tension load in the latch bolt and later releases the bolt itself. The HFTL can be used in place of pyrotechnically activated spacecraft release devices in those instances where the elimination of both pyrotechnic shock-loading and rapid strain-energy release take precedence over the near instantaneous release offered by ordnance initiated devices.

  5. Applications catalog of pyrotechnically actuated devices/systems

    NASA Technical Reports Server (NTRS)

    Seeholzer, Thomas L.; Smith, Floyd Z.; Eastwood, Charles W.; Steffes, Paul R.

    1995-01-01

    A compilation of basic information on pyrotechnically actuated devices/systems used in NASA aerospace and aeronautic applications was formatted into a catalog. The intent is to provide (1) a quick reference digest of the types of operational pyro mechanisms and (2) a source of contacts for further details. Data on these items was furnished by the NASA Centers that developed and/or utilized such devices to perform specific functions on spacecraft, launch vehicles, aircraft, and ground support equipment. Information entries include an item title, user center name, commercial contractor/vendor, identifying part number(s), a basic figure, briefly described purpose and operation, previous usage, and operational limits/requirements.

  6. Development and testing of hermetic, laser-ignited pyrotechnic and explosive components

    NASA Technical Reports Server (NTRS)

    Kramer, Daniel P.; Beckman, Thomas M.; Spangler, Ed M.; Munger, Alan C.; Woods, C. M.

    1993-01-01

    During the last decade there has been increasing interest in the use of lasers in place of electrical systems to ignite various pyrotechnic and explosive materials. The principal driving force for this work was the requirement for safer energetic components which would be insensitive to electrostatic and electromagnetic radiation. In the last few years this research has accelerated since the basic concepts have proven viable. At the present time it is appropriate to shift the research emphasis in laser initiation from the scientific arena--whether it can be done--to the engineering realm--how it can be put into actual practice in the field. Laser initiation research and development at EG&G Mound was in three principal areas: (1) laser/energetic material interactions; (2) development of novel processing techniques for fabricating hermetic (helium leak rate of less than 1 x 10(exp -8) cu cm/s) laser components; and (3) evaluation and testing of laser-ignited components. Research in these three areas has resulted in the development of high quality, hermetic, laser initiated components. Examples are presented which demonstrate the practicality of fabricating hermetic, laser initiated explosive or pyrotechnic components that can be used in the next generation of ignitors, actuators, and detonators.

  7. Laser-initiated ordnance for air-to-air missiles

    NASA Technical Reports Server (NTRS)

    Sumpter, David R.

    1993-01-01

    McDonnell Douglas Missile Systems Company (MDMSC) has developed a laser ignition subsystem (LIS) for air-to-air missile applications. The MDMSC subsystem is designed to activate batteries, unlock fins, and sequence propulsion system events. The subsystem includes Pyro Zirconium Pump (PZP) lasers, mechanical Safe & Arm, fiber-optic distribution system, and optically activated pyrotechnic devices (initiators, detonators, and thermal batteries). The LIS design has incorporated testability features for the laser modules, drive electronics, fiber-optics, and pyrotechnics. Several of the LIS have been fabricated and have supported thermal battery testing, integral rocket ramjet testing, and have been integrated into integral rocket ramjet flight test vehicles as part of the flight control subsystem.

  8. Engineering Design Handbook - Military Pyrotechnics Series. Part Four. Design of Ammunition for Pyrotechnic Effects

    DTIC Science & Technology

    1974-03-15

    Type 1) is a mixture of 88.5 percent gasoline and 11.5 percent napalm thickener. Napalm thickener is a granular base aluminum soap of naphthenic ...methacrylate polymer AE (IM) 5.0 5.0 2.0 3.0 3.0 3.0 3.0 Stearic acid 3.0 — — 1.0 4.0 3.0 4.5 Fatty acids - 2.5 3.0 - — — — Naphthenic acid - 2.5...3.0 3.0 — 1.0 0.5 Calcium oxide 2.0 — — 3.1 4.0 3.5 _ Caustic soda (40% solution) — 3.0 4.5 — — — — Ammonium hydroxide (27% solution

  9. Report on Alternative Devices to Pyrotechnics on Spacecraft

    NASA Technical Reports Server (NTRS)

    Lucy, M. H.; Hardy, R. C.; Kist, E. H., Jr.; Watson, J. J.; Wise, S. A.

    1996-01-01

    Pyrotechnics accomplish many functions on today's spacecraft, possessing minimum volume/weight, providing instantaneous operation on demand, and requiring little input energy. However, functional shock, safety, and overall system cost issues, combined with emergence and availability of new technologies question their continued use on space missions. Upon request from the National Aeronautics and Space Administration's (NASA) Program Management Council (PMC), Langley Research Center (LaRC) conducted a survey to identify and evaluate state-of-the-art non-explosively actuated (NEA) alternatives to pyrotechnics, identify NEA devices planned for NASA use, and investigate potential interagency cooperative efforts. In this study, over 135 organizations were contacted, including NASA field centers, Department of Defense (DOD) and other government laboratories, universities, and American and European industrial sources resulting in further detailed discussions with over half, and 18 face-to-face briefings. Unlike their single use pyrotechnic predecessors, NEA mechanisms are typically reusable or refurbishable, allowing flight of actual tested units. NEAs surveyed include spool-based devices, thermal knife, Fast Acting Shockless Separation Nut (FASSN), paraffin actuators, and shape memory alloy (SMA) devices (e.g., Frangibolt). The electro-mechanical spool, paraffin actuator and thermal knife are mature, flight proven technologies, while SMA devices have a limited flight history. There is a relationship between shock, input energy requirements, and mechanism functioning rate. Some devices (e.g., Frangibolt and spool based mechanisms) produce significant levels of functional shock. Paraffin, thermal knife, and SMA devices can provide gentle, shock-free release but cannot perform critically timed, simultaneous functions. The FASSN flywheel-nut release device possesses significant potential for reducing functional shock while activating nearly instantaneously. Specific study recommendations include: (1) development of NEA standards, specifically in areas of material characterization, functioning rates, and test methods; (2) a systems level approach to assure successful NEA technology application; and (3) further investigations into user needs, along with industry/government system-level real spacecraft cost benefit trade studies to determine NEA application foci and performance requirements. Additional survey observations reveal an industry and government desire to establish partnerships to investigate remaining unknowns and formulate NEA standards, specifically those driven by SMAs. Finally, there is increased interest and need to investigate alternative devices for such functions as stage/shroud separation and high pressure valving. This paper summarizes results of the NASA-LaRC survey of pyrotechnic alternatives. State of-the-art devices with their associated weight and cost savings are presented. Additionally, a comparison of functional shock characteristics of several devices are shown, and potentially related technology developments are highlighted.

  10. Proceedings of the International Pyrotechnics Seminar (7th) Held at Vail, Colorado, 14-18 July 1980. Volume 1

    DTIC Science & Technology

    1980-07-18

    DISTRIBUTION STAMP DATE RETURNED 84 08 28 040 DA rE RECEIVED IN DTIC REGISTERED OR CERTIFIED NO. PHOTOGRAPH THIS SHEET AND RETURN TO DTIC.I) DAC DTIC FORM 70A...indicated that pressed pyrotechnic and explosive samples 310 00 ;Z 41 -J -o Qj d• O Ob~e.o to 0 CLC 00 4-) 4.- cJC S4-)u0)0 to 0 CA 0)0 ,4) - a) S-4...1430, 1040 cm-1 (also 1295 and 1170 cm- 1 but not apparent due to CIO) TLC Rf .75..79 TA ,nm I, (moles/ý)- 1 I2 1 334 60 T’Ig Ag 464 60 326 15 The N

  11. Measurement and analysis of force-time outputs of pyrotechnic nuts

    NASA Technical Reports Server (NTRS)

    Neubert, V. H.

    1973-01-01

    The dynamic loadings produced by two standard pyrotechnic nuts were compared with loadings produced by four recently developed low-shock nuts. The nuts were manufactured by separate contractors. Each nut was given a number designation, the number having no special significance. The results show that the use of the Hopkinson bar to measure force-time outputs of the nuts at stud and housing sides aided greatly in understanding the events occurring in the nuts. Acceleration data appear to be dependable, for the most part, but of more limited value. The low-shock designs show considerable improvement over the standard designs above 4,000 Hz when the results are plotted in shock spectrum form. They involve some penalties with regard to weight and cost.

  12. Long-life mission reliability for outer planet atmospheric entry probes

    NASA Technical Reports Server (NTRS)

    Mccall, M. T.; Rouch, L.; Maycock, J. N.

    1976-01-01

    The results of a literature analysis on the effects of prolonged exposure to deep space environment on the properties of outer planet atmospheric entry probe components are presented. Materials considered included elastomers and plastics, pyrotechnic devices, thermal control components, metal springs and electronic components. The rates of degradation of each component were determined and extrapolation techniques were used to predict the effects of exposure for up to eight years to deep space. Pyrotechnic devices were aged under accelerated conditions to an equivalent of eight years in space and functionally tested. Results of the literature analysis of the selected components and testing of the devices indicated that no severe degradation should be expected during an eight year space mission.

  13. 32 CFR 552.100 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... pyrotechnic devices. Any type of military or commercial explosive, incendiary, gas or smoke bomb, grenade... as firecrackers, cherry bombs, bottlerockets, and starclusters. (e) Firearms. Any type of weapon...

  14. 32 CFR 552.126 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ..., gas or smoke bomb, grenade, rocket, missile, mine, blasting cap, “dummy” and/or practice device such... live charge, and pyrotechnic devices such as firecrackers, cherry bombs, bottlerockets, and...

  15. 27 CFR 555.141 - Exemptions.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... generally known as “consumer fireworks” or “articles pyrotechnic.” (8) Gasoline, fertilizers, propellant... intended purposes. (9) Industrial and laboratory chemicals which are intended for use as reagents and which...

  16. 27 CFR 555.141 - Exemptions.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... generally known as “consumer fireworks” or “articles pyrotechnic.” (8) Gasoline, fertilizers, propellant... intended purposes. (9) Industrial and laboratory chemicals which are intended for use as reagents and which...

  17. Inert Reassessment Document for Ammonium Nitrate

    EPA Pesticide Factsheets

    Magnesium nitrate is used in preservation. Other uses for magnesium nitrate include use as a catalyst in the manufacture of petrochemicals, as a densensitizer for lithographic plates and in pyrotechnics.

  18. Explosives and pyrotechnic propellants for use in long term deep space missions

    NASA Technical Reports Server (NTRS)

    Gorzynski, C. S., Jr.; Maycock, J. N.

    1973-01-01

    Explosives and pyrotechnic propellant materials which will withstand heat sterilization cycling at 125 C and ten year deep space aging under 10 to the minus 6th power torr and 66 C have been selected. The selection was accomplished through a detailed literature survey and an analytical evaluation of the physicochemical properties of the materials. The chemical components of the electroexplosive devices used in U.S. missiles and spacecraft were categorized into primary explosives, secondary explosives, and propellant ingredients. Kinetic data on such parameters as thermal decomposition and sublimation were obtained for these materials and used as a basis for the ten year life prediction. From these experimental data and some analytical calculations, a listing of candidate materials for deep space missions was made.

  19. Microelectromechanical safe arm device

    DOEpatents

    Roesler, Alexander W [Tijeras, NM

    2012-06-05

    Microelectromechanical (MEM) apparatus and methods for operating, for preventing unintentional detonation of energetic components comprising pyrotechnic and explosive materials, such as air bag deployment systems, munitions and pyrotechnics. The MEM apparatus comprises an interrupting member that can be moved to block (interrupt) or complete (uninterrupt) an explosive train that is part of an energetic component. One or more latching members are provided that engage and prevent the movement of the interrupting member, until the one or more latching members are disengaged from the interrupting member. The MEM apparatus can be utilized as a safe and arm device (SAD) and electronic safe and arm device (ESAD) in preventing unintentional detonations. Methods for operating the MEM apparatus include independently applying drive signals to the actuators coupled to the latching members, and an actuator coupled to the interrupting member.

  20. 46 CFR 160.038-2 - Type.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... APPROVAL LIFESAVING EQUIPMENT Magazine Chests, Portable, for Merchant Vessels § 160.038-2 Type. (a) Portable magazine chests shall be of a type suitable for stowage of pyrotechnic distress signals, rockets...

  1. Green colorants based on energetic azole borates.

    PubMed

    Glück, Johann; Klapötke, Thomas M; Rusan, Magdalena; Stierstorfer, Jörg

    2014-11-24

    The investigation of green-burning boron-based compounds as colorants in pyrotechnic formulations as alternative for barium nitrate, which is a hazard to health and to the environment, is reported. Metal-free and nitrogen-rich dihydrobis(5-aminotetrazolyl)borate salts and dihydrobis(1,3,4-triazolyl)borate salts have been synthesized and characterized by NMR spectroscopy, elemental analysis, mass spectrometry, and vibrational spectroscopy. Their thermal and energetic properties have been determined as well. Several pyrotechnic compositions using selected azolyl borate salts as green colorants were investigated. Formulations with ammonium dinitramide and ammonium nitrate as oxidizers and boron and magnesium as fuels were tested. The burn time, dominant wavelength, spectral purity, luminous intensity, and luminous efficiency as well as the thermal and energetic properties of these compositions were measured. © 2014 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

  2. Europa Lander Material Selection Considerations

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

    Tappan, Alexander S.; Heller, Mellisa

    2017-01-10

    Energetic materials (EMs, explosives, pyrotechnics, propellants) provide high-power output of high temperature reaction products. These products can be solid, liquid, or gaseous during reaction or after the products have equilibrated with the surroundings. For example, high explosives typically consist of carbon, hydrogen, nitrogen, and oxygen bonded within a single molecule, and produce almost exclusively gaseous products. Conversely, intermetallics consist of physical mixtures of metals and metalloids, and produce almost exclusively condensed products. Other materials such as pyrotechnics and propellants have intermediate behavior. All energetic materials react in a self-propagating manner that after ignition, does not necessarily require energy input frommore » the surroundings. The range of reaction velocities can range from mm/s for intermetallics, to km/s for high explosives. Energetic material selection depends on numerous requirements specific to the needs of a system. High explosives are used for applications where high pressure gases are necessary for pushing or fracturing materials (e.g., rock, metal) or creating shock waves or air blast. Propellants are used to produce moderate-pressure, high-temperature products without a shock wave. Pyrotechnics are used to produce numerous effects including: high-temperature products, gases, light, smoke, sound, and others. Thermites are used to produce heat, high-temperature products, materials, and other effects that require condensed products. Intermetallics are used to produce high-temperature condensed products and materials, with very little gas production. Numerous categories of energetic materials exist with overlapping definitions, effects, and properties.« less

  3. Outer planet probe engineering model structural tests

    NASA Technical Reports Server (NTRS)

    Smittkamp, J. A.; Gustin, W. H.; Griffin, M. W.

    1977-01-01

    A series of proof of concept structural tests was performed on an engineering model of the Outer Planets Atmospheric Entry Probe. The tests consisted of pyrotechnic shock, dynamic and static loadings. The tests partially verified the structural concept.

  4. Alternate methods for high level pyrotechnic shock simulation

    NASA Astrophysics Data System (ADS)

    Gray, Phillip J., Sr.

    Two effective methods to recreate a realistic pyrotechnic shock are presented. The first method employs a resonant beam and is used for SRS levels of 12,000 G or more. The test unit is at one end of the beam and a hammer strikes the opposite end causing a shock to be transmitted to the other end of the fixture. The second method is based on a standard shaker system with a resonant beam to amplify the input signal. The engineer defines the duration of the shock signal induced to the vibration amplifier using the GenRad 2514 controller. The shock signal is then input via the shaker to the resonant beam, which amplifies the signal to produce the desired response at the end of the fixture. The shock response spectrum stays within a +/-6 dB tolerance with levels as high as 3000 G peak. These methods are repeatable, reliable, cost-effective, and consistent with a real pyroevent.

  5. SLM Produced Hermetically Sealed Isolation Valve

    NASA Technical Reports Server (NTRS)

    Richard, James

    2014-01-01

    Marshall Space Flight Center (MSFC) has developed a valve concept to replace traditional pyrotechnic-driven isolation valves. This paper will describe the valve design and development process. The valve design uses a stem/wedge to support a disk inside the valve. That disk hermetically seals the pressurized fluids. A release mechanism holds the stem/wedge and a large spring in place. When required to open, a solenoid is energized and pulls the release mechanism allowing the spring to pull the stem/wedge away from the disk. Now the disk is unsupported and the pressure ruptures the disk allowing flow to the outlet of the valve. This paper will provide details of this design, describe the development testing, and show the results from the valve level tests performed. Also, a trade study is presented to show the advantages of this design to a conventional pyrotechnic-based valve.

  6. [Combustion temperature measurement of pyrotechnic composition using remote sensing Fourier transform infrared spectrometry].

    PubMed

    Zhou, Xin-li; Li, Yan; Liu, Zu-liang; Zhu, Chang-jiang; Wang, Jun-de; Lu, Chun-xu

    2002-10-01

    In this paper, combustion characterization of pyrotechnic composition is investigated using a remote sensing Fourier transform infrared spectrometry. The emission spectra have been recorded between 4,700 and 740 cm-1 with a spectral resolution of 4 cm-1. The combustion temperature can be determined remotely from spectral line intensity distribution of the fine structure of the emission fundamental band of gaseous products such as HF. The relationship between combustion temperature and combustion time has been given. Results show that there is a violent mutative temperature field with bigger temperature gradient near combustion surface. It reveals that the method of temperature measurement using remote sensing FTIR for flame temperature of unstable, violent and short time combustion on real time is a rapid, accurate and sensitive technique without interference the flame temperature field. Potential prospects of temperature measurement, gas product concentration measurement and combustion mechanism are also revealed.

  7. SLM Produced Hermetically Sealed Isolation Valve

    NASA Technical Reports Server (NTRS)

    Richard, James A.

    2014-01-01

    Marshall Space Flight Center (MSFC) has developed a valve concept to replace traditional pyrotechnic driven isolation valves. This paper will describe the valve design and development process. The valve design uses a stem/wedge to support a disk inside the valve. That disk hermetically seals the pressurized fluids. A release mechanism holds the stem/wedge and a large spring in place. When required to open, a solenoid is energized and pulls the release mechanism allowing the spring to pull the stem/wedge away from the disk. Now the disk is unsupported and the pressure ruptures the disk allowing flow to the outlet of the valve. This paper will provide details of this design, describe the development testing, and show the results from the valve level tests performed. Also, a trade study is presented to show the advantages of this design to a conventional pyrotechnic based valve.

  8. Implications of Dynamic Pressure Transducer Mounting Variations on Measurements in Pyrotechnic Test Apparatus

    NASA Technical Reports Server (NTRS)

    Dibbern, Andreas; Crisafulli, Jeffrey; Hagopia, Michael; McDougle, Stephen H.; Saulsberry, Regor L.

    2009-01-01

    Accurate dynamic pressure measurements are often difficult to make within small pyrotechnic devices, and transducer mounting difficulties can cause data anomalies that lead to erroneous conclusions. Delayed initial pressure response followed by data ringing has been observed when using miniaturized pressure transducer mounting adapters required to interface transducers to small test chambers. This delayed pressure response and ringing, combined with a high data acquisition rate, has complicated data analysis. This paper compares the output signal characteristics from different pressure transducer mounting options, where the passage distance from the transducer face to the pyrotechnic chamber is varied in length and diameter. By analyzing the data and understating the associated system dynamics, a more realistic understanding of the actual dynamic pressure variations is achieved. Three pressure transducer mounting configurations (elongated, standard, and face/flush mount) were simultaneously tested using NASA standard initiators in closed volume pressure bombs. This paper also presents results of these pressure transducer mounting configurations as a result of a larger NASA Engineering and Safety Center pyrovalve test project. Results from these tests indicate the improved performance of using face/flush mounted pressure transducers in this application. This type of mounting improved initial pressure measurement response time by approximately 19 s over standard adapter mounting, eliminating most of the lag time; provided a near step-function type initial pressure increase; and greatly reduced data ringing in high data acquisition rate systems. The paper goes on to discuss other issues associated with the firing and instrumentation that are important for the tester to understand.

  9. 46 CFR 160.024-4 - Approval and production tests.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... every ten lots of signals produced, except that the number of technical tests must be at least one but... satisfactorily when shot from a pistol of the type described in subpart 160.028. The parachute and pyrotechnic...

  10. 46 CFR 160.024-4 - Approval and production tests.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... every ten lots of signals produced, except that the number of technical tests must be at least one but... satisfactorily when shot from a pistol of the type described in subpart 160.028. The parachute and pyrotechnic...

  11. Effects of unregulated anthropogenic activities on mixing ratios of volatile organic air pollutants--A case study.

    PubMed

    Majumdar, Dipanjali; Rao, Padma S; Chakraborty, Bipasha Dinda; Srivastava, Anjali

    2015-09-01

    During the months of October to November, many important festivals are celebrated in India. Celebration of these festivals are marked by extensive use of fireworks or pyrotechnics, bonfire, incense burning, open air community cooking, and temporary eateries using crude fuel such as coal, wood, kerosene, cow dung, burning of raw/semiwood, and coconut shells. The present study deals with the influence of these unregulated anthropogenic activities on ambient mixing level of volatile organic compounds (VOCs), especially some carbonyl compounds. The study was undertaken in the metropolitan city of Kolkata, India, with very high population density, which is even higher during festival period. The average total carbonyl level at different sites in Kolkata varied from 134.8 to 516.5 μg m(-3) in pre-festival season, whereas in post-festival season the same varied from 252.2 to 589.3 μg m(-3). Formaldehyde to acetaldehyde ratio altered from 0.62 in pre-festival season to 1.78 in post-festival season. Diurnal variation also altered, indicating variation in source composition of carbonyls. The total ozone forming potential calculated for all 14 carbonyls in pre-festival season increased by 35% in post-festival season. The effect of anthropogenic activities typical to the event of Diwali night characterized by intense execution of pyrotechnics resulted in significantly high level of carbonyl VOCs. Principal component analysis study for the event of Diwali shows clear contribution of the event on certain carbonyl VOCs. The results indicate elevated primary emissions of these pollutants and also their effect on formation of secondary pollutants. The study emphasizes the need of generating awareness among the communities in society as well as need for regulations to minimize the emissions and related hazards to the extent possible. Altered anthropogenic activities typical of festival season including extensive use of pyrotechnics affect ambient level of volatile organic compounds, especially some carbonyls. Such activities have considerable effect on interspecies ratio and diurnal variation. They also affect formation of secondary pollutants such as tropospheric ozone. Principal component analysis (PCA) study shows clear contribution of the pyrotechnics execution on certain carbonyl VOCs. The findings emphasize the need of generating awareness in society and need for regulations to minimize the emissions.

  12. Ariane 5 Payload Fairing Test

    NASA Image and Video Library

    2012-04-30

    NASA Glenn conducted a test on the Ariane 5 Payload Fairing at Plum Brook’s Space Power Facility (SPF). The test was to qualify a new horizontal pyrotechnic separation system, which blew the two fairing halves apart and away from the payload during flight.

  13. Pyrotechnic Shock Analysis Using Statistical Energy Analysis

    DTIC Science & Technology

    2015-10-23

    SEA subsystems. A couple of validation examples are provided to demonstrate the new approach. KEY WORDS : Peak Ratio, phase perturbation...Ballistic Shock Prediction Models and Techniques for Use in the Crusader Combat Vehicle Program,” 11th Annual US Army Ground Vehicle Survivability

  14. Theoretical Studies of Nanoclusters (Briefing Charts)

    DTIC Science & Technology

    2015-07-23

    nanoclusters. However, scanning transmission electron microscopy ( STEM ) measures show cluster inversion occurred to produce MgyCux(!) a) copper atoms b...methane (née CLL -1) as a potential explosive ingredient: a theoretical study”, Propellants, Explosives, Pyrotechnics 38, 9-13 (2013). Jesus Paulo L

  15. 46 CFR 160.038-5 - Marking.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ...: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Magazine Chests, Portable, for Merchant Vessels § 160.038-5 Marking. (a) Portable magazine chests used for the stowage of pyrotechnic signals, rockets, and powder for...: “Portable Magazine Chest, Inflammable—Keep Lights and Fire Away.” (b) [Reserved] ...

  16. GEMINI-TITAN (GT)-11 - PREFLIGHT PREP - CHECKOUT - CAPE

    NASA Image and Video Library

    1966-07-21

    S66-47635 (21 July 1966) --- McDonnell Aircraft Corporation personnel bolt the Gemini-11 spacecraft to a support ring for bore sighting in the Pyrotechnic Installation Building, Merritt Island, during checkout and preflight preparations at the Kennedy Space Center. Photo credit: NASA

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

    Abbas, Syed Haider; Lee, Jung-Ryul; Jang, Jae-Kyeong

    Pyroshock can cause failure to the objective of an aerospace structure by damaging its sensitive electronic equipment, which is responsible for performing decisive operations. A pyroshock is the high intensity shock wave that is generated when a pyrotechnic device is explosively triggered to separate, release, or activate structural subsystems of an aerospace architecture. Pyroshock measurement plays an important role in experimental simulations to understand the characteristics of pyroshock on the host structure. This paper presents a technology to measure a pyroshock wave at multiple points using laser Doppler vibrometers (LDVs). These LDVs detect the pyroshock wave generated due to anmore » explosive-based pyrotechnical event. Field programmable gate array (FPGA) based data acquisition is used in the study to acquire pyroshock signals simultaneously from multiple channels. This paper describes the complete system design for multipoint pyroshock measurement. The firmware architecture for the implementation of multichannel data acquisition on an FPGA-based development board is also discussed. An experiment using explosive bolts was configured to test the reliability of the system. Pyroshock was generated using explosive excitation on a 22-mm-thick steel plate. Three LDVs were deployed to capture the pyroshock wave at different points. The pyroshocks captured were displayed as acceleration plots. The results showed that our system effectively captured the pyroshock wave with a peak-to-peak magnitude of 303 741 g. The contribution of this paper is a specialized architecture of firmware design programmed in FPGA for data acquisition of large amount of multichannel pyroshock data. The advantages of the developed system are the near-field, multipoint, non-contact, and remote measurement of a pyroshock wave, which is dangerous and expensive to produce in aerospace pyrotechnic tests.« less

  18. Development of an FPGA-based multipoint laser pyroshock measurement system for explosive bolts

    NASA Astrophysics Data System (ADS)

    Abbas, Syed Haider; Jang, Jae-Kyeong; Lee, Jung-Ryul; Kim, Zaeill

    2016-07-01

    Pyroshock can cause failure to the objective of an aerospace structure by damaging its sensitive electronic equipment, which is responsible for performing decisive operations. A pyroshock is the high intensity shock wave that is generated when a pyrotechnic device is explosively triggered to separate, release, or activate structural subsystems of an aerospace architecture. Pyroshock measurement plays an important role in experimental simulations to understand the characteristics of pyroshock on the host structure. This paper presents a technology to measure a pyroshock wave at multiple points using laser Doppler vibrometers (LDVs). These LDVs detect the pyroshock wave generated due to an explosive-based pyrotechnical event. Field programmable gate array (FPGA) based data acquisition is used in the study to acquire pyroshock signals simultaneously from multiple channels. This paper describes the complete system design for multipoint pyroshock measurement. The firmware architecture for the implementation of multichannel data acquisition on an FPGA-based development board is also discussed. An experiment using explosive bolts was configured to test the reliability of the system. Pyroshock was generated using explosive excitation on a 22-mm-thick steel plate. Three LDVs were deployed to capture the pyroshock wave at different points. The pyroshocks captured were displayed as acceleration plots. The results showed that our system effectively captured the pyroshock wave with a peak-to-peak magnitude of 303 741 g. The contribution of this paper is a specialized architecture of firmware design programmed in FPGA for data acquisition of large amount of multichannel pyroshock data. The advantages of the developed system are the near-field, multipoint, non-contact, and remote measurement of a pyroshock wave, which is dangerous and expensive to produce in aerospace pyrotechnic tests.

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

    Lechman, Jeremy B.; Battaile, Corbett Chandler.; Bolintineanu, Dan

    This report summarizes a project in which the authors sought to develop and deploy: (i) experimental techniques to elucidate the complex, multiscale nature of thermal transport in particle-based materials; and (ii) modeling approaches to address current challenges in predicting performance variability of materials (e.g., identifying and characterizing physical- chemical processes and their couplings across multiple length and time scales, modeling information transfer between scales, and statically and dynamically resolving material structure and its evolution during manufacturing and device performance). Experimentally, several capabilities were successfully advanced. As discussed in Chapter 2 a flash diffusivity capability for measuring homogeneous thermal conductivity ofmore » pyrotechnic powders (and beyond) was advanced; leading to enhanced characterization of pyrotechnic materials and properties impacting component development. Chapter 4 describes success for the first time, although preliminary, in resolving thermal fields at speeds and spatial scales relevant to energetic components. Chapter 7 summarizes the first ever (as far as the authors know) application of TDTR to actual pyrotechnic materials. This is the first attempt to actually characterize these materials at the interfacial scale. On the modeling side, new capabilities in image processing of experimental microstructures and direct numerical simulation on complicated structures were advanced (see Chapters 3 and 5). In addition, modeling work described in Chapter 8 led to improved prediction of interface thermal conductance from first principles calculations. Toward the second point, for a model system of packed particles, significant headway was made in implementing numerical algorithms and collecting data to justify the approach in terms of highlighting the phenomena at play and pointing the way forward in developing and informing the kind of modeling approach originally envisioned (see Chapter 6). In both cases much more remains to be accomplished.« less

  20. Development of Methodologies Evaluating Emissions from Metal-Containing Explosives and Propellants

    DTIC Science & Technology

    Experiments were performed to develop methodologies that will allow determination of pollutant emission factors for gases and particles produced by...micrometer, 16 by weight). Although not included here, the analysis methods described will be directly applicable to the study of pyrotechnics.

  1. 46 CFR 160.066-15 - Production testing.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 6 2011-10-01 2011-10-01 false Production testing. 160.066-15 Section 160.066-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  2. 46 CFR 160.066-7 - Performance requirements.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 6 2011-10-01 2011-10-01 false Performance requirements. 160.066-7 Section 160.066-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  3. 46 CFR 160.066-10 - Expiration date.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 6 2010-10-01 2010-10-01 false Expiration date. 160.066-10 Section 160.066-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  4. 46 CFR 160.066-7 - Performance requirements.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 6 2010-10-01 2010-10-01 false Performance requirements. 160.066-7 Section 160.066-7 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  5. 46 CFR 160.066-15 - Production testing.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 6 2010-10-01 2010-10-01 false Production testing. 160.066-15 Section 160.066-15 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  6. 46 CFR 160.066-10 - Expiration date.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 6 2011-10-01 2011-10-01 false Expiration date. 160.066-10 Section 160.066-10 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160...

  7. 76 FR 38053 - Clarification of the Fireworks Approvals Policy

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    .... Background The pyrotechnic industry is a global logistics supply chain comprised of mostly foreign fireworks... between these two entities. All participants throughout the supply chain will be held accountable for... document. One commenter requests PHMSA consider waste management of used or defective fireworks when...

  8. Pyrotechnic Smoke Compositions Containing Boron Carbide

    DTIC Science & Technology

    2012-06-10

    resulting smoke. The inhalation of zinc fumes is known to cause “metal fume fever” and the smoke also contains various chlorinated organic compounds...matches were used to ignite the slurried items. Bare pellets were ignited with electrically heated nickel- chromium wire (hot wire). Small HC smoke

  9. Kinetics Modeling of Hypergolic Propellants

    DTIC Science & Technology

    2013-07-01

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

  10. A Statistical Representation of Pyrotechnic Igniter Output

    NASA Astrophysics Data System (ADS)

    Guo, Shuyue; Cooper, Marcia

    2017-06-01

    The output of simplified pyrotechnic igniters for research investigations is statistically characterized by monitoring the post-ignition external flow field with Schlieren imaging. Unique to this work is a detailed quantification of all measurable manufacturing parameters (e.g., bridgewire length, charge cavity dimensions, powder bed density) and associated shock-motion variability in the tested igniters. To demonstrate experimental precision of the recorded Schlieren images and developed image processing methodologies, commercial exploding bridgewires using wires of different parameters were tested. Finally, a statistically-significant population of manufactured igniters were tested within the Schlieren arrangement resulting in a characterization of the nominal output. Comparisons between the variances measured throughout the manufacturing processes and the calculated output variance provide insight into the critical device phenomena that dominate performance. Sandia National Laboratories is a multi-mission laboratory managed and operated by Sandia Corporation, a wholly owned subsidiary of Lockheed Martin Corporation, for the U.S. Department of Energy's NNSA under contract DE-AC04-94AL85000.

  11. Process for preparing energetic materials

    DOEpatents

    Simpson, Randall L [Livermore, CA; Lee, Ronald S [Livermore, CA; Tillotson, Thomas M [Tracy, CA; Hrubesh, Lawrence W [Pleasanton, CA; Swansiger, Rosalind W [Livermore, CA; Fox, Glenn A [Livermore, CA

    2011-12-13

    Sol-gel chemistry is used for the preparation of energetic materials (explosives, propellants and pyrotechnics) with improved homogeneity, and/or which can be cast to near-net shape, and/or made into precision molding powders. The sol-gel method is a synthetic chemical process where reactive monomers are mixed into a solution, polymerization occurs leading to a highly cross-linked three dimensional solid network resulting in a gel. The energetic materials can be incorporated during the formation of the solution or during the gel stage of the process. The composition, pore, and primary particle sizes, gel time, surface areas, and density may be tailored and controlled by the solution chemistry. The gel is then dried using supercritical extraction to produce a highly porous low density aerogel or by controlled slow evaporation to produce a xerogel. Applying stress during the extraction phase can result in high density materials. Thus, the sol-gel method can be used for precision detonator explosive manufacturing as well as producing precision explosives, propellants, and pyrotechnics, along with high power composite energetic materials.

  12. Sol-Gel Manufactured Energetic Materials

    DOEpatents

    Simpson, Randall L.; Lee, Ronald S.; Tillotson, Thomas M.; Hrubesh, Lawrence W.; Swansiger, Rosalind W.; Fox, Glenn A.

    2005-05-17

    Sol-gel chemistry is used for the preparation of energetic materials (explosives, propellants and pyrotechnics) with improved homogeneity, and/or which can be cast to near-net shape, and/or made into precision molding powders. The sol-gel method is a synthetic chemical process where reactive monomers are mixed into a solution, polymerization occurs leading to a highly cross-linked three dimensional solid network resulting in a gel. The energetic materials can be incorporated during the formation of the solution or during the gel stage of the process. The composition, pore, and primary particle sizes, gel time, surface areas, and density may be tailored and controlled by the solution chemistry. The gel is then dried using supercritical extraction to produce a highly porous low density aerogel or by controlled slow evaporation to produce a xerogel. Applying stress during the extraction phase can result in high density materials. Thus, the sol-gel method can be used for precision detonator explosive manufacturing as well as producing precision explosives, propellants, and pyrotechnics, along with high power composite energetic materials.

  13. Sol-gel manufactured energetic materials

    DOEpatents

    Simpson, Randall L.; Lee, Ronald S.; Tillotson, Thomas M.; Hrubesh, Lawrence W.; Swansiger, Rosalind W.; Fox, Glenn A.

    2003-12-23

    Sol-gel chemistry is used for the preparation of energetic materials (explosives, propellants and pyrotechnics) with improved homogeneity, and/or which can be cast to near-net shape, and/or made into precision molding powders. The sol-gel method is a synthetic chemical process where reactive monomers are mixed into a solution, polymerization occurs leading to a highly cross-linked three dimensional solid network resulting in a gel. The energetic materials can be incorporated during the formation of the solution or during the gel stage of the process. The composition, pore, and primary particle sizes, gel time, surface areas, and density may be tailored and controlled by the solution chemistry. The gel is then dried using supercritical extraction to produce a highly porous low density aerogel or by controlled slow evaporation to produce a xerogel. Applying stress during the extraction phase can result in high density materials. Thus, the sol-gel method can be used for precision detonator explosive manufacturing as well as producing precision explosives, propellants, and pyrotechnics, along with high power composite energetic materials.

  14. 46 CFR 199.45 - Tests and inspections of lifesaving equipment and arrangements.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... rescue boats, including engines and release mechanisms; (3) The proper condition of flotation equipment... indicating radiobeacons (EPIRB), search and rescue transponders (SART), and pyrotechnic signaling devices; (5... repeated; (2) The proper condition and operation of lifeboats and rescue boats, including engines and...

  15. 46 CFR 199.45 - Tests and inspections of lifesaving equipment and arrangements.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... rescue boats, including engines and release mechanisms; (3) The proper condition of flotation equipment... indicating radiobeacons (EPIRB), search and rescue transponders (SART), and pyrotechnic signaling devices; (5... repeated; (2) The proper condition and operation of lifeboats and rescue boats, including engines and...

  16. 46 CFR 199.45 - Tests and inspections of lifesaving equipment and arrangements.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... rescue boats, including engines and release mechanisms; (3) The proper condition of flotation equipment... indicating radiobeacons (EPIRB), search and rescue transponders (SART), and pyrotechnic signaling devices; (5... repeated; (2) The proper condition and operation of lifeboats and rescue boats, including engines and...

  17. Alternatives to Pyrotechnic Distress Signals; Laboratory and Field Studies

    DTIC Science & Technology

    2015-03-01

    using night vision imaging systems (NVIS) with “minus-blue” filtering,” the project recommends additional research and testing leading to the inclusion...18  5.2.3  Background Images ...Example of image capture from radiant imaging colorimeter. ....................................................... 16  Figure 10. Laboratory setup

  18. LIFE-CYCLE IMPACT ASSESSMENT DEMONSTRATION FOR THE BGU-24

    EPA Science Inventory

    The primary goal of this project was to develop and demonstrate a life-cycle impact assessment (LCIA) approach using existing life-cycle inventory (LCI) data on one of the propellants, energetics, and pyrotechnic (PEP) materials of interest to the U.S. Department of Defense (DoD)...

  19. Rapidly Degradable Pyrotechnic System

    DTIC Science & Technology

    2009-02-01

    casing. The second material and primary focus of the program effort was the improvement of a newly emerging enzyme , a thermophilic hydrolase formed...12 3.2.4.1 Details of Selected Enzyme (Description, Production and Environmental Impact) ......................14 4. MATERIALS AND METHODS...24 5.3 Improvement of extracelular enzyme secretion

  20. 46 CFR 199.45 - Tests and inspections of lifesaving equipment and arrangements.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... rescue boats, including engines and release mechanisms; (3) The proper condition of flotation equipment... indicating radiobeacons (EPIRB), search and rescue transponders (SART), and pyrotechnic signaling devices; (5... repeated; (2) The proper condition and operation of lifeboats and rescue boats, including engines and...

  1. 46 CFR 199.45 - Tests and inspections of lifesaving equipment and arrangements.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... rescue boats, including engines and release mechanisms; (3) The proper condition of flotation equipment... indicating radiobeacons (EPIRB), search and rescue transponders (SART), and pyrotechnic signaling devices; (5... repeated; (2) The proper condition and operation of lifeboats and rescue boats, including engines and...

  2. 16 CFR 1507.6 - Burnout and blowout.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 16 Commercial Practices 2 2011-01-01 2011-01-01 false Burnout and blowout. 1507.6 Section 1507.6... FIREWORKS DEVICES § 1507.6 Burnout and blowout. The pyrotechnic chamber in fireworks devices shall be constructed in a manner to allow functioning in a normal manner without burnout or blowout. ...

  3. 16 CFR 1507.6 - Burnout and blowout.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 16 Commercial Practices 2 2014-01-01 2014-01-01 false Burnout and blowout. 1507.6 Section 1507.6... FIREWORKS DEVICES § 1507.6 Burnout and blowout. The pyrotechnic chamber in fireworks devices shall be constructed in a manner to allow functioning in a normal manner without burnout or blowout. ...

  4. 16 CFR 1507.6 - Burnout and blowout.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 16 Commercial Practices 2 2012-01-01 2012-01-01 false Burnout and blowout. 1507.6 Section 1507.6... FIREWORKS DEVICES § 1507.6 Burnout and blowout. The pyrotechnic chamber in fireworks devices shall be constructed in a manner to allow functioning in a normal manner without burnout or blowout. ...

  5. 16 CFR 1507.6 - Burnout and blowout.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 16 Commercial Practices 2 2010-01-01 2010-01-01 false Burnout and blowout. 1507.6 Section 1507.6... FIREWORKS DEVICES § 1507.6 Burnout and blowout. The pyrotechnic chamber in fireworks devices shall be constructed in a manner to allow functioning in a normal manner without burnout or blowout. ...

  6. 6. Photocopy of drawing (1976 structural drawing by the Space ...

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

    6. Photocopy of drawing (1976 structural drawing by the Space and Missile Test Center, VAFB, USAF) FLOOR PLAN, ELEVATIONS, SECTIONS, AND DETAILS FOR THE PYROTEST AND STORAGE BUILDING, SHEET S22 - Vandenberg Air Force Base, Space Launch Complex 3, Pyrotechnic Shed, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  7. 75 FR 60017 - Hazardous Materials; Miscellaneous Amendments

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-09-29

    .... 173.56(j) to further clarify the use of the American Pyrotechnics Association (APA) standard for... language in Sec. 172.404(c) obviates the need for a separate definition for ``consolidation bin'' in Sec... standards include, but are not limited to, the following: Section 172.101(c) provides instruction on the use...

  8. 49 CFR 173.186 - Matches.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... matches the heads of which are prepared with a friction-sensitive igniter composition and a pyrotechnic... combined with or attached to the box, book or card that can be ignited by friction only on a prepared surface. (3) Strike anywhere matches are matches that can be ignited by friction on a solid surface. (4...

  9. 49 CFR 173.186 - Matches.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... matches the heads of which are prepared with a friction-sensitive igniter composition and a pyrotechnic... combined with or attached to the box, book or card that can be ignited by friction only on a prepared surface. (3) Strike anywhere matches are matches that can be ignited by friction on a solid surface. (4...

  10. 49 CFR 173.186 - Matches.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... matches the heads of which are prepared with a friction-sensitive igniter composition and a pyrotechnic... combined with or attached to the box, book or card that can be ignited by friction only on a prepared surface. (3) Strike anywhere matches are matches that can be ignited by friction on a solid surface. (4...

  11. 49 CFR 173.186 - Matches.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... matches the heads of which are prepared with a friction-sensitive igniter composition and a pyrotechnic... combined with or attached to the box, book or card that can be ignited by friction only on a prepared surface. (3) Strike anywhere matches are matches that can be ignited by friction on a solid surface. (4...

  12. LIFE-CYCLE IMPACT ASSESSMENT DEMONSTRATION FOR THE GBU-24

    EPA Science Inventory

    The primary goal of this project was to develop and demonstrate a life-cycle impact assessment (LCIA) approach using existing life-cycle inventory (LCI) data on one of the propellants, energetics, and pyro-technic (PEP) materials of interest to the U.S. Department of Defense (DoD...

  13. 46 CFR 160.066-5 - Design, construction, and manufacturing requirements.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 46 Shipping 6 2010-10-01 2010-10-01 false Design, construction, and manufacturing requirements... Boats, Red Aerial Pyrotechnic Flare § 160.066-5 Design, construction, and manufacturing requirements. (a... details occurs; (2) Any change in sources of raw materials occurs; (3) Production is started on a new...

  14. 49 CFR 173.186 - Matches.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... matches the heads of which are prepared with a friction-sensitive igniter composition and a pyrotechnic... combined with or attached to the box, book or card that can be ignited by friction only on a prepared surface. (3) Strike anywhere matches are matches that can be ignited by friction on a solid surface. (4...

  15. LOW-LEVEL DETERMINATION OF PERCHLORATE IN DRINKING WATER USING ION CHROMATOGRAPHY MASS SPECTROMETRY

    EPA Science Inventory

    Perchlorate is a drinking water contaminant originating from the dissolution of the salts of ammonium, potassium, magnesium, or sodium in water. It is used primarily as an oxidant in solid propellant for rockets, missiles, pyrotechnics, as a component in air bag inflators, and i...

  16. DEVELOPMENT OF A BETTER METHOD TO IDENTIFY AND MEASURE PERCHLORATE IN DRINKING WATER

    EPA Science Inventory

    Perchlorate (ClO4 -) is an oxidant used primarily in solid propellant for rockets, missiles, pyrotechnics, as a component in air bag inflators, and in highway safety flares. Perchlorate tainted water has been found throughout the southwestern United States where its source has o...

  17. Low-Cost Production of Nano-Pyrotechnics

    DTIC Science & Technology

    2010-07-01

    possibly flawed. Two well-known materials. HMX and picric acid , with known impact sensitivities were tested and the results were compared with...However, the HMX used could not be confirmed to be a high level of purity. As a result, lab grade picric acid was tested and EMPl’s numbers agreed

  18. 16 CFR § 1507.6 - Burnout and blowout.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 16 Commercial Practices 2 2013-01-01 2013-01-01 false Burnout and blowout. § 1507.6 Section Â... REGULATIONS FIREWORKS DEVICES § 1507.6 Burnout and blowout. The pyrotechnic chamber in fireworks devices shall be constructed in a manner to allow functioning in a normal manner without burnout or blowout. ...

  19. 77 FR 429 - Clarification and Further Guidance on the Fireworks Approvals Policy

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-01-05

    ...) and the American Pyrotechnic Association (APA) Standard 87-1. PHMSA understands that it is a common... approval is requested conforms to the APA Standard 87-1, and the descriptions and technical information... manufacturer must sign and certify that the device for which the approval is requested conforms to the APA...

  20. The Swedish Rocket Corps, 1833 - 1845

    NASA Technical Reports Server (NTRS)

    Skoog, A. I.

    1977-01-01

    Rockets for pyrotechnic displays used in Sweden in the 19th century are examined in terms of their use in war situations. Work done by the Swedish chemist J. J. Berzelius, who analyzed and improved the propellants of such rockets, and the German engineer, Martin Westermaijer, who researched manufacturing techniques of these rockets is also included.

  1. Suitability of Potential Alternatives to Pyrotechnic Distress Signals

    DTIC Science & Technology

    2012-02-01

    the following convolution : )()()( tqtIti  Equation (1) Given that  2 )( ta a tq   Equation (2) Where a = 0.2 for night time use...military five-finger gloves, equipped with a three-layer laminate insert. The back of the gloves is made from five-color camouflage fabric; the

  2. 46 CFR 160.066-5 - Design, construction, and manufacturing requirements.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 6 2011-10-01 2011-10-01 false Design, construction, and manufacturing requirements. 160.066-5 Section 160.066-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-5...

  3. 46 CFR 160.066-5 - Design, construction, and manufacturing requirements.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 6 2014-10-01 2014-10-01 false Design, construction, and manufacturing requirements. 160.066-5 Section 160.066-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-5...

  4. 46 CFR 160.066-5 - Design, construction, and manufacturing requirements.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 6 2013-10-01 2013-10-01 false Design, construction, and manufacturing requirements. 160.066-5 Section 160.066-5 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) EQUIPMENT, CONSTRUCTION, AND MATERIALS: SPECIFICATIONS AND APPROVAL LIFESAVING EQUIPMENT Distress Signal for Boats, Red Aerial Pyrotechnic Flare § 160.066-5...

  5. MEASUREMENT OF PERCHLORATE IN WATER USING AN OXYGEN-18 ENRICHED ISOTOPE STANDARD AND ION CHROMATOGRAPHY MASS SPECTROMETRIC DETECTION

    EPA Science Inventory

    Perchlorate (ClO4 -) is a drinking water contaminant originating from the dissolution of the salts of ammonium, potassium, magnesium, or sodium in water. It is used primarily as an oxidant in solid propellant for rockets, missiles, pyrotechnics, as a component in air bag infla...

  6. 49 CFR 173.166 - Air bag inflators, air bag modules and seat-belt pretensioners.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ..., pyrotechnic for technical purposes” as specified in Special Provision 161 (see § 172.102 of this subchapter... Class 9 material. (4) Shipments to recycling or waste disposal facilities. When offered for domestic...) of this section. However, when these articles are shipped to a recycling facility, the word “Recycled...

  7. 49 CFR 173.166 - Air bag inflators, air bag modules and seat-belt pretensioners.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ..., pyrotechnic for technical purposes” as specified in Special Provision 161 (see § 172.102 of this subchapter... Class 9 material. (4) Shipments to recycling or waste disposal facilities. When offered for domestic...) of this section. However, when these articles are shipped to a recycling facility, the word “Recycled...

  8. Compilation and Preliminary Analysis of Sensitivity Data for Pyrotechnics. Phase 1

    DTIC Science & Technology

    1975-05-01

    700-2, except Green smoke (sulfur based) and match head Mix VI which were tested 6 and 11 times respectively. Optical pyrometer measurements of the...Photographic estimates indicated that an acoustic wave was formed during dust cloud fireball growth. 17 2. 2.3.11.5 Jet Airmix Blending. Bench

  9. Simulator for Testing Spacecraft Separation Devices

    NASA Technical Reports Server (NTRS)

    Johnston, Nick; Gaines, Joe; Bryan, Tom

    2006-01-01

    A report describes the main features of a system for testing pyrotechnic and mechanical devices used to separate spacecraft and modules of spacecraft during flight. The system includes a spacecraft simulator [also denoted a large mobility base (LMB)] equipped with air thrusters, sensors, and data-acquisition equipment. The spacecraft simulator floats on air bearings over an epoxy-covered concrete floor. This free-flotation arrangement enables simulation of motion in outer space in three degrees of freedom: translation along two orthogonal horizontal axes and rotation about a vertical axis. The system also includes a static stand. In one application, the system was used to test a bolt-retraction system (BRS) intended for separation of the lifting-body and deorbit-propulsion stages of the X- 38 spacecraft. The LMB was connected via the BRS to the static stand, then pyrotechnic devices that actuate the BRS were fired. The separation distance and acceleration were measured. The report cites a document, not yet published at the time of reporting the information for this article, that is said to present additional detailed information.

  10. Neutron radiography in Indian space programme

    NASA Astrophysics Data System (ADS)

    Viswanathan, K.

    1999-11-01

    Pyrotechnic devices are indispensable in any space programme to perform such critical operations as ignition, stage separation, solar panel deployment, etc. The nature of design and configuration of different types of pyrotechnic devices, and the type of materials that are put in their construction make the inspection of them with thermal neutrons more favourable than any other non destructive testing methods. Although many types of neutron sources are available for use, generally the radiographic quality/exposure duration and cost of source run in opposite directions even after four decades of research and development. But in the area of space activity, by suitably combining the X-ray and neutron radiographic requirements, the inspection of the components can be made economically viable. This is demonstrated in the Indian space programme by establishing a 15 MeV linear accelerator based neutron generator facility to inspect medium to giant solid propellant boosters by X-ray inspection and all types of critical pyro and some electronic components by neutron radiography. Since the beam contains unacceptable gamma, transfer imaging technique has been evolved and the various parameters have been optimised to get a good quality image.

  11. 78 FR 39057 - Hours of Service of Drivers; Renewal and Expansion of American Pyrotechnics Association Exemption...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-06-28

    ... Association (APA) from FMCSA's regulation prohibiting drivers of commercial motor vehicles (CMVs) from driving after the 14th hour after coming on duty. The FMCSA renews the exemption for 45 APA member-companies and... carrier is being denied. Additionally, the APA advised FMCSA of the removal from the original renewal...

  12. 3. VIEW OF WEST AND SOUTH FACES OF VEHICLE SUPPORT ...

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

    3. VIEW OF WEST AND SOUTH FACES OF VEHICLE SUPPORT BUILDING. NOTE BLAST-PROTECTION WALL SURROUNDING DOOR TO ROOM 106 (PYROTECHNIC STORAGE ROOM) NEAR SOUTHWEST CORNER. East face not accesible for photography due to proximity of security fence. - Vandenberg Air Force Base, Space Launch Complex 3, Vehicle Support Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  13. 46 CFR 160.038-3 - Materials, workmanship, and construction.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... of the metal chest and fittings shall be given a heavy coat of quick drying red lead, zinc chromate... be constructed of metal and lined with wood. (b) The lining shall be so fitted and finished as to... explosives or pyrotechnics from contact with metal surfaces. (c) The metal shall be 1/8 inch thick and free...

  14. 46 CFR 160.038-3 - Materials, workmanship, and construction.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... of the metal chest and fittings shall be given a heavy coat of quick drying red lead, zinc chromate... be constructed of metal and lined with wood. (b) The lining shall be so fitted and finished as to... explosives or pyrotechnics from contact with metal surfaces. (c) The metal shall be 1/8 inch thick and free...

  15. 46 CFR 160.038-3 - Materials, workmanship, and construction.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... of the metal chest and fittings shall be given a heavy coat of quick drying red lead, zinc chromate... be constructed of metal and lined with wood. (b) The lining shall be so fitted and finished as to... explosives or pyrotechnics from contact with metal surfaces. (c) The metal shall be 1/8 inch thick and free...

  16. 46 CFR 160.038-3 - Materials, workmanship, and construction.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... of the metal chest and fittings shall be given a heavy coat of quick drying red lead, zinc chromate... be constructed of metal and lined with wood. (b) The lining shall be so fitted and finished as to... explosives or pyrotechnics from contact with metal surfaces. (c) The metal shall be 1/8 inch thick and free...

  17. 46 CFR 160.038-3 - Materials, workmanship, and construction.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... of the metal chest and fittings shall be given a heavy coat of quick drying red lead, zinc chromate... be constructed of metal and lined with wood. (b) The lining shall be so fitted and finished as to... explosives or pyrotechnics from contact with metal surfaces. (c) The metal shall be 1/8 inch thick and free...

  18. Pulmonary Effects of Pyrotechnically Disseminated Titanium Dioxide Smoke in Rats

    DTIC Science & Technology

    2007-05-01

    Series Perkin Elmer AA (Boston, MA) with a nitrous oxide/acetylene burner head. Hollow cathode lamp elements specific for each metal were used. The primary...supematant was removed from the cell pellet . The pellet was resuspended in 1 mL of 50% bovine serum albumin and total cell counts were taken on a ZBI

  19. Mound powder loader, Mod 1

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

    Gress, A.V. Jr.

    1985-08-21

    At the investigation of Sandia Albuquerque, a semiautomatic powder loader was designed and fabricated for pyrotechnics devices. The basic functions of the system were to load a precise, measured amount of powder into a charge holder and to compact the mixture to a specified density. This report documents the history, rationale, design, and performance of the Mod 1 loader.

  20. 75 FR 79085 - Notice and Request for Comments on the Clarification of the Fireworks Approvals Policy

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-12-17

    ...., Washington, DC 20590. Background The pyrotechnic industry is a global logistics supply chain comprised of... position in the supply chain. It is unclear as to what was the justification for this action. Regardless... Docket Management System (FDMS), including any personal information. Docket: For access to the dockets to...

  1. 76 FR 71535 - Taking of Marine Mammals Incidental to Specified Activities; U.S. Marine Corps Training Exercises...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-11-18

    ... small arms, large arms, bombs, rockets, missiles, and pyrotechnics. All munitions used at BT-11 are... shapes each time. Mine simulation shapes include MK76, MK80 series, and BDU practice bombs ranging from... disabling enemy ships or boats. During training, fixed wing or rotary wing aircraft deliver bombs against...

  2. 76 FR 64969 - Notice of Final Supplementary Rules Concerning Fireworks on Public Land in Colorado

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-19

    .... ADDRESSES: You may send inquiries by mail to the Office of Law Enforcement, BLM Colorado State Office, 2850... above individual. You will receive a reply during normal business hours. SUPPLEMENTARY INFORMATION: I... fountains, total pyrotechnic composition not to exceed 75 grams each for a single tube or, when more than...

  3. DETERMINATION OF PERCHLORATE BY ION CHROMATOGRAPHY, SUPPRESSED CONDUCTIVITY AND MASS SPECTROMETRIC DETECTION USING AN OXYGEN-18 ENRICHED ISOTROPIC INTERNAL STANDARD

    EPA Science Inventory

    Perchlorate (ClO4 -) is a drinking water contaminant originating from the dissolution of the salts of ammonium, potassium, magnesium, or sodium in water. It is used primarily as an oxidant in solid propellant for rockets, missiles, pyrotechnics, as a component in air bag infla...

  4. SUB-PPB QUANTITATION AND CONFIRMATION OF PERCHLORATE IN DRINKING WATERS CONTAINING HIGH TOTAL DISSOLVED SOLIDS USING ION CHROMATOGRAPHY WITH MASS SPECTROMETRIC DETECTION

    EPA Science Inventory

    Perchlorate (ClO4 -) is a drinking water contaminant originating from the dissolution of the salts of ammonium, potassium, magnesium, or sodium in water. It is used primarily as an oxidant in solid propellant for rockets, missiles, pyrotechnics, as a component in air bag infla...

  5. MEASUREMENT OF PERCHLORATE IN WATER BY USE OF AN 18O-ENRICHED ISOTOPIC STANDARD AND ION CHROMATOGRAPHY WITH MASS SPECTROMETRIC DETECTION

    EPA Science Inventory

    Perchlorate (ClO4-) is a drinking water contaminant originating from the dissolution of the salts of ammonium, potassium, magnesium, or sodium in water. It is used primarily as an oxidant in solid propellant for rockets, missiles, pyrotechnics, as a compone...

  6. 46 CFR 160.024-4 - Approval and production tests.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... every ten lots of signals produced, except that the number of technical tests must be at least one but.... (Table 160.024-4(c)(2)) is assigned a score (failure percent) in accordance with the table. In the case... satisfactorily when shot from a pistol of the type described in subpart 160.028. The parachute and pyrotechnic...

  7. 46 CFR 160.024-4 - Approval and production tests.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... every ten lots of signals produced, except that the number of technical tests must be at least one but.... (Table 160.024-4(c)(2)) is assigned a score (failure percent) in accordance with the table. In the case... satisfactorily when shot from a pistol of the type described in subpart 160.028. The parachute and pyrotechnic...

  8. 46 CFR 160.024-4 - Approval and production tests.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... every ten lots of signals produced, except that the number of technical tests must be at least one but.... (Table 160.024-4(c)(2)) is assigned a score (failure percent) in accordance with the table. In the case... satisfactorily when shot from a pistol of the type described in subpart 160.028. The parachute and pyrotechnic...

  9. 76 FR 16852 - Hours of Service (HOS) of Drivers; Assessing the Safety Impact of the Exemption From the 14-Hour...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-03-25

    ... previous decision granting certain members of the American Pyrotechnics Association (APA) an exemption from... renewed (49 CFR 381.300(b)). APA's Independence Day Operations and the Exemption from 49 CFR 395.3(a)(2) APA is a trade association that represents the domestic fireworks industry. Its members have been...

  10. Gunner's Mate G 3 and 2; Rate Training Manual. Revised.

    ERIC Educational Resources Information Center

    Naval Education and Training Command, Pensacola, FL.

    The rate training manual has been prepared for men of the regular Navy and of the Naval Reserve for the purpose of advancement to increase knowledge in the various aspects of the Gunner's Mate rating (G 3 and 2). Chapters 1 through 14 deal with the following topics: the requirements of the Gunner's Mate G Rating, explosives and pyrotechnics,…

  11. 78 FR 19224 - Taking of Marine Mammals Incidental to Specified Activities; U.S. Marine Corps Training Exercises...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-29

    ... arms, large arms, bombs, rockets, missiles, and pyrotechnics. All munitions used at BT-11 are inert... shapes each time. Mine simulation shapes include MK76, MK80 series, and BDU practice bombs ranging from... bombs against surface maritime targets at BT-9 or BT-11,day or night, using either unguided or precision...

  12. 78 FR 27304 - Safety Zone; Melrose Pyrotechnics Fireworks Display; Chicago Harbor, Chicago, IL

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-10

    ... any novel legal or policy issues. The safety zone created by this rule will be small and enforced for... through the safety zone when permitted by the Captain of the Port. 2. Impact on Small Entities Under the... entities. The Coast Guard certifies under 5 U.S.C. 605(b) that this proposed rule will not have a...

  13. Optical Pressure Measurements of Explosions

    DTIC Science & Technology

    2013-09-01

    near field detonation product gases can have a significant effect upon afterburn ignition times (4). The implication being that afterburning times...can be tuned to bring detonation product afterburning into proximity of the leading shock, influencing brisance, and explosive impulse on target. 3...R. Z.; McAndrew, B. A. Afterburn Ignition Delay and Shock Augmentation in Fuel Rich Solid Explosives. Propellants, Explosives, Pyrotechnics 2010

  14. Wireless device for activation of an underground shock wave absorber

    NASA Astrophysics Data System (ADS)

    Chikhradze, M.; Akhvlediani, I.; Bochorishvili, N.; Mataradze, E.

    2011-10-01

    The paper describes the mechanism and design of the wireless device for activation of energy absorber for localization of blast energy in underground openings. The statistics shows that the greatest share of accidents with fatal results associate with explosions in coal mines due to aero-methane and/or air-coal media explosion. The other significant problem is terrorist or accidental explosions in underground structures. At present there are different protective systems to reduce the blast energy. One of the main parts of protective Systems is blast Identification and Registration Module. The works conducted at G. Tsulukidze Mining Institute of Georgia enabled to construct the wireless system of explosion detection and mitigation of shock waves. The system is based on the constant control on overpressure. The experimental research continues to fulfill the system based on both threats, on the constant control on overpressure and flame parameters, especially in underground structures and coal mines. Reaching the threshold value of any of those parameters, the system immediately starts the activation. The absorber contains a pyrotechnic device ensuring the discharge of dispersed water. The operational parameters of wireless device and activation mechanisms of pyrotechnic element of shock wave absorber are discussed in the paper.

  15. Design and Demonstration of Bolt Retractor Separation System for X-38 Deorbit Propulsion Stage

    NASA Technical Reports Server (NTRS)

    Ahmed, Raf; Johnston, A. S.; Garrison, J. C.; Gaines, J. L.; Waggoner, J. D.

    2003-01-01

    A separation system was designed for the X-38 experimental crew return vehicle program to allow the Deorbit Propulsion Stage (DPS) to separate from the X-38 lifting body during reentry operations. The configuration chosen was a spring-loaded plunger, known as the Bolt Retractor Subsystem (BRS), that retracts each of the six DPS-to-lifting body attachment bolts across the interface plane after being triggered by a separation nut mechanism. The system was designed to function on the ground in an atmospheric environment as well as in space. The BRS provides the same functionality as that of a completely pyrotechnic shear separation system that would normally be considered ideal for this application, but at a much lower cost. This system also could potentially be applied to future space station crew return vehicles. The design goal of 40 ms retraction time was successfully met in a series of demonstrations performed at the NASA Marshall Space Flight Center s Pyrotechnic Shock Facility (PSF) and Flight Robotics Laboratory (FRL). It must be emphasized that a full-scale test series was not performed on the BRS due to program schedule and cost constraints.

  16. Double swivel toggle release

    NASA Technical Reports Server (NTRS)

    King, Guy L.; Schneider, William C.

    1989-01-01

    A pyrotechnic actuated structural release device is disclosed which is mechanically two fault tolerant for release. The device comprises a fastener plate and fastener body each attachable to one of a pair of structures to be joined. The fastener plate and the fastener body are fastened by a dual swivel toggle member. The toggle member is supported at one end on the fastener plate and mounted for universal pivotal movement thereon. Its other end is received in a central opening in the fastener body, and has a universally mounted retainer ring member. The toggle member is restrained by three retractable latching pins symmetrically disposed in equiangular spacing about the axis of the toggle member and positionable in latching engagement with the retainer ring member on the toggle member. Each pin is retractable by a pyrotechnic charge, the expanding gases of which are applied to a pressure receiving face on the latch pins to effect retraction from the ring member. While retraction of all three pins releases the ring member, the fastener is mechanically two fault tolerant since the failure of any single one or pair of the latch pins to retract results in an asymmetrical loading on the ring member and its dual pivotal movement ensures a release.

  17. Verification and Validation Testing of the Parachute Decelerator System Prior to the First Supersonic Flight Dynamics Test for the Low Density Supersonic Decelerator Program

    NASA Technical Reports Server (NTRS)

    Gallon, John C.; Witkowski, Allen

    2015-01-01

    The Parachute Decelerator System (PDS) is comprised of all components associated with the supersonic parachute and its associated deployment. During the Supersonic Flight Dynamics Test (SFDT), for the Low Density Supersonic Decelerators Program, the PDS was required to deploy the supersonic parachute in a defined fashion. The PDS hardware includes three major subsystems that must function together. The first subsystem is the Parachute Deployment Device (PDD), which acts as a modified pilot deployment system. It is comprised of a pyrotechnic mortar, a Kevlar ballute, a lanyard actuated pyrotechnic inflation aid, and rigging with its associated thermal protection material (TPS). The second subsystem is the supersonic parachute deployment hardware. This includes all of the parachute specific rigging that includes the parachute stowage can and the rigging including TPS and bridle stiffeners for bridle management during deployment. The third subsystem is the Supersonic Parachute itself, which includes the main parachute and deployment bags. This paper summarizes the verification and validation of the deployment process, from the initialization of the PDS system through parachute bag strip that was done prior to the first SFDT.

  18. Preparation and Characterization of Pyrotechnics Binder-Coated Nano-Aluminum Composite Particles

    NASA Astrophysics Data System (ADS)

    Ye, Mingquan; Zhang, Shuting; Liu, Songsong; Han, Aijun; Chen, Xin

    2017-07-01

    The aim of this article is to protect the activity of nano-aluminum (Al) particles in solid rocket propellants and pyrotechnics. The morphology, structure, active aluminum content, and thermal and catalytic properties of the coated samples were characterized by scanning electron microscopy (SEM), transmission electron microscopy (TEM), Fourier transform infrared spectroscopy (FTIR), thermogravimetry-differential scanning calorimetry (TG-DSC), and oxidation-reduction titration methods. The results indicated that nano-Al particles could be effectively coated with phenolic resin (PF), fluororubber (Viton B), and shellac through a solvent/nonsolvent method. The energetic composite particles have core-shell structures and the thickness of the coating film is about 5-15 nm. Analysis of the active Al content revealed that Viton B coating had a much better protective effect. The TG-DSC results showed that the energy amount and energy release rate of PF-, Viton B-, and shellac-coated Al particles were larger than those of the raw nano-Al particles. The catalytic effects of coated Al particles on the thermal decomposition of ammonium perchlorate (AP) were better than those of raw nano-Al particles, and the effect of shellac-coated Al particles was significantly better than that of Viton B-coated Al particles.

  19. Explosive and pyrotechnic aging demonstration

    NASA Technical Reports Server (NTRS)

    Rouch, L. L., Jr.; Maycock, J. N.

    1976-01-01

    The survivability was experimentally verified of fine selected explosive and pyrotechnic propellant materials when subjected to sterilization, and prolonged exposure to space environments. This verification included thermal characterization, sterilization heat cycling, sublimation measurements, isothermal decomposition measurements, and accelerated aging at a preselected elevated temperature. Temperatures chosen for sublimation and isothermal decomposition measurements were those in which the decomposition processess occurring would be the same as those taking place in real-time aging. The elevated temperature selected (84 C) for accelerated aging was based upon the parameters calculated from the kinetic data obtained in the isothermal measurement tests and was such that one month of accelerated aging in the laboratory approximated one year of real-time aging at 66 C. Results indicate that HNS-IIA, pure PbN6, KDNBF, and Zr/KC10 are capable of withstanding sterilization. The accelerated aging tests indicated that unsterilized HNS-IIA and Zr/KC104 can withstand the 10 year, elevated temperature exposure, pure PbN6 and KDNBF exhibit small weight losses (less than 2 percent) and B/KC104 exhibits significant changes in its thermal characteristics. Accelerated aging tests after sterilization indicated that only HNS-IIA exhibited high stability.

  20. Time evolution of atmospheric particle number concentration during high-intensity pyrotechnic events

    NASA Astrophysics Data System (ADS)

    Crespo, Javier; Yubero, Eduardo; Nicolás, Jose F.; Caballero, Sandra; Galindo, Nuria

    2014-10-01

    The Mascletàs are high-intensity pyrotechnic events, typical of eastern Spanish festivals, in which thousands of firecrackers are burnt at ground level in an intense, short-time (<8 min) deafening spectacle that generates short-lived, thick aerosol clouds. In this study, the impact of such events on air quality has been evaluated by means of particle number concentration measurements performed close to the venue during the June festival in Alicante (southeastern Spain). Peak concentrations and dilution times observed throughout the Mascletàs have been compared to those measured when conventional aerial fireworks were launched 2 km away from the monitoring site. The impact of the Mascletàs on the total number concentration of particles larger than 0.3 μm was higher (maximum ∼2·104 cm-3) than that of fireworks (maximum ∼2·103 cm-3). The effect of fireworks depended on whether the dominant meteorological conditions favoured the transport of the plume to the measurement location. However, the time required for particle concentrations to return to background levels is longer and more variable for firework displays (minutes to hours) than for the Mascletàs (<25 min).

  1. ASTRONAUT JAMES A. LOVELL, JR. - TRAINING - WEIGHT AND BALANCE - PRIME CREW (GT-7)

    NASA Image and Video Library

    1965-10-25

    S65-57481 (25 Oct. 1965) --- Astronaut James A. Lovell Jr., pilot of the Gemini-7 spaceflight, undergoes weight and balance tests in the Pyrotechnic Installation Building, Merritt Island, Kennedy Space Center. Talking with Lovell are (left to right) Charlie Beaty, McDonnell Aircraft Corporation; Karl Stoien, MAC; NASA suit technician Al Rochferd; and Norm Batterson, Weber Aircraft Corporation. Photo credit: NASA

  2. Chemical Characterization of the Pyrotechnically Disseminated KM03 Red Phosphorus Floating Smoke Pot

    DTIC Science & Technology

    2006-05-01

    concentrations. Some of the other compounds observed were sulfur dioxide, hexamethylcyclotrisiloxane, xylene, octamethylcyclotetrasiloxane, dl- limonene ...for the complete analysis of the VOC’s collected. Limonene , xylene, and sulfur dioxide were also detected in small quantities during the...disseminations. Usually, limonene occurs naturally in trees, bushes, and/or citrus oils, but its reason for its presence in the characterized smoke is unclear

  3. Chemical Characterization of the Pyrotechnically Disseminated 66MM Red Phosphorous Smoke Screening IR, Vehicle Launched Grenade

    DTIC Science & Technology

    2008-07-01

    for the redesign of the previously fielded 66mm M76 grenade. Although the M76 grenades provided effective screening in the visual and thermal IR...Environmental and Field Testing Team, Engineering Directorate (ECBC), for coordinating and transporting the test items to the downrange testing site and to...13 2.2 Experimental Design-Downrange Testing ............................................. 14 2.3

  4. 75 FR 32398 - Taking of Marine Mammals Incidental to Specified Activities; U.S. Marine Corps Training Exercises...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-08

    ... include small arms, large arms, bombs, rockets, missiles, and pyrotechnics. All munitions used at BT-11... shapes include MK76, MK80 series, and BDU practice bombs ranging from 25 to 2,000 pounds in weight. There... training, fixed wing or rotary wing aircraft deliver bombs against surface maritime targets at BT-9 or BT...

  5. Things That Go Boom!: Noise and Toxic Exposures Associated with Weapon Systems

    DTIC Science & Technology

    2010-06-17

    Munitions Pyrotechnics Tracers Spot ing Charges Oxidizers Delay Elements Propellatl s Fuses De· onators Pr~n1ers Constituent of Concern BariL ...r11 chromate Potassium perchlorate lead oxide BariL m chromate P a tass ~L m perch I o r,ate l e ad chromate An1n1onil tll perch lara e P a

  6. A Compilation of Hazard and Test Data for Pyrotechnic Compositions

    DTIC Science & Technology

    1980-10-01

    heated. These changes may be related to dehydration , decomposition , crystal- line transition, melting, boiling, vaporization, polymerization, oxidation...123 180 + 66 162 + 16 506 +169 447 +199 448+ 159 Decomposition temperature °C 277 + 102 561 j; 135 205 + 75 182 + 24 550 + 168 505 +224 517 + 153...of compatibility or classification. The following tests are included in the parametric tests: 1. Autoignition Temperature 2. Decomposition

  7. Elimination of Perchlorate Oxidizers from Pyrotechnic Flare Compositions

    DTIC Science & Technology

    2007-03-09

    in candelas ( cd ), where the candela is defined as, 1 cd = 1 lumen /steradian-1. DSC A thermal analysis technique known as Differential...Shorter Wavelength Infrared band routinely monitored in decoy flare performance tests. TGA A thermal analysis technique known as Thermogravimetric ...Scanning Calorimetry DTA A thermal analysis technique known as Differential Thermal Analysis GAP Glycidyl Azide Polymer used as a curable binder in some

  8. Test Operations Procedure (TOP) 5-2-521 Pyrotechnic Shock Test Procedures

    DTIC Science & Technology

    2007-11-20

    Clipping will produce a signal that resembles a square wave . (2) Filters are used to limit the frequency bandwidth of the signal . Low pass filters...video systems permit observation of explosive items under test. c. Facilities to perform non-destructive inspections such as x-ray, ultrasonic , magna...test. (1) Accelerometers (2) Signal Conditioners (3) Digital Recording System (4) Data Processing System with hardcopy output

  9. Low hygroscopicity of ambient fresh carbonaceous aerosols from pyrotechnics smoke

    DOE PAGES

    Carrico, Christian M.; Gomez, Samantha Laray; Dubey, Manvendra Krishna; ...

    2018-01-31

    Pyrotechnics (fireworks) displays are common for many cultures worldwide, with Independence Day celebrations occurring annually on July 4th as the most notable in the U.S. Given an episodic nature, fireworks aerosol properties are poorly characterized. Here we report observations of optical properties of fresh smoke emissions from Independence Day fireworks smoke sampled at Los Alamos National Laboratory, New Mexico U.S.A. on 4–5 July 2016. Aerosol optical properties were measured with a photoacoustic extinctiometer (PAX, DMT, Inc., Model 870 nm) at low RH < 30% and a humidity controlled nephelometry system (Ecotech, Inc., 450 nm Aurora). ‘Dry’ light scattering coefficient (σsp)more » increased from background < 15 Mm –1 reaching 120 Mm –1 (450 nm) as a 2-min event peak, while the absorption coefficient increased from background of 0.5–4.4 Mm –1 (870 nm). The event peak occurred at 00:35 on 5 July 2016, ~3 h after local fireworks events, and decreased to background by 04:00 on 5 July 2016, showing well mixed aerosol properties. A notable result is that the aerosol hygroscopic response, as characterized by the ratio of wet to dry light scattering or f(RH = 85%), declined to 1.02 at the peak fireworks influence from a background ~1.7. Strong wavelength dependence of light scattering with Ångström exponent ~2.2 throughout the event showed a size distribution dominated by sub-micrometer particles. Likewise, single scattering albedo at 870 nm remained constant throughout the event with ω = 0.86 ± 0.03, indicating light absorbing carbon, though not dominant, was mixed with organic carbon. Subsequent laboratory testing with ground-level sparklers showed that pyrotechnics smoke can generate a strong hygroscopic response, however. As confirmed with chemical analysis, the chemistry of the fireworks was key to defining the hygroscopic response. As a result, sparkler smoke was dominated by salt species such as hygroscopic potassium chloride while it lacked the black powder explosives in aerial fireworks that contribute organic and elemental carbon to its non-hygroscopic smoke.« less

  10. Low hygroscopicity of ambient fresh carbonaceous aerosols from pyrotechnics smoke

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

    Carrico, Christian M.; Gomez, Samantha Laray; Dubey, Manvendra Krishna

    Pyrotechnics (fireworks) displays are common for many cultures worldwide, with Independence Day celebrations occurring annually on July 4th as the most notable in the U.S. Given an episodic nature, fireworks aerosol properties are poorly characterized. Here we report observations of optical properties of fresh smoke emissions from Independence Day fireworks smoke sampled at Los Alamos National Laboratory, New Mexico U.S.A. on 4–5 July 2016. Aerosol optical properties were measured with a photoacoustic extinctiometer (PAX, DMT, Inc., Model 870 nm) at low RH < 30% and a humidity controlled nephelometry system (Ecotech, Inc., 450 nm Aurora). ‘Dry’ light scattering coefficient (σsp)more » increased from background < 15 Mm –1 reaching 120 Mm –1 (450 nm) as a 2-min event peak, while the absorption coefficient increased from background of 0.5–4.4 Mm –1 (870 nm). The event peak occurred at 00:35 on 5 July 2016, ~3 h after local fireworks events, and decreased to background by 04:00 on 5 July 2016, showing well mixed aerosol properties. A notable result is that the aerosol hygroscopic response, as characterized by the ratio of wet to dry light scattering or f(RH = 85%), declined to 1.02 at the peak fireworks influence from a background ~1.7. Strong wavelength dependence of light scattering with Ångström exponent ~2.2 throughout the event showed a size distribution dominated by sub-micrometer particles. Likewise, single scattering albedo at 870 nm remained constant throughout the event with ω = 0.86 ± 0.03, indicating light absorbing carbon, though not dominant, was mixed with organic carbon. Subsequent laboratory testing with ground-level sparklers showed that pyrotechnics smoke can generate a strong hygroscopic response, however. As confirmed with chemical analysis, the chemistry of the fireworks was key to defining the hygroscopic response. As a result, sparkler smoke was dominated by salt species such as hygroscopic potassium chloride while it lacked the black powder explosives in aerial fireworks that contribute organic and elemental carbon to its non-hygroscopic smoke.« less

  11. Low hygroscopicity of ambient fresh carbonaceous aerosols from pyrotechnics smoke

    NASA Astrophysics Data System (ADS)

    Carrico, Christian M.; Gomez, Samantha L.; Dubey, Manvendra K.; Aiken, Allison C.

    2018-04-01

    Pyrotechnics (fireworks) displays are common for many cultures worldwide, with Independence Day celebrations occurring annually on July 4th as the most notable in the U.S. Given an episodic nature, fireworks aerosol properties are poorly characterized. Here we report observations of optical properties of fresh smoke emissions from Independence Day fireworks smoke sampled at Los Alamos National Laboratory, New Mexico U.S.A. on 4-5 July 2016. Aerosol optical properties were measured with a photoacoustic extinctiometer (PAX, DMT, Inc., Model 870 nm) at low RH < 30% and a humidity controlled nephelometry system (Ecotech, Inc., 450 nm Aurora). 'Dry' light scattering coefficient (σsp) increased from background < 15 Mm-1 reaching 120 Mm-1 (450 nm) as a 2-min event peak, while the absorption coefficient increased from background of 0.5-4.4 Mm-1 (870 nm). The event peak occurred at 00:35 on 5 July 2016, ∼3 h after local fireworks events, and decreased to background by 04:00 on 5 July 2016, showing well mixed aerosol properties. A notable result is that the aerosol hygroscopic response, as characterized by the ratio of wet to dry light scattering or f(RH = 85%), declined to 1.02 at the peak fireworks influence from a background ∼1.7. Strong wavelength dependence of light scattering with Ångström exponent ∼2.2 throughout the event showed a size distribution dominated by sub-micrometer particles. Likewise, single scattering albedo at 870 nm remained constant throughout the event with ω = 0.86 ± 0.03, indicating light absorbing carbon, though not dominant, was mixed with organic carbon. Subsequent laboratory testing with ground-level sparklers showed that pyrotechnics smoke can generate a strong hygroscopic response, however. As confirmed with chemical analysis, the chemistry of the fireworks was key to defining the hygroscopic response. Sparkler smoke was dominated by salt species such as hygroscopic potassium chloride while it lacked the black powder explosives in aerial fireworks that contribute organic and elemental carbon to its non-hygroscopic smoke.

  12. Pneumatic preloaded scanning science launch latch system

    NASA Technical Reports Server (NTRS)

    Kievit, J. C.

    1979-01-01

    A relatively simple system using a preloaded pneumatic piston latch with a pyrotechnic valve release was developed. The system was the only candidate that met all the imposed requirements utilizing reliable state-of-art components. The development of the latch system from its first use on Mariner '69 Mars Flyby Spacecraft through its most recent use on the Voyager Spacecraft that will fly to Jupiter and Saturn is reviewed.

  13. Preparation, characterization and thermolysis of phenylenediammonium dinitrate salts.

    PubMed

    Kapoor, Inder Pal Singh; Srivastava, Pratibha; Singh, Gurdip

    2008-02-11

    Four phenylenediammonium dinitrate salts were prepared and characterized by elemental, Infrared spectroscopy (IR), Ultraviolet spectroscopy (UV) and gravimetric methods. These dinitrates find application in propellant, explosives and pyrotechnics. Their thermal decomposition has been studied using thermogravimetry (TG) and simultaneous thermogravimetry-differential scanning calorimetry (TG-DSC). Kinetics parameters were evaluated by model fitting and isoconversional methods. Their thermolytic pathways have also been suggested, which involves decomposition followed by ignition.

  14. Harpoon Pyrotechnic Shock Study

    DTIC Science & Technology

    1979-09-01

    Air Systems Command, was performed from July 1973 to July 1979. In the Interest of economy and timeliness in presenting the information, the report is...Both actual test data and predicted shock levey are presented. .L{U’Shock spectra environment predictions are made for several types of explosive ...mounting structure 5 to 10 inches (127 to 254 mm) from the explosive device. Attenuation across the component mounting interface is the only loss

  15. Applications of High-Nitrogen Energetics in Pyrotechnics: Development of Perchlorate-Free Red Star M126A1 Hand-Held Signal Formulations with Superior Luminous Intensities and Burn Times

    DTIC Science & Technology

    2011-03-25

    short-term administration of 3-amino- triazole. The US Army Public Health Command has stated that quantitative structure activity relationship ( QSAR ...modeling is not a useful tool in determining the toxic nature of high nitrogen salts such as bis-tetrazolate 1. Therefore, no data on the toxicology of

  16. Acute and Four-Week Inhalation Toxicity Study in Rats Exposed to Pyrotechnically Disseminated Black Smoke (PVA)

    DTIC Science & Technology

    2014-06-01

    to the Black Smoke formulation demonstrates the beginning of lesion recovery/ healing . Toxicant-induced nasal lesions in laboratory animals generally...material inside an empty inhalation chamber with solid rubber stoppers placed in the faceplate to contain the smoke atmosphere. This inhalation...level of activity, gait and posture, reactivity to handling or sensory stimuli, altered strength, and stereotypes or bizarre behavior (e.g., self

  17. Advanced Technology for Pyrotechnic Mixtures and Munitions

    DTIC Science & Technology

    1977-07-01

    or at ambient I ,/ BLENDING AND CASTING CURING REMOVING MOLD WAFER MANUFACTURING ? / I / SI ,/ iAUTOMATIC LOADING Figure 1. Plastic Bonded Starter Mix...material (fines) is recycled through the compacting rollers. asshwn The Chilsonator used at EA consisted only of the compaction rollers and the controls ...standardized process controls . Oversize material is pulverized and combined with the undersize material for s" ,regranulation in another batch. 2 ,Both the

  18. Making Microscopic Cubes Of Boron

    NASA Technical Reports Server (NTRS)

    Faulkner, Joseph M.

    1993-01-01

    Production of finely divided cubes of boron involves vacuum-deposition technology and requires making of template. Template supports pattern of checkered squares 25 micrometers on side, which are etched 25 micrometers into template material. Template coasted uniformly with paralyene or some similar vacuum coating with low coefficient of adhesion. Intended application to solid rocket fuels, explosives, and pyrotechnics; process used for other applications, from manufacture of pharmaceuticals to processing of nuclear materials.

  19. Organic Substitutes for Charcoal in ’Black Powder’ Type Pyrotechnic Formulations

    DTIC Science & Technology

    1984-07-01

    mixture, containing phenolphthalein, strand-burn rates were measured at various high pressures of nitrogen. Cinematography , at 1000 frames per second...the cinematography the burning phenolphthalein "sticks" showed a liquid surface that was in extreme turbulence and liquid drops were propelled by...This has led to a hypothetical mechanism explaining sulfur’s role in flame spreading which should be explored in future work. From cinematography

  20. Direct Fixed-Bed Biological Perchlorate Destruction Demonstration

    DTIC Science & Technology

    2008-09-01

    1 mg/L)? This issue targets the question of whether the FXB bioreactor system can be applied at a remediation site (i.e., a non-potable...incineration). 11 3. PERFORMANCE OBJECTIVES 3.1 Summary Performance objectives listed in Table 3.1 apply to the complete FXB bioreactor...potential sources of perchlorate. Other areas near Well #2 have been used by a multitude of companies for ordnance and pyrotechnics manufacturing

  1. Environmentally Sustainable Yellow Smoke Formulations for Use in the M194 Hand Held Signal

    DTIC Science & Technology

    2012-06-10

    of the pyrotechnic train through the system hardware, potassium chlorate (oxidizer) and the sugar (fuel, or reducing agent) engage in a reduction...1: Composition of M194 control formulation Ingredient Wt. % Function Potassium Chlorate 35.0 Oxidizer Sugar (sucrose) 20.0 Fuel Vat yellow...Experimental Section 1. Materials Potassium chlorate , potassium nitrate, sodium bicarbonate, stearic acid, and sugar were purchased from Hummel

  2. Hazards in the theater.

    PubMed

    Rossol, M; Hinkamp, D

    2001-01-01

    The authors offer a survey of the myriad and unique safety and health hazards faced past and present by performers and theatrical workers, from preproduction work, through the show, and during the strike (dismantling). Special emphasis is given to health hazards posed by the many new plastic resin systems and adhesives used in set, prop, and costume construction; the hazards of special-effect fogs, smokes, haze, dusts, and pyrotechnic emissions; and theatrical makeup.

  3. Swell Sleeves for Testing Explosive Devices

    NASA Technical Reports Server (NTRS)

    Hinkel, Todd J.; Dean, Richard J.; Hohmann, Carl W.; Hacker, Scott C.; Harrington, Douglas W.; Bacak, James W.

    2003-01-01

    A method of testing explosive and pyrotechnic devices involves exploding the devices inside swell sleeves. Swell sleeves have been used previously for measuring forces. In the present method, they are used to obtain quantitative indications of the energy released in explosions of the devices under test. A swell sleeve is basically a thick-walled, hollow metal cylinder threaded at one end to accept a threaded surface on a device to be tested (see Figure 1). Once the device has been tightly threaded in place in the swell sleeve, the device-and-swell-sleeve assembly is placed in a test fixture, then the device is detonated. After the explosion, the assembly is removed from the test fixture and placed in a coordinate-measuring machine for measurement of the diameter of the swell sleeve as a function of axial position. For each axial position, the original diameter of the sleeve is subtracted from the diameter of the sleeve as swollen by the explosion to obtain the diametral swelling as a function of axial position (see Figure 2). The amount of swelling is taken as a measure of the energy released in the explosion. The amount of swelling can be compared to a standard amount of swelling to determine whether the pyrotechnic device functioned as specified.

  4. Compilation of Blast Parameters of Selected High Explosives, Propellants, and Pyrotechnics in Surface Burst Configurations.

    DTIC Science & Technology

    1987-01-01

    APPENDIX B- DATA REDUCTION PROGRAM .............................. 403 LIST OF ILLUSTRATIONS FIGURE NO. PAGE 1. Instrumented Test Pad Layout...weight to produce the same yield relative to hemis- pherical TNT. The test specimens were placed at ground zero in a particular in- plant geometry...The containers were either scaled from the original size or tested in full- scale configurations. The test charges were placed at ground zero and

  5. The Shock and Vibration Bulletin. Part 1. Welcome, Keynote Address, Invited Papers, Pyrotechnic Shock, and Shock Testing and Analysis

    DTIC Science & Technology

    1983-05-01

    DESIGN PROCEDURE M. S. IIAndal, University of Vermont, Burlington, VT Machinery Dynamics ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF ROTATING BLADE... methodology to accurately predict rotor vibratory loads and has recently been initiated for detail design and bench test- coupled rotor/airframe vibrations... design methodology , a trating on the basic disciplines of aerodynamics and struc. coupled rotor/airframe vibration analysis has been developed. tural

  6. Alternatives to Pyrotechnic Distress Signals; Additional Signal Evaluation

    DTIC Science & Technology

    2017-06-01

    conducted a series of laboratory experiments designed to determine the optimal signal color and temporal pattern for identification against a variety of...practice” trials at approximately 2030 local time and began the actual Test 1 observation trials at approximately 2130. The series of trials finished at...Lewandowski , 860-271-2692, email: M.J.Lewandowski@uscg.mil 16. Abstract (MAXIMUM 200 WORDS) This report is the fourth in a series that details work

  7. Aircraft Infrared Principles, Signatures, Threats, and Countermeasures

    DTIC Science & Technology

    2012-09-26

    advances have been in two:   Indium antimonide (InSb)—MWIR of approximately 1.5 to 5.5 m  Mercury cadmium telluride (HgCdTe)—LWIR of...Surface Warfare Center [NSWC]), Crane, Indiana . A pyrotechnic does not depend upon external oxygen for reaction; and, consequently, the reaction...the analysis of missile signals necessary to score effectiveness. FIGURE 77. Seeker Test Van, NSWC, Crane, Indiana . NAWCWD TP 8773 91

  8. DEMONSTRATION REPORT: Demonstration of Advanced Geophysics and Classification Technologies on Munitions Response Sites Former Fort Ord, Monterey County, CA

    DTIC Science & Technology

    2017-06-01

    DGM Digital Geophysical Mapping DTSC California Department of Toxic Substances Control EM Electromagnetic EPA U.S. Environmental...land mines, pyrotechnics, bombs , and demolition materials. Surface sweeps identified MEC items throughout Units 11 and 12, including 37mm, 40mm, 57mm...electromagnetic ( EM ) data are being collected. If no GPS readings are collected during that period, the most recent GPS position and the platform

  9. Electronic safing of a diode laser arm-fire device

    NASA Astrophysics Data System (ADS)

    Willis, Kenneth E.; Chang, Suk T.

    1993-06-01

    The paper describes a rocket motor arm-fire device which uses a diode laser protected from unintentional function with a specially designed RF frequency attenuating coupler (RFAC). The RFAC transfers power into a Faraday cage via magnetic flux, thereby protecting the diode, its drive circuit, and the pyrotechnic from all electromagnetic and electrostatic hazards. Diagrams of the diode laser arm-fire device are presented together with a diagram illustrating the RFAC principle of operation.

  10. Alternative for Perchlorates in Incendiary and Pyrotechnic Formulations for Projectiles

    DTIC Science & Technology

    2009-08-01

    although other copper salts including chloride, acetate, sulfate and carbonate are highly bioavailable in animal nutrition. The toxicity of a single oral...6 hours to 820 mg m-3 after 2 hr. In experimental animals, single inhalation exposures to hydrogen sulfide result in death and respiratory...is in general regulated by the equilibria between CO2, HCO3 - and CO3 2-. The buffer capacity depends on the concentration of these substances

  11. Development of Environmentally Friendly Insensitive Pyrotechnic Munitions with Enhanced Battlefield Performance

    DTIC Science & Technology

    2011-11-30

    STATEMENT A. Distribution Unlimited. Other requests shall be referred to US Army RDECOM-ARDEC, Picatinny Public Affairs Office, Bldg. 1 , Picatinny...document. Report Documentation Page Form ApprovedOMB No. 0704-0188 Public reporting burden for the collection of information is estimated to average 1 ...subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. 1 . REPORT

  12. Potassium Benzoate for Pyrotechnic Whistling Compositions: Its Synthesis and Characterization as an Anhydrous Salt,

    DTIC Science & Technology

    1983-02-01

    subsequently established that potassium benzoate crystallizes from water at 293 - 298 K (20-25*C) and also precipitates from aqueous alcohol as colourless...benzoic acid and potassium bicarbonate or benzoic acid and potassium hydroxide, recrystallizes from water and also precipitates from aqueous alcohol...and a copious white precipitate was formed. The mixture was taken to dryness under reduced pressure and water (100 ml) added to the mixture, which

  13. Axisymmetric single shear element combustion instability experiment

    NASA Technical Reports Server (NTRS)

    Breisacher, Kevin J.

    1993-01-01

    The combustion stability characteristics of a combustor consisting of a single shear element and a cylindrical chamber utilizing LOX and gaseous hydrogen as propellants are presented. The combustor geometry and the resulting longitudinal mode instability are axisymmetric. Hydrogen injection temperature and pyrotechnic pulsing were used to determine stability boundaries. Mixture ratio, fuel annulus gap, and LOX post configuration were varied. Performance and stability data were obtained for chamber pressures of 300 and 1000 psia.

  14. Axisymmetric single shear element combustion instability experiment

    NASA Technical Reports Server (NTRS)

    Breisacher, Kevin J.

    1993-01-01

    The combustion stability characteristics of a combustor consisting of a single shear element and a cylindrical chamber utilizing LOX and gaseous hydrogen as propellants are presented. The combustor geometry and the resulting longitudinal mode instability are axisymmetric. Hydrogen injection temperature and pyrotechnic pulsing were used to determine stability boundaries. Mixture ratio, fuel annulus gap, and LOX post configuration were varied. Performance and stability data are presented for chamber pressures of 300 and 1000 psia.

  15. Electrostatic Discharge Sensitivity and Electrical Conductivity of Composite Energetic Materials

    DTIC Science & Technology

    2013-02-01

    intermetallic) [13,14], a metal oxide ( thermite ) [13e15], or a fluoropolymer [16,17]. They can be used as additives in explosives to decrease...research on ESD ignition sensitivity of thermites and intermetallics. Because thermites are composed of particulate media and widely used, they pose a... thermites and intermetallics for pyrotechnic applications, in: 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 1996. [15] K.W. Watson, M.L

  16. Controlling the Electrostatic Discharge Ignition Sensitivity of Composite Energetic Materials Using Carbon Nanotube Additives

    DTIC Science & Technology

    2014-08-10

    Electrostatic discharge Ignition Aluminum Thermites Energetic materials a b s t r a c t Powder energetic materials are highly sensitive to electrostatic...Fundamentals, in: Heat Conduction, Wiley, Hoboken, NJ, 2012. [12] Davin G. Piercey, Thomas M. Klapotke, Nanoscale aluminum metal oxide ( thermite ) reactions for...propagation velocity in thermites with a nanoscale oxidizer, Propellants Explos. Pyrotechn. 39 (3) (2014) 407 415. [18] Kevin Moore, Michelle L

  17. Light metal explosives and propellants

    DOEpatents

    Wood, Lowell L.; Ishikawa, Muriel Y.; Nuckolls, John H.; Pagoria, Phillip F.; Viecelli, James A.

    2005-04-05

    Disclosed herein are light metal explosives, pyrotechnics and propellants (LME&Ps) comprising a light metal component such as Li, B, Be or their hydrides or intermetallic compounds and alloys containing them and an oxidizer component containing a classic explosive, such as CL-20, or a non-explosive oxidizer, such as lithium perchlorate, or combinations thereof. LME&P formulations may have light metal particles and oxidizer particles ranging in size from 0.01 .mu.m to 1000 .mu.m.

  18. Self-Rupturing Hermetic Valve

    NASA Technical Reports Server (NTRS)

    Tucker, Curtis E., Jr.; Sherrit, Stewart

    2011-01-01

    For commercial, military, and aerospace applications, low-cost, small, reliable, and lightweight gas and liquid hermetically sealed valves with post initiation on/off capability are highly desirable for pressurized systems. Applications include remote fire suppression, single-use system-pressurization systems, spacecraft propellant systems, and in situ instruments. Current pyrotechnic- activated rupture disk hermetic valves were designed for physically larger systems and are heavy and integrate poorly with portable equipment, aircraft, and small spacecraft and instrument systems. Additionally, current pyrotechnically activated systems impart high g-force shock loads to surrounding components and structures, which increase the risk of damage and can require additional mitigation. The disclosed mechanism addresses the need for producing a hermetically sealed micro-isolation valve for low and high pressure for commercial, aerospace, and spacecraft applications. High-precision electrical discharge machining (EDM) parts allow for the machining of mated parts with gaps less than a thousandth of an inch. These high-precision parts are used to support against pressure and extrusion, a thin hermetically welded diaphragm. This diaphragm ruptures from a pressure differential when the support is removed and/or when the plunger is forced against the diaphragm. With the addition of conventional seals to the plunger and a two-way actuator, a derivative of this design would allow nonhermetic use as an on/off or metering valve after the initial rupturing of the hermetic sealing disk. In addition, in a single-use hermetically sealed isolation valve, the valve can be activated without the use of potential leak-inducing valve body penetrations. One implementation of this technology is a high-pressure, high-flow-rate rupture valve that is self-rupturing, which is advantageous for high-pressure applications such as gas isolation valves. Once initiated, this technology is self-energizing and requires low force compared to current pyrotechnic-based burst disk hermetic valves. This is a novel design for producing a single-use, self-rupturing, hermetically sealed valve for isolation of pressurized gas and/or liquids. This design can also be applied for single-use disposable valves for chemical instruments. A welded foil diaphragm is fully supported by two mated surfaces that are machined to micron accuracies using EDM. To open the valve, one of the surfaces is moved relative to the other to (a) remove the support creating an unsupported diaphragm that ruptures due to over pressure, and/or (b) produce tension in the diaphragm and rupture it.

  19. Hydraulic Apparatus for Mechanical Testing of Nuts

    NASA Technical Reports Server (NTRS)

    Hinkel, Todd J.; Dean, Richard J.; Hacker, Scott C.; Harrington, Douglas W.; Salazar, Frank

    2004-01-01

    The figure depicts an apparatus for mechanical testing of nuts. In the original application for which the apparatus was developed, the nuts are of a frangible type designed for use with pyrotechnic devices in spacecraft applications in which there are requirements for rapid, one-time separations of structures that are bolted together. The apparatus can also be used to test nonfrangible nuts engaged without pyrotechnic devices. This apparatus was developed to replace prior testing systems that were extremely heavy and immobile and characterized by long setup times (of the order of an hour for each nut to be tested). This apparatus is mobile, and the setup for each test can now be completed in about five minutes. The apparatus can load a nut under test with a static axial force of as much as 6.8 x 10(exp 5) lb (3.0 MN) and a static moment of as much as 8.5 x 10(exp 4) lb in. (9.6 x 10(exp 3) N(raised dot)m) for a predetermined amount of time. In the case of a test of a frangible nut, the pyrotechnic devices can be exploded to break the nut while the load is applied, in which case the breakage of the nut relieves the load. The apparatus can be operated remotely for safety during an explosive test. The load-generating portion of the apparatus is driven by low-pressure compressed air; the remainder of the apparatus is driven by 110-Vac electricity. From its source, the compressed air is fed to the apparatus through a regulator and a manually operated valve. The regulated compressed air is fed to a pneumatically driven hydraulic pump, which pressurizes oil in a hydraulic cylinder, thereby causing a load to be applied via a hydraulic nut (not to be confused with the nut under test). During operation, the hydraulic pressure is correlated with the applied axial load, which is verified by use of a load cell. Prior to operation, one end of a test stud (which could be an ordinary threaded rod or bolt) is installed in the hydraulic nut. The other end of the test stud passes through a bearing plate; a load cell is slid onto that end, and then the nut to be tested is threaded onto that end and tightened until the nut and load cell press gently against the bearing plate.

  20. Preliminary Investigation into Pyrotechnic Chemical Products via Mass Spectrometry Techniques

    DTIC Science & Technology

    2015-03-11

    i m u m ) Py/GC/MS: PVC 11 • Pyrolysis of PVC exclusively yield cyclic hydrocarbons – 24.3% benzyl derivatives and 75.6% polycyclic aromatic ...Determination of EPA’s priority pollutant polycyclic aromatic hydrocarbons in drinking waters by solid phase extraction-HPLC” Bruzzoniti et al., Anal... aromatic hydrocarbons (PAH) – 42.3% hydrocarbons , 53.5% phenols, 4.7% nitrogen-containing O NH OH OH N DISTRIBUTION STATEMENT A. Approved for public

  1. 76 FR 77125 - Safety Zone; Sausalito Yacht Club's Annual Lighted Boat Parade and Fireworks Display, Sausalito, CA

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-12-12

    ..., pyrotechnics will be loaded onto a barge at Pier 50 near position 37[deg]46'28'' N, 122[deg]23'06'' W (NAD 83... position 37[deg]51'30.92'' N, 122[deg]28'27.97'' W (NAD 83). The temporary safety zone will extend 100 feet... Pier 50 to position 37[deg]51'30.92'' N, 122[deg]28'27.97'' W (NAD 83). The fireworks display is...

  2. Proceedings of International Pyrotechnics Seminar (4th), Held at Steamboat Village, Colorado, 22-26 July 1974

    DTIC Science & Technology

    1974-06-17

    10-1 I1. Burning Rate Modifiers, D.R. Dillehay ............................. 11-1 12. Spectroscopic Analysis of Azide Decomposition Products for use...solid, and Pit that they ignite a short distance from the surface. Further- more, decomposition of sodium nitrate, which produces the gas to blow the...decreasing U the thermal conductivity of the basic binary. Class 2 compounds, con- sisting of nanganese oxides, catalyze the normal decomposition of

  3. Mechanical environmental test program for the Communications Technology Satellite

    NASA Technical Reports Server (NTRS)

    Buckingham, R.; Sharp, G. R.

    1974-01-01

    This paper describes the spacecraft and subsystem level mechanical environmental test program which was developed for the Communications Technology Satellite (CTS). At the spacecraft level it includes sine and random vibration, static loading, centrifuge loading, pyrotechnic and separation shock simulation and (tentatively) acoustics. At the subsystem level it entails the same type of environmental exposure as applicable. Matrices of system and subsystem tests are presented showing type, level and hardware status for each major test.

  4. Evaluation of State-of-the-Art High Speed Deluge Systems Presently in Service at Various U.S. Army Ammunition Plants

    DTIC Science & Technology

    1993-09-01

    designed to respond to. No data exists on spectral irradiances in the IR or UV spectral bands where the current detectors operate. A need exists to...appropriate fire/explosion detection spectral bands. Setting a pyrotechnic fire and testing the responses of commercial UV and IR detectors that are designed...PNZ B. DETECTOR BACKGROUND ............... 30 C. UV DETECTORS . . ............ . . . 32 D. IR DETECTORS . . . ......... . . ... 34 E. MACHINE VISION

  5. BZ Disposal Facility Development and Design. Task 4, Incineration of Pyrotechnic Munitions in a Deactivation Furnace

    DTIC Science & Technology

    1982-07-01

    up to 5 percent. Normally the plume completely dissapated in less than 200 feet from the stack. 37 fo r^. -^ d. o !>. "^ .^ 0) O ON...each of the sampling points for particulate loading was analyzed for metals and organic content. The particulate analysis was combined with analysis...ducting from the mist eliminator to the ID fan and the stack can be constructed of FRP. The ID fan can be FRP, or epoxy coated steel or a combination

  6. Simulation of pyroshock environments using a tunable resonant fixture

    DOEpatents

    Davie, N.T.

    1996-10-15

    Disclosed are a method and apparatus for simulating pyrotechnic shock for the purpose of qualifying electronic components for use in weapons, satellite, and aerospace applications. According to the invention, a single resonant bar fixture has an adjustable resonant frequency in order to exhibit a desired shock response spectrum upon mechanical impact. The invention eliminates the need for availability of a large number of different fixtures, capable of exhibiting a range of shock response characteristics, in favor of a single tunable system. 32 figs.

  7. Boron Carbide as a Barium-Free Green Light Emitter and Burn Rate Modifier in Pyrotechnics

    DTIC Science & Technology

    2011-05-09

    We thank the US Army and Picatinny Arsenal, NJ for funding this work. Communications 4624 2011 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim Angew...Chem. Int. Ed. 2011 , 50, 4624 –4626 Report Documentation Page Form ApprovedOMB No. 0704-0188 Public reporting burden for the collection of information is...control number. 1. REPORT DATE 30 JUN 2011 2. REPORT TYPE 3. DATES COVERED 4. TITLE AND SUBTITLE Boron Carbide as a Barium-Free Green Light

  8. Development and Performance of the W/Sb2O3/KIO4/Lubricant Pyrotechnic Delay in the US Army Hand-Held Signal

    DTIC Science & Technology

    2013-01-01

    Gany, Investigation of Slow-Propagation Tung- sten Delay Mixtures, Propellants Explos. Pyrotech. 1997, 22, 207–211. [3] Tungsten Delay Composition ...apex. This delay ele- ment then ignites an expulsion charge, which ejects and ig- nites the smoke or illumination payload. The current delay composition ...used in HHS consists of 32.0% tungsten, 56.3% barium chromate, 11.4% potassium perchlorate, and 0.3% VAAR. (All composition percentages in this

  9. Simulation of pyroshock environments using a tunable resonant fixture

    DOEpatents

    Davie, Neil T.

    1996-01-01

    Disclosed are a method and apparatus for simulating pyrotechnic shock for the purpose of qualifying electronic components for use in weapons, satellite, and aerospace applications. According to the invention, a single resonant bar fixture has an adjustable resonant frequency in order to exhibit a desired shock response spectrum upon mechanical impact. The invention eliminates the need for availability of a large number of different fixtures, capable of exhibiting a range of shock response characteristics, in favor of a single tunable system.

  10. System level mechanical testing of the Clementine spacecraft

    NASA Technical Reports Server (NTRS)

    Haughton, James; Hauser, Joseph; Raynor, William; Lynn, Peter

    1994-01-01

    This paper discusses the system level structural testing that was performed to qualify the Clementine Spacecraft for flight. These tests included spin balance, combined acoustic and axial random vibration, lateral random vibration, quasi-static loads, pyrotechnic shock, modal survey and on-orbit jitter simulation. Some innovative aspects of this effort were: the simultaneously combined acoustic and random vibration test; the mass loaded interface modal survey test; and the techniques used to assess how operating on board mechanisms and thrusters affect sensor vision.

  11. A Study of the Radiant Ignition of a Range of Pyrotechnic Materials Using a CO2 Laser

    DTIC Science & Technology

    1990-08-01

    of colored smoke compositions. The experimental data serves as a us,/.I probe into ignition mechanisms, and may prove of value in the design of...Therefore, it is measured directly from the oscilloscope recording and is designated ti. Secondly, time to Ignition may be measured using the Go/No-Go or...calculated. This is designated tiG. Both approaches were examined in this study. However, because of the large number of tests required for the Go/No-Go

  12. Data Collection using the MetalMapper in Dynamic Data Acquisition and Cued Modes

    DTIC Science & Technology

    2017-07-01

    land mines, pyrotechnics, bombs , and demolition materials. Surface sweeps identified MEC items throughout Units 11 and 12, including 37mm, 40mm...munitions testing and as impact areas for 4.2-in mortars, large caliber projectiles (75mm–155mm), and numerous types of bombs . With the exception of some...RSA-073 includes AN-M76 bombs , PT1 (incendiary mixture similar to “goop”)-filled; M47-type bombs , Isobutyl Methacrylate Incendiary Mix (IM-AE)- and

  13. A Laboratory Investigation of Aerosol and Extinction Characteristics for SALTY DOG, NWC 29 and NWC 78 Pyrotechnics

    DTIC Science & Technology

    1980-10-01

    The artificial fogs are produced by 1’SALTY DOC,14 and phosphorus pentoxide smokeS~in Calspan’s 590 cubic meter chamber at controlled relative...the chamber experiments, an isokinetic sampling inlet was employed for minimizing aerosol losses during sampling. Instrumentation used to monitor...with a 1 cfm critical orifice and vacuum pump. Additionally, a flow meter , placed behind the filter, was monitored to assure that filter loading did

  14. Acute and Subacute Inhalation Toxicity Study in Rats Exposed to Pyrotechnically-Disseminated M18 Red Smoke

    DTIC Science & Technology

    2017-04-12

    ranged from 36 - 39%. Exposure chamber oxygen remained constant at 21%. The animal exposure box temperature ranged from 72 – 73°F and the...0036333, April - September 2015 Chamber Oxygen Chamber Temperature Chamber Relative (N) Exposure Box Exposure Box Relative (N) Exposure No. Date Range...Study No. S.0036333-15, April - September 2015 Chamber Oxygen Chamber Temperature Chamber Relative (N) Exposure Box Exposure Box Relative (N

  15. New Potentials in Red Phosphorus Compositions

    DTIC Science & Technology

    1976-08-01

    COMMAND 101 1 76 WASHINGTON, D. C. 20361 I A Best Avai~lable copy Submi tte:--’,.. . E . DOUA, Manager Chemical Sciences Branch Pyrotechnic Division...PHOPHORUS 7 naw,.pot o tOMPOSITIONS 1.. July 3751,-- 1 Jun 17 Ś. PER WORMING ORG. REPORT NUMBER 7. AUTHOR(s) S. CONTRACT OR GRýANT NUMBER( O ) Henry A...non Dat &.MRM*4) 4I )~ ° o PREFACE The authors would like to thank Mr. John Brown, Mr. Ed Colvin and Mr. William T. Biggs for their assistance in the

  16. Proceedings of the International Pyrotechnics Seminar (5th) Held 12-16 July 1976, Vail, Colorado.

    DTIC Science & Technology

    1976-01-01

    conducted to look for chromium metal and none was found. Further work is needed to characterize the chemical species which are present in the residue...insoluble hexavalent chromium compounds have been declared a carcinogen by the National Institute of Occupational Safety and Health (NIOSH). The evaluation... trivalent and tin quadrivalent the ratio of valence electrons to atoms has the value 3 for these compounds. 𔃼 CuZn (I + 2)/2 = 3/ 2 Cu3Al (3 + 3)/4 - 3 2

  17. 28. VIEW SOUTH FROM SLC3W MST STATION 63. FOREGROUND LEFT: ...

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

    28. VIEW SOUTH FROM SLC-3W MST STATION 63. FOREGROUND LEFT: THEODOLITE SHELTER (BLDG. 786) CENTER LEFT TO RIGHT: GLOBAL POSITIONING SYSTEM AZIMUTH STATION (BLDG. 775), PYROTECHNIC SHED (BLDG. 757), PORTABLE GUARD SHED, METEOROLOGICAL SHED (BLDG. 756), METEOROLOGICAL TOWER. BACKGROUND CENTER TO RIGHT: STORAGE SHED (BLDG. 776), LIQUID OXYGEN APRON, SLC-3E MST, TOP OF SLC-3E FUEL STORAGE TANK. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  18. RDT&E for Emerging Contaminants

    DTIC Science & Technology

    2010-06-01

    Perchlorate ● NDMA ● 1,4-Dioxane ● PFCs 8 Perchlorate Issue ● Broad Use & Occurrence  DoD - Rocket propellant - Insensitive munitions  Pyrotechnics and...and 18O -20 -15 -10 -5.0 0.0 5.0 -30 -25 -20 -15 -10 -5 0 5 10 Laboratory Military Natural Herbicides Gunpowder Road Flares Taiwan 3 7 C l 18 O 27 NDMA ...Toxicology  NDMA is a potent mutagen, teratogen, & carcinogen.  EPA 10-6 Lifetime Cancer Risk = 0.7 ng/L.  California DHS; 10 ng/L Action

  19. 90. VIEW OF OXIDIZER APRON AND SOUTH SIDE OF SKID ...

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

    90. VIEW OF OXIDIZER APRON AND SOUTH SIDE OF SKID 9, SKID 7, AND SKID 9A. COOLING TOWER ON NORTH SIDE OF OXIDIZER APRON. LEFT TO RIGHT IN BACKGROUND: METEOROLOGICAL TOWER, SLC-3W MST, SURPLUS ATLAS E/F LAUNCHER, PYROTECHNIC SHED (BLDG. 757), STORAGE SHED (BLDG. 776), CABLE TRAYS, AND TOP OF LAUNCH OPERATIONS BUILDING (BLDG. 763). - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  20. A Chamber Investigation of the IR and Visible Wavelength Obscuration Properties of Pyrotechnically Generated Smokes,

    DTIC Science & Technology

    1985-05-01

    13 3 Extinction Spectra (Visible to 14 pm Wavelength) of the NWC Smokes at High and Low Humidity.................. 17 4 Relative Size Distributions...percent over the wave- length interval from 2.5- 14 urn. Data acqitisition and reduction are computer controlled. Intensity measurements are obtained at...approximately 0.02 um wavelength intervals, with a complete 2.5- 14 um scan requiring 2 minutes. 4,.N N -Z . Ai,. Figure 1 INTERIOR VIEW OF CAISPAN’S 590m

  1. High-Nitrogen-Based Pyrotechnics: Development of Perchlorate-Free Green-Light Illuminants for Military and Civilian Applications

    DTIC Science & Technology

    2012-01-01

    Table 1. Magnesium served as the main fuel in the formulation, barium nitrate and potassium per- chlorate served as the oxidizers, and dechlorane plus...course of the investigation needed to be changed. Although the initial investigation set out to remove potassium per- chlorate oxidizer from the M195 HHS...become a concern of the US Department of Defense is the “perchlorate issue.” Potassium perchlorate and ammonium perchlorate oxidizers, once believed to be

  2. Rescue Equipment

    NASA Technical Reports Server (NTRS)

    1995-01-01

    The Lifeshear cutter, a rescue tool for freeing accident victims from wreckage, was developed under the Clinton Administration's Technology Reinvestment Program. Prior cutting equipment was cumbersome and expensive; the new cutter is 50 percent lighter and 70 percent cheaper. The cutter is pyrotechnically-actuated, using a miniature version of the power cartridges used for separation devices on the Space Shuttle and other NASA spacecraft. Hi-Shear Technology Corporation developed the cutter with the Jet Propulsion Laboratory and input from the City of Torrance (California) Fire Department.

  3. Demonstration of the B4C/NaIO4/PTFE Delay in the U.S. Army Hand-Held Signal

    DTIC Science & Technology

    2015-05-20

    Figure 1. Partial cross section diagram of a hand-held signal showing the rocket motor , delay element, expelling charge, and pyrotechnic payload as...The black powder-based rocket motor , consisting of propellant pellets (G) encased in a cardboard tube, contains an axial core hole to accommodate the...that ignites the rocket motor . Simultaneously, the delay element is ignited and burns for an interval (preferably 5−6 s) before it ignites the black

  4. Ab initio Quantum Chemical Reaction Kinetics: Recent Applications in Combustion Chemistry (Briefing Charts)

    DTIC Science & Technology

    2015-06-28

    HMX RDX  Recent Works  See Geith et al...Propellants, Explosives, Pyrotechnics, 29, 3 (2004)  ∆Hcomb(DNB) = (5195 ± 300) kJ kg-1 (bomb calorimetry and MP2/cc-pVTZ ∆Hf) cf HMX 9435 & RDX 9560 kJ...kg-1  Vd = 8660 ms-1, cf HMX 9100 & RDX 8750 ms-1  See Geith et al., Combust and Flame, 139, 358 (2004)  Recent synthesis (known since 1898 by

  5. Age Life Evaluation of Space Shuttle Crew Escape System Pyrotechnic Components Loaded with Hexanitrostilbene (HNS)

    NASA Technical Reports Server (NTRS)

    Hoffman, William C., III

    1996-01-01

    Determining deterioration characteristics of the Space Shuttle crew escape system pyrotechnic components loaded with hexanitrostilbene would enable us to establish a hardware life-limit for these items, so we could better plan our equipment use and, possibly, extend the useful life of the hardware. We subjected components to accelerated-age environments to determine degradation characteristics and established a hardware life-limit based upon observed and calculated trends. We extracted samples using manufacturing lots currently installed in the Space Shuttle crew escape system and from other NASA programs. Hardware included in the study consisted of various forms and ages of mild detonating fuse, linear shaped charge, and flexible confined detonating cord. The hardware types were segregated into 5 groups. One was subjected to detonation velocity testing for a baseline. Two were first subjected to prolonged 155 F heat exposure, and the other two were first subjected to 255 F, before undergoing detonation velocity testing and/or chromatography analysis. Test results showed no measurable changes in performance to allow a prediction of an end of life given the storage and elevated temperature environments the hardware experiences. Given the lack of a definitive performance trend, coupled with previous tests on post-flight Space Shuttle hardware showing no significant changes in chemical purity or detonation velocity, we recommend a safe increase in the useful life of the hardware to 20 years, from the current maximum limits of 10 and 15 years, depending on the hardware.

  6. The Meteosat Second Generation (MSG) power system

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

    Haines, J.E.; Levins, D.; Robben, A.

    1997-12-31

    Under the direction of the European Meteorological Satellite Organization (EUMETSAT) and the European Space Agency (ESA), space industries within Europe are in the process of developing a new series of larger and more performant geostationary weather satellites. The initial three spacecraft within this new series, which are known by the name of Meteosat Second Generation (MSG), are due to be progressively launched from the year 2000 onwards. The major objective of this mission is the continuation of the European weather watch and space borne atmospheric sensing services provided by the present series of Meteosat spacecraft. To satisfy this mission requirement,more » the payload compliment to be supported by MSG will consist of a comprehensive earth viewing instrument capable of operating in both the infra-red and visible spectrum, an earth radiation measurement system and a search and rescue facility. In furnishing the power needs for these payloads, the power generating element on the spin stabilized MSG spacecraft consists of a body mounted solar array, capable of providing 628 watts of electrical power at the end of seven years of geosynchronous orbital lifetime. The energy storage elements for the spacecraft consists of two, 29 ampere-hour batteries, while centralized power management is achieved by the Power Control Unit (PCU), which satisfies the payload and battery re-charge demands by controlling the available solar array power. Power distribution for the spacecraft electrical loads and heaters is achieved by the Power Distribution Unit (PDU) and for the pyrotechnic devices by the Pyrotechnic Release Unit.« less

  7. Failure Mode Analysis of V-Shaped Pyrotechnically Actuated Valves

    NASA Technical Reports Server (NTRS)

    Sachdev, Jai S.; Hosangadi, A.; Chenoweth, James D.; Saulsberry, Regor L.; McDougle, Stephen H.

    2012-01-01

    Current V-shaped stainless steel pyrovalve initiators have rectified many of the deficiencies of the heritage Y-shaped aluminum design. However, a credible failure mode still exists for dual simultaneous initiator (NSI) firings in which low temperatures were detected at the booster cap and less consistent ignition was observed than when a single initiator was fired. In order to asses this issue, a numerical framework has been developed for predicting the flow through pyrotechnically actuated valves. This framework includes a fully coupled solution of the gas-phase equation with a non-equilibrium dispersed phase for solid particles as well as the capability to model conjugate gradient heat transfer to the booster cap. Through a hierarchy of increasingly complex simulations, a hypothesis for the failure mode of the nearly simultaneous dual NSI firings has been proven. The simulations indicate that the failure mode for simultaneous dual NSI firings may be caused by flow interactions between the flame channels. The shock waves from each initiator interact in the booster cavity resulting in a high pressure that prevents the gas and particulate velocity from rising in the booster cap region. This impedes the bulk of the particulate phase from impacting the booster cap and reduces the heat transfer to the booster cap since the particles do not impact it. Heat transfer calculations to the solid metal indicate that gas-phase convective heat transfer may not be adequate by itself and that energy transfer from the particulate phase may be crucial for the booster cap burn through.

  8. HIDEF Igniter Technology Program. Phase I. Final Report. Appendix A. Polyhedral Boranes in Pyrotechnic Applications

    DTIC Science & Technology

    1980-06-15

    confirmed by its infrared ab- sorption sivcirum. Thtf s.ills of this invention arc especially useful as high encr.uy fuel«, because of their hi^h...very strcn.c acid, having an equivalence point at a pH of 7. The infrared ab- sorption sp’.ctrum (-I- tic add, which, free of solvent of crysta...ia the reaction vessel is collected, washed thoroughly with dry ether and dri^d to give 2.’J8 g. of a white solid. The infrared ab- sorption

  9. Proceedings of the International Pyrotechnics Seminar (6th) Held at Estes Park, Colorado, 17-21 July 1978

    DTIC Science & Technology

    1978-06-01

    in metal form, and not as an oxide , as with conventional HC compositions. "That verified the fact that the aluminum did not take part in the chemical...the melting of the protective oxide layer on the aluminum particle with an attendant increase in surface reaction rate leading to ignition. Oxide ...detonation 5 aluminum BrF5 partial detonation 6 propylene oxide ClF3 partial detonation 621 041 IR! Each teat used about 5 kg of fuel, about 400 g

  10. Pyrotechnic Panel Minutes. Volume 13, Numbers 518-579

    DTIC Science & Technology

    1946-11-01

    fron 5.3.1*6 to 29.10.1*6. Lt. Cdr. M. P. Price , (D.M.O.) from 13.7.1*6. Mr. P. Trier, R.N. (D.N.O.) from 1.1*.1*6. Lt. Col. 0. H...34. Aluminium Cases. Designs and Production . 538 Bomb, Practice, A/C) 10_lb. Nk.IV, Flame. Leakage Test. 539 S.3.432 filling for dockets...Signal and Target Practice. Climatic Trials: Abolition of T7ar Production Permits. DS 82227/1 3 Minute _ , . , PJ. No. SubJect 544

  11. High-nitrogen-based pyrotechnics: development of perchlorate-free green-light illuminants for military and civilian applications.

    PubMed

    Sabatini, Jesse J; Raab, James M; Hann, Ronald K; Damavarapu, Reddy; Klapötke, Thomas M

    2012-06-01

    The development of perchlorate-free hand-held signal illuminants for the US Army's M195 green star parachute is described. Compared with the perchlorate-containing control, the optimized perchlorate-free illuminants were less sensitive toward various ignition stimuli while offering comparable burn times and visible-light outputs. The results were also important from the perspective of civilian fireworks because the development of perchlorate-free illuminants remains an important objective of the commercial fireworks industry. Copyright © 2012 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

  12. Computer modeling of electrical performance of detonators

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

    Furnberg, C.M.; Peevy, G.R.; Brigham, W.P.

    1995-05-01

    An empirical model of detonator electrical performance which describes the resistance of the exploding bridgewire (EBW) or exploding foil initiator (EFI or slapper) as a function of energy, deposition will be described. This model features many parameters that can be adjusted to obtain a close fit to experimental data. This has been demonstrated using recent experimental data taken with the cable discharge system located at Sandia National Laboratories. This paper will be a continuation of the paper entitled ``Cable Discharge System for Fundamental Detonator Studies`` presented at the 2nd NASA/DOD/DOE Pyrotechnic Workshop.

  13. NASA Standard Initiator Susceptibility to UHF and S-Band Radio Frequency Power and Lightning Strikes

    NASA Technical Reports Server (NTRS)

    Burnham, Karen; Scully, Robert; Norgard, John

    2013-01-01

    The NASA Standard Initiator (NSI) is an important piece of pyrotechnic equipment used in many space applications. This presentation will outline the results of a series of tests done at UHF and S-Band frequencies to determine NSI susceptibility to Radio Frequency (RF) power. The results show significant susceptibility to pulsed RF power in the S-Band region. Additional testing with lightning pulses injected into the firing line harness, modelling the indirect effects of a lightning strike to a spacecraft, showed no vulnerability

  14. Metal Residue Deposition from Military Pyrotechnic Devices and Field Sampling Guidance

    DTIC Science & Technology

    2012-05-01

    given NA 0.002 NA NA Chromium Oxide 1308-38-9 NA NA NA 0.015 Cobalt Naphthenate 61789-51-3 NA NA NA 0.017 Copper Oxide Black 1317-38-0 NA 1.32 NA...the whistling booby trap simulators included 73% potassium perchlorate, 24% gallic acid , and 3 % red gum (McIntyre 1980). Whereas the booby-trap...M21 Flash Artillery Simulator 50 3785.8 2/5/10 All – indicates the entire volume of stained snow was removed . MI – multi-increment. Rep

  15. Metal Residue Deposition from Military Pyrotechnic Devices and Field Sampling Guidance

    DTIC Science & Technology

    2012-05-01

    0.002 26.4 NA 0.082 Cerium none given NA 0.002 NA NA Chromium Oxide 1308-38-9 NA NA NA 0.015 Cobalt Naphthenate 61789-51-3 NA NA NA 0.017 Copper...the 1980s, the constituents in the whistling booby trap simulators included 73% potassium perchlorate, 24% gallic acid , and 3 % red gum (McIntyre...Test 3, MI snow sample, Rep 3 M21 Flash Artillery Simulator 50 3785.8 2/5/10 All – indicates the entire volume of stained snow was removed . MI

  16. NASA Standard Initiator Susceptibility to UHF and S-Band Radio Frequency Power and Lightning Strikes

    NASA Technical Reports Server (NTRS)

    Burnham, Karen; Scully, Robert C.; Norgard, John D.

    2013-01-01

    The NASA Standard Initiator (NSI) is an important piece of pyrotechnic equipment used in many space applications. This paper outlines the results of a series of tests done at UHF and S-Band frequencies to determine NSI susceptibility to Radio Frequency (RF) power. The results show significant susceptibility to pulsed RF power in the S-Band region. Additional testing with lightning pulses injected into the firing line harness, modelling the indirect effects of a lightning strike to a spacecraft, showed no vulnerability.

  17. New Generation Power System for Space Applications

    NASA Technical Reports Server (NTRS)

    Jones, Loren; Carr, Greg; Deligiannis, Frank; Lam, Barbara; Nelson, Ron; Pantaleon, Jose; Ruiz, Ian; Treicler, John; Wester, Gene; Sauers, Jim; hide

    2004-01-01

    The Deep Space Avionics (DSA) Project is developing a new generation of power system building blocks. Using application specific integrated circuits (ASICs) and power switching modules a scalable power system can be constructed for use on multiple deep space missions including future missions to Mars, comets, Jupiter and its moons. The key developments of the DSA power system effort are five power ASICs and a mod ule for power switching. These components enable a modular and scalab le design approach, which can result in a wide variety of power syste m architectures to meet diverse mission requirements and environments . Each component is radiation hardened to one megarad) total dose. The power switching module can be used for power distribution to regular spacecraft loads, to propulsion valves and actuation of pyrotechnic devices. The number of switching elements per load, pyrotechnic firin gs and valve drivers can be scaled depending on mission needs. Teleme try data is available from the switch module via an I2C data bus. The DSA power system components enable power management and distribution for a variety of power buses and power system architectures employing different types of energy storage and power sources. This paper will describe each power ASIC#s key performance characteristics as well a s recent prototype test results. The power switching module test results will be discussed and will demonstrate its versatility as a multip urpose switch. Finally, the combination of these components will illu strate some of the possible power system architectures achievable fro m small single string systems to large fully redundant systems.

  18. Proposed system safety design and test requirements for the microlaser ordnance system

    NASA Technical Reports Server (NTRS)

    Stoltz, Barb A.; Waldo, Dale F.

    1993-01-01

    Safety for pyrotechnic ignition systems is becoming a major concern for the military. In the past twenty years, stray electromagnetic fields have steadily increased during peacetime training missions and have dramatically increased during battlefield missions. Almost all of the ordnance systems in use today depend on an electrical bridgewire for ignition. Unfortunately, the bridgewire is the cause of the majority of failure modes. The common failure modes include the following: broken bridgewires; transient RF power, which induces bridgewire heating; and cold temperatures, which contracts the explosive mix away from the bridgewire. Finding solutions for these failure modes is driving the costs of pyrotechnic systems up. For example, analyses are performed to verify that the system in the environment will not see more energy than 20 dB below the 'No-fire' level. Range surveys are performed to determine the operational, storage, and transportation RF environments. Cryogenic tests are performed to verify the bridgewire to mix interface. System requirements call for 'last minute installation,' 'continuity checks after installation,' and rotating safety devices to 'interrupt the explosive train.' As an alternative, MDESC has developed a new approach based upon our enabling laser diode technology. We believe that Microlaser initiated ordnance offers a unique solution to the bridgewire safety concerns. For this presentation, we will address, from a system safety viewpoint, the safety design and the test requirements for a Microlaser ordnance system. We will also review how this system could be compliant to MIL-STD-1576 and DOD-83578A and the additional necessary requirements.

  19. Sea-Level Flight Demonstration and Altitude Characterization of a LO2/LCH4 Based Accent Propulsion Lander

    NASA Technical Reports Server (NTRS)

    Collins, Jacob; Hurlbert, Eric; Romig, Kris; Melcher, John; Hobson, Aaron; Eaton, Phil

    2009-01-01

    A 1,500 lbf thrust-class liquid oxygen (LO2)/Liquid Methane (LCH4) rocket engine was developed and tested at both sea-level and simulated altitude conditions. The engine was fabricated by Armadillo Aerospace (AA) in collaboration with NASA Johnson Space Center. Sea level testing was conducted at Armadillo Aerospace facilities at Caddo Mills, TX. Sea-level tests were conducted using both a static horizontal test bed and a vertical take-off and landing (VTOL) test bed capable of lift-off and hover-flight in low atmosphere conditions. The vertical test bed configuration is capable of throttling the engine valves to enable liftoff and hover-flight. Simulated altitude vacuum testing was conducted at NASA Johnson Space Center White Sands Test Facility (WSTF), which is capable of providing altitude simulation greater than 120,000 ft equivalent. The engine tests demonstrated ignition using two different methods, a gas-torch and a pyrotechnic igniter. Both gas torch and pyrotechnic ignition were demonstrated at both sea-level and vacuum conditions. The rocket engine was designed to be configured with three different nozzle configurations, including a dual-bell nozzle geometry. Dual-bell nozzle tests were conducted at WSTF and engine performance data was achieved at both ambient pressure and simulated altitude conditions. Dual-bell nozzle performance data was achieved over a range of altitude conditions from 90,000 ft to 50,000 ft altitude. Thrust and propellant mass flow rates were measured in the tests for specific impulse (Isp) and C* calculations.

  20. Flame Temperatures and Internal Pressures of Pyrotechnic Igniters Used in Liquid Propellant Gun Firings

    DTIC Science & Technology

    1982-03-01

    IP AT 655 ~~I . . . . . 45 7 I. INTRODUCTION The lack of quantitative ignition design criteria in liquid propellant gun firings requires the...Meeting~ CPIA PubUaation No. :300~ VoZ . I, AppUed Physias Laboratory~ SiZver Spring~ MD~ p. :39:3 (19?9). 26 REFERENCES 1. J. D. Knapton, I. C. Stobie...T9E6 Igniter and a Booster Charge of M30 and Eimite !I I ll[[l 1!13 IP -111 .. Sll tiiiiML I RRX-P.D. !1252 I ~· s 1: 31~ 211 z II Figure B2

  1. De-Trending Techniques: Methods for Cleaning Questionable Shock Data

    NASA Technical Reports Server (NTRS)

    Grillo, Vincent J.

    2010-01-01

    Not all zero shifted acceleration data can De-trended using this technique. DC shifts, improper AC coupling, Circuit noise/EMI/EMR, Equivalent RC circuit gain response/Circuit saturation(Slew Rate Limited), fixture grounding and wiring losses can all contribute to bad shock data being recorded. Some data that is zero-shifted or exhibit large instantaneous velocity shifts is inherently bad and a retest is warranted. Clean Acceleration-Time history data can be bad upon examining the Velocity & Displacement profiles. Laser Vibrometers provide a high level of accuracy for pyrotechnic shock testing. Engineering judgment and experience will determine the validity of Shock data.

  2. Thin-film optical initiator

    DOEpatents

    Erickson, Kenneth L.

    2001-01-01

    A thin-film optical initiator having an inert, transparent substrate, a reactive thin film, which can be either an explosive or a pyrotechnic, and a reflective thin film. The resultant thin-film optical initiator system also comprises a fiber-optic cable connected to a low-energy laser source, an output charge, and an initiator housing. The reactive thin film, which may contain very thin embedded layers or be a co-deposit of a light-absorbing material such as carbon, absorbs the incident laser light, is volumetrically heated, and explodes against the output charge, imparting about 5 to 20 times more energy than in the incident laser pulse.

  3. Problem Definition Studies on Potential Environmental Pollutants. V. Physical, Chemical, Toxicological, and Biological Properties of Seven Chemicals used in Pyrotechnic Compositions

    DTIC Science & Technology

    1979-10-01

    obLrved in raLs treated it 500 mg/animal for three days. Produces cystic changes in rat kidneys. Vat Yellow 4 No definitive infrrmation retrieved on... pulmonary function, and oxygen consumption. Exposure to a nominal concentration of 2.5 mg/L (260 ppm) for B hours showed no toxic signs during exposure or for...to 260 ppmn icxachlzroethane showed severe s’gns of irritation, no changeq ii pulmonary function could be detectt-d.o4’ Six- tek exposure to 260 ppm

  4. Development, qualification, and delivery of a hydrogen burnoff igniter

    NASA Technical Reports Server (NTRS)

    Ray, D.

    1981-01-01

    The hydrogen burnoff igniter, a pyrotechnic device used to burn off excess hydrogen gas near the Space Shuttle Main Engine (SSME) nozzle, was designed, fabricated, and qualified. Characteristics of the burnoff igniter include a function time of 8 + or - 2 seconds, a minimum three foot flame length at maximum output, and hot particles projected 15 feet when fired directly into or perpendicular to a 34.5 knot wind. The three foot flame length was considered to be of questionable importance, since the hot particles are the media for igniting the hydrogen. Flame temperature is greater than 1500 F.

  5. Effects of a Near Field Pyroshock on the Performance of a Nitramine Nitrocellulose Propellant

    NASA Technical Reports Server (NTRS)

    Baca, Arcenio

    2016-01-01

    The purpose of this study is to investigate the effects of a pyroshock environment on the performance characteristics of a propellant used in pyrotechnic devices such as guillotine cutters. A heritage pressure cartridge assembly which uses a nitramine nitrocellulose propellant with a known performance baseline will be exposed to a near field pyroshock event. The pressure cartridge will then be fired in an ambient closed bomb firing to collect pressure time history. This data will be compared to the baseline data to evaluate the effects of the shock on the performance of the propellant.

  6. 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.

  7. Logistics Complete Round Charts: Grenades, Mines, Pyrotechnics, Rockets, Rocket Motors, Demolition Material

    DTIC Science & Technology

    1986-06-01

    Flash 3. (342 g) Electrically Comp Actuated By Blasting Machine or Battery 5/ 8 STD 37524 Simulator, Projectile M1lSA2 0.30 7549246 MIL-S-10058 Hand...8799710 Blastin Comp (0.07 oz) Blasting (Whistle) Fuze Fuze 8-14 Frictio Friction (Burst) ’ l3AI M3A1 721 Igniter 8833721 Igniter last 5-10 8799714...8799715 iBlasti Blasting Sec FuzeN Fuze M3A1 •721 Igniter 8833721 Igniter Inst 6-10 8799714 879971 Blast Blasting See Fuze Puze N13A1 587 FrictLi 8848587

  8. Four-terminal electrical testing device. [initiator bridgewire resistance

    NASA Technical Reports Server (NTRS)

    Robinson, Robert L. (Inventor); Graves, Thomas J. (Inventor); Hoffman, William C., III (Inventor)

    1987-01-01

    The invention relates to a four-terminal electrical connector device for testing and measuring unknown resistances of initiators used for starting pyrotechnic events aboard the space shuttle. The testing device minimizes contact resistance degradation effects and so improves the reliability of resistance measurements taken with the device. Separate and independent voltage sensing and current supply circuits each include a pair of socket contacts for mating engagement with the pins of the initiator. The unknown resistance that is measured by the device is the resistance of the bridgewire of the initiator which is required to be between 0.95 and 1.15 ohms.

  9. Viton's Impact on NASA Standard Initiator Propellant Properties

    NASA Technical Reports Server (NTRS)

    Hohmann, Carl; Tipton, Bill, Jr.

    2000-01-01

    This paper discusses some of the properties of Viton that are relevant to its use as a pyrotechnic binder in a NASA standard initiator (NSI) propellant. Nearly every aspect of NSI propellant manufacture and use is impacted by the binder system. The effect of Viton's molecular weight on solubility, solution viscosity, glass transition temperature, and strength characteristics as applied to NSI production and performance are reviewed. Emphasis is placed on the Viton fractionation that occurs during the precipitation cycle and its impact on bridgewire functions. Special consideration is given to the production of bridgewire slurry mixtures.

  10. A summary of the mechanical design, testing and performance of the IMP-H and J attitude control systems

    NASA Technical Reports Server (NTRS)

    Metzger, J. R.

    1974-01-01

    The main aspects of the attitude control system used on both the IMP-H and J spacecraft are presented. The mechanical configuration is described. Information on all the specific components comprising the flight system is provided. The acceptance and qualification testing of both individual components and the installed system are summarized. Functional information regarding the operation and performance in relation to the orbiting spacecraft and its mission is included. Related topics which are discussed are: (1) safety requirements, (2) servicing procedures, (3) anomalous behavior, and (4) pyrotechnic devices.

  11. NASA Space Mechanisms Handbook and Reference Guide Expanded Into CD-ROM Set

    NASA Technical Reports Server (NTRS)

    Fusaro, Robert L.

    2002-01-01

    Several NASA missions suffered failures and anomalies due to problems in applying space mechanisms technology to specific projects. Research shows that engineers often lack either adequate knowledge of mechanism design or sufficient understanding of how mechanisms affect sensitive systems. The Space Mechanisms Project conducted a Lessons Learned study and published a Space Mechanisms Handbook to help space industry engineers avoid recurring design, qualification, and application problems. The Space Mechanisms Handbook written at the NASA Glenn Research Center details the state-of-the-art in space mechanisms design as of 1998. NASA's objective in developing this Space Mechanisms Handbook was to provide readily accessible information on such areas as space mechanisms design, mechanical component availability and use, testing and qualification of mechanical systems, and a listing of worldwide space mechanisms experts and testing facilities in the United States. This handbook has been expanded into a two-volume CD-ROM set in an Adobe Acrobat format. In addition to the handbook, the CD's include (1) the two volume Space Mechanisms Lessons Learned Study, (2) proceedings from all the NASA hosted Aerospace Mechanisms Symposia held through the year 2000, (3) the Space Materials Handbook, (4) the Lubrication Handbook for the Space Industry, (5) the Structural & Mechanical Systems Long-Life Assurance Design Guidelines, (6) the Space Environments and Effects Source-Book, (7) the Spacecraft Deployable Appendages manual, (8) the Fastener Design Manual, (9) A Manual for Pyrotechnic Design, Development and Qualification, (10) the Report on Alternative Devices to Pyrotechnics on Spacecraft, and (11) Gearing (a manual). In addition, numerous other papers on tribology and lubrication are included.This technical summary of the project provides information on how to obtain the handbook and related information.

  12. Diversionary device history and revolutionary advancements.

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

    Cooper, Paul W.; Grubelich, Mark Charles

    Diversionary devices also known as flash bangs or stun grenades were first employed about three decades ago. These devices produce a loud bang accompanied by a brilliant flash of light and are employed to temporarily distract or disorient an adversary by overwhelming their visual and auditory senses in order to gain a tactical advantage. Early devices that where employed had numerous shortcomings. Over time, many of these deficiencies were identified and corrected. This evolutionary process led to today's modern diversionary devices. These present-day conventional diversionary devices have undergone evolutionary changes but operate in the same manner as their predecessors. Inmore » order to produce the loud bang and brilliant flash of light, a flash powder mixture, usually a combination of potassium perchlorate and aluminum powder is ignited to produce an explosion. In essence these diversionary devices are small pyrotechnic bombs that produce a high point-source pressure in order to achieve the desired far-field effect. This high point-source pressure can make these devices a hazard to the operator, adversaries and hostages even though they are intended for 'less than lethal' roles. A revolutionary diversionary device has been developed that eliminates this high point-source pressure problem and eliminates the need for the hazardous pyrotechnic flash powder composition. This new diversionary device employs a fuel charge that is expelled and ignited in the atmosphere. This process is similar to a fuel air or thermobaric explosion, except that it is a deflagration, not a detonation, thereby reducing the overpressure hazard. This technology reduces the hazard associated with diversionary devices to all involved with their manufacture, transport and use. An overview of the history of diversionary device development and developments at Sandia National Laboratories will be presented.« less

  13. Treatment of Solid Rocket Motors that Complies with Established Protocols to Ensure Planetary Protection

    NASA Technical Reports Server (NTRS)

    Stefanski, Philip L.; Soler-Luna, Adrian

    2017-01-01

    This presentation discusses recent work being conducted by the National Aeronautics and Space Administration (NASA) at Marshall Space Flight Center (MSFC) to evaluate various methods that could be employed to provide for planetary protection of those solar system bodies that are candidates for extraterrestrial life, thus preventing contamination of such bodies. MSFC is presently involved in the development phase of the Europa Lander De-Orbital Stage (DOS) braking motor. In order to prevent bio-contamination of this Jovian satellite, three paths are currently being considered. The first is (1) Bio-Reduction of those microscopic organisms in or on the vehicle (in this case a solid rocket motor (SRM)) that might otherwise be transported during the mission. Possible methods being investigated include heat sterilization, application or incorporation of biocide materials, and irradiation. While each method can be made to work, effects on the SRM's components (propellant, liner, insulation, etc.) could well prove deleterious. A second path would be use of (2) Bio-Barrier material(s). So long as such barrier(s) can maintain their integrity, planetary protection should be afforded. Under the harsh conditions encountered during extended spaceflight (vacuum, temperature extremes, radiation), however, such barrier(s) could well experience a breach. Finally, a third path would be to perform (3) Pyrotechnic Sterilization of the SRM during its end-of-mission phase. Multiple pyrotechnic units would be triggered to ensure activation of such an event and provide for a final sterilization before vehicle impact. In light of Europa's stringent bio-reduction targets, the final and best choice to minimize risk will probably be some combination of the above.

  14. A low cost igniter utilizing an SCB and titanium sub-hydride potassium perchlorate pyrotechnic

    NASA Technical Reports Server (NTRS)

    Bickes, R. W., Jr.; Grubelich, M. C.; Hartman, J. K.; McCampbell, C. B.; Churchill, J. K.

    1994-01-01

    A conventional NSI (NASA Standard Initiator) normally employs a hot-wire ignition element to ignite ZPP (zirconium potassium perchlorate). With minor modifications to the interior of a header similar to an NSI device to accommodate an SCB (semiconductor bridge), a low cost initiator was obtained. In addition, the ZPP was replaced with THKP (titanium sub-hydride potassium perchlorate) to obtain increased overall gas production and reduced static-charge sensitivity. This paper reports on the all-fire and no-fire levels obtained and on a dual mix device that uses THKP as the igniter mix and a thermite as the output mix.

  15. Dual mode warhead

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

    Obrsky, J.; Alexander, A.A.; Griffen, O.H.

    1980-12-31

    A dual mode warhead is provided for use against both soft and hard targets and capable of sensing which type of target has been struck comprising a casing made of a ductile material containing an explosive charge and a fuze assembly. The ductile warhead casing will mushroom and later split upon striking a hard target while still confining the explosive. Proper ductility and confinement are necessary for fuze sensing. The fuze assembly contains a pair of parallel firing trains, one initiated only by high and one by low impact deceleration. The firing train actuated by low impact deceleration contains amore » pyrotechnic delay to allow penetration of soft targets.« less

  16. Final report on the oxidation of energetic materials in supercritical water. Final Air Force report

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

    Buelow, S.J.; Allen, D.; Anderson, G.K.

    1995-04-03

    The objective of this project was to determine the suitability of oxidation in supercritical fluids (SCO), particularly water (SCWO), for disposal of propellants, explosives, and pyrotechnics (PEPs). The SCO studies of PEPs addressed the following issues: The efficiency of destruction of the substrate. The products of destruction contained in the effluents. Whether the process can be conducted safely on a large scale. Whether energy recovery from the process is economically practicable. The information essential for process development and equipment design was also investigated, including issues such as practical throughput of explosives through a SCWO reactor, reactor materials and corrosion, andmore » models for process design and optimization.« less

  17. Pyrotechnically Operated Valves for Testing and Flight

    NASA Technical Reports Server (NTRS)

    Conley, Edgar G.; St.Cyr, William (Technical Monitor)

    2002-01-01

    Pyrovalves still warrant careful description of their operating characteristics, which is consistent with the NASA mission - to assure that both testing and flight hardware perform with the utmost reliability. So, until the development and qualification of the next generation of remotely controlled valves, in all likelihood based on shape memory alloy technology, pyrovalves will remain ubiquitous in controlling flow systems aloft and will possibly see growing use in ground-based testing facilities. In order to assist NASA in accomplishing this task, we propose a three-phase, three-year testing program. Phase I would set up an experimental facility, a 'test rig' in close cooperation with the staff located at the White Sands Test Facility in Southern New Mexico.

  18. Deployment Mechanism for the Space Technology 5 Micro Satellite

    NASA Technical Reports Server (NTRS)

    Rossoni, Peter; Cooperrider, Caner; Durback, Gerard

    2004-01-01

    Space Technology 5 (ST5) is a technology mission that will send three spin-stabilized, 25-kg satellites into a highly elliptical Earth orbit. Each of these satellites must be deployed separately from the same launch vehicle with a spin rate of 3.4 rads (32.4 rpm). Because of the satellite's small size and the requirement to achieve its mission spin rate on deploy, typical spin table, pyrotechnic deployment devices or spin up thrusters could not be used. Instead, this new mechanism design employs a "Frisbee" spin up strategy with a shape memory alloy actuated Pinpuller to deploy each satellite. The mechanism has undergone several design and test iterations and has been successfully qualified for flight.

  19. On firework blasts and qualitative parameter dependency.

    PubMed

    Zohdi, T I

    2016-01-01

    In this paper, a mathematical model is developed to qualitatively simulate the progressive time-evolution of a blast from a simple firework. Estimates are made for the blast radius that one can expect for a given amount of detonation energy and pyrotechnic display material. The model balances the released energy from the initial blast pulse with the subsequent kinetic energy and then computes the trajectory of the material under the influence of the drag from the surrounding air, gravity and possible buoyancy. Under certain simplifying assumptions, the model can be solved for analytically. The solution serves as a guide to identifying key parameters that control the evolving blast envelope. Three-dimensional examples are given.

  20. Portable heatable container

    NASA Technical Reports Server (NTRS)

    Yang, L. C. (Inventor)

    1980-01-01

    A container is provided which can be designed to heat its outer surface to sterilize it, or to heat its inner surface and any contents therewithin. In a container that self sterilizes its outer surface, the container includes a combustible layer of thermite-type pyrotechnic material which can be ignited to generate considerable heat, and a thin casing around the combustible layer which is of highly thermally conductive materials such as aluminum which can be heated to a high temperature by the ignited combustible layer. A buffer layer which may be of metal, lies within the combustible layer, and a layer of insulation such as Teflon lies within the buffer layer to insulate the contents of the container from the heat.

  1. Deployment Mechanism for the Space Technology 5 Micro Satellite

    NASA Technical Reports Server (NTRS)

    Rossoni, Peter; Cooperrider, Caner; Durback, Gerard

    2004-01-01

    Space Technology 5 (ST5) is a technology mission that will send three spin-stabilized, 25-kg satellites into a highly elliptical Earth orbit. Each of these satellites must be deployed separately from the same launch vehicle with a spin rate of 3.4 rad/s (32.4 rpm). Because of the satellite's small size and the requirement to achieve its mission spin rate on deploy, typical spin table, pyrotechnic deployment devices or spin up thrusters could not be used. Instead, this new mechanism design employs a 'Frisbee' spin up strategy with a shape memory alloy actuated Pinpuller to deploy each satellite. The mechanism has undergone several design and test iterations and has been successfully qualified for flight.

  2. Portable heatable container

    NASA Astrophysics Data System (ADS)

    Yang, L. C.

    1980-03-01

    A container is provided which can be designed to heat its outer surface to sterilize it, or to heat its inner surface and any contents therewithin. In a container that self sterilizes its outer surface, the container includes a combustible layer of thermite-type pyrotechnic material which can be ignited to generate considerable heat, and a thin casing around the combustible layer which is of highly thermally conductive materials such as aluminum which can be heated to a high temperature by the ignited combustible layer. A buffer layer which may be of metal, lies within the combustible layer, and a layer of insulation such as Teflon lies within the buffer layer to insulate the contents of the container from the heat.

  3. On firework blasts and qualitative parameter dependency

    PubMed Central

    Zohdi, T. I.

    2016-01-01

    In this paper, a mathematical model is developed to qualitatively simulate the progressive time-evolution of a blast from a simple firework. Estimates are made for the blast radius that one can expect for a given amount of detonation energy and pyrotechnic display material. The model balances the released energy from the initial blast pulse with the subsequent kinetic energy and then computes the trajectory of the material under the influence of the drag from the surrounding air, gravity and possible buoyancy. Under certain simplifying assumptions, the model can be solved for analytically. The solution serves as a guide to identifying key parameters that control the evolving blast envelope. Three-dimensional examples are given. PMID:26997903

  4. Comparison of Thoracic Injury Risk in Frontal Car Crashes for Occupant Restrained without Belt Load Limiters and Those Restrained with 6 kN and 4 kN Belt Load Limiters.

    PubMed

    Foret-Bruno, J Y; Trosseille, X; Page, Y; Huère, J F; Le Coz, J Y; Bendjellal, F; Diboine, A; Phalempin, T; Villeforceix, D; Baudrit, P; Guillemot, H; Coltat, J C

    2001-11-01

    In France, as in other countries, accident research studies show that a large proportion of restrained occupants who sustain severe or fatal injuries are involved in frontal impacts (65% and 50%, respectively). In severe frontal impacts with restrained occupants and where intrusion is not preponderant, the oldest occupants very often sustain severe thoracic injuries due to the conventional seat belt. As we have been observing over the last years, we will expect in the coming years developments which include more solidly-built cars, as offset crash test procedures are widely used to evaluate the passive safety of production vehicles. The reduction of intrusion for the most severe frontal impacts, through optimization of car deformation, usually translates into an increase in restraint forces and hence thoracic injury risk with a conventional retractor seat belt for a given impact severity. It is, therefore essential to limit the restraint forces exerted by the seat belt on the thorax in order to reduce the number of road casualties. In order to address thoracic injury risk in frontal impact, Renault cars have been equipped with the Programmed Restraint System (PRS) since 1995. The PRS is a restraint system that combines belt load limitation and pyrotechnic belt pretension. In an initial design of the Programmed Restraint System (PRS1), the belt load limiter was a steel component designed to shear at a given shoulder force, namely 6 kN. It was mounted between the retractor and the lower anchorage point of the belt. The design of the PRS was modified in 1998 (PRS2), but the principle of load limitation was maintained. The threshold was decreased to 4 kN and this lower belt belt-force limiter has been combined with a specially designed airbag. This paper reports on 347 real-world frontal accidents where the EES (Equivalent Energy Speed) ranged from 35 to 75 km/h. One hundred and ninety-eight (198) of these accidents involved cars equipped with the 6 kN load limiter, and 149 involved cars equipped with the 4 kN load limiter. Based on this accident data, the study compares the thoracic injury risk for two occupant populations: belted occupants involved in accidents in which the vehicle was not equipped with a load limiter (378 cases with pyrotechnic pretensioners), and belted occupants involved in accidents in which the vehicles were equipped with 4 or 6 kN load limiters and pyrotechnic pretensioners (347 cases). One observes that a 4 kN load limitation results in a very important reduction of thoracic injury risk for all AIS levels, compared to others samples. 50 to 60% reduction for AIS 2+ was observed, as well as 75 to 85% for AIS 3+. The complete absence of AIS 4+ with a 4 kN load limiter must be stressed, though it remains more than 8% for the other samples (no limiter and 6 kN limiter).

  5. [Tadeusz Tucholski (1898-1940). A contribution to the scientific biography].

    PubMed

    Tucholska-Załuska, Hanna

    2014-01-01

    Assistant professor Tadeusz Tucholski Ph.D., murdered in Katyń, was one of the most outstanding representatives of the younger generation of Polish physical chemist scholars of the interwar period. He published over 30 scientific papers in the field of physical and chemical properties of explosions, kinetics and catalysis and also toxicology and forensics. Thesere searches were partly performed at the University of Poznań, in the period 1926-1939, at the Faculty of Medicine of the Department of Physics where Tucholski was employed as a senior assistant and was the closest associate of professor S. Kalandyk, partly at the Department of Forensic Medicine headed by professor S. Horoszkiewicz in the chemical-toxicological laboratory which Tucholski ranin the years 1931-1939, partly at the Warsaw University of Technology in the Department of Explosives Technology of the Faculty of Chemistry headed by professor T. Urbański, where he had been lecturing "On the latest theories of explosives" since 1937 and in 1934-35 in Cambridge, as a teaching fellow of the National Culture Fund, in Colloid Science Laboratory headed by professor E.K. Rideal. In 1903 Tucholski moved with his parents to Zabaykalye, in 1911--to Brazil. He returned to Poland in 1920, joined the Polish Army and with the 14th Polish Medium Regiment fought on the fronts of the Polish-Bolshevik War. He was drafted to the School of Pyrotechnics Foremen at Corps District Command number VII (Poznań). After graduating, Tucholski remained on active duty as a professional pyrotechnic: from 1921 to 1929 he was appointed the head of the Laboratory of Chemical and Pyrotechnic Ammunition Workshop No. 2 in Poznań and as an inspector of magazines of explosives. In 1927 he was transferred to the reserves, in 1932 after having graduated from the Officer Cadet School in Jarocin, Tucholski was appointed a second lieutenant in the Army Reserve, and later moved from the officers infantry corpsto the army ordnance corps. As part of his specialty, he constantly cooperated with the army. In the years 1937-1939,Tucholski was a technical adviser to the Ministry of Military Affairs and from August 1939--an independent researcher at the Institute of Armament Technology. He took part in the works of the Explosives Commission of the Military Technical Society. Tadeusz Tucholski was a self-taught man. He passed his A-level examsin course of his military service in October 1923 and began studying chemistry at the Faculty of Mathematics and Natural Sciences of the University of Poznań. He obtained his Master's degree in 1927, the rank and the degree of Ph.D. in the field of chemical sciences and physics in 1930. In 1936, he became the Associate Professor of physical chemistry of explosives at the Faculty of Chemistry at the University of Technology in Warsaw. Tucholski invented the method of the differential thermal analysis. He is the author of the widely used differential calorimeter which records the-processes of conversion of explosives during heating, presently known as the Differential Scanning Calorimeter.

  6. Cost as a technology driver. [in aerospace R and D

    NASA Technical Reports Server (NTRS)

    Fitzgerald, P. E., Jr.; Savage, M.

    1976-01-01

    Cost managment as a guiding factor in optimum development of technology, and proper timing of cost-saving programs in the development of a system or technology with payoffs in development and operational advances are discussed and illustrated. Advances enhancing the performance of hardware or software advances raising productivity or reducing cost, are outlined, with examples drawn from: thermochemical thrust maximization, development of cryogenic storage tanks, improvements in fuel cells for Space Shuttle, design of a spacecraft pyrotechnic initiator, cost cutting by reduction in the number of parts to be joined, and cost cutting by dramatic reductions in circuit component number with small-scale double-diffused integrated circuitry. Program-focused supporting research and technology models are devised to aid judicious timing of cost-conscious research programs.

  7. A spin-recovery parachute system for light general-aviation airplanes

    NASA Technical Reports Server (NTRS)

    Bradshaw, C.

    1980-01-01

    A tail mounted spin recovery parachute system was designed and developed for use on light general aviation airplanes. The system was designed for use on typical airplane configurations, including low wing, high wing, single engine and twin engine designs. A mechanically triggered pyrotechnic slug gun is used to forcibly deploy a pilot parachute which extracts a bag that deploys a ring slot spin recovery parachute. The total system weighs 8.2 kg. System design factors included airplane wake effects on parachute deployment, prevention of premature parachute deployment, positive parachute jettison, compact size, low weight, system reliability, and pilot and ground crew safety. Extensive ground tests were conducted to qualify the system. The recovery parachute was used successfully in flight 17 times.

  8. Galileo probe battery systems design

    NASA Technical Reports Server (NTRS)

    Dagarin, B. P.; Van Ess, J. S.; Marcoux, L. S.

    1986-01-01

    NASA's Galileo mission to Jupiter will consist of a Jovian orbiter and an atmospheric entry probe. The power for the probe will be derived from two primary power sources. The main source is composed of three Li-SO2 battery modules containing 13 D-size cell strings per module. These are required to retain capacity for 7.5 years, support a 150 day clock, and a 7 hour mission sequence of increasing loads from 0.15 to 9.5 amperes for the last 30 minutes. This main power source is supplemented by two thermal batteries (CaCrO4-Ca) for use in firing the pyrotechnic initiators during the atmospheric staging events. This paper describes design development and testing of these batteries at the system level.

  9. A smoke generator system for aerodynamic flight research

    NASA Technical Reports Server (NTRS)

    Richwine, David M.; Curry, Robert E.; Tracy, Gene V.

    1989-01-01

    A smoke generator system was developed for in-flight vortex flow studies on the F-18 high alpha research vehicle (HARV). The development process included conceptual design, a survey of existing systems, component testing, detailed design, fabrication, and functional flight testing. Housed in the forebody of the aircraft, the final system consists of multiple pyrotechnic smoke cartridges which can be fired simultaneously or in sequence. The smoke produced is ducted to desired locations on the aircraft surface. The smoke generator system (SGS) has been used successfully to identify vortex core and core breakdown locations as functions of flight condition. Although developed for a specific vehicle, this concept may be useful for other aerodynamic flight research which requires the visualization of local flows.

  10. ESTA Exit Report

    NASA Technical Reports Server (NTRS)

    Lundebjerg, Kristen

    2016-01-01

    The Energy Test System's Area (ESTA) provides test capabilities and facilities to develop, evaluate or certify hardware in support of human spaceflight. The branch has a few different technical areas including pyrotechnics, batteries, electrical systems, power systems, propulsion and fluids. I will be mainly worked in the propulsion and fluids area. The tests/activities include testing the fluid and energy conversion systems that are required for the exploration and development of space. This group includes function and vibration tests, as well as thermal and vacuum tests. I was trained and certified as an ESTA test director in order to work on tests and sub tests with my mentor as well as the rest of the ESTA team. As a test director, I had the responsibility and authority for planning, developing, safety, execution and reporting on assigned test programs.

  11. Investigation of crew restraint system biomechanics. Report for May 79-Mar 81

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

    Phillips, N.S.; Thomson, R.A.; Fiscus, I.B.

    1982-05-01

    Experimental data were collected and analyses were performed to study the influence of the dynamic mechanical properties of restraint system components on human response to impact and restraint system haulback. Tests were accomplished to isolate the characteristics of the restraint system and the human body. Three restraint webbing materials were studied at varied strain rates. A pyrotechnically powered inertia reel was tested, but could not be analytically modeled successfully. Analytical models of the human and restraint system were used to study the influence of restraint material properties changes on human response parameters. An analytical model of a rhesus monkey wasmore » also used to study the efficacy of animal tests and scaling techniques to evaluate restraint systems for human use applications.« less

  12. Plasma Properties of an Exploding Semiconductor Igniter

    NASA Astrophysics Data System (ADS)

    McGuirk, J. S.; Thomas, K. A.; Shaffer, E.; Malone, A. L.; Baginski, T.; Baginski, M. E.

    1997-11-01

    Requirements by the automotive industry for low-cost, pyrotechnic igniters for automotive airbags have led to the development of several semiconductor devices. The properties of the plasma produced by the vaporization of an exploding semiconductor are necessary in order to minimize the electrical energy requirements. This work considers two silicon-based semiconductor devices: the semiconductor bridge (SCB) and the semiconductor junction igniter both consisting of etched silicon with vapor deposited aluminum structures. Electrical current passing through the device heats a narrow junction region to the point of vaporization creating an aluminum and silicon low-temperature plasma. This work will investigate the electrical characteristics of both devices and infer the plasma properties. Furthermore optical spectral measurements will be taken of the exploding devices to estimate the temperature and density of the plasma.

  13. Ballistics Analysis of Orion Crew Module Separation Bolt Cover

    NASA Technical Reports Server (NTRS)

    Howard, Samuel A.; Konno, Kevin E.; Carney, Kelly S.; Pereira, J. Michael

    2013-01-01

    NASA is currently developing a new crew module to replace capabilities of the retired Space Shuttles and to provide a crewed vehicle for exploring beyond low earth orbit. The crew module is a capsule-type design, which is designed to separate from the launch vehicle during launch ascent once the launch vehicle fuel is expended. The separation is achieved using pyrotechnic separation bolts, wherein a section of the bolt is propelled clear of the joint at high velocity by an explosive charge. The resulting projectile must be contained within the fairing structure by a containment plate. This paper describes an analytical effort completed to augment testing of various containment plate materials and thicknesses. The results help guide the design and have potential benefit for future similar applications.

  14. Identification of an anaerobic bacterium which reduces perchlorate and chlorate as Wolinella succinogenes

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

    Wallace, W.; Attaway, H.

    1995-12-31

    Perchlorate and chlorate salts are widely used by the chemical, aerospace and defense industries as oxidizers in propellant, explosives and pyrotechnics. The authors have isolated a anaerobic bacterium which is capable of the dissimilatory reduction of both perchlorate and chlorate for energy and growth. Strain HAP-1 is a gram negative, thin rod, non-sporeforming, highly motile strict anaerobe. Antibiotic resistance profiles, utilization of carbon substrates and electron acceptors demonstrated similar physiological characteristics to Wolinella succinogenes. Pairwise comparisons of 16S RNA sequences showed only a 0.75% divergence between strain HAP-1 and W. succinogenes. Physiological, morphological and 16S RRNA sequence data indicate strainmore » HAP-1 is a subspecies of W. succinogenes that can utilize perchlorate and chlorate as terminal electron acceptors.« less

  15. Report for MaRIE Drivers Workshop on needs for energetic material's studies.

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

    Specht, Paul Elliott

    Energetic materials (i.e. explosives, propellants, and pyrotechnics) have complex mesoscale features that influence their dynamic response. Direct measurement of the complex mechanical, thermal, and chemical response of energetic materials is critical for improving computational models and enabling predictive capabilities. Many of the physical phenomena of interest in energetic materials cover time and length scales spanning several orders of magnitude. Examples include chemical interactions in the reaction zone, the distribution and evolution of temperature fields, mesoscale deformation in heterogeneous systems, and phase transitions. This is particularly true for spontaneous phenomena, like thermal cook-off. The ability for MaRIE to capture multiple lengthmore » scales and stochastic phenomena can significantly advance our understanding of energetic materials and yield more realistic, predictive models.« less

  16. KSC-2013-2344

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, Lockheed Martin crews begin uncovering the Orion ground test vehicle in the Launch Equipment Test Facility, or LETF. The GTA was moved from the Operations and Checkout Facility to the LETF for a series of pyrotechnic bolt tests. The GTA is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  17. KSC-2013-2345

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, Lockheed Martin crews uncover the Orion ground test vehicle in the Launch Equipment Test Facility, or LETF. The GTA was moved from the Operations and Checkout Facility to the LETF for a series of pyrotechnic bolt tests. The GTA is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  18. Prime Contract Awards Alphabetically by Contractor, by State or Country, and Place, FY83, Part 8 (Piros Construction Inc-Smith Russ Corp).

    DTIC Science & Technology

    1983-01-01

    44 4 J 00137 0377 Di 4 K 00137 0037 Di 4 J 00137 0075 Di TEXARKANA TEXAS 094263 7840 44 4 J 00137 0074 Di 7-83-C0103 B C E 1 2 2 2159 000 C2 MAINT...G PYROTECHNIC SPECIA 2 J JAII6 0193 NOC TEXARKANA 1EXAS 090063 7840 44 2 C JAI16 2449 NOC -83-C0108 E C E 1 2 2 Z199 000 C2 MAINT-REPAIR-ALTER...AZ1 000 C2 RDTE/OTHER RESEARCH AND DEVE 8 A 3 4 J 018 1 J 1 LOCATION TOTAL 5 1,572 RED EAGLE CONSTRUCTION CO TEXARKANA TEXAS 034886 7840 44 5 0 0CW63

  19. Space Shuttle Program (SSP) Shock Test and Specification Experience for Reusable Flight Hardware Equipment

    NASA Technical Reports Server (NTRS)

    Larsen, Curtis E.

    2012-01-01

    As commercial companies are nearing a preliminary design review level of design maturity, several companies are identifying the process for qualifying their multi-use electrical and mechanical components for various shock environments, including pyrotechnic, mortar firing, and water impact. The experience in quantifying the environments consists primarily of recommendations from Military Standard-1540, Product Verification Requirement for Launch, Upper Stage, and Space Vehicles. Therefore, the NASA Engineering and Safety Center (NESC) formed a team of NASA shock experts to share the NASA experience with qualifying hardware for the Space Shuttle Program (SSP) and other applicable programs and projects. Several team teleconferences were held to discuss past experience and to share ideas of possible methods for qualifying components for multiple missions. This document contains the information compiled from the discussions

  20. Solid Rocket Booster (SRB) Flight System Integration at Its Best

    NASA Technical Reports Server (NTRS)

    Wood, T. David; Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.

    2011-01-01

    The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads, environments and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. However, the in-flight data and postflight assessment process revealed the hardware was affected much more strongly than originally anticipated. Assembly and integration of the booster subsystems required acceptance testing of reused hardware components for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges and technical issues, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

  1. Particulate oxidative burden associated with firework activity.

    PubMed

    Godri, Krystal J; Green, David C; Fuller, Gary W; Dall'Osto, Manuel; Beddows, David C; Kelly, Frank J; Harrison, Roy M; Mudway, Ian S

    2010-11-01

    Firework events are capable of inducing particulate matter (PM) episodes that lead to exceedances of regulatory limit values. As short-term peaks in ambient PM concentration have been associated with negative impacts on respiratory and cardiovascular health, we performed a detailed study of the consequences of firework events in London on ambient air quality and PM composition. These changes were further related to the oxidative activity of daily PM samples by assessing their capacity to drive the oxidation of physiologically important lung antioxidants including ascorbate, glutathione and urate (oxidative potential, OP). Twenty-four hour ambient PM samples were collected at the Marylebone Road sampling site in Central London over a three week period, including two major festivals celebrated with pyrotechnic events: Guy Fawkes Night and Diwali. Pyrotechnic combustion events were characterized by increased gas phase pollutants levels (NO(x) and SO(2)), elevated PM mass concentrations, and trace metal concentrations (specifically Sr, Mg, K, Ba, and Pb). Relationships between NO(x), benzene, and PM(10) were used to apportion firework and traffic source fractions. A positive significant relationship was found between PM oxidative burden and individual trace metals associated with each of these apportioned source fractions. The level of exposure to each source fraction was significantly associated with the total OP. The firework contribution to PM total OP, on a unit mass basis, was greater than that associated with traffic sources: a 1 μg elevation in firework and traffic PM fraction concentration was associated with a 6.5 ± 1.5 OP(T) μg(-1) and 5.2 ± 1.4 OP(T) μg(-1) increase, respectively. In the case of glutathione depletion, firework particulate OP (3.5 ± 0.8 OP(GSH) μg(-1)) considerably exceeded that due to traffic particles (2.2 ± 0.8 OP(GSH) μg(-1)). Therefore, in light of the elevated PM concentrations caused by firework activity and the increased oxidative activity of this PM source, there is value in examining if firework derived PM is related to acute respiratory outcomes.

  2. Solid Rocket Booster (SRB) - Evolution and Lessons Learned During the Shuttle Program

    NASA Technical Reports Server (NTRS)

    Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.; Wood, T. David; Vaccaro, Mark V.

    2011-01-01

    The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Obsolescence issues occasionally required component recertification. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. Assembly and integration of the booster subsystems was a unique process and acceptance testing of reused hardware components was required for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

  3. Understanding pyrotechnic shock dynamics and response attenuation over distance

    NASA Astrophysics Data System (ADS)

    Ott, Richard J.

    Pyrotechnic shock events used during stage separation on rocket vehicles produce high amplitude short duration structural response that can lead to malfunction or degradation of electronic components, cracks and fractures in brittle materials, local plastic deformation, and can cause materials to experience accelerated fatigue life. These transient loads propagate as waves through the structural media losing energy as they travel outward from the source. This work assessed available test data in an effort to better understand attenuation characteristics associated with wave propagation and attempted to update a historical standard defined by the Martin Marietta Corporation in the late 1960's using out of date data acquisition systems. Two data sets were available for consideration. The first data set came from a test that used a flight like cylinder used in NASA's Ares I-X program, and the second from a test conducted with a flat plate. Both data sets suggested that the historical standard was not a conservative estimate of shock attenuation with distance, however, the variation in the test data did not lend to recommending an update to the standard. Beyond considering attenuation with distance an effort was made to model the flat plate configuration using finite element analysis. The available flat plate data consisted of three groups of tests, each with a unique charge density linear shape charge (LSC) used to cut an aluminum plate. The model was tuned to a representative test using the lowest charge density LSC as input. The correlated model was then used to predict the other two cases by linearly scaling the input load based on the relative difference in charge density. The resulting model predictions were then compared with available empirical data. Aside from differences in amplitude due to nonlinearities associated with scaling the charge density of the LSC, the model predictions matched the available test data reasonably well. Finally, modeling best practices were recommended when using industry standard software to predict shock response on structures. As part of the best practices documented, a frequency dependent damping schedule that can be used in model development when no data is available is provided.

  4. Burn rates of TiH2/KClO4/Viton and output testing of NASA SKD26100098-301 pressure cartridges

    NASA Technical Reports Server (NTRS)

    Holy, John A.

    1993-01-01

    The burn rates of the pyrotechnic TiH2/KClO4/Viton with a mass ratio of 30/65/5 have been measured as a function of pressure in nitrogen up to 312 MPa(45 Kpsi). The burn rates were fit to R = a pn, with a = 2.055 cm/sec/MPan and n = 0.472 between 0.15 MPa (22 psi) and 21.6 MPa (3.13 Kpsi) and a = 4.38 cm/sec/MPan and n = 0.266 between 70 MPa (10.15 Kpsi) and 312 MPa (45.25 Kpsi). The decrease in slope at the higher pressures is attributed to a diffusion limited reaction. No acoustically driven flame instabilities or large conductive-to-convective burn transitions were observed. Solid reaction products were analyzed by x-ray diffraction and scanning electron microscopy (SEM). X-ray diffraction detected only TiO2 and KC1. SEM showed that the particle size of the reaction products increased as the nitrogen pressure increased. There were no anomalous characteristics of the burn of this pyrotechnic that could be interpreted as a cause of the o-ring blow-by problem in the forward shear bolt assembly. Three NASA SKD26100098-301 pressure cartridges were fired into a fixed volume vessel that was sealed with an O-ring. A maximum pressure of 181.7 MPa(26,350 psi) was reached in around 100 ,mu sec for two shots fired into a volume of 16.3 cm3(0.996 in3). A maximum pressure of 33,460 psi was reached for one shot fired into a volume of 9.55 cm3(0.583 in3). The O-ring burned through on one shot in the larger volume and leaked on the other two thereby simulating the effects of an O-ring leak. The results imply that the piston in the shear bolt assembly would receive a large impulse even if there was a leak in an O-ring seal.

  5. MARS PATHFINDER PYRO SYSTEMS SWITCHING ACTIVITY

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The Mars Pathfinder lander is subjected to a electrical and functional tests of its pyrotechic petal deployer system by Jet Propulsion Laboratory (JPL) engineers and technicians in KSC's Spacecraft Assembly and Encapsulation Facility (SAEF-2). In the background is the Pathfinder cruise stage, which the lander will be mated to once its functional tests are complete. The lander will remain attached to this stage during its six-to-seven-month journey to Mars. When the lander touches down on the surface of Mars next year, the pyrotechnic system will deploy its three petals open like a flower and allow the Sojourner autonomous rover to explore the Martian surface. The Mars Pathfinder is scheduled for launch aboard a Delta II expendable launch vehicle on Dec. 2, the beginning of a 24-day launch period. JPL is managing the Mars Pathfinder project for NASA.

  6. Outer planet entry probe system study. Volume 4: Common Saturn/Uranus probe studies

    NASA Technical Reports Server (NTRS)

    1973-01-01

    Results are summarized of a common scientific probe study to explore the atmospheres of Saturn and Uranus. This was a three-month follow-on effort to the Outer Planet Entry Probe System study. The report presents: (1) a summary, conclusions and recommendations of this study, (2) parametric analysis conducted to support the two system definitions, (3) common Saturn/Uranus probe system definition using the Science Advisory Group's exploratory payload and, (4) common Saturn/Uranus probe system definition using an expanded science complement. Each of the probe system definitions consists of detailed discussions of the mission, science, system and subsystems including telecommunications, data handling, power, pyrotechnics, attitude control, structures, propulsion, thermal control and probe-to-spacecraft integration. References are made to the contents of the first three volumes where it is feasible to do so.

  7. Practical aspects of instrumentation system installation, volume 13

    NASA Technical Reports Server (NTRS)

    Borek, R. W.; Pool, A. (Editor); Sanderson, K. C. (Editor)

    1981-01-01

    A review of factors influencing installation of aircraft flight test instrumentation is presented. Requirements, including such factors as environment, reliability, maintainability, and system safety are discussed. The assessment of the mission profile is followed by an overview of electrical and mechanical installation factors with emphasis on shock/vibration isolation systems and standardization of the electric wiring installation, two factors often overlooked by instrumentation engineers. A discussion of installation hardware reviews the performance capabilities of wiring, connectors, fuses and circuit breakers, and a guide to proper selections is provided. The discussion of the installation is primarily concerned with the electrical wire routing, shield terminations and grounding. Also inclued are some examples of installation mistakes that could affect system accuracy. System verification procedures and special considerations such as sneak circuits, pyrotechnics, aircraft antenna patterns, and lightning strikes are discussed.

  8. KSC-2013-2342

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, into the Launch Equipment Test Facility, or LETF, from the Operations and Checkout Building. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  9. KSC-2013-2340

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers prepare to move the Orion ground test vehicle, or GTA, from the Operations and Checkout Building to the Launch Equipment Test Facility, or LETF. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  10. KSC-2013-2341

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, from the Operations and Checkout Building to the Launch Equipment Test Facility, or LETF. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  11. KSC-2013-2343

    NASA Image and Video Library

    2013-05-13

    CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, into the Launch Equipment Test Facility, or LETF, from the Operations and Checkout Building. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

  12. Apparatus for simultaneously disreefing a centrally reefed clustered parachute system

    DOEpatents

    Johnson, Donald W.

    1988-01-01

    A single multi-line cutter is connected to each of a cluster of parachutes by a separate short tether line that holds the parachutes, initially reefed by closed loop reefing lines, close to one another. The closed loop reefing lines and tether lines, one from each parachute, are disposed within the cutter to be simultaneously cut by its actuation when a central line attached between the payload and the cutter is stretched upon deployment of the cluster. A pyrotechnic or electronic time delay may be included in the cutter to delay the actual simultaneous cutting of all lines until the clustered parachutes attain a measure of stability prior to being disreefed. A second set of reefing lines and second tether lines may be provided for each parachute, to enable a two-stage, separately timed, step-by-step disreefing.

  13. Apparatus for simultaneously disreefing a centrally reefed clustered parachute system

    DOEpatents

    Johnson, D.W.

    1988-06-21

    A single multi-line cutter is connected to each of a cluster of parachutes by a separate short tether line that holds the parachutes, initially reefed by closed loop reefing lines, close to one another. The closed loop reefing lines and tether lines, one from each parachute, are disposed within the cutter to be simultaneously cut by its actuation when a central line attached between the payload and the cutter is stretched upon deployment of the cluster. A pyrotechnic or electronic time delay may be included in the cutter to delay the actual simultaneous cutting of all lines until the clustered parachutes attain a measure of stability prior to being disreefed. A second set of reefing lines and second tether lines may be provided for each parachute, to enable a two-stage, separately timed, step-by-step disreefing. 13 figs.

  14. Centaur Standard Shroud (CSS) cryogenic unlatch tests

    NASA Technical Reports Server (NTRS)

    1973-01-01

    Cryogenic tanking and partial jettison (unlatch) tests were performed on a full scale Centaur vehicle and Centaur Standard Shroud (CSS) to develop and qualify the CSS insulation system, the CSS and Centaur ground-hold purge systems, and the Centaur hydrogen tank flight vent system. Operation of the shroud/Centaur pyrotechnic systems, seals, and the shroud jettison springs, hinges, and other separation systems was demonstrated by a partial jettison of the shroud into catch nets. The Centaur tanks were filled with liquid hydrogen and liquid nitrogen. Prelaunch operations were performed, and data taken to establish system performances. Results from the initial tests showed a higher than expected heat transfer rate to the Centaur hydrogen tank. In addition, the release mechanism for the forward seal between the Centaur and the CSS did not function properly, and the seal was torn during jettison of the shroud.

  15. Energy Systems Test Area (ESTA) Pyrotechnic Operations: User Test Planning Guide

    NASA Technical Reports Server (NTRS)

    Hacker, Scott

    2012-01-01

    The Johnson Space Center (JSC) has created and refined innovative analysis, design, development, and testing techniques that have been demonstrated in all phases of spaceflight. JSC is uniquely positioned to apply this expertise to components, systems, and vehicles that operate in remote or harsh environments. We offer a highly skilled workforce, unique facilities, flexible project management, and a proven management system. The purpose of this guide is to acquaint Test Requesters with the requirements for test, analysis, or simulation services at JSC. The guide includes facility services and capabilities, inputs required by the facility, major milestones, a roadmap of the facility s process, and roles and responsibilities of the facility and the requester. Samples of deliverables, facility interfaces, and inputs necessary to define the cost and schedule are included as appendices to the guide.

  16. Four channel Laser Firing Unit using laser diodes

    NASA Technical Reports Server (NTRS)

    Rosner, David, Sr.; Spomer, Edwin, Sr.

    1994-01-01

    This paper describes the accomplishments and status of PS/EDD's (Pacific Scientific/Energy Dynamics Division) internal research and development effort to prototype and demonstrate a practical four channel laser firing unit (LFU) that uses laser diodes to initiate pyrotechnic events. The LFU individually initiates four ordnance devices using the energy from four diode lasers carried over the fiber optics. The LFU demonstrates end-to-end optical built in test (BIT) capabilities. Both Single Fiber Reflective BIT and Dual Fiber Reflective BIT approaches are discussed and reflection loss data is presented. This paper includes detailed discussions of the advantages and disadvantages of both BIT approaches, all-fire and no-fire levels, and BIT detection levels. The following topics are also addressed: electronic control and BIT circuits, fiber optic sizing and distribution, and an electromechanical shutter type safe/arm device. This paper shows the viability of laser diode initiation systems and single fiber BIT for typing military applications.

  17. KSC-2013-3008

    NASA Image and Video Library

    2013-05-14

    CAPE CANAVERAL, Fla. -- Inside the Launch Equipment Test Facility at NASA’s Kennedy Space in Florida, a second firing of the escape hold down post has occurred during a pyrotechnic bolt test on the Orion ground test vehicle. Lockheed Martin performed tests over a series of days on the explosive bolts that separate Orion from the launch abort system. Data was collected on the effect of shock waves on Orion during the explosive bolt separation. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Jim Grossmann

  18. Method of making an integral window hermetic fiber optic component

    DOEpatents

    Dalton, R.D.; Kramer, D.P.; Massey, R.T.; Waker, D.A.

    1996-11-12

    In the fabrication of igniters, actuators, detonators, and other pyrotechnic devices to be activated by a laser beam, an integral optical glass window is formed by placing a preform in the structural member of the device and then melting the glass and sealing it in place by heating at a temperature between the ceramming temperature of the glass and the melting point of the metal, followed by rapid furnace cooling to avoid devitrification. No other sealing material is needed to achieve hermeticity. A preferred embodiment of this type of device is fabricated by allowing the molten glass to flow further and form a plano-convex lens integral with and at the bottom of the window. The lens functions to decrease the beam divergence caused by refraction of the laser light passing through the window when the device is fired by means of a laser beam. 9 figs.

  19. Method of making an integral window hermetic fiber optic component

    DOEpatents

    Dalton, Rick D.; Kramer, Daniel P.; Massey, Richard T.; Waker, Damon A.

    1996-11-12

    In the fabrication of igniters, actuators, detonators, and other pyrotechnic devices to be activated by a laser beam, an integral optical glass window is formed by placing a preform in the structural member of the device and then melting the glass and sealing it in place by heating at a temperature between the ceramming temperature of the glass and the melting point of the metal, followed by rapid furnace cooling to avoid devitrification. No other sealing material is needed to achieve hermeticity. A preferred embodiment of this type of device is fabricated by allowing the molten glass to flow further and form a plano-convex lens integral with and at the bottom of the window. The lens functions to decrease the beam divergence caused by refraction of the laser light passing through the window when the device is fired by means of a laser beam.

  20. Impact of the volume of rooms on shock wave propagation within a multi-chamber system

    NASA Astrophysics Data System (ADS)

    Julien, B.; Sochet, I.; Vaillant, T.

    2016-03-01

    The behavior of a shock wave generated by a hemispherical gaseous charge and propagating within a confined multi-chamber system is analyzed through the evolution of some of the shock parameters (maximum overpressure and positive impulse). The influence of a variation in the volume of the rooms on the pressure history inside the building is also studied. Several small-scale experiments have been carried out using an adjustable model representative of a pyrotechnic workshop. The experimental results show that the pressure histories are very complex. Yet, using a global approach, we were able to link the evolution of the arrival time of the shock wave within the building with the reference obtained in the free field. New parameters were developed to best fit the experimental maximal overpressure in the cells and in the corridor leading to two predictive laws used to estimate the maximal overpressure in the model.

  1. Shuttle Ground Support Equipment (GSE) T-0 Umbilical to Space Shuttle Program (SSP) Flight Elements Consultation

    NASA Technical Reports Server (NTRS)

    Wilson, Timmy R.; Kichak, Robert A.; McManamen, John P.; Kramer-White, Julie; Raju, Ivatury S.; Beil, Robert J.; Weeks, John F.; Elliott, Kenny B.

    2009-01-01

    The NASA Engineering and Safety Center (NESC) was tasked with assessing the validity of an alternate opinion that surfaced during the investigation of recurrent failures at the Space Shuttle T-0 umbilical interface. The most visible problem occurred during the Space Transportation System (STS)-112 launch when pyrotechnics used to separate Solid Rocket Booster (SRB) Hold-Down Post (HDP) frangible nuts failed to fire. Subsequent investigations recommended several improvements to the Ground Support Equipment (GSE) and processing changes were implemented, including replacement of ground-half cables and connectors between flights, along with wiring modifications to make critical circuits quad-redundant across the interface. The alternate opinions maintained that insufficient data existed to exonerate the design, that additional data needed to be gathered under launch conditions, and that the interface should be further modified to ensure additional margin existed to preclude failure. The results of the assessment are contained in this report.

  2. Shock wave propagation within a confined multi-chamber system

    NASA Astrophysics Data System (ADS)

    Julien, B.; Sochet, I.; Tadini, P.; Vaillant, T.

    2018-07-01

    The influence of a variation of the opening ratios of rooms and side walls on the propagation of a shock wave within a confined multi-chamber system is analyzed through the evolution of some of the shock parameters (maximum overpressure and positive impulse). The shock wave is generated by the detonation of a hemispherical gaseous charge in one of the rooms. Several small-scale experiments have been carried out using an adjustable model representative of a pyrotechnic workshop. Using the same approach as for a previous article dealing with the impact of the volume of the rooms, we were able to link the evolution of the arrival time of the shock wave within the building with the reference obtained in the free field. Moreover, using a new parameter taking into account the opening ratios of the rooms and side walls, a predictive law was developed to model the maximal overpressure in the rooms.

  3. The challenge of improvised explosives

    DOE PAGES

    Maienschein, Jon L.

    2012-06-14

    Energetic materials have been developed for decades, and indeed centuries, with a common set of goals in mind. Performance (as a detonating explosive, a propellant, or a pyrotechnic) has always been key, equally important have been the attributes of safety, stability, and reproducibility. Research and development with those goals has led to the set of energetic materials commonly used today. In the past few decades, the adoption and use of improvised explosives in attacks by terrorists or third-world parties has led to many questions about these materials, e.g., how they may be made, what threat they pose to the intendedmore » target, how to handle them safely, and how to detect them. The unfortunate advent of improvised explosives has opened the door for research into these materials, and there are active programs in many countries. I will discuss issues and opportunities facing research into improvised explosives.« less

  4. Buckybomb: Reactive Molecular Dynamics Simulation

    DOE PAGES

    Chaban, Vitaly V.; Fileti, Eudes Eterno; Prezhdo, Oleg V.

    2015-02-24

    Energetic materials, such as explosives, propellants, and pyrotechnics, are widely used in civilian and military applications. Nanoscale explosives represent a special group because of the high density of energetic covalent bonds. The reactive molecular dynamics (ReaxFF) study of nitrofullerene decomposition reported here provides a detailed chemical mechanism of explosion of a nanoscale carbon material. Upon initial heating, C 60(NO 2) 12 disintegrates, increasing temperature and pressure by thousands of Kelvins and bars within tens of picoseconds. The explosion starts with NO 2 group isomerization into C-O-N-O, followed by emission of NO molecules and formation of CO groups on the buckyballmore » surface. NO oxidizes into NO 2, and C 60 falls apart, liberating CO 2. At the highest temperatures, CO 2 gives rise to diatomic carbon. Lastly, the study shows that the initiation temperature and released energy depend strongly on the chemical composition and density of the material.« less

  5. Shock sensing dual mode warhead

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

    Shamblen, M.; Walchak, M.T.; Richmond, L.

    1980-12-31

    A shock sensing dual mode warhead is provided for use against both soft and hard targets and is capable of sensing which type of target has been struck. The warhead comprises a casing made of a ductile material containing an explosive charge and a fuze assembly. The ductile warhead casing will mushroom upon striking a hard target while still confining the explosive. Proper ductility and confinement are necessary for fuze shock sensing. The fuze assembly contains a pair of parallel firing trains, one initiated only by dynamic pressure caused high impact deceleration and one initiated by low impact deceleration. Themore » firing train actuated by high impact deceleration senses dynamic pressure transmitted, during deformation of the warhead, through the explosive filler which is employed as a fuzing signature. The firing train actuated by low impact deceleration contains a pyrotechnic delay to allow penetration of soft targets.« less

  6. A midsummer-night's shock wave

    NASA Astrophysics Data System (ADS)

    Hargather, Michael; Liebner, Thomas; Settles, Gary

    2007-11-01

    The aerial pyrotechnic shells used in professional display fireworks explode a bursting charge at altitude in order to disperse the ``stars'' of the display. The shock wave from the bursting charge is heard on the ground as a loud report, though it has by then typically decayed to a mere sound wave. However, viewers seated near the standard safety borders can still be subjected to weak shock waves. These have been visualized using a large, portable, retro-reflective ``Edgerton'' shadowgraph technique and a high-speed digital video camera. Images recorded at 10,000 frames per second show essentially-planar shock waves from 10- and 15-cm firework shells impinging on viewers during the 2007 Central Pennsylvania July 4th Festival. The shock speed is not measurably above Mach 1, but we nonetheless conclude that, if one can sense a shock-like overpressure, then the wave motion is strong enough to be observed by density-sensitive optics.

  7. The longstanding challenge of the nanocrystallization of 1,3,5-trinitroperhydro-1,3,5-triazine (RDX)

    PubMed Central

    Spitzer, Denis

    2017-01-01

    Research efforts for realizing safer and higher performance energetic materials are continuing unabated all over the globe. While the thermites – pyrotechnic compositions of an oxide and a metal – have been finely tailored thanks to progress in other sectors, organic high explosives are still stagnating. The most symptomatic example is the longstanding challenge of the nanocrystallization of 1,3,5-trinitroperhydro-1,3,5-triazine (RDX). Recent advances in crystallization processes and milling technology mark the beginning of a new area which will hopefully lead the pyroelectric industry to finally embrace nanotechnology. This work reviews the previous and current techniques used to crystallize RDX at a submicrometer scale or smaller. Several key points are highlighted then discussed, such as the smallest particle size and its morphology, and the scale-up capacity and the versatility of the process. PMID:28326236

  8. Emergency in-flight egress opening for general aviation aircraft

    NASA Technical Reports Server (NTRS)

    Bement, L. J.

    1980-01-01

    In support of a stall/spin research program, an emergency in-flight egress system is being installed in a light general aviation airplane. To avoid a major structural redesign for a mechanical door, an add-on 11.2 kg pyrotechnic-actuated system was developed to create an opening in the existing structure. The airplane skin will be explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel will be jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mock-ups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics.

  9. Hydrodynamic simulations of microjetting from shock-loaded grooves

    NASA Astrophysics Data System (ADS)

    Roland, C.; de Rességuier, T.; Sollier, A.; Lescoute, E.; Soulard, L.; Loison, D.

    2017-01-01

    The interaction of a shock wave with a free surface which has geometrical defects, such as cavities or grooves, may lead to the ejection of micrometric debris at velocities of km/s. This process can be involved in many applications, like pyrotechnics or industrial safety. Recent laser shock experiments reported elsewhere in this conference have provided some insight into jet formation as well as jet tip velocities for various groove angles and shock pressures. Here, we present hydrodynamic simulations of these experiments, in both 2D and 3D geometries, using both finite element method and smoothed particle hydrodynamics. Numerical results are compared to several theoretical predictions including the Richtmyer-Meshkov instabilities. The role of the elastic-plastic behavior on jet formation is illustrated. Finally, the possibility to simulate the late stage of jet expansion and fragmentation is explored, to evaluate the mass distribution of the ejecta and their ballistic properties, still essentially unknown in the experiments.

  10. Outer planet entry probe system study. Volume 2: Supporting technical studies

    NASA Technical Reports Server (NTRS)

    1972-01-01

    The environment, science investigations, and general mission analysis considerations are given first. These data are followed by discussions of the studies pertaining to the planets Jupiter, Saturn, Uranus, and Neptune. Except for Neptune, each planet discussion is divided into two parts: (1) parametric activities and (2) probe definition for that planet, or the application of a given probe for that planet. The Neptune discussion is limited to parametrics in the area of science and mission analysis. Each of the probe system definitions consists of system and subsystem details including telecommunications, data handling, power pyrotechnics, attitude control, structures, propulsion, thermal control, and probe to spacecraft integration. The first configuration is discussed in detail and the subsequent configuration discussions are limited to the differences. Finally, the hardware availability to support a probe system and commonality of science, missions, and subsystems for use at the various planets are considered.

  11. Thermoplasmonic Ignition of Metal Nanoparticles.

    PubMed

    Mutlu, Mehmet; Kang, Ju-Hyung; Raza, Søren; Schoen, David; Zheng, Xiaolin; Kik, Pieter G; Brongersma, Mark L

    2018-03-14

    Explosives, propellants, and pyrotechnics are energetic materials that can store and quickly release tremendous amounts of chemical energy. Aluminum (Al) is a particularly important fuel in many applications because of its high energy density, which can be released in a highly exothermic oxidation process. The diffusive oxidation mechanism (DOM) and melt-dispersion mechanism (MDM) explain the ways powders of Al nanoparticles (NPs) can burn, but little is known about the possible use of plasmonic resonances in NPs to manipulate photoignition. This is complicated by the inhomogeneous nature of powders and very fast heating and burning rates. Here, we generate Al NPs with well-defined sizes, shapes, and spacings by electron beam lithography and demonstrate that their plasmonic resonances can be exploited to heat and ignite them with a laser. By combining simulations with thermal-emission, electron-, and optical-microscopy studies, we reveal how an improved control over NP ignition can be attained.

  12. Supplier's Status for Critical Solid Propellants, Explosive, and Pyrotechnic Ingredients

    NASA Technical Reports Server (NTRS)

    Sims, B. L.; Painter, C. R.; Nauflett, G. W.; Cramer, R. J.; Mulder, E. J.

    2000-01-01

    In the early 1970's a program was initiated at the Naval Surface Warfare Center/Indian Head Division (NSWC/IHDIV) to address the well-known problems associated with availability and suppliers of critical ingredients. These critical ingredients are necessary for preparation of solid propellants and explosives manufactured by the Navy. The objective of the program was to identify primary and secondary (or back-up) vendor information for these critical ingredients, and to develop suitable alternative materials if an ingredient is unavailable. In 1992 NSWC/IHDIV funded Chemical Propulsion Information Agency (CPIA) under a Technical Area Task (TAT) to expedite the task of creating a database listing critical ingredients used to manufacture Navy propellant and explosives based on known formulation quantities. Under this task CPIA provided employees that were 100 percent dedicated to the task of obtaining critical ingredient suppliers information, selecting the software and designing the interface between the computer program and the database users. TAT objectives included creating the Explosive Ingredients Source Database (EISD) for Propellant, Explosive and Pyrotechnic (PEP) critical elements. The goal was to create a readily accessible database, to provide users a quick-view summary of critical ingredient supplier's information and create a centralized archive that CPIA would update and distribute. EISD funding ended in 1996. At that time, the database entries included 53 formulations and 108 critical used to manufacture Navy propellant and explosives. CPIA turned the database tasking back over to NSWC/IHDIV to maintain and distribute at their discretion. Due to significant interest in propellant/explosives critical ingredients suppliers' status, the Propellant Development and Characterization Subcommittee (PDCS) approached the JANNAF Executive committee (EC) for authorization to continue the critical ingredient database work. In 1999, JANNAF EC approved the PDCS panel task. This paper is designed to emphasize the necessity of maintaining a JANNAF community supported database, which monitors PEP critical ingredient suppliers' status. The final product of this task is a user friendly, searchable database that provides a quick-view summary of critical ingredient supplier's information. This database must be designed to serve the needs of JANNAF and the propellant and energetic commercial manufacturing community as well. This paper provides a summary of the type of information to archive each critical ingredient.

  13. Command Interface ASIC - Analog Interface ASIC Chip Set

    NASA Technical Reports Server (NTRS)

    Ruiz, Baldes; Jaffe, Burton; Burke, Gary; Lung, Gerald; Pixler, Gregory; Plummer, Joe; Katanyoutanant,, Sunant; Whitaker, William

    2003-01-01

    A command interface application-specific integrated circuit (ASIC) and an analog interface ASIC have been developed as a chip set for remote actuation and monitoring of a collection of switches, which can be used to control generic loads, pyrotechnic devices, and valves in a high-radiation environment. The command interface ASIC (CIA) can be used alone or in combination with the analog interface ASIC (AIA). Designed primarily for incorporation into spacecraft control systems, they are also suitable for use in high-radiation terrestrial environments (e.g., in nuclear power plants and facilities that process radioactive materials). The primary role of the CIA within a spacecraft or other power system is to provide a reconfigurable means of regulating the power bus, actuating all valves, firing all pyrotechnic devices, and controlling the switching of power to all switchable loads. The CIA is a mixed-signal (analog and digital) ASIC that includes an embedded microcontroller with supporting fault-tolerant switch control and monitoring circuitry that is capable of connecting to a redundant set of interintegrated circuit (I(sup 2)C) buses. Commands and telemetry requests are communicated to the CIA. Adherence to the I(sup 2)C bus standard helps to reduce development costs by facilitating the use of previously developed, commercially available components. The AIA is a mixed-signal ASIC that includes the analog circuitry needed to connect the CIA to a custom higher powered version of the I(sup 2)C bus. The higher-powered version is designed to enable operation with bus cables longer than those contemplated in the I(sup 2)C standard. If there are multiple higher-power I(sup 2)C-like buses, then there must an AIA between the CIA and each such bus. The AIA includes two identical interface blocks: one for the side-A I(sup 2)C clock and data buses and the other for the side B buses. All the AIAs on each side are powered from a common power converter module (PCM). Sides A and B of the I(sup 2)C buses are electrically isolated from each other (see figure). They are also isolated from the CIA by use of transformer coupling of signals between the AIA blocks and the CIA.

  14. Uncontrolled re-entry of satellite parts after finishing their mission in LEO: Titanium alloy degradation by thermite reaction energy

    NASA Astrophysics Data System (ADS)

    Monogarov, K. A.; Pivkina, A. N.; Grishin, L. I.; Frolov, Yu. V.; Dilhan, D.

    2017-06-01

    Analytical and experimental studies conducted at Semenov Institute of Chemical Physics for investigating the use of pyrotechnic compositions, i.e., thermites, to reduce the risk of the fall of thermally stable parts of deorbiting end-of-life LEO satellites on the Earth are described. The main idea was the use of passive heating during uncontrolled re-entry to ignite thermite composition, fixed on the titanium surface, with the subsequent combustion energy release to be sufficient to perforate the titanium cover. It is supposed, that thus destructed satellite parts will lose their streamline shape, and will burn out being aerodynamically heated during further descending in atmosphere (patent FR2975080). On the base of thermodynamic calculations the most promising thermite compositions have been selected for the experimental phase. The unique test facilities have been developed for the testing of the efficiency of thermite charges to perforate the titanium TA6V cover of 0.8 mm thickness under temperature/pressure conditions duplicated the uncontrolled re-entry of titanium tank after its mission on LEO. Experiments with the programmed laser heating inside the vacuum chamber revealed the only efficient thermite composition among preliminary selected ones to be Al/Co3O4. Experimental searching of the optimal aluminum powder between spherical and flaked nano- and micron-sized ones revealed the possibility to adjust the necessary ignition delay time, according to the titanium cover temperature dependency on deorbiting time. For the titanium tank the maximum temperature is 1100 °C at altitude 68 km and pressure 60 Pa. Under these conditions Al/Co3O4 formulations with nano-Al spherical particles provide the ignition time to be 13.3 s, and ignition temperature as low as 592±5 °C, whereas compositions with the micron-sized spherical Al powder reveal these values to be much higher, i.e., 26.3 s and 869±5 °C, respectively. The analytical and experimental studies described in this paper provide a portion of the basic information required for the development of pyrotechnic device to reduce the risk of the fall of thermally stable parts of deorbiting end-of-life LEO satellites on the Earth.

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

    NASA Technical Reports Server (NTRS)

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

    2009-01-01

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

  16. Microjetting from grooved surfaces in metallic samples subjected to laser driven shocks

    NASA Astrophysics Data System (ADS)

    de Rességuier, T.; Lescoute, E.; Sollier, A.; Prudhomme, G.; Mercier, P.

    2014-01-01

    When a shock wave propagating in a solid sample reflects from a free surface, geometrical effects predominantly governed by the roughness and defects of that surface may lead to the ejection of tiny jets that may breakup into high velocity, approximately micrometer-size fragments. This process referred to as microjetting is a major safety issue for engineering applications such as pyrotechnics or armour design. Thus, it has been widely studied both experimentally, under explosive and impact loading, and theoretically. In this paper, microjetting is investigated in the specific loading conditions associated to laser shocks: very short duration of pressure application, very high strain rates, small spatial scales. Material ejection from triangular grooves in the free surface of various metallic samples is studied by combining transverse optical shadowgraphy and time-resolved velocity measurements. The influences of the main parameters (groove angle, shock pressure, nature of the metal) on jet formation and ejection velocity are quantified, and the results are compared to theoretical estimates.

  17. Ignition sensitivity study of an energetic train configuration using experiments and simulation

    NASA Astrophysics Data System (ADS)

    Kim, Bohoon; Yu, Hyeonju; Yoh, Jack J.

    2018-06-01

    A full scale hydrodynamic simulation intended for the accurate description of shock-induced detonation transition was conducted as a part of an ignition sensitivity analysis of an energetic component system. The system is composed of an exploding foil initiator (EFI), a donor explosive unit, a stainless steel gap, and an acceptor explosive. A series of velocity interferometer system for any reflector measurements were used to validate the hydrodynamic simulations based on the reactive flow model that describes the initiation of energetic materials arranged in a train configuration. A numerical methodology with ignition and growth mechanisms for tracking multi-material boundary interactions as well as severely transient fluid-structure coupling between high explosive charges and metal gap is described. The free surface velocity measurement is used to evaluate the sensitivity of energetic components that are subjected to strong pressure waves. Then, the full scale hydrodynamic simulation is performed on the flyer impacted initiation of an EFI driven pyrotechnical system.

  18. Galileo spacecraft power management and distribution system

    NASA Technical Reports Server (NTRS)

    Detwiler, R. C.; Smith, R. L.

    1990-01-01

    The Galileo PMAD (power management and distribution system) is described, and the design drivers that established the final as-built hardware are discussed. The spacecraft is powered by two general-purpose heat-source-radioisotope thermoelectric generators. Power bus regulation is provided by a shunt regulator. Galileo PMAD distributes a 570-W beginning of mission (BOM) power source to a user complement of some 137 load elements. Extensive use of pyrotechnics requires two pyro switching subassemblies. They initiate 148 squibs which operate the 47 pyro devices on the spacecraft. Detection and correction of faults in the Galileo PMAD is an autonomous feature dictated by requirements for long life and reliability in the absence of ground-based support. Volatile computer memories in the spacecraft command and data system and attitude control system require a continuous source of backup power during all anticipated power bus fault scenarios. Power for the Jupiter Probe is conditioned, isolated, and controlled by a Probe interface subassembly. Flight performance of the spacecraft and the PMAD has been successful to date, with no major anomalies.

  19. Pyrotechnic hazards classification and evaluation program. Electrostatic vulnerability of the E8 and XM15/XM165 clusters, phase 2

    NASA Technical Reports Server (NTRS)

    1971-01-01

    An investigation into the electrostatic phenomena associated with the manufacturing and handling of explosives is discussed. The testing includes measurement of the severity of the primary charge generation mechanism, triboelectric effects between dissimilar surfaces; refinement of equivalent circuits of the XM15/XM165 and E8 fuse trains; evaluation of the electrostatic spark discharge characteristics predicted by an equivalent circuit analysis; and determination of the spark ignition sensitivity of materials, components, junctions, and subassemblies which compose the XM15/XM165 and E8 units. Special studies were also performed. These special tests included ignition sensitivity of the complete XM15 fuse train when subjected to discharges through its entire length, measurement of electrostatic potentials which occur during the E8 foaming operation during fabrication, and investigation of the inadvertent functioning of an XM15 cluster during manufacturing. The test results are discussed and related to the effectiveness of suggested modification to reduce the electrostatic ignition sensitivity.

  20. A study of an advanced confined linear energy source

    NASA Technical Reports Server (NTRS)

    Anderson, M. C.; Heidemann, W. B.

    1971-01-01

    A literature survey and a test program to develop and evaluate an advanced confined linear energy source were conducted. The advanced confined linear energy source is an explosive or pyrotechnic X-Cord (mild detonating fuse) supported inside a confining tube capable of being hermetically sealed and retaining all products of combustion. The energy released by initiation of the X-Cord is transmitted through the support material to the walls of the confining tube causing an appreciable change in cross sectional configuration and expansion of the tube. When located in an assembly that can accept and use the energy of the tube expansion, useful work is accomplished through fracture of a structure, movement of a load, reposition of a pin, release of a restraint, or similar action. The tube assembly imparts that energy without release of debris or gases from the device itself. This facet of the function is important to the protection of men or equipment located in close proximity to the system during the time of function.

  1. Hyper-X Stage Separation Trajectory Validation Studies

    NASA Technical Reports Server (NTRS)

    Tartabini, Paul V.; Bose, David M.; McMinn, John D.; Martin, John G.; Strovers, Brian K.

    2003-01-01

    An independent twelve degree-of-freedom simulation of the X-43A separation trajectory was created with the Program to Optimize Simulated trajectories (POST II). This simulation modeled the multi-body dynamics of the X-43A and its booster and included the effect of two pyrotechnically actuated pistons used to push the vehicles apart as well as aerodynamic interaction forces and moments between the two vehicles. The simulation was developed to validate trajectory studies conducted with a 14 degree-of-freedom simulation created early in the program using the Automatic Dynamic Analysis of Mechanics Systems (ADAMS) simulation software. The POST simulation was less detailed than the official ADAMS-based simulation used by the Project, but was simpler, more concise and ran faster, while providing similar results. The increase in speed provided by the POST simulation provided the Project with an alternate analysis tool. This tool was ideal for performing separation control logic trade studies that required the running of numerous Monte Carlo trajectories.

  2. Open-systems architecture of a standardized command interface chip-set for switching and control of a spacecraft power bus

    NASA Technical Reports Server (NTRS)

    Ruiz, Ian B.; Burke, Gary R.; Lung, Gerald; Whitaker, William D.; Nowicki, Robert M.

    2004-01-01

    The Jet Propulsion Laboratory (JPL) has developed a command interface chip-set that primarily consists of two mixed-signal ASICs'; the Command Interface ASIC (CIA) and Analog Interface ASIC (AIA). The Open-systems architecture employed during the design of this chip-set enables its use as both an intelligent gateway between the system's flight computer and the control, actuation, and activation of the spacecraft's loads, valves, and pyrotechnics respectfully as well as the regulator of the spacecraft power bus. Furthermore, the architecture is highly adaptable and employed fault-tolerant design methods enabling a host of other mission uses including reliable remote data collection. The objective of this design is to both provide a needed flight component that meets the stringent environmental requirements of current deep space missions and to add a new element to a growing library that can be used as a standard building block for future missions to the outer planets.

  3. The faulty Master Events Controller is removed from STS-99 Endeavour

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Technicians remove a faulty Enhanced Main Events Controller (E- MEC) from Shuttle Endeavour at Launch Pad 39A. The E-MEC became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  4. The faulty Master Events Controller is carried away from STS-99 Endeavour

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Workers carry away the faulty Enhanced Main Events Controller (E- MEC) from Shuttle Endeavour at Launch Pad 39A. The E-MEC became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  5. Continuous Improvement in Battery Testing at the NASA/JSC Energy System Test Area

    NASA Technical Reports Server (NTRS)

    Boyd, William; Cook, Joseph

    2003-01-01

    The Energy Systems Test Area (ESTA) at the Lyndon B. Johnson Space Center in Houston, Texas conducts development and qualification tests to fulfill Energy System Division responsibilities relevant to ASA programs and projects. EST A has historically called upon a variety of fluid, mechanical, electrical, environmental, and data system capabilities spread amongst five full-service facilities to test human and human supported spacecraft in the areas of propulsion systems, fluid systems, pyrotechnics, power generation, and power distribution and control systems. Improvements at ESTA are being made in full earnest of offering NASA project offices an option to choose a thorough test regime that is balanced with cost and schedule constraints. In order to continue testing of enabling power-related technologies utilized by the Energy System Division, an especially proactive effort has been made to increase the cost effectiveness and schedule responsiveness for battery testing. This paper describes the continuous improvement in battery testing at the Energy Systems Test Area being made through consolidation, streamlining, and standardization.

  6. Spacecraft on-orbit deployment anomalies - What can be done?

    NASA Astrophysics Data System (ADS)

    Freeman, Michael T.

    1993-04-01

    Modern communications satellites rely heavily upon deployable appendage (i.e. solar arrays, communications antennas, etc.) to perform vital functions that enable the spacecraft to effectively conduct mission objectives. Communications and telemetry antennas provide the radiofrequency link between the spacecraft and the earth ground station, permitting data to be transmitted and received from the satellite. Solar arrays serve as the principle source of electrical energy to the satellite, and recharge internal batteries during operation. However, since satellites cannot carry backup systems, if a solar array fails to deploy, the mission is lost. This article examines the subject of on-orbit anomalies related to the deployment of spacecraft appendage, and possible causes of such failures. Topics discussed shall include mechanical launch loading, on-orbit thermal and solar concerns, reliability of spacecraft pyrotechnics, and practical limitations of ground-based deployment testing. Of particular significance, the article will feature an in-depth look at the lessons learned from the successful recovery of the Telesat Canada Anik-E2 satellite in 1991.

  7. On-orbit deployment anamolies: What can be done?

    NASA Technical Reports Server (NTRS)

    Freeman, Michael

    1992-01-01

    Modern communications satellites rely heavily upon deployable appendage (i.e., solar arrays, communications antennas, etc.) to perform vital functions that enable the spacecraft to effectively conduct mission objectives. Communications and telemetry antennas provide the radio-frequency link between the spacecraft and the earth ground station, permitting data to be transmitted and received from the satellite. Solar arrays serve as the principle source of electrical energy to the satellite, and re-charge internal batteries during operation. However, since satellites cannot carry back-up systems, if a solar array fails to deploy, the mission is lost. The subject of on-orbit anomalies related to the deployment of spacecraft appendage, and possible causes of such failures are examined. Topics discussed include mechanical launch loading, on-orbit thermal and solar concerns, reliability of spacecraft pyrotechnics, and practical limitations of ground-based deployment testing. Of particular significance, the article features an in-depth look at the lessons learned from the successful recovery of the Telesat Canada Anik-E2 satellite in 1991.

  8. Artificial O3 formation during fireworks

    NASA Astrophysics Data System (ADS)

    Fiedrich, M.; Kurtenbach, R.; Wiesen, P.; Kleffmann, J.

    2017-09-01

    In several previous studies emission of ozone (O3) during fireworks has been reported, which was attributed to either photolysis of molecular oxygen (O2) or nitrogen dioxide (NO2) by short/near UV radiation emitted during the high-temperature combustion of fireworks. In contrast, in the present study no O3 formation was observed using a selective O3-LOPAP instrument during the combustion of pyrotechnical material in the laboratory, while a standard O3 monitor using UV absorption showed extremely high O3 signals. The artificial O3 response of the standard O3 monitor was caused by known interferences associated with high levels of co-emitted VOCs and could also be confirmed in field measurements during New Year's Eve in the city of Wuppertal, Germany. The present results help to explain unreasonably high ozone levels documented during ambient fireworks, which are in contradiction to the fast titration of O3 by nitrogen monoxide (NO) in the night-time atmosphere.

  9. Emergency in-flight egress opening for general aviation aircraft. [pilot bailout

    NASA Technical Reports Server (NTRS)

    Bement, L. J.

    1980-01-01

    An emergency in-flight egress system was installed in a light general aviation airplane. The airplane had no provision for egress on the left side. To avoid a major structural redesign for a mechanical door, an add on 11.2 kg (24.6 lb) pyrotechnic-actuated system was developed to create an opening in the existing structure. The skin of the airplane was explosively severed around the side window, across a central stringer, and down to the floor, creating an opening of approximately 76 by 76 cm. The severed panel was jettisoned at an initial velocity of approximately 13.7 m/sec. System development included a total of 68 explosive severance tests on aluminum material using small samples, small and full scale flat panel aircraft structural mockups, and an actual aircraft fuselage. These tests proved explosive sizing/severance margins, explosive initiation, explosive product containment, and system dynamics. This technology is applicable to any aircraft of similar construction.

  10. Microjetting from grooved surfaces in metallic samples subjected to laser driven shocks

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

    Rességuier, T. de, E-mail: resseguier@ensma.fr; Lescoute, E.; Sollier, A.

    2014-01-28

    When a shock wave propagating in a solid sample reflects from a free surface, geometrical effects predominantly governed by the roughness and defects of that surface may lead to the ejection of tiny jets that may breakup into high velocity, approximately micrometer-size fragments. This process referred to as microjetting is a major safety issue for engineering applications such as pyrotechnics or armour design. Thus, it has been widely studied both experimentally, under explosive and impact loading, and theoretically. In this paper, microjetting is investigated in the specific loading conditions associated to laser shocks: very short duration of pressure application, verymore » high strain rates, small spatial scales. Material ejection from triangular grooves in the free surface of various metallic samples is studied by combining transverse optical shadowgraphy and time-resolved velocity measurements. The influences of the main parameters (groove angle, shock pressure, nature of the metal) on jet formation and ejection velocity are quantified, and the results are compared to theoretical estimates.« less

  11. Influence of edge conditions on material ejection from periodic grooves in laser shock-loaded tin

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

    Rességuier, T. de; Roland, C.; Prudhomme, G.

    2016-05-14

    In a material subjected to high dynamic compression, the breakout of a shock wave at a rough free surface can lead to the ejection of high velocity debris. Anticipating the ballistic properties of such debris is a key safety issue in many applications involving shock loading, including pyrotechnics and inertial confinement fusion experiments. In this paper, we use laser driven shocks to investigate particle ejection from calibrated grooves of micrometric dimensions and approximately sinusoidal profile in tin samples, with various boundary conditions at the groove edges, including single groove and periodic patterns. Fast transverse shadowgraphy provides ejection velocities after shockmore » breakout. They are found to depend not only on the groove depth and wavelength, as predicted theoretically and already observed in the past, but also, unexpectedly, on the edge conditions, with a jet tip velocity significantly lower in the case of a single groove than behind a periodic pattern.« less

  12. Development of Lead Free Energy Absorber for Space Shuttle Blast Container

    NASA Technical Reports Server (NTRS)

    Ingram, T.; Balles, D.; Schricker, A.; Novak, H.

    1998-01-01

    The Space Shuttle vehicle (SSV) is connected to the mobile launch platform (MLP) by four aft skirt hold down studs on each solid rocket booster (SRB). Prior to lift-off, the frangible nuts inside the aft skirt blast containers (BC) are severed into two nut halves by two pyrotechnic booster cartridges. This action releases the SSV and allows the hold down studs to eject through the aft skirt bore and then down into the MLP. USBI has been tasked to upgrade the BC for two specific reasons; 1. to eliminate lead for environmental concerns, and 2. to reduce the chance of nut recontact with the holddown stud. Nut recontact with the stud has been identified as a likely contributor to stud hangups. This upgrade will replace the lead liner with an aluminum foam material. The aluminum foam used as a energy absorber is a proven design in many other aerospace/defense applications. Additional benefits of using the open cell, energy absorbent aluminum foam in place of the solid lead liner are: A. Lead handling/ exposure, and possible contamination, along with hazardous waste disposal will be eliminated; B. Approximately 200 lbs. weight savings will be contributed to each Space Shuttle flight by using aluminum foam over lead; C. The new aluminum liner is designed to catch all shrapnel from frangible nuts thus virtually eliminating chance of foreign object debris (FOD) exiting the HDP, and causing potential damage to the vehicle; D. Potential of using the lighter aluminum liner over lead, allows for easier assembly and disassembly of blast container elements, also allowing for improvements in safety, operator handling, and efficiency of operations. Six BC firing tests will be required to determine if the new liner material will perform in a way to decrease the chance of stud hangups and enhance the ability of the BC to retain blast debris. Testing will be performed at the Kennedy Space Center (KSC) facility known as the Launch Equipment Test Facility (LETF), and will simulate the SRB hold- down post, with actual BC hardware and pyrotechnics assembled, and then test fired. Initial testing was performed in 1997 using a frangible nut in a static drop test over lead and aluminum foam sheet materials. The aluminum foam showed a dramatic improvement of energy absorption over the lead liner material. Proof-of-Principle testing at the KSC-LETF commenced in May, 1998, and is expected to be completed by June, 1998.

  13. Low-Impact Mating System for Docking Spacecraft

    NASA Technical Reports Server (NTRS)

    Lewis, James L.; Robertson, Brandan; Carroll, Monty B.; Le, Thang; Morales, Ray

    2008-01-01

    A document describes a low-impact mating system suitable for both docking (mating of two free-flying spacecraft) and berthing (in which a robot arm in one spacecraft positions an object for mating with either spacecraft). The low-impact mating system is fully androgynous: it mates with a copy of itself, i.e., all spacecraft and other objects to be mated are to be equipped with identical copies of the system. This aspect of the design helps to minimize the number of unique parts and to standardize and facilitate mating operations. The system includes a closed-loop feedback control subsystem that actively accommodates misalignments between mating spacecraft, thereby attenuating spacecraft dynamics and mitigating the need for precise advance positioning of the spacecraft. The operational characteristics of the mating system can be easily configured in software, during operation, to enable mating of spacecraft having various masses, center-of-gravity offsets, and closing velocities. The system design provides multi-fault tolerance for critical operations: for example, to ensure unmating at a critical time, a redundant unlatching mechanism and two independent pyrotechnic release subsystems are included.

  14. Computing Q-D Relationships for Storage of Rocket Fuels

    NASA Technical Reports Server (NTRS)

    Jester, Keith

    2005-01-01

    The Quantity Distance Measurement Tool is a GIS BASEP computer program that aids safety engineers by calculating quantity-distance (Q-D) relationships for vessels that contain explosive chemicals used in testing rocket engines. (Q-D relationships are standard relationships between specified quantities of specified explosive materials and minimum distances by which they must be separated from persons, objects, and other explosives to obtain specified types and degrees of protection.) The program uses customized geographic-information-system (GIS) software and calculates Q-D relationships in accordance with NASA's Safety Standard For Explosives, Propellants, and Pyrotechnics. Displays generated by the program enable the identification of hazards, showing the relationships of propellant-storage-vessel safety buffers to inhabited facilities and public roads. Current Q-D information is calculated and maintained in graphical form for all vessels that contain propellants or other chemicals, the explosiveness of which is expressed in TNT equivalents [amounts of trinitrotoluene (TNT) having equivalent explosive effects]. The program is useful in the acquisition, siting, construction, and/or modification of storage vessels and other facilities in the development of an improved test-facility safety program.

  15. Investigation of failure to separate an Inconel 718 frangible nut

    NASA Technical Reports Server (NTRS)

    Hoffman, William C., III; Hohmann, Carl

    1994-01-01

    The 2.5-inch frangible nut is used in two places to attach the Space Shuttle Orbiter to the External Tank. It must be capable of sustaining structural loads and must also separate into two pieces upon command. Structural load capability is verified by proof loading each flight nut, while ability to separate is verified on a sample of a production lot. Production lots of frangible nuts beginning in 1987 experienced an inability to reliably separate using one of two redundant explosive boosters. The problems were identified in lot acceptance tests, and the cause of failure has been attributed to differences in the response of the Inconel 718. Subsequent tests performed on the frangible nuts resulted in design modifications to the nuts along with redesign of the explosive booster to reliably separate the frangible nut. The problem history along with the design modifications to both the explosive booster and frangible nut are discussed in this paper. Implications of this failure experience impact any pyrotechnic separation system involving fracture of materials with respect to design margin control and lot acceptance testing.

  16. Analysis and Testing of a Composite Fuselage Shield for Open Rotor Engine Blade-Out Protection

    NASA Technical Reports Server (NTRS)

    Pereira, J. Michael; Emmerling, William; Seng, Silvia; Frankenberger, Charles; Ruggeri, Charles R.; Revilock, Duane M.; Carney, Kelly S.

    2015-01-01

    The Federal Aviation Administration is working with the European Aviation Safety Agency to determine the certification base for proposed new engines that would not have a containment structure on large commercial aircraft. Equivalent safety to the current fleet is desired by the regulators, which means that loss of a single fan blade will not cause hazard to the Aircraft. The NASA Glenn Research Center and The Naval Air Warfare Center (NAWC), China Lake, collaborated with the FAA Aircraft Catastrophic Failure Prevention Program to design and test lightweight composite shields for protection of the aircraft passengers and critical systems from a released blade that could impact the fuselage. In the test, two composite blades were pyrotechnically released from a running engine, each impacting a composite shield with a different thickness. The thinner shield was penetrated by the blade and the thicker shield prevented penetration. This was consistent with pre-test predictions. This paper documents the live fire test from the full scale rig at NAWC China Lake and describes the damage to the shields as well as instrumentation results.

  17. Keeping the Deal

    NASA Technical Reports Server (NTRS)

    Hecht, Michael

    2002-01-01

    On the 4th of July 1997, I lay on a blanket with my family at a fireworks display near our home in Los Angeles, California. The pyrotechnics, they tell me, were dazzling. I wouldn't know. My attention was fixed on a tiny orange dot in the sky - Mars. A month earlier, NASA had released an Announcement of Opportunity for a supplementary payload on the Mars Surveyor Lander mission scheduled for launch in 2001. The Human Exploration and Development of Space (HEDS) organization had been authorized to make the most preliminary of investigations into the feasibility of sending humans to Mars. Among the requested investigations was an opportunity to study the dust and soil of the Red Planet, emphasizing possible hazards to human explorers. I spent that summer of '97 working on a proposal for the project I would eventually lead, the Mars Environmental Compatibility Assessment (MECA). MECA was selected in February of '98. We promised to deliver four new instruments by April 2000 with a modest budget of $5M. This is a story about some of the people who created MECA.

  18. Oxygen Compatibility Testing of Composite Materials

    NASA Technical Reports Server (NTRS)

    Graf, Neil A.; Hudgins, Richard J.; McBain, Michael

    2000-01-01

    The development of polymer composite liquid oxygen LO2 tanks is a critical step in creating the next generation of launch vehicles. Future launch vehicles need to minimize the gross liftoff weight (GLOW), which is possible due to the 25%-40% reduction in weight that composite materials could provide over current aluminum technology. Although a composite LO2 tank makes these weight savings feasible, composite materials have not historically been viewed as "LO2 compatible." To be considered LO2 compatible, materials must be selected that will resist any type of detrimental, combustible reaction when exposed to usage environments. This is traditionally evaluated using a standard set of tests. However, materials that do not pass the standard tests can be shown to be safe for a particular application. This paper documents the approach and results of a joint NASA/Lockheed Martin program to select and verify LO2 compatible composite materials for liquid oxygen fuel tanks. The test approach developed included tests such as mechanical impact, particle impact, puncture, electrostatic discharge, friction, and pyrotechnic shock. These tests showed that composite liquid oxygen tanks are indeed feasible for future launch vehicles.

  19. Pyroshock: Bibliography

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

    Zimmerman, R.M.

    1993-01-01

    This paper represents a review copy for text that is to be included in the Shock and Vibration Recommended Practice Document. This section on pyroshock is written an a general introduction to and description of the topic loading to presentation of an extensive bibliography on the subject. Pyroshock is an evolving science that needs continued focus on both achieving improvements in testing and measurement techniques and advancing instrumentation capabilities. When desired in the near future, recommended practices can be presented. Pyroshock phenomena are associated with separation systems of missiles. spacecraft, and in some cases airplanes. During launch, a rocket drivenmore » vehicle may be exposed to 19 to 30 g's of acceleration with predominant frequencies less than 200 Hz. After launch or takeoffs sections or parts of vehicles may be separated rapidly using explosive driven release mechanisms. Separations can involve stage disconnections for spacecraft sections or payload ejections from missiles and airplanes. At separation, localized pyrotechnic induced accelerations may range from 1000 to over 100,000 g's at frequencies much higher than 1000 Hz. These pyroshocks are characterized by high intensity, high frequency transients that decay rapidly. Pyroshock impulses have insignificant velocity changes.« less

  20. STS-99 workers carry new Master Events Controller to Endeavour

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Workers carry the replacement Enhanced Main Events Controller (E- MEC) to Shuttle Endeavour at Launch Pad 39A for installation in the aft compartment of the payload bay. The original E-MEC became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  1. STS-99 workers move new Master Events Controller into aft compartment

    NASA Technical Reports Server (NTRS)

    2000-01-01

    At Launch Pad 39A, workers move the replacement Enhanced Main Events Controller (E-MEC) into Shuttle Endeavour's aft compartment in the payload bay. The original E-MEC became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  2. Space Shuttle SRM Ignition System. [Solid Rocket Motor

    NASA Technical Reports Server (NTRS)

    Bolieau, C. W.; Baker, J. S.; Folkman, S. L.

    1978-01-01

    This paper presents the Space Shuttle SRM Ignition System, which consists of a large solid propellant main igniter, a small solid propellant initiating igniter and an electromechanical safety and arming device containing two NASA Standard Initiators and a B-KNO3 pyrotechnic booster charge. In development motors, the igniter also has a valve through which CO2 is injected for post-firing quench of the SRM. The igniter has redundant, testable seals at all pressurized joints and three major reusable components; the case, the adapter, and the S&A device. Two development problem areas are discussed. One problem area was transverse mode combustion instability in the main igniter with maximum amplitude of 340 psi peak-to-peak at a frequency of 1500 Hz, which was reduced by a propellant grain configuration change and a change from a 2% aluminum content propellant to a formulation containing 10% aluminum. The other problem area was an excessively rapid rise of thrust in the SRM, which was reduced by reducing the igniter mass flow rate. This mass flow rate reduction was accomplished by removing portions of the grain starpoints in the head end.

  3. Shape Memory Alloy (SMA)-Based Launch Lock

    NASA Technical Reports Server (NTRS)

    Badescu, Mircea; Bao, Xiaoqi; Bar-Cohen, Yoseph

    2014-01-01

    Most NASA missions require the use of a launch lock for securing moving components during the launch or securing the payload before release. A launch lock is a device used to prevent unwanted motion and secure the controlled components. The current launch locks are based on pyrotechnic, electro mechanically or NiTi driven pin pullers and they are mostly one time use mechanisms that are usually bulky and involve a relatively high mass. Generally, the use of piezoelectric actuation provides high precession nanometer accuracy but it relies on friction to generate displacement. During launch, the generated vibrations can release the normal force between the actuator components allowing shaft's free motion which could result in damage to the actuated structures or instruments. This problem is common to other linear actuators that consist of a ball screw mechanism. The authors are exploring the development of a novel launch lock mechanism that is activated by a shape memory alloy (SMA) material ring, a rigid element and an SMA ring holding flexure. The proposed design and analytical model will be described and discussed in this paper.

  4. On the Initiation Mechanism in Exploding Bridgewire and Laser Detonators

    NASA Astrophysics Data System (ADS)

    Stewart, D. Scott; Thomas, K.; Saenz, J.

    2005-07-01

    Since its invention by Los Alamos during the Manhattan Project era the exploding bridgewire detonator (EBW) has seen tremendous use and study. Recent development of a laser-powered device with detonation properties similar to an EBW is reviving interest in the basic physics of the Deflagration-to-Detonation (DDT) process in both of these devices,[1]. Cutback experiments using both laser interferometry and streak camera observations are providing new insight into the initiation mechanism in EBWs. These measurements are being correlated to a DDT model of compaction to detonation and shock to detonation developed previously by Xu and Stewart, [2]. The DDT model is incorporated into a high-resolution, multi-material model code for simulating the complete process. Model formulation and predictions against the test data will be discussed. REFS. [1] A. Munger, J. Kennedy, A. Akinci, and K. Thomas, "Dev. of a Laser Detonator" 30th Int. Pyrotechnics Seminar, Fort Collins, CO, (2004). [2] Xu, S. and Stewart, D. S. Deflagration to detonation transition in porous energetic materials: A model study. J. Eng. Math., 31, 143-172 (1997)

  5. Recent Progress on the Conversion of Surplus Picric Acid/Explosive D to Higher Value Products

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

    R.Mitchell, A; Hsu, P C; Coburn, M D

    2004-07-06

    The global demilitarization of nuclear and conventional munitions is producing millions of pounds of surplus energetic materials. Historically, energetic materials (high explosives, propellants, and pyrotechnics) have been disposed of by open burning/open detonation (OB/OD). The use of OB/OD is becoming unacceptable due to public concerns and increasingly stringent environmental regulations. Clearly, there is a great need to develop environmentally sound and cost-effective alternatives to OB/OD. The conversion of surplus picric acid and/or ammonium picrate (Explosive D) to1,3,5-triamino-2,4,6- trinitrobenzene (TATB) has been subject of extensive process development studies at Lawrence Livermore National Laboratory (LLNL). LLNL, under the direction and sponsorship ofmore » the U.S. Army Defense Ammunition Center (DAC), is developing a process for the conversion of picric acid to TATB on a larger scale. In FY 03, a 10 g per batch process was developed with good results. Development for a one pound per batch system is required as part of overall scale up process for producing TATB from the surplus feedstocks.« less

  6. Development and qualification testing of a laser-ignited, all-secondary (DDT) detonator

    NASA Technical Reports Server (NTRS)

    Blachowski, Thomas J.; Krivitsky, Darrin Z.; Tipton, Stephen

    1994-01-01

    The Indian Head Division, Naval Surface Warfare Center (IHDIV, NSWC) is conducting a qualification program for a laser-ignited, all-secondary (DDT) explosive detonator. This detonator was developed jointly by IHDIV, NSWC and the Department of Energy's EG&G Mound Applied Technologies facility in Miamisburg, Ohio to accept a laser initiation signal and produce a fully developed shock wave output. The detonator performance requirements were established by the on-going IHDIV, NSWC Laser Initiated Transfer Energy Subsystem (LITES) advanced development program. Qualification of the detonator as a component utilizing existing military specifications is the selected approach for this program. The detonator is a deflagration-to-detonator transfer (DDT) device using a secondary explosive, HMX, to generate the required shock wave output. The prototype development and initial system integration tests for the LITES and for the detonator were reported at the 1992 International Pyrotechnics Society Symposium and at the 1992 Survival and Flight Equipment National Symposium. Recent results are presented for the all-fire sensitivity and qualification tests conducted at two different laser initiation pulses.

  7. A database system for characterization of munitions items in conventional ammunition demilitarization stockpiles

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

    Chun, K.C.; Chiu, S.Y.; Ditmars, J.D.

    1994-05-01

    The MIDAS (Munition Items Disposition Action System) database system is an electronic data management system capable of storage and retrieval of information on the detailed structures and material compositions of munitions items designated for demilitarization. The types of such munitions range from bulk propellants and small arms to projectiles and cluster bombs. The database system is also capable of processing data on the quantities of inert, PEP (propellant, explosives and pyrotechnics) and packaging materials associated with munitions, components, or parts, and the quantities of chemical compounds associated with parts made of PEP materials. Development of the MIDAS database system hasmore » been undertaken by the US Army to support disposition of unwanted ammunition stockpiles. The inventory of such stockpiles currently includes several thousand items, which total tens of thousands of tons, and is still growing. Providing systematic procedures for disposing of all unwanted conventional munitions is the mission of the MIDAS Demilitarization Program. To carry out this mission, all munitions listed in the Single Manager for Conventional Ammunition inventory must be characterized, and alternatives for resource recovery and recycling and/or disposal of munitions in the demilitarization inventory must be identified.« less

  8. Ballistic properties of ejecta from a laser shock-loaded groove: smoothed particles hydrodynamics compared with experiments

    NASA Astrophysics Data System (ADS)

    Roland, Caroline; de Resseguier, Thibaut; Sollier, Arnaud; Lescoute, Emilien; Tangiang, Diouwel; Toulminet, Marc; Soulard, Laurent

    2017-06-01

    The interaction of a shock wave with a rough free surface may lead to micrometric material ejection of high velocity (km/s-order). This microjetting phenomenon is a key issue for many applications, such as industrial safety, pyrotechnics or inertial confinement fusion experiments. We have studied this process from single V-shaped grooves of various angles in copper and tin samples shock-loaded by a high energy laser. Experimental details are presented elsewhere in this conference [T. de Rességuier, C. Roland et al., abstract #000154]. As the Smoothed Particles Hydrodynamics formulation is well-suited for the high strains involved in jet expansion and for subsequent fragmentation, this mesh-free method was chosen to simulate microjetting. Computed predictions are compared to experimental results including jet tip and planar surface velocities, spall fracture, and size distribution of the fragments inferred from both fast shadowgraphy and post-recovery observations. Special focus is made on the dependence of the ballistic properties (velocity and mass distributions) of the ejecta on numerical parameters such as the initial inter-particular distance, the smoothing length and a random noise introduced to simulate inner irregularities of the material.

  9. Automotive Airbag Safety Enhancement Final Report CRADA No. TSB-1165-95

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

    Cutting, Jack; Durrell, Robert

    The Vehicle Safety systems (VSS) Division of Quantic Industries, Inc. (QII) manufactured automotive airbag components. When both the driver and the passenger side airbags inflated in a tightly sealed passenger compartment, the compression of the surrounding air could and, in some instances, would cause damage to the eardrums of the occupants. The Aerospace and Division (ADD) of QII had partially developed the technology to fracture the canopy of a jet aircraft at the time of pilot ejection. The technical problem was how to adapt the canopy fracturing technology to the rear window of a motor vehicle in a safe andmore » cost effective manner. The existing approach was to replace the embedded rear window defroster with a series-parallel network of exploding bridge wires (EBWs). This would still provide the defrost function at low voltage/ current, but would cause fracturing of the window when a high current/voltage pulse was applied without pyrotechnics or explosives. The elements of this system were the embedded EBW network and a trunk-mounted fireset. The fireset would store the required energy to fire the network upon the receipt of a trigger signal from the existing air bag crash sensor.« less

  10. ESA Human rating Requirements:Status

    NASA Astrophysics Data System (ADS)

    Trujillo, M.; Sgobba, T.

    2012-01-01

    The European Space Agency (ESA) human rating safety requirements are based on heritage requirements of the International Space Station as well as the knowledge and experience derived from European participation on international partnerships. This expertise in conjunction with recommendations derived from past accidents (i.e.: Columbia) and lessons learned have led to the identification of m inimum core safety tech nical requirements for hum an rated space syst ems. These requirements apply to th e crewed space vehicle, integrated space system (i.e.: cre wed vehicle on its launcher) and its interfaces with control centres, la unch pad, etc. In 2009, a first draft was issued. Then, in the summer of 2010, ESA established a working group comprised of more than twenty experts (from disciplines including propulsion, pyrotechnics, structures, avionics, human factors and life support among others) across the Agency to review this draft. This paper provides an overview of ESA "Safety technical re quirements for human rated s pace systems" document, its scope a nd structure, as well as the planned steps for verification of these requirements in term s of achieving the identified safety objectives for crew safety in t erms of a quantitative risk evaluation.

  11. Status of WSTF Pyrovalve Handbook Development in Year 2000

    NASA Technical Reports Server (NTRS)

    Howard, Julien L.; Hart, Matthew; Smith, William; Saulsberry Regor L.; Fries, Joseph (Technical Monitor)

    1999-01-01

    Significant data have been generated through various spacecraft propulsion system projects involving the use of pyrotechnically operated valves (pyrovalves). These data need to be analyzed, interpreted, summarized, associated, and formatted so they can be made available for spacecraft propulsion system design involving pyrovalves and used to specify test procedures in the performance evaluation and qualification of these systems. To meet this need, a Pyrovalve Handbook is being developed at the NASA White Sands Test Facility. Standards of performance for pyrovalve applications are being formulated under the sponsorship of the NASA Technical Standards Program, as are pyrovalve testing standards under the sponsorship of the NASA Safety and Risk Management Program. The ultimate goal is to have the Handbook adopted as a voluntary standard under the guidance of the AIAA Energetic Components and Systems Technical Committee and, in a more restrictive format, become an integral part of ISO standards for Explosive Systems and Devices Used on Space Vehicles. Feedback from both Government and industry is encouraged and will be the focus of the presentation. It is especially critical that feedback be received on content and formatting of the Handbook to maximize benefit to the technical community. Submission of validated data from organizations outside of NASA is also encouraged.

  12. Pyroshock: Bibliography

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

    Zimmerman, R.M.

    1993-02-01

    This paper represents a review copy for text that is to be included in the Shock and Vibration Recommended Practice Document. This section on pyroshock is written an a general introduction to and description of the topic loading to presentation of an extensive bibliography on the subject. Pyroshock is an evolving science that needs continued focus on both achieving improvements in testing and measurement techniques and advancing instrumentation capabilities. When desired in the near future, recommended practices can be presented. Pyroshock phenomena are associated with separation systems of missiles. spacecraft, and in some cases airplanes. During launch, a rocket drivenmore » vehicle may be exposed to 19 to 30 g`s of acceleration with predominant frequencies less than 200 Hz. After launch or takeoffs sections or parts of vehicles may be separated rapidly using explosive driven release mechanisms. Separations can involve stage disconnections for spacecraft sections or payload ejections from missiles and airplanes. At separation, localized pyrotechnic induced accelerations may range from 1000 to over 100,000 g`s at frequencies much higher than 1000 Hz. These pyroshocks are characterized by high intensity, high frequency transients that decay rapidly. Pyroshock impulses have insignificant velocity changes.« less

  13. Pure Water From a Pure Genius

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Ammonium perchlorate is widely used throughout the aerospace, munitions, and pyrotechnics industries as a primary ingredient in solid rocket and missile propellants, fireworks, and explosive charges. This highly soluble salt has tainted soils and water sources all over the world, and is believed to be an endocrine disrupter, adversely affecting the growth patterns of a fetus or a young child. UMPQUA Research Company (URC), once a small drinking water testing laboratory and a research and development contractor for NASA's manned spaceflight applications, has evolved to become a leader in water purification and analysis. With a total of 11 patents issued for new technologies created by URC under NASA SBIR contracts and a 25-year commitment to water recycling, the company clearly possessed the qualifications necessary to tackle the presence of perchlorate in water. An SBIR contract with NASA's Marshall Space Flight Center that concentrated on the stringent water quality requirements of long-term, manned spaceflight was the source for URC's process and catalyst to facilitate the destruction of perchlorate and nitrate in water. URC licensed the rights of its unique reduction reaction process to Calgon Carbon Corporation for use with the company's perchlorate/nitrate remediation process, otherwise known as ISEP(R).

  14. The discrimination of 72 nitrate, chlorate and perchlorate salts using IR and Raman spectroscopy

    NASA Astrophysics Data System (ADS)

    Zapata, Félix; García-Ruiz, Carmen

    2018-01-01

    Inorganic oxidizing energetic salts including nitrates, chlorates and perchlorates are widely used in the manufacture of not only licit pyrotechnic compositions, but also illicit homemade explosive mixtures. Their identification in forensic laboratories is usually accomplished by either capillary electrophoresis or ion chromatography, with the disadvantage of dissociating the salt into its ions. On the contrary, vibrational spectroscopy, including IR and Raman, enables the non-invasive identification of the salt, i.e. avoiding its dissociation. This study focuses on the discrimination of all nitrate, chlorate and perchlorate salts that are commercially available, using both Raman and IR spectroscopy, with the aim of testing whether every salt can be unequivocally identified. Besides the visual spectra comparison by assigning every band with the corresponding molecular vibrational mode, a statistical analysis based on Pearson correlation was performed to ensure an objective identification, either using Raman, IR or both. Positively, 25 salts (out of 72) were unequivocally identified using Raman, 30 salts when using IR and 44 when combining both techniques. Negatively, some salts were undistinguishable even using both techniques demonstrating there are some salts that provide very similar Raman and IR spectra.

  15. NASA Tech Briefs, June 2009

    NASA Technical Reports Server (NTRS)

    2009-01-01

    Topics covered include: Device for Measuring Low Flow Speed in a Duct, Measuring Thermal Conductivity of a Small Insulation Sample, Alignment Jig for the Precise Measurement of THz Radiation, Autoignition Chamber for Remote Testing of Pyrotechnic Devices, Microwave Power Combiners for Signals of Arbitrary Amplitude, Synthetic Foveal Imaging Technology, Airborne Antenna System for Minimum-Cycle-Slip GPS Reception, Improved Starting Materials for Back-Illuminated Imagers, Multi-Modulator for Bandwidth-Efficient Communication, Some Improvements in Utilization of Flash Memory Devices, GPS/MEMS IMU/Microprocessor Board for Navigation, T/R Multi-Chip MMIC Modules for 150 GHz, Pneumatic Haptic Interfaces, Device Acquires and Retains Rock or Ice Samples, Cryogenic Feedthrough Test Rig, Improved Assembly for Gas Shielding During Welding or Brazing, Two-Step Plasma Process for Cleaning Indium Bonding Bumps, Tool for Crimping Flexible Circuit Leads, Yb14MnSb11 as a High-Efficiency Thermoelectric Material, Polyimide-Foam/Aerogel Composites for Thermal Insulation, Converting CSV Files to RKSML Files, Service Management Database for DSN Equipment, Chemochromic Hydrogen Leak Detectors, Compatibility of Segments of Thermoelectric Generators, Complementary Barrier Infrared Detector, JPL Greenland Moulin Exploration Probe, Ultra-Lightweight Self-Deployable Nanocomposite Structure for Habitat Applications, and Room-Temperature Ionic Liquids for Electrochemical Capacitors.

  16. Dynamical and statistical behavior of discrete combustion waves: a theoretical and numerical study.

    PubMed

    Bharath, Naine Tarun; Rashkovskiy, Sergey A; Tewari, Surya P; Gundawar, Manoj Kumar

    2013-04-01

    We present a detailed theoretical and numerical study of combustion waves in a discrete one-dimensional disordered system. The distances between neighboring reaction cells were modeled with a gamma distribution. The results show that the random structure of the microheterogeneous system plays a crucial role in the dynamical and statistical behavior of the system. This is a consequence of the nonlinear interaction of the random structure of the system with the thermal wave. An analysis of the experimental data on the combustion of a gasless system (Ti + xSi) and a wide range of thermite systems was performed in view of the developed model. We have shown that the burning rate of the powder system sensitively depends on its internal structure. The present model allows for reproducing theoretically the experimental data for a wide range of pyrotechnic mixtures. We show that Arrhenius' macrokinetics at combustion of disperse systems can take place even in the absence of Arrhenius' microkinetics; it can have a purely thermal nature and be related to their heterogeneity and to the existence of threshold temperature. It is also observed that the combustion of disperse systems always occurs in the microheterogeneous mode according to the relay-race mechanism.

  17. Dynamical and statistical behavior of discrete combustion waves: A theoretical and numerical study

    NASA Astrophysics Data System (ADS)

    Bharath, Naine Tarun; Rashkovskiy, Sergey A.; Tewari, Surya P.; Gundawar, Manoj Kumar

    2013-04-01

    We present a detailed theoretical and numerical study of combustion waves in a discrete one-dimensional disordered system. The distances between neighboring reaction cells were modeled with a gamma distribution. The results show that the random structure of the microheterogeneous system plays a crucial role in the dynamical and statistical behavior of the system. This is a consequence of the nonlinear interaction of the random structure of the system with the thermal wave. An analysis of the experimental data on the combustion of a gasless system (Ti + xSi) and a wide range of thermite systems was performed in view of the developed model. We have shown that the burning rate of the powder system sensitively depends on its internal structure. The present model allows for reproducing theoretically the experimental data for a wide range of pyrotechnic mixtures. We show that Arrhenius’ macrokinetics at combustion of disperse systems can take place even in the absence of Arrhenius’ microkinetics; it can have a purely thermal nature and be related to their heterogeneity and to the existence of threshold temperature. It is also observed that the combustion of disperse systems always occurs in the microheterogeneous mode according to the relay-race mechanism.

  18. STS-99 Technicians work in Endeavour's aft compartment of the payload bay

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Technicians work in the aft compartment of Shuttle Endeavour's payload bay, where a new Enhanced Main Events Controller (E-MEC) will be installed. The original E-MEC in Endeavour became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. Before workers can begin E-MEC replacement efforts at the launch pad, cryogenic reactants had to be offloaded from the orbiter and Space Shuttle ordnance disconnected. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  19. Vibroacoustic Impact on the Architectonic Heritage When Using Replicas of 16th Century Weapons

    PubMed Central

    Lloret, Angel Tomas; Sendra, Sandra; Louis Cereceda, Miguel

    2017-01-01

    The recreation of historical battles next to old buildings, walls, churches, fortifications or historical facades belonging to the historical heritage of a city, has always been a source of controversy and discussion. In the absence of a clear legislation about how these buildings can be affected by the use of blunderbusses and pyrotechnics, it is necessary to carry out practical experiments to test the effect of these celebrations on these buildings. For this reason, this paper presents a set of practical experiments where the vibroacoustic effect of using weapons such as blunderbusses and harquebuses is analyzed. To gather these measurements, we have used several sound level meters and 3-axis accelerometers placed on the facade of an old building. The tests have been carried out at the Moors and Christians festival of Villajoyosa (Spain) which is internationally famous for this festival. In order to carry out the tests, six harquebusiers shot their firearms and the sensors placed along the facade of the building at different height collected the data. The results of these devices allow us to study the vibroacoustic impact on the facade depending on the height. PMID:28805738

  20. Development of a Fatigue Crack Growth Coupon for Highly Plastic Stress Conditions

    NASA Technical Reports Server (NTRS)

    Allen, Phillip A.; Aggarwal, Pravin K.; Swanson, Gregory R.

    2003-01-01

    This paper presents an analytical approach used to develop a novel fatigue crack growth coupon for a highly plastic 3-D stress field condition. The flight hardware investigated in this paper is a large separation bolt that fractures using pyrotechnics at the appointed time during the flight sequence. The separation bolt has a deep notch that produces a severe stress concentration and a large plastic zone when highly loaded. For this geometry, linear-elastic fracture mechanics (LEFM) techniques are not valid due to the large nonlinear stress field. Unfortunately, industry codes that are generally available for fracture mechanics analysis and fatigue crack growth (e.g. NASGRO (11) are limited to LEFM and are available for only a limited number of geometries. The results of LEFM based codes are questionable when used on geometries with significant plasticity. Therefore elastic-plastic fracture mechanics (EPFM) techniques using the finite element method (FEM) were used to analyze the bolt and test coupons. scale flight hardware is very costly in t e r n of assets, laboratory resources, and schedule. Therefore to alleviate some of these problems, a series of novel test coupons were developed to simulate the elastic-plastic stress field present in the bolt.

  1. A full scale hydrodynamic simulation of pyrotechnic combustion

    NASA Astrophysics Data System (ADS)

    Kim, Bohoon; Jang, Seung-Gyo; Yoh, Jack

    2017-06-01

    A full scale hydrodynamic simulation that requires an accurate reproduction of shock-induced detonation was conducted for design of an energetic component system. A series of small scale gap tests and detailed hydrodynamic simulations were used to validate the reactive flow model for predicting the shock propagation in a train configuration and to quantify the shock sensitivity of the energetic materials. The energetic component system is composed of four main components, namely a donor unit (HNS + HMX), a bulkhead (STS), an acceptor explosive (RDX), and a propellant (BKNO3) for gas generation. The pressurized gases generated from the burning propellant were purged into a 10 cc release chamber for study of the inherent oscillatory flow induced by the interferences between shock and rarefaction waves. The pressure fluctuations measured from experiment and calculation were investigated to further validate the peculiar peak at specific characteristic frequency (ωc = 8.3 kHz). In this paper, a step-by-step numerical description of detonation of high explosive components, deflagration of propellant component, and deformation of metal component is given in order to facilitate the proper implementation of the outlined formulation into a shock physics code for a full scale hydrodynamic simulation of the energetic component system.

  2. Alkali and alkaline earth metal salts of tetrazolone: structurally interesting and excellently thermostable.

    PubMed

    He, Piao; Wu, Le; Wu, Jin-Ting; Yin, Xin; Gozin, Michael; Zhang, Jian-Guo

    2017-07-04

    Tetrazolone (5-oxotetrazole) was synthesized by a moderate strategy through three steps (addition, cyclization and catalytic hydrogenation) avoiding the unstable intermediate diazonium, as reported during the previous preparation. Alkali and alkaline earth metal salts with lithium (1), sodium (2), potassium (3), rubidium (4) caesium (5), magnesium (6), calcium (7), strontium (8) and barium (9) were prepared and fully characterized using elemental analysis, IR and NMR spectroscopy, DSC and TG analysis. All metal salts were characterized via single-crystal X-ray diffraction. They crystallize in common space groups with high densities ranging from 1.479 (1) to 3.060 g cm -3 (5). Furthermore, the crystal structures of 7, 8 and 9 reveal interesting porous energetic coordination polymers with strong hydrogen bond interactions. All new salts have good thermal stabilities with decomposition temperature between 215.0 °C (4) and 328.2 °C (7), significantly higher than that of the reported nitrogen-rich salt neutral tetrazolone. The sensitivities towards impact and friction were tested using standard methods, and all the tetrazolone-based compounds investigated can be classified into insensitive. The flame test of these metal salts supports their potential use as perchlorate-free pyrotechnics or eco-friendly insensitive energetic materials.

  3. Flat H Frangible Joint Evolution

    NASA Technical Reports Server (NTRS)

    Diegelman, Thomas E.; Hinkel, Todd J.; Benjamin, Andrew; Rochon, Brian V.; Brown, Christopher W.

    2016-01-01

    Space vehicle staging and separation events require pyrotechnic devices. They are single-use mechanisms that cannot be tested, nor can failure-tolerant performance be demonstrated in actual flight articles prior to flight use. This necessitates the implementation of a robust design and test approach coupled with a fully redundant, failure-tolerant explosive mechanism to ensure that the system functions even in the event of a single failure. Historically, NASA has followed the single failure-tolerant (SFT) design philosophy for all human-rated spacecraft, including the Space Shuttle Program. Following the end of this program, aerospace companies proposed building the next generation human-rated vehicles with off-the-shelf, non-redundant, zero-failure-tolerant (ZFT) separation systems. Currently, spacecraft and launch vehicle providers for both the Orion and Commercial Crew Programs (CCPs) plan to deviate from the heritage safety approach and NASA's SFT human rating requirements. Both programs' partners have base-lined ZFT frangible joints for vehicle staging and fairing separation. These joints are commercially available from pyrotechnic vendors. Non-human-rated missions have flown them numerous times. The joints are relatively easy to integrate structurally within the spacecraft. In addition, the separation event is debris free, and the resultant pyro shock is lower than that of other design solutions. It is, however, a serious deficiency to lack failure tolerance. When used for critical applications on human-rated vehicles, a single failure could potentially lead to loss of crew (LOC) or loss of mission (LOM)). The Engineering and Safety & Mission Assurance directorates within the NASA Johnson Space Center took action to address this safety issue by initiating a project to develop a fully redundant, SFT frangible joint design, known as the Flat H. Critical to the ability to retrofit on launch vehicles being developed, the SFT mechanisms must fit within the same three-dimensional envelope as current designs as well as meet structural loads requirements. There is increased mass associated with the redundant design, and the goal is to minimize the weight impact as much as possible. These requirements presented significant challenges, both technically and financially; these challenges will be explored in this paper. Perhaps greater than the technical issues confronted during this design process, were the financial considerations. These were a significant part of the story of this design and development plan. Insufficient financial and labor resources were formidable barriers to completing this project. Nevertheless, JSC personnel successfully conducted several test series at JSC with very useful results. The many lessons learned drove design improvements, performance efficiency, and increased functional reliability. This paper examines the significant technical and financial challenges that these requirements posed to the project team. It discusses the evolution of the SFT frangible joint design, including optimization, testing, and successful partnering of the Johnson Space Center (JSC) engineering and JSC safety organizations, to enhance the flight safety margin for America's next generation of human-rated space vehicles.

  4. Linear actuation using milligram quantities of CL-20 and TAGDNAT.

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

    Snedigar, Shane; Salton, Jonathan Robert; Tappan, Alexander Smith

    2009-07-01

    There are numerous applications for small-scale actuation utilizing pyrotechnics and explosives. In certain applications, especially when multiple actuation strokes are needed, or actuator reuse is required, it is desirable to have all gaseous combustion products with no condensed residue in the actuator cylinder. Toward this goal, we have performed experiments on utilizing milligram quantities of high explosives to drive a millimeter-diameter actuator with a stroke of 30 mm. Calculations were performed to select proper material quantities to provide 0.5 J of actuation energy. This was performed utilizing the thermochemical code Cheetah to calculate the impetus for numerous propellants and tomore » select quantities based on estimated efficiencies of these propellants at small scales. Milligram quantities of propellants were loaded into a small-scale actuator and ignited with an ignition increment and hot wire ignition. Actuator combustion chamber pressure was monitored with a pressure transducer and actuator stroke was monitored using a laser displacement meter. Total actuation energy was determined by calculating the kinetic energy of reaction mass motion against gravity. Of the materials utilized, the best performance was obtained with a mixture of 2,4,6,8,10,12-hexanitro-2,4,6,8,10,12-hexaazaisowurtzitane (CL-20) and bis-triaminoguanidinium(3,3{prime}dinitroazotriazolate) (TAGDNAT).« less

  5. Galileo probe battery system -- An update

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

    Dagarin, B.P.; Taenaka, R.K.; Stofel, E.J.

    NASA`s Galileo 6-year trip to Jupiter is in its final phase. The mission consists of a Jovian Orbiter and an atmospheric entry Probe. The Probe is designed to coast autonomously for up to 190 days and turn itself on 6 hours prior to entry. It will then descend through the upper atmosphere for 50 to 75 minutes with the aid of an 8-foot parachute. This paper discusses sources of electrical power for the Probe and battery testing at the systems level. Described are the final production phase, qualification, and systems testing prior to and following launch, as well as decisionsmore » made regarding the Probe separation Li/SO{sub 2} battery configuration. In addition, the paper briefly describes the thermal battery verification program. The main power source comprises three Li/SO{sub 2} battery modules containing 13 D-sized cell strings per module. These modules are required to retain capacity for 7.5 years and support a 150-day clock, ending with a 7-hour mission sequence of increasing loads from 0.15 A to 9.5 A during the last 30 minutes. The main power source is supplemented by two thermal batteries (CaCrO{sub 4}-Ca), which will be used for firing the pyrotechnic initiators during the atmospheric entry.« less

  6. NASA Tech Briefs, September 2004

    NASA Technical Reports Server (NTRS)

    2004-01-01

    Topics covered include: Brazing SiC/SiC Composites to Metals; Composite-Material Tanks with Chemically Resistant Liners; Thermally Conductive Metal-Tube/Carbon-Composite Joints; Improved BN Coatings on SiC Fibers in SiC Matrices; Iterative Demodulation and Decoding of Non-Square QAM; Measuring Radiation Patterns of Reconfigurable Patch Antennas on Wafers; Low-Cutoff, High-Pass Digital Filtering of Neural Signals; Further Improvement in 3DGRAPE; Ground Support Software for Spaceborne Instrumentation; MER SPICE Interface; Simulating Operation of a Planetary Rover; Analyzing Contents of a Computer Cache; Discrepancy Reporting Management System; Silicone-Rubber Microvalves Actuated by Paraffin; Hydraulic Apparatus for Mechanical Testing of Nuts; Heat Control via Torque Control in Friction Stir Welding; Manufacturing High-Quality Carbon Nanotubes at Lower Cost; Setup for Visual Observation of Carbon-Nanotube Arc Process; Solution Preserves Nucleic Acids in Body-Fluid Specimens; Oligodeoxynucleotide Probes for Detecting Intact Cells; Microwave-Spectral Signatures Would Reveal Concealed Objects; Digital Averaging Phasemeter for Heterodyne Interferometry; Optoelectronic Instrument Monitors pH in a Culture Medium; Imaging of gamma-Irradiated Regions of a Crystal; Photodiode-Based, Passive Ultraviolet Dosimeters; Discrete Wavelength-Locked External Cavity Laser; Flexible Shields for Protecting Spacecraft Against Debris; Part 2 of a Computational Study of a Drop-Laden Mixing Layer; Controllable Curved Mirrors Made from Single-Layer EAP Films; and Demonstration of a Pyrotechnic Bolt-Retractor System.

  7. KSC-2012-1952

    NASA Image and Video Library

    2012-04-03

    DELAMAR DRY LAKE BED, Nev. -- The Boeing Company's CST-100 boilerplate crew capsule floats toward a smooth landing beneath three main parachutes after being released from an Erickson Sky Crane helicopter at about 11,000 feet above Delamar Dry Lake Bed near Alamo, Nev. This is one of two tests that Boeing will perform for NASA's Commercial Crew Program CCP in order to validate the spacecraft's parachute system architecture and deployment scheme, characterize pyrotechnic shock loads, confirm parachute sizing and design, and identify potential forward compartment packaging and deployment issues. In 2011, NASA selected Boeing during Commercial Crew Development Round 2 CCDev2) activities to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also are maturing launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, Excalibur Almaz Inc., Blue Origin, Sierra Nevada, Space Exploration Technologies SpaceX, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Boeing

  8. KSC-06pd2818

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- One of the five THEMIS probes arrives at the hazardous processing facility after leaving Astrotech Space Operations in Titusville, Fla. At the facility, the probes will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  9. KSC-06pd2817

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- One of the five THEMIS probes is being transported from Astrotech Space Operations in Titusville, Fla., to the hazardous processing facility. There the probes will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  10. Hydrocarbon-Seeded Ignition System for Small Spacecraft Thrusters Using Ionic Liquid Propellants

    NASA Technical Reports Server (NTRS)

    Whitmore, Stephen A.; Merkley, Daniel P.; Eilers, Shannon D.; Taylor, Terry L.

    2013-01-01

    "Green" propellants based on Ionic-liquids (ILs) like Ammonium DiNitramide and Hydroxyl Ammonium Nitrate have recently been developed as reduced-hazard replacements for hydrazine. Compared to hydrazine, ILs offer up to a 50% improvement in available density-specific impulse. These materials present minimal vapor hazard at room temperature, and this property makes IL's potentially advantageous for "ride-share" launch opportunities where hazards introduced by hydrazine servicing are cost-prohibitive. Even though ILs present a reduced hazard compared to hydrazine, in crystalline form they are potentially explosive and are mixed in aqueous solutions to buffer against explosion. Unfortunately, the high water content makes IL-propellants difficult to ignite and currently a reliable "coldstart" capability does not exist. For reliable ignition, IL-propellants catalyst beds must be pre-heated to greater than 350 C before firing. The required preheat power source is substantial and presents a significant disadvantage for SmallSats where power budgets are extremely limited. Design and development of a "micro-hybrid" igniter designed to act as a "drop-in" replacement for existing IL catalyst beds is presented. The design requires significantly lower input energy and offers a smaller overall form factor. Unlike single-use "squib" pyrotechnic igniters, the system allows the gas generation cycle to be terminated and reinitiated on demand.

  11. Analysis and Testing of a Composite Fuselage Shield for Open Rotor Engine Blade-Out Protection

    NASA Technical Reports Server (NTRS)

    Pereira, J. Michael; Emmerling, William; Seng, Silvia; Frankenberger, Charles; Ruggeri, Charles R.; Revilock, Duane M.; Carney, Kelly S.

    2016-01-01

    The Federal Aviation Administration is working with the European Aviation Safety Agency to determine the certification base for proposed new engines that would not have a containment structure on large commercial aircraft. Equivalent safety to the current fleet is desired by the regulators, which means that loss of a single fan blade will not cause hazard to the Aircraft. The NASA Glenn Research Center and The Naval Air Warfare Center (NAWC), China Lake, collaborated with the FAA Aircraft Catastrophic Failure Prevention Program to design and test lightweight composite shields for protection of the aircraft passengers and critical systems from a released blade that could impact the fuselage. LS-DYNA® was used to predict the thickness of the composite shield required to prevent blade penetration. In the test, two composite blades were pyrotechnically released from a running engine, each impacting a composite shield with a different thickness. The thinner shield was penetrated by the blade and the thicker shield prevented penetration. This was consistent with pre-test LS-DYNA predictions. This paper documents the analysis conducted to predict the required thickness of a composite shield, the live fire test from the full scale rig at NAWC China Lake and describes the damage to the shields as well as instrumentation results.

  12. Effects of Near Field Pyroshock on the Performance of a Nitramine Nitrocellulose Propellant

    NASA Technical Reports Server (NTRS)

    Baca, Arcenio B.

    2016-01-01

    The overall purpose of this study is to investigate the effects of a pyroshock environment on the performance characteristics of a propellant used in pyrotechnic devices such as guillotine cutters. Near field pyroshock which is defined by acceleration amplitudes in excess of 10,000g at a frequency of greater than 10,000 Hz is a highly transient environment that has a known potential to cause failure in both structural and electronic components. A heritage pressure cartridge assembly which uses a nitramine nitrocellulose propellant with a known performance baseline will be exposed to a near field pyroshock event. The pressure cartridge will then be fired in an ambient closed bomb firing to collect pressure time history. The two performance characteristics that will be evaluated are the pressure amplitude and time to peak pressure. This data will be compared to the base-lined ambient closed bomb data to evaluate the effects of the shock on the performance of the propellant. It is expected that the pyroshock environment will cause brittle failures of the propellant increasing the surface area of said propellant. This increase of surface area should result in increased combustion rate which should show as an increased pressure peak and decreased time to peak pressure in the pressure time data.

  13. A new Master Events Controller is prepared for installation in STS-99 Endeavour

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Workers in a Quality trailer in the Launch Pad 39B Area unwrap a new Enhanced Main Events Controller (E-MEC) to be installed in Shuttle Endeavour. The original E-MEC in Endeavour became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. The E-MECs are located in the orbiter's aft compartment and both are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. Before workers can begin E-MEC replacement efforts at the launch pad, cryogenic reactants must be offloaded from the orbiter and Space Shuttle ordnance disconnected. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  14. A new Master Events Controller is prepared for installation in STS-99 Endeavour

    NASA Technical Reports Server (NTRS)

    2000-01-01

    A new Enhanced Main Events Controller (E-MEC) for Shuttle Endeavour sits on a table in a Quality trailer in the Launch Pad 39B area. The original E-MEC in Endeavour became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. The E-MECs are located in the orbiter's aft compartment and both are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. Before workers can begin E-MEC replacement efforts at the launch pad, cryogenic reactants must be offloaded from the orbiter and Space Shuttle ordnance disconnected. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

  15. Firework displays as sources of particles similar to gunshot residue.

    PubMed

    Grima, Matthew; Butler, Mark; Hanson, Robert; Mohameden, Ahmed

    2012-03-01

    In light of past research being targeted to find specific particles which may be similar to gunshot residue (GSR), this project was formulated to detect any possible particulate by random particle fallout onto substrates at firework displays and to assess the impact this may have on GSR evidence. Firework residue was collected at a display site, from amongst spectators as well as from the author's hair 90min after the display. SEM-EDX analysis has detected such particulate in all three scenarios, with the firework particle population at large providing a solid ground for discrimination from GSR. Wind dispersal was found to decrease the particle population and subsequently, the latter's discriminatory power. Some particles, if treated individually were found to be indistinguishable from GSR. Findings also include residues which may mimic strontium based GSR as well as GSR which may be mixed with that from previous firings. The continuous changes made to primer and propellant compositions by manufacturers also call for greater consideration when classifying particles as originating from pyrotechnic devices. Furthermore, authorities such as police forces should be made more aware about the incidence of such particle transfer in firework related periods. Copyright © 2011 Forensic Science Society. Published by Elsevier Ireland Ltd. All rights reserved.

  16. Multi-Wavelength Diagnostics of Starbirth in Starbursts

    NASA Astrophysics Data System (ADS)

    Waller, William

    2005-07-01

    From the Orion Nebula to the Hubble Deep Field, starburst activity can be seen transforming galaxian clouds of gas into populous clusters of stars. The pyrotechnics and chemical enrichment associated with this activity have led to outcomes as ubiquitous as interstellar dust and as exquisite as life on Earth. In this talk, I will focus on the circumstances of star formation in the environmental context of ongoing starburst activity. I begin with the premises that (1) the formation of a single star takes time, (2) the formation of a populous cluster takes even more time, and (3) ``stuff'' happens in the interim. Hubble images of the Orion Nebula and Eagle Nebula show how hot stars can excavate neighboring clouds of gas and photoevaporate the star-forming cores that are exposed. Hubble observations of giant HII regions in M33 reveal a significant variation in the stellar populations, such that the most metal-rich HII regions contain the greatest proportions of the most massive stars. ISO and Spitzer observations of these same HII regions reveal corresponding variations in the nebular response. These multi-wavelength diagnostics of the stellar-nebular feedback in galaxian starbursts suggest a star-forming mechanism which is subject to photo-evaporative ablation -- an erosive process that is mediated by the metal abundance and corresponding amounts of protective dust in the starbursting environment.

  17. Analyses of scattering characteristics of chosen anthropogenic aerosols

    NASA Astrophysics Data System (ADS)

    Kaszczuk, Miroslawa; Mierczyk, Zygmunt; Muzal, Michal

    2008-10-01

    In the work, analyses of scattering profile of chosen anthropogenic aerosols for two wavelengths (λ1 = 1064 nm and λ2 = 532 nm) were made. As an example of anthropogenic aerosol three different pyrotechnic mixtures (DM11, M2, M16) were taken. Main parameters of smoke particles were firstly analyzed and well described, taking particle shape and size into special consideration. Shape of particles was analyzed on the basis of SEM pictures, and particle size was measured. Participation of particles in each fixed fraction characterized by range of sizes was analyzed and parameters of smoke particles of characteristic sizes and function describing aerosol size distribution (ASD) were determinated. Analyses of scattering profiles were carried out on the basis of both model of scattering on spherical and nonspherical particles. In the case of spherical particles Rayleigh-Mie model was used and for nonspherical particles analyses firstly model of spheroids was used, and then Rayleigh-Mie one. For each characteristic particle one calculated value of four parameters (effective scattering cross section σSCA, effective backscattering cross section σBSCA, scattering efficiency QSCA, backscattering efficiency QBSCA) and value of backscattering coefficient β for whole particles population. Obtained results were compared with the same parameters calculated for natural aerosol (cirrus cloud).

  18. Anomalous Oxidative Diffusion in Titanium Pyrotechnic Powders

    DOE PAGES

    Erikson, William W.; Coker, Eric N.

    2016-11-10

    It has long been observed that oxidation processes in metals tend to follow a parabolic rate law associated with the growth of a surface oxide layer. Here we observe that for certain titanium powders, the expected parabolic law (∝t 1/2) is recovered, yet for others, the exponent differs significantly. One explanation for this non-parabolic, anomalous diffusion arises from fractal geometry. Theoretical considerations indicate that the time response of diffusion-limited processes in an object closely follow a power-law in time (t n) with n=(E–D)/2, where E is the object's Euclidean dimension and D is its boundary's Hausdorff dimension. Non-integer, (fractal) valuesmore » of D will result in n≠1/2. Finite element simulations of several canonical fractal objects were performed to verify the application of this theory; the results matched the theory well. Two different types of titanium powder were tested in isothermal thermogravimetric tests under dilute oxygen. Time-dependent mass uptake data were fit with power-law forms and the associated exponents were used to determine an equivalent fractal dimension. One Ti powder type has an implied surface dimension of ca. 2.3 to 2.5, suggesting fractal geometry may be operative. Finally, the other has a dimension near 2.0, indicating it behaves like traditional material.« less

  19. Investigation of heat transfer in zirconium potassium perchlorate at low temperature: A study of the failure mechanism of the NASA standard initiator

    NASA Technical Reports Server (NTRS)

    Varghese, Philip L.

    1989-01-01

    The objective of this work was to study the reasons for the failure of pyrotechnic initiators at very low temperatures (10 to 100 K). A two-dimensional model of the NASA standard initiator was constructed to model heat transfer from the electrically heated stainless steel bridgewire to the zirconium potassium perchlorate explosive charge and the alumina charge cup. Temperature dependent properties were used in the model to simulate initiator performance over a wide range of initial temperatures (10 to 500 K). A search of the thermophysical property data base showed that pure alumina has a very high thermal conductivity at low temperatures. It had been assumed to act as a thermal insulator in all previous analyses. Rapid heat transfer from the bridgewire to the alumina at low initial temperatures was shown to cause failure of the initiators if the wire did not also make good contact with the zirconium potassium perchlorate charge. The mode is able to reproduce the results of the tests that had been conducted to investigate the cause for failure. It also provides an explanation for previously puzzling results and suggests simple design changes that will increase reliability at very low initial temperatures.

  20. Pilot Deployment of the LDSD Parachute via a Supersonic Ballute

    NASA Technical Reports Server (NTRS)

    Tanner, Christopher L.; O'Farrell, Clara; Gallon, John C.; Clark, Ian G.; Witkowski, Allen; Woodruff, Paul

    2015-01-01

    The Low Density Supersonic Decelerator (LDSD) Project required the use of a pilot system due to the inability to mortar deploy its main supersonic parachute. A mortar deployed 4.4 m diameter supersonic ram-air ballute was selected as the pilot system for its high drag coefficient and stability relative to candidate supersonic parachutes at the targeted operational Mach number of 3. The ballute underwent a significant development program that included the development of a new liquid methanol-based pre-inflation system to assist the ballute inflation process. Both pneumatic and pyrotechnic mortar tests were conducted to verify orderly rigging deployment, bag strip, inflation aid activation, and proper mortar performance. The ballute was iteratively analyzed between fluid and structural analysis codes to obtain aerodynamic and aerothermodynamic estimates as well as estimates of the ballute's structural integrity and shape. The ballute was successfully flown in June 2014 at a Mach number of 2.73 as part of the first LDSD supersonic flight test and performed beyond expectations. Recovery of the ballute indicated that it did not exceed its structural or thermal capabilities. This flight set a historical precedent as it represented the largest ballute to have ever been successfully flown at this Mach number by a NASA entity.

  1. Equations of State and High-Pressure Phases of Explosives

    NASA Astrophysics Data System (ADS)

    Peiris, Suhithi M.; Gump, Jared C.

    Energetic materials, being the collective name for explosives, propellants, pyrotechnics, and other flash-bang materials, span a wide range of composite chemical formulations. Most militarily used energetics are solids composed of particles of the pure energetic material held together by a binder. Commonly used binders include various oils, waxes, and polymers or plasticizers, and the composite is melt cast, cured, or pressed to achieve the necessary mechanical properties (gels, putties, sheets, solid blocks, etc.) of the final energetic material. Mining, demolition, and other industries use liquid energetics that are similarly composed of an actual energetic material or oxidizer together with a fuel, that is to be mixed and poured for detonation. Pure energetic materials that are commonly used are nitroglycerine, ammonium nitrate, ammonium or sodium perchlorate, trinitrotoluene (TNT), HMX, RDX, and TATB. All of them are molecular materials or molecular ions that when initiated or insulted undergoes rapid decomposition with excessive liberation of heat resulting in the formation of stable final products. When the final products are gases, and they are rapidly produced, the sudden pressure increase creates a shock wave. When decomposition is so rapid that the reaction moves through the explosive faster than the speed of sound in the unreacted explosive, the material is said to detonate. Typically, energetic materials that undergo detonation are known as high explosives (HEs) and energetic materials that burn rapidly or deflagrate are known as low explosives and/or propellants.

  2. Public health assessment for Longhorn Army Ammunition Plant, Karnack, Harrison County, Texas, Region 6, CERCLIS number TX6213820529. Final report

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

    NONE

    1999-07-09

    Longhorn Army Ammunition Plant (Longhorn) is an 8,493 acre government-owned former industrial facility approximately 14 miles northeast of Marshall, Harrison County, Texas. Longhorn has been intermittently in operation since 1942 when it was established to produce the explosive 2,4,6-trinitrotoluene (TNT). Pyrotechnic ammunition also was produced at Longhorn and Morton Thiokol Corporation produced a plastic explosive at the facility until August 1997. According to document record for the hazardous ranking system, releases of 1,3-dinitrobenzene, 1,3,5-trinitrobenzene, arsenic, barium, chromium, and lead occurred. The Agency for Toxic Substances and Disease Registry (ATSDR) reviewed available environmental information for the site and evaluated several potentialmore » exposure situations. These exposure situations include potential contact with site contaminants in surface water, sediment, surface soil, wasteline material, and groundwater. Although site-related contaminants have been found in these various environmental media, currently the contaminants are not accessible, on or off the site, at levels that would pose a public health threat. Based on available information, the authors have concluded that overall, the Longhorne Army Ammunition Plant poses on apparent public health hazard. In the future, the conclusion category for this site could change if additional data were to indicate that contaminants from the site were migrating towards the public water supply wells near the site.« less

  3. Effects of variables upon pyrotechnically induced shock response spectra

    NASA Technical Reports Server (NTRS)

    Smith, J. L.

    1986-01-01

    Throughout the aerospace industry, large variations of 50 percent (6 dB) or more are continually noted for linear shaped charge (LSC) generated shock response spectra (SRS) from flight data (from the exact same location on different flights) and from plate tests (side by side measurements on the same test). A research program was developed to investigate causes of these large SRS variations. A series of ball drop calibration tests to verify calibration of accelerometers and a series of plate tests to investigate charge and assembly variables were performed. The resulting data were analyzed to determine if and to what degree manufacturing and assembly variables, distance from the shock source, data acquisition instrumentation, and shock energy propagation affect the SRS. LSC variables consisted of coreload, standoff, and apex angle. The assembly variable was the torque on the LSC holder. Other variables were distance from source of accelerometers, accelerometer mounting methods, and joint effects. Results indicated that LSC variables did not affect SRS as long as the plate was severed. Accelerometers mounted on mounting blocks showed significantly lower levels above 5000 Hz. Lap joints did not affect SRS levels. The test plate was mounted in an almost free-free state; therefore, distance from the source did not affect the SRS. Several varieties and brands of accelerometers were used, and all but one demonstrated very large variations in SRS.

  4. Investigating Premature Ignition of Thruster Pressure Cartridges by Mechanical Impact of Internal Components

    NASA Technical Reports Server (NTRS)

    Woods, Stephen S.; Saulsberry, Regor

    2010-01-01

    Pyrotechnic thruster pressure cartridges (TPCs) are used for aeroshell separation on a new NASA crew launch vehicle. The premature ignition concern was hypothesized based on the potential range of motion of the subassemblies, projected worst case accelerations, and the internal geometry that could subject propellant grains to mechanical impact sufficiently high for ignition. This possibility was investigated by fabricating a high-fidelity model of the suspected contact geometry, placing a representative amount of propellant in it, and impacting the propellant with a range of forces equivalent to and greater than the maximum possible during launch. Testing demonstrated that the likelihood of ignition is less than 1 in 1,000,000. The test apparatus, methodology, and results are described in this paper. Nondestructive evaluation ( NDE) during TPC acceptance testing indicated that internal assemblies moved during shock and vibration testing due to an internal bond anomaly. This caused concerns that the launch environment might produce the same movement and release propellant grains that might be prematurely ignited through impact or through electrostatic discharge (ESD) as grains vibrated against internal surfaces. Since a new lot could not be fabricated in time, a determination had to be made as to whether the lot was acceptable to fly. This paper discusses the analysis and impact testing used to address the potential impact issue and a separate paper addresses the ESD issue.

  5. Research and test facilities

    NASA Technical Reports Server (NTRS)

    1993-01-01

    A description is given of each of the following Langley research and test facilities: 0.3-Meter Transonic Cryogenic Tunnel, 7-by 10-Foot High Speed Tunnel, 8-Foot Transonic Pressure Tunnel, 13-Inch Magnetic Suspension & Balance System, 14-by 22-Foot Subsonic Tunnel, 16-Foot Transonic Tunnel, 16-by 24-Inch Water Tunnel, 20-Foot Vertical Spin Tunnel, 30-by 60-Foot Wind Tunnel, Advanced Civil Transport Simulator (ACTS), Advanced Technology Research Laboratory, Aerospace Controls Research Laboratory (ACRL), Aerothermal Loads Complex, Aircraft Landing Dynamics Facility (ALDF), Avionics Integration Research Laboratory, Basic Aerodynamics Research Tunnel (BART), Compact Range Test Facility, Differential Maneuvering Simulator (DMS), Enhanced/Synthetic Vision & Spatial Displays Laboratory, Experimental Test Range (ETR) Flight Research Facility, General Aviation Simulator (GAS), High Intensity Radiated Fields Facility, Human Engineering Methods Laboratory, Hypersonic Facilities Complex, Impact Dynamics Research Facility, Jet Noise Laboratory & Anechoic Jet Facility, Light Alloy Laboratory, Low Frequency Antenna Test Facility, Low Turbulence Pressure Tunnel, Mechanics of Metals Laboratory, National Transonic Facility (NTF), NDE Research Laboratory, Polymers & Composites Laboratory, Pyrotechnic Test Facility, Quiet Flow Facility, Robotics Facilities, Scientific Visualization System, Scramjet Test Complex, Space Materials Research Laboratory, Space Simulation & Environmental Test Complex, Structural Dynamics Research Laboratory, Structural Dynamics Test Beds, Structures & Materials Research Laboratory, Supersonic Low Disturbance Pilot Tunnel, Thermal Acoustic Fatigue Apparatus (TAFA), Transonic Dynamics Tunnel (TDT), Transport Systems Research Vehicle, Unitary Plan Wind Tunnel, and the Visual Motion Simulator (VMS).

  6. The Alpha-Proton-X-ray Spectrometer deployment mechanism: an anthropomorphic approach to sensor placement on Martian rocks and soil

    NASA Astrophysics Data System (ADS)

    Blomquist, Richard S.

    1995-05-01

    On July 4,1997, the Mars Pathfinder spacecraft lands on Mars and starts conducting technological and scientific experiments. One experiment, the Alpha-Proton-X-ray Spectrometer, uses a sensor head placed against rocks and soil to determine their composition. To guarantee proper placement, a deployment mechanism mounted on the Mars Rover aligns the sensor head to within 20 deg of the rock and soil surfaces. In carrying out its task, the mechanism mimics the action of a human hand and arm. Consisting of a flexible wrist, a parallel link arm, a brush dc motor actuator, and a revolutionary non-pyrotechnic fail-safe release device, the mechanism correctly positions the sensor head on rocks as high as 0.29 m and on targets whose surfaces are tilted as much as 45 deg from the nominal orientation of the sensor head face. The mechanism weighs less than 0.5 kg, can withstand 100 g's, and requires less than 2.8 N x m of actuation torque. The fail-safe coupler utilizes Cerrobend, a metal alloy that melts at 60 C, to fuse the actuator and the rest of the mechanism together. A film heater wrapped around the coupler melts the metal, and Negator springs drive the mechanism into its stowed position. The fail-safe actuates using 6.75 Watts for 5 minutes in the event of an actuator failure.

  7. KSC-06pd2813

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- At Astrotech Space Operations in Titusville, Fla., one of the five THEMIS probes is ready to be covered for its move to the hazardous processing facility. There it will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  8. KSC-06pd2812

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- At Astrotech Space Operations in Titusville, Fla., technicians are preparing one of five THEMIS probes to be secured inside a shipping container (behind it). The probes are being moved to the hazardous processing facility where they will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  9. KSC-06pd2815

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- At Astrotech Space Operations in Titusville, Fla., technicians release the overhead crane from the shipping container placed around one of the five THEMIS probes for its move to the hazardous processing facility. There the probes will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  10. KSC-06pd2814

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- At Astrotech Space Operations in Titusville, Fla., technicians help lower a shipping container over one of the five THEMIS probes for its move to the hazardous processing facility. There it will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  11. KSC-06pd2816

    NASA Image and Video Library

    2006-12-14

    KENNEDY SPACE CENTER, FLA. -- At Astrotech Space Operations in Titusville, Fla., one of the five THEMIS probes is moved out of the facility and will be transported to the hazardous processing facility. There the probes will be placed on a stand in preparation for fueling operations. Once fueling is complete, each probe will be weighed and individually mated to the payload carrier before pyrotechnics are installed. The fully integrated THEMIS payload is then ready for spin-balance testing and weighing. The final milestone is mating THEMIS to its upper stage booster. THEMIS consists of five identical probes, the largest number of scientific satellites ever launched into orbit aboard a single rocket. This unique constellation of satellites will resolve the tantalizing mystery of what causes the spectacular sudden brightening of the aurora borealis and aurora australis - the fiery skies over the Earth's northern and southern polar regions. These lights are the visible manifestations of invisible energy releases, called geomagnetic substorms, in near-Earth space. THEMIS will not only seek to answer where and when substorms start, but will also provide clues as to how and why these space storms create havoc on satellites, terrestrial power grids, and communication systems. THEMIS will be transported to Pad 17-B at Cape Canaveral Air Force Station on February 1 for mating to the Delta II rocket. Launch is scheduled for Feb. 15. Photo credit: NASA/George Shelton

  12. NASA Tech Briefs, December 2010

    NASA Technical Reports Server (NTRS)

    2010-01-01

    Topics include: Coherent Frequency Reference System for the NASA Deep Space Network; Diamond Heat-Spreader for Submillimeter-Wave Frequency Multipliers; 180-GHz I-Q Second Harmonic Resistive Mixer MMIC; Ultra-Low-Noise W-Band MMIC Detector Modules; 338-GHz Semiconductor Amplifier Module; Power Amplifier Module with 734-mW Continuous Wave Output Power; Multiple Differential-Amplifier MMICs Embedded in Waveguides; Rapid Corner Detection Using FPGAs; Special Component Designs for Differential-Amplifier MMICs; Multi-Stage System for Automatic Target Recognition; Single-Receiver GPS Phase Bias Resolution; Ultra-Wideband Angle-of-Arrival Tracking Systems; Update on Waveguide-Embedded Differential MMIC Amplifiers; Automation Framework for Flight Dynamics Products Generation; Product Operations Status Summary Metrics; Mars Terrain Generation; Application-Controlled Parallel Asynchronous Input/Output Utility; Planetary Image Geometry Library; Propulsion Design With Freeform Fabrication (PDFF); Economical Fabrication of Thick-Section Ceramic Matrix Composites; Process for Making a Noble Metal on Tin Oxide Catalyst; Stacked Corrugated Horn Rings; Refinements in an Mg/MgH2/H2O-Based Hydrogen Generator; Continuous/Batch Mg/MgH2/H2O-Based Hydrogen Generator; Strain System for the Motion Base Shuttle Mission Simulator; Ko Displacement Theory for Structural Shape Predictions; Pyrotechnic Actuator for Retracting Tubes Between MSL Subsystems; Surface-Enhanced X-Ray Fluorescence; Infrared Sensor on Unmanned Aircraft Transmits Time-Critical Wildfire Data; and Slopes To Prevent Trapping of Bubbles in Microfluidic Channels.

  13. The Alpha-Proton-X-ray Spectrometer deployment mechanism: An anthropomorphic approach to sensor placement on Martian rocks and soil

    NASA Technical Reports Server (NTRS)

    Blomquist, Richard S.

    1995-01-01

    On July 4,1997, the Mars Pathfinder spacecraft lands on Mars and starts conducting technological and scientific experiments. One experiment, the Alpha-Proton-X-ray Spectrometer, uses a sensor head placed against rocks and soil to determine their composition. To guarantee proper placement, a deployment mechanism mounted on the Mars Rover aligns the sensor head to within 20 deg of the rock and soil surfaces. In carrying out its task, the mechanism mimics the action of a human hand and arm. Consisting of a flexible wrist, a parallel link arm, a brush dc motor actuator, and a revolutionary non-pyrotechnic fail-safe release device, the mechanism correctly positions the sensor head on rocks as high as 0.29 m and on targets whose surfaces are tilted as much as 45 deg from the nominal orientation of the sensor head face. The mechanism weighs less than 0.5 kg, can withstand 100 g's, and requires less than 2.8 N x m of actuation torque. The fail-safe coupler utilizes Cerrobend, a metal alloy that melts at 60 C, to fuse the actuator and the rest of the mechanism together. A film heater wrapped around the coupler melts the metal, and Negator springs drive the mechanism into its stowed position. The fail-safe actuates using 6.75 Watts for 5 minutes in the event of an actuator failure.

  14. Use of Heritage Hardware on Orion MPCV Exploration Flight Test One

    NASA Technical Reports Server (NTRS)

    Rains, George Edward; Cross, Cynthia D.

    2012-01-01

    Due to an aggressive schedule for the first space flight of an unmanned Orion capsule, currently known as Exploration Flight Test One (EFT1), combined with severe programmatic funding constraints, an effort was made within the Orion Program to identify heritage hardware, i.e., already existing, flight-certified components from previous manned space programs, which might be available for use on EFT1. With the end of the Space Shuttle Program, no current means exists to launch Multi-Purpose Logistics Modules (MPLMs) to the International Space Station (ISS), and so the inventory of many flight-certified Shuttle and MPLM components are available for other purposes. Two of these items are the MPLM cabin Positive Pressure Relief Assembly (PPRA), and the Shuttle Ground Support Equipment Heat Exchanger (GSE HX). In preparation for the utilization of these components by the Orion Program, analyses and testing of the hardware were performed. The PPRA had to be analyzed to determine its susceptibility to pyrotechnic shock, and vibration testing had to be performed, since those environments are predicted to be more severe during an Orion mission than those the hardware was originally designed to accommodate. The GSE HX had to be tested for performance with the Orion thermal working fluids, which are different from those used by the Space Shuttle. This paper summarizes the activities required in order to utilize heritage hardware for EFT1.

  15. Use of Heritage Hardware on MPCV Exploration Flight Test One

    NASA Technical Reports Server (NTRS)

    Rains, George Edward; Cross, Cynthia D.

    2011-01-01

    Due to an aggressive schedule for the first orbital test flight of an unmanned Orion capsule, known as Exploration Flight Test One (EFT1), combined with severe programmatic funding constraints, an effort was made to identify heritage hardware, i.e., already existing, flight-certified components from previous manned space programs, which might be available for use on EFT1. With the end of the Space Shuttle Program, no current means exists to launch Multi Purpose Logistics Modules (MPLMs) to the International Space Station (ISS), and so the inventory of many flight-certified Shuttle and MPLM components are available for other purposes. Two of these items are the Shuttle Ground Support Equipment Heat Exchanger (GSE Hx) and the MPLM cabin Positive Pressure Relief Assembly (PPRA). In preparation for the utilization of these components by the Orion Program, analyses and testing of the hardware were performed. The PPRA had to be analyzed to determine its susceptibility to pyrotechnic shock, and vibration testing had to be performed, since those environments are predicted to be significantly more severe during an Orion mission than those the hardware was originally designed to accommodate. The GSE Hx had to be tested for performance with the Orion thermal working fluids, which are different from those used by the Space Shuttle. This paper summarizes the certification of the use of heritage hardware for EFT1.

  16. Synthesis and Performance Characterization of a Nanocomposite Ternary Thermite: Al/Fe2O3/SiO2

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

    Prentice, D; Pantoya, M L; Clapsaddle, B J

    2005-02-04

    Making solid energetic materials requires the physical mixing of solid fuels and oxidizers or the incorporation of fuel and oxidizing moieties into a single molecule. The former are referred to as composite energetic materials (i.e., thermites, propellants, pyrotechnics) and the latter are deemed monomolecular energetic materials (i.e., explosives). Mass diffusion between the fuel and oxidizer is the rate controlling step for composite reactions while bond breaking and chemical kinetics control monomolecular reactions. Although composites have higher energy densities than monomolecular species, they release that energy over a longer period of time because diffusion controlled reactions are considerably slower than chemistrymore » controlled reactions. Conversely, monomolecular species exhibit greater power due to more rapid kinetics than physically mixed energetics. Reducing the diffusion distance between fuel and oxidizer species within an energetic composite would enhance the reaction rate. Recent advances in nanotechnology have spurred the development of nano-scale fuel and oxidizer particles that can be combined into a composite and effectively reduce diffusion distances to nano-scale dimensions or less. These nanocomposites have the potential to deliver the best of both worlds: high energy density of the physically mixed composite with the high power of the monomolecular species. Toward this end, researchers at Lawrence Livermore National Laboratory (LLNL) developed nano-particle synthesis techniques, based on sol-gel chemistry, for the production of thermite nanocomposites.« less

  17. Lidar ceilometer observations and modeling of a fireworks plume in Vancouver, British Columbia

    NASA Astrophysics Data System (ADS)

    van der Kamp, Derek; McKendry, Ian; Wong, May; Stull, Roland

    Observations of a plume emanating from a 30-min duration pyrotechnic display with a lidar ceilometer are described for an urban setting in complex, coastal terrain. Advection of the plume across the ceilometer occurred at a mean height of 250 m AGL. The plume traveled downwind at ˜3 m s -1, and at a distance of 8 km downwind, was ˜100 m in vertical thickness with particulate matter (PM) concentrations of order 30-40 μg m -3. Surface PM observations from surrounding urban monitoring stations suggest that the plume was not mixed to ground over the urban area. Plume trajectories at ˜250 m simulated by three numerical models all traveled to the northeast of the ceilometer location. Horizontal plume dispersion estimates suggest that the model trajectories were too far north to accommodate the likely lateral plume spread necessary to explain the ceilometer observations. This poor agreement between near surface observations and model output is consistent with previous mesoscale model validations in this region of complex urbanized terrain, and suggests that despite improvements in mesoscale model resolution, there remains an urgent need to improve upstream initial conditions over the Pacific Ocean, data assimilation over complex terrain, the representation of urban areas in mesoscale models, and to further validate such models for nocturnal applications in complex settings.

  18. Selected Lessons Learned in Space Shuttle Orbiter Propulsion and Power Subsystems

    NASA Technical Reports Server (NTRS)

    Hernandez, Francisco J.; Martinez, Hugo; Ryan, Abigail; Westover, Shayne; Davies, Frank

    2011-01-01

    Over its 30 years of space flight history, plus the nearly 10 years of design, development test and evaluation, the Space Shuttle Orbiter is full of lessons learned in all of its numerous and complex subsystems. In the current paper, only selected lessons learned in the areas of the Orbiter propulsion and power subsystems will be described. The particular Orbiter subsystems include: Auxiliary Power Unit (APU), Hydraulics and Water Spray Boiler (WSB), Mechanical Flight Controls, Main Propulsion System (MPS), Fuel Cells and Power Reactant and Storage Devices (PRSD), Orbital Maneuvering System (OMS), Reaction Control System (RCS), Electrical Power Distribution (EPDC), electrical wiring and pyrotechnics. Given the complexity and extensive history of each of these subsystems, and the limited scope of this paper, it is impossible to include most of the lessons learned; instead the attempt will be to present a selected few or key lessons, in the judgment of the authors. Each subsystem is presented separate, beginning with an overview of the hardware and their function, a short description of a few historical problems and their lessons, followed by a more comprehensive table listing of the major subsystem problems and lessons. These tables serve as a quick reference for lessons learned in each subsystem. In addition, this paper will establish common lessons across subsystems as well as concentrate on those lessons which are deemed to have the highest applicability to future space flight programs.

  19. Environmental risk assessment of white phosphorus from the use of munitions - a probabilistic approach.

    PubMed

    Voie, Øyvind Albert; Johnsen, Arnt; Strømseng, Arnljot; Longva, Kjetil Sager

    2010-03-15

    White phosphorus (P(4)) is a highly toxic compound used in various pyrotechnic products. Ammunitions containing P(4) are widely used in military training areas where the unburned products of P(4) contaminate soil and local ponds. Traditional risk assessment methods presuppose a homogeneous spatial distribution of pollutants. The distribution of P(4) in military training areas is heterogeneous, which reduces the probability of potential receptors being exposed to the P(4) by ingestion, for example. The current approach to assess the environmental risk from the use of P(4) suggests a Bayesian network (Bn) as a risk assessment tool. The probabilistic reasoning supported by a Bn allows us to take into account the heterogeneous distribution of P(4). Furthermore, one can combine empirical data and expert knowledge, which allows the inclusion of all kinds of data that are relevant to the problem. The current work includes an example of the use of the Bn as a risk assessment tool where the risk for P(4) poisoning in humans and grazing animals at a military shooting range in Northern Norway was calculated. P(4) was detected in several craters on the range at concentrations up to 5.7g/kg. The risk to human health was considered acceptable under the current land use. The risk for grazing animals such as sheep, however, was higher, suggesting that precautionary measures may be advisable.

  20. A semi-automatic parachute separation system for balloon payloads

    NASA Astrophysics Data System (ADS)

    Farman, M.

    At the National Scientific balloon Facility (NSBF), when operating stratospheric balloons with scientific payloads, the current practice for separating the payload from the parachute after descent requires the sending of commands, over a UHF uplink, from the chase airplane or the ground control site. While this generally works well, there have been occasions when, due to shadowing of the receive antenna or unfavorable aircraft attitude, the command has not been received and the parachute has failed to separate. In these circumstances the payload may be dragged for long distances before being recovered, with consequent danger of damage to expensive and sometimes irreplaceable scientific instrumentation. The NSBF has therefore proposed a system which would automatically separate the parachute without the necessity for commanding after touchdown. Such a system is now under development.. Mechanical automatic release systems have been tried in the past with only limited success. The current design uses an electronic system based on a tilt sensor which measures the angle that the suspension train subtends relative to the gravity vector. With the suspension vertical, there is minimum output from the sensor. When the payload touches down, the parachute tilts and in any tilt direction the sensor output increases until a predetermined threshold is reached. At this point, a threshold detector is activated which fires the pyrotechnic cutter to release the parachute. The threshold level is adjustable prior to the flight to enable the optimum tilt angle to be determined from flight experience. The system will not operate until armed by command. This command is sent during the descent when communication with the on-board systems is still normally reliable. A safety interlock is included to inhibit arming if the threshold is already high at the time the command is sent. While this is intended to be the primary system, the manual option would be retained as a back- up. A market survey was carried out to choose a suitable tilt sensor and three prototype systems were built for evaluation. These were installed in standard NSBF terminate units, and flown on routine operational flights throughout 2001 with the automatic pyrotechnic cutter active but off-line. A data logger was also installed to record system parameters during the descent phase. The results of these flights validated the system concept and it was found that the telemetry threshold monitor was also an asset to the operator in deciding when it was safe to send a manual parachute release command. However, the accumu lated test experience indicated that the originally- chosen tilt sensor, which uses a liquid electrolyte and requires an in-flight microprocessor, was not sufficiently rugged or reliable. A solid-state accelerometer, with encapsulated analog signal processing, was therefore selected as a replacement and the threshold electronics redesigned to match this sensor. This system is currently being evaluated on NSBF operation al flights during 2002. On completion of this phase, NASA will review the results and a decision will be made whether to use this design as the primary operational system on future flights. This paper discusses the requirements for such a system and describes the current design in detail. It reports on the evaluation flights of 2001 and 2002 and their results to date.

Some links on this page may take you to non-federal websites. Their policies may differ from this site.
Top