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  • 1
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    Determination of pyrotechnic functional margin (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Following the failure of a previously qualified pyrotechnically actuated pin puller design, an investigation led to a redesign and requalification. The emphasis of the second qualification was placed on determining the functional margin of the pin puller by comparing the energy deliverable by the pyrotechnic cartridge to the energy required to accomplish the function. Also determined were the effects of functional variables. This paper describes the failure investigation, the test methods employed and the results of the evaluation, and provides a recommended approach to assure the successful functioning of pyrotechnic devices.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA. Stennis Space Center, The First NASA Aerospace Pyrotechnic Systems Workshop; p 34-50
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Development of a NASA standard gas generator (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The goals of the NASA Standard Gas Generator (NSGG) Program are to create a NASA standard gas generating cartridge, characterize its performance, and make it readily available to users. A cartridge within the same envelope as the NASA Standard Initiator (NSI) has the greatest potential use. This potential use is described in viewgraph form. Our approach for NSGG development and qualification was planned to be conducted in several phases. Test methods were developed to evaluate output performance for a variety of potential applications. A feasibility study using modified NSI's was accomplished. Preliminary and final development will be conducted with a delta qualification to evaluate the effects of manufacturing lots and environments. Feasibility study results, feasibility study conclusions, and future plans are presented.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA. Stennis Space Center, The First NASA Aerospace Pyrotechnic Systems Workshop; p 51-82
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Integration of pyrotechnics into aerospace systems (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: 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.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA. Ames Research Center, The 27th Aerospace Mechanisms Symposium; p 93-106
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Performance of blasting caps (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Common blasting caps are made from an aluminum shell in the form of a tube which is closed at both ends. One end, which is called the output end, terminates in a principal side or face, and contains a detonating agent which communicates with a means for igniting the detonating agent. The improvement of the present invention is a flat, steel foil bonded to the face in a position which is aligned perpendicularly to the longitudinal axis of the tube.
    Keywords: PROPELLANTS AND FUELS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Determination of pyrotechnic functional margin (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Following the failure of a previously qualified pyrotechnically actuated pin puller design, an investigation led to a redesign and requalification. The emphasis of the second qualification was placed on determining the functional margin of the pin puller by comparing the energy deliverable by the pyrotechnic cartridge to the energy required to accomplish the function. Also determined were the effects of functional variables. This paper describes the failure investigation, the test methods employed and the results of the evaluation, and provides a recommended approach to assure the successful functioning of pyrotechnic devices.
    Keywords: PROPELLANTS AND FUELS
    Type: Annual SAFE Symposium; Nov 11, 1991 - Nov 13, 1991; Las Vegas, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Output testing of small-arms primers (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The performance of two standard primers for initiating small-caliber ammunition are compared to that of a primer for initiating aircraft escape-system components. Three testing methods are employed including: (1) firing the primer to measure total energy delivered; (2) monitoring output in terms of gaseous product-mass flow rate and pressure as a function of time; and (3) firing the primer onto ignition material to study gas pressure produced during ignition and burning as a function of time. The results of the test demonstrate differences in the ignitability factors of the standard primers and time peak pressures of less than 100 microseconds. One unexpected result is that two percussion primers (the FA-41 and the M42C1) developed for different applications have the same ignitability. The ignitability test method is shown to yield the most useful data and can be used to specify percussion primers and optimize their performance.
    Keywords: PROPELLANTS AND FUELS
    Type: Annual SAFE Symposium; Dec 11, 1990 - Dec 13, 1990; San Antonio, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Super-Zip separation joint performance investigation (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Following functional failures of two of five Lockheed Super-Zip spacecraft separation joints in a development test series to quantify thermal effects, an investigation program was initiated on this and related systems to assist in preventing recurrence. The Super-Zip joint, applied in a ring configuration, utilizes an explosively expanded tube to fracture surrounding prenotched aluminum plates to achieve planar separation. A unique test method was developed and more than 300 individual test firings were conducted to provide an understanding of severance mechanisms, the functional performance effects of system variables, and the most likely cause of system failure. An approach for defining functional margin was developed, as well as specific recommendations for improving existing and future systems.
    Keywords: PROPELLANTS AND FUELS
    Type: Symposium on Explosives and Pyrotechnics; Dec 02, 1986 - Dec 04, 1986; Hilton Head Island, SC; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Helicopter in-flight stores jettison (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A helicopter emergency external-stores jettison system accommodating an experimental simplified mounting system is presented. The system's conceptual approach is described, including store interface, attachment, functional mechanisms, and system initiation. It is novel both in the stores' mounting interface logic and in the modifications to existing technology for the components. Two nonfragmenting 'ridge cut' explosive bolts were mounted in each 600-pound store to interface with a simple plate on the aircraft. Starting designs with proven technology and functional margins were demonstrated by analysis and test through the design and development. Design details of the system's components, from the explosive bolt to the initiation handle, are described.
    Keywords: PROPELLANTS AND FUELS
    Type: Annual SAFE Symposium; Dec 05, 1989 - Dec 08, 1989; New Orleans, LA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Ignitability test method. II (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: To determine functional performance of initiating devices, the NASA's Langley Research Center's novel ignitability research on percussion primers has been expanded in 1989 to include measurements of function time, the evaluation of six primer lots (five types), and the determination of the effects of the military cold-temperature requirement of -65 F and primer output closure disks. This test method, a major improvement over the prior primer output test methods, fully met all objectives, while showing a significant amount of ignition variability.
    Keywords: PROPELLANTS AND FUELS
    Type: Annual SAFE Symposium; Dec 05, 1989 - Dec 08, 1989; New Orleans, LA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Ignitability test method (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: To overcome serious weaknesses in determining the performance of initiating devices, a novel 'ignitability test method', representing actual design interfaces and ignition materials, has been developed. Ignition device output consists of heat, light, gas an burning particles. Past research methods have evaluated these parameters individually. This paper describes the development and demonstration of an ignitability test method combining all these parameters, and the quantitative assessment of the ignition performance of two widely used percussion primers, the M42C1-PA101 and the M42C2-793. The ignition materials used for this evaluation were several powder, granule and pellet sizes of black powder and boron-potassium nitrate. This test method should be useful for performance evaluation of all initiator types, quality assurance, evaluation of ignition interfaces, and service life studies of initiators and ignition materials.
    Keywords: PROPELLANTS AND FUELS
    Type: Annual SAFE Symposium; Dec 05, 1988 - Dec 08, 1988; Las Vegas, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
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