Publications

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The blast parameters for the 6-foot diameter by 200-foot long, explosively driven shock tube are presented in this report. The purpose, main characteristics, and blast simulation capabilities of this PETN Primacord, explosively driven facility are included. Experimental data are presented for air and Sulfurhexaflouride (SF6) test gases with initial pressures between 0.5 to 12.1 psia (ambient). Experimental data are presented and include shock wave time of amval at various test stations, flow duration, static or side-on overpressure, and stagnation or head-on overpressure. The blast parameters calculated from the above measured parameters and presented in this report include shock wave velocity, shock strength, shock Mach number, flow Mach Number, reflected pressure, dynamic pressure, particle velocity, density, and temperature. Graphical data for the above parameters are included. Algorithms and least squares fit equations are also included.

This report describes the 19-foot diameter blast tunnel at Sandia National Laboratories. The blast tunnel configuration consists of a 6 foot diameter by 200 foot long shock tube, a 6 foot diameter to 19 foot diameter conical expansion section that is 40 feet long, and a 19 foot diameter test section that is 65 feet long. Therefore, the total blast tunnel length is 305 feet. The development of this 19-foot diameter blast tunnel is presented. The small scale research test results using 4 inch by 8 inch diameter and 2 foot by 6 foot diameter shock tube facilities are included. Analytically predicted parameters are compared to experimentally measured blast tunnel parameters in this report. The blast tunnel parameters include distance, time, static, overpressure, stagnation pressure, dynamic pressure, reflected pressure, shock Mach number, flow Mach number, shock velocity, flow velocity, impulse, flow duration, etc. Shadowgraphs of the shock wave are included for the three different size blast tunnels.

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The Precision Linear Shaped Charge (PLSC) design concept involves the independent fabrication and assembly of the liner (wedge of PLSC), the tamper/confinement, and explosive. The liner is the most important part of a linear shaped charge (LSC) and should be fabricated by a more quality controlled, precise process than the tamper material. Also, this concept allows the liner material to be different from the tamper material. The explosive can be loaded between the liner and tamper as the last step in the assembly process rather than the first step as in conventional LSC designs. PLSC designs have been shown to produce increased jet penetrations in given targets, more reproducible jet penetration, and more efficient explosive cross-section geometries using a minimum amount of explosive. The Linear Explosive Shaped Charge Analysis (LESCA) code developed at Sandia National Laboratories has been used to assist in the design of PLSCs. LESCA predictions for PLSC jet tip velocities, jet-target impact angles, and jet penetration in aluminum and steel targets are compared to measured data. The advantages of PLSC over conventional LSC are presented. As an example problem, the LESCA code was used to analytically develop a conceptual design for a PLSC component to sever a three-inch thick 1018 steel plate at a water depth of 500 feet (15 atmospheres).

Phase II work for this Laboratory Directed Research and Development project is presented. Historically, high velocity, solid, electrically conducting armatures or projectiles have been utilized to generate or magnify existing electric fields in magnetohydrodynamic (MHD) devices. Useful power can be extracted from high velocity ionized, electrically conductive plasma jets. The MHD device current output can be switched to power other devices. The purpose of this project is to investigate the use of an Explosively-Driven Ionized Plasma Jet Generator (EDMG) to more efficiently obtain velocities much higher than can be achieved with solid armatures or projectiles. The armature velocity is one of the more important parameters in the electric field magnification process. The ionized plasma jet is generated by explosively collapsing a gas (neon, argon, xenon, hydrogen) filled cavity and directing the jet through a shocktube or core of an MHD device. Data are presented for two different size and configuration explosive drivers, one explosive (COMP-C4), one gas (argon), different driver pressures (90-200 psia), different shocktube or test section pressures (0.01-11.7 psia), and for two different shocktube inside dimensions. Measured time-of-arrival, current, voltage, resistance, power and energy data are presented for tests conducted. Measured time-of-arrival and plasma flow velocity data are compared to the predicted CTH hydrocode data. CTH code calculations are also presented to compare EDMG performance of various test gases and various explosive liner materials.

Sandia National Laboratories' design and development of an optimized Plane Shock Generator Explosive Lens (PSGEL) is detailed in this report. This PSGEL component is designed to generate a planar shock wave transmitted to perform a function through a steel bulkhead without rupturing or destroying the integrity of the bulkhead. The PSGEL component consists of a detonator, explosive, brass cone, and confinement or tamper housing. The purpose of the PSGEL component is to generate a plane shock wave input to a stainless steel bulkhead (wave separator) with a ferro-electric (PZT) ceramic disk attached to the steel on the surface opposite the PSGEL. The planar shock wave depolarizes the PZT 65/35 ferro-electric ceramic to produce an electrical output. Elastic, plastic I and plastic II waves with different velocities are generated in the steel bulkhead. The depolarization of the PZT ceramic is produced by the elastic wave of specific amplitude (10-20 kilobars) and this process must be completed before (about 0.15 microseconds) the first plastic wave arrives at the PZT ceramic. Measured particle velocity versus time profiles, using a Velocity Interferometer System for Any Reflector (VISAR), are presented for the brass and steel output free surfaces. Shock wave planarity data, using an electronic streak camera, are presented for the brass and steel wave separator free surfaces.

Plasma jet generators have been designed and tested which used an explosive driver and shocktube with a rectangular cross section that optimize the flow velocity and electrical conductivity. The latest in a series of designs has been tested using a reactive load to diagnose the electrical properties of the MHD generator/electromagnet combination. The results of these tests indicate that the plasma jet/MHD generator design does generate a flow velocity greater than 25 km/s and produces several gigawatts of pulsed power in a very small package size. A larger, new generator design is also presented.

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The work for the development of an Annular Precision Linear Shaped Charge (APLSC) Flight Termination System (FTS) for the Operation and Deployment Experiment Simulator (ODES) program is discussed and presented in this report. The Precision Linear Shaped Charge (PLSC) concept was recently developed at Sandia. The APLSC component is designed to produce a copper jet to cut four inch diameter holes in each of two spherical tanks, one containing fuel and the other an oxidizer that are hyperbolic when mixed, to terminate the ODES vehicle flight if necessary. The FTS includes two detonators, six Mild Detonating Fuse (MDF) transfer lines, a detonator block, detonation transfer manifold, and the APLSC component. PLSCs have previously been designed in ring components where the jet penetrating axis is either directly away or toward the center of the ring assembly. Typically, these PLSC components are designed to cut metal cylinders from the outside inward or from the inside outward. The ODES program requires an annular linear shaped charge. The (Linear Shaped Charge Analysis) LESCA code was used to design this 65 grain/foot APLSC and data comparing the analytically predicted to experimental data are presented. Jet penetration data are presented to assess the maximum depth and reproducibility of the penetration. Data are presented for full scale tests, including all FTS components, and conducted with nominal 19 inch diameter, spherical tanks.

Sandia National Laboratories is currently involved in the optimization of a Plane Shock Generator Explosive Lens (PSGEL). This PSGEL component is designed to generate a planar shock wave transmitted to perform a function through a steel bulkhead without rupturing or destroying the integrity of the bulkhead. The PSGEL component consists of a detonator, explosive, brass cone and tamper housing. The purpose of the PSGEL component is to generate a plane shock wave input to 4340 steel bulkhead (wave separator) with a ferro-electric (PZT) ceramic disk attached to the steel on the surface opposite the PSGEL. The planar shock wave depolarizes the PZT 65/35 ferroelectric ceramic to produce an electrical output. Elastic, plastic I and plastic II waves with different velocities are generated in the steel bulkhead. The depolarization of the PZT ceramic is produced by the elastic wave of specific amplitude (10--20 Kilobars) and this process must be completed before (about 0. 15 microseconds) the first plastic wave arrives at the PZT ceramic. Measured particle velocity versus time profiles, using a Velocity Interferometer System for Any Reflector (VISAR) are presented for the brass and steel output free surfaces. Peak pressures are calculated from the particle velocities for the elastic, plastic I and plastic 11 waves in the steel. The work presented here investigates replacing the current 4340 steel with PH 13-8 Mo stainless steel in order to have a more corrosion resistant, weldable and more compatible material for the multi-year life of the component. Therefore, the particle velocity versus time profile data are presented comparing the 4340 steel and PH 13-8 Mo stainless steel. Additionally, in order to reduce the amount of explosive, data are presented to show that LX-13 can replace PBX-9501 explosive to produce more desirable results.

The Precision Linear Shaped Charge (PLSC) design concept involves the independent fabrication and assembly of the liner (wedge of PLSC), the tamper/confinement, and explosive. The liner is the most important part of an LSC and should be fabricated by a more quality controlled, precise process than the tamper material. Also, this concept allows the liner material to be different from the tamper material. The explosive can be loaded between the liner and tamper as the last step in the assembly process rather than the first step as in conventional LSC designs. PLSC designs are shown to produce increased jet penetrations in given targets, more reproducible jet penetration, and more efficient explosive cross sections using a minimum amount of explosive. The Linear Explosive Shaped Charge Analysis (LESCA) code developed at SandiaNational Laboratories has been used to assist in the design of PLSCs. LESCA predictions for PLSC jet penetration in aluminum targets, jet tip velocities and jet-target impact angles are compared to measured data.

The analytical procedures for establishing the fragment hazard zone for explosive test facilities are presented. Environment, safety and health regulations require that a hazard zone analysis be conducted for every explosive test facility. Analyses are presented for explosively driven missile fragment trajectories resultant from cased explosive configurations. Fragment trajectory parameter data are presented in graphical form for three different fragment materials (aluminum, steel and tantalum), initial velocities between 0.6mm/{mu}s (2000 ft/sec) to 4.3mm/{mu}s (14,000 ft/sec), and for various geometries. This trajectory information is used, as an example, to determine the safe distance or hazard zone for the Area 2 explosive test facility at Sandia National Laboratories.

Analytical equations for explosively accelerated flyer plates are used to generate graphical solutions to flyer problems. Given the problem geometrical configuration, explosive weight, flyer weight, tamping weight and Gurney velocity, the graphical representation of the calculated data allows for a fast approximation of the final or maximum flyer velocity. The graphical solution for flyer velocity is particularly useful when a computer is not available. The graphical analysis scheme can be used with any explosive, tamper and flyer materials. Analytical data are presented for grazing, spherical, cylindrical, open, symmetric and asymmetric sandwich explosive configurations. 13 refs., 7 figs., 4 tabs.

The Linear Explosive Shaped Charge Analysis (LESCA) code is used to analytically model and optimize the design of a linear shaped charge (LSC). A variety of LSCs are initially modeled with the LESCA code, and the predicted jet penetration versus standoff data are compared to experimental data. The LSCs varied in explosive loading size form 600 to 10,500 grains per foot. The LSC liner material for this study was cooper. The variables optimized in this study included the LSC apex angle, liner thickness, explosive width, and explosive width, and explosive height. 8 ref., 24 figs.

Analytical equations for barrel-tamped explosively accelerated flyer plates are used to generate graphical solutions to flyer problems. Given the problem geometrical dimensions, explosive weight, detonation velocity, explosive exponent, barrel-tamping weight, and flyer weight, the graphical representation of the calculated data allows for a fast approximation of the final or maximum flyer plate velocity. Graphically obtained flyer velocities are compared to experimentally published data. The graphical solution for flyer velocity is particularly useful when a computer is not available. The graphical representation of the various barrel-tamped flyer parameters results in a parametric study which illustrates the effect on final flyer velocity in varying parameters. The graphical analysis scheme can be used with any explosive, tamper and flyer materials. 15 refs., 12 figs., 4 tabs.

The Rankine Hugoniot equation relating the conversion of momentum across a shock front and the empirical relationship for shock velocity as a function of particle velocity are used to calculate the impact pressures for selected materials. The shock velocity and particle velocities are then calculated as a function of impact pressures. The calculated data are graphically presented sets of three figures for the selected materials as follows: Impact pressure as a function of impact velocity, impact pressure as a function of particle velocity, impact pressure as a function of shock velocity. Given the projectile impact velocity and material Hugoniot information, this graphical representation of the data allows for a fast approximation of the impact pressure particle velocity, and shock velocity in the target material. 9 refs., 1 fig., 3 tabs.

The Precision Linear Shaped Charge (PLSC) design concept involves the independent fabrication and assembly of the liner (wedge of PLSC), the tamper/confinement, and explosive. The liner is the most important part of an LSC and should be fabricated by a more quality controlled, precise process than the tamper material. Also this allows the liner material to be different from the tamper material. The explosive can be loaded into the liner and tamper as the last step in the assembly process rather than the first step as in conventional LSC designs. PLSC designs are shown to produce increased jet penetrations in given targets, more reproducible jet penetration, and more efficient explosive cross-sections using a minimum amount of explosive. The Linear Shaped Charge Analysis Program (LSCAP) being developed at Sandia National Laboratories has been used to assist in the design of PLSCs. LSCAP predictions for PLSC jet penetration in aluminum targets, jet tip velocities and jet-target impact angles are compared to measured data. 8 refs., 19 figs., 1 tab.