34 results about "Shock front" patented technology

An embedded flight sensor system having a laser and one or more flight sensors in optical communication with the laser plus a data processing device in optical communication with the flight sensors. The flight sensors may be laser based optical components such as a fiber Bragg grating in combination with an optical detector, a spectroscopy grating and detector or an optical detector associated with catch optics. The parameters sensed by the flight sensors may be used to determine any flight parameter. Representative flight parameters include but are not limited to an airframe or external surface temperature, airstream velocity, combustion zone temperature, engine inlet temperature, a gas concentration or a shock front position.

An emitter for atomizing and discharging a liquid entrained in a gas stream is disclosed. The emitter has a nozzle with an outlet facing a deflector surface. The nozzle discharges a gas jet against the deflector surface. The emitter has a duct with an exit orifice adjacent to the nozzle outlet. Liquid is discharged from the orifice and is entrained in the gas jet where it is atomized. A method of operating the emitter is also disclosed. The method includes establishing a first shock front between the outlet and the deflector surface, a second shock front proximate to the deflector surface, and a plurality of shock diamonds in a liquid-gas stream discharged from the emitter.

A fire suppression system is disclosed. The system includes a gaseous extinguishing agent and a liquid extinguishing agent. At least one emitter is in fluid communication with the liquid and gas. The emitter is used to establish a gas stream, atomize and entrain the liquid into the gas stream and discharge the resulting liquid-gas stream onto the fire. A method of operating the system is also disclosed. The method includes establishing a gas stream having first and second shock fronts using the emitter, atomizing and entraining the liquid with the gas at one of the two shock fronts to form a liquid-gas stream, and discharging the stream onto the fire. The method also includes creating a plurality of shock diamonds in the liquid-gas stream discharged from the emitter.

An internal combustion engine having a compression ignition initiation device is provided. The compression ignition initiation device includes a body defining a chamber and an outlet from the chamber. The device further includes means, within the chamber, for generating a combustion initiating shock front from the outlet. A method is provided, including compressing a mixture of fuel and air in an internal combustion engine cylinder to a point less than a compression ignition threshold, and initiating ignition of the mixture by subjecting it to a shock front.

A fusible target is embedded in a high Z liner, ohmically heated and then shock wave heated by implosion of an enveloping high Z liner. The target is adiabatically heated by compression, fusibly ignited and charged-particle heated as it is being ignited. A shock front forms as the liner implodes which shock front detaches from the more slowly moving liner, collides with the outer surface of the target, accelerates inward, rapidly heating the target, adiabatically compressing the target and liner and amplifying the current to converge the liner mass toward a central axis thereby compressing the target to a fusion condition when it begins to ignite and produce charged particles. The charged particles are trapped in a large magnetic field surrounding the target. The energy of the charged particles is deposited into the target to further heat the target to produce an energy gain.

Radionuclides are produced with a pulsed neutron flux from a multiple repetition rate staged Z-pinch machine, the pulsed neutron flux is moderated, an activatable radionuclide precursor is exposed to the moderated pulsed neutron flux, and a corresponding radionuclide from the activatable radionuclide precursor is produced. High current pulses are passed through a target plasma of fusible material enclosed in a cylindrical liner plasma composed of a high-Z plasma to generate a magnetic field that compresses the liner plasma, and generates shock waves. The shock implodes the target plasma. The shock front propagates between an outer shock front and an axis of the target plasma so it is heated through shock dissipation and by adiabatic compression due to an imploding shock front produced in the outer liner plasma to fuse light nuclei and generate alpha particles and neutrons. Alpha particles trapped within the magnetic field further heat the target plasma.

An internal combustion engine having a compression ignition initiation device is provided. The compression ignition initiation device includes a body defining a chamber and an outlet from the chamber. The device further includes means, within the chamber, for generating a combustion initiating shock front from the outlet. A method is provided, including compressing a mixture of fuel and air in an internal combustion engine cylinder to a point less than a compression ignition threshold, and initiating ignition of the mixture by subjecting it to a shock front.

The invention relates to a method and device for eliminating nanoparticles on the surfaces of substrates, such as a silicon wafer under the assistance of laser and in particular relates to a method and device which are characterized in that air is subjected to dielectric breakdown by using laser focusing to form sharply inflated plasmas, the air around the plasmas is rapidly compressed into a stronger shock front, and the stronger shock front directly acts on the surface of the substrate so that the nanoparticles are separated from the substrate, such as a wafer or a photomask under the action of force or rolling torque. The method and device disclosed by the invention are particularly suitable for removing 100nm and even smaller particles on the surface of the substrate.

Bacteria on and in meat, for example hamburger, is killed by subjecting the meat to an explosive shock front pressure wave propagated through an inert liquid medium at a rate of at least 6100 meters per second.

An explosive event may be produced by mixing reactive material and water to form a mixture. The reactive material may be mixed with a substantially stoichiometric amount of water needed for complete reaction of the water with the reactive material. After forming the mixture, the mixture may be detonated with opposing shock waves. Shock fronts of the opposing shock waves may coincide to form a mach front or mach stem, which may enhance the explosive effect.

The invention represents a novel system for controlling the yield of an explosive charge that enables the explosive yield to be selected or decreased from full-yield detonation incrementally down to low-yield detonation using a continuous linear shaped charge jet spiraled around the main charge explosive and deflagrating a selected portion of the main charge explosive. The spiral linear shaped charge jet initiation system activates and projects a liner in a radial direction across a diameter of the main charge explosive in a spiral around its axis at a preselected deflagration velocity toward a main-charge detonation shock front reducing the main charge explosive.

Radionuclides are produced with a pulsed neutron flux from a multiple repetition rate staged Z-pinch machine, the pulsed neutron flux is moderated, an activatable radionuclide precursor is exposed to the moderated pulsed neutron flux, and a corresponding radionuclide from the activatable radionuclide precursor is produced. High current pulses are passed through a target plasma of fusible material enclosed in a cylindrical liner plasma composed of a high-Z plasma to generate a magnetic field that compresses the liner plasma, and generates shock waves. The shock implodes the target plasma. The shock front propagates between an outer shock front and an axis of the target plasma so it is heated through shock dissipation and by adiabatic compression due to an imploding shock front produced in the outer liner plasma to fuse light nuclei and generate alpha particles and neutrons. Alpha particles trapped within the magnetic field further heat the target plasma.

A device for generating an intense radio frequency pulse through use of a helical Magneto-Cumulative Generator (MCG). The MCG provides a chemical explosion and acts as a converter to transform the chemical / mechanical energy into an electrical energy impulse. Due to the detonation / combustion process, a vortex wake is produced which assumes the role of a quarter-wave trap / antenna. If the MCG is in high velocity flight, a bow-shaped shockwave, followed by a second shock front, is established around the head of the MCG, becoming a second antenna. Without flight, two MCG's are placed head-to-head so that the vortex wakes emit in opposite directions. Since the explosion destroys the MCG, a model is created to perform multiple tests of the ability of an MCG to act as an RF device.

An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling (through a combination of superconductivity and / or superemissivity) driven by the cryogenic power of liquid hydrogen and / or regenerative evaporation of liquid hydrogen and / or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality at Mach 1. The ensuing supercool / chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Under conditions of optimality the incipient air stream may be compressed in accord with the stagnation pressure of the Mach number and liquefacted in one-step via the power of supercooling and isothermal compression

A method for estimating the detonation performance of a material is executed by first preparing a small sample of the material to be tested. That sample is lased with a laser beam having sufficient energy to induce a plasma from a portion of the sample and to produce a shock wave, without detonation of the sample. The velocity of the shock wave is then measured at different times. And a characteristic shock velocity determined for the material based on the relationship between shock velocity and time. The characteristic shock velocity represents the velocity of the shock wave at the point in time when the shock front expands freely without additional energy input from the plasma or subsequent chemical reactions. The characteristic shock velocity can be used to determine whether a material is non-energetic or energetic; if it is energetic, the estimated detonation performance can be determined.

A method for estimating the detonation performance of a material is executed by first preparing a small sample of the material to be tested. That sample is lased with a laser beam having sufficient energy to induce a plasma from a portion of the sample and to produce a shock wave, without detonation of the sample. The velocity of the shock wave is then measured at different times. And a characteristic shock velocity determined for the material based on the relationship between shock velocity and time. The characteristic shock velocity represents the velocity of the shock wave at the point in time when the shock front expands freely without additional energy input from the plasma or subsequent chemical reactions. The characteristic shock velocity can be used to determine whether a material is non-energetic or energetic; if it is energetic, the estimated detonation performance can be determined.

A woodwind mouthpiece has a tone chamber in communication with a central bore running through the mouthpiece and a window exposing the tone chamber. A table is located at a first end of the window, and a tip rail is located at a second end of the window opposite the first end. A pair of side rails run along opposite sides of the window from the table to the tip rail. Each side rail includes a side rail top surface. A pair of flanges are provided in the mouthpiece such that each flange extending out from one of the side rail top surfaces in a direction opposite the window. This arrangement reduces the intensity of the shock fronts at the aperture into the tone chamber.

The invention discloses a ship cab with an anti-shock front window. The ship cab comprises a shell, front side glass, rear side glass and a rectangular frame. The front side of the shell is provided with a rectangular window and installation screws. A rectangular installation frame is arranged on the periphery of the rear side glass and fixed to the front side of the rectangular window. A rectangular glass frame is installed on the periphery of the front side glass. An elastic rubber frame is arranged on the periphery of the rectangular glass frame. A rubber ring clamping base is arranged on the front side of the rectangular glass frame. A sealing rubber strip is installed on the rubber ring clamping base. Guide holes are formed in the rear side face of the rectangular glass frame at intervals. The ends of the installation screws are inserted in the guide holes in a sliding mode respectively. A pressure spring, an annular gasket and an adjusting nut are arranged on each installation screw. By means of the ship cab with the anti-shock front window, when strong wind and rain impact on the front side glass, the front side glass can elastically retreat under the effect of the pressuresprings, and front side impact force is weakened.

An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The ensuing supercool / chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension, liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Also described are the details of an isentropically expanded hypersonic stochastic switch (a singularity), which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle whereby a continuous flow continuum is transformed into a stochastic flux.

The invention discloses a shock-absorbing AC low-voltage power distribution cabinet, which comprises an outer box, a cylindrical tube is fixedly installed on each side of the outer wall of the outer box, a spring one is fixedly installed in the inner cavity of the cylindrical tube, and the upper end of the spring one The bottom end of the movable rod is fixedly connected, and the top end of the movable rod penetrates through the top of the cylinder and is fixedly connected with the arc plate, and the spring two is fixedly installed on the arc plate, and the top end of the spring two is fixedly connected with a rubber ball, and the rubber ball The top of the ball is fixedly connected to the lining plate, and the shock absorbing box is fixedly installed on the lining plate. The present invention reduces the external force and vibration through the multi-layer shock absorbing device from the outside to the inside, cuts layer by layer, controls layer by layer, and cooperates with each other. Most of the vibration is completely eliminated before reaching the inner compartment, and a very small part of the vibration needs to be eliminated by the rubber pad to achieve an excellent shock absorption effect.