A hardware configuration and related control strategy is disclosed that accepts an electric power input typical of space flight systems and converts that energy into a spark pulse train with fixed/predetermined performance metrics for the following system parameters: time to first spark, peak breakdown voltage amplitude, spark repetition rate and energy delivered per spark, which have all been optimally chosen to reliably ignite certain fuel mixtures, which have been proven to be beneficial for use in aerospace applications.

A hardware configuration and related control strategy is disclosed that accepts an electric power input typical of space flight systems and converts that energy into a spark pulse train with fixed/predetermined performance metrics for the following system parameters: time to first spark, peak breakdown voltage amplitude, spark repetition rate and energy delivered per spark, which have all been optimally chosen to reliably ignite certain fuel mixtures, which have been proven to be beneficial for use in aerospace applications.

The invention involves centric insertion of electronic equipment (26) undergoing destruction by a drawer (15) into a destroying device, into an air gap (21) between the central arms of the cores (11) of an electromagnet (10), and initiating the discharge of the accumulated electrical energy in order to destroy this electronic equipment (26) by means of a movable spark gap (14). This spark gap constitutes a moving assembly (13) comprising a motor (20) with a controller, a movable carriage (16) with an electrode (12) seated on the guides (17) of the moving assembly (13), and a fixed carriage (18) with an electrode (12).

The invention involves centric insertion of electronic equipment (26) undergoing destruction by a drawer (15) into a destroying device, into an air gap (21) between the central arms of the cores (11) of an electromagnet (10), and initiating the discharge of the accumulated electrical energy in order to destroy this electronic equipment (26) by means of a movable spark gap (14). This spark gap constitutes a moving assembly (13) comprising a motor (20) with a controller, a movable carriage (16) with an electrode (12) seated on the guides (17) of the moving assembly (13), and a fixed carriage (18) with an electrode (12).

A downhole electrohydraulic movement arrangement including a spark gap device positioned and configured to move a separate component, and an energy source electrically connected to the spark gap device. A method for moving a component in a downhole environment including disposing an electrohydraulic arrangement having a spark gap device and an energy source electrically connected to the spark gap device operably proximate a component, actuating the spark gap device, generating a pressure wave with the spark gap device, and moving the component with the pressure wave. A downhole system including a borehole, a component moved within the borehole by an electrohydraulic arrangement.

A downhole electrohydraulic movement arrangement including a spark gap device positioned and configured to move a separate component, and an energy source electrically connected to the spark gap device. A method for moving a component in a downhole environment including disposing an electrohydraulic arrangement having a spark gap device and an energy source electrically connected to the spark gap device operably proximate a component, actuating the spark gap device, generating a pressure wave with the spark gap device, and moving the component with the pressure wave. A downhole system including a borehole, a component moved within the borehole by an electrohydraulic arrangement.

A casing for a laser spark plug, in particular, of an internal combustion engine of a motor vehicle, or of a stationary engine; the casing including at least one casing part and a combustion chamber window joined to the casing part to form a seal at least regionally; characterized in that at least one sealing element, whose coefficient of thermal expansion at an operating temperature of the laser spark plug is greater than the coefficient of thermal expansion of the casing part at the operating temperature of the laser spark plug, is provided between the casing part and the combustion chamber window.

A casing for a laser spark plug, in particular, of an internal combustion engine of a motor vehicle, or of a stationary engine; the casing including at least one casing part and a combustion chamber window joined to the casing part to form a seal at least regionally; characterized in that at least one sealing element, whose coefficient of thermal expansion at an operating temperature of the laser spark plug is greater than the coefficient of thermal expansion of the casing part at the operating temperature of the laser spark plug, is provided between the casing part and the combustion chamber window.

A coated body includes a body (1) with a body surface (3) and a coating system (20) deposited on at least a portion of the body surface (3). The coating system (20) includes at least one hard friction reducing coating deposited as an outermost layer (9) which exhibits droplets (10) at its surface. The outermost layer (9) includes molybdenum copper nitride and/or molybdenum nitride and copper nitride, and at least some of the droplets (10) consist mainly of copper. Preferably most of the largest droplets (10) consist mainly of copper.

A hardware configuration and related variable control strategy is disclosed that accepts an electric power input typical of space flight systems and converts that energy into a spark pulse train with variable performance metrics for the following system parameters: time to first spark, peak breakdown voltage amplitude, spark repetition rate and energy delivered per spark, which have all been optimally chosen to reliably ignite certain fuel mixtures and which have been proven to be beneficial for use in aerospace applications.