Abstract: Systems and methods for enabling charged (ionized) air mass measurement for reliable air data computation onboard an aircraft. Ionic charge sensing may be used to derive air data having improved reliability. The systems and methods for ionic charge sensing employ an emitter electrode and two or more collector electrodes, which electrodes are disposed in proximity to the exterior skin of the aircraft and exposed to ambient air. The emitter electrode is positioned forward of the collector electrodes. The system further includes a solid-state ionic air data module that converts currents from the collector electrodes into air data parameter values. More specifically, the ionic air data module is configured to sense currents induced in the collector electrodes in response to corona discharge produced by the high-voltage emitter electrode.

Abstract: Systems include a test object that comprises a surface having a non-planar topographical feature, and an electrode comprising a non-linear segment that is proximate to the non-planar topographical feature of the surface of the test object. The electrode is positioned proximate to but not in contact with the surface of the test object such that the perpendicular distances between the electrode and the surface of the test object are uniform across the electrode. The electrode is further configured to (i) be translated across the surface of the test object while maintaining the perpendicular distances between the electrode and the surface of the test object, and (ii) impart a layer of charge across the surface of the test object when the test object is translated across the surface.

Abstract: A neutron generator includes a fuel source configured to provide a neutron-producing fuel. The neutron generator includes a plasma confinement device coupled to the fuel source and configured to generate a z-pinch of the neutron-producing fuel.

Abstract: A single-use neutron generator includes a power supply. The single-use neutron generator includes a fuel source configured to provide neutron-producing fuel. The single-use neutron generator includes a plasma confinement device coupled to the power supply and the fuel source and configured to generate a plasma pinch of the neutron-producing fuel. At least one component of the single-use neutron generator is configured for single use.

Abstract: A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

Abstract: A micro-hollow cathode discharge device. The device includes a first electrode layer comprising a first electrode. A hole is disposed in the first electrode layer. The device also includes a dielectric layer having a first surface that is disposed on the first electrode layer. The hole continues from the first electrode layer through the dielectric layer. The device also includes a semi-conducting layer disposed on a second surface of the dielectric layer opposite the first surface. The semi-conducting layer is a semiconductor material that spans across the hole such that the hole terminates at the semi-conducting layer. The device also includes a second electrode layer disposed on the semi-conducting layer opposite the dielectric layer.

Abstract: A plurality of magnetic field sensors, for example arranged in an array, is operative to measure changes in magnetic field strength proximate the surface(s) of a test structure. The test structure may approximate the geometry of an airplane fuselage, wing, or the like. An electric current is applied to the test structure, and the magnetic field sensors sense changes in a magnetic field caused by the current. A corresponding plurality of integrators convert the sensor outputs to magnetic field strength values. From the plurality of magnetic field strength values and corresponding sensor locations, a current density over the target surface is inferred.

Abstract: Systems include a test object that comprises a surface having a non-planar topographical feature, and an electrode comprising a non-linear segment that is proximate to the non-planar topographical feature of the surface of the test object. The electrode is positioned proximate to but not in contact with the surface of the test object such that the perpendicular distances between the electrode and the surface of the test object are uniform across the electrode. The electrode is further configured to (i) be translated across the surface of the test object while maintaining the perpendicular distances between the electrode and the surface of the test object, and (ii) impart a layer of charge across the surface of the test object when the test object is translated across the surface.

Abstract: A nondestructive bond strength testing method, including: coupling an expendable device to a structure under test, the expendable device including a patterned planar array of exploding bridge wires; simultaneously vaporizing the patterned planar array of exploding bridge wires by applying a pulse of electrical energy to the patterned planar array of exploding bridge wires; and sensing an initial disbonding signature of the structure under test.

Abstract: Laser amplification utilizing plasma confinement of a gas laser gain media is described. The gas laser gain media is compressed into plasma utilizing a self-reinforcing magnetic field referred to a plasma pinch (e.g., a flow stabilized z-pinch). In the plasma pinch, the gas laser gain media is compressed to a high density, which improves the gain of the media. An optical resonator partially surrounds the plasma pinch and utilizes the laser gain media compressed within the plasma pinch to generate an output of coherent light.

Abstract: Laser amplification utilizing plasma confinement of a gas laser gain media is described. The gas laser gain media is compressed into plasma utilizing a self-reinforcing magnetic field referred to a plasma pinch (e.g., a flow stabilized z-pinch). In the plasma pinch, the gas laser gain media is compressed to a high density, which improves the gain of the media. An optical resonator partially surrounds the plasma pinch and utilizes the laser gain media compressed within the plasma pinch to generate an output of coherent light.

Abstract: An example method for producing thrust includes injecting a neutral gas into a cavity between an outer electrode and an inner electrode of a thruster, ionizing the neutral gas within the cavity into a plasma, causing the plasma to form into a plasma arc between the end of the inner electrode and the exhaust orifice of the outer electrode, generating a magnetic field that applies pressure on the plasma arc, maintaining stability of the plasma arc, and exhausting the plasma arc out of the exhaust orifice based on the applied pressure of the magnetic field, thereby producing thrust.

Abstract: An example method for plasma cleaning a container includes generating plasma flowing within the container, applying a magnet to an exterior surface of the container causing the plasma within the container to be attracted to the magnet, and moving the magnet in a motion over the exterior surface to control movement of the plasma within the container and to clean one or more areas of the container with the plasma according to the motion. An example system for plasma cleaning a container includes a power source, a gas inlet on the container for dispersing a gas within the container, and based on current flowing, the gas converts to plasma. The system also includes a robotic manipulator having an end effector coupled to a magnet to move the magnet in a motion over an exterior surface of the container causing the plasma within the container to be attracted to the magnet.

Abstract: Propagating brush discharge testing systems include an initiation electrode, a high-voltage switch, a sensor, and a controller. The initiation electrode has an exposed tip positioned adjacent to a surface of a test article. The high-voltage switch is configured to selectively isolate the initiation electrode from ground potential. The sensor is positioned and configured to detect a propagating brush discharge between the initiation electrode and the test article. The controller is programmed to operate the high-voltage switch to ground the initiation electrode.

Abstract: A nondestructive bond strength testing method, including: coupling an expendable device to a structure under test, the expendable device including a patterned planar array of exploding bridge wires; simultaneously vaporizing the patterned planar array of exploding bridge wires by applying a pulse of electrical energy to the patterned planar array of exploding bridge wires; and sensing an initial disbonding signature of the structure under test.

Abstract: A method for placing electrical conductors interior to a composite structure prior to curing. A laminate stack is formed by assembling one or more composite layers, wherein the composite layers are pre-impregnated with a resin. One or more electrical conductors are placed on at least one of the composite layers prior to curing the laminate stack. One or more electrical insulators is optionally placed in proximity to one or more of the electrical conductors in at least one of the composite layers prior to curing the laminate stack. The laminate stack, including the composite layers, the electrical conductors, and the electrical insulators, is then cured to create the composite structure.

Abstract: A micro-hollow cathode discharge device. The device includes a first electrode layer comprising a first electrode. A hole is disposed in the first electrode layer. The device also includes a dielectric layer having a first surface that is disposed on the first electrode layer. The hole continues from the first electrode layer through the dielectric layer. The device also includes a semi-conducting layer disposed on a second surface of the dielectric layer opposite the first surface. The semi-conducting layer is a semiconductor material that spans across the hole such that the hole terminates at the semi-conducting layer. The device also includes a second electrode layer disposed on the semi-conducting layer opposite the dielectric layer.

Abstract: Propagating brush discharge testing systems include an initiation electrode, a high-voltage switch, a sensor, and a controller. The initiation electrode has an exposed tip positioned adjacent to a surface of a test article. The high-voltage switch is configured to selectively isolate the initiation electrode from ground potential. The sensor is positioned and configured to detect a propagating brush discharge between the initiation electrode and the test article. The controller is programmed to operate the high-voltage switch to ground the initiation electrode.

Abstract: A plurality of magnetic field sensors (26), for example arranged in an array (30), is operative to measure changes in magnetic field strength proximate the surface(s) (18, 24) of a test structure (10). The test structure (10) may approximate the geometry of an airplane fuselage, wing, or the like. An electric current is applied to the test structure (10), and the magnetic field sensors (26) sense changes in a magnetic field caused by the current. A corresponding plurality of integrators (32) convert the sensor (26) outputs to magnetic field strength values. From the plurality of magnetic field strength values and corresponding sensor locations (27), a current density over the target surface (10) is inferred.

Abstract: A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.