Abstract: A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, are placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft.

Abstract: A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, may be placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft. The MHD flow control mechanism may also be configured to provide additional thermal protection of the electrodes therein.

Abstract: A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, are placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft.

Abstract: Systems and methods for enhancing operations of an aircraft may include a plasma generator, a sensor, and a controller. The plasma generator may be positioned on an exterior of the aircraft such that it can provide localized heating thereon. The sensor may be configured to sense and transmit information regarding a transonic flight condition such as speed to the controller. The controller may be configured to activate the plasma generator in response to information from the sensor, so as to mitigate a transonic shock wave through localized heating.

Abstract: Systems and methods for enhancing operations of an aircraft may include a plasma generator, a sensor, and a controller. The plasma generator may be positioned on an exterior of the aircraft such that it can provide localized heating thereon. The sensor may be configured to sense and transmit information regarding a transonic flight condition such as speed to the controller. The controller may be configured to activate the plasma generator in response to information from the sensor, so as to mitigate a transonic shock wave through localized heating.

Abstract: Systems, methods and apparatus for harvesting atmospheric electricity are provided. The system includes a laser configured to form a plasma filament and a collector configured to collect electricity flowing along the plasma filament. The plasma filament comprises an electrically conducting plasma filament. Atmospheric electricity may be collected by having the plasma filament form at least a part of a conducting path: (1) between ground and a cloud, (2) between differently charged regions of the same cloud, (3) between differently charged regions of different clouds, and (4) between different regions of atmosphere, where there is a vertical voltage gradient. When the plasma filament is not long enough to form the entire conducting path, a lightning may be triggered to complete the conducting path needed to collect atmospheric electricity.

Abstract: A plasma-actuated vortex generator arrangement includes a plurality of spaced-apart vortex generators, and a plasma actuator distributed amongst the plurality of vortex generators.

Abstract: The present invention provides a method of obtaining a bright source of ions with narrow energy spread for focused ion beam applications using micro plasmas. As a preferred embodiment, a high pressure microplasma source operating in a normal glow discharge regime is used to produce a cold bright focused beam of Xe+ and/or Xe2+ ions having ion temperature of the order of 0.5-1 eV and a current density on the order of 0.1-1 A/cm2 or higher.

Abstract: A cross flow instability inhibiting assembly generates periodic aerodynamic disturbances on a swept wing. The cross flow instability inhibiting assembly is dynamic in that it can be selectively turned on and off as needed. The cross flow instability inhibiting assembly is a strip of material separating a set of electrodes from a set of electrodes. When energized, the fields created between the electrodes and electrodes create plasma disturbances around the electrodes. The electric fields and plasma create heating and body force disturbances on the air or surrounding fluid. These plasma generated disturbances disrupt development of unstable voriticity due to cross flow, inhibiting transition to turbulent flow of the wing to which it is attached. The electrodes may be connected to electrical power in series or they may be connected to an alternating configuration. The system allows for various uses based on the design of the wing and the conditions in which the host aircraft is flying.

Abstract: The present invention provides a method of obtaining a bright source of ions with narrow energy spread for focused ion beam applications using micro plasmas. As a preferred embodiment, a high pressure microplasma source operating in a normal glow discharge regime is used to produce a cold bright focused beam of Xe+ and/or Xe2+ ions having ion temperature of the order of 0.5-1 eV and a current density on the order of 0.1-1 A/cm2 or higher.

Abstract: A high pressure microplasma source operating in a normal glow discharge regime is used to produce a cold bright focused beam of Xe+ and/or Xe2+ ions having ion temperature of the order of 0.5-1 eV and a current density on the order of 0.1-1 A/cm2 or higher for focused ion beam applications.

Abstract: Systems, methods and apparatus for harvesting atmospheric electricity are provided. The system includes a laser configured to form a plasma filament and a collector configured to collect electricity flowing along the plasma filament. The plasma filament comprises an electrically conducting plasma filament. Atmospheric electricity may be collected by having the plasma filament form at least a part of a conducting path: (1) between ground and a cloud, (2) between differently charged regions of the same cloud, (3) between differently charged regions of different clouds, and (4) between different regions of atmosphere, where there is a vertical voltage gradient. When the plasma filament is not long enough to form the entire conducting path, a lightning may be triggered to complete the conducting path needed to collect atmospheric electricity.

Abstract: Systems and methods for enhancing operations of an aircraft may include a plasma generator, a sensor, and a controller. The plasma generator may be positioned on an exterior of the aircraft such that it can provide localized heating thereon. The sensor may be configured to sense and transmit information regarding a transonic flight condition such as speed to the controller. The controller may be configured to activate the plasma generator in response to information from the sensor, so as to mitigate a transonic shock wave through localized heating.

Abstract: A plasma-actuated vortex generator arrangement includes a plurality of spaced-apart vortex generators, and a plasma actuator distributed amongst the plurality of vortex generators.

Abstract: An object moving through a fluid uses plasma to keep turbulent mixing vortices associated with turbulent air away from the majority of the surface of the object. The plasma may be used to enhance physical riblets, or the plasma may create a virtual riblet.

Abstract: A cross flow instability inhibiting assembly generates periodic aerodynamic disturbances on a swept wing. The cross flow instability inhibiting assembly is dynamic in that it can be selectively turned on and off as needed. The cross flow instability inhibiting assembly is a strip of material separating a set of electrodes from a set of electrodes. When energized, the fields created between the electrodes and electrodes create plasma disturbances around the electrodes. The electric fields and plasma create heating and body force disturbances on the air or surrounding fluid. These plasma generated disturbances disrupt development of unstable voriticity due to cross flow, inhibiting transition to turbulent flow of the wing to which it is attached. The electrodes may be connected to electrical power in series or they may be connected to an alternating configuration. The system allows for various uses based on the design of the wing and the conditions in which the host aircraft is flying.

Abstract: An object moving through a fluid uses plasma to keep turbulent mixing vortices associated with turbulent air away from the majority of the surface of the object. The plasma may be used to enhance physical riblets, or the plasma may create a virtual riblet.

Abstract: Systems and methods for controlling flow with electrical pulses are disclosed. An aircraft system in accordance with one embodiment includes an aerodynamic body having a flow surface exposed to an adjacent air stream, and a flow control assembly that includes a first electrode positioned at least proximate to the flow surface and a second electrode positioned proximate to and spaced apart from the first electrode. A dielectric material can be positioned between the first and second electrodes, and a controller can be coupled to at least one of the electrodes, with the controller programmed with instructions to direct air-ionizing pulses to the electrode, and provide a generally steady-state signal to the electrode during intervals between the pulses.