Abstract: A system includes a probe assembly, a camera, and a control system. The probe assembly includes a rigid substrate, a compliant layer provided on the rigid substrate, one or more rigid probes can be arranged on the compliant layer to cover at least a portion of the compliant layer, and a reflective layer can cover the one or more rigid probes and uncovered portions of the compliant layer. The camera is configured to generate image data from the probe assembly. The control system is configured to receive image data from the camera and develop a topographical image of a surface of a sample, based at least in part on the received image data.

Abstract: A system includes a probe assembly, a camera, and a control system. The probe assembly includes a rigid substrate, a compliant layer provided on the rigid substrate, one or more rigid probes can be arranged on the compliant layer to cover at least a portion of the compliant layer, and a reflective layer can cover the one or more rigid probes and uncovered portions of the compliant layer. The camera is configured to generate image data from the probe assembly. The control system is configured to receive image data from the camera and develop a topographical image of a surface of a sample, based at least in part on the received image data.

Abstract: A propulsion system for an orbiting vehicle such as a low-Earth orbit (LEO) satellite includes a set of surfaces over which a gas passes during orbital flight, and a plurality of electrodes on the surfaces. The electrodes are configured to create an electric field having a spatial field pattern in response to field signals, experienced by passing gas molecules as an oscillating field having a frequency on the order of a polarization-resonance frequency of the molecules to impart a propulsive traveling-wave dielectrophoretic force to the passing molecules. The electrodes extend over sufficient area to impart sufficient traveling-wave dielectrophoretic force to the gas to overcome aerodynamic drag and thereby sustain orbital flight of the vehicle. A power source applies the field signals to the electrodes, providing sufficient power to overcome power lost to aerodynamic drag and thereby sustain orbital flight.

Abstract: A propulsion system for an orbiting vehicle such as a low-Earth orbit (LEO) satellite includes a set of surfaces over which a gas passes during orbital flight, and a plurality of electrodes on the surfaces. The electrodes are configured to create an electric field having a spatial field pattern in response to field signals, experienced by passing gas molecules as an oscillating field having a frequency on the order of a polarization-resonance frequency of the molecules to impart a propulsive traveling-wave dielectrophoretic force to the passing molecules. The electrodes extend over sufficient area to impart sufficient traveling-wave dielectrophoretic force to the gas to overcome aerodynamic drag and thereby sustain orbital flight of the vehicle. A power source applies the field signals to the electrodes, providing sufficient power to overcome power lost to aerodynamic drag and thereby sustain orbital flight.