Abstract: A system for registering multiple point clouds captured by an aircraft is disclosed. The system includes a speckle generator, at least one three-dimensional (3D) scanner, and a processor coupled thereto. In operation, the speckle generator projects a laser speckle pattern onto a surface (e.g., a featureless surface). The at least one 3D scanner scans the featureless surface to generate a plurality of point clouds of the featureless surface and to image at least a portion of the laser speckle pattern. The processor, which is communicatively coupled with the at least one 3D scanner, registers the plurality of point clouds to generate a complete 3D model of the featureless surface based at least in part on the laser speckle pattern.

Abstract: A display device is described including a display panel for displaying an image and an input sensing unit disposed on the display panel for sensing a user input. The input sensing unit includes: an electrode unit including first electrodes and second electrodes which intersect each other and a control unit for determining the proximity of an object or the shape of the object, based on capacitance change values of the first electrodes and the second electrodes. In a first mode the input sensing unit is driven using a self-capacitance method. The control unit may merge the capacitance change values, and determine the proximity of the object based on the merged value. In a second mode based on mutual capacitance, the control unit may determine the shape of the object.

Abstract: An automated inspection system for monitoring a manufacturing process includes a core platform to operatively connect a plurality of systems or subsystems via one or more interfaces. A sensor system operatively coupled with the core platform to monitor one or more characteristics of a manufactured article. An actuation system operatively coupled with the core platform to implement the manufacturing process based on instruction from the core platform. The core platform is configured to receive a first measurement of the one or more characteristics of a composite article from the sensor system after application of a plurality of layers of one or more raw materials; receive data regarding a second measurement of the one or more characteristics from the sensor system after curing the composite article; and generate an alert in response to a determination that a defect exists in the composite article based on the first or second measurement.

Abstract: A display device is described including a display panel for displaying an image and an input sensing unit disposed on the display panel for sensing a user input. The input sensing unit includes: an electrode unit including first electrodes and second electrodes which intersect each other and a control unit for determining the proximity of an object or the shape of the object, based on capacitance change values of the first electrodes and the second electrodes. In a first mode the input sensing unit is driven using a self-capacitance method. The control unit may merge the capacitance change values, and determine the proximity of the object based on the merged value. In a second mode based on mutual capacitance, the control unit may determine the shape of the object.

Abstract: A system and method for tracking non-cooperative obstacles during operation of a vehicle is provided. The system may include a radar system, an optical sensor, and a processor. The radar system can be coupled to the vehicle and configured to scan a first airspace and generate radar information having a first resolution. The optical sensor can be coupled to the vehicle and configured to image a second airspace and generate optical information at a second resolution that is higher than the first resolution, where the second airspace is within said first airspace and includes a non-cooperative obstacle. The processor can be configured to identify the non-cooperative obstacle within the first airspace based at least in part on the radar information, and direct the optical sensor toward a location of the non-cooperative obstacle using the radar information.

Abstract: An input sensing unit may include the following elements: a first sensing electrode including first sensors and a first connector coupling the first sensors; a second sensing electrode including second sensors and a second connector coupling the second sensors; a first sensing line including first sensing line parts and a third connector coupling the first sensing line parts; a second sensing line; and an insulating layer including a first insulating side and a second insulating side opposite the first insulating side. The first sensing line parts may overlap the first sensors and may be disposed on the first insulating side. The second sensing line may overlap the second sensors and may be disposed on the first insulating side. The first sensors may be disposed on the second insulating side. The second sensors may be disposed on the second insulating side.

Abstract: A functional contactor is provided. A functional contactor according to an exemplary embodiment of the present invention comprises; a clip-shaped conductor having elasticity which is in electrical contact with a conductor of an electronic device; a functional element which is electrically connected to the clip-shaped conductor in series via a solder and comprises a first electrode and a second electrode respectively provided on the entire upper and lower surfaces thereof; and an arrangement guide which is formed to surround at least a part of the clip-shaped conductor on the upper surface of the functional element so as to arrange the position of the clip-shaped conductor and is made of nonconductive resin.

Abstract: The present invention is an aquifer storage and recovery system using a natural coagulant, in which in purifying raw water through aquifer storage and recovery, assimilable organic carbon (AOC) included in the raw water is effectively removed using a natural coagulant produced in the aquifer storage and recovery process, thereby reducing the time required to purify raw water by aquifer storage and recovery.

Abstract: The subject disclosure relates an aerial system to track a detected obstacle. The aerial system may comprise a plurality of aircraft, an aircraft storage system to house the plurality of aircraft, an aircraft controller in communication with each of a tracking system and the plurality of aircraft. In operation, one or more of the plurality of aircraft may engage the detected threat. At least one of the plurality of aircraft may include a target neutralization device to strike the detected threat.

Abstract: A touch panel includes first touch electrodes, second touch electrodes, and third touch electrodes. The first touch electrodes include sub electrodes spaced apart from one another in a first direction. The second touch electrodes extend in a second direction crossing the first direction. The second touch electrodes are spaced apart from one another in the first direction. The third touch electrodes extend in the second direction and are spaced apart from one another in the first direction. The third touch electrodes are shaped differently than the second touch electrodes.

Abstract: A LIDAR system for vehicle operation that can operate in degraded visual environments (DVE) is described. The LIDAR system may use a spatial light modulator to find the phase conjugate of the DVE being traversed by the laser beam and cancel out the backscatter from the DVE, which allows the detection of extremely small numbers of directly reflected photons reflected by a target surface. If the target is not detected, the LIDAR is iteratively scanned to its maximum available depth of focus until the target is acquired. The LIDAR system is especially useful for autonomous landing of VTOL aerial vehicles in locations where the target landing spot is approximately known but cannot be directly visualized due to DVE media, such as smoke, dust, fog, or the like.

Abstract: A stator structure and a gas turbine having the same are provided. The stator structure includes a plurality of rows of stators arranged on an inner peripheral surface of a casing, the stators being arranged alternately with a plurality of rows of blades arranged on an outer peripheral surface of a rotor, wherein each of the stators includes a vane including a first end and a second end, the first end of the vane being coupled to the inner peripheral surface of the casing by a first rotating member and a diaphragm coupled to the second end of the vane by a second rotating member. A first gap is formed between the first end of the vane and the inner peripheral surface of the casing, and a second gap is formed between the second end of the vane and the diaphragm. The vane may be provided with a slot part connected to the first and second ends of the vane to bypass a part of working fluid to the first and second gaps.

Abstract: The subject disclosure relates to a simulation system having an aircraft, a local wireless transceiver, and a simulation computer. The aircraft may include an onboard wireless transceiver and a flight controller operatively coupled with an onboard sensor payload to perceive a physical environment and to generate position and pose data. The simulation computer may be configured to communicate wirelessly with the aircraft via the local wireless transceiver. In operation, the simulation computer may be configured to generate one or more virtual reality sensor inputs and to receive the position and pose data from the aircraft. The simulation computer can be configured to transmit the one or more virtual reality sensor inputs to the flight controller of the aircraft.

Abstract: An input sensing unit may include the following elements: a first sensing electrode including first sensors and a first connector coupling the first sensors; a second sensing electrode including second sensors and a second connector coupling the second sensors; a first sensing line including first sensing line parts and a third connector coupling the first sensing line parts; a second sensing line; and an insulating layer including a first insulating side and a second insulating side opposite the first insulating side. The first sensing line parts may overlap the first sensors and may be disposed on the first insulating side. The second sensing line may overlap the second sensors and may be disposed on the first insulating side. The first sensors may be disposed on the second insulating side. The second sensors may be disposed on the second insulating side.

Abstract: The subject disclosure relates to a tracking system to mount to an aircraft and to image and track a target aircraft. The tracking system may include a structured light source operatively coupled to a processor, an inertial measurement unit (IMU) operatively coupled with the processor, a mirror to steer light from the light source toward the target aircraft, and a stereo-vision system having a first camera and a second camera. The IMU may be configured to generate position data representing a position of the aircraft. The stereo-vision system may be operatively coupled to the processor and configured to determine a 3D position of the target aircraft as a function of the position data. The processor may be configured to adjust the mirror position as a function of a mirror position.

Abstract: A touch panel includes first touch electrodes, second touch electrodes, and third touch electrodes. The first touch electrodes include sub electrodes spaced apart from one another in a first direction. The second touch electrodes extend in a second direction crossing the first direction. The second touch electrodes are spaced apart from one another in the first direction. The third touch electrodes extend in the second direction and are spaced apart from one another in the first direction. The third touch electrodes are shaped differently than the second touch electrodes.

Abstract: A workpiece manipulation system to provide high-precision manipulation of a workpiece by an aircraft. The workpiece manipulation system comprises a lifting mechanism to couple with the aircraft, an end-effector, and a processor. The lifting mechanism includes one or more joint actuators to extend or retract the lifting mechanism relative to the aircraft. The end-effector includes an end-effector actuator to control an operation of the end-effector to manipulate the workpiece. The processor is communicatively coupled with the aircraft processor and configured to control operation of the end-effector actuator and the one or more joint actuators. In operation, the processor provides feedback to the aircraft.

Abstract: The present disclosure is directed to scanning radar reflector systems, methods, and apparatuses; even more particularly to a system, method, and apparatus for scanning and reflecting a radar beam transmitted by a radar transmitter onboard an aerial vehicle with radar reflectors equipped on unmanned aerial vehicles. The radar reflection system may include one or more unmanned aerial vehicles equipped with a one or more axis gimbal upon which a radar reflector is mounted. A user may position the unmanned aerial vehicle and the radar reflector to target a specific region for radar scanning.

Abstract: A compressor vane is provided. The compressor vane may include a first surface directed toward air introduced into a compressor, a second surface directed in a direction opposite to the first surface, and two tangent lines in which the first and second surfaces meet, wherein a rate of change, with respect to a height of the compressor vane, of a maximum separation distance, between the first surface and the second surface, divided by a distance from one to the other of the two tangent lines in a cross-section at one position of the height of the compressor vane in a direction starting from a portion of the compressor vane closest to a center tie rod and toward a compressor housing varies with the height of the compressor vane away from the portion of the compressor vane closest to the center tie rod.

Abstract: The present disclosure is directed to scanning radar reflector systems, methods, and apparatuses; even more particularly to a system, method, and apparatus for scanning and reflecting a radar beam transmitted by a radar transmitter onboard an aerial vehicle with radar reflectors equipped on unmanned aerial vehicles. The radar reflection system may include one or more unmanned aerial vehicles equipped with a one or more axis gimbal upon which a radar reflector is mounted. A user may position the unmanned aerial vehicle and the radar reflector to target a specific region for radar scanning.