Abstract: A system and method for testing no-back systems. In one embodiment, the system and method includes multiple actuators that are driven in an asynchronous manner as to impart internal forces that mimic external loads on the system. The actuators can be monitored to determine whether the no-back systems are performing as expected when loads are applied to the actuators.

Abstract: A themed aerial vehicle entertainment system or platform useful for generating crowd-pleasing shows or displays through the use of dynamically-coordinated show systems. Instead of use of a fixed flight plan, the new entertainment platform is configured to include one or more UAVs that is enclosed within or supports thematic cladding such as the outer shell of a spacecraft or flying character, and the show is dynamically coordinated to present a cohesive performance. Onboard show effects provided by onboard or UAV supported show system components such as high brightness lights are dynamically adjusted in the new system/platform to ensure the best show appearance to the audience while providing safer operations. The dynamic adjustments may involve selecting or generating a second script or “B show” in a contingent manner based on the current location or timing of movement of the UAV along a flight plan.

Abstract: The present disclosure provides a geomagnetic positioning device, comprising a base assembly and a connecting assembly. The base assembly comprises a control component, a driving component, and a first geomagnetic component. The control component is electrically connected with the driving component and the first geomagnetic component. The connecting assembly is disposed at the driving component and comprises a second geomagnetic component. Wherein the control component obtains the deviation angle of the second geomagnetic component relative to the first geomagnetic component. The control component controls the driving component according to the deviation angle to adjust the relative angle of the connecting assembly relative to the base assembly.

Abstract: A method for performing one or more tasks on a surface via an unmanned aerial vehicle (UAV) or aerial robotics system (ARS) includes tethering a first UAV to a ceiling, a vertical wall, or a second UAV via a tethering cord with an extendible and retractable length, performing at least one task via the first UAV to an object during flight of the first UAV, sensing at least one parameter of the surface of the object via a task sensor, and resiliently adjusting an adjustable sensor arm of the first UAV to facilitate performance of the task(s). The adjustable sensor arm may support the task sensor and be resilient to impact forces caused by direct contact of the task sensor or the adjustable sensor arm with the surface. The tethering cord may be extended or retracted via at least one motor while the first UAV performs the task(s).

Abstract: A method for controlling a thrust vectored aircraft includes mapping aircraft control commands with a flight controller through a number of transformations including: transforming, with the flight controller, a command space into an inner-mixing space, which comprises of at least a pair of two orthogonal force components located at each thrusting motor; transforming, with the flight controller, the inner-mixing space into an outer-mixing space, which comprises a thrust angle and thrust magnitude pair located at each thrusting motor; and generating output commands with the flight controller.

Abstract: Systems and methods for path planning by creating a three dimensional weighted graph representing a physical area wherein the third dimension comprise planes, wherein each plane represents a time unit, further wherein nodes can be connected only between different planes.

Abstract: Methods, systems and apparatus, including computer programs encoded on computer storage media for unmanned aerial vehicle flight operations near physical structures or objects. In particular, a point cloud of the physical structure is generated using aerial images of the structure. The point cloud is then referenced to determine a flight path for the UAV to follow around the physical structure, determine whether a planned flight path to desired locations around the structure is possible, determine the fastest route to return home and land from a given position around the physical structure, determine possibility of inflight collision to surface represented in point cloud, or determine an orientation of a fixed or gimballed camera given a position of the UAV relative the point cloud.

Abstract: The present invention relates to a hydrofoil system the includes a controller; a foil for engagement with the waterborne vessel, the foil comprising a plurality of adjustment members operable to vary the lift characteristics of the waterborne vessel; a propeller; an engine and gearbox located adjacent the foil and operable/in mechanical communication with the propeller; a plurality of sensors in electrical communication with the controller, each sensor configured to monitor flight parameters of the waterborne vessel and generate measured flight parameter data; wherein the controller is in communication with the adjustment members, the engine and the sensors and wherein the controller is configured to receive measured flight parameter data from the sensors and to control the operation of the engine and the position of the adjustment members in dependence upon the received measured flight parameter data. Further provided is a waterborne vessel including such a hydrofoil system.

Abstract: An alternative piloting system arranged to be integrated in a pre-existing aircraft that includes original systems having flight control and autopilot systems.

Abstract: A braking unit includes a braking means and means, configured to receive power from a power line, for engaging and disengaging the braking means. A first power signal line is provided that is connected to the means for engaging and disengaging said braking means and a second power signal line is also provided that is connected to said means for engaging and disengaging said braking means. The first power signal line is connected to the means for engaging and disengaging the braking means via a first power switching device and the second power signal line is connected to the means for engaging and disengaging the braking means via a second power switching device.

Abstract: To facilitate improved Controller-Pilot Data Link Communication (CPDLC) interfacing, report messages can be automatically armed and displayed in a threaded message format in the same message panel with other CPDLC messages between a vehicle and a ground system. Upon determining that a report is needed based on an uplink CPDLC message from the ground system, a report message label is displayed on the CPDLC message panel. Once the report is ready, it is automatically armed and the report message label indicates to the operator that the report message is ready to be sent. The operator can also select the report message label in the message panel to display the report message.

Abstract: A mission monitor for planning non-scheduled flight plan operations during a flight such that a user or the system may direct the aircraft to a safe position if the pilot or aircraft cease to perform as planned. Upon user selection or a triggering event the mission monitor may select and cause the aircraft to fly a determined best course of action at any particular point inflight. The mission monitor may remotely and wirelessly receive flight, pilot, aircraft, and operator information. In some implementations mission monitor features may be distributed between individual modules. In one embodiment the system determines current aircraft configuration against an expected aircraft configuration to detect configuration errors, and then utilize configuration errors and error trends to manage aircraft configuration and mission operation. The system may divert the aircraft to the best available landing sites or reconfigure the aircraft to resolve configuration errors.

Abstract: In an aspect an apparatus for encrypting external communication for an electric aircraft. The apparatus may comprise a communication component configured to communicate with a network node. The apparatus may also include a battery pack configured to power the electric aircraft and a battery sensor, wherein a battery senor is configured to generate battery datum. A computing device may be included within the apparatus. The computing device may be configured to be receive the battery datum, encrypt the battery datum using an encryption process, identify the network node and transmit the encrypted battery datum to the network node using the communication component.

Abstract: Systems and methods for an energy managed autoflight function that enables maneuvers previously done by the speed-on-elevator modes to be achieved while maintaining the autoflight function in speed-on-throttle mode. An autoflight guidance algorithm and strategy replaces speed-on-elevator modes with an automatic flight path angle (Auto-FPA) mode that can control speed-controlled climbs and descents. The autoflight guidance algorithm and strategy provide (i) autothrust and autoflight coordination during speed-on-throttle modes, (ii) and Auto-FPA control law or mode, (iii) the Auto-FPA control law being configurable for fixed thrust modes, and (iv) a speed protection monitoring scheme.

Abstract: The X-ray imaging system according to the present embodiment includes an X-ray tube, a holding assembly, a flying object, an X-ray detector, and processing circuitry, The X-ray tube is configured to emit X-rays. The holding assembly is configured to hold the X-ray tube. The flying object is equipped with the holding assembly. The X-ray detector is configured to detect the X-rays emitted by the X-ray tube. The processing circuitry is configured to control a flight of the flying object, and to control the flight of the flying object such that the X-ray tube is arranged on a predetermined position with respect to the X-ray detector.

Abstract: Provided is an unmanned aircraft that is used to quickly and accurately specify a target location and operate a specific mechanism having a predetermined function at the target location. An unmanned aircraft 100 refers to a target location marker pattern 120d3 representing an appearance of a target location marker 161 disposed to have a predetermined relative position relationship with the target location, detects an image portion corresponding to the target location marker 161 from an image obtained by a camera 106 that obtains the image below the unmanned aircraft 100, and is guided directly above the target location, based on the image portion, where the specific mechanism is operated.

Abstract: A missile controller guides a missile along a flight path to a stationary or moving target object. The missile controller has at least one side-looking sensor, configured to record surroundings data and has a field of view aligned transverse to the longitudinal axis of the missile, and a control unit having a reception unit for receiving target object data regarding the target object. The target object data containing position data, orientation data and/or speed data of the target object. The control unit is configured to set the orientation of the missile during the guidance at least partly based on the received target object data such that the target object is located in the field of view of the side-looking sensor at least in sections of a final guidance phase.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: An electromechanical rudder system control using electromagnetic actuators provides dual redundancy to comply with safety demands. Diversity of possible interconnection distribution allows the manufacturer to choose the proper configuration to satisfy aircraft safety design, hardware savings and overall system quality improvements. A dual channel rudder system architecture includes reconfigurable electronic controllers used to control plural electromechanical primary actuators for rudder control, and a distribution of aircraft and cockpit sensors through the electronic controllers to guarantee minimum required safety standards in case of loss of input data. The plural electromechanical actuators driving a rudder surface are arranged in independent and redundant load paths.

Abstract: Systems and methods for powering and controlling flight of an unmanned aerial vehicle are provided. The unmanned aerial vehicles can be used in a networked communication system. A tether management system can be used to facilitate both mobile and static tethered operation to provide power and/or voice and data communication.

Abstract: A UAV having a manual gimbal including a camera, and a flight mode selector configured to select both a flight mode and manually establish a camera position as a function of the selected fight mode. A controller responds to a position of the gimbal or selector to establish the flight mode. The flight mode is selected from several available modes, for example, a horizontal flight mode, a 45-degree flight mode, and a vertical (aerial) flight mode. The flight mode selector is mechanically coupled to the gimbal and establishes a pitch angle of the gimbal, and thus the camera angle attached to the gimbal.

Abstract: The method includes a step of acquisition of an image of the leading aircraft, a step of extraction of the outline, an adjustment step including implementing an outline registration algorithm, to determine an optimized profile from a comparison of the outline of the leading aircraft with a profile of the leading aircraft determined from a three-dimensional model of the leading aircraft and from an initial position of the following aircraft with respect to the leading aircraft, and a step of determination of the positioning according to six degrees of freedom of the following aircraft with respect to the leading aircraft, from the optimized profile and from the three-dimensional model of the leading aircraft. The method thus makes it possible to rapidly and accurately determine the positioning of the following aircraft with respect to the leading aircraft, this positioning being used to implement a formation flight.

Abstract: In one embodiment, method for determining capability boundary of a safety redundancy of an autonomous driving vehicle (ADV) includes obtaining a sensor layout associated with the ADV representing a system having a plurality of sensors mounted on a plurality of locations of the ADV. A zone failure risk of one or more sensors within the predetermined zones is estimated based on statistical operational data of the one or more sensors for each of the plurality of predetermined zones. An overall failure risk of the sensors is determined based on the zone failure risks of the predetermined zones based on relative locations of the sensors across the predetermined zones. A dynamic risk adjustment is determined based on the overall failure risk of the sensors, the dynamic risk adjustment representing a reliability of a sensor system associated with the ADV for estimating a safety of autonomous driving of the ADV.

Abstract: Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

Abstract: An aircraft and method of operating an aircraft include a flight formation control unit configured to automatically transition the aircraft into an automatic flight formation mode in response to the aircraft being within one or both of a predetermined speed or a predetermined range in relation to at least one other aircraft flying within the automatic flight formation mode. The flight formation control unit can be further configured to automatically transition the aircraft out of the automatic flight formation mode in response to detection of a control signal received from one or more flight controls of the aircraft. The flight formation control unit can be further configured to automatically cycle the aircraft and the at least one other aircraft to different positions during the automatic flight formation mode.

Abstract: Systems and methods for lag optimization of pilot intervention is provided. A critical event may be identified while an electric aircraft is in an autopilot mode and operating primarily under autonomous functions; as a result, a flight controller of the system may switch from an autopilot mode to a manual mode, allowing pilot intervention. System made determine a lag duration as a function of the critical event and a phase of operation of the electric aircraft to determine a lag duration before pilot intervention occurs.

Abstract: Tape layup systems and associated methods. A tape layup system includes a feed spool and an uptake spool. The feed spool is configured to carry a tape roll of tackifier tape that includes a tackifier material and a backing material, and the uptake spool is configured to carry a backing material roll of the backing material. The tape layup system further includes a torque transmission system configured to convey a torque from the feed spool to the uptake spool. The tape layup system is configured such that conveying a torque from the feed spool to the uptake spool operates to draw the backing material onto the backing material roll. A method of operating a tape layup system includes generating tension in a tackifier tape to rotate a feed spool and consequently rotating an uptake spool to draw a backing material onto a backing material roll.

Abstract: An apparatus for trace gas detection includes an unmanned aerial vehicle and a sensor package including an ambient environmental parameter sensor and a gas sensor for trace gas detection. A trace gas detection system includes two such unmanned aerial vehicles and a ground station all adapted for monitoring ambient environmental parameters and trace gas detection.

Abstract: An unmanned aircraft includes: at least two generators generating forces to fly the unmanned aircraft, each including a rotor blade generating an airflow; a sensor detecting a tilt of the unmanned aircraft; and a processor controlling the generators to control flight of the unmanned aircraft. The processor: obtains an output force adjustment trigger for the generators; obtaining the trigger, causes each generator to individually operate at least until the tilt of the unmanned aircraft detected by the sensor satisfies a predetermined condition; determines a reference value related to an output force of each generator from a value related to the output force of each generator when the tilt of the unmanned aircraft satisfies the predetermined condition and a positional relationship between the generators; and controls the flight of the unmanned aircraft, using the reference values determined.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: A method for operating a transport system for passenger transportation, including the following steps: providing a plurality of vertically taking-off and vertically landing aircraft for passengers; providing a plurality of handing facilities for the take-off and landing of aircraft, wherein each handling facility has parking spaces for a plurality of aircraft; setting-up air routes between the handing facilities so that each handing facility is connected to at least one further handling facility via an air route, wherein there is continuous air traffic of aircraft on the air routes, at least in one flight direction, with automated take-off, automated flight along the air routes, and automated landing.

Abstract: The present invention relates to a hydrofoil system for a waterborne vessel, the hydrofoil system comprising a controller, a foil for engagement with the waterborne vessel, the foil comprising a plurality of adjustment members operable to vary the lift characteristics of the waterborne vessel, a propeller, an engine and gearbox located adjacent the foil and operable/in mechanical communication with the propeller, a plurality of sensors in electrical communication with the controller, each sensor configured to monitor flight parameters of the waterborne vessel and generate measured flight parameter data, wherein the controller is in communication with the adjustment members, the engine and the sensors and wherein the controller is configured to receive measured flight parameter data from the sensors and to control the operation of the engine and the position of the adjustment members in dependence upon the received measured flight parameter data.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

Abstract: A system and apparatus for assisting in determining the best course of action at any point inflight for an emergency. The system may monitor a plurality of parameters including atmospheric conditions along the flight path, ground conditions and terrain, conditions aboard the aircraft, and pilot/crew data. Based on these parameters, the system may provide continually updated information about the best available landing sites or recommend solutions to aircraft configuration errors. In case of emergency, the system may provide a pilot with a procedure for execution for landing the aircraft.

Abstract: An engine vibration monitoring and control system includes an aircraft autopilot and a flight management system (FMS). The FMS is in operable communication with the aircraft autopilot and is configured to determine when the aircraft autopilot is engaged and disengaged. The FMS is also adapted to receive vibration data from an engine vibration data source and is configured, upon determining that the aircraft autopilot is engaged, to: process the vibration data to determine when engine vibrations exceed one or more first thresholds, and when the engine vibrations exceed the one or more first thresholds, supply commands to the autopilot that cause the autopilot to take corrective actions to reduce the engine vibrations below the one or more first thresholds.

Abstract: The present disclosure provides systems and methods for predicting ground effects along a flight plan. The systems and methods provide a processor executed process including the steps: receiving a flight plan for a vertical take-off and landing (VTOL) aircraft; receiving terrain and obstacles geospatial data for the flight plan from the database; determining weight of the VTOL aircraft along the flight plan; determining temperature of the environment along the flight plan; determining ground effect data along the flight plan based on the temperature and the weight; and generating one or more commands to control a system of the VTOL aircraft based on the ground effect data.

Abstract: In an aspect an apparatus for encrypting external communication for an electric aircraft. The apparatus may comprise a communication component configured to communicate with a network node. The apparatus may also include a battery pack configured to power the electric aircraft and a battery sensor, wherein a battery senor is configured to generate battery datum. A computing device may be included within the apparatus. The computing device may be configured to be receive the battery datum, encrypt the battery datum using an encryption process, identify the network node and transmit the encrypted battery datum to the network node using the communication component.

Abstract: In an embodiment, a system includes a frame configured to support a load, a first set of wheels provided on the frame, a second set of wheels provided on the frame, and a controller. The first set of wheels is configured to descend or ascend in response to the controller, and is oriented to move in a first direction. The second set of wheels is configured to descent or ascend in response to the controller, and is oriented to move in a different direction from the first direction. The controller configured to control the descent and ascent of the second set of wheels and the first set of wheels.

Abstract: An optimal-route generating system for generating an optimal route for achieving a predetermined state relative to a target includes a route candidate generator and an optimal route generator. The route candidate generator is configured to generate a plurality of route candidates for allowing a first craft to reach a predetermined state relative to the target after a predetermined elapsed time period from a current state of the first craft by changing the acceleration of the first craft among a current position, speed, and acceleration of the first craft. The optimal route generator is configured to generate the optimal route by selecting a route candidate with an optimal evaluation result based on an evaluation function from among route candidates, included in the plurality of generated route candidates, not deviating from a predetermined limitation and unlikely to collide with another object including either one of a ground and the target.

Abstract: A mechanical synchronization device for a distributed system. A plurality of actuators actuate movement of control surface components of an aircraft. Each actuator has a first end coupled to a structure of the aircraft and a second end coupled to a control surface component, and a drive path from a motion provider to the control surface component, the control surface component being configured to move along the respective drive path. A power module controller is operable to simultaneously output motor drive power from a power module through an electrical bus to at least two of the motion providers in a synchronous or nearly synchronous manner to actuate movement of control surface components. The mechanical synchronization device is between at least two of the actuators and transfers torque between the actuators to maintain symmetry between the actuators. A load limiting device may limit the power transferred through the mechanical synchronization device.

Abstract: An underwater vehicle having a hovering system using a tube type launcher. The underwater vehicle includes a streamlined body and a hovering system connected to a rear of the streamlined body to generate a kinetic force of the streamlined body. The hovering system includes an extension shaft extended to be connected to the rear, a connection assembly connected to the rear through the extension shaft, and an auxiliary propeller assembly connected to the connection assembly.

Abstract: Systems and methods for lag optimization of pilot intervention is provided. A critical event may be identified while an electric aircraft is in an autopilot mode and operating primarily under autonomous functions; as a result, a flight controller of the system may switch from an autopilot mode to a manual mode, allowing pilot intervention. System made determine a lag duration as a function of the critical event and a phase of operation of the electric aircraft to determine a lag duration before pilot intervention occurs.

Abstract: A drone is provided that includes a controller, a time measurer that measures a present time, a position measurer that obtains a current position of the drone, and a storage that stores a time period for which the flight of the drone is permitted. The controller performs operations including determining a possible flight area of the drone in accordance with a difference between an end of the time period for which flight of the drone is permitted and the present time, and determining whether the drone is located within the possible flight area on the basis of the current position of the drone.

Abstract: The present invention relates to a director mount arrangement for automatic alignment of a subsystem relative to a platform, wherein said director mount arrangement is arranged to pivotably support the subsystem. The director mount arrangement comprises a pivot frame arrangement and a control system. The control system comprises a control unit arranged to generate control signals so as to control the orientation of and stabilize the subsystem. The control signals are generated based on angular rate of subsystem and orientation operating commands provided from an operator. The control unit further generates estimated control signals based on platform orientation information and determine a difference between the control signals and the estimated control signals, wherein the difference is indicative of mechanical misalignments between the subsystem and the platform.

Abstract: A computer apparatus includes a touchscreen display. The computer apparatus generates a graphical user interface on the touchscreen display and receive user inputs via the touchscreen display. The graphical user interface includes symbology representing a flight path of multiple unmanned teamed assets from a current position to a current objective. The graphical user interface also includes symbology representing a card associated with each of the unmanned teamed assets. By the touchscreen display, an operator selects one of the unmanned teamed assets, for emphasis of the flight path. The flight paths of the non-selected unmanned teamed assets remain displayed when the selected flight path is emphasized. The operator may select the unmanned teamed asset by the flight path or by the unmanned teamed asset card.

Abstract: A method for determining an optimized trajectory to be followed by an aircraft, the method being implemented by a determining system of the aircraft and comprising: a first step for acquiring at least one constraint relative to at least one parameter of the trajectory to be followed, the constraint being determined by a control system of a remote station as a function of the air traffic and/or the aircraft mission; a step for calculating a desired trajectory as a function of the constraint; a step for transmitting the desired trajectory to the remote station; a second step for acquiring an instruction comprising an authorization to follow the desired trajectory or a refusal of the desired trajectory.

Abstract: A flying object (drone) has a propeller drive unit provided in a fuselage thereof, and flies through the air by being driven by the propeller drive unit. The drone has a gravitational center movement device which is provided in the upper section of the fuselage and is capable of moving the total gravitational center position of the entire drone. The drone is equipped with a movement controller which moves the total gravitational center position to a target position by acquiring the total gravitational center position and controlling operation of the gravitational center movement device.

Abstract: An airflow separation detecting method includes: applying an alternating-current voltage having a predetermined voltage value to a plasma actuator, the plasma actuator being disposed on a part of a surface of an object; and detecting that separation, from the surface of the object, of an airflow flowing on the surface of the object is occurring, in a case where an absolute value of a temporal variation rate of an electric power consumption value of the plasma actuator or an absolute value of a temporal variation rate of a current value of the plasma actuator is equal to or greater than a predetermined value, the temporal variation rate being a rate of variation relative to time, the electric power consumption value or the current value of the plasma actuator being measured under application of the alternating-current voltage having the predetermined voltage value to the plasma actuator.

Abstract: Innovative instrument holders used for minimally invasive surgical simulation and training are disclosed when used in conjunction with a smartphone, tablet or mini-tablet computer enabling visualization of the surgical field. The surgical field used with these instrument holders can include animal models, physical models, and both virtual and augmented reality models. Some embodiments can be used with applications that can be downloaded to the smartphone, tablet or mini-tablet computer in order to enhance specific hand-eye coordination tasks. Some embodiments can be used as an adjunct surgical trainer for endoscopy, colonoscopy, and other minimally invasive gastrointestinal and gynecological surgical procedures using surgical instruments that incorporate fiber optics.