| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244175000 | Electric course control | 89 |
| 20100012789 | Vortex detection and turbulence measurement - A vortex detection device suitable for use in fighter aircraft including an angle-of-attack sensor, an angle-of-attack processing unit connected to the angle-of-attack sensor capable of forming a signal representative of current air stream's angle-of-attack, a synthetic angle-of-attack estimation unit capable of forming a synthetic angle-of-attack signal, and a vortex level calculation unit connected to the processing and estimation unit, capable of calculating a vortex level signal, and a vortex detection unit connected to the vortex level calculation unit, for deciding, based on the vortex level signal, if a vortex is detected. | 01-21-2010 |
| 20100102173 | Light Aircraft Stabilization System - Control systems, controllers, systems, and methods of stabilizing a light aircraft during flight and/or ground maneuvers, such as by detecting and/or correcting undesired yaw characteristic, such as, for example, yaw angle, yaw rate, and/or yaw fluctuations. | 04-29-2010 |
| 20100181431 | FLIGHT ASSISTANCE APPARATUS - A flight assistance apparatus for providing assistance in flying an aircraft, including: a yoke operated by a pilot of the aircraft; and a flight instruction section that instructs, with an aid of the yoke, the pilot to fly the aircraft in such a manner as to avoid a critical flight range when the aircraft approaches the critical flight range. | 07-22-2010 |
| 20100230546 | CONTROL SYSTEM AND CONTROL METHOD FOR AIRBORNE FLIGHT - A control system and method for control of a cyclical flying system which uses lift segments, which may be airfoils, which rotate around a central hub, similar to the mechanics of an autogyro. The airfoils may achieve speeds significantly above the wind speed feeding the system. The airfoils may be linked to the central hub by flexible radial tethers which stiffen considerably as the speed of the airfoil increases. The central hub may be linked to the ground with an extendible main tether. Power generation turbines may reside on the airfoils and utilize the high apparent wind speed for power generation. The generated power may travel down the radial tethers and across a rotating power conduit to the main tether and to the ground. The airborne assembly may have the rotational speed of the airfoils, its altitude, and its attitude controlled by using control surfaces linked to the airfoils, or by control of the angle of attack of the airfoils relative to a central hub, or relative to each other. The attitude and altitude sensors and the control system may be airborne and may be part of the rotating assembly. The airborne assembly can be moved to areas of appropriate wind speed for the system using these controls. | 09-16-2010 |
| 20100282916 | Four-Dimensional Guidance of an Aircraft - The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position. | 11-11-2010 |
| 20110057074 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 03-10-2011 |
| 20120181388 | Unmanned Aerial Vehicle Drag Augmentation by Reverse Propeller Rotation - An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal. | 07-19-2012 |
| 20120199698 | UNMANNED AIR VEHICLE (UAV), CONTROL SYSTEM AND METHOD - A gust-insensitive unmanned air vehicle (UAV) for imaging the ground, comprising a substantially neutrally stable air frame having a fuselage and at least three wings which include control surfaces. The wings are arranged in symmetrical relation about the fuselage and confer the UAV with a roll stability about a longitudinal axis of the fuselage for any roll angle. The UAV also includes a propulsion device for propelling the UAV in flight, an image sensor for imaging the ground, and a flight control system for controlling the in-flight operation of the UAV. The flight control system includes flight control sensors and is operative to render the UAV gust insensitive in response to inputs from the flight control sensors. | 08-09-2012 |
| 20120248254 | METHOD OF COMMUNICATION ON AN AIRCRAFT OR A SPACECRAFT, VIA THE OUTSIDE ENVIRONMENT - In the method of communication on a vehicle including an aircraft or a spacecraft, the vehicle transmits an electromagnetic signal from at least one transmitter on-board the vehicle directly to at least one receiver on-board the vehicle and with transmission taking place solely through an environment outside the vehicle. Transmission takes place several times over, and during transmission at least one member from the group including the transmitter and the receiver is set into movement relative to a support in direct contact with the member and with a portion of the vehicle carrying the member. | 10-04-2012 |
| 20120280087 | Unmanned Aerial Vehicle Control Using a Gamepad - In accordance with particular embodiments, a system includes a path creation module configured to create future flight paths for unmanned aerial vehicles (UAVs). Each future flight path comprises one or more branch points marking changes in the UAV's flight path. The system also includes a display that is configured to present a graphical user interface that may include a 3D view of a geographic area; flight paths; and a menu of commands. The system also includes a gamepad that may include two thumb-sticks to adjust the displayed geographic area and the perspective of the displayed geographic area. The gamepad also includes time buttons configured to scroll through a flight time that begins with a current actual time and ends with the end of the UAV's flight. The gamepad further includes buttons configured to select a command from the menu and to select a first future flight path of the one or more future flight paths to be sent to the UAV. | 11-08-2012 |
| 20130043353 | LENTICULAR AIRSHIP AND ASSOCIATED CONTROLS - A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each configured to provide a thrust associated with the airship, and a yaw control configured to receive an input indicative of a desired yaw angle. The system may further include a controller communicatively connected to the yaw control, the one or more vertical control surfaces, and the first and second power sources. The controller may be configured to receive an output signal from the yaw control corresponding to the desired yaw angle and to generate a control signal configured to modify a state associated with at least one of the one or more vertical control surfaces, the first power source, and the second power source, such that the airship substantially attains the desired yaw angle. | 02-21-2013 |
| 20140027579 | HAND LAUNCHABLE UNMANNED AERIAL VEHICLE - An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder. | 01-30-2014 |
| 20140166816 | AUTOMATED HAZARD HANDLING ROUTINE ENGAGEMENT - Disclosed herein are example embodiments for automated hazard handling routine engagement. For certain example embodiments, at least one machine, such as an unoccupied flying vehicle (UFV), may: (i) detect at least one motivation to engage at least one automated hazard handling routine of the UFV; or (ii) engage at least one automated hazard handling routine of a UFV based at least partially on at least one motivation. However, claimed subject matter is not limited to any particular described embodiments, implementations, examples, or so forth. | 06-19-2014 |
| 20140231590 | AERIAL DISPLAY SYSTEM WITH MARIONETTES ARTICULATED AND SUPPORTED BY AIRBORNE DEVICES - A system for performing an aerial display. The system includes a plurality of unmanned aerial vehicles (UAVs) and a ground control system with a processor executing a fleet manager module and with memory storing a different flight plan for each of the UAVs. The system further includes a marionette with a body and articulatable appendages attached to the body. The body and appendages are supported with tether lines extending between the marionette and the UAVs. Then, during a display time period, the UAVs concurrently execute the flight plans to position and articulate the marionette within a display air space. In some embodiments, the UAVs each is a multicopter, and each of the multicopters includes a local controller operating to move the multicopter through a series of way points defined by the flight plan associated with the multicopter. | 08-21-2014 |
| 20140231591 | AIRCRAFT AND CONTROL METHOD THEREFOR - An aircraft is provided with: an attitude control command calculating section which calculates an attitude control command for target attitude on the basis of a control stick operation amount; a gain value generating section which generates a gain value equal to or less than 1 which decreases as the control stick operation amount is larger; a multiplication section which multiplies the attitude control command for target attitude by the gain value; and a addition section which adds a rate damping control command to the attitude control command for target attitude multiplied by the gain value and outputs a result to a subtraction section for calculating an SAS command. | 08-21-2014 |
| 20140284429 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 09-25-2014 |
| 20140346280 | System And Method For Controlling An Aircraft - A system for controlling an aircraft control parameter including a control interface including a mobile element configured to move on a travel, of which at least two portions are separated by a neutral position; a return element bringing the mobile element back to the neutral position when it is not actuated; and an interaction element, and a control unit configured to memorize an item of information corresponding to a first position of the mobile element at an instant of activation of the interaction element; and generate a setpoint of the aircraft control parameter, as a function of a control associated with the first position of the mobile element for which said information has been memorized; or a current position of the mobile element, when this current position is situated on the same portion of travel as the first position and is more remote than the latter from the neutral position. | 11-27-2014 |
| 20150021441 | REDUNDANT CURRENT-SUM FEEDBACK ACTUATOR - A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current. | 01-22-2015 |
| 20150053824 | UNMANNED AIRCRAFT WITH FAILSAFE SYSTEM - An unmanned aircraft comprises:
| 02-26-2015 |
| 20150060606 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | 03-05-2015 |
| 20150097086 | AIRBORNE WIND ENERGY CONVERSION SYSTEMS, DEVICES, AND METHODS - Wind energy conversion systems including an airborne wing, a tether, a generator, and a control system arranged to communicate with the airborne wing so that the control system directs the airborne wing to follow a predetermined flight path including a power generating phase. The predetermined flight path, during the power generating phase, includes a crosswind flight path of increasing altitude and a plurality of airborne wing turns, at each turn the airborne wing turn around an axis of the airborne wing, so that a vertical airspace for the predetermined flight path during the power generating phase is minimized. | 04-09-2015 |
| 20150360771 | FLY BY WIRE SERVOS WITH INTERNAL LOOP CLOSURE - Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude. | 12-17-2015 |
| 20150375852 | Plastic Optical Fiber for Reliable Low-Cost Avionic Networks - An airborne wind turbine system including an aerial vehicle having a main wing, an electrically conductive tether having a first end secured to the aerial vehicle and a second end secured to a ground station, a plurality of power generating turbines connected to the main wing, a communication network positioned with the aerial vehicle, including a first flight control computer, and first plastic optical fiber signal transmission lines extending between the first flight control computer and the plurality of power generating turbines. | 12-31-2015 |
| 244177000 | Multiple-axis altitude stabilization | 5 |
| 20130082148 | Aircraft Guidance Method and System - A system and method for steering aircraft along a predetermined track is disclosed herein. The system and method relate to steering an aircraft along a lateral path (e.g. a track described by reference to latitude and longitude) by a method comprising: calculating a nominal track correction; providing an upper limit and a lower limit for the nominal track correction; setting a desired track correction as: (i) the nominal track correction if the nominal track is between the upper limit and the lower limit; (ii) the upper limit if the nominal track correction is greater than or equal to the upper limit; or (iii) the lower limit if the nominal track correction is less than or equal to the lower limit; and steering the aircraft using the desired track correction. | 04-04-2013 |
| 20160152330 | ROTORCRAFT AUTOPILOT AND METHODS | 06-02-2016 |
| 244178000 | Trim control | 3 |
| 20090065648 | COMPENSATION ACTUATOR FOR A ROTORCRAFT FLIGHT CONTROL - The invention relates to an actuator ( | 03-12-2009 |
| 20090283642 | BREAKABLE COUPLING DEVICE, AND AN ASSOCIATED TRIM ACTUATOR - A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque. | 11-19-2009 |
| 20100123045 | DEVICE FOR SWITCHABLE PILOT CONTROL FORCES - A device for controlling vehicles having a manual control unit configured to influence the direction of movement of a vehicle. The manual control unit provides, in a neutral position of the manual control unit, a trim point to determine a preferred direction of movement. The device further includes a force generating device, generating at least one force acting in the direction of the neutral position of the manual control unit; a trim coupling operable to reduce the at least one force acting on the manual control unit; and a trim control unit configured to store and retain the trim point existing prior to an operation of the trim coupling. | 05-20-2010 |
| 244180000 | By change in altitude | 4 |
| 20090314896 | AIRCRAFT PILOTING METHOD AND DEVICE FOR PICKING UP A VERTICAL PROFILE OF A FLIGHT PLAN - An aircraft piloting method and device for picking up a vertical profile of a flight plan. | 12-24-2009 |
| 20130221164 | METHOD FOR FLYING AN AIRCRAFT ALONG A FLIGHT PATH - A method of flying an aircraft, where the aircraft has an associated performance envelope, along a flight path based determining an altitude profile for a cruise-climb along the flight path based on the performance envelope of the aircraft and flying the aircraft along the flight path to approximate the altitude profile. | 08-29-2013 |
| 244182000 | By change in speed | 2 |
| 20080308681 | Autodrag Function for Glide Slope Control - Systems and methods for providing supplemental drag to an aircraft are disclosed. In one embodiment, a method includes detecting changes in at least one throttle resolver angle (TRA). Deflections are determined for one or more flight control surfaces based on the changes in TRA, and accordingly, the one or more flight control surfaces are deflected automatically to generate supplemental drag. The one or more flight control surfaces include at least one at least one of an aileron, a spoiler, and an elevator. Additionally, in one instance, the deflections of the one or more flight control surfaces is implemented as a rated limited time lag function of the changes in TRA. | 12-18-2008 |
| 20080308682 | Automatic Velocity Control System For Aircraft - A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal. | 12-18-2008 |
| 244183000 | Of aircraft on its landing course | 12 |
| 20090152403 | METHOD FOR PILOTING AN AIRCRAFT IN APPROACH PHASE - According to the invention, high lift Leading-edge slats ( | 06-18-2009 |
| 20100219298 | METHOD AND DEVICE FOR GENERATING AN OPTIMUM AERODYNAMIC CONFIGURATION OF AN AIRCRAFT DURING A FLIGHT - A process and device for the automatic flight optimisation of the aerodynamic configuration of an aircraft. | 09-02-2010 |
| 20110006164 | SYSTEM FOR AUTOMATIC OR PILOT CONTROLLED LANDING OF AIR VEHICLE - A system for automatic or auto pilot controlled landing of air vehicle ( | 01-13-2011 |
| 20110057075 | METHOD FOR VERTICAL TAKEOFF FROM AND LANDING ON INCLINED SURFACES - Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces. | 03-10-2011 |
| 20110121140 | AUTOMATIC TAKEOFF APPARATUS FOR AIRCRAFT, AUTOMATIC LANDING APPARATUS FOR AIRCRAFT, AUTOMATIC TAKEOFF AND LANDING APPARATUS FOR AIRCRAFT, AUTOMATIC TAKEOFF METHOD FOR AIRCRAFT, AUTOMATIC LANDING METHOD FOR AIRCRAFT AND AUTOMATIC TAKEOFF AND LANDING METHOD FOR AIRCRAFT - An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude. | 05-26-2011 |
| 20120261516 | LADAR SENSOR FOR LANDING, DOCKING AND APPROACH - A system for landing or docking a mobile platform is enabled by a flash LADAR sensor having an adaptive controller with Automatic Gain Control (AGC). Range gating in the LADAR sensor penetrates through diffuse reflectors. The LADAR sensor adapted for landing/approach comprises a system controller, pulsed laser transmitter, transmit optics, receive optics, a focal plane array of detectors, a readout integrated circuit, camera support electronics and image processor, an image analysis and bias calculation processor, and a detector array bias control circuit. The system is capable of developing a complete | 10-18-2012 |
| 20130001366 | LANDING SYSTEM - A system for landing a VTOL aircraft on a landing platform, comprises a) a net, positioned in a plane substantially parallel to the plane of the landing platform; b) proximity sensors suitable to provide data indicative of the distance and orientation of the aircraft from said net; c) sensors suitable to gauge environmental conditions relevant to the landing of the aircraft; and d) control apparatus to control the speed at which the aircraft approaches said net. | 01-03-2013 |
| 244186000 | Vertical glide path control | 5 |
| 20090050746 | METHOD AND DEVICE FOR AUTOMATICALLY PROTECTING AN AIRCRAFT AGAINST A HARD LANDING - Method and device for automatically protecting an aircraft against a hard landing. | 02-26-2009 |
| 20090314897 | PROCEDURE AND DEVICE FOR IMPROVING THE MANEUVERABILITY OF AN AIRCRAFT DURING THE APPROACH TO LANDING AND FLARE-OUT PHASES - The process improves the maneuverability of an aircraft during the approach to landing and then flare-out phases, the aircraft being equipped with air brakes. According to the process, the air brakes are put in a first deployed position during the approach phase, and as a function of a representative parameter of a given altitude and in case of a steep angle approach, they are actuated to transition to a second more retracted position than the first position so as to achieve a flare-out allowing to essentially maintain the same angle of incidence, corresponding in case of a steep angle approach to achieve a flare-out with habitual exterior piloting references during the flare-out phase. | 12-24-2009 |
| 20130009013 | PARAFOIL ELECTRONIC CONTROL UNIT HAVING WIRELESS CONNECTIVITY - A method is described that includes performing a), b) and c) below with an electronic control unit of a parafoil: a) after being dropped from an airborne vehicle, wirelessly receiving the parafoil's desired landing location; b) determining a flight path for the parafoil that lands at the desired landing location; and, c) controlling the parafoil's flight path consistently with the determined flight path. | 01-10-2013 |
| 20160147232 | UNMANNED AERIAL VEHICLE DRAG AUGMENTATION BY REVERSE PROPELLER ROTATION - An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal. | 05-26-2016 |
| 244188000 | Slope control by throttle | 1 |
| 20140353432 | UNMANNED AERIAL VEHICLE DRAG AUGMENTATION BY REVERSE PROPELLER ROTATION - An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal. | 12-04-2014 |
| 244189000 | By remote radio signal | 20 |
| 20120061521 | SYSTEM AND METHOD FOR TRANSFERRING AIRPLANES - An airplane transfer system for transferring an airplane comprising an airplane control component. The system comprises: a transfer module comprising at least one motor and adapted to transfer an airplane; and a controller coupled to the transfer module and configured to: i) receive a at least one transfer signal that is responsive to one or more commands provided via the airplane control component; and ii) control the transfer module in response to the transfer signal, wherein the commands are a priori capable of controlling the airplane or components thereof. | 03-15-2012 |
| 20120256055 | AIRCRAFT ROTARY WING MOTION CONTROL AND INSTRUMENTED MOTION CONTROL FLUID DEVICE - An aircraft rotary wing motion control fluid device providing motion control and with wireless sensing of at least one fluid property inside the fluid device is provided. The wireless sensing system is integrated with at least one of the first and second aircraft rotary wing motion control fluid device bodies. The wireless sensing system includes at least one fluid property sensor in sensing proximity to the at least one fluid chamber and a communications device for wirelessly conveying a measurement made by the at least one fluid property sensor to a remote location. | 10-11-2012 |
| 20130009014 | INSTANTANEOUS WIRELESS NETWORK ESTABLISHED BY SIMULTANEOUSLY DESCENDING PARAFOILS - A method is described that involves establishing a wireless network between a wireless access node of an existing network and a remote location by wirelessly linking a plurality of electronic processing circuits each transported by a respective parafoil. The wirelessly linked processing circuits are to route packets from the wireless access node to the remote location. | 01-10-2013 |
| 20130306800 | FLIGHT GUIDANCE SYSTEM - The invention relates to a flight guidance system for the flight support of a aircraft ( | 11-21-2013 |
| 244190000 | Of pilotless aircraft | 16 |
| 20080203231 | Control apparatus of wireless remote-control model and operating parameter setup system thereof - A control apparatus of a wireless remote-control model and its operating parameter setup system is set up and changed by a personal computer, and various settings of setup information are transmitted to a wireless remote-control helicopter through a communication line, and control parameters are stored in a set value storage module of a memory, such that control parameters for the movement characteristics of a wireless remote-control model can be set up or changed easily to reduce the burden on the side of a signal transmitter. | 08-28-2008 |
| 20090050747 | Remote control model aircraft with laser tag shooting action - The present invention is a radio-controlled (RC) model aircraft system with laser tag capabilities. A transmitter and receiver are each installed in at least two separate RC aircrafts. The transmitter on one aircraft emits an infrared light beam to the receiver on the other aircraft(s) that changes the infrared signal to a first servo to move an arm, which releases a model aircraft door behind which there are ribbons. The ribbons escape from the aircraft wings to show a hit. An optional second servo operate a smoke screen and eject a pilot to simulate actual combat. The system may also include audio and lighting effects to simulate firing and hit sequences with accompanying theatrical, physical effects including release of smoke and ribbons, and ejection of the pilot that realistically simulates air combat. | 02-26-2009 |
| 20090108140 | Checklist Administration System for a Vehicle - According to one embodiment, code embodied in a computer readable storage medium is configured to generate a checklist for a vehicle by receiving a measured value obtained from at least one sensor configured on the vehicle, setting a parameter value that is associated with the at least one sensor to the measured value, and displaying the checklist on a user interface. The checklist has a number of parameter fields associated with various operating characteristics of the vehicle. | 04-30-2009 |
| 20100084513 | METHOD AND SYSTEM FOR DIRECTING UNMANNED VEHICLES - A method of remotely controlling an aerial vehicle within an environment, including providing a control station in communication with the aerial vehicle, providing a map of the environment, receiving target world coordinates for the aerial vehicle within the environment, determining a desired velocity vector to direct the aerial vehicle to the target world coordinates at a speed proportional to the distance between the aerial vehicle and the target world coordinates, and directing the aerial vehicle along the desired velocity vector until the aerial vehicle reaches the target world coordinates. | 04-08-2010 |
| 20100224732 | WIRELESSLY CONTROLLING UNMANNED AIRCRAFT AND ACCESSING ASSOCIATED SURVEILLANCE DATA - Controlling an unmanned aerial vehicle (UAV) may be accomplished by using a wireless device (e.g., cell phone) to send a control message to a receiver at the UAV via a wireless telecommunication network (e.g., an existing cellular network configured primarily for mobile telephone communication). In addition, the wireless device may be used to receive communications from a transmitter at the UAV, wherein the wireless device receives the communications from the transmitter via the wireless network. Examples of such communications include surveillance information and UAV monitoring information. | 09-09-2010 |
| 20100237199 | ADJUSTABLE SERVOMECHANISM ASSEMBLIES AND ASSOCIATED SYSTEMS AND METHODS - Adjustable servomechanism assemblies and associated systems and methods are disclosed herein. An unmanned aircraft system in accordance with one embodiment of the disclosure includes a movable mechanism and a servomechanism assembly operably coupled to the movable mechanism. The system also includes an interface assembly operably coupled to an output shaft of the servo and the movable mechanism. The interface assembly includes an adapter portion carried by the output shaft and an output arm releasably engaged with the adapter portion. The adapter portion includes a first aperture having a non-round surface mated with a non-round surface of the output shaft, and a generally smooth, non-splined, engagement surface. The output arm includes a second aperture sized to receive at least a portion of the outer surface of the adapter portion. The second aperture includes generally smooth inner surface in contact with and rotatable through 360 degrees relative to the engagement surface of the adapter portion. | 09-23-2010 |
| 20110204187 | Homeostatic Flying Hovercraft - A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control. | 08-25-2011 |
| 20120175468 | Remote Controlled Drone Aircraft to Mist and Cool Roofs - A system for delivering cooling water to building roofs by means of drone aircraft is disclosed. Control systems for navigation and precisely targeting a water spray are disclosed. | 07-12-2012 |
| 20130068892 | FLYING APPARATUS FOR AERIAL AGRICULTURAL APPLICATION - A remotely controlled flying apparatus ( | 03-21-2013 |
| 20130126679 | SYSTEM AND METHODS FOR SITUATION AWARENESS, ADVISORY, TRACKING, AND AIRCRAFT CONTROL INFORMATION - A portable device for presenting situation awareness information is provided. The portable device is operable onboard an aircraft and includes a communications module configured to communicate with a data center to receive situation awareness information that includes at least a real-time position for each of a plurality of additional aircraft, a sensor module configured to determine a real-time position of the portable device, and a display device configured to overlay a moving map display with the situation awareness information and the real-time position of the portable device. | 05-23-2013 |
| 20130248656 | INTEGRATED WAFER SCALE, HIGH DATA RATE, WIRELESS REPEATER PLACED ON FIXED OR MOBILE ELEVATED PLATFORMS - Methods and systems are provided for relocatable repeaters for wireless communication links to locations that may present accessibility problems using, for example, small unmanned aerial systems (sUAS). An sUAS implemented as an easy-to-operate, small vertical take-off and landing (VTOL) aircraft with hovering capability for holding station position may provide an extended range, highly secure, high data rate, repeater system for extending the range of point-to-point wireless communication links (also referred to as “crosslinks”) in which repeater locations are easily relocatable with very fast set-up and relocating times. A repeater system using beam forming and power combining techniques enables a very high gain antenna array with very narrow beam width and superb pointing accuracy. The aircraft includes a control system enabling three-dimensional pointing and sustaining directivity of the beam independently of flight path of the aircraft. | 09-26-2013 |
| 20140166817 | INTER-VEHICLE COMMUNICATION FOR HAZARD HANDLING FOR AN UNOCCUPIED FLYING VEHICLE (UFV) - Disclosed herein are example embodiments for inter-vehicle communication for hazard handling with an unoccupied flying vehicle (UFV). For certain example embodiments, at least one machine may: (i) receive one or more flight attributes from a remote UFV, with the one or more flight attributes indicative of one or more flight characteristics of the remote UFV; or (ii) adjust a flight path of a UFV based at least partially on one or more flight attributes received from a remote UFV. However, claimed subject matter is not limited to any particular described embodiments, implementations, examples, or so forth. | 06-19-2014 |
| 20140246545 | Aerial material distribution apparatus - An aircraft for distributing granular material on a target area is provided. The aircraft includes an electric sifter, which includes a motor to distribute the granular material on the target area and a screen on the bottom surface of the electric sifter. The screen allows the granular material to pass through the screen to the target area. The aircraft also includes a circuit to activate the motor, one or more power sources to power the motor and the circuit, and an interface for an operator to control the circuit. The granular material is stored in the electric sifter. The operator manipulates the interface to signal the circuit to activate the motor. The electric sifter distributes the granular material when the motor is activated. | 09-04-2014 |
| 20150041596 | Aerial material distribution method and apparatus - A remotely-piloted aircraft for distributing a payload to a target area is provided. The aircraft includes an enclosure, which includes a top lid covering the top, an internal compartment to store the payload, a bottom surface, and a distribution apparatus to allow the payload to pass through the bottom surface. The aircraft also includes a circuit to control the distribution apparatus, a wireless receiver, to receive commands to activate and inactivate the distribution apparatus, and one or more power sources coupled to the distribution apparatus and the wireless receiver. The one or more power sources provide electrical power to the distribution apparatus and the wireless receiver. An operator controls the aircraft and the circuit with at least one of a wireless transmitter and an uploaded program in the circuit. When the wireless receiver receives a command to activate the distribution apparatus, the distribution apparatus distributes the payload from the enclosure. | 02-12-2015 |
| 20150122950 | Aerial beneficial insect distribution vehicle - A remotely-piloted aircraft for distributing beneficial insects on a target area is provided. The aircraft includes an enclosure, including a top lid, one or more internal compartments, a door for each of the one or more internal compartments, and an actuator to open and close each of the doors. The aircraft also includes a circuit to control the actuators, a wireless receiver, coupled to the circuit, to receive commands to open and close the doors, and one or more power sources to power the actuators and the wireless receiver. An operator controls the aircraft and the circuit with at least one of a wireless transmitter and an uploaded program in the circuit. When the wireless receiver receives a command to open a door, the circuit controls an actuator corresponding to the door. The actuator opens the door, and the beneficial insects are distributed from internal compartments. | 05-07-2015 |
| 20160052649 | FAIL-SAFE COMMAND DESTRUCT SYSTEM - A fail safe command destruct system for a multi-stage rocket comprising a first stage flight termination system and an upper stage command enable system. The flight termination system has the added feature that the same battery is the sole power source to the flight termination receiver and to a normally off flight inhibitor that requires power to permit engine operation. The command enable system has a normally inhibiting flight inhibitor that requires power to permit engine operation. The same battery is the sole source of power to the command enable receiver and the flight inhibitor such that battery failure prevents engine ignition. Lack of a command from outside the rocket to the command enable receiver also prevents engine ignition. | 02-25-2016 |
| 244194000 | Monitoring circuit or response | 17 |
| 20090020651 | METHOD AND DEVICE FOR PILOTING AN AIRCRAFT ABOUT A PILOTING AXIS - The flight-control device ( | 01-22-2009 |
| 20090152404 | LIMITED AUTHORITY AND FULL AUTHORITY MODE FLY-BY-WIRE FLIGHT CONTROL SURFACE ACTUATION CONTROL SYSTEM - An aircraft flight control surface actuation control system includes an actuator control unit and a flight control module. The actuator control unit includes at least two independent actuator control channels to generate limited authority flight control surface actuator commands based on pilot inceptor position signals and flight control augmentation data. The flight control module supplies the flight control augmentation data to each of the independent actuator control channels, determines operability of each of the actuator control channels and, based on the determined operability of each independent actuator control channel, selectively prevents one of the independent actuator control channels from supplying the limited authority flight control surface actuator commands. The flight control module may also generate full authority flight control surface actuator commands for supply to flight control surface actuators. | 06-18-2009 |
| 20100044518 | METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT - A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed. | 02-25-2010 |
| 20100288886 | Aircraft High Lift System and Method for Determining an Operating Condition of an Aircraft High Lift System - The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system. | 11-18-2010 |
| 20100301170 | CONTROL SYSTEM FOR ACTUATION SYSTEM - A method for controlling a plant assembly includes providing a plant assembly having a first plant including a first sensor that monitors the first plant. The plant assembly further includes a second plant in communication with the first plant. The second plant includes a second sensor that monitors the second plant. The method further includes providing a controller that is adapted to control the plant assembly. An outer control loop of the controller receives a setpoint and a feedback signal, which is provided by the second sensor. A first control output signal is communicated from the outer control loop to an inner control loop of the controller. The inner control loop receives the first control output signal and a feedback signal, which is provided by the first sensor of the first plant. An output signal is provided to the first plant. | 12-02-2010 |
| 20110084173 | METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT - A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed. | 04-14-2011 |
| 20110210210 | Secure Monitoring and Control Device for Aircraft Piloting Actuator - A monitoring and control device for an aircraft actuator includes a control module, delivering control signals for the actuator and position signals for the actuator determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning the position of the actuator, and a monitoring module, delivering position signals for the actuator and receiving the control signals received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor. The control and monitoring modules are capable of assessing the consistency of the signals processed therein and of controlling accordingly a power supply and disabling module of the actuator. | 09-01-2011 |
| 20110248121 | Apparatus and Method for Backup Control in a Distributed Flight Control System - Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid. The remote electronics unit may be configured to output an actuator command based on the primary control signal if the primary control signal is available and valid and to output the actuator command based on the backup control signal if the primary control signal is unavailable or invalid. | 10-13-2011 |
| 20130068893 | CONTROL SURFACE ELEMENT SKEW AND / OR LOSS DETECTION SYSTEM - A control surface element skew and/or loss detection system ( | 03-21-2013 |
| 20130087660 | DEVICE FOR ASSISTING THE PILOTING OF A ROTORCRAFT - A device for assisting the piloting of a rotorcraft, the rotorcraft having a flight control ( | 04-11-2013 |
| 20130233975 | METHOD AND APPARATUS FOR IMPROVED LATERAL CONTROL OF AN AIRCRAFT ON THE GROUND DURING TAKEOFF - A method and apparatus for carrying out a symmetric deflection of the spoilers so as to reduce the lift of the aircraft during a takeoff roll thereby improving lateral and directional control on the ground. | 09-12-2013 |
| 244195000 | Self-adaptive control | 6 |
| 20080283671 | ENGINE ANTICIPATION FOR ROTARY-WING AIRCRAFT - A flight control system and method which determines an expected power required data in response to a flight control command of the at least one model following control law and utilizes the expected power required data to perform at least one action to control an engine speed. | 11-20-2008 |
| 20090127400 | ADAPTIVE CONTROL IN THE PRESENCE OF INPUT CONSTRAINTS - An adaptive control system is provided that scales both gain and commands to avoid input saturation. The input saturation occurs when a commanded input u | 05-21-2009 |
| 20090200430 | INTELLIGENT MULTIFUNCTIONAL ACTUATION SYSTEM FOR VIBRATION AND BUFFET SUPPRESSION - Circuits and methods for use on a mobile platform including a flight control system, a structure, an aerodynamic surface, and an actuator operatively coupled to the surface to control the surface. The circuit includes a first and a second input, a summing element, and an output. The first input accepts commands from the flight control system while the second input accepts a vibration signal from the structure. The summing element communicates with the inputs and sums the signal and the command. In turn, the summing element controls the actuator with the summed signal and command. | 08-13-2009 |
| 20110108671 | FLIGHT CONTROL SURFACE ACTUATION FORCE FIGHT MITIGATION SYSTEM AND METHOD - A system and method of mitigating a force fight between hydraulically-operated actuators that are coupled to a single flight control surface is provided. The differential fluid pressure across each hydraulically-operated actuator is sensed. The position of a user interface is sensed using a plurality of user interface position sensors. Flight control surface position is sensed using one or more position sensors. The sensed differential pressures, the sensed user interface positions, and the sensed flight control surface position are used to generate a plurality of substantially equal actuator commands. | 05-12-2011 |
| 20120298806 | CONTROL SYSTEM OF AIRCRAFT, METHOD FOR CONTROLLING AIRCRAFT, AND AIRCRAFT - Stable flight can be achieved without the need for a complicated throttle operation by a pilot even when part or all of control surfaces malfunction. A computation means ( | 11-29-2012 |
| 20130026298 | ACTUATOR FORCE EQUALIZATION CONTROLLER - An actuation system including a plurality of actuators; a plurality of position sensors coupled to the actuators, the plurality of position sensors providing rate feedback signals proportional to an actuator rate; a plurality of force sensors coupled to the actuators, the plurality of force sensors providing delta pressure signals; and a feedback control loop configured to receive the rate feedback signals and delta pressure signals and compute a difference in actual actuator rates and sum the difference with a computed difference in actuator forces to generate actuator positioning commands that equalize the actuator forces on a control surface. | 01-31-2013 |
| 244196000 | Override of automatic control by human pilot | 8 |
| 20100258678 | AIRCRAFT STALL PROTECTION SYSTEM - A stall protection system for use with an aircraft may have at least one sensor configured to provide an indication of a pressure differential associated with airflow across an airfoil, and a controller in communication with the at least one sensor. The controller may be configured to compare the pressure differential to a pressure differential threshold associated with a stall condition of the airfoil, and to selectively generate a recovery response signal based on the comparison. | 10-14-2010 |
| 20120241563 | EMERGENCY PILOTING BY MEANS OF A SERIES ACTUATOR FOR A MANUAL FLIGHT CONTROL SYSTEM IN AN AIRCRAFT - For emergency piloting of a manual flight control system ( | 09-27-2012 |
| 20130075535 | ELECTRICAL RUDDER CONTROL SYSTEM FOR AN AIRCRAFT - The rudder control system ( | 03-28-2013 |
| 20140332633 | EMERGENCY COLLECTIVE ACTUATOR AND METHOD FOR A HELICOPTER - A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force. | 11-13-2014 |
| 20150329199 | CONTROL INTERFACE, SYSTEM AND METHOD - A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations. | 11-19-2015 |
| 20160251078 | EMERGENCY COLLECTIVE ACTUATOR AND METHOD FOR A HELICOPTER | 09-01-2016 |
| 244197000 | By engaging manual control system | 2 |
| 20120097800 | LINE REPLACEABLE, FLY-BY-WIRE CONTROL COLUMNS WITH PUSH-PULL INTERCONNECT RODS - A control input system is provided. The system includes a pair of control columns that are selectively interconnected such that manipulation of one of the control columns is translated to the other one of the control columns. The system includes a disconnect arrangement for each of the degrees of freedom (pitch and roll) of the system that operably disconnects the two control columns such that the two control columns can operate independently such as in the event of failure of one of the control columns. The system may also include a discontinuous force profile for a restoring force mechanism that provides tactile feedback to the pilots simulating resistance provided by control surfaces of the aircraft. The system may also include an autopilot lockout mechanism that increases the force profile experienced by the pilots when autopilot mode is entered. | 04-26-2012 |
| 20160185448 | CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT - A control system and method for an aircraft configured to operate according to a first mode of operation corresponding to an automatic piloting of the aircraft and a second mode of operation corresponding to a manual piloting of the aircraft, the system including a selection member. The system is configured to operate according to the first mode of operation when the selection member is not actuated continuously and to operate according to the second mode of operation when the selection member is actuated continuously. | 06-30-2016 |
