Monitoring Circuit Or Response Patents (Class 244/194)
  • Patent number: 10322816
    Abstract: Methods and systems for detecting skew in a wing slat of an aircraft are provided. At least one pair of sensors associated with the wing slat is excited via at least one first electronic device. In response to the exciting and at the at least one first electronic device, at least one pair of signals indicative of at least one pair of state-change counts for the at least one pair of sensors is obtained. The at least one pair of state-change counts is transmitted to at least one second electronic device communicatively coupled to the at least one first electronic device. At the at least one second electronic device, a skew level of the wing slat is determined based on the at least one pair of state-change counts.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: June 18, 2019
    Assignee: BOMBARDIER INC.
    Inventors: Robert Young, Waseem Wahba, Vlad Iliescu
  • Patent number: 10303381
    Abstract: A method having a safety sensor and a safety sensor having at least one first evaluation unit having a first evaluation program, and at least one second evaluation unit having a second evaluation program. A two-channel system is formed with each evaluation unit being connected to a respective random access memory, and with each evaluation unit having a respective program memory, with a bidirectional communication channel being arranged between the evaluation units. A cross-comparison of the evaluation results can be carried out between the evaluation units, with a user program being able to be stored in at least one of the two program memories and/or in one of the two random access memories, with at least that evaluation unit which executes the user program having a memory protection device which is configured to restrict memory access of the user program to a defined memory region within the random access memory.
    Type: Grant
    Filed: September 19, 2016
    Date of Patent: May 28, 2019
    Assignee: SICK AG
    Inventors: Felix Dreher, Patrick Vollmer
  • Patent number: 10296685
    Abstract: The present invention provides a failure logic modeling method for a high-speed railway train operation control on-board system, including the following steps: determining the functional relationship between the structure and the parts of the train control on-board system; analyzing the failures of the parts based on known failures of the train control on-board system in combination with brainstorming; establishing an FMEA table to generalize the failures of the parts; editing and simulating the failures by using a modeling tool. By adopting the present invention, the failure modes analyzed are more systematic, and the failure logic modeling can be carried out from a global perspective more easily, the whole process can be better targeted meanwhile, the security analysis complexity of the train control system will be effectively reduced and the development period of the train control system will be shortened.
    Type: Grant
    Filed: April 24, 2014
    Date of Patent: May 21, 2019
    Assignee: BEIJING JIAOTONG UNIVERSITY
    Inventors: Wei Zheng, Lingyun Yang, Weijie Kong, Dewang Ren, Lixiang Wang
  • Patent number: 10235819
    Abstract: Method and apparatus for calculating probabilities of service interruptions based on fault event indications. Instances of fault event indications are filtered to remove duplicate indications for the same fault event. Then a probability of the fault event indication causing a service interruption is calculated by dividing a number of service interruptions caused by instances of the fault event indication by the number of fault event indications. In the event that a particular fault event indication is associated with a high probability of causing a service interruption, a message can be automatically generated and transmitted upon receipt of a future instance of the service interruption. The message can provide information related to short-term solutions to address the fault event, long-term solutions to address the fault event, and parts and tools for addressing the fault event.
    Type: Grant
    Filed: October 20, 2017
    Date of Patent: March 19, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Jonathan Leung, Brian Pontrello, Roxanne Hirst, Cameron L. Carnegie, Rashed M. Noman, Johanne Friedrichs
  • Patent number: 10216561
    Abstract: A system includes a processor and a memory system in communication with the processor. The memory system stores instructions that when executed by the processor result in the system being operable to identify a system hazard boundary of a monitored system and a system nuisance boundary of the monitored system. The system is also operable to determine a must-trip condition based on the system hazard boundary and a must-not-trip condition based on the system nuisance boundary. The system is further operable to output a protection margin for the monitored system based on the system hazard boundary and a difference between the must-trip condition and the must-not-trip condition.
    Type: Grant
    Filed: April 20, 2015
    Date of Patent: February 26, 2019
    Assignees: C SERIES AIRCRAFT LIMITED PARTNERSHIP, BOMBARDIER INC.
    Inventors: Suleyman Tarkan Karsidag, Philippe Desy
  • Patent number: 10211073
    Abstract: A semiconductor chip has a first transistor that amplifies a first signal and outputs a second signal, a second transistor that amplifies the second signal and outputs a third signal, and a semiconductor substrate having a main surface parallel to a plane defined by first and second directions and which has the first and second transistors formed thereon. The main surface has thereon a first bump connected to a collector or drain of the first transistor, a second bump connected to an emitter or source of the first transistor, a third bump connected to a collector or drain of the second transistor, and a fourth bump connected to an emitter or source of the second transistor. The first bump is circular, the second through fourth bumps are rectangular or oval, and the area of each of the second through fourth bumps is larger than that of the first bump.
    Type: Grant
    Filed: December 20, 2017
    Date of Patent: February 19, 2019
    Assignee: Murata Manufacturing Co., Ltd.
    Inventor: Kenichi Shimamoto
  • Patent number: 10124882
    Abstract: 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.
    Type: Grant
    Filed: May 10, 2017
    Date of Patent: November 13, 2018
    Assignee: Merlin Technology Inc.
    Inventors: Carlos E. Golborne, Ray E. Debs, Mark Marvin, John E. Mercer
  • Patent number: 10101719
    Abstract: A flight control system is disclosed. In various embodiments, a flight control system includes a data storage device configured to store an aerodynamic model; and a processor coupled to the data storage device and configured to use the aerodynamic model to determine a set of actuators and for each actuator in the set a corresponding set of one or more actuator parameters to achieve a desired set of forces and moments. The aerodynamic model provides for each actuator in the set of actuator corresponding force and moment data for each of a first set of operating conditions based on a first set of simulations performed by varying one or more actuator parameters while holding other actuators at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions.
    Type: Grant
    Filed: December 12, 2017
    Date of Patent: October 16, 2018
    Assignee: Kitty Hawk Corporation
    Inventors: Ilan Kroo, Marshall Gusman, Neel Vora, Jim Bungener, Eric Allison
  • Patent number: 10101194
    Abstract: A sensor system for identifying a transient sensor failure in an industrial system and for recovering from an erroneous estimation of an expected mass flow rate resulting from the transient sensor failure. The sensor system includes one or more sensors for measuring at least one fluid property of the industrial system. The sensor system includes an enhanced flow soft sensing (EFSS) computing device configured to determine an estimated mass flow rate. The EFSS computing device is also configured to generate expected measurements to be received from one or more sensors. If an error value is not within predetermined parameters, the transient sensor failure is detected. The EFSS computing device is further configured to identify a resurgence of the sensor from the transient sensor failure. An erroneous expected mass flow rate then converges toward a correct expected mass flow rate.
    Type: Grant
    Filed: December 31, 2015
    Date of Patent: October 16, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Carlos Gonzaga, Luca Parolini
  • Patent number: 10082801
    Abstract: An input attitude associated with an input device of an aircraft is received. A supplemental attitude is generated, including by selecting a position-based supplemental attitude to be the supplemental attitude in the event the input device is in a disengaged state and selecting a velocity-based supplemental attitude to be the supplemental attitude in the event the input device is in an engaged state. The input attitude and the supplemental attitude are combined in order to obtain a combined attitude. The aircraft is controlled using the combined attitude.
    Type: Grant
    Filed: December 4, 2017
    Date of Patent: September 25, 2018
    Assignee: Kitty Hawk Corporation
    Inventors: Alexander David Selwa, Mark Johnson Cutler
  • Patent number: 10059463
    Abstract: A sensor system for a wing panel assembly of an aircraft includes a first end of a linkage assembly operatively coupled to a first slat panel. Also included is a second end of the linkage assembly operatively coupled to a second slat panel with a first ball joint. Further included is a block having a cutout portion surrounding the first ball joint. Yet further included is a sensing element disposed proximate the block to detect rotation of the block beyond a predetermined angle.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: August 28, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Michael Carbone, Scott C. Bonnett
  • Patent number: 10029782
    Abstract: An actuator system includes an actuator which is configured to generate a loading on a control surface, as a function of an actuation order received, a command unit of the actuator, which is configured to compute an actuation order of the actuator, a reception element for receiving a current value of the loading generated by the actuator, and a limitation unit configured to reduce the control authority of the command unit as a function of the current value of the loading and to limit the loading of the actuator to a predetermined setpoint value.
    Type: Grant
    Filed: April 9, 2015
    Date of Patent: July 24, 2018
    Assignee: Airbus Operations S.A.S.
    Inventors: Chiheb Kossentini, Nicholas Larrieu, Mathieu Delabre, Xavier Pol
  • Patent number: 10025307
    Abstract: A modular vehicle management system is described, comprising a controller module configured to control different types of carrier modules. The controller module includes a computer system and optionally one or more sensors. The computer system is configured to perform operations comprising detecting whether a carrier module is connected to the controller module. If the carrier module is connected to the controller module, the carrier module is authenticated. If the authentication fails, operation of the vehicle is inhibited. The control module is configured to determine carrier module capabilities including information regarding a navigation processing device, and/or a radio modem. The controller adapts to the capabilities of the controller module. Using information from the sensors and the navigation processing device, the vehicle management system navigates the vehicle.
    Type: Grant
    Filed: January 7, 2016
    Date of Patent: July 17, 2018
    Assignee: Unmanned Innovation, Inc.
    Inventors: Jonathan B. Downey, Bernard J. Michini
  • Patent number: 9988139
    Abstract: An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: June 5, 2018
    Assignee: Eaton Intelligent Power Limited
    Inventors: John David Neely, Stanley Lawrence Seely, John Mendenhall White
  • Patent number: 9977432
    Abstract: A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: May 22, 2018
    Assignee: Kitty Hawk Corporation
    Inventors: Mark Johnson Cutler, Todd Reichert, James Jackson
  • Patent number: 9951825
    Abstract: A multi-plate clutch apparatus is provided and includes a multi-plate clutch disposed to occupy clutch and non-clutch positions at which rotation of an input shaft is and is not transmitted to an output shaft, respectively, a drive element disposed about the multi-plate clutch and configured to generate rotational energy and a linear actuator disposed to convert the rotational energy of the drive element to linear movement by which the multi-plate clutch is controllable to occupy one of the clutch and non-clutch positions.
    Type: Grant
    Filed: June 24, 2014
    Date of Patent: April 24, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: David A. Darrow, Thomas L. Tully, Jr.
  • Patent number: 9944384
    Abstract: A method of controlling subsystems of an aircraft. During a preparation step, at least one global order is stored in a database, each global order including an eligibility condition, and at least one global order including an activation condition, each global order specifying a command sequence comprising at least two actions to be implemented one after another or in parallel by two different members. During an initialization step, an onboard computer determines whether a global order is selected automatically or by a pilot. During an activation step, an onboard computer determines, where appropriate, whether the selected global order is feasible. During an implementation step, and providing the selected global order is feasible, the onboard computer performs the actions specified by the selected global order.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: April 17, 2018
    Assignee: Airbus Helicopters
    Inventors: Arnaud Violette, Jean-Pierre Baudry
  • Patent number: 9891978
    Abstract: A system and method may ensure certified operation of a safety-critical avionics system incorporating a multi-core processor (MCP) aboard an aircraft via external architectural mitigation. A redundant processing element (RPE) may be associated with a processing core of the MCP and with safety-critical applications configured to execute on the core. The critical applications generate critical results based on sensed critical data parameters and pass the parameters and results to an external system monitor. The system monitor performs fault detection external to the original core by comparing the critical results and the critical data parameters and notifies the associated critical application if a fault is detected. The associated critical application may then log the fault to a fault history, reset an associated sensor, or notify the crew of the fault.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: February 13, 2018
    Assignee: Rockwell Collins, Inc.
    Inventors: Donald Mark Fejfar, Eric N. Anderson
  • Patent number: 9884686
    Abstract: An aircraft including a fuselage extending along a longitudinal axis and having a rear end pointing reward of the aircraft, a main gear connected to the fuselage in a main gear position with respect to the longitudinal axis, and an engine for propelling the aircraft provided outside of the fuselage and attached to the fuselage via an attachment device between the main gear position and the rear end, wherein the engine generates a repulsive air stream streaming in the reverse direction. A surface element is moveably connected to the attachment device. The surface element moves between a neutral position at which it does not deflect the repulsive air stream, and a deflected position at which it deflects the repulsive air stream to assist aircraft rotation during take-off.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: February 6, 2018
    Assignees: Airbus Operations GmbH, Airbus Operations (S.A.S.)
    Inventors: Bernd Trahmer, Mickael Lallemand, Damien Prat
  • Patent number: 9880021
    Abstract: Systems and methods for attitude fault detection in an inertial measurement unit (IMU) are disclosed. In one embodiment, an avionics system comprises: an IMU configured to produce a calculated pitch solution, a calculated roll solution, or both; a monitor coupled to the IMU and configured to produce an estimated pitch solution, an estimated roll solution, or both; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and a display device communicatively coupled to the comparator; wherein the display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: January 30, 2018
    Assignee: Honeywell International Inc.
    Inventors: Mats Anders Brenner, John R. Morrison
  • Patent number: 9802557
    Abstract: A method and an apparatus are provided for providing a vehicle component fault score. Faults that occur on vehicle components in a plurality of vehicles are tracked. One or more sets of attribute values are compiled for the tracked faults. A set of attribute values is collected for each item within one or more preset vehicle categories. A fault score is calculated for each set of the compiled attribute values. A set of one or more items with respective fault scores is displayed based on a preset vehicle category selected by a user.
    Type: Grant
    Filed: May 3, 2013
    Date of Patent: October 31, 2017
    Assignee: Clever Devices, Ltd
    Inventors: Kirk Alexander Shore, Philip P. Piazza
  • Patent number: 9772897
    Abstract: A processing subsystem for providing diagnostic of a processing system is provided. The processing subsystem includes a real-time processing unit that receives a first input that includes data from one or more sensors and processes the first input to generate first output that controls an actuator. The processing subsystem also includes a power and safety management unit that receives a second input and processes the second input to generate second output for testing of the first output. A method and a system for providing diagnostic for a processing system are provided as well.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: September 26, 2017
    Assignee: XILINX, INC.
    Inventors: Sagheer Ahmad, Giulio Corradi
  • Patent number: 9758236
    Abstract: A system that improves on known systems for reducing output torque by a motor in the event of a jam may include an electromechanical actuator (EMA), a motor configured to drive the EMA and a controller. The controller may be coupled to the motor and configured to receive a speed of the EMA and a position of the EMA. The controller may be further configured to determine whether a jam of the EMA is imminent or is occurring according to the EMA speed, EMA position, and a known range of motion of the EMA, and to provide an input signal to the motor to reduce a torque of the motor if a jam of the EMA is imminent or is occurring.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: September 12, 2017
    Assignee: Eaton Corporation
    Inventors: John David Neely, John Mendenhall White
  • Patent number: 9746851
    Abstract: According to various embodiments, the present invention relates to a platform and method for testing aircraft message trigger logics are disclosed. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (a Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: August 29, 2017
    Assignee: Air China Limited
    Inventors: Weixi Chai, Dechao Zhong, Xueliang Wu, Qixiang Li, Tang Li, Chengli Ouyang, Yuanbin Li, Wenjing Bi
  • Patent number: 9733135
    Abstract: A method and a device for automatically detecting an incorrect measurement of a total temperature on an aircraft. The detection device comprises several monitoring units configured to monitor the variations of the measured total temperature, provided by a temperature probe, and current values of the Mach number and of the altitude of the aircraft over a predetermined monitoring period of time, and a detection unit configured to detect an incorrect measurement of the total temperature when said monitoring units simultaneously detect particular conditions relative to said variations.
    Type: Grant
    Filed: April 14, 2014
    Date of Patent: August 15, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Julien Feau, Xavier Bousquet
  • Patent number: 9697655
    Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving signals that represent inertial forces experienced by the aircraft from an inertial sensor mounted in an aircraft. Identifying a pattern within the signals that represents a reduction of thrust on one side of the aircraft caused by an engine failure. Causing an indication within the aircraft to be activated in response to identifying the pattern, and thereby, alerting a pilot to a possible engine failure.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: July 4, 2017
    Inventor: Christopher Eyhorn
  • Patent number: 9688416
    Abstract: Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution; an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: June 27, 2017
    Assignee: Honeywell International Inc
    Inventors: Mark A. Ahlbrecht, Michael R. Ibis, John R. Morrison
  • Patent number: 9656764
    Abstract: A skew detection system for a high lift system for an aircraft, wherein pairs of sensors 4a, 4b with onboard data processing capabilities provide an onboard determination of relative skew between the sensors of each pair as an indication of skew of a flap of the high lift system.
    Type: Grant
    Filed: May 8, 2015
    Date of Patent: May 23, 2017
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventor: Tony Jones
  • Patent number: 9580189
    Abstract: The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to operate and move the control surface; an actuation mechanism configured to effect movement of the support frame between the second position and the first position; and a detection device for detecting a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a fault in the actuation mechanism.
    Type: Grant
    Filed: May 14, 2014
    Date of Patent: February 28, 2017
    Assignee: Airbus Operations GmbH
    Inventors: Michael Brady, Christoph Winkelmann
  • Patent number: 9567070
    Abstract: A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: February 14, 2017
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Ken Shundo, Carlos A. Fenny, Frank B. Stamps
  • Patent number: 9563523
    Abstract: An integrated fail-silence and fail-operational control system includes a primary controller controlling features of devices while operating under non-fault operating conditions. A secondary controller includes a fail detector/decider module monitoring faults in the primary controller. The fail detector/decider module determines whether the fault in the primary controller is associated with a fail-silence requirement or a fail-operational requirement. If the fail detector/decider module determines the fault is a fail-silence requirement, then the fail detector/decider module actuates a shutdown command to the primary controller to shut down a feature affected by the fault where the feature becomes non-operational. If the fail detector/decider module determines that the feature associated with the fault is a fail-operational requirement, then the fail detector/decider module signals the primary controller to relinquish controls of the feature to the secondary controller.
    Type: Grant
    Filed: April 16, 2015
    Date of Patent: February 7, 2017
    Assignee: GM Global Technology Operations LLC
    Inventors: Thomas E. Fuhrman, Soheil Samii
  • Patent number: 9527460
    Abstract: A modular rack intended for an aircraft includes a set of electrical machines each equipped with a position sensor including inverters, a supervision member, a first communication channel to transmit to each of the inverters the inverter setpoint determined by the supervision member, and a second communication channel to transmit a position information item to each of the inverters, each of the inverters including a way to generate an electrical signal as a function of the inverter setpoint and of the position information transmitted by the supervision member. The first and second communication channels include a single link for the supervision member and the inverters, and transmitting both the inverter setpoints and the position information items.
    Type: Grant
    Filed: January 17, 2014
    Date of Patent: December 27, 2016
    Assignee: Thales
    Inventors: Arnaud Dal, Stéphane Guguen, Tony Texeira
  • Patent number: 9503192
    Abstract: A data network, especially a data network for an aircraft or spacecraft, includes a primary data grid, and at least one secondary data grid, the primary data grid including primary data nodes, wherein the primary data nodes are directly or indirectly coupled in data communication with each other, and the at least one secondary data grid comprising secondary data nodes, wherein the at least one secondary data grid is configured to connect the secondary data nodes in a data communication chain and to connect the first secondary data node of the data communication chain to a first respective primary data node and/or the last secondary data node of the data communication chain to a second respective primary data node.
    Type: Grant
    Filed: November 7, 2014
    Date of Patent: November 22, 2016
    Assignees: Airbus Operations GmbH, Airbus Operations (S.A.S.)
    Inventors: Nicholas Brownjohn, Stefan Osternack, Stéphane Poulain, Xavier Valancogne, Nils Fischer
  • Patent number: 9494925
    Abstract: A hybrid control system and a method for predicting a behavior of a physical system using the hybrid control system is disclosed. The hybrid control system may include a model inverting control system capable of implementing a model inverting control law and determining an active set of goals and limits and a model predictive control system capable of implementing a model predictive control law and utilizing the active set of goals and limits to determine current effector requests, the current effector requests being used to control behavior of the physical system.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: November 15, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: James W. Fuller
  • Patent number: 9457890
    Abstract: A control device 20 for an aircraft steering apparatus controls an aircraft steering apparatus 1 comprising an operation unit including rudder pedals 4, a main pilot steering handle 2 and a co-pilot steering handle 3 which are provided in a cockpit of an aircraft, and an actuator 6 driven in accordance with an operation amount output from the operation unit for driving and steering at least a steered wheel 5, and the control device 20 includes a switching control unit 22 exclusively switches, based on instruction input from at least one of a main pilot and a co-pilot, which of operation amounts corresponding to operation of the rudder pedals 4, the main pilot steering handle 2 and the co-pilot steering handle 3 is used for driving the actuator 6.
    Type: Grant
    Filed: March 1, 2013
    Date of Patent: October 4, 2016
    Assignee: SUMITOMO PRECISION PRODUCTS CO., LTD.
    Inventors: Kazushi Furuichi, Kazunari Tada, Yutaro Minami
  • Patent number: 9459609
    Abstract: An actuator monitoring circuit 1 which is mounted in an airplane and monitors an actuator 30 having a piston (output portion) calculates the moving distance of the piston, and outputs, when the moving distance exceeds a predetermined threshold, an approaching notification signal 78s and a progression notification signal 79s to notify the excess over the threshold.
    Type: Grant
    Filed: April 13, 2010
    Date of Patent: October 4, 2016
    Assignee: Nabtesco Corporation
    Inventors: Takashi Koizumi, Hiroshi Usui, Kiyoshi Yasuda
  • Patent number: 9437056
    Abstract: Methods and apparatus for operating flight control systems of aircrafts are disclosed. An example apparatus includes a flight control system including a first sensor and a second sensor. The example apparatus also includes a processor to, based on data from the first and second sensors, determine first and second input values and, based the input values, determine an approximate location of a jam in the flight control system of an aircraft.
    Type: Grant
    Filed: October 9, 2014
    Date of Patent: September 6, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Neal V. Huynh, Robert S. Eick, Thomas G. Heineman, Michael D. Bills, Patrick M. Fahey, John C. Nicholas
  • Patent number: 9377784
    Abstract: Systems and methods for displaying to a tilt rotor aircraft pilot an optimum nacelle position and/or automatically controlling movement of the nacelles for the pilot. An automatic nacelle conversion function employs an active flight director speed mode to provide a current desired speed and a final speed. When the automatic nacelle conversion function is in a passive (uncoupled) mode of operation, the pilot follows visual cues, manually achieving the commanded nacelle position by rotating a thumbwheel. When in an active (coupled) mode of operation, the automatic nacelle conversion function provides a fully automatic nacelle controller requiring no pilot input. This automatic nacelle controller provides a variable nacelle rate along with several angle versus speed schedules tailored for different guidance speed modes and a wide range of aircraft configurations. The automatic nacelle conversion function is improved though the inclusion of altitude, rate of climb, and deceleration rate commands.
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: June 28, 2016
    Assignee: The Boeing Company
    Inventors: Jacob Kowalski, Ivan Grill, Robert T. Seminole
  • Patent number: 9216816
    Abstract: A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition. The method includes generating the control limits, modifying the control limits based upon the impending hazardous flight condition, and displaying the displacement of actuator position relative to the displayed control limits thus cueing the pilot as to the cyclic stick or pedal inputs required to increase the control margin from the impending hazardous condition.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: December 22, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Robert L. Fortenbaugh, Frank Conway, Jeffery S. Greenwood
  • Patent number: 9085363
    Abstract: The method and system may be used to control the movement of a remote aerial device in an incremental step manner during a close inspection of an object or other subject matter. At the inspection location, a control module “stabilizes” the remote aerial device in a maintained, consistent hover while maintaining a close distance to the desired object. The control module may retrieve proximal sensor data that indicates possible nearby obstructions to the remote aerial device and may transmit the data to a remote control client. The remote control module may determine and display the possible one or more non-obstructed directions that the remote aerial device is capable of moving by an incremental distance. In response to receiving a selection of one of the directions, the remote control module may transmit the selection to the remote aerial device to indicate the next movement for the remote aerial device.
    Type: Grant
    Filed: June 16, 2014
    Date of Patent: July 21, 2015
    Assignee: STATE FARM MUTUAL AUTOMOBILE INSURANCE COMPANY
    Inventors: Nathan L. Tofte, James M. Freeman, Brian N. Harvey
  • Patent number: 9026325
    Abstract: This invention relates to the field of very high current integrated power systems and defines a system where an alternating current inductive generator (13), controlled by a generator voltage regulator (14), is coupled to alternating current inductive load (11), controlled by an alternating current inductive load controller (12), all controlled by a supervisory control and data acquisition system (17) with externally adjustable power rate constraints (21) that define a new anticipatory mode integrated power system (10).
    Type: Grant
    Filed: March 10, 2011
    Date of Patent: May 5, 2015
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Thomas D. Roettger, Mohamed Belkhayat, Craig J. Nordby, Joseph M. Maurio, William Patalon
  • Patent number: 8989923
    Abstract: A method of formulating a specification for temporal and vertical required navigation performance is described. The method assesses various flight management guidance systems methods and allows a specification to be set for an airport. The specification may be used to increase aircraft traffic into the airport. The specification sets limits on deviations in time and altitude, for example, on approach into arrivals at the airport. The method comprises: calculating temporal and vertical deviations from a reference trajectory for one or more flight management guidance methods for one or more aircraft types; and comparing the temporal and vertical deviations with operational requirements of the airport. The deviations from a reference trajectory may result from uncertainties affecting trajectory prediction, such as wind and temperature prediction accuracy.
    Type: Grant
    Filed: November 26, 2013
    Date of Patent: March 24, 2015
    Assignee: The Boeing Company
    Inventors: Johan L. De Prins, Ramon Gomez
  • Patent number: 8888036
    Abstract: Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
    Type: Grant
    Filed: June 27, 2012
    Date of Patent: November 18, 2014
    Assignees: Airbus Helicopters, Airbus Helicopters Deutschland GmbH
    Inventors: Bruno Chaduc, Boris Grohmann, Christophe Tempier
  • Publication number: 20140254896
    Abstract: Provided is a system and method for delivering mail and goods using a mobile robot drone system. The method may comprise self-moving the mobile robot drone system to a mail or goods receiving location. Data on the mail or goods receiving location and mail or goods to deliver id received from a user. Itinerary to the mail or goods receiving location is determined based on itinerary data received from a GPS unit. In the location, the mobile robot drone system receives the mail or goods via a mail and goods compartment and then delivers the mail or goods to a predefined location. Based on user instructions, the mobile robot drone system electronically signs receipt verification documents or performs payment by displaying a payment barcode encoding user payment information. After delivering the mail or goods, the mobile robot drone system provides access to the mail and goods compartment.
    Type: Application
    Filed: May 23, 2014
    Publication date: September 11, 2014
    Inventors: Tiger T G Zhou, Dylan T X Zhou, Andrew H B Zhou
  • Patent number: 8763950
    Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.
    Type: Grant
    Filed: September 3, 2013
    Date of Patent: July 1, 2014
    Assignee: Texron Innovations Inc.
    Inventors: Shyhpyng Jack Shue, John James Corrigan, Eric Thomas Bird, Tommie Lynn Wood, Alan Carl Ewing
  • Patent number: 8761966
    Abstract: A six degree-of-freedom trajectory linearization controller (TLC) architecture (30) for a fixed-wing aircraft (46) is set forth. The TLC architecture (30) calculates nominal force and moment commands by dynamic inversion of the nonlinear equations of motion. A linear time-varying (LTV) tracking error regulator provides exponential stability of the tracking error dynamics and robustness to model uncertainty and error. The basic control loop includes a closed-loop, LTV stabilizing controller (12), a pseudo-inverse plant model (14), and a nonlinear plant model(16). Four of the basic control loops (34, 36, 40, 42) are nested to form the TLC architecture (30).
    Type: Grant
    Filed: March 25, 2010
    Date of Patent: June 24, 2014
    Assignee: Ohio University
    Inventors: Jianchao Zhu, Tony M. Adami
  • Patent number: 8740134
    Abstract: An unmanned aircraft system includes a manned aircraft and an unmanned aircraft. The manned aircraft includes a manned aircraft main wing, a manned aircraft fuselage, a manned aircraft landing system, and a manned aircraft joining mechanism provided at a bottom portion of the manned aircraft fuselage. The unmanned aircraft includes an unmanned aircraft main wing, an unmanned aircraft fuselage, an unmanned aircraft landing system, and an unmanned aircraft joining mechanism provided at a roof portion of the unmanned aircraft fuselage. The manned aircraft joining mechanism and the unmanned aircraft joining mechanism are detachably joined. The unmanned aircraft system can take off or land in a state that the unmanned aircraft and the manned aircraft are joined.
    Type: Grant
    Filed: August 13, 2009
    Date of Patent: June 3, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Satoshi Suzuki
  • Patent number: 8718931
    Abstract: A computer implemented method, apparatus, and computer usable program product for cross checking required navigation performance procedures. A required navigation performance procedure in a flight management system is executed in an aircraft. A global positioning system signal in an electronic flight bag or other independent data processing system located onboard the aircraft is received while executing the required navigation performance procedure. A current position of the aircraft based on the global positioning system signal is presented on a moving map. A set of containment lines on the moving map are displayed to indicate whether deviations from the required navigation performance procedure have occurred.
    Type: Grant
    Filed: October 31, 2007
    Date of Patent: May 6, 2014
    Assignee: The Boeing Company
    Inventor: Robert C. Belcher
  • Patent number: 8695921
    Abstract: A method of aiding the piloting of an airplane ensures the availability of an automatic pilot and a thrust regulation system on board the airplane. To this end, the method includes determining first information by measuring the actual airspeed of the airplane, and this first information is used to control the automatic pilot and the thrust regulation system in a primary mode during normal operations of the airplane. When the first information is lost by becoming unavailable or unreliable, the automatic pilot and the thrust regulation system are each controlled in a secondary mode by control parameters determined using additional flight data independent from the actual airspeed of the airplane and the first information. Consequently, an alternative or redundant control is supplied for ensuring the continued operation of an automatic pilot without necessary intervention from crew members on board the airplane.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: April 15, 2014
    Assignee: Airbus Operations (SAS)
    Inventors: Thierry Bourret, Pascale Louise, Jean Muller, Xavier Dal Santo
  • Patent number: 8690101
    Abstract: A system and method are provided for controlling aircraft flight control surfaces. The system may include at least three pilot sensor channels, each pilot sensor channel including a set of pilot sensor data. The system may also include at least three aircraft sensor channels, each aircraft sensor channel including a set of aircraft sensor data. The system may further include an actuator control component configured to synchronously receive and vote on the pilot sensor data and the aircraft sensor data, such that a voted output of the at least three pilot sensor channels is transmitted to a flight control computer and augmented before being transmitted to remote electronics units. The voted output of the at least three pilot sensor channels providing for the control of the aircraft surfaces coupled to the remote electronics units.
    Type: Grant
    Filed: May 18, 2012
    Date of Patent: April 8, 2014
    Assignee: Rockwell Collins, Inc.
    Inventors: Zafar S. Ahmad, John W. Roltgen, Mark C. Singer, Douglas L. Bader