Threshold Or Reference Value Patents (Class 701/8)
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Patent number: 8346408Abstract: A method, apparatus, and computer program product for identifying a number of air states for a vehicle. A deflection of a control surface associated with an actuator is identified to form an identified deflection. A current in the actuator is identified to form a measured current. The number of air states for the vehicle is estimated using the identified deflection and the measured current.Type: GrantFiled: November 10, 2008Date of Patent: January 1, 2013Assignee: The Boeing CompanyInventor: Ryan Todd Ratliff
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Patent number: 8340843Abstract: The invention relates to a method for determining the speed of an aircraft that is subject to a time constraint. The invention consists no longer in calculating a single CAS/MACH pair during climb/descent but in adapting the speed in a continuous manner to the bounds of curves of minimum Vmin and maximum Vmax speed defining a flight envelope of the aircraft. The calculation of these speeds is carried out on the basis of constant maximum and minimum speed setpoints and of a coefficient taking into account a deviation to the time constraint.Type: GrantFiled: November 5, 2009Date of Patent: December 25, 2012Assignee: ThalesInventors: François Coulmeau, Manuel Gutierrez-Castaneda, Nicolas Simi, Xavier Blanchon
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Patent number: 8340837Abstract: Methods and systems for displaying an en-route visible terrain display for an aircraft are provided. The method includes representing each pixel of a terrain display using a geographical location and an elevation above the location, each pixel further represented using at least one of a color value and a grayscale value, receiving a minimum elevation value, setting the at least one of a color value and a grayscale value of the pixels represented by an elevation value less than the received minimum elevation value to a uniform value, and displaying the en-route visible terrain display such that pixels representing terrain that includes an elevation value less than the minimum elevation value are displayed with the uniform value such that non-terrain-impacted, primary-navigation areas of the display are more easily readable.Type: GrantFiled: October 11, 2006Date of Patent: December 25, 2012Assignee: The Boeing CompanyInventor: Sven D. Aspen
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Patent number: 8295996Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).Type: GrantFiled: September 21, 2009Date of Patent: October 23, 2012Assignee: Airbus Operations SASInventors: Paule Botargues, Xavier Dal Santo, Pierre Fabre, Xavier Guery
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Patent number: 8280622Abstract: A system indicating to a pilot that an aircraft has passed the limit-point of success of a standard vertical avoidance maneuver is disclosed. To determine the limit-point, the system monitors a penetration of a model of the terrain being flown over into a first protection volume linked to the aircraft and configured so as to model a standard vertical avoidance maneuver path executed without delay. To determine disengagement azimuth sectors, the system monitors the penetrations of the model of the terrain being flown over into a second protection volume with large azimuth aperture, linked to the aircraft and configured so as to contain the limit-point protection volume and, for the various azimuths covered, paths of a composite maneuver beginning with change-of-heading maneuvers with which to reach the azimuth concerned and continuing with the standard terrain vertical avoidance maneuver.Type: GrantFiled: October 31, 2006Date of Patent: October 2, 2012Assignee: ThalesInventors: Hugues Meunier, Nicolas Marty
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Patent number: 8275496Abstract: In one embodiment of a method to reduce vertical position errors of an aircraft, a disturbance input acting on the aircraft may be determined. The magnitude of the disturbance may be converted into a delta lift command if the magnitude of the disturbance is outside a criteria. The delta lift command may be post processed. The delta lift command may be converted into symmetric lateral surface position commands for control surfaces. The symmetric lateral surface position commands may be communicated to lateral control surface actuators to move the control surfaces according to the symmetric lateral surface position commands.Type: GrantFiled: November 21, 2007Date of Patent: September 25, 2012Assignee: The Boeing CompanyInventors: Brian K. Rupnik, Sean J. Flannigan
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Patent number: 8255096Abstract: Minimizing dynamic structural loads of an aircraft, introduced by an external excitation, which, includes generating a signal (x) indicative of the external excitation; deriving signals (y) of pre-controlling for actuating control elements of the aircraft from the excitation indicating signal (x) in accordance with a pre-controlling rule, so as to reduce the dynamic structural loads introduced to the aircraft; generating an error signal (e, e*) representing performance of said pre-controlling; optimizing the pre-controlling rule by the error signal (e, e*) and/or the excitation indicating signal (x) so as to minimize the dynamic structural loads.Type: GrantFiled: January 19, 2007Date of Patent: August 28, 2012Assignee: Airbus Operations SASInventors: Andreas Wildschek, Rudolf Maier, Falk Hoffmann, Matthieu Jeanneau, Nicky Aversa
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Patent number: 8249761Abstract: The invention relates to a method for calculating a flight path avoiding a collision with the ground when an aircraft dives towards the ground. The method includes receiving signals including information of a dive angle of the aircraft in relation to the imaginary ground plane, and a present roll angle of the aircraft, and calculating a flight path that avoids collision with the ground on the basis of the information. The calculation includes calculating a need for rolling the aircraft based on the present roll angle, and calculating a need for changing the direction of the velocity vector of the aircraft so that the change has a component in an upward direction in relation to the reference frame of the aircraft.Type: GrantFiled: July 8, 2009Date of Patent: August 21, 2012Assignee: Saab ABInventors: Hasse Persson, Jonas Lovgren
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Patent number: 8239077Abstract: A method and a device for an aircraft for detecting noise in a signal of LOC type. A first step includes estimating a first lateral speed of the aircraft according to a first set of parameters. Concurrently, at least one second lateral speed of the aircraft is estimated according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the first set of parameters. A second step includes comparing the first lateral speed and the at least one second lateral speed according to a threshold. If the difference between the first lateral speed and the at least one second lateral speed is greater than the threshold, the presence of noise in the signal of LOC type is detected.Type: GrantFiled: April 25, 2008Date of Patent: August 7, 2012Assignee: Airbus Operations SASInventor: Alexandre Colomer
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Patent number: 8224504Abstract: A method and device for updating the position of an aircraft includes a flight management system incorporating first and second position supplying devices for supplying first and second positions during flight. The first position is based on inertial data and based on data from a satellite positioning system. The second position is based on inertial data and based on data from a radio-navigation system. The flight management system also includes an updating system that includes a fly over updating device, a radar updating device, and a take off updating device. The updating system is operable to generate an updating position manually or automatically that will be used as the second position and selected as a new position for use with the flight management system.Type: GrantFiled: March 30, 2011Date of Patent: July 17, 2012Assignee: Airbus Operations (SAS)Inventors: Yohann Roux, Alexandre Pericart
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Patent number: 8209068Abstract: A control system (12) for controlling velocity and attitude of a dynamic system (20) includes a velocity controller configured to receive a desired velocity command and output a velocity error in the form of Euler angle commands to an attitude controller system. The attitude controller system includes a converter (14) configured to receive the Euler angle commands and output a desired quaternion based on the Euler angle commands. The attitude controller system further includes an attitude error generator (16) configured to receive the desired quaternion and an estimated quaternion indicative of an estimated velocity and attitude of the dynamic system (20) and to output attitude errors associated with the dynamic system (20). The attitude controller system also includes an attitude controller (18) configured to receive the attitude errors and to output error commands to the dynamic system (20) based on the attitude errors.Type: GrantFiled: June 2, 2005Date of Patent: June 26, 2012Assignee: Rockwell Collins Control Technologies, Inc.Inventors: David William Vos, Vladislav Gavrilets, Michael Daniel Piedmonte
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Patent number: 8200421Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.Type: GrantFiled: October 20, 2009Date of Patent: June 12, 2012Assignee: Airbus Operations SASInventors: Paule Botargues, Nicolas Caule, Christelle Ledauphin, Jerome Bailly, Isabelle Lacaze, Sylvain Thezelais, Jerome Goyet
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Patent number: 8195813Abstract: The invention concerns a communication system via ACARS messages intended to be placed onboard an aircraft, said system comprising a router (310, 310?) adapted to route said messages from and to a plurality of VHF, HF, SATCOM sub-networks. The system comprises a switch (360, 365) and an AoIP conversion gateway (380), the switch being connected to an HF or SATCOM transceiver module (340, 350) by means of a first two-way link (341, 351), and to said AoIP gateway by means of a second two-way link (381), the switch being adapted to select said first two-way link when it lies in a first switch position and the second two-way link when it lies in a second switch position, the switch lying in the second switch position if the aircraft is on the ground or less than a predetermined distance from the ground, otherwise it lies in the first position.Type: GrantFiled: August 11, 2009Date of Patent: June 5, 2012Assignee: Airbus OperationsInventors: Pierre Gruyer, David Rose, Christophe Servieres-Bordes
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Patent number: 8193948Abstract: A present novel and non-trivial system, module, and method for presenting runway advisory information are disclosed. A runway reference may be established using data received from a source of navigation reference data, where such data could represent runway information, runway awareness zone information, landing awareness zone information, and/or runway threshold line information. Navigation data representative of at least aircraft location and input factor data may be received from a source. Phase of flight may be determined using input factor data, and a runway advisory data set may be generated as a function of phase of flight and the positional relationship between aircraft location and the runway reference. Runway advisory data set may be representative of advisory information comprised of visual runway advisory information, aural runway advisory information, tactile advisory information, or a combination thereof.Type: GrantFiled: September 30, 2009Date of Patent: June 5, 2012Assignee: Rockwell Collins, Inc.Inventors: Geoffrey A. Shapiro, Alena L. Benson, Matthew J. Carrico, Randy H. Jacobson
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Patent number: 8190308Abstract: A method and device for detecting a risk of collision of an aircraft, having a profile unit having knowledge of the terrain profile, a determination unit for determining effective values of particular flight parameters, a checking unit for verifying whether a flight path determined by the effective values is compatible with the terrain profile, and a transmitting unit for emitting a warning signal in case of incompatibility. The checking unit includes at least one element for calculating a height variation due to an energy transfer and a total slope variation generated by a speed reduction, during an evasive action, an element deter mining an evasive course using the height variation, and an element verifying whether the evasive course determined is compatible with the terrain profile.Type: GrantFiled: July 25, 2006Date of Patent: May 29, 2012Assignee: Airbus Operations SASInventors: Fabien Pitard, Jean-Pierre Demortier, Florence Aubry
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Patent number: 8175760Abstract: A device comprises means for computing the air-craft (A) current position, means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the flight plan according to accuracy and integrity performances of said current position computation and to the restriction of a flight range authorized in a flight corridor (6A, 6B), and a display system (7) for displaying at least one a distance scale (9) on a viewing screen (8), at least one a fixed symbol (10) displaying the current position and two movable pointers (13, 14) displaying the limits of said maximum permitted deviation (E1).Type: GrantFiled: June 19, 2006Date of Patent: May 8, 2012Assignee: Airbus Operations SASInventors: Patrice Rouquette, Nolween Laveant, Didier Have, Arnaud Le Tellier
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Patent number: 8150566Abstract: A system for selecting a datum among a set of data representing an air parameter, this set comprising at least two engine data obtained by measurement respectively in the zone of two engines of an aircraft and at least two reference data obtained by measurement in the zone of the fuselage of the aircraft, the system comprising: means for verifying pairwise agreement of three data of the set of data; means for selecting a reference datum among the said three data if such agreement is verified. A process and a computer program relating thereto are also proposed.Type: GrantFiled: May 16, 2008Date of Patent: April 3, 2012Assignee: Airbus Operations SASInventor: Julien Feau
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Patent number: 8145365Abstract: The invention relates to a calculation method for an aircraft navigation aid system making it possible to maintain a vertical safety margin with an obstruction profile, the aircraft comprising a navigation system, an automatic piloting system, a database system and a display device, characterized in that the method comprises the following steps: calculation of an obstruction altitude profile, calculation of a vertical safety margin with respect to the obstruction profile, of a plurality of vertical safety trajectories and of the respective flight setpoints for the aircraft to execute the trajectories, selection of the flight setpoints making it possible to maintain the aircraft as close as possible to the obstruction profile while maintaining between the aircraft and the obstruction profile at least the vertical safety margin, filtering of the flight set point values so that the variation of the values of the setpoints does not exceed a variation difference in a duration predefined in the system.Type: GrantFiled: June 19, 2009Date of Patent: March 27, 2012Assignee: ThalesInventors: Laurent Flotte, Nicolas Marty, Aurélie Sallier
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Patent number: 8135503Abstract: An unmanned aerial vehicle comprises a housing, a rotor that is rotated to propel the housing, a pressure sensor that generates a signal indicative of an air pressure proximate a bottom surface of the housing, and a processor configured to determine, based on the signal, when an increase in air pressure proximate the bottom surface is greater than or equal to a threshold value associated with the ground effect of the rotor, wherein the processor controls the rotor to cease rotating or decrease rotational speed to land the unmanned aerial vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.Type: GrantFiled: April 27, 2010Date of Patent: March 13, 2012Assignee: Honeywell International Inc.Inventor: Gerald Parras
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Patent number: 8121746Abstract: The present invention relates to a method and a device for monitoring the minimum flying altitude of an aircraft.Type: GrantFiled: March 21, 2007Date of Patent: February 21, 2012Assignee: ThalesInventors: Gilles François, Nicolas Marty, Frédéric Thomas
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Patent number: 8116923Abstract: Systems and methods for suppressing an unstable alert when the aircraft is in the process of landing on a temporarily displaced threshold. In an example process, a processor on the aircraft determines the aircraft is on an approach to landing on a runway based on information received from one or more data sources on the aircraft, then retrieves predefined glideslope information for the runway from a memory device that is in signal communication with the processor. Next, the processor determines whether position of the aircraft is above the predefined glideslope by a first threshold amount. If the aircraft is determined to be above the predefined glideslope by the first threshold amount, the processor issues an unstable alert only if a flight path angle of the aircraft is greater than an angle of the predefined glideslope by a second threshold amount.Type: GrantFiled: November 19, 2009Date of Patent: February 14, 2012Assignee: Honeywell InternationalInventors: Yasuo Ishihara, Steve Johnson
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Publication number: 20120022724Abstract: Automatic management method and device of a lateral trajectory for an emergency descent of an aircraft. The device automatically modifies lateral setpoints of the aircraft (AC) when a failure (5) triggers an emergency descent, by taking account of the lateral trajectory (TLO) initially followed.Type: ApplicationFiled: July 15, 2011Publication date: January 26, 2012Applicants: AIRBUS OPERATIONS (S.A.S.), AIRBUS (S.A.S.)Inventors: Paule Botargues, Erwin Grandperret, Lucas Burel, Jacques Rosay, Didier Ronceray
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Patent number: 8103393Abstract: A computer-implemented function monitors and displays exhaust gas temperatures (EGT) in a plurality of cylinders in an engine. The invention provides an easy way to read exhaust gas temperature on a specific cylinder, and to provide a means for leaning the engine while in a climb. Efficient leaning in a climb reduces fuel consumption and reduces the chance of harmful conditions that can lead to engine failure.Type: GrantFiled: October 19, 2007Date of Patent: January 24, 2012Assignee: Vertical Power, Inc.Inventors: Marc Ausman, Kevin DeVries
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Publication number: 20120016540Abstract: The device includes means (15A, 15B) for determining and using a heading target which represents the heading value reached by the aircraft (AC) at the end of a procedure of folding the wings of the aircraft (AC) flat, initiated at the current instant, from a rolling angle holding mode.Type: ApplicationFiled: July 14, 2011Publication date: January 19, 2012Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Pascale Louise, Alain Dupre, Anthony Atencia, Emmanuel Cortet, Xavier Dal Santo
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Publication number: 20120016539Abstract: A system includes a memory device, and a processor coupled to the memory device. The processor is configured to receive, in a first time interval, from a first component a signal indicating an altitude of the aircraft, from a second component a signal indicating a first heading of the aircraft, and from a third component a signal indicating a first position of the aircraft. The processor is further configured to receive, in a second time interval later than the first time interval, and from the second and third components, signals respectively indicating a second heading and second position of the aircraft. The processor does not receive a signal from the first component in the second time interval. The processor is further configured to determine an estimated altitude of the aircraft and a geometric altitude of the aircraft.Type: ApplicationFiled: July 15, 2010Publication date: January 19, 2012Applicant: Honeywell International, Inc.Inventors: Rupa Bhavani Krishnamurthy, Nainatara Kumble
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Patent number: 8098176Abstract: Systems and methods for improving landing gear alerting on a rotary wing aircraft. An example system includes a user interface device that allows a user to set a bug altitude value and a radio altimeter that produces an altitude value, both of which are in communication with a processor. The processor receives a bug altitude setting, generates a landing gear alert altitude value based on the received bug altitude setting and a predefined additive, receives a radio altitude value for the rotary-wing aircraft, and generates a landing gear alert if the radio altitude value is less than the landing gear alert altitude value and the landing gear is not in a landing position. An output device in signal communication with the processor, outputs the generated landing gear alert.Type: GrantFiled: June 23, 2010Date of Patent: January 17, 2012Assignee: Honeywell International Inc.Inventors: Yasuo Ishihara, Steve Johnson, Gary Ostrom
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Patent number: 8095252Abstract: A piloting method and device for avoiding pilot induced oscillations filters a piloting order with a non-linear filtering function that is controlled by speed comparison information.Type: GrantFiled: May 15, 2009Date of Patent: January 10, 2012Assignee: Airbus Operations SASInventor: Pierre Fabre
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Patent number: 8090485Abstract: The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).Type: GrantFiled: November 27, 2007Date of Patent: January 3, 2012Assignee: Embraer S.A.Inventors: Erick Vile Grinits, Marco Antonio de Oliveira Alves Junior, Dagfinn Gangsaas, Roberto Garcia Negrao, Bianca Prazim Trotta, Fabiano Prieto Silva, Mauricio Martins de Almeida Filho, Marco Antonio Coccolin, Karina Sanches Garcia, Daniel Carmona de Campos, Cristina Minioli Saracho, Fernando Jose de Oliveira Moreira
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Patent number: 8086362Abstract: Method and device for assisting the piloting of an aircraft. The device (1) comprises means (4) for determining, using a roll instruction and measured current values of external characteristics and of flight characteristics of the aircraft, a predicted path which is a flight path having a constant roll angel, taking account of the effect of the wind.Type: GrantFiled: August 20, 2008Date of Patent: December 27, 2011Assignees: Airbus Operations SAS, AirbusInventors: Alain Dupre, Nicolas Ferret, Philippe Foucault
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Patent number: 8082070Abstract: Methods and systems for displaying assistance messages to aircraft operators are disclosed. A method in accordance with one embodiment includes receiving an input from an aircraft operator at an aircraft flight deck, comparing a characteristic of the input to at least one target value for the characteristic, and, if the characteristic of the input differs from the at least one target value for the characteristic by at least a threshold amount, displaying an assistance message to the aircraft operator. The assistance message can include a complying input and/or an instruction for creating a complying input. The input and the assistance message can be displayed simultaneously.Type: GrantFiled: June 25, 2010Date of Patent: December 20, 2011Assignee: The Boeing CompanyInventors: Peter D. Gunn, John C. Griffin, III
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Patent number: 8077055Abstract: Method, device and item of equipment for filtering alarms originating from a windshear detection system embedded in an aircraft being able to emit an alarm. The aircraft has at least one sensor allowing the acquisition of a flight parameter. The device includes: units for the calculation of the second derivative of the flight parameter, units for the calculation of the absolute value of the second derivative of the flight parameter, units for the comparison of the absolute value of the second derivative of the flight parameter with a threshold C1, units for evaluating whether the absolute value of the second derivative of the flight parameter exceeds the threshold C1 over a duration greater than a time threshold T, and units for suppressing the alarm originating from the windshear detection system.Type: GrantFiled: January 15, 2009Date of Patent: December 13, 2011Assignee: ThalesInventors: Bertrand Baillon, Stéphane Fleury, Laurence Mutuel
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Patent number: 8073578Abstract: A method of creating and modifying a flight plan using a cursor control device and a display to represent the flight plan in the context of terrain. The method includes inserting waypoints, including origin and destination waypoints, into a flight plan using a cursor control device to position the waypoints in a display and commanding a flight management system (FMS) to connect the waypoints into a flight plan. The flight plan is drawn in the context of terrain on a display where conflicts between the flight plan and terrain are indicated. Selected elements of the flight plan are selected with a cursor control device and the selected elements are dragged to new positions on the display until terrain conflicts are eliminated, thus generating a modified flight plan. The modified flight plan is reviewed in the context of terrain to determine its acceptability and making further modifications thereof if desired.Type: GrantFiled: September 18, 2008Date of Patent: December 6, 2011Assignee: Rockwell Collins, Inc.Inventor: Patrick D. McCusker
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Patent number: 8050808Abstract: The device includes a calculation unit to automatically calculate an overall thrust moment of the engines which represents a thrust asymmetry of the engines of a multi-engine aircraft, a determination unit to automatically determine, using this overall moment, a maximum roll rate, and a limiting unit to automatically limit a roll command using this maximum roll rate.Type: GrantFiled: March 21, 2008Date of Patent: November 1, 2011Assignees: Airbus Operations SAS, AirbusInventors: Martin Delporte, Sophie Lambeaux, Didier Ronceray, Jean-Philippe Legier
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Patent number: 8050842Abstract: The present invention relates to a method and to an apparatus (9) for controlling and regulating a rotorcraft turbine engine (1). The apparatus is provided with an electronic control and regulation computer (3) that receives signals relating to monitored parameters of the turbine engine (1). The apparatus is remarkable in that it is provided with an alarm (4) controlled by the electronic computer (3) via an analog connection (8) to operate whenever an event occurs that might diminish the safety of the rotorcraft.Type: GrantFiled: June 20, 2008Date of Patent: November 1, 2011Assignee: EurocopterInventor: Lionel Iraudo
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Patent number: 8046119Abstract: The parts of the flight plan of an aircraft corresponding to lateral trajectories at low altitude can comprise passages with limited lateral freedom of deployment because of risks of collision with the ground, or because of obstacles on the ground. The method makes it possible to signal them for the attention of the crew, so that said crew should redouble their attention. To do this it uses the display, on an onboard navigation screen, of a vertical profile of margin of maneuver relating to the navigation band widened to the right and to the left by lateral margins of maneuver, superimposed on the vertical navigation profile relating only to the navigation band.Type: GrantFiled: June 3, 2005Date of Patent: October 25, 2011Assignee: ThalesInventors: Elias Bitar, Nicolas Marty
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Patent number: 8046118Abstract: The invention relates to flight control systems for aircraft, which have large control loops delivering load factor commands and which are applied to flight controls more suited to the following by the pilot of a longitudinal attitude deviation instruction than to the following of a load factor instructions. It consists of a small control loop generating a deviation indicator displayed by the flight director on the PFD screen, with a converter for converting a controlled load factor into a longitudinal attitude deviation instruction comprising a bandpass filter allowing the integration for the calculation of the longitudinal attitude deviation instruction value in the piloting frequency span only.Type: GrantFiled: June 20, 2007Date of Patent: October 25, 2011Assignee: ThalesInventor: Marc Riedinger
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Patent number: 8041472Abstract: A positioning device that detects a position of a mobile body with a radio navigation positioning unit includes: first and second autonomous sensors obtaining behavioral information on the mobile body; a position detecting unit obtaining an estimated position and an estimated direction by updating a detection result based on the behavioral information from the first autonomous sensor; a map data positioning unit that refers to a map data storage unit based on the estimated position and obtains a map data linked position at a predetermined distance away from a link; a direction detecting unit obtaining a cumulative estimated direction by updating the detection result based on the behavioral information from the second autonomous sensor; and a most probable position estimating unit estimating the position of the mobile body from the estimated positions and directions using the Kalman filter.Type: GrantFiled: June 8, 2007Date of Patent: October 18, 2011Assignee: Toyota Jidosha Kabushiki KaishaInventors: Norimasa Kobori, Kazunori Kagawa
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Patent number: 8041471Abstract: A vertical take-off and landing aircraft that includes AC motors, which drive fans that propel the aircraft, and a control device for controlling the AC motors adaptively based on a thrust control amount from an attitude controller. In particular, the drive controller performs switching to convert DC from a power source to three-phase AC at a predetermined frequency to be supplied to the AC motors. The drive controller reduces the control frequency of the three-phase AC to be applied to the AC motor to reduce the control resolution when the flight mode is switched from a vertical flight control mode to a horizontal flight control mode, in which the control amount to correct the external forces is smaller. Therefore, it is possible to reduce the power loss in the controller and thus the power consumption compared to conventional vertical take-off and landing aircrafts, in which the control resolution is always constant.Type: GrantFiled: November 13, 2007Date of Patent: October 18, 2011Assignee: Toyota Jidosha Kabushiki KaishaInventor: Masatsugu Ishiba
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Publication number: 20110251740Abstract: 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 the actual along-track position and the actual vertical position of the aircraft relative to the corresponding desired positions on the predetermined flight path. The aircraft's elevators are used to correct deviations of the along-track position and the aircraft's throttle is used to correct deviations of the vertical position.Type: ApplicationFiled: July 24, 2009Publication date: October 13, 2011Applicant: THE BOEING COMPANYInventors: Ramon Gomez Ledesma, David Garrido-Lopez, Luis Pedro D'Alto
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Patent number: 8032268Abstract: Methods and systems are provided for indicating whether an aircraft is below a designated minimum safe altitude level for an altitude sector. A method comprises displaying a graphical representation of a first sector on a display device associated with the aircraft. The first sector corresponds to a geographic area having a first minimum altitude criterion. If a current altitude of the aircraft is below the first minimum altitude criterion, the method continues by displaying the graphical representation of the first sector using a first visually distinguishing characteristic chosen to indicate that the aircraft is below the designated altitude level for the first sector.Type: GrantFiled: September 29, 2008Date of Patent: October 4, 2011Assignee: Honeywell International Inc.Inventors: Roger W. Burgin, Aaron Gannon, Blake Wilson, Edward Tomaszewski
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Patent number: 8027756Abstract: Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP/ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV/VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and/or landing.Type: GrantFiled: December 7, 2006Date of Patent: September 27, 2011Assignee: The Boeing CompanyInventors: Robert B. Davis, Daniel J. Boorman, L. Kirk Gagnon, William L. Goodman, Alan R. Jacobsen, William A. Miller, James E. Mitchell, Victor A. Riley, William F. Royce, William D. Tafs
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Patent number: 8014910Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.Type: GrantFiled: May 4, 2006Date of Patent: September 6, 2011Assignee: Airbus FranceInventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron
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Patent number: 8009027Abstract: A tire monitoring system and associated method is disclosed. The tire monitoring system includes a plurality of tire sensor modules, employing contactless sensors, configured to transmit tire data at a predetermined time interval. The system also includes a central control unit that is configured to receive the tire data from the tire sensor modules, and is further configured with an external control unit that can communicate with the tire sensor modules, the central control units and outside sources.Type: GrantFiled: May 31, 2006Date of Patent: August 30, 2011Assignee: Infineon Technologies AGInventors: Michael A. Thomas, Peter Knittl
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Patent number: 8010243Abstract: A device used in an aircraft with an electrical flight control system to reduce load applied to the wing during a lateral roll maneuver, by comparing a roll control with a threshold, and filtering a control. As a result of this action on the roll control, resulting load increases on the wing can be anticipated and reduced. Loads can thus remain below a maximum design value for the wing if the applied roll control is too high for planned use of the aircraft, therefore limiting overdesign of the wing.Type: GrantFiled: July 6, 2006Date of Patent: August 30, 2011Assignee: Airbus Operations SASInventor: Tania Livet
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Publication number: 20110196549Abstract: A method and apparatus for displaying a predicted path on a vertical profile to operate a vehicle. A path is predicted for the vehicle in response to an event occurring. The path has a turning section and a straight section after the turning section. A portion of terrain relative to the path predicted for the vehicle is identified. A vertical profile view of the terrain is displayed, including the portion of the terrain relative to the path predicted for the vehicle.Type: ApplicationFiled: February 11, 2010Publication date: August 11, 2011Applicant: The Boeing CompanyInventors: Frank C. Sharkany, John Tarbaux
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Patent number: 7996120Abstract: The device for flying an aircraft includes a first unit for determining a control value corresponding to an instruction value representing the actuation of a control member by a pilot, a second unit for determining an effective control value corresponding to the instruction value which is actually applied to the aircraft, a third unit for automatically controlling the aircraft, a fourth unit for computing an auxiliary control value, which is closer to the effective controlled value, and a fifth unit for monitoring the control value and for detecting a pilot induced oscillation, where the automatic control is carried out with the aid of the controlled effective value and the auxiliary control value in the case of the detection of the pilot induced oscillation.Type: GrantFiled: July 17, 2006Date of Patent: August 9, 2011Assignee: Airbus FranceInventor: Stéphane Delannoy
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Patent number: 7970501Abstract: An inertial navigation system which includes a first control system and a second control system is described. The first control system is configured to estimate a vertical velocity based in part on received vertical acceleration data. The second control system is configured to receive the estimated vertical velocity from the first control system and determine a compensated vertical velocity utilizing the estimated vertical velocity and airspeed.Type: GrantFiled: March 8, 2005Date of Patent: June 28, 2011Assignee: Honeywell International Inc.Inventors: Jeffrey W. Kirkland, John F. Anderson
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Patent number: 7962255Abstract: A method for estimating inertial acceleration bias errors including obtaining uncorrected acceleration measurements on board a vehicle; obtaining independent position and independent velocity data of the vehicle; transforming the uncorrected acceleration measurements into a reference frame of the independent position and independent velocity data; blending the transformed acceleration measurements with the independent position and the independent velocity data to produce feedback errors; transforming the feedback errors into the reference frame of the acceleration measurements; multiplying the feedback errors by a gain and integrating to estimate the acceleration measurement bias errors.Type: GrantFiled: December 12, 2006Date of Patent: June 14, 2011Assignee: The Boeing CompanyInventors: Steven B. Krogh, Tiffany R. Lapp
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Patent number: 7949152Abstract: A driver assistance system for a vehicle includes an imaging device having a field of view forward of a vehicle and an image processor operable to process image data captured by the imaging device. The vehicle includes a control system operable at least in part to control the speed of the vehicle. The control system may reduce the speed of the vehicle responsive at least in part to a detection of a curve in the road ahead of the vehicle via processing by the image processor of image data captured by the imaging device. The control system may control the speed of the vehicle to a reduced speed for traveling around the detected curve in the road, and may increase the speed of the vehicle to above the reduced speed when the vehicle is traveling along a straighter section of road after the curve in the road.Type: GrantFiled: December 28, 2010Date of Patent: May 24, 2011Assignee: Donnelly CorporationInventors: Kenneth Schofield, Niall R. Lynam
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Patent number: RE42708Abstract: A field unit for warning of a danger of collision between an aircraft and an obstacle, in particular a topographical ground obstacle or an obstacle formed by a mast, building or aerial cable structure, comprises a multi-part tubular mast having devices for fixing a solar panel and a radar antenna; an elongate radar antenna in an environment-protective casing, which, with an electronics unit, forms a radar system for synthesized radar detection of an aircraft in a radar coverage area; a central processing unit for identifying on the basis of information from the radar system an aircraft which is in a zone of the radar coverage area and which on the basis of radar information such as direction, distance and/or speed computes a collision danger area; and a high-intensity light system and radio transmitter system that can be activated by the central processing unit upon detection of an aircraft in a collision danger area.Type: GrantFiled: January 11, 2010Date of Patent: September 20, 2011Assignee: OCAS ASInventors: Morten Mark, Rolf Bakken