Air Speed Or Velocity Measurement Patents (Class 701/7)
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Patent number: 7865289Abstract: A method of distribution braking between the brakes of an aircraft. The method includes a first step of estimating a braking force objective and a steering torque objective to be achieved by the brakes of the aircraft. It also includes the steps of defining at least two groups of brakes (12, 13) and determining, for each group, a braking level that is to be achieved by the group. The braking levels being calculated in such a manner that braking performed in application of the braking levels is, at least under normal operating conditions of the brakes, in compliance with a braking force objective and with a steering torque objective.Type: GrantFiled: March 13, 2007Date of Patent: January 4, 2011Assignee: Messier-BugattiInventors: Stéphane Dellac, Arnaud Jacquet, Gérard Léon Gissinger, Michel Basset, Yann Chamaillard, Jean-Pierre Garcia
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Publication number: 20100309025Abstract: The invention relates to a method for managing an anti-collision system for aircraft, said system comprising means of detecting collision with a threat and at least one head-up viewing device. The symbol system comprises two display modes dedicated to collision detection which are: on the one hand an “action” mode: a potential collision is detected by the system, the symbol system comprises at least one symbol representative of the limits of the disengagement path of the aircraft to avoid the collision and enabling the pilot to engage his avoidance maneuver, and on the other hand a “control” mode: this mode is displayed when the avoidance maneuver is engaged and the collision avoided, the symbol system comprises at least the symbol representative of the limits of the disengagement path of the aircraft and a plan view representing the air space around the aircraft and including at least one representation of the threat.Type: ApplicationFiled: August 25, 2008Publication date: December 9, 2010Applicant: THALESInventors: Thierry Ganille, Regis Azarian, Eric Filliatre
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Publication number: 20100286850Abstract: The invention relates to a standby instrument for the piloting of aircraft allowing a pilot to restore a display similar to that of a head-up display in the event that the latter should fail. According to the invention, the standby instrument comprises means for determining and displaying a speed vector (11) of the aircraft only with the aid of means usually present in a standby instrument, namely means for measuring static and total pressures of the airstream surrounding the aircraft and means for inertial measurement.Type: ApplicationFiled: July 15, 2008Publication date: November 11, 2010Applicant: THALESInventors: Lionel Collot, Henri LeBlond, Jerome Papineau
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Patent number: 7826971Abstract: A method for filtering anti-collision alarms for aircraft, the said aircraft comprising means for calculating its speed and extrapolated positions on its trajectory, the said extrapolated positions being calculated over a fixed maximum time period, called extrapolation time, and a topographical database of the terrain, the said database comprising, within a given perimeter, data on the density of obstacles, comprises a calculation of a weighting coefficient for the extrapolation time of the calculated extrapolated trajectories of the aircraft as a function of the density of obstacles within a surface area included within the perimeter.Type: GrantFiled: March 13, 2008Date of Patent: November 2, 2010Assignee: ThalesInventors: Sylvain Fontaine, Nicolas Marty, Pierre Gamet
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Publication number: 20100250030Abstract: A flight deck display system for an aircraft or other vehicle includes a first data source of visual feature data that is indicative of visual features of a location of interest, a second data source of flight data for the aircraft, a processor architecture, and a display element. The processor architecture is operatively coupled to the first data source and to the second data source, and it is configured to process the visual feature data, process the flight data, and, based upon the visual feature data and the flight data, generate image rendering display commands. The display element receives the image rendering display commands and, in response thereto, renders a dynamic graphical representation of the location of interest using the visual feature data. The dynamic graphical representation of the location conveys an amount of visible detail that varies as a function of the flight data.Type: ApplicationFiled: March 27, 2009Publication date: September 30, 2010Applicant: Honeywell International Inc.Inventors: Troy Nichols, Thea L. Feyereisen, Gang He, Dave Pepitone
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Patent number: 7791529Abstract: The invention relates to a method of determining an estimated speed of an aircraft relative to ground being overflown by the aircraft, in which use is made of the sum of an acceleration measurement of the aircraft plus a difference value, the difference value being obtained from observation data or signals relating to a region of the ground.Type: GrantFiled: May 18, 2006Date of Patent: September 7, 2010Assignee: EurocopterInventors: François Xavier Filias, Jean-Paul Petillon, Richard Pire
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Patent number: 7783393Abstract: A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.Type: GrantFiled: June 30, 2004Date of Patent: August 24, 2010Assignee: The Boeing CompanyInventors: Michael J. Tucker, Sherwin S. Chen, John Wiedemann, Jason L. Hammack
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Patent number: 7756612Abstract: The invention relates to a method of piloting a rotorcraft having a plurality of engines for driving at least one lift and propulsion rotor, in which method, so long as the rotorcraft has not reached an optimum climb speed (OCS), a pitch attitude control signal (Upitch) is determined that is adapted so that the rotorcraft accelerates in application of a profile (P1, P2, P3) that varies as a function of the elapsed time and as a function of the operating state of the engines (OEI/AEO).Type: GrantFiled: April 30, 2007Date of Patent: July 13, 2010Assignee: EurocopterInventor: Marc Salesse-Lavergne
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Publication number: 20100152930Abstract: 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: ApplicationFiled: November 5, 2009Publication date: June 17, 2010Applicant: ThalesInventors: Francois Coulmeau, Manuel Gutierrez-Castaneda, Nicolas Simi, Xavier Blanchon
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Patent number: 7726117Abstract: The invention relates to a method for controlling an internal combustion engine with a motor control system that adjusts the exhaust-gas temperature by influencing the air-fuel mixture. Said motor control system has a temperature model so as to determine a preset temperature for a component in the exhaust manifold, which is achieved after a longer period of time while maintaining current operating and driving conditions. The motor control system regulates the exhaust-gas temperature depending on the preset temperature for the purpose of component protection.Type: GrantFiled: June 27, 2005Date of Patent: June 1, 2010Assignee: Continental Automotive GmbHInventor: Gerhard Haft
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Patent number: 7693613Abstract: In distance maps used in order to facilitate the navigation of craft such as an aircraft, the distances estimated take into account obstacles to be circumvented but not the maneuverability of the craft. The adaptation route required by the craft in order to take the right direction is not taken into account so that certain distance estimates for accessible points located in the neighborhood of the craft are unrealistic. In order to make a distance map more realistic, it is proposed that an obstacle of concave shape associated with the craft be added behind the position of the craft, forcing the estimations of distances to be circumvented an area that is inaccessible to the craft for reasons of maneuverability.Type: GrantFiled: February 9, 2005Date of Patent: April 6, 2010Assignee: ThalesInventors: Elias Bitar, Nicolas Marty
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Patent number: 7689328Abstract: A routing tool is disclosed. In one embodiment, the method and system include receiving flight data and geographic data in the aircraft, and generating route data based on the flight data and the geographic data. The route data provides information about attainable landing areas for the aircraft.Type: GrantFiled: December 21, 2006Date of Patent: March 30, 2010Assignee: Boeing CompanyInventor: Charles B. Spinelli
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Publication number: 20100036549Abstract: Systems and apparatus are provided for using a flight management system in an aircraft for airborne fire fighting. An apparatus is provided for a display system for use in an aircraft equipped for transporting a fire retardant material. The display system comprises a display device associated with the aircraft, and a flight management system coupled to the display device. The flight management system is adapted to control the rendering of a navigational map on the display device, determine a predicted distribution region for a release of the fire retardant material, and overlay a graphical representation of the predicted distribution region on the navigational map.Type: ApplicationFiled: July 18, 2008Publication date: February 11, 2010Applicant: Honeywell International Inc.Inventors: William Kwan, John Zwagerman
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Publication number: 20100023187Abstract: A flight deck display system for an aircraft includes a processor architecture configured to receive aircraft instrument data (e.g., altimeter or airspeed) and position data for the aircraft and, based upon the instrument data and the position data, generate image rendering display commands. The system also includes a display element configured to receive the image rendering display commands and, in response thereto, to render a graphical instrument tape. The instrument tape includes a graphical representation of a scrolling altitude or airspeed range that dynamically scrolls in response to changes in the altitude/airspeed data, along with a graphical representation of a position-dependent altitude/airspeed clearance element that conveys an altitude/airspeed restriction for an approaching geographic position of the aircraft. The content of the position-dependent clearance element is influenced by the position data.Type: ApplicationFiled: July 28, 2008Publication date: January 28, 2010Applicant: Honeywell International Inc.,Inventors: Aaron Gannon, Gang He, Thea L. Feyereisen, Ivan S. Wyatt
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Publication number: 20090326743Abstract: A throttle control system that is compensated for mountain wave conditions includes an auto throttle computer and a detector for detecting the pitch or pitch angle of the aircraft. The computer is used for determining the rate of change of pitch i.e. the first derivative of pitch angle and the rate of change of the rate of change of pitch i.e. the second derivative for generating a signal indicative of the rate of change of the rate of change of pitch. The signal from the auto throttle computer is combined with the signal from the signal indicative of the second derivative to produce a combined signal which is fed to a servo assemble and motor for adjusting the throttle of an aircraft.Type: ApplicationFiled: June 26, 2008Publication date: December 31, 2009Inventors: Leonard M. Greene, Richard A. Sporn
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Patent number: 7640083Abstract: Multiple data and images are multiplexed and sequenced in order to minimize the recording and monitoring hardware required to process the images, providing a detailed record of an event, greatly enhancing event reconstruction efforts. The multi-media safety and surveillance system for aircraft incorporates a plurality of strategically spaced sensors including video imaging generators for monitoring critical components and critical areas of both the interior and the exterior of the aircraft. The captured data and images are recorded and may be transmitted to ground control stations for real time or near real time surveillance. The system includes a plurality of strategically located video image sensors such as, by way of example, analog and/or digital video cameras, a video data recorder (VDR) and a pilot display module (MCDU or MIDU). All data is in recorded in an IP format. The IP encoder may be an integral component of the VDR, or the data may be transmitted in an IP format from the data generator device.Type: GrantFiled: November 21, 2003Date of Patent: December 29, 2009Inventor: David A. Monroe
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Publication number: 20090319101Abstract: The invention relates to a method for controlling the formation flight of at least two aircraft (1,2). The first aircraft (1) includes means of transmitting its position, its velocity and its flight plan. The flight plan has predictions of altitude, velocity and time for at least one next waypoint (WPT). The second aircraft (2) includes means of receiving the information transmitted by the first aircraft (1). According to the invention, the second aircraft (2) determines its future flight plan as a function of the information received from the first aircraft (1) in order to maintain a constant separation (T) from the first aircraft (1).Type: ApplicationFiled: November 21, 2006Publication date: December 24, 2009Inventor: Francois Bernard René Coulmeau
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Patent number: 7626514Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.Type: GrantFiled: October 4, 2006Date of Patent: December 1, 2009Assignee: Honeywell International Inc.Inventors: Yasuo Ishihara, Charles D. Bateman
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Publication number: 20090281684Abstract: A flight guidance and navigation display (10) for a helicopter, includes a three-dimensional, semicircular flight guidance and navigation tunnel (12) to display a planned flight path of the helicopter; a circular surface (14), which is integrated in the flight guidance and navigation tunnel (12), which circular surface (14) includes a diameter that corresponds to that of the flight guidance and navigation tunnel (12), for displaying a longitudinal position within the flight guidance and navigation tunnel (12); a flight path prediction icon (16) for displaying a position of the helicopter relative to the flight guidance and navigation tunnel (12); and a command signal (18) that relates to the air speed, wherein via the command signal (18) a deviation from a reference speed that has been predetermined by flight planning is displayed.Type: ApplicationFiled: May 6, 2009Publication date: November 12, 2009Applicant: EUROCOPTER DEUTSCHLAND GmbHInventor: Jorrit van der Spek
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Patent number: 7617023Abstract: A process for monitoring the validity of a speed cue of an aircraft may include computing a coefficient of lift, which is representative of the lift of the aircraft, on the basis of values of static and total pressure. A first value of angle of incidence is computed on the basis of the computed coefficient of lift, and a second value of angle of incidence is determined. The difference between the first and second values of angle of incidence is computed, and the absolute value of the difference is compared with a predetermined threshold value. Based on the comparison, the speed cue is deemed valid if the absolute value of the difference is below the threshold value and deemed invalid otherwise.Type: GrantFiled: July 16, 2004Date of Patent: November 10, 2009Assignee: AIRBUS FranceInventor: Philippe Seve
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Patent number: 7610123Abstract: A method and system for guiding a vehicle comprises a location determining receiver for collecting location data for the vehicle. A vision module collects vision data for the vehicle. A location quality estimator estimates the location quality data for the location data during an evaluation time window. A vision module estimates vision quality data for the vision data during the evaluation time window. A supervisor module selects at least one of a location data weight and a vision data weight based on the quality data.Type: GrantFiled: April 15, 2005Date of Patent: October 27, 2009Assignee: Deere & CompanyInventors: Shufeng Han, John Franklin Reid, Francisco Rovira-Más
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Publication number: 20090259351Abstract: The device (1) comprises means (4) for determining speed setpoints making it possible to guide the aircraft so that it arrives at a particular waypoint at a time corresponding to a time constraint, by taking account of an upper speed limit for a current flight stretch and of an auxiliary upper speed limit for a distant flight stretch.Type: ApplicationFiled: April 13, 2009Publication date: October 15, 2009Applicant: AIRBUS FranceInventors: Maxime Wachenheim, Jean-Louis De Menorval, Sylvain Raynaud
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Publication number: 20090222150Abstract: The disclosed embodiments concern a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure, a device for measuring a side-slip angle of the aircraft, a device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, and a data-processing device capable of determining anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack, a least one laser anemometer to measure at least one true airspeed parameter of the aircraft.Type: ApplicationFiled: September 21, 2006Publication date: September 3, 2009Applicant: AIRBUS FRANCEInventor: Guillaume Preaux
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Patent number: 7561067Abstract: A measurement system for an aircraft having the three-axis components of the airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and the wind speed distribution ahead of the aircraft simultaneously in real time. It comprises a Doppler anemometer measuring the airflow speeds at a plurality of points separated by a prescribed distance in the beam irradiation direction that changes in a time series, and an inertial data measurement device measuring the movement information and positional information of the aircraft. Moreover, the display system of the aircraft includes the horizontal two-axis airspeed of the aircraft, the three-axis components of the wind speed currently encountered by the aircraft, and information on the wind speed distribution ahead of the aircraft are displayed simultaneously in real time.Type: GrantFiled: March 30, 2006Date of Patent: July 14, 2009Assignees: Japan Aerospace Exploration Agency, Mitsubishi Denki Kabushiki KaishaInventors: Naoki Matayoshi, Kimio Asaka, Yoshinori Okuno, Masahiro Hagio, Yoshihito Hirano, Shumpei Kameyama, Toshiyuki Ando, Hidetaka Kiyosue, Masashi Furuta, Tomoya Matsuda
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Patent number: 7561945Abstract: A process and device for estimating the vertical speed of a rotary wing aircraft may include integrating the sum of: (1) a first component corresponding to a vertical acceleration measurement and (2) a second component obtained from the difference between: (a) a first value incorporating a barometric measurement and (b) a second value incorporating a previous estimation of the vertical speed. The second component is derived from the difference between the first and second values by clipping this difference to eliminate, as appropriate, the part of the difference which is greater, in absolute value, than a predetermined value.Type: GrantFiled: June 29, 2005Date of Patent: July 14, 2009Assignee: EurocopterInventors: Jean-Louis Giraudy, Jean-Paul Petillon
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Patent number: 7539561Abstract: An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control systems for a small unmanned helicopter, to be mounted on said small unmanned helicopter; a servo pulse mixing/switching unit; a radio-controlled pulse generator; and autonomous control algorithms that are appropriate for the autonomous control of the aforementioned small unmanned helicopter, thereby providing an autonomous control system that provides autonomous control on the helicopter toward target values.Type: GrantFiled: December 26, 2006Date of Patent: May 26, 2009Assignees: Hirobo LimitedInventors: Kenzo Nonami, Jin Ok Shin, Daigo Fujiwara, Kensaku Hazawa, Keitaro Matsusaka
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Publication number: 20090093919Abstract: The present invention relates to a method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator (1) that comprises at least: first means (1?) for measuring the instantaneous vertical speed v of a rotorcraft; second means (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; and third means (3) for calculating the predictive vertical speed vAP of a rotorcraft, the third means being connected firstly to the first and second means via respective first and second connections (l1, l2) and containing in memory predetermined values for the minimum-power speed VY and a characteristic constant k that are constants relating to said rotorcraft of a given type of rotorcraft.Type: ApplicationFiled: September 26, 2008Publication date: April 9, 2009Applicant: EUROCOPTERInventor: Bernard CERTAIN
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Publication number: 20090062973Abstract: A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.Type: ApplicationFiled: September 4, 2007Publication date: March 5, 2009Inventors: Fabricio Reis Caldeira, Dagfinn Gangsaas, Alvaro Vitor Polati de Souza, Eduardo da Silva Martins, Marco Tulio Sguerra Vita, Jose Marcio Vieira Dias Filho, Marcos Vinicius Campos, Emerson Freitas
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Patent number: 7496433Abstract: The method includes a preliminary period in which a reference rotorcraft is used that corresponds to a rotorcraft of a particular type, with a series of noise measurements being performed on said rotorcraft (1) in flight using noise sensors (C) disposed on said reference rotorcraft, and with operating domains being determined for the reference rotorcraft in which noise is less than a maximum noise level. Thereafter, the operating point without wind and operating domains with wind are subsequently determined for a rotorcraft of the particular type on the basis of operating domains for the reference rotorcraft.Type: GrantFiled: March 30, 2005Date of Patent: February 24, 2009Assignee: EurocopterInventor: Henri-James Marze
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Patent number: 7480548Abstract: It is an object of the present invention to solve the problem of a drop in precision in conventional systems using a square pyramid type five-hole probe due to the drop in atmospheric pressure in high altitude ranges, and to provide a wide velocity range flight velocity vector measurement system that can prevent a drop in measurement precision. Furthermore, it is also an object of the present invention to provide a method for eliminating the effects of detection fluctuations caused by adhering water droplets, ice particles or dust in a wide velocity range flight velocity vector measurement system.Type: GrantFiled: September 13, 2005Date of Patent: January 20, 2009Assignees: Japan Aerospace Exploration Agency, Fuji Heavy Industries Ltd., Tokyo Aircraft Instrument Co., Ltd.Inventors: Masashi Shigemi, Akira Koike, Makoto Ueno, Tomonari Hirotani, Teruomi Nakaya, Hiroshi Wakai, Toru Iwata
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Patent number: 7471996Abstract: In an electronic control system, three-dimensional data sets (data cubes L11-L14) for different power-limiting engine parameters are stored at different engine ratings for setting a respective maximum engine power in relation to flight altitude (ALT), ambient temperature (DTAMB) and flight Mach number (MN) to separately calculate a maximum power corresponding to each parameter. For power reduction due to air bleed, corresponding separate data cubes (L21-L24) are stored. In a comparator, the respective smallest power reduction value is determined and, subsequently, the fuel supply is set according to that power reduction value. Under conforming boundary conditions, the same data cubes (L24) can be stored for different engine ratings. The system requires low storage capacity and low calculating effort.Type: GrantFiled: June 25, 2004Date of Patent: December 30, 2008Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Matthias Bartel
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Publication number: 20080312779Abstract: The flight management computer discloses and carried onboard an aircraft can be programmed with a newly apparent speed constraint while it ensures the guidance of the aircraft in the course of a landing runway approach. It then takes account of the speed constraint by using it as target speed, when it is greater than an instruction speed which depends on the number of extended flap settings and which corresponds to the addition of a further flap setting. If appropriate, the speed constraint may be bounded below, thus making it possible to remain within the limits of the flight domain of the aircraft in its configuration at the time.Type: ApplicationFiled: March 4, 2008Publication date: December 18, 2008Applicant: ThalesInventors: Jerome SACLE, Francois Coulmeau
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Publication number: 20080306639Abstract: The present invention relates to a device and methods for filtering anti-collision alerts for aircraft having a locating system charting the position of the aircraft and estimating the precision of its position. A navigation system of the aircraft calculates at least the actual speed of the aircraft, the speed instruction and a first deviation between the instruction and the actual speed, and the deviation being compared with a first reference overshoot threshold. An anti-collision system generates alerts. An alarms manager of the aircraft centralizes the alerts transmitted by the terrain anti-collision equipment of the aircraft to the crew. The alerts each posses a coding of the danger level, and the danger levels form part of a first predetermined set. The alert filter according to the invention filters sets of alerts according to the coding of their danger level.Type: ApplicationFiled: March 13, 2008Publication date: December 11, 2008Applicant: THALESInventors: Stephane Fleury, Nicolas Marty, Julia Percier
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Publication number: 20080297396Abstract: The invention generally relates to the field of computer software particularly to an improved method of providing aircrew decision aids for use in determining the optimum placement of an Electronic Attack (EA) aircraft. The core of the invention is a software program that will dynamically provide the EA flight crew situational awareness regarding a threat emitter's coverage relative to the position of the EA aircraft and to the position of any number of protected entities (PE). The software program generates information to provide visual cues representing a Jam Acceptability Region (JAR) contour, a Jam Assessment Strobe (JAS) and text for display on a number of flexibly configurable display formats posted on display units. The JAR and JAS graphics and text will aid the EA aircrew in rapidly assessing the effectiveness of a given jamming approach.Type: ApplicationFiled: February 29, 2008Publication date: December 4, 2008Inventors: James Dark, James Buscemi, Scott Burkholder
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Publication number: 20080294307Abstract: Systems and methods for aircraft guidance using a localizer capture criteria for rectilinear displacement data are disclosed. In one embodiment, the method includes determining a rectilinear deviation D between a current aircraft location and a final defined path (FDP) of an aircraft and determining a location at which the aircraft should begin a reposition maneuver based on the rectilinear deviation D. The method starts a reposition maneuver of the aircraft at a location determined based on a relationship between D and characteristics of the aircraft during the reposition maneuver. In some embodiments, the characteristics of the aircraft may include a velocity of the aircraft with respect to ground, an aircraft track angle, a heading of the FDP of the aircraft, a maximum allowed bank angle of the aircraft during a reposition maneuver, and a time allowance for aircraft rollup and rollout.Type: ApplicationFiled: August 30, 2007Publication date: November 27, 2008Applicant: The Boeing CompanyInventor: Steven B. Krogh
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Publication number: 20080269964Abstract: A system for transitioning navigation data on a mobile platform (such as a train, ship, aircraft or automobile) is provided. The system includes a source of navigation display data and an image control module. The image control module generates image data from the navigation display data based on a position of the mobile platform. The image data includes at least one first navigation display data at a first opacity and at least one second navigation display data at a second opacity. The second opacity is computed based on the position of the mobile platform. The system also includes a display device disposed within the mobile platform that displays the image data.Type: ApplicationFiled: April 30, 2007Publication date: October 30, 2008Inventor: Matthew T. Majka
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Publication number: 20080249672Abstract: A flight control system includes an Acceleration and Attitude Command/Velocity Hold mode (AACVH) algorithm which blends attitude commands with acceleration commands. This blending determines a trim attitude for a given rotorcraft flight condition.Type: ApplicationFiled: April 3, 2007Publication date: October 9, 2008Inventor: Igor Cherepinsky
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Patent number: 7433765Abstract: A static longitudinal stability (SLS) system provides an unobtrusive airspeed hold function that reacts to the pilot control inputs into the flight control system and the measured states of the aircraft to engage and disengage smoothly without any explicit mode selection by the pilot. The SLS engages airspeed hold when the aircraft is close to trimmed, non-accelerating state. This logic allows the pilot to either fly close to a desired airspeed and let SLS engage, or trim the aircraft in an accelerating/decelerating maneuver and just wait for the SLS to capture a speed when longitudinal acceleration is small. The SLS is not dependant on the pilot specifically selecting this mode, but rather engages and disengages in response to flight control system status and how the aircraft is being maneuvered.Type: GrantFiled: May 3, 2005Date of Patent: October 7, 2008Assignee: Sikorsky Aircraft CorporationInventors: Todd M. Fanciullo, Phillip J. Gold
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Publication number: 20080243314Abstract: Embodiments of the present invention provide methods, computer programs, and apparatus for adjusting a speed target of an aircraft. In particular, the adjustment of the speed target of the aircraft may allow that aircraft to maintain merging and spacing constraints with respect to a leading aircraft. According to one embodiment of the present invention, the speed target of an aircraft may be adjusted by obtaining a speed target, obtaining own ship track data for the aircraft, obtaining lead ship track data for a leading aircraft, and calculating a speed target adjustment based on the speed target, the own ship track data, the lead ship track data and merging and spacing constraints.Type: ApplicationFiled: April 2, 2007Publication date: October 2, 2008Inventor: Richard D. Ridenour
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Publication number: 20080243315Abstract: A device and method for assisting in the management of an engine failure on an aircraft. The device (1) comprises means (3, 7, 11) for automatically determining, when an engine failure is detected, vectoring settings comprising speed, thrust and altitude settings designed to be implemented on the aircraft in such a manner as to allow it to fly to a particular airport.Type: ApplicationFiled: February 5, 2008Publication date: October 2, 2008Applicant: AIRBUS FranceInventor: Daniel FERRO
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Publication number: 20080234881Abstract: A flight control system includes a collective position command algorithm for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command algorithm utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.Type: ApplicationFiled: March 19, 2007Publication date: September 25, 2008Inventors: Igor Cherepinsky, Michael R. Skaggs
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Publication number: 20080195264Abstract: The invention relates to a method of automatically managing the flight of an aircraft in turbulent air comprising notably the determination of the current speed (Vc), of an optimal turbulence speed (Vt), of a current thrust value (P). The data relating to a turbulence is acquired. An optimal turbulence speed is determined. Measuring a deviation (?) between the current speed (Vc) and the turbulence speed (Vt). Comparing the deviation (?) and a maximum deviation value (?max). Iterating k times of the previous three steps, to determine whether the deviation (?) is greater than the maximum deviation (?max) for the kth consecutive time, and the readjustment of the current thrust (P) so as to reduce the deviation (?) to a value less than that of the maximum deviation (?max) and to make the current speed (Vc) converge to the turbulence speed (Vt).Type: ApplicationFiled: October 24, 2007Publication date: August 14, 2008Applicant: ThalesInventors: Guy Deker, Jerome Sacle, Francois Coulmeau
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Patent number: 7412308Abstract: A graphical display of a dynamic vertical speed indicator (VSI).Type: GrantFiled: October 7, 2003Date of Patent: August 12, 2008Assignee: Universal Avionics Systems Corp.Inventors: Ted Naimer, Sam Hyatt, Jim Brannen, Tom Lawrence
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Publication number: 20080188999Abstract: A reference value VRef is arbitrarily selected from the range of possible rotation speeds, the position of the trimmable horizontal stabiliser is angled at least in accordance with the centring, for said value VRef, the deviation between said reference value and the accelerating aircraft speed value VC is determined, and the elevators and/or the trimmable horizontal stabiliser of the aircraft are controlled, prior to rotation, in such a way that said deviation is taken into account.Type: ApplicationFiled: May 4, 2005Publication date: August 7, 2008Applicant: AIRBUS FRANCEInventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron
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Publication number: 20080179454Abstract: An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.Type: ApplicationFiled: October 18, 2007Publication date: July 31, 2008Inventor: Pierre Balaskovic
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Publication number: 20080177428Abstract: An avionic aviation system (80) and corresponding method with ground station (81) for automatic elimination of resulting failures in aircraft (40/41/42) are proposed. The avionic aviation system (80) is linked to a multiplicity of aircraft (40/41/42) via a wireless interface (402) of the avionics (403). If a failure is detected in an aircraft (40, . . . , 42) by means of a sensor (3/401/601), a dedicated failure deployment device (603) for automatic failure elimination is selected by means of a filter module (2) and a switching device (1) of the ground station (81) for activation of the failure deployment device (603) is specifically enabled.Type: ApplicationFiled: January 24, 2008Publication date: July 24, 2008Inventors: Marcel Fok, Shinji Shirai
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Patent number: 7398182Abstract: An aircraft performance degradation detection system may include information sources, a central unit connected to the information sources, and a warning device that is connected to the central unit. Using information received from the information sources, the central unit computes the current weight and drag of the aircraft and computes a theoretical drag based on the current weight. The current and theoretical drags are compared, and a determination is made regarding performance degradation based on the comparison.Type: GrantFiled: June 23, 2005Date of Patent: July 8, 2008Assignee: Avions de Transport RegionalInventor: Gérard Petit
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Publication number: 20080161983Abstract: The invention relates to a method of piloting a rotorcraft having a plurality of engines for driving at least one lift and propulsion rotor, in which method, so long as the rotorcraft has not reached an optimum climb speed (OCS), a pitch attitude control signal (Upitch) is determined that is adapted so that the rotorcraft accelerates in application of a profile (P1, P2, P3) that varies as a function of the elapsed time and as a function of the operating state of the engines (OEI/AEO).Type: ApplicationFiled: April 30, 2007Publication date: July 3, 2008Applicant: EUROCOPTERInventor: Marc Salesse-Lavergne
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Publication number: 20080154447Abstract: A routing tool is disclosed. In one embodiment, the method and system include receiving flight data and geographic data in the aircraft, and generating route data based on the flight data and the geographic data. The route data provides information about attainable landing areas for the aircraft.Type: ApplicationFiled: December 21, 2006Publication date: June 26, 2008Inventor: Charles B. Spinelli
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Patent number: 7389163Abstract: A method of and a system for controlling personal air vehicle (PAV) traffic provides a take-off-and-landing zone, and a forward flight zone. The take-off-and-landing zone may be from the ground up to a first altitude. The forward flight zone may be from the first altitude up to a second altitude. A maximum airspeed is provided in the take-off-and-landing zone. Minimum and maximum airspeeds are provided in the forward flight zone. In the forward flight zone there is a single heading for each altitude. Any change in heading must be accompanied by a change in altitude.Type: GrantFiled: February 17, 2005Date of Patent: June 17, 2008Assignee: The Boeing CompanyInventor: Joseph M. Colich