Electric Course Control Patents (Class 244/175)
  • Patent number: 8280564
    Abstract: The method of optimizing the exit of an aircraft traversing for a known duration (D) a holding circuit forming a racecourse comprising two parallel branches of the same distance, the branches being traversed in a first time (t1), and two arcs of the same radius linking respectively the ends of each branch, the two arcs being traversed in a second time (t2), the holding circuit comprising an exit point situated at the end of one of the branches is characterized in that the distance of the branches of the holding circuit for the last two loops performed are adjusted so that the aircraft is substantially in proximity to the exit point when the duration (D) has elapsed.
    Type: Grant
    Filed: May 1, 2008
    Date of Patent: October 2, 2012
    Assignee: Thales
    Inventors: Jérôme Sacle, Manuel Gutierrez-Castaneda
  • Patent number: 8275499
    Abstract: The invention relates to a device for formulating a flight plan ensuring sufficient safety margins for a duration of a few minutes in relation to the set of flight constraints that could arise and comprising means for: detecting the surrounding moving objects (aircraft or meteorological phenomena), evaluating their type and the danger that they represent, formulating a reconfiguration flight plan ensuring a separation with these phenomena and taking best account of the constraints of the initially followed flight plan, avoiding prohibited or regulated airspaces and avoiding the surrounding relief with ad hoc operational margins.
    Type: Grant
    Filed: October 14, 2009
    Date of Patent: September 25, 2012
    Assignee: Thales
    Inventors: Francois Coulmeau, Manuel Gutierrez-Castaneda, Nicolas Marty
  • Patent number: 8249761
    Abstract: 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: Grant
    Filed: July 8, 2009
    Date of Patent: August 21, 2012
    Assignee: Saab AB
    Inventors: Hasse Persson, Jonas Lovgren
  • Publication number: 20120199698
    Abstract: A gust-insensitive unmanned air vehicle (UAV) for imaging the ground, comprising a substantially neutrally stable air frame having a fuselage and at least three wings which include control surfaces. The wings are arranged in symmetrical relation about the fuselage and confer the UAV with a roll stability about a longitudinal axis of the fuselage for any roll angle. The UAV also includes a propulsion device for propelling the UAV in flight, an image sensor for imaging the ground, and a flight control system for controlling the in-flight operation of the UAV. The flight control system includes flight control sensors and is operative to render the UAV gust insensitive in response to inputs from the flight control sensors.
    Type: Application
    Filed: September 6, 2011
    Publication date: August 9, 2012
    Applicant: CRANFIELD AEROSPACE LTD
    Inventors: Peter Geoffrey THOMASSON, Robert Idris JONES, David Ian Alistair POLL
  • Patent number: 8234068
    Abstract: A present novel and non-trivial system, module, and method for constructing a flight path used by an avionics system are disclosed. A processor receives flight plan data and object data associated with terrain and obstacles. Free cells are extracted above the objects using a recursive space decomposition technique, and a reference path is formed through traversable free space determined from the availability of free cells. In an additional embodiment, threat data associated with hostile military weaponry and significant meteorological conditions could affect the availability of free cells. A genetic algorithm applying genetic operators which include mutators is employed with aircraft kinematic constraints to refine the reference path used to form a population of best path candidates. When a best path is reached after cycling through a re-generation process of path candidates, flight path data representative of the best path is generated and provided to at least one avionics system.
    Type: Grant
    Filed: January 15, 2009
    Date of Patent: July 31, 2012
    Assignee: Rockwell Collins, Inc.
    Inventors: Shih-Yih Young, Kristen M. Jerome
  • Publication number: 20120181388
    Abstract: An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal.
    Type: Application
    Filed: January 14, 2011
    Publication date: July 19, 2012
    Inventor: Martyn Cowley
  • Publication number: 20120175468
    Abstract: A system for delivering cooling water to building roofs by means of drone aircraft is disclosed. Control systems for navigation and precisely targeting a water spray are disclosed.
    Type: Application
    Filed: February 11, 2011
    Publication date: July 12, 2012
    Inventor: Eric Zerof
  • Patent number: 8214136
    Abstract: The invention relates to assistance in the navigation of an aircraft in the cruising phase, particularly in an emergency rerouting situation. The invention relates to a method of assisting in the choice of rerouting airports for an aircraft having a position P and a speed V.: generating A first list LAC—1 of airport names Ai is generated. The first list LAC—1 has N airport names, with i being an index between 1 and N which uniquely identifies an airport that an organization operating the aircraft chooses as a relevant destination. A number m is determined which is a minimum between a predefined number M and the number N. M airport names are presented from the first list LAC—1 to an operator of the aircraft in a predefined order.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: July 3, 2012
    Assignee: Thales
    Inventor: Christophe Caillaud
  • Patent number: 8190308
    Abstract: 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: Grant
    Filed: July 25, 2006
    Date of Patent: May 29, 2012
    Assignee: Airbus Operations SAS
    Inventors: Fabien Pitard, Jean-Pierre Demortier, Florence Aubry
  • Patent number: 8190305
    Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft.
    Type: Grant
    Filed: September 11, 2009
    Date of Patent: May 29, 2012
    Assignee: Orbital Research Inc.
    Inventors: Troy S. Prince, Richard Kolacinski, Mehul Patel
  • Publication number: 20120061521
    Abstract: An airplane transfer system for transferring an airplane comprising an airplane control component. The system comprises: a transfer module comprising at least one motor and adapted to transfer an airplane; and a controller coupled to the transfer module and configured to: i) receive a at least one transfer signal that is responsive to one or more commands provided via the airplane control component; and ii) control the transfer module in response to the transfer signal, wherein the commands are a priori capable of controlling the airplane or components thereof.
    Type: Application
    Filed: September 21, 2011
    Publication date: March 15, 2012
    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Arie PERRY, Ran BRAIER
  • Patent number: 8128034
    Abstract: In rotorcraft having rotors on multiple masts, a controller causes opposing roll mast moments to be applied to the different rotors. In preferred embodiments, the opposing roll moment is the result of increasing the lift on the advancing blade and reducing the lift on the retreating blade on the second rotor. This can be accomplished in any suitable manner, such as by applying differential cyclic roll control to the two rotors by tilting the two Swashplates of the two rotors or by using Individual Blade Control (IBC).
    Type: Grant
    Filed: August 15, 2006
    Date of Patent: March 6, 2012
    Inventor: Abe Karem
  • Patent number: 8121747
    Abstract: Embodiments of a process and a program product are provided suitable for implantation by a flight management system (FMS), which is deployed onboard an aircraft and including a display device and a user interface. The FMS operable in a plurality of non-precision approach modes. In one embodiment, the process includes the steps of: (i) receiving data via the user interface designating an approach in a flight plan; (ii) enabling the pilot to utilize the user interface to select a non-precision approach mode from the plurality of non-precision approach modes if the designated approach is a non-precision approach; and (iii) placing the FMS in the selected non-precision approach mode during the designated approach.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: February 21, 2012
    Assignee: Honeywell International Inc.
    Inventors: Dennis David Loots, Erwan Paricaud, Yannick Thebault
  • Patent number: 8115149
    Abstract: A Hybrid Projectile is provided for delivering an explosive payload to a target wherein the Hybrid Projectile may be steered in flight using relatively inexpensive means. The Hybrid Projectile is exteriorly configured in the same physical exterior configuration of conventional ammunition of various standard types so it can be launched in conventional manner from the same weapon systems. However, internal features allow the Hybrid Projectile to be transformed in flight from a command signal to deploy wings and fins, and in some projectiles to telescope open to deploy such wings and fins. An inexpensive televisual means is activated in the fore region of the round which through RF uplink command can be used to select a path, while motors on the wings can then be used to more precisely glide the projectile to a target, or otherwise to abort the target run.
    Type: Grant
    Filed: July 21, 2009
    Date of Patent: February 14, 2012
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Leon R. Manole, Ernest L. Logsdon, Jr., Mohan J. Palathingal, Anthony J. Sebasto
  • Patent number: 8087616
    Abstract: A system operates to guide an aircraft to or along a route designed to maintain the aircraft within a safe glide distance of an acceptable emergency landing area. The system uses a database of emergency landing areas with glide characteristics of an aircraft to determine a route that minimizes travel time or other specified parameter, while keeping the aircraft within a safe glide distance of a landing area in the database meeting the landing requirements for the aircraft.
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: January 3, 2012
    Assignee: Hoshiko, LLC
    Inventor: Gary Stephen Shuster
  • Patent number: 8089033
    Abstract: A method and apparatus for attacking a plurality of dispersed targets are herein presented. In particular, the method and apparatus herein presented allow the user to upload target data onto a pod mounted on a host aircraft. Upon reaching the pre loaded target location, the pod releases a plurality of individually targeted Micro Air Vehicles (MAVs), thereby allowing the user to attack a plurality of dispersed targets from a single aircraft standing off at a significant distance from the target area.
    Type: Grant
    Filed: June 18, 2008
    Date of Patent: January 3, 2012
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Paul A. Zank, Paul D. Zemany
  • Publication number: 20110315546
    Abstract: The present disclosure relates to an altitude-adjustable apparatus comprising: a platform; a device for controllably raising the altitude of the platform; a water supply combined with said platform; a device for converting water into the components thereof through solar power; and means for liquefying and storing the resulting liquefied hydrogen in tanks, the latter being built into flying bodies that are designed to arrive at a target area and dispense the liquefied hydrogen.
    Type: Application
    Filed: March 10, 2010
    Publication date: December 29, 2011
    Applicant: ASTRIUM SAS
    Inventor: Jean-François Geneste
  • Patent number: 8085168
    Abstract: An electronic display instrument configured to secure in a desired position over multiple pre-existing instrument holes in a dashboard of an aircraft in place of multiple conventional display instruments, each conventional instrument having a conventional readout. The instrument comprises a display screen having a plurality of readouts corresponding to the conventional readouts of the multiple conventional instruments that the electronic display instrument replaces. The instrument further includes a body having a front and a back opposite the front and a top and a bottom opposite the top. The body is positioned adjacent and connected to the display screen. The instrument also includes an electronics module protruding from the back of the body to position in one of the pre-existing instrument holes in the dashboard panel of the aircraft.
    Type: Grant
    Filed: July 4, 2007
    Date of Patent: December 27, 2011
    Inventor: Jeffrey D. Bethel
  • Patent number: 8025255
    Abstract: An aircraft piloting method and device for picking up a vertical profile of a flight plan. The device combines a manual piloting device that enables a pilot to control the start of the picking-up of a vertical profile and an automatic piloting device for automatically ending the vertical profile picking-up and following the vertical profile.
    Type: Grant
    Filed: June 12, 2008
    Date of Patent: September 27, 2011
    Assignee: Airbus Operations SAS
    Inventors: Patrice Rouquette, Erwan Cadot, Martin Legay
  • Patent number: 7969110
    Abstract: The invention relates to an actuator having an (auto)synchronous rotary electric motor and a reversible speed-reducing gearbox coupled to the motor to be driven in rotation thereby An outlet shaft is coupled to the speed-reducing gearbox to be driven in rotation thereby A first angular position sensor and a control circuit are connected to the motor. The circuit delivers a motor power supply signal that varies as a function of a position setpoint signal applied to the control circuit and as a function of signals delivered by the angular position sensor. The gearbox has a plurality of speed-reducing each having a pair of gears mounted to rotate about two parallel axes of rotation.
    Type: Grant
    Filed: September 8, 2008
    Date of Patent: June 28, 2011
    Assignee: Eurocopter
    Inventors: Philippe Vincent, Sébastien Pellegrino, Bernard Gemmati
  • Patent number: 7970502
    Abstract: Apparatuses and methods for controlling autoflight systems are disclosed herein. An apparatus for use with an aircraft having an autoflight system can include an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes. The autoflight performance selector has at least a first selection and a second selection different than the first selection. Selecting the first selection causes the response of the autoflight system to flight guidance instructions to not exceed a first level in the at least two axes, and selecting the second selection causes the response of the autoflight system to the flight guidance instructions to not exceed a second level in the at least two axes different than the first level.
    Type: Grant
    Filed: March 30, 2009
    Date of Patent: June 28, 2011
    Assignee: The Boeing Company
    Inventors: Daniel J. Boorman, Peter D. Gunn, John C. Griffin, III
  • Publication number: 20110121140
    Abstract: An automatic takeoff apparatus for an aircraft includes: an altitude sensor; an airspeed sensor; an attitude angle sensor; a direction sensor; a takeoff command inputting section; and a control device for controlling a propulsion device and an control surface of the aircraft, wherein the control device includes: a takeoff run control section for realizing a takeoff run by controlling the propulsion device to provide a maximum output and by controlling the control surface to maintain the attitude angle and the traveling direction constant, in response to the takeoff command; a rotation control section for controlling the control surface to rotate when the airspeed exceeds a predetermined speed; and an ascending flight control section for controlling the propulsion device and the control surface to perform an ascending flight up to a target altitude with a predetermined speed maintained, when the altitude exceeds a predetermined altitude.
    Type: Application
    Filed: November 24, 2010
    Publication date: May 26, 2011
    Inventors: Akihiro Yamane, Mitsuru Kono, Takahiro Kumamoto
  • Patent number: 7942370
    Abstract: A vortex detection device suitable for use in fighter aircraft including an angle-of-attack sensor, an angle-of-attack processing unit connected to the angle-of-attack sensor capable of forming a signal representative of current air stream's angle-of-attack, a synthetic angle-of-attack estimation unit capable of forming a synthetic angle-of-attack signal, and a vortex level calculation unit connected to the processing and estimation unit, capable of calculating a vortex level signal, and a vortex detection unit connected to the vortex level calculation unit, for deciding, based on the vortex level signal, if a vortex is detected.
    Type: Grant
    Filed: May 7, 2007
    Date of Patent: May 17, 2011
    Assignee: SAAB AB
    Inventors: Robert Hillgren, Tommy Persson, Fredrik Karlsson
  • Patent number: 7925394
    Abstract: The method in accordance with the invention is a method of providing a 3D emergency descent trajectory for aircraft comprising the steps of searching for at least one possible better trajectory allowing a secure continuation in relation to the relief and/or the surrounding conditions towards a homing point as soon as a situation requiring an unscheduled modification of the current trajectory occurs, wherein this trajectory is updated as a function of the alterations in the surrounding conditions, as a function of the information provided by the onboard sensors and/or outside information received.
    Type: Grant
    Filed: October 10, 2007
    Date of Patent: April 12, 2011
    Assignee: Thales
    Inventors: Guy Deker, Nicolas Marty, François Coulmeau
  • Publication number: 20110057075
    Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.
    Type: Application
    Filed: November 18, 2010
    Publication date: March 10, 2011
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: David C. Hursig, Steven D. Martinez
  • Publication number: 20110057074
    Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.
    Type: Application
    Filed: September 9, 2009
    Publication date: March 10, 2011
    Applicant: Aurora Flight Sciences Corporation
    Inventors: Adam Woodworth, Brandon Suarez
  • Patent number: 7904213
    Abstract: The invention relates to a method of assisting in the navigation of an aircraft comprising a step for updating a flight plan according to a new clearance received on board by a ground/onboard communication system. The clearance comprises an action conditional on the flight plan linked to a floating point of the path defined by an altitude constraint of the aircraft; on receipt of the new clearance, the update is performed directly by means of the FMS linked to the communication system. This is a predictive method.
    Type: Grant
    Filed: March 14, 2007
    Date of Patent: March 8, 2011
    Assignee: Thales
    Inventor: François Coulmeau
  • Patent number: 7874521
    Abstract: A system operates to guide an aircraft to or along a route designed to maintain the aircraft within a safe glide distance of an acceptable emergency landing area. The system uses a database of emergency landing areas with glide characteristics of an aircraft to determine a route that minimizes travel time or other specified parameter, while keeping the aircraft within a safe glide distance of a landing area in the database meeting the landing requirements for the aircraft.
    Type: Grant
    Filed: October 17, 2006
    Date of Patent: January 25, 2011
    Assignee: Hoshiko LLC
    Inventor: Gary Stephen Shuster
  • Publication number: 20110006166
    Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.
    Type: Application
    Filed: August 31, 2010
    Publication date: January 13, 2011
    Inventors: Paul E. ARLTON, David J. Arlton
  • Patent number: 7841563
    Abstract: An air data system and method for a ducted fan air-vehicle is described. The air data system includes a plurality of air pressure sensors placed around a lip of an air duct of the ducted fan air-vehicle. The air data system calculates the speed and direction of airflow surrounding the ducted fan air-vehicle based on pressure data measured across the lip of the air duct. Additionally, the air data system may estimate forces generated by airflow surrounding the air-vehicle.
    Type: Grant
    Filed: March 13, 2007
    Date of Patent: November 30, 2010
    Assignee: Honeywell International Inc.
    Inventors: Emray R. Goossen, Jonathan Lee Fleming
  • Publication number: 20100282916
    Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.
    Type: Application
    Filed: April 15, 2010
    Publication date: November 11, 2010
    Applicant: THE BOEING COMPANY
    Inventors: David Garrido-Lopez, Ramon Gomez Ledesma
  • Publication number: 20100256839
    Abstract: Methods and systems are provided for using a measurement of only one axis of a three-axis magnetometer to perform at least one corrective action on an unmanned aerial vehicle (“UAV”). An exemplary embodiment comprises (i) receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, (ii) comparing the measurement to an allowable range of attitudes, (iii) determining that the measurement is not within the allowable range of attitudes, and (iv) performing at least one corrective action on the UAV.
    Type: Application
    Filed: April 2, 2009
    Publication date: October 7, 2010
    Applicant: Honeywell International Inc.
    Inventor: David Fitzpatrick
  • Publication number: 20100230546
    Abstract: A control system and method for control of a cyclical flying system which uses lift segments, which may be airfoils, which rotate around a central hub, similar to the mechanics of an autogyro. The airfoils may achieve speeds significantly above the wind speed feeding the system. The airfoils may be linked to the central hub by flexible radial tethers which stiffen considerably as the speed of the airfoil increases. The central hub may be linked to the ground with an extendible main tether. Power generation turbines may reside on the airfoils and utilize the high apparent wind speed for power generation. The generated power may travel down the radial tethers and across a rotating power conduit to the main tether and to the ground. The airborne assembly may have the rotational speed of the airfoils, its altitude, and its attitude controlled by using control surfaces linked to the airfoils, or by control of the angle of attack of the airfoils relative to a central hub, or relative to each other.
    Type: Application
    Filed: September 25, 2009
    Publication date: September 16, 2010
    Inventors: Joeben Bevirt, Jeffrey K. Gibboney, Giles M. Biddison, David D. Craig, Allen Harris Ibara
  • Publication number: 20100228406
    Abstract: Disclosed herein is a method and system for flying a ducted-fan air-vehicle, such as an unmanned air-vehicle. The method includes receiving a first input associated with a target point of interest and pointing the gimbaled sensor at the target point of interest. The method further includes receiving a second input corresponding to a desired flight path and selecting a velocity vector flight command to achieve the desired flight path. Selecting the velocity vector flight command includes converting attitude data from the gimbaled sensor into a velocity vector flight command. The method further includes operating the flight of the UAV according to the selected velocity vector flight command and the gimbaled sensor remains fixed on the target point of interest during the flight of the UAV.
    Type: Application
    Filed: March 3, 2009
    Publication date: September 9, 2010
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Eric E. Hamke, John Ihlein
  • Publication number: 20100219298
    Abstract: A process and device for the automatic flight optimisation of the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.
    Type: Application
    Filed: February 26, 2010
    Publication date: September 2, 2010
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventor: Frederic Sauvinet
  • Publication number: 20100181431
    Abstract: A flight assistance apparatus for providing assistance in flying an aircraft, including: a yoke operated by a pilot of the aircraft; and a flight instruction section that instructs, with an aid of the yoke, the pilot to fly the aircraft in such a manner as to avoid a critical flight range when the aircraft approaches the critical flight range.
    Type: Application
    Filed: January 11, 2010
    Publication date: July 22, 2010
    Inventor: Masatsugu ISHIBA
  • Patent number: 7761194
    Abstract: A method and device that assist a pilot of a follower aircraft during a patrol flight, by presenting on a viewing screen an indicator that provides information as to the possibility of engagement of an automatic pilot during a patrol flight.
    Type: Grant
    Filed: February 22, 2007
    Date of Patent: July 20, 2010
    Assignee: Airbus France
    Inventors: Falk Winkler, Guillaume Fouet, Didier Menras
  • Patent number: 7742846
    Abstract: A method of transitioning from a complex response flight state to a ground operation control state. Pilot intent is determined through collective position information to control the transition. An independent cockpit switch activates an emergency surface contact transition function for use with a fly-by-wire (FBW) flight control system. Once the surface contact transition function is active, FBW control laws transition from a fully augmented flight state, through an augmentation deactivation state and into the surface contact state.
    Type: Grant
    Filed: June 2, 2006
    Date of Patent: June 22, 2010
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Todd M. Fanciullo, Paul Morphy, Lorren Stiles, Alex Faynberg
  • Publication number: 20100102173
    Abstract: Control systems, controllers, systems, and methods of stabilizing a light aircraft during flight and/or ground maneuvers, such as by detecting and/or correcting undesired yaw characteristic, such as, for example, yaw angle, yaw rate, and/or yaw fluctuations.
    Type: Application
    Filed: October 21, 2009
    Publication date: April 29, 2010
    Inventors: Michael L. Everett, Louis J. Everett, Mario Ruiz
  • Patent number: 7693614
    Abstract: An emergency navigational system that monitors the navigation of an aircraft by comparing actual flight parameter data to predefined flight parameter data to thereby determine if the actual flight parameter data deviates beyond a defined value, and if so, activating a navigational controller to at least partially control the navigation of the aircraft.
    Type: Grant
    Filed: March 12, 2004
    Date of Patent: April 6, 2010
    Inventor: Brian E. Turung
  • Patent number: 7689324
    Abstract: A vehicle operator interface is disclosed. The vehicle operator interface comprises a visual display device. A first indicator which is representative of a vehicle energy target, a second indicator representative of a vehicle energy vector and a third indicator representative of a vehicle capability zone are on the display.
    Type: Grant
    Filed: June 21, 2004
    Date of Patent: March 30, 2010
    Assignee: Rockwell Collins, Inc.
    Inventors: Michael J. Krenz, David J. Weiler
  • Publication number: 20100076625
    Abstract: A flight control system for aircraft, such as for a vehicle with a ducted fan propulsion system which also produces rotary moments and side forces for control purposes. The flight control system of the present invention is designed in a manner that will ensure the safety of the vehicle in event of a malfunction in any one of its channels and enable the flight to continue down to a safe landing.
    Type: Application
    Filed: November 29, 2007
    Publication date: March 25, 2010
    Inventor: Raphael Yoeli
  • Publication number: 20100012789
    Abstract: A vortex detection device suitable for use in fighter aircraft including an angle-of-attack sensor, an angle-of-attack processing unit connected to the angle-of-attack sensor capable of forming a signal representative of current air stream's angle-of-attack, a synthetic angle-of-attack estimation unit capable of forming a synthetic angle-of-attack signal, and a vortex level calculation unit connected to the processing and estimation unit, capable of calculating a vortex level signal, and a vortex detection unit connected to the vortex level calculation unit, for deciding, based on the vortex level signal, if a vortex is detected.
    Type: Application
    Filed: May 7, 2007
    Publication date: January 21, 2010
    Applicant: SAAB AB
    Inventors: Robert Hillgren, Tommy Persson, Fredrik Karlsson
  • Patent number: 7631834
    Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.
    Type: Grant
    Filed: April 19, 2007
    Date of Patent: December 15, 2009
    Assignee: Stealth Robotics, LLC
    Inventors: Samuel Alan Johnson, William Dennis Burkard, Robert H. Mimlitch, III, Robert Henry Mimlitch, Jr., David Anthony Norman
  • Publication number: 20090218439
    Abstract: A method for emplacing sensors, comprising the steps of modifying an existing sensor to attach an autorotational mechanism and deploying said sensor by autorotational means.
    Type: Application
    Filed: May 6, 2009
    Publication date: September 3, 2009
    Applicant: BAE Systems Information and Electronic Systems Integration Inc.
    Inventor: Mark A. Carlson
  • Patent number: 7571878
    Abstract: 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: Grant
    Filed: May 18, 2006
    Date of Patent: August 11, 2009
    Assignee: SAAB AB
    Inventors: Hasse Persson, Jonas Lövgren
  • Patent number: 7568662
    Abstract: A method and system for preventing the control of an aircraft from the cockpit. In an exemplary embodiment, the system could be triggered externally. For example, an air traffic control (ATC) station could determine that the aircraft has deviated from its planned flight path. If personnel at the ATC station decide that the deviation is not attributable to the actions of the authorized flight crew, the personnel can transmit a signal to the aircraft that disables all normal cockpit control of the aircraft. Once normal flight controls are disabled, the aircraft may execute a preprogrammed emergency flight plan via its autopilot system, with or without the use of a flight management system (FMS). The emergency flight plan could cause the aircraft to fly to a sparsely populated area and enter a holding pattern, or it could cause the aircraft to land in a sparsely populated area or at an airport using an autoland system.
    Type: Grant
    Filed: November 27, 2001
    Date of Patent: August 4, 2009
    Assignee: Honeywell International Inc.
    Inventor: James P. Conner
  • Patent number: 7568655
    Abstract: A vertical takeoff and landing aircraft according to the invention includes multiple thrust producing devices that produce thrusts applied in the substantially vertically upward direction; a target attitude setting portion that sets a target attitude used in attitude control of the aircraft; an inertia moment deriving portion that derives an inertia moment applied around a predetermined rotational axis of the aircraft; and a thrust adjustment portion that adjusts, during the attitude control of the aircraft, the thrusts to be produced by the respective thrust producing devices based on the target attitude set by the target attitude setting portion and the inertia moment during the attitude control, which is derived by the inertia moment deriving portion.
    Type: Grant
    Filed: August 16, 2006
    Date of Patent: August 4, 2009
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masatsugu Ishiba
  • Patent number: 7556224
    Abstract: An aircraft flight control surface actuation system includes a plurality of flap actuators, and a plurality of slat actuators. The actuators receive actuator position commands from an actuator control unit and, in response, move flaps and slats between stowed and deployed positions. The flight control surface actuator control unit includes a plurality of independent actuator control channels. One or more of the independent actuator control channels is coupled to both a flap actuator and a slat actuator, and is configured to selectively supply the actuator position commands thereto.
    Type: Grant
    Filed: December 27, 2005
    Date of Patent: July 7, 2009
    Assignee: Honeywell International Inc.
    Inventors: Andrew T. Johnson, Casey Hanlon, Calvin C. Potter
  • Patent number: 7543780
    Abstract: A small unmanned air vehicle system having autonomous electrical energy transmission line docking capability and especially usable in military or other surveillance situations. Transmission line field sensing by the small unmanned air vehicle is used as an addition to global position system and other navigation methods and is especially applied to vehicle docking maneuvers. A plurality of vehicle carried electromagnetic fields-responsive sensors provides transmission line based signals to the vehicle guidance system in both far field and near field environments. Surveillance sensors are included in the vehicle payload. Vehicle battery charging energy procurement from the transmission line docking is included. Related commonly assigned patent documents are identified.
    Type: Grant
    Filed: January 13, 2006
    Date of Patent: June 9, 2009
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventors: Patrick T. Marshall, Douglas M. Abner, Robert Williams