And Vertical Glide Path Control Patents (Class 244/185)
  • Patent number: 10430653
    Abstract: A system for localizing an autonomous vehicle to a target area can include a position indicator adapted for association with the vehicle in a three dimensional configuration, a detection device configured to detect the position indicator, a computation device configured to compute a position of the vehicle based on the detected position indicator and the relationship of the configuration to the vehicle orientation, a transmitter configured to receive information from the computation device and produce a signal carrying the information, a receiver configured to receive the signal from the transmitter and filter the information therefrom, and a control system configured for association with and control of one or more directional control components of the vehicle, the control being based on the information received from the receiver relating to localizing the vehicle to the target area. A method of for localizing a vehicle to a target area is also disclosed.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: October 1, 2019
    Assignee: Landing Technologies, Inc.
    Inventors: Robert S. Malecki, Lue Her, Ryan S. Thompson, Anthony H. Giang
  • Patent number: 10409293
    Abstract: The present invention extends to methods, systems, devices, apparatus, and computer program products for gimbal stabilized components for remotely operated vehicles. Aspects of the invention include a gimbal stabilized radar system. A radar unit is mounted on a vertical (or horizontal) gimbal attached to a remotely operated aerial vehicle. In aspects, a radar unit is mounted to a gimbal having multiple degrees of freedom. When the remotely operated aerial vehicle rotates and/or changes its orientation in space, the gimbal compensates keeping the direction and elevation angle of the radar essentially constant.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: September 10, 2019
    Assignee: Olaeris, Inc.
    Inventors: Paul E. I. Pounds, Edward Lindsley
  • Patent number: 10252788
    Abstract: A user interface presented to an operator of an unmanned aerial vehicle (UAV) may be presented to facilitate the ease of operation of the UAV. The information displayed in the user interface may be customized by the operator to display selected data. The display configuration data may be saved and imported into other systems for future use. Various entities related to one or more UAVs may be presented in a hierarchical tree structure illustrating the relationship between the entities. Electronic checklists may be presented to a user to facilitate addressing common and emergency situations.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: April 9, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Andrew Royds Hayes, Darcy Lynn Davidson, Jr.
  • Patent number: 10228692
    Abstract: Systems and aircraft are provided. An avionics system for an aircraft includes: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition; a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path; a limit comparison module configured to determine whether the modeled flight condition violates aircraft limits; and a violation indicator module configured to generate an indication of impending violation.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: March 12, 2019
    Assignee: Gulfstream Aerospace Corporation
    Inventor: Kevin Prosser
  • Patent number: 10202199
    Abstract: A method and a device for monitoring a deviation of a first rotational speed of a first drive unit for an aircraft from a second rotational speed of an at least second drive unit of an aircraft. The monitoring of the deviation of the first rotational speed of the first drive unit from the second rotational speed of the at least second drive unit is carried out as a function of a comparison of a detection of a first event of the first drive unit to a detection of a second event of the at least second drive unit.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: February 12, 2019
    Assignee: ROBERT BOSCH GMBH
    Inventor: Martin Widmer
  • Patent number: 9789952
    Abstract: Methods and apparatus of notification of a flight asymmetry influencing an aircraft are disclosed herein. An example method includes monitoring a roll characteristic of an aircraft and determining an output of an autopilot system of the aircraft to control the roll characteristic. The example method further includes generating an alert based on the output and an authority of the autopilot system to control the roll characteristic.
    Type: Grant
    Filed: June 19, 2013
    Date of Patent: October 17, 2017
    Assignee: The Boeing Company
    Inventors: Dickson Fong, Frederick Emil Ludtke, II
  • Patent number: 9738399
    Abstract: A control method for an unmanned aerial vehicle (UAV) is provided. The method includes: obtaining, from a depth-sensing camera, images of a surface below the unmanned aerial vehicle; obtaining, from a gyroscope, current pitch angle of the unmanned aerial vehicle; determining, at the unmanned aerial vehicle, a current altitude of the unmanned aerial vehicle based on the images and the current pitch angle; determining, at the unmanned aerial vehicle, whether the current altitude of the unmanned aerial vehicle is less than a predefined value; and controlling, at the unmanned aerial vehicle, a drive unit to rotate so as to cause the unmanned aerial vehicle to slow down in a balanced condition if the current altitude of the unmanned aerial vehicle is less than a predefined value.
    Type: Grant
    Filed: July 29, 2015
    Date of Patent: August 22, 2017
    Assignee: HON HAI PRECISION INDUSTRY CO., LTD.
    Inventors: Hou-Hsien Lee, Chang-Jung Lee, Chih-Ping Lo
  • Patent number: 9718550
    Abstract: A seat arrangement of a passenger cabin includes at least two seat groups. The at least two seat groups are arranged consecutively between two passenger aisles running parallel to a longitudinal direction of the passenger cabin and each have two outer seat units and just one central seat unit. The seat units are set in a seating configuration. A central seat unit of at least one of the at least two seat groups is arranged offset with respect to at least one of the outer seat units of the same seat group in the longitudinal direction of the passenger cabin, as a result of which each seat unit has obstacle-free access to at least one cabin aisle.
    Type: Grant
    Filed: May 3, 2011
    Date of Patent: August 1, 2017
    Assignee: RECARO Aircraft Seating GmbH & Co. KG
    Inventor: Djunianto Ko
  • Patent number: 9676472
    Abstract: A user interface presented to an operator of an unmanned aerial vehicle (UAV) may be presented to facilitate the ease of operation of the UAV. The information displayed in the user interface may be customized by the operator to display selected data. The display configuration data may be saved and imported into other systems for future use. Various entities related to one or more UAVs may be presented in a hierarchical tree structure illustrating the relationship between the entities. Electronic checklists may be presented to a user to facilitate addressing common and emergency situations.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: June 13, 2017
    Assignee: Insitu, Inc.
    Inventors: Andrew Royds Hayes, Darcy Lynn Davidson, Jr.
  • Patent number: 9621258
    Abstract: Bi-directional personal communication systems and processes may be utilized to control unmanned systems. Such systems and processes may enable operator interface with unmanned systems as a replacement or a supplement to use of specialized hardware and rich, graphical interfaces. The bi-directional communication systems and methods also may be integrated as a subsystem within a ground control station. The system may include a personal communications device with a native interface for an operator to select command, control and/or communication (C3) messages to interact with the unmanned system, and a communication link operable to send the C3 messages selected by the operator to the unmanned system, wherein the unmanned system includes a receiver that receives the C3 messages over the communication link and an onboard computing device that processes and responds to the C3 messages received by the receiver.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: April 11, 2017
    Assignee: Kutta Technologies, Inc.
    Inventors: Douglas V. Limbaugh, David Howard Barnhard, Geoffrey David Simms
  • Patent number: 9511858
    Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
    Type: Grant
    Filed: August 16, 2012
    Date of Patent: December 6, 2016
    Assignee: AeroVironment, Inc.
    Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
  • Patent number: 9430948
    Abstract: A landing alert system and method for preventing runway excursions may include determining, during an approach of an aircraft to landing on a runway, a target touchdown point on the runway, determining a boundary descent path configured to permit safe approach and touchdown of the aircraft on the runway at or before the target touchdown point, and, in response to the aircraft crossing within a selected margin of the boundary path, alerting an operator of the aircraft.
    Type: Grant
    Filed: April 16, 2014
    Date of Patent: August 30, 2016
    Assignee: The Boeing Company
    Inventor: Mark Henderson
  • Patent number: 9163909
    Abstract: A vehicle comprises a platform, a propulsion system, a communications system, a sensor system, and a computer system. The propulsion system, communications system, sensor system, and computer system are associated with the platform. The propulsion system is configured to move the platform on a ground. The communications system is configured to establish a wireless communications link to a remote location. The sensor system is configured to generate sensor data. The computer system is configured to run a number of control processes to perform a mission and configured to perform operations in response to a number of commands from the number of operators if the number of requests is valid.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: October 20, 2015
    Assignee: THE BOEING COMPANY
    Inventor: Mahesh K. Chengalva
  • Patent number: 8897932
    Abstract: Disclosed is a flight control support device which sets a flight restricted area W along a terrain, thereby achieving improvement in safety of a small aircraft A and sufficiently securing the degree of freedom of flight course selection of a pilot. The flight control support device includes a terrain information acquirer, an aircraft information acquirer, a flight restricted area setter which sets the flight restricted area W along the terrain on the basis of the terrain information acquired by the terrain information acquirer and the aircraft information acquired by the aircraft information acquirer, and a flight control supporter which supports flight control of a flying object on the basis of the flight restricted area set by the flight restricted area setter.
    Type: Grant
    Filed: June 7, 2010
    Date of Patent: November 25, 2014
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventors: Kosuke Komatsuzaki, Masatsugu Ishiba
  • Patent number: 8498758
    Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.
    Type: Grant
    Filed: November 26, 2012
    Date of Patent: July 30, 2013
    Assignee: Rockwell Collins, Inc.
    Inventors: Douglas A Bell, James H. Doty, Sarah Barber, Felix B. Turcios
  • Patent number: 8430362
    Abstract: The invention relates to an aircraft comprising a force transmission element which detachably connects a cabin structural segment to an aircraft primary structure and which comprises a cabin bearing element and a structure bearing element, the cabin bearing element being connected to the cabin structural segment and the structure bearing element being connected to the aircraft primary structure. The force transmission element is designed in such a manner that a force transmission can take place between the cabin structural segment and the aircraft primary structure with at least one degree of freedom of movement.
    Type: Grant
    Filed: March 20, 2009
    Date of Patent: April 30, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Ulrike Graeber, Peter Grosse-Plankermann, Martin Pätz, Holger Becker
  • Patent number: 8346408
    Abstract: 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: Grant
    Filed: November 10, 2008
    Date of Patent: January 1, 2013
    Assignee: The Boeing Company
    Inventor: Ryan Todd Ratliff
  • Patent number: 8313059
    Abstract: A passenger seat assembly for a vehicle, particularly an aircraft, which is adapted to provide self-contained, individual seating and sleeping accommodation for a passenger, said seating assembly includes a supporting structure (42) for supporting said assembly off the floor of a vehicle; one or more movable, passenger-bearing, structural components (71,72); and means for connecting said movable, structural components to said structure such that said components can be selectively moved between a seat configuration, in which a plurality of passenger-bearing surfaces on said one or more structural, movable components (71,71) or said supporting structure form a seat for the passenger, and a bed configuration, in which a plurality of said bearing surfaces (47,48,67,74,76) are disposed substantially coplanarly and substantially contiguously to form a bed for the passenger; characterized in that at least one of said movable components (72) is double-sided, comprising first and second opposite sides, one of said sid
    Type: Grant
    Filed: November 20, 2008
    Date of Patent: November 20, 2012
    Assignee: Virgin Atlantic Airways Limited
    Inventors: David Ferry, Adam Bernard Wells, Luke Miles, Andrew Leslie Lawler, David Edward Starkey, Simon Frederick Mills, Gary Doy
  • Patent number: 8239077
    Abstract: 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: Grant
    Filed: April 25, 2008
    Date of Patent: August 7, 2012
    Assignee: Airbus Operations SAS
    Inventor: Alexandre Colomer
  • Patent number: 8170727
    Abstract: The invention relates to a method for calculating an approach trajectory of an aircraft (200) to an airport The aircraft is slaveable in terms of trajectory, thrust and/or speed. The aircraft is able to advance at reduced engine revs. The airport has a runway The approach trajectory terminates in an impact point (205) on the runway and has a high-altitude descent segment (217) and an intermediate geometric segment (207), to which the aircraft is slaved in terms of trajectory and speed. A step of calculating a final approach segment (208) at reduced engine revs and a landing segment is performed with a greater thrust than the reduced revs so as to prepare a possible go-around (209), to which the aircraft is slaved in terms of thrust and speed.
    Type: Grant
    Filed: April 16, 2008
    Date of Patent: May 1, 2012
    Assignee: Thales
    Inventor: Guy Deker
  • Patent number: 7991516
    Abstract: A system for supervising the landing of an aircraft by a supervisor in a control station, each of the aircraft being incapable of being controlled by any personnel onboard, the system comprises a control station and onboard aircraft control apparatus. The station includes an input device, responsive to the supervisor, for producing a control signal for controlling the landing of the aircraft; and a transmitting device, coupled to the input device, for communication with the aircraft. The aircraft apparatus includes a receiving device for communication with the station; a logic device, coupled to the receiving device, for controlling the aircraft which is programmed to pilot the aircraft to the vicinity of the airfield. The control signal is selected by the supervisor, based on the supervisor's observations of the aircraft and is transmitted to the logic device; in response thereto, the logic device controls the aircraft.
    Type: Grant
    Filed: September 4, 2007
    Date of Patent: August 2, 2011
    Inventor: Jeffrey A. Matos
  • Patent number: 7756637
    Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: July 13, 2010
    Assignee: The Boeing Company
    Inventors: Patrick Ralf Wipplinger, Richard William Ellerbrock
  • Patent number: 7502684
    Abstract: A method of automatic piloting of an aircraft during a phase of approach to a predetermined airdrop position includes automatically applying a speed profile with decreasing speed such that the aircraft will reach the airdrop position at a predetermined theoretical arrival time with a predetermined speed, the speed profile having a plurality of constant-speed levels separated by deceleration phases. An actual arrival time is automatically determined and a difference between the theoretical and actual arrival times is calculated. If the calculated difference differs from zero, the speed profile is corrected by modifying the length lengths of time that at least two constant-speed levels are applied to the aircraft so as to cancel the difference.
    Type: Grant
    Filed: December 3, 2004
    Date of Patent: March 10, 2009
    Assignee: Airbus France
    Inventor: Philippe Haas
  • Patent number: 7463956
    Abstract: This invention relates to the concept of managing the rate of change of energy in a helicopter or other aeronautical vehicle. The invention uses energy management calculations to determine the maximum longitudinal and lateral inputs that can be made while still enabling the vehicle to maintain a desired vertical state. The results of the calculations can be cued to the pilot either tactilely, aurally, or visually, or used for internal software limiting.
    Type: Grant
    Filed: July 3, 2003
    Date of Patent: December 9, 2008
    Assignee: The Boeing Company
    Inventors: Pieter G. Einthoven, Channing S. Morse
  • Patent number: 7428450
    Abstract: A method and system for providing a bearing from a vehicle to a transmitting station are described. The method includes accessing a database to obtain transmitter position information for the transmitter, obtaining vehicle position information based on a GPS signal, and generating the bearing from the vehicle to the station utilizing the transmitter position information and the vehicle position information. The system includes a database storing transmitter position information identifying a position of the transmitter, a GPS receiver obtaining vehicle position information identifying a current position of the vehicle based on a GPS signal, and a controller generating a bearing from the vehicle to the transmitter utilizing the transmitter position information and the vehicle position information.
    Type: Grant
    Filed: April 6, 2004
    Date of Patent: September 23, 2008
    Assignee: Garmin International, Inc
    Inventor: Joseph M. Oberg
  • Publication number: 20040245409
    Abstract: A method and system for alerting an aircrew of terrorist activity in a cabin of an aircraft. When a terrorist or emergency situation is detected by a flight attendant, the flight attendant speaks an activation word, which turns the personal alert unit to an active mode. The flight attendant then says one or more specific words stored as a vocabulary within the personal alert unit. Upon recognition of a spoken word stored in the personal alert unit, the personal alert unit converts the recognized word or words into a signal sent to the cockpit via the ASU to the CDU. The CDU provides an indicator to the cockpit crew of the recognized words spoken by the flight attendant.
    Type: Application
    Filed: June 21, 2004
    Publication date: December 9, 2004
    Inventors: Joseph L. Cordina, Anthony B. Couzelis
  • Patent number: 6636786
    Abstract: An energy systems management method includes steps of providing a hierarchically arranged, interrelated set of synoptic displays interfaced to an energy system for receiving information from and providing command inputs to the energy system. One synoptic display of the set of synoptic displays is an overall energy synoptic, and the other synoptic displays of the set of synoptic displays are synoptics displaying the status of corresponding energy systems. The method also includes steps of acquiring human inputs through the synoptic displays, for example, by means of a computer user interface device, and controlling the energy system by processing the human inputs through the synoptic displays to provide command inputs to the energy system.
    Type: Grant
    Filed: October 18, 2001
    Date of Patent: October 21, 2003
    Assignee: The Boeing Company
    Inventor: Walter V. Partel
  • Patent number: 6577931
    Abstract: A terrain avoidance system, method and computer program product for reducing nuisance alarms. The system includes a geometric altitude component, first and second vertical safety margin generators, and an alert component.
    Type: Grant
    Filed: July 27, 2001
    Date of Patent: June 10, 2003
    Assignee: Honeywell International Inc.
    Inventors: Kevin J Conner, Yasuo Ishihara, Steve C. Johnson
  • Patent number: 6450445
    Abstract: A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct.
    Type: Grant
    Filed: October 12, 2001
    Date of Patent: September 17, 2002
    Assignee: Moller International, Inc.
    Inventor: Paul S. Moller
  • Patent number: 5957412
    Abstract: The present invention relates to a method and a device for guiding an aircraft (A) according to a prescribed vertical flight path (T).According to the invention:the vertical distance he between said aircraft (A) and said flight path (T) is determined;the difference ve between the actual vertical velocity (Vz) of the aircraft (A) and the vertical velocity (Vzth) which it would have on the flight path (T) is determined;a vertical acceleration variation Anz is calculated:.DELTA.nz=((k1.(he-hc))+(ve-vc)).k2k1 and k2 being characteristic coefficients, hc and vc being precontrol terms, and k1.(he-hc) being restricted; andsaid restricted variation Anz is applied to the aircraft.
    Type: Grant
    Filed: September 24, 1997
    Date of Patent: September 28, 1999
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventors: Yves Saint Upery, Eric Peyrucain
  • Patent number: 5826834
    Abstract: A self adaptive limiter for use in aircraft control systems during approach and landing is disclosed. Estimated flight path angle is continuously computed during the glidepath tracking phase until a predetermined lock altitude above ground when a nominal flight path angle is latched. Nominal vertical speed is continuously computed below the lock altitude as a function of the latched nominal flight path angle and ground speed of the aircraft. A vertical speed limit function is generated as a function of the nominal vertical speed and radio altitude. During approach and landing a pitch limit is computed from the vertical speed limit, vertical speed, ground speed, and pitch. When a pitch command to the autopilot exceeds the pitch limit(i.e. commands excessive pitch down attitude), it is limited to the pitch limit thus preventing the aircraft from descending below a safe altitude.
    Type: Grant
    Filed: October 19, 1994
    Date of Patent: October 27, 1998
    Assignee: Honeywell Inc.
    Inventors: William F. Potter, Byron F. Birkedahl
  • Patent number: 5799846
    Abstract: A portable holder for holding containers for feeding a product from the container to the human body such as intravenous feeding or colon flushing in which the holder is strapped to the upper torso of the human body. Being strapped to the body, it enables the person to be mobile without having to push along a cart or a stand. It also gives the person an unlimited range since the container goes with the person.
    Type: Grant
    Filed: November 7, 1996
    Date of Patent: September 1, 1998
    Inventor: Frederick W. Pfleger
  • Patent number: 5716032
    Abstract: An automatic landing system for guiding an unmanned aerial vehicle along a predetermined path to a predetermined point on the ground. The system includes an image processing means resident in the motion compensation processor that computes aerial vehicle parameters. The computed parameters are altitude, changes in altitude, changes in pitch and yaw angles, roll angle and changes thereto, and changes in cross range and down range position. These computations are based on the movement of elements in the video of an imaging sensor onboard the aerial vehicle. The motion compensation processor also measures the distance (in pixels or picture elements) between two beacons placed a known distance apart on either side of the apparent touchdown point. A recovery control processor uses these parameters to compute both desired and actual altitude as a function of range from the vehicle to the apparent point of touchdown and to provide offset error in azimuth from the desired flight path to the landing area.
    Type: Grant
    Filed: April 22, 1996
    Date of Patent: February 10, 1998
    Assignee: United States of America as represented by the Secretary of the Army
    Inventor: Pat H. McIngvale
  • Patent number: 5590853
    Abstract: An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value.
    Type: Grant
    Filed: February 3, 1992
    Date of Patent: January 7, 1997
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonard M. Greene
  • Patent number: 5377937
    Abstract: An aircraft autoland flare control system which augments the autopilot's aircraft flare control commands in the event the aircraft exceeds defined flare envelopes, monitors aircraft longitudinal position, altitude, altitude rate, lateral position and lateral position rate during flare, and outputs commands to correct aircraft position thus minimizing touchdown dispersion in both the longitudinal and lateral axes. When the aircraft deviates from the flare envelopes, such as may be due to extreme atmospheric conditions such as wind gusts, a signal commanding pitch or roll correction is output to the pitch or roll control loop which subsequently acts to adjust aircraft position such that the aircraft's flarepath is returned to within the flare envelopes.
    Type: Grant
    Filed: September 3, 1991
    Date of Patent: January 3, 1995
    Assignee: The Boeing Company
    Inventors: Brian K. LaMay, Asamitsu Maeshiro, William F. Shivitz
  • Patent number: 4488233
    Abstract: A path indicating apparatus for indicating a path so that a moving vehicle movable in the horizontal and vertical directions, such as an aircraft, may move along such a predetermined path. The predetermined path is defined as an intersecting line of two scanning planes which are formed by scanning signals having a narrow beam width in a horizontal plane and a vertical plane, respectively. The vehicle is provided with a plurality of detectors arranged in the horizontal and vertical directions for detecting the signals being scanned in the horizontal and vertical planes, respectively, so that the detectors arranged in the vertical and horizontal directions may detect deviation of the vehicle in the horizontal and vertical planes, respectively. The vehicle is responsive to the detected signals from the respective detectors to determine the moving direction to be taken by the vehicle so that the vehicle may move along the path and the vehicle is steered responsive to the determined direction outputs.
    Type: Grant
    Filed: September 28, 1981
    Date of Patent: December 11, 1984
    Inventor: Toshihiro Tsumura
  • Patent number: 4345310
    Abstract: The present invention deals with a flight control process and device for an aircraft approach and landing. More in particular, the invention in use simulates ILS by using an infrared radiation source at the desired landing site. The invention comprises the steps of determining an axis defined by the infrared radiation source, forming a predetermined guide slope line with respect to the horizontal and oriented according to a determined approach magnetic heading, recording the aircraft position with respect to the source, determining the angular deviations in azimuth and in elevation of the sighting axis with respect to the said glide slope line, and operating the aircraft flight controls to return said deviations to zero.
    Type: Grant
    Filed: January 2, 1980
    Date of Patent: August 17, 1982
    Assignee: Societe Francaise d'Equipements pour la Navigation Aerienne
    Inventor: Bernard Gautier
  • Patent number: 4040005
    Abstract: Flight path angle is displayed relative to the aircraft reference indicator in a unique display and aircraft control system particularly useful during approach operations. Flight path angle is computed as a function of vertical velocity of the aircraft and air speed. Angle of attack is displayed as an angle relative to the flight path angle and is derived by computing the difference between pitch and flight path angle. Thrust command is displayed vertically relative to the aircraft reference indicator while heading command is displayed laterally with respect to the aircraft reference indicator.
    Type: Grant
    Filed: November 12, 1975
    Date of Patent: August 2, 1977
    Inventor: William W. Melvin
  • Patent number: 4004758
    Abstract: Method and apparatus for providing a helicopter with a decelerated approach owards a landing site. An MLS system provides the aircraft with azimuth, elevation, range and range rate information. The aircraft flies towards the approach path and once it is acquired, the aircraft is decelerated until a predetermined range rate is achieved, typically 40 knots, at which point the aircraft's heading is frozen and further corrections to the aircraft's lateral position are made by exclusive use of lateral roll commands.
    Type: Grant
    Filed: December 10, 1975
    Date of Patent: January 25, 1977
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Robert P. Boriss, Thomas F. McNamara
  • Patent number: 3964053
    Abstract: 1. A system adapted to guide an aircraft along a path defined by frequency modulated signals of a transmitted conical scan pattern, comprising a receiver carried by said aircraft to receive said signals, means to detect from said signals and the amplitude modulation of said signals caused by the movement of said aircraft relative to the axis of said conical scan pattern any rate of change of the direction of movement of said aircraft with respect to the nutation axis of said conical scan pattern, and means responsive to said detected rate of change to direct the movement of said aircraft along a path within said conical scan pattern defined by any line of constant scan modulation.
    Type: Grant
    Filed: March 15, 1957
    Date of Patent: June 15, 1976
    Assignee: International Telephone and Telegraph Corporation
    Inventor: William H. Heiser