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A vest or belt is integrally formed with tubular, pet receiving passageways which extend around the wearer's body and terminate in pocket-like chambers for feeding and retrieval.
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| Number | Title | Issue Date |
| 7959111 | Angle of attack automated flight control system vertical control function The present invention is directed to an AOA (angle of attack) vertical control function for an AFCS (automated flight control system) for an aircraft. The AOA vertical control function of the AFCS causes the aircraft to climb or descend while maintaining the aircraf... | 06/14/2011 |
| 7874522 | Systems and methods for tracing aircraft vortices Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the trace... | 01/25/2011 |
| 7428450 | Method and system for using a database and GPS position data to generate bearing data 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,... | 09/23/2008 |
| 7406369 | Ground effects compensated angle of attack command system and method A take off ground effects compensated angle of attack system includes a radio altimeter and/or timer, a pitch angle system and a flight control computer. The radio altimeter generates a signal which is indicative of the aircraft's altitude from 0 i.e., weight off wh... | 07/29/2008 |
| 7350750 | Control system for airbrakes of an aircraft The present invention relates to a control system for aircraft airbrakes, which comprises control means of a continuous operating mode or of an incremental operating mode in nominal operation of the airbrakes and control means of an incremental operating mode in the... | 04/01/2008 |
| 7340327 | Longitudinal piloting system for a taxiing aircraft The system includes a plurality of engines that generate a thrust of an aircraft, each of the engines controlled by a first controllable actuator. A plurality of brakes reduce the speed of the aircraft when it is taxiing, each of the brakes controlled by a second co... | 03/04/2008 |
| 7305286 | System and method for gyro enhanced vertical flight information A flight instrument and associated method where vertical speed information is combined with gyro information to produce gyro enhanced vertical speed information that is displayed to a pilot. The gyro information may include a pitch rate gyro and may include an azimu... | 12/04/2007 |
| 7272473 | Methods and systems for analyzing system operator coupling susceptibility Methods for analyzing system operator coupling susceptibility are described herein. In one embodiment, an open loop frequency response can be compared to a related over-steer point. An over-steer point can be the condition where, as operator gain is increased for an... | 09/18/2007 |
| 7269486 | Method and device for automatically determining a capture trajectory of a flight trajectory for an aircraft, as well as a procedure and system for automatic guidance of an aircraft The present invention provides a method and device for automatically determining a capture trajectory of a flight trajectory for an aircraft, as well as a procedure and system for automatic guidance of an aircraft. The flight trajectory includes at least one lateral... | 09/11/2007 |
| 7263414 | Method and device for controlling the attitude of an aircraft A method and device for controlling the attitude of an aircraft may employ spoilers that are arranged on the wings of the aircraft and whose respective angular positions can be adjusted by controllable actuators. A command attitude determining section determines a c... | 08/28/2007 |
| 7237748 | Landing gear method and apparatus for braking and maneuvering Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The wheel hub motor/generator can provide motive force to the wheel when electrical power is ... | 07/03/2007 |
| 7226018 | Landing gear method and apparatus for braking and maneuvering Aircraft landing gear comprised of a wheel hub motor/generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The invention can provide motive force to the wheel when electrical power is applied, e.g. pr... | 06/05/2007 |
| 7089090 | Flight control indicator determining the maximum slope for the flight control of an aircraft by terrain following The flight control indicator may include a set of information sources, a computation unit connected to said set of information sources, and a head-up display device. The computation unit determines, on the basis of information emanating from the set of information s... | 08/08/2006 |
| 7043345 | System and method with adaptive angle-of-attack autopilot A control system includes a rate-damping loop that uses a calculated angle-of attack error to non-linearly scale a rate-feedback signal so that at lower angle-of attack (AOA) error values, an acceleration feedback term plays a greater role in pitch compensation, whi... | 05/09/2006 |
| 7031811 | Fuel efficient airspeed trim A system and method are provided for precisely adjusting individual aircraft airspeed system in order to provide more accurate cruise Indicated Airspeed (IAS). The system includes a flight data computer, an autopilot, and airspeed displays. The flight data computer ... | 04/18/2006 |
| 6980153 | Radar altimeter for helicopter load carrying operations A radar altimeter for vehicles that operate with a load suspended underneath is described. The radar altimeter includes a transmitter configured to transmit radar signals toward the ground, a receiver configured to receive reflected radar signals from the ground and... | 12/27/2005 |
| 6976656 | Method for controlling the flight of an aircraft A method for controlling an aircraft includes the steps of receiving acceleration data related to an acceleration of a front portion of the aircraft, and receiving pitch, roll, and/or yaw rate data related to a rate of a center portion of the aircraft. The method al... | 12/20/2005 |
| 6970107 | Flight situation presentation system and method A flight situation presentation system displays a large majority of the information required for piloting an aircraft in an enhanced manner to reduce potential for misinterpretation and instances of piloting error. Approaches include visual integration of flight dat... | 11/29/2005 |
| 6947814 | Process and device for estimating at least the vertical speed of an aircraft, in particular of a rotary wing aircraft A process 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 in... | 09/20/2005 |
| 6942057 | Feel control for active steering A method and apparatus for controlling the feel back torque of a motor provides for receiving a difference between a desired motor position and an actual motor position; filtering the difference into two or more frequency bands; and applying a gain to one or more of... | 09/13/2005 |
| 6935596 | Process and system for piloting an aircraft The piloting system (1) for generating orders for piloting the aircraft according to at least one piloting axis, for example the pitch axis, the roll axis, the yaw axis or the engine thrust control axis, comprises at least two piloting means (2, 3), ea... | 08/30/2005 |
| 6928341 | Computational air data system for angle-of-attack and angle-of-sideslip A computational air data method and system for estimating angle-of-attack and angle-of-sideslip of an aircraft utilizing a detailed aerodynamic model of the aircraft, extended Kalman filters, inertial system measurements of body rates and body accelerations, and com... | 08/09/2005 |
| 6904340 | Flight control indicator for an aircraft, in particular a transport airplane, intended to supply the thrust generated by at least one engine of the aircraft Flight control indicator for an aircraft, in particular a transport airplane, intended to supply the thrust generated by at least one engine of the aircraft. The flight control indicator (1) comprises display means (4) which present, on a viewin... | 06/07/2005 |
| 6870490 | Display of altitude and path capture trajectories Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during... | 03/22/2005 |
| 6761336 | Aircraft tailstrike avoidance system An aircraft flight control system is provided for reducing the likelihood of an aircraft tailstrike. The flight control system includes a pitch command provided to a pitch control device for altering the aircraft's pitch attitude. The improvement is a system of alte... | 07/13/2004 |
| 6693559 | System and method for flight mode annunciators The pilot's awareness of the aircraft's state is enhanced by supplementing the flight modes area (FMA) in the upper region of the primary flight display (PFD) with additional annunciators. The FMA in the present invention displays, in the active lateral m... | 02/17/2004 |
| 6591169 | Method and computer program product for controlling the actuators of an aerodynamic vehicle A method and computer program product are provided for controlling the actuators of an aerodynamic vehicle to affect a desired change in the time rate of change of the system state vector. The method initially determines the differences between anticipate... | 07/08/2003 |
| 6539290 | Method, apparatus and design procedure for controlling multi-input, multi-output (MIMO) parameter dependent systems using feedback LTI'zation A method and apparatus are provided for controlling a dynamic device having multi-inputs and operating in an environment having multiple operating parameters. A method of designing flight control laws using multi-input, multi-output feedback LTI'zation is... | 03/25/2003 |
| 6484071 | Ground proximity warning system, method and computer program product for controllably altering the base width of an alert envelope A ground proximity warning system, method and computer program product are provided that controllably alter the base width of the alert envelope in order to accommodate uncertainties associated with the current position of the aircraft. In one embodiment,... | 11/19/2002 |
| 6430479 | Methods, apparatus and computer program products for determining the vertical speed of an aircraft A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation sy... | 08/06/2002 |
| 6422517 | Aircraft tailstrike avoidance system An improvement to an aircraft flight control system is provided for reducing the likelihood of an aircraft tailstrike. The flight control system includes a pitch command provided to a pitch control device for altering the aircraft's pitch attitude. The im... | 07/23/2002 |
| 6366836 | Method and apparatus for providing adaptive altitude preselector units A method of changing a preselect altitude value includes receiving an input from a pilot. In response, the preselect altitude value is changed by a first amount from a current preselect altitude value toward a minimum altitude value. The first amount that... | 04/02/2002 |
| 6325333 | Aircraft pitch-axis stability and command augmentation system A bias correction system for use in a neutrally-stable aircraft having a control column and a pitch control system is provided. The position of the control column is generally represented by a control column position signal. The bias correction system is ... | 12/04/2001 |
| 6324448 | Methods, apparatus and computer program products for determining the vertical speed of an aircraft A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation sy... | 11/27/2001 |
| 6273370 | Method and system for estimation and correction of angle-of-attack and sideslip angle from acceleration measurements A method and system is disclosed for using inertial sensors in an Inertial Navigation System (INS) to obtain analytic estimates of angle-of-attack () and sideslip angle (). The inertial sensors consist of one or more ac... | 08/14/2001 |
| 6169496 | Banked flight stall warning device and method A flight warning system comprises an outside temperature probe for sensing outside temperature, a gyroscope for sensing aircraft bank angle, a static transducer for sensing static pressure, and a dynamic pressure sensor for receiving total pressure from a... | 01/02/2001 |
| 6168117 | Flight control system for airplane A flight control system according to the present invention includes a vertical acceleration control device for calculating a pitch axis steering angle command to make a difference between a vertical acceleration of an airplane and a target turn accelerati... | 01/02/2001 |
| 6111526 | Vehicle course steering aid device A device for assisting the piloting of a vehicle by instruments. Various indications are displayed on an aircraft head-up view finder including a horizontal line graduated in terms of heading, a perpendicular line graduated in terms of atitude, an aircraf... | 08/29/2000 |
| 6092007 | Aircraft course correction for wind and fuzzy logic course intercept profile based upon accuracy and efficiency An aircraft autopilot system provides a wind correction angle which is added to the desired course to provide commanded heading, the wind correction angle being generated as a proportional and integral function of ground track error. When the aircraft is ... | 07/18/2000 |
| 6073084 | Process and device for verifying the consistency of the measurements from an angle-of-attack probe A process and a device for verifying the consistency of the measurements made by an angle-of-attack probe (2) mounted on an aircraft. The device (1) includes: first system (3) for computing a first coefficient of lift of the aircraft from a measurement fr... | 06/06/2000 |
