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| Number | Title | Issue Date |
| 7367530 | Aerospace vehicle yaw generating systems and associated methods Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system... | 05/06/2008 |
| 7364121 | Methods and systems for automatically controlling aircraft takeoff rolls Methods and systems for automatically controlling aircraft takeoff rolls. A method in accordance with one embodiment of the invention includes receiving an indication of a target takeoff roll path for an aircraft, and automatically controlling a direction of an airc... | 04/29/2008 |
| 7305285 | Method and device for piloting an aircraft A piloting device may include a section for generating control orders for the control surfaces acting on the yaw movement of an aircraft. A central unit determines an instruction to rotate the aircraft, based on control orders, and determines a global moment to be a... | 12/04/2007 |
| 7237747 | Device for assisting an airplane in intercepting a segment of a flight path utilizing positional and ground speed indicators Device assisting with interception by an aircraft of a flight path segment located in a horizontal plane and a system of assistance with interception and follow-up of such a segment. The device includes means of determining a ground speed vector and means of display... | 07/03/2007 |
| 7206674 | Information display system for atypical flight phase Method and system for displaying information on one or more aircraft flights, where at least one flight is determined to have at least one atypical flight phase according to specified criteria. A flight parameter trace for an atypical phase is displayed and compared... | 04/17/2007 |
| 7185859 | Aerospace vehicle yaw generating systems and associated methods Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system... | 03/06/2007 |
| 6937924 | Identification of atypical flight patterns Method and system for analyzing aircraft data, including multiple selected flight parameters for a selected phase of a selected flight, and for determining when the selected phase of the selected flight is atypical, when compared with corresponding data for the same... | 08/30/2005 |
| 6575410 | Glide slope tracking system An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slop... | 06/10/2003 |
| 6549829 | Skipping filter for inertially augmented landing system The present method and apparatus consists of storing past values of estimated IRU error and using these past values to update the coasting filter when switching from GPS to inertial mode. Through the storage of past IRU error estimates, it is possible to ... | 04/15/2003 |
| 6341247 | Adaptive method to control and optimize aircraft performance A measurement-based method to control and optimize the performance of an airborne vehicle. The stability and control of the vehicle is modified to induce a response in the airborne vehicle as reflected by a plurality of response signals. Excitations signa... | 01/22/2002 |
| 6102330 | Emergency multiengine aircraft system for lateral control using differential thrust control of wing engines An emergency flight control system is disclosed for lateral control using only differential engine thrust modulation of multiengine aircraft having at least two engines laterally displaced to the left and right from the axis of the aircraft in response to... | 08/15/2000 |
| 6061611 | Closed-form integrator for the quaternion (euler angle) kinematics equations The invention is embodied in a method of integrating kinematics equations for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of the vehicle, which includes computing an integrating factor matrix from quantiti... | 05/09/2000 |
| 5677685 | Device for assistance in the piloting of an aircraft This optoelectronic device is designed to provide assistance in the piloting of an aircraft under conditions of poor visibility, at the final approach stage, during taxiing and at take-off from a runway equipped with an ILS. The device consists of a colli... | 10/14/1997 |
| 5669582 | Method and apparatus for reducing unwanted sideways motion in the aft cabin and roll-yaw upsets of an airplane due to atmospheric turbulence and wind gusts A method and apparatus for reducing the unwanted sideways motion of an airplane by reducing the lateral side loads and upsets caused by atmospheric turbulence and gusts is disclosed. A rudder modification command that causes the rudder command of the airp... | 09/23/1997 |
| 5657949 | Method and apparatus for providing a dynamic thrust asymmetry rudder compensation command with no direct thrust measurement A method and apparatus for producing a dynamic thrust asymmetry airplane rudder compensation command with no direct thrust measurement is disclosed. An excess thrust estimate based on measured acceleration along the flight path of the airplane and measure... | 08/19/1997 |
| 5590853 | Aircraft control system 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 tr... | 01/07/1997 |
| 5458304 | Disk spoiler system Spoilers, mounted on vertical stabilizer tail surfaces of large aircraft release controllable Bernoulli forces to augment rudder and aileron aircraft controls. Data from surface pressure sensors, also mounted on vertical stabilizer tail surface, is comput... | 10/17/1995 |
| 5375793 | Process for the control of the control surfaces of an aircraft for the low speed compensation of a lateral path deviation The present invention relates to a process for the automatic control of the control surfaces of an aircraft for the low speed compensation of a lateral path deviation, in which beyond a given deflection threshold (20) of the deflected rudder (17), there i... | 12/27/1994 |
| 5265825 | Helicopter engine control having yaw input anticipation A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121,123) of yaw control (107) position change generate... | 11/30/1993 |
| 5213283 | Low speed turn coordination for rotary wing aircraft A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a low speed banked turn. The ... | 05/25/1993 |
| 5178307 | High speed yaw control system for rotary wing aircraft A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output comman... | 01/12/1993 |
| 5060889 | Apparatus and methods for maintaining aircraft track angle during an asymmetric flight condition When an aircraft is operating in an asymmetrical flight condition, such as during a landing decrab maneuver or during inflight engine out, the pilot is normally required to make precise compensatory roll control inputs to keep the aircraft moving along it... | 10/29/1991 |
| 5014053 | Method and apparatus for determining actual lateral deviation from runway centerline A method of and apparatus for determining the actual lateral deviation from the centerline of a runway of an aircraft located outside the normal region covered by a glideslope beam is disclosed. The method comprises the steps of scaling a geometrically de... | 05/07/1991 |
| 4916612 | Dual channel signal selection and fault detection system A signal selection and fault detection system that provides triple functional redundancy using the outputs (YA, YB) of two unmonitored primary channels and the output of one or the other of two complementary filters (22, 34) that eac... | 04/10/1990 |
| 4814764 | Apparatus and method for warning of a high yaw condition in an aircraft A system for warning the pilot when the aircraft has reached a high yaw condition. A differential in pressure or angle of attack between the port and starboard sides of the aircraft is measured and converted into a measured sideslip angle. If the measured... | 03/21/1989 |
| 4471280 | Anti-log power amplifier for reversible D.C. motor in automotive steering controls An anti-log power amplifier for energizing a reversible electric motor of an electrically assisted power steering system for an automotive vehicle. The power amplifier has a preamplifier which amplifies the output signal of a torque sensor detecting the t... | 09/11/1984 |
| 4354240 | Flight path transition control apparatus with predictive roll command The flight path transition control apparatus provides a roll attitude command to control the aircraft to execute an exponential transition path to a predetermined course in accordance with the exponential control law Y+KY where Y is the lateral displaceme... | 10/12/1982 |
| 4098215 | Steering control system for hydrofoils An improved steering control system is provided for improving the handling qualities of hydrofoil craft during takeoff. In steering control systems for hydrofoils, the craft is banked by operation of control surfaces and the rudder is turned in the corres... | 07/04/1978 |
| 4094479 | Side slip angle command SCAS for aircraft A yaw axis stability and command augmentation system (SCAS) particularly applicable to STOL type aircraft includes three primary control terms proportional to side slip angle, side slip angle rate and rudder pedal force, wherein side slip angle rate is sy... | 06/13/1978 |
| 4061297 | Approach range monitor An area navigation system capable of operating during an ILS approach to provide the pilot range and bearing with respect to the outer and middle markers for a front course approach, and with respect to the final approach fix and the end of the runway for... | 12/06/1977 |
| 4034936 | Device for damping the tipping and yawing oscillations of the guidance system of a flying vehicle The guidance system for a flying vehicle having at least one guidance channel for converting an error signal to a command signal for a control surface servo of the vehicle includes means for damping oscillations at the natural frequency of the vehicle. A ... | 07/12/1977 |
| 4006870 | Self-aligning roll out guidance system Guidance along the runway centerline when visibility conditions do not permit adequate visual cues for manual control are provided utilizing lateral acceleration and bank angle information. An aircraft type airborne vehicle can touchdown with a crab angle... | 02/08/1977 |
| 3989209 | Apparatus for guiding an aircraft along a multi-segment path when landing the craft For use with a microwave landing system of the type including a ground based station for generating a relatively wide aircraft navigational beam and airborne equipment for deriving precision azimuth, elevation, and range data therefrom, airborne equipment... | 11/02/1976 |
