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8584989 |
Method of managing movement of an aircraft on the ground
The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each... |
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8478456 |
Variable bandwidth control actuation methods and apparatus
Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a... |
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8376266 |
Method of controlling a hybrid helicopter in yaw, and a hybrid helicopter provided with a yaw control device suitable for implementing said method
A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the... |
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8359129 |
Method and device for controlling the thrust of a multi-engine aircraft
A method and device control the thrust of a multi-engine aircraft. At least one engine command is determined by a command determining unit, with the determined command commanding each engine that... |
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8209068 |
Systems and methods for controlling dynamic systems
A control system (12) for controlling velocity and attitude of a dynamic system (20) includes a velocity controller configured to receive a desired velocity command and output a velocity error in... |
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8200421 |
Method and device of terrain avoidance for an aircraft
An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the... |
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8185259 |
Fuzzy logic-based control method for helicopters carrying suspended loads
The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing... |
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8175760 |
Displaying method and device for an aircraft following a flight plan
A device comprises means for computing the air-craft (A) current position, means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the... |
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8072172 |
Redundant electromechanical actuator for control surfaces
A redundant electromechanical actuator is provided that includes first and second electric motors, a common output shaft, first and second drive cable drums, first and second driven cable drums, a... |
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7756637 |
Methods and systems for displaying electronic enroute maps
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... |
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7731122 |
Method for managing the wheel steering control of an aircraft
The invention relates to a method for managing a steering control of an aircraft landing gear provided with at least one wheel steerable by the steering control, comprising the following steps:... |
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7539561 |
Autonomous control system apparatus and program for a small, unmanned helicopter
An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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.... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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3911436 |
Device for aircraft trajectory guidance
When approaching an airport at which there is a localizer and glide path transmitter, a localizer and glide path receiver supplies azimuth angle signals and elevation angle signals, and a distance... |
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3837603 |
LATERAL AXIS ROLLOUT, GO-AROUND, TAKEOFF CONTROL FOR AIRCRAFT
Automatic control of aircraft which provides runway centerline guidance during landing rollout, takeoff roll and low altitude initiated go-around flight modes, wherein lateral dispersion is... |
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3815850 |
CRAB ANGLE REFERENCE SIGNAL DEVELOPMENT FOR LIMITED FORWARD SLIP LANDING MANEUVER
A signal processing apparatus for developing a yaw command signal as might be advantageously employed in effecting decrab prior to touchdown. The signal is formulated from utlizing course datum... |
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3812333 |
LAGGED ROLL SYNCHRONIZATION AND WASHOUT MEANS FOR AIRCRAFT LATERAL AXIS CONTROL SYSTEM
A limited washout and synchronization means for developing a beam closure rate signal from bank gyro and lateral accelerometer input sensors permits a lagged roll signal mix with radio deviation... |
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3801049 |
AUTOMATIC APPROACH LANDING AND GO-AROUND PITCH AXIS CONTROL SYSTEM FOR AIRCRAFT
The invention relates to a system utilizing an exponential control law for glide slope capture and flare. The capture maneuver from above or below the beam, is a function of decreasing glide slope... |
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3788579 |
AIRCRAFT CONTROL SYSTEM USING INERTIALLY SENSED DATA
A system using signals available from an on-board inertial platform for controlling an aircraft through an autopilot or flight director during localizer beam capture, tracking and runway alignment... |
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3773281 |
AUTOMATIC FLIGHT CONTROL SYSTEM USING INSTRUMENT LANDING SYSTEM INFORMATION AND INCLUDING INERTIAL FILTERING MEANS FOR REDUCING ILS NOISE
A flight control system includes localizer and glide path couplers using instrument landing system (ILS) information and inertially sensed data to generate appropriate control signals, and... |
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3761691 |
RUNWAY ALIGNMENT SYSTEM UTILIZING A LATERAL ACCELERATION SIGNAL
A landing control system utilizing a lateral acceleration signal in formulation of roll steering command such that a decrab maneuver effects a "wing down into the wind" forward slip maneuver,... |
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3739382 |
AIRCRAFT LATERAL GUIDANCE SYSTEM
Course and directional radio signals are combined to produce an aircraft guidance signal. The guidance signal is amplified and applied to control the intercept of the aircraft with a directional... |