Abstract: A method includes estimating, as a function of an angular speed of wheels of an axle of a vehicle, a value of adhesion of a contact area of the wheels of said axle to a route, and calculating a value of slip of the wheels of said axle. The method also includes generating signals representative of a derivative of said adhesion as a function of the slip of the wheels of said axle, and calculating an error signal as a difference between a value of said derivative and a predetermined reference value. The method includes generating, via an adaptive filter that implements a Least Mean Square (LMS) algorithm, a driving signal based on said derivative. The LMS algorithm is continuously adapted based on the error signal to reduce and keep the error signal substantially at zero. The method includes applying said driving signal to a torque control module.

Abstract: A piston housing may comprise: a main annular ring defining a main bore; a torque takeout annular ring defining a torque takeout bore; a torque takeout arm extending from the main annular ring to the torque takeout annular ring and defining an aperture therethrough; and a structural rib disposed within the aperture and extending from the main annular ring to the torque takeout annular ring.

Abstract: A system for controlling landing gear subsystems may comprise a controller and a first motor drive unit in operable communication with the controller. A first electric motor and a second electric motor may be in operable communication with the first motor drive unit. A second motor drive unit may be in operable communication with the controller. A third electric motor and a fourth electric motor may be in operable communication with the second motor drive unit. An AC/DC converter may be electrically coupled to the first drive unit and the second motor drive unit.

Abstract: Methods and apparatus for controlling landing gear retract braking are described. A controller is to determine an on-ground status of a wheel of a landing gear. The controller is to generate a control signal based on the on-ground status of the wheel. The control signal is to initiate a retract braking process for the wheel. The retract braking process is to decelerate the wheel from a first rate of rotation to a second rate of rotation less than the first rate of rotation.

Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

Abstract: A brake fluid pressure control system for a vehicle is provided with: a master cylinder activated by the operation of a brake pedal; a motor cylinder device that generates brake hydraulic pressure in response to an operation amount of the brake pedal; first brake fluid flow lines that allow the master cylinder to communicate with wheel cylinders; two-position three-way valves arranged at connection points between the first brake fluid lines and second brake fluid lines. The two-position three-way valves switch between a state in which the master cylinder communicates with the wheel cylinder and a state in which the motor cylinder device communicates with the wheel cylinder.

Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.

Abstract: According to various embodiments, disclosed is an axle saddle system for an axle having an undercut between the outboard and inboard bearing lands of the axle. According to various embodiments, the axle saddle system comprises a saddle configured to fill the axle undercut in order to protect the axle from damage by the installation of a wheel onto the axle.

Abstract: A system includes a first brake actuator for controlling pressure applied to a first brake, a BCU configured to receive a first plurality of inputs and to output a first BCU control signal for controlling the first brake actuator based on the first plurality of inputs, and a first switch coupled between the first brake actuator and the BCU. The system also includes a backup controller designed to receive a second plurality of inputs, determine a first backup control signal for controlling the first brake actuator based on the second plurality of inputs, determine that the BCU is functioning improperly based on the second plurality of inputs, and control the first switch to prevent the first BCU control signal from controlling the first brake actuator and to output the first backup control signal to the first brake actuator in response to determining that the BCU is functioning improperly.

Abstract: A suspended rudder bar for aircraft and aircraft having a suspended rudder bar, which includes a set of primary hinges, a set of secondary hinges including control and synchronization devices, and a set of linkages generating functional and structural links between the set of primary hinges and the set of secondary hinges, wherein the primary hinges are configured to be suspended at least on a structure supporting the instrument panel of the flight deck of the aircraft, and the secondary hinges configured to be suspended at least on a structural component of an area situated forward of the flight deck.

Abstract: Systems and methods for aircraft braking are disclosed. The systems and methods may comprise a control mode executive configured to receive a pedal input and calculate a gear deceleration command comprising a desired deceleration rate based on the pedal input; a pedal deceleration controller in electronic communication with the control mode executive configured to receive the gear deceleration command from the control mode executive and calculate a gear pedal command based on at least one of the gear deceleration command and a deceleration feedback; and a pedal executive in electronic communication with the pedal deceleration controller configured to receive the gear pedal command, and generate a pedal braking command based on the gear pedal command.

Abstract: A method for determining actual aircraft ground speed may comprise receiving a reference ground speed value; receiving a wheel speed value of a nose wheel of an aircraft; comparing the wheel speed value of the nose wheel and the reference ground speed value; and/or determining the actual aircraft ground speed based on the reference ground speed value and the wheel speed value.

Abstract: A wheel speed sensor may comprise a magnet; an induction coil coupled to the magnet; a rotor comprising a plurality of teeth, wherein the magnet is disposed proximate the plurality of teeth; a gear system coupled to the rotor comprising an initial gear, wherein the initial gear may be configured to be coupled to a wheel and configured to rotate at a speed equal to a wheel rotational speed of the wheel. The gear system may be configured to cause a rotor rotational speed of the rotor to be greater than the wheel rotational speed in response to the wheel rotating.

Abstract: Systems and methods for detecting wheel speed are provided. An electric circuit for detecting a speed of a wheel may comprise: a transducer in electronic communication with an operational amplifier (OP-AMP), the transducer configured to output a variable signal in response to an angular velocity of a rotatable member of a wheel assembly; a constant voltage source in electronic communication with the OP-AMP; and a sensor in electronic communication with an output terminal of the OP-AMP configured to monitor an output signal of the OP-AMP, the output signal including a period; and a controller configured to receive the output signal and configured to calculate the speed of the wheel according to a pre-determined ratio of the wheel speed and the period. In various embodiments, the circuit may allow for slow wheel speed detection.

Abstract: A braking controller and method in a towing vehicle towing one or more towed vehicles as a combination vehicle provides brake control of the one or more towed vehicles based on a level of braking force applied to the towing vehicle. A non-enhanced braking mode applies a first level of braking force to the towed vehicles in a predetermined reduced proportion relative to the level of braking force applied to the towing vehicle, and an enhanced braking mode applies a second level of braking force to the towed vehicles greater than the first level of braking force. A controller deceleration command input receives a deceleration command signal which is compared against predetermined threshold deceleration rate value or against a current deceleration value being executed by the combination vehicle and, based on a result of the comparisons, either the enhanced or the non-enhanced braking modes are implemented by the controller.

Abstract: A braking controller and method in a towing vehicle towing one or more towed vehicles as a combination vehicle provides brake control of the one or more towed vehicles based on a level of braking force applied to the towing vehicle. A non-enhanced braking mode applies a first level of braking force to the towed vehicles in a predetermined reduced proportion relative to the level of braking force applied to the towing vehicle, and an enhanced braking mode applies a second level of braking force to the towed vehicles greater than the first level of braking force. A controller deceleration command input receives a deceleration command signal which is compared against predetermined threshold deceleration rate value or against a current deceleration value being executed by the combination vehicle and, based on a result of the comparisons, either the enhanced or the non-enhanced braking modes are implemented by the controller.

Abstract: Systems and methods for aircraft electric taxi brake optimization are provided. The system may comprise an aircraft having a landing gear comprising a wheel, a friction brake having a brake material coupled to the wheel, a regenerative brake comprising a reversible taxi motor coupled to the wheel, a sensor configured to measure a wheel parameter of the wheel and a temperature of the friction brake, a tangible, non-transitory memory configured to communicate with a controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising: receiving, by the controller, a command signal and the friction brake temperature and calculating, by the controller, a brake material temperature based on the wheel parameter, the friction brake temperature, and the command signal.

Abstract: A vehicle brake system includes a brake control device, a vehicle acceleration sensor, and a trailer brake controller. The trailer brake controller outputs an initial trailer brake torque demand based on an input received from the brake control device and adjusts the initial trailer brake torque demand to converge a signal from the vehicle acceleration sensor to an expected negative acceleration value correlated with the input from the brake control device.

Abstract: Methods and systems are provided for providing real-time assessment and analysis for reduced engine taxi operations (RETO) for an aircraft. The method includes retrieving time sensitive data, non-time sensitive data and ground operational data that all affect RETO of the aircraft. This data is collected with an RETO analyzer which applies a predetermined ruleset to determine a RETO recommendation for the aircraft. The recommendation is transmitted to a RETO support module which retrieves historical flight data and cost model and financial model data for the aircraft. The support module then generates and displays RETO alerts, implementation plans and map overlays for the aircraft.

Abstract: Braking control systems and methods, such as for an aircraft, use a first pressure sensor and a second pressure sensor from a non-primary braking system to validate the first pressure sensor. In response to the first pressure sensor being validated, a health status of a servo valve is monitored based on predetermined characteristics about the servo valve, including electrical current input into the servo valve and hydraulic pressure output from the servo valve.

Abstract: A pedal system containing a right foot pedal, a left foot pedal and a motion inverter mechanism. The right foot pedal is moveable from a right foot pedal neutral position to a depressed acceleration position. The left foot pedal is moveable from a left foot pedal neutral position to a depressed braking position. The motion inverter mechanism operatively couples to the right and left foot pedals, for movement of the right foot pedal or the left foot pedal in an opposite direction to a raised position upon depression of the other of the right foot pedal or the left foot pedal. Also disclosed is a method of preventing concurrent depression of the gas and brake pedal. The pedal system disclosed can allow left foot braking and can also prevent concurrent depression of the gas and brake pedals, and hence, avoid stalling an automobile. The pedal system may also be installed with “drive by wire” type automobiles.

Abstract: A drive system for an aircraft landing gear is disclosed having a wheel rotatable about a wheel axis, a driven gear arranged to be attached to the wheel and capable of rotating the wheel about the wheel axis, a drive train comprising an input gear rotatable by an input shaft, an intermediate gear meshed with the input gear and rotatable by an intermediate shaft, and a support member arranged to support the input shaft and intermediate shaft. The support member is arranged to pivot about the input shaft between a neutral configuration in which the drive train is disengaged from the driven gear and a driven configuration in which the drive train is engaged with the driven gear to enable the drive train to rotate the driven gear. The drive system includes brake capable of being engaged with the input shaft to prevent rotation of the input shaft relative to the support member and of being disengaged from the input shaft to permit rotation of the input shaft relative to the support member.

Abstract: An airport computing system is communicatively coupled to a first airplane and to one or more second airplanes over a network system. The airport computing system comprises a plurality of sensors associated with the first airplane. The airport computing system comprises a data module configured to receive data from the first airplane over the network. The data comprises runway data sampled using the plurality of sensors while the first airplane is on a runway. The airport computing system also comprises a parameter module configured to determine one or more parameters that describe a condition for the runway based on the received runway data. The airport computing system further comprises a transmission module configured to transmit the one or more parameters to the one or more second airplanes over the network.

Abstract: A method for controlling brakes may comprise detecting, by a brake control unit (BCU), an aircraft speed, determining, by the BCU, that the aircraft speed is at least one of at or above a threshold value, determining, by the BCU, that an auto-brake control has been enabled, receiving, by the BCU, an antiskid desired pressure that is output from an antiskid control, the BCU comprising a brake control executive (BKX), the antiskid desired pressure being received by the BCU, and receiving, by the BCU, a desired pressure comprising at least one of a deceleration control desired pressure from a deceleration control (DK) or a pilot desired pressure from a manual brake control, the desired pressure being received by the BKX.

Abstract: A brake system of an aircraft may include a first brake control assembly, a second brake control assembly, a first brake control unit electrically coupled to the first brake control assembly, a second brake control unit electrically coupled to the second brake control assembly, and an arbitration control module. The arbitration control module may be configured to determine an operational integrity of the first brake control unit and the second brake control unit. In response to determining that one of the first brake control unit and the second brake control unit does not have sufficient operational integrity, the arbitration control module may enable the other of the first brake control unit and the second brake control unit to control both the first brake control assembly and the second brake control assembly.

Abstract: A system, method, and apparatus for brake load alleviation amongst at least one first brake and at least one second brake is disclosed. The method involves sensing an amount of brake pedal application in response to engagement of at least brake pedal. The method further involves determining whether the amount of brake pedal application is greater than a brake pedal application threshold value. Also, the method involves generating a brake application profile, when it is determined that the amount of brake pedal application is greater than the brake pedal application threshold value. The brake application profile indicates that actuation of at least one first brake is delayed by a first time delay, and that actuation of at least one second brake is delayed by a second time delay. Further, the method involves actuating at least one first brake and at least one second brake according to the brake application profile.

Abstract: Systems and methods for detecting runway conditions are disclosed. A weight on wheel system may determine that an aircraft is on the ground. Wheel speed sensors may measure the speed of the aircraft wheels. Axle reference speeds may be calculated for each landing gear based on the speed of the aircraft wheels. A weight on wheel time limit may be reached prior to the axle reference speeds reaching an on ground threshold. A brake control unit may determine that the runway is contaminated if the on ground threshold was not reached.

Abstract: A method for controlling brakes is provided. The method comprises detecting an imminent skid by an anti-skid controller/deceleration controller (ASK/DK). The ASK/DK outputs at least one of a negative desired pressure command to a pressure control unit (PK) in response to detecting the imminent skid and causes a current command output from the PK to be reduced to release braking pressure if the negative desired pressure command minus a measured feedback pressure is greater than a deadband of the PK or outputs a negative desired force command to a force control unit (ForK) in response to detecting the imminent skid and causing a current command output from the ForK to be reduced to release braking force if the negative desired force command minus a measured feedback force is greater than a deadband of the Fork. A brake control system is also provided.

Abstract: A ram air turbine control valve includes a sleeve, a spool, and a return housing. The sleeve defines a first exit port disposed proximate a first end of the sleeve and defines a second exit port disposed between the first exit port and the first end. The spool is radially contained within the sleeve and is movable between a first position and a second position. The return housing is coupled to the first end of the sleeve and defines a cavity that receives a biasing member that engages the spool.

Abstract: A system, method, and apparatus for brake load alleviation amongst at least one first brake and at least one second brake is disclosed. The method involves sensing an amount of brake pedal application in response to engagement of at least brake pedal. The method further involves determining whether the amount of brake pedal application is greater than a brake pedal application threshold value. Also, the method involves generating a brake application profile, when it is determined that the amount of brake pedal application is greater than the brake pedal application threshold value. The brake application profile indicates that actuation of at least one first brake is delayed by a first time delay, and that actuation of at least one second brake is delayed by a second time delay. Further, the method involves actuating at least one first brake and at least one second brake according to the brake application profile.

Abstract: An acoustic device that is adapted to be worn on the body of a user, with a first acoustic transducer and a second acoustic transducer, where the first transducer is closer to the expected location of a first ear of the user than is the second transducer, a third acoustic transducer and a fourth acoustic transducer, where the third transducer is closer to the expected location of a second ear of the user than is the fourth transducer, and a controller that is adapted to independently control the phase and frequency response of the first, second, third and fourth transducers.

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.

Abstract: An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.

Abstract: A system and method for braking an aircraft. A processor unit identifies an operating condition of the aircraft. The processor unit displays available modes indications on a display device on the aircraft. The available modes indications indicate modes of operating an automatic braking system on the aircraft that are available for selection by an operator based on the operating condition of the aircraft. The processor unit receives a mode selection from an operator interface. The mode selection indicates a selected mode of operating the automatic braking system that is selected by the operator from the available modes. The processor unit displays on the display device a selected mode indication indicating the selected mode.

Abstract: An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.

Abstract: A system for detecting a stuck brake friction component of a motor vehicle may include a tire pressure monitoring system and a steering wheel angle sensor. The system may also include a controller configured to receive signals from the tire pressure monitoring system and the steering wheel angle sensor and to generate a notification if the signals indicate that one or more of the friction components of the vehicle's braking system is stuck in an engaged position.

Abstract: Methods and means for reducing wear in electric or electro-hydraulic braking systems utilizing an adjustable (adaptive) filter, wherein the adaptive filter provides for rapid response during anti-skid operation and a smooth and filtered response during non-anti-skid operation.

Abstract: In various embodiments, a method for utilizing a determined coefficient of friction along a portion of a runway is disclosed. The method may include receiving, by a brake control unit, friction estimation map data for a specific runway. The method may include setting, by the brake control unit, a condition of the braking control algorithm based on the received friction estimation map data. The method may include initiating, by the brake control unit, a brake control system to slow a wheel of an aircraft based on the braking control algorithm.

Abstract: A data improvement system, including an initial database, a verification database, and a processing device in communication with the initial database and the verification database. The processing device receives data from the initial database and the verification database, and determines verification data based thereon. A track data improvement system and a track database improvement system are also disclosed.

Abstract: A landing gear force and moment distributor system for an aircraft having a longitudinal axis aligned in a forward-aft direction, a vertical axis perpendicular to the longitudinal axis, and a landing gear including a pair of bogies arranged symmetrically about the longitudinal axis, each bogie having an actuator arranged to brake and/or drive one or more wheels. The force distribution system includes a distribution module arranged to: receive an input demand including a longitudinal force input demand corresponding to a desired braking or driving force along the longitudinal axis for the landing gear and a moment input demand corresponding to a desired moment about the vertical axis for the landing gear; and to use the received input demand to calculate an output command including, for each bogie, a longitudinal force output command corresponding to a braking or driving force along the longitudinal axis to be applied to the bogie.

Abstract: Systems and methods disclosed herein include preventing use of a Focal Plane Array (“FPA”) in a thermal imaging system if used in conjunction with a weapons-related activity by disabling the FPA in response to detecting one or more shock pulse events using accelerometers coupled with the thermal imaging system. The method includes monitoring an output from the one or more of the accelerometers to determine whether a shock pulse acceleration event has been detected that exceeds a predetermined threshold. The method also includes determining that a second acceleration event associated with the accelerometers exceeds a second predetermined threshold. The method further includes disabling the thermal imaging system in response to the detected acceleration events.

Abstract: An electric generator includes a wheel coupled to an axle of a vehicle which includes battery. A rotator is fixedly mounted to the wheel and includes a series of magnets positioned so that the north pole of one magnet abuts the south pole of an adjacent magnet. A stator is rotatably mounted to the axle, and includes a mass positioned off-center from the axle for biasing the stator toward a position that is generally stationary relative to the vehicle. The stator further includes a plurality of electric coils for generating electric current when the rotator is moved relative to the stator and the magnetic field of each magnet passes through the plurality of electric coils, the coils being electrically coupled to each other and to the battery of the vehicle to transmit electric current generated from the plurality of coils to the battery.

Abstract: An apparatus for stabilizing a conduit, such as a riser, against motion. The apparatus comprises an outer wall portion, an inner tubular member having a longitudinal channel extending therethrough, a first tubular member at least partially located between the outer wall portion and the inner tubular member, and a second tubular member at least partially located between the outer wall portion and the inner tubular member. The outer wall portion at least partially surrounds the inner tubular member and the first and second tubular members are movable about the inner tubular member and are movable relative to each other. The first and second tubular members are adapted for securing to the conduit, such as a riser.

Abstract: Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, system comprising an electric motor coupled to a first transmission, a first clutch for selectively engaging the first transmission to a propulsion transmission and a brake clamping system, wherein, in response to engagement with the propulsion transmission, the electric motor drives an aircraft wheel, wherein, in response to engagement with the actuator ram, the electric motor drives the brake clamping system to apply force to an aircraft brake disk stack.

Abstract: Systems and methods for detecting an on ground condition of an aircraft are disclosed. A weight on wheel system may determine that an aircraft is on the ground. Wheel speed sensors may measure the speed of the aircraft wheels. Axle reference speeds may be calculated for each landing gear based on the speed of the aircraft wheels. A brake control unit may determine that the axle reference speed for each axle of the landing gears is above an on ground threshold speed, and the brake control unit may allow braking to be applied.

Abstract: Aircraft landing gear comprised of a wheel hub motor/generator includes alternating rotors and stators mounted with respect to the wheel support and wheel. The invention in certain embodiments can provide motive force to the wheel when electrical power is applied, e.g. prior to touch-down, thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway and reducing the sliding friction wear of the tire. After touchdown the wheel hub motor/generator may be used as a generator thus applying a regenerative braking force and/or a motorized braking action to the wheel. The energy generated upon landing may be dissipated through a resistor and/or stored for later use in providing a source for motive power to the aircraft wheels for taxiing and ground maneuvers of the aircraft. Methods and apparatuses for nose gear steering and ABS braking using the disclosed invention are described.

Abstract: This invention relates to a computer network for calculating and distributing the true braking coefficient of aircraft on runways and taxiways using a computer which obtains data from an aircraft, including in some preferable embodiments dynamic aircraft properties recorded on the aircraft's flight data management system. Environmental and aircraft parameters may also be used to calculate the braking friction coefficient. A computer and network are used to obtain data and to calculate the friction coefficient, and may be used to distribute the result. The network may utilize, at least in part, wireless local area networks to facilitate data transfer and distribution of the result. The computer for calculating the braking coefficient may be located on the aircraft.

Abstract: The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135).

Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: A computer network for calculating a value for the true braking coefficient of friction for an aircraft runway or taxiway using data from one or more aircraft's flight data recorders or flight data management systems, and reporting the calculated value information to individuals and agencies including air traffic control, airport operations and maintenance, and aircraft pilots and ground crews is described and claimed herein. The data may be obtained in real-time by either an onboard or an off-aircraft high-power computing system, calculating the aircraft's true braking coefficient of friction, and reporting the calculated information to the individuals and agencies.