HYDRO-AIRE, INC. Patent applications |
Patent application number | Title | Published |
20140156160 | SYSTEM AND METHOD FOR AIRCRAFT BRAKE METERING TO ALLEVIATE STRUCTURAL LOADING - In a system and method for aircraft brake metering to alleviate structural loading, one or more electric brake actuators for wheel brakes having a range of brake clamping force are provided, and a brake actuation controller is configured to monitor commanded initiation of the aircraft, to limit initial brake effort of the electric brake actuators to a preset fraction of a maximum possible braking effort for a preset period of time, and to permit brake effort of the electric brake actuators up to the maximum possible braking effort after the preset period of time after initiation of braking has been commanded. The preset fraction is preferably approximately 50% of the maximum possible braking effort, and may be tuneable. The preset period of time is preferably approximately one second, and also may be tuneable. | 06-05-2014 |
20140032076 | METHOD OF MAINTAINING OPTIMAL BRAKING AND SKID PROTECTION FOR A TWO-WHEELED VEHICLE HAVING A SPEED SENSOR FAILURE ON A SINGLE WHEEL - The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel. | 01-30-2014 |
20130080011 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 03-28-2013 |
20120259500 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear, utilize one or more sensors to sense a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. | 10-11-2012 |
20120130613 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 05-24-2012 |
20110320101 | METHOD OF MAINTAINING OPTIMAL BRAKING AND SKID PROTECTION FOR A TWO-WHEELED VEHICLE HAVING A SPEED SENSOR FAILURE ON A SINGLE WHEEL - The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel. | 12-29-2011 |
20110320100 | METHOD OF MAINTAINING OPTIMAL BRAKING AND SKID PROTECTION FOR A TWO-WHEELED VEHICLE HAVING A SPEED SENSOR FAILURE ON A SINGLE WHEEL - The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel. | 12-29-2011 |
20110226569 | ELECTRONIC MOTOR ACTUATORS BRAKE INHIBIT FOR AIRCRAFT BRAKING SYSTEM - A brake system control unit controls one of first and second portions of a wheel brakes electric brake actuators to activate one of the first and second portions of the actuators and deactivate the other during an inhibited braking mode. The control unit controls the activated portion of the brake actuators to generate a braking force greater than the commanded braking force of the brake pedal command, such as twice the commanded braking force, to compensate for the deactivated portion of the brake actuators. The inhibited braking mode is discontinued during emergency braking when the commanded braking force is greater than or equal to a predetermined braking force. The inhibited braking mode is also discontinued when failure of one or more brake actuators is detected. | 09-22-2011 |
20110106389 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 05-05-2011 |
20100268404 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 10-21-2010 |
20100250028 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 09-30-2010 |
20100222942 | TAXI BRAKE INHIBIT SYSTEM - A taxi brake inhibit system overcomes problems of discontinuities in pedal “feel” that can occur by use of a taxi brake inhibit system, by adding a new pedal “feel” logic in which twice the brake force is commanded for a given brake pedal application when taxi brake inhibit is active. The taxi brake inhibit system relies upon two different brake force vs. brake pedal application curves to compensate for the difference in deceleration that is achieved for a given brake pedal application depending upon whether the taxi brake inhibit is active or inactive. Such system effectively eliminates undesirable deceleration bumps, yaw effects and changes in pedal feel during braking. The taxi brake inhibit feature is also shut off to both fore-aft brake pairs if any non-normal taxi brake inhibit condition exists on either fore-aft brake pair. | 09-02-2010 |
20100170752 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 07-08-2010 |
20100013296 | METHOD OF MAINTAINING OPTIMAL BRAKING AND SKID PROTECTION FOR A TWO-WHEELED VEHICLE HAVING A SPEED SENSOR FAILURE ON A SINGLE WHEEL - The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel. | 01-21-2010 |
20090315541 | ANGULAR POSITION SENSOR - An angular position sensor and method that relies on a stationary circular array of Hall sensors and a rotatable circular array of magnets arranged about a common axis. A periodic and simultaneous reading of all of the Hall sensor outputs is used to determine angular velocity. | 12-24-2009 |
20090184571 | METHOD TO REDUCE CARBON BRAKE WEAR THROUGH RESIDUAL BRAKE FORCE - The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs. | 07-23-2009 |
20090150031 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 06-11-2009 |
20090120735 | SYSTEM AND METHOD FOR AIRCRAFT BRAKING SYSTEM USAGE MONITORING - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance traveled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 05-14-2009 |
20090099794 | FLOW METER - A simple, passive and rugged device for measuring the flow rate of liquid. A variable area obstruction valve, a differential pressure sensor and a densitometer are combined in a single housing to provide for a highly accurate and precise measure of mass flow. | 04-16-2009 |
20090001806 | METHOD AND SYSTEM TO INCREASE ELECTRIC BRAKE CLAMPING FORCE ACCURACY - The method and system for increasing accuracy of clamping force of electric aircraft carbon brakes, once braking has been commenced, provides a first pair of electric brake actuators with a range of low brake clamping force responsive to low brake clamping force commands, and a second pair of electric brake actuators with a range of high brake clamping force responsive to high brake clamping force commands. The first pair of electric brake actuators is actuated to apply a minimum residual braking force once wheel braking is commenced, and the second pair of electric brake actuators is actuated only when the commanded braking force is in the high range of brake clamping force. | 01-01-2009 |
20080316658 | AIRCRAFT APPLICABLE CIRCUIT IMBALANCE DETECTION AND CIRCUIT INTERRUPTER AND PACKAGING THEREOF - The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor system for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller including a power relay having contacts capable of surviving carry-break and make-carry-break types of ground fault conditions at anticipated current levels. At power up, the device performs a test to confirm that none of the relay contacts have failed in a closed position, and to check whether a switching FET which controls the relay coil has shorted. | 12-25-2008 |
20080304190 | AIRCRAFT APPLICABLE CIRCUIT IMBALANCE DETECTION AND CIRCUIT INTERRUPTER AND PACKAGING THEREOF - The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor system for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller including a power relay having contacts capable of surviving carry-break and make-carry-break types of ground fault conditions at anticipated current levels. At power up, the device performs a test to confirm that none of the relay contacts have failed in a closed position, and to check whether a switching FET which controls the relay coil has shorted. | 12-11-2008 |
20080275599 | System and Method for Aircraft Braking System Usage Monitoring - The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. As applied to monitoring wear of an aircraft brake, a linear brake wear indicator attached to the brake moves a discrete distance when the brake is actuated, and a linear position encoder measures the distance travelled by the linear brake wear indicator as an indication of brake usage. A wheel speed monitor may also be provided for measuring the aircraft wheel speed, for distinguishing between static brake applications and moving brake applications, based upon the wheel speed signal. | 11-06-2008 |
20080221768 | SYSTEM AND METHOD FOR ADAPTIVE BRAKE APPLICATION AND INITIAL SKID DETECTION - The adaptive brake application and initial skid detection system allows rapid brake application and prevents deep initial skids. Brake pressure is compared with a predetermined threshold brake pressure. Wheel velocity error signals are also generated to indicated the difference between the wheel velocity and a reference velocity signal. A pressure bias modulator integrator responsive to brake pressure signals adjusts the wheel velocity error signals to provide an anti-skid control signal. The pressure bias modulator integrator can also be initialized to the value of the measured brake pressure when the wheel velocity error signals indicate the beginning of a skid. Brake pressure difference signals are generated to indicate the difference between brake pressure and a commanded brake pressure, and an adjusted brake pressure error signal is generated in response to the brake pressure difference signals. | 09-11-2008 |