| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 340960000 | Landing gear indicator | 10 |
| 20090040072 | AIRCRAFT STEERING ANGLE WARNING SYSTEM - A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres. | 02-12-2009 |
| 20090091476 | LOCK SENSOR FOR AN INTERNALLY LOCKING ACTUATOR - The present invention provides a lock sensor for use in an actuator such as is used in aircraft landing gear systems. The lock sensor comprises at least one field emitting device ( | 04-09-2009 |
| 20090207047 | Wireless Landing Gear Verification System - According to one embodiment, a verification system for an aircraft includes a cockpit instrument in communication with a wireless communication circuit. The wireless communication circuit is coupled to a landing gear member and operable to determine a position of the landing gear member and transmit the position to the cockpit instrument using a wireless signal. | 08-20-2009 |
| 20100225503 | SYSTEM AND METHOD FOR DETECTING A DRAGGING BRAKE - Systems and methods to determine whether a brake is dragging based on post-takeoff spindown data are provided. The method comprises measuring spindown of a wheel to obtain spindown data. The spindown data is compared with a spindown envelope, and notification is provided if the spindown data indicates a wheel is spinning down outside a spindown envelope. | 09-09-2010 |
| 20120056759 | SYSTEM FOR DISPLAYING MULTIPLE OVERLAID IMAGES TO A PILOT OF AN AIRCRAFT DURING FLIGHT - A system for displaying first and second images to a pilot of an aircraft includes, but is not limited to, a sensor subsystem that detects a light transmission originating from outside the aircraft and generates a first signal indicative of the light transmission, a dynamic condition sensor that detects a dynamic condition of the aircraft and generates a second signal indicative of the dynamic condition of the aircraft, a display unit, and a processor that is communicatively coupled to the sensor subsystem and to the dynamic condition sensor and operatively coupled to the display unit. The processor is configured to command the display unit to display a first image corresponding to the first signal, to display a second image overlaid over the first image corresponding to the second signal, and to modify the appearance of the second image to enhance the pilot's ability to discern the first image. | 03-08-2012 |
| 20120119925 | Illuminated Aircraft Wheel Chock Indicator - A visual display used to indicate when aircraft wheel chocks have been inserted against the aircraft tires and the tarmac. The display is mounted on the exterior of an aircraft terminal at an elevation that is easily viewable by an aircraft operator. The indicator system contains illuminated characters operated from an electrical switch. The electrical switch is located remotely from the display where it is accessible by personnel standing on the tarmac. The switch positions include “OUT” and “IN”. When the switch is moved to the “IN” position, the arrow characters are illuminated. When the switch is moved to the “OUT” position, the arrow characters are not illuminated. This system provides a safe and efficient means for ground personnel to signal the aircraft operator that the wheel chocks are in place against the aircraft wheel assembly. | 05-17-2012 |
| 20120326894 | METHOD OF PROTECTING AN AIRCRAFT LANDING GEAR WHILE THE AIRCRAFT IS BEING TOWED, AND PIN FOR COUPLING A TOWING BAR TO AN ORIENTABLE LOWER PART OF A LANDING GEAR - A method of protecting an aircraft undercarriage ( | 12-27-2012 |
| 20130021173 | User-Defined Pages for Aircraft - A method and apparatus for displaying aircraft information. A selection of a piece of dynamic information is detected about an aircraft on a first display on a user interface. The piece of dynamic information is used to operate the aircraft and changes during operation of the aircraft. The piece of dynamic information selected from the first display is added to a custom display on the user interface. The custom display is displayed on the user interface on a display system for the aircraft. | 01-24-2013 |
| 20140210647 | SWITCH ASSEMBLY AND OVER-STEER DETECTION SYSTEM - A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manually rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators. | 07-31-2014 |
| 20150145703 | METHODS TO MONITOR COMPONENTS OF AN AIRCRAFT LANDING SYSTEM - Methods to monitor components of an aircraft landing system are disclosed herein. An example method includes determining a brake assembly temperature and determining a wheel temperature. The example method also includes retrieving an estimated increase in the wheel temperature from a data structure based on the wheel temperature and the brake assembly temperature. The example method further includes determining a maximum wheel temperature based on the wheel temperature and the estimated increase in the wheel temperature. | 05-28-2015 |
