Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method and apparatus for eliminating aircraft landing gear fore-and-aft vibration is provided. The method includes using a tuned mass absorber attached to the landing gear. The gear walk motion has a peak amplitude motion and a pre-peak amplitude motion. The tuned mass absorber includes a mass and a spring, with the mass being oriented to move in a fore-and-aft direction at a frequency and amplitude that counterbalances the gear fore-and-aft vibration. The mass in one embodiment is of an amount in the range of 1 to 2 percent of the effective landing gear mass. In one embodiment, the tuned mass absorber is attached to a landing gear strut near the strut's distal end. The motion of the tuned mass absorber mass moves at a frequency and amplitude that counterbalances the gear walk pre-peak amplitude motion. Therefore, the absorber mass is of an amount less than the mass required to counterbalance gear walk peak amplitude motion.

Abstract: An aircraft automatic braking system processes the flight crew selected stopping position of the aircraft on the runway via a control display unit (30) and the aircraft's actual position, provided by a global positioning system (34), to generate a stop-to-position deceleration control signal in a provided control logic (36). If the flight crew selects the stop-to-position autobraking mode, the system determines whether or not a stop-to-position autobraking mode meets several predetermined criteria and, if the criteria are met, applies a control signal to the aircraft's braking system (62, 66) such that the aircraft is smoothly braked tending it to stop at the selected runway stopping position. The system eliminates the need for pilot lookup in a manual to determine a desired autobraking setting to choose based on altitude, temperature, approach speed and runway conditions and also operates to reduce pilot workload during limited visibility conditions.

Abstract: Left and right main gear wheel speed signals are processed by a circuit which is a model of aircraft rigid body motion to provide a synthesized nose wheel velocity representative signal.

Abstract: Left and right main gear wheel speed signals are processed by a circuit which is a model of aircraft rigid body motion to provide a synthesized nose wheel velocity representative signal.

Abstract: An anti-skid valve in an aircraft braking system achieving advantages by the application of hydraulic system pressure, rather than metered braking pressure, to the first stage of a two stage anti-skid valve. When the valve is not in use the quiescent flow tends to erode the first stage valve, thereby degrading performance. The present system shutoff valve eliminates this disadvantage by shutting off system pressure to the valve whenever the brakes are not in use, as indicated by the absence of metered braking pressure.

Abstract: Aircraft velocity information signals are utilized to provide a brake release signal to one or more, but not more than half of the wheels in each locked wheel set e.g. the two rear wheels in a four wheel set on a gear, so that if all braked wheels lock up and hydroplane, the brake relase signal holds half the brakes released and when the released wheels come out of hydroplaning and spinup, then they, in turn, provide conventional locked wheel protection to the remaining wheels in the same locked wheel set.