Abstract: An outboard wheel half has an axis and includes an outboard wheel structure configured to receive at least a portion of a tire. The outboard wheel half also includes a structure defining an alignment hole usable to align a hubcap relative to the structure. The structure defines a pocket circumferentially aligned with the alignment hole to reduce an amount of stress at a location of the alignment hole.

Abstract: A valve includes an electrical park valve configured to receive an electrical park signal and to allow hydraulic fluid to flow through a first electrically-controlled channel in response to the signal indicating a parking request, and a main valve configured to receive the hydraulic fluid from the first electrically-controlled channel and to allow the hydraulic fluid to flow to a braking actuator in response to receiving the hydraulic fluid. The valve also includes an electrical emergency control valve configured to allow the hydraulic fluid to flow through a first control channel in response to a request for emergency braking. The valve also includes an emergency enable valve configured to receive the hydraulic fluid from the first control channel and to allow the hydraulic fluid to flow to the braking actuator in response to receiving the hydraulic fluid from the electrical emergency control valve.

Abstract: Systems and methods for an aircraft emergency and park brake system are disclosed. The emergency and park brake system may comprise an emergency and park brake controller. The emergency and park brake controller may be configured to receive brake signals from mechanical and electrical inputs, generate a braking command comprising data from the brake signal, and transmit the braking command to control braking force. The emergency and park brake controller may receive brake signals from multiple locations including from the aircraft and from a remote location.

Abstract: An electrically controlled park and emergency brake system is disclosed. The brake system may comprise a brake control module having a shut-off valve in fluid communication with an outboard servo-valve and an inboard servo-valve. An emergency/park power source may supply fluid to the shut-off valve. The brake system may also comprise a vehicle management system in electronic communication with the brake control module. The brake system may also comprise mechanical inputs, including a wheel well brake handle and a cockpit brake handle. The brake system may also comprise redundant emergency/park power sources.

Abstract: A brake system for an aircraft is provided according to various embodiments. The system may include a left pedal arrangement comprising a left pedal, a first left sensor to generate a first left signal in response to translation of the left pedal. The system also includes a right pedal arrangement comprising a right pedal, a first right sensor to generate a first right signal in response to translation of the right pedal. Normal brake control logic controls the brake system in response to a normal condition being set. The normal brake control logic commands a left brake based on the left signal, and a right brake based on the first right signal. Emergency brake control logic controls the brake system in response to an emergency condition being set. The emergency brake control logic commands a same force to the left and right brakes based the left and right signals.

Abstract: Systems and methods for emergency brake systems are provided herein. In this regard, a brake system may comprise a summing lever having a first end and a second end, a brake handle coupled to the first end of the summing lever, the brake handle rotatably coupled about a first axis, and a linear actuator having a plunger, the plunger being coupled to the second end of the summing lever. In various embodiments, an idler link may be coupled between the brake handle and the first end of the summing lever. The brake system may further comprise a brake cable coupled between the summing lever and a brake metering valve. The brake metering valve may be actuated in response to at least one of the brake handle being rotated about the first axis or the linear actuator being actuated.

Abstract: The present disclosure provides systems and methods for stiction tolerant brake force estimation. In various embodiments, a method for stiction tolerant brake force estimation may comprise receiving, by a controller, a first motor state at a first time, calculating, by the controller, a first uncompensated brake force estimate based upon the first motor state, calculating, by the controller, a first linear speed based upon the first motor state, and calculating, by the controller, a first stiction compensated brake force estimate based upon at least one of the first linear speed and the first uncompensated brake force estimate.

Abstract: The present disclosure relates to control actuation smoothing, and more particularly, to a control actuation smoothing system that smoothes brake actuation. The smoothing may be determined in response to a filter. In various embodiments, the smoothing may enhance brake component performance.

Abstract: The present disclosure provides systems and methods related to determining observed applied brake force of an aircraft braking system. In various embodiments, a system for calculating observed applied force comprises a current sensor in communication with a controller, a position sensor in communication with the controller and configured to measure a rotational speed of a motor shaft, and a tangible, non-transitory memory configured to communicate with the controller.

Abstract: The present disclosure provides systems and methods for stiction tolerant brake force estimation. In various embodiments, a method for stiction tolerant brake force estimation may comprise receiving, by a controller, a first motor state at a first time, calculating, by the controller, a first uncompensated brake force estimate based upon the first motor state, calculating, by the controller, a first linear speed based upon the first motor state, and calculating, by the controller, a first stiction compensated brake force estimate based upon at least one of the first linear speed and the first uncompensated brake force estimate.

Abstract: The present disclosure relates to rate detection components, and more particularly, to a rate detection system that determines the update rate of commands. The update rate of the commands may be determined in response to the incidence of similarities and differences among samples of the commands.

Abstract: The present disclosure provides systems and methods related to determining observed applied brake force of an aircraft braking system. In various embodiments, a system for calculating observed applied force comprises a current sensor in communication with a controller, a position sensor in communication with the controller and configured to measure a rotational speed of a motor shaft, and a tangible, non-transitory memory configured to communicate with the controller.

Abstract: The present disclosure relates to rate detection components, and more particularly, to a rate detection system that determines the update rate of commands. The update rate of the commands may be determined in response to the incidence of similarities and differences among samples of the commands.

Abstract: The present disclosure relates to control actuation smoothing, and more particularly, to a control actuation smoothing system that smoothes brake actuation. The smoothing may be determined in response to a filter. In various embodiments, the smoothing may enhance brake component performance.