Electronic aircraft braking system with brake wear measurement, running clearance adjustment and plural electric motor- actuator ram assemblies

a technology of actuator rams and actuators, applied in the field of electronic aircraft braking systems, can solve the problems of inherently imprecise, increased running clearance of actuator rams, and devices adding weight and complexity to the braking system

US20070125607A1Inactive Publication Date: 2007-06-07THE BF GOODRICH CO
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Patent Information

Authority / Receiving Office
US · United States
Patent Type
Applications(United States)
Current Assignee / Owner
Publication Date
2007-06-07
Estimated Expiration
Not applicable · inactive patent

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Abstract

An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor. Also provided is an actuator housing including a guideway for each ram, the guideway and ram having the same polygonal cross-section, whereby the ram nut is guided and restrained from rotation by the guideway as it is translated by a ball screw in threaded engagement with the ram nut for selective movement into and out of forceful engagement with the brake disk stack for applying and releasing braking force on a rotatable wheel. An electric motor is drivingly connected to each ball screw by a first gear integral with the ball screw, a second gear in mesh with the first gear, and a pinion on a rotating drive shaft of the electric motor.
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Description

RELATED APPLICATION DATA

[0001] This application is a continuation of U.S. patent application Ser. No. 10 / 796,776 filed Mar. 9, 2004, which is a continuation of U.S. patent application Ser. No. 10 / 268,409 filed Oct. 10, 2002, which is a continuation of U.S. patent application Ser. No. 09 / 486,687, filed Mar. 1, 2000, which is a continuation-in-part of U.S. patent application Ser. No. 08 / 853,513, filed May 9, 1997. The aforesaid applications are hereby incorporated herein by reference in their entireties.FIELD OF THE INVENTION

[0002] The invention herein described relates generally to brake control systems, more particularly to electronic braking systems, and still more particularly to aircraft braking systems. BACKGROUND OF THE INVENTION

[0003] Known in the prior art are aircraft wheel and brake assemblies including a non-rotatable wheel support, a wheel mounted to the wheel support for rotation, and a brake disk stack having front and rear axial ends and alternating rotor and stator...

Examples

Embodiment Construction

[0041] Referring now in detail to the drawings, FIG. 1 diagrammatically illustrates an exemplary multi-actuator computer controlled brake actuation system 20 to which the principles of the invention may be applied. The major functions of the system 20 are performed by a controller 21 and a brake actuator assembly 22. The brake actuator assembly 22 may be mounted in a conventional manner on a wheel and brake assembly 23 to apply and release braking force on a rotatable wheel 24 of such wheel and brake assembly. The present invention is particularly suited for use in aircraft braking systems, as will be appreciated by those skilled in the art.

[0042] Because the invention was conceived and developed for use in an aircraft braking system and particularly in association with the system 20, it will be herein described chiefly in this context. However, the principles of the invention in their broader aspects can be adapted to other types of systems including, for example, hydraulic system...