Abstract:
An electro-mechanical brake assembly comprising a brake disk stack having a center axis; and a plurality electro-mechanical actuators for applying braking pressure to the brake disk stack. The actuators are circumferentially arranged around the center axis, and each actuator includes a housing, a linearly movable ram, a screw for linearly moving the ram, a nut mounted for rotation in the housing and operatively engaged with the screw such that rotation of the nut effects linear movement of the screw for urging the ram into forceful engagement with the brake disk stack, an electric motor for rotating the nut, and an anti-rotation device for preventing rotation of the screw relative to the housing when the nut is rotated to effect linear movement of the screw. The foregoing arrangement provides for greater stroke than prior art actuators without sacrificing durability and performance.

Description:
RELATED APPLICATION DATA 
     This application is a continuation of U.S. patent application Ser. No. 10/878,290 filed on Jun. 28, 2004 now abandoned, which is a continuation of U.S. patent application Ser. No. 09/660,063 filed on Sep. 12, 2000 now abandoned, which claims benefit of U.S. Provisional Application No. 60/153,731 filed Sep. 13, 1999, all of which are hereby incorporated herein by reference in their entirety. 
    
    
     FIELD OF THE INVENTION 
     The invention herein described relates generally to an electric brake actuator module particularly useful in aircraft. 
     BACKGROUND OF THE INVENTION 
     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 disks mounted with respect to the wheel support and wheel for relative axial movement. Each rotor disk is coupled to the wheel for rotation therewith and each stator disk is coupled to the wheel support against rotation. A back plate is located at the rear end of the disk pack and a brake head is located at the front end. The brake head houses a plurality of actuator rams that extend to compress the brake disk stack against the back plate. Torque is taken out by the stator disks through a static torque tube or the like. 
     Electrically actuated aircraft brakes of various configurations are known, as exemplified by U.S. Pat. Nos. 4,381,049, 4,432,440, 4,542,809 and 4,567,967. The brake assemblies shown in these patents include electric motors which respond to an electrical control signal to effect rotation of a ring gear member which interacts through a plurality of balls to drive a linearly movable ram member into contacting engagement with a brake disk stack to effect compression thereof and braking of a wheel. 
     In U.S. Pat. No. 4,596,316, another configuration of an electrically actuated brake uses a roller screw drive wherein a ring gear member interacts through a plurality of roller screws to drive a ram member into engagement with the brake pressure plate to effect compression of the brake disk stack for braking action. A plurality of electric motors and their associated pinions drive a ring gear into rotation and the plurality of roller screws effect linear axial movement of the ram member. 
     In U.S. Pat. No. 4,865,162, a further electrically actuated aircraft brake employs a roller screw drive mechanism driven by an electric torque motor through a gear drive associated with either the screw or the nut of the roller screw drive mechanism. Rotation of the gear drive by the torque motor moves the other one of the screw or nut into axial engagement with a brake disk stack to compress the stack for braking. A plurality of the roller screw drive mechanisms and respective gear drives and torque motors are mounted in a balanced arrangement about the axis of the wheel to apply and release a brake pressure force on the brake disk stack in response to an electrical control signal to the torque motors. 
     In U.S. Pat. No. 4,995,483, there is described a motor position feedback control system for an electrically actuated aircraft brake. The system controller provides brake clamping and declamping in response to a position feedback controlled brake actuator in which an electric torque motor drives a rotating member of a reciprocating drive mechanism to axially move another member into and out of engagement with a brake pressure plate of a multi-disk brake assembly. The position feedback is obtained using a rotor position resolver which provides relative position information to the controller. Such a system requires a re-calibration of the position sensor after a power interruption which may result in loss of braking capability, long recovery time and possible uncommanded brake clamp force application. 
     Among other things, it would be desirable to have an electrically actuated aircraft brake actuator module that has a greater stroke than prior art actuators, thereby to provide longer use between brake disk replacement. 
     SUMMARY OF THE INVENTION 
     The present invention provides an electro-mechanical brake assembly comprising a brake disk stack having a center axis; and a plurality electro-mechanical actuators for applying braking pressure to the brake disk stack. The actuators are circumferentially arranged around the center axis, and each actuator includes a housing, a linearly movable ram, a screw for linearly moving the ram, a nut mounted for rotation in the housing and operatively engaged with the screw such that rotation of the nut effects linear movement of the screw for urging the ram into forceful engagement with the brake disk stack, an electric motor for rotating the nut, and an anti-rotation device for preventing rotation of the screw relative to the housing when the nut is rotated to effect linear movement of the screw. The foregoing arrangement provides for greater stroke than prior art actuators without sacrificing durability and performance. 
     According to one embodiment of the invention, the screw has a bore opening to an end thereof opposite the ram, and the anti-rotation device includes an anti-rotation guide extending into the bore opening in the screw for rotationally interfering with one another to restrain rotation of screw relative to the housing. Preferably, the anti-rotation guide further functions to support the screw against lateral movement. To this latter end, anti-rotation guide extends to a point overlapping the internally threaded portion of the nut that is operatively engaged with the screw. 
     A preferred nut and screw are a ball-screw device. Also, it is preferably that the electric motor be mounted to and carried by the housing. Ideally, each actuator is a self-contained unit mounted to a wheel mount of a wheel and brake assembly for removal independently of one another and the brake disk stack. 
     According to another embodiment of the invention, the anti-rotation device includes a bellows connected between the screw and the housing and fixed against rotation relative to the housing, the bellows functioning to restrain rotation of screw relative to the housing. The bellows preferably is sealed with respect to the housing and screw to prevent foreign material from entering the housing at the screw. 
     Further in accordance with the invention, a position sensor supplies a position signal representative of the position of the ram. The position sensor is fully enclosed within the housing and is connected directly to the screw or ram, or indirectly to a threaded portion on the nut. 
     The foregoing and other features of the invention are hereinafter fully described and particularly pointed out in the claims, the following description and the annexed drawings setting forth in detail one or more illustrative embodiments of the invention, such being indicative, however, of but one or a few of the various ways in which the principles of the invention may be employed. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is cross-sectional view of an aircraft wheel and brake assembly 
         FIG. 2  is a plan view of an exemplary electro-mechanical actuator that has particular application in the aircraft wheel and brake assembly of  FIG. 1 . 
         FIG. 3  is a cross-sectional view of the brake actuator of  FIG. 1  taken along the line  2 - 2  of  FIG. 2 . 
         FIG. 4  is an exploded perspective view of the brake actuator of  FIG. 1 . 
         FIG. 5  is a diagrammatic illustration of another embodiment of an electro-mechanical actuator according to the invention. 
         FIG. 6  is an illustration similar to  FIG. 5 , but showing the ram extended. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Because the invention was conceived and developed for use in an aircraft braking system, 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 braking systems, such as in train brake systems. 
     Referring now in detail to the drawings and initially to  FIG. 1 , a wheel and brake assembly according to the present invention is generally indicated at  10 . The assembly  10  generally comprises a brake  11  and an aircraft wheel  12  which is supported for rotation by bearings  13  and  14  on an axle  15 . The axle  15  forms a wheel mount and is attached to the end of an aircraft landing gear strut  16  or a truck attached to the end of a landing gear strut. The brake  11  includes a brake disk stack  20 , torque tube  21  and an actuator assembly  22 . 
     The actuator assembly  22  includes a brake head  25  having an integral torque take-out arm  26 . The torque take-out arm  26  extends radially and functions as an interface between the brake actuator assembly and the landing gear axle structure (the strut  16  in the illustrated embodiment). The torque take-out arm  26  and a torque reaction arm  28  on the strut  16  have interengaging devices which provide for transfer of torque from the torque take-out arm to the torque reaction arm when braking force is being applied to the disk brake stack  20  by the brake actuator assembly  22 . In the illustrated embodiment, the take-out arm  26  has on the inboard side thereof an axially opening recess (socket)  29  for receiving a torque reaction lug  30  on the torque reaction arm  28  and a load transducer  31 . The output of the load transducer (load cell) may be supplied to a brake controller for use in controlling the braking operation. 
     The brake disk stack  20  includes stationary brake elements and rotary brake elements that are interleaved and surround the torque tube. The stationary and rotary brake elements are in the form of stator disks  35  and rotor disks  36 . The stator disks  35  are splined to the torque tube  21  and the rotor disks  36  are splined to the wheel  12  interiorly of the wheel&#39;s rim. As is conventional, the splined connection may be effected by a plurality of spline or drive keys  38  and  39  that are spaced around the circumference of the rim/torque tube to permit axial movement of the rotor/stator disks while being held to the wheel/torque tube against relative rotation. 
     The disk stack  20  is located between a back pressure member  42  and the brake head  25 . The back pressure member  42  is formed by a radial flange at the outer end of the torque tube  21  that engages the last brake disk at the outboard end of the disk stack. 
     Pressure is applied to the inboard end of the disk stack  20  by one or more actuator rams  45 . The actuator rams  45  are included in respective actuator modules  46  mounted to the brake head  25  by suitable means that may enable quick and easy attachment and detachment of the actuator modules to and from the brake head. The actuator modules preferably are mounted in a circular arrangement around the rotational axis  48  of the wheel, preferably with the actuator rams  45  circumferentially equally spaced apart. 
     Preferably, the modules  46  are identical and interchangeable, and a representative one of the actuator modules is shown in  FIG. 2-4 . Each actuator module  46  preferably includes an electric motor  50 , a gear train  51 , and a ball screw assembly  52 . The motor  50 , gearing  51  and ball screw assembly are all carried in a module housing  53 . A mounting flange (not shown) may be provided on the housing for securing the module to the brake head  20 . 
     The gearing  51  includes a pinion  59  on the drive shaft of the electric motor  50 , a first-stage transfer gear member  60  in mesh at its input end with the pinion  59 , a second stage transfer gear member  61  in mesh at its input end with the output end of the first stage gear member  60 , and a ball nut gear  62  in mesh with the output end of the second stage gear  61 . The ball nut gear  62  may be formed integrally with the ball nut  65  of the ball screw assembly  52  (although reference herein is made to certain structures as being integral as is preferred, it should be understood such structures alternatively may be composed of discrete components joined together to form a functionally equivalent structure). Suitable bearings are provided for the various rotating components. The first stage transfer gear member  60  is supported by bearings  67  and  68 . The second stage transfer gear member  61  is supported by bearings  69 . The nut  65  is supported at one end by a rotational bearing  71  and at its other end by a rotational bearing  72  and a thrust bearing  73 . A thrust washer  74  may be interposed between the thrust bearing  73  and a housing shoulder  75 , such shoulder  75  in the illustrated embodiment being formed on a removable access cover  76 . 
     The ball screw assembly  52  is comprised of the ball nut  65  with the integral gear  62 , a ball screw  80  that moves linearly upon rotation of the ball nut, an anti-rotation guide member  82  extending into the hollow interior of the ball screw, and a ram pad  84  that attaches to the end of the ball screw and provides an insulating interface with the brake disk stack ( FIG. 2 ). The ball screw and ball nut have respective spiral grooves/threads and associated balls for converting rotary motion to linear motion. Also, other rotary to linear motion conversion devices may by employed, if desired, with the linear moving member coinciding with the ball screw and functioning at its outboard end as the actuator ram. 
     In the illustrated ball screw assembly, the interior bore  88  of the screw  80  and the anti-rotation guide  82  have corresponding polygonal cross-sections defined by plural inner/outer side surfaces which rotationally interfere with one another to restrain rotation of the screw relative to the housing  53 . As is preferred and illustrated, one or more of the side surfaces, most preferably all of the side surfaces, are planar and form regular polyhedrons providing a close sliding fit between the ball screw and the guide member. It will be appreciated, however, that other configurations may be used although less preferred. The guide member is fixedly mounted to the housing by a nut  89 . 
     Each actuator module  46  preferably includes an output ram resolver or position sensor  90  which provides for actuator rotation and/or position feedback. For example, the ball nut  65  may be mechanically connected to an RVDT position sensor or other absolute position sensor by gears  92  and  93 , the latter being in mesh with gear  94  on the nut  65 . Other types of position sensors/transducers may be used as desired for a particular application. 
     Referring now to  FIGS. 5 and 6 , another embodiment of electro-mechanical brake actuator  100  according to the invention is illustrated, respectively in a retracted and extended position. The brake actuator  100  is essentially as above described, except that in place of the anti-rotation guide, a metal bellows  102  is used as an anti-rotation device. The bellows  102  is connected at one end to the housing  103  and at its other end to the screw  104  directly or via the ram  105 . The bellows additionally functions as a seal preventing foreign material from entering the housing at the screw. 
     The brake actuator  100  also differs in that a position sensor  108  is provided within the interior of the screw. The sensor may by an LVDT or other absolute position sensor with one end connected to the screw by an insulator  110  and the other end connected to the housing, as at an actuator component cover  109  forming part of the overall housing. 
     Although the invention has been shown and described with respect to a certain preferred embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described integers (components, assemblies, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such integers are intended to correspond, unless otherwise indicated, to any integer which performs the specified function of the described integer (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application. 
     In addition, the invention is considered to reside in all workable combinations of features herein disclosed, whether initially claimed in combination or not and whether or not disclosed in the same embodiment.