Aircraft brake

• US 5,205,382 A
• Filed: 03/05/1992
• Issued: 04/27/1993
• Est. Priority Date: 10/09/1990
• Status: Expired due to Fees

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Edmisten, Frank D.
• Primary Examiner(s): HALVOSA, GEORGE
• Application Number:
  US07/846,318
• Time in Patent Office: 418 Days
• Field of Search: 188/264 G, 188/217, 188/196 R, 188/196 P, 188/71.8, 188/71.5, 188/72.4, 188/369, 188/370, 192/70.2, 192/70.25, 92/129, 403/74, 403/76, 403/114, 403/115, 403/122
• US Class Current: 188/71.5
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes
• CPC Class Codes: F16D 2055/0058 Fully lined, i.e. braking surface extending over the entire disc circumference
• CPC Class Codes: F16D 2121/02 Fluid pressure
• CPC Class Codes: F16D 2125/587 Articulation, e.g. ball-socket
• CPC Class Codes: F16D 55/40 actuated by a fluid-pressure device arranged in or one the brake
• CPC Class Codes: F16D 65/18 adapted for drawing members together , e.g. for disc brakes
• CPC Class Codes: F16D 65/543 comprising a plastically-deformable member
• CPC Class Codes: F16D 65/84 for disc brakes discs characterised by means for cooling F16D65/128
• CPC Class Codes: Y10T 403/32181 Universal

Abstract

An aircraft multiple disc and brake assembly having an axle with a cylindrical wheel member journaled thereon. The inner peripheral portion of the wheel member has a plurality of circumferentially spaced splines to support axially spaced rotor discs which are interleaved with stator discs which are splined to axially extending ribs mounted on a torque tube which in turn is connected to the axle. A piston support member is secured to the axle via a hub member and has a plurality of circumferentially spaced cylinders with a piston slidably mounted therein. One end of each piston cooperates with the receiving cylinder to define a piston chamber that permits pressurization to actuate the braking action. The other end of the piston has a pair of discs with mating spherical contoured surfaces to permit a tilting therebetween to eliminate side loading and provide even wear.

Claims

1. In an aircraft multiple disc and brake assembly having an axle means with a central axis;

a cylindrical wheel member journaled on said axle means;

said cylindrical wheel member having an inner peripheral circumferentially extending portion and a radially disposed rim portion for mounting on said axle means for rotation thereon;

said inner peripheral portion has a plurality of circumferentially spaced splines;

a plurality of axially spaced rotor discs mounted on said axle and keyed to said splines for rotation therewith;

said axle means having a stationary hub means;

a torque tube secured to said hub means;

said torque tube having a plurality of axially extending ribs;

a plurality of stator discs with circumferentially spaced slots engaging said ribs for axial movement of said stator discs;

said rotor discs interleaved between said stator discs to define a brake stack;

a piston support member secured to said hub, a plurality of circumferentially spaced cylinders mounted on said piston support member;

each cylinder having an elongated piston sleeve slidably mounted therein;

one end of said piston sleeve has an end wall that is cooperative with said cylinder to define a piston chamber which is selectively pressurized, the other end of said piston sleeve has a pair of caps integral therewith and with annular mating surfaces;

one of said caps has an annular portion secured to said sleeve while the other one of said caps has a rearwardly disposed annular portion movably retained relative to said one cap, said other one of said caps has a forwardly disposed disc portion operative to engage said brake stack; and

said annular mating surface of said one cap secured to said sleeve has a convex surface mating with a concave surface of said other cap to distribute forces away from the axis of said sleeve as said other cap engages said brake stack.

2. In an aircraft multiple brake disc and brake assembly as set forth in claim 1 wherein said caps are heat insulators.

3. In an aircraft multiple brake disc and brake assembly as set forth in claim 2 wherein said mating surfaces of said caps have a dry film lubricant thereon.

4. In an aircraft multiple brake disc and brake assembly as set forth in claim 1 wherein wear adjuster means are mounted in each of said piston sleeves which cooperates with said caps to define cup shaped pistons.

5. In an aircraft multiple brake disc and brake assembly as set forth in claim 4 wherein each of said wear adjuster means has a rod member extending through said end wall of said piston sleeve which is secured to said cylinder, and said wear adjuster means is operative upon pressurization of said piston chamber to extend said caps a substantial distance beyond said cylinder under substantial wear of said brake discs.

6. In an aircraft multiple brake disc assembly having an axis means with a central axis;

a wheel member journaled on said axle means for rotation thereon;

said wheel member having an inner peripheral portion with a plurality of circumferentially spaced splines;

a plurality of axially spaced rotor brake discs mounted on said axle means and keyed to said splines for rotation with said wheel member;

said axle means having a stationary hub;

a torque tube secured to said hub;

said torque tube having a plurality of circumferentially spaced axially extending ribs;

a plurality of axially spaced stator brake discs mounted on said axle means and keyed to said ribs for axial movement thereon;

said rotor discs interleaved with said stator discs;

a piston housing secured to said hub;

one of said stator discs being closely adjacent to said piston housing defining a pressure plate for said rotor and stator brake discs;

a plurality of circumferentially spaced cylinders mounted on said piston housing;

each cylinder having a bore therein with an end plate at one end thereof;

a piston member slidably mounted in each of said bores and cooperative with an adjacent end plate of said cylinder to define piston chambers;

each piston member having an elongated cylindrically shaped sleeve member;

each sleeve member having a piston head that extends out of said bore of said cylinder;

each of said piston heads having an inner cap and an outer cap integral therewith;

said inner cap having an annular rearwardly disposed portion secured to said sleeve member;

said outer caps being operative to frictionally engage said pressure plate;

said inner cap and outer cap of each piston head having annular mating surfaces with the annular mating surface of said inner cap having a convex shape to allow pivoting movement of the outer cap relative to the inner cap upon deflection of said piston housing upon brake application to distribute forces away from the axis of said cylindrically shaped sleeve member.

7. In an aircraft multiple brake disc assembly as set forth in claim 6 wherein said outer cap has a central hub secured to said inner cap by a retaining ring to allow angular displacement of said outer cap relative to said inner cap.