초록 ▼

An aircraft brake rotor (60) or stator (110) includes a circular disk having first and second walls (62, 112) and a peripheral wall (64, 114) including at least one notch (66, 116) having a bottom (70) and first and second sides (72). The disk further includes first and second peripheral wall portio

An aircraft brake rotor (60) or stator (110) includes a circular disk having first and second walls (62, 112) and a peripheral wall (64, 114) including at least one notch (66, 116) having a bottom (70) and first and second sides (72). The disk further includes first and second peripheral wall portions separated by the notch (66, 116). An insert (10) is mounted in the notch (66, 116) and has first and second legs (14) with inner and outer walls (20, 22) extending along the notch first and second sides (72). The insert (10) has a first portion having a first width. A circumferential distance between the notch first wall (72) and the notch second wall (72) at a position toward the peripheral wall having the notch (66, 116) has a width less than the insert first portion first width. A retainer (30, 118) overlies the disk first and second walls (62, 112) and a portion of the insert (10) to limit axial movement of the insert (10) relative to the rotor (60) or stator (110) disk.

대표청구항 ▼

I claim: 1. An aircraft brake element comprising: a circular disk having first and second walls and a peripheral wall connecting said first and second walls, said peripheral wall including at least one notch having a bottom, first and second sides extending away from said bottom, and first and seco

I claim: 1. An aircraft brake element comprising: a circular disk having first and second walls and a peripheral wall connecting said first and second walls, said peripheral wall including at least one notch having a bottom, first and second sides extending away from said bottom, and first and second edges at said peripheral wall; an insert mounted in said notch and having first and second legs extending along said notch first and second sides, said first and second legs including inner and outer walls, said insert having a first portion having a first width between said outer walls of said insert first and second legs, wherein a circumferential distance between said notch first side and said notch second side at a position between said notch edge and said insert first portion has a width less than said insert first portion first width; and a retainer overlying said disk first and second walls and a portion of said insert to limit axial movement of said insert relative to said disk, said retainer including a central portion having first and second flexible flaps projecting away from the central portion and from each other, said flexible retainer flaps engaging a portion of the inner walls of said insert. 2. The aircraft brake element of claim 1 wherein said retainer overlies said first and second notch edges. 3. The aircraft brake element of claim 1 wherein said inner walls of said insert first and second legs are separated by a first distance at a first location and separated by a second distance less than said first distance at a location between said first location and said notch first edge. 4. The aircraft brake element of claim 1 wherein each of said inner walls includes a soffit. 5. The aircraft brake element of claim 4 wherein said retainer includes a flexible retainer flap engaging said soffits of said inner walls. 6. The aircraft brake element of claim 1 wherein said retainer is connected to said insert. 7. The aircraft brake element of claim 1, wherein said retainer overlies said peripheral wall, each of said inner walls includes a soffit, and said retainer includes a flexible retainer flap engaging said soffits. 8. The aircraft brake element of claim 1 wherein said outer walls of said insert first and second legs converge toward each other in a direction toward the distal ends of said legs. 9. An aircraft brake element comprising: a circular rotor or stator disk having first and second walls and a peripheral wall connecting said first and second walls, said peripheral wall including at least one notch having a bottom and first and second sides extending away from said bottom; an insert mounted in said notch and having first and second legs extending along said notch first and second sides, said first and second legs including inner and outer walls, said insert and notch being mutually configured such that said insert is axially but not radially removable from said notch; and a retainer overlying said disk first and second walls to limit axial movement of said insert relative to said rotor or stator disk, said retainer including a central portion having first and second flexible flaps projecting away from the central portion and from each other, said a flexible flaps engaging a portion of the insert first side inner wall. 10. The aircraft brake element of claim 9 wherein the distance between said notch first and second sides at said notch bottom is greater than the distance between said notch first and second sides at said peripheral wall. 11. A method of securing an insert in a peripheral notch of an aircraft brake element comprising the steps of: providing an aircraft brake disk having first and second sides and a peripheral wall having a notch, the notch having side edges converging in a direction toward the peripheral wall having the notch; providing an insert comprising a central body and first and second legs projecting from the central body, outer portions of the first and second legs converging toward each other; axially inserting the insert into the peripheral notch; providing a retainer having a central portion and having first and second parallel walls; radially inserting the central portion of the retainer into the notch such that the retainer first and second parallel walls overlie the rotor first and second sides; and securing the retainer to the insert wherein said step of providing a retainer having a central portion comprises the step of providing a retainer having a central portion having first and second flexible flaps projecting away from the central portion and from each other, and said step of radially inserting the central portion into the notch comprises the step of inserting the central portion until the flaps each engage a soffit on the first and second legs.