WO1997025548B1 - Multi-disc aircraft brake with restrained torque tube - Google Patents
Multi-disc aircraft brake with restrained torque tubeInfo
- Publication number
- WO1997025548B1 WO1997025548B1 PCT/US1997/000889 US9700889W WO9725548B1 WO 1997025548 B1 WO1997025548 B1 WO 1997025548B1 US 9700889 W US9700889 W US 9700889W WO 9725548 B1 WO9725548 B1 WO 9725548B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- torque tube
- wheel
- foot
- axle
- annular
- Prior art date
Links
- 230000000452 restraining Effects 0.000 claims 8
- 239000012212 insulator Substances 0.000 claims 6
- 230000002093 peripheral Effects 0.000 claims 2
- 210000001847 Jaw Anatomy 0.000 claims 1
- 230000004323 axial length Effects 0.000 claims 1
- 230000003247 decreasing Effects 0.000 claims 1
- 230000001419 dependent Effects 0.000 claims 1
- 230000002401 inhibitory effect Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 claims 1
- 230000000670 limiting Effects 0.000 claims 1
- 230000000712 assembly Effects 0.000 abstract 1
Abstract
Axial and rotational movement of the torque tube foot (49) of an aircraft's disc brake assembly (10) is restrained to substantially dampen or eliminate the short interval high frequency vibration previously experienced on brake application. Vibration damage experienced to brake and landing gear components with brake assemblies of the prior design is avoided.
Claims
AMENDED CLAIMS
[received by the International Bureau on 12 August 1997 (12.08.97); original claims 1, 3, 4, 7 and 8 replaced by amended claims 1 and 7; original claims 2, 5, 9 and 12 amended;
original claims 3, 4, 8 and 15 cancelled; remaining claims unchanged (9 pages)]
1. An improved aircraft brake installation
circumferentially disposed in a complete annulus about an aircraft wheel axle defining an axis and brake assembly having a brake housing attached to aircraft landing gear structure, a torque tube attached at one end to said brake housing, a plurality of brake discs rotationally fixed to said housing through said torque tube and being axially movable, a plurality of wheel discs located alternately and adjacently to said brake discs and radially fixed to an aircraft wheel while axially moveable, brake operating means for axially engaging said brake discs with said wheel discs, said brake operating means including piston means, said torque tube including a radially inwardly extending torque tube leg spaced from said end of said torque tube attached to said brake housing, and said torque tube leg supporting a circumferentially extending torque tube foot adjacent said wheel axle, the improvement comprising;
restraining means for restricting axial and rotational movement of said torque tube foot, said restraining means comprising;
an annular flange member mounted to the axle and positioned adjacent a first side of said torque tube foot to stop lateral movement of said torque tube foot in the direction of said first side, and
wheel spacer means, said wheel spacer means
containing a cylindrical passage for mounting said wheel spacer means to said axle opposite said annular flange member on a second side of said torque tube foot, said wheel spacer means containing an annular portion extending radially outwardly from said wheel axis, said annular portion being positioned adjacent said second side of said torque tube foot to stop lateral movement of said torque tube foot in the
direction of said second side such that said torque tube foot is restrained from moving in both axial directions and both rotational directions relative to said axle.
2. The improvement as defined in claim 1, wherein said aircraft wheel brake includes sleeve means for ensleeving a portion of the length of said aircraft wheel axle and for separating said torque tube foot from said wheel axle; said annular flange member being integrally formed in and radially protruding outwardly from said axle sleeve member.
5. The invention as defined in claim 2, wherein said wheel axle includes a tapered portion at a predetermined position along said wheel axle coincident with an end to said sleeve means, and wherein said sleeve means includes a radially inwardly extending rim means; and wherein said wheel spacer means includes a surface for abutment with said rim means; and said sleeve means being shrink fit upon said wheel axle to hold said sleeve means in fixed axial position on said wheel axle.
6. The invention as defined in claim 5, wherein said torque tube foot includes heat insulator means located at the distal end thereof, said heat insulator means comprising a hollow cylindrical geometry having a cylindrical wall of predetermined thickness; and wherein said invention further comprises:
foot bushing means, said foot bushing means being located underlying said torque tube foot and overlying said axle sleeve means, for filling an annular gap between said distal end of said torque tube foot adjacent said heat
insulator and said axle sleeve means, said foot bushing comprising a grommet shape in geometry having a hollow cylindrical portion and a circular radially outwardly extending rim portion circumferentially bordering an end of said hollow cylinder; said foot bushing being oriented with said hollow cylindrical portion filling said annular gap and said rim portion being located in between said second side of said foot and said annular portion of said wheel spacer means.
7. In an aircraft multiple disc and brake assembly having an axle with a central axis of rotation;
bearing means mounted on said axle;
a rotatable cylindrical wheel member journaled on said bearing means for rotation about said axle;
said cylindrical wheel member having an inner
peripheral circumferentially extending portion and a
radially disposed web portion for mounting on said bearing means;
a plurality of rotor discs coupled to said inner peripheral portion of said wheel for rotation therewith and for axial positioning relative thereto;
a torque tube mounted over said axle to encompass at least a portion thereof;
a plurality of εtator discs, said stator discs being coupled to said torque tube for axial movement therealong; said rotor discs being interleaved between said εtator discs to define a brake stack;
piston means positioned to one end of said brake stack, said piston means being operative to move said discs axially into frictional engagement to provide a braking of said cylindrical wheel member;
said torque tube further including:
an annular hub at one end of said torque tube which is attached to said piston means;
a torque tube backplate located to the remaining end of said brake stack for bracing said remaining end against force exerted by said piston means;
a radially inwardly extending annular leg, and a circumferentially extending torque tube foot for mechanically bracing said torque tube against said axle, said torque tube foot connected to an inner end of said annular leg;
said torque tube foot being supported by said annular leg at a predetermined axial position along said wheel axle between said torque tube annular hub and said torque tube backplate;
said torque tube foot having an annular portion extending about the outer periphery of said wheel axle; and
restraining means, supported by said wheel axle, for restraining axial movement of said torque tube foot from said predetermined axial position and inhibiting rotational movement of said torque tube foot, said restraining means comprising;
first radially outwardly extending annular flange means, said first flange means being mounted to said wheel axle and fixed in axial position thereon, said flange means being located alongside a first side of said torque tube foot for restricting movement of said torque tube foot in a first axial direction along said wheel axis; and
second radially outwardly extending annular flange means being mounted to said wheel axle and fixed in axial position thereon, said second flange means being located alongside a second side of said torque tube foot for limiting movement of said torque tube foot in a second axial direction, opposite to said first axial direction.
9. The invention as defined in claim 7, wherein said wheel axle includes an annular ridge located at an axial position to one side of said torque tube foot and circumferentially extending about said wheel axle; and, further comprising: axle sleeve means ensleeving a portion of the axial length of said wheel axle, including portions of the length of said wheel underlying said torque tube foot;
said axle sleeve means including rim means for engaging said annular ridge of said wheel axle for preventing axial movement of said sleeve in one axial direction;
wheel spacer means mounted on said axle, said wheel spacer means being in abutment with said rim means of said axle sleeve means for preventing axial movement of said sleeve means in the opposite axial direction. 10. The invention as defined in claim 9, wherein said first flange means is integrally connected to said wheel spacer means; and wherein said second flange means is integrally connected to said sleeve means.
11. The invention as defined in claim 10, wherein said torque tube foot includes heat insulator means located at
the distal end thereof, said heat insulator means comprising a hollow cylindrical geometry having a cylindrical wall of predetermined thickness; and wherein said invention further comprises :
foot bushing means, said foot bushing means being located underlying said torque tube foot and overlying said axle sleeve means, for filling an annular gap between said distal end of said torque tube foot adjacent said heat insulator and said axle sleeve means, said foot bushing comprising a grommet shape in geometry having a hollow cylindrical portion and a circular radially outwardly extending rim portion circumferentially bordering an end of said hollow cylinder; said foot bushing being oriented with said hollow cylindrical portion filling said annular gap and said rim portion being located in between said second side of said foot and said annular portion of said wheel spacer means.
12. The invention as defined in claim 7, wherein said wheel axle includes an annular ridge located at an axial position to one side of said torque tube foot and
circumferentially extending about said wheel axle; and wherein said restraining means comprises :
a first member having a cylindrical outer wall and a hollow interior defining first, second and third cylindrical wall portions of decreasing diameter located in coaxial side by side order, wherein first and second annular ridges are formed at the juncture between said inner wall portions; a first radially outwardly extending annular flange portion coaxially mounted to said first cylindrical portion at a first position thereon;
said outer wall of said second cylindrical portion including nut threads;
washer shaped spacer means for fitting over said cylindrical outer wall to one side of said torque tube foot; circular nut means for threading engagement with said nut threads on said cylindrical outer wall for holding said washer shaped spacer means in place; and
bushing means, said bushing means fitting inside said first member; said bushing means containing a
circumferentially extending ridge at an intermediate
position along an outer surface for abutment with said second rim portion of said first member; and said bushing means including an annular rim at one end for abutting engagement with said wheel axle ridge.
13. The invention as defined in claim 7, wherein said wheel axle includes an annular ridge located at an axial position to one side of said torque tube foot and circumferentially extending about said wheel axle; and wherein said
restraining means comprises:
a first clamping member having a cylindrical outer wall and a hollow interior and a first radially outwardly
extending annular flange portion to serve as a clamping jaw; said first clamping member being mounted to said axle at a predetermined axial position and covering at least a portion of said axle sleeve;
a second clamping member, said second clamping member fitting over a portion of said first clamping member and
STATEMENT UNDER ARTICLE 19
This Statement is submitted to explain the reasons for the accompanying Article 19 amendments . Independent Claim 1 has been amended to define further the torque tube foot restraining means to include (1) an annular flange member on a first side of the torque tube foot and (2) a wheel spacer means opposite the annular flange member on a second side of the torque tube foot . Claim 1 further recites that the torque tube foot is restrained from moving in both axial and rotational directions relative to said axle . As such, the recitations of former Claims 3 and 4 have been incorporated into Claim 1 and Claims 3 and 4 have been cancelled. With regard to Claim 7 , the retraining means has been further defined in a manner similar to Claim 1 and includes first and second radially outwardly extending annular flange means for restricting movement of the torque tube foot . Claim 8
formerly recited these features in dependent form and has thus been cancelled. Claim 15 has also been cancelled and Claims 2 , 5 , 9 and 12 have been amended for consistency and to correct several typographical errors in the claims as filed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US09/585,791 | 1996-01-12 | ||
| US08/585,791 US5862890A (en) | 1996-01-16 | 1996-01-16 | Restrained aircraft brake apparatus |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| WO1997025548A2 WO1997025548A2 (en) | 1997-07-17 |
| WO1997025548A3 WO1997025548A3 (en) | 1997-10-16 |
| WO1997025548B1 true WO1997025548B1 (en) | 1997-10-16 |
Family
ID=24342979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US1997/000889 WO1997025548A2 (en) | 1996-01-12 | 1997-01-09 | Multi-disc aircraft brake with restrained torque tube |
Country Status (2)
| Country | Link |
|---|---|
| US (2) | US5862890A (en) |
| WO (1) | WO1997025548A2 (en) |
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| US5862890A (en) * | 1996-01-16 | 1999-01-26 | Mcdonnell Douglas Corporation | Restrained aircraft brake apparatus |
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| GB2342415B (en) * | 1998-10-02 | 2000-10-04 | Dunlop Ltd | Torque transmission device |
| FR2786239B1 (en) * | 1998-11-25 | 2001-02-16 | Messier Bugatti | PNEUMATICALLY CONTROLLED DISC FRICTION DEVICE FOR TRANSMISSION |
| CA2318688C (en) * | 1999-09-13 | 2008-11-18 | The B.F. Goodrich Company | Aircraft landing gear with integrated brake actuation system |
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| US20030150674A1 (en) * | 2002-02-13 | 2003-08-14 | White Hydraulics, Inc. | Disk spring hydraulic clutch/brake |
| FR2842496B1 (en) * | 2002-07-19 | 2005-02-11 | Messier Bugatti | BRAKING SYSTEM FOR AIRCRAFT WHEELS |
| FR2859259B1 (en) | 2003-08-28 | 2006-02-03 | Messier Bugatti | AIRCRAFT BRAKE ASSEMBLY |
| FR2862280B1 (en) * | 2003-11-14 | 2006-03-03 | Messier Bugatti | LANDING DEVICE, BRAKE FOR AIRCRAFT WHEEL, AIRCRAFT AIRBORNE WHEEL ASSEMBLY, AND METHOD OF MAINTAINING SUCH A LICENSOR |
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| US10473171B2 (en) | 2017-05-15 | 2019-11-12 | Goodrich Corporation | Extended torque tube |
| US10145429B1 (en) * | 2017-09-08 | 2018-12-04 | Goodrich Corporation | Aircraft brake torque and clamp force reaction through landing gear structure |
| US10598209B2 (en) * | 2017-09-08 | 2020-03-24 | Goodrich Corporation | Aircraft brake torque load reaction through landing gear bogie structure |
| US10309468B2 (en) * | 2017-10-20 | 2019-06-04 | Goodrich Corporation | Torque plate barrel having blended barrel support pedestal |
| US10408290B2 (en) * | 2018-02-08 | 2019-09-10 | Goodrich Corporation | Insulated torque plate foot assembly |
| FR3083579B1 (en) * | 2018-07-06 | 2020-11-27 | Safran Landing Systems | ANTI-VIBRATION CENTERING RING FOR TORSION TUBE FOOT OF AN AIRCRAFT BRAKE AND BRAKE EQUIPPED WITH SUCH RING |
| EP3597496B1 (en) | 2018-07-16 | 2020-09-02 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
| FR3085453B1 (en) * | 2018-08-29 | 2020-11-20 | Safran Landing Systems | REAR DISC OF A STACK OF AIRCRAFT BRAKE CARBON DISCS EQUIPPED WITH PLOTS, AND BRAKE APPLYING |
| CN110203380B (en) * | 2019-07-08 | 2024-02-23 | 西安航空制动科技有限公司 | Integral heat shield for aircraft brake device |
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-
1996
- 1996-01-16 US US08/585,791 patent/US5862890A/en not_active Expired - Lifetime
-
1997
- 1997-01-09 WO PCT/US1997/000889 patent/WO1997025548A2/en active Application Filing
- 1997-07-08 US US08/889,245 patent/US6003641A/en not_active Expired - Lifetime
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