WO2010120700A1 - Shock and vibration isolation for aircraft brake control valve - Google Patents
Shock and vibration isolation for aircraft brake control valve Download PDFInfo
- Publication number
- WO2010120700A1 WO2010120700A1 PCT/US2010/030781 US2010030781W WO2010120700A1 WO 2010120700 A1 WO2010120700 A1 WO 2010120700A1 US 2010030781 W US2010030781 W US 2010030781W WO 2010120700 A1 WO2010120700 A1 WO 2010120700A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- shock
- vibration
- insulating sheath
- brake control
- control valve
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/04—Arrangements of piping, valves in the piping, e.g. cut-off valves, couplings or air hoses
Definitions
- This invention relates to generally to shock and vibration isolation for aircraft brake control valves, and more particularly relates to improved mounting of an electro- hydraulic brake control valve and a shock and vibration isolation system including shock and vibration isolators that can be used to isolate the mounting of the electro-hydraulic brake control valve from the undesirable effects of aircraft shock and vibration, and structural loads generated at the manifold mounting interface.
- one type of brake control valve uses a pressure control valve with a flapper nozzle first stage that incorporates an armature that is essentially an undamped spring with a natural frequency in the 300 to 500 Hz range, depending on the armature spring rate. Vibration profiles at brake control valve mounting locations almost always contain this frequency, so that vibrations in this range will result in some degree of damage to the flapper nozzle as a result of motion of the undamped armature at its resonant frequency that can result in unsatisfactory performance or even failure of the brake control valves.
- One known type of active/passive damping apparatus for large structures includes a passive type damping mechanism to be mounted on the structure, including an added mass, spring, and dampener. Hydraulic cylinders are mounted on the structure and connected to the added mass, with an electro-hydraulic servo mechanism to switch the hydraulic cylinders between passive and active type operation, and a control unit is provided for switching the electro-hydraulic servo mechanism between passive and active type operation in response to the velocity and displacement of the added mass as well as the velocity of the structure.
- a force actuator applies a force between the inertial mass and the member, and resonance of the active vibration absorber is damped.
- a first sensor provides a first signal indicative of at least one movement and/or stress related parameter for the member, and a second sensor provides a second signal indicative of a reaction of the inertial mass.
- a control unit is provided for controlling the force actuator arrangement using the first signal and the second signal.
- a tuned mass damper is also known for damping dynamic response in a primary structure in one, two, or three dimensions.
- the tuned mass damper includes a secondary mass, a spring, and a viscoelastic element, with the spring and viscoelastic element interposed between the primary structure and the secondary mass.
- shock and vibration isolation mounting system for an aircraft brake control valve to allow the aircraft brake control valve to be mounted in environments that are often too severe for conventional hard mounted valve mounting arrangements.
- the present invention provides a system for hard mounting of a manifold of a brake control valve by providing shock and vibration isolators to be used in mounting of the manifold of the brake control valve, wherein the shock and vibration isolators are operative to protect components of the brake control valve from shock, vibration and high pressure pulses that can occur in response to harmonic resonance of a component that can damage the component, such as a flapper valve of the brake control valve.
- the shock and vibration isolation mounting system of the invention allows the manifold of an aircraft brake control valve to be mounted in severe environments, such as in an aircraft wheel well, or on or near landing gear.
- the brake control valve shock and vibration isolation mounting system also allows for brake control electronics to be co- located on a shock and vibration isolated brake control valve manifold to provide for improved signal processing and signal integrity.
- the present invention provides for a brake control valve shock and vibration isolation mounting system including a shock and vibration isolator that can be incorporated in mounting feet of an aircraft brake control valve manifold.
- the mounting feet of the brake control valve manifold typically have mounting apertures each configured to receive and retain a shock and vibration isolator.
- Each of the shock and vibration isolators has a natural frequency selected to protect components of a brake control valve from random vibration and to avoid gun fire sinusoidal frequencies that can otherwise damage components of the brake control valve.
- the natural frequency of the shock and vibration isolators is pre-selected and predetermined to be in a range to protect one or more components of a brake control valve, such as a flapper nozzle, for example, from random shocks and vibration and to avoid gun fire sinusoidal frequencies
- the pre-selected, predetermined natural frequency of the shock and vibration isolators is preferably below the natural frequency range of 300 to 500 Hz of the flapper nozzle of the brake control valve, such as approximately 75.5 Hz, for example.
- each of the generally tubular shock and vibration isolators includes a radially inner generally spool shaped rigid insert portion and a radially outer generally spool shaped vibration insulating sheath portion.
- the radially inner generally spool shaped rigid insert portion is formed of a first or upper radially inner rigid tubular member and a second or lower radially inner rigid tubular member that overlaps and interfits with the first or upper radially inner rigid tubular member
- the radially outer generally spool shaped vibration insulating sheath portion is formed of a first or lower generally tubular radially outer vibration insulating sheath portion and a second or upper generally tubular radially outer vibration insulating sheath portion that overlaps and interfits with the first or lower generally tubular outer vibration insulating sheath portion.
- each shock and vibration isolator has a radially outer diameter that is dimensioned such that a fastener placed through the central aperture of the rigid tubular insert portion will be spaced apart from the mounting foot in which the shock and vibration isolator is placed by the vibration insulating sheath portion or jacket, wherein vibrations transmitted through the fastener from the aircraft structural part will be substantially isolated from the mounting feet of the manifold of the brake control valve.
- the first or upper radially inner rigid tubular member of the radially inner generally spool shaped rigid insert portion includes an upper radially outwardly flared annular end portion and a lower tubular shaft portion
- the second or lower radially inner rigid tubular member of the radially inner generally spool shaped rigid insert portion includes a lower radially outwardly flared annular end portion and an upper flange that overlaps and interfits with the lower tubular shaft portion of the first or upper radially inner rigid tubular member.
- the first or upper radially inner rigid tubular member and the second or lower radially inner rigid tubular member of the generally spool shaped rigid insert portion together define a central aperture therethrough for receiving a fastener for hard mounting of the mounting feet of the brake control valve manifold to a structural part of the aircraft.
- the second or upper generally tubular radially outer vibration insulating sheath portion includes a radially outer tubular portion and a radially inner annular portion
- the first or lower generally tubular radially outer vibration insulating sheath portion includes a lower radially outwardly flared end portion with a lower lip portion that extends over the lower radially outwardly flared end portion of the second or lower radially inner rigid tubular member of the radially inner generally spool shaped rigid insert portion
- the first or lower generally tubular radially outer vibration insulating sheath portion includes an upper radially inner flange that is overlapped by and interfits with the radially inner annular portion of the second or upper generally tubular radially outer vibration insulating sheath portion.
- the first or lower generally tubular radially outer vibration insulating sheath portion is secured about the upper radially inner tubular shaft portion and lower radially outwardly flared annular end portion of the second tubular member of the generally spool shaped rigid insert portion, and the second or upper generally tubular radially outer vibration insulating sheath portion is secured about an upper radially outwardly flared annular end portion of the first or upper radially inner rigid tubular member.
- first and second radially inner rigid tubular members forming the inner, generally spool shaped rigid insert portion are typically made of metal, such as stainless steel, titanium, aluminum, copper, brass and the like, and combinations thereof, for example, and the first and second radially outer vibration insulating sheath portions of the radially outer generally spool shaped vibration insulating sheath portion are typically formed of a vibration isolating elastomer such as fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof, and the like, for example.
- a vibration isolating elastomer such as fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof, and the like, for example.
- FIG. 1 is a perspective view of an aircraft brake control valve manifold with shock and vibration isolators installed in the mounting feet of the aircraft brake control valve manifold, according to the present invention, and showing servo-brake control valves, park brake and shutoff solenoids also assembled into the unit.
- FIG. 2 is a top plan view of the aircraft brake control valve manifold of Fig. 1 with portions of the aircraft brake control valve manifold and shock and vibration isolators removed for clarity, showing the interior portions of the mounting feet of the aircraft brake control valve manifold, according to the present invention.
- FIG. 3 is a perspective view of one of the shock and vibration isolators of Fig. 1, according to the present invention.
- FIG. 4 is a top plan view of the shock and vibration isolator of Fig. 3.
- Fig. 5 is a side elevational view of the shock and vibration isolator of Fig. 3.
- Fig. 6 is a cross-sectional view through a mounting aperture of a mounting foot of an aircraft brake control valve manifold.
- Fig. 7 is a cross-sectional view through the mounting aperture of a mounting foot of Fig. 6, showing a shock and vibration isolator assembled in the mounting aperture.
- Fig. 8 is a top plan view of an upper portion of a shock and vibration isolator according to the present invention.
- Fig. 9 is a cross-sectional view of the upper portion of the shock and vibration isolator taken along line 9-9 of Fig. 8.
- Fig. 10 is a bottom plan view of a lower portion of a shock and vibration isolator according to the present invention.
- Fig. 11 is a cross-sectional view of the lower portion of the shock and vibration isolator taken along line 11 - 11 of Fig. 10.
- Fig. 12 is an illustration of a transmissibility curve for the shock and vibration isolators according to the invention placed in mounting feet of a manifold of a brake control valve.
- an aircraft brake control valve manifold 10 including a plurality of mounting feet, such as four mounting feet 12a, 12b, 12c, 12d, for example, as illustrated in Figs. 1 and 2, configured to be rigidly or hard mounted to a structural part of an aircraft (not shown), such as by bolts or other type of fasteners, for example.
- Each of the plurality of mounting feet typically has a corresponding generally cylindrical central mounting aperture 14a, 14b, 14c, 14d configured to receive and retain a shock and vibration isolator 16 assembled into the mounting aperture.
- the shock and vibration isolator of the invention advantageously has a preselected, predetermined natural frequency selected to protect one or more selected components of an aircraft brake control valve from random vibration and to avoid gun fire sinusoidal frequencies that can otherwise damage sensitive components of the brake control valve.
- the natural frequency of the shock and vibration isolators is predetermined to be in a range to protect a sensitive flapper nozzle of the aircraft brake control valve from random vibration and to avoid gun fire sinusoidal frequencies, and is preferably below the natural frequency range of the flapper nozzle of the brake control valve, such as below 300 to 500 Hz, for example.
- the natural frequency of the shock and vibration isolators of the present invention can be approximately 75.5 Hz, for example.
- each shock and vibration isolator has a central aperture configured to receive a fastener such as a bolt for hard mounting of the mounting feet of the brake control valve manifold to a structural part of the aircraft.
- each shock and vibration isolator 16 is generally spool shaped, having a first or upper widened side 18 and a second or lower widened side 20 with an assembled height 21, and having a radially outer diameter D 2 , and a narrower middle portion 22 having a radially outer diameter D] .
- the shock and vibration isolator 16 includes a radially inner generally spool shaped rigid insert portion 24 and a radially outer generally spool shaped vibration insulating sheath portion or jacket 26. As is best seen in Figs.
- the radially inner generally spool shaped rigid insert portion 24 is formed of a first or upper radially inner rigid tubular member 28 and a second or lower radially inner rigid tubular member 30 that overlaps and interfits with the first or upper radially inner rigid tubular member 28.
- the first or upper radially inner rigid tubular member 28 includes an upper radially outwardly flared annular end portion 32 and a lower tubular shaft portion 33 having a radially outer surface 34.
- the second or lower radially inner rigid tubular member 30 includes a lower radially outwardly flared annular end portion 36 and an upper flange 40 that can be assembled to overlap and interfit with the lower tubular shaft portion 33 of the first or upper radially inner rigid tubular member.
- the lower tubular shaft portion 33 and outer surface 34 of the lower tubular shaft portion can be matingly assembled into the upper flange 40; however, a threaded mating of these portions or a bonding interface between these portions may also be suitable.
- the internal diameter D 3 of the cylindrical mounting aperture 14 is preferably smaller than the external diameter D 4 of the upper radially outwardly flared annular end portion 32 and the lower radially outwardly flared annular end portion 36 that are part of the rigid insert portion 24, to prevent the shock and vibration isolator 16 from pulling out of the brake control manifold, thereby making the assembly of the shock and vibration isolators in the mounting feet of the brake control manifold fail safe.
- the first or upper radially inner rigid tubular member 28 and the second or lower radially inner rigid tubular member 30 of the generally spool shaped rigid insert portion together define the central aperture 42 therethrough for receiving a fastener (not shown) such as a bolt for hard mounting of the mounting feet of the brake control valve manifold to a structural part of the aircraft.
- the first and second inner rigid tubular members 28, 30 forming the inner, generally spool shaped rigid insert portion are typically made of a rigid material such as a metal, such as 300 series stainless steel.
- the first and second inner rigid tubular members may also be formed from other types of stainless steel, titanium, aluminum, copper, brass and the like, and combinations thereof, for example, which may also be suitable for providing rigidity to the hard mounting, particularly when a bolt or other type of fastener is placed through the shock and vibration isolator and is tightened over the rigid tubular insert portion of the shock and vibration isolator.
- the radially outer generally spool shaped vibration insulating sheath portion or jacket 26 is formed of a first or lower generally tubular radially outer vibration insulating sheath portion 44 and a second or upper generally tubular radially outer vibration insulating sheath portion 46 that overlaps and interfits with the first or lower generally tubular radially outer vibration insulating sheath portion 44.
- the second or upper generally tubular radially outer vibration insulating sheath portion 46 includes a radially outer tubular portion 48 and a radially inner annular portion 50.
- the first or lower generally tubular radially outer vibration insulating sheath portion 44 includes a lower radially outwardly flared end portion 52 with a lower lip portion 54 that extends over the lower radially outwardly flared end portion 36 of the second or lower radially inner rigid tubular member 30 of the radially inner generally spool shaped rigid insert portion 24, and an upper radially inner tubular shaft portion 56 having an upper radially inner flange 58 that is overlapped by and interfits with the radially inner annular portion 50 of the second or upper generally tubular radially outer vibration insulating sheath portion 46.
- the first or lower generally tubular radially outer vibration insulating sheath portion 44 is secured about the upper radially inner tubular shaft portion 38 and lower radially outwardly flared annular end portion of the second or lower radially inner rigid tubular member 30 of the generally spool shaped rigid insert portion 24, and the second or upper generally tubular radially outer vibration insulating sheath portion 46 is secured about the first or upper radially outwardly flared annular end portion 32 of the first or upper radially inner rigid tubular member 28.
- the first or lower generally tubular or annular outer vibration insulating sheath portion 44 and the second or upper generally tubular radially outer vibration insulating sheath portion 46 of the radially outer generally spool shaped vibration insulating sheath portion or jacket are typically formed of an elastomer such as fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof, and the like, for example.
- an elastomer such as fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof, and the like, for example.
- the outside diameter D 2 of the shock and vibration isolator is dimensioned such that a bolt or other type of fastener placed through the central aperture of the rigid tubular insert portion will be spaced apart from the mounting foot in which the shock and vibration isolator is placed by the vibration insulating sheath portion or jacket, so that vibrations transmitted through the bolt or other type of fastener from the aircraft structural part or framework will be substantially isolated from the mounting feet of the manifold of the brake control valve.
- vibrations transmitted through the bolt or other type of fastener from the aircraft structural part or framework can only be transmitted through the vibration insulating sheath portion or jacket portions of the shock and vibration isolators, and are damped due to the preselected, predetermined natural frequency of the shock and vibration isolators.
- Fig. 12 illustrates a transmissibility curve for the mounting of a manifold of a brake control valve having a part or component such as a flapper nozzle first stage that incorporates an armature with a natural frequency in the 300 to 500 Hz range, for protection against shock and vibration in this frequency range, by providing shock and vibration isolators according to the invention that can be incorporated in the mounting feet of the manifold.
- the natural frequency of the shock and vibration isolators must always be selected to be to be in a vibration attenuation region of isolation lower than the natural frequency of whatever part or component that must be protected from shock and vibration, such as a flapper nozzle, for example, although other similar parts or components with other natural frequencies for which the natural frequency of the shock and vibration isolators must be lower may also be suitable targets for protection from shock and vibration, hi this example, the natural frequency of the shock and vibration isolators of the present invention were approximately 75.5 Hz in all axes, so that the maximum transmissibility in the region of amplification 60 was a maximum of 6.0, at the natural frequency of the shock and vibration isolators, and the transmissibility of the frequencies of concern in the range of 300 to 500 Hz is substantially minimized, falling well within the attenuation region of isolation 62 of the shock and vibration isolators.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Transportation (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Valves And Accessory Devices For Braking Systems (AREA)
- Springs (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2012506100A JP2012523352A (en) | 2009-04-13 | 2010-04-12 | Aircraft brake control valve shock and vibration isolation |
BRPI1013745A BRPI1013745B8 (en) | 2009-04-13 | 2010-04-12 | MOUNTING SYSTEM WITH SHOCK AND VIBRATION INSULATION FOR RIGID MOUNTING OF AN AIRCRAFT BRAKE CONTROL VALVE TO A STRUCTURAL PART OF AN AIRCRAFT |
EP10764976.6A EP2419308B8 (en) | 2009-04-13 | 2010-04-12 | Shock and vibration isolation for aircraft brake control valve |
CA2758498A CA2758498A1 (en) | 2009-04-13 | 2010-04-12 | Shock and vibration isolation for aircraft brake control valve |
ES10764976T ES2711252T3 (en) | 2009-04-13 | 2010-04-12 | Insulation against shocks and vibrations for aircraft brake control valve |
CN2010800263717A CN102458937A (en) | 2009-04-13 | 2010-04-12 | Shock and vibration isolation for aircraft brake control valve |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/422,923 US8136894B2 (en) | 2009-04-13 | 2009-04-13 | Shock and vibration isolation for aircraft brake control valve |
US12/422,923 | 2009-04-13 | ||
US12/496,557 | 2009-07-01 | ||
US12/496,557 US8308149B2 (en) | 2009-04-13 | 2009-07-01 | Shock and vibration isolation for aircraft brake control valve |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010120700A1 true WO2010120700A1 (en) | 2010-10-21 |
Family
ID=42933750
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2010/030781 WO2010120700A1 (en) | 2009-04-13 | 2010-04-12 | Shock and vibration isolation for aircraft brake control valve |
Country Status (8)
Country | Link |
---|---|
US (1) | US8308149B2 (en) |
EP (1) | EP2419308B8 (en) |
JP (1) | JP2012523352A (en) |
CN (1) | CN102458937A (en) |
BR (1) | BRPI1013745B8 (en) |
CA (1) | CA2758498A1 (en) |
ES (1) | ES2711252T3 (en) |
WO (1) | WO2010120700A1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8661833B2 (en) * | 2011-01-14 | 2014-03-04 | Hamilton Sundstrand Corporation | Bleed valve module |
US9609773B2 (en) * | 2012-11-16 | 2017-03-28 | Te Connectivity Corporation | Isolator for an electronic device |
US9548144B2 (en) * | 2012-11-16 | 2017-01-17 | Tyco Electronics Corporation | Isolation system for an electronic device |
JP5753225B2 (en) * | 2013-06-17 | 2015-07-22 | 住友理工株式会社 | Vibration isolator |
JP6666177B2 (en) * | 2016-03-15 | 2020-03-13 | 本田技研工業株式会社 | Engine driven work machine |
US11162553B2 (en) * | 2019-02-12 | 2021-11-02 | Deere & Company | Externally-damped electromechanical valve assemblies |
DE102019005092B4 (en) * | 2019-07-22 | 2022-05-12 | Sumitomo Riko Company Limited | Vibration damper and method for manufacturing a vibration damper |
DE202021106327U1 (en) | 2021-11-19 | 2023-02-27 | Reinz-Dichtungs-Gmbh | Tolerance-independent movable hole reinforcement unit for a shield unit, with defined clamping when tightening the screws |
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US2616641A (en) * | 1946-05-31 | 1952-11-04 | Bendix Aviat Corp | Aircraft equalizing brake control valve |
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US4738435A (en) * | 1985-05-16 | 1988-04-19 | Flower Wallace C | Fluid filled vibration isolator which operates quietly over broad frequency and amplitude ranges |
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US8136894B2 (en) * | 2009-04-13 | 2012-03-20 | Hydro-Aire, Inc., A Subsidiary Of Crane Co. | Shock and vibration isolation for aircraft brake control valve |
-
2009
- 2009-07-01 US US12/496,557 patent/US8308149B2/en active Active
-
2010
- 2010-04-12 WO PCT/US2010/030781 patent/WO2010120700A1/en active Application Filing
- 2010-04-12 JP JP2012506100A patent/JP2012523352A/en active Pending
- 2010-04-12 CA CA2758498A patent/CA2758498A1/en not_active Abandoned
- 2010-04-12 ES ES10764976T patent/ES2711252T3/en active Active
- 2010-04-12 EP EP10764976.6A patent/EP2419308B8/en active Active
- 2010-04-12 CN CN2010800263717A patent/CN102458937A/en active Pending
- 2010-04-12 BR BRPI1013745A patent/BRPI1013745B8/en active IP Right Grant
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US2477972A (en) * | 1945-08-27 | 1949-08-02 | Mb Mfg Company Inc | Vibration isolator unit |
US2616641A (en) * | 1946-05-31 | 1952-11-04 | Bendix Aviat Corp | Aircraft equalizing brake control valve |
US2658710A (en) * | 1950-05-04 | 1953-11-10 | Robinson Aviat Inc | Vibration isolation unit |
US2894711A (en) * | 1956-05-11 | 1959-07-14 | Wells & Company Ltd A | Vibration isolator and shock mount |
US3245727A (en) * | 1962-08-15 | 1966-04-12 | Crane Co | Anti-skid brake control system |
US4738435A (en) * | 1985-05-16 | 1988-04-19 | Flower Wallace C | Fluid filled vibration isolator which operates quietly over broad frequency and amplitude ranges |
US6910671B1 (en) | 2000-09-06 | 2005-06-28 | Illinois Tool Works Inc. | Shock mount assembly with polymeric thimble tube |
Non-Patent Citations (1)
Title |
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See also references of EP2419308A4 |
Also Published As
Publication number | Publication date |
---|---|
EP2419308A4 (en) | 2017-10-18 |
ES2711252T3 (en) | 2019-04-30 |
CN102458937A (en) | 2012-05-16 |
EP2419308A1 (en) | 2012-02-22 |
BRPI1013745A2 (en) | 2016-04-05 |
EP2419308B8 (en) | 2022-09-21 |
BRPI1013745B8 (en) | 2023-01-10 |
BRPI1013745B1 (en) | 2019-09-10 |
CA2758498A1 (en) | 2010-10-21 |
US20100258989A1 (en) | 2010-10-14 |
EP2419308B1 (en) | 2019-01-02 |
JP2012523352A (en) | 2012-10-04 |
US8308149B2 (en) | 2012-11-13 |
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