• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to aircraft assemblies, vibration isolation, and methods of assembling vibration isolation assemblies. An aircraft includes a fuselage, a mounted component disposed within the fuselage, and a vibration isolation assembly disposed within the fuselage, and mounting the fuselage mounted component. The vibration isolation assembly includes a mounting rail, an interior member, a support connection, and an elastomer. The mounting rail defines a cavity and an opening. The inner member has an upright and a flange, knowing that the flange is disposed in the cavity. The support fitting is attached to the upright and mounted component. The elastomer is arranged between the flange and the mounting rail within the cavity.
    公开号:FR3026089A1
    申请号:FR1558955
    申请日:2015-09-23
    公开日:2016-03-25
    发明作者:Michael Lucas；Kristopher Philip Lynch；Benjamin Frank Wilson；Jeffrey Jonas
    申请人:Gulfstream Aerospace Corp；
    IPC主号:
    专利说明:

    [0001] AIRCRAFT AND ARMCHAIR RAIL ARRANGEMENTS FOR THE VIOLATION ISOLATION OF FLOOR-COMPONENT COMPONENTS TECHNICAL FIELD [001] The technical field generally relates to sets of rails for securing wheelchairs and aircraft for insulation against floor-mounted component vibration, and more specifically, relates to mountings of mounting rails and aircraft with enclosed elastomeric interior elements arranged in a seat rail cavity. BACKGROUND [002] A conventional passenger aircraft comprises a fuselage, a cabin interior attached to and / or supported by the fuselage, and a floor that defines a bottom of the interior of the cabin and which is supported by the fuselage. When the aircraft is in flight, the fuselage interacts with the atmosphere. This interaction generates vibrations that flow through the floor to any component attached to the floor. Vibrating components, if unchecked, will be perceived by the occupants of the aircraft as noise, which is undesirable. [003] The noise generated by these vibration components can be reduced by using a vibration isolation assembly. A conventional vibration isolation assembly rigidly mounts a floor support fitting and then attaches the mounted component to the support fitting using an antivibrator. These conventional sets have spatial constraints that limit the size of the anti-vibration assemblies. Such a limited size can reduce the noise reduction potential of these conventional assemblies. Although these conventional vibration isolation assemblies are suitable for their intended purpose, improvements can be made. [4] Thus, it is desirable to provide improved aircraft and assemblies for vibration isolation of floor-mounted components. In addition, other desirable attributes and features will become apparent with the following summary and detailed description, as well as the appended claims, taken into account in conjunction with the accompanying drawings and this context. SUMMARY OF EMBODIMENTS [5] Various non-limiting embodiments of aircraft assemblies, vibration isolation, and methods of assembling vibration isolation assemblies are disclosed herein. [6] In a first non-limiting embodiment, an aircraft includes, but is not limited to, a fuselage, a mounted component arranged within the fuselage, and a vibration isolation assembly arranged at the inside the fuselage and mounting the component mounted on the fuselage. The vibration isolation assembly includes a mounting rail, an interior member, a support connection, and an elastomer. The mounting rail defines a cavity and an opening. The inner member has an upright and a flange, knowing that the flange is disposed in the cavity. The support fitting is attached to the upright and mounted component. The elastomer is arranged between the flange and the mounting rail within the cavity. [7] In a second non-limiting embodiment, a vibration isolation assembly for an aircraft includes, but is not limited to, a chair rail, an interior member, and an elastomer. The armchair rail defines a cavity and an opening. The inner member has an upright and a flange, knowing that the flange is disposed in the cavity and the amount configured to attach a mounted component. The elastomer is arranged inside the cavity between the flange and the arm rail. [8] In a third nonlimiting embodiment, a method of assembling a vibration isolation assembly in an aircraft includes, but is not limited to, the provision of a seat rail defining a cavity and an opening. The method further includes inserting a flange of an inner member and an elastomer into the cavity with an amount of the inner member extending at least partially through the opening. The method further further comprises attaching a support fitting to the upright of the inner member. The method still further includes attaching a floor-mounted component to the support fitting. BRIEF DESCRIPTION OF THE DRAWINGS [9] The advantages of the present invention will be readily apparent, these being better understood with reference to the following detailed description taken into account in conjunction with the accompanying drawings in which: FIG. 1 is a sectional view illustrating a non-limiting embodiment of an aircraft having a vibration isolation assembly in accordance with the teachings of the present disclosure; [0011] FIG. 2 is a sectional view illustrating a non-limiting embodiment of the vibration isolation assembly used in the aircraft of FIG. 1 in accordance with the teachings of this disclosure; [0012] FIG. 3 is a sectional view of the vibration isolation assembly of FIG. Taken across line 3-3; and [0013] FIG. 4 is a block diagram of a method of assembling a vibration isolation assembly in accordance with the teachings of the present disclosure. DETAILED DESCRIPTION [0014] The detailed description has the nature to be given purely by way of example and is not intended to limit the invention or application and uses of the present invention. In addition, the intention is not to be constrained by any theory presented in the preceding context or the detailed description that follows. Various non-limiting embodiments of aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are disclosed herein. Embodiments include various configurations of an inner member encompassed by an elastomer disposed within a cavity of a chair mounting rail in an aircraft. By using the cavity in the armchair rail, the size of the elastomer and the inner member interacting with the elastomer can be increased compared to conventional vibration isolation assemblies with elastomeric material within a compartment of an aircraft. The larger size allows for greater vibration damping and less noise in the aircraft compartment. In addition, the embodiments disclosed herein are able to mitigate vibration with a larger volume of elastomer to improve noise isolation performance over conventional assemblies. A greater understanding of aircraft assemblies and vibration isolation can be obtained by examining the illustrations accompanying this application in conjunction with the discussion of the detailed description that follows. [0016] Referring now to FIG. 1, an aircraft 100 is shown in a sectional view according to the teachings of the present disclosure. The aircraft 100 comprises a fuselage 110, a floor 112, a compartment 113, floor-mounted components 114 and a vibration isolation assembly 116 for each of the floor-mounted components 114. In the example provided, the aircraft 100 is a jet aircraft. In other embodiments, the aircraft 100 may be any other type of airborne vehicle, including but not limited to helicopters, propeller airplanes or airships, without departing from the scope of the aircraft. present disclosure. The fuselage 110 comprises an outer coating 120 and a frame structure 122 on which the outer coating 120 is fixed. The floor 112 includes a plurality of transverse struts, a plurality of floor panels, and a plurality of seat rails or mounting rails that are also included in the vibration isolation assembly 116. The arrangement of the transverse struts , floor panels and mounting rails can have any suitable configuration based on the specific implementation, as will be appreciated by those skilled in the art. In general, the floor 112 is attached to the fuselage 110. The compartment 113 is a cabin, a cockpit or other area surrounded by the floor 112 and the fuselage 110. The floor-mounted components 114 include any floor-mounted component 112 by the vibration isolation assembly 116. In the example provided, two passenger seats and a partition are illustrated as floor-mounted components 114. It will be understood that other components such as chests, sofas, tables, drawers or other floor-mounted components may be mounted to the floor 112 with the vibration isolation assembly 116. [0019] Referring now to FIG. 2 and FIG. 3, the vibration isolation assembly 116 is illustrated in more detail. FIG. 2 shows a sectional view of a vibration isolation assembly 116 before a floor mounted component 114 has been mounted thereto, and FIG. 3 shows a partition mounted on the vibration isolation assembly 116. The vibration isolation assembly 116 includes a chair rail 130, an interior member 132, an elastomer 134, a support fitting 136, and 138. [0020] The chair rail 130 is attached to the fuselage 110 and is typically oriented to extend along a longitudinal direction of the fuselage 110. In some embodiments, the chair rail 130 may be oriented into other directions, such as a lateral direction of the fuselage 110. As used herein, the term "seat rail" refers to a rail configured to be attached to a floor structure of a vehicle, such as an aircraft 100, and on which components are mounted. It will be understood that the components mounted on the arm rail 130 are not limited to armchairs. The arm rail 130 is a type of mounting rail. As used herein, the term "mounting rail" refers to a rail that is configured to mount components to the vehicle, but may be configured to be attached to any portion of the vehicle and may be oriented in any direction. In the example provided, four longitudinally oriented armchairs 130 are spaced laterally within the floor 112. It will be appreciated that any suitable number of arm rails 130 may be used without departing from the scope of the present disclosure. The arm rail 130 is formed of a rigid material which defines a cavity 140 and an opening 142 which faces a ceiling of the aircraft 100 when installed in the fuselage 110, as shown in FIG. FIG. In the example provided, the arm rail 130 is an extruded aluminum rail with a substantially C-shaped cross section that opens towards the ceiling of the aircraft 100 in the installed position shown in FIG. 1. The width of the opening 142 is less than a width of the cavity 140 to form first flange portions 144. Second flange portions 146 extend laterally outwardly from a bottom of the arm rail 130. The second flange portions 146 improve the stiffness of the arm rail 130 in the longitudinal direction and provide a surface on which floor boards and cross members of the floor 112 may be attached. The arm rail 130 may be fixed to the interior of the floor 112 by any fastener or any suitable connector. For example, the arm rail 130 may be bolted or riveted to side transverse members of the floor 112 and may support planks of the floor 112. The arm rail 130 is attached to the fuselage 110 by such cross members and may be secured in further to the fuselage 110 at each longitudinal end of the arm rail 130. The inner member 132 is formed of a rigid material and has an amount 150 and a flange 152. The rigid material of the inner member 132 may be any suitable material, including but not limited to aluminum, steel and other rigid metals or plastics. The flange 152 is disposed within the cavity 140 and has a cross-sectional width greater than the cross-sectional width of the opening 142 in the lateral direction of the fuselage 110. As a result, the flange 152 engages with the first flange portions 144 of the arm rail 130 for retaining the flange 152 within the interior cavity 140. The stud 150 is configured to secure the mounted components 114 using a threaded bore 154. Drilling Threaded thread 154 is configured to mate with the threads of fasteners 138. It will be understood that stud 150 may be configured to secure components mounted with other fasteners or arrangements. The post 150 is partially arranged in, and extends through, the opening 142 of the arm rail 130. It will be understood that the post 150 may have shorter lengths that do not extend through the opening 142, and other suitable attachment configurations may be used without departing from the scope of the present disclosure. The elastomer 134 is disposed in the cavity 140 between the flange 152 and the armchair rail 130 to attenuate the vibrations passing from the armchair rail 130 to the inner member 132. Such attenuation reduces the vibration of the support connection 136 and the mounted component 114 to reduce the noise perceived by the passengers of the aircraft 100. In the example provided, the elastomer 134 includes the flange 152 and substantially fills the entire transverse region of the cavity 140 not occupied by the inner member 132. A flange length 152 and elastomer 134 along a longitudinal direction of the arm rail 130 may be selected according to the particular embodiment. Because the cavity 140 is inside the arm rail 130, the length of the flange 152 and the elastomer 134 are not limited by the space available inside the compartment 113 or by aesthetic considerations. . Therefore, a larger flange 152 and elastomer can be used compared to prior vibration isolation assemblies. The support connection 136 is made of a metal or other rigid material to fix the mounted components 114 on the inner member 132. In the example provided, the support fitting 136 is an aluminum piece L having a horizontal portion 160 and a vertical portion 162. In some embodiments, the support fitting 136 has other shapes and is made of other materials. The support fitting 136 is attached to the inner member 132 with a fastener 138 when the fastener 138 threads into the threaded bore 154. [0027] The support connector 136 is also contiguous and directly affixed to the component mounted 114 by a second fastener 138. Since the support fitting 136 is isolated from the vibrations of the arm rail 130, no additional elastomeric material is required between the support fitting 136 and the mounted component 114. Therefore, The vibration isolation assembly 116 requires less space in the compartment 113 and reduces the noise generated by the support fittings compared to conventional vibration isolation assemblies. [0028] Referring now to FIG. 4, and continuing to refer to FIGS. 1-3, a non-limiting embodiment of a method 200 for assembling a vibration isolation assembly is illustrated. In step 210, a rail of chairs is obtained and installed in the fuselage of an aircraft. Any suitable seat rail may be used and may be installed in any suitable fuselage of any suitable aircraft. In one example, a chair rail 130 can be obtained and installed in the fuselage 110 of an aircraft 100. In the operation 212, an inner member is inserted into a cavity of the armchair rail. For example, the flange 152 of the inner member 132 and the elastomer 134 may be inserted into the cavity 140 of the arm rail 130. In the operation 214, a support connection is attached to the inner member. For example, the support fitting 136 may be attached directly to the inner member 132 with the attachment 138. In the operation 216, a floor mounted component is attached directly to the support fitting. For example, the floor-mounted component 114 may be attached directly to the support fitting 136 with another fastener 138. While at least one exemplary embodiment has been presented in the detailed description herein, prior to the invention, it will be understood that there is a large number of variations. It will also be understood that the exemplary embodiment (s) is / are only examples, and are in no way intended to limit the scope, applicability or configuration of the invention. Rather, the foregoing detailed description will provide those skilled in the art with practical guidance for carrying out an exemplary embodiment of the invention. It is understood that various modifications may be made in the operation and arrangement of the elements described in any embodiment by way of example without departing from the scope of the invention as defined in the appended claims.
    权利要求:
    Claims (20)
    [0001]
    REVENDICATIONS1. Aircraft comprising: a fuselage; a mounted component arranged inside the fuselage; and a vibration isolation assembly arranged inside the fuselage and mounting the fuselage-mounted component, the vibration isolation assembly comprising: a mounting rail defining a cavity and an opening, an interior member having an upright and a flange, knowing that the flange is disposed in the cavity, a support fitting attached to the upright and mounted component, and an elastomer arranged between the flange and the mounting rail within the cavity.
    [0002]
    2. Aircraft according to claim 1, wherein the amount is at least partially arranged in the opening.
    [0003]
    An aircraft according to claim 1, wherein the mounting rail has a substantially C-shaped cross section.
    [0004]
    An aircraft according to claim 1, wherein the support fitting is mounted directly to the upright of the inner member.
    [0005]
    An aircraft according to claim 1, wherein the mounted component is contiguous and directly attached to the support fitting.
    [0006]
    An aircraft according to claim 1, wherein the elastomer includes at least a portion of the inner member.
    [0007]
    An aircraft according to claim 6, wherein the elastomer substantially fills an entire longitudinal cross section of the cavity.
    [0008]
    An aircraft according to claim 1, wherein the flange has a first cross-sectional width greater than a second cross-sectional width of the opening for retaining the flange in the cavity.
    [0009]
    A vibration isolating assembly for an aircraft, the vibration isolation assembly comprising: a seat rail defining a cavity and an opening, an interior member having a post and a flange, wherein the flange is disposed in the cavity, and the post is configured to attach a mounted component; and an elastomer arranged inside the cavity between the flange and the arm rail.
    [0010]
    The vibration isolation assembly of claim 9, wherein the post is at least partially arranged in the opening.
    [0011]
    The vibration isolation assembly of claim 9, wherein the chair rail has a substantially C-shaped cross section.
    [0012]
    The vibration isolation assembly of claim 9, further comprising a support fitting mounted directly on the inner member.
    [0013]
    The vibration isolation assembly of claim 12, further comprising the mounted component connected directly to and contiguous with the support fitting.
    [0014]
    The vibration isolation assembly of claim 9, wherein the elastomer includes at least a portion of the inner member.
    [0015]
    The vibration isolation assembly of claim 14, wherein the elastomer substantially fills an entire longitudinal cross section of the cavity.
    [0016]
    The vibration isolation assembly of claim 9, wherein the flange has a first cross-sectional width greater than a second cross-sectional width of the opening for retaining the flange in the cavity.
    [0017]
    The vibration isolation assembly of claim 9, wherein the chair rail is configured to be attached to a fuselage of the aircraft.
    [0018]
    18. A method of assembling a vibration isolation assembly in an aircraft, the method comprising: providing a chair rail defining a cavity and having an opening, inserting a flange of a an inner member and an elastomer in the cavity with an amount of the inner member extending at least partially through the opening; attaching a support fitting to the upright of the inner member; and attaching a floor mounted component to the support fitting.
    [0019]
    The method of claim 18, wherein attaching the floor-mounted component to the support fitting includes attaching the floor-mounted component directly to the support fitting such that the floor-mounted component is contiguous to the support fitting. .
    [0020]
    The method of claim 18, wherein the insertion of the flange and the elastomer comprises filling substantially a whole longitudinal cross section of the cavity with the flange and the elastomer.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN105438436B|2021-02-26|
    CN105438436A|2016-03-30|
    FR3026089B1|2019-05-03|
    US20160083098A1|2016-03-24|
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    法律状态:
    2016-09-26| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-25| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-23| PLSC| Search report ready|Effective date: 20180223 |
    2018-09-25| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-25| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-27| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/495,667|US20160083098A1|2014-09-24|2014-09-24|Aircraft and seat track assemblies for vibration isolation of floor mounted components|
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