Patent Application
20180356007
The present disclosure relates in general to securing cabling and/or wiring to a support structure, which may be used within an aircraft.
Ring posts are used to secure cables or wire bundles to a support structure in a vehicle. However, such ring posts often increase weight to the vehicle in a substantial manner, as they include metallic studs to ensure proper connection of ring posts. In some vehicles, such as airplanes, hundreds, or thousands of ring posts can be used, substantially increasing the weight of the vehicle, which can add to fuel costs and the like.
Further, such conventional ring posts require labor intensive installation techniques, as the ring posts need to be installed and connected using tools. This increases manufacturing time and can limit the flexibility for design change and cable rewiring and the like because the ring posts are affixed to each other using tools.
In one embodiment, an assembly is provided that includes a first device. The first device includes a main body and a ring disposed around the main body. The main body is provided with at least one protuberance and at least one recess. The first device is adapted to fit to an adjacent second device by virtue of engagement of the at least one protuberance or the at least one recess to the adjacent second device.
In another embodiment, an apparatus for securing at least one cable to a structure is provided. The apparatus includes a main body having a first end and a second end spaced from one another, the first end defining an orifice and the second end defining a plurality of recesses in a predetermined pattern. The apparatus further includes a plurality of protuberances extending from the first end, around the orifice. The apparatus includes a ring disposed about the main body, a plurality of ribs radially spaced along an outer surface of the main body for coupling the ring and the main body to each other, a plurality of legs extending from the second end, and a detent disposed on each of the legs opposite the main body. The legs and detents are complementary to the configuration of the orifice defined by the first end of the main body.
In another embodiment, a method for securing cabling in an airplane is provided. The method includes connecting a plurality of ring posts, each ring post comprising a main body, a ring disposed around the main body, an orifice provided at one end of the main body, and at least one detent extending from the main body at an end opposite from the orifice, to each other. The connecting of the plurality of ring posts includes placing protuberances of one of the plurality of the ring posts on recesses of an other of the plurality of ring posts, and placing detents of the one of the plurality of ring posts into the orifice of the other of the plurality of the ring posts, so as to provide for a removable snap-fit assembly of ring posts. The method further includes affixing the ring posts to a support structure of the airplane, and placing cabling through the plurality of ring posts.
The following detailed description of certain embodiments will be better understood when read in conjunction with the appended drawings. It should be understood that the various embodiments are not limited to the arrangements and instrumentality shown in the drawings.
As used herein, the term “cable” or “cabling” refers to any rope-like structure of a sufficient diameter and length so as to be laid across, alongside, or suspended above a surface. While cabling comprised of a wire and electronic conducting material are within the scope of cabling as used herein, the term cabling is also intended to refer simply to any structure having the appearance of a cable, including a rope without any electrical conduction characteristics.
As used herein, the term orifice refers to any opening of a structure through which something may enter. The term orifice may include an opening that has two open ends, or one open end and one closed end. The orifice can be any applicable shape, e.g., circular, oval, square, rectangle or the like.
As used herein, the term detent refers to a device for positioning and holding one mechanical part in relation to another in a manner such that the device can be released by force applied to one of the parts.
Various embodiments provide apparatuses and methods for securing cables and/or wires to a support structure. One or more embodiments allow for an assembly that includes multiple ring posts that can be snap-fit or otherwise attached to each other. The ring posts can be stacked to an unlimited height (if laid vertically) or length (if laid horizontally or otherwise nonvertically) and can reduce the number of parts needed, as well as eliminate the need for a metallic stud to attach ring posts together.
With reference to
The ring 120 may have a ring-like circular structure and be provided of a diameter sufficient to be able to fully house the main body 110 without direct contact. In some embodiments, the main body 110 may have any suitable diameter, may be about ½ inch or more in diameter, or one inch or more, or between one and six inches. The ring 120 may have any suitable diameter, and may have a diameter large enough to fully surround the main body 110. The ring 120 may be secured to the main body 110 by means of one or more ribs 130. The ribs 130 may be staggered and/or spaced around the outer circumference of the main body 110. In some embodiments, a plurality of ribs 130 are evenly spaced, for example circumferentially spaced and radially extended around the outer circumference of the main body 110, connecting from an inner surface of the ring 120 to an outer surface of the main body 110. While the number of ribs is not particularly limited, in some embodiments four, or five, or six ribs may be used. Additionally, in one embodiment, the main body 110, ring 120 and ribs 130 may be integrally formed as a single unitary piece. In other embodiments, one or more of these elements may be separately formed and coupled to the other elements.
A longitudinal thickness at the main body 110 may be described as a first longitudinal thickness, and a longitudinal thickness at the ring 120 is a second longitudinal thickness. In some embodiments, the first longitudinal thickness being greater than the second longitudinal thickness. The ribs 130 may have a structure whereby their top surface 130A bends upward in a radial direction toward an inside of the ring post 100. That is, the portion of the ribs 130 closest to or contacting the main body 110 is disposed at a higher orientation than the portion of the ribs 130 closest to or contacting the ring 120.
In embodiments where the main body 110 is substantially cylindrical in nature, the main body 110 can include an orifice 111 (which may be referred to as a first orifice) at one end, which may be a first end. That is, one end 110A of the main body 110 may be an open end in view of the presence of the orifice 111. The orifice 111 may extend any distance into the main body 110, so long as the space created by the orifice 111 is sufficient to house legs and detents of an adjacent ring post 100 (e.g., receive therein complementary legs and detents of an adjacent ring post) as described in more detail herein. That is, the space 110 may establish the complementary configuration to the legs and detent described in further detail below. While the orifice 111 may extend an entire length of the main body 110, the orifice 111 need not extend the entire length of the main body 110. With reference to
In embodiments, the main body 110 includes at least one protuberance 114 and/or at least one recess 112, which may be integrally formed. The recesses 112 and/or protuberances 114 may be formed along a rim of the end 110A or 110B of the ring post. With reference to
With reference to
The location of the recesses are not particularly limited to the locations illustrated. Recesses may also be present, for example, along the outer circumference of the one end 110A of the main body 110. It is contemplated that in some embodiments, either or both ends 110A and 100B of the main body include both the protuberances 114 and the recesses 112, which may be arranged in different ordering as desired or needed. Thus, The number and spacing of the recesses 112 and protuberances 114 is not particularly limited. The depth of the recesses 112 are not particularly limited, provided that the recesses 112 have a depth sufficient to receive a protuberance 114 from an adjacent ring post therein so as to allow for a secure arrangement in a stacked configuration of ring posts as illustrated in
On the other end 110B opposite the orifice 111, at least one leg 140A and at least one detent 140 are provided. The at least one leg 140A and at least one detent 140 are provided so as to extend from the other end 110B, in a direction away from the center of the main body 110. The at least one detent 140 is adapted to snap-fit into an orifice 111 of an adjacent ring post 100. The leg 140A is provided between the main body 110 and the detent 140.
The number of legs 140A and detents 140 is not particularly limited. However, in some embodiments, the legs 140A and detents 140 are evenly radially spaced around the circumference of the bottom surface of the other end 110B of the main body 110. In some embodiments, four, or five, or six legs 140A and detents 140 are used. The lengths and widths of the legs 140A and detents 140 are not particularly limited, provided that the combined structure 140/140A is able to snap fit into the orifice 111 of an adjacent ring post 100. The orifice 111 of the adjacent ring post for receiving the detents 140 and legs 140A may have a spacing or complementary indentation therein that allows the detents 140 and legs 140A to removably snap fit into the orifice without causing deformation or destruction of any surface of either ring post 100.
The ring post 100 may be made of a thermal plastic material, or of any other material capable of achieving the required strength while achieving a snap-fit flexibility. All portions of the ring posts 100 may be made of the same material, or materials can be selectively chosen for particular portions of the ring post 100 (e.g., legs and detents 140A/140, ring 120, main body 110) to achieve desired properties.
With reference to
With reference to
In some embodiments, the recesses 112 of a ring post 100 correspond with the protuberances 114 of a second assembly, or an adjacent ring post 150. That is, when two ring posts are provided in a stacked configuration, such as those shown in
The configuration whereby the a plurality of protuberances 114 and recesses 112 of adjacent ring posts 100 mesh allows for the ring posts to be moved and turned with respect to each other, so as to improve maneuverability. Further, the snap-fit relationship of the legs 140A and detents 140 of one ring post 100 and the orifice 111 of the adjacent ring post 100 may improve the stackability of the ring posts and avoid the use of machining or tooling that would otherwise be necessary to manufacture and place a ring post assembly within a structure.
In some embodiments, the ring posts 100 may be fitted with a locking mechanism. The locking mechanism may be a part of the ring posts 100, or a separate device provided so as to ensure that the assembly of ring posts 100 is secured. Once secured, the ring posts 100 may have zero tolerance for twisting.
In some embodiments, the plurality of ring posts 100 may be arranged in an area of the airplane, such as an area that holds a substantial amount of wiring or cabling 200. The arrangement of the ring posts 100 may lead to a reduction in parts and also a weight reduction since the ring posts 100 can be stacked to an unlimited height or length, and double or triple ring posts will no longer be necessary, while still achieving the flexibility necessary to house the cabling 200.
In some embodiments, the number of protuberances 114 and recesses 112 can be chosen so as to ensure ease of engagement between adjacent ring posts, while also defining different relative angular orientations. Thus, while one protuberance 114 and one recess 112 may be sufficient, a plurality of protuberances 114 and recesses 112 may improve and simplify alignment techniques and for securing ring posts 100 stacked together.
As described in
Examples of the disclosure may be described in the context of an aircraft manufacturing and service method 900 as shown in
Each of the processes of the illustrative method 900 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on.
As shown
The disclosure and drawing figure(s) describing the operations of the method(s) set forth herein should not be interpreted as necessarily determining a sequence in which the operations are to be performed. Rather, although one illustrative order is indicated, it is to be understood that the sequence of the operations may be modified when appropriate. Accordingly, certain operations may be performed in a different order or simultaneously. Additionally, in some aspects of the disclosure, not all operations described herein need be performed.
Apparatus and methods shown or described herein may be employed during any one or more of the stages of the manufacturing and service method 900. For example, components or subassemblies corresponding to component and subassembly manufacturing 906 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 1000 is in service. Also, one or more aspects of the apparatus, method, or combination thereof may be utilized during the production states 906 and 908, for example, by substantially expediting assembly of or reducing the cost of an aircraft 1000. Similarly, one or more aspects of the apparatus or method realizations, or a combination thereof, may be utilized, for example and without limitation, while the aircraft 1000 is in service, e.g., maintenance and service 914.
Thus, various embodiments provide a scalable and stackable ring post arrangement that is easier to install and maintain, while also being lighter weight.
Different examples and aspects of the apparatus and methods are disclosed herein that include a variety of components, features, and functionality. It should be understood that the various examples and aspects of the apparatus and methods disclosed herein may include any of the components, features, and functionality of any of the other examples and aspects of the apparatus and methods disclosed herein in any combination, and all of such possibilities are intended to be within the spirit and scope of the present disclosure.
As used herein, an element or step recited in the singular and proceeded with the word “a” or “an” should be understood as not excluding plural of said elements or steps, unless such exclusion is explicitly stated. Furthermore, references to “one embodiment” are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features. Moreover, unless explicitly stated to the contrary, embodiments “comprising” or “having” an element or a plurality of elements having a particular property may include additional such elements not having that property.
It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described embodiments (and/or aspects thereof) may be used in combination with each other. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the various embodiments without departing from their scope. While the dimensions and types of materials described herein are intended to define the parameters of the various embodiments, the embodiments are by no means limiting and are exemplary embodiments. Many other embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the various embodiments should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims, the terms “including” and “in which” are used as the plain-English equivalents of the respective terms “comprising” and “wherein.” Moreover, in the following claims, the terms “first,” “second,” and “third,” etc. are used merely as labels, and are not intended to impose numerical requirements on their objects. Further, the limitations of the following claims are not written in means-plus-function format and are not intended to be interpreted based on 35 U.S.C. § 112, paragraph (f), unless and until such claim limitations expressly use the phrase “means for” followed by a statement of function void of further structure.
This written description uses examples to disclose the various embodiments, including the best mode, and also to enable any person skilled in the art to practice the various embodiments, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various embodiments is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements with insubstantial differences from the literal languages of the claims.
