Aircraft cable clamp

Abstract

The present application relates to the technical field of aircraft cable fixation. Disclosed is an aircraft cable clamp. The aircraft cable clamp of the present application comprises a clamp body (1) and a clamp base (2) connected to each other. The clamp body (1) comprises a first body section (11), a second body section (12), and an axial through hole (10) defined by the first body section (11) and the second body section (12) for a cable to pass through. The clamp base (2) is connected to and protrudes above an aircraft fuselage, so as to space the cable passing through the axial through hole (10) apart from the aircraft fuselage. The cable clamp of the present application improves cable installation efficiency and prevents cable loosening and wear, thereby ensuring civil aviation airworthiness requirements.

Description

Aircraft cable clamps Technical Field

[0001] This application relates to the field of aircraft cable fixing technology, and in particular to an aircraft cable clamp. Background Technology

[0002] Aircraft contain many electrical components that require power to operate. Many cables need to be fixed to the aircraft fuselage, which requires an insulating, flame-retardant, and reliable method to fix the cables and prevent them from loosening and abrasion, thereby meeting civil aviation airworthiness requirements. Summary of the Invention

[0003] The purpose of this application is to provide an aircraft cable clamp that improves cable installation efficiency, prevents cable loosening and wear, and ensures civil aviation airworthiness requirements.

[0004] To solve the above-mentioned technical problems, this application provides an aircraft cable clamp, including: a clamp body and a clamp base connected to each other. The clamp body includes a first body part, a second body part, and an axial through hole formed by the first body part and the second body part for the cable to pass through. The clamp base is connected to and protrudes above the aircraft fuselage to arrange the cable passing through the axial through hole at intervals from the aircraft fuselage.

[0005] Optionally, an insulating liner is provided on the inner side of the clamp body.

[0006] Optionally, one end of the first body part and the second body part are rotatably connected, and the other end can move away from or connect with the body as it rotates, thereby opening or closing the axial through hole.

[0007] Optionally, the insulating liner is detachably disposed on the inside of the clamp body.

[0008] Optionally, both the first body portion and the second body portion include a semi-circular ring portion and a fixing portion, with each semi-circular ring portion forming an axial through hole, and the fixing portion being used to connect with the clamp base.

[0009] Optionally, each of the fixing parts and the clamp base is connected by a connecting bolt.

[0010] Optionally, each of the fixing parts includes upper bolt holes and lower bolt holes that correspond to each other, and the connecting bolt passes through the upper bolt holes and lower bolt holes and is threadedly connected to the clamp base.

[0011] Optionally, the clamp body is made of PEek material.

[0012] Optionally, the insulating liner is made of silicone material.

[0013] The cable clamps in this application improve cable installation efficiency, prevent cable loosening and wear, and ensure civil aviation airworthiness requirements. Attached Figure Description

[0014] Figure 1 shows a schematic diagram of the structure of the aircraft cable clamp according to an embodiment of this application;

[0015] Figure 2 shows a schematic diagram of the structure of the clamp body according to an embodiment of this application;

[0016] Figure 3 shows a schematic diagram of the structure of the clamp body without an insulating liner in an embodiment of this application;

[0017] Figure 4 shows a schematic diagram of the structure of the clamp body when it is rotated open according to an embodiment of this application;

[0018] Figure 5 shows a schematic diagram of the structure of the insulating liner in an embodiment of this application. Detailed Implementation

[0019] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. This application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and application systems without departing from the spirit of this application. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0020] The embodiments of this application will now be described in detail with reference to the accompanying drawings, so that those skilled in the art can easily implement the application. This application may be embodied in many different forms and is not limited to the embodiments described herein.

[0021] To clearly illustrate this application, devices unrelated to the description are omitted, and the same or similar constituent elements throughout the specification are given the same reference numerals.

[0022] Throughout this specification, when it is said that a device is "connected" to another device, this includes not only "direct connection" but also "indirect connection" by placing other components in between. Furthermore, when it is said that a device "comprises" a certain constituent element, unless otherwise stated otherwise, this does not exclude other constituent elements, but rather implies that other constituent elements may be included.

[0023] When we say that a device is "above" another device, this can mean that it is directly above the other device, or it can mean that other devices are present in between. Conversely, when we say that a device is "directly" "above" another device, there are no other devices present in between.

[0024] Although the terms first, second, etc., are used in some instances herein to describe various elements, these elements should not be limited by these terms. These terms are used only to distinguish one element from another. For example, descriptions such as first interface and second interface, etc. Furthermore, as used herein, the singular forms “a,” “an,” and “the” are intended to also include the plural forms unless the context indicates otherwise. It should be further understood that the terms “comprising,” “including,” indicate the presence of the stated feature, step, operation, element, component, item, kind, and / or group, but do not exclude the presence, occurrence, or addition of one or more other features, steps, operations, elements, components, items, kinds, and / or groups. The terms “or” and “and / or” as used herein are interpreted as inclusive, or mean any one or any combination thereof. Thus, “A, B, or C” or “A, B, and / or C” means “any one of: A; B; C; A and B; A and C; B and C; A, B, and C.” Exceptions to this definition occur only when combinations of elements, functions, steps, or operations are inherently mutually exclusive in some way.

[0025] The technical terms used herein are for reference only to specific embodiments and are not intended to limit the scope of this application. The singular form used herein includes the plural form unless the statement explicitly indicates otherwise. The word "comprising" as used in the specification means to specify a particular characteristic, region, integer, step, operation, element, and / or component, and does not exclude the presence or addition of other characteristics, regions, integers, steps, operations, elements, and / or components.

[0026] Terms such as "below" and "above" indicating relative space are used to more easily explain the relationship of one device relative to another in the accompanying drawings. These terms refer not only to their meaning as shown in the drawings but also to other meanings or operations of the device in use. For example, if the device in the drawings is flipped, a device previously described as "below" another device may now be described as "above" another device. Therefore, the exemplary term "below" encompasses both above and below. The device may be rotated 90° or other angles, and the terms representing relative space are interpreted accordingly.

[0027] Although not explicitly defined, all terms, including technical and scientific terms used herein, shall have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains. Terms defined in commonly used dictionaries shall be further interpreted as having a meaning consistent with the relevant technical literature and the content of this present application, and shall not be over-interpreted as having an ideal or overly formulaic meaning unless otherwise defined.

[0028] The term "aircraft" is defined as an air transport system of any size having at least one lift propeller as its propulsion source. The term "aircraft" can include both "manned" and "unmanned" air transport systems. A manned aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the aircraft. A manned aircraft can also mean an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the aircraft. An unmanned aircraft can mean an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0029] In this specification, "aircraft" includes manned aircraft and any unmanned vehicle, such as unmanned aerial vehicles (UAVs), unmanned aircraft, remote-controlled aircraft, unmanned aircraft systems, any aircraft covered under cycle 328AN / 190 of the International Civil Aviation Organization (ICAO) classification, etc. As an example, a drone can take the form of a single- or multi-rotor helicopter (such as a quadcopter) or a fixed-wing aircraft. Furthermore, certain portions of this disclosure can be used in conjunction with drones in the form of other types of unmanned vehicles (e.g., wheeled, tracked, and / or watercraft).

[0030] The embodiments of this application are described below with reference to the accompanying drawings. As shown in Figures 1 and 2, the aircraft cable clamp of this application includes: a clamp body 1 and a clamp base 2 connected to each other. The clamp body 1 includes a first body part 11, a second body part 12, and an axial through hole 10 formed by the first body part 11 and the second body part 12 for the cable to pass through. The clamp base 2 is connected to and extends above the aircraft fuselage to arrange the cable passing through the axial through hole 10 at intervals from the aircraft fuselage.

[0031] Specifically, one end of the first body part 11 and the second body part 12 are rotatably connected, and the other end can move away from or connect with the body as it rotates, thereby opening or closing the axial through hole 10. In one embodiment, the first body part 11 and the second body part 12 are connected by a movable shaft.

[0032] Both the first body part 11 and the second body part 12 include a semi-circular ring portion and a fixing portion. The semi-circular ring portions together form an axial through hole 10, and the fixing portion is used to connect with the clamp base 2. As shown in Figures 3 and 4, the first body part 11 includes a first semi-circular ring portion 111 and a first fixing portion 112, and the second body part 12 includes a second semi-circular ring portion 121 and a second fixing portion 122. The first fixing portion 112 is provided with an upper bolt hole 110, and the second fixing portion 122 is provided with a lower bolt hole 120. When the first body part 11 and the second body part 12 together form the axial through hole 10, the upper bolt hole 110 and the lower bolt hole 120 correspond to each other. The clamp base 2 is provided with a threaded hole, and a connecting bolt 4 passes through the upper bolt hole 110 and the lower bolt hole 120, and is fixedly connected through the threaded hole on the clamp base 2.

[0033] The clamp base 2 has a certain height and is connected to the aircraft fuselage. This allows the cable to be kept at a certain distance from the aircraft fuselage, preventing wear and tear on the cable and direct contact with high-temperature components that could lead to cable aging and damage. This extends the service life of the cable and internal components, and facilitates disassembly and maintenance. In one embodiment, the connecting bolt 4 does not penetrate the clamp base 2; instead, the clamp base 2 is bonded to the aircraft fuselage. Eliminating the need for bolts reduces damage to the fuselage, avoids reducing its strength, and minimizes weight by eliminating the need for fastening bolts.

[0034] Furthermore, an insulating liner 3 is arranged on the inner side of the clamp body 1. The insulating liner 3 is detachably arranged on the inner side of the clamp body 1. As shown in Figure 4, the insulating liner 3 includes a first part 31 and a second part 32, which together form an axial through hole 10 for the cable to pass through. The cable passes through the clamp body and the insulating liner can fix the cable bundle and insulate the cable from the machine body. At the same time, the raised base isolates the cable from the machine body, creating an overall isolation effect. The addition of the insulating liner also prevents the cable from shaking and increases the stability of the cable fixation. Preferably, the insulating liner 3 is made of silicone material, which can prevent wear on the cable, damage to the insulation layer on the cable surface, and serious problems such as short circuits, while also providing insulation.

[0035] Preferably, the clamp body 1 is made of PEEK material, which can withstand a high temperature of 800 degrees Celsius. The clamp base 2 is made of aluminum material, which can reduce weight.

[0036] In this embodiment, the clamp base is connected to the aircraft fuselage. Because it has a certain height, it can keep the cable a certain distance from the aircraft fuselage, avoiding wear between the cable and the fuselage, and avoiding direct contact between the cable and some high-temperature components, which would cause the cable to age and be damaged. This extends the service life of the cable and the vehicle's internal parts, and it is easy to disassemble and maintain, thus improving the efficiency of cable installation.

[0037] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. An aircraft cable clamp, characterized in that, include: The clamp body (1) and clamp base (2) are interconnected. The clamp body (1) includes a first body part (11), a second body part (12), and an axial through hole (10) formed by the first body part (11) and the second body part (12) for the cable to pass through. The clamp base (2) is connected to and extends above the fuselage of the aircraft to arrange the cable passing through the axial through hole (10) at intervals from the fuselage of the aircraft.

2. The aircraft cable clamp according to claim 1, characterized in that, An insulating liner (3) is arranged on the inner side of the clamp body (1).

3. The aircraft cable clamp according to claim 1, characterized in that, The first body part (11) and the second body part (12) are rotatably connected at one end, and the other end can move away from or connect with each other as they rotate, thereby opening or closing the axial through hole (10).

4. The aircraft cable clamp according to claim 2, characterized in that, The insulating liner (3) is detachably arranged inside the clamp body (1).

5. The aircraft cable clamp according to claim 1, characterized in that, The first body part (11) and the second body part (12) both include a semi-circular ring part and a fixing part. Each of the semi-circular ring parts forms an axial through hole (10). The fixing part is used to connect with the clamp base (2).

6. The aircraft cable clamp according to claim 5, characterized in that, Each of the fixing parts and the clamp base (2) is connected by a connecting bolt (4).

7. The aircraft cable clamp according to claim 6, characterized in that, Each of the fixing parts includes an upper bolt hole (110) and a lower bolt hole (120) that correspond to each other. The connecting bolt (4) passes through the upper bolt hole (110) and the lower bolt hole (120) and is threadedly connected to the clamp base (2).

8. The aircraft cable clamp according to claim 6, characterized in that, The clamp body (1) is made of PEEK material.

9. The aircraft cable clamp according to claim 2, characterized in that, The insulating liner (3) is made of silicone material.

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