Wire passing groove and wing conformal structure

Abstract

The utility model belongs to the technical field of structural design of aircrafts, and particularly relates to a structure with conformal wiring ducts and wings. Comprising a wing left wall plate, a wing right wall plate, countersunk bolts / nuts, a wing joint, a front cabin, a rear cabin, a cable and twisted screws / nuts, the wing left wall plate and the wing right wall plate are symmetrical pieces and are screwed into an integral piece through a plurality of groups of countersunk bolts / nuts, sinking grooves are formed in the inner surfaces of the wing left wall plate and the wing right wall plate, and wing joint matching areas and connecting holes are formed in the root chord positions; the front cabin and the rear cabin are connected in a sleeved mode and are fixedly connected through a plurality of sets of bolts and supporting plate nuts. According to the utility model, the wiring channel is arranged in the wing, so that the conformal design of the wiring groove and the wing is realized. Laying channels of lines and pipelines only need to be formed in the wings; compared with a traditional common ventral fin, a side fin and a dorsal fin, the design without an independent wire passing groove is achieved, the whole-missile aerodynamic resistance is effectively reduced, and the problems of connection and watertightness of the wire passing groove and a cabin body are effectively solved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aircraft structure design technology, especially relates to a structure of wire trough conforming to wing. BACKGROUND

[0002] In unmanned aerial vehicle, rocket, spaceship and other unmanned aerial vehicles, the wire trough is a relatively common structure, and the cables and pipelines are often connected with each other between each cabin section. Some accessories do not allow the cables to pass through the interior, or the cables passing through the interior have the disadvantages of high cost, high risk coefficient, poor maintainability, etc. For example, the engine, warhead, fuel tank and the like. Therefore, it is necessary to set up external wire trough structures such as belly fin, side fin and back fin on the outside of the unmanned aerial vehicle body. However, the existence of the external wire trough will bring difficulties in waterproof sealing and fixed connection of the unmanned aerial vehicle, and also increase the aerodynamic resistance of the unmanned aerial vehicle.

[0003] At present, data signals are mainly transmitted between each cabin section of the unmanned aerial vehicle through a wired mode, or oil, gas and other media are transmitted through pipelines, so the external wire trough is indispensable. If the wire trough can be cancelled, the wind area of the unmanned aerial vehicle will be reduced, the aesthetic degree of the unmanned aerial vehicle will be increased, and the manufacturing and maintenance cost will be reduced. For special equipment, the effect of cancelling the wire trough is more remarkable. UTILITY MODEL CONTENT

[0004] The utility model aims at designing a wire trough structure conforming to the wing for unmanned aerial vehicles, which aims to cancel the separate wire trough, utilize the space inside the wing to form a cable and pipeline routing channel, realize the arrangement of the cables and pipelines under the premise of not increasing parts, reduce the aerodynamic resistance area, increase the aesthetic degree of the unmanned aerial vehicle, and reduce the manufacturing cost.

[0005] Technical scheme: a wire trough structure conforming to the wing, comprising a wing left wall plate, a wing right wall plate, a countersunk head bolt / nut, a wing joint, a front cabin, a rear cabin, a cable and a cross screw / nut; the wing left wall plate and the wing right wall plate are symmetrical parts, are screwed into an integral part through a plurality of groups of countersunk head bolts / nuts, and the inner surfaces of the wing left wall plate and the wing right wall plate are provided with a sink groove and a wing joint matching area and a connecting hole at a root chord position; the front cabin and the rear cabin are connected in a sleeved mode and are fixedly connected by a plurality of groups of bolts and a supporting plate nut.

[0006] Further, the front cabin only allows the cables to pass through the interior in the region near the front end face, and the remaining regions are integral closed pressure cavities which prohibit the cables from passing through the interior.

[0007] Further, the outer surface of the front cabin is provided with four groups of joints arranged in the shape of "X", and each group of joints can realize the installation of one wing.

[0008] Furthermore, the front cabin of each joint is designed with circular wiring holes at the symmetrical position of the plane, and the rear cabin also has wiring holes at the wing chord plane position.

[0009] Furthermore, before the left and right wing panels are screwed together as a whole, the cables are laid into the cable trays of the left or right wing panel, and a small amount of epoxy resin is used to pre-fix the cables in the trays to prevent the cables from slipping into the mating surface and being crushed when the left / right wing panels are connected into a whole using countersunk bolts / nuts.

[0010] Furthermore, after the wings are screwed together into an integral assembly, they are positioned by the mating area of ​​the wing panel and the lug slot at the front cabin connector, and locked in place by using screw-on bolts / nuts to achieve fixed installation with the front cabin. However, before installation, the exposed cable ends at the root chord of the wing are inserted into the cable holes in the front and rear cabins respectively.

[0011] Technical Effects: This invention achieves a conformal design between the cable tray and the wing by setting a cable routing channel in the wing. Only a channel for laying cables and pipes needs to be formed within the wing. Compared to the commonly used ventral, side, and dorsal fins, this invention achieves a design without a separate cable tray, effectively reducing overall aerodynamic drag and solving the problems of cable tray connection and watertightness with the fuselage. Attached Figure Description

[0012] Fig. 1 This is a global view of the conformal structure of the wire groove and the wing in this invention;

[0013] Fig. 2 This is an exploded view of the conformal structure of the wire groove and the wing in this invention;

[0014] Fig. 3 This is a schematic diagram of the front compartment of the conformal structure between the cable groove and the wing in this invention;

[0015] Fig. 4 This is a schematic diagram of the conformal cable channel between the cable tray and the wing in this invention;

[0016] Fig. 5 This is a schematic diagram of the bolts / nuts that are tightened together with the conformal structure of the wire groove and the wing in this invention;

[0017] In the diagram, 1-wing panel assembly, 2-forward cabin, 3-rear cabin, 4-cable, 5 / 6-tightening bolt / nut, 7-screw, 11-right panel, 114-countersunk, 12-left panel, 121-wing joint mating area, 122-connection hole, 123-countersunk hole, 13 / 14-countersunk bolt / nut, 21-inner sleeve area, 211-inner sleeve connection hole, 212-plate nut, 22-wing joint, 221-ear slot, 222-countersunk recess, 23-threading hole, 31-outer sleeve mating surface, 311-countersunk hole, 32-threading hole. DETAILED DESCRIPTION

[0018] In order to more clearly illustrate the technical scheme of the embodiments of the present application, the present application will be described in detail below in combination with the drawings or specific implementation cases. It should be noted that some (but not all) of the disclosed examples are shown in the drawings. In fact, many different examples can be described and these examples should not be understood as being limited to the examples set forth herein. On the contrary, these examples are described so that the positive effects of the present application are more embodied, and the details not described herein are regarded as known or conventional technical means in the art.

[0019] Referring to the drawings Figs. 1-4 In the specific implementation process of the present application, a wire slot and wing conformal structure are provided, which comprises a wing assembly 1, a front cabin 2, a rear cabin 3, a cable 4, a screw bolt / nut 5 / 6, and a screw 7. The wing assembly 1 is integrally connected by a plurality of groups of countersunk bolts / nuts 13 / 14 through left / right wall plates 12 / 11, and is installed on the front cabin 2 through a wing joint 22. The rear cabin 3 is connected with the front cabin 2 in a sleeved manner, and is fixed through the screw 7 and a supporting plate nut 212.

[0020] In some implementation cases, the left wing wall plate 12 and the right wing wall plate 11 are symmetrically provided with a sink groove 114 inside, which can be used to lay a plurality of cables (or pipelines) 4, forming a good wire channel instead of the wire slot designed for the wire of the ventral fin, lateral fin and dorsal fin;

[0021] In some implementation cases, a plurality of groups of countersunk holes 123 (only two groups are shown in the figure) are symmetrically provided in the entire chord plane area of the left wing wall plate 12 and the right wing wall plate 11. The countersunk bolts / nuts 13 / 14 are respectively screwed through the countersunk holes 123 from both sides, so as to realize the butt joint assembly of the left wing wall plate 12 and the right wing wall plate 11 into an integral piece 1. The left wing wall plate 12 and the right wing wall plate 11 are both designed with two wing joint matching areas 121 at the wing root position. Each matching area is designed with two groups of through holes 122. When the wing joint matching area 121 is matched with the lug insertion slot 221, the wing assembly 1 and the front cabin 2 can be positioned. When the screw bolt / nut 5 / 6 is screwed through the countersunk hole 222 and the through hole 122, the wing assembly 1 and the front cabin 2 can be fixedly connected.

[0022] In some implementation cases, the front cabin 2 is a closed cavity, and only the front and rear sections are open areas for sleeved connection. A plurality of wing joints 22 are arranged in an "X" shape on the outside of the front cabin 2 (only one joint is drawn in this patent for convenience of description). Each joint 22 is provided with front and rear lug insertion slots 221. Each lug insertion slot is designed with two countersunk holes 222.

[0023] In some embodiments, the front end of the front cabin 2 coincides with the chord plane of the wing, and four groups of through holes 23 are arranged in the form of "X" for leading the cable 4 from the wing root to the inside of the cabin, and a silicone rubber ring is added between the cable 4 and the through hole 23 to achieve waterproof sealing;

[0024] In some embodiments, the rear end of the front cabin 2 is designed as an inner sleeve joint area 21, and a plurality of through holes 211 are uniformly distributed along the circumference of the sleeve joint area, and a group of supporting plate nuts 212 are riveted on the inner side of each through hole 211;

[0025] In some embodiments, the rear cabin 3 coincides with the chord plane of the wing, and four through holes 32 are arranged in the form of "X" for leading the cable 4 from the wing root to the inside of the cabin, and a silicone rubber ring is added between the cable 4 and the through hole 32 to achieve waterproof sealing;

[0026] In some embodiments, the front end of the rear cabin 3 is designed as an outer sleeve joint area 31, and a plurality of groups of countersunk holes 311 are designed along the circumferential position of the outer sleeve joint area 31, and the screw 7 passes through the countersunk hole 311 and the through hole 211, and is screwed with the supporting plate nut 212, so as to realize the fixed connection of the front cabin 2 and the rear cabin 3.

[0027] The above specific embodiments or cases are only used to explain the technical solutions of the present application, and are not limited to the present application, and the parts not described in detail are regarded as conventional technical means or common knowledge in the art; It can be understood by those skilled in the art that: based on the design idea of the present application, the technical solutions recorded in the foregoing embodiments can be modified adaptively, or some or all of the technical features can be replaced equivalently, and these modified, equivalent, adaptive improved technical solutions do not deviate from the technical essence of the present application, and should be covered within the protection scope of the present application.

Claims

1. A wireway and wing conformal structure, characterized by, The left wing wall plate, the right wing wall plate, the countersunk bolt / nut, the wing joint, the front cabin, the rear cabin, the cable, the counter-screwed bolt / nut; the left wing wall plate and the right wing wall plate are symmetrical parts, which are connected into an integral part by a plurality of groups of countersunk bolts / nuts, the inner surfaces of the left wing wall plate and the right wing wall plate are provided with countersunk grooves, and the root chord position is provided with a wing joint matching area and a connecting hole; the front cabin and the rear cabin are connected by sleeving, and are fixedly connected by a plurality of groups of bolts and plate nuts.

2. A wire slot and wing conformal structure as claimed in claim 1, wherein, The front cabin only allows the cable to pass through the inside near the front end face area, and the remaining area is a whole closed pressure cavity, and the cable is prohibited from passing through the inside.

3. A wire slot and wing conformal structure as claimed in claim 1, wherein, The outer surface of the front cabin is provided with four groups of joints in "X" layout, and each group of joints can realize the installation of a group of wings.

4. A wire slot and wing conformal structure as claimed in claim 3, wherein, The front cabin body at the position of the symmetrical surface of each group of joints is designed with a circular threading hole, and the rear cabin is also provided with a threading hole at the wing chord plane position.

5. A wire slot and wing conformal structure as claimed in claim 4, wherein, Before the left and right wing wall plates are counter-screwed into an integral part, the cable is laid in the wire laying countersunk groove of the left wall plate or the right wall plate, and a small amount of epoxy resin is used to pre-fix the cable in the groove, so as to prevent the cable from being pressed and damaged when the left / right wall plate is connected into an integral part by using countersunk bolts / nuts.

6. A wire slot and wing conformal structure as claimed in claim 5, wherein, After the wing is connected into an integral assembly, the wing wall plate matching area is positioned in the ear slot of the front cabin joint, and is locked and fixed by using counter-screwed bolts / nuts, so as to realize the fixed installation with the front cabin, but the cable end exposed at the wing root chord position is inserted into the threading hole of the front cabin and the rear cabin respectively before installation.

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