A wing-body connection structure and connection method for a cargo drone

Abstract

The present invention discloses a wing-body connection structure and a connection method for a cargo drone, belonging to the field of drones. The wing-body connection structure of the cargo drone includes: a fuselage assembly located on the fuselage side, which includes a front fuselage frame, a rear fuselage frame, and a rear fixing seat; a wing assembly located on the wing side, which includes a front wing beam, a rear wing beam, wing tip ribs, a front plug wing joint, a rear pin, and a quick-release pin; and a loosening prevention assembly located on the rear fixing seat, which includes an outer limiting member, an inner pressing block, a lead screw, and a spring. The wing-body connection structure and the connection method for the cargo drone provided by the present invention can achieve the quick disassembly and assembly of the fuselage and the wing, and have the characteristics of high docking accuracy, convenient disassembly and assembly, and high structural reliability. It can make up for the problems of cumbersome disassembly and assembly, time-consuming and laborious of the existing wing-body assembly.

Description

Technical Field

[0001] The present application relates to the field of unmanned aerial vehicles, and particularly to a wing-body connection structure and connection method for a cargo unmanned aerial vehicle. Background Art

[0002] The unmanned aerial vehicle industry has developed rapidly in recent years and is applied in fields such as map surveying and mapping, cargo transportation, line inspection, road rescue, and border reconnaissance. Compared with small consumer-grade unmanned aerial vehicles, unmanned aerial vehicles applied in the field of cargo logistics usually have a larger wingspan and a take-off weight of more than one hundred kilograms, and require a special transport box for transfer. The wing and the fuselage are usually set separately to reduce the volume for packing. The existing connection form between the wing and the fuselage mostly adopts lug docking and is then fixed by bolts and nuts. During assembly, the wing needs to be lifted to continuously adjust the wing attitude to align with the fuselage lugs, and at the same time, personnel are required to align the lugs and insert the bolts. During installation, not only multiple adjustments are required to ensure that all connection holes are aligned, but also the operating space at the wing-body connection is limited, and disassembly and assembly are time-consuming and laborious.

[0003] Therefore, developing an unmanned aerial vehicle wing-body connection structure with simple assembly, reliable docking, and fewer required personnel is the key to solving the above problems. Summary of the Invention

[0004] Aiming at the problems existing in the prior art, the present invention provides a wing-body connection structure and connection method for a cargo unmanned aerial vehicle, which can realize the rapid disassembly and assembly of the fuselage and the wing, and has the characteristics of high docking accuracy, convenient disassembly and assembly, and high structural reliability. It can make up for the problems of cumbersome and time-consuming disassembly and assembly of the existing wing-body assembly.

[0005] According to the first aspect of the technical solution of the present invention, a wing-body connection structure for a cargo unmanned aerial vehicle is provided, including:

[0006] A fuselage assembly located on the fuselage side, including a front fuselage frame, a rear fuselage frame, and a rear fixing seat;

[0007] A wing assembly located on the wing side, including a front wing beam, a rear wing beam, wing tip ribs, a front plug wing joint, a rear pin, and a quick-release pin;

[0008] A loosening prevention assembly located on the rear fixing seat, including an outer limiting member, an inner pressing block, a lead screw, and a spring.

[0009] Further, a guiding groove and a first fixing pin hole are provided on the front fuselage frame.

[0010] Further, a front plug wing joint is fixed on the front wing beam, the width of the front plug wing joint is equal to the inner width of the guiding groove, and a second fixing pin hole is provided on the front plug wing joint, and the first fixing pin hole and the second fixing pin hole have the same diameter.

[0011] Further, when the front wing joint is inserted into the guiding groove of the front frame of the fuselage, the quick-release pin can simultaneously pass through the first fixing pin hole and the second fixing pin hole that are aligned with each other for fixing.

[0012] Further, the rear pin is fixed on the wing end rib.

[0013] Further, an insertion hole is provided on the rear fixing seat. When the front wing joint is inserted into the guiding groove of the front frame of the fuselage, the rear pin can be aligned with and inserted into the insertion hole on the rear fixing seat.

[0014] Further, the outer limiting member of the anti-loosening assembly is in a sheet-shaped hollow shape, and the lower part of the hollow is a circular lower edge.

[0015] Further, one side of the outer limiting member is fixedly attached to the rear fixing seat; a pair of lead screws are provided on the side of the outer limiting member facing the outside, and a spring is sleeved on the lead screws; limiting blocks are respectively provided near the lead screws between the pair of lead screws, and the limiting blocks are located below the circular edge of the hollow of the anti-loosening assembly.

[0016] Further, the inner pressing block is located on the side of the outer limiting member facing the outside, and includes a pressing portion and a locking portion. The locking portion is in a circular opening shape, with a circular upper edge at the upper part and an opening at the lower part, and flanges are symmetrically arranged inwardly at the opening.

[0017] Further, the inner pressing block can move up and down along the lead screw under the action of the spring.

[0018] Further, when the pressing portion of the inner pressing block is pressed, so that the inner pressing block moves downward along the lead screw until the lower edge of the locking portion abuts against the limiting block on the outer limiting member, the circular upper edge of the locking portion of the inner pressing block and the circular lower edge of the outer limiting member of the anti-loosening assembly form a standard circular through hole.

[0019] Here, the "standard circular through hole" means that the shape of this through hole is a standard circle with a certain diameter.

[0020] Further, the standard circular through hole has the same diameter as the insertion hole on the rear fixing seat.

[0021] Further, the rear pin includes a cylindrical insertion portion, and a step is protruded along the circumference at the rear of the cylindrical insertion portion, and a limiting groove is recessed inwardly at the rear side of the step.

[0022] Further, the cross-sectional diameter of the step is less than or equal to the diameters of the standard circular through hole and the insertion hole on the rear fixing seat, so that the rear pin can pass through the standard circular through hole and be inserted into the insertion hole on the rear fixing seat.

[0023] Furthermore, the distance between the symmetrically arranged flanges of the internal pressure clamping block is greater than or equal to the cross-sectional diameter of the limiting groove of the rear pin and less than or equal to the cross-sectional diameter of the step of the rear pin. When the rear pin passes through the standard circular through-hole and is inserted into the insertion hole on the rear fixing seat, the symmetrically arranged flanges of the internal pressure clamping block are clamped in the limiting groove of the rear pin, and due to the limitation of the step of the rear pin, the internal pressure clamping block locks the rear pin.

[0024] According to the second aspect of the technical solution of the present invention, a method for connecting the wing and fuselage of a cargo drone is provided, including:

[0025] Insert the front wing joint of the wing assembly into the guiding groove of the front fuselage frame;

[0026] Press the pressing part of the internal pressure clamping block, so that the internal pressure clamping block moves downward along the screw rod until the lower edge of the locking part abuts against the limiting block on the outer limiting part. At this time, the circular upper edge of the locking part of the internal pressure clamping block and the circular lower edge of the outer limiting part of the anti-loosening component form a standard circular through-hole;

[0027] Insert the rear pin through the standard circular through-hole and into the insertion hole on the rear fixing seat until the step on the rear pin passes through the internal pressure clamping block;

[0028] Release the internal pressure clamping block, so that it resets under the action of the spring, driving the flange to move upward and insert into the limiting groove of the rear pin, realizing the locking of the rear pin by the internal pressure clamping block;

[0029] Insert the quick-release pin through the first fixing pin hole and the second fixing pin hole that are aligned with each other on the front fuselage frame and the front wing beam at the same time to realize the docking and fixing of the wing and fuselage.

[0030] Furthermore, when wing-fuselage separation is required, remove the quick-release pin and press the internal pressure clamping block to drive the flange to move downward until the lower edge of the locking part abuts against the limiting block on the outer limiting part. At this time, the circular upper edge of the locking part of the internal pressure clamping block and the circular lower edge of the outer limiting part of the anti-loosening component form a standard circular through-hole, and pull out the rear pin to realize wing-fuselage separation.

[0031] Advantages of the present invention:

[0032] The present invention proposes a quick disassembly and assembly structure for the wing and fuselage of a cargo drone. This disassembly and assembly mechanism adopts a front and rear connection form. The front connection uses a front wing joint and is fastened by a quick-release pin; the rear connection method uses a rear pin and is fastened and loosened by an anti-loosening component. The front and rear connections realize the quick assembly and disassembly of the wing and fuselage, and have strong applicability;

[0033] The present invention has the characteristics of simple wing-fuselage docking operation, high installation accuracy, good structural stability, and can realize quick disassembly and assembly.

[0034] The structural form of the quick-disassembly and assembly structure connection component between the wing and the fuselage proposed by the present invention is simple, can be realized through simple mechanical processing, and has a low cost;

[0035] The quick-disassembly and assembly structure between the wing and the fuselage proposed by the present invention is easy to install. Without the aid of auxiliary tooling and tools, the accuracy of the installation position can be ensured, and it has strong adaptability to field operations.

[0036] The quick-disassembly and assembly structure between the wing and the fuselage proposed by the present invention can quickly complete the assembly and deployment work of the UAV, improve the transportation efficiency and reduce the operation cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0038] Figure 1 Shown is a schematic diagram of wing-body docking according to an embodiment of the present invention;

[0039] Figure 2 Shown is a docking diagram of the front insertion wing joint according to an embodiment of the present invention;

[0040] Figure 3 Shown is an exploded view of the rear insertion pin docking of the wing according to an embodiment of the present invention;

[0041] Figure 4 Shown are schematic diagrams of the locked state and the unlocked state of the anti-loosening component according to an embodiment of the present invention;

[0042] Figure 5 Shown is a schematic diagram of the rear insertion pin structure of the wing according to an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0043] Here, the exemplary embodiments will be described in detail, and the examples are shown in the drawings. When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. On the contrary, they are only examples of devices and methods consistent with some aspects of the present disclosure as detailed in the appended claims.

[0044] The terms "first", "second", etc. in the description and claims of the present disclosure are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances so that the embodiments of the present disclosure described herein can be implemented, for example, in an order other than those illustrated or described herein.

[0045] In addition, the terms "comprising", "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0046] "Plurality" includes two or more.

[0047] For "and / or" used in the present disclosure, it should be understood that it is merely an association relationship describing associated objects, indicating that three relationships can exist. For example, A and / or B can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone.

[0048] The present invention provides a wing-body connection structure and connection method for a cargo drone, which can achieve quick disassembly and assembly of the fuselage and the wing, and has the characteristics of high docking accuracy, convenient disassembly and assembly, and high structural reliability.

[0049] The wing-body connection structure of the cargo drone according to the technical solution of the present invention includes: a fuselage assembly located on the fuselage side, including a front fuselage frame, a rear fuselage frame, and a rear fixing seat; a wing assembly located on the wing side, including a front wing beam, a rear wing beam, wing tip ribs, a front wing insertion joint, a rear pin, and a quick-release pin; and a loosening prevention assembly located on the rear fixing seat, including an outer limiting member, an inner pressing block, a lead screw, and a spring.

[0050] A guiding groove and a first fixing pin hole are provided on the front fuselage frame. A front wing insertion joint is fixed on the front wing beam. The width of the front wing insertion joint is equal to the inner width of the guiding groove, and a second fixing pin hole is provided on the front wing insertion joint. The first fixing pin hole and the second fixing pin hole have the same diameter. When the front wing insertion joint is inserted into the guiding groove of the front fuselage frame, the quick-release pin can simultaneously pass through the aligned first fixing pin hole and the second fixing pin hole for fixation.

[0051] The rear pin is fixed on the wing tip rib. An insertion hole is provided on the rear fixing seat. When the front wing insertion joint is inserted into the guiding groove of the front fuselage frame, the rear pin can be aligned and inserted into the insertion hole on the rear fixing seat.

[0052] The outer limiting member of the anti-loosening component is in a sheet-shaped hollow shape, and the lower part of the hollow is a circular lower edge. The shape of the upper edge of the hollow is not limited and can be, for example, circular, rectangular or irregular.

[0053] One side of the outer limiting member is fixedly attached to the rear fixing seat; a pair of screw rods are arranged on the side facing the outside, and the spring is sleeved on the screw rods; limiting blocks are respectively arranged near the screw rods between the pair of screw rods, and the limiting blocks are located below the circular edge of the hollow of the anti-loosening component.

[0054] The inner pressing block is located on the side of the outer limiting member facing the outside and includes a pressing part and a locking part. The locking part is in a circular opening shape, with a circular upper edge at the upper part and an opening at the lower part, and flanges are symmetrically arranged inward at the opening. The inner pressing block can move up and down along the screw rod under the action of the spring.

[0055] When pressing the pressing part of the inner pressing block, the inner pressing block moves downward along the screw rod until the lower edge of the locking part abuts against the limiting block on the outer limiting member, and the spring is compressed and stores energy. At this time, the circular upper edge of the locking part of the inner pressing block and the circular lower edge of the outer limiting member of the anti-loosening component form a standard circular through-hole, and the diameter of the standard circular through-hole is the same as that of the insertion hole on the rear fixing seat.

[0056] The rear pin includes a cylindrical insertion part, and a step protrudes along the circumference at the rear of the cylindrical insertion part, and a limiting groove is recessed inward at the rear of the step. The cross-sectional diameter of the step is less than or equal to the diameters of the standard circular through-hole and the insertion hole on the rear fixing seat, so that the rear pin can smoothly pass through the standard circular through-hole and be inserted into the insertion hole on the rear fixing seat.

[0057] The distance between the symmetrically arranged flanges of the inner pressing block is greater than or equal to the cross-sectional diameter of the limiting groove of the rear pin and less than or equal to the cross-sectional diameter of the step of the rear pin. When the rear pin passes through the standard circular through-hole and is inserted into the insertion hole on the rear fixing seat, the symmetrically arranged flanges of the inner pressing block are clamped in the limiting groove of the rear pin, and due to the limitation of the step of the rear pin, the inner pressing block locks the rear pin.

[0058] According to the technical solution of the present invention, the method for connecting the wing and the fuselage of a cargo drone includes:

[0059] Insert the front insertion wing joint of the wing assembly into the guiding groove of the front frame of the fuselage;

[0060] Press the pressing part of the inner pressing block so that the inner pressing block moves downward along the screw rod until the lower edge of the locking part abuts against the limiting block on the outer limiting member, and the circular upper edge of the locking part of the inner pressing block and the circular lower edge of the outer limiting member of the anti-loosening component form a standard circular through-hole;

[0061] Insert the rear pin through the standard circular through-hole into the insertion hole on the rear fixing seat until the step on the rear pin passes through the inner pressure clamping block;

[0062] Release the inner pressure clamping block, so that it resets under the action of the spring, driving the flange to move upward and insert into the limiting groove of the rear pin, realizing the locking of the rear pin by the inner pressure clamping block;

[0063] Insert the quick-release pin through the first fixing pin hole and the second fixing pin hole aligned with each other on the front frame of the fuselage and the front beam of the wing at the same time to realize the docking and fixing of the wing and the fuselage.

[0064] When wing-fuselage separation is required, remove the quick-release pin and press the inner pressure clamping block to drive the flange to move downward until the lower edge of the locking part abuts against the limiting block on the outer limiting part, and the circular upper edge of the locking part of the inner pressure clamping block and the circular lower edge of the outer limiting part of the anti-loosening component form a standard circular through-hole, then pull out the rear pin to realize wing-fuselage separation.

[0065] Embodiment

[0066] An embodiment of the present invention provides a quick connection structure between the wing and the fuselage of a cargo drone, which is composed of a fuselage assembly, a wing assembly, and an anti-loosening assembly. The fuselage assembly consists of a front fuselage frame, a rear fuselage frame, and a rear fixing seat. The wing assembly consists of a front wing beam, a rear wing beam, wing end ribs, a front wing joint, and a rear pin. The anti-loosening assembly consists of an outer limiting part, an inner pressure clamping block, a lead screw, and a spring fixed on the rear fixing seat of the fuselage.

[0067] Wing assembly: 11 - front wing beam; 12 - rear wing beam; 13 - wing end rib; 14 - front wing joint; 15 - rear pin; 16 - quick-release pin;

[0068] Fuselage assembly: 21 - front fuselage frame; 22 - rear fuselage frame; 23 - rear fixing seat;

[0069] Anti-loosening assembly: 31 - outer limiting part; 32 - inner pressure clamping block; 33 - lead screw; 34 - spring.

[0070] As Figure 1 and 2 shown, the front wing joint provided on the front wing beam is cooperatively connected with the front fuselage frame and fastened with a quick-release pin; as Figure 3 shown, the rear wing pin provided on the wing end rib is cooperatively connected with the rear fixing seat provided on the rear fuselage frame to realize the docking of the wing assembly and the fuselage assembly, and the fastening is realized through the anti-loosening assembly.

[0071] The quick disassembly and assembly structure of the drone wing and fuselage proposed by the present invention. The disassembly and assembly mechanism is provided with a guide groove and a fixing pin hole on the front frame 21 of the fuselage, and a front wing insertion joint 14 matching the guide groove and the pin hole is fixed on the front beam 11 of the wing, so that the front wing insertion joint 14 is inserted into the guide groove of the front frame 21 of the fuselage to realize the mating connection between the front joint of the wing body and the front frame of the fuselage; by providing a pin hole on the rear fixing seat 23, the rear insertion pin 15 fixed on the wing end rib 13 is inserted into the rear fixing seat 23; when the wing body is assembled, the guide groove on the front frame 21 of the fuselage and the pin hole on the rear fixing seat 23 limit the up, down, left, right and rotational movements of the wing components, which can ensure that the pin hole on the front wing insertion joint is aligned with the pin hole of the front frame of the fuselage, and the quick release pin 16 can be inserted along the course without further adjusting the wing, realizing the quick docking of the wing body.

[0072] As Figure 4 and 5 shown, the outer limiting member 31 in the anti-loosening component is fixed on the rear fixing seat 23, and the inner pressing block 32 is arranged in its cavity and can move up and down; when the wing body is docked, the inner pressing block 32 is pressed, and the flange 321 arranged on the inner pressing block moves downward along the lead screw 33. When the flange 321 moves to the unlocking position, the step 151 arranged on the rear insertion pin 15 can pass through the inner pressing block 32 and be inserted into the rear fixing seat 23, and the inner pressing block 32 is reset under the action of the spring 34, driving the flange 321 to move upward and insert into the limiting groove 152 arranged on the step of the rear insertion pin of the wing. The inner pressing block 32 locks the rear insertion pin 15, and no additional operation on the wing is required during this process.

[0073] When the wing body needs to be separated, the quick release pin 16 is removed, and the inner pressing block 32 is pressed to drive the flange 321 to move downward to the unlocking position, so as to unlock the wing.

[0074] The embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, the present invention is not limited to the above specific embodiments. The above specific embodiments are merely illustrative and not restrictive. Under the inspiration of the present invention, those of ordinary skill in the art can also make many forms without departing from the spirit and scope protected by the present invention and the claims. All of these are within the protection scope of the present invention.

Claims

1. A wing-body connection structure for a cargo drone, characterized in that Comprising: The fuselage assembly is located on the side of the fuselage and includes a front fuselage frame, a rear fuselage frame, and a rear fixing seat. Among them, a guiding groove and a first fixing pin hole are provided on the front fuselage frame; The wing assembly is located on the side of the wing and includes a front wing beam, a rear wing beam, wing tip ribs, a front wing insertion joint, a rear pin, and a quick-release pin; the front wing insertion joint is fixed on the front wing beam, the width of the front wing insertion joint is equal to the inner width of the guiding groove, and a second fixing pin hole is provided on the front wing insertion joint. The first fixing pin hole and the second fixing pin hole have the same diameter; when the front wing insertion joint is inserted into the guiding groove of the front fuselage frame, the quick-release pin can pass through the aligned first fixing pin hole and the second fixing pin hole simultaneously for fixation; an insertion hole is provided on the rear fixing seat. When the front wing insertion joint is inserted into the guiding groove of the front fuselage frame, the rear pin can be aligned and inserted into the insertion hole on the rear fixing seat; The anti-loosening assembly is located on the rear fixing seat and includes an outer limiting member, an inner pressing block, a lead screw, and a spring; among them, the outer limiting member of the anti-loosening assembly is in a sheet-shaped hollow shape, and the lower part of the hollow part is a circular lower edge; one side of the outer limiting member is fixedly attached to the rear fixing seat; a pair of lead screws are provided on the side of the outer limiting member facing outward, and the spring is sleeved on the lead screws; limiting blocks are respectively provided between the pair of lead screws near the lead screws, and the limiting blocks are located below the circular edge of the hollow part of the anti-loosening assembly; the inner pressing block is located on the side of the outer limiting member facing outward and includes a pressing part and a locking part.

2. The wing-body connection structure of the cargo drone according to claim 1, wherein, The upper part of the locking part is a circular upper edge, the lower part is an opening, and flanges are symmetrically provided inward at the opening; the inner pressing block can move up and down along the lead screw under the action of the spring.

3. The wing-body connection structure of the cargo drone according to claim 2, wherein When pressing the pressing part of the inner pressing block to make the inner pressing block move downward along the lead screw until the lower edge of the locking part abuts against the limiting block on the outer limiting member, the circular upper edge of the locking part of the inner pressing block and the circular lower edge of the outer limiting member of the anti-loosening assembly form a standard circular through hole; the standard circular through hole has the same diameter as the insertion hole on the rear fixing seat.

4. The wing-body connection structure of the cargo drone according to claim 3, characterized in that, The rear pin includes a cylindrical insertion part, and a step is protruding along the circumference at the rear of the cylindrical insertion part, and a limiting groove is recessed inward at the rear of the step; Among them, the cross-sectional diameter of the step is less than or equal to the diameter of the standard circular through hole and the insertion hole on the rear fixing seat, so that the rear pin can pass through the standard circular through hole and be inserted into the insertion hole on the rear fixing seat.

5. The wing-body connection structure of the cargo drone according to claim 4, wherein, The distance between the symmetrically arranged flanges of the inner pressing block is greater than or equal to the cross-sectional diameter of the limiting groove of the rear pin and less than or equal to the cross-sectional diameter of the step of the rear pin.

6. A method for connecting the wing and fuselage of a cargo drone, characterized in that, The wing-body connection method of the cargo unmanned aerial vehicle is based on wing-body connection according to the wing-body connection structure of any one of claims 1 to 5. The wing-body connection method of the cargo unmanned aerial vehicle includes: Inserting the front wing insertion joint of the wing assembly into the guiding groove of the front fuselage frame; Press the pressing part of the internal pressure clamping block, so that the internal pressure clamping block moves downward along the lead screw. When the lower edge of the locking part abuts against the limiting block on the outer limiting part, a standard circular through hole is formed between the circular upper edge of the locking part of the internal pressure clamping block and the circular lower edge of the outer limiting part of the anti-loosening component; Insert the rear pin through the standard circular through hole into the insertion hole on the rear fixing seat until the step on the rear pin passes through the internal pressure clamping block; Release the internal pressure clamping block, so that it resets under the action of the spring, driving the flange to move upward and insert into the limiting groove of the rear pin, realizing the locking of the rear pin by the internal pressure clamping block; Insert the quick-release pin through the first fixing pin hole and the second fixing pin hole aligned with each other on the front frame of the fuselage and the front beam of the wing at the same time to realize the docking and fixing of the wing and the fuselage.

7. The method for connecting the wing and fuselage of a cargo drone according to claim 6, wherein When wing-fuselage separation is required, remove the quick-release pin and press the internal pressure clamping block to drive the flange to move downward. When the lower edge of the locking part abuts against the limiting block on the outer limiting part, a standard circular through hole is formed between the circular upper edge of the locking part of the internal pressure clamping block and the circular lower edge of the outer limiting part of the anti-loosening component, and pull out the rear pin to realize wing-fuselage separation.

Images