CN218112964U - Split docking structure with replaceable central wing panel and double-fuselage unmanned aerial vehicle - Google Patents
Split docking structure with replaceable central wing panel and double-fuselage unmanned aerial vehicle Download PDFInfo
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- CN218112964U CN218112964U CN202222857747.1U CN202222857747U CN218112964U CN 218112964 U CN218112964 U CN 218112964U CN 202222857747 U CN202222857747 U CN 202222857747U CN 218112964 U CN218112964 U CN 218112964U
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- fuselage
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Abstract
The utility model discloses a split docking structure with replaceable central wing sections and a double-fuselage unmanned aerial vehicle, relating to the technical field of flight equipment; removable central wing's components of a whole that can function independently butt joint structure includes: the butt joint side of the left machine body is provided with a plurality of left universal joints, and the left universal joints are arranged at intervals along the length direction of the butt joint side of the left machine body; the right machine body is provided with a plurality of right universal joints and replaceable joints on the butt joint side, the replaceable joints are positioned at the end part of the butt joint side of the right machine body, and the right universal joints and the replaceable joints are arranged at intervals along the length direction of the butt joint side of the right machine body; the replaceable joint is detachably connected with the right machine body, and can be connected with central wing sections of different configurations according to functional requirements, so that the modularization requirements of the central wing sections of multiple configurations are met. Double fuselage unmanned aerial vehicle, the components of a whole that can function independently butt joint structure that the adaptation has foretell removable central wing section on the unmanned aerial vehicle body.
Description
Technical Field
The utility model relates to a flight equipment technical field, concretely relates to components of a whole that can function independently butt-joint structural and double fuselage unmanned aerial vehicle of removable central wing section.
Background
The double-fuselage unmanned aerial vehicle is generally connected through a central wing section or a central wing box to form a good force transmission path, so that the functional requirements and the structural rigidity requirements of the unmanned aerial vehicle on the central wing section are met. At present, most of central wings of double-fuselage unmanned aerial vehicles are single-configuration, and fuselage butt joint lug structural style is fixed, can't satisfy the removable demand of multi-configuration central wing.
SUMMERY OF THE UTILITY MODEL
The unmanned aerial vehicle aims at the technical problem that the existing unmanned aerial vehicle with double bodies cannot meet the replaceable requirement of a multi-configuration central wing; the utility model provides a components of a whole that can function independently butt-joint structural and double fuselage unmanned aerial vehicle of removable central wing section can satisfy the modularization demand of the central wing section of many configurations according to the central wing section of different configurations is connected to the functional demand.
The utility model discloses a following technical scheme realizes:
in a first aspect, the utility model provides a components of a whole that can function independently butt-joint structural of removable central wing section, include: the left universal joint is arranged at intervals along the length direction of the butt joint side of the left body; the right machine body is provided with a plurality of right universal joints and replaceable joints on the butt joint side, the replaceable joints are positioned at the end part of the butt joint side of the right machine body, and the right universal joints and the replaceable joints are arranged at intervals along the length direction of the butt joint side of the right machine body; wherein, the interchangeable connects with right fuselage detachable connects.
The utility model provides a components of a whole that can function independently butt-joint structure of removable central wing section, butt joint side length direction interval at left fuselage sets up a plurality of left universal joints, can be connected with the left standard butt joint of central wing section of different configurations, butt joint side length direction interval at right fuselage sets up a plurality of right universal joints and interchangeable joint simultaneously, and the interchangeable joint is located the butt joint side tip of right fuselage, its right universal joint can be connected with the standard butt joint on central wing section right side of different configurations, and the interchangeable joint then can be according to the joint type and the position of the central wing section tip of corresponding configuration, change and adjust, thereby with the central wing section fixed connection of corresponding configuration between left fuselage and right fuselage.
Therefore, the utility model provides a components of a whole that can function independently butt joint structure of removable central wing section can connect the central wing section of different configurations according to the functional requirement, satisfies the modularization demand of many configurations central wing section.
In an optional embodiment, a plurality of left bulkheads are disposed on the butt joint side of the left fuselage, and each left universal joint is integrally formed with the corresponding left bulkhead, so as to ensure the structural strength of the connection between the left universal joint and the left fuselage.
In an optional embodiment, a plurality of right bulkheads are disposed on the butt joint side of the right body, each right universal joint is integrally formed with the corresponding right bulkhead, and each interchangeable joint is detachably connected with the corresponding right bulkhead, so as to ensure the structural strength of the connection between the left universal joint and the right body as well as the connection between the interchangeable joint and the right body.
In an alternative embodiment, the replaceable joint is connected with the right bulkhead through a bolt, so that the replaceable joint can be detached and installed conveniently.
In an alternative embodiment, three left universal joints are provided to meet the requirement for left side attachment of the center panel in a common configuration.
In an alternative embodiment, there are two right universal joints to meet the requirement for attachment to the right side of the center panel in a common configuration.
In a second aspect, the utility model provides a double-fuselage unmanned aerial vehicle, including the unmanned aerial vehicle body, in the adaptation has the components of a whole that can function independently butt-joint structural of foretell removable central wing section on the unmanned aerial vehicle body.
The utility model provides a double-fuselage unmanned aerial vehicle based on the components of a whole that can function independently butt-joint structural of aforementioned removable central wing section, can connect the central wing section of different configurations according to the functional requirement, satisfies the modularization demand of many configurations central wing section.
In an optional embodiment, the aircraft further comprises a first central wing panel, the first central wing panel is of a symmetrical structure, the left side of the first central wing panel is connected with the butt joint side of the left fuselage, the right side of the first central wing panel is connected with the butt joint side of the right fuselage, namely, the central wing panel connected between the left fuselage and the right fuselage is of a common standard configuration.
In an optional embodiment, the first central wing section includes a plurality of first spars, and a length direction of each of the first spars is parallel to a width direction of the first central wing section, so as to meet structural requirements of a conventional dual-fuselage unmanned aerial vehicle.
In an optional embodiment, the wing further comprises a second central wing section, the second central wing section comprises a plurality of second spars, and the included angle between the length direction of each second spar and the width direction of the second central wing section is an acute angle; the left side of the second central wing section is connected with the butt joint side of the left fuselage, the right side of the second central wing section is connected with the butt joint side of the right fuselage, and the central wing section capable of executing special tasks is connected between the left fuselage and the right fuselage.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
1. the utility model provides a components of a whole that can function independently butt-joint structural of removable central wing section, butt joint side length direction interval at left fuselage sets up a plurality of left universal joints, can be connected with the left standard butt joint of central wing section of different configurations, butt joint side length direction interval at right fuselage sets up a plurality of right universal joints and interchangeable joint simultaneously, and the interchangeable joint is located the butt joint side tip of right fuselage, its right universal joint can be connected with the standard butt joint on central wing section right side of different configurations, and the interchangeable joint then can be according to the joint type and the position of the central wing section tip of corresponding configuration, change and adjust, thereby central wing section fixed connection with corresponding configuration is between left fuselage and right fuselage, can connect the central wing section of different configurations according to the function demand, satisfy the modularization demand of multi-configuration central wing section.
2. The utility model provides a double-fuselage unmanned aerial vehicle, based on the components of a whole that can function independently butt-joint structural of aforementioned removable central wing section, can connect the central wing section of different configurations according to the functional requirement, satisfy the modularization demand of many configurations central wing section.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
In the drawings:
fig. 1 is a schematic structural view of a left body of the embodiment of the present invention;
fig. 2 is a schematic structural view of a right body according to an embodiment of the present invention;
FIG. 3 is a schematic view of a first center panel according to an embodiment of the present invention;
fig. 4 is a schematic structural view illustrating a first central wing section connected to a left fuselage and a right fuselage according to an embodiment of the present invention;
fig. 5 is a schematic structural view of a second center panel according to an embodiment of the present invention;
fig. 6 is a schematic structural view of the second central wing section connected to the left fuselage and the right fuselage according to the embodiment of the present invention.
Reference numbers and corresponding part names in the drawings:
1-left fuselage, 2-left universal joint, 3-right fuselage, 4-right universal joint, 5-interchangeable joint, 6-left bulkhead, 7-right bulkhead, 8-first center wing section, 9-first wing spar, 10-first rib, 11-first pair of joints, 12-first lower skin, 13-first left fairing, 14-first right fairing, 15-second center wing section, 16-second wing spar, 17-second rib, 18-second pair of joints, 19-second lower skin, 20-second left fairing, 21-second right fairing.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, as generally described and illustrated in the figures herein, could be arranged and designed in a wide variety of different configurations.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. The embodiments and features of the embodiments in the present application may be combined with each other without conflict.
In the description of the embodiments of the present application, the terms "central," "upper," "lower," "left," "right," "vertical," "longitudinal," "lateral," "horizontal," "inner," "outer," "front," "rear," "top," "bottom," and the like refer to orientations or positional relationships that are conventionally used in the manufacture of the present application, or that are routinely understood by those of ordinary skill in the art, but are merely used to facilitate the description and to simplify the description and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be considered limiting of the present application.
In the description of the present invention, unless otherwise explicitly specified or limited, the terms "disposed", "opened", "mounted", "connected", and "connected" are to be understood broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
With reference to fig. 1 and 2, the present embodiment provides a split docking structure of a replaceable center wing, including: the butt joint side of the left machine body 1 is provided with a plurality of left universal joints 2, and the left universal joints 2 are arranged at intervals along the length direction of the butt joint side of the left machine body 1; the right machine body 3 is provided with a plurality of right universal joints 4 and replaceable joints 5 on the butt joint side, the replaceable joints 5 are positioned at the end part of the butt joint side of the right machine body 3, and the right universal joints 4 and the replaceable joints 5 are arranged at intervals along the length direction of the butt joint side of the right machine body 3; wherein, interchangeable connect 5 with right fuselage 3 is detachable connects.
With reference to fig. 1, specifically, a plurality of left bulkheads 6 are disposed on the butt-joint side of the left body 1, and each of the left universal joints 2 is integrally formed with the corresponding left bulkhead 6, so as to ensure the structural strength of the connection between the left universal joint 2 and the left body 1.
The number of the left universal joints 2 is determined according to the model of the double-fuselage, and only the left fuselage 1 is required to be connected with the central wing section four times, so that the left universal joints have enough structural strength. In this embodiment, there are three left universal joints 2 provided to meet the requirement of a common configuration for left side attachment of the center panel.
With reference to fig. 2, a plurality of right bulkheads 7 are disposed on the butt joint side of the right body 3, each right universal joint 4 and the corresponding right bulkheads 7 are integrally formed, and each interchangeable joint 5 and the corresponding right bulkheads 7 are detachably connected to ensure the structural strength of the connection between the left universal joint 2 and the interchangeable joint 5 and the right body 3.
Optionally, the replaceable joint 5 is connected with the right bulkhead 7 through a bolt, so that the replaceable joint 5 can be conveniently detached and installed.
The number of the right universal joints 4 is determined according to the model of the double-fuselage, and only the right fuselage 3 is required to be connected with the central wing section four, so that the structural strength is enough. In this embodiment, there are two right universal joints 4 to meet the requirement of connecting the right side of the center panel in a common configuration.
It should be noted that the number and position of the interchangeable joints 5 are determined according to the configuration of the central panel to be joined, and are generally arranged at the front and/or rear end of the butt side of the right fuselage 3. The type of interchangeable joint 5 is also determined by the configuration of the central panel to be joined.
In summary, in the split docking structure of the replaceable center wing segment provided in this embodiment, a plurality of left universal joints 2 are arranged at intervals in the docking side length direction of the left fuselage 1, and can be connected with standard docking joints on the left sides of center wing segments of different configurations, a plurality of right universal joints 4 and replaceable joints 5 are arranged at intervals in the docking side length direction of the right fuselage 3, and the replaceable joints 5 are located at the docking side end of the right fuselage 3, and the right universal joints 4 can be connected with standard docking joints on the right sides of center wing segments of different configurations, and the replaceable joints 5 can be replaced and adjusted according to the joint types and positions of the center wing segment ends of corresponding configurations, so as to fixedly connect the center wing segments of corresponding configurations between the left fuselage 1 and the right fuselage 3.
Therefore, the split butt joint structure with the replaceable central wing panel provided by the embodiment can be connected with central wing panels of different configurations according to functional requirements, and meets the modular requirements of multi-configuration central wing panels.
Example 2
Combine fig. 4, this embodiment provides a double fuselage unmanned aerial vehicle, including the unmanned aerial vehicle body, in the adaptation has the components of a whole that can function independently butt-joint structural of the removable central wing section that embodiment 1 recorded on the unmanned aerial vehicle body.
The double-fuselage unmanned aerial vehicle that this embodiment provided, based on the components of a whole that can function independently butt-joint structural of the removable central wing section of embodiment 1 record, can connect the central wing section of different configurations according to the function demand, satisfy the modularization demand of many configurations central wing section.
Example 3
Combine fig. 3 and 4, this embodiment provides a double fuselage unmanned aerial vehicle, based on the double fuselage unmanned aerial vehicle who records in embodiment 2, still include first central wing section 8, first central wing section 8 is symmetrical structure, first central wing section 8 left side with the butt joint side of left fuselage 1 links to each other, first central wing section 8 right side with the butt joint side of right fuselage 3 links to each other, and the central wing section of connecting between left fuselage 1 and right fuselage 3 promptly is standard configuration commonly used.
Generally, the first central wing section 8 comprises a plurality of first wing spars 9, and the length direction of each first wing spar 9 is parallel to the width direction of the first central wing section 8, so as to meet the structural requirements of a conventional double-fuselage unmanned aerial vehicle.
Referring again to FIG. 3, it will be appreciated that the first center panel 8 is of a standard configuration commonly used and is constructed to meet the load requirements. In the present embodiment, the first central panel 8 is a three-spar layout, consisting of spars, ribs, skin and fairings. Wherein, three first wing beams 9 are respectively arranged at the front, middle and rear parts along the vertical airflow direction, and each first wing beam 9 is an I-shaped section; three first wing ribs 10 are respectively arranged along the direction parallel to the airflow direction, 4 sections of each wing rib are C-shaped sections and are connected with a web plate of a first wing beam 9 through corner pieces; the skin comprises a first lower skin 12 and the fairing comprises a first left fairing 13 and a first right fairing 14.
Of course, the number, the structural type, and the layout of the first spars 9 and the first ribs 10 are not limited to those described above, and may be butted against the left fuselage 1 and the right fuselage 3 only when the load is satisfied.
The first center panel 8 according to the present embodiment is fixed by bolts while abutting first pair joints 11 at the left and right frames 3 with first pair joints 11 at the corresponding bulkheads of the left and right frames 1 and 3. The first butt joint on the first spar 9 is a member integrally formed with the first spar 9, that is, the first butt joints 11 at both ends are integral with the first spar 9.
Referring again to fig. 4, when connecting the first central wing section 8, the first pair of joints 11 on the first wing spar 9 at the rear end thereof and the replaceable joint 5 at the rearmost end of the right fuselage 3 are connected and fixed with the right bulkhead 7 of the right fuselage 3 by bolts, and the rest connections are conventional connections of standard joints.
Example 4
With reference to fig. 5 and 6, the present embodiment provides a dual-fuselage unmanned aerial vehicle, based on the dual-fuselage unmanned aerial vehicle described in embodiment 2, further including a second central wing section 15, where the second central wing section 15 includes a plurality of second spars 16, and an included angle between a length direction of each of the second spars 16 and a width direction of the second central wing section 15 is an acute angle; the left side of the second central wing section 15 is connected with the butt joint side of the left fuselage 1, the right side of the second central wing section 15 is connected with the butt joint side of the right fuselage 3, and the central wing section capable of executing special tasks is connected between the left fuselage 1 and the right fuselage 3.
Again, specifically with reference to figure 5, the second central panel 15 is again of a three-spar type layout, consisting of spars, ribs, skins and fairings. Wherein, the front, middle and rear third second wing beams 16 are respectively arranged along the specific angle direction of the vertical airflow, and are all in I-shaped cross section; the four second ribs 17 are arranged along the direction parallel to the airflow direction, 4 sections of the second ribs 17 at two ends and 3 sections of the other second ribs 17 are all C-shaped cross sections and are connected with a web plate of a second wing beam 16 through corner pieces; the skin section comprises a second lower skin 19 and the fairing comprises a second left fairing 20 and a second right fairing 21.
Of course, the number, the structural type, and the arrangement of the second spars 16 and the first ribs are not limited to those described above, and may be butted against the left fuselage 1 and the right fuselage 3 only when the load is satisfied.
It will be appreciated that the second central wing section provided in this embodiment is also butted up with the joints on the corresponding bulkheads of the left and right fuselages 1, 3 by the second pair of joints 18 at the left and right fuselages 3, and is fixed by bolts. The second pair of joints 18 on the second spar 16 are integrally formed with the spar, i.e. the second pair of joints 18 at both ends are integrally formed with the second spar 16.
Referring again to fig. 6, when connecting the second central wing section 15, the second pair of joints 18 on the second wing spar 16 at the front end thereof and the replaceable joint 5 at the foremost end of the right fuselage 3 are connected and fixed with the right bulkhead 7 of the right fuselage 3 by bolts, and the rest of the connections are conventional connections of standard joints.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. The utility model provides a components of a whole that can function independently butt-joint structural of removable central wing section which characterized in that includes:
the butt joint device comprises a left machine body (1), wherein a plurality of left universal joints (2) are arranged on the butt joint side, and the left universal joints (2) are arranged at intervals along the length direction of the butt joint side of the left machine body (1);
the butt joint side of the right machine body (3) is provided with a plurality of right universal joints (4) and replaceable joints (5), the replaceable joints (5) are located at the end part of the butt joint side of the right machine body (3), and the right universal joints (4) and the replaceable joints (5) are arranged at intervals along the length direction of the butt joint side of the right machine body (3);
wherein, the replaceable joint (5) is detachably connected with the right machine body (3).
2. The split docking structure of a replaceable center wing section according to claim 1, wherein a plurality of left bulkheads (6) are provided at the docking side of the left fuselage (1), and each left universal joint (2) is integrally formed with the corresponding left bulkheads (6).
3. The split docking structure of a replaceable center wing section according to claim 1, wherein a plurality of right bulkheads (7) are arranged on the docking side of the right fuselage (3), each right universal joint (4) is integrally formed with the corresponding right bulkheads (7), and each replaceable joint (5) is detachably connected with the corresponding right bulkheads (7).
4. The split docking structure of an exchangeable centre panel according to claim 3, characterised in that the exchangeable joint (5) is bolted to the right bulkhead (7).
5. The split docking structure of a replaceable center wing according to any one of claims 1 to 4, characterized in that there are three left universal joints (2).
6. The split docking structure of a replaceable center wing segment according to claim 5, wherein there are two right universal joints (4).
7. An unmanned aerial vehicle with double bodies comprises an unmanned aerial vehicle body and is characterized in that the unmanned aerial vehicle body is provided with the split butt joint structure with the replaceable central wing section according to any one of claims 1 to 6 in an adaptive mode.
8. Twin-fuselage unmanned aerial vehicle according to claim 7, further comprising a first central wing section (8), the first central wing section (8) being of a symmetrical structure, the left side of the first central wing section (8) being connected to the docking side of the left fuselage (1), the right side of the first central wing section (8) being connected to the docking side of the right fuselage (3).
9. Twin-fuselage unmanned aerial vehicle according to claim 8, characterised in that the first central wing section (8) comprises a plurality of first spars (9), the length direction of each of the first spars (9) being parallel to the width direction of the first central wing section (8).
10. The twin-fuselage unmanned aerial vehicle of claim 7, further comprising a second central wing section (15), wherein the second central wing section (15) comprises a plurality of second spars (16), and an included angle between a length direction of each second spar (16) and a width direction of the second central wing section (15) is an acute angle;
the left side of the second central wing section (15) is connected with the butt joint side of the left fuselage (1), and the right side of the second central wing section (15) is connected with the butt joint side of the right fuselage (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222857747.1U CN218112964U (en) | 2022-10-28 | 2022-10-28 | Split docking structure with replaceable central wing panel and double-fuselage unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222857747.1U CN218112964U (en) | 2022-10-28 | 2022-10-28 | Split docking structure with replaceable central wing panel and double-fuselage unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN218112964U true CN218112964U (en) | 2022-12-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222857747.1U Active CN218112964U (en) | 2022-10-28 | 2022-10-28 | Split docking structure with replaceable central wing panel and double-fuselage unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218112964U (en) |
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- 2022-10-28 CN CN202222857747.1U patent/CN218112964U/en active Active
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