CN218198796U - Double-fuselage unmanned aerial vehicle horizontal tail structure - Google Patents
Double-fuselage unmanned aerial vehicle horizontal tail structure Download PDFInfo
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- CN218198796U CN218198796U CN202222858640.9U CN202222858640U CN218198796U CN 218198796 U CN218198796 U CN 218198796U CN 202222858640 U CN202222858640 U CN 202222858640U CN 218198796 U CN218198796 U CN 218198796U
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Abstract
The utility model discloses a double-fuselage unmanned aerial vehicle horizontal tail structure, relating to the technical field of flight equipment; the hanging corner box is used for being connected with a task pod, the right side of the hanging corner box is fixedly connected with the front end of the left side of the right frame, the left side of the hanging corner box is connected with the front end of the right side of the left frame, the right side of the connecting corner box is fixedly connected with the rear end of the left side of the right frame, and the left side of the connecting corner box is connected with the rear end of the right side of the left frame. The utility model discloses a carry angle box, right frame, left frame and connection angle box and connect into firm support body structure, and carry the angle box and then become the load angle box of horizontal tail front end, can transmit the load of task nacelle for whole frame, and carry the angle box and can connect the task nacelle, consequently, the utility model discloses satisfy two fuselage unmanned aerial vehicle to the rigidity and the intensity requirement of the carry function demand of horizontal tail and horizontal tail structure, and the task nacelle can convenient the change.
Description
Technical Field
The utility model relates to a flight equipment technical field, concretely relates to double-fuselage unmanned aerial vehicle horizontal tail structure.
Background
At present, the horizontal tail of the double-fuselage unmanned aerial vehicle is simple in general shape, only the pneumatic function of the double-fuselage unmanned aerial vehicle needs to be realized, a hanging task nacelle does not need to be mounted, and the mounting function is generally realized by a central wing section. However, the front end of the horizontal tail of a certain type of double-body unmanned aerial vehicle requires a mounting task nacelle (such as a mounting infrared/optical multifunctional task nacelle), so that the mounting function requirement of the unmanned aerial vehicle on the horizontal tail and the rigidity and strength requirement of a horizontal tail structure need to be met at the same time.
SUMMERY OF THE UTILITY MODEL
Aiming at the technical problem that a task nacelle needs to be mounted on the horizontal tail of a double-fuselage unmanned aerial vehicle; the utility model provides a two-fuselage unmanned aerial vehicle horizontal tail structure can satisfy two-fuselage unmanned aerial vehicle to the rigidity and the intensity requirement of the carry function demand of horizontal tail and horizontal tail structure, and the task nacelle can convenient the change.
The utility model discloses a following technical scheme realizes:
the utility model provides a two-fuselage unmanned aerial vehicle horizontal tail structure, including carry angle box, right frame, left frame and connection angle box, carry angle box is used for connecting the task nacelle, carry angle box right side with right frame left side front end fixed connection, carry angle box left side with left side frame right side front end links to each other, connect angle box right side with right side frame left side rear end fixed connection, connect angle box left side with left side frame right side rear end links to each other.
The utility model provides a two-fuselage unmanned aerial vehicle horizontal tail structure, carry angle box right side and right frame left side front end fixed connection, carry angle box left side and left frame right side front end and link to each other, connect angle box right side and right frame left side rear end fixed connection, it links to each other with left frame right side rear end to connect angle box left side, so that carry angle box, right frame, left frame and connection angle box connect into firm support body structure, and carry angle box and then become the load angle box of horizontal tail front end, can transmit the load of task nacelle for whole frame, and carry angle box can connect the task nacelle, therefore, the utility model discloses satisfy two-fuselage unmanned aerial vehicle to the rigidity and the intensity requirement of the carry function demand and the horizontal tail structure of horizontal tail, and the task nacelle can convenient change.
In an optional implementation mode, the right frame and the left frame are symmetrically arranged about the mounting angle box and the connection center of the connection angle box, so that the balance of stress of the horizontal tail structure of the unmanned aerial vehicle with the double bodies is ensured, and the flying stability of the unmanned aerial vehicle is ensured.
In an optional embodiment, the right frame includes a front side beam and a rear side beam, the left end of the front side beam is fixedly connected to the mounting corner box, the left end of the rear side beam is fixedly connected to the connecting corner box, and the right end of the front side beam is connected to the right end of the rear side beam through an end rib, so that the front side beam, the rear side beam, the end rib, the mounting corner box and the connecting corner box are connected to form a stable frame structure.
In an optional embodiment, the right frame further includes a horizontal vertical fin butt-joint rib, one end of the horizontal vertical fin butt-joint rib is fixedly connected with the middle of the front side beam, and the other end of the horizontal vertical fin butt-joint rib is fixedly connected with the middle of the rear side beam.
In an optional embodiment, the right rack is provided with a box side rib, one end of the box side rib is fixedly connected with the mounting corner box, and the other end of the box side rib is fixedly connected with the connecting corner box, so as to improve the stability of connection between the mounting corner box and the connecting corner box.
In an optional embodiment, the right frame is further provided with a plurality of box section ribs at intervals, one end of each box section rib is fixedly connected with the front side beam, the other end of each box section rib is fixedly connected with the rear side beam, and each box section rib is located between the corresponding horizontal and vertical tail butt joint rib and the corresponding box side rib, so that a closed force transmission path is formed by matching the box section ribs with the front side beam and the rear side beam, and the structural strength and rigidity of the horizontal tail structure are improved.
In an alternative embodiment, a plurality of front edge ribs are provided on the front side of the front side member, and the front edge ribs are spaced apart along the length of the front left side of the front side member to maintain a front edge profile by the front edge ribs.
In an alternative embodiment, the rear side of the rear side member is provided with a rear edge rib to maintain a rear edge profile by the rear edge rib.
In an alternative embodiment, a plurality of control surface suspension ribs are arranged on the rear side of the rear side beam, and the plurality of control surface suspension ribs are arranged at intervals along the length direction of the left front side of the rear side beam.
In an alternative embodiment, the right frame and the left frame are each provided with a skin.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
the utility model provides a two fuselage unmanned aerial vehicle horizontal tail structure, carry angle box right side and right frame left side front end fixed connection, carry angle box left side and left frame right side front end and link to each other, connect angle box right side and right frame left side rear end fixed connection, it links to each other with left frame right side rear end to connect angle box left side, so that carry angle box, right frame, left frame and connection angle box connect into firm support body structure, and carry angle box has then become the load angle box of horizontal tail front end, can transmit the load of task nacelle for whole frame, and carry angle box can connect the task nacelle, therefore, the utility model discloses satisfy two fuselage unmanned aerial vehicle to the rigidity and the intensity requirement of the hanging function demand of horizontal tail and horizontal tail structure, and the task nacelle can convenient the change.
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 bottom view of a horizontal tail structure according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of the task pod and the mounting corner box according to an embodiment of the present invention;
fig. 3 is a schematic bottom view of the horizontal tail structural skin according to the embodiment of the present invention.
Reference numbers and corresponding part names in the drawings:
1-mounted corner box, 2-right frame, 3-left frame, 4-connected corner box, 5-mission nacelle, 6-front side beam, 7-rear side beam, 8-horizontal vertical tail butt rib, 9-box side rib, 10-box section rib, 11-leading edge rib, 12-trailing edge rib, 13-rudder face suspension rib, 14-upper skin, 15-lower skin, 16-left outside leading edge skin, 17-left inside leading edge skin, 18-right outside leading edge skin, 19-right inside leading edge skin, 20-left trailing edge skin, 21-right rear edge skin, 22-flap, 23-end rib.
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, generally described and illustrated in the figures herein, can 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 or 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 as a specific case by those skilled in the art.
Examples
With reference to fig. 1, this embodiment provides a two-fuselage unmanned aerial vehicle horizontal tail structure, including carry corner box 1, right frame 2, left frame 3 and connection corner box 4, carry corner box 1 and be used for connecting task nacelle 5, carry corner box 1 right side with 2 left sides front end fixed connection of right frame, carry corner box 1 left side with 3 right sides front end of left frame links to each other, connect corner box 4 right side with 2 left sides rear end fixed connection of right frame, connect corner box 4 left side with 3 right sides rear end of left frame links to each other.
Referring to fig. 2, specifically, the types of the mission pods 5 are different according to the mission to be performed by the dual-fuselage drone. Aiming at optical tasks to be executed, the task nacelle 5 with a cone-shaped body is usually adopted, an optical window can be arranged at the head of the task nacelle 5 according to needs, task equipment such as an infrared camera or an optical camera can be installed in the task nacelle 5, the tail of a cabin body of the task nacelle 5 is sleeved in an installation flange provided by the mounting angle box 1, the installation flange and the installation flange are matched through cylindrical surfaces and connected through screws, and the task nacelle is convenient to replace quickly.
It should be understood that the right frame 2 and the left frame 3 are both symmetrically arranged about the connection centers of the mounting angle box 1 and the connection angle box 4, so as to ensure the balance of the stress of the horizontal tail structure of the unmanned aerial vehicle with two bodies and ensure the stability of the unmanned aerial vehicle in flight. For convenience of subsequent description, the right frame 2 is taken as an example in the present embodiment for detailed description, and the left frame 3 and the right frame 2 are completely symmetrical, and will not be described in detail, specifically:
the right rack 2 comprises a front side beam 6 and a rear side beam 7, the left end of the front side beam 6 is fixedly connected with the mounting corner box 1, the left end of the rear side beam 7 is fixedly connected with the connecting corner box 4, and the right end of the front side beam 6 is connected with the right end of the rear side beam 7 through an end rib 23 so as to connect the front side beam 6, the rear side beam 7, the end rib 23, the mounting corner box 1 and the connecting corner box 4 into a stable frame structure.
Generally, the front side member 6 is divided into a right front inner side member and a right front outer side member which are connected in series, the left end of the right front inner side member is fixedly connected to the mounting corner box 1, the right end thereof is fixedly connected to the left end of the right front outer side member, and the right end thereof is fixedly connected to the front end of the end rib 23. As for the specific structure of the front side member 6 and the rear side member 7, the cross sections thereof are reinforced cross sections common in engineering, and in the present embodiment, the front side member 6 and the rear side member 7 are both C-section beams. For the end ribs 23, which are located at one end of the butt structure, a reinforced section, such as a C-section rib, is also used.
It can be understood that, in order to facilitate installation of the horizontal vertical fin, the right frame 2 further comprises a horizontal vertical fin butt joint rib 8, one end of the horizontal vertical fin butt joint rib 8 is fixedly connected with the middle part of the front side beam 6, and the other end of the horizontal vertical fin butt joint rib 8 is fixedly connected with the middle part of the rear side beam 7.
In the embodiment, the rear end of the vertical fin butt joint rib 8 is fixedly connected with the middle part of the rear side beam 7, and the front end of the vertical fin butt joint rib is fixedly connected with the joint of the right front inner side beam and the right front outer side beam. That is, the right front outer and inner side rails are integrally connected with the horizontal depending fin butt rib 8 bead and the web.
In order to ensure the structural strength of the flattail butt joint rib 8, in the present embodiment, the interface of the flattail butt joint rib 8 is an i-shaped cross section, and the lower portion thereof is provided with 2 double lugs and connected with the flattail butt joint through bolts.
On this basis, right side frame 2 is provided with box side rib 9, box side rib 9 one end with carry corner box 1 fixed connection, box side rib 9 other end with connect corner box 4 fixed connection to improve carry corner box 1 and the stability of being connected of connecting corner box 4.
Furthermore, a plurality of box section ribs 10 are arranged at intervals on the right rack 2, one ends of the box section ribs 10 are fixedly connected with the front side beam 6, the other ends of the box section ribs 10 are fixedly connected with the rear side beam 7, and each box section rib 10 is located between the flatwise butt joint rib 8 and the box side rib 9, so that the box section ribs 10 are matched with the front side beam 6 and the rear side beam 7 to form a closed force transmission path, and the structural strength and the rigidity of a flatwise structure are improved.
In the embodiment, the box side ribs 9 and the box section ribs 10 are fixedly connected with the right front inner side beam, the sections of the box side ribs and the box section ribs are all C-shaped sections, and a closed force transmission path is formed by the box side ribs, the front side beam 6, the rear side beam 7 and the skin, so that the requirements of horizontal tail rigidity and strength are met. The rib strips of the box side ribs 9 and the box section ribs 10 are embedded in the corresponding beam edge strips.
Accordingly, a plurality of front edge ribs 11 are provided on the front side of the front side member 6, and the plurality of front edge ribs 11 are provided at intervals along the longitudinal direction of the left front side of the front side member 6 so as to maintain the front edge profile by the front edge ribs 11.
Meanwhile, the rear side member 7 is provided at the rear side with a rear edge rib 12 to maintain a rear edge profile by the rear edge rib 12.
The C-section structure is also adopted for the leading edge rib 11 and the trailing edge rib 12 to ensure sufficient structural strength and rigidity thereof.
Further, a plurality of control surface suspension ribs 13 are provided on the rear side of the rear side member 7, and the plurality of control surface suspension ribs 13 are provided at intervals in the longitudinal direction of the front left side of the rear side member 7. Also, to ensure sufficient structural strength and rigidity of the rudder surface suspension rib 13, a reinforced cross-sectional structure, such as a cross-sectional structure of a i-shaped cross-section, is adopted. Meanwhile, the end of each control surface suspension rib 13 is provided with a single lug to be connected with the elevator butt joint through the single lug, and a fisheye bearing is arranged in the single lug so as to facilitate the rotation of the control surface.
In the present embodiment, the connection form between the end rib 23, the front edge rib 11, the rear edge rib 12, the flattail butt rib 8, the box section rib 10, the box side rib 9, and the control surface suspension rib 13 and the beams (the front side member 6 and the rear side member 7) is: the rib webs are connected to the beam webs by corner pieces.
With reference to fig. 3, it can be understood that the right frame 2 and the left frame 3 are each provided with a skin. For the skin, the skin is divided into eight parts, namely an upper skin 14, a lower skin 15, a left outer front edge skin 16, a left inner front edge skin 17, a right outer front edge skin 18, a right inner front edge skin 19, a left rear edge skin 20 and a right rear edge skin 21, and all the spars and ribs are connected with the upper skin 15 and the lower skin 15 through glue rivets. Wherein, lower covering 15 has seted up 2 department flaps 22 (bilateral symmetry) as required, is convenient for carry out the installation and the maintenance of steering wheel etc. relevant equipment.
In conclusion, the double-fuselage unmanned aerial vehicle horizontal tail structure that this embodiment provided, mount 1 right side of corner box and 2 left side front end fixed connection of right frame, mount 1 left side of corner box links to each other with 3 right side front ends of left frame, connect 4 right sides of corner box and 2 left side rear end fixed connection of right frame, it links to each other with 3 right side rear ends of left frame to connect 4 left sides of corner box, so that mount 1, right frame 2, left frame 3 and connection corner box 4 connect into firm frame body structure, and mount 1 has then become the bearing corner box of horizontal tail front end, can transmit the load of task nacelle 5 for whole frame, and mount 1 can connect task nacelle 5, consequently, can satisfy double-fuselage unmanned aerial vehicle to the rigidity and the intensity requirement of horizontal tail's the function demand of hanging of horizontal tail and horizontal tail structure, and task nacelle 5 can conveniently change.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. 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 two fuselage unmanned aerial vehicle horizontal tail structure, its characterized in that, includes carry angle box (1), right frame (2), left frame (3) and connection angle box (4), carry angle box (1) and be used for connecting task nacelle (5), carry angle box (1) right side with right frame (2) left side front end fixed connection, carry angle box (1) left side with left side frame (3) right side front end links to each other, connect angle box (4) right side with right side frame (2) left side rear end fixed connection, connect angle box (4) left side with left side frame (3) right side rear end links to each other.
2. Double-fuselage unmanned aerial vehicle horizontal tail structure according to claim 1, characterized in that the right rack (2) and the left rack (3) are both symmetrically arranged with respect to the connection center of the mounting corner boxes (1) and the connection corner boxes (4).
3. The twin-fuselage unmanned aerial vehicle horizontal tail structure of claim 2, wherein the right frame (2) comprises a front side beam (6) and a rear side beam (7), the left end of the front side beam (6) is fixedly connected with the mounting corner box (1), the left end of the rear side beam (7) is fixedly connected with the connecting corner box (4), and the right end of the front side beam (6) is connected with the right end of the rear side beam (7) through an end rib (23).
4. The unmanned aerial vehicle horizontal tail structure of double bodies according to claim 3, wherein the right rack (2) further comprises a horizontal vertical tail butt rib (8), one end of the horizontal vertical tail butt rib (8) is fixedly connected with the middle of the front side beam (6), and the other end of the horizontal vertical tail butt rib (8) is fixedly connected with the middle of the rear side beam (7).
5. The twin-fuselage unmanned aerial vehicle horizontal tail structure of claim 4, wherein the right frame (2) is provided with a box side rib (9), one end of the box side rib (9) is fixedly connected with the mounting corner box (1), and the other end of the box side rib (9) is fixedly connected with the connecting corner box (4).
6. The twin-fuselage unmanned aerial vehicle horizontal tail structure of claim 5, wherein the right frame (2) is further provided with a plurality of box section ribs (10) at intervals, one ends of the box section ribs (10) are fixedly connected with the front side beams (6), the other ends of the box section ribs (10) are fixedly connected with the rear side beams (7), and each box section rib (10) is located between the horizontal vertical tail butt joint rib (8) and the box side rib (9).
7. The unmanned aerial vehicle horizontal tail structure of double bodies according to claim 3, wherein a plurality of front edge ribs (11) are arranged at the front side of the front side beam (6), and the plurality of front edge ribs (11) are arranged at intervals along the length direction of the left front side of the front side beam (6).
8. The twin-fuselage unmanned aerial vehicle horizontal tail structure according to claim 3, characterized in that the rear side beams (7) are provided with rear edge ribs (12) at the rear side.
9. The twin-fuselage unmanned aerial vehicle horizontal tail structure of claim 3, wherein a plurality of control surface suspension ribs (13) are arranged on the rear side of the rear side beam (7), and the control surface suspension ribs (13) are arranged at intervals along the length direction of the left front side of the rear side beam (7).
10. The twin-fuselage unmanned aerial vehicle horizontal tail structure of any one of claims 1 to 9, wherein the right frame (2) and the left frame (3) are provided with a skin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222858640.9U CN218198796U (en) | 2022-10-28 | 2022-10-28 | Double-fuselage unmanned aerial vehicle horizontal tail structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222858640.9U CN218198796U (en) | 2022-10-28 | 2022-10-28 | Double-fuselage unmanned aerial vehicle horizontal tail structure |
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| Publication Number | Publication Date |
|---|---|
| CN218198796U true CN218198796U (en) | 2023-01-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222858640.9U Active CN218198796U (en) | 2022-10-28 | 2022-10-28 | Double-fuselage unmanned aerial vehicle horizontal tail structure |
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| CN (1) | CN218198796U (en) |
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2022
- 2022-10-28 CN CN202222858640.9U patent/CN218198796U/en active Active
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