CN220410927U - Vertical tail wing and solar unmanned aerial vehicle with same - Google Patents
Vertical tail wing and solar unmanned aerial vehicle with same Download PDFInfo
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- CN220410927U CN220410927U CN202321952744.4U CN202321952744U CN220410927U CN 220410927 U CN220410927 U CN 220410927U CN 202321952744 U CN202321952744 U CN 202321952744U CN 220410927 U CN220410927 U CN 220410927U
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- rib
- rudder
- stabilizer
- ribs
- vertical tail
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- 239000003381 stabilizer Substances 0.000 claims abstract description 48
- 239000000725 suspension Substances 0.000 claims abstract description 27
- 239000006260 foam Substances 0.000 claims description 15
- 239000002131 composite material Substances 0.000 claims description 14
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 210000001503 joint Anatomy 0.000 description 10
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- OFCNXPDARWKPPY-UHFFFAOYSA-N allopurinol Chemical compound OC1=NC=NC2=C1C=NN2 OFCNXPDARWKPPY-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
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- Vehicle Body Suspensions (AREA)
Abstract
The application belongs to the field of aircraft structural design, and particularly relates to a vertical tail wing and a solar unmanned aerial vehicle with the same. The vertical tail includes: the stabilizer comprises a main beam, an auxiliary beam, a stabilizer rib and a stabilizer skin, wherein the main beam and the auxiliary beam are arranged in parallel, butt joints for connecting with a machine body are arranged on the main beam and the auxiliary beam, the stabilizer rib is respectively connected with the main beam and the auxiliary beam through butt angle pieces, and the stabilizer skin is paved outside a framework structure consisting of the main beam, the auxiliary beam and the stabilizer rib; the auxiliary beam is provided with a suspension support; the rudder comprises a rudder beam, a rudder wing rib and a rudder skin, wherein the rudder wing rib is connected with the rudder beam through a butt-joint angle piece, and the rudder skin is paved outside a skeleton structure formed by the rudder beam and the rudder wing rib; a suspension joint is arranged on the rudder beam; the rudder is mounted on the suspension mount of the stabilizer by means of a suspension joint.
Description
Technical Field
The application belongs to the field of aircraft structural design, and particularly relates to a vertical tail wing and a solar unmanned aerial vehicle with the same.
Background
At present, the vertical tail fin of a large-scale solar unmanned aerial vehicle basically adopts a common composite material trough type beam structure, sectional rib butt joint is used, the structural adhesive consumption is high, the use of fasteners is reduced, but the tail fin is heavy, and the vertical tail fin has no advantages in the aspects of strength, weight and the like of the unmanned aerial vehicle.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The purpose of this application is to provide a vertical fin and have its solar unmanned aerial vehicle to solve at least one problem that prior art exists.
The technical scheme of the application is as follows:
a first aspect of the present application provides a vertical tail comprising:
the stabilizer comprises a main beam, an auxiliary beam, a stabilizer rib and a stabilizer skin, wherein,
the main beam and the auxiliary beam are arranged in parallel, butt joints for connecting with a machine body are arranged on the main beam and the auxiliary beam, the stabilizer rib is respectively connected with the main beam and the auxiliary beam through butt angle pieces, a suspension support is arranged on the stabilizer rib, and the stabilizer skin is paved outside a framework structure formed by the main beam, the auxiliary beam and the stabilizer rib;
a rudder comprising a rudder beam, a rudder rib and a rudder skin, wherein,
the rudder wing ribs are connected with the rudder beam through butt-joint corner pieces, and the rudder skin is paved outside a framework structure formed by the rudder beam and the rudder wing ribs;
a suspension joint is arranged on the rudder beam;
the rudder is mounted on a suspension support of the stabilizer through a suspension joint.
In at least one embodiment of the present application, the main beam is a circular tubular beam, and is made of a carbon fiber composite material.
In at least one embodiment of the present application, the root of the main beam is provided with a tail wheel through a tail wheel bracket, the tail wheel bracket comprises an upper fixing part and a lower rotating part, the upper fixing part is glued with the main beam, the lower rotating part is connected with the upper fixing part through a bolt, and the tail wheel is arranged on the lower rotating part.
In at least one embodiment of the present application, the auxiliary beam is a rectangular beam, and is made of a carbon fiber composite material and a foam sandwich.
In at least one embodiment of the present application, the stabilizer rib extends to the leading edge and is glued to the stabilizer skin of the leading edge.
In at least one embodiment of the present application, the stabilizer rib is along a plurality of first ribs, a plurality of second ribs and two first end ribs that the spanwise was arranged, wherein, be provided with on the first rib and hang the support, first rib and first end rib all are foam sandwich rib, the second rib is the truss rib.
In at least one embodiment of the present application, the rudder rib comprises a plurality of third ribs arranged in the spanwise direction and two second end ribs, and further comprises a fourth rib arranged in a pairwise crossing manner, wherein,
the third rib is a truss rib, the second end rib and the fourth rib are foam sandwich ribs, and the third rib, the first rib and the second rib are arranged oppositely;
and the fourth ribs are arranged in a crossing way between the third ribs and the second end ribs.
In at least one embodiment of the present application, the rudder is provided with a foam front that is connected to the rudder beam.
In at least one embodiment of the present application, the suspension mount and the suspension joint are each provided with four.
A second aspect of the present application provides a solar unmanned aerial vehicle comprising a vertical tail as described above.
The utility model has at least the following beneficial technical effects:
the vertical tail fin is light in weight, easy to assemble and disassemble, reduces the weight of the vertical tail, reduces the use of fasteners, meets the requirements of strength and vibration, and meets the use requirements of the solar unmanned aerial vehicle tail fin structure in the near space for large-scale long voyage.
Drawings
FIG. 1 is a schematic illustration of a vertical tail according to one embodiment of the present application;
FIG. 2 is a schematic view of a stabilizer according to one embodiment of the present application;
fig. 3 is a schematic view of a rudder of an embodiment of the present application.
Wherein:
1-a stabilizer; 11-main beams; 12-auxiliary beams; 13-stabilizer ribs; 131-first rib; 132-second rib; 133-first end ribs; 14-butt joint; 15-hanging a support; 16-tail wheel bracket; 17-tail wheel; 2-rudder; 21-rudder beams; 22-rudder ribs; 221-third rib; 222-second end ribs; 223-fourth rib; 23-hanging joints; 24-foam front.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application. Embodiments of the present application are described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The present application is described in further detail below in conjunction with fig. 1-3.
A first aspect of the present application provides a vertical tail comprising: stabilizer 1 and rudder 2.
Specifically, as shown in fig. 2, the stabilizer 1 includes a main beam 11, an auxiliary beam 12, a stabilizer rib 13, and a stabilizer skin. The stabilizer 1 adopts a main beam 11, an auxiliary beam 12 and a stabilizer rib 13 to form an internal framework structure, and a configuration form of externally paving a film skin. The main beam 11 and the auxiliary beam 12 are arranged in parallel, metal butt joints 14 used for being connected with the machine body are arranged on the main beam 11 and the auxiliary beam 12, the stabilizer rib 13 is respectively connected with the main beam 11 and the auxiliary beam 12 through composite material butt angle pieces, a suspension support 15 used for installing the rudder 2 is arranged on the stabilizer rib 13, and a stabilizer skin is paved outside a framework structure formed by the main beam 11, the auxiliary beam 12 and the stabilizer rib 13.
In the preferred embodiment of the present application, the main beam 11 is a circular tubular beam, and is made of a carbon fiber composite material, and the main beam 11 is a main bearing member, is designed in full section with equal thickness, and is used for bearing most of the total load of the vertical tail, and transmitting the load to the fuselage through the butt joint of the vertical tail and the fuselage. In this embodiment, the root of the main beam 11 is provided with a tail wheel 17 through a tail wheel bracket 16, the tail wheel bracket 16 includes an upper fixing part and a lower rotating part, the upper fixing part is glued with the main beam 11, the lower rotating part is connected with the upper fixing part through a bolt, and the tail wheel 17 is mounted on the lower rotating part. It will be appreciated that in order to prevent the tailwheel 17 from being deflected too far, it is preferable to design an angular stop on the upper fixed part.
In the preferred embodiment of the present application, the auxiliary beam 12 is a rectangular beam, made of carbon fiber composite and foam sandwich, the auxiliary beam 12 being disposed at full height for providing spanwise stiffness of the rib rear section and rudder suspension support.
In the preferred embodiment of the present application, the stabilizer rib 13 extends into the interior of the leading edge and is glued directly to the stabilizer skin of the leading edge. The stabilizer rib 13 is made of a carbon fiber composite material and comprises a plurality of first ribs 131, a plurality of second ribs 132 and two first end ribs 133 which are arranged along the span-wise direction, wherein a suspension support 15 is arranged on the first ribs 131, the first ribs 131 and the first end ribs 133 are of foam sandwich structures, and the second ribs 132 are truss ribs. In this embodiment, two first end ribs 133 are located at two ends of the stabilizer 1, and the first ribs 131 include three ribs, two ribs corresponding to the butt joint 14, and diagonal ribs disposed along the fuselage interface.
As shown in fig. 3, the rudder 2 is located at the trailing edge of the vertical tail and functions to generate yaw moment to the aircraft and provide heading manoeuvrability to the aircraft. The rudder 2 includes a rudder beam 21, a rudder rib 22, and a rudder skin, and the rudder 2 adopts a single-beam structure in which a plurality of rudder ribs 22 are arranged in the spanwise direction in consideration of the structure, strength, weight, assembly, and the like. The rudder wing ribs 22 are connected with the rudder beam 21 through butt-joint corner pieces, and the rudder skin is paved outside a framework structure formed by the rudder beam 21 and the rudder wing ribs 22; the rudder beam 21 is provided with a suspension joint 23; the rudder 2 is mounted on the suspension mount 15 of the stabilizer 1 by means of a suspension joint 23.
In the preferred embodiment of the present application, the rudder rib 22 includes a plurality of third ribs 221 and two second end ribs 222 arranged along the spanwise direction, and in order to improve the rigidity of the control surface, fourth ribs 223 arranged in a crossing manner are designed between the ribs, wherein the third ribs 221 are truss ribs, the second end ribs 222 and the fourth ribs 223 are foam sandwich ribs, and the third ribs 221 are disposed opposite to the first ribs 131 and the second ribs 132; the fourth rib 223 disposed to intersect two by two is disposed between the third rib 221 and the second end rib 222. Advantageously, in the present embodiment, lightening holes are provided in the fourth rib 223 and in the rudder skin at the trailing edge of the rudder.
In this embodiment, the rudder 2 is provided with a foam front 24 connected to the rudder beam 21. The fixed shaft type movement principle is adopted, the rotating shaft is positioned at the front edge of the rudder 2, and four suspension support 15 and suspension joint 23 are respectively provided with four points. The rudder 2 is attached to the trailing edge suspension mount 15 by 4 suspension joints 23.
The vertical tail fin of this application, the assembly flow is: vertical tail fin and fuselage butt joint 14 positioning bond, foam sandwich rib bond, auxiliary Liang Nianjie, landing gear tail wheel assembly, tail wheel assembly to main beam bond, leading edge bond, rudder bond.
The vertical tail fin of the application creatively uses a cementing truss type double-beam structure of carbon fiber tube beams, rectangular beams, ribs and composite material butt joint angle pieces; the main beam adopts a circular tube type, and is glued with the wing ribs through composite corner pieces, so that a large amount of fasteners are omitted; the truss structure improves the structural stability and reduces the structural weight; the design of the large-size light composite material is adopted, and most of other structures except the special connection part adopts a metal material are made of the composite material, so that the weight of the vertical tail is greatly reduced; the supporting connection points with other structures are directly arranged on the wing ribs, so that the weight gain of the structure caused by the independent design of the joint is avoided; the rudder is innovatively designed with cross foam ribs, so that the rigidity of the control surface is improved.
A second aspect of the present application provides a solar unmanned aerial vehicle having the vertical tail as described above.
Because the weight coefficient of the solar unmanned aerial vehicle body is very low, the weight index control is very strict, and a large number of light carbon fiber reinforced composite material laminated structures and composite material sandwich structures are used in the vertical tail wing structure, so that the weight is greatly reduced.
The vertical tail wing and the solar unmanned aerial vehicle with the same are simple in structure and connection form and convenient to check, maintain and disassemble; the truss type circular tube beam is adopted, so that the structural weight is greatly reduced, and the design of the circular tube beam is stronger than that of a common box type beam in the aspect of structural bearing capacity; the economy is good, and the manufacturing cost is lower than that of the vertical tail of the common unmanned aerial vehicle; the vertical tail structure can be used for long-endurance large-aspect-ratio solar unmanned aerial vehicle, is used in a certain type of aircraft, and successfully completes static test, test flight and first flight, and is currently subjected to environmental test.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A vertical tail comprising:
the stabilizer (1), the stabilizer (1) comprises a main beam (11), an auxiliary beam (12), a stabilizer rib (13) and a stabilizer skin, wherein,
the main beam (11) and the auxiliary beam (12) are arranged in parallel, butt joints (14) used for being connected with a machine body are arranged on the main beam (11) and the auxiliary beam (12), the stabilizer rib (13) is respectively connected with the main beam (11) and the auxiliary beam (12) through butt angle pieces, a suspension support (15) is arranged on the stabilizer rib (13), and the stabilizer skin is paved outside a framework structure formed by the main beam (11), the auxiliary beam (12) and the stabilizer rib (13);
rudder (2), the rudder (2) comprising a rudder beam (21), a rudder rib (22) and a rudder skin, wherein,
the rudder rib (22) is connected with the rudder beam (21) through a butt-joint corner piece, and the rudder skin is paved outside a framework structure formed by the rudder beam (21) and the rudder rib (22);
a suspension joint (23) is arranged on the rudder beam (21);
the rudder (2) is mounted on a suspension support (15) of the stabilizer (1) through a suspension joint (23).
2. The vertical tail according to claim 1, characterized in that the main beams (11) are circular tubular beams made of carbon fiber composite material.
3. The vertical tail according to claim 2, characterized in that the root of the main beam (11) is fitted with a tail wheel (17) by means of a tail wheel bracket (16), the tail wheel bracket (16) comprising an upper fixed part glued to the main beam (11) and a lower rotating part connected to the upper fixed part by means of bolts, the tail wheel (17) being fitted on the lower rotating part.
4. The vertical tail according to claim 1, characterized in that the auxiliary beam (12) is a rectangular beam made of carbon fiber composite material and foam sandwich.
5. A vertical tail according to claim 1, characterized in that the stabilizer rib (13) extends to the leading edge and is glued to the stabilizer skin of the leading edge.
6. The vertical tail according to claim 5, characterized in that the stabilizer rib (13) comprises a plurality of first ribs (131), a plurality of second ribs (132) and two first end ribs (133) arranged along the spanwise direction, wherein the first ribs (131) are provided with suspension supports (15), the first ribs (131) and the first end ribs (133) are foam sandwich ribs, and the second ribs (132) are truss ribs.
7. The vertical tail according to claim 6, characterized in that the rudder rib (22) comprises a plurality of third ribs (221) and two second end ribs (222) arranged in the spanwise direction, and a fourth rib (223) arranged in a crossing manner, wherein,
the third rib (221) is a truss rib, the second end rib (222) and the fourth rib (223) are foam sandwich ribs, and the third rib (221) is opposite to the first rib (131) and the second rib (132);
a fourth rib (223) is disposed between the third rib (221) and the second end rib (222) in a staggered arrangement.
8. A vertical tail as claimed in claim 1, characterized in that the rudder (2) is provided with a foam front (24) connected to the rudder beam (21).
9. A vertical tail according to claim 1, characterized in that the suspension mount (15) and the suspension joint (23) are each provided with four.
10. A solar unmanned aerial vehicle comprising a vertical tail as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321952744.4U CN220410927U (en) | 2023-07-24 | 2023-07-24 | Vertical tail wing and solar unmanned aerial vehicle with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321952744.4U CN220410927U (en) | 2023-07-24 | 2023-07-24 | Vertical tail wing and solar unmanned aerial vehicle with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220410927U true CN220410927U (en) | 2024-01-30 |
Family
ID=89640883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321952744.4U Active CN220410927U (en) | 2023-07-24 | 2023-07-24 | Vertical tail wing and solar unmanned aerial vehicle with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220410927U (en) |
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2023
- 2023-07-24 CN CN202321952744.4U patent/CN220410927U/en active Active
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