CN220410927U - Vertical tail wing and solar unmanned aerial vehicle with same - Google Patents

Abstract

This application belongs to the field of aircraft structure design, and particularly relates to a vertical tail and a solar-powered UAV having the same. The vertical tail includes: a stabilizer. The stabilizer includes a main beam, an auxiliary beam, a stabilizer rib, and a stabilizer skin. The main beam and the auxiliary beam are set parallel to each other. The main beam and the auxiliary beam are provided with butt joints for connection with the fuselage. The joints and stabilizer ribs are connected to the main beam and auxiliary beam respectively through butt angle pieces. The stabilizer skin is covered on the outside of the skeleton structure composed of the main beam, auxiliary beam and stabilizer ribs; the auxiliary beam is equipped with a suspension Support; rudder. The rudder includes a rudder beam, a rudder rib and a rudder skin. The rudder ribs are connected to the rudder beam through butt angle pieces. The rudder skin is laid on the skeleton structure composed of the rudder beam and the rudder ribs. Externally; the rudder beam is provided with a suspension joint; the rudder is installed on the suspension support of the stabilizer through the suspension joint.

Description

Vertical tail and solar unmanned aerial vehicle having the same

Technical field

This application belongs to the field of aircraft structure design, and particularly relates to a vertical tail and a solar-powered UAV having the same.

Background technique

At present, the vertical tails of large-scale solar UAVs basically adopt ordinary composite channel beam structures, using segmented rib joints and a large amount of structural glue. Although the use of fasteners is reduced, the tails are heavier and UAVs have no advantages in terms of strength and weight.

Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Utility model content

The purpose of this application is to provide a vertical tail and a solar drone with the same, so as to solve at least one problem existing in the existing technology.

The technical solution of this application is:

A first aspect of the present application provides a vertical tail including:

Stabilizer, the stabilizer includes main beams, auxiliary beams, stabilizer ribs and stabilizer skin, wherein,

The main beam and the auxiliary beam are arranged in parallel, and the main beam and the auxiliary beam are provided with butt joints for connecting to the fuselage. The stabilizer ribs are respectively connected to the main beam and the main beam through butt angle pieces. The auxiliary beams are connected, the stabilizer ribs are provided with suspension supports, and the stabilizer skin is covered on the outside of the skeleton structure composed of the main beam, the auxiliary beam and the stabilizer ribs. ;

a rudder, which includes a rudder beam, a rudder rib and a rudder skin, wherein,

The rudder ribs are connected to the rudder beam through butt angle pieces, and the rudder skin is covered on the outside of the skeleton structure composed of the rudder beam and the rudder ribs;

The rudder beam is provided with a suspension joint;

The rudder is mounted on the suspension support of the stabilizer through a suspension joint.

In at least one embodiment of the present application, the main beam is a circular tube beam made of carbon fiber composite material.

In at least one embodiment of the present application, a tail wheel is installed at the root of the main beam through a tail wheel bracket. The tail wheel bracket includes an upper fixed component and a lower rotating component. The upper fixed component is glued to the main beam. Then, the lower rotating part is connected to the upper fixed part through bolts, and the tail wheel is installed on the lower rotating part.

In at least one embodiment of the present application, the auxiliary beam is a rectangular beam made of carbon fiber composite material and foam sandwich.

In at least one embodiment of the present application, the stabilizer ribs extend to the leading edge and are glued to the stabilizer skin of the leading edge.

In at least one embodiment of the present application, the stabilizer rib includes a plurality of first ribs, a plurality of second ribs and two first end ribs arranged along the span, wherein the first rib A suspension support is provided on the upper body, the first wing ribs and the first end ribs are foam sandwich ribs, and the second wing ribs are truss ribs.

In at least one embodiment of the present application, the rudder ribs include a plurality of third ribs and two second end ribs arranged along the span, and further include fourth ribs arranged crosswise, wherein,

The third wing rib is a truss rib, the second end rib and the fourth wing rib are both foam sandwich ribs, and the third wing rib is opposite to the first wing rib and the second wing rib. set up;

A pair of fourth ribs arranged crosswise are provided 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 leading edge connected to the rudder beam.

In at least one embodiment of the present application, there are four suspension supports and four suspension joints.

A second aspect of the present application provides a solar powered drone including a vertical tail as described above.

Utility models have at least the following beneficial technical effects:

The vertical tail of this application is light in weight, easy to disassemble and assemble, reduces the weight of the vertical tail, reduces the use of fasteners, meets the strength and flutter requirements, and meets the use requirements of the tail structure of large-scale long-endurance solar UAVs in adjacent space.

Description of the drawings

Figure 1 is a schematic diagram of a vertical tail according to an embodiment of the present application;

Figure 2 is a schematic diagram of a stabilizer according to an embodiment of the present application;

Figure 3 is a schematic diagram of a rudder according to an embodiment of the present application.

in:

1-stabilizer; 11-main beam; 12-auxiliary beam; 13-stabilizer rib; 131-first wing rib; 132-second wing rib; 133-first end rib; 14-butt joint; 15- Suspension support; 16-tail wheel bracket; 17-tail wheel; 2-rudder; 21-rudder beam; 22-rudder rib; 221-third wing rib; 222-second end rib; 223-fourth wing rib ; 23-Suspension joint; 24-Foam front edge.

Detailed ways

In order to make the purpose, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numbers throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present application, but should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of this application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of this application, it needs to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outside", etc. are based on the orientations or positional relationships shown in the drawings. They are only for the convenience of describing the present application and simplifying the description, and are not indicated or implied. The devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of the present application.

The present application will be further described in detail below with reference to Figures 1 to 3.

The first aspect of this application provides a vertical tail including: a stabilizer 1 and a rudder 2 .

Specifically, as shown in Figure 2, the stabilizer 1 includes a main beam 11, an auxiliary beam 12, a stabilizer rib 13 and a stabilizer skin. The stabilizer 1 uses main beams 11, auxiliary beams 12 and stabilizer ribs 13 to form an internal skeleton structure, and the outside is covered with a film skin. Among them, the main beam 11 and the auxiliary beam 12 are arranged in parallel. The main beam 11 and the auxiliary beam 12 are both provided with metal butt joints 14 for connecting to the fuselage. The stabilizer ribs 13 are respectively connected to the main beam 11 through composite material butt angle pieces. and the auxiliary beam 12. The stabilizer rib 13 is provided with a suspension support 15 for installing the rudder 2. The stabilizer skin is covered with a skeleton structure composed of the main beam 11, the auxiliary beam 12 and the stabilizer rib 13. external.

In the preferred embodiment of the present application, the main beam 11 is a circular tube beam made of carbon fiber composite material. The main beam 11 is the main load-bearing component and is designed to have the same thickness throughout. It bears most of the overall vertical tail body. The load is transferred to the fuselage through the butt joint between the vertical tail and the fuselage. In this embodiment, the tail wheel 17 is installed at the root of the main beam 11 through the tail wheel bracket 16. The tail wheel bracket 16 includes an upper fixed part and a lower rotating part. The upper fixed part is glued to the main beam 11, and the lower rotating part is connected to the main beam 11 through bolts. The upper fixed parts are connected, and the tail wheel 17 is installed on the lower rotating part. It can be understood that, in order to prevent the deflection angle of the tail wheel 17 from being too large, it is preferable to design an angle limiter on the upper fixed component.

In the preferred embodiment of the present application, the auxiliary beam 12 is a rectangular beam made of carbon fiber composite material and foam sandwich. The auxiliary beam 12 is arranged at the full height to provide spanwise stiffness of the rear section of the rib and rudder suspension support.

In the preferred embodiment of the present application, the stabilizer ribs 13 extend to the inside of the leading edge and are directly glued to the stabilizer skin of the leading edge. The stabilizer rib 13 is made of carbon fiber composite material and includes a plurality of first ribs 131, a plurality of second ribs 132 and two first end ribs 133 arranged along the span. The first rib 131 A suspension support 15 is provided on the upper body. The first wing rib 131 and the first end rib 133 have a foam sandwich structure, and the second wing rib 132 is a truss rib. In this embodiment, two first end ribs 133 are located at both ends of the stabilizer surface 1 . The first wing ribs 131 include three, two ribs corresponding to the butt joints 14 , and diagonal ribs arranged along the fuselage interface.

As shown in Figure 3, the rudder 2 is located at the trailing edge of the vertical tail, and its function is to allow the aircraft to generate a yaw moment so that the aircraft has directional controllability. The rudder 2 includes a rudder beam 21, a rudder rib 22 and a rudder skin. Considering the structure, strength, weight, assembly, etc., the rudder 2 adopts a single beam structure with multiple rudder ribs 22 arranged along the span. Among them, the rudder rib 22 is connected to the rudder beam 21 through butt angle pieces, and the rudder skin is covered on the outside of the skeleton structure composed of the rudder beam 21 and the rudder rib 22; the rudder beam 21 is provided with a suspension joint 23; the rudder 2 It is mounted on the suspension support 15 of the stabilizer 1 via 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 span direction. In order to improve the stiffness of the rudder surface, two intersections are designed between the ribs. The fourth rib 223 is arranged, wherein the third rib 221 is a truss rib, the second end rib 222 and the fourth rib 223 are both foam sandwich ribs, the third rib 221 and the first rib 131 and the second The wing ribs 132 are arranged oppositely; the fourth wing ribs 223 arranged crosswise are arranged between the third wing ribs 221 and the second end ribs 222 . Advantageously, in this embodiment, weight reduction holes are opened in the fourth rib 223 and the rudder skin at the trailing edge of the rudder.

In this embodiment, the rudder 2 is provided with a foam front edge 24 connected to the rudder beam 21 . The principle of fixed-axis motion is adopted, the rotating axis is located at the leading edge of the rudder 2, and a four-point suspension is adopted. Four suspension supports 15 and four suspension joints 23 are provided. The rudder 2 is connected to the vertical tail trailing edge suspension support 15 through four suspension joints 23.

The assembly process of the vertical tail of this application is: positioning and bonding of the vertical tail and the fuselage butt joint 14, foam sandwich rib bonding, auxiliary beam bonding, landing gear tail wheel assembly assembly, tail wheel assembly and main beam bonding, front Edge bonding and rudder bonding.

The vertical tail of this application innovatively uses a glued truss-type double-beam structure of carbon fiber tube beam + rectangular beam + rib + composite butt corner piece; the main beam adopts the form of a circular tube, and the ribs pass through the composite corner piece Glued joints eliminate the need for extensive use of fasteners; the truss structure improves structural stability and reduces structural weight; it is designed using large-size lightweight composite materials. Except for special connection parts that are made of metal materials, most of the other structures are The use of composite materials greatly reduces the weight of the vertical tail; the support connection points with other structures are arranged directly on the wing ribs to avoid the structural weight increase caused by separately designed joints; the rudder is innovatively designed with cross-foam ribs to improve the stiffness of the rudder surface .

A second aspect of the present application provides a solar drone with the above-mentioned vertical tail.

Since the weight coefficient of the solar drone body is very low and the weight index is strictly controlled, a large number of lightweight carbon fiber reinforced composite laminate structures and composite sandwich structures are used in the vertical tail structure of this application, which greatly reduces the weight.

The vertical tail of this application and the solar drone with it have a simple structure and connection form, which is convenient for inspection, maintenance and disassembly; they adopt the form of a truss-type round tube beam, which greatly reduces the structural weight. The design of the round tube beam is in the structure The load-bearing capacity is stronger than ordinary box beams; it is economical and cheaper to manufacture than ordinary UAV vertical tails; the vertical tail structure can be used for long-endurance large-aspect-ratio solar-powered UAVs, and has been used in certain aircraft It has been used and successfully completed static tests, test flights and first flights, and is currently undergoing environmental tests.

The above are only specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application. All are covered by the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claims.

Claims (10)

1. A vertical tail, characterized in that it includes: Stabilizer (1), the stabilizer (1) includes 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, and the main beam (11) and the auxiliary beam (12) are both provided with butt joints (14) for connection with the fuselage, so The stabilizer rib (13) is connected to the main beam (11) and the auxiliary beam (12) respectively through butt angle pieces, and a suspension support (15) is provided on the stabilizer rib (13). The stabilizer skin is laid on the outside of the skeleton structure composed of the main beam (11), the auxiliary beam (12) and the stabilizer rib (13); Rudder (2), the rudder (2) includes a rudder beam (21), a rudder rib (22) and a rudder skin, wherein, The rudder rib (22) is connected to the rudder beam (21) through butt angle pieces, and the rudder skin is covered with a skeleton composed of the rudder beam (21) and the rudder rib (22) the exterior of a structure; The rudder beam (21) is provided with a suspension joint (23); The rudder (2) is installed on the 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 beam (11) is a circular tube beam made of carbon fiber composite material. 3. The vertical tail according to claim 2, characterized in that a tail wheel (17) is installed at the root of the main beam (11) through a tail wheel bracket (16), and the tail wheel bracket (16) includes an upper part Fixed parts and lower rotating parts, the upper fixed parts are glued to the main beam (11), the lower rotating parts are connected to the upper fixed parts through bolts, and the tailwheel (17) is installed on the lower part on rotating parts. 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. The 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) has a plurality of first ribs (131), a plurality of second ribs (132) arranged along the span direction, and Two first end ribs (133), wherein the first wing rib (131) is provided with a suspension support (15), the first wing rib (131) and the first end rib (133) They are all foam sandwich ribs, and the second wing ribs (132) are truss ribs. 7. The vertical tail according to claim 6, wherein the rudder rib (22) includes a plurality of third ribs (221) arranged along the span and two second end ribs (222), It also includes fourth wing ribs (223) arranged crosswise in pairs, wherein, The third wing rib (221) is a truss rib, the second end rib (222) and the fourth wing rib (223) are both foam sandwich ribs, and the third wing rib (221) and the The first wing rib (131) and the second wing rib (132) are arranged oppositely; The fourth ribs (223) arranged crosswise are provided between the third ribs (221) and the second end ribs (222). 8. The vertical tail according to claim 1, characterized in that the rudder (2) is provided with a foam leading edge (24) connected to the rudder beam (21). 9. The vertical tail according to claim 1, characterized in that there are four suspension supports (15) and four suspension joints (23). 10. A solar-powered drone, characterized by comprising the vertical tail according to any one of claims 1 to 9.