A vertical tail and aircraft
By designing support ribs with open box structures, the problems of unstable center of gravity and low aerodynamic efficiency of the vertical tail fin were solved, thereby improving the stability and efficiency of the aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- ZHONGFU SHENYING CARBON FIBER
- Filing Date
- 2024-01-10
- Publication Date
- 2026-06-05
AI Technical Summary
Existing vertical tail fins suffer from problems such as unstable center of gravity, low aerodynamic efficiency, small structural space, and high rigidity requirements, resulting in poor flight performance of aircraft.
Design a vertical tail fin with a box-shaped support rib structure with openings. The openings of the support ribs face different directions to reduce the center of gravity and flight drag, avoid structural interference, and improve space utilization.
It improves the flight performance of the aircraft by simplifying the structure, reducing weight and flight drag, thereby enhancing the stability and efficiency of the aircraft.
Smart Images
Figure CN122144131A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of flight equipment technology, and more particularly to a vertical tail fin and an aircraft. Background Technology
[0002] As the application of drones and other aircraft becomes increasingly widespread, their mission payloads and flight durations are constantly increasing, leading to ever-higher requirements for their flight performance. The vertical tail is a crucial component in aircraft used for controlling heading and balance. It has high aerodynamic loads, limited structural space, and high rigidity requirements. However, existing vertical tails often suffer from problems such as unstable center of gravity and low aerodynamic efficiency, resulting in poor flight performance. Summary of the Invention
[0003] The main objective of this invention is to provide a vertical tail fin and an aircraft, which aims to solve the technical problem of poor flight performance of aircraft.
[0004] According to a first aspect of the present invention, a vertical tail fin is provided, mounted on the tail boom of an aircraft, the vertical tail fin comprising:
[0005] A support beam, the first end of which is connected to the tail support tube, and the second end of which is away from the tail support tube;
[0006] Multiple support ribs are connected to the support beam, and the multiple support ribs are arranged along the extension direction of the support beam;
[0007] The support rib is a box-shaped structure with an opening. The opening of the support rib located at the second end of the support beam faces the tail support tube, while the opening of the support rib located between the first and second ends of the support beam faces away from the tail support tube.
[0008] In some embodiments, along the extending direction of the tail support tube, the plurality of support ribs include a front edge rib, a middle rib, and a rear edge rib, and the support beam includes a tail front beam and a tail rear wall, the tail front beam being located between the front edge rib and the middle rib, and the tail rear wall being located between the middle rib and the rear edge rib.
[0009] In some embodiments, the front beam of the vertical tail is an I-shaped structure with a first groove and a second groove, and the rear wall of the vertical tail is a C-shaped structure with a third groove.
[0010] The end of the leading edge rib near the vertical tail beam extends into the first groove, and the side of the leading edge rib away from the vertical tail beam has an arc-shaped surface.
[0011] The two ends of the intermediate rib extend into the second groove and the third groove, respectively;
[0012] The end of the trailing edge rib closest to the rear wall of the tail is in contact with the rear wall of the tail, and the end of the trailing edge rib furthest from the rear wall of the tail has a sharp angle.
[0013] In some embodiments, the leading edge rib includes a first leading edge rib, a second leading edge rib, and at least one third leading edge rib. The first leading edge rib is located at a first end of the tail boom, the second leading edge rib is located at a second end of the tail boom, and the third leading edge rib is located between the first and second ends of the tail boom. The openings of the first and third leading edge ribs face away from the tail support tube, and the opening of the second leading edge rib faces the tail support tube; and / or,
[0014] The intermediate rib includes a first intermediate rib, a second intermediate rib, and at least one third intermediate rib. The first intermediate rib is located at a first end of the tail boom, the second intermediate rib is located at a second end of the tail boom, and the third intermediate rib is located between the first and second ends of the tail boom. The openings of the first and third intermediate ribs face away from the tail support tube, and the opening of the second intermediate rib faces the tail support tube; and / or,
[0015] The trailing edge ribs include a first trailing edge rib and a second trailing edge rib. The first trailing edge rib is located at the first end of the aft wall of the vertical tail, and the second trailing edge rib is located at the second end of the aft wall of the vertical tail. The openings of the first trailing edge rib and the second trailing edge rib face the tail support tube.
[0016] In some embodiments, the third leading edge rib is provided with a first through hole, and both the first intermediate rib and the third intermediate rib are provided with a second through hole.
[0017] In some embodiments, the ends of the first leading edge rib, the first intermediate rib, and the first trailing edge rib facing the tail support tube form arc-shaped recesses in a direction away from the tail support tube, and the arc-shaped recesses fit into the arc-shaped outer shell of the tail support tube.
[0018] In some embodiments, the vertical tail fin further includes a leading-edge skin that covers the outside of the leading-edge ribs. The leading-edge skin has a plurality of foam sandwich structures on its side facing the leading-edge ribs, and the foam sandwich structures are located between adjacent leading-edge ribs; and / or,
[0019] The vertical tail fin also includes a middle skin that covers the outside of the middle rib. The middle skin includes multiple honeycomb sandwich panels located between two adjacent middle ribs.
[0020] In some embodiments, the vertical tail fin further includes a rudder and a connector, the rudder including a trailing edge skin and a foam core, the trailing edge skin enclosing a trailing edge cavity, and the foam core filling the trailing edge cavity;
[0021] One end of the connector is fixedly connected to the rear wall of the vertical tail, and the other end of the connector is rotatably connected to the rear edge skin.
[0022] In some embodiments, the trailing edge rib includes at least one third trailing edge rib located between a first end and a second end of the aft wall of the vertical tail, the third trailing edge rib being disposed inside the rudder, and the opening of the third trailing edge rib facing away from the tail boom tube.
[0023] According to a second aspect of the invention, an aircraft is provided, the aircraft including a tail boom tube and a vertical tail fin as described in any of the above embodiments, the vertical tail fin being mounted on the tail boom tube.
[0024] The beneficial effects of this invention are:
[0025] The vertical tail fin provided by this invention features an open box-shaped structure that simplifies the support rib structure, makes it lightweight, and increases its rigidity. Furthermore, the support ribs at different locations have different opening orientations, which can reduce the center of gravity height and flight drag of the vertical tail fin, as well as prevent interference between structures within the vertical tail fin. This improves the space utilization rate inside the vertical tail fin and effectively enhances the flight performance of the aircraft. Attached Figure Description
[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0027] Figure 1 This is a schematic diagram illustrating a vertical tail fin and tail boom tube according to an exemplary embodiment;
[0028] Figure 2 This is a schematic diagram illustrating a support beam and support rib according to an exemplary embodiment;
[0029] Figure 3 This is a schematic diagram of an explosion of a vertical tail fin according to an exemplary embodiment;
[0030] Figure 4 This is a schematic diagram illustrating the front beam and rear wall of the tail section according to an exemplary embodiment.
[0031] Figure 5 This is a schematic diagram illustrating the leading edge rib and leading edge skin according to an exemplary embodiment;
[0032] Figure 6 This is a schematic diagram illustrating the intermediate rib and intermediate skin according to an exemplary embodiment;
[0033] Figure 7 This is a cross-sectional view of a honeycomb sandwich panel according to an exemplary embodiment;
[0034] Figure 8 This is a cross-sectional view of a rudder according to an exemplary embodiment;
[0035] Figure 9 This is a schematic diagram of a connector according to an exemplary embodiment.
[0036] In the diagram: 1-Support beam; 11-Front beam of the tail section; 111-First groove; 112-Second groove; 12-Rear wall of the tail section; 121-Third groove; 2-Support rib; 21-Leading edge rib; 211-First leading edge rib; 212-Second leading edge rib; 213-Third leading edge rib; 214-First through hole; 22-Intermediate rib; 221-First intermediate rib; 222-Second intermediate rib; 223-Third intermediate rib; 224-Second through hole; 23-Rear edge rib; 231-First rear edge Rib; 232-Second trailing edge rib; 233-Third trailing edge rib; 3-Leading edge skin; 31-Foam sandwich structure; 4-Intermediate skin; 41-Honeycomb sandwich panel; 411-First intermediate skin; 412-Second intermediate skin; 413-Honeycomb sandwich layer; 5-Rudder; 51-Large trailing edge skin; 511-First trailing edge skin; 512-Second trailing edge skin; 52-Foam core; 53-Recess; 6-Connector; 61-Fixing seat; 62-Third through hole; 7-Tail support tube. Detailed Implementation
[0037] As a crucial component in aircraft used for directional control and balance maintenance, the vertical tail fin experiences significant aerodynamic loads and requires high rigidity. Simultaneously, to reduce drag, the vertical tail fin's dimensions are limited, resulting in a small structural space. To simultaneously meet rigidity and dimensional requirements, the vertical tail fin typically incorporates internal frameworks such as beams and ribs. However, existing frameworks often suffer from high structural weight and low strength utilization, leading to instability and low aerodynamic efficiency during flight, ultimately resulting in poor flight performance.
[0038] To address the problems existing in related technologies, this invention provides a vertical tail fin and an aircraft. The vertical tail fin is mounted on the tail boom tube of the aircraft and includes a support beam and multiple support ribs connected to the support beam. A first end of the support beam is connected to the tail boom tube, and a second end is located away from the tail boom tube. The multiple support ribs are arranged along the extension direction of the support beam. The support ribs are box-shaped structures with openings. The openings of the support ribs located at the second end of the support beam face the tail boom tube, while the openings of the support ribs located between the first and second ends of the support beam face away from the tail boom tube. The box-shaped structure with openings makes the support rib structure simple, lightweight, and highly rigid. Furthermore, the different opening orientations of the support ribs at different locations can reduce the center of gravity height and flight drag of the vertical tail fin, and avoid interference between structures within the vertical tail fin, improving the internal space utilization of the vertical tail fin and effectively enhancing the flight performance of the aircraft.
[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the protection scope of the present invention.
[0040] like Figures 1 to 3 As shown, this embodiment provides a vertical tail fin. The vertical tail fin is connected to the main body of the aircraft through the tail boom tube 7. The vertical tail fin changes the flight direction of the aircraft by adjusting the deflection angle of part of the wing structure, thereby controlling the aircraft's ascent, yaw and stable flight.
[0041] like Figure 1 and Figure 2 As shown, the vertical tail fin includes a support beam 1 and multiple support ribs 2 connected to the support beam 1. The first end of the support beam 1 is connected to the tail boom tube 7, and the second end of the support beam 1 is away from the tail boom tube 7. The multiple support ribs 2 are arranged along the extending direction of the support beam 1. As an example, such as... Figure 1 and Figure 2 As shown, the extension direction of the tail support tube 7 ( Figure 1 (shown in the +x and -x directions) and the extension direction of support beam 1 ( Figure 1 The +y and -y directions shown are perpendicular to each other, and the extension direction of each support rib 2 is parallel to the extension direction of the tail boom tube 7. Multiple support ribs 2 and support beam 1 together form the skeleton of the vertical tail fin. Each support rib 2 is directly connected to the support beam 1, and the support rib 2 located at the first end of the support beam 1 is also directly connected to the tail boom tube 7. The connection method can be, for example, bonding, riveting, or a combination of bonding and riveting to further improve the strength of the connection. Of course, other connection methods are also possible, and there are no restrictions on this.
[0042] The number of supporting beams 1 and supporting ribs 2 is determined according to actual needs, and this embodiment does not impose any restrictions on this. For example, in one example, such as Figure 1 and Figure 2 As shown, the vertical tail fin includes two support beams 1 and three sets of support ribs 2. Along the extension direction of the tail boom tube 7, the two support beams 1 and the three sets of support ribs 2 are alternately connected. In another example (not shown in the attached figure), the vertical tail fin includes one support beam and two sets of support ribs. Along the extension direction of the tail boom tube, the two sets of support ribs are connected to both ends of the support beam.
[0043] The materials and manufacturing processes of the support beam 1 and support rib 2 can also be set according to actual needs. In this embodiment, both the support beam 1 and support rib 2 are composite material parts, such as carbon fiber, and are manufactured using a prepreg laying and curing process. The thickness of the support rib 2 can be, for example, 0.90-1.10 mm, to achieve both a smaller size (to reduce weight) and better rigidity. Of course, other materials and sizes can also be used, and there are no restrictions on this.
[0044] Each supporting rib 2 is a box-type structure with an opening, see reference. Figure 2 The support rib 2 has a bottom surface and a surrounding edge structure around the bottom surface, with the surrounding edge structure perpendicular to the bottom surface. The extension direction of the support beam 1 is perpendicular to the bottom surface of each support rib 2, so that the bottom surface of each support rib 2 can provide support to the support beam 1 through the surrounding edge structure.
[0045] The opening of the support rib 2 located at the second end of the support beam 1 faces the tail support tube 7, while the opening of the support rib 2 located between the first and second ends of the support beam 1 faces away from the tail support tube 7. For example, as shown... Figure 2 As shown, the support rib 2 located at the second end of the support beam 1, such as the second leading edge rib 212, has its opening facing the tail support tube 7, that is, towards... Figure 2 The +y direction shown serves two purposes: firstly, it prevents structural interference between the bottom surface of the support rib 2 and other structures of the vertical tail, improving the space utilization within the vertical tail; secondly, it smooths the outer surface of the vertical tail, reducing flight drag. The support rib 2, located between the first and second ends of the support beam 1, such as the third leading edge rib 213, has its opening facing away from the tail boom tube 7, i.e., towards... Figure 2 As shown in the -y direction, since the vertical tail is located above the tail boom tube during flight, this configuration can effectively lower the center of gravity of the vertical tail and improve the flight stability of the aircraft.
[0046] As can be seen from the above, the box-shaped structure with openings in the vertical tail provided in this embodiment makes the support rib structure simple, lightweight and rigid. At the same time, the support ribs at different positions have different opening orientations, which can reduce the center of gravity height and flight drag of the vertical tail, and avoid interference between the structures inside the vertical tail, thereby improving the space utilization rate inside the vertical tail and effectively improving the flight performance of the aircraft.
[0047] In one embodiment, reference Figure 1 and Figure 2 Along the extension direction of the tail support tube 7 ( Figure 2 (As shown in the x-direction), multiple support ribs 2 include a front edge rib 21, a middle rib 22, and a rear edge rib 23. The support beam 1 includes a vertical tail front beam 11 and a vertical tail rear wall 12. The vertical tail front beam 11 is located between the front edge rib 21 and the middle rib 22, and the vertical tail rear wall 12 is located between the middle rib 22 and the rear edge rib 23. As an example, Figure 2 As shown, the extension direction of the tail support tube is as follows Figure 2 As shown in the +x and -x directions, in flight, the +x direction is forward of the flight direction, and the -x direction is backward of the flight direction. Leading edge rib 21, intermediate rib 22, and trailing edge rib 23 are arranged sequentially along the -x direction. The vertical tail front spars 11 and vertical tail rear wall 12 are also arranged sequentially along the -x direction and are parallel to each other. The rear end of the leading edge rib 21 and the front end of the intermediate rib 22 are connected to both ends of the vertical tail front spars 11, and the rear end of the intermediate rib 22 and the front end of the trailing edge rib 23 are connected to both ends of the vertical tail rear wall 12. This creates a multi-vertical and multi-horizontal mesh-like skeleton inside the vertical tail, resulting in high structural strength and light weight. Along the extension direction of the tail boom 7, the vertical tail front spars 1 are located at 15% of the vertical tail length, and the vertical tail rear wall 12 are located at 55% of the vertical tail length, ensuring that the mass distribution of the vertical tail conforms to mechanical design and is more conducive to improving the flight performance of the aircraft.
[0048] In one embodiment, reference Figure 2 and Figure 4 The vertical tail front spars 11 has an I-shaped structure with a first groove 111 and a second groove 112. The vertical tail rear wall 12 has a C-shaped structure with a third groove 121. The end of the leading edge rib 21 near the vertical tail front spars 11 extends into the first groove 111 of the vertical tail front spars 11. The side of the leading edge rib 21 away from the vertical tail front spars 11 has an arc-shaped surface. During flight, the arc-shaped surface of the leading edge rib 21 is the foremost structure of the vertical tail. Setting this part of the structure as an arc-shaped surface makes the vertical tail have a streamlined shape, which conforms to the mechanical design of the vertical tail and can significantly reduce the flight drag of the aircraft. The two ends of the intermediate rib 22 extend into the second groove 112 and the third groove 121, respectively. The end of the trailing edge rib 23 near the vertical tail rear wall 12 fits against the vertical tail rear wall 12. The end of the trailing edge rib 23 away from the vertical tail rear wall 12 has a sharp corner.
[0049] As an example, such as Figure 4 As shown, the first groove 111 is located on the side of the front beam 11 facing away from the rear wall 12 of the tailstock, the second groove 112 is located on the side of the front beam 11 facing the rear wall 12 of the tailstock, and the third groove is located on the side of the rear wall 12 facing the front beam 11 of the tailstock. Figure 2 As shown, the rear end of the leading edge rib 21 extends into the first groove 111, the front end of the middle rib 22 extends into the second groove 112, and the rear end of the middle rib 22 extends into the third groove 121, with its surrounding structure fitting against the inner wall of the groove. The front end of the trailing edge rib 23 fits against the rear end face of the vertical tail rear wall 12. This arrangement effectively improves the connection reliability between the support rib 2 and the support beam 1. When the vertical tail is subjected to force in the flight direction, it can quickly disperse the impact force to each support beam 1 and support rib 2, enabling the vertical tail to withstand a strong impact force.
[0050] In one embodiment, reference Figures 1 to 3 The leading edge rib 21 includes a first leading edge rib 211, a second leading edge rib 212, and at least one third leading edge rib 213. The first leading edge rib 211 is located at the first end of the vertical tail front beam 11, the second leading edge rib 212 is located at the second end of the vertical tail front beam 11, and the third leading edge rib 213 is located between the first and second ends of the vertical tail front beam 11. The openings of the first leading edge rib 211 and the third leading edge rib 213 face away from the tail support tube 7, and the opening of the second leading edge rib 212 faces the tail support tube 7. As an example, such as Figures 1 to 3 As shown, the leading edge rib 21 includes a first leading edge rib 211, a second leading edge rib 212, and two third leading edge ribs 213, extending along the direction of the vertical tail front beam 11 away from the tail support tube 7. Figure 2 As shown in the -y direction), the first leading edge rib 211, two third leading edge ribs 213, and the second leading edge rib 212 are arranged sequentially, and the spacing between two adjacent leading edge ribs 21 is equal. The number of third leading edge ribs 213 can be set according to actual needs, for example, it can be one or three, or it can be other numbers, and there is no restriction on this.
[0051] In one embodiment, reference Figures 1 to 3 The intermediate rib 22 includes a first intermediate rib 221, a second intermediate rib 222, and at least one third intermediate rib 223. The first intermediate rib 221 is located at the first end of the tail beam 11, the second intermediate rib 222 is located at the second end of the tail beam 11, and the third intermediate rib 223 is located between the first and second ends of the tail beam 11. The openings of the first intermediate rib 221 and the third intermediate rib 223 face away from the tail support tube 7, while the opening of the second intermediate rib 222 faces the tail support tube 7. The arrangement and number of intermediate ribs 22 can be the same as those of the leading edge ribs 21 in the aforementioned embodiment, and will not be described again.
[0052] In one embodiment, reference Figures 1 to 3The trailing edge rib 23 includes a first trailing edge rib 231 and a second trailing edge rib 232. The first trailing edge rib 231 is located at the first end of the tail aft wall 12, and the second trailing edge rib 232 is located at the second end of the tail aft wall 12. The openings of the first trailing edge rib 231 and the second trailing edge rib 232 face the tail support tube 7. As an example, such as Figures 1 to 3 As shown, the first trailing edge rib 231 and the second trailing edge rib 232 are located at both ends of the vertical tail rear wall 12 and their opening directions are both towards the tail support tube. The opening direction of the first trailing edge rib 231 is opposite to the opening direction of the first leading edge rib 211 and the first intermediate rib 221, forming a misaligned support at the connection between the vertical tail fin and the tail support tube 7, which increases the structural stability.
[0053] In one embodiment, such as Figure 2 As shown, the third leading edge rib 213 is provided with a first through hole 214, and both the first intermediate rib 221 and the third intermediate rib 223 are provided with second through holes 224. As an example, as... Figure 2 As shown, the first through hole 214 is formed on the bottom surface of the third leading edge rib 213, which can further reduce the structural weight of the vertical tail. The second through hole 224 is formed on the bottom surface of the first intermediate rib 221 and the third intermediate rib 223. While reducing the structural weight of the vertical tail, it can also serve as a through hole for internal aviation cables, facilitating cable installation. The shape and size of the first through hole 214 and the second through hole 224 can be set according to actual needs, for example, they can be circular, and there is no limitation thereto.
[0054] In one embodiment, reference Figure 1 , Figure 2 , Figure 5 and Figure 6 The outer shell of the tail boom 7 is cylindrical, and the portion of the tail boom 7 that contacts the vertical tail fin is arc-shaped. To ensure a secure connection between the vertical tail fin and the tail boom 7, the ends of the first leading edge rib 211, the first intermediate rib 221, and the first trailing edge rib 231 facing the tail boom 7 form arc-shaped recesses in a direction away from the tail boom 7. These arc-shaped recesses fit snugly against the arc-shaped outer shell of the tail boom 7. As an example, such as... Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, the first leading edge rib 211, the first intermediate rib 221, and the first trailing edge rib 231 are in Figure 2 One end shown is oriented in the +y direction. Figure 2 The indentation is shown in the -y direction and is an arc-shaped indentation that fits the arc-shaped outer shell of the tail support tube 7. The bottom surfaces of the first leading edge rib 211 and the first intermediate rib 221 form the indented surface (see reference). Figure 5 and Figure 6 ).
[0055] In some embodiments, such as Figure 1 and Figure 4 As shown, the ends of the vertical tail front spar 11 and the vertical tail rear wall 12 that connect to the tail boom tube 7 are also recessed in a direction away from the tail boom tube 7, so as to further improve the connection effect between the vertical tail fin and the tail boom tube 7.
[0056] In one embodiment, reference Figure 1 , Figure 3 and Figure 6 The vertical tail fin also includes a central skin 4, which covers the outside of the central rib 22. The central skin 4 includes multiple honeycomb sandwich panels 41, which are located between adjacent central ribs 22. As an example, such as Figure 1 , Figure 3 and Figure 6 As shown, the intermediate skin 4 is covered by the intermediate rib 22. Figure 3 The middle skin 4 includes six honeycomb sandwich panels 41 on both sides in the +z and -z directions, and three honeycomb sandwich panels 41 on each side of the middle rib 22. In the arrangement direction of the middle rib 22, two honeycomb sandwich panels 41 are provided between each two adjacent middle ribs 22. At this time, the honeycomb sandwich panels 41, the middle rib 22, the front beam 11 of the vertical tail and the rear wall 12 of the vertical tail form a closed box structure, which effectively improves the torsional stiffness and strength of the vertical tail fin.
[0057] In one embodiment, reference Figure 6 and Figure 7 The honeycomb sandwich panel 41 includes a first intermediate skin 411, a second intermediate skin 412, and a honeycomb sandwich layer 413. The first intermediate skin 411 is located on the side of the honeycomb sandwich panel 41 facing inward toward the vertical tail fin, and the second intermediate skin 412 is located on the side of the honeycomb sandwich panel 41 facing outward toward the vertical tail fin. The first intermediate skin 411 forms a protrusion facing inward toward the vertical tail fin, and the interior of the protrusion is filled by the honeycomb sandwich layer 413. The included angle α between the first intermediate skin 411 and the second intermediate skin 412 can be, for example, 15°-35°.
[0058] In one embodiment, reference Figure 1 , Figure 3 and Figure 5 The vertical tail fin also includes a leading-edge skin 3, which covers the outside of the leading-edge rib 21. Multiple foam sandwich structures 31 are provided on the side of the leading-edge skin 3 facing the leading-edge rib 21, and the foam sandwich structures 31 are located between two adjacent leading-edge ribs 21. As an example, such as... Figure 1 , Figure 3 and Figure 5 As shown, the leading edge skin 3 covers the front side of the leading edge rib 21, and the leading edge rib 21 is located on... Figure 3As shown, on both sides in the +z and -z directions, the outer surface of the leading edge skin 3 is a smooth surface, and three foam core structures 31 are provided on the inner surface of the leading edge skin 3. In the arrangement direction of the leading edge ribs 21, a foam core structure 31 is provided between every two adjacent leading edge ribs 21. The specific structure of the foam core structure 31 can be found in [reference needed]. Figure 7 This will not be elaborated upon here.
[0059] Since the leading edge skin 3 is located at the forefront of the vertical tail in the flight direction, it is subjected to a large impact force during flight. The middle skin 4 is located in the middle of the vertical tail and is subjected to a smaller impact force. Therefore, a stronger and more stable foam sandwich structure 31 can be set on the leading edge skin 3 to improve the stress resistance of the vertical tail. A lighter honeycomb sandwich panel 41 can be set in the middle skin 4 to reduce the structural weight of the vertical tail.
[0060] During the flight of the aircraft, the leading edge skin 3, which is located at the forefront in the flight direction of the vertical tail, is first subjected to the impact force such as flight drag. The impact force is transmitted through the leading edge skin 3 to each leading edge rib 21, and then to the vertical tail front spars 11, the middle rib 22 and the vertical tail rear wall 12. Finally, it is transmitted to the tail support tube 7 through the first end of the vertical tail front spars 11 and the vertical tail rear wall 12 connected to the tail support tube 7.
[0061] In one embodiment, reference Figure 1 , Figure 3 and Figure 8 The vertical tail fin also includes a rudder 5 and a connector 6. The rudder 5 includes a trailing edge skin 51 and a foam core 52. The trailing edge skin 51 encloses and forms a trailing edge cavity, and the foam core 52 fills the trailing edge cavity. One end of the connector 6 is fixedly connected to the rear wall 12 of the vertical tail, and the other end of the connector 6 is rotatably connected to the trailing edge skin 51.
[0062] In one example, such as Figure 1 and Figure 3 As shown, the rudder 5 is rotatably connected to the rear wall 12 of the vertical tail via the connector 6. During flight, the rudder 5 can rotate at a certain angle to adjust the aircraft's flight direction. Figure 3 and Figure 9 As shown, the connector 6 includes a fixing seat 61, which is used to fix the connector to the tail fin rear wall 12. For example, the fixing seat can be installed on the tail fin rear wall 12 by means of bolt connection. The front end of the rudder 5 is provided with a recess 53 corresponding to the connector 6. Each recess 53 is provided with a connecting post. The end of the connector 6 facing the rudder 5 is provided with a third through hole 62. The connector 6 extends into the corresponding recess 53 and rotates with the connecting post to realize the rotational connection with the rudder 5.
[0063] In one example, such as Figure 3 and Figure 8As shown, the rudder 5 includes a trailing edge skin 51, which comprises a first trailing edge skin 511 covering the front end of the rudder 5 and a second trailing edge skin 512 covering the middle and rear ends of the rudder 5. The first trailing edge skin 511 and the second trailing edge skin 512 together form a teardrop-shaped trailing edge cavity, which is filled with a foam core 52 to ensure that the rudder 5 has strong structural strength and improve the maneuverability of the aircraft. The foam core 52 can be made of, for example, polymethacrylamide foam. In some embodiments, an adhesive film is also provided between the foam core 52 and the trailing edge skin 51 to allow the trailing edge skin 51 and the foam core 52 to be integrally cured and molded.
[0064] In one embodiment, reference Figure 1 and Figure 2 The trailing edge rib 23 includes at least one third trailing edge rib 233 located between the first and second ends of the vertical tail rear wall 12. The third trailing edge rib 233 is disposed inside the rudder 5, and the opening of the third trailing edge rib 233 faces away from the tail boom tube 7. As an example, such as Figure 1 and Figure 2 As shown, the trailing edge rib 23 also includes two third trailing edge ribs 233. The third trailing edge ribs 233 are located between the first and second ends of the vertical tail aft wall 12, that is, between the first trailing edge rib 231 and the second trailing edge rib 232. The vertical distance between each pair of adjacent trailing edge ribs 23 is equal. The opening of the third trailing edge rib 213 faces away from the tail boom tube 7 to reduce the center of gravity height of the vertical tail fin. The third trailing edge ribs 233 are located inside the foam core 52 of the rudder 5 to provide support for the rudder 5 and enhance its structural strength. The number of third trailing edge ribs 233 can be set according to actual needs, for example, it can be one or three, or other numbers, without limitation.
[0065] This embodiment provides an aircraft, including a tail boom and a vertical tail fin as described in any of the above embodiments, the vertical tail fin being mounted on the tail boom. In one embodiment, as... Figure 1 and Figure 2 As shown, the tail support tube 7 is a cylindrical tube with an internal cavity, and its tail end ( Figure 1 The end shown in the +x direction is a streamlined, closed end with a smooth surface, which reduces flight drag. A fourth through hole is provided on the tail support tube 7 at a position corresponding to the second through hole 224 of the first intermediate rib 221. The interior of the tail support tube 7 and the interior of the vertical tail fin are connected through the second through hole 224 and the fourth through hole, facilitating the installation of aviation cables inside the aircraft into the vertical tail fin. The fourth through hole also helps to balance pressure. The aircraft can be, for example, a drone or other flying equipment; there are no restrictions.
[0066] The embodiments described in this specification are merely examples of implementations of the inventive concept. The scope of protection of this invention should not be considered as limited to the specific forms stated in the embodiments. The scope of protection of this invention also includes equivalent technical means that can be conceived by those skilled in the art based on the inventive concept.
Claims
1. A vertical tail fin, characterized in that, Mounted on the tail boom of the aircraft, the vertical tail fin includes: A support beam, the first end of which is connected to the tail support tube, and the second end of which is away from the tail support tube; Multiple support ribs are connected to the support beam, and the multiple support ribs are arranged along the extension direction of the support beam; The support rib is a box-shaped structure with an opening. The opening of the support rib located at the second end of the support beam faces the tail support tube, while the opening of the support rib located between the first and second ends of the support beam faces away from the tail support tube.
2. The vertical tail fin according to claim 1, characterized in that, Along the extension direction of the tail support tube, the plurality of support ribs include a front edge rib, a middle rib and a rear edge rib, and the support beam includes a tail front beam and a tail rear wall. The tail front beam is located between the front edge rib and the middle rib, and the tail rear wall is located between the middle rib and the rear edge rib.
3. The vertical tail fin according to claim 2, characterized in that, The front beam of the vertical tail is an I-shaped structure with a first groove and a second groove, and the rear wall of the vertical tail is a C-shaped structure with a third groove. The end of the leading edge rib near the vertical tail beam extends into the first groove, and the side of the leading edge rib away from the vertical tail beam has an arc-shaped surface. The two ends of the intermediate rib extend into the second groove and the third groove, respectively; The end of the trailing edge rib closest to the rear wall of the tail is in contact with the rear wall of the tail, and the end of the trailing edge rib furthest from the rear wall of the tail has a sharp angle.
4. The vertical tail fin according to claim 2 or 3, characterized in that, The leading edge rib includes a first leading edge rib, a second leading edge rib, and at least one third leading edge rib. The first leading edge rib is located at the first end of the vertical tail front beam, the second leading edge rib is located at the second end of the vertical tail front beam, and the third leading edge rib is located between the first end and the second end of the vertical tail front beam. The openings of the first leading edge rib and the third leading edge rib face away from the tail support tube, and the opening of the second leading edge rib faces the tail support tube. And / or, The intermediate rib includes a first intermediate rib, a second intermediate rib, and at least one third intermediate rib. The first intermediate rib is located at the first end of the tail beam, the second intermediate rib is located at the second end of the tail beam, and the third intermediate rib is located between the first end and the second end of the tail beam. The openings of the first intermediate rib and the third intermediate rib face away from the tail support tube, and the opening of the second intermediate rib faces the tail support tube. And / or, The trailing edge ribs include a first trailing edge rib and a second trailing edge rib. The first trailing edge rib is located at the first end of the aft wall of the vertical tail, and the second trailing edge rib is located at the second end of the aft wall of the vertical tail. The openings of the first trailing edge rib and the second trailing edge rib face the tail support tube.
5. The vertical tail fin according to claim 4, characterized in that, The third leading edge rib is provided with a first through hole, and the first intermediate rib and the third intermediate rib are both provided with a second through hole.
6. The vertical tail fin according to claim 4, characterized in that, The first leading edge rib, the first intermediate rib, and the first trailing edge rib form an arc-shaped recess at one end facing the tail support tube and moving away from the tail support tube. The arc-shaped recess fits into the arc-shaped outer shell of the tail support tube.
7. The vertical tail fin according to claim 2 or 3, characterized in that, The vertical tail fin also includes a leading-edge skin that covers the outside of the leading-edge ribs. The leading-edge skin has multiple foam core structures on its side facing the leading-edge ribs, and these foam core structures are located between adjacent leading-edge ribs; and / or, The vertical tail fin also includes a middle skin that covers the outside of the middle rib. The middle skin includes multiple honeycomb sandwich panels located between two adjacent middle ribs.
8. The vertical tail fin according to claim 2, characterized in that, The vertical tail fin also includes a rudder and a connector. The rudder includes a trailing edge skin and a foam core. The trailing edge skin encloses a trailing edge cavity, and the foam core fills the trailing edge cavity. One end of the connector is fixedly connected to the rear wall of the vertical tail, and the other end of the connector is rotatably connected to the rear edge skin.
9. The vertical tail fin according to claim 8, characterized in that, The trailing edge rib includes at least one third trailing edge rib located between the first end and the second end of the aft wall of the vertical tail, the third trailing edge rib being disposed inside the rudder, and the opening of the third trailing edge rib facing away from the tail boom tube.
10. An aircraft, characterized in that, The aircraft includes a tail boom tube and a vertical tail fin as described in any one of claims 1-9, the vertical tail fin being mounted on the tail boom tube.