High-speed unmanned aerial vehicle and empennage thereof
By designing a high-speed drone tail with a stabilizer surface and a torsional servo, the problems of easy failure of the full-movement rudder surface and large space occupied by the control components during high-speed flight are solved, and the aerodynamic and control characteristics of the drone are improved.
Patent Information
- Application Number
- CN202411747883.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-29
- Publication Date
- 2025-02-14
AI Technical Summary
When high-speed drones fly at high speed, the full-movement rudder surface structure is prone to fail due to excessive local stress, and the control components occupy a lot of space in the fuselage, affecting the aerodynamic and control characteristics.
A high-speed drone tail wing including a torsion servo, a stabilizer surface, a rudder surface and a rudder surface control system is designed, which is fixed to the fuselage through the stabilizer surface. The rudder surface control system is rotatably connected to the stabilizer surface and outputs to the torsion servo. The end is fixed, and the servo is raised and twisted to the top of the stabilizer surface.
In high-speed flight, the tail wing is not prone to failure due to excessive local stress in the structure, and the space occupied by the control components is reduced, which improves the aerodynamic and operating characteristics of the drone.
Smart Images
Figure CN119429244A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aircraft technology, and in particular to a high-speed unmanned aerial vehicle and its tail wing. Background Art
[0002] The tail is a component used to balance, stabilize and control the aircraft, usually including vertical tail, horizontal tail, V-shaped tail, inverted Y-shaped tail, etc. The tail structure usually consists of two parts: stabilizer and rudder. The above tail is usually used on low-speed UAVs. High-speed UAV tails usually use full-moving rudders, eliminating the stabilizer structure. The full-moving rudder is connected to the drive unit through a connecting rod mechanism.
[0003] The fully movable rudders of high-speed UAVs are sensitive to changes in wind speed and density. Due to the reliance on aerodynamic forces, the fully movable rudders may fail due to excessive local structural stress in high-speed flight. In order to obtain better control characteristics, the fully movable rudders are generally arranged with four small aspect ratio wing rudders to increase the control area, so the control components need to occupy more fuselage space.
[0004] Therefore, how to improve the aerodynamic characteristics and maneuverability of UAVs during high-speed flight is a technical problem that technicians in this field urgently need to solve. Summary of the invention
[0005] The present application provides a high-speed UAV and its tail wing, which improve the aerodynamic characteristics and maneuverability characteristics of the UAV during high-speed flight.
[0006] In order to solve the above technical problems, this application provides the following technical solutions:
[0007] A high-speed UAV tail wing comprises: a torsion servo, a stabilizer, a rudder and a rudder control system; wherein the inner side of the stabilizer is used to be fixed to a fuselage, and the inner side of the rudder is attached to the outer side of the stabilizer; the rudder control system is rotatably connected to the upper surface of the stabilizer, and the outer end of the rudder control system is fixedly connected to the part of the upper surface of the rudder close to the inner side, and the inner end of the rudder control system is fixedly connected to the output end of the torsion servo, and the torsion servo is located in the UAV fuselage.
[0008] The high-speed UAV tail wing as described above, wherein preferably, the stabilizer surface comprises: a stabilizer surface left wall plate and a stabilizer surface right wall plate; wherein the stabilizer surface left wall plate and the stabilizer surface right wall plate are spliced and enclosed to form the stabilizer surface.
[0009] The high-speed UAV tail wing as described above, wherein preferably, the stabilizer surface also includes: two bearing supports, the inner and outer sides of the stabilizer surface have inwardly concave support mounting grooves, and the two ports of the rotating channel are located in the two support mounting grooves; one bearing support is located in one support mounting groove and is fixedly connected to the stabilizer surface, and the other bearing support is located in the other support mounting groove and is fixedly connected to the stabilizer surface; the rudder surface control system passes through a bearing support, the rotating channel and the other bearing support in sequence to realize the rotational connection between the rudder surface control system and the stabilizer surface.
[0010] As described above, in the high-speed UAV tail wing, preferably, the two bearing supports are located near the rear side of the stabilizer, and the rudder control system is supported by the two bearing supports.
[0011] The high-speed UAV tail wing as described above, wherein preferably, the rudder surface comprises: a rudder surface left wall plate and a rudder surface right wall plate; wherein the rudder surface left wall plate and the rudder surface right wall plate are spliced and enclosed to form the rudder surface.
[0012] As described above, in the high-speed UAV tail wing, preferably, the upper surface of the rudder surface has a downwardly concave mounting groove near the inner side, and the outer end of the rudder surface control system is fixed in the mounting groove.
[0013] The high-speed UAV tail wing as described above, wherein preferably, the rudder surface control system includes: a torsion shaft and a torsion shaft support ear; the torsion shaft passes through the rotation channel of the bearing support and the stabilizer surface; the outer end of the torsion shaft is fixedly connected to the torsion shaft support ear, and the torsion shaft support ear is fixed to the mounting groove of the rudder surface; the inner end of the torsion shaft is fixedly connected to the output end of the torsion servo.
[0014] In the high-speed UAV tail wing as described above, preferably, the outer end of the torsion shaft is fixedly connected to the torsion shaft support ear by means of screws.
[0015] The high-speed UAV tail wing as described above, wherein preferably, the material of the stabilizer left wall plate and the stabilizer right wall plate is aluminum alloy material, the material of the bearing support is alloy steel material, the material of the rudder left wall plate and the rudder right wall plate is aluminum alloy material, and the material of the torsion shaft and the torsion shaft support ear is alloy steel material.
[0016] A high-speed UAV comprises: a fuselage and any one of the high-speed UAV tail wings described above; two high-speed UAV tail wings are respectively fixed to two sides of the fuselage.
[0017] Compared with the above-mentioned background technology, since the high-speed UAV tail wing of the present application has a stabilizer surface, failure caused by excessive local structural stress will not occur under high-speed flight conditions. Also, since the present application raises the torsion servo of the high-speed UAV tail wing to above the stabilizer surface, the space occupied by the control components on the fuselage is reduced. Therefore, the high-speed UAV tail wing of the present application improves the aerodynamic characteristics and control characteristics of the UAV during high-speed flight. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.
[0019] Figure 1 is a schematic diagram of a high-speed UAV tail provided in an embodiment of the present application;
[0020] Figure 2 Schematic diagram of the stabilizer surface of the tail wing of a high-speed UAV provided in an embodiment of the present application;
[0021] Figure 3 The embodiment of the present invention provides a decomposition of the stabilizer surface of the high-speed UAV tail wing. Figure 1 ;
[0022] Figure 4 The embodiment of the present invention provides a decomposition of the stabilizer surface of the high-speed UAV tail wing. Figure 2 ;
[0023] Figure 5 Schematic diagram of the control surface of the tail wing of a high-speed UAV provided in an embodiment of the present application;
[0024] Figure 6 It is a schematic diagram of the rudder control system of the high-speed UAV tail wing provided in an embodiment of the present application. DETAILED DESCRIPTION
[0025] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. In addition, spatial relationship terms such as "upper", "lower", "left", "right", "front", "rear", etc. are used to facilitate description to explain the positional relationship between two components. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and are not to be construed as limitations on the present invention.
[0026] like Figure 1As shown, the present application provides a high-speed UAV tail wing, including: a torsion servo 10, a stabilizer 20, a rudder 30 and a rudder control system 40.
[0027] The inner side of the stabilizer 20 is used to be fixed to the fuselage, and the inner side of the rudder 30 is attached to the outer side of the stabilizer 20; the stabilizer 20 has a rotation channel running through both sides, and the rudder control system 40 passes through the rotation channel and is rotatably connected to the stabilizer 20, and the outer end of the rudder control system 40 is fixedly connected to the part of the upper surface of the rudder 30 close to the inner side, and the inner end of the rudder control system 40 is fixedly connected to the output end of the torsion servo 10, and the torsion servo 10 is located in the fuselage of the UAV. When in use, the torsion servo 10 is twisted, so that the rudder control system 40 rotates relative to the stabilizer 20, thereby driving the rudder 30 to rotate.
[0028] The present invention is fixed to the fuselage by the stabilizer 20, so as to support the torsion servo 10, the rudder surface 30 and the rudder surface control system 40. The stabilizer 20 supports the rudder surface control system 40, thereby optimizing the force transmission path of the tail wing and improving the reliability of the tail wing. In addition, compared with the full-moving rudder surface, the present invention has fewer rudder surfaces, thereby reducing the space occupied by the rudder surface control system 40 in the fuselage.
[0029] like Figure 2-Figure 4 As shown, the stabilizer 20 includes: a stabilizer left wall plate 21 and a stabilizer right wall plate 22; wherein, the stabilizer left wall plate 21 and the stabilizer right wall plate 22 are spliced and enclosed to form the stabilizer 20, and the shape of the stabilizer 20 is a thin airfoil and a symmetrical airfoil with a small aspect ratio. The stabilizer 20 mainly bears the aerodynamic load and the bending moment transmitted by the rudder 30, so the stabilizer 20 must have high strength and rigidity. In the present application, the material of the stabilizer left wall plate 21 and the stabilizer right wall plate 22 is aluminum alloy material. Under the condition of meeting the design requirements, the stabilizer 20 can use other materials or structural forms, such as aluminum alloy plus composite materials, all-composite materials, etc.
[0030] The stabilizer 20 also includes: two bearing supports 23; the inner and outer sides of the stabilizer 20 have inwardly concave support mounting grooves, and the two ports of the rotating channel are located in the two support mounting grooves; one bearing support 23 is located in one support mounting groove and is fixedly connected to the stabilizer 20, and the other bearing support 23 is located in the other support mounting groove and is fixedly connected to the stabilizer 20; the rudder control system 40 passes through one bearing support 23, the rotating channel and the other bearing support 23 in sequence to realize the rotation connection between the rudder control system 40 and the stabilizer 20. Optionally, the two bearing supports 23 are located near the rear side of the stabilizer 20, and the rudder control system 40 is supported by the two bearing supports 23, so that the rudder control system 40 can rotate more smoothly and stably. Optionally, the material of the bearing support 23 is alloy steel.
[0031] like Figure 3 As shown, the rudder surface 30 includes: a left rudder surface panel 31 and a right rudder surface panel 32; wherein, the left rudder surface panel 31 and the right rudder surface panel 32 are spliced and enclosed to form the rudder surface 30. The rudder surface 30 mainly bears aerodynamic loads. In order to ensure the control accuracy of the UAV, the rudder surface 30 must have sufficient strength and rigidity to meet the design technical requirements, and the rudder surface 30 must also be light in weight to reduce the moment of inertia and improve maneuverability. In this application, the material of the left rudder surface panel 31 and the right rudder surface panel 32 is aluminum alloy material, and other materials can be used if the design conditions are met.
[0032] Optionally, the upper surface of the rudder surface 30 has a downwardly concave mounting groove near the inner side, and the outer end of the rudder surface control system 40 is fixed to the mounting groove, so that the upper surface of the outer end of the rudder surface operating system 40 can be flush with the upper surface of the rudder surface 30, which is beneficial to the aerodynamic characteristics of the rudder surface 30. Optionally, there is a threaded hole in the mounting groove, and the outer end of the rudder surface control system 40 is fixed to the mounting groove by screws. Optionally, the mounting groove is close to the rear side of the rudder surface 30.
[0033] like Figure 4 As shown, the rudder control system 40 includes: a torsion shaft 41 and a torsion shaft support ear 42; the torsion shaft 41 passes through the rotation channel of the bearing support 23 and the stabilizer surface 20, and the torsion shaft 41 can rotate in the rotation channel of the bearing support 23 and the stabilizer surface 20; the outer end of the torsion shaft 41 is fixedly connected to the torsion shaft support ear 42, and the torsion shaft support ear 42 is fixed to the mounting groove of the rudder surface 30; the inner end of the torsion shaft 41 is fixedly connected to the output end of the torsion servo 10.
[0034] Optionally, the outer end of the torsion shaft 41 is fixedly connected to the torsion shaft support ear 42 by means of screws. Also optionally, the outer end of the torsion shaft 41 is fixedly connected to the torsion shaft support ear 42 by means of hexagon socket flat round head screws. The above connection method can withstand the torque and bending moment transmitted by the rudder surface 30. In the present application, the material of the torsion shaft 41 and the torsion shaft support ear 42 is alloy steel material. Other methods and materials can also be used if the design requirements are met. Also optionally, the shape of the torsion shaft support ear 42 is plate-shaped so that there is a larger contact area between the rudder control system 40 and the rudder surface 30.
[0035] The present application also provides a high-speed drone, comprising: a fuselage and two high-speed drone tail wings as described above; the two high-speed drone tail wings are respectively fixed to both sides of the fuselage. Optionally, the two high-speed drone tail wings are arranged in a V shape on both sides of the symmetric plane of the fuselage.
[0036] Since the high-speed UAV tail wing of the present application has a stabilizer, failure due to excessive local structural stress will not occur during high-speed flight. Also, since the present application raises the torsion servo of the high-speed UAV tail wing to above the stabilizer, the space occupied by the control components on the fuselage is reduced. Therefore, the high-speed UAV tail wing of the present application improves the aerodynamic characteristics and control characteristics of the UAV during high-speed flight.
[0037] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.
[0038] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.
Claims
1. A high-speed UAV tail wing, characterized in that: include: Torque steering gear, stabilizers, rudders and rudder control systems; Among them, the inner side of the stabilizer is used to be fixed to the fuselage, and the inner side of the rudder is attached to the outer side of the stabilizer; the rudder control system is rotatably connected to the upper surface of the stabilizer, and the outer end of the rudder control system is fixedly connected to the part of the upper surface of the rudder close to the inner side, and the inner end of the rudder control system is fixedly connected to the output end of the torsion servo, and the torsion servo is located inside the fuselage of the UAV.
2. The high-speed UAV tail wing according to claim 1, characterized in that: The stabilizer surface comprises: a stabilizer surface left wall plate and a stabilizer surface right wall plate; wherein the stabilizer surface left wall plate and the stabilizer surface right wall plate are spliced and enclosed to form the stabilizer surface.
3. The high-speed UAV tail wing according to claim 2, characterized in that: The stabilizer also includes: two bearing supports, the inner and outer sides of the stabilizer have inwardly concave support mounting grooves, and the two ports of the rotating channel are located in the two support mounting grooves; one bearing support is located in one support mounting groove and is fixedly connected to the stabilizer, and the other bearing support is located in the other support mounting groove and is fixedly connected to the stabilizer; the rudder control system passes through a bearing support, the rotating channel and the other bearing support in sequence to realize the rotating connection between the rudder control system and the stabilizer.
4. The high-speed UAV tail wing according to claim 3, characterized in that: The two bearing supports are located near the rear side of the stabilizer, and the rudder control system is supported by the two bearing supports.
5. The high-speed UAV tail wing according to claim 3 or 4, characterized in that: The rudder includes: A left wall plate of a rudder surface and a right wall plate of a rudder surface; wherein, the left wall plate of the rudder surface and the right wall plate of the rudder surface are spliced and enclosed to form the rudder surface.
6. The high-speed UAV tail wing according to claim 5, characterized in that: The upper surface of the rudder surface is provided with a downwardly concave mounting groove near the inner side, and the outer end of the rudder surface control system is fixed in the mounting groove.
7. The high-speed UAV tail wing according to claim 6, characterized in that: The rudder control system includes: a torsion shaft and a torsion shaft support ear; the torsion shaft passes through the bearing support and the rotation channel of the stabilizer surface; the outer end of the torsion shaft is fixedly connected to the torsion shaft support ear, and the torsion shaft support ear is fixed to the mounting groove of the rudder surface; the inner end of the torsion shaft is fixedly connected to the output end of the torsion servo.
8. The high-speed UAV tail wing according to claim 7, characterized in that: The outer end of the torsion shaft is fixedly connected to the torsion shaft support ear by means of screws.
9. The high-speed UAV tail wing according to claim 6, characterized in that: The material of the left wall plate and the right wall plate of the stabilizer is aluminum alloy material, the material of the bearing support is alloy steel material, the material of the left wall plate and the right wall plate of the rudder surface is aluminum alloy material, and the material of the torsion shaft and the torsion shaft support ear is alloy steel material.
10. A high-speed drone, characterized in that: include: A fuselage and a high-speed UAV tail as described in any one of claims 1 to 9; two high-speed UAV tails are respectively fixed to both sides of the fuselage.