Wingtip tilting structure of vertical take-off and landing aircraft
By adopting a wingtip tilting structure in a vertical takeoff and landing aircraft and connecting the tilting servo to the wing pivot, the problem of increased servo load on the wing root tilting mechanism is solved, achieving low power consumption and high reliability wing tilting, improving flight safety and reducing maintenance costs.
Patent Information
- Application Number
- CN202520684070.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-11
- Publication Date
- 2026-02-03
- Estimated Expiration
- 2035-04-11
AI Technical Summary
The existing wing root tilt mechanism of vertical takeoff and landing aircraft increases the load on the servo motors during flight state transitions, has high power requirements and low reliability, and is difficult to maintain the wing tilt state.
It adopts a wingtip tilt structure, including winglets and wingtip nacelles, which are connected to the wing pivot via tilt servos to achieve wingtip tilting, reducing power requirements and improving reliability.
It reduces the load requirements of the tilt servo, improves the flight safety and reliability of the aircraft, simplifies the maintenance of the wing in tilt mode, and reduces maintenance costs.
Smart Images
Figure CN223865095U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the field of aircraft technology, especially vertical take-off and landing aircraft's wing tip tilt structure. BACKGROUND
[0002] The vertical take-off and landing aircraft (VTOL) can take off and land vertically like a multi-rotor aircraft or a helicopter, and can fly at high speed like a fixed-wing aircraft, and has very broad application prospects.
[0003] The current vertical take-off and landing aircraft mostly uses tiltable structure to improve the propeller efficiency and flight performance, wherein the tilting mechanism can be located at the wing root or the wing tip. The tilting mechanism located at the wing root can rotate the whole wing, and the tilting mechanism located at the wing tip can rotate the wing tip nacelle. However, when the aircraft needs to be converted in the flight state, tilting the whole wing by using the wing root tilting method will increase the load of the steering engine, require a large power supply, and have low reliability, and the wing tilting state is difficult to maintain, which cannot meet the current market demand.
[0004] Therefore, it is necessary to provide a wing tip tilting structure which can realize wing tilting by using wing tip tilting. TECHNICAL PROBLEM
[0005] The main purpose of the utility model is to provide a wing tip tilting structure of a vertical take-off and landing aircraft in view of the deficiencies of the prior art.
[0006] To achieve the above-mentioned purpose, the utility model provides the following technical scheme.
[0007] The wing tip tilting structure of the vertical take-off and landing aircraft comprises a wing tip and a wing assembled in a matched manner with the wing tip, the wing tip comprises a wing tip winglet and a wing tip nacelle connected with a winglet skeleton, the wing tip nacelle is provided with a nacelle trailing edge, one side of the wing tip nacelle close to the winglet is provided with a wing tip rib, a vertical direction of one end of the wing tip rib away from the nacelle trailing edge is provided with a nacelle front frame, a vertical direction of one end of the wing tip rib close to the nacelle trailing edge is provided with a nacelle rear frame, and one side of the wing tip nacelle away from the winglet is provided with a nacelle rib; a sleeve hole is arranged on the nacelle rib, and a tilting bearing is sleeved and installed in the sleeve hole; a wing rotating shaft is arranged in the wing, an upper end of the wing rotating shaft passes through the tilting bearing and enters the wing tip nacelle, and a tilting steering engine is installed on the wing rotating shaft and connected with the nacelle front frame and the nacelle rear frame respectively.
[0008] As a preferred scheme of the wing tip tilting structure of the vertical take-off and landing aircraft, the outer peripheral surface of the winglet and the outer peripheral surface of the wing tip nacelle are both provided with a skin.
[0009] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the wing tip winglet is filled with composite carbon fiber fabric and foam sandwich.
[0010] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the wing tip rib is glued with wing tip foam through structural glue.
[0011] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the bottom of the nacelle front frame is fixedly connected with the nacelle rib.
[0012] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the outer periphery of the wing shaft is sleeved with a limiting ring for fixing the tilt rudder.
[0013] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the wing is provided with a front beam and a rear beam, the front beam and the rear beam are located below the two sides of the nacelle rib, and the lower end of the wing shaft is fixedly connected with the top of the front beam through fastening screws.
[0014] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the front beam and the rear beam are both provided with gaps between the bottom of the nacelle rib.
[0015] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, the wing box section located between the front beam and the rear beam in the wing is filled with foam.
[0016] As the vertical take-off and landing aircraft wing tip tilt structure of the utility model, a beam rib is transversely installed between the front beam and the rear beam, one end of the beam rib is fixedly connected with the front beam, and the other end of the beam rib is fixedly connected with the rear beam.
[0017] Compared with the prior art, the utility model has at least the following beneficial effects:
[0018] ①The wing tip tilt structure is simple, the required power is low, the load of the tilt rudder can be reduced, the demand for electric quantity can be reduced, and the reliability is high. ②The rudder is installed on the wing shaft and connected with the nacelle front frame and the nacelle rear frame, after the tilt rudder is connected with the wing shaft and the wing tip nacelle, the tilt rudder is started to work, and the wing tip is tilted and rotated. ③The flight state of the aircraft is changed. The tilt state of the wing is easy to maintain, and the flight safety of the aircraft is improved.
[0019] The maintenance cost is low. BRIEF DESCRIPTION OF DRAWINGS
[0020] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely exemplary embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort, wherein:
[0021] Figure 1 This is a schematic diagram of the wingtip tilting structure of the vertical takeoff and landing aircraft of this utility model;
[0022] Figure 2 for Figure 1 Schematic diagram of the mid-wingtip structure;
[0023] Figure 3 for Figure 2 A cross-sectional diagram;
[0024] Figure 4 for Figure 1 A schematic diagram of the structure of the mid-wing;
[0025] Figure 5 for Figure 1 A cross-sectional diagram;
[0026] Figure 6 This is a schematic diagram showing the connection between the wing pivot and the wing front spars of the vertical take-off and landing aircraft of this utility model.
[0027] The reference numerals in the figures include:
[0028] 1. Winglet; 2. Wingtip nacelle; 3. Nacelle trailing edge; 4. Wingtip rib; 5. Nacelle rib; 6. Nacelle front frame; 7. Nacelle rear frame; 8. Sleeve hole; 9. Tilting bearing; 10. Wing; 11. Wing pivot; 12. Limiting ring; 13. Front spars; 14. Rear spars; 15. Wing box section; 16. Beam rib; 17. Fastening screw. Detailed Implementation
[0029] The technical solutions in the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are merely exemplary embodiments of this utility model, and not the only embodiments.
[0030] like Figures 1 to 6 As shown, the wingtip tilt structure of the vertical takeoff and landing aircraft includes the wingtip and the wing 10 assembled with it. The wingtip includes a winglet 1 and a wingtip nacelle 2 connected to the winglet 1 frame. The winglet 1 is connected to the wingtip nacelle 2 frame by structural adhesive. The wingtip nacelle 2 is made of composite material carbon fiber fabric skin and aluminum alloy frame. The outer peripheral surfaces of both the winglet 1 and the wingtip nacelle 2 are covered with skin.
[0031] The wing tip winglet 1 is filled with a composite carbon fiber fabric and a foam sandwich, wherein the composite carbon fiber fabric can provide the wing tip winglet 1 with stronger structural strength and rigidity, the foam sandwich improves the overall structural efficiency of the wing tip winglet 1, and the combination of the composite carbon fiber fabric and the foam sandwich can make the wing tip winglet 1 have high efficient load transfer, high specific stiffness, and shock absorption and durability.
[0032] The wing tip nacelle 2 is provided with a nacelle trailing edge 3, the wing tip nacelle 2 is provided with a wing tip rib 4 near one side of the wing tip winglet 1, the wing tip rib 4 is glued with a wing tip foam through structural glue, the wing tip nacelle 2 is provided with a nacelle rib 5 away from the wing tip winglet 1, the nacelle rib 5 is provided with a sleeve hole 8, and the sleeve hole 8 is sleeved and installed with a tilting bearing 9.
[0033] The wing tip rib 4 is vertically installed with a nacelle front frame 6 at one end away from the nacelle trailing edge 3, and is vertically installed with a nacelle rear frame 7 at one end close to the nacelle trailing edge 3.
[0034] The wing 10 is externally covered with a composite carbon fiber fabric skin and internally provided with a beam rib 16 and a foam sandwich, wherein the composite carbon fiber fabric and the foam sandwich have the same functions as described above, and in this application scenario, the functions are to improve the related performance of the wing 10, that is, to make the wing 10 have stronger structural strength and rigidity, improve the overall structural efficiency of the wing 10, and make the wing 10 have high efficient load transfer, high specific stiffness, and shock absorption and durability after the combination of the composite carbon fiber fabric and the foam sandwich. The beam rib 16 is provided to make the wing 10 have stronger fastening performance, improve the structural strength and safety performance of the wing 10.
[0035] The wing 10 is provided with a wing rotating shaft 11, the upper end of the wing rotating shaft 11 passes through the tilting bearing 9 sleeved and installed in the sleeve hole 8 of the nacelle rib 5 and enters the wing tip nacelle 2, so as to realize the assembly and connection of the wing tip and the wing 10.
[0036] The tilting rudder is installed on the wing rotating shaft 11 and connected with the nacelle front frame 6 and the nacelle rear frame 7, wherein the connection of the tilting rudder with the nacelle front frame 6 and the nacelle rear frame 7 means that the tilting rudder is connected with the wing tip nacelle 2, and after the tilting rudder is connected with the wing rotating shaft 11 and the wing tip nacelle 2, the tilting rudder is started to work, the wing tip is tilted and rotated, and the flight state of the aircraft is changed. Such wing tip tilting structure is simple, requires low power, can reduce the load of the tilting rudder, reduce the demand for electric quantity, has strong reliability, and the tilting state of the wing 10 is easy to maintain, thereby improving the flight safety of the aircraft, and reducing the maintenance cost.
[0037] In order to strengthen the fixing effect of the tilting rudder in the wing tip nacelle 2, the bottom of the nacelle front frame 6 is fixedly connected with the nacelle rib 5, so that the position of the tilting rudder connected with the nacelle front frame 6 is fixed, and the tilting rudder is not easy to deviate in the wing tip nacelle 2
[0038] Since the tilting rudder needs to be installed on the wing pivot 11, the position of the tilting rudder on the wing pivot 11 needs to be fixed, and therefore a limiting ring 12 for fixing the tilting rudder is sleeved on the outer periphery of the wing pivot 11, the limiting ring 12 can be rotated according to the position of the tilting rudder on the wing pivot 11 and the relative position of the limiting ring 12 on the tilting rudder is fixed, generally, the position of the limiting ring 12 on the wing pivot 11 is located at the bottom of the position of the tilting rudder on the wing pivot 11.
[0039] The wing 10 is provided with a front beam 13 and a rear beam 14, the front beam 13 and the rear beam 14 are located below the two sides of the nacelle rib 5, and the lower end of the wing pivot 11 is fixedly connected with the top of the front beam 13 through a fastening screw 17, so that the wing pivot 11 is fixedly connected with the front beam 13, and then the wing tip is assembled with the wing 10.
[0040] The front beam 13 and the rear beam 14 are both provided with a gap between the bottom of the nacelle rib 5, so that the wing tip and the wing 10 are provided with a gap, and the wing tip has a rotating space during tilting and does not affect the state of the wing 10.
[0041] The bottom of the front beam 13 and the rear beam 14 is inserted on the aircraft to realize the connection between the wing 10 and the aircraft.
[0042] The wing box section of the wing 10 located on the two sides of the front beam 13 and the rear beam 14 is filled with foam, wherein the foam improves the overall structural efficiency of the wing box section 15, and also improves the safety performance of the wing box section 15, thereby improving the overall structural safety of the wing 10.
[0043] The beam rib 16 for strengthening the structural strength of the wing 10 is transversely installed between the front beam 13 and the rear beam 14, one end of the beam rib 16 is fixedly connected with the front beam 13, and the other end of the beam rib 16 is fixedly connected with the rear beam 14.
[0044] The above only describes the preferred embodiments of the present application, and the protection scope of the present application is not limited to the above embodiments, and any technical solution falling within the concept of the present application belongs to the protection scope of the present application. It should be noted that, for ordinary skilled persons in the art, some improvements and decorations without departing from the principles of the present application are also considered to be within the protection scope of the present application.
Claims
1. A wingtip tilting structure for a vertical takeoff and landing aircraft, comprising a wingtip and a wing (10) assembled in conjunction with the wingtip, characterized in that, The wingtip includes a winglet (1) and a wingtip nacelle (2) connected to the winglet (1) frame. The wingtip nacelle (2) is provided with a nacelle trailing edge (3). A wingtip rib (4) is provided on the side of the wingtip nacelle (2) near the winglet (1). A nacelle front frame (6) is installed vertically on the end of the wingtip rib (4) away from the nacelle trailing edge (3). A nacelle rear frame (7) is installed vertically on the end of the wingtip rib (4) near the nacelle trailing edge (3). A nacelle rib (5) is provided on the side of the wingtip nacelle (2) away from the winglet (1). The nacelle rib (5) is provided with a sleeve hole (8), and a tilt bearing (9) is sleeved and installed in the sleeve hole (8); A wing pivot (11) is provided inside the wing (10). The upper end of the wing pivot (11) passes through the tilt bearing (9) and enters the wingtip nacelle (2). The tilt servo is installed on the wing pivot (11) and is connected to the front frame (6) and the rear frame (7) of the nacelle, respectively.
2. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 1, characterized in that, The outer surfaces of the winglets (1) and the wingtip nacelles (2) are both covered with skin.
3. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 1, characterized in that, The wingtip winglet (1) is filled with composite carbon fiber fabric and foam core.
4. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 1, characterized in that, The wingtip rib (4) contains wingtip foam bonded with structural adhesive.
5. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 1, characterized in that, The bottom of the nacelle front frame (6) is fixedly connected to the nacelle rib (5).
6. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 1, characterized in that, The outer periphery of the wing pivot (11) is fitted with a limiting ring (12) for fixing the tilt servo.
7. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 6, characterized in that, The wing (10) is provided with a front spar (13) and a rear spar (14). The front spar (13) and the rear spar (14) are located on both sides below the nacelle rib (5). The lower end of the wing pivot (11) is fixedly connected to the top of the front spar (13) by fastening screws (17).
8. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 7, characterized in that, The front beam (13) and the rear beam (14) are both separated from the bottom of the stub rib (5) by a gap.
9. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 7, characterized in that, The wing box section (15) located on both sides of the front spar (13) and the rear spar (14) of the wing (10) is filled with foam.
10. The wingtip tilting structure of the vertical takeoff and landing aircraft according to claim 7, characterized in that, A beam rib (16) is installed laterally between the front beam (13) and the rear beam (14). One end of the beam rib (16) is fixedly connected to the front beam (13), and the other end of the beam rib (16) is fixedly connected to the rear beam (14).