Main wing tilting and folding mechanism for supporting multi-mode variant flight of aircraft

Abstract

The invention discloses a main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft. The main wing tilting and folding mechanism comprises a main bearing plate in a fuselage, a driving mechanism and a central wing, wherein the driving mechanism and the central wing are mounted on the main bearing plate in the fuselage; the driving mechanism comprises a transmission belt mechanism, a driving support arm and two driving rod groups; the transmission belt mechanism is mounted on a main bearing plate in the machine body; the driving support arm is fixed on a main bearing plate in the machine body in a sliding manner and is driven to move back and forth through a transmission belt mechanism; two ends of the driving rod group are respectively hinged with one side of the driving support arm and the corresponding outer wing; the outer wing is connected with the central wing through a crossed roller bearing; in the process that the transmission belt mechanism drives the driving supporting arms to move front and back, the driving rod sets are synchronously driven to move front and back, and therefore the outer wings are driven to rotate around the central wing with the crossed roller bearing as the support. The tilting wing unmanned aerial vehicle has enough high strength, rigidity and stability, and switching among multiple flight modes of the tilting wing unmanned aerial vehicle can be achieved.

Description

Technical Field

[0001] The invention belongs to the field of aircraft, and in particular relates to a main wing tilting and folding mechanism for supporting multi-modal variant flight of an aircraft. Background Art

[0002] Tilt-wing UAVs are a type of vertical take-off and landing UAVs. They change the direction of thrust by tilting their wings, thereby taking into account the high-speed, long-term cruising capabilities of fixed-wing UAVs and the vertical take-off and landing, fixed-point hovering capabilities of multi-rotor UAVs. Compared with other types of vertical take-off and landing UAVs such as compound vertical take-off and landing UAVs and tail-seat vertical take-off and landing UAVs, tilt-wing vertical take-off and landing UAVs have better cruising performance and more stable hovering performance, so they have greater application potential.

[0003] For example, the Chinese patent document with publication number CN107933909A discloses a high-speed and efficient tilt-wing unmanned aerial vehicle, in which the tilt-rotor and the tilt-wing surface can rotate along the rotating shaft through an actuating mechanism, and the tilt-rotor can be variable pitch. The Chinese patent document with publication number CN107042884A discloses a tilt-rotor UAV, including a fuselage, a tiltable wing, a tiltable horizontal tail, a vertical tail, a power system and a landing gear, in which the wing and the horizontal tail can be tilted at a large angle through a tilt mechanism, and the multi-rotor mode and the fixed-wing mode can be freely switched under the control of a control system.

[0004] However, since the wing carries most of the weight of the aircraft, the tilt mechanism needs to support the entire main wing to achieve three variant flight modes: level flight, tilt transition and quadrotor. It needs to withstand the large aerodynamic load from the main wing during the tilt and folding process, and needs to smoothly switch the tilt and folding process with the main wing, which places high demands on the strength, rigidity and stability of the tilt mechanism. Summary of the invention

[0005] The present invention provides a main wing tilt-folding mechanism supporting multi-mode variant flight of an aircraft, which has sufficiently high strength, rigidity and stability and can realize switching between multiple flight modes of a tilt-wing UAV.

[0006] A main wing tilting and folding mechanism supporting multi-modal variant flight of an aircraft comprises a main load-bearing plate in a fuselage, a driving mechanism and a central wing mounted on the main load-bearing plate in the fuselage;

[0007] The driving mechanism comprises a transmission belt mechanism, a driving arm and two driving rod groups; the transmission belt mechanism is installed on the main load-bearing plate in the fuselage; the driving arm is slidably fixed on the main load-bearing plate in the fuselage and driven to move forward and backward by the transmission belt mechanism; the two ends of the driving rod group are respectively hinged to one side of the driving arm and the corresponding outer wing;

[0008] The outer wing is connected to the central wing through a cross roller bearing; when the transmission belt mechanism drives the driving arm to move forward and backward, it synchronously drives the driving rod group to move forward and backward, thereby driving the outer wing to rotate around the central wing based on the cross roller bearing.

[0009] The present invention realizes the front and rear movement of the driving rod group relative to the fuselage as the driving control signal changes through the connection and combined movement among the transmission belt mechanism, the driving support arm and the driving rod group. The two ends of the driving rod group are respectively hinged to the driving support arm and the outer wing end, so that the final force acts on the outer wing, and the outer wing can be rotated relative to the fuselage around the cross roller bearing, thereby finally realizing the deformation effect of the wing.

[0010] Furthermore, the transmission belt mechanism includes a servo motor, a driving wheel, a transmission belt, a tensioning wheel mechanism, a driven wheel mechanism, a slide rail mechanism, and a transmission belt fixing base;

[0011] Among them, the servo motor and the driving wheel are fixed at the front of the main bearing plate in the fuselage, the driving wheel and the servo motor are limited and synchronized through the keyway, and the torsional force output by the servo motor is transmitted; the driven wheel mechanism is fixed at the rear of the main bearing plate in the fuselage, and the transmission belt is sleeved on the driving wheel and the driven wheel mechanism; the tensioning wheel mechanism is fixed on the main bearing plate in the fuselage to achieve the tensioning effect of the entire transmission belt; the slide rail mechanism is fixed in the middle of the main bearing plate in the fuselage to provide limiting support for the forward and backward movement of the driving arm; the transmission belt fixing base is used to fix the transmission belt and the driving arm.

[0012] Furthermore, the tensioning wheel mechanism comprises a tensioning wheel and a tensioning wheel bracket;

[0013] The tensioning wheel is fixed to the tensioning wheel bracket through a pin shaft, and the tensioning wheel bracket is fixed to the main load-bearing plate in the fuselage; a threaded hole structure is provided on the tensioning wheel bracket for installing a bolt push rod, and the tensioning wheel is moved up and down by adjusting the bolt push rod, thereby achieving the effect of tensioning the transmission belt.

[0014] Furthermore, the slide rail mechanism comprises two slide rails fixed on the main bearing plate in the fuselage and a slider arranged in the slide rails, and a cushion block with a through hole is arranged on the slider.

[0015] Furthermore, the two slide rails are symmetrically arranged on both sides of the transmission belt.

[0016] Further, the driving support arm comprises a driving arm and a ball stud;

[0017] Among them, the driving arm is fixed to the driving belt fixing base through the driving belt base connecting screw, so that the driving belt drives the driving arm to move forward and backward; the driving arm is fixedly connected to the slider after passing through the pad by the slider connecting screw, thereby providing limiting support for the forward and backward movement of the driving arm; the driving arm is fixedly connected to one end of the driving rod group through the ball head bolt, thereby driving the forward and backward movement of the driving rod group through the forward and backward movement of the driving support arm.

[0018] Furthermore, the driving rod assembly includes a carbon tube, a connecting joint, and a universal ball joint;

[0019] Wherein, both ends of the carbon tube are fixedly connected to the universal ball joint through a connecting joint, wherein the universal ball joint at one end is hinged to the driving arm, and the universal ball joint at the other end is hinged to the outer wing.

[0020] Furthermore, in the process of the transmission belt mechanism driving the driving arm to move forward and backward, the aircraft can be switched between the level flight wing spread mode, the tilt transition mode and the quadrotor mode.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. Compared with the traditional tilt-rotor technology and tilt-wing technology, the tilt-folding mechanism of the present invention adds a folding function. Through the power support of the transmission mechanism and the limit support of the cross-roller bearing, the rotor can tilt around the central main wing along with the outer wing, so that the aircraft can adapt to different flight environments while reducing the wingspan of the aircraft during take-off and landing, greatly reducing the space requirements during the take-off and landing of the aircraft.

[0023] 2. The tilting and folding mechanism of the present invention is simple, lightweight and highly reliable.

[0024] 3. The tilting and folding mechanism of the present invention is designed to be located inside the fuselage. Compared with the traditional tilting technology, it can ensure the smoothness of the wing surface, thereby improving the cruising performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the horizontal flight mode during the tilting and folding process of the wing of the present invention;

[0026] Figure 2 A schematic diagram of a tilt transition flight mode during the tilt folding process of the wing of the present invention;

[0027] Figure 3 A schematic diagram of a quadrotor mode during the tilting and folding process of the wing of the present invention;

[0028] Figure 4 It is a schematic diagram of the transmission belt mechanism;

[0029] Figure 5It is a schematic diagram of the driven wheel and the transmission belt base;

[0030] Figure 6 It is a schematic diagram of the tension wheel structure;

[0031] Figure 7 is a schematic diagram of the driving rod assembly;

[0032] Figure 8 Schematic diagram of the outer wing tilting principle.

[0033] In the figure: 1. Main load-bearing plate in fuselage; 2. Transmission belt mechanism; 21. servo motor; 22. Driving wheel; 23. Transmission belt; 24. Tensioning wheel mechanism; 241. Tensioning wheel; 242. Tensioning wheel bracket; 243. Tensioning wheel bracket connecting screw; 25. Driven wheel mechanism; 251. Driven wheel bracket connecting screw; 252. Driven wheel bracket; 253. Driven wheel; 26. Slide rail mechanism; 261. Slide rail; 262. Slide rail connecting screw; 263. Pad; 264. Slider; 27. Transmission belt fixing base; 3. Driving support arm; 31. Driving arm; 32. Transmission belt base connecting screw; 33. Slider connecting screw; 34. Ball stud; 4. Driving rod group; 41. Carbon tube; 42. Connecting joint; 43. Universal ball joint; 5. Cross roller bearing; 6. Outer wing; 7. Central wing. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be pointed out that the embodiments described below are intended to facilitate the understanding of the present invention and do not have any limiting effect on the present invention.

[0035] like Figures 1 to 3 As shown, a main wing tilting and folding mechanism supporting multi-mode variant flight of an aircraft corresponds to three flight modes, namely Figure 1 Level flight mode, Figure 2 The tilt transition flight mode and Figure 3 Quadrotor mode.

[0036] The main wing tilting and folding mechanism of the present invention mainly comprises a main bearing plate 1 in the fuselage, a transmission belt mechanism 2, a driving arm 3, a driving rod group 4, a cross roller bearing 5, an outer wing 6, and a central wing 7. The structure and connection method of each component will be specifically described below.

[0037] The main load-bearing plate 1 in the fuselage is fixed in the fuselage and remains stationary during the entire wing tilting process.

[0038] In practical application, the transmission belt mechanism 2 is specifically adopted as follows Figure 4 The structure shown is implemented as follows:

[0039] The transmission belt mechanism 2 includes a servo motor 21 , a driving wheel 22 , a transmission belt 23 , a tensioning wheel mechanism 24 , a driven wheel mechanism 25 , a slide rail mechanism 26 and a transmission belt fixing base 27 . The servo motor 21 is fixed to the main load-bearing plate 1 in the fuselage by bolts, and the servo motor 21 starts to rotate under the control of the control system; the driving wheel 22 and the servo motor 21 are limited and synchronized through the keyway to transmit the torsional force output by the servo motor 21; the transmission belt 23 provides transmission support for the movement of the transmission belt mechanism 2, and the torque provided by the servo motor 21 and the driving wheel 22 drives the forward and backward movement of the transmission belt 23; the tensioning wheel mechanism 24 is fixed to the main load-bearing plate 1 in the fuselage, which can achieve the tensioning effect of the entire transmission belt 23; the driven wheel mechanism 25 is fixed to the main load-bearing plate 1 in the fuselage, which can support the forward and backward movement of the transmission belt 23; the slide rail mechanism 26 is fixed to the main load-bearing plate 1 in the fuselage, and provides limited support for the forward and backward movement of the driving arm 3; the transmission belt fixing base 27 can be installed in conjunction with the transmission belt 23, and then fixed to the driving arm 3 by bolts to achieve the effect of fixing the driving arm 3 and the transmission belt 23.

[0040] Furthermore, the specific structure of the driven wheel mechanism 25 is as follows: Figure 5 The driven wheel mechanism 25 comprises a driven wheel bracket connecting screw 251, a driven wheel bracket 252 and a driven wheel 253, wherein the driven wheel bracket 252 is fixedly connected to the main bearing plate 1 in the fuselage through the driven wheel bracket connecting screw 251, and supports the driven wheel 253 to rotate; the driven wheel 253 is selected in the same manner as the driving wheel 22, but does not have a keyway, and is fixed to the driven wheel bracket 252 by a pin shaft.

[0041] Furthermore, the specific structure of the slide rail mechanism 26 is as follows: Figure 5 The slide rail mechanism 26 includes a slide rail 261, a slide rail connecting screw 262, a cushion block 263 and a slider 264, wherein the slide rail 261 is fixedly connected to the main load-bearing plate 1 in the fuselage through the slide rail connecting screw 262, providing a limit support for the forward and backward movement of the driving arm 3; the cushion block 263 is designed with a through hole, fixedly connected with the slider 264 and the driving arm 3, and plays a role of padding to ensure that the driving arm 3 and the transmission belt 23 are on the same horizontal line; the slider 264 has the same specifications as the slide rail 261, and is used in conjunction with it to play a role of fixing the driving arm.

[0042] Further, the specific structure of the tensioning wheel mechanism 24 is as follows: Figure 6The tensioning wheel mechanism 24 includes a tensioning wheel 241, a tensioning wheel bracket 242 and a tensioning wheel bracket connecting screw 243, wherein the tensioning wheel 241 is fixed to the tensioning wheel bracket 242 through a pin shaft, and the position of the tensioning wheel 241 can be adjusted through the threaded hole on the tensioning wheel bracket 242 to achieve the tensioning effect of the transmission belt 23; the tensioning wheel bracket 242 is fixedly connected to the main bearing plate 1 in the fuselage through the tensioning wheel bracket connecting screw 243, and the tensioning wheel bracket 242 is designed with a threaded hole structure for installing a bolt push rod. By adjusting the position of the bolt, the tensioning wheel 241 moves up and down, thereby achieving the tensioning effect of the transmission belt 23.

[0043] In practical application, the specific structure of the driving arm 3 is as follows: Figure 5 As shown, the details are as follows:

[0044] The driving arm 3 includes a driving arm 31, a transmission belt base connecting screw 32, a slider connecting screw 33 and a ball head bolt 34, wherein the driving arm 31 is fixedly connected to the transmission belt fixing base 27 through the transmission belt base connecting screw 32, so that the forward and backward movement of the transmission belt 23 drives the forward and backward movement of the driving arm 3; the driving arm 31 is fixedly connected to the slider 264 through the slider connecting screw 33, thereby providing limiting support for the forward and backward movement of the driving arm 3; the driving arm 31 is fixedly connected to the driving rod group 4 through the ball head bolt 34, so that the forward and backward movement of the driving arm 3 drives the driving rod group 4 to move forward and backward.

[0045] The driving arm 3 is designed with 4 bolt holes inside for connecting and fixing with the drive belt fixing base bolts 32; 4 through holes are designed on both sides for fixing with the slider connecting screws 33; and two bolt holes are designed on the outside of both sides for connecting and fixing with the driving rod group 4.

[0046] In practical applications, the specific structure of the driving rod group 4 is as follows: Figure 7 As shown, the details are as follows:

[0047] The driving rod group 4 includes a carbon tube 41, a connecting joint 42 and a universal ball joint 43, wherein the carbon tube 41 is the main body of the driving rod group 4, providing force transmission support for the tilt mechanism, and both ends of the carbon tube 41 are fixedly connected to the universal ball joint 43 through the connecting joint 42; the universal ball joint 43 at one end of the driving rod group 4 is hinged to the driving arm 3 through the ball stud 34, and the universal ball joint 43 at the other end is hinged to the outer wing 6 through the ball stud. Thus, the driving rod group 4 realizes force transmission support from the driving arm 3 to the outer wing 6.

[0048] In practical application, Figure 8 The structure shown is the tilt mechanism of the wing, which is as follows:

[0049] The tilt mechanism includes a driving rod group 4, a cross roller bearing 5, an outer wing 6 and a central wing 7, wherein the driving rod group 4 and the outer wing 6 are hinged by a ball bolt, so that the forward and backward movement of the driving rod group 4 drives the movement of the outer wing 6; the outer wing 6 is connected to the central wing 7 through the cross roller bearing 5, so that the driving rod group 4 pushes or pulls the outer wing 6 to rotate around the central wing 7 based on the cross roller bearing 5; the central wing 7 is fixedly connected to the main load-bearing plate 1 in the fuselage.

[0050] like Figures 1 to 3 As shown in FIG. 1 , the tilting and folding process of the wing is as follows:

[0051] During this tilting and folding process, the servo motor 21 starts to rotate under the control of the control system, and drives the driving wheel 22 to rotate synchronously. The rotation of the driving wheel 22 drives the transmission belt 23 to move forward. The transmission belt 2.3 drives the driving arm 3 through the transmission belt fixing base 27, and moves forward with the two slide rails 261 as support. The driving arm 3 pushes the driving rod group 4 on both sides to move forward. The driving rod group 4 pushes the outer wing 6 to rotate around the central wing 7 with the support of the cross roller bearing 5, and finally realizes the entire tilting and folding process.

[0052] The embodiments described above provide a detailed description of the technical solutions and beneficial effects of the present invention. It should be understood that the above are only specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, supplements and equivalent substitutions made within the scope of the principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A main wing tilting and folding mechanism supporting multi-mode variant flight of an aircraft, characterized in that: It comprises a main load-bearing plate (1) in a fuselage, and a driving mechanism and a central wing (7) installed on the main load-bearing plate (1) in the fuselage; The driving mechanism comprises a transmission belt mechanism (2), a driving arm (3) and two driving rod groups (4); the transmission belt mechanism (2) is mounted on the main load-bearing plate (1) in the fuselage; the driving arm (3) is slidably fixed on the main load-bearing plate (1) in the fuselage and driven to move forward and backward by the transmission belt mechanism (2); the two ends of the driving rod group (4) are respectively hinged to one side of the driving arm (3) and the corresponding outer wing (6); The outer wing (6) is connected to the central wing (7) via a cross roller bearing (5); when the transmission belt mechanism (2) drives the driving arm (3) to move forward and backward, it simultaneously drives the driving rod group (4) to move forward and backward, thereby driving the outer wing (6) to rotate around the central wing (7) based on the cross roller bearing (5).

2. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 1, characterized in that: The transmission belt mechanism (2) comprises a servo motor (21), a driving wheel (22), a transmission belt (23), a tensioning wheel mechanism (24), a driven wheel mechanism (25), a slide rail mechanism (26), and a transmission belt fixing base (27); The servo motor (21) and the driving wheel (22) are fixed to the front of the main bearing plate (1) in the fuselage, and the driving wheel (22) and the servo motor (21) are limited and synchronized through a keyway to transmit the torsional force output by the servo motor (21); the driven wheel mechanism (25) is fixed to the rear of the main bearing plate (1) in the fuselage, and the transmission belt (23) is sleeved on the driving wheel (22) and the driven wheel mechanism (25); the tensioning wheel mechanism (24) is fixed to the main bearing plate (1) in the fuselage to achieve the tensioning effect of the entire transmission belt (23); the slide rail mechanism (26) is fixed to the middle of the main bearing plate (1) in the fuselage to provide limited support for the forward and backward movement of the driving support arm (3); and the transmission belt fixing base (27) is used to fix the transmission belt (23) and the driving support arm (3).

3. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 2, characterized in that: The tensioning wheel mechanism (24) comprises a tensioning wheel (241) and a tensioning wheel bracket (242); The tension wheel (241) is fixed to the tension wheel bracket (242) via a pin shaft, and the tension wheel bracket (242) is fixed to the main load-bearing plate (1) in the fuselage; a threaded hole structure is provided on the tension wheel bracket (242) for installing a bolt push rod, and the tension wheel (241) is moved up and down by adjusting the bolt push rod, thereby achieving the effect of tensioning the transmission belt (23).

4. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 2, characterized in that: The slide rail mechanism (26) comprises two slide rails (261) fixed on the main load-bearing plate (1) in the fuselage and a slider (264) arranged in the slide rails (261), and a cushion block (263) with a through hole is arranged on the slider (264).

5. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 4, characterized in that: The two slide rails (261) are symmetrically arranged on both sides of the transmission belt (23).

6. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 4, characterized in that: The driving support arm (3) comprises a driving arm (31) and a ball stud (34); The driving arm (31) is fixed to the driving belt fixing base (27) by means of a driving belt base connecting screw (32), so that the driving belt (23) drives the driving arm (31) to move forward and backward; the driving arm (31) is fixedly connected to the sliding block (264) after passing through the cushion block (263) by means of a sliding block connecting screw (33), so as to provide a limiting support for the forward and backward movement of the driving arm (31); the driving arm (31) is fixedly connected to one end of the driving rod group (4) by means of a ball stud (34), so as to drive the forward and backward movement of the driving rod group (4) by means of the forward and backward movement of the driving support arm (3).

7. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 1, characterized in that: The driving rod group (4) comprises a carbon tube (41), a connecting joint (42), and a universal ball joint (43); Wherein, both ends of the carbon tube (41) are fixedly connected to the universal ball joint (43) through the connecting joint (42), wherein the universal ball joint (43) at one end is hinged to the driving support arm (3), and the universal ball joint (43) at the other end is hinged to the outer wing (6).

8. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 1, characterized in that: In the process of the transmission belt mechanism (2) driving the driving support arm (3) to move forward and backward, the aircraft is switched between the level flight wing spread mode, the tilt transition mode and the quadrotor mode.

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