A main wing tilting and folding mechanism supporting multi-modal variant flight of an aircraft

Abstract

The present invention discloses a main wing tilting and folding mechanism that supports multi-modal variant flight of an aircraft, comprising 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; the driving mechanism comprises a transmission belt mechanism, a driving arm and two driving rod groups; the transmission belt mechanism is mounted 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; the outer wing is connected to the central wing via a cross roller bearing; in the process of the transmission belt mechanism driving the driving arm to move forward and backward, the transmission belt mechanism synchronously drives the driving rod group to move forward and backward, thereby driving the outer wing to rotate around the central wing with the cross roller bearing as the support. The present invention has sufficiently high strength, rigidity and stability, and can realize switching between multiple flight modes of a tilt-wing UAV.

Description

Technical Field

[0001] The present 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 drones are a type of vertical take-off and landing (VTOL) drone. By tilting their wings to redirect thrust, they combine the high-speed, long-range cruising capabilities of fixed-wing drones with the vertical take-off and landing (VTOL) and fixed-point hovering capabilities of multi-rotor drones. Compared to other types of VTOL drones, such as combined VTOL and tail-seat VTOL drones, tilt-wing VTOL drones offer improved cruising performance and more stable hovering, thus holding greater potential for application.

[0003] For example, Chinese patent publication CN107933909A discloses a high-speed, high-efficiency tilt-wing unmanned aerial vehicle (UAV). The tilt-rotor and tilt-wing surfaces can be rotated along a rotation axis via an actuating mechanism, allowing the tilt-rotor to have variable pitch. Chinese patent publication CN107042884A discloses a tilt-rotor UAV comprising a fuselage, tiltable wings, a tiltable horizontal tail, a vertical tail, a power system, and landing gear. Both the wings and horizontal tail can be tilted through large angles via a tilt mechanism, enabling flexible switching between multi-rotor and fixed-wing modes under control of a control system.

[0004] However, since the wings carry 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. During the tilt and folding process, it needs to withstand the large aerodynamic load from the main wing, and needs to smoothly switch the tilt and folding process with the main wing. This 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 tilting and folding mechanism that supports multi-modal variant flight of an aircraft. The mechanism 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 includes 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 drive mechanism includes a transmission belt mechanism, a drive arm, and two drive rod groups; the transmission belt mechanism is mounted on the main load-bearing plate inside the fuselage; the drive arm is slidably fixed to the main load-bearing plate inside the fuselage and driven to move forward and backward by the transmission belt mechanism; the two ends of the drive rod group are respectively hinged to one side of the drive arm and the corresponding outer wing;

[0008] The outer wings are connected to the central wings through cross roller bearings. 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 wings to rotate around the central wing based on the cross roller bearings.

[0009] The present invention realizes the connection and combined movement between the transmission belt mechanism, the driving support arm and the driving rod group, so that the driving rod group can move forward and backward relative to the fuselage as the driving control signal changes. 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 achieving 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 load-bearing plate in the fuselage, and the driving wheel and the servo motor are limited and synchronized through the keyway to transmit the torsional force output by the servo motor; the driven wheel mechanism is fixed at the rear of the main load-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 load-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 load-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 includes 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 includes two slide rails fixed on the main load-bearing plate in the fuselage and a slider arranged in the slide rails, and a pad with a through hole is provided on the slider.

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

[0016] Furthermore, the driving arm includes a driving arm and a ball stud;

[0017] Among them, the driving arm is fixed to the transmission belt fixing base through the transmission belt base connecting screw, so that the transmission 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, 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 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 wings. This allows the aircraft to adapt to different flight environments while reducing the wingspan of the aircraft during takeoff and landing, greatly reducing the space requirements during the aircraft's takeoff and landing process.

[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 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 and folding process of the wing of the present invention;

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

[0028] Figure 4 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 Schematic diagram of the tensioning wheel structure;

[0031] Figure 7 Schematic diagram of the driving rod group;

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

[0033] In the figure: 1. Main load-bearing plate in the fuselage; 2. Transmission belt mechanism; 21. Servo motor; 22. Driving wheel; 23. Transmission belt; 24. Tensioner mechanism; 241. Tensioner; 242. Tensioner bracket; 243. Tensioner 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 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. Center wing. DETAILED DESCRIPTION

[0034] The present invention will be described in further detail below with reference to the accompanying drawings and examples. It should be noted that the following examples are intended to facilitate 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-modal variant flight of an aircraft corresponds to three flight modes, namely Figure 1 Level flight mode, Figure 2 Tilt transition flight mode and Figure 3 Quadrotor mode.

[0036] The main wing tilt-and-fold mechanism of the present invention primarily comprises a main load-bearing plate 1 within the fuselage, a transmission belt mechanism 2, a drive arm 3, a drive rod assembly 4, cross-roller bearings 5, outer wings 6, and a center wing 7. The structure and connection of each component are described in detail 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 inside 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 transmission belt 23 to move back and forth; the tensioning wheel mechanism 24 is fixed on the main load-bearing plate 1 inside the fuselage, which can achieve the tensioning effect of the entire transmission belt 23; the driven wheel mechanism 25 is fixed on the main load-bearing plate 1 inside the fuselage, which can support the back and forth movement of the transmission belt 23; the slide rail mechanism 26 is fixed on the main load-bearing plate 1 inside the fuselage, providing limiting support for the back and forth 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 includes a driven wheel bracket connecting screw 251, a driven wheel bracket 252, and a driven wheel 253. The driven wheel bracket 252 is fixedly connected to the main load-bearing plate 1 in the fuselage via the driven wheel bracket connecting screw 251 and supports the rotation of the driven wheel 253. The driven wheel 253 is of the same type as the driving wheel 22, but does not have a keyway and is fixed to the driven wheel bracket 252 by a pin.

[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 pad 263, and a slider 264. The slide rail 261 is fixedly connected to the main load-bearing plate 1 in the fuselage via the slide rail connecting screw 262, providing limited support for the forward and backward movement of the drive arm 3. The pad 263 is designed with a through hole and is fixedly connected to the slider 264 and the drive arm 3, playing a cushioning role to ensure that the drive arm 3 is on the same horizontal line as the transmission belt 23. The slider 264 has the same specifications as the slide rail 261 and is used in conjunction with it to fix the drive arm.

[0042] Furthermore, 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. The tensioning wheel 241 is fixed to the tensioning wheel bracket 242 via a pin. 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 load-bearing plate 1 in the fuselage via the tensioning wheel bracket connecting screw 243. 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 fixed 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 drive rod assembly 4 includes a carbon tube 41, a connecting joint 42, and a universal ball joint 43. The carbon tube 41 serves as the main body of the drive rod assembly 4, providing force transmission support for the tilt mechanism. Both ends of the carbon tube 41 are fixedly connected to the universal ball joint 43 via the connecting joint 42. The universal ball joint 43 at one end of the drive rod assembly 4 is hinged to the drive arm 3 via a ball stud 34, while the universal ball joint 43 at the other end is also hinged to the outer wing 6 via a ball stud. Thus, the drive rod assembly 4 transmits force support from the drive 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 drive rod group 4, a cross roller bearing 5, an outer wing 6 and a central wing 7, wherein the drive rod group 4 and the outer wing 6 are hinged by a ball bolt, so that the forward and backward movement of the drive 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 drive 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 inside the fuselage.

[0050] like Figures 1 to 3 As shown in the figure, 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 support of two slide rails 261. 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, finally realizing 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 scope of protection of the present invention.

Claims

1. A main wing tilting and folding mechanism supporting multi-modal variant flight of an aircraft, characterized in that: It comprises a main load-bearing plate (1) in the fuselage, and a driving mechanism and a central wing (7) mounted 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 wings (6) are connected to the central wings (7) via cross roller bearings (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 wings (6) to rotate around the central wing (7) based on the cross roller bearings (5); 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); wherein the servo motor (21) and the driving wheel (22) are fixed to the front of the main load-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 ( The main bearing plate (1) 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); the transmission belt fixing base (27) is used to fix the transmission belt (23) and the driving support arm (3).

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 tensioning wheel mechanism (24) comprises a tensioning wheel (241) and a tensioning wheel bracket (242); The tensioning wheel (241) is fixed to the tensioning wheel bracket (242) via a pin shaft, and the tensioning wheel bracket (242) is fixed to the main load-bearing plate (1) in the fuselage; a threaded hole structure is provided on the tensioning wheel bracket (242) for installing a bolt push rod, and the tensioning wheel (241) is moved up and down by adjusting the bolt push rod, thereby achieving the effect of tensioning the transmission belt (23).

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

4. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 3, characterized in that: The two slide rails (261) are symmetrically arranged on both sides of the transmission belt (23).

5. The main wing tilting and folding mechanism for supporting multi-mode variant flight of an aircraft according to claim 3, characterized in that: The driving 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) through the 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 slider (264) after passing through the pad (263) using the slider connecting screw (33), thereby providing 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) through the ball head bolt (34), thereby driving the forward and backward movement of the driving rod group (4) through the forward and backward movement of the driving support arm (3).

6. 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 assembly (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).

7. 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 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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