Wing rotating device and tilt-rotor aircraft

Abstract

The utility model relates to a wing rotating device and a tilt-rotor aircraft, belongs to the technical field of aerospace, and solves the problems that in the prior art, a tilt-rotor aircraft is large in wingspan and not easy to transport and store. The device comprises a rotating unit, the rotating unit comprises a driving assembly and a rotating ring; the driving assembly comprises a rotary driving structure and a gear rack structure, and the gear rack structure is arranged on an output shaft of the rotary driving structure; the inner side of the rotating ring is connected with the output end of the gear rack structure; the upper part of the rotating ring is connected with the wing. According to the utility model, the angles of the wings can be accurately switched, and the transportation is convenient.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a wing rotation device and a tiltrotor aircraft. Background Technology

[0002] Tiltrotor aircraft combine the advantages of fixed-wing aircraft and helicopters, and are now widely used in both military and civilian fields. They are also moving from low-load to high-load aircraft, and from unmanned to manned aircraft. However, tiltrotor aircraft have the disadvantage of taking up a lot of space during transportation and storage due to their large wingspan. Utility Model Content

[0003] Based on the above analysis, the present invention aims to provide a wing rotation device and a tiltrotor aircraft to solve the problem that tiltrotor aircraft have a large wingspan and are difficult to transport and store.

[0004] The objective of this utility model is mainly achieved through the following technical solutions:

[0005] In a first aspect, this utility model provides a wing rotation device, including a rotation unit, the rotation unit being used to rotate the wing relative to the fuselage about a vertical axis;

[0006] The rotating unit includes a driving component and a rotating ring with a vertical axis; the driving component includes a rotary drive structure with a gear and rack structure, the gear and rack structure being disposed on the output shaft of the rotary drive structure, the output axis of the rotary drive structure being horizontal, and the rotary drive structure being fixed to the machine body.

[0007] Furthermore, the gear rack structure includes a bevel gear and a bevel gear rack;

[0008] The bevel gear is connected to the rotary drive structure and rotates under the drive of the rotary drive structure; the bevel gear rack meshes with the bevel gear; the bevel gear rack is connected to the rotating ring and drives the rotating ring to rotate.

[0009] Furthermore, the bevel gear rack has a fan-shaped structure with a central angle of 120°.

[0010] Furthermore, it also includes a connecting unit, which includes a wing-body joint; the lower part of the wing-body joint is connected to the fuselage, and the upper part of the wing-body joint is connected to the rotating ring.

[0011] Furthermore, it also includes a limiting unit; the limiting unit includes a limiting pressure block and a limiting stop block;

[0012] The upper part of the wing-body joint is provided with an annular receiving groove, the side wall of the rotating ring is provided in the annular receiving groove, and the limiting pressure block is provided on both sides of the side wall.

[0013] The inner and outer sides of the sidewall are respectively provided with annular grooves, and the limiting pressure block can slide within the annular groove; the limiting stop block is disposed within the annular groove.

[0014] Furthermore, the limiting unit also includes a U-shaped friction plate and a flat friction plate;

[0015] The U-shaped friction plate is disposed at the bottom of the annular receiving groove, and the U-shaped friction plate is used to limit the radial movement of the rotating ring;

[0016] The flat friction plate is disposed at the lower part of the limiting pressure block and is used to limit the axial movement of the rotating ring.

[0017] Furthermore, it also includes a locking unit, which includes a quick-release pin;

[0018] The rotating ring is provided with a first pin hole, and the wing-body joint is provided with a second pin hole; the quick-release pin can be inserted into the first pin hole and the second pin hole to lock the wing state.

[0019] Furthermore, the connection unit also includes a single-ear connector; the single-ear connector is disposed on the upper part of the rotating ring, and the single-ear connector is used to connect with the wing.

[0020] A second aspect of this utility model provides a tiltrotor aircraft, including a fuselage and a wing; the wing-body joint of the wing has a fuselage connection portion;

[0021] The fuselage is connected to the fuselage connection part.

[0022] Furthermore, the slewing drive structure of the wing rotation device is located on the longitudinal center plane of the fuselage;

[0023] The conical gear rack of the wing rotation device is configured such that one side of the longitudinal center plane of the fuselage is a 105° sector and the other side of the longitudinal center plane of the fuselage is a 15° sector.

[0024] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0025] (1) Compared with the prior art, the present invention sets the driving components as a rotary drive structure and a gear rack structure. The rotary drive structure drives the gear rack structure to drive the rotating ring to rotate. The rotating ring is connected to the wing. The rotating ring drives the wing to rotate, realizing the switching of the wing between 0° and 90°. The wing rotation device of the present invention uses a gear rack structure as the transmission structure, which has high reliability. It enables the wing to accurately switch to 0° or 90° during transportation, so that the wing can be switched from the normal flight use state to the parking state. This greatly reduces the overall lateral size of the aircraft, reduces the transportation and parking space, improves the usage scenarios of tiltrotor aircraft and improves parking and transportation efficiency.

[0026] (2) Compared with the prior art, the present invention sets the gear rack structure as a bevel gear and a bevel gear rack. The bevel gear rotates under the drive of the rotary drive structure, driving the bevel gear rack to rotate, so as to realize the rotation of the rotating ring. The transmission efficiency is high and the transmission is stable. The bevel gear rack matches the rotational motion of the rotating ring and is set as a sector structure. The central angle of the sector is set to 120° to ensure that the tiltrotor aircraft has a safe distance from both ends of the large bevel gear rack when parked in the normal flight state position and the transport and storage state position.

[0027] (3) In this utility model, the limiting unit uses a limiting block set on the rotating ring and a limiting pressure block set on the wing joint to limit the rotation of the rotating ring to prevent the rotating ring from rotating excessively; a flat friction plate is used to limit the up and down movement of the rotating ring, and a U-shaped friction plate and a limiting block are used to limit the radial movement of the rotating ring. In addition, the U-shaped friction plate and the flat friction plate also have the function of reducing the rotational friction coefficient of the rotating ring.

[0028] (4) In this utility model, the locking unit uses a quick-release pin to fix the state of the rotating ring. The quick-release pin is inserted into the first pin hole of the rotating ring and the second pin hole of the wing joint to fix the rotating ring. This is simple, quick and improves the operating efficiency.

[0029] (5) The connection unit of this utility model includes a wing-body joint and a single-ear joint. The wing-body joint is used to connect the fuselage, and the single-ear joint is used to connect the wing. The wing-body joint is located at the lower part of the rotating ring and has a supporting function for the entire wing and the wing rotation device. The load of the wing is transferred to the fuselage through the wing-body joint and the single-ear joint.

[0030] (6) Considering the efficient use of space and weight distribution, the servo is located on the longitudinal center plane of the fuselage; the entire conical gear rack is a 120° fan shape, with 105° distributed on one side and 15° distributed on the other side, with the longitudinal center plane of the fuselage as the boundary. The entire wing is required to have a 90° turning angle, with a 15° safety distance on both sides.

[0031] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages will become apparent from the description or be learned by practicing this invention. The objectives and other advantages of this invention can be realized and obtained from the details specifically pointed out in the text and accompanying drawings. Attached Figure Description

[0032] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0033] Figure 1 This is a schematic diagram of the wing rotation device in Example 1;

[0034] Figure 2 This is a schematic diagram of the servo motor and bevel gear in Example 1;

[0035] Figure 3 This is a schematic diagram of the rotating ring, connecting unit, limiting unit, and locking unit of Embodiment 1;

[0036] Figure 4 This is a schematic diagram of the rotating ring structure in Example 1;

[0037] Figure 5 This is a schematic diagram of the wing-body joint and limiting unit in Embodiment 1;

[0038] Figure 6 This is a schematic diagram of the wing during normal operation in Example 1;

[0039] Figure 7 This is a structural schematic diagram of the wing in the parking and transport states of Example 1;

[0040] Figure 8 This is a schematic diagram of the wing structure of Example 2;

[0041] Figure 9 This is one of the partial structural schematic diagrams of the tiltrotor aircraft in Example 3;

[0042] Figure 10 This is the second structural schematic diagram of the tiltrotor aircraft in Example 3.

[0043] Figure label:

[0044] 1-Wing rotating device, 11-Rotating unit, 111-Servo, 1111-Servo support, 1112-Bearing, 112-Bevel gear, 113-Bevel gear rack, 1131-Rack and pinion connector, 114-Rotating ring, 1141-Inner annular groove, 1142-Outer annular groove, 1143-First pin hole, 12-Connecting unit, 121-Wing-body joint, 1211-Annular receiving groove, 1212-Fuselage connecting part, 1213-Second pin hole, 122-Single ear joint, 13-Limiting unit, 131-Limiting pressure block, 132-Limiting stop, 133-U-shaped friction plate, 134-Flat friction plate, 14-Quick release pin, 2-Wing joint, 3-Wing body, 4-Fuselage. Detailed Implementation

[0045] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0046] Example 1

[0047] Tiltrotor aircraft have the disadvantage of large wingspan, requiring a lot of space during transportation and storage. In flight, the centerline of the aircraft's wing is at 90° to the fuselage 4. When parked or in transport, the centerline of the wing is horizontal or collinear with the fuselage 4, i.e., at 0°. Therefore, the wing rotation device 1 needs to switch the wing between 0° and 90°.

[0048] A specific embodiment of this utility model is as follows: Figure 1 As shown, a wing rotation device 1 is disclosed, including a rotation unit 11.

[0049] The rotating unit 11 includes a rotary drive structure and a rotating ring 114; the drive assembly includes a rotary drive structure and a gear and rack structure, the gear and rack structure being mounted on the output shaft of the servo motor 111.

[0050] The inner side of the rotating ring 114 is connected to the output end of the gear rack structure, and the upper part of the rotating ring 114 is connected to the wing.

[0051] Compared with the prior art, this embodiment sets the driving components as a rotary drive structure and a gear and rack structure. The rotary drive structure drives the gear and rack structure to rotate the rotating ring 114. The rotating ring 114 is connected to the wing, and the rotating ring 114 drives the wing to rotate, realizing the switching of the wing between 0° and 90°. The wing rotation device 1 of this embodiment uses a gear and rack structure as the transmission structure, which has high reliability and enables the wing to rotate accurately to 0° or 90° during transportation. This allows the wing to change from the normal flight use state to the parking state, greatly reducing the overall lateral size of the aircraft, reducing the transportation space, improving the usage scenarios of tiltrotor aircraft and improving parking and transportation efficiency.

[0052] For example, such as Figure 2 As shown, the slewing drive structure is a servo motor 111. The servo motor 111 has a servo motor support 1111. The servo motor support 1111 is fixed to the fuselage 4. Considering efficient space utilization and weight distribution, the servo motor 111 is located on the longitudinal center plane of the fuselage.

[0053] The gear rack structure includes a bevel gear 112 and a bevel gear rack 113.

[0054] The bevel gear 112 is connected to the servo motor 111 and rotates under the drive of the servo motor 111.

[0055] A tapered ball bearing 1112 is fitted onto the output shaft of the servo motor 111. A bearing sleeve is provided on the outside of the tapered ball bearing 1112. The bearing sleeve is provided with a bearing cover plate and a bearing support, and the bearing support is mounted on the fuselage 4. The output shaft of the servo motor 111 is connected to the bevel gear 112 via a keyway.

[0056] The bevel gear rack 113 meshes with the bevel gear 112, and the bevel gear rack 113 moves under the drive of the bevel gear 112. The bevel gear rack 113 is connected to the rotating ring 114 through the rack connector 1131, driving the rotating ring 114 to rotate.

[0057] Compared with the prior art, this embodiment sets the gear rack structure as a bevel gear 112 and a bevel gear rack 113. The bevel gear 112 rotates under the drive of the servo motor 111, which drives the bevel gear rack 113 to rotate, so as to realize the rotation of the rotating ring 114, ensuring the precise and stable rotation position of the wing and efficient switching.

[0058] Preferably, to match the rotational motion of the bevel gear rack 113 with that of the rotating ring 114, the bevel gear rack 113 is configured as a fan-shaped structure with a central angle of 120°. Specifically, to ensure a safe distance between the tiltrotor aircraft and the two ends of the large bevel gear rack when parked in normal flight and transport / storage positions, the fan-shaped distribution is such that one side of the longitudinal center plane of the fuselage is 105° and the other side is 15°, ensuring a safe distance of 15° on both sides.

[0059] The rotating ring 114 is located on the upper part of the body 4. For example... Figure 3 and Figure 4 As shown, the inner and outer sides of the rotating ring 114 are respectively provided with an inner annular groove 1141 and an outer annular groove 1142.

[0060] Furthermore, it also includes a connecting unit 12, which includes a wing-body joint 121 and a single-ear joint 122. The wing-body joint 121 is circumferentially distributed on the rotating ring 114. The wing-body joint 121 provides support for the entire wing and the wing rotating device 1.

[0061] For example, such as Figure 5 As shown, the upper middle part of the wing-body joint 121 is provided with an annular receiving groove 1211 for accommodating the rotating ring 114. The lower part is the fuselage connecting part 1212, which is used to connect the front and rear sides of the fuselage 4.

[0062] The single-ear connector 122 is circumferentially distributed around the rotating ring 114, and has an upwardly extending lug shape on its upper part. The single-ear connector 122 is used for connection with the wing.

[0063] The wing transmits the load to the fuselage 4 through the wing-body joint 121 and the single-ear joint 122.

[0064] Furthermore, it also includes a limiting unit 13. For example... Figure 3 and 4 As shown, the limiting unit 13 includes a limiting pressure block 131 and a limiting stop block 132.

[0065] A limiting block 131 is disposed within the annular receiving groove 1211 of the wing-body joint 121. Each wing-body joint 121 is provided with two limiting blocks 131, which are respectively disposed on both sides of the rotating ring 114. The limiting blocks 131 can slide within the inner annular groove 1141 and the outer annular groove 1142. When the rotating ring 114 rotates, the limiting blocks 131 on both sides limit the radial movement of the rotating ring 114.

[0066] The limiting block 132 is disposed within the inner annular groove 1141 and the outer annular groove 1142 of the rotating ring 114. When the limiting block 131 encounters the limiting block 132 during sliding, the rotating ring 114 stops rotating. The limiting block 132 prevents the rotating ring 114 from over-rotating.

[0067] Furthermore, the limiting block 132 is arranged circumferentially along the annular groove of the rotating ring 114, and the angle between adjacent limiting blocks 132 is 90° in order to adapt to the switching angle of the wing.

[0068] Furthermore, such as Figure 5As shown, the limiting unit 13 also includes a U-shaped friction plate 133 and a flat friction plate 134.

[0069] U-shaped friction plate 133 is disposed at the bottom of the annular receiving groove 1211, and is used to limit the radial movement of the rotating ring 114. Flat friction plate 134 is disposed at the lower part of the limiting pressure block 131, and is used to limit the axial movement of the rotating ring 114.

[0070] Both the U-shaped friction plate 133 and the flat friction plate 134 are made of brass, which can reduce the rotational friction coefficient of the rotating ring 114.

[0071] Furthermore, it also includes a locking unit, which includes a quick-release pin 14.

[0072] The rotating ring 114 is provided with a first pin hole 1143, and the wing-body joint 121 is provided with a second pin hole 1213; the quick-release pin can be inserted into the first pin hole 1143 and the second pin hole 1213 to lock the wing state.

[0073] In this embodiment, the locking unit uses a quick-release pin 14 to fix the state of the rotating ring 114. The quick-release pin 14 is inserted into the first pin hole 1143 of the rotating ring 114 and the second pin hole 1213 of the wing-body joint 121, so that the rotating ring 114 is fixed. This is simple, quick and improves the efficiency of operation.

[0074] Furthermore, the locking unit also includes an angle sensor, which is set on the rotating disk. During the rotation, the angle sensor feeds back the rotation angle of the rotating disk to the flight control system in real time. The flight control system designs different motion parameters at different rotation angle positions according to the requirements to ensure that the speed and running time in the stopped state meet the design requirements.

[0075] The usage method of this embodiment is as follows:

[0076] like Figure 6 As shown, when the tiltrotor aircraft is stationary, the servo motor 111 drives the bevel gear 112 to rotate, which in turn drives the bevel gear rack 113 to rotate the rotating ring 114 and the wing. When the wing rotates to 0°, the limiting block 131 contacts the limiting stop block 132, and the rotating ring 114 stops rotating. The centerline of the wing is parallel to the fuselage 4.

[0077] like Figure 7 As shown, when the tiltrotor aircraft needs to fly normally, the servo motor 111 drives the bevel gear 112 to rotate, which in turn drives the bevel gear rack 113 to rotate the rotating ring 114 and the wing. When the wing rotates to 90°, the limiting block 131 contacts the limiting stop block 132, and the rotating ring 114 stops rotating. The centerline of the wing is perpendicular to the fuselage 4.

[0078] During the rotation of the rotating ring 114, the angle sensor feeds back the rotation angle of the rotating disk to the flight control system in real time. The flight control system designs different motion parameters at different rotation angle positions according to the requirements to ensure that the speed and running time in the stationary state meet the design requirements.

[0079] Example 2

[0080] This embodiment discloses a tiltrotor aircraft, such as Figures 8-10 As shown, it includes fuselage 4 and wings.

[0081] like Figure 8 and Figure 9 As shown, the wing includes a wing body 3, a wing connector 2, and a wing rotating device 1. One end of the wing connector 2 is connected to the single-ear connector 122 of the wing rotating device 1, and the other end of the wing connector 2 is connected to the wing body 3.

[0082] Furthermore, the wing also includes the wing structure. The wing structure includes the fairings, tiltrotor system, nacelles, and other structures and systems attached to the wing and connected to the front and rear spars.

[0083] The fuselage 4 is connected to the fuselage connection part 1212 of the wing-body joint 121.

[0084] Compared with the prior art, the tiltrotor aircraft of this utility model has the same advantages as the wing rotation device 1 and the wing described above, and will not be repeated here.

[0085] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A wing turning device, characterized by The application relates to a rotating unit (1) for rotating a wing relative to a fuselage about a vertical axis. The rotating unit (1) comprises a driving assembly and a rotating ring (114) with a vertical axis; the driving assembly comprises a rotary driving structure gear and rack structure arranged on an output shaft of the rotary driving structure, the output shaft of the rotary driving structure is horizontal, and the rotary driving structure is fixed to the fuselage. The inner side of the rotating ring (114) is connected to the output end of the gear and rack structure, and the upper part of the rotating ring (114) is connected to the wing.

2. The wing turning device of claim 1, wherein The gear and rack structure comprises a bevel gear (112) and a bevel gear strip (113). The bevel gear (112) is connected to the rotary driving structure and rotates under the driving of the rotary driving structure; the bevel gear strip (113) is engaged with the bevel gear (112), the bevel gear strip (113) is connected to the rotating ring (114), and the bevel gear strip (113) drives the rotating ring (114) to rotate.

3. The wing turning device of claim 2, wherein The bevel gear strip (113) is a fan-shaped structure, and the central angle of the fan-shaped structure is 120 degrees.

4. The wing turning device of claim 1, wherein The application further relates to a connecting unit (12) comprising a wing-body joint (121); the lower part of the wing-body joint (121) is connected to the fuselage (4), and the upper part of the wing-body joint (121) is connected to the rotating ring (114).

5. The wing turning device of claim 4, wherein The application further relates to a limiting unit (13) comprising a limiting pressing block (131) and a limiting stop block (132). The upper part of the wing-body joint (121) is provided with a ring accommodating groove (1211), the side wall of the rotating ring (114) is arranged in the ring accommodating groove (1211), and the limiting pressing block (131) is arranged on the two sides of the side wall. The inner side and the outer side of the side wall are respectively provided with annular grooves (1141, 1142), the limiting pressing block (131) can slide in the annular grooves (1141, 1142), and the limiting stop block (132) is arranged in the annular grooves (1141, 1142).

6. The wing turning device of claim 5, wherein The limiting unit (13) further comprises a U-shaped friction plate (133) and a flat plate friction plate (134). The U-shaped friction plate (133) is arranged at the bottom of the ring accommodating groove (1211) and is used for limiting the radial movement of the rotating ring (114). The flat plate friction plate (134) is arranged at the lower part of the limiting pressing block (131) and is used for limiting the axial movement of the rotating ring (114).

7. The wing turning device of claim 4, wherein The application further relates to a locking unit comprising a quick-release bolt (14). The rotating ring (114) is provided with a first bolt hole (1143), the wing-body joint (121) is provided with a second bolt hole (1213), and the quick-release bolt (14) can be inserted into the first bolt hole (1143) and the second bolt hole (1213) to lock the state of the wing body (3).

8. The wing turning device of claim 4, wherein The connecting unit (12) further comprises a single ear joint (122), which is arranged on the upper part of the rotating ring (114) and used for connecting with the wing body (3).

9. A tiltrotor aircraft, characterized in that, The wing rotating device comprises a fuselage (4) and the wing rotating device according to any one of claims 1-8. The wing-body joint (121) of the wing rotating device has a fuselage connecting part (1212). The fuselage (4) is connected with the fuselage connecting part (1212).

10. The gyroplane of claim 9, wherein, The rotation driving structure of the wing rotating device is located on the longitudinal center plane of the fuselage (4). The conical gear strip (113) of the wing rotating device is arranged as a 105° sector on one side of the longitudinal center plane of the fuselage (4) and a 15° sector on the other side of the longitudinal center plane of the fuselage (4).

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