CN217864739U - Tilting mechanism, tilting rotor wing and aircraft - Google Patents

Abstract

The utility model provides a mechanism, rotor and aircraft vert to vert through rotary drive device drive rotor normal position. This mechanism of verting is applied to the aircraft, the mechanism of verting includes: treat base, rotary driving device, pendulum rod and connecting rod of verting. Treat that the base that verts rotates to be installed on the organism of aircraft, the duplex winding first articulated shaft rotates. The rotary driving device is fixedly arranged on the machine body, and a rotary output end of the rotary driving device rotates in a reciprocating manner within a set angle range; one end of the swing rod is fixedly connected with the rotary output end; one end of the connecting rod is connected with the other end of the oscillating rod in a rotating mode, and the other end of the connecting rod is connected with the base to be tilted in a rotating mode.

Description

Tilting mechanism, tilting rotor wing and aircraft

Technical Field

The utility model relates to an aircraft field, concretely relates to mechanism, rotor and aircraft vert.

Background

Aiming at the aerospace industry, the existing aircraft is mainly a fixed-wing aircraft, the fixed-wing aircraft has higher requirements on runway length and field when taking off and landing, and the hovering function cannot be realized. In order to improve the flight efficiency, the aircraft (especially the EVTOL) needs to have the functions of vertical take-off and landing, hovering and flat flying at the same time.

The power device of the rotor wing tilting mechanism for the aircraft is mostly an electric push rod. The electric push rod has the advantages of large thrust, large stroke range and the like. But this type of mechanism that verts is through the extension volume of adjusting the push rod in order to drive link mechanism and overturn, finally realizes the purpose that the rotor verts. Electric putter's stroke is generally great among the mechanism that verts, and electric putter self is bulky, will directly increase the volume and the range of motion of whole mechanism, is not suitable for the less aircraft organism part of inner space, and the commonality is relatively poor.

SUMMERY OF THE UTILITY MODEL

In view of the above prior art's shortcoming, the utility model provides a mechanism, rotor and aircraft vert to vert through the rotary drive device drive rotor normal position.

In order to realize above-mentioned purpose and other relevant purposes, the utility model provides a mechanism verts is applied to on the organism of aircraft, the mechanism that verts includes: treat base, rotary driving device, pendulum rod and connecting rod of verting. Treat that the base that verts rotates to be installed on the organism, the duplex winding first articulated shaft rotates. The rotary driving device is fixedly arranged on the machine body, and a rotary output end of the rotary driving device rotates in a reciprocating manner within a set angle range; one end of the swing rod is fixedly connected with the rotary output end; one end of the connecting rod is rotatably connected with the other end of the oscillating rod, and the other end of the connecting rod is rotatably connected with the base to be tilted; when the rotation driving device drives the rotation output end to rotate, the base to be tilted is driven to rotate around the first hinge shaft; when the rotary output end is locked relative to the rotary output device, the base to be tilted is locked relative to the machine body.

In an example of the tilting mechanism of the present invention, the rotation driving device is an external rotor motor having a self-locking characteristic.

In an example of the tilting mechanism of the present invention, the base to be tilted includes a base body, and a support is fixedly mounted on the base body; the support is rotatably connected with the machine body.

The utility model discloses in an example of the mechanism that verts, the connecting rod deviates from the one end of pendulum rod with the support or base body rotates and connects.

In an example of the tilting mechanism of the present invention, the support and/or the connecting rod are provided with lightening holes.

In an example of the tilting mechanism, the support is detachably mounted on the base body through a fastening assembly.

In an example of the tilting mechanism of the present invention, the tilting mechanism further includes a mechanical locking structure that can lock the entire mechanism.

The utility model also provides a tilting rotor wing, which comprises a rotor wing, a rotor wing driving device and any one tilting mechanism; the base of the rotor wing driving device is fixedly connected with a base to be tilted of the tilting mechanism; the rotor wing driving device and the rotor wing incline and lock relative to the machine body under the action of the inclining mechanism.

The utility model discloses in an example of tiltrotor, the organism structure include the covering and set up in crossbeam in the covering, rotary drive device's stator with crossbeam fixed connection.

The utility model discloses in an example of rotor verts, be equipped with mechanism's mount pad additional strengthening verts on the crossbeam.

The utility model also provides an aircraft, including fuselage, wing and above-mentioned arbitrary any the rotor verts.

The utility model discloses the mechanism that verts can realize treating that the base that verts rotates and the locking for the normal position of first articulated shaft, and rotary drive device's stroke is short, and ageing is strong to the mechanism chain of whole mechanism is short, and the hinge is small in quantity, and mechanism frictional force is little, and the jamming probability is low, and the reliability is high. And simultaneously the utility model discloses the mechanism commonality that verts is strong, can be applicable to treating of polymorphic type size part that verts. Additionally the utility model discloses the normal position mechanism of verting's structure is simple relatively, assembly efficiency is high, pass power directness, and from taking self-locking function, improves the security of mechanism.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic three-dimensional structure diagram of an example of a tiltrotor according to the present invention;

fig. 2 is a three-dimensional exploded view of an example of a tiltrotor according to the present invention;

fig. 3 is a schematic structural view of an exemplary tilt rotor according to the present invention in a horizontal position;

fig. 4 is a front view of an exemplary tilt rotor according to the present invention after the rotor is tilted in place;

fig. 5 is a schematic three-dimensional structure of another example of a tilt rotor wing according to the present invention;

fig. 6 is a three-dimensional exploded view of another example of a tiltrotor rotor according to the present invention;

fig. 7 is a schematic structural view of another example of a tilt rotor according to the present invention in a horizontal position;

fig. 8 is a front view of another example of a tilt rotor according to the present invention after the rotor is tilted in place;

fig. 9 is a three-dimensional schematic diagram of an example of the aircraft of the present invention.

Description of the element reference numerals:

100. a tilting mechanism; 101. a first hinge shaft; 102. a second hinge shaft; 103. a third hinge shaft; 110. A base to be tilted; 111. a base body; 1111. a first fixed seat; 1112. a second fixed seat; 11121. a third hinge shaft hole; 112. a support; 120. a rotation driving device; 130. a swing rod; 140. a connecting rod; 200. a body; 210. a first hinge shaft mount; 211. a first hinge shaft mounting hole; 220. a rotating device base; 230. a tilting mechanism mounting seat reinforcing structure; 231. a first reinforcing rib; 232. a second reinforcing rib; 233. frame reinforcing ribs; 240. a cross beam; 250. covering a skin; 300. a rotor drive; 400. a rotor; 500. an aircraft; 510. a first tilt rotor; 520. a second tilt rotor.

Detailed Description

The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. The present invention can be implemented or applied by other different specific embodiments, and various details in the present specification can be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. It is also to be understood that the terminology used in the examples of the present invention is for the purpose of describing particular embodiments, and is not intended to limit the scope of the present invention. Test methods in which specific conditions are not noted in the following examples are generally performed under conventional conditions or conditions recommended by each manufacturer.

When numerical ranges are given in the examples, it is understood that both endpoints of each of the numerical ranges and any number between the endpoints are optional unless the utility model discloses otherwise. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs and are intended to describe the same, and all methods, apparatus and materials similar or equivalent to those described herein may be used in the practice of this invention.

It should be understood that the terms "upper", "lower", "left", "right", "middle" and "one" used herein are for clarity of description, and are not intended to limit the scope of the invention, but rather the scope of the invention.

Referring to fig. 1 to 8, the present invention provides a tilting mechanism 100, wherein the tilting mechanism 100 is suitable for an aircraft, in particular, an electric vertical takeoff and landing device (EVTOL). The tilting mechanism 100 has the advantages of self-locking capability, small stroke, simple structure, direct force transmission and the like on the premise of realizing the tilting function of the rotor wing. Moreover, the tilting mechanism 100 can simplify the structure of the existing tilting mechanism, and realizes the in-situ tilting of the rotor wing around the first hinge shaft 101.

The tilting mechanism 100 is applied to the body 200 of the aircraft 500, and may be mounted on the arm of the electric vertical takeoff and landing device, for example, to implement tilting of the rotor 400, or may be mounted at the tail of the electric vertical takeoff and landing device to implement tilting of the tail thrust. The tilting mechanism 100 includes: a base 110 to be tilted, a rotary driving device 120, a swing link 130 and a connecting rod 140. Treat that base 110 of verting rotates through first articulated shaft 101 and installs organism 200 is last to can rotate around first articulated shaft 101. The stator of the rotary driving device 120 is fixedly installed on the machine body 200, and the rotary output end of the rotary driving device 120 reciprocates within a set angle range to drive the tilting mechanism 100 to tilt or reset. One end of the swing rod 130 is fixedly connected with the rotary output end of the rotary driving device 120; one end of the connecting rod 140 is rotatably connected with the other end of the swing rod 130 through a second hinge shaft 102, and the other end of the connecting rod 140 is rotatably connected with the base to be tilted 110 through a third hinge shaft 103; when the rotation driving device 120 drives the rotation output end to rotate, the to-be-tilted base 110 is driven to rotate around the first hinge shaft 101; when the rotary output is locked relative to the stator of the rotary drive, the to-be-tilted base 110 is locked relative to the machine body 200.

The utility model discloses in, rotary drive device 120 can be for having self-locking function and can realize all suitable drive structure of rotary drive, for example, the motor that has self-locking function, the combination form of motor and speed reducer, in this embodiment, rotary drive device 120 can be all suitable drive structure that has self-locking function, for example servo motor, motor + worm gear class speed reducer, or the combination of motor plus stopper etc.. Of course, those skilled in the art can also understand that, in the present invention, the motor may also be a motor without a self-locking function, such as an external rotor motor, but is realized by the mechanical locking structure of the present invention, for example, an electromagnetic bolt is provided, and after the mechanism reaches the set position, the bolt is controlled to pop out to perform mechanical limitation on the mechanism, etc., or to cooperate with the existing mechanical locking structure to realize the locking of the base 110 to be tilted at different rotational positions. It is to be understood that the tilting mechanism may include the above-described mechanical lock mechanism which may be separately provided in order to achieve integration of functions.

Referring to fig. 1 and fig. 2, in an embodiment of the tilting mechanism of the present invention, the base 110 to be tilted includes a base body 111, a first fixing seat 1111 is disposed on the base body 111, and a support 112 is fixedly mounted on the first fixing seat 1111; the support 112 is detachably and fixedly mounted on the base body 111 through a fastening assembly. The support 112 is rotatably connected to the body 200 by a first hinge shaft 101. The distance between the base 110 to be tilted and the machine body 200 can be properly increased by arranging the support 112, the interference between the base 110 to be tilted and the machine body 200 in the tilting process is reduced, and the avoidance gap required to be formed in the machine body 200 can be reduced.

In an embodiment of the tilting mechanism 100, the support 112 and the connecting rod 140 are provided with lightening holes (not shown). The position of the lightening hole is not limited, and the lightening hole can keep the weight of each connecting rod light without influencing the strength. Of course, it will be understood by those skilled in the art that the lightening holes may be provided only on the support 112 or the connecting rod 140.

The utility model discloses in, connecting rod 140 deviates from the one end of pendulum rod 130 with support 112 or base body 111 rotates and connects to the rotation around first articulated shaft 101 of base 110 that realizes waiting to vert.

Referring to fig. 1 to 4, in an embodiment of the present invention, the base 110 to be tilted is provided with a second fixing seat 1112, the first fixing seat 1111 and the second fixing seat 1112 are respectively disposed at two ends of the base 110 to be tilted, one end of the connecting rod 140 departing from the swing rod 130 is rotatably connected to the second fixing seat 1112 through a third hinge shaft 103, and axes of the third hinge shaft 103, the second hinge shaft 102 and the first hinge shaft 101 are all parallel to each other. Specifically, a first hinge shaft hole (not shown) is formed in the support 112, the first hinge shaft hole penetrates through the support 112, first hinge shaft mounting seats 210 are respectively arranged on the cross beams on two sides of the support 112 in the machine body 200, first hinge shaft mounting holes 211 are respectively arranged on the two first hinge shaft mounting seats 210, the first hinge shaft 101 penetrates through the first hinge shaft hole, and two ends of the first hinge shaft 101 are respectively inserted into the first hinge shaft mounting holes 211 on the two cross beams, so that the rotatable installation between the support 112 and the machine body 200 is formed. A third hinge shaft hole 11121 is formed in the second fixing seat 1112, a third hinge shaft mounting hole (not shown) is formed in the connecting rod 140, and the third hinge shaft 103 is inserted into the third hinge shaft hole 11121 and the third hinge shaft mounting hole, so that the connecting rod 140 and the base body 111 can be rotatably mounted.

Referring to fig. 3 to 4, when the rotary output end of the rotary driving device 120 rotates counterclockwise, the swing link 130 and the rotary output end rotate counterclockwise synchronously, the swing link 130 drives the connecting rod 140 to perform an arc motion around the center of the rotary output end when rotating, and the connecting rod 140 pushes the base 110 to be tilted to rotate through the third hinge shaft 103, so as to drive the rotor driving device 300 and the rotor 400 to tilt to a vertical position. It should be noted that, when the rotor needs to be tilted from the vertical position to the horizontal position, the process is opposite to the above process, and is not described herein again.

Referring to fig. 6, in another embodiment of the present invention, the second fixing seat 1112 is not disposed on the base 110 to be tilted, and one end of the connecting rod 140 departing from the swing rod 130 is rotatably connected to the support 112 through a third hinge shaft 103. Specifically, a first hinge shaft hole (not shown) and a fourth hinge shaft hole 1121 are formed in the support 112, the first hinge shaft hole and the fourth hinge shaft hole 1121 penetrate through the support 112, the axes of the first hinge shaft hole and the fourth hinge shaft hole are parallel to each other, first hinge shaft mounting seats 210 are respectively arranged on the cross beams on two sides of the support 112 in the machine body 200, first hinge shaft mounting holes 211 are respectively arranged on the two first hinge shaft mounting seats 210, the first hinge shaft 101 penetrates through the first hinge shaft holes, and two ends of the first hinge shaft 101 are respectively inserted into the first hinge shaft mounting holes 211 on the two cross beams, so that the rotatable installation between the support 112 and the machine body 200 is formed. The connecting rod 140 is provided with a third hinge shaft mounting hole 141, and the third hinge shaft 103 is inserted into the third hinge shaft hole 1121 and the third hinge shaft mounting hole 141, so as to form a rotatable mounting between the connecting rod 140 and the support 112.

When the rotary output end of the rotary driving device 120 rotates counterclockwise, the swing link 130 rotates counterclockwise synchronously with the rotary output end, the swing link 130 drives the connecting rod 140 to perform arc motion around the center of the rotary output end when rotating, the connecting rod 140 pushes the support 112 to rotate counterclockwise through the third hinge shaft 103, and simultaneously drives the base 110 to be tilted, which is fixedly connected with the support 112, to rotate counterclockwise, so as to drive the rotor driving device 300 and the rotor 400 to tilt to the vertical position. It should be noted that, when the rotor needs to be tilted from the vertical position to the horizontal position, the process is opposite to the above process, and the description is omitted here.

Referring to fig. 1 to 8, the present invention further provides a tilt rotor, wherein the tilt rotor 400 includes a rotor 400, a rotor driving device 300, and any one of the tilt mechanisms 100 described above; the rotor 400 is installed on an output shaft of the rotor driving device 300 and rotates with the output shaft, and a fairing (not marked) is arranged at the front end of the rotor 400, wherein a base of the rotor driving device 300 is fixedly connected with a base 110 to be tilted of the tilting mechanism 100; rotor drive device 300 and rotor 400 tilt and lock with respect to body 200 under the action of tilt mechanism 100.

Referring to fig. 1 and 9, in an embodiment of the present invention, the body 200 is configured as a horn, the horn is mounted on a wing of an aircraft 500, and the horn includes a skin 250 and a beam 240 disposed in the skin; the tilt rotor 400 is installed at the end of the horn, the support 112 is installed on the cross beam 240 through the first hinge shaft 101, and the stator of the rotary driving device 120 is also fixedly installed on the cross beam 240 in the horn.

In another embodiment of the present invention, the tilt rotor 400 is also installed as a tiltable tail rotor 400 at the tail of the aircraft 500, in which case the support 112 is rotatably installed on the skin 250 or the cross beam 240 at the tail of the fuselage, and the stator of the rotary driving device 120 is fixedly installed on the skin 250 or the cross beam 240 at the tail of the fuselage. The bottom of rotor driving device 300 is installed on base 110 to be tilted, and rotor driving device 300 and rotor 400 are tilted and locked relative to the wing or the tail under the action of rotary driving device 120.

The utility model discloses tilt rotor an embodiment, the crossbeam includes first crossbeam and second crossbeam, first crossbeam and second crossbeam parallel arrangement, install respectively at first articulated shaft 101 both ends on first crossbeam and the second crossbeam, rotary drive device 120's stator fixed mounting is on first crossbeam or second crossbeam. This kind of structure can make the even transmission of power of verting give two crossbeams, is favorable to the atress dispersion.

The utility model discloses in the rotor that verts an embodiment, be equipped with first articulated axle mount pad 210 and rotary device seat 220 on the crossbeam, be provided with mechanism's mount pad additional strengthening 230 that verts on the crossbeam. The tilting mechanism mounting base reinforcing structure 230 includes a first reinforcing rib 231, a second reinforcing rib 232, and a frame reinforcing rib 233, one end of the first reinforcing rib 231 is connected to the first hinge shaft mounting base 210, and the other end of the first reinforcing rib 231 is connected to the rotating device base 220. The frame reinforcing ribs 233 are protruded in a direction perpendicular to the surface of the first beam or the second beam, and the protrusions extend along the edges of the first beam or the second beam. The second reinforcing ribs 232 are connected with the first hinge shaft mounting seat 210 and the frame reinforcing ribs 233, and a reinforcing rib force transmission channel can be formed among the first hinge shaft mounting seat 210, the rotating device seat 220 and the frame of the cross beam through the arrangement mode, so that the bearing capacity of the cross beam can be greatly improved. It should be noted that, in this embodiment, the cross beam may also be deformed into other structural forms, and the number may be, but is not limited to, 2, and the arrangement position may also be adjusted according to the deformed structural form.

Consider that the utility model discloses mainly use in the aircraft field to a drive rotor 400 switches between horizontal position and vertical position the utility model discloses in the mechanism of verting one embodiment, rotary drive device 120 drives treat to vert base 110 and switch between horizontal position and vertical position. However, it can be understood by those skilled in the art that the tilting angle of the tilting mechanism 100 in the present invention is not limited to the horizontal position and the vertical position.

Referring to fig. 9, the present invention further provides an aircraft 500, the type of the aircraft is not limited, in this embodiment, the aircraft 500 is an electric vtol, the aircraft 500 includes a fuselage, wings, a related power system, and a control system, and the aircraft 500 further includes any of the tilt rotors 400 described above. Tilt rotor 400's mounted position is not restricted, can install on horn and/or wing and/or fin, and in this embodiment, aircraft 500 includes first tilt rotor 510 and a plurality of second tilt rotor 520, and a plurality of second tilt rotor 520 symmetry is installed on the horn of fuselage both sides, first tilt rotor 510 installs the afterbody of fuselage forms the tail that has the function of tilting and pushes away the structure.

The utility model discloses the mechanism that verts can realize treating that the base that verts rotates and the locking for the normal position of first articulated shaft, and rotary drive device's stroke is short, and ageing is strong to the mechanism chain of whole mechanism is short, and the hinge is small in quantity, and mechanism frictional force is little, and the jamming probability is low, and the reliability is high. And simultaneously the utility model discloses the mechanism commonality that verts is strong, can be applicable to treating of polymorphic type size part that verts. Additionally the utility model discloses the structure of mechanism of verting is simple relatively, assembly efficiency is high, pass power directness, and from taking self-locking function, improves the security of mechanism. Therefore, the utility model discloses thereby effectively overcome some practical problems among the prior art and had very high use value and use meaning. The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention shall be covered by the claims of the present invention.

Claims (10)

1. The utility model provides a tilting mechanism, is applied to the aircraft which characterized in that, tilting mechanism includes:

the base to be tilted is rotatably arranged on the aircraft body of the aircraft and rotates around the first hinge shaft; the rotary driving device is fixedly arranged on the machine body, and a rotary output end of the rotary driving device rotates in a reciprocating manner within a set angle range;

one end of the swing rod is fixedly connected with the rotary output end;

one end of the connecting rod is rotatably connected with the other end of the oscillating rod, and the other end of the connecting rod is rotatably connected with the base to be tilted;

wherein, the rotation driving device drives when rotatory output rotates, drives treat that the base that verts winds first articulated shaft rotates.

2. A tilt mechanism according to claim 1, wherein the rotary drive arrangement has a self-locking feature such that when the rotary output is locked relative to the rotary drive arrangement, the base to be tilted is locked relative to the housing.

3. The tilt mechanism of claim 1, wherein the base to be tilted comprises a base body to which a mount is fixedly mounted; the support is rotatably connected with the machine body.

4. The tilt mechanism of claim 3, wherein an end of the connecting rod facing away from the rocker lever is rotatably coupled to the support or the base body.

5. The tilt mechanism of claim 4, wherein the mount is removably mounted to the base body via a fastening assembly.

6. The tilt mechanism of claim 1, further comprising a mechanical locking arrangement that enables locking of the entire mechanism.

7. A tiltrotor rotor comprising a rotor and a rotor drive, further comprising the tiltrotor mechanism of any one of claims 1-6; the base of the rotor wing driving device is fixedly connected with a base to be tilted of the tilting mechanism; the rotor wing driving device and the rotor wing incline and lock relative to the machine body under the action of the inclining mechanism.

8. A tiltrotor rotor according to claim 7, wherein the airframe structure includes a skin and a beam disposed within the skin, the rotary drive being fixedly connected to the beam.

9. A tiltrotor rotor according to claim 8, wherein the transom is provided with tilt mechanism mount reinforcement structure.

10. An aircraft comprising a fuselage and a wing, characterized in that it further comprises a tiltrotor rotor according to any one of claims 7 to 9.

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