A large unmanned aerial vehicle flap actuator and its mounting structure

Abstract

The present invention discloses a large unmanned aerial vehicle flap actuator and its mounting structure. The actuator includes an actuator housing, in which a rotating ball screw, a screw nut, a turbine and a worm are arranged, a screw pair is formed between the ball screw and the screw nut, the screw nut is fixedly connected to the turbine, the turbine is meshed with the worm, a joint bearing is arranged at the front end of the ball screw, and the actuator housing is arranged on a universal ring mechanism. The mounting structure includes the above-mentioned large unmanned aerial vehicle flap actuator, and also includes a wing frame and a flap frame, the flap frame slides along the flap slide rail on the wing frame, the universal ring mechanism is installed on the wing frame, and the flap actuator is connected to the flap frame through a joint bearing. The beneficial effects of the present invention are as follows: 1. It can output a greater actuating force; 2. The actuating stroke is long; 3. The structure is simple and reliable, and the weight is light; 4. The actuator force transmission path is guaranteed to be direct through the universal mechanism; 5. Single transmission chain, reliable transmission, and precise actuation; 6. It has a locking function.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft flaps, and in particular relates to a large unmanned aerial vehicle flap actuator and a mounting structure thereof. Background Art

[0002] Flaps are small wings that are set on the trailing edge of the aircraft wing and can slide to increase the wing area and improve the lift and drag of the wing. The sliding of the flaps is achieved by flap actuators. Traditional UAV flap actuators are driven by motors. Due to the limitations of the power supply and weight of the UAV, electric flap actuators have defects such as low actuation force, short stroke, low reliability, and inconvenient maintenance. At the same time, a single flap requires multiple actuators to drive it at the same time, and the inner and outer flaps also need to move in coordination. Therefore, multiple actuators are required to work synchronously, otherwise the flaps are easy to get stuck, and the electric actuators are complex to control, have low reliability, and are prone to failure, causing flight accidents. The electric actuator does not have a locking function. After the power is off, the flap position cannot be fixed, which is also easy to cause flight accidents. Summary of the invention

[0003] The purpose of the present invention is to provide a large-scale UAV flap actuator and its installation structure, which solves the problems of small actuating force, short stroke and low reliability of traditional UAV flap actuators.

[0004] The object of the present invention is achieved through the following technical solutions:

[0005] A large unmanned aerial vehicle flap actuator comprises an actuator housing, wherein a rotating ball screw, a screw nut, a turbine and a worm are arranged in the actuator housing, a screw pair is formed between the ball screw and the screw nut, the screw nut is fixedly connected with the turbine, the turbine is meshed with the worm, a joint bearing is arranged at the front end of the ball screw, and the actuator housing is arranged on a universal ring mechanism.

[0006] Furthermore, the front end of the ball screw is an annular actuator joint, the spherical bearing is arranged on the actuator joint, and the rear end of the ball screw is provided with a stop cap.

[0007] Furthermore, the front end of the screw nut is connected to the first adapter ring, and the rear end of the screw nut is connected to the second adapter ring. The first adapter ring and the second adapter ring are both mounted on the ball screw, and the turbine is connected to the first adapter ring.

[0008] Furthermore, the first adapter ring is provided with a first limiting bushing and a second limiting bushing, the first limiting bushing is clamped at the front end of the turbine, and the second limiting bushing is clamped at the rear end of the turbine.

[0009] Furthermore, a first bearing is provided between the first adapter ring and the actuator housing, a second bearing is provided between the second adapter ring and the actuator housing, and a third bearing and a fourth bearing are provided between both ends of the worm and the actuator housing.

[0010] Furthermore, the front end of the actuator housing is connected to the end cover, a third sealing ring is provided between the first bearing and the end cover, a second sealing ring is provided between the actuator housing and the end cover, a first sealing ring is provided between the second bearing and the actuator housing, the side end of the actuator housing is connected to the side cover, a fourth sealing ring is provided between the actuator housing and the side cover, and an oil seal is provided between the side cover and the worm.

[0011] Furthermore, the universal ring mechanism includes a mounting support and a universal ring, the left and right ends of the universal ring are hinged to the mounting support through a horizontal second rotating pin, and the front and rear ends of the universal ring are hinged to the actuator housing through a vertical first rotating pin.

[0012] Furthermore, the actuator housing is connected to the first rotating pin through an anti-rotation pin, one end of the first rotating pin is clamped with the actuator housing, and the other end of the first rotating pin is clamped with a universal ring through a retaining spring.

[0013] Furthermore, a universal ring is clamped on one end of the second rotating pin shaft, and a mounting support is clamped on the other end of the second rotating pin shaft via a limiting nut.

[0014] Furthermore, wear-resistant bushings are provided between the first rotating pin shaft, the second rotating pin shaft and the universal ring.

[0015] A mounting structure for a large unmanned aerial vehicle flap actuator comprises the above-mentioned large unmanned aerial vehicle flap actuator, and also comprises a wing frame and a flap frame, wherein the flap frame slides along a flap slide rail on the wing frame, a universal ring mechanism is mounted on the wing frame, and the flap actuator is connected to the flap frame via a joint bearing.

[0016] Furthermore, the wing frame is provided with a wing trailing edge opening, and the actuator housing is inserted into the wing trailing edge opening.

[0017] Furthermore, the spherical bearing is connected between the actuator joint at the front end of the ball screw and the flap joint of the flap frame.

[0018] Furthermore, it also includes a driving device, which is connected to the worm gear of the flap actuator through a transmission shaft, and the worm gears of two adjacent flap actuators are connected through a transmission shaft.

[0019] Functions achieved by the present invention:

[0020] 1. Through the internal worm gear and ball screw, a large transmission ratio is formed, so a large working force can also be achieved.

[0021] 2. By designing the lead of the ball screw and the transmission ratio of the worm gear, any length of actuation per unit time can be achieved, and it can be arranged at any position. At the same time, single transmission chain transmission can be realized to ensure the precise actuation of the flaps and avoid flap jamming.

[0022] 3. By setting the length of the lead screw, the flap can slide over a long distance.

[0023] 4. The universal ring mechanism set at the rear of the actuator can ensure that when the actuator pushes the flap to slide, the actuator can always ensure that the screw is only subjected to tension and pressure, and will not be subjected to bending moment, ensuring that the force transmission path of the actuator is direct and prolonging its service life.

[0024] 5. The worm gear has a locking function, which can lock the flaps when there is no power to ensure flight safety.

[0025] 6. At the same time, since it is a pure mechanical transmission, it has better reliability. Under the premise of the same actuating force, the designed actuator is lighter and easier to maintain.

[0026] The beneficial effects of the present invention are as follows: 1. It can output a greater actuating force; 2. The actuating stroke is long; 3. The structure is simple and reliable, and the weight is light; 4. The universal joint mechanism is used to ensure that the force transmission path of the actuator is direct; 5. Single transmission chain, reliable transmission, and precise actuation; 6. It has a locking function.

[0027] The aforementioned main scheme of the present invention and its further options can be freely combined to form multiple schemes, all of which are schemes that can be adopted and claimed for protection by the present invention; and in the present invention, (non-conflicting options) options and other options can also be freely combined. After understanding the scheme of the present invention, those skilled in the art can understand that there are many combinations based on the prior art and common knowledge, all of which are technical schemes to be protected by the present invention, and they are not exhaustively listed here. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the appearance structure of the flap actuator of the present invention.

[0029] Figure 2 It is a transverse sectional schematic diagram of the flap actuator of the present invention.

[0030] Figure 3 It is a longitudinal sectional schematic diagram of the flap actuator of the present invention.

[0031] Figure 4 It is a partial schematic diagram of the appearance of the flap actuator of the present invention.

[0032] Figure 5 It is a structural schematic diagram of the universal ring mechanism of the present invention.

[0033] Figure 6 It is a structural schematic diagram of the universal ring of the present invention.

[0034] Figure 7 It is a schematic diagram of the flap actuator installation structure of the present invention.

[0035] Figure 8 yes Figure 6 A partial enlarged view of .

[0036] In the figure: 1-wing frame, 2-flap frame, 3-flap rail, 4-flap actuator, 5-universal ring mechanism; 101-wing trailing edge opening, 201-flap joint, 401-actuator joint, 402-spherical bearing, 403-actuator housing, 404-ball screw, 405-stop cap, 406-end cover, 407-screw nut, 408-first adapter ring, 409-second adapter ring, 410-turbine, 411-worm, 412-first limit bushing, 413-second limit bushing, 414 -first bearing, 415-second bearing, 416-first sealing ring, 417-second sealing ring, 418-third sealing ring, 419-third bearing, 420-fourth bearing, 421-fourth sealing ring, 422-oil seal, 423-side cover, 424-spline, 425-oil filling port, 426-oil drain port, 501-mounting support, 502-universal ring, 503-second rotating pin, 504-limiting nut, 505-first rotating pin, 506-circlip, 507-wear-resistant bushing, 508-anti-rotation pin. DETAILED DESCRIPTION

[0037] The following non-limiting examples serve to illustrate the invention.

[0038] Embodiment 1:

[0039] refer to Figure 1 to Figure 6 As shown, a large unmanned aerial vehicle flap actuator includes an actuator joint 401, a spherical bearing 402, an actuator housing 403, a ball screw 404, a stop cap 405, an end cover 406, a screw nut 407, a first adapter ring 408, a second adapter ring 409, a turbine 410, a worm 411, a first limit bushing 412, a second limit bushing 413, a first bearing 414, a second bearing 415, a first sealing ring 416, a second sealing ring 417, a third sealing ring 418, a third bearing 419, a fourth bearing 420, a fourth sealing ring 421, an oil seal 422, a side cover 423, a spline 424, an oil filling port 425 and an oil prevention port 426.

[0040] A rotating ball screw 404, a screw nut 407, a turbine 410 and a worm 411 are arranged in the actuator housing 403. A screw pair is formed between the ball screw 404 and the screw nut 407. The screw nut 407 is fixedly connected to the turbine 410, and the turbine 410 is meshed with the worm 411. When in motion, the worm 411 is driven to move by the driving device, and then the turbine 410 is driven to rotate, thereby synchronously driving the screw nut 407 to rotate, further realizing the forward and backward extension of the ball screw 404, and finally driving the flap frame 2 to slide forward and backward.

[0041] The front end of the ball screw 404 is an annular actuator joint 401, and the spherical bearing 402 is arranged on the actuator joint 401. When the flap moves along the flap rail 3, the actuator joint 401 moves together with the flap, and the motion trajectory is a space curve. In order to ensure that the actuator is always in a two-force rod state, the front end of the ball screw 404 is provided with a spherical bearing 402. The rear end of the ball screw 404 is provided with a stop cap 405 to limit the position of the ball screw 404.

[0042] The front end of the lead screw nut 407 is connected to the first adapter ring 408, and the rear end of the lead screw nut 407 is connected to the second adapter ring 409. The first adapter ring 408 and the second adapter ring 409 are both sleeved on the ball screw 404. The two ends of the ball screw 404 are matched with the first adapter ring 408 and the second adapter ring 409 with a small gap to ensure that debris does not enter the actuator. At the same time, the first adapter ring 408 and the second adapter ring 409 are fixed together with the lead screw nut 407 by bolts, and the first adapter ring 408 is fixedly connected to the turbine 410 to achieve synchronous rotation.

[0043] The first adapter ring 408 is provided with a first limit bushing 412 and a second limit bushing 413. The first limit bushing 412 clamps the front end of the turbine 410, and the second limit bushing 413 clamps the rear end of the turbine 410. The first limit bushing 412 and the second limit bushing 413 ensure the axial position of the turbine 410 on the first adapter ring 408.

[0044] A first bearing 414 is provided between the first adapter ring 408 and the actuator housing 403, and a second bearing 415 is provided between the second adapter ring 409 and the actuator housing 403. Both the first bearing 414 and the second bearing 415 are needle roller thrust bearings for transmitting the tensile and compressive loads borne by the ball screw.

[0045] The front end of the actuator housing 403 is connected to the end cover 406 by bolts, and the end cover 406 holds the bushing, adapter ring and other components inside. In order to ensure the lubrication of the worm gear, a third sealing ring 418 is provided between the first bearing 414 and the end cover 406, a second sealing ring 417 is provided between the actuator housing 403 and the end cover 406, and a first sealing ring 416 is provided between the second bearing 415 and the actuator housing 403, which can ensure that the actuator housing 403 stores the lubricating oil required for lubrication.

[0046] The flap actuator has the same structure on both sides. The two side ends of the actuator housing 403 are connected to the side cover 423 by bolts. The side cover 423 holds the bearing and other components inside. A third bearing 419 and a fourth bearing 420 are provided between the two ends of the worm 411 and the actuator housing to support the worm and transmit the load borne by the worm. A fourth sealing ring 421 is provided between the actuator housing 403 and the side cover 423, and an oil seal 422 is provided between the side cover 423 and the worm, in order to fix the grease required for lubricating the ball screw inside the actuator housing 403.

[0047] The two ends of the worm 411 are processed into splines 424 for connecting to an external drive and driving the subsequent actuator. The actuator housing 403 is provided with a lubricating oil filling port 425 and an oil drain port 426 for replenishing and draining the lubricating oil inside the actuator, which is convenient for regular replacement of lubricating oil and improves operation and maintenance.

[0048] The rear end of the actuator housing 403 is arranged on the universal ring mechanism 5, which includes a mounting support 501 and a universal ring 502. The universal ring 502 is designed to be hexagonal in order to improve rigidity while ensuring a small space size. The universal ring is provided with four rotation holes, which correspond to the openings on the mounting support 501 and the actuator housing 403 respectively.

[0049] The left and right ends of the universal ring 502 are both hinged to the mounting support 501 through the horizontal second rotating pin 503, so that the mounting support 501 and the universal ring 502 can be hinged and rotated relative to the horizontal axis. The front and rear ends of the universal ring 502 are both hinged to the actuator housing 403 through the vertical first rotating pin 505, so that the universal ring 502 and the actuator housing 403 can be hinged and rotated relative to the vertical axis. That is, through the transition of the universal ring 502, the universal motion of the actuator housing 403 on the wing frame 1 is realized.

[0050] The universal ring mechanism 5 is provided with two mounting supports 501, and the mounting supports 501 are provided with bolt holes, which are connected to the rear beam of the wing by bolts, and ensure that the actuator housing and the rear ball screw pass through the opening on the rear beam. One end of the second rotating pin 503 is clamped with a universal ring 502, and the other end of the second rotating pin 503 is clamped with the mounting support 501 through a limiting nut 504, and the limiting nut 504 prevents the second rotating pin 503 from falling out.

[0051] The actuator housing 403 is connected to the first rotating pin 505 via an anti-rotation pin 508. In order to protect the actuator housing 403 from wear during rotation, through holes are provided on the actuator housing 403 and the first rotating pin 505, and the actuator housing 403 and the first rotating pin 505 are connected via the anti-rotation pin 508. When the universal joint rotates around the first rotating pin 505, the anti-rotation pin 508 can prevent the actuator housing 403 and the first rotating pin 505 from relative rotation, thereby avoiding wear.

[0052] One end of the first rotating pin 505 is clamped with the actuator housing 403, and the other end of the first rotating pin 505 is clamped with the universal ring 502 through a clamping spring 506, and the clamping spring prevents the first rotating pin 505 from coming out. A wear-resistant bushing 507 is provided between the first rotating pin 505 and the second rotating pin 503 and the universal ring 502 to improve the wear resistance of the rotation.

[0053] Embodiment 2:

[0054] refer to Figure 7 and Figure 8 As shown, a mounting structure for a large UAV flap actuator includes the large UAV flap actuator described in Example 1, and also includes a wing frame 1 and a flap frame 2. The flap frame 2 slides along the flap rail 3 on the wing frame 1. The flap is located behind the wing. During take-off and landing, the flap needs to move back and forth along the flap rail 3 to ensure the flight attitude of the aircraft.

[0055] The rear end of the flap actuator 4 is mounted on the wing frame 1 through the universal ring mechanism 5, and the front end of the flap actuator 4 is connected to the flap frame 2 through the joint bearing 402. The wing frame 1 is provided with a wing trailing edge opening 101, and the actuator housing 403 is inserted into the wing trailing edge opening 101. The size of the opening can ensure that the actuator does not interfere with the wing trailing edge during movement.

[0056] The joint bearing 402 is connected between the actuator joint 401 at the front end of the ball screw 404 and the flap joint 201 of the flap frame 2, ensuring that the actuator joint 401 moves together with the flap, and the movement trajectory is a space curve.

[0057] It also includes a driving device, which is connected to the worm 411 of the flap actuator 4 through a transmission shaft, and the worm 411 of two adjacent flap actuators 4 are connected through a transmission shaft.

[0058] The drive device drives the transmission shaft to rotate, and the transmission shaft is connected to the worm of the flap actuator through the spline, driving the worm to rotate, and the rotation of the worm drives the turbine to rotate, and the rotation of the turbine drives the screw nut to rotate, and the screw nut drives the screw to move forward and backward. The spline on the other side of the worm drives the subsequent transmission shaft, and the transmission shaft drives the next flap actuator. The two flap actuators are linked, and finally push the flap to move along the slide rail. At the same time, since the turbine cannot drive the worm to rotate, a self-locking function is achieved.

[0059] The above basic examples of the present invention and their further optional examples can be freely combined to form multiple embodiments, all of which are embodiments that can be adopted and claimed for protection by the present invention. In the scheme of the present invention, each optional example can be arbitrarily combined with any other basic examples and optional examples.

[0060] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A large unmanned aerial vehicle flap actuator, comprising an actuator housing (403), characterized in that: The actuator housing (403) is provided with a rotating ball screw (404), a screw nut (407), a turbine (410) and a worm (411); a screw pair is formed between the ball screw (404) and the screw nut (407); the screw nut (407) is fixedly connected to the turbine (410); the turbine (410) is meshed with the worm (411); a joint bearing (402) is provided at the front end of the ball screw (404); and the actuator housing (403) is arranged on a universal ring mechanism (5); The front end of the lead screw nut (407) is connected to the first adapter ring (408), and the rear end of the lead screw nut (407) is connected to the second adapter ring (409). The first adapter ring (408) and the second adapter ring (409) are both sleeved on the ball screw (404), and the turbine (410) is connected to the first adapter ring (408). A first bearing (414) is provided between the first adapter ring (408) and the actuator housing (403), a second bearing (415) is provided between the second adapter ring (409) and the actuator housing (403), and a third bearing (419) and a fourth bearing (420) are provided between both ends of the worm (411) and the actuator housing; The front end of the actuator housing (403) is connected to the end cover (406), a third sealing ring (418) is provided between the first bearing (414) and the end cover (406), a second sealing ring (417) is provided between the actuator housing (403) and the end cover (406), a first sealing ring (416) is provided between the second bearing (415) and the actuator housing (403), the side end of the actuator housing (403) is connected to the side cover (423), a fourth sealing ring (421) is provided between the actuator housing (403) and the side cover (423), and an oil seal (422) is provided between the side cover (423) and the worm (411); The universal ring mechanism (5) comprises a mounting support (501) and a universal ring (502), the left and right ends of the universal ring (502) are hinged to the mounting support (501) via a horizontal second rotating pin (503), and the front and rear ends of the universal ring (502) are hinged to the actuator housing (403) via a vertical first rotating pin (505); The actuator housing (403) is connected to the first rotating pin (505) via an anti-rotation pin (508); one end of the first rotating pin (505) is clamped with the actuator housing (403), and the other end of the first rotating pin (505) is clamped with a universal ring (502) via a retaining spring (506); one end of the second rotating pin (503) is clamped with the universal ring (502), and the other end of the second rotating pin (503) is clamped with a mounting support (501) via a limiting nut (504).

2. The large unmanned aerial vehicle flap actuator according to claim 1, characterized in that: The front end of the ball screw (404) is an annular actuator joint (401), the joint bearing (402) is arranged on the actuator joint (401), and the rear end of the ball screw (404) is provided with a stop cap (405).

3. The large unmanned aerial vehicle flap actuator according to claim 1, characterized in that: The first adapter ring (408) is provided with a first limiting bushing (412) and a second limiting bushing (413); the first limiting bushing (412) is clamped at the front end of the turbine (410), and the second limiting bushing (413) is clamped at the rear end of the turbine (410).

4. A mounting structure for a large unmanned aerial vehicle flap actuator, comprising the large unmanned aerial vehicle flap actuator according to any one of claims 1 to 3, and further comprising a wing frame (1) and a flap frame (2), wherein the flap frame (2) slides along a flap slide rail (3) on the wing frame (1), characterized in that: The universal ring mechanism (5) is mounted on the wing frame (1), and the flap actuator (4) is connected to the flap frame (2) via a joint bearing (402).

5. The installation structure of the flap actuator of a large unmanned aerial vehicle according to claim 4, characterized in that: It also includes a driving device, which is connected to the worm gear (411) of the flap actuator (4) via a transmission shaft, and the worm gears (411) of two adjacent flap actuators (4) are connected via the transmission shaft.

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