A deployment mechanism for a variable configuration wing

Abstract

The present invention discloses a deployment mechanism for a variable configuration wing, belonging to the field of aircraft design technology. The mechanism includes a power mechanism for driving the variable configuration wing to change its configuration and a transmission structure connected to the variable configuration wing. The transmission structure includes an upper cone, a lower cone, an outer cone sleeve, and a rocker arm. The outer cone sleeve is a fixed hollow structure, and its inner diameter increases from the middle toward the two ends, forming an upper cone cavity and a lower cone cavity, respectively. The lower cone, the upper cone, and the rocker arm are connected and fixed as a whole and rotatably connected within the outer cone sleeve. The lower cone is connected to the variable configuration wing, and the rocker arm is connected to the output end of the power mechanism. Under the action of the power mechanism, the rocker arm rotates around the cone axis, thereby driving the variable configuration wing to rotate synchronously and change its configuration. The present invention, through the design of a conical sliding bearing structure, can effectively eliminate the gap between the wing and the fuselage when the cross wing rotates relative to the fuselage, thereby ensuring accurate aerodynamic configuration.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle (UAV) design, and in particular to a deployment mechanism for a variable-configuration wing. Background Art

[0002] In certain application scenarios, drones must operate in both high-speed and low-speed flight modes. For example, when a small drone is deployed from a high-speed platform (such as a fighter jet, bomber, military transport aircraft, or large jet drone), the carrier aircraft may travel at a high speed (over 450 km / hr), while the deployed small drone (sub-drone) is designed for low-speed cruising (around 200 km / hr). To accommodate these two significantly different flight speeds, the drone requires a variable aerodynamic design.

[0003] In the prior art, a Chinese invention patent application with publication number CN109250105A, entitled "A Variable Configuration Supersonic Flying Wing Layout Aircraft and Its Flight Method," discloses the following technical solution: A variable configuration supersonic flying wing layout aircraft, comprising an outer wing and an inner wing, wherein the outer wing folds upward, and the folding angle between the outer wing and the inner wing is 30° to 60°; the folded span length of the outer wing accounts for 45% to 70% of the aircraft's wing span length. The present invention achieves static stability in the aircraft's heading by folding the outer wing upward, facilitating the control of the flying wing layout aircraft and having good practicality. During supersonic flight, the present invention achieves static stability in the aircraft's heading by folding the outer wing upward, facilitating the control of the flying wing layout aircraft.

[0004] The above patent realizes configuration transformation by changing the angle between the outer wing and the inner wing, but does not involve changing the driving structure of the configuration transformation. Since there is currently no deployment mechanism with high positioning accuracy and convenient assembly and positioning in the existing technology, based on this, the present invention provides a deployment mechanism for variable configuration wings. Summary of the Invention

[0005] The present invention aims to solve the problem that there is no reasonable unmanned aircraft configuration transformation mechanism in the prior art, and proposes a deployment mechanism for variable configuration wings. The deployment mechanism can eliminate the gap between rotating parts and ensure positioning accuracy through its structural design.

[0006] In order to achieve the above-mentioned object of the invention, the technical solution of the present invention is as follows:

[0007] A deployment mechanism for a variable configuration wing, characterized in that it includes a power mechanism for driving the variable configuration wing to change its configuration and a transmission structure connected to the variable configuration wing, the transmission structure includes an upper cone, a lower cone, an outer cone sleeve, and a rocker arm, the outer cone sleeve is a fixed hollow structure, and its inner diameter increases sequentially from the middle toward both ends, forming an upper cone cavity and a lower cone cavity respectively; the lower cone, the upper cone and the rocker arm are connected and fixed as a whole and are rotatably connected in the outer cone sleeve, the lower cone is connected to the variable configuration wing, and the rocker arm is connected to the output end of the power mechanism, and under the action of the power mechanism, the rocker arm rotates around the cone axis, thereby driving the variable configuration wing to rotate synchronously to change the configuration.

[0008] Specifically, in a certain embodiment, it further includes a fuselage bulkhead connected to the aircraft, wherein the fuselage bulkhead includes a bottom plate, a through hole is opened on the bottom plate, and the outer cone sleeve passes through the through hole and is fixedly connected to the fuselage bulkhead.

[0009] Specifically, in a certain embodiment, the lower cone, upper cone and rocker arm are all detachably fixedly connected to each other, and the upper cone and the lower cone are respectively located in the upper cone cavity and the lower cone cavity of the outer cone sleeve, and fit with the inner cone surface of the outer cone sleeve.

[0010] Specifically, in one embodiment, screws with different pitches are provided on the upper part of the lower cone, the screw located at the bottom is connected to the upper cone, the screw located at the top is connected to the center of the rocker arm, and the rocker arm is fixedly connected to the upper cone by bolts.

[0011] Specifically, in a certain embodiment, the power mechanism is a fire-actuated actuator, the output end of the fire-actuated actuator is connected to a piston rod, the piston rod is connected to a rocker arm through a connecting rod, and the two ends of the connecting rod are rotationally connected to the piston rod and the rocker arm through a pin shaft.

[0012] Specifically, in one embodiment, a shear pin is provided on the path where the piston rod drives the connecting rod to move through a shear pin seat. The shear pin passes through the connecting rod body, so that the variable configuration wing is maintained in a small aspect ratio configuration.

[0013] Specifically, in a certain embodiment, a locking mechanism is provided on the pyrotechnic actuator for placing the variable configuration wing in a high aspect ratio configuration.

[0014] In summary, the present invention has the following advantages:

[0015] 1. The present invention utilizes a conical sliding bearing structure to effectively eliminate the gap between the wing and the fuselage when the variable configuration wing rotates relative to the fuselage through the conical surface constraint, ensuring accurate aerodynamic configuration. At the same time, the conical surface constraint transfers the wing lift to the fuselage structure in the form of a distributed force, creating favorable structural stress conditions.

[0016] 2. The mechanism of the present invention is easily adjustable, reducing the manufacturing precision requirements for individual parts. Final positioning of the mechanism is achieved by directly measuring the pneumatic configuration. By utilizing the stroke margin of the pyrotechnic actuator, the effects of machining errors in the transmission components on the two pneumatic configurations can be effectively eliminated. This reduces the manufacturing precision requirements for individual parts and reduces manufacturing costs.

[0017] 3. The assembly and positioning of the deployment mechanism of the present invention can ensure accurate pneumatic configuration and is simple. The mechanism positioning is completed by measuring and confirming the final pneumatic configuration, ensuring accurate pneumatic configuration; the positioning process is simple and reliable.

[0018] 4. In the solution of the present invention, two screws with different pitches are arranged at intervals on the upper part of the lower cone, which are respectively connected to the rocker arm and the upper cone, and the upper cone and the rocker arm are fixedly connected by bolts, so that the sliding bearing structure composed of the upper cone, lower cone, rocker arm and outer cone sleeve is integrated, and no relative rotation occurs, thereby ensuring the reliability of the transmission. At the same time, such a structural design is also convenient for adjustment and disassembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of a cross-shaped wing configuration variation according to the present invention;

[0020] Figure 2 It is a schematic diagram of the overall structure of the present invention;

[0021] Figure 3 Schematic diagram of the transmission structure of the present invention;

[0022] Figure 4 Schematic diagram of the transmission structure position when the wing is in a low aspect ratio configuration;

[0023] Figure 5 Schematic diagram of the transmission structure position when the wing is in a high aspect ratio configuration;

[0024] Figure 6 This is a schematic diagram of positioning measurement of the large-ratio configuration of the wing of the present invention;

[0025] Figure 7 This is a schematic diagram of positioning measurement of the wing with a small aspect ratio configuration of the present invention;

[0026] Figure 8 This is a schematic diagram of Scheme 1 in Example 4;

[0027] In the picture:

[0028] 1. Power mechanism, 2. Variable configuration wing, 3. Transmission structure, 301. Rocker arm, 302. Upper cone, 303. Lower cone, 304. Connecting rod, 305. Piston rod, 4. Outer cone sleeve, 5. Fuselage bulkhead, 6. Pin, 7. Shear pin, 8. Shear pin seat, 9. Locking mechanism, 10. Screw, 11. Hinge, 12. Fuselage position, 13. Wing trailing edge tip, 14. Cone axis. DETAILED DESCRIPTION

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0030] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are intended to fall within the scope of protection of the present invention.

[0031] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0032] In the description of the present invention, it should be noted that the terms "upper," "vertical," "inner," "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the inventive product is typically placed when in use, or are commonly understood by those skilled in the art. These terms are intended solely to facilitate the description of the present invention and simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," etc., are used solely to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0033] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0034] Example 1

[0035] This embodiment provides a deployment mechanism for a variable configuration wing, wherein the variable configuration wing 2 is a cross-shaped wing, including a large-span wing and a small-span wing. The large-span wing and the small-span wing are arranged at 90° in span, forming a "cross-shaped" layout. The center of the cross wing is connected to the fuselage through a transmission and connection structure similar to a bearing, and can rotate relative to the fuselage. When the large-span wing is facing the fuselage, the sub-machine is in a small aspect ratio configuration; when the small-span wing is facing the fuselage, the sub-machine is in a large aspect ratio configuration. The cross wing can be rotated 90° by a power device inside the fuselage to achieve configuration change.

[0036] The configuration scheme is as attached Figure 1 As shown: A low aspect ratio configuration is used during mounting / deployment. The shape and size of the low aspect ratio wing are determined according to the high-speed flight conditions during deployment. Figure 1 ; A high aspect ratio configuration is used during mission cruise. The shape and size of the high aspect ratio wing are determined according to the flight conditions during mission cruise. Figure 1 .

[0037] Specifically, the overall structure of the expansion mechanism is as follows Figure 2 As shown, it includes an actuator for driving the variable configuration wing 2 to change its configuration and a transmission structure 3 connected to the variable configuration wing 2.

[0038] like Figure 3 As shown, the transmission structure 3 comprises an upper cone 302, a lower cone 303, an outer cone sleeve 4, and a rocker arm 301. The outer cone sleeve 4 is a fixed, funnel-shaped hollow structure whose inner diameter increases from the center toward its ends, forming an upper cone cavity and a lower cone cavity, respectively. The outer cone sleeve 4 is connected to the fuselage bulkhead 5, which comprises a base plate and two opposing vertical plates disposed on the base plate. The base plate has a through-hole through which the outer cone sleeve 4 is fixedly mounted to the fuselage bulkhead 5. The lower cone 303, upper cone 302, and rocker arm 301 are connected and fixed as a single unit and rotatably attached within the outer cone sleeve 4. The lower cone 303 is connected to the variable configuration wing 2, and the rocker arm 301 is connected to the output end of the power mechanism 1. Under the action of the power mechanism 1, the rocker arm 301 rotates about the cone axis 14, thereby driving the variable configuration wing 2 to rotate synchronously and change its configuration.

[0039] Specifically, such as Figure 3As shown, the lower cone 303 passes through the outer cone sleeve 4 from below. The lower portion of the lower cone 303 is fixedly connected to the center of the variable configuration wing 2. The upper portion of the lower cone 303 is provided with a screw 10 for connecting to the upper cone 302. The outer conical surfaces of the upper cone 302 and the lower cone 303 respectively match the upper and lower conical cavities of the outer cone sleeve 4. That is, the outer conical surface at the lower position of the lower cone 303 fits the inner conical surface of the lower conical cavity, and the outer conical surface of the upper cone 302 fits the inner conical surface of the upper conical cavity. The conical surfaces can slide and rotate to realize the rotation of the cross-shaped wing assembly and complete the aerodynamic configuration transformation. In addition, the conical surface constraint effectively eliminates the mechanism gap, ensuring that the aerodynamic configuration is fixed and accurate.

[0040] Example 2

[0041] This embodiment provides a deployment mechanism for a variable configuration wing. Based on Example 1, two screws 10 with different pitches are further spaced apart on the upper portion of the lower cone 303. The lower screw 10 is connected to the upper cone 302, while the upper screw 10 is connected to the rocker arm 301. Furthermore, the rocker arm 301 and the upper cone 302 are removably fixed together by screws. Due to the different pitches of the screws 10, when the rocker arm 301 rotates about the conical axis 14 under the drive of the power mechanism 1, the rocker arm 301, the upper cone 302, and the lower cone 303 can maintain a removable fixed connection with each other without relative rotation, thus ensuring transmission reliability.

[0042] Example 3

[0043] This embodiment provides a deployment mechanism for a variable configuration wing. Based on the first embodiment, the power mechanism 1 further utilizes a pyrotechnic actuator. The output end of the pyrotechnic actuator is connected to a piston rod 305, and the end of the piston rod 305 is connected to one end of a rocker arm 301 via a connecting rod 304. The ends of the connecting rod 304 are rotatably connected to the rocker arm 301 and the piston rod 305, respectively. Specifically, the rocker arm 301 and the connecting rod 304 are connected by a pin 6, and the connecting rod 304 and the piston rod 305 are also connected by a pin 6.

[0044] The transmission relationship of the configuration change mechanism is as follows: the piston rod 305 is driven by the pyrotechnic actuator. When the piston rod 305 extends and retracts along its axis (linear motion), it drives the rocker arm 301 to rotate about the conical axis through the connecting rod 304, thereby driving the variable configuration wing 2 to rotate. A shear pin 7 is provided through the shear pin seat 8 on the path of the piston rod 305 driving the connecting rod 304. In the initial position (see attached Figure 4), the rocker arm 301 is positioned at an angle so that the short span of the variable configuration wing 2 is perpendicular to the fuselage. At this time, the position of the rocker arm 301 is locked by the shear pin 7; when the pyrotechnic actuator is started, the piston rod 305 pulls the connecting rod 304 to cut the shear pin 7, pulling the rocker arm 301 to rotate; when the rocker arm 301 rotates 90°, the locking mechanism 9 provided on the pyrotechnic actuator locks the actuator (see attached Figure 5 ), so that the cross wing is fixed in a position with a large wingspan perpendicular to the fuselage.

[0045] The assembly and positioning method of the deployment mechanism has the following specific steps:

[0046] First, put the piston rod 305 into the fire actuator and lock the fire actuator locking mechanism 9; make the deployment mechanism Figure 5 The position shown is measured with the cross wing's maximum span perpendicular to the fuselage, such as Figure 6 As shown, the distance from the nose reference point to the wingtip reference point with the largest wingspan is equal; in this state, the actuator is fixed to the fuselage by drilling the actuator mounting screw holes, and the mechanism is positioned in this state.

[0047] Then, unlock the actuator locking mechanism 9 and rotate the cross wing in the opposite direction (the direction of rotation is opposite to the actual working direction) to make the deployment mechanism Figure 4 The measurement standard is that the cross winglet is perpendicular to the fuselage, such as Figure 7 As shown, the distance from the nose reference point to the small span wingtip reference point is equal; in this state, the mechanism is positioned in this state by drilling shear pin holes on the shear pin seat 8.

[0048] Example 4

[0049] As an optional implementation of the present invention, this embodiment provides a deployment mechanism for a variable configuration wing. Unlike Example 1, the rotation of the cross wing can be achieved by other methods.

[0050] Option 1:

[0051] The fire actuator has the characteristics of simple and reliable use, and is suitable for use in aviation products. Fire actuators generally move in a straight line. However, this solution converts the straight line motion of the fire actuator into the rotational motion of the rocker arm 301 through the connecting rod 304. You can also use the following Figure 8 The method shown converts the linear motion of the actuator into the rotation of the rocker arm 301. This solution requires that the actuator can swing freely, that is, the connection between the actuator and the fuselage needs to be achieved through the hinge 11.

[0052] Option 2:

[0053] The spring is used to replace the fire actuator. The following mechanisms need to be added:

[0054] First, in the initial position (small aspect ratio configuration), a locking and releasing device is added to the design mechanism, which must be released by an external force when the mechanism is in motion;

[0055] Then, in the final position (high aspect ratio configuration), a mechanism locking device is added that automatically locks after the mechanism is rotated into position.

[0056] Although the specific embodiments of the present invention are described in detail in conjunction with the accompanying drawings, this should not be construed as limiting the scope of protection of this patent. Within the scope described by the claims, various modifications and variations that can be made by those skilled in the art without creative work still fall within the scope of protection of this patent.

[0057] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A deployment mechanism for a variable configuration wing, characterized in that: The invention comprises a power mechanism (1) for driving a variable configuration wing (2) to change its configuration and a transmission structure (3) connected to the variable configuration wing (2), wherein the transmission structure (3) comprises an upper cone (302), a lower cone (303), an outer cone sleeve (4), and a rocker arm (301), wherein the outer cone sleeve (4) is a fixed hollow structure, and its inner diameter increases from the middle toward both ends, forming an upper cone cavity and a lower cone cavity respectively; the lower cone (303), the upper cone (302), and the rocker arm (301) are connected and fixed as a whole, and are rotatably connected in the outer cone sleeve (4); the lower cone (303) is connected to the variable configuration wing (2), and the rocker arm (301) is connected to the output end of the power mechanism (1); under the action of the power mechanism (1), the rocker arm (301) rotates around the cone axis (14), thereby driving the variable configuration wing (2) to rotate synchronously and change its configuration.

2. The deployment mechanism of a variable configuration wing according to claim 1, characterized in that: It also includes a fuselage bulkhead (5) connected to the aircraft, wherein the fuselage bulkhead (5) includes a bottom plate, a through hole is provided on the bottom plate, and the outer cone sleeve (4) passes through the through hole and is fixedly connected to the fuselage bulkhead (5).

3. The deployment mechanism of a variable configuration wing according to claim 1, characterized in that: The lower cone (303), the upper cone (302) and the rocker arm (301) are all detachably fixedly connected to each other. The upper cone (302) and the lower cone (303) are respectively located in the upper cone cavity and the lower cone cavity of the outer cone sleeve (4) and fit in contact with the inner cone surface of the outer cone sleeve (4).

4. The deployment mechanism of a variable configuration wing according to claim 1, characterized in that: The upper portion of the lower cone (303) is provided with screws (10) with different pitches. The screw (10) located at the lower portion is connected to the upper cone (302), and the screw (10) located at the upper portion is connected to the center of the rocker arm (301). The rocker arm (301) and the upper cone (302) are fixedly connected by bolts.

5. The deployment mechanism of a variable configuration wing according to claim 1, characterized in that: The power mechanism (1) is a fire-actuated actuator, the output end of which is connected to a piston rod (305), the piston rod (305) being connected to a rocker arm (301) via a connecting rod (304), and the two ends of the connecting rod (304) being rotationally connected to the piston rod (305) and the rocker arm (301) respectively via a pin.

6. The deployment mechanism of a variable configuration wing according to claim 5, characterized in that: A shear pin (7) is provided on a path where the piston rod (305) drives the connecting rod (304) to move, via a shear pin seat (8). The shear pin (7) passes through the connecting rod (304) body, thereby maintaining the variable configuration wing (2) in a small aspect ratio configuration.

7. The deployment mechanism of a variable configuration wing according to claim 5, characterized in that: The pyrotechnic actuator is provided with a locking mechanism (9) for placing the variable configuration wing (2) in a high aspect ratio configuration.

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