Coaxial folding wing mechanism of unmanned aerial vehicle

Abstract

The invention provides an unmanned aerial vehicle coaxial folding wing mechanism which comprises a right wing, a left wing, a directional base, a right wing rotating shaft upper bearing, a right wing rotating shaft lower bearing, a right wing rotating shaft, an actuating cylinder, a limiting pin, an actuating rod, a left wing rotating shaft upper bearing, a left wing rotating shaft lower bearing and a left wing rotating shaft. After the unmanned aerial vehicle goes out of the cylinder, the actuating cylinder pushes the actuating rod to drive the limiting pin to linearly move upwards from the bottom end of the directional base guide groove, and the right wing rotating shaft and the left wing rotating shaft are forced to synchronously rotate in opposite directions through the right wing rotating shaft guide groove and the left wing rotating shaft guide groove, so that the right wing and the left wing are driven to synchronously and stably spread. According to the technical scheme, the technical problems that in the prior art, an unmanned aerial vehicle folding wing mechanism is complex in structure, and wing unfolding stability and synchronism are insufficient can be solved.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle (UAV) structural design, and in particular relates to a coaxial folding wing mechanism for an unmanned aerial vehicle (UAV). Background Art

[0002] Small drones and swarm drones need to be stored in launch tubes or launch boxes when they are in storage or waiting to be launched. Traditional fixed-wing drone wings are mostly designed in an integrated or segmented assembly, with a long wingspan, requiring a large storage space and a long launch preparation time. Folding-wing drones can reduce the lateral size of the drone by folding their wings, improve the storage efficiency of the box, and the wings will automatically pop open after the drone is launched, reducing the launch preparation time.

[0003] Currently, most UAV folding wing designs adopt an up-and-down arrangement of the wings. When the wings are unfolded, the left and right wings are prone to unfolding asynchronously. The unequal wing sweep angles cause the fuselage to be subjected to an additional rolling torque, affecting the rolling stability of the UAV during the wing unfolding stage.

[0004] The driving force for the folding wings of drones is currently provided by elastic mechanisms such as tension springs and torsion springs or motor drives. The elastic mechanism is large in size, occupies a large space inside the body, and the elastic parts have a complex structure. There is a risk of metal fatigue failure in long-term storage; the motor drive needs to be driven by meshing of worm gears and gear sets, which has poor synchronization, a complex structure and slow wing deployment. Summary of the invention

[0005] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0006] The invention provides a coaxial folding wing mechanism of an unmanned aerial vehicle, which comprises: a right wing, a left wing, a directional base, an upper bearing of a right wing rotating shaft, a lower bearing of a right wing rotating shaft, a right wing rotating shaft, an actuating cylinder, a limit pin, an actuating rod, an upper bearing of a left wing rotating shaft, a lower bearing of a left wing rotating shaft and a left wing rotating shaft. The left wing and the right wing are stacked up and down along the longitudinal direction of the unmanned aerial vehicle, the root of the right wing is fixedly connected to the right wing rotating shaft, and the root of the left wing is fixedly connected to the left wing rotating shaft; the right wing rotating shaft is installed inside the directional base through the upper bearing of the right wing rotating shaft and the lower bearing of the right wing rotating shaft, and the left wing rotating shaft is installed inside the right wing rotating shaft through the upper bearing of the left wing rotating shaft and the lower bearing of the left wing rotating shaft; the shaft cylinder of the directional base has two directional base guide grooves which are straight in a vertical direction of the unmanned aerial vehicle, and the right wing rotating shaft is fixedly connected to the left wing rotating shaft. The shaft cylinder of the shaft has two right wing shaft guide grooves which are in a zigzag shape along the vertical direction of the UAV, and the shaft cylinder of the left wing shaft has two left wing shaft guide grooves which are in a zigzag shape along the vertical direction of the UAV; the guiding direction of the right wing shaft guide groove is opposite to that of the left wing shaft guide groove; one end of the actuating rod is connected to the actuating cylinder, and the other end is located inside the left wing shaft and is connected to the limit pin; the limit pin passes through the directional base guide groove, the right wing shaft guide groove and the left wing shaft guide groove in sequence from the outside to the inside, and is connected to the actuating rod; wherein, after the UAV comes out of the cylinder, the actuating cylinder pushes the actuating rod to drive the limit pin to move straight upward from the bottom end of the directional base guide groove, and through the right wing shaft guide groove and the left wing shaft guide groove, the right wing shaft and the left wing shaft are forced to rotate synchronously in opposite directions, thereby driving the right and left wings to unfold synchronously and smoothly.

[0007] Furthermore, the directional base guide groove of the directional base, the right wing shaft guide groove of the right wing shaft, and the left wing shaft guide groove of the left wing shaft maintain a consistent height along the vertical direction of the drone.

[0008] Furthermore, the right wing rotating shaft guide groove of the right wing rotating shaft and the left wing rotating shaft guide groove of the left wing rotating shaft are both in a three-section broken line shape.

[0009] Furthermore, the other end of the actuating rod is provided with a pin hole, and the limiting pin is inserted into the pin hole and moves with the actuating rod.

[0010] Furthermore, the coaxial folding wing mechanism of the UAV also includes two retaining rings, which are respectively located at both ends of the limit pin and are used to limit the installation position of the limit pin.

[0011] Furthermore, the coaxial folding wing mechanism of the UAV also includes a bottom cover, which is located at the bottom of the directional base away from the wing. The bottom cover blocks the directional base and is fixedly connected to the actuator cylinder.

[0012] Furthermore, the actuator is a gas actuator, fuel is filled inside the actuator, and gas is generated instantly after the gas actuator is triggered to push the actuator rod.

[0013] Furthermore, when the UAV is in standby mode, the left wing and the right wing are longitudinally folded and stored in the launch tube, and the limit pins are located at the bottom of each guide groove along the vertical direction of the UAV.

[0014] Furthermore, when the actuating rod reaches the top of each guide groove, the wing deployment action is completed, the limit pin stops at the upper end of the right wing shaft guide groove and the left wing shaft guide groove, the rotating sub-mechanics is self-locked, and the UAV wings maintain the set deployment angle; the actuating cylinder continues to act on the bottom of the actuating rod to lock the height position of the limit pin, and the limit pin remains in the upper position during the flight of the UAV.

[0015] Furthermore, after the UAV is recovered, the residual gas inside the actuator cylinder is released, the retaining ring is unscrewed, the limit pin is pulled out, the right wing and the left wing are folded into place, the limit pin is inserted back, and the retaining ring is screwed back to complete the resetting of the folding wing mechanism.

[0016] By applying the technical solution of the present invention, a coaxial folding wing mechanism for a UAV is provided. When the UAV is on standby, the wings are folded and stored in the launch tube; after the UAV is out of the tube, the coaxial rotating shaft is driven by the actuator to rotate and unfold the wings, which has a fast response speed and a simple and reliable structure. At the same time, the coaxial rotating shaft mechanism allows the left and right wings to remain synchronized throughout the entire unfolding process, ensuring the rolling stability of the UAV. Compared with the prior art, the technical solution of the present invention can solve the technical problems of the complex structure of the UAV folding wing mechanism and the insufficient stability and synchronization of the wing unfolding in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 It shows a cross-sectional view of a coaxial folding wing mechanism of a UAV in a state where the wings are folded in place according to a specific embodiment of the present invention;

[0019] Figure 2 A schematic diagram of a coaxial folding wing mechanism of a UAV is shown in a state where the wings are folded in place according to a specific embodiment of the present invention;

[0020] Figure 3 A schematic diagram of a coaxial folding wing mechanism of a drone in a wing-opening state according to a specific embodiment of the present invention is shown;

[0021] Figure 4It shows a schematic diagram of the rotating shaft state of the coaxial folding wing mechanism of the UAV when the wing is fully opened according to a specific embodiment of the present invention;

[0022] Figure 5 A schematic structural diagram of an actuating cylinder, an actuating rod, a stop pin and a retaining ring provided according to a specific embodiment of the present invention is shown;

[0023] Figure 6 A cross-sectional view of a coaxial folding wing mechanism of a UAV (excluding the wing) is shown in a state where the wing is fully opened according to a specific embodiment of the present invention;

[0024] Figure 7 A schematic structural diagram of a directional base provided according to a specific embodiment of the present invention is shown;

[0025] Figure 8 It shows a schematic structural diagram of a right wing shaft provided according to a specific embodiment of the present invention;

[0026] Fig. 9 A schematic structural diagram of a left wing shaft provided according to a specific embodiment of the present invention is shown.

[0027] The above drawings include the following reference numerals:

[0028] 1. Right wing; 2. Left wing; 3. Directional base; 4. Upper bearing of right wing shaft; 5. Lower bearing of right wing shaft; 6. Right wing shaft; 7. Bottom cover; 8. Actuator; 9. Limit pin; 10. Actuator rod; 11. Retaining ring; 12. Upper bearing of left wing shaft; 13. Lower bearing of left wing shaft; 14. Left wing shaft; 15. Guide groove of directional base; 16. Guide groove of right wing shaft; 17. Guide groove of left wing shaft. DETAILED DESCRIPTION

[0029] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in 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. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0031] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present invention. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0032] like Figures 1 to 9 As shown, according to a specific embodiment of the present invention, a coaxial folding wing mechanism of a UAV is provided, and the coaxial folding wing mechanism of the UAV comprises: a right wing 1, a left wing 2, a directional base 3, an upper bearing 4 of a right wing rotating shaft, a lower bearing 5 of a right wing rotating shaft, a right wing rotating shaft 6, an actuating cylinder 8, a stop pin 9, an actuating rod 10, an upper bearing 12 of a left wing rotating shaft, a lower bearing 13 of a left wing rotating shaft and a left wing rotating shaft 14,

[0033] The left wing 2 and the right wing 1 are stacked up and down along the longitudinal direction of the UAV, the right wing root is fixedly connected to the right wing shaft 6, and the left wing root is fixedly connected to the left wing shaft 14;

[0034] The right wing shaft 6 is installed inside the directional base 3 through the right wing shaft upper bearing 4 and the right wing shaft lower bearing 5, and the left wing shaft 14 is installed inside the right wing shaft 6 through the left wing shaft upper bearing 12 and the left wing shaft lower bearing 13;

[0035] The shaft cylinder of the directional base 3 has two directional base guide grooves 15 which are straight along the vertical direction of the drone, the shaft cylinder of the right wing shaft 6 has two right wing shaft guide grooves 16 which are folded along the vertical direction of the drone, and the shaft cylinder of the left wing shaft 14 has two left wing shaft guide grooves 17 which are folded along the vertical direction of the drone; the guiding directions of the right wing shaft guide groove 16 and the left wing shaft guide groove 17 are opposite;

[0036] One end of the actuating rod 10 is connected to the actuating cylinder 8, and the other end is located inside the left wing shaft 14 and connected to the limit pin 9;

[0037] The limit pin 9 passes through the directional base guide groove 15, the right wing shaft guide groove 16 and the left wing shaft guide groove 17 from the outside to the inside in sequence, and is connected to the actuating rod 10;

[0038] Among them, after the UAV comes out of the tube, the actuator cylinder 8 pushes the actuator rod 10 to drive the limit pin 9 to move straight upward from the bottom end of the directional base guide groove 15, and through the right wing shaft guide groove 16 and the left wing shaft guide groove 17, the right wing shaft 6 and the left wing shaft 14 are forced to rotate synchronously in opposite directions, thereby driving the right and left wings to unfold synchronously and smoothly.

[0039] This configuration method is used to provide a coaxial folding wing mechanism for UAVs. When the UAV is on standby, the wings are folded and stored in the launch tube; after the UAV is out of the tube, the coaxial shaft is driven by the actuator to rotate and unfold the wings, which has a fast response speed and a simple and reliable structure. At the same time, the coaxial shaft mechanism allows the left and right wings to remain synchronized throughout the entire unfolding process, ensuring the rolling stability of the UAV.

[0040] As a specific embodiment of the present invention, the directional base guide groove 15 of the directional base 3, the right wing shaft guide groove 16 of the right wing shaft 6, and the left wing shaft guide groove 17 of the left wing shaft 14 can be set to maintain the same height along the vertical direction of the drone.

[0041] In addition, if Figure 8 and 9 As shown, the right wing shaft guide groove 16 of the right wing shaft 6 and the left wing shaft guide groove 17 of the left wing shaft 14 may also be arranged to be in a three-section broken line shape.

[0042] In the present invention, the right wing shaft 6 and the left wing shaft 14 are coaxially located in the directional base 3, and the directional base 3, the right wing shaft 6 and the left wing shaft 14 are all hollow cylindrical, and corresponding guide grooves are set on their respective shaft cylinders. The directional base 3 and the actuator 8 are fixed on the body structure.

[0043] As another specific embodiment of the present invention, the actuator 8 may be a gas actuator, which is filled with fuel. When the gas actuator is triggered, gas is generated instantly to push the actuator rod 10.

[0044] After the UAV is recovered, the gas actuator cylinder 8 is cleaned and refilled with fuel after passing the launch condition test, so that the mechanism can be reused.

[0045] Furthermore, in the present invention, the other end of the actuating rod 10 has a pin hole, and the limiting pin 9 is inserted into the pin hole and moves with the actuating rod 10 .

[0046] In addition, in the present invention, the coaxial folding wing mechanism of the UAV further includes two retaining rings 11 , which are respectively located at the two ends of the limit pin 9 and are used to limit the installation position of the limit pin 9 .

[0047] As a specific embodiment of the present invention, threaded sections may be machined at both ends of the limit pin 9 , the interior of the retaining ring 11 is a threaded hole, and the limit pin 9 is threadedly connected to the retaining ring 11 .

[0048] With this configuration, when the UAV is recovered, the residual gas inside the gas actuator 8 is released, the retaining ring 11 is unscrewed, the limit pin 9 is pulled out, the right wing 1 and the left wing 2 are folded into place, the limit pin 9 is inserted back, and the retaining ring 11 is screwed back to complete the reset of the folding wing mechanism.

[0049] Furthermore, in the present invention, the coaxial folding wing mechanism of the UAV also includes a bottom cover 7, which is located at the bottom of the directional base 3 away from the wing. The bottom cover 7 blocks the directional base 3 and is fixedly connected to the actuator 8.

[0050] As a specific embodiment of the present invention, the bottom cover 7 is fixedly connected to the directional base 3 and the actuator 8 by bolts.

[0051] The working principle of the present invention is as follows:

[0052] When the UAV is in standby mode, the left wing 2 and the right wing 1 are folded and stored in the launch tube, and the limit pin 9 is located at the bottom of each guide groove along the vertical direction of the UAV.

[0053] After the drone leaves the tube, the gas actuator 8 is triggered to generate gas instantly, pushing the actuator rod 10 to drive the limit pin 9 to move straight upward along the directional base guide groove 15. During the upward movement of the limit pin 9, the right wing shaft 6 and the left wing shaft 14 are forced to rotate synchronously in opposite directions through the right wing shaft guide groove 16 and the left wing shaft guide groove 17, so that the right and left wings can be deployed synchronously and smoothly.

[0054] When the actuator rod 10 reaches the top of each guide groove, the wing deployment action is completed, the limit pin 9 stops at the upper straight section of the right wing shaft guide groove 16 and the left wing shaft guide groove 17, the rotary auxiliary mechanism is self-locked, and the drone wing maintains the set deployment angle. The residual gas pressure inside the gas actuator cylinder 8 continues to act on the bottom of the actuator rod 10, locking the height position of the limit pin 9, and the limit pin 9 remains in the upper position during the flight of the drone.

[0055] After the UAV is recovered, the residual gas in the gas actuator 8 is released, the retaining ring 11 is unscrewed, the limit pin 9 is pulled out, the right wing 1 and the left wing 2 are folded into place, the limit pin 9 is inserted back, and the retaining ring 11 is screwed back to complete the reset of the folding wing mechanism.

[0056] The folding wing mechanism of the present invention is mainly used for small UAVs and cluster UAVs, and has the following beneficial effects compared with the prior art:

[0057] (1) This mechanism ensures that the wings of the drone unfold quickly after launch, and the left and right wings rotate coaxially at the same time. The entire unfolding process always maintains state synchronization, ensuring the stability of the drone in the initial stage of flight;

[0058] (2) The mechanism relies on mechanical limit rigid transmission, has no elastic elements or gear sets, and the deployment process is smooth, with a simple and reliable structure;

[0059] (3) The multi-axis coaxial design adopted by the mechanism compresses the volume of the transmission mechanism, improves the utilization rate of the internal space of the UAV body, and can be reused as needed, which helps to achieve low-cost design of the UAV.

[0060] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0061] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0062] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A coaxial folding wing mechanism for an unmanned aerial vehicle, characterized in that: The unmanned aerial vehicle coaxial folding wing mechanism comprises: a right wing (1), a left wing (2), a directional base (3), an upper bearing of a right wing rotating shaft (4), a lower bearing of a right wing rotating shaft (5), a right wing rotating shaft (6), an actuating cylinder (8), a stop pin (9), an actuating rod (10), an upper bearing of a left wing rotating shaft (12), a lower bearing of a left wing rotating shaft (13) and a left wing rotating shaft (14). The left wing (2) and the right wing (1) are stacked up and down along the longitudinal direction of the drone, the right wing root is fixedly connected to the right wing shaft (6), and the left wing root is fixedly connected to the left wing shaft (14); The right wing rotating shaft (6) is installed inside the directional base (3) through the right wing rotating shaft upper bearing (4) and the right wing rotating shaft lower bearing (5), and the left wing rotating shaft (14) is installed inside the right wing rotating shaft (6) through the left wing rotating shaft upper bearing (12) and the left wing rotating shaft lower bearing (13); The shaft cylinder of the directional base (3) has two directional base guide grooves (15) in a straight line along the vertical direction of the drone, the shaft cylinder of the right wing shaft (6) has two right wing shaft guide grooves (16) in a broken line along the vertical direction of the drone, and the shaft cylinder of the left wing shaft (14) has two left wing shaft guide grooves (17) in a broken line along the vertical direction of the drone; the guiding directions of the right wing shaft guide groove (16) and the left wing shaft guide groove (17) are opposite; One end of the actuating rod (10) is connected to the actuating cylinder (8), and the other end is located inside the left wing shaft (14) and connected to the limit pin (9); The limit pin (9) passes through the directional base guide groove (15), the right wing shaft guide groove (16) and the left wing shaft guide groove (17) from the outside to the inside in sequence, and is connected to the actuating rod (10); After the UAV is ejected from the tube, the actuating cylinder (8) pushes the actuating rod (10) to drive the limit pin (9) to move straight upward from the bottom end of the directional base guide groove (15), and through the right wing shaft guide groove (16) and the left wing shaft guide groove (17), the right wing shaft (6) and the left wing shaft (14) are forced to rotate synchronously in opposite directions, thereby driving the right and left wings to unfold synchronously and smoothly.

2. The coaxial folding wing mechanism of the drone according to claim 1, characterized in that: The directional base guide groove (15) of the directional base (3), the right wing shaft guide groove (16) of the right wing shaft (6), and the left wing shaft guide groove (17) of the left wing shaft (14) maintain a consistent height along the vertical direction of the drone.

3. The coaxial folding wing mechanism of the UAV according to claim 1, characterized in that: The right wing rotating shaft guide groove (16) of the right wing rotating shaft (6) and the left wing rotating shaft guide groove (17) of the left wing rotating shaft (14) are both in a three-section broken line shape.

4. The coaxial folding wing mechanism of the UAV according to claim 1, characterized in that: The other end of the actuating rod (10) is provided with a pin hole, and the limiting pin (9) is inserted into the pin hole and moves along with the actuating rod (10).

5. The coaxial folding wing mechanism of a drone according to any one of claims 1 to 4, characterized in that: The drone coaxial folding wing mechanism further comprises two retaining rings (11), which are respectively located at two ends of the limit pin (9) and are used to limit the installation position of the limit pin (9).

6. The coaxial folding wing mechanism of the drone according to claim 1, characterized in that: The drone coaxial folding wing mechanism also includes a bottom cover (7), which is located at the bottom of the directional base (3) away from the wing. The bottom cover (7) blocks the directional base (3) and is fixedly connected to the actuator cylinder (8).

7. The coaxial folding wing mechanism of the drone according to claim 1, characterized in that: The actuator cylinder (8) is a gas-fired actuator cylinder, the interior of which is filled with fuel. When the gas-fired actuator cylinder is triggered, gas is generated instantly to push the actuator rod (10).

8. The coaxial folding wing mechanism of the drone according to claim 1, characterized in that: When the drone is in standby mode, the left wing (2) and the right wing (1) are longitudinally folded and stored in the launch tube, and the limit pin (9) is located at the bottom of each guide groove along the vertical direction of the drone.

9. The coaxial folding wing mechanism of the drone according to claim 1, characterized in that: When the actuating rod (10) reaches the top of each guide groove, the wing deployment action is completed, the limit pin (9) stops at the upper end of the right wing shaft guide groove (16) and the left wing shaft guide groove (17), the rotary auxiliary mechanism is self-locked, and the UAV wing maintains the set deployment angle; the actuating cylinder (8) continues to act on the bottom of the actuating rod (10) to lock the height position of the limit pin (9), and the limit pin (9) remains in the upper position during the flight of the UAV.

10. The coaxial folding wing mechanism of the drone according to claim 5, characterized in that: After the UAV is recovered, the residual gas in the actuator cylinder (8) is released, the retaining ring (11) is unscrewed, the limit pin (9) is pulled out, the right wing (1) and the left wing (2) are folded into place, the limit pin (9) is inserted back, and the retaining ring (11) is screwed back to complete the resetting of the folding wing mechanism.

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