CN219884118U - Synchronous folding/unfolding mechanism for wing surfaces - Google Patents

Abstract

The utility model provides an airfoil synchronous folding/unfolding mechanism, and belongs to the field of unmanned aerial vehicles. The airfoil synchronous folding/unfolding mechanism comprises an upper fixing plate, an upper bearing, a locking mechanism, an actuating mechanism, a rotating main shaft, a lower bearing, an actuator and a lower fixing plate. According to the utility model, a torque rod structure is introduced into the unmanned airfoil folding/unfolding mechanism, and the lengths of a torque rod driving end force arm and a torque rod driven end force arm can be adjusted according to the type and actual needs of an actuator, so that the proportion between the actuating distance of the actuator and the rotating angle of the airfoil and the proportion between the actuating speed of the actuator and the rotating speed of the airfoil are adjusted. The actuating distance of the actuating can be effectively reduced, the structural space is saved, and meanwhile, the unfolding speed of the wing surface can be improved, so that the unmanned aerial vehicle can quickly reach a stable state. When the torque rod is reversely utilized, the unfolding speed of the airfoil can be slowed down, for example, when a fire tool is used as an actuator, the movement speed is reduced, and the impact of the airfoil during unfolding can be effectively reduced.

Description

Synchronous folding/unfolding mechanism for wing surfaces

Technical Field

The utility model belongs to the field of unmanned aerial vehicles, and particularly relates to an airfoil synchronous folding/unfolding mechanism.

Background

Unmanned aerial vehicles are advanced technical weaponry with high efficiency and low risk in modern warfare. The fixed wing unmanned aerial vehicle occupies an important position in the market by virtue of the advantages of simple structure, symmetrical distribution, mature dynamic model, strong portability of a flight control system and the like. However, the fixed wing unmanned aerial vehicle, especially the unmanned aerial vehicle with a large aspect ratio, has a large transverse dimension and is not beneficial to storage. The folding wing unmanned aerial vehicle is folded and stored through the parts such as the unmanned aerial vehicle wing surface and the like, so that the purpose of reducing the transverse size of the unmanned aerial vehicle is achieved. Therefore, the space geometric dimension of the unmanned aerial vehicle can be changed through the folding and unfolding states of the wings in the storage, launching, flying and recycling stages, and the storage and transportation performance, the launching and recycling performance and the aerodynamic performance of the unmanned aerial vehicle are improved. The application range of the unmanned aerial vehicle can be greatly improved through the folding wing technology, and the unmanned aerial vehicle can be widely applied to carrier-borne unmanned aerial vehicles, shooting unmanned aerial vehicles, submerged unmanned aerial vehicles and the like.

At present, a lot of researches have been carried out in the technical field of unmanned wing surface folding/unfolding, and related patents are abundant. After the unmanned aerial vehicle is launched, the higher the wing surface unfolding speed and the higher the unfolding synchronism are, the unmanned aerial vehicle is facilitated to reach a stable state rapidly, and the wing surface actuating, transmission and locking mechanism are required to have the characteristics of high synchronism, quick actuating response and the like.

The prior art deployment mechanism can be divided into: motor drive, pyrotechnic drive, and spring drive. The initiating explosive device driving mode has quick response, but can only drive in one direction, has large impact load and has high structural use requirement; the spring driving mode has moderate actuation response speed, but can only move unidirectionally, and in addition, the spring in the folded state is in a force accumulation state for a long time, so that the spring performance can be influenced; the response speed of the general motor driving structure is slower, but the bidirectional movement can be realized, and the problems of other two actuation modes are avoided.

The mechanism provided by the utility model can solve the problem of slow actuating response in a motor driving mode through structures such as a connecting rod, a lever and the like, and is connected to the same actuating source through a symmetrical driving mechanism so as to ensure the synchronism of the mechanism in the folding/unfolding process. The mechanism provided by the utility model can also adopt driving modes such as a fire machine, a spring and the like so as to further improve the response speed.

Disclosure of Invention

The utility model aims to solve the problems of asynchronous folding/unfolding process, long actuating distance, slow actuating response and the like of the longitudinal folding wing.

The technical scheme of the utility model is as follows:

an airfoil synchronous folding/unfolding mechanism, as shown in FIG. 1, comprises an upper fixing plate 1, an upper bearing 2, a locking mechanism 3, an actuating mechanism 4, a rotating main shaft 5, a lower bearing 6, an actuator 7 and a lower fixing plate 8; the rotating main shaft 5 is fixedly connected with the airfoil 9 and is arranged between the upper fixing plate 1 and the lower fixing plate 8 through the upper bearing 2 and the lower bearing 6, so that the airfoil 9 can be fixed and the airfoil 9 can be ensured to rotate in a low resistance state. The actuating mechanism 4 is connected with a rocker arm of the rotary spindle 5, and the actuator 7 is connected with the actuating mechanism 4; the actuator 7 drives the actuating mechanism 4 to operate the main shaft 5 to rotate clockwise/anticlockwise, so that the wing surface 9 is unfolded/folded. The locking mechanism 3 drives the locking pin to be inserted into/pulled out of the corresponding pin hole of the rotating main shaft 5 in a spring or electric mode and the like, so that the locking/unlocking function of the whole set of mechanism is realized.

Further, the upper bearing 2 is arranged in a corresponding groove of the upper fixing plate 1 in an interference fit manner; the lower bearing 6 is arranged in a corresponding groove of the lower fixing plate 8 in an interference fit mode.

Further, both ends of the rotating main shaft 5 can rotate relative to the upper fixing plate 1 and the lower fixing plate 8 through the upper bearing 2 and the lower bearing 6, respectively.

Further, the rocker arm of the rotating spindle 5 is located at a middle position of the rotating spindle 5.

Further, the upper fixing plate 1 and the locking mechanism 3 are provided on the frame of the machine body.

Further, the actuation mechanism 4 includes a main shaft link 41, a torque-changing lever 42, a torque-changing shaft 43, and an actuation lever 44; one end of the torque rod 42 is provided with a long round hole, and the other end and the middle part are provided with round holes; the actuator 7 is connected with the end of an actuating rod 44, the middle part of the actuating rod 44 is rotationally connected with one end of a torque rod 42 with a slotted hole, the other end of the torque rod 42 is rotationally connected with one end of a main shaft connecting rod 41, the other end of the main shaft connecting rod 41 is rotationally connected with a rocker arm of a rotary main shaft 5, and the middle part of the torque rod 42 is rotationally connected with a torque shaft 43 vertically fixed on a lower fixing plate 8.

The utility model has the beneficial effects that: according to the utility model, a torque rod structure is introduced into the unmanned airfoil folding/unfolding mechanism, and the lengths of a torque rod driving end force arm and a torque rod driven end force arm can be adjusted according to the type and actual needs of an actuator, so that the proportion between the actuating distance of the actuator and the rotating angle of the airfoil and the proportion between the actuating speed of the actuator and the rotating speed of the airfoil are adjusted. The actuating distance of the actuating can be effectively reduced, so that the structural space is saved, and meanwhile, the unfolding speed of the wing surface can be improved, so that the unmanned aerial vehicle can quickly reach a stable state. When the torque rod is reversely utilized, the unfolding speed of the airfoil can be slowed down, for example, when a fire tool is used as an actuator, the movement speed is reduced, and the impact of the airfoil during unfolding can be effectively reduced.

Drawings

FIG. 1 is an exploded view of an airfoil folding/unfolding mechanism.

FIG. 2 is a top view of the airfoil fold and unfold mechanism.

Fig. 3 airfoil folded state (fixed plate 1 on the removed part).

Fig. 4 airfoil deployment (fixed plate 1 on the stripper).

In the figure: 1, a fixing plate is arranged on the upper part; 2 upper bearing; 3, a locking mechanism; 4, an actuating mechanism; 5, rotating the main shaft; 6 lower bearing; 7, an actuator; 8, a lower fixing plate; 9 airfoil surfaces; 41 spindle connecting rod; a 42 torque converter lever; 43 torque converter shaft; 44 act as levers.

Detailed Description

As shown in fig. 1, the upper fixing plate 1 is used as a basis of a wing folding/unfolding mechanism and is mechanically connected with a front bulkhead and a rear bulkhead of the unmanned aerial vehicle body. The upper bearing 2 adopts an angular contact ball bearing, and is tightly assembled with a corresponding groove on the upper fixing plate 1 by adopting a small interference size. The rotating main shaft 5 passes through the inner hole of the upper bearing 2 and is installed in a small clearance fit way. The rotating spindle 5 is then connected to the relevant parts of the actuating mechanism 4. The wing surface 9 presses the lower fixing plate 8 and the lower bearing 6 through the fastening piece to be fixedly connected with the rotating main shaft 5. The actuator 7 employs a reciprocating motor as a power source. The locking mechanism 3 adopts a zipper and spring pin structure. Wherein, the ratio of the moment arm at the driving end and the moment arm at the driven end of the torque rod 42 in the actuating mechanism 4 is 0.55:1, which is used for accelerating the folding/unfolding speed and angle of the airfoil 9.

Specific operation principle is as shown in fig. 2, in the folded state of the airfoil 9, the actuator 7 drives the actuating rod 44 to move forward, the actuating rod 44 drives the upper left torque rod 42 to rotate anticlockwise around the torque shaft 43, the torque rod 42 drives the rotating main shaft 5 and the airfoil 9 to rotate clockwise by pushing the main shaft connecting rod 41, the effect of unfolding the airfoil 9 is achieved, and at the moment, the locking mechanism 3 stretches out of the locking pin to be inserted into the corresponding pin hole of the main shaft 3, and the position of the airfoil 9 is locked. The torque shaft 43 is fixed between the upper and lower fixing plates 1, 8 so that both ends form levers when the torque rod 42 rotates, and the ratio of the driving distance of the actuating rod 44 to the rotation angle response value of the airfoil 9 is adjusted by adjusting the length ratio of the arms at both ends when the torque rod 42 rotates. When the moment arm at the driving end of the torque rod 42 is smaller than the moment arm at the driven end, a larger rotation distance and a faster rotation speed of the airfoil 9 can be realized under the same operation distance and operation speed of the actuator 7. Similarly, the right flank surface is connected by adopting the same structure, and the two side mechanisms are driven by adopting the same actuating source, so that the rotation synchronization of the two side wing surfaces is ensured.

Conversely, when the wing surface 9 is in the unfolded state, the locking mechanism 3 pulls out the locking pin, the actuator 7 drives the actuating rod 44 to move backwards, the actuating rod 44 drives the left torque rod 42 to rotate clockwise around the torque shaft 43, and the torque rod 42 drives the rotating main shaft 5 and the wing surface 9 to rotate anticlockwise by pulling the main shaft connecting rod 41, so that the wing surface folding effect is achieved. The folding process airfoil angle and rotational speed are also amplified due to the lever effect of torque rod 42.

The folding and unfolding states of the whole set of mechanism are shown in fig. 3 and 4, and when the moment arm ratio of the torque rod is adopted and the actuation distance of the actuator is 12mm, the opening and closing angle of the airfoil surface can reach 50 degrees. If the motor with the action speed of 1m/s is selected, the wing surface can be opened only by 1.2ms, the opening time is extremely short, and the flight state of the unmanned aerial vehicle is not influenced basically.

The utility model adopts a torque rod to adjust the proportion between the actuating distance of the actuator and the wing surface rotation angle and the proportion between the actuating speed of the actuator and the wing surface rotation speed. When the moment arm of the moment rod driving end is smaller than the moment arm of the driven end, the actuating distance of the actuator can be reduced, and the wing surface can be accelerated to rotate; similarly, when the moment arm of the driving end of the torque rod is larger than the moment arm of the driven end, the rotation speed of the airfoil can be reduced.

Claims (6)

1. The synchronous folding/unfolding mechanism for the airfoil is characterized by comprising an upper fixing plate (1), an upper bearing (2), a locking mechanism (3), an actuating mechanism (4), a rotating main shaft (5), a lower bearing (6), an actuator (7) and a lower fixing plate (8); the rotary main shaft (5) is fixedly connected with the airfoil (9) and is arranged between the upper fixing plate (1) and the lower fixing plate (8) through the upper bearing (2) and the lower bearing (6); the actuating mechanism (4) is connected with a rocker arm of the rotary spindle (5), and the actuator (7) is connected with the actuating mechanism (4); the locking mechanism (3) drives the locking pin to be inserted into/pulled out of the corresponding pin hole of the rotating main shaft (5) through a spring or an electric mode.

2. The synchronous folding/unfolding mechanism of the airfoil surface according to claim 1, wherein the upper bearing (2) is arranged in a corresponding groove of the upper fixing plate (1) in an interference fit manner; the lower bearing (6) is arranged in a groove corresponding to the lower fixing plate (8) in an interference fit mode.

3. The synchronous folding/unfolding mechanism of the airfoil surface according to claim 1, wherein two ends of the rotating main shaft (5) can rotate relative to the upper fixing plate (1) and the lower fixing plate (8) through the upper bearing (2) and the lower bearing (6) respectively.

4. An airfoil synchronous folding/unfolding mechanism as claimed in claim 1 characterized in that the swing arm of the rotary main shaft (5) is located at a central position of the rotary main shaft (5).

5. An airfoil synchronous folding/unfolding mechanism as claimed in claim 1 characterized in that the upper fixing plate (1) and the locking mechanism (3) are provided on the frame of the fuselage.

6. The synchronous folding/unfolding mechanism for an airfoil according to claim 1, characterized in that the actuating mechanism (4) includes a main shaft connecting rod (41), a torque rod (42), a torque shaft (43) and an actuating rod (44); one end of the torque-changing rod (42) is provided with a long round hole, and the other end and the middle part are provided with round holes; the actuator (7) is connected with the end part of the actuating rod (44), the middle part of the actuating rod (44) is rotationally connected with one end of the torque rod (42) with a slotted hole, the other end of the torque rod (42) is rotationally connected with one end of the main shaft connecting rod (41), the other end of the main shaft connecting rod (41) is rotationally connected with a rocker arm of the rotary main shaft (5), and the middle part of the torque rod (42) is rotationally connected with a torque-changing shaft (43) vertically fixed on the lower fixing plate (8).