Airfoil extension and retraction control mechanism

Abstract

The invention provides an airfoil extension control mechanism, which comprises a rotating disc, the shaft part of the rotating disc is fixedly connected with a motor connecting shaft, and the rotating disc is driven by the motor connecting shaft to rotate; a control shaft is fixed on the outer ring of the rotating disc; the movement control mechanism is arranged on one side of the rotating disc and can do linear reciprocating motion along the plane where the rotating disc is located; the wing surface is fixed on the movement control mechanism; a guide hole is formed in the moving control mechanism, and at least part of the guide hole and the moving direction of the moving control mechanism are arranged at an angle; the control shaft is inserted into the guide hole and can slide along the guide hole; the control shaft moves along the guide hole to drive the movement control mechanism to stretch out and draw back in the linear direction. The airfoil extension and retraction control mechanism is of a pure mechanical structure, is simple and durable, and can realize extension and retraction of the airfoil through the structure of the airfoil extension and retraction control mechanism in the atmosphere or marine environment so as to achieve the purpose of adjusting the attitude of the aircraft.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing, and in particular to a wing surface extension and retraction control mechanism. Background Art

[0002] In an environment with complex working conditions, the aircraft needs to control and adjust its flight attitude, direction and trajectory, which places strict requirements on the strength of the material, the connection reliability of the mechanism and the processing accuracy. As an important force-bearing component, the wing surface must ensure its flexibility as well as its strength and rigidity while continuously expanding and contracting. Summary of the invention

[0003] In view of this, the present invention aims to overcome the defects existing in the above-mentioned prior art and provide a wing extension and retraction control mechanism.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows: A wing extension and retraction control mechanism, comprising: A rotating disk, the shaft of which is fixedly connected to the motor connecting shaft and driven to rotate by the motor connecting shaft; a control shaft is fixed to the outer ring of the rotating disk; A moving control mechanism is arranged on one side of the rotating disk and can perform linear reciprocating motion along the plane where the rotating disk is located; the wing surface is fixed on the moving control mechanism; A guide hole is provided on the mobile control mechanism, and at least a part of the guide hole is set at an angle to the moving direction of the mobile control mechanism; the control shaft is inserted into the guide hole and can slide along the guide hole; the movement of the control shaft along the guide hole can drive the mobile control mechanism to extend and retract in a linear direction.

[0005] Furthermore, the motor connecting shaft is inserted into a socket provided on the rotating disk; the motor connecting shaft and the socket are respectively provided with splines and a spline shaft, and the motor connecting shaft and the rotating disk are limited in circumferential position by matching the splines and the spline shaft.

[0006] Furthermore, an adjustment hole is provided on the rotating disk, and the adjustment hole extends in the radial direction of the rotating disk. The control shaft is fixedly assembled in the adjustment hole; and the control shaft can move along the length direction of the adjustment hole.

[0007] Furthermore, the control shaft includes a fixed part, a baffle and a sliding part connected in sequence, wherein the fixed part is inserted into the adjustment hole, a fastening nut is screwed on its free end, and the control shaft clamps the rotating disk to a fixed position through the fastening nut and the baffle; the sliding part is inserted into the guide hole.

[0008] Furthermore, the guide hole is in an arc shape; the center of the arc coincides with the axis of the rotating disk; and the radius of the arc is the same as the rotation radius of the control shaft.

[0009] Furthermore, buffer sections are extended from both ends of the guide hole; the buffer sections are perpendicular to the moving direction of the movement control mechanism.

[0010] Furthermore, the wing extension and retraction control mechanism also includes a limiter for limiting the moving direction of the mobile control mechanism; a limit hole is provided on the limiter, one end of the mobile control mechanism is inserted into the limit hole, and can slide along the channel direction of the limit hole.

[0011] Compared with the prior art, the beneficial effects of the present invention are: The wing extension and retraction control mechanism provided by the present invention is driven by a rotating disk to make a circular motion of the control shaft, and through the limit of the control shaft and the mobile control mechanism, the linear displacement of the control shaft during the circular motion is converted into the linear displacement of the mobile control mechanism, thereby realizing the extension and retraction of the wing. The wing extension and retraction control mechanism is a purely mechanical structure, which is simple and durable, and can realize the extension and retraction of the wing through its own structure in the atmosphere or marine environment, so as to achieve the purpose of adjusting the attitude of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0013] Figure 1 It is a schematic diagram of the top view of the structure of a wing extension and retraction control mechanism according to the present invention; Figure 2 It is a schematic diagram of the overall structure of a wing extension and retraction control mechanism according to the present invention from a first viewing angle; Figure 3 It is a schematic diagram of the overall structure of a wing extension and retraction control mechanism according to the present invention from a second viewing angle; Figure 4 This is a schematic diagram of the structure of a stepping motor connecting shaft of a wing extension and retraction control mechanism according to the present invention; Figure 5 It is a schematic diagram of the structure of a rotating disk of a wing extension and retraction control mechanism according to the present invention; Figure 6 It is a schematic diagram of the structure of a mobile control mechanism of a wing extension and retraction control mechanism according to the present invention; Figure 7 It is a schematic diagram of the structure of a movable control axis of a wing extension and retraction control mechanism according to the present invention; Figure 8It is a schematic diagram of the structure of a fastening nut of a wing telescopic control mechanism according to the present invention; Fig. 9 It is a schematic diagram of the structure of a limiter of a wing extension and retraction control mechanism according to the present invention; Fig.10 The present invention is a schematic diagram of the structure of the wing surface portion of the wing surface extension and retraction control mechanism.

[0014] Description of reference numerals: 1-motor connecting shaft; 2-rotating disk; 21-adjusting hole; 3-moving control mechanism; 31-guide hole; 4-control shaft; 41-fixing part; 42-baffle; 43-sliding part; 5-fastening nut; 6-limiter; 7-wing surface. DETAILED DESCRIPTION

[0015] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0016] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0017] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0018] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments: The purpose of the present invention is to solve the problem that the prior art cannot guarantee reliability under high load conditions and has a simple mechanical structure. For aerospace transmission control technology products, a device is provided that can realize aircraft flight attitude adjustment, flight trajectory change, and flight speed change.

[0019] like Figure 1-Figure 10 As shown, the wing extension and retraction control mechanism provided in this embodiment includes a rotating disk 2 and a moving control mechanism 3, wherein the shaft portion of the rotating disk 2 is fixedly connected to the motor connecting shaft 1 and is driven to rotate by the motor connecting shaft 1; the outer ring of the rotating disk 2, that is, the non-shaft position of the rotating disk 2 is fixed with a control shaft 4; the moving control mechanism 3 is arranged on one side of the rotating disk 2, which can be separated from the rotating disk 2 or movably connected to the rotating disk 2; the moving control mechanism 3 can make a linear reciprocating motion along the plane where the rotating disk 2 is located; the wing surface 7 is fixed on the moving control mechanism 3; a guide hole 31 is opened on the moving control mechanism 3, and at least a part of the guide hole 31 is set at an angle to the moving direction of the moving control mechanism 3; the control shaft 4 is inserted in the guide hole 31 and can slide along the guide hole 31; the movement of the control shaft 4 along the guide hole 31 can drive the moving control mechanism 3 to extend and retract along the linear direction.

[0020] The wing extension and retraction control mechanism provided in this embodiment is driven by a rotating disk to make a circular motion of the control shaft 4, and through the limit of the control shaft 4 and the mobile control mechanism 3, the linear displacement of the control shaft 4 when making a circular motion is converted into the linear displacement of the mobile control mechanism 3, thereby realizing the extension and retraction of the wing 7. The wing 7 extension and retraction control mechanism is a purely mechanical structure, which is simple and durable, and can realize the extension and retraction of the wing 7 in the atmosphere or marine environment through its own structure, so as to achieve the purpose of adjusting the attitude of the aircraft.

[0021] In this embodiment, the parts of the product can be customized into titanium alloy, structural steel or other metal materials according to the frequency of use.

[0022] In some embodiments, in order to improve the firmness of fixation, the motor connecting shaft 1 is inserted into the socket provided on the rotating disk 2. Preferably, the motor connecting shaft 1 and the socket are respectively provided with splines and spline shafts, and the motor connecting shaft 1 and the rotating disk 2 are limited in circumferential position by matching splines and spline shafts. Of course, in other embodiments, the circumferential limitation can also be performed by matching the non-cylindrical motor connecting shaft 1 and the socket, and a flat key interference fit connection can be selected, or the motor connecting shaft 1 and the rotating disk 2 can be fixedly connected by existing methods such as welding, etc., which are not limited here.

[0023] The motor in this embodiment is preferably a stepper motor, one end of the motor connecting shaft 1 is interference fit with the rotating disk 2 through a spline, and the other end is controlled by a programmable stepper motor. More preferably, the motor connecting shaft 1 is used as the main execution connecting shaft of the device, and the load-loading main shaft material design is preferably stainless steel, and should be quenched and tempered (hardness 38-42HRC).

[0024] In this embodiment, the rotating disk 2 is the main force transmission device and needs to withstand a large torsional force. The spline hole of the rotating disk 2 cooperates with the motor connecting shaft 1 to form a stable interference fit, and no gap is allowed to ensure accurate transmission. The material design of the rotating disk 2 is preferably a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb≥1100Mp).

[0025] In some embodiments, an adjustment hole 21 is provided on the rotating disk 2, and the adjustment hole 21 extends radially of the rotating disk 2. The control shaft 4 is fixedly assembled in the adjustment hole 21, and the control shaft 4 can move along the length direction of the adjustment hole 21. This design adjusts the position of the control shaft 4 through the mutual cooperation between the adjustment hole 21 and the control shaft 4, provides better installation conditions for the control shaft 4, changes its rotation radius, and thus changes the movement mode of the mobile control mechanism 3, and can adjust the extension distance of the final wing surface.

[0026] In other embodiments, the rotating disk 2 can also remove the straight adjustment hole 21 according to actual working conditions, and use multi-hole threaded holes to thread the control shaft 4, or use pins to connect. In other embodiments, the rotating disk 2 is allowed to add weight reduction holes if it meets the strength requirements, so that the rotating disk 2 becomes a multi-pair rotating disk.

[0027] This embodiment also provides a way to fix the control shaft 4. Specifically, the control shaft 4 is a stepped shaft, including a fixed portion 41, a baffle 42 and a sliding portion 43 connected in sequence, wherein the fixed portion 41, i.e., the large end in the figure, is inserted into the adjustment hole 21, and a fastening nut 5 is screwed on its free end. The control shaft 4 is fixed in position by clamping the rotating disk 2 with the fastening nut 5 and the baffle 42; the sliding portion 43, i.e., the small end in the figure, is inserted into the guide hole 31. The shape of the fastening nut 5 can be cylindrical, or hexagonal or other shapes. Of course, in other examples, the positioning of the control shaft 4 can also be achieved through other existing structures, such as by screwing a nut on the fixed portion 41 to fix its position, etc., which is not limited here.

[0028] Preferably, the sliding part 43 acts as an actuator and cooperates with the mobile control mechanism 3 to enable the mobile control mechanism 3 to achieve telescopic movement. Therefore, the sliding part 43 also needs to be plasma sprayed with molybdenum disulfide to ensure good contact and excellent lubrication effect, so that the control shaft 4 can slide smoothly on the slide rail with less friction resistance. The diameter of the sliding part 43 matches the guide hole 31, and the clearance after assembly is required to be no more than 0.05mm. The material design of the control shaft 4 is preferably a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb≥1100Mp).

[0029] Preferably, the fastening nut 5 matches the thread of the control shaft 4, and both threads are connected by anti-loosening threads. According to the working conditions, high-temperature resistant thread anti-loosening glue, mechanical anti-loosening and other thread anti-loosening measures are adopted. The material design of the fastening nut 5 is preferably a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb≥1100Mp).

[0030] This embodiment also provides a specific structure of the guide hole 31, that is, a telescopic method of the mobile control mechanism 3 is provided. Specifically, the guide hole 31 is in an arc shape, the center of the arc coincides with the axis of the rotating disk 2, and the radius of the arc is the same as the rotation radius of the control shaft 4. This guide hole 31 structure can make the control shaft 4 move to the position such as Figure 2 As shown, when the position is coaxial with the rotating disk 2, the movement control mechanism 3 and the wing surface 7 remain stationary.

[0031] Of course, in other embodiments, the guide hole 31 may also be set to other structures, such as an inclined linear structure set at an angle to the moving direction of the mobile control mechanism 3, or other anisotropic structures, etc., so that the moving mode of the mobile control mechanism 3 can be changed by changing the structure of the guide hole 31.

[0032] As a preferred solution, buffer sections may be extended at both ends of the guide hole 31 . Furthermore, the buffer sections are perpendicular to the moving direction of the moving control mechanism 3 and have arc chamfers at the joints to ensure smooth movement of the control shaft 4 .

[0033] In this embodiment, the mobile control mechanism 3 is the core actuator of the wing telescopic control mechanism, which is connected to the rotating disk 2 through the control shaft 4, and has a guide rail. The surface of the rail needs to be plasma sprayed with molybdenum disulfide to ensure good contact and excellent lubrication effect, so that the control shaft 4 can slide smoothly on the rail with less friction resistance. The shape of the rail depends on the actual working conditions. The material design of the mobile control mechanism 3 is preferably a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb ≥ 1100Mp).

[0034] This embodiment provides a stopper 6 for limiting the moving direction of the mobile control mechanism 3. The stopper 6 is provided with a stopper hole as a slide rail. One end of the mobile control mechanism 3 is inserted into the stopper hole and can slide along the channel direction of the stopper hole. The stopper 6 can be used as a separate component to serve the wing telescopic control mechanism, or it can be used together with the body, allowing the stopper 6 to have other shapes and other functions.

[0035] The stopper 6 is fixed on the aircraft body, and is tightly connected with the mobile control mechanism 3 through the stopper hole, and has relative friction during the execution of the mechanism. Therefore, the inner surface of the stopper hole of the stopper 6 is plasma-sprayed with molybdenum disulfide for solid lubrication in a high temperature environment. The shape of the stopper hole is consistent with the mobile control mechanism 3, and can be a chamfered square or oval, etc. The material design of the stopper 6 is preferably a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb≥1100Mp).

[0036] In the wing surface extension and retraction control mechanism, the wing surface 7 is the final actuator, which executes the action requirements of the programmable stepper motor by changing the extension amount, and finally achieves the purpose of controlling the aircraft. Its shape can be a traditional triangle, trapezoid, or other irregular shapes, and the shape of the wing surface 7 can also be adjusted according to the actual working conditions. The wing surface 7 is connected to the mobile control mechanism 3, and can be connected by welding or other connection methods such as threaded connection. Depending on the working conditions, the material of the wing surface 7 can be designed to be a material that can withstand high temperatures, such as a high-temperature alloy, and should be heat treated (σb≥1100Mp); it can also be designed to be a stainless steel material, and should be tempered heat treated (hardness 38-42HRC).

[0037] Installation and operation process: 1. Press the rotating disk 2 onto the motor connecting shaft 1 by interference fit, and then check the installation clearance; 2. Insert the control shaft 4 into the adjustment hole 21, and tighten the other end with the fastening nut 5. Add high temperature resistant thread anti-loosening glue as needed; 3. Put the guide hole 31 of the mobile control mechanism 3 into the small end of the control shaft 4, and insert it into the limit hole of the limiter 6 at the same time, and detect the connection clearance and smoothness of the mobile control mechanism 3 and the control shaft 4, and the connection clearance and smoothness of the mobile control mechanism 3 and the limit hole of the limiter 6; 4. Weld the wing surface 7 to the mobile control mechanism 3, prevent the mechanism from deforming during the welding process and check the firmness of the welding; 5. According to the actual working conditions, program the stepper motor; 6. Run the stepper motor so that the motor connecting shaft 1 of the stepper motor drives the entire mechanism to operate, detect the overall operation status, and adjust the program according to the actual operation results.

[0038] Note: For the fixed connection methods described in this article, unless otherwise specified, existing fixed connection methods such as threaded connection, welding, and bonding can be used.

[0039] 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, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A wing extension and retraction control mechanism, characterized in that: include: A rotating disk (2) has a shaft portion fixedly connected to a motor connecting shaft (1) and driven to rotate by the motor connecting shaft (1); a control shaft (4) is fixed to the outer ring of the rotating disk (2); A moving control mechanism (3) is arranged on one side of the rotating disk (2) and is capable of performing linear reciprocating motion along the plane where the rotating disk (2) is located; a wing surface (7) is fixed on the moving control mechanism (3); The mobile control mechanism (3) is provided with a guide hole (31), and at least a portion of the guide hole (31) is arranged at an angle with the moving direction of the mobile control mechanism (3); the control shaft (4) is inserted into the guide hole (31) and can slide along the guide hole (31); the movement of the control shaft (4) along the guide hole (31) can drive the mobile control mechanism (3) to extend and retract along a linear direction.

2. A wing extension and retraction control mechanism according to claim 1, characterized in that: The motor connecting shaft (1) is inserted into a socket provided on the rotating disk (2); a spline and a spline shaft are respectively provided in the motor connecting shaft (1) and the socket, and the circumferential position of the motor connecting shaft (1) and the rotating disk (2) is limited by the matching splines and the spline shaft.

3. The wing extension and retraction control mechanism according to claim 1, characterized in that: The rotating disk (2) is provided with an adjustment hole (21), the adjustment hole (21) extends radially along the rotating disk (2), and the control shaft (4) is fixedly assembled in the adjustment hole (21); the control shaft (4) is movable along the length direction of the adjustment hole (21).

4. A wing extension and retraction control mechanism according to claim 3, characterized in that: The control shaft (4) comprises a fixing portion (41), a baffle (42) and a sliding portion (43) connected in sequence, wherein the fixing portion (41) is inserted into the adjusting hole (21), and a fastening nut (5) is screwed on the free end thereof, and the control shaft (4) is clamped to a fixed position of the rotating disk (2) through the fastening nut (5) and the baffle (42); and the sliding portion (43) is inserted into the guide hole (31).

5. The wing extension and retraction control mechanism according to claim 1, characterized in that: The guide hole (31) is in the shape of an arc; the center of the arc coincides with the axis of the rotating disk (2); and the radius of the arc is the same as the rotation radius of the control shaft (4).

6. The wing extension and retraction control mechanism according to claim 1, characterized in that: Buffer sections are extended from both ends of the guide hole (31); the buffer sections are perpendicular to the moving direction of the moving control mechanism (3).

7. The wing extension and retraction control mechanism according to claim 1, characterized in that: It also includes a limiter (6) for limiting the moving direction of the moving control mechanism (3); a limit hole is provided on the limiter (6), one end of the moving control mechanism (3) is inserted into the limit hole and can slide along the channel direction of the limit hole.

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