A mechanical control surface folding and unfolding mechanism, usage method and flying device

Abstract

The present invention discloses a mechanical rudder surface folding and unfolding mechanism, a usage method and a flying device, which relate to the technical field of high-overload-resistant steering gears, and solve the technical problems of large volume, complex structure and inability to fit the mechanical environment of the steering gear during launch of the existing unfolding mechanism. Among them: there are multiple rudder shafts, rudder surfaces and elastic recovery components. The rudder shafts are evenly installed on the circumferential side of the housing. The rudder surfaces are hinged to the ends of the rudder shafts far from the housing. The elastic recovery components are installed in the cavities in the middle of the rudder shafts; the connecting rod is installed on the housing through a guide rod and fixed by a shear pin. The first return spring is installed on the connecting rod and abuts against the housing and is in a compressed state. When not unfolded, the limit post at the end of the connecting rod is inserted into the positioning groove at the end of the rudder surface. Activity clearances for the connecting rod to move towards the housing when overloaded are preset between the connecting rod and the housing and the rudder surface. The above unfolding mechanism and usage method have an integrated structural design, are small in volume, fit the mechanical environment of the steering gear during launch, and have high practicality.

Description

Technical Field

[0001] The present invention relates to the technical field of high-overload servo mechanisms, and particularly to a mechanical rudder surface folding and unfolding mechanism, a usage method, and a flying device. Background Art

[0002] To meet the needs of modern warfare and improve the cost-effectiveness of warfare, both domestic and foreign countries have vigorously carried out the transformation and upgrading of conventional ammunition to improve the range and accuracy of ammunition. As the actuator of precision-guided ammunition, in order to fully exert the flight ability of the shell, the structural mass of the servo mechanism for controlling the flight attitude of the shell should be minimized as much as possible. The installation space of the servo mechanism on the shell is limited, and it is required that the servo mechanism uses the shell diameter as the rudder cabin body to achieve the integration of four rudders. Since the shell is a one-time use product with a large usage amount and the mechanism cannot be discharged automatically once a failure occurs, it is required that the servo mechanism has low cost and high reliability. The shell is stored in a harsh environment according to specific requirements, and the overall shell has poor sealing with the external environment. Therefore, it is required that the servo mechanism has long-term storage performance in a harsh environment. Since the gun barrel diameter fits the shell diameter, the rudder surface needs to be locked inside the shell before launch and quickly unlock after exiting the gun barrel to control the flight attitude of the shell. Therefore, it is required that the rudder surface of the servo mechanism has a folding and unfolding function.

[0003] Most of the current domestic rudder surface folding and unfolding mechanisms in production use pyrotechnics to achieve rudder surface locking and unfolding. The components are large in volume, complex in structure, expensive in price, and pyrotechnics have high requirements for the storage environment and are prone to failure, which increases the design difficulty and manufacturing cost of the servo mechanism for integration, miniaturization, and light weight; and pyrotechnics unlock and unfold the rudder surface according to the electro-mechanical control timing instructions, and cannot meet the functional requirements of other types of shells to quickly unlock the rudder at the moment of exiting the muzzle. Therefore, according to the unlocking and opening requirements of the new type of gun-launched servo mechanism, designing a rudder surface folding and unfolding mechanism that fits its launch mechanical environment is an urgent problem to be solved at present. Summary of the Invention

[0004] The purpose of the present invention is to provide a mechanical rudder surface folding and unfolding mechanism, a usage method, and a flying device, which are used to solve the technical problems that the components of the current domestic rudder surface folding and unfolding mechanism are large in volume, complex in structure, expensive in price, and cannot fit the launch mechanical environment of the servo mechanism.

[0005] To achieve the above purpose, the present invention provides the following technical solutions:

[0006] A mechanical rudder surface folding and unfolding mechanism includes: a housing, a first return spring, a connecting rod, a guide rod, and an equal number of rudder shafts, rudder surfaces, and elastic return components;

[0007] The rudder shafts, the rudder surfaces, and the elastic restoring components are all multiple and correspond one by one. The rudder shafts are evenly installed on the circumferential side of the housing. The rudder surfaces are hinged to the ends of the corresponding rudder shafts away from the housing. A cavity is provided in the middle of the rudder shafts, and the elastic restoring components are installed in the cavity;

[0008] The guide rod is vertically installed on the housing. The connecting rod is slidably installed on the guide rod. The starting end of the connecting rod is fixedly connected to the housing through a shear pin. The first return spring is installed on the connecting rod, abuts against the housing and is in a compressed state. A limiting post is provided at the end of the connecting rod, and a positioning groove is provided at the tail end of the rudder surface. An activity gap for the connecting rod to move towards the housing when overloaded is preset between the connecting rod and the housing and the rudder surface;

[0009] When the rudder surface is not unfolded, the elastic restoring component abuts against the rudder surface and is in a compressed state, and the limiting post is inserted into the positioning groove; when the connecting rod is overloaded and cuts off the shear pin, the limiting post is separated from the positioning groove, and the rudder surface unfolds under the action of the elastic restoring component.

[0010] Compared with the prior art, in the mechanical rudder surface folding and unfolding mechanism provided by the present invention, the rudder surface is hinged to the rudder shaft through a support pin and can rotate around the support pin, approaching or separating from each other. The elastic restoring component in a compressed state can provide a restoring force for the unfolding of the rudder surface. The setting of the guide rod enables the connecting rod to move along the guide rod without detaching from the housing. The connecting rod and the housing are fixed by a shear pin. When the connecting rod is overloaded, the shear pin can be cut off, and the first return spring is further compressed. After the overload disappears, the connecting rod will move away from the housing under the action of the first return spring and then separate from the rudder surface. The unlocked rudder surface will unfold under the action of the elastic restoring device. The above mechanical rudder surface folding and unfolding mechanism adopts a miniaturized and integrated structural design technology, integrating the four-rudder locking function. It is designed with a simple mechanism, has a compact structure, occupies a small space, has a high space utilization rate for the steering gear, and the unfolding mechanism makes full use of the overload force generated during the shell firing process for unlocking the mechanism. The unlocking function is reliable, meeting the functional requirements for the steering gear to open the rudder at the muzzle, solving the timing drawbacks of unlocking the rudder surface by electrical instructions, and has high practicability.

[0011] The present invention also provides a usage method for a mechanical rudder surface folding and unfolding mechanism, including the following steps:

[0012] When locking: Rotate the rudder surface to the locking position. The rudder surface compresses the elastic restoring device and pushes the connecting rod to move towards the housing until the limiting post provided at the end of the connecting rod is inserted into the positioning groove corresponding to the tail end of the rudder surface, and use a shear pin to fix the starting end of the connecting rod to the housing;

[0013] When unlocked: the connecting rod moves towards the housing due to overload, compressing the first return spring. The connecting rod shears the shear pin. After the overload disappears, the connecting rod moves away from the housing under the action of the first return spring and separates from the control surface. The control surface unfolds under the action of the elastic return device.

[0014] The present invention also discloses a flying device, including a steering gear and a mechanical control surface folding and unfolding mechanism.

[0015] The mechanical control surface folding and unfolding mechanism is installed on the housing of the steering gear. The steering gear is installed on the flying device. The mechanical control surface folding and unfolding mechanism unfolds after the flying device is launched.

[0016] Compared with the prior art, the beneficial effects of the usage method provided by the present invention are the same as those of the mechanical control surface folding and unfolding mechanism described in the above technical solution, and will not be elaborated here. Description of the Drawings

[0017] The drawings described herein are used to provide a further understanding of the present invention and form a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0018] Figure 1 is a schematic diagram of the locked state of the mechanical control surface folding and unfolding mechanism provided by the present invention;

[0019] Figure 2 is Figure 1 a schematic diagram of the unfolded state of the mechanical control surface folding and unfolding mechanism in.

[0020] Reference Signs:

[0021] 1 - steering shaft, 2 - housing, 3 - second return spring, 4 - unlocking pin, 5 - support pin, 6 - control surface, 7 - locking nut, 8 - shear pin, 9 - bottom plate, 10 - first return spring, 11 - connecting rod, 12 - guide rod. Detailed Embodiments

[0022] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0023] It should be noted that when an element is referred to as "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0024] In addition, the terms "first" and "second" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more, unless otherwise specifically defined. "Several" means one or more, unless otherwise specifically defined.

[0025] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the indicated device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0026] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "mounted", "connected", and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and may be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0027] Common electro - hydraulic actuator flap folding and unfolding mechanisms use pyrotechnics for flap locking and unlocking. The overall mechanism is relatively complex, occupies a large volume in the steering gear compartment, is not conducive to long - term storage, and cannot be tested after assembly. Therefore, it greatly increases the difficulty of lightweight miniaturization design and manufacturing cost of the actuator. At the same time, pyrotechnics need to use electro - mechanical control timing instructions for flap unlocking and unfolding, and cannot meet the functional requirements of other types of projectiles to open the flap instantaneously at the muzzle.

[0028] Common flap folding and unfolding mechanisms mainly have the following disadvantages:

[0029] 1) Common flap folding and unfolding mechanisms are complex, with a large variety of parts, difficult to manufacture and integrate, and can only be applied to actuators with low requirements for structural space, weight, and reliability, resulting in a high cost;

[0030] 2) Flap locking and unfolding require a combination of mechanical and electrical means, and flap opening has a certain timing, unable to meet the requirement of instantaneous muzzle flap opening;

[0031] 3) Using pyrotechnics for flap locking and unfolding, the long - term storage reliability of pyrotechnics is not high, prone to leakage, and difficult to detect and repair.

[0032] The mechanical rudder surface folding and unfolding mechanism has a compact structure, and the principle of realizing rudder surface locking and unfolding is simple and reliable. This mechanism makes full use of the characteristics of the huge overload acceleration generated by the steering gear during launch for structural design, breaking through the technical bottleneck that the steering gear needs to be unlocked immediately after leaving the barrel, and solving the design technical problems of realizing rudder surface locking and unfolding of the steering gear under the action of non-explosive devices. The overall structure of this mechanism is simple, with few parts involved and low production costs. At the same time, the pure mechanical structure can be maintained without maintenance for a long time, reducing the risk of explosive device storage deflation and assembly, and having high reliability. It has positive significance for promoting the miniaturization, modularization, structural weight reduction design and low cost of electric steering gears.

[0033] The mechanical rudder surface folding and unfolding mechanism has relatively successfully solved the above problems. The folding and locking of the four rudder surfaces of the steering gear are realized through the same locking mechanism. The whole mechanism has a compact structure, few parts involved, occupies a small space of the steering gear, and improves the economy of the mechanism. The unlocking of the rudder surface is realized through the overload force generated during the launch of the shell, without the need to add other mechanisms. The unfolding of the rudder surface is realized through the opening rudder spring. The mechanism can meet the functional requirements of the shell for the rudder surface to be unlocked at the muzzle. The whole mechanism is composed of mechanical components, and the long-term storage requirements of the mechanism can be realized by surface treatment of the parts.

[0034] Please refer to Figure 1 and Figure 2 As shown in [figures not specified in the original text], the mechanical rudder surface folding and unfolding mechanism provided by the embodiment of the present invention includes: a housing 2, a first return spring 10, a connecting rod 11, a guide rod 12, and an equal number of rudder shafts 1, rudder surfaces 6, and elastic return components; there are multiple rudder shafts 1, rudder surfaces 6, and elastic return components, and they are in one-to-one correspondence. The rudder shafts 1 are evenly installed on the circumference of the housing 2. The rudder surfaces 6 are hinged to the ends of the corresponding rudder shafts 1 away from the housing 2. A cavity is provided in the middle of the rudder shaft 1, and the elastic return component is installed in the cavity; the guide rod 12 is vertically installed on the housing 2, the connecting rod 11 is slidably installed on the guide rod 12. The starting end of the connecting rod 11 is fixedly connected to the housing 2 through a shear pin. The first return spring 3 is installed on the connecting rod 11, abuts against the housing 2 and is in a compressed state. A limiting post is provided at the end of the connecting rod 11, and a positioning groove is provided at the tail end of the rudder surface 6. An activity gap for the connecting rod 11 to move towards the housing 2 when overloaded is preset between the connecting rod 11 and the housing 2 and the rudder surface 6; when the rudder surface 6 is not unfolded, the elastic return component abuts against the rudder surface 6 and is in a compressed state, and the limiting post is inserted into the positioning groove; when the connecting rod 11 is overloaded and the shear pin is cut, the limiting post is separated from the positioning groove, and the rudder surface 6 is unfolded under the action of the elastic return component.

[0035] During specific implementation:

[0036] The rudder shaft 1 and the rudder surface 6 are hinged through a support pin 5; the second return spring 3 and the unlocking pin 4 are installed in the cavity of the rudder shaft 1; the bottom plate 9 and the connecting rod 11 are fixedly connected through a shear pin 8; the locking nut 7 is fixed to the tail end thread of the shear pin 11; the first return spring 10 is compressively installed in the installation groove of the connecting rod 11; the bottom plate 9 is fixed to the housing 2 by screws, and the guide rod 12 passes through the through hole on the connecting rod 11 and is screwed and installed on the housing 2 through its own tail end thread, while restricting the degrees of freedom of the connecting rod 11 in other directions except the axial direction. The connecting rod 11 is fixed to the rudder surface 6 by being embedded in the positioning groove at the tail end of the rudder surface 6. Further, there are 4 rudder surfaces 6 and 4 rudder shafts 1, and the 4 rudder shafts 1 are evenly distributed on the circumferential side of the housing 2. The number of the rudder shafts 1 and the rudder surfaces 6 can also be other numbers that are structurally stable during locking and unfolding, such as 3. The rudder surface 6 is generally a planar structure, and its shape can be set according to the actual requirements of flight. The longitudinal section of the connecting rod 11 is a T-shaped structure, which can include a vertical rod and a fixed plane arranged at the top of the vertical rod. Taking 4 rudder surfaces 6 as an example, the fixed plane can be circular or square, and a number of limit posts equal to the number of the rudder surfaces 6 are evenly arranged on the circumferential side of the fixed plane, and the limit posts are arranged perpendicular to the fixed plane. In order to avoid interference between the limit posts, the rudder surface 6 and the fixed plane, affecting the unfolding of the rudder surface 6, extension parts equal to the number of the rudder surfaces 6 can be arranged on the circumferential side of the fixed plane, and the limit posts are vertically arranged on the corresponding extension parts. In order to facilitate the installation and fixation of the first return spring 3, a fixed groove can be arranged at the position where the vertical rod contacts the fixed plane, and one end of the first return spring 3 is installed in the fixed groove. The number of the guide rods 12 is preferably the same as the number of the rudder surfaces 6. The guide rods 12 pass through the connecting rod 11 from top to bottom and are installed on the housing 2 through the tail thread, which can effectively ensure the stability of the connecting rod 11 moving upward along the guide rods 12 under the action of the first return spring 3 after the shear pin 8 is disconnected.

[0037] The initial state of the rudder surface is folded and locked. It is designed that the rudder surface 6 can rotate around the support pin 5, and the degrees of freedom of the rudder surface 6 in other directions are restricted by the notch of the rudder shaft 1 and the connecting rod 11. At the same time, by pushing the unlocking pin 4, the second return spring 3 is compressed and moves in the installation hole of the rudder shaft 1. The connecting rod 11 is fixed to the bottom plate 9 through a shear pin and axially compresses the first return spring 10. Further, the fixing of the connecting rod 11 is realized by fixing the bottom plate 9 to the housing 2, and the connecting rod 11 effectively locks the rudder surface 6 by embedding the limit posts into the positioning groove at the tail end of the rudder surface 6.

[0038] Unlocking and deployment of the control surface 6: When the servo is launched, it is subject to an axial downward overload acceleration. Under the action of the overload force, the connecting rod 11 shears the shear pin 8 that locks its movement. After the shear pin 8 breaks, the connecting rod 11 continues to move downward until the housing 2 limits its movement. When the overload of the servo disappears, the connecting rod 11 moves upward along the guide rod 12 under the elastic potential energy stored in the first return spring 10. When the limit post of the connecting rod 11 disengages from the positioning groove at the end of the control surface 6, the control surface 6 is unlocked. At the same time, the first return spring 10 continues to push the connecting rod 11 upward until the top of the guide rod 12 limits its movement. After the control surface 6 is unlocked, under the elastic potential energy stored in the lock spring 3, the opening and closing pin 4 is pushed forward to form a torque to push the control surface 6 to rotate around the support pin 5. The control surface 6 rotates clockwise and unfolds. When the control surface 6 is fully deployed, the control shaft 1 restricts the control surface 6 from continuing to rotate clockwise. The unlocking pin 4 abuts against the limit boss on the control surface 6, and the limit boss limits the unlocking pin 4, thus realizing the deployment and locking of the control surface 6. As Figure 2 shown.

[0039] Compared with the prior art, in the mechanical control surface folding and unfolding mechanism provided by the present invention, the control surface is hinged to the control shaft through a support pin and can rotate around the support pin, approaching or separating from each other. The elastic return assembly in the compressed state can provide a return force for the deployment of the control surface. The setting of the guide rod enables the connecting rod to move along the guide rod without detaching from the housing. The connecting rod and the housing are fixed by a shear pin. When the connecting rod is overloaded, the shear pin can be cut off, and the first return spring is further compressed. After the overload disappears, the connecting rod will move away from the housing under the action of the first return spring, and then separate from the control surface. The unlocked control surface will unfold under the action of the elastic recovery device. The above mechanical control surface folding and unfolding mechanism adopts an integrated structure design, with a compact structure, small occupied space, high space utilization rate of the servo, and the unfolding mechanism makes full use of the overload force generated during the shell launch process to unlock the mechanism, with a reliable unlocking function, meeting the functional requirements of the servo to open the control surface at the muzzle, solving the timing disadvantages of using electrical commands to unlock the control surface, and having high practicability.

[0040] The present invention also has the following effects:

[0041] a) Adopting miniaturized and integrated structure design technology, integrating the four-control-surface locking function into one, designing with a simple mechanism, having a compact structure, small occupied space, and high space utilization rate of the servo;

[0042] b) This mechanism makes full use of the overload force generated during the shell launch process to unlock the mechanism, with a reliable unlocking function, and at the same time can meet the functional requirements of the servo to open the control surface at the muzzle, avoiding the timing disadvantages of using electrical commands to unlock the control surface;

[0043] c) The principle of the mechanism for locking and deploying the rudder surface is simple, the structure is compact, the number of parts is small, the mechanism is reliable, it has the ability to withstand high overloads, meets the requirements of the guided projectile for the structural strength of the mechanism, and at the same time has a relatively low manufacturing cost and good economy, which promotes the low-cost and integrated design of the actuator;

[0044] d) The mechanism uses a mechanical structure to achieve the locking and deployment of the rudder surface. At the same time, it can be tested, disassembled and assembled multiple times without affecting its performance, does not require special maintenance, and can achieve long-term storage in various harsh environments.

[0045] As an implementable manner, the elastic recovery component includes a second return spring 3 and an unlocking pin 4; the second return spring 3 is installed in the cavity in the middle of the rudder shaft 1, and the unlocking pin 4 is installed at one end of the second return spring 3 away from the housing 2. The unlocking pin 4 is received in the rudder shaft 1 and abuts against the rudder surface 6.

[0046] The second return spring 3 is in a compressed state when the rudder surface 6 is locked, and can provide an elastic recovery force for the deployment of the rudder surface 6. The setting of the unlocking pin 4 replaces the contact between the second return spring 3 and the rudder surface 6, ensuring the contact effect between the unlocking pin 4 and the rudder surface 6. Further, one end of the second return spring 3 away from the rudder surface 6 can be selected to be clamped in the rudder shaft 1 to avoid the situation that the second return spring 3 and the unlocking pin 4 come out of the rudder shaft 1 after the rudder surface 6 is deployed.

[0047] As an implementable manner, a limit boss is provided on the rudder surface 6. When the rudder surface 6 is not deployed, the unlocking pin 4 abuts against the front surface of the limit boss. After the rudder surface 6 is deployed, the unlocking pin 4 abuts against the side surface of the limit boss.

[0048] The setting of the limit boss ensures the contact effect between the unlocking pin and the rudder surface when the rudder surface is not deployed. When deployed, it abuts against the unlocking pin, which can prevent the second return spring and the unlocking pin from coming out of the rudder shaft, and can also continue to support the rudder surface to avoid the shaking of the rudder surface.

[0049] As an implementable manner, an installation platform is provided at one end of the rudder shaft 1 away from the housing 2. The rudder surface 6 is hinged on the installation platform, and the rudder surface 6 is in a horizontal state after deployment. Further, a fixing block is provided on one side of the rudder surface 6 away from the limit boss. After the rudder surface 6 is deployed, the fixing block abuts against the installation platform.

[0050] The setting of the installation platform facilitates the installation and fixation of the rudder surface. The setting of the fixing block on the rudder surface makes the fixing block abut against the installation platform after the rudder surface is deployed, avoiding the continuous rotation of the rudder surface, and cooperating with the second return spring and the unlocking pin to avoid the shaking of the rudder surface.

[0051] As an implementable manner, the housing 2 further includes a bottom plate 9; the bottom plate 9 is fixedly installed on the housing 2, a through hole is provided in the middle of the bottom plate 9, the starting end of the connecting rod 11 is inserted into the through hole and fixed by a shear pin 8. When not fixed, the connecting rod 11 can move along the opening direction of the through hole.

[0052] The bottom plate is installed on the housing by screws. A through hole penetrating up and down is provided in the middle of the bottom plate. The starting end of the connecting rod is inserted into the through hole and fixed by a shear pin. The shear pin is fixed by a lock nut, ensuring the fixing effect of the shear pin on the connecting rod. When the connecting rod is overloaded, it moves towards the housing, cuts off the shear pin, continues to move towards the housing, and compresses the first return spring. The starting end of the connecting rod finally contacts the housing to limit the connecting rod.

[0053] As an implementable manner, a ring-shaped boss is provided on the periphery of the bottom plate 9, and one end of the first return spring 10 facing the housing 2 abuts against the ring-shaped boss. Further, the shear pin 8 is located on the side of the ring-shaped boss facing the housing 2.

[0054] The setting of the ring-shaped boss can provide good support for the first return spring and also avoid the direct contact between the first return spring and the housing. The first return spring is located on the side of the ring-shaped boss on the bottom plate away from the housing, and the shear pin is installed on the other side of the ring-shaped boss on the bottom plate. Without the interference of the first return spring, the installation of the shear pin is more convenient. Using a pure mechanical structure, it can be tested, disassembled and assembled multiple times without affecting its performance and without special maintenance, and it can be stored for a long time in various harsh environments.

[0055] In order to better ensure the movement of the connecting rod 11, the length of the guide rod 12 is greater than the length of the connecting rod 11. The setting of the guide rod 12 plays a guiding role in the movement of the connecting rod 11. The length of the guide rod 12 is greater than the length of the connecting rod 11, ensuring that the limit post of the connecting rod 11 can be disengaged from the positioning groove on the rudder surface. The connecting rod 11 moves along the guide rod 12 and finally abuts against the end of the guide rod 12 to prevent the connecting rod 11 from disengaging.

[0056] The present invention also provides a usage method of a mechanical rudder surface folding and unfolding mechanism, including the following steps:

[0057] When locking: Rotate the rudder surface to the locking position, compress the elastic return device by the rudder surface, push the connecting rod towards the housing until the limit post provided at the end of the connecting rod is inserted into the positioning groove corresponding to the tail end of the rudder surface, and use a shear pin to fix the starting end of the connecting rod on the housing;

[0058] When unlocking: The connecting rod moves towards the housing due to overload, compresses the first return spring, the connecting rod shears the shear pin. After the overload disappears, the connecting rod moves away from the housing under the action of the first return spring and separates from the rudder surface. The rudder surface unfolds under the action of the elastic return device.

[0059] Compared with the prior art, the beneficial effects of the usage method provided by the present invention are the same as those of the mechanical control surface folding and unfolding mechanism described in the above technical solution, and will not be elaborated here.

[0060] The present invention also discloses a flying device, including a servo and a mechanical control surface folding and unfolding mechanism;

[0061] The mechanical control surface folding and unfolding mechanism is installed on the housing of the servo, the servo is installed on the flying device, and the mechanical control surface folding and unfolding mechanism unfolds after the flying device is launched.

[0062] Compared with the prior art, the beneficial effects of the usage method provided by the present invention are the same as those of the mechanical control surface folding and unfolding mechanism described in the above technical solution, and will not be elaborated here.

[0063] In the description of the above embodiments, the specific features, structures, materials or characteristics may be combined in a suitable manner in any one or more embodiments or examples.

[0064] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claimed rights.

Claims

1. A mechanical control surface folding and unfolding mechanism, characterized in that Comprising: A housing, a first return spring, a connecting rod, a guide rod, a rudder shaft, a rudder surface, and an elastic return assembly; There are multiple of the rudder shafts, the rudder surfaces, and the elastic return assemblies, and they correspond one by one. The rudder shafts are evenly installed on the periphery of the housing. The rudder surfaces are hinged to the ends of the corresponding rudder shafts away from the housing. A cavity is provided in the middle of the rudder shafts, and the elastic return assemblies are installed in the cavities; The guide rod is vertically installed on the housing. The connecting rod is slidably installed on the guide rod. The starting end of the connecting rod is fixedly connected to the housing through a shear pin. The first return spring is installed on the connecting rod, abuts against the housing and is in a compressed state. A limit post is provided at the end of the connecting rod. A positioning groove is provided at the tail end of the rudder surface. An activity gap for the connecting rod to move towards the housing when overloaded is preset between the connecting rod and the housing and the rudder surface. The longitudinal section of the connecting rod is a T-shaped structure, including a vertical rod and a fixed plane provided at the top of the vertical rod. A number of limit posts equal to the number of the rudder surfaces are evenly provided on the periphery of the fixed plane. The limit posts are perpendicular to the fixed plane. Extensions equal to the number of the rudder surfaces are provided on the periphery of the fixed plane. The limit posts are vertically provided on the corresponding extensions; When the rudder surface is not deployed, the elastic return assembly abuts against the rudder surface and is in a compressed state, and the limit post is inserted into the positioning groove; when the connecting rod is overloaded and cuts off the shear pin, the limit post is separated from the positioning groove, and the rudder surface is deployed under the action of the elastic return assembly.

2. The mechanical control surface folding and unfolding mechanism according to claim 1, characterized in that, The elastic return assembly includes a second return spring and an unlocking pin; The second return spring is installed in the cavity. The unlocking pin is installed at the end of the second return spring away from the housing. The unlocking pin is received in the cavity and abuts against the rudder surface.

3. The mechanical control surface folding and unfolding mechanism according to claim 2, characterized in that, A limit boss is provided on the rudder surface. When the rudder surface is not deployed, the unlocking pin abuts against the front surface of the limit boss. After the rudder surface is deployed, the unlocking pin abuts against the side surface of the limit boss.

4. The mechanical control surface folding and unfolding mechanism according to claim 3, characterized in that An installation platform is provided at the end of the rudder shaft away from the housing. The rudder surface is hinged on the installation platform. After the rudder surface is deployed, it is in a horizontal state.

5. The mechanical control surface folding and unfolding mechanism according to claim 4, characterized in that, A fixed block is provided on one side of the rudder surface away from the limit boss. After the rudder surface is deployed, the fixed block abuts against the installation platform.

6. The mechanical control surface folding and unfolding mechanism according to claim 1, characterized in that, The housing includes a bottom plate; The bottom plate is fixedly installed on the housing. A through hole is provided in the middle of the bottom plate. One end of the connecting rod is inserted into the through hole and fixed by the shear pin. When not fixed, the connecting rod can move along the opening direction of the through hole.

7. The mechanical control surface folding and unfolding mechanism according to claim 6, characterized in that, A ring-shaped boss is provided on the periphery of the bottom plate. The end of the first return spring facing the housing abuts against the ring-shaped boss.

8. The mechanical control surface folding and unfolding mechanism according to claim 7, characterized in that, The shear pin is located on the side of the ring-shaped boss facing the housing.

9. A method for using the mechanical control surface folding and unfolding mechanism according to any one of claims 1 to 8, characterized in that, Including the following steps: When locking: Rotate the rudder surface to the locking position. The rudder surface compresses the elastic return device, pushes the connecting rod to move towards the housing until the limit post provided at the end of the connecting rod is inserted into the positioning groove corresponding to the tail end of the rudder surface, and use the shear pin to fix the starting end of the connecting rod on the housing; When unlocked: the connecting rod moves towards the housing due to overload, compressing the first return spring, and the connecting rod shears the shear pin. After the overload disappears, the connecting rod moves away from the housing under the action of the first return spring, separating from the control surface, and the control surface unfolds under the action of the elastic return device.

10. A flying device, comprising a servo, characterized in that, It further includes the mechanical control surface folding and unfolding mechanism according to any one of claims 1 to 8; The mechanical control surface folding and unfolding mechanism is installed on the housing of the steering gear, the steering gear is installed on the flying device, and the mechanical control surface folding and unfolding mechanism unfolds after the flying device is launched.

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