A quick-release mechanism for rudder surfaces

Abstract

This invention belongs to the field of aircraft structural design technology, specifically relating to a quick-release control surface mechanism. It comprises a control surface, a fixed wing surface, a pull rod, a cam, a compression spring, a rotating shaft, a control surface square block, and a servo square block. The control surface square block and the servo square block are supported by their square surfaces. The cylindrical portion of the servo square block is connected to the servo, while the other portion engages with the control surface square block. The locking principle is as follows: there is a continuous contact force between the cam and the fixed pin. If the torque generated by the contact force on the cam is less than the torque generated by friction, the cam will not rotate. The rotation is independent of the magnitude of the contact force but depends on the coefficient of friction between the cam and the fixed pin, and the perpendicular distance from the center of the rotating shaft to the contact force. By configuring these parameters, the mechanism can achieve a self-locking effect. The cam is subjected to the force of the compression spring in its assembled state. The quick-release mechanism proposed in this invention adopts a self-locking structure, which is simple in structure, has few parts, and is convenient for disassembly / maintenance. The mechanism uses a large square area fit, resulting in good load-bearing capacity. The mechanism's shape is consistent with the control surface's shape, with most of the mechanism located within the control surface, and there is no large bulge at the fixed control surface, reducing aerodynamic drag.

Description

Technical Field

[0001] This invention belongs to the field of aircraft structural design technology, specifically relating to a quick-release mechanism for control surfaces. Background Technology

[0002] To meet the requirements for maintenance and use of the wing surfaces in the field, and to facilitate storage and transportation, the control surfaces need to adopt a quick-release structure for easy assembly and disassembly, reducing the space occupied by the aircraft during transportation and storage. Existing control surface connection schemes mainly include single-axis connections, tenon and mortise connections, and disc connections. While these structures are reliable, they are not convenient to assemble and disassemble, requiring the installation or removal of multiple screws, and thus cannot meet the need for rapid assembly and disassembly. Summary of the Invention

[0003] Purpose of the invention: In view of the above-mentioned existing technology, the purpose of this invention is to design a new type of quick-release mechanism for control surfaces, which can achieve the effect of quick connection and disassembly while ensuring the reliability of structural connection.

[0004] Technical solution: To achieve the above-mentioned objectives, this invention provides a quick-release control surface mechanism, comprising a control surface, a fixed wing surface, a pull rod, a cam, a compression spring, a fixing pin, a control surface square block, and a servo motor square block.

[0005] One end of the servo motor block is fixed to the fixed wing surface, and the other end is inserted into the rudder surface block. The fixing pin is fixed to the servo motor block.

[0006] One end of the rudder surface square block is fixed to the rudder surface, and the other end can be embedded into the servo motor square block. After being embedded, the inner wall of the rudder surface square block is in contact with the outer edge of the fixing pin.

[0007] The square block of the rudder surface has a mounting cavity in the middle and a through hole at each end;

[0008] One end of the cam is rotatably connected to the mounting cavity of the square block of the rudder surface, and the other end is designed as an arc-shaped structure. The arc-shaped structure rotates around the rotation point at the root of the cam. During rotation, the edge of the arc-shaped structure contacts and engages with the outer edge of the other side of the fixing pin. The arc-shaped structure is rotatably connected to one end of the pull rod. A limiting boss is provided in the middle section of the pull rod. The other end of the pull rod passes through the end through hole of the square block of the rudder surface. The spring is fitted on the pull rod. The spring is in a compressed state. One end of the spring abuts against the boss in the middle of the pull rod, and the other end abuts against the bottom of the mounting cavity of the square block of the rudder surface. After the square block of the rudder surface is inserted into the square block of the servo motor, under the combined action of the spring and gravity, there is a continuous contact force between the arc-shaped structure of the cam and the fixing pin. The torque generated by this contact force on the cam is less than the torque generated by the friction force, so the cam will not rotate, thus achieving locking.

[0009] When unlocking, pull the end of the lever to overcome the force of the spring, the contact force between the fixing pin and the cam arc structure. The cam rotates clockwise. After rotating a certain angle, the rudder surface can be removed vertically, completing the disassembly of the rudder surface.

[0010] Furthermore, the cam includes a cylindrical portion and a fan-shaped plate structure, the fan-shaped plate structure having an oblong hole, and the pull rod and the fan-shaped plate structure being rotatably connected by a small shaft.

[0011] Furthermore, the mounting cavity at one end of the servo motor square block is inserted into the servo motor square block and extends outward by a certain space to make room for the cylindrical pin.

[0012] Furthermore, the control surface square block and the servo motor square block are supported by the square surface mating, wherein the servo motor square block is set with a cylindrical structure at one end that mates with the servo motor; the cylindrical part is connected to the servo motor, and the other part mates with the control surface square block.

[0013] Furthermore, a bearing is provided between the cylindrical structure of the servo block and the fixed wing surface.

[0014] Furthermore, the servo block is connected to the drive structure, driving the servo block to rotate, which in turn drives the rudder surface to rotate.

[0015] Furthermore, the end of the pull rod is provided with a thread to cooperate with the pull rod head, and the outer diameter of the pull rod head is larger than the diameter of the through hole at the end of the square block of the rudder surface.

[0016] Furthermore, a pull rod head groove is provided on the rudder surface, and the pull rod head at the end of the pull rod is placed in the pull rod head groove.

[0017] The locking principle is as follows: Analyzing the forces acting on the cam, in the locked state, the cam experiences a contact force from the fixing pin, generating a torque of T1. The friction between the cam and the fixing pin results in a torque of T2, and the force exerted by the pull rod on the cam generates a torque of T3. In the locked state, T1 < T2 + T3 must be satisfied for the mechanism to remain locked. Upon unlocking, the spring pressure is canceled out by the unlocking force, generating a torque in the opposite direction, T4. The unlocking condition is T1 + T4 > T2. Based on the above formula, the outer dimensions of the cam are designed according to the internal space dimensions. In the locked state, the edge of the rotating part of the cam is kept in contact with the fixed pin. The cam can only be separated by rotation. Since the servo block and the control surface block are in a plug-in fit, the cam is also subject to rotational constraint under the spring pressure of the pull rod and cannot rotate freely. The axial movement of the control surface block is also strongly constrained by the fixed pin and is always in a plug-in fit and locked with the servo block. The servo block can then drive the control surface block to achieve rotational transmission, thereby driving the control surface to rotate. At the same time, in order to further improve the locking effect, the spring is selected according to the working conditions, and a suitable unlocking force range is determined. The mechanism is designed comprehensively.

[0018] To unlock, pull the lever to release the constraint on the cam. Due to the rotational engagement between the lever and the cam, when the lever is pulled to a certain position, it can drive the cam to rotate around its own root. When the cam rotates to a state where it is completely separated from the fixing pin, the fixing pin can release the cam's restriction. At this time, the entire control surface can be axially pulled away from the servo block, thus unlocking the servo.

[0019] Technical benefits: The quick-release mechanism adopts a self-locking structure, which is simple in structure, has few parts, is convenient for disassembly / maintenance, and has high locking reliability; the mechanism adopts a square large-area fit, which has good load-bearing capacity; the mechanism shape is consistent with the shape of the control surface, most of the mechanism is located inside the control surface, and there is no large bulge at the fixed control surface, which reduces aerodynamic drag. Attached Figure Description

[0020] Figure 1 This is a structural diagram showing the assembly state of the quick-release mechanism for the control surfaces.

[0021] Figure 2 This is a partial sectional view of the assembled state;

[0022] Figure 3 This is a partial sectional view showing the disassembled state.

[0023] The components include: 1. Rod head, 2. Rod head groove, 3. Rod, 4. Control surface square block, 5. Compression spring, 6. Shaft, 7. Control surface, 8. Fixed wing surface, 9. Fixed pin, 10. Cam, 11. Servo square block, 12. Bearing, and 13. Small shaft. Detailed Implementation

[0024] To more clearly illustrate the technical solutions of the embodiments of the present invention, the present invention will be described in detail below with reference to the accompanying drawings or specific implementation examples. It should be noted that some (but not all) of the disclosed examples are shown in the drawings. In fact, many different examples can be described, and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described to better demonstrate the positive effects of the present invention, and all aspects not detailed herein are considered to be well-known or conventional techniques in the art.

[0025] like Figure 1 As shown, in a specific design of the rudder surface quick-release mechanism of the present invention, the basic components of the mechanism include a pull rod head 1, a pull rod head groove 2, a pull rod 3, a rudder surface square block 4, a compression spring 5, a rotating shaft 6, a rudder surface 7, a fixed wing surface 8, a fixed pin 9, a cam 10, a servo motor square block 11, a bearing 12, a small shaft 13, etc.

[0026] One end of the servo motor square block 11 is fixed to the fixed wing surface 7, and the other end is inserted into the control surface square block 4. The fixing pin 9 is fixed to the servo motor square block 11. Both the servo motor square block 11 and the control surface square block 4 adopt a square design to ensure that the two are always in a tight fit during the rotation of the control surface.

[0027] One end of the rudder surface square block 4 is fixed to the rudder surface 7, and the other end can be embedded in the servo motor square block 11. After being embedded, the inner wall of the rudder surface square block 4 is in contact with the outer edge of the fixing pin 9. The fixing pin 9 fixed on the servo motor square block 11 works with the cam 10 to provide a good limiting effect on the rudder surface square block 4.

[0028] For the rudder square block 4, there is a mounting cavity in the middle for installing a locking mechanism that cooperates with the fixing pin 9. The locking mechanism can move within the mounting cavity. There is a through hole at the end (upper end) of the rudder square block 4, which can be unlocked and adjusted by using external tools.

[0029] For this invention, the key component that cooperates with the fixing pin 9 is the locking mechanism. The locking mechanism is located in the mounting cavity of the square block 4 of the rudder surface. The locking mechanism includes a pull rod 3, a compression spring 5, a rotating shaft 6, a cam 10, and a small shaft 13. One end of the cam 10 is rotatably connected to the mounting cavity of the square block of the rudder surface through the rotating shaft 6, and the other end is designed as an arc-shaped structure. The arc-shaped structure rotates around the rotation point at the root of the cam 10. During rotation, the edge of the arc-shaped structure contacts and cooperates with the outer edge of the other side of the fixing pin 9. The arc-shaped structure is rotatably connected to one end of the pull rod 3. As shown in the figure, the connection position is set as a straight section small hole. The end of the pull rod 3 is fitted into the straight section small hole through the small shaft 13. This design can ensure a certain degree of flexibility during the unlocking process of the pull rod 3. A limiting boss is provided in the middle section of the pull rod 3. The other end of the pull rod 3 passes through the end through hole of the rudder surface square block 4. The compression spring 5 is fitted on the pull rod 3. The compression spring 5 is in a compressed state, with one end pressing against the boss in the middle of the pull rod and the other end abutting against the bottom of the mounting cavity of the rudder surface square block. After the rudder surface square block is inserted into the servo motor square block, under the combined action of the compression spring 5 and gravity, there is a continuous contact force between the arc structure of the cam 10 and the fixing pin 9. The torque generated by this contact force on the cam is less than the torque generated by the friction force, so the cam will not rotate, thus achieving locking.

[0030] In the design of this invention, the design of cam 10 is particularly important. On the one hand, it needs to consider the flexibility of unlocking, and on the other hand, it needs to ensure the reliability of locking. During the design process, by analyzing the cooperation relationship between the control surface square block and the servo square block, force analysis is performed on the cam. In the locked state, the cam is subjected to the contact force of the fixing pin, generating a torque T1. The torque T2 is caused by the frictional force between the cam and the fixing pin, and the torque T3 is generated by the force exerted by the pull rod on the cam. In the locked state, T1 < T2 + T3 must be satisfied to maintain the locked state of the mechanism. During unlocking, the spring pressure is canceled out by the unlocking force, generating a torque T4 in the opposite direction. The unlocking condition is T1 + T4 > T2. Based on the above force analysis, the cam structure of this invention is designed.

[0031] The locking assembly structure designed in this invention ensures that, in the locked state, the edge of the rotating part of the cam remains in contact with the fixing pin. The cam can only be separated by rotation. Since the servo block and the rudder block are in a plug-in fit, the cam is also subject to rotational constraint under the spring pressure of the pull rod and cannot rotate freely. The rudder block's axial movement is also strongly constrained by the fixing pin, and it is always in a plug-in fit and locked with the servo block. The servo block can then drive the rudder block to rotate, thereby driving the rudder to rotate.

[0032] Specifically, when the rudder mechanism is assembled, the fixing pin 9 and the cam 10 are in contact, and the cam 10 is subjected to the force of the compression spring 5 at this position. The compression spring 5 is in a compressed state at this time, with one end acting on the rudder square block 4 and the other end acting on the platform of the pull rod 3. The slot on the cam 10 is clearance-fitted with the small shaft 13, and the kinematic pair between the small shaft 13 and the cam 10 includes a rotary joint and a sliding joint. The small shaft 13 and the pull rod 3 are interference-fitted, and the head of the pull rod 3 has an external thread that mates with the internal thread of the pull rod head 1. The cylindrical part of the pull rod 3 is inserted into the circular hole of the rudder square block 4, where a nominal clearance is provided to prevent excessive friction during movement. The rudder square block 4 and the servo square block 11 are surface-to-surface transition fits and are the main load-bearing components. The rudder square block 4 and the rudder 7 are fixed by four sets of screw-on bolts and nuts. The servo square block 11 and the fixing pin 9 are interference-fitted, and then a punching process is performed to prevent the fixing pin 9 from coming out. During disassembly, use a fine screwdriver or similar tool to pull the pull rod head 1 upwards, overcoming the force of the compression spring 5 and the contact force between the fixing pin 9 and the cam 10. The cam 10 will rotate clockwise, and after rotating a certain angle, it will reach... Figure 3 At the position shown, the rudder surface 7 is then removed vertically to complete the disassembly of the mechanism.

[0033] During installation, first install the servo block 11 and the fixing pin 9, then punch a hole to prevent the fixing pin 9 from coming out. Next, install the servo block 11 and the bearing 12, completing the installation of the fixed end. Then, align the pull rod 3 and the cam 10, and install the small shaft 13 into the hole of the pull rod 3. Next, insert the compression spring 5 into the pull rod 3, and install this part together with the rudder surface block 4 and the rotating shaft 6. Then, screw the pull rod head 1 into the pull rod 3. Finally, install the rudder surface block part and the rudder surface 7 using four sets of screws and nuts, completing the installation of the moving end. Then, install the rudder surface block 4 of the moving end and the servo block 11 of the fixed end, and push the pull rod head 1 downwards to a position close to the bottom of the pull rod head groove 2, completing the installation of the entire rudder surface.

[0034] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. Those skilled in the art should understand that, based on the design concept of the present application, adaptive modifications can be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the features. These modifications or substitutions do not cause the corresponding technical solutions to depart from the protection scope of the claims of the present invention.

Claims

1. A quick-release mechanism for a control surface, characterized in that, It consists of a control surface, a fixed wing surface, a pull rod, a cam, a spring, a retaining pin, a control surface square block, and a servo motor square block. One end of the servo motor block is fixed to the fixed wing surface, and the other end is inserted into the rudder surface block. The fixing pin is fixed to the servo motor block. One end of the rudder surface square block is fixed to the rudder surface, and the other end can be embedded into the servo motor square block. After being embedded, the inner wall of the rudder surface square block is in contact with the outer edge of the fixing pin. The square block of the rudder surface has a mounting cavity in the middle and a through hole at each end; One end of the cam is rotatably connected to the mounting cavity of the square block of the rudder surface, and the other end is designed as an arc-shaped structure. The arc-shaped structure rotates around the rotation point at the root of the cam. During rotation, the edge of the arc-shaped structure contacts and engages with the outer edge of the other side of the fixing pin. The arc-shaped structure is rotatably connected to one end of the pull rod. A limiting boss is provided in the middle section of the pull rod. The other end of the pull rod passes through the end through hole of the square block of the rudder surface. The spring is fitted on the pull rod. The spring is in a compressed state. One end of the spring abuts against the boss in the middle of the pull rod, and the other end abuts against the bottom of the mounting cavity of the square block of the rudder surface. After the square block of the rudder surface is inserted into the square block of the servo motor, under the combined action of the spring and gravity, there is a continuous contact force between the arc-shaped structure of the cam and the fixing pin. The torque generated by this contact force on the cam is less than the torque generated by the friction force, so the cam will not rotate, thus achieving locking. When unlocking, pull the end of the lever to overcome the force of the spring, the contact force between the fixing pin and the cam arc structure. The cam rotates clockwise. After rotating a certain angle, the rudder surface can be removed vertically, completing the disassembly of the rudder surface.

2. The quick-release mechanism for a control surface as described in claim 1, characterized in that, The cam includes a cylindrical part and a fan-shaped plate structure. The fan-shaped plate structure has a waist-shaped hole, and the pull rod and the fan-shaped plate structure are rotatably connected by a small shaft.

3. The quick-release mechanism for a control surface as described in claim 2, characterized in that, The mounting cavity at one end of the servo motor square block is inserted into the servo motor square block and expands outward by a certain space to make room for the cylindrical pin.

4. The quick-release mechanism for a control surface as described in claim 1, characterized in that, The control surface square block and the servo motor square block are supported by the square surface mating. The servo motor square block has a cylindrical structure at one end that mates with the servo motor. The cylindrical part is connected to the servo motor, and the other part mates with the control surface square block.

5. A quick-release mechanism for a control surface as described in claim 4, characterized in that, A bearing is installed between the cylindrical structure of the servo motor square block and the fixed wing surface.

6. A quick-release mechanism for a control surface as described in any one of claims 1, 4, or 5, characterized in that, The servo block is connected to the drive structure, which drives the servo block to rotate, thereby causing the rudder surface to rotate.

7. A quick-release mechanism for a control surface as described in claim 1, characterized in that, The end of the pull rod is threaded and mates with the pull rod head. The outer diameter of the pull rod head is larger than the diameter of the through hole at the end of the square block of the rudder surface.

8. A quick-release mechanism for a control surface as described in claim 7, characterized in that, The control surface has a pull rod head groove, and the pull rod head at the end of the pull rod is placed in the pull rod head groove.

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