Quick control surface dismounting tool
By designing a rapid control surface disassembly tool, which utilizes a clamping rod and a linear drive mechanism to unlock the control surface, the problem of low efficiency in existing two-person collaborative operations is solved, enabling rapid disassembly by a single person and improving safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-02-09
- Publication Date
- 2026-03-17
AI Technical Summary
In existing technologies, control surface disassembly requires two people to work together, which consumes a lot of manpower and is inefficient, affecting the maintenance efficiency of aircraft.
Design a rapid control surface removal tool, including a fixing frame, a clamping rod, and a linear drive mechanism. The clamping rod hooks onto a pin, and the linear drive mechanism moves the top clamping part to unlock and remove the control surface.
It enables a quick and simple single-person disassembly process for the control surfaces, improving disassembly efficiency, reducing safety risks, and simplifying the operation process.
Smart Images
Figure CN121670566A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of rudder surface disassembly technology, and more particularly to a rapid rudder surface disassembly tool. Background Technology
[0002] Attitude control and adjustment are crucial for the stable flight of an aircraft. Some aircraft adjust their flight attitude by oscillating control surfaces. The control surfaces of these aircraft are usually detachably connected to the aircraft body using a locking mechanism to facilitate transportation, maintenance, replacement, or configuration according to different mission requirements.
[0003] Currently, some control surfaces employ a spring-loaded automatic locking mechanism. When disassembling the control surface, operators typically need to apply a certain force to push a specially designed unlocking pin horizontally backward to overcome the spring-loaded locking force and release the constraint on the connecting pin before the control surface can be pulled from the aircraft. However, in actual control surface disassembly, two people are usually required to work together: one person uses both hands to push the unlocking pin backward to the limit position of the slot, while the other person simultaneously pulls out the control surface assembly. This method not only consumes more manpower but is also inefficient, severely impacting aircraft maintenance efficiency. Summary of the Invention
[0004] To overcome the shortcomings mentioned in the background art, this application provides a quick control surface disassembly tool.
[0005] A quick control surface removal tool includes a mounting frame with a clamping rod for hooking a pin. The mounting frame is equipped with a linear drive mechanism, the drive direction of which is parallel to the clamping rod. The linear drive mechanism is equipped with a clamping part for abutting against the control surface. When the linear drive mechanism drives the clamping part to move, the clamping part moves relative to the clamping rod.
[0006] In one embodiment, the linear drive mechanism includes a push rod, a grip handle, a push trigger, and a push plate. The push rod is slidably mounted on the fixed frame, and the clamping part is mounted on the end of the push rod. The push rod is arranged parallel to the clamping rod. The grip handle is fixedly mounted on the fixed frame, and the push trigger is rotatably mounted on the fixed frame. The push trigger has a push plate near the push rod for driving the push rod to move. The push plate has a through hole with a diameter larger than that of the push rod. The push rod passes through the through hole of the push plate, and the position of the through hole of the push plate is in frictional engagement with the push rod.
[0007] As one embodiment, a first return spring is sleeved on the push rod. The first return spring is located on the side of the push plate near the tightening part, and the two ends of the first return spring are respectively connected to the push plate and the fixing frame.
[0008] As one embodiment, a backstop plate for preventing the push rod from retracting is rotatably mounted on the fixing frame. The backstop plate has an opening with a diameter larger than that of the push rod. The push rod passes through the opening of the backstop plate. When the backstop plate can prevent the push rod from retracting, there is an angle between the vertical plane perpendicular to the axis of the push rod and the backstop plate. At this time, the friction between the opening of the backstop plate and the push rod can prevent the push rod from retracting during the disassembly of the rudder surface.
[0009] As one embodiment, a second return spring for resetting the anti-reverse pressure plate is installed at one end away from its rotation axis, and the two ends of the second return spring are respectively connected to the anti-reverse pressure plate and the fixing frame.
[0010] As one embodiment, the end of the clamping rod is provided with a hook for hooking the pin, and the inner diameter of the hook on the clamping rod is equal to the outer diameter of the pin.
[0011] As one embodiment, the top clamping part is provided with a clamping groove corresponding to the shape of the end of the rudder surface, and a flexible pad for increasing friction is provided inside the clamping groove.
[0012] As one embodiment, a handle is provided at the end of the push rod away from the tightening part.
[0013] As one embodiment, the grip handle and the push trigger are provided with an anti-slip layer to increase friction.
[0014] As one embodiment, the clamping part is detachably mounted on the push rod.
[0015] The beneficial effects of this application are: This invention involves installing a clamping rod and a linear drive mechanism on a fixed frame, and installing a clamping part on the linear drive mechanism. When disassembling the control surface, the clamping rod hooks onto a pin, driving the linear drive mechanism to move the clamping part, causing the clamping part to abut against the control surface. Continuing to drive the linear drive mechanism causes relative displacement between the clamping rod and the clamping part, and the clamping rod pulls the pin to move, unlocking the control surface from the aircraft. Subsequently, the control surface is pulled to remove it from the aircraft. The entire process is simple, convenient, and quick, improving the efficiency of control surface disassembly.
[0016] Other technical solutions of the present invention can also achieve the following technical effects: The push rod is mounted on the end of the push rod with a clamping part, and the handle is fixedly mounted on the lower part of the mounting frame. The push trigger is rotatably mounted on the mounting frame. A push plate is installed on the end of the push trigger near its own rotation axis. The push plate has a through hole with a diameter larger than that of the push rod. The through hole of the push plate can frictionally engage with the push rod. By pressing the push trigger, the push trigger rotates towards the handle. When the push trigger rotates, it drives the push plate to rotate. The first return spring on the push plate is compressed. Before the push plate rotates to the vertical position, the through hole of the push plate contacts and squeezes the push rod. As the push plate continues to rotate, the push plate drives the push rod forward under the action of friction, thereby bringing the clamping part closer to the control surface. After the clamping part is clamped on the leading or trailing edge of the control surface, the pin moves along its respective slide groove, and the control surface is unlocked from the aircraft. Pulling the disassembly tool outward, the disassembly tool drives the control surface away from the aircraft until the control surface is separated from the aircraft. The whole process can be operated by a single person and is simple and convenient, which can improve the efficiency of control surface disassembly.
[0017] By rotating and installing a backstop plate on the fixed frame, the backstop plate is provided with an opening with a diameter larger than that of the push rod. The push rod passes through the opening of the backstop plate, and the backstop plate can prevent the push rod from abnormally retracting, so that the clamping rod can remain stable after contacting the rudder surface, thereby improving the safety of rudder surface disassembly and reducing safety risks. Attached Figure Description
[0018] Figure 1 This is a three-dimensional structural diagram of the rapid control surface disassembly tool disclosed in the embodiments of the present invention; Figure 2 This is a schematic diagram of the three-dimensional structure of the rudder surface disclosed in the embodiments of the present invention.
[0019] In the attached diagram, the following are the reference numerals: 1. Fixing bracket, 2. Clamping rod, 3. Tightening part, 4. Push rod, 5. Grip handle, 6. Push trigger, 7. Push pressure plate, 8. Handle, 9. First return spring, 10. Anti-reverse pressure plate, 11. Second return spring. Detailed Implementation
[0020] To make the above-mentioned objectives, features, and advantages of the present invention more apparent and understandable, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0021] A quick control surface removal tool, such as Figure 1 and Figure 2As shown, the system includes a fixed frame 1, on which a clamping rod 2 is mounted. The clamping rod 2 is used to hook the locking pin on the rudder surface. A pair of clamping rods 2 can be provided so that the number of clamping rods 2 is consistent with the number of pins. The clamping rod 2 can be detachably installed from the fixed frame 1 to facilitate replacement and use of clamping rods 2 of different sizes. A linear drive mechanism is provided on the fixed frame 1. The driving direction of the linear drive mechanism is parallel to the length direction of the clamping rod 2. A clamping part 3 is installed on the linear drive mechanism for abutting against the rudder surface. The inner side of the clamping part 3 can deform to fit the rudder surface. When the linear drive mechanism drives the clamping part 3 to move, the clamping part 3 moves relative to the clamping rod 2. The linear drive mechanism can be an electric push rod. The fixed end of the electric push rod is fixedly installed on the fixed frame 1, and the telescopic end of the electric push rod is equipped with the clamping part 3. When the control surface needs to be removed, lift the disassembly tool so that the locking rod 2 on the disassembly tool hooks the pin on the control surface. Then, align the tightening part 3 with the leading or trailing edge of the control surface. If the pin is located on the side of the slide near the leading edge when locked, the tightening part 3 can be aligned with the trailing edge of the control surface. If the pin is located on the side of the slide near the trailing edge when locked, the tightening part 3 can be aligned with the leading edge of the control surface. Then, activate the electric push rod. When the extension end of the electric push rod drives the tightening part 3 to abut against the leading or trailing edge of the control surface, the two locking rods 2 simultaneously pull the two pins on the control surface, causing the pins to move along their respective slides. When the pins move to the end of the slides, the control surface is unlocked from the aircraft. At this time, the electric push rod closes, and the disassembly tool is pulled outward, causing the disassembly tool to move the control surface away from the aircraft until the control surface is separated from the aircraft. The disassembly tool can be set to a size and weight that can be picked up and operated by a single person, allowing the operator to disassemble the control surface by one person. Of course, the size and weight of the disassembly tool can be freely set according to needs.
[0022] In one embodiment, such as Figure 1 and Figure 2As shown, the linear drive mechanism includes a push rod 4, a grip handle 5, a push trigger 6, and a push plate 7. The push rod 4 is slidably mounted on a fixed frame 1. The fixed frame 1 can be a frame structure or other structures. The sliding direction of the push rod 4 is parallel to its axial direction and the length direction of the clamping rod 2. A clamping part 3 is mounted on the end of the push rod 4, and the clamping part 3 and the clamping rod 2 are located on the same side of the fixed frame 1. The grip handle 5 is fixedly mounted on the lower part of the fixed frame 1, and the grip handle 5 facilitates the hand gripping of the disassembly tool. The push trigger 6 is rotatably mounted on the fixed frame 1, and the push trigger 6 is located on the lower part of the fixed frame 1. The handle 5 is held near the top clamping part 3. A push plate 7 is installed at the end of the push trigger 6 near its own rotation axis. The push plate 7 has a through hole, which allows frictional engagement with the push rod 4. An annular soft pad, such as a rubber pad, can be provided inside the through hole. The through hole can be circular or of other shapes. When the through hole is circular, its diameter is slightly larger than the diameter of the push rod 4, approximately 4mm-5mm larger. The push rod 4 passes through the through hole of the push plate 7. When the push plate 7 is in its initial position (… Figure 1 When the position shown for the push plate 7 is the initial position, the push plate 7 and the push rod 4 do not need to contact each other. There is an angle between the vertical plane perpendicular to the axis of the push rod 4 and the push plate 7. The through hole of the push plate 7 can be frictionally transmitted with the push rod 4. The push rod 4 is fitted with a first return spring 9. The first return spring 9 is located on the side of the push plate 7 near the top clamping part 3. The two ends of the first return spring 9 are fixedly connected to the push plate 7 and the fixing frame 1 respectively. The first return spring 9 is used to reset the push plate 7 and the push trigger 6.
[0023] like Figure 1 As shown, a backstop plate 10 for preventing the push rod 4 from retracting is rotatably mounted on the fixed frame 1. This "retraction" should be understood as retraction under abnormal conditions, that is, retraction that may cause safety risks or be unexpected during the disassembly of the rudder surface, rather than retraction required by the operator's active operation. The rotation axis of the anti-reverse pressure plate 10 can be parallel to the horizontal plane and perpendicular to the driving direction of the push rod 4. The anti-reverse pressure plate 10 is provided with an opening located in the middle of the anti-reverse pressure plate 10. The opening can be round or other shapes. The diameter of the opening is slightly larger than the diameter of the push rod 4. The push rod 4 passes through the opening of the anti-reverse pressure plate 10. The diameter of the opening can be 1mm-1.5mm larger than the diameter of the push rod 4. A second return spring 11 for resetting the anti-reverse pressure plate 10 is installed at one end of the anti-reverse pressure plate 10 away from its rotation center. The two ends of the second return spring 11 are connected to the anti-reverse pressure plate 10 and the fixing frame 1, respectively. When the anti-reverse pressure plate 10 can prevent the push rod 4 from retracting, there is an angle between the vertical plane (hereinafter referred to as the vertical plane) perpendicular to the axis of the push rod 4 and the anti-reverse pressure plate 10. At this time, there is friction between the opening of the anti-reverse pressure plate 10 and the push rod 4, and the magnitude of the friction is sufficient to prevent the push rod 4 from retracting when the rudder surface is removed.
[0024] Specific working process: When it is necessary to remove the rudder surface, the operator holds the handle 5, picks up the tool, aligns the two locking rods 2 with the two pins and hooks the pins, then aligns the tightening part 3 with the leading or trailing edge of the rudder surface, and then the operator presses the push trigger 6, causing the push trigger 6 to rotate towards the handle 5. When the push trigger 6 rotates, it drives the push plate 7 on it to rotate, and the first return spring 9 on the push plate 7 is compressed. Before the push plate 7 rotates to the vertical position, the rubber pad at the through hole of the push plate 7 contacts and squeezes the push rod 4, causing the rubber pad to deform. As the push plate 7 continues to rotate, the rubber pad at the through hole drives the push rod 4 forward under the action of friction, thereby bringing the tightening part 3 closer to the rudder surface. As push rod 4 moves forward, it drives anti-reverse pressure plate 10 to rotate under the action of friction, causing the projected area of the opening on the vertical plane to gradually increase. The friction between anti-reverse pressure plate 10 and push rod 4 decreases until push rod 4 and anti-reverse pressure plate 10 move relative to each other, that is, push rod 4 can move forward normally, and anti-reverse pressure plate 10 remains in position after rotation. Since the tightening part 3 may not still be in contact with the control surface after the operator presses the push trigger 6 once, the operator can release the push trigger 6. At this time, under the action of the first return spring 9, push plate 7 and push trigger 6 are reset. During the reset process of push plate 7, there is still friction between push plate 7 and push rod 4 and between push plate 7 and anti-reverse pressure plate 10, causing push rod 4 to retract a small distance under the action of friction. Anti-reverse pressure plate 10 rotates and resets under the action of friction. It should be emphasized that even though push rod 4 will retract a small distance each time push trigger 6 is released, this will not affect the disassembly of control surface. When the anti-reverse pressure plate 10 is reset, the friction between the push rod 4 and the anti-reverse pressure plate 10 is large enough that the push rod 4 cannot retract further. The operator can press and release the push trigger 6 repeatedly to make the push rod 4 drive the clamping part 3 forward step by step. After the clamping part 3 is pressed against the control surface, continuing to press the push trigger 6 will cause the locking rod 2 to pull the two pins on the control surface simultaneously, causing the pins to move along their respective slides. When the pins move to the end of the slides, the control surface is unlocked from the aircraft. At this time, the operator pulls the disassembly tool outward to make the disassembly tool move the control surface away from the aircraft until the control surface is separated from the aircraft. When it is necessary to reset the push rod 4, the operator can manually press the anti-reverse pressure plate 10 to compress the second return spring 11, increasing the projected area of the opening on the vertical plane and reducing the friction between the anti-reverse pressure plate 10 and the push rod 4. When the friction is reduced to the point that the push rod 4 can retract, the operator can pull the push rod 4 to retract. When using this tool to disassemble the control surface, the entire disassembly process can be performed by a single person, and the operation is simple and convenient, which can improve the efficiency of control surface disassembly.
[0025] In one embodiment, such as Figure 1As shown, the end of the clamping rod 2 away from the fixing frame 1 is provided with a hook for hooking the pin. The inner diameter of the hook on the clamping rod 2 can be equal to or greater than the outer diameter of the pin. The size of the inner diameter of the hook can be freely set according to the outer diameter of the pin.
[0026] In one embodiment, such as Figure 1 As shown, the clamping part 3 is provided with a clamping groove. The shape of the clamping groove can correspond to the shape of the front edge or the rear edge of the rudder, so that the clamping groove can be more stably clamped on the rudder surface. The inside of the clamping groove is provided with a flexible gasket. The flexible gasket can not only increase the friction between it and the rudder surface, thus making it easier to remove the rudder surface, but also protect the rudder surface when the clamping part 3 contacts the rudder surface, so as to avoid damage to the rudder surface.
[0027] In one embodiment, such as Figure 1 As shown, a handle 8 is fixedly installed at the end of the push rod 4 away from the top clamping part 3, so that the operator can pull the push rod 4 back and forth by using the handle 8.
[0028] In one embodiment, a handle 8 is rotatably mounted on the end of the push rod 4 away from the tightening part 3. The push rod 4 is a hollow rod, and a conveying rod is slidably mounted inside the push rod 4. The tightening part 3 is mounted on the push rod 4 via the conveying rod. The tightening part 3 is located at the end of the conveying rod away from the handle 8. The conveying rod is a hollow rod with internal threads. A screw is fixedly mounted on the handle 8, located inside the conveying rod and threadedly connected to it. When the operator rotates the handle 8, the handle 8 drives the screw to rotate, and the rotation of the screw causes the conveying rod to slide along the push rod 4.
[0029] When using the device, the operator can first replace the clamping rod 2 with a different size according to the size of the rudder surface. After the clamping rod 2 hooks the pin, the operator can first press and release the push trigger 6 in a cycle to make the top clamping part 3 quickly contact the rudder surface. Then, rotate the handle 8, and the conveying rod gradually extends from the push rod 4. At this time, the clamping rod 2 can pull the pin on the rudder surface to move. By rotating the handle 8, the conveying rod pulls the pin, converting the rotational stroke into a linear stroke. This is suitable for situations where the pin locking force is large.
[0030] In one embodiment, the handle 5 and the trigger 6 are provided with an anti-slip layer, which can increase the friction with the human hand and reduce the probability of the operator's hand slipping.
[0031] In one embodiment, the clamping part 3 is detachably mounted on the push rod 4, which facilitates the replacement of different clamping parts 3 for different rudder surfaces, thus expanding the applicability of the disassembly tool.
[0032] The embodiments described above are merely preferred embodiments of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications, improvements, and substitutions without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of this patent should be determined by the appended claims.
Claims
1. A rapid rudder surface disassembly tool characterized by, The utility model provides a kind of straight-line driving mechanism, comprising fixed frame (1), the fixed frame (1) is equipped with the clamping rod (2) for hooking pin, the fixed frame (1) is provided with linear drive mechanism, the driving direction of linear drive mechanism is parallel with the clamping rod (2), linear drive mechanism is equipped with the top tight part (3) for being in abutment with rudder surface, when linear drive mechanism drives the top tight part (3) moves, the top tight part (3) moves relative to the clamping rod (2).
2. A rapid control surface disassembly tool according to claim 1, wherein, The linear drive mechanism includes a push rod (4), a holding handle (5), a push trigger (6), and a push pressing plate (7). The push rod (4) is slidingly installed on the fixed frame (1), and the top tight part (3) is installed at the end of the push rod (4). The push rod (4) is arranged in parallel with the clamping rod (2). The holding handle (5) is fixedly installed on the fixed frame (1). The push trigger (6) is rotatably installed on the fixed frame (1). The push trigger (6) is installed with the push pressing plate (7) at one end close to the push rod (4) for driving the push rod (4) to move. The push pressing plate (7) is provided with a through hole. The diameter of the through hole of the push pressing plate (7) is larger than the diameter of the push rod (4). The push rod (4) passes through the through hole of the push pressing plate (7). The position of the through hole of the push pressing plate (7) is in frictional engagement with the push rod (4).
3. A rapid control surface disassembly tool according to claim 2, wherein, A first return spring (9) is sleeved on the push rod (4). The first return spring (9) is located at the side of the push pressing plate (7) close to the top tight part (3). The two ends of the first return spring (9) are respectively connected with the push pressing plate (7) and the fixed frame (1).
4. A rapid control surface disassembly tool according to claim 2, wherein, A retreat stopping pressing plate (10) is rotatably installed on the fixed frame (1) for preventing the push rod (4) from retreating. The retreat stopping pressing plate (10) is provided with an opening with a diameter larger than the diameter of the push rod (4). The push rod (4) passes through the opening of the retreat stopping pressing plate (10). When the retreat stopping pressing plate (10) can prevent the push rod (4) from retreating, there is an included angle between the vertical plane perpendicular to the axis of the push rod (4) and the retreat stopping pressing plate (10). At this time, the frictional force between the opening position of the retreat stopping pressing plate (10) and the push rod (4) can prevent the push rod (4) from retreating during the disassembly of the rudder surface.
5. A rapid control surface disassembly tool according to claim 4, wherein, An end of the retreat stopping pressing plate (10) away from the rotation axis of the retreat stopping pressing plate (10) is installed with a second return spring (11) for resetting the retreat stopping pressing plate (10). The two ends of the second return spring (11) are respectively connected with the retreat stopping pressing plate (10) and the fixed frame (1).
6. A rapid control surface disassembly tool as defined in claim 1, wherein, The end of the clamping rod (2) is provided with a hook for hooking the pin. The inner diameter of the hook on the clamping rod (2) is equal to the outer diameter of the pin.
7. A rapid rudder disassembly tool according to claim 1, wherein The top tight part (3) is provided with a clamping groove corresponding to the shape of the end of the rudder surface. The inside of the clamping groove is provided with a flexible gasket for increasing the frictional force.
8. A rapid control surface disassembly tool according to claim 1, wherein, An end of the push rod (4) away from the top tight part (3) is provided with a handle (8).
9. A rapid rudder disassembly tool according to claim 1, wherein The holding handle (5) and the push trigger (6) are provided with an anti-skid layer for increasing the frictional force.
10. A rapid rudder surface disassembly tool according to claim 1, wherein, The top-tight part (3) is detachably mounted on the push rod (4).