Large aircraft vertical fin overturning transportation platform and control method thereof

Abstract

The invention relates to the technical field of aeronautical manufacturing, and discloses a large aircraft vertical fin overturning transportation platform and a control method thereof.The overturning transportation platform comprises an overturning frame and an overturning mechanism, and the overturning mechanism comprises a swing connecting rod, an overturning connecting rod and a telescopic push rod. The telescopic push rod and the connecting rods (including the swing connecting rod and the overturning connecting rod) are adopted to form a three-connecting-rod overturning structure, and the relative positions of the hinge seats are reasonably arranged, so that the requirement for the bearing capacity of the vertical fin of the airplane is met while the horizontal state and the vertical state of the overturning frame are switched under the action of the telescopic push rod; the turnover action can be quickly and accurately completed, and the working efficiency of the whole transportation platform is improved; in addition, the overturning and transporting platform for the vertical fin of the large aircraft in the embodiment is compact in structure, small in occupied space and capable of bearing large loads, and the stability and safety of the vertical fin of the aircraft in the overturning process are guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aviation manufacturing technology, and discloses a large aircraft vertical tail tilting transport platform and its control method. Background Technology

[0002] The vertical tail of medium and large aircraft is typically tall and large. During assembly, it is laid flat before installation to facilitate construction. However, during installation, the vertical tail must be lifted and connected vertically, necessitating its rotation from a flat to a vertical position. Currently, vertical tail rotation for medium and large aircraft relies on rotating cranes or rotating vehicles. However, existing rotating cranes or vehicles have several limitations in operation, such as: The operation of flipping and hoisting is complex, requiring precise control of the position of the hoisting point and the hoisting force. The slightest carelessness may lead to damage to the tail. Moreover, it requires a high level of professional skills from the operators, which increases the difficulty of operation and safety risks. While the tilting mechanism improves the stability of the tilting action to some extent, its fixed structure makes it less adaptable. For the vertical tails of medium and large aircraft of different models and sizes, it is often necessary to customize a special tilting mechanism, which not only increases the cost but also extends the production cycle.

[0003] In addition, existing tilting equipment has difficulty in accurately positioning and stably supporting the vertical tail during the tilting process, which can easily lead to problems such as swaying and displacement of the vertical tail during the tilting process, affecting the accuracy and efficiency of hoisting and docking. Summary of the Invention

[0004] The purpose of this invention is to provide a large aircraft vertical tail tilting and transport platform and its control method, which can quickly and accurately complete the tilting action and realize the switching between the horizontal and vertical states of the tilting frame.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A large aircraft vertical tail tilting transport platform includes: A tilting frame is used to fix and install the vertical tail of an aircraft. The tilting frame is provided with two hinge points, which are hinged to the installation platform by a fixed hinge seat. A flipping mechanism includes a swing link, a flipping link, and a telescopic push rod. One end of the swing link is hinged to the mounting platform via a first hinge point, and the other end of the swing link is hinged to the flipping link via a second hinge point. The flipping link is hinged to the flipping frame at the end away from the swing link. One end of the telescopic push rod is hinged to the mounting platform via a hinge seat, and the other end of the telescopic push rod is hinged to the flipping link. The swing link, the flipping link, and the flipping frame form a quadrilateral linkage mechanism on the mounting platform, which is used to switch the flipping frame between horizontal and vertical states under the action of the telescopic push rod. An adjustment mechanism is provided on the mounting platform. The hinge seat is movably mounted on the mounting platform via the adjustment mechanism. The adjustment mechanism is used to adjust the distance between the hinge seat and the first hinge point in the quadrilateral linkage mechanism.

[0006] Furthermore, the tilting frame includes a horizontal support and a vertical support. The horizontal support and the vertical support are fixedly connected to form an L-shaped structure. The horizontal support is provided with multiple brackets for supporting the bottom of the aircraft's vertical tail when the tilting frame is in a horizontal state. Furthermore, the vertical support of the tilting frame is provided with multiple positioning components for limiting the aircraft vertical tail on the tilting frame when the tilting frame is in a horizontal state; and for limiting and fixing the aircraft vertical tail during the process of the tilting frame switching from a horizontal state to a vertical state, or from a vertical state to a horizontal state.

[0007] Furthermore, there are at least three positioning components, at least two of which are fixed positioning components, and the rest are retractable positioning components that can extend and retract in a direction perpendicular to the vertical support.

[0008] Furthermore, the adjustment mechanism includes a lead screw and a guide assembly mounted on the mounting platform. A sliding assembly is fitted on the lead screw, and the guide assembly is used to limit the sliding assembly so that the sliding assembly slides along the axial direction of the lead screw. The hinge seat is fixed to the sliding assembly.

[0009] Furthermore, the bottom of the installation platform is equipped with multiple casters.

[0010] Furthermore, the installation platform is also equipped with a lifting support assembly that can contact the ground.

[0011] To achieve the above-mentioned technical effects, the present invention also provides a control method for a large aircraft vertical tail tilting transport platform, used to control the large aircraft vertical tail tilting transport platform, comprising: Based on the quadrilateral linkage mechanism formed by the swing link, the flip link, and the flip frame on the mounting platform, and the hinge point position of the telescopic push rod, a combined structural mechanical analysis model of the quadrilateral linkage mechanism and the telescopic push rod is constructed. Based on the structural and performance parameters of the aircraft vertical tail and the tilting frame, the maximum load of the telescopic push rod at the hinge point on the tilting link is obtained by simulation analysis using the combined structural mechanical analysis model. If the maximum load is greater than or equal to the allowable stress of the flipping link, or greater than or equal to the allowable stress of the telescopic push rod at the hinge point of the flipping link, then the relative position of the hinge seat on the mounting platform is adjusted by the adjusting component until the maximum load is less than the allowable stress of the flipping link and less than the allowable stress of the telescopic push rod at the hinge point of the flipping link, and the corresponding hinge seat position is output. The control and adjustment component adjusts the articulation seat to the output articulation seat position, forming a quadrilateral linkage mechanism of the corresponding shape, and controls the telescopic push rod to switch the horizontal and vertical states of the tilting frame according to the state requirements of the aircraft's vertical tail.

[0012] Compared with the prior art, the beneficial effects of this invention are: 1. This invention adopts a "three-link" flipping structure composed of a telescopic push rod and a connecting rod (including a swing connecting rod and a flipping connecting rod). By reasonably arranging the relative positions of the hinge seats, the horizontal and vertical states of the flipping frame can be switched under the action of the telescopic push rod, while meeting the load-bearing capacity requirements of the aircraft's vertical tail. Moreover, it can quickly and accurately complete the flipping action, improving the working efficiency of the entire transport platform. 2. The flipping transport platform of the present invention has a compact structure, occupies little space, and can withstand a large load, ensuring the stability and safety of the aircraft's vertical tail during the flipping process. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overturning transport platform structure in the embodiment; Figure 2 This is a schematic diagram of the tilting transport platform structure when the horizontal support is in a horizontal state, as shown in the embodiment. Figure 3 This is a schematic diagram of the flipping mechanism in the embodiment; Figure 4 This is a schematic diagram of the flipping frame in the embodiment; Figure 5 This is a schematic diagram of the positioning component in the embodiment; Figure 6 This is a schematic diagram of the adjustment mechanism in the embodiment; The components include: 1. Tilting frame; 101. Horizontal support; 102. Vertical support; 103. Bracket; 104. Positioning assembly; 2. Fixed hinge seat; 3. Mounting platform; 4. Tilting mechanism; 401. Swinging link; 402. Tilting link; 403. Telescopic push rod; 404. First hinge point; 405. Second hinge point; 406. Hinge seat; 5. Lead screw; 6. Guide assembly; 7. Sliding assembly; 8. Caster wheel; 9. Lifting support assembly. Detailed Implementation

[0014] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0015] Example See Figures 1 to 6 A large aircraft vertical tail tilting transport platform, comprising: The tilting frame 1 is used to fix and install the aircraft vertical tail. The tilting frame 1 is provided with two hinge points, and the two hinge points are hinged to the installation platform 3 through the fixed hinge seat 2. The flipping mechanism 4 includes a swing link 401, a flipping link 402, and a telescopic push rod 403. One end of the swing link 401 is hinged to the mounting platform 3 via a first hinge point 404, and the other end of the swing link 401 is hinged to the flipping link 402 via a second hinge point 405. The flipping link 402 is hinged to the flipping frame 1 at the end away from the swing link 401. One end of the telescopic push rod 403 is hinged to the mounting platform 3 via a hinge seat 406, and the other end of the telescopic push rod 403 is hinged to the flipping link 402. The swing link 401, the flipping link 402, and the flipping frame 1 form a quadrilateral linkage mechanism on the mounting platform 3, which is used to switch the horizontal and vertical states of the flipping frame 1 under the action of the telescopic push rod 403. An adjustment mechanism is provided on the mounting platform 3. The hinge seat 406 is movably mounted on the mounting platform 3 through the adjustment mechanism. The adjustment mechanism is used to adjust the distance between the hinge seat 406 and the first hinge point 404 in the quadrilateral linkage mechanism.

[0016] The control method for the overturning transport platform in this embodiment is as follows: Step 1: Based on the swing linkage 401, the flip linkage 402, the quadrilateral linkage mechanism formed by the flip frame 1 on the mounting platform 3, and the hinge point position of the telescopic push rod 403, construct a mechanical analysis model of the combined structure of the quadrilateral linkage mechanism and the telescopic push rod 403. Step 2: Based on the structural and performance parameters of the aircraft vertical tail and the tilting frame 1, the maximum load of the telescopic push rod 403 at the hinge point on the tilting link 402 is obtained by simulation analysis using the combined structural mechanical analysis model. Step 3: If the maximum load is greater than or equal to the allowable stress of the flipping link 402, or greater than or equal to the allowable stress of the telescopic push rod 403 at the hinge point of the flipping link 402, then adjust the relative position of the hinge seat 406 on the mounting platform 3 by adjusting the adjustment component until the maximum load is less than the allowable stress of the flipping link 402 and less than the allowable stress of the telescopic push rod 403 at the hinge point of the flipping link 402, and output the corresponding position of the hinge seat 406. Step 4: The control adjustment component adjusts the hinge seat 406 to the output hinge seat 406 position to form a quadrilateral linkage mechanism of the corresponding shape, and controls the telescopic push rod 403 to switch the horizontal and vertical states of the tilting frame 1 according to the state of the aircraft vertical tail.

[0017] In this embodiment, a "three-bar" flipping structure is formed by a telescopic push rod 403 and connecting rods (including a swing connecting rod 401 and a flipping connecting rod 402). By reasonably arranging the relative positions of the hinge seats 406, the telescopic push rod 403 can switch the flipping frame 1 between horizontal and vertical states while meeting the load-bearing requirements of the aircraft vertical tail. It can also complete the flipping action quickly and accurately, improving the working efficiency of the entire transport platform. In addition, the large aircraft vertical tail flipping transport platform in this embodiment has a compact structure, occupies little space, and can withstand a large load, ensuring the stability and safety of the aircraft vertical tail during the flipping process.

[0018] In this embodiment, the flipping frame 1 includes a horizontal support 101 and a vertical support 102. The horizontal support 101 and the vertical support 102 are fixedly connected to form an L-shaped structure. A plurality of brackets 103 are provided on the horizontal support 101 for supporting the bottom of the aircraft vertical tail when the flipping frame 1 is in a horizontal state. In this embodiment, the vertical support 102 of the flipping frame 1 is provided with a plurality of positioning components 104, which are used to limit the aircraft vertical tail on the flipping frame 1 when the flipping frame 1 is in a horizontal state; and to limit and fix the aircraft vertical tail during the process of the flipping frame 1 switching from a horizontal state to a vertical state, or switching from a vertical state to a horizontal state.

[0019] In this embodiment, there are at least three positioning components 104. At least two of the positioning components 104 are fixed positioning components 104, and the rest are retractable positioning components 104 that can extend and retract in a direction perpendicular to the vertical support 102. This facilitates the positioning of the aircraft vertical tail on the flipping frame 1 by the fixed positioning components 104 when the flipping frame 1 is in a horizontal state, and the overall positioning and fixation of the aircraft vertical tail by the retractable positioning components 104.

[0020] In this embodiment, the adjustment mechanism includes a lead screw 5 and a guide assembly 6 mounted on the mounting platform 3. A sliding assembly 7 is fitted onto the lead screw 5, and the guide assembly 6 limits the sliding assembly 7 to slide along the axial direction of the lead screw 5. The hinge seat 406 is fixed to the sliding assembly 7. One end of the lead screw 5 can be manually adjusted and rotated, or it can be connected to a drive motor. The drive motor drives the lead screw 5 to rotate, thereby driving the sliding assembly 7 to move along the length of the lead screw 5. Since the hinge seat 406 is fixed to the sliding assembly 7, the movement of the sliding assembly 7 can drive the hinge seat 406 to move synchronously, thereby achieving position adjustment of the hinge seat 406.

[0021] In this embodiment, the mounting platform 3 is equipped with multiple casters 8 at its bottom, evenly distributed around the bottom perimeter of the mounting platform 3. These casters allow for flexible changes in the direction of movement of the transport platform, making its movement on the ground more convenient and labor-saving. This allows it to easily adapt to transportation needs in different site environments, facilitating the transport of the aircraft's vertical stabilizer to a designated location. Furthermore, the casters 8 in this embodiment are also equipped with braking devices. After the transport platform reaches its destination, the braking devices securely fix the platform in its corresponding position, preventing accidental movement during placement and ensuring the safety and stability of transportation and operation.

[0022] In this embodiment, the installation platform 3 is further equipped with a lifting support assembly 9 that can contact the ground. This lifting support assembly 9 can employ multiple lifting support legs, evenly distributed at the bottom of the installation platform 3. When the transport platform reaches the designated position, the lifting support legs can be extended downwards to contact the ground, thereby lifting the entire transport platform and lifting the casters 8 off the ground. This effectively distributes the pressure exerted on the transport platform by the aircraft's vertical tail, enhancing the stability of the transport platform during placement, preventing damage to the casters 8 due to excessive force, and further improving the safety and reliability of the transport platform when carrying the vertical tail of a large aircraft. When it is necessary to move the transport platform, the lifting support legs can be retracted upwards, allowing the casters 8 to re-contact the ground, making the transport platform easy to move.

[0023] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A large aircraft vertical tail tilting and transport platform, characterized in that, include: A flip frame (1) is used to fix and install the vertical tail of an aircraft. The flip frame (1) has two hinge points, which are hinged to the mounting platform (3) by a fixed hinge seat (2). A flipping mechanism (4) is provided, comprising a swing link (401), a flipping link (402), and a telescopic push rod (403). One end of the swing link (401) is hinged to the mounting platform (3) via a first hinge point (404), and the other end of the swing link (401) is hinged to the flipping link (402) via a second hinge point (405). The flipping link (402) is hinged to the flipping frame at the end away from the swing link (401). (1) On the mounting platform (3), one end of the telescopic push rod (403) is hinged to the mounting platform (3) through the hinge seat (406), and the other end of the telescopic push rod (403) is hinged to the flipping link (402); and the swing link (401), the flipping link (402), and the flipping frame (1) form a quadrilateral linkage mechanism on the mounting platform (3) for switching the horizontal and vertical states of the flipping frame (1) under the action of the telescopic push rod (403); An adjustment mechanism is provided on the installation platform (3). The hinge seat (406) is movably provided on the installation platform (3) through the adjustment mechanism. The adjustment mechanism is used to adjust the distance between the hinge seat (406) and the first hinge point (404) in the quadrilateral linkage mechanism.

2. The large aircraft vertical tail tilting and transport platform according to claim 1, characterized in that, The flipping frame (1) includes a horizontal support (101) and a vertical support (102). The horizontal support (101) and the vertical support (102) are fixedly connected to form an L-shaped structure. The horizontal support (101) is provided with a plurality of brackets (103) for supporting the bottom of the aircraft vertical tail when the flipping frame (1) is in a horizontal state.

3. The large aircraft vertical tail tilting and transport platform according to claim 2, characterized in that, The vertical support (102) of the flipping frame (1) is provided with a plurality of positioning components (104) for limiting the aircraft vertical tail on the flipping frame (1) when the flipping frame (1) is in a horizontal state; and for limiting and fixing the aircraft vertical tail during the process of the flipping frame (1) switching from a horizontal state to a vertical state or from a vertical state to a horizontal state.

4. The large aircraft vertical tail tilting and transport platform according to claim 3, characterized in that, There are at least three positioning components (104), at least two of which are fixed positioning components (104), and the rest are retractable positioning components (104) that can extend and retract in a direction perpendicular to the vertical support (102).

5. The large aircraft vertical tail tilting and transport platform according to claim 1, characterized in that, The adjustment mechanism includes a lead screw (5) and a guide assembly (6) mounted on the mounting platform (3). A sliding assembly (7) is fitted on the lead screw (5). The guide assembly (6) is used to limit the sliding assembly (7) so that the sliding assembly (7) slides along the axial direction of the lead screw (5). The hinge seat (406) is fixed on the sliding assembly (7).

6. The large aircraft vertical tail tilting and transport platform according to claim 1, characterized in that, The installation platform (3) is equipped with multiple casters (8) at its bottom.

7. The large aircraft vertical tail tilting and transport platform according to claim 1, characterized in that, The installation platform (3) is also equipped with a lifting support assembly (9) that can contact the ground.

8. A control method for a large aircraft vertical tail tilting transport platform, used to control the large aircraft vertical tail tilting transport platform according to any one of claims 1-7, characterized in that, include: Based on the quadrilateral linkage mechanism formed by the swing link (401), the flip link (402), and the flip frame (1) on the mounting platform (3), and the hinge point position of the telescopic push rod (403), a mechanical analysis model of the combined structure of the quadrilateral linkage mechanism and the telescopic push rod (403) is constructed. Based on the structural and performance parameters of the aircraft vertical tail and the tilting frame (1), the maximum load of the telescopic push rod (403) at the hinge point on the tilting link (402) is obtained by simulation analysis using the combined structural mechanical analysis model. If the maximum load is greater than or equal to the allowable stress of the flip link (402), or greater than or equal to the allowable stress of the hinge pin of the telescopic push rod (403) on the flip link (402), then the relative position of the hinge seat (406) on the mounting platform (3) is adjusted by the adjusting component until the maximum load is less than the allowable stress of the flip link (402) and less than the allowable stress of the hinge pin of the telescopic push rod (403) on the flip link (402), and the corresponding hinge seat (406) position is output. The control adjustment component adjusts the articulation seat (406) to the output articulation seat (406) position to form a quadrilateral linkage mechanism of the corresponding shape, and controls the telescopic push rod (403) to switch the horizontal and vertical states of the tilting frame (1) according to the state of the aircraft vertical tail.

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