Aircraft vibration simulation device and method

Abstract

The present invention discloses an aircraft vibration simulation device and method, the device comprises: a working box, a first opening and at least one group of first material loading plates are arranged on the top of the working box, a cover is arranged at the first opening, and a rack is arranged on the top of the cover; a lifting plate, which moves up and down under the driving of power, and at least one group of second material loading plates are arranged on the top of the lifting plate; when the lifting plate is located in the working box, it is located below the first opening; a moving plate; a rotating plate, which is arranged on the working box; a plurality of pairs of rotating rods, each pair of rotating rods is arranged on the rotating plate and the moving plate respectively, each rotating rod on the moving plate can rotate, and each pair of rotating rods corresponds to a group of first material loading plates and a group of second material loading plates respectively; one end of each rotating rod is provided with a receiving groove; a screw rod; a nut, which is arranged on the screw rod, and one end of the moving plate is fixedly connected to the nut; a gear, which is fixed on one end of the screw rod and meshes with the rack. The device of the present invention has a simple structure, is simple to use, and can save costs.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft test piece vibration simulation equipment, and more specifically, to an aircraft vibration simulation device and method. Background Art

[0002] During the operation of an aircraft, it needs to withstand great impact and vibration. Therefore, it is very necessary to conduct reliability tests on airborne precision instruments and aircraft structural parts in a laboratory environment.

[0003] Existing aircraft vibration simulation devices, such as an aircraft shaft system impact vibration simulation test device disclosed in China Patent Authorization Announcement No. CN111323197B, require manual removal of the first and second protective plates at the beginning of use. After the vibration simulation is completed, the protective plates need to be manually pulled out, the fourth hydraulic rod works to realize the downward movement of the material shifting frame, and the dual-axis motor works to realize the movement of the material loading blocks on both sides toward each other until the material loading blocks are located below the aircraft shaft, the third hydraulic rod works to realize the movement of the slide plate, and then the fourth hydraulic rod works to realize the upward movement of the material loading block, and the aircraft shaft is located in the material loading slot of the material loading block, so as to realize the removal of the aircraft shaft. It can be seen that after the simulation is completed, a complex structure needs to be designed separately to remove the aircraft shaft upward, which makes the production cost high. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft vibration simulation device and method, which has a simple structure and after the simulation, only needs to move the plate to continue to push the aircraft test piece forward until it is placed on each group of first loading plates, thereby reducing production costs.

[0005] In order to achieve these objects and other advantages of the present invention, there is provided an aircraft vibration simulation device, comprising:

[0006] The working box is in the shape of a rectangular parallelepiped with a hollow interior, a first opening is arranged at one end of the top of the working box, and at least one set of first material loading plates and a second opening is arranged at the other end, the shape of the first material loading plates is adapted to the shape of the aircraft test piece, each set of first material loading plates is composed of a plurality of first material loading plates arranged at intervals along the length direction of the working box, a cover is arranged corresponding to the first opening, and a rack is arranged on one side of the top of the cover along the width direction of the working box;

[0007] a lifting plate, which moves up and down between a first position and a second position under the drive of a first power device, at least one group of second loading plates is arranged on the top of the lifting plate, the shape of the second loading plates is adapted to the shape of the aircraft test piece, and each group of second loading plates is composed of a plurality of second loading plates arranged at intervals along the length direction of the working box; when the lifting plate is in the first position, the lifting plate is located in the working box and below the first opening;

[0008] a movable plate, which is arranged vertically;

[0009] A rotating plate is arranged on the working box and is rotatably connected to the top of the working box, and can be rotated from a vertical state to a horizontal state toward the direction where each group of first material loading plates are located, or from a horizontal state to a vertical state;

[0010] The first baffle and the second baffle are both vertically arranged and opposite to the second opening, the height of the top of the first baffle is higher than the height of the top of the second baffle, and the first baffle and the second baffle can be driven by the second power device located in the working box to move up and down between the highest position and the lowest position; when the first baffle and the second baffle are both in the highest position and the rotating plate is in the vertical state, the rotating plate is clamped between the first baffle and the second baffle, and the first baffle is close to each group of first loading plates; when the first baffle and the second baffle are in the lowest position and the rotating plate is in the horizontal position, the first baffle and the second baffle are both located in the working box; during the process of the rotating plate rotating from the horizontal state to the vertical state under the push of the first baffle, the second baffle is always located in the working box, and when the rotating plate rotates from the horizontal state to the vertical state under the push of the first baffle, the second baffle moves to the outside of the working box;

[0011] A plurality of pairs of rotating rods, each pair of rotating rods is respectively arranged on the rotating plate and the moving plate, each rotating rod on the moving plate can rotate under the drive of the third power device, each rotating rod on the rotating plate is respectively rotatably connected to the rotating plate, each pair of rotating rods is respectively corresponding to a group of first material loading plates and a group of second material loading plates; one end of each rotating rod is provided with a receiving groove for receiving the aircraft test piece;

[0012] A screw rod is arranged along the length direction of the working box;

[0013] A nut is arranged on the screw rod, and one end of the moving plate is fixedly connected to the nut;

[0014] A gear, which is fixed to one end of the lead screw and meshes with the rack;

[0015] When the screw rod rotates under the drive of the fourth power device, the cover moves between the third position and the fourth position along the width direction of the working box, and the moving plate moves between the fifth position and the sixth position along the length direction of the working box and can stay at the seventh position. When the moving plate is at the seventh position, the cover is at the eighth position.

[0016] When the movable plate is in the fifth position, the cover seals the first opening, the rotating plate is located between the cover and each group of first material loading plates and is in a horizontal state, and the height of the top of the rotating rod on the rotating plate is not higher than the height of the bottom of the movable plate, and the rotating rod on the movable plate can push the aircraft test piece on the movable plate to the corresponding group of first material loading plates;

[0017] When the movable plate is in the sixth position, the lifting plate is in the second position, the rotating plate is in the vertical state, and one aircraft test piece is placed in each group of second loading plates, the cover opens the first opening, the lifting plate is located between the movable plate and the rotating plate, and both ends of each aircraft test piece are respectively separated from the corresponding pair of rotating rods by a preset distance;

[0018] When the movable plate is in the seventh position, the cover is in the eighth position, the lifting plate is in the second position, the rotating plate is in the vertical state, and one aircraft test piece is placed in each group of second loading plates, both ends of each aircraft test piece are respectively located in a pair of accommodating grooves corresponding thereto, and the cover is separated from the first opening by a preset distance;

[0019] When the lifting plate is in the second position, the rotating plate is in a vertical state, and each group of second loading plates has an aircraft test piece placed therein, one end of the aircraft test piece is located in the receiving groove of the rotating rod on the corresponding moving plate, and the other end is placed in at least one first loading plate located on the inner side of a group of first loading plates corresponding thereto, the moving plate is in contact with the lifting plate or is separated by a preset distance.

[0020] Preferably, in the aircraft vibration simulation device, there are multiple groups of the first loading plates.

[0021] Preferably, in the aircraft vibration simulation device, two L-shaped steps are arranged at intervals on the top of the working box along the length direction of the working box, both steps extend along the width direction of the working box, and the first opening is located between the two steps; when the cover seals the first opening, the cover is placed on the horizontal parts of the two steps, and both sides of the cover are in contact with the vertical parts of the two steps.

[0022] Preferably, in the aircraft vibration simulation device, a support platform is provided on one side of the working box, and when the cover is in the fourth position, the support platform supports the cover.

[0023] Preferably, in the aircraft vibration simulation device, each rotating rod on the movable plate is provided with a sprocket, each sprocket is connected by a chain, and one rotating rod among each rotating rod on the movable plate rotates under the drive of the third power device.

[0024] Preferably, in the aircraft vibration simulation device, a notch is provided on the rotating plate;

[0025] The aircraft vibration simulation device also includes:

[0026] A guide rod passes through the notch, and both ends of the guide rod are respectively fixedly connected to the top of the working box.

[0027] Preferably, in the aircraft vibration simulation device, a rotating shaft is provided on the rotating plate, the rotating shaft is provided along the width direction of the working box, and one end of the rotating shaft rotates under the drive of the second power device.

[0028] The method for using the aircraft vibration simulation device comprises the following steps:

[0029] Step 1: rotate the rotating plate to a horizontal position, the movable plate is in the fifth position, and the cover is in the third position; then the fourth power device drives the screw to rotate, so that the movable plate moves to the sixth position, and the cover moves to the fourth position;

[0030] Step 2: The second power device drives the first baffle plate and the second baffle plate upward, and the first baffle plate is used to push the rotating plate to rotate to a vertical position, and the first baffle plate and the second baffle plate are used to clamp the rotating plate, and the first driving device drives the lifting plate to move to the second position, and then an aircraft test piece is placed on each group of second loading plates;

[0031] Step 3: The fourth power device drives the screw rod to rotate in the opposite direction, and the movable plate pushes each aircraft test piece to move toward the rotating plate. After the two ends of the aircraft test piece are respectively located in a pair of accommodating grooves corresponding thereto, the lifting plate is lowered to the first position, and then the third power device drives each rotating rod on the movable plate to rotate, and the aircraft test piece and the rotating rod on the rotating plate rotate synchronously;

[0032] Step 4: Perform vibration simulation on the aircraft test piece;

[0033] Step 5, raise the lifting plate to the second position, then the second power device drives the first baffle and the second baffle to descend to the lowest position, then the fourth power device drives the screw rod to rotate until the movable plate moves to the sixth position, then the operator moves each aircraft test piece toward the movable plate, after the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position, then the fourth power device drives the screw rod to continue to rotate in the opposite direction, and the movable plate pushes each aircraft test piece to move toward a corresponding group of first loading plates, when one end of the aircraft test piece is located in the accommodating groove of the rotating rod on the corresponding movable plate, and the other end is placed in at least one first loading plate located on the inner side of the corresponding group of first loading plates, the first driving device drives the lifting plate to move to the first position, then the fourth power device drives the screw rod to continue to rotate in the opposite direction until the movable plate is in the fifth position, the cover is in the third position, each aircraft test piece is placed on a corresponding group of first loading plates, then each aircraft test piece is removed, and the above steps are repeated.

[0034] The present invention has at least the following beneficial effects:

[0035] 1. High precision and reliability

[0036] Precise control: Through the coordinated work of multiple power devices (first, second, third, and fourth power devices), the movements of various components (such as lifting plates, moving plates, rotating plates, etc.) are ensured to be accurate and correct, which improves the accuracy of test piece placement and removal.

[0037] Stable support: A variety of carrier plates (primary carrier plate and secondary carrier plate) are designed. The shapes of these carrier plates are adapted to the different shapes of test pieces and provide stable support to ensure that the position of the test piece remains fixed during the test.

[0038] 2. Efficient operation process

[0039] Fast switching state: Through the cooperation of the screw and gear rack mechanism, the cover can be opened and closed and the position of the moving plate can be adjusted quickly, shortening the preparation time and cycle.

[0040] 3. Optimized space utilization

[0041] Compact layout: All functional components are cleverly integrated into a rectangular work box, saving space and facilitating maintenance and management.

[0042] 4. Monitoring and feedback

[0043] Real-time monitoring: Equipped with an impact vibration monitoring system, it can monitor the impact force and frequency in real time during the vibration simulation process, as well as the vibration of the simulated casing and three-point simulated shaft system, providing reliable data support for subsequent analysis.

[0044] In summary, the aircraft vibration simulation device of the present invention not only realizes efficient and accurate vibration simulation of aircraft test pieces, but also has a high level of automation and wide applicability, representing an important advancement in vibration testing technology in the field of aerospace engineering.

[0045] Other advantages, objectives and features of the present invention will be embodied in part through the following description, and in part will be understood by those skilled in the art through study and practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 is a top view of an aircraft vibration simulation device in a use state according to an embodiment of the present invention;

[0047] Figure 2 is a top view of another use state of the aircraft vibration simulation device according to one embodiment of the present invention;

[0048] Figure 3 is a schematic structural diagram of a lifting plate according to an embodiment of the present invention;

[0049] Figure 4Schematic diagram of the structure of a cover and two steps according to an embodiment of the present invention. DETAILED DESCRIPTION

[0050] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0051] It should be noted that, in the description of the present invention, the terms "lateral", "longitudinal", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc. indicating orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0052] like Figures 1 to 3 As shown, the present invention provides an aircraft vibration simulation device, comprising:

[0053] The working box 1 is a rectangular parallelepiped with a hollow interior, and one end of the top of the working box 1 (such as Figure 1 As shown, the rear end of the top of the working box 1 is provided with a first opening, and the other end (as shown Figure 1 As shown, at least one set of first material loading plates 2 and a second opening is provided at the front end of the top of the working box 1, and each set of first material loading plates 2 is formed along the length direction of the working box 1 (such as Figure 1 The first carrier plate 2 is composed of a plurality of first carrier plates 2 spaced apart in the front and rear directions (shown in the figure), the shape of the first carrier plate 2 is adapted to the shape of the aircraft test piece, for example, if the aircraft test piece is cylindrical, the first carrier plate 2 is an arc-shaped opening upward, and if the aircraft test piece is a rectangular parallelepiped, the first carrier plate 2 is a concave-shaped opening upward, each group of first carrier plates 2 can independently support one aircraft test piece 12, the first opening is correspondingly provided with a cover 3, and a rack 15 is provided on one side of the top of the cover 3 along the width direction of the working box 1, as shown in FIG. Figure 1 As shown, the rack 15 is located at the rear side of the top of the cover 3, so as not to affect the movement of the moving plate 6;

[0054] The lifting plate 4 is driven by the first power device to be in the first position ( Figure 1 The lifting plate 4 indicated by the dotted line is in the first position. Figure 3As shown, the lifting plate 4 is in the first position) and moves up and down between the second position, and at least one group of second loading plates 5 is arranged on the top of the lifting plate 4, and each group of second loading plates 5 is composed of a plurality of second loading plates 5 arranged at intervals along the length direction of the working box 1, and the shape of the second loading plates 5 is adapted to the shape of the aircraft test piece. For example, if the aircraft test piece is cylindrical, the second loading plates 5 are arc-shaped with the opening upward, and if the aircraft test piece is rectangular, the second loading plates 5 are concave-shaped with the opening upward, and each group of second loading plates 5 can independently support one aircraft test piece 12; when the lifting plate 4 is in the first position, the lifting plate 4 is located in the working box 1, opposite to the first opening, and located below the first opening; when the lifting plate 4 is in the second position, the lifting plate 4 is located outside the working box 1, and located above the first opening;

[0055] A movable plate 6, which is arranged vertically;

[0056] The rotating plate 7 is arranged on the working box 1 and is rotatably connected to the top of the working box, and can be rotated from a vertical state to a horizontal state (such as Figure 1 The state shown is a horizontal state, in which the rotating rod 8 on the rotating plate 7 is vertical) or rotated from a horizontal state to a vertical state (such as Figure 2 The state shown is a vertical state, in which the rotating rod 8 on the rotating plate 7 is horizontal, the same as the rotating rod 8 on the moving plate 6). When vibration simulation is required, the rotating plate 7 is in a vertical state, and can be in a horizontal state at other times;

[0057] The first baffle 16 and the second baffle 17 are both vertically arranged and opposite to the second opening. The top of the first baffle 16 is higher than the top of the second baffle 17. The first baffle 16 and the second baffle 17 can be driven by the second power device in the working box to move up and down between the highest position and the lowest position. Figure 2 As shown, when the first baffle plate 16 and the second baffle plate 17 are both in the highest position and the rotating plate is in the vertical state, the rotating plate is clamped between the first baffle plate 16 and the second baffle plate 17, so that the rotating plate can no longer rotate, and the first baffle plate 16 is close to each group of first loading plates. When the first baffle plate 16 and the second baffle plate 17 are in the lowest position and the rotating plate is in the horizontal position, the first baffle plate 16 and the second baffle plate 17 are both located in the working box; during the process of the rotating plate rotating from the horizontal state to the vertical state driven by the first baffle plate 16, the second baffle plate 17 is always located in the working box, and when the rotating plate rotates from the horizontal state to the vertical state driven by the first baffle plate 16, the second baffle plate 17 moves to the outside of the working box (at this time, the first baffle plate 16 and the second baffle plate 17 have not yet reached the highest position), so that the second baffle plate 17 will not affect the rotation of the rotating plate, and can keep the rotating plate in the vertical state after the rotating plate rotates to the vertical state;

[0058] A plurality of pairs of rotating rods 8, each pair of rotating rods 8 is respectively arranged on the rotating plate 7 and the moving plate 6. For any pair of rotating rods 8, one rotating rod 8 is respectively arranged on the rotating plate 7 and the moving plate 6, and the pair of rotating rods 8 are arranged opposite to each other. Each rotating rod 8 on the moving plate 6 can rotate under the drive of the third power device. Each rotating rod 8 on the rotating plate 7 is respectively rotatably connected to the rotating plate 7 (through a bearing). Each pair of rotating rods 8 corresponds to a group of first loading plates 2 and a group of second loading plates 5 respectively. One end of each rotating rod 8 is provided with a receiving groove 801 for receiving an aircraft test piece 12. The shape of the receiving groove 801 is adapted to the aircraft test piece. For example, if the aircraft test piece is cylindrical, the receiving groove 801 is circular. If the aircraft test piece is rectangular, the receiving groove 801 is square.

[0059] A screw rod 9 is arranged along the length direction of the working box 1;

[0060] A nut 10 is arranged on the screw rod 9, and one end of the moving plate 6 is fixedly connected to the nut 10;

[0061] A gear 11 is fixed to one end of the screw rod 9 and meshes with the rack 15;

[0062] When the screw rod 9 is driven by the fourth power device to rotate, the cover 3 moves between the third position and the fourth position along the width direction of the working box 1, and the moving plate 6 moves between the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position) and the sixth position ( Figure 1 When the movable plate 6 is in the seventh position, the cover 3 is in the eighth position; that is, when the cover 3 is in the third position, the movable plate 6 is in the fifth position, when the cover 3 is in the fourth position, the movable plate 6 is in the sixth position, and when the movable plate 6 is in the seventh position, the cover 3 is in the eighth position;

[0063] like Figure 1 As shown, when the movable plate 6 is in the fifth position ( Figure 1 When the moving plate 6 indicated by the solid line is in the fifth position), the cover 3 seals the first opening, the rotating plate 7 is located between the cover 3 and each group of first material loading plates 2 and is in a horizontal state, and the top of the rotating rod 8 thereon is not higher than the bottom of the moving plate 6 (so that the movement of the moving plate 6 is not affected), and the rotating rod 8 on the moving plate 6 can push the aircraft test piece 12 thereon to the corresponding group of first material loading plates 2; when the rotating rod 8 on the moving plate 6 pushes the aircraft test piece 12 thereon to the corresponding group of first material loading plates 2, the aircraft test piece 12 is supported by the group of first material loading plates 2;

[0064] When the movable plate 6 is in the sixth position ( Figure 1 When the movable plate 6 indicated by the dotted line is in the sixth position, the lifting plate 4 is in the second position, the rotating plate 7 is in the vertical state, and each group of second loading plates 5 has an aircraft test piece 12 placed therein, the first opening is fully opened, the lifting plate 4 is located between the movable plate 6 and the rotating plate 7, and both ends of each aircraft test piece 12 are respectively separated from the corresponding pair of rotating rods 8 by a preset distance L, L being 1-2 cm. In actual use, the preset distance L can be a little larger, but it does not need to be too large, so that when the aircraft test piece 12 is placed on a group of second loading plates 5, the distance between the pair of rotating rods 8 is sufficient and will not interfere with the placement of the aircraft test piece 12;

[0065] like Figure 2 As shown, when the movable plate 6 is in the seventh position, the cover 3 is in the eighth position, the lifting plate 4 is in the second position, the rotating plate 7 is in the vertical state, and each group of second loading plates 5 has an aircraft test piece 12 placed therein, both ends of each aircraft test piece 12 are respectively located in the receiving groove 801 of the pair of rotating rods 8 corresponding thereto, and the cover 3 is separated from the first opening by a preset distance; when the movable plate 6 is in the sixth position and the rotating plate 7 is in the vertical state, the distance between the pair of rotating rods 8 is relatively large, so that the aircraft test piece 12 is easily placed on a group of second loading plates 5, and then the movable plate 6 is moved from the sixth position ( Figure 1 The movable plate 6 indicated by the dotted line is in the sixth position) moves toward the rotating plate 7 to the seventh position, and the distance between the pair of rotating rods 8 becomes smaller, so that the aircraft test piece 12 can be clamped.

[0066] When the lifting plate 4 is in the second position, the rotating plate 7 is in a vertical state, and each group of second loading plates 5 has an aircraft test piece 12 placed therein, one end of the aircraft test piece 12 is located in the receiving groove 801 of the rotating rod 8 on the corresponding moving plate 6, and the other end is placed in at least one first loading plate 2 located inside the corresponding group of first loading plates 2 (such as the innermost first loading plate 2), the moving plate 6 is in contact with the lifting plate 4 or separated by a preset distance, so that in the initial process of the moving plate 6 pushing the aircraft test piece 12 forward, the lifting plate 4 will not interfere with the movement of the moving plate 6, and thereafter, the lifting plate 4 needs to be lowered to the first position so that the moving plate 6 can continue to push the aircraft test piece 12 forward to a group of first loading plates 2. Figure 2 As shown, one end of the aircraft test piece 12 can be made to extend out of the lifting plate 4 to a longer length, so that in the initial process of the movable plate 6 pushing the aircraft test piece 12 forward, the movable plate 6 and the lifting plate 4 are always separated by a preset distance, and the lifting plate 4 will not interfere with the movement of the movable plate 6. When the other end of the aircraft test piece 12 is placed on the innermost first loading plate 2 in a group of first loading plates 2 corresponding thereto, the aircraft test piece 12 does not need to be supported by the lifting plate 4, and the lifting plate 4 can be lowered into the working box 1.

[0067] The method for using the aircraft vibration simulation device provided in this scheme comprises the following steps:

[0068] Step 1: rotate the rotating plate 7 to the horizontal position, the movable plate 6 is in the fifth position, and the cover 3 is in the third position. Then, the fourth power device drives the screw 9 to rotate, so that the movable plate 6 moves to the sixth position, and the cover 3 moves to the fourth position;

[0069] Step 2: The second power device drives the first baffle 16 and the second baffle 17 upward, and the first baffle 16 pushes the rotating plate 7 to rotate to a vertical position, and the first baffle 16 and the second baffle 17 clamp the rotating plate, and the first driving device drives the lifting plate 4 to move to the second position, and then puts an aircraft test piece 12 on each group of second loading plates 5;

[0070] Step 3: The fourth power device drives the screw 9 to rotate in the opposite direction, and the movable plate 6 pushes each aircraft test piece 12 to move toward the rotating plate 7. After the two ends of the aircraft test piece 12 are respectively located in the pair of accommodating grooves 801 corresponding thereto, the lifting plate 4 is lowered to the first position (after the lifting plate 4 is lowered, the rotation of the aircraft test piece will not be affected). Then, the third power device drives each rotating rod 8 on the movable plate 6 to rotate, and the aircraft test piece and the rotating rod on the rotating plate rotate synchronously.

[0071] Step 4: Perform vibration simulation on the aircraft test piece;

[0072] Step 5: After the vibration simulation is completed, the lifting plate 4 is raised to the second position to continue to support the aircraft test piece. Then, the second power device drives the first baffle 16 and the second baffle 17 to descend to the lowest position, and the rotating plate is no longer clamped by the first baffle 16 and the second baffle 17. Then, the fourth power device drives the screw to rotate until the moving plate moves to the sixth position ( Figure 1The movable plate 6 indicated by the dotted line is in the sixth position), and then the operator moves each aircraft test piece toward the movable plate 6 (during this process, the aircraft test piece is always supported by the second loading plate 5). After the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position, and then the fourth power device drives the screw rod 9 to continue to rotate in the opposite direction, and the movable plate 6 pushes each aircraft test piece 12 to move toward a group of first loading plates 2 corresponding thereto. When one end of the aircraft test piece 12 is located in the receiving groove 801 of the rotating rod 8 on the movable plate 6 corresponding thereto, and the other end is placed in at least one first loading plate 2 located on the inner side of the group of first loading plates 2 corresponding thereto, the first driving device drives the lifting plate 4 to move to the first position, and then the fourth power device drives the screw rod 9 to continue to rotate in the opposite direction until the movable plate 6 is in the fifth position, the cover 3 is in the third position, and each aircraft test piece 12 is placed on a group of first loading plates 2 corresponding thereto, respectively. Then, each aircraft test piece 12 is removed, and the above steps are repeated. In actual use, it is not necessary to remove it. When the next aircraft test piece 12 is placed on a corresponding set of first material carrier plates 2, the previous aircraft test piece 12 is pushed forward and then placed at the other end of the working box 1 (such as Figure 1 As shown, the front end of the working box 1) can be collected.

[0073] The device provided by the present invention has a simple structure, and after the simulation is finished, it is only necessary to move the plate to continue to push the aircraft test piece forward until it is placed on each group of first material loading plates, thereby reducing production costs.

[0074] The present invention drives the screw rod to rotate through the fourth power device, so that the movement of the movable plate and the movement of the cover can be synchronized, so that the operator does not need to move the cover manually, and the degree of automation is high.

[0075] In another embodiment, in the aircraft vibration simulation device, there are multiple groups of the first material carrier plates 2, so that vibration simulation can be performed on multiple aircraft test pieces 12 at one time.

[0076] In another embodiment, in the aircraft vibration simulation device, as Figure 4 As shown, two L-shaped steps are arranged at intervals on the top of the working box 1 along the length direction of the working box 1, and the two steps extend along the width direction of the working box 1, and the first opening is located between the two steps; when the cover 3 covers the first opening, the cover 3 is placed on the horizontal parts of the two steps, and the two sides of the cover 3 are in contact with the vertical parts of the two steps, and the cover 3 is guided by the vertical parts of the two steps when moving.

[0077] In another embodiment, in the aircraft vibration simulation device, a support platform 13 is provided on one side of the working box 1, and when the cover 3 is in the fourth position, the support platform 13 supports the cover 3, and after the cover 3 is moved out, it is supported by the support platform 13.

[0078] In another embodiment, in the aircraft vibration simulation device, each rotating rod 8 on the movable plate 6 is provided with a sprocket, and each sprocket is connected by a chain. One rotating rod 8 among the rotating rods 8 on the movable plate 6 rotates under the drive of the third power device, and the third power device drives the rotating rod 8 connected thereto to rotate, so that all the rotating rods 8 on the movable plate 6 can rotate synchronously.

[0079] In another embodiment, in the aircraft vibration simulation device, a notch 701 is provided on the rotating plate 7, and by providing the notch 701, the guide rod 14 does not affect the rotation of the rotating plate 7;

[0080] The aircraft vibration simulation device also includes:

[0081] A guide rod 14 passes through the notch 701, and its two ends are respectively fixedly connected to the top of the working box 1, and the guide rod 14 can play a guiding role in the movement of the moving plate 6. In another embodiment, in the aircraft vibration simulation device, a rotating shaft is provided on the rotating plate 7, and the rotating shaft is arranged along the width direction of the working box 1. One end of the rotating shaft rotates under the drive of the second power device, so that the rotating plate 7 can rotate from a vertical state to a horizontal state or from a horizontal state to a vertical state in the direction of each group of first loading plates 2.

[0082] The method for using the aircraft vibration simulation device comprises the following steps:

[0083] Step 1: Rotate the rotating plate 7 to a horizontal position (eg Figure 1 The state shown is a horizontal state), the movable plate 6 is in the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position, and the cover 3 is in the third position ( Figure 1 The middle cover 3 is in the third position, at which time the cover 3 seals the first opening), and then the fourth power device drives the screw 9 to rotate, so that the movable plate 6 moves to the sixth position ( Figure 1 The movable plate 6 indicated by the dotted line is in the sixth position), and the cover 3 moves to the fourth position, at which time the first opening is opened;

[0084] Step 2: The second power device drives the first baffle 16 and the second baffle 17 upward, and the first baffle 16 pushes the rotating plate 7 to rotate to a vertical position (such as Figure 2The state shown is a vertical state), and the rotating plate is clamped by the first baffle 16 and the second baffle 17, and the first driving device drives the lifting plate 4 to move to the second position, and then an aircraft test piece 12 is placed on each group of second loading plates 5;

[0085] Step 3: The fourth power device drives the screw 9 to rotate in the opposite direction, and the moving plate 6 pushes each aircraft test piece 12 to move toward the rotating plate 7. Figure 2 As shown, after the two ends of the aircraft test piece 12 are respectively located in the pair of accommodating grooves 801 corresponding thereto, the lifting plate 4 is lowered to the first position (after the lifting plate 4 is lowered, the rotation of the aircraft test piece will not be affected), and then the rotating rods 8 on the moving plate 6 are driven to rotate by the third power device, so that the aircraft test piece and the rotating rods on the rotating plate rotate synchronously;

[0086] Step 4: Perform vibration simulation on the aircraft test piece;

[0087] Step 5, raise the lifting plate 4 to the second position to continue supporting the aircraft test piece, then the second power device drives the first baffle plate 16 and the second baffle plate 17 to descend to the lowest position, then the fourth power device drives the screw rod to rotate until the movable plate moves to the sixth position, then the operator moves each aircraft test piece toward the movable plate, after the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position, then the fourth power device drives the screw rod 9 to continue to rotate in the opposite direction, the movable plate 6 pushes each aircraft test piece 12 to move toward a corresponding group of first loading plates 2, when one end of the aircraft test piece 12 is located in the receiving groove 801 of the rotating rod 8 on the corresponding movable plate 6, and the other end is placed in at least one first loading plate 2 located on the inner side of the corresponding group of first loading plates 2, the first driving device drives the lifting plate 4 to move to the first position (such as Figure 3 As shown, the lifting plate 4 is in the first position), and then the fourth power device drives the screw 9 to continue to rotate in the reverse direction until the moving plate 6 is in or returns to the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position), the cover 3 is in or returns to the third position ( Figure 1 The middle cover 3 is in the third position, at which time the cover 3 seals the first opening), each aircraft test piece 12 is placed on a corresponding set of first material loading plates 2, then each aircraft test piece 12 is removed, and the above steps are repeated. In actual use, it is not necessary to remove it, and when the next aircraft test piece 12 is placed on the corresponding set of first material loading plates 2, the previous aircraft test piece 12 is pushed forward, and then at the other end of the working box 1 (such as Figure 1 As shown, the front end of the working box 1) can be collected.

[0088] Example 1

[0089] The present invention is specifically implemented using an aircraft shaft as an aircraft test piece.

[0090] like Figures 1 to 3 As shown, the present invention provides an aircraft vibration simulation device, comprising:

[0091] The working box 1 is a rectangular parallelepiped with a hollow interior, and one end of the top of the working box 1 (such as Figure 1 As shown, the rear end of the top of the working box 1 is provided with a first opening, and the other end (as shown Figure 1 As shown, the front end of the top of the working box 1 is provided with at least one set of first loading plates 2 and a second opening. The first loading plates 2 are arc-shaped with the opening upward, which is adapted to the aircraft shaft. Each set of first loading plates 2 is formed along the length direction of the working box 1 (such as Figure 1 The first opening is provided with a cover 3, and a rack 15 is provided on one side of the top of the cover 3 along the width direction of the working box 1. Figure 1 As shown, the rack 15 is located at the rear side of the top of the cover 3, so as not to affect the movement of the moving plate 6;

[0092] The lifting plate 4 is driven by the first power device to be in the first position ( Figure 1 The lifting plate 4 indicated by the dotted line is in the first position. Figure 3 As shown, the lifting plate 4 is in the first position) and moves up and down between the second position, and at least one group of second loading plates 5 is arranged on the top of the lifting plate 4, and the second loading plates 5 are arc-shaped with the opening upward, which are adapted to the aircraft shaft, and each group of second loading plates 5 is composed of a plurality of second loading plates 5 arranged at intervals along the length direction of the working box 1, and each group of second loading plates 5 can independently support an aircraft shaft 12; when the lifting plate 4 is in the first position, the lifting plate 4 is located in the working box 1, and is opposite to the first opening, and is located below the first opening, and when the lifting plate 4 is in the second position, the lifting plate 4 is located outside the working box 1, and is located above the first opening;

[0093] A movable plate 6, which is arranged vertically;

[0094] The rotating plate 7 is arranged on the working box 1 and is rotatably connected to the top of the working box, and can be rotated from a vertical state to a horizontal state (such as Figure 1 The state shown is a horizontal state, in which the rotating rod 8 on the rotating plate 7 is vertical) or rotated from a horizontal state to a vertical state (such as Figure 2 The state shown is a vertical state, in which the rotating rod 8 on the rotating plate 7 is horizontal, the same as the rotating rod 8 on the moving plate 6). When vibration simulation is required, the rotating plate 7 is in a vertical state, and can be in a horizontal state at other times;

[0095] The first baffle 16 and the second baffle 17 are both vertically arranged and opposite to the second opening. The height of the top of the first baffle 16 is higher than the height of the top of the second baffle 17. The first baffle 16 and the second baffle 17 can be driven by the second power device in the working box to move up and down between the highest position and the lowest position. When the first baffle 16 and the second baffle 17 are both in the highest position and the rotating plate is in a vertical state, the rotating plate is clamped between the first baffle 16 and the second baffle 17, so that the rotating plate can no longer rotate, and the first baffle 16 is close to each group of first loading plates. When the first baffle 16 and the second baffle 17 are at the lowest position and the rotating plate is in the horizontal position, the first baffle 16 and the second baffle 17 are both located in the working box; during the process of the rotating plate rotating from the horizontal state to the vertical state under the push of the first baffle 16, the second baffle 17 is always located in the working box, and when the rotating plate rotates from the horizontal state to the vertical state under the push of the first baffle 16, the second baffle 17 moves to the outside of the working box, so that the second baffle 17 will not affect the rotation of the rotating plate, and can keep the rotating plate in the vertical state after the rotating plate rotates to the vertical state;

[0096] A plurality of pairs of rotating rods 8, each pair of rotating rods 8 is respectively arranged on the rotating plate 7 and the moving plate 6, for any pair of rotating rods 8, one rotating rod 8 is respectively arranged on the rotating plate 7 and the moving plate 6, and a pair of rotating rods 8 are arranged opposite to each other, each rotating rod 8 on the moving plate 6 can rotate under the drive of the third power device, each rotating rod 8 on the rotating plate 7 is respectively rotatably connected to the rotating plate 7 (through a bearing), and each pair of rotating rods 8 corresponds to a group of first loading plates 2 and a group of second loading plates 5; one end of each rotating rod 8 is provided with a receiving groove 801 for receiving the aircraft shaft 12;

[0097] A screw rod 9 is arranged along the length direction of the working box 1;

[0098] A nut 10 is arranged on the screw rod 9, and one end of the moving plate 6 is fixedly connected to the nut 10;

[0099] A gear 11 is fixed to one end of the screw rod 9 and meshes with the rack 15;

[0100] When the screw rod 9 is driven by the fourth power device to rotate, the cover 3 moves between the third position and the fourth position along the width direction of the working box 1, and the moving plate 6 moves between the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position) and the sixth position ( Figure 1When the movable plate 6 is in the seventh position, the cover 3 is in the eighth position; that is, when the cover 3 is in the third position, the movable plate 6 is in the fifth position, when the cover 3 is in the fourth position, the movable plate 6 is in the sixth position, and when the movable plate 6 is in the seventh position, the cover 3 is in the eighth position;

[0101] like Figure 1 As shown, when the movable plate 6 is in the fifth position ( Figure 1 When the moving plate 6 indicated by the solid line is in the fifth position), the cover 3 seals the first opening, the rotating plate 7 is located between the cover 3 and each group of first loading plates 2 and is in a horizontal state, and the top of the rotating rod 8 thereon is not higher than the bottom of the moving plate 6 (so that the movement of the moving plate 6 is not affected), and the rotating rod 8 on the moving plate 6 can push the aircraft shaft 12 thereon to the corresponding group of first loading plates 2; when the rotating rod 8 on the moving plate 6 pushes the aircraft shaft 12 thereon to the corresponding group of first loading plates 2, the aircraft shaft 12 is supported by the group of first loading plates 2;

[0102] When the movable plate 6 is in the sixth position ( Figure 1 When the movable plate 6 indicated by the dotted line is in the sixth position, the lifting plate 4 is in the second position, the rotating plate 7 is in a vertical state, and an aircraft shaft 12 is placed in each group of second loading plates 5, the first opening is fully opened, the lifting plate 4 is located between the movable plate 6 and the rotating plate 7, and the two ends of each aircraft shaft 12 are respectively separated from the corresponding pair of rotating rods 8 by a preset distance, so that when the aircraft shaft 12 is placed on a group of second loading plates 5, the distance between the pair of rotating rods 8 is sufficient and will not interfere with the placement of the aircraft shaft 12;

[0103] like Figure 2 As shown, when the movable plate 6 is in the seventh position, the cover 3 is in the eighth position, the lifting plate 4 is in the second position, the rotating plate 7 is in the vertical state, and each group of second loading plates 5 is provided with an aircraft shaft 12, both ends of each aircraft shaft 12 are respectively located in the receiving groove 801 of the pair of rotating rods 8 corresponding thereto, and the cover 3 is separated from the first opening by a preset distance; when the movable plate 6 is in the sixth position and the rotating plate 7 is in the vertical state, the distance between the pair of rotating rods 8 is large, so that the aircraft shaft 12 is easily placed on a group of second loading plates 5, and then the movable plate 6 is moved from the sixth position ( Figure 1 The movable plate 6 indicated by the dotted line is in the sixth position) moves toward the rotating plate 7 to the seventh position, and the distance between the pair of rotating rods 8 becomes smaller, so that the aircraft shaft 12 can be clamped.

[0104] When the lifting plate 4 is in the second position, the rotating plate 7 is in a vertical state, and each group of second loading plates 5 is provided with an aircraft shaft 12, one end of the aircraft shaft 12 is located in the receiving groove 801 of the rotating rod 8 on the corresponding moving plate 6, and the other end is placed in at least one first loading plate 2 located inside the corresponding group of first loading plates 2 (such as the innermost first loading plate 2), the moving plate 6 is in contact with the lifting plate 4 or separated by a preset distance, so that in the initial process of the moving plate 6 pushing the aircraft shaft 12 forward, the lifting plate 4 will not interfere with the movement of the moving plate 6. After that, the lifting plate 4 needs to be lowered to the first position so that the moving plate 6 can continue to push the aircraft shaft 12 forward to a group of first loading plates 2. Figure 2 As shown, one end of the aircraft shaft 12 can be made to extend out of the lifting plate 4 for a longer length, so that in the initial process of the moving plate 6 pushing the aircraft shaft 12 forward, the moving plate 6 and the lifting plate 4 are always separated by a preset distance, and the lifting plate 4 will not interfere with the movement of the moving plate 6. When the other end of the aircraft shaft 12 is placed on the innermost first loading plate 2 in a group of first loading plates 2 corresponding to it, the aircraft shaft 12 does not need to be supported by the lifting plate 4, and the lifting plate 4 can be lowered into the working box 1.

[0105] The method for using the aircraft vibration simulation device provided in this scheme comprises the following steps:

[0106] Step 1: rotate the rotating plate 7 to the horizontal position, the movable plate 6 is in the fifth position, and the cover 3 is in the third position. Then, the fourth power device drives the screw 9 to rotate, so that the movable plate 6 moves to the sixth position, and the cover 3 moves to the fourth position;

[0107] Step 2: The second power device drives the first baffle 16 and the second baffle 17 upward, and the first baffle 16 pushes the rotating plate 7 to rotate to a vertical position, and the first baffle 16 and the second baffle 17 clamp the rotating plate, and the first driving device drives the lifting plate 4 to move to the second position, and then puts an aircraft shaft 12 on each group of second loading plates 5;

[0108] Step 3: The fourth power device drives the screw 9 to rotate in the opposite direction, and the movable plate 6 pushes each aircraft shaft 12 to move toward the rotating plate 7. After the two ends of the aircraft shaft 12 are respectively located in the pair of accommodating grooves 801 corresponding thereto, the lifting plate 4 is lowered to the first position (after the lifting plate 4 is lowered, it will not affect the rotation of the aircraft test piece). Then, the third power device drives each rotating rod 8 on the movable plate 6 to rotate, and the aircraft test piece and the rotating rods on the rotating plate rotate synchronously.

[0109] Step 4: The vertical low-frequency exciter impacts the aircraft shaft 12 according to the preset amplitude and frequency, and the aircraft shaft 12 transmits the impact to the simulated shaft system platform through the simulated shock absorber to realize the vertical impact vibration simulation of the three-point simulated shaft system of the rotating machinery; the horizontal low-frequency exciter impacts the simulated shaft system platform according to the preset amplitude and frequency to realize the horizontal impact simulation. During this process, the impact vibration monitoring system monitors the impact force and frequency, and monitors the vibration of the simulated casing and the three-point simulated shaft system;

[0110] Step 5. After the vibration simulation is completed, the lifting plate 4 is raised to the second position to continue supporting the aircraft test piece. Then, the second power device drives the first baffle 16 and the second baffle 17 to descend to the lowest position, and the rotating plate is no longer clamped by the first baffle 16 and the second baffle 17. Then, the fourth power device drives the screw rod to rotate until the moving plate moves to the sixth position. Then, the operator moves each aircraft test piece toward the moving plate. After the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position. Then, the fourth power device drives the screw rod 9 to continue to rotate in the opposite direction, and the moving plate 6 pushes each aircraft shaft 12 Move toward the corresponding group of first loading plates 2, and when one end of the aircraft shaft 12 is located in the receiving groove 801 of the rotating rod 8 on the corresponding moving plate 6, and the other end is placed in at least one first loading plate 2 located on the inner side of the corresponding group of first loading plates 2, the first driving device drives the lifting plate 4 to move to the first position, and then the fourth power device drives the screw 9 to continue to rotate in the opposite direction until the moving plate 6 is in the fifth position and the cover 3 is in the third position. Each aircraft shaft 12 is placed on the corresponding group of first loading plates 2, and then each aircraft shaft 12 is removed and the above steps are repeated. In actual use, it is not necessary to remove it. When the next aircraft shaft 12 is placed on the corresponding group of first loading plates 2, the previous aircraft shaft 12 is pushed forward, and then at the other end of the working box 1 (such as Figure 1 As shown, the front end of the working box 1) can be collected.

[0111] In another embodiment, in the aircraft vibration simulation device, there are multiple groups of the first material loading plates 2, so that vibration simulation can be performed on multiple aircraft shafts 12 at one time.

[0112] In another embodiment, in the aircraft vibration simulation device, as Figure 4 As shown, two L-shaped steps are arranged at intervals on the top of the working box 1 along the length direction of the working box 1, and the two steps extend along the width direction of the working box 1, and the first opening is located between the two steps; when the cover 3 covers the first opening, the cover 3 is placed on the horizontal parts of the two steps, and the two sides of the cover 3 are in contact with the vertical parts of the two steps, and the cover 3 is guided by the vertical parts of the two steps when moving.

[0113] In another embodiment, in the aircraft vibration simulation device, a support platform 13 is provided on one side of the working box 1, and when the cover 3 is in the fourth position, the support platform 13 supports the cover 3, and after the cover 3 is moved out, it is supported by the support platform 13.

[0114] In another embodiment, in the aircraft vibration simulation device, each rotating rod 8 on the movable plate 6 is provided with a sprocket, and each sprocket is connected by a chain. One rotating rod 8 among the rotating rods 8 on the movable plate 6 rotates under the drive of the third power device, and the third power device drives the rotating rod 8 connected thereto to rotate, so that all the rotating rods 8 on the movable plate 6 can rotate synchronously.

[0115] In another embodiment, in the aircraft vibration simulation device, a notch 701 is provided on the rotating plate 7, and by providing the notch 701, the guide rod 14 does not affect the rotation of the rotating plate 7;

[0116] The aircraft vibration simulation device also includes:

[0117] A guide rod 14 passes through the notch 701 , and both ends of the guide rod 14 are respectively fixedly connected to the top of the working box 1 . The guide rod 14 can play a guiding role during the movement of the moving plate 6 .

[0118] In another embodiment, in the aircraft vibration simulation device, a rotating shaft is provided on the rotating plate 7, and the rotating shaft is arranged along the width direction of the working box 1. One end of the rotating shaft rotates under the drive of the second power device, so that the rotating plate 7 can rotate from a vertical state toward the direction of each group of first loading plates 2 to a horizontal state or from a horizontal state to a vertical state.

[0119] The method for using the aircraft vibration simulation device comprises the following steps:

[0120] Step 1: Rotate the rotating plate 7 to a horizontal position (eg Figure 1 The state shown is a horizontal state), the movable plate 6 is in the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position, and the cover 3 is in the third position ( Figure 1 The middle cover 3 is in the third position, at which time the cover 3 seals the first opening), and then the fourth power device drives the screw 9 to rotate, so that the movable plate 6 moves to the sixth position ( Figure 1 The movable plate 6 indicated by the dotted line is in the sixth position), and the cover 3 moves to the fourth position, at which time the first opening is opened;

[0121] Step 2: The second power device drives the first baffle 16 and the second baffle 17 upward, and the first baffle 16 pushes the rotating plate 7 to rotate to a vertical position (such as Figure 2The state shown is a vertical state), and the rotating plate is clamped by the first baffle 16 and the second baffle 17, and the first driving device drives the lifting plate 4 to move to the second position, and then an aircraft shaft 12 is placed on each group of second loading plates 5;

[0122] Step 3: The fourth power device drives the screw 9 to rotate in the opposite direction, and the moving plate 6 pushes each aircraft shaft 12 to move toward the rotating plate 7. Figure 2 As shown, after the two ends of the aircraft shaft 12 are respectively located in the pair of receiving grooves 801 corresponding thereto, the lifting plate 4 is lowered to the first position (after the lifting plate 4 is lowered, the rotation of the aircraft test piece will not be affected), and then the rotating rods 8 on the moving plate 6 are driven to rotate by the third power device, and the aircraft test piece and the rotating rods on the rotating plate rotate synchronously;

[0123] Step 4: The vertical low-frequency exciter impacts the aircraft shaft 12 according to the preset amplitude and frequency, and the aircraft shaft 12 transmits the impact to the simulated shaft system platform through the simulated shock absorber to realize the vertical impact vibration simulation of the three-point simulated shaft system of the rotating machinery; the horizontal low-frequency exciter impacts the simulated shaft system platform according to the preset amplitude and frequency to realize the horizontal impact simulation. During this process, the impact vibration monitoring system monitors the impact force and frequency, and monitors the vibration of the simulated casing and the three-point simulated shaft system;

[0124] Step 5. After the vibration simulation is completed, the lifting plate 4 is raised to the second position to continue supporting the aircraft test piece. Then, the second power device drives the first baffle 16 and the second baffle 17 to descend to the lowest position, and the rotating plate is no longer clamped by the first baffle 16 and the second baffle 17. Then the fourth power device drives the screw rod to rotate until the movable plate moves to the sixth position. Then, the operator moves each aircraft test piece toward the movable plate. After the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position. Then, the fourth power device drives the screw rod 9 to continue to rotate in the opposite direction. The movable plate 6 pushes each aircraft shaft 12 to move toward a corresponding group of first loading plates 2. When one end of the aircraft shaft 12 is located in the receiving groove 801 of the rotating rod 8 on the corresponding movable plate 6, and the other end is placed in at least one first loading plate 2 located on the inner side of the corresponding group of first loading plates 2, the first driving device drives the lifting plate 4 to move to the first position (such as Figure 3 As shown, the lifting plate 4 is in the first position), and then the fourth power device drives the screw 9 to continue to rotate in the reverse direction until the moving plate 6 is in or returns to the fifth position ( Figure 1 The moving plate 6 indicated by the solid line is in the fifth position), the cover 3 is in or returns to the third position ( Figure 1The middle cover 3 is in the third position, at which time the cover 3 seals the first opening), each aircraft shaft 12 is placed on a corresponding set of first material loading plates 2, then each aircraft shaft 12 is removed, and the above steps are repeated. In actual use, it is not necessary to remove it, and when the next aircraft shaft 12 is placed on the corresponding set of first material loading plates 2, the previous aircraft shaft 12 is pushed forward, and then at the other end of the working box 1 (such as Figure 1 As shown, the front end of the working box 1) can be collected.

[0125] Although the embodiments of the present invention have been disclosed as above, they are not limited to the applications listed in the specification and the implementation modes, and they can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily implemented. Therefore, without departing from the general concept defined by the claims and the scope of equivalents, the present invention is not limited to the specific details and the illustrations shown and described herein.

Claims

1. An aircraft vibration simulation device, characterized in that: include: The working box is in the shape of a rectangular parallelepiped with a hollow interior, a first opening is arranged at one end of the top of the working box, and at least one set of first material loading plates and a second opening is arranged at the other end, the shape of the first material loading plates is adapted to the shape of the aircraft test piece, each set of first material loading plates is composed of a plurality of first material loading plates arranged at intervals along the length direction of the working box, a cover is arranged corresponding to the first opening, and a rack is arranged on one side of the top of the cover along the width direction of the working box; a lifting plate, which moves up and down between a first position and a second position under the drive of a first power device, at least one group of second loading plates is arranged on the top of the lifting plate, the shape of the second loading plates is adapted to the shape of the aircraft test piece, and each group of second loading plates is composed of a plurality of second loading plates arranged at intervals along the length direction of the working box; when the lifting plate is in the first position, the lifting plate is located in the working box and below the first opening; a movable plate, which is arranged vertically; A rotating plate is arranged on the working box and is rotatably connected to the top of the working box, and can be rotated from a vertical state to a horizontal state toward the direction where each group of first material loading plates are located, or from a horizontal state to a vertical state; The first baffle and the second baffle are both vertically arranged and opposite to the second opening, the height of the top of the first baffle is higher than the height of the top of the second baffle, and the first baffle and the second baffle can be driven by the second power device located in the working box to move up and down between the highest position and the lowest position; when the first baffle and the second baffle are both in the highest position and the rotating plate is in the vertical state, the rotating plate is clamped between the first baffle and the second baffle, and the first baffle is close to each group of first loading plates; when the first baffle and the second baffle are in the lowest position and the rotating plate is in the horizontal position, the first baffle and the second baffle are both located in the working box; during the process of the rotating plate rotating from the horizontal state to the vertical state under the push of the first baffle, the second baffle is always located in the working box, and when the rotating plate rotates from the horizontal state to the vertical state under the push of the first baffle, the second baffle moves to the outside of the working box; A plurality of pairs of rotating rods, each pair of rotating rods is respectively arranged on the rotating plate and the moving plate, each rotating rod on the moving plate can rotate under the drive of the third power device, each rotating rod on the rotating plate is respectively rotatably connected to the rotating plate, each pair of rotating rods is respectively corresponding to a group of first material loading plates and a group of second material loading plates; one end of each rotating rod is provided with a receiving groove for receiving the aircraft test piece; A screw rod is arranged along the length direction of the working box; A nut is arranged on the screw rod, and one end of the moving plate is fixedly connected to the nut; A gear, which is fixed to one end of the lead screw and meshes with the rack; When the screw rod rotates under the drive of the fourth power device, the cover moves between the third position and the fourth position along the width direction of the working box, and the moving plate moves between the fifth position and the sixth position along the length direction of the working box and can stay at the seventh position. When the moving plate is at the seventh position, the cover is at the eighth position. When the movable plate is in the fifth position, the cover seals the first opening, the rotating plate is located between the cover and each group of first material loading plates and is in a horizontal state, and the height of the top of the rotating rod on the rotating plate is not higher than the height of the bottom of the movable plate, and the rotating rod on the movable plate can push the aircraft test piece on the movable plate to the corresponding group of first material loading plates; When the movable plate is in the sixth position, the lifting plate is in the second position, the rotating plate is in the vertical state, and one aircraft test piece is placed in each group of second loading plates, the cover opens the first opening, the lifting plate is located between the movable plate and the rotating plate, and both ends of each aircraft test piece are respectively separated from the corresponding pair of rotating rods by a preset distance; When the movable plate is in the seventh position, the cover is in the eighth position, the lifting plate is in the second position, the rotating plate is in the vertical state, and one aircraft test piece is placed in each group of second loading plates, both ends of each aircraft test piece are respectively located in a pair of accommodating grooves corresponding thereto, and the cover is separated from the first opening by a preset distance; When the lifting plate is in the second position, the rotating plate is in a vertical state, and each group of second loading plates has an aircraft test piece placed therein, one end of the aircraft test piece is located in the receiving groove of the rotating rod on the corresponding moving plate, and the other end is placed in at least one first loading plate located on the inner side of a group of first loading plates corresponding thereto, the moving plate is in contact with the lifting plate or is separated by a preset distance.

2. The aircraft vibration simulation device according to claim 1, characterized in that: There are multiple groups of the first material carrying plates.

3. The aircraft vibration simulation device according to claim 1, characterized in that: The top of the working box is provided with two L-shaped steps spaced apart along the length direction of the working box, both steps extend along the width direction of the working box, and the first opening is located between the two steps; when the cover seals the first opening, the cover is placed on the horizontal parts of the two steps, and both sides of the cover are in contact with the vertical parts of the two steps.

4. The aircraft vibration simulation device according to claim 1, characterized in that: A support platform is provided on one side of the working box, and when the cover is in the fourth position, the support platform supports the cover.

5. The aircraft vibration simulation device according to claim 2, characterized in that: Each rotating rod on the moving plate is provided with a sprocket, and each sprocket is connected by a chain. One of the rotating rods on the moving plate rotates under the drive of the third power device.

6. The aircraft vibration simulation device according to claim 1, characterized in that: The rotating plate is provided with a notch; The aircraft vibration simulation device also includes: A guide rod passes through the notch, and both ends of the guide rod are respectively fixedly connected to the top of the working box.

7. The aircraft vibration simulation device according to claim 6, characterized in that: The rotating plate is provided with a rotating shaft, which is arranged along the width direction of the working box, and one end of the rotating shaft rotates under the driving of the second power device.

8. The method for using the aircraft vibration simulation device according to claim 1, characterized in that: The following steps are involved: Step 1: rotate the rotating plate to a horizontal position, the movable plate is in the fifth position, and the cover is in the third position; then the fourth power device drives the screw to rotate, so that the movable plate moves to the sixth position, and the cover moves to the fourth position; Step 2: The second power device drives the first baffle plate and the second baffle plate upward, and the first baffle plate is used to push the rotating plate to rotate to a vertical position, and the first baffle plate and the second baffle plate are used to clamp the rotating plate, and the first driving device drives the lifting plate to move to the second position, and then an aircraft test piece is placed on each group of second loading plates; Step 3: The fourth power device drives the screw rod to rotate in the opposite direction, and the movable plate pushes each aircraft test piece to move toward the rotating plate. After the two ends of the aircraft test piece are respectively located in a pair of accommodating grooves corresponding thereto, the lifting plate is lowered to the first position, and then the third power device drives each rotating rod on the movable plate to rotate, and the aircraft test piece and the rotating rod on the rotating plate rotate synchronously; Step 4: Perform vibration simulation on the aircraft test piece; Step 5, raise the lifting plate to the second position, then the second power device drives the first baffle and the second baffle to descend to the lowest position, then the fourth power device drives the screw rod to rotate until the movable plate moves to the sixth position, then the operator moves each aircraft test piece toward the movable plate, after the aircraft test piece is separated from the rotating rod on the rotating plate, the operator rotates the rotating plate to a horizontal position, then the fourth power device drives the screw rod to continue to rotate in the opposite direction, and the movable plate pushes each aircraft test piece to move toward a corresponding group of first loading plates, when one end of the aircraft test piece is located in the accommodating groove of the rotating rod on the corresponding movable plate, and the other end is placed in at least one first loading plate located on the inner side of the corresponding group of first loading plates, the first driving device drives the lifting plate to move to the first position, then the fourth power device drives the screw rod to continue to rotate in the opposite direction until the movable plate is in the fifth position, the cover is in the third position, each aircraft test piece is placed on a corresponding group of first loading plates, then each aircraft test piece is removed, and the above steps are repeated.

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