An aircraft carrier landing simulation test system

Abstract

The present application relates to a kind of aircraft carrier landing simulation test system, belong to aerospace technology field, solve the problem such as the insufficient precision of the existing technology in rope guide, it is difficult to simulate multiple position landing, and one of rope fixing unreliable etc..The present application includes simulation deck, rope, guide component and fixing component;Guide component is set in the central region of simulation deck;Guide component includes guide plate, and the guide plate has a plurality of via modules, and a plurality of via modules are adjacent to each other;Via module has the arc surface of lower convex, and the center of arc surface is provided with guide hole, and guide hole is used for the rope to pass through;Fixing component is used to fix the rope that is passed in guide hole.The present application improves the guide precision and position stability of rope when multiple position landing and the reliability of rope fixing.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to an aircraft carrier landing simulation test system. Background Technology

[0002] Existing aircraft carrier landing simulation test systems typically use fixed pulleys or vertical guides to guide the arresting cables. However, the cables are prone to deviation or jumping when passing through these guides, resulting in insufficient guidance accuracy and difficulty in accurately simulating the spatial attitude of the arresting cables during a real landing. Furthermore, existing simulation systems usually use only a single cable or a few cables, making it difficult to simulate arresting cable layouts at different landing positions and angles on the same simulated deck, limiting the flexibility and coverage of the tests. The lack of effective cable fixing and clamping mechanisms also makes the cables susceptible to loosening or displacement during simulation testing, affecting the accuracy and repeatability of the test results. Summary of the Invention

[0003] Based on the above analysis, the present invention aims to provide an aircraft carrier landing simulation test system to solve one of the technical problems in the prior art, such as insufficient rope guidance accuracy, difficulty in simulating multi-position carrier landing, and unreliable rope fixation.

[0004] This invention is achieved through the following technical solution: An aircraft carrier landing simulation test system includes a simulation deck, ropes, guidance components, and fixing components; The guide assembly is located in the central area of ​​the simulated deck; the guide assembly includes a guide plate, the guide plate has multiple through-hole modules, the multiple through-hole modules are adjacent to each other; the through-hole module has a downwardly convex arc-shaped surface, the center of the arc-shaped surface is provided with a guide hole, the guide hole is used for the rope to pass through; The fixing component is used to secure the rope passing through the guide hole.

[0005] Furthermore, the via modules are arranged in a straight line and uniformly disposed along the first direction and the second direction of the guide plate, respectively; wherein the first direction and the second direction are perpendicular to each other.

[0006] Furthermore, the number of via modules arranged along the first direction of the guide plate is an even number.

[0007] Furthermore, the fixing component includes a first fixing component and a second fixing component; the first fixing component and the second fixing component are respectively disposed at opposite ends of the guide plate.

[0008] Furthermore, the first fixing component includes a first telescopic motor and a first sliding plate, with the output end of the first telescopic motor connected to the first sliding plate; The second fixing component includes a second telescopic motor and a second sliding plate, with the output end of the second telescopic motor connected to the second sliding plate; The first telescopic motor and the second telescopic motor respectively drive the first sliding plate and the second sliding plate to run in opposite directions or towards each other along the first direction of the guide plate, so as to clamp or release the rope.

[0009] Furthermore, the upper surfaces of the first and second sliding plates are at the same horizontal height as the lowest point of the arcuate surface of the via module.

[0010] Furthermore, the sidewalls of the first and second sliding plates are respectively provided with a plurality of grooves and a plurality of protrusions, and the plurality of grooves and the plurality of protrusions are alternately arranged along the length direction of the sidewalls.

[0011] Furthermore, the grooves on the sidewalls of the first and second slide plates are positioned corresponding to the guide holes in the first direction of the guide plate.

[0012] Furthermore, a gravity ball is provided at the end of the rope, and the diameter of the guide hole is larger than the diameter of the gravity ball.

[0013] Furthermore, the fixing assembly also includes a support frame and a first laser positioner; the support frame is disposed below the first and second sliding plates, and the first laser positioner is disposed on the support frame, the first laser positioner being used to monitor the height of the gravity ball.

[0014] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects: 1. This invention provides multiple through-hole modules on a guide plate. Each through-hole module has a downwardly convex arc-shaped surface with a guide hole at its center. When the rope passes through the guide hole, the arc-shaped surface structure provides natural centering and guidance, reducing rope deviation or jumping when passing through the guide hole and improving the guiding accuracy and positional stability of the rope. By threading ropes through the guide holes of different through-hole modules, different landing positions can be simulated on the same simulated deck, improving the flexibility and test coverage of the simulation test system.

[0015] 2. In this invention, a first fixing component and a second fixing component are respectively disposed at both ends of a guide plate. A first telescopic motor and a second telescopic motor respectively drive a first sliding plate and a second sliding plate to run relative to each other in a first direction to clamp the rope and reliably fix the rope passing through the guide hole, thereby reducing the loosening or displacement of the rope during the test and improving the accuracy and repeatability of the test results.

[0016] 3. In this invention, the via modules are arranged in a straight line and uniformly along the first and second directions of the guide plate, respectively; wherein, the first and second directions are perpendicular to each other, and the guide holes are distributed in an array on the guide plate, enabling the aircraft to land at different landing positions on the simulated deck, further improving the flexibility and coverage of the test.

[0017] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0018] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts. Figure 1 A schematic diagram of the structure of the ship landing simulation system provided by the present invention; Figure 2 A schematic diagram of the front structure of the guide plate provided by the present invention; Figure 3 A schematic diagram of the back structure of the guide plate provided by the present invention; Figure 4 A schematic diagram of the internal structure of the gravity sphere provided by the present invention; Figure 5 A schematic diagram showing the positions of the guide plate, fixing assembly, rope, and gravity ball provided by the present invention; Figure 6 This is a schematic diagram of the structure of the guide plate and fixing assembly provided by the present invention; Figure 7 A schematic diagram of the groove and protrusion of the first sliding plate provided by the present invention; Figure 8 A schematic diagram of the structure of the first sliding plate, support frame, and first laser positioner provided by the present invention; Figure 9 This is a schematic diagram of the structure of the swing lifting device provided by the present invention; Figure 10 A schematic diagram of the structure of the swing assembly, the rotating assembly, and the clamping assembly provided by the present invention; Figure 11 A schematic diagram of the structure of the ball head and connecting rod provided by the present invention; Figure 12 This is a schematic diagram of the internal structure of the clamping assembly provided by the present invention; Figure 13 A partial schematic diagram of the internal structure of the clamping arm provided by the present invention.

[0019] Figure label: 1-Simulated deck; 11-Fixed seat; 2-Guide plate; 21-Through hole module; 211-Guide hole; 212-Arc-shaped surface; 213-Arc-shaped edge; 3-Fixing component; 31-First fixing component; 311-First telescopic motor; 312-First sliding plate; 32-Second fixing component; 321-Second telescopic motor; 322-Second sliding plate; 33-Support frame; 34-First laser positioner; 4- Rope; 5-Gravity sphere; 51-Inner sphere; 52-Outer ring; 6-Swing lifting device; 61-Swing assembly; 611-Connecting rod; 612-Ball head; 613-Base; 62-Clamping assembly; 621-Clamping arm; 6211-Inner rod; 6212-Outer cylinder; 6213-Second laser positioner; 6214-Spring; 622-Support; 623-Electric servo motor; 63-Rotating component; 631-Turntable; 632-Fixed disk; 64-Lifting assembly; 641-Drive motor; 642-Actuating rod; 643-Actuating sleeve; 65-Positioning device; 66-Stress sensor; 67-Laser rangefinder; 68-Shock absorber. Detailed Implementation

[0020] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0021] A specific embodiment of the present invention discloses an aircraft carrier landing simulation test system, such as... Figure 1 and Figure 5 As shown, it includes a simulated deck 1, ropes 4, a guide assembly, and a fixing assembly 3.

[0022] The guide assembly is located in the central area of ​​the simulated deck 1. The guide assembly includes a guide plate 2, such as... Figure 2 As shown, the guide plate 2 has multiple through-hole modules 21, which are adjacent to each other. Each through-hole module 21 has a convex arc-shaped surface 212, and a guide hole 211 is provided at the center of the arc-shaped surface 212 for the rope 4 to pass through.

[0023] like Figure 5 As shown, the fixing component 3 is used to fix the rope 4 that passes through the guide hole 211.

[0024] Compared to existing technologies that use pulleys or vertical guides to guide the rope in a landing simulation, this embodiment provides multiple through-hole modules 21 on the guide plate 2. Each through-hole module 21 has a downwardly convex arc-shaped surface 212 with a guide hole 211 at its center. When the rope 4 passes through the guide hole 211, the arc-shaped surface 212 structure can naturally center and guide the rope 4, reducing the rope 4 from deviating or jumping when passing through the guide hole 211, thus improving the guiding accuracy and positional stability of the rope 4. By threading the rope 4 through the guide holes 211 of different through-hole modules 21, different landing positions can be simulated on the same simulated deck 1, improving the flexibility and test coverage of the simulation test system.

[0025] Furthermore, such as Figure 4 As shown, a gravity ball 5 is provided at the end of the rope 4. The gravity ball 5 keeps the rope 4 in a vertical position and reduces the risk of the rope 4 coming out of the guide hole 211 or retracting. The diameter of the guide hole is larger than the diameter of the gravity ball 5, allowing the gravity ball 5 to pass freely through the guide hole 211 without getting stuck.

[0026] The gravity ball 5 includes an inner sphere 51 and an outer ring 52. The outer ring 52 is a rubber layer, the inner sphere 51 is made of metal, and the inner wall of the outer ring 52 forms a spherical groove. The diameter of the spherical groove is larger than the diameter of the inner sphere 51 to reduce wear between the inner sphere 51 and the outer ring 52.

[0027] Furthermore, to make the guidance components in the carrier landing simulator more easily guide the aircraft to different landing positions, such as... Figure 2 As shown, in this embodiment, the via modules 21 are arranged linearly and uniformly along the first and second directions of the guide plate 2, respectively; wherein, the first direction is the length direction of the simulated ship plate, and the second direction is the width direction of the simulated ship plate. The first and second directions are perpendicular to each other, and the guide holes 211 are distributed in an array on the guide plate 2, enabling the aircraft to land at different positions on the simulated deck 1, further improving the flexibility and coverage of the test.

[0028] Furthermore, the via module 21 also includes an arc-shaped edge 213 with its concave surface facing upwards. When the gravity ball 5 falls into the arc-shaped edge 213, it slides into an adjacent arc-shaped concave surface 212 under its arc-shaped guide, and then enters the guide hole 211. The structure of the arc-shaped edge 213 and the arc-shaped surface 213 improves the accuracy of guiding the gravity ball 5 and the rope 4.

[0029] like Figure 6 As shown, the fixing component 3 includes a first fixing component 31 and a second fixing component 32. The first fixing component 31 and the second fixing component 32 are respectively disposed at opposite ends of the guide plate 2.

[0030] For example, the first fixing component 31 includes a first telescopic motor 311 and a first sliding plate 312, with the output end of the first telescopic motor 311 connected to the first sliding plate 312.

[0031] The second fixing component 32 includes a second telescopic motor 321 and a second sliding plate 322, with the output end of the second telescopic motor 321 connected to the second sliding plate 322.

[0032] The first telescopic motor 311 and the second telescopic motor 321 respectively drive the first sliding plate 312 and the second sliding plate 322 to run towards or away from each other along the first direction of the guide plate 2, so as to clamp or release the rope 4.

[0033] Specifically, such as Figure 3 As shown, the bottom of the first slide plate 312 and the second slide plate 322 are provided with guide protrusions, and the ends of both ends of the guide plate 2 in the second direction are provided with guide grooves. The guide protrusions can slide in the guide grooves to realize the sliding of the first slide plate 312 and the second slide plate 322 along the first direction of the guide plate 2.

[0034] Furthermore, in order to address the problem of localized stress concentration affecting the lifespan of rope 4 after clamping, such as... Figure 7 As shown, the sidewalls of the first sliding plate 312 and the second sliding plate 322 are respectively provided with multiple grooves and multiple protrusions, which are alternately arranged along the length of the sidewalls. The positions of the grooves on the sidewalls of the first sliding plate 312 and the second sliding plate 322 correspond to the positions of the guide holes 211 in the first direction of the guide plate 2. When clamping the rope 4, the rope 4 is located in the grooves of the first sliding plate 312 and the second sliding plate 322. The first sliding plate 312 and the second sliding plate 322 squeeze each other to clamp the rope 4, reducing the damage to the rope 4 caused by local stress concentration. Moreover, the clamping force is distributed at multiple points along the length of the sliding plate, resulting in more uniform force distribution, improving the clamping stability and the service life of the rope 4.

[0035] Furthermore, a pressure sensor is installed in the groove. When the groove comes into contact with the rope, the pressure sensor detects the rope and the telescopic motor of the corresponding fixing component stops moving.

[0036] Furthermore, to address the issue of slippage or deformation of the rope 4 during clamping, preferably, the number of through-hole modules 21 arranged along the first direction of the guide plate 2 is an even number. After the rope 4 enters the guide hole 211 of one of the through-hole modules 21, when the fixing component 3 clamps the rope 4, one of the fixing components (the first fixing component 31 or the second fixing component 32) will first contact the rope 4. At this time, the pressure sensor in the groove senses the rope 4, and the corresponding telescopic motor stops running. After the other fixing component approaches and contacts the rope 4, the first sliding plate 312 and the second sliding plate 322 together clamp the rope 4.

[0037] Furthermore, to address the issue of excessive unidirectional clamping force in the first fixing component 31 and the second fixing component 32, the upper surfaces of the first sliding plate 312 and the second sliding plate 322 are at the same horizontal level as the lowest point of the arc-shaped surface 212 of the through-hole module 21. When the rope 4 is clamped, after the first sliding plate 312 and the second sliding plate 322 clamp the rope 4, the lowest point of the arc-shaped surface 212 of the through-hole module 21 contacts the upper surfaces of the first sliding plate 312 and the second sliding plate 322, and the arc-shaped surface 212 bulges downward to bear part of the clamping force.

[0038] Furthermore, such as Figure 8 As shown, the fixing component 3 also includes a support frame 33 and a first laser positioner 34. The support frame 33 is disposed below the first sliding plate 312 and the second sliding plate 322. The first laser positioner 34 is disposed on the support frame 33 and is used to monitor the height of the gravity ball 5. When the first laser positioner 34 detects that the falling height of the gravity ball 5 is level with the height of the first laser positioner 34, it sends a feedback signal, and the rope 4 continues to fall for a distance until its height is lower than the height of the first laser positioner 34, at which point it stops. The first fixing component 31 and the second fixing component 32 then begin to move to clamp the rope 4.

[0039] Furthermore, to address the challenges posed by different operating conditions during aircraft landing, such as... Figure 1 and Figure 10 As shown, the simulation system also includes a swaying and lifting device 6. A fixed base 11 is provided on the lower surface of the simulated deck 1 for fixing the swaying and lifting device 6. The swaying and lifting device 6 is used to sway and lift the simulated deck 1 to simulate different operating conditions when an aircraft lands on a ship.

[0040] like Figure 9 As shown, the swing lifting device 6 includes a swing assembly 61 and a lifting assembly 64. The lifting assembly 64 is located below the swing assembly 61.

[0041] like Figure 10 and Figure 11 As shown, the rocker assembly 61 includes a connecting rod 611, a ball head 612, and a base 613.

[0042] A ball joint 612 is disposed in a base 613, and a connecting rod 611 connects the ball joint 612 and the fixed seat 11. The base 613 has a concave surface for the ball joint, and the ball joint 612 cooperates with the concave surface. The ball joint 612 can rotate freely within the concave surface to change the tilt angle of the fixed seat 11 and the aircraft on the simulated deck 1, thereby simulating the dynamic center of gravity shift and vibration response of the aircraft in the air caused by load changes, airflow disturbances and attitude adjustments.

[0043] Preferably, a portion of the ball head 612 extends beyond the base 613 to limit the angle of rotation of the ball head 612. In this embodiment, the maximum spatial rotation angle of the ball head 612 is 40°.

[0044] Furthermore, to address the technical problem of the aircraft's inability to maintain a preset attitude stably when tilted, thus affecting test repeatability, the swing lifting device 6 also includes a clamping assembly 62. For example... Figure 10 As shown, the clamping assembly 62 includes clamping arms 621, supports 622, and electric servos 623. The clamping arms 621 are located on both sides of the connecting rod 611, and the electric servos 623 connect the supports 622 and the clamping arms 621. Preferably, there are two clamping arms 621 and two electric servos 623, each driving one clamping arm 621. When the connecting rod 611 is locked, the electric servos 623 on both sides drive the clamping arms 621 to extend, with the ends of the clamping arms 621 abutting against the connecting rod 611, fixing the connecting rod 611 in place. When the electric servos 623 on both sides drive the clamping arms 621 to retract, the ends of the clamping arms 621 disengage from the connecting rod 611, the connecting rod 611 is unlocked, and the connecting rod 611 can rotate freely. The clamping arms 621 on both sides extend to different lengths, allowing the aircraft to tilt at different angles.

[0045] For example, the electric servo motor 623 and the clamping arm 621 are obliquely disposed between the support 622 and the connecting rod 611. One end of the electric servo motor 623 is hinged to the support 622, and the other end of the electric servo motor 623 is connected to the clamping arm 621. The support 622 is connected to the turntable 631. When the connecting rod 611 is unlocked, the support 622 can drive the electric servo motor 623 and the clamping arm 621 to rotate around the swing assembly 61, thereby changing the angle and orientation of the aircraft on the device.

[0046] In this embodiment, the electric servo motor 623 and the clamping arm 621 work together to control the attitude of the connecting rod 611, realizing the dual functions of aircraft attitude fine-tuning and dynamic locking. This enables the aircraft to stably maintain the preset attitude during testing and respond to attitude adjustment commands in real time, thereby improving testing accuracy and dynamic simulation accuracy.

[0047] Furthermore, to address the technical problem of relative slippage and unreliable locking between the clamping arm 621 and the connecting rod 611 during locking, the end of the clamping arm 621 and the connecting rod 611 are connected by a toothed engagement. This toothed engagement achieves mechanical rigid locking, improves locking reliability, reduces the risk of slippage of the connecting rod 611 under stress, and thus ensures the stability of the aircraft's attitude during testing.

[0048] Specifically, such as Figure 12 As shown, the inner wall of the end of the clamping arm 621 is provided with a first tooth, such as... Figure 11As shown, a toothed ring structure is provided on the outer circumference of the connecting rod 611, and the first tooth of the clamping arm 621 meshes with the second tooth of the toothed ring. Preferably, the toothed ring is sleeved on the outside of the connecting rod 611. Figure 13 As shown, the inner wall of the gear ring has a groove, and the outer side of the connecting rod 611 has a protrusion, which is located in the groove and is used to limit the movement of the gear ring. It should be noted that there is a gap between the protrusion and the inner wall of the groove. Due to the gap, the teeth of the clamping arm 621 wobble when meshing with the gear ring, thereby avoiding wear impact between the first and second teeth. Therefore, the gap has a damping and vibration reduction function.

[0049] A second laser positioner 6213 is provided at the near end of the clamping arm 621 to track and detect the extension length of the clamping arm 621 in real time, accurately know the extension amount of the clamping arm 621, and thus provide a data basis for precise control of the attitude angle and repeated positioning.

[0050] Further, preferably, the clamping arm 621 includes an inner rod 6211 and an outer cylinder 6212, with the inner rod 6211 capable of slight movement within the outer cylinder 6212. A second laser positioner 6213 is disposed outside the outer cylinder 6212. A limiting groove is provided inside the outer cylinder 6212 corresponding to the position of the second laser positioner 6213. A limiting block is provided outside the inner rod 6211, capable of moving within the limiting groove. The two ends of the limiting groove limit the range of motion of the limiting block, thereby limiting the extension / retraction length of the clamping arm 621. The second laser positioner 6213 can track the position of the limiting block to calculate the extension / retraction length of the clamping arm 621.

[0051] Furthermore, to address the technical problem of insufficient locking force or component damage caused by rigid contact when the inner rod 6211 abuts against the gear ring, a spring 6214 is provided between the inner rod 6211 and the output end of the electric servo motor 623. When the end of the inner rod 6211 abuts against the gear ring of the connecting rod 611, the spring 6214 is in a compressed state. This embodiment utilizes the compressive force of the spring 6214 to provide continuous and flexible locking pressure, ensuring a tight contact between the inner rod 6211 and the gear ring while absorbing impact forces during the locking process, reducing the risk of rigid collision damage, and improving locking life and reliability.

[0052] Furthermore, the swing lifting device 6 also includes a positioning device 65. A connector is provided at the end of the connecting rod 611 away from the ball head 612, and the connector is connected to the lower latch. The connector is a square plate, and the positioning device 65 is provided on the four sides of the connector to detect and calculate the extension length of the clamping arm 621.

[0053] The sway assembly 61 landing gear can generate deflection motion while bearing vertical loads, simulating the yaw condition of the aircraft when landing on a carrier or when one side touches the ground first, so that the test can be carried out under boundary conditions that are closer to the real flight mechanics.

[0054] Furthermore, to address the technical problem of the aircraft becoming stuck and unable to flexibly simulate dynamic attitude due to component interference when tilted, the swaying and lifting device 6 also includes a rotating assembly 63. The rotating assembly 63 includes a turntable 631 and a fixed plate 632 arranged concentrically. The turntable 631 is located outside the fixed plate 632 and can rotate relative to the fixed plate 632. The swaying assembly 61 is mounted on the fixed plate 632, and the clamping assembly 62 is connected to the fixed plate 632. Specifically, a base 613 is located in the middle of the fixed plate 632, and supports 622 are located at both ends of the turntable 631. The turntable 631 can drive the supports 622, clamping arms 621, and electric servos 623 to rotate around the base 613 and the connecting rod 611.

[0055] The lifting assembly 64 is used to raise and lower different parts of the simulated deck 1 to different heights. The lifting assembly 64 includes a drive motor 641 and an actuator 642, with the drive motor 641 driving the actuator 642 to perform lifting and lowering movements.

[0056] Specifically, the lifting assembly 64 also includes an actuating sleeve 643, and the drive motor 641 drives the actuating rod 642 to extend and retract along the axial direction of the actuating sleeve 643 to regulate the vertical displacement of the aircraft.

[0057] Furthermore, it also includes a stress sensor 66, which is mounted on the oscillation assembly 61 to detect the gravity load state of the aircraft. By acquiring load distribution data in real time through the stress sensor 66, the center of gravity offset can be dynamically monitored, providing key mechanical parameters for attitude control and vibration analysis.

[0058] Specifically, stress sensor 66 is mounted on connecting rod 611 to collect stress distribution data of the contact surface between the aircraft landing gear and the fixed structure in real time. Combined with three-dimensional attitude data, it reflects the center of gravity offset and vibration characteristics of the aircraft under different operating conditions, thereby providing data support for aircraft structural design, take-off and landing impact analysis and active vibration suppression.

[0059] Furthermore, the swing lifting device 6 also includes a laser rangefinder 67, which is mounted on the actuating sleeve 643. The laser rangefinder 67 is used to collect the extension height of the actuating rod 642 to achieve closed-loop displacement control. By combining the data from the stress sensor 66 and the laser rangefinder 67, the vibration and center of gravity shift trend of the aircraft under load changes can be calculated in real time.

[0060] Furthermore, the swing and lifting device 6 also includes a shock absorber 68, which is disposed between the swing assembly 61 and the lifting assembly 64. In this embodiment, the shock absorber 68 is a rubber shock absorber. The rubber shock absorber absorbs the high-frequency impact energy generated by the aircraft during attitude adjustment and vibration response through elastic deformation, attenuates transient vibrations caused by sudden attitude changes or external disturbances, and improves the dynamic stability and repeatability of the test system.

[0061] Furthermore, the swing lifting device 6 also includes a controller, which is electrically connected to pressure sensors in the grooves of the first telescopic motor 311, the second telescopic motor 321, the first slide plate 312, and the second slide plate 322, as well as to the first laser locator 34, the second laser locator 6213, the drive motor 641, the stress sensor 66, and the laser rangefinder 67, and is also electrically connected to the attitude monitoring device built into the aircraft. When the first laser locator 34 monitors the falling height of the gravity ball 5 and its height is aligned with the height of the ball, it sends a feedback signal to the controller. The controller then drives the output shafts of the first telescopic motor 311 and the second telescopic motor 321 to extend and retract closer to the rope 4. After the pressure sensor in the groove of the first slide plate 312 or the second slide plate 322 contacts the rope 4, it sends a signal back to the controller. After the rope 4 continues to fall for a while, the controller controls the first telescopic motor 311 or the second telescopic motor 321 to stop moving, while the other slide plate continues to move. Both slide plates contact the rope 4 and clamp, thus achieving the clamping and releasing of the rope 4. The controller can control the drive motor 641 to drive the actuator 642 to extend and retract precisely, and can receive real-time data from the stress sensor 66 and the laser rangefinder 67, as well as the attitude monitoring data of the aircraft. It can calculate the three-dimensional attitude error, center of gravity offset and vibration parameters of the aircraft in real time, and dynamically generate closed-loop control commands according to the preset algorithm to drive the actuator 642 and the electric servo motor 623 to work together to realize the integrated closed-loop control of attitude fine adjustment, dynamic center of gravity compensation and vibration suppression.

[0062] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft carrier landing simulation test system, characterized in that, Includes a simulated deck (1), ropes (4), a guide assembly, and a fixing assembly (3); The guide assembly is located in the central area of ​​the simulated deck (1); the guide assembly includes a guide plate (2), the guide plate (2) has a plurality of through-hole modules (21), the plurality of through-hole modules (21) are adjacent to each other; the through-hole module (21) has a downwardly convex arc surface (212), the center of the arc surface (212) is provided with a guide hole (211), the guide hole (211) is used for the rope (4) to pass through; The fixing component (3) is used to fix the rope (4) that passes through the guide hole (211).

2. The aircraft carrier landing simulation test system according to claim 1, characterized in that, The via modules (21) are arranged in a straight line and uniformly along the first and second directions of the guide plate (2); wherein the first direction and the second direction are perpendicular to each other.

3. The aircraft carrier landing simulation test system according to claim 2, characterized in that, The number of via modules (21) arranged along the first direction of the guide plate (2) is an even number.

4. The aircraft carrier landing simulation test system according to claim 1, characterized in that, The fixing component (3) includes a first fixing component (31) and a second fixing component (32); the first fixing component (31) and the second fixing component (32) are respectively disposed at opposite ends of the guide plate (2).

5. The aircraft carrier landing simulation test system according to claim 4, characterized in that, The first fixing component (31) includes a first telescopic motor (311) and a first sliding plate (312), and the output end of the first telescopic motor (311) is connected to the first sliding plate (312); The second fixing component (32) includes a second telescopic motor (321) and a second sliding plate (322), wherein the output end of the second telescopic motor (321) is connected to the second sliding plate (322); The first telescopic motor (311) and the second telescopic motor (321) respectively drive the first sliding plate (312) and the second sliding plate (322) to run towards or away from each other along the first direction of the guide plate (2) to clamp or release the rope (4).

6. The aircraft carrier landing simulation test system according to claim 5, characterized in that, The upper surfaces of the first slide plate (312) and the second slide plate (322) are at the same horizontal height as the lowest point of the arc surface (212) of the through-hole module (21).

7. The aircraft carrier landing simulation test system according to claim 5, characterized in that, The first slide plate (312) and the second slide plate (322) are respectively provided with a plurality of grooves and a plurality of protrusions on their sidewalls, and the plurality of grooves and the plurality of protrusions are alternately arranged along the length direction of the sidewalls.

8. The aircraft carrier landing simulation test system according to claim 7, characterized in that, The grooves on the sidewalls of the first slide plate (312) and the second slide plate (322) are positioned corresponding to the guide holes (211) in the first direction of the guide plate (2).

9. The aircraft carrier landing simulation test system according to claim 5, characterized in that, The end of the rope (4) is provided with a gravity ball (5), and the diameter of the guide hole (211) is larger than the diameter of the gravity ball (5).

10. The aircraft carrier landing simulation test system according to claim 9, characterized in that, The fixing component (3) also includes a support frame (33) and a first laser locator (34); the support frame (33) is disposed below the first slide plate (312) and the second slide plate (322), and the first laser locator (34) is disposed on the support frame (33) and is used to monitor the height of the gravity ball (5).

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