Model supporting structure and ejection device suitable for aircraft dampening test

Abstract

The utility model relates to a model bearing structure and an ejection device suitable for an aircraft dampening test, the model bearing structure comprises a vehicle body matched with the ejection device and a bracket used for bearing a scale model, the bracket is rotatably connected with the vehicle body, the rotation axis between the bracket and the vehicle body is parallel to the sliding track of the vehicle body when the vehicle body is ejected, and the ejection device is arranged on the vehicle body. The bracket and the vehicle body are configured in the mode that when the bracket bearing the scale model is not subjected to external force, the bracket and the vehicle body are kept relatively static. When the bearing structure is subjected to the ejection acting force of the ejection device, the acting force between the vehicle body and the bracket is parallel to the rotating axis between the vehicle body and the bracket, so that the vehicle body and the bracket do not deflect and are not prone to dislocation in the ejection process, and the vehicle can be used for a long time under the working condition that high-strength ejection acting force is frequently borne, and is stable and reliable.

Description

Technical Field

[0001] This utility model relates to the field of aircraft water landing, and in particular to a model support structure and ejection device suitable for aircraft water landing tests. Background Technology

[0002] Advanced air transportation utilizing unmanned low-altitude aircraft to transport people and goods is considered an emerging strategic sector globally. In regions with well-developed waterways, unmanned low-altitude water-crossing aircraft will see tremendous development opportunities. Furthermore, as global flights increasingly cross oceans, water landing capabilities, as one of the key safety performance indicators for aircraft, are gaining increasing attention from governments worldwide. Therefore, it is essential to conduct water landing airworthiness compliance tests on aircraft.

[0003] Research on emergency landings of aircraft on water needs to focus on whether the aircraft's attitude is optimal at the moment of impact, whether the integrity of the aircraft can be guaranteed at the moment of impact and after it comes to a stop on the water, and whether the aircraft has enough time to float and wait for rescue after it stops on the water.

[0004] While my country's civil aviation standards currently contain explicit regulations regarding water landings, they lack realistic research findings on specific water entry attitudes, optimal control, and structural damage. Using actual aircraft for test flights is prohibitively expensive and poses safety risks. Furthermore, current domestic CFD calculations and water tank towing tests fall significantly short of simulating real-world conditions.

[0005] Testing with a scaled-down model of the aircraft presents challenges. During water tank towing tests, the scaled-down model is subjected to traction from the towing equipment, resulting in complex stress conditions that make it difficult to accurately simulate the motion characteristics of the scaled-down model upon water landing. In contrast, catapult tests, where the scaled-down model is launched into the water, simplify the stress conditions and accurately simulate the aircraft's motion upon water landing. However, during catapult tests, the support structure supporting the scaled-down model is repeatedly launched by the catapult device, subjecting it to frequent high-intensity ejection forces. Therefore, it is crucial to ensure the support structure is simple, reliable, and capable of long-term use under these conditions to obtain accurate test results throughout the entire catapult test process. Currently, no suitable support structure meets these requirements. Utility Model Content

[0006] This invention addresses the problem that during the catapult water landing test of a scaled-down aircraft model, the supporting structure of the model is frequently subjected to high-intensity catapult forces, and there is currently no simple, reliable supporting structure that can be used for a long time under such conditions. It provides a model supporting structure and catapult device suitable for aircraft water landing tests to solve this technical problem. The supporting structure uses a simple mechanical structure and optimizes its structural design, making it less prone to misalignment when subjected to catapult forces, and enabling long-term use under conditions of frequent high-intensity catapult forces.

[0007] To solve the above-mentioned technical problems, the technical solution of this utility model is as follows:

[0008] A model support structure suitable for water landing tests of aircraft includes a vehicle body that cooperates with a catapult and a bracket for supporting a scaled-down model. The bracket is rotatably connected to the vehicle body, and the axis of rotation between the bracket and the vehicle body is parallel to the sliding trajectory of the vehicle body when it is launched. The bracket and the vehicle body are configured such that when the bracket supporting the scaled-down model is not subjected to external force, the bracket and the vehicle body remain relatively stationary.

[0009] Preferably, the bracket is provided with two first support blocks for supporting the two wings of the scaled-down model and a second support block for supporting the tail. The support blocks are connected to support rods parallel to the pitch axis of the scaled-down model. A connecting block is provided below the scaled-down model, with the forward direction of the scaled-down model during launch as the front side and the other side as the rear side. The rear side of the connecting block is provided with a support groove adapted to the support rod.

[0010] Preferably, the connecting block is detachably connected to the scaled-down model, each of the brackets is detachably connected to the bracket, and the bracket is provided with at least two sets of installation positions, each set of installation positions including two first bracket installation positions and one second bracket installation position.

[0011] Preferably, the support block is further provided with a spring pin assembly for preventing the scaled model from sliding off the support block. The spring pin assembly includes a pin structure that abuts against the scaled model to prevent the scaled model from sliding off the support structure and a spring that pushes the pin structure to keep it in contact with the scaled model. One end of the pin structure is an inclined surface, and it abuts against the scaled model through the inclined surface.

[0012] Preferably, the bracket is provided with two first hanging blocks for suspending the two wings of the scaled model and a second hanging block for suspending the tail. The hanging blocks are connected to support rods parallel to the pitch axis of the scaled model. The scaled model is provided with a connecting structure on the top, with the forward direction of the scaled model during ejection as the front side and the other side as the rear side. The rear side of the connecting block is provided with a support groove adapted to the support rod.

[0013] Preferably, the connecting block is detachably connected to the scaled-down model, each of the hanging blocks is detachably connected to the bracket, and the bracket is provided with at least two sets of hanging block installation positions, each set of hanging block installation positions including two first hanging block installation positions and one second hanging block installation position.

[0014] Preferably, when the bracket supports the scaled-down model, the axis of rotation between the bracket and the vehicle body coincides with the roll axis of the scaled-down model.

[0015] A catapult device suitable for water landing tests of aircraft, the catapult device being suitable for launching the aforementioned model support structure, the catapult device comprising a mounting base having a horizontal reference plane, a catapult slide rail movably connected below the mounting base with one end facing the water tank, a locking and releasing mechanism for locking the support structure before the catapult operation and unlocking the support structure at the start of the catapult operation, and a catapult action mechanism for driving the support structure to perform the catapult operation, the catapult action mechanism comprising a drive component that applies different magnitude catapult forces to the support structure to give it different speeds, and an interception component for stopping the support structure to allow the scaled model to be launched and detached.

[0016] Preferably, the ejector rail includes two hinge points that are directly or indirectly hinged to the mounting base, and the hinge axis of each hinge point is a horizontal line perpendicular to the sliding trajectory of the supporting structure, wherein at least one hinge point is hinged to the mounting base through a controlled telescopic module.

[0017] Preferably, the two ends of the ejection rail are defined as the near-water end and the far-water end, respectively, and the locking release mechanism is located at the far-water end of the ejection rail;

[0018] The drive assembly of the ejection mechanism includes an elastic rope for pulling the support structure to slide from the far end of the ejection rail to the near end, a servo winch for winding the elastic rope, and a winding mechanism for driving the servo winch to rotate. The servo winch rotates in conjunction with the ejection rail. The interception assembly of the ejection mechanism includes an arresting rope connected to the ejection rail. The arresting rope is located on the sliding trajectory of the support structure along the ejection rail.

[0019] The beneficial technical effects of this utility model's technical solution are as follows:

[0020] (I) The ejection device is used to launch the scaled-down model into the water. The supporting structure includes a rotatably connected vehicle body and a bracket, which is simple in structure. The axis of rotation between the bracket and the vehicle body is parallel to the sliding trajectory of the vehicle body. By rotating the bracket, the roll angle of the scaled-down model can be changed. The bracket and the vehicle body have mutually contacting sides, which remain in a tight abutment. When the bracket supporting the scaled-down model is not subjected to external force, the bracket and the vehicle body will remain relatively stationary. That is, the friction between the bracket supporting the scaled-down model and the vehicle body is sufficient to keep them relatively stationary. The bracket can only rotate when the tester adjusts it. After the tester completes the angle adjustment of the bracket, the bracket supporting the scaled-down model can no longer shift relative to the vehicle body.

[0021] Furthermore, when the supporting structure is subjected to the ejection force of the ejection device, the force between the vehicle body and the bracket is parallel to the axis of rotation between them, so that the vehicle body and the bracket will not deflect during the ejection process and are not prone to misalignment. This allows for long-term use under conditions of frequent high-intensity ejection forces, ensuring stability and reliability. Attached Figure Description

[0022] Figure 1 This diagram illustrates the cooperation between the ejection device and the model support structure in Embodiment 1 of this utility model.

[0023] Figure 2 A schematic diagram showing the fit between the model support structure and the scaled-down model in Embodiment 1 of this utility model is shown;

[0024] Figure 3 It shows Figure 2 Enlarged view of point A in the middle;

[0025] Figure 4 This diagram illustrates the working state of the ejection device and the model support structure in Embodiment 1 of this utility model.

[0026] Figure 5 A cross-sectional view of the model support structure and the scaled-down model in Embodiment 1 of this utility model is shown;

[0027] Figure 6 The diagram shows the cooperation between the model support structure and the scaled-down model in Embodiment 2 of this utility model.

[0028] Marked in the attached diagram:

[0029] 1-Mounting base; 11-Telescopic module; 2-Ejection rail; 2a-Distant water end; 2b-Near water end; 21-Servo winch; 22-Elastic rope; 23-Barrier rope; 24-Locking release mechanism; 3-Supporting structure; 31-Car body; 32-Bracket; 320-Hanging block; 321-Supporting block; 322-Supporting rod; 323-Spring pin assembly; 4-Scale model; 41-Connecting block; 411-Supporting groove; 5-Water pool; 51-Pullhole wall; 511-Window; 52-Camera unit; 53-Light source. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a model support structure and ejection device suitable for water landing tests of aircraft. The advantages and features of this utility model will become clearer from the following description. It should be noted that the accompanying drawings are in a very simplified form and use non-precise proportions, used only to facilitate and clearly illustrate the purpose of the embodiments of this utility model. Please refer to the accompanying drawings to make the objectives, features, and advantages of this utility model more apparent and understandable. It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are only for illustrative purposes to aid those skilled in the art and are not intended to limit the implementation conditions of this utility model. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to the size, without affecting the effects and objectives achieved by this utility model, should still fall within the scope of the technical content disclosed in this utility model.

[0031] The following will be combined with the appendix Figures 1 to 6 The present invention provides a detailed description of the technical solution of a model support structure and catapult device suitable for water landing testing of aircraft, and specific embodiments thereof.

[0032] Example

[0033] like Figures 1 to 5As shown, this embodiment of a model support structure suitable for water landing tests of aircraft includes a vehicle body 31 that cooperates with a catapult device and a bracket 32 ​​for supporting a scaled-down model 4. The bracket 32 ​​is rotatably connected to the vehicle body 31, and the bracket 32 ​​and the vehicle body 31 have mutually contacting sides that remain in a tight abutment. Furthermore, the axis of rotation between the bracket 32 ​​and the vehicle body 31 is parallel to the sliding trajectory of the vehicle body 31 when it is launched. The bracket 32 ​​and the vehicle body 31 are configured such that when the bracket 32 ​​supporting the scaled-down model 4 is not subjected to external force, the bracket 32 ​​and the vehicle body 31 remain relatively stationary. That is, when the bracket 32 ​​supporting the scaled-down model 4 is not subjected to external force, the friction between the bracket 32 ​​and the vehicle body 31 is sufficient to keep them relatively stationary. In other words, the bracket 32 ​​can only rotate when the tester adjusts it. After the tester completes the angle adjustment of the bracket 32, the bracket 32 ​​supporting the scaled-down model 4 can no longer shift relative to the vehicle body 31. Furthermore, when the supporting structure 3 is subjected to the ejection force of the ejection device, the force between the vehicle body 31 and the bracket 32 ​​of the scaled model 4 is parallel to the axis of rotation between them, so that the vehicle body 31 and the bracket 32 ​​will not deflect during the ejection process and are not prone to misalignment. They can be used for a long time under the condition of frequent high-intensity ejection force, and are stable and reliable.

[0034] Furthermore, the side of the bracket 32 ​​that is in contact with the vehicle body 31 is perpendicular to the sliding trajectory of the vehicle body 31 when it is ejected, so that the friction between the bracket 32 ​​and the vehicle body 31 can be used to keep the bracket 32 ​​and the vehicle body 31 relatively stable during ejection, and prevent misalignment.

[0035] The relative rotation between the control bracket 32 ​​and the vehicle body 31 can change the roll angle of the scaled model 4 and adjust the water entry attitude angle of the scaled model 4, thereby simulating various water entry attitudes of the aircraft during testing.

[0036] This embodiment also discloses a launch device that cooperates with the aforementioned support structure 3. The launch device includes a mounting base 1 with a horizontal reference plane, a launch rail 2 movably connected to the mounting base 1, a locking and releasing mechanism 24 for locking the support structure 3 before launch and unlocking the support structure 3 when launch begins, and a launch action mechanism for driving the support structure 3 to launch. In this embodiment, the mounting base 1 is fixedly connected to the ceiling of the test site, and the bottom surface of the mounting base 1 is horizontal. The launch rail 2 is movably connected to the mounting base 1, and the swing of the launch rail 2 relative to the mounting base 1 can be directly controlled. The support structure 3 slides with the launch rail 2, that is, the entry attitude angle of the scaled model 4 can also be adjusted by adjusting the angle of the launch rail 2. The launch action mechanism includes a driving component that can drive the support structure 3 to slide along the length direction of the launch rail 2 at different speeds and an intercepting component for stopping the support structure 3 so that the scaled model 4 can be launched away.

[0037] The connection relationship between the ejection rail 2 and the mounting base 1 is described in detail below:

[0038] During the water launch test of the scaled-down model 4, the supporting structure 3 slides along the launch rail 2 towards the water surface, requiring the scaled-down model 4 to be launched at an angle towards the water surface. Therefore, one end of the launch rail 2 is positioned lower and closer to the water surface, while the other end is positioned higher and farther from the water surface. First, the end of the launch rail 2 closer to the water surface is defined as the near-water end 2b, and the end of the launch rail 2 farther from the water surface is defined as the far-water end 2a. The launch rail 2 has two hinge points that are directly or indirectly hinged to the mounting base 1. These two hinge points are arranged along the length of the launch rail 2, and the hinge axis of each hinge point is a horizontal line perpendicular to the sliding trajectory of the supporting structure 3. In this embodiment, both hinge points of the ejector slide rail 2 are connected to the mounting base 1 by a telescopic module 11. Both ends of the telescopic module 11 are hinged to both the ejector slide rail 2 and the mounting base 1. When the two telescopic modules 11 extend and retract asynchronously, the ejector slide rail 2 can be tilted. Adjustment is achieved by connecting at least one hinge point to the mounting base 1 via the controlled telescopic module 11. In this embodiment, the telescopic module 11 is a pneumatic cylinder. The cylinder body is connected to the mounting base 1, and the piston rod is connected to the ejector slide rail 2. Controlling the extension and retraction of the pneumatic cylinder changes the tilt angle of the ejector slide rail 2. It should be noted that in this embodiment, a fixing rod is also connected between the pneumatic cylinder near the water-near end 2b of the ejector slide rail 2 and the mounting base 1. Both ends of the fixing rod are fixedly connected to the mounting base 1 and the cylinder body of the pneumatic cylinder, respectively, thus locking the position of the pneumatic cylinder and preventing it from swinging, allowing only extension and retraction. However, in this embodiment, the two pneumatic cylinders can also drive the ejector slide rail 2 to swing.

[0039] It should be understood that in another embodiment, one hinge point of the catapult slide rail 2 can be directly connected to the mounting base 1, and the other hinge point can be connected to the mounting base 1 through the telescopic module 11. Controlling the telescopic module 11 to extend or retract can also drive the catapult slide rail 2 to swing, thereby changing the pitch angle of the scaled model 4 and adjusting the water entry attitude angle of the scaled model 4.

[0040] The specific structure of supporting structure 3 is as follows:

[0041] The supporting structure 3 includes a car body 31 that slides with the catapult rail 2 and a bracket 32 ​​for supporting the scale model 4. The car body 31 is installed below the catapult rail 2, and the bracket 32 ​​is rotatably connected to the car body 31. Moreover, the axis of rotation between the bracket 32 ​​and the car body 31 is parallel to the sliding trajectory of the car body 31.

[0042] In addition, the ejection mechanism can also be used to change the ejection speed of the scaled model 4. Based on this test equipment, the sliding speed of the supporting structure 3, the pitch angle and roll angle of the scaled model 4 can be changed, thereby simulating various water entry attitudes and water entry speeds of the aircraft. The relationship between the motion characteristics and force characteristics of the scaled model 4 during water entry can be comprehensively analyzed and understood. This enables successful flight test verification, water wading performance verification, extreme condition test, and fault simulation test of the aircraft, providing guidance for aircraft structural design and improving the safety and reliability of aircraft design.

[0043] The aforementioned locking and releasing mechanism 24 is installed at the far end 2a of the catapult rail 2. The locking and releasing mechanism 24 switches between locking and releasing the supporting structure 3. Before the catapult operation begins, the locking and releasing mechanism 24 locks the car body 31 of the supporting structure 3 to the far end 2a of the catapult rail 2. Once the catapult mechanism is ready for catapult operation, the locking and releasing mechanism 24 releases the car body 31 of the supporting structure 3, and the catapult operation can begin. The locking and releasing mechanism 24 can be a controlled gripper, which grips or releases the car body 31 of the supporting structure 3. Alternatively, it can use an electromagnet, vacuum suction cup, or other structure to attract the car body 31 of the supporting structure 3, locking its position. After releasing the attraction to the supporting structure 3, it can be released.

[0044] In this embodiment, the driving component of the ejection mechanism includes a servo winch 21 mounted and rotatably connected to the ejection rail 2, a winding mechanism that drives the servo winch 21 to rotate, and an elastic rope 22 wound on the servo winch 21. One end of the elastic rope 22 is fixedly connected to the servo winch 21, and the other end is connected to the vehicle body 31 of the support structure 3. The servo winch 21 is rotated under the control of the winding mechanism. By winding the elastic rope 22, the tension of the elastic rope 22 can be changed. When the locking release mechanism 24 releases the support structure 3, the elastic ropes 22 with different tensions pull the support structure 3 to slide, which can make the support structure 3 reach different sliding speeds. Furthermore, it should be understood that the drive component of the ejection mechanism needs to pull the support structure 3 from the far end 2a of the ejection rail 2 to the near end 2b. In this embodiment, the drive component is installed at the far end 2a of the ejection rail 2, and a pulley is rotatably connected to the near end 2b of the ejection rail 2. The elastic rope 22 of the drive component first passes around the pulley at the near end 2b of the ejection rail 2, and then connects to the support structure 3. When the support structure 3 is released, the taut elastic rope 22 will inevitably slide from the far end 2a of the ejection rail 2 to the near end 2b. The interception component of the ejection mechanism includes an arresting rope 23 on the sliding trajectory of the vehicle body 31. Both ends of the arresting rope 23 are connected to the ejection rail 2. The arresting rope 23 is suspended below the ejection rail 2. When the supporting structure 3 slides past the arresting rope 23, the supporting structure 3 is blocked by the arresting rope 23 and cannot continue to slide. The scaled model 4 installed on the supporting structure 3 will be ejected due to inertia and fly into the water pool, completing the ejection operation.

[0045] Specifically, three support blocks 321 are installed above the bracket 32 ​​of the supporting structure 3, including two first support blocks and one second support block. The two first support blocks are used to support the two wings of the scaled-down model 4, and the second support block is used to support the tail. Each support block 321 has a through slot on its top that runs along the roll axis of the scaled-down model 4, and each through slot is connected to a support rod 322 that is parallel to the pitch axis of the scaled-down model 4. The scaled-down model 4 is also connected to three connecting blocks 41 that correspond to each support block 321. The connecting blocks 41 are detachably connected to the scaled-down model 4. Each connecting block 41 has a support groove 411 that fits into the support rod 322 on the side facing the far end 2a of the catapult slide rail 2. The support groove 411 passes through the connecting block 41 along the pitch axis of the scaled-down model 4. When the scaled-down model 4 is installed on the bracket 32, each connecting block 41 is embedded in the through groove of the corresponding support block 321. The support rod 322 connected to the support block 321 passes through the support groove 411 of the corresponding connecting block 41. During the process of the support structure 3 driving the scaled-down model 4 to slide towards the water surface, the support rod 322 connected to each support block 321 abuts against the groove wall of the support groove 411 of the corresponding connecting block 41 to ensure that the pitch angle of the scaled-down model 4 remains stable.

[0046] In addition, when the scaled model 4 is installed on the support structure 3, the near end 2b of the ejection rail 2 is generally lower, which causes the scaled model 4 to tend to slide downward and detach from the support structure 3. In order to prevent the scaled model 4 from detaching from the support structure 3 before the ejection operation begins, a spring pin assembly 323 is also installed on the support block 321 to prevent the scaled model 4 from sliding off the support block 321. The spring pin assembly 323 includes a pin structure that abuts against the connecting block 41 of the scaled model 4 to prevent the scaled model 4 from sliding off the support structure 3, and a spring that pushes the pin structure to slide toward the connecting block 41 of the scaled model 4. After the scale model 4 is installed on the support structure 3, one end of the pin structure faces the connecting block 41, and the end face of the pin structure facing the connecting block 41 is inclined. The spring pushes the pin structure to slide towards the connecting block 41 of the scale model 4, so that the pin structure abuts against the connecting block 41 of the scale model 4 through the aforementioned inclined surface. Before the ejection operation begins, it is necessary to ensure that the force exerted by the pin structure on the scale model 4 is sufficient to prevent the scale model 4 from sliding downward. When the support structure 3 is stopped by the interception component, the scale model 4 will continue to move towards the pool 5 due to inertia. At the same time, the connecting block 41 of the scale model 4 pushes the pin structure of the spring pin assembly 323 to retract, and the spring pin assembly 323 releases the obstruction to the scale model 4, so that the scale model 4 can be ejected into the water.

[0047] Furthermore, when the bracket 32 ​​supports the scaled-down model 4, the axis of rotation between the bracket 32 ​​and the vehicle body 31 coincides with the roll axis of the scaled-down model 4, ensuring that the rotation angle of the bracket 32 ​​corresponds to the roll angle of the scaled-down model 4. Therefore, by controlling the bracket 32 ​​to rotate by a specified angle, the roll angle of the scaled-down model 4 can be accurately adjusted.

[0048] To facilitate understanding of the catapult device's structural design, a water landing test system incorporating the aforementioned catapult device is introduced. This system includes the aforementioned catapult device, a catapult device for launching a scaled-down model 4 of the aircraft, a water tank 5 for testing the scaled-down model 4's landing in the water, a first data acquisition module for collecting motion characteristic information of the scaled-down model 4 during landing, a second data acquisition module for collecting force characteristic information of the scaled-down model 4 during landing, and a data processing module for analyzing the relationship between the motion characteristic information and the force characteristic information. The aforementioned motion characteristic information includes the water entry attitude angle and water entry velocity of the scaled-down model 4. By simulating various water entry attitudes and velocities of the aircraft, the relationship between the motion characteristic information and the force characteristic information of the scaled-down model 4 during landing can be comprehensively analyzed and understood.

[0049] Specifically, when collecting motion characteristic information of the scaled-down model 4 during its water landing process, since the actual water entry attitude angle and velocity of the scaled-down model 4 cannot be accurately obtained, the first data acquisition module includes a camera unit 52 that captures images of the scaled-down model 4's water landing process from outside the pool 5, and an analysis and processing unit that identifies the motion characteristic information of the scaled-down model 4 based on the water landing process images. The camera unit 52 captures images of the scaled-down model 4's water landing process, and the analysis and processing unit uses video analysis and image analysis techniques to obtain motion characteristic information such as the water entry attitude angle and water entry velocity of the scaled-down model 4. The obtained motion characteristic information is highly accurate, which is beneficial for accurately analyzing the relationship between the motion characteristic information and the force characteristic information of the scaled-down model 4 during its water landing process. Specifically, the camera unit 52 can be set on one side of the scaled-down model 4's water landing trajectory or simultaneously on both sides of the scaled-down model 4's water landing trajectory, and the lens of the camera unit 52 is flush with the water surface in the pool 5, allowing for horizontal viewing of the scaled-down model 4's water landing process, which helps to accurately obtain the water entry attitude angle.

[0050] Since the camera unit 52 needs to capture images from outside the pool 5, both the pool wall 51 and the water surface in the pool 5 are configured to be higher than the ground level, facilitating personnel access to the outside of the pool 5 and the installation of the camera unit 52. In this embodiment, the pool wall 51 is a concrete structure, and the pool wall 51 also has a through hole for the lens to capture images of the scaled-down model 4 during the water immersion process. A transparent window 511 is installed in the through hole to facilitate image acquisition by the camera unit 52. It is understood that the pool wall 51 of the pool 5 could also be configured as a transparent glass panel, which would provide better light transmission and facilitate shooting, but a transparent observation window on a concrete side wall is more suitable as it is less prone to breakage.

[0051] The aforementioned camera unit 52 is a high-speed camera, including at least two lenses for capturing images of the scaled-down model 4 during the water-immersion process in the form of binocular or multi-lens shooting. When performing binocular shooting, the two lenses are positioned at a 90° angle for binocular shooting.

[0052] To ensure that the camera unit 52 can capture clear images, the first data acquisition module also includes a light source 53 that provides supplemental light to the water-covered position of the scale model 4. In this embodiment, the light source 53 is fixedly installed on the bottom surface of the mounting base 1.

[0053] In addition, the first data acquisition module can also use an underwater robot to capture images of the scaled-down model 4 during its immersion in water. The underwater robot can be used alone or in conjunction with the camera unit 52 to capture images from different angles.

[0054] Furthermore, the camera unit 52 is a non-contact measurement device. The first data acquisition module also includes a gyroscope and an accelerometer built into the scaled-down model 4. The gyroscope is used to measure the attitude angle of the scaled-down model 4, while the accelerometer can measure the acceleration and velocity of the scaled-down model 4. The measurement scheme combining the camera unit 52 with the built-in sensors of the scaled-down model 4 offers advantages: the gyroscope and accelerometer built into the scaled-down model 4 have high measurement accuracy, while the camera unit 52 provides convenient data transmission and can record motion video information of the scaled-down model 4. This combination of the camera unit 52 and the built-in sensors of the scaled-down model 4 can later support measurement data fusion analysis, further improving measurement accuracy and system reliability.

[0055] The surface of the scaled-down model 4 that comes into contact with the water during its immersion is defined as the stress surface. The second data acquisition module includes a thin-film sensor (not shown in the figure) attached to the stress surface. When the scaled-down model 4 is immersed in water, the thin-film sensor can conveniently monitor the pressure distribution information of the stress surface. In the scaled-down model 4, the stress surface includes the areas corresponding to the fuselage, lower wing surface, and engine nacelle of the aircraft under test.

[0056] Example 2

[0057] Reference Figure 6 The difference between this embodiment and Embodiment 1 is that three hanging blocks 320 are installed below the bracket 32, including two first hanging blocks and one second hanging block. The two first hanging blocks are used to suspend the two wings of the scaled model 4, and the second hanging block is used to suspend the tail. Each hanging block 320 has a through groove at its bottom that runs along the roll axis of the scaled model 4, and each through groove is connected to a support rod 322 that is parallel to the pitch axis of the scaled model 4. Above the scaled-down model 4 are three connecting blocks 41 that correspond to each hanging block 320. The connecting blocks 41 are detachably connected to the scaled-down model 4. Each connecting block 41 has a support groove 411 on the side facing the far end 2a of the catapult slide rail 2, which fits into the support rod 322. The support groove 411 passes through the connecting block 41 along the pitch axis of the scaled-down model 4. When the scaled-down model 4 is installed on the bracket 32, each connecting block 41 is embedded in the through groove of the corresponding hanging block 320. The support rod 322 connected to the hanging block 320 passes through the support groove 411 of the corresponding connecting block 41. During the process of the support structure 3 driving the scaled-down model 4 to slide towards the water surface, the support rod 322 connected to each hanging block 320 abuts against the groove wall of the support groove 411 of the corresponding connecting block 41, ensuring that the pitch angle of the scaled-down model 4 remains stable.

[0058] By connecting the connecting block 41 above the scale model 4, when the scale model 4 is submerged in water, the connecting block 41 will hardly impact the water surface, thus avoiding the connecting block 41 affecting the accuracy of the test results of the scale model 4 being submerged in water.

[0059] In addition, the scaled-down model 4 in this embodiment also has a tendency to slide downwards and detach from the support structure 3. In order to prevent the scaled-down model 4 from detaching from the support structure 3 before the launch operation begins, a spring pin assembly 323 is also installed on the hanging block 320 to prevent the scaled-down model 4 from sliding off the support block 321.

[0060] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0061] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A model support structure suitable for water landing tests of aircraft, characterized in that, It includes a vehicle body that cooperates with a catapult and a bracket for supporting a scaled-down model. The bracket is rotatably connected to the vehicle body, and the axis of rotation between the bracket and the vehicle body is parallel to the sliding trajectory of the vehicle body when it is launched. The bracket and the vehicle body are configured such that when the bracket supporting the scaled-down model is not subjected to external force, the bracket and the vehicle body remain relatively stationary.

2. The model support structure for aircraft water landing tests as described in claim 1, characterized in that, Above the bracket are two first support blocks for supporting the two wings of the scaled-down model and a second support block for supporting the tail. The support blocks are connected to support rods parallel to the pitch axis of the scaled-down model. Below the scaled-down model is a connecting block with the forward direction of the scaled-down model during launch as the front side and the other side as the rear side. The rear side of the connecting block has a support groove adapted to the support rod.

3. A model support structure suitable for aircraft water landing tests as described in claim 2, characterized in that, The connecting block is detachably connected to the scaled-down model, and each of the brackets is detachably connected to the bracket. The bracket is provided with at least two sets of installation positions, and each set of installation positions includes two first bracket installation positions and one second bracket installation position.

4. A model support structure suitable for water landing tests of aircraft as described in claim 2, characterized in that, The support block is also provided with a spring pin assembly for preventing the scaled model from sliding off the support block. The spring pin assembly includes a pin structure that abuts against the scaled model to prevent the scaled model from sliding off the support structure and a spring that pushes the pin structure to keep it in contact with the scaled model. One end of the pin structure is an inclined surface, and it abuts against the scaled model through the inclined surface.

5. A model support structure suitable for water landing tests of aircraft as described in claim 1, characterized in that, Below the bracket are two first hanging blocks for suspending the two wings of the scaled-down model and a second hanging block for suspending the tail. The hanging blocks are connected to support rods parallel to the pitch axis of the scaled-down model. Above the scaled-down model is a connecting block with the forward direction of the scaled-down model during launch as the front side and the other side as the rear side. The rear side of the connecting block has a support groove adapted to the support rod.

6. A model support structure suitable for water landing tests of aircraft as described in claim 5, characterized in that, The connecting block is detachably connected to the scaled-down model, and each of the hanging blocks is detachably connected to the bracket. The bracket is provided with at least two sets of hanging block installation positions, and each set of hanging block installation positions includes two first hanging block installation positions and one second hanging block installation position.

7. A model support structure suitable for water landing tests of aircraft as described in claim 1, characterized in that, When the bracket supports the scaled-down model, the axis of rotation between the bracket and the vehicle body coincides with the roll axis of the scaled-down model.

8. A catapult device suitable for water landing tests of aircraft, characterized in that, The ejection device is suitable for ejecting the model support structure according to any one of claims 1 to 7. The ejection device includes a mounting base with a horizontal reference plane, an ejection slide rail movably connected below the mounting base and with one end facing the pool, a locking and releasing mechanism for locking the support structure before the ejection operation and unlocking the support structure when the ejection operation begins, and an ejection action mechanism for driving the support structure to perform the ejection operation. The ejection action mechanism includes a driving component that applies different ejection forces to the support structure to give it different speeds and an interception component for stopping the support structure so that the scaled model is ejected and detached.

9. A catapult device suitable for water landing tests of aircraft as described in claim 8, characterized in that, The ejection rail includes two hinge points that are directly or indirectly hinged to the mounting base. The hinge axis of each hinge point is a horizontal line perpendicular to the sliding trajectory of the supporting structure. At least one hinge point is hinged to the mounting base through a controlled telescopic module.

10. A catapult device suitable for water landing tests of aircraft as described in claim 8, characterized in that, The two ends of the ejection slide rail are defined as the near-water end and the far-water end, respectively, and the locking release mechanism is located at the far-water end of the ejection slide rail; The drive assembly of the ejection mechanism includes an elastic rope for pulling the support structure to slide from the far end of the ejection rail to the near end, a servo winch for winding the elastic rope, and a winding mechanism for driving the servo winch to rotate. The servo winch rotates in conjunction with the ejection rail. The interception assembly of the ejection mechanism includes an arresting rope connected to the ejection rail. The arresting rope is located on the sliding trajectory of the support structure along the ejection rail.

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