A water non-rotary body aircraft motion simulation rotation acceleration device

Abstract

The application relates to a motion simulation rotary acceleration device for a non-rotary aircraft on water, and belongs to the technical field of aircraft motion acceleration test. The application solves the problem that the existing cylinder type motion acceleration device is not suitable for the motion simulation acceleration of a non-rotary aircraft. The power device and the push seat rebound device are arranged in parallel with each other, one end of the power device and one end of the push seat rebound device are arranged in the axial sliding mode on the connecting shaft on the two sides of the support, the other end of the power device and the other end of the push seat rebound device are fixedly arranged, the aircraft loading platform is arranged in the sliding mode on the slide rail, the connecting piece is connected in the relative rotation mode with the connecting shaft, the piston connecting rod assembly is arranged in the sliding mode in the piston cylinder and connected in the relative rotation mode with the connecting shaft at one end, and the piston cylinder is fixedly arranged and filled with high-pressure gas. The application simultaneously has the simulation acceleration functions of the non-rotary aircraft and the rotary aircraft, the safety of the adjustment process is strengthened, and the operation difficulty is reduced.

Description

Technical Field

[0001] This invention relates to a motion simulation and acceleration device for a non-rotating waterborne aircraft, belonging to the field of aircraft motion acceleration testing technology. Background Technology

[0002] Reciprocating cross-medium aircraft are a new type of aircraft that can fly in the air and navigate underwater, can traverse different media environments of water and air multiple times, survive for a long time, and maintain optimal performance and efficiency in a variety of mission environments. It combines the speed of an aircraft with the stealth of an underwater vehicle, can acquire target information in the air, on the surface and underwater, and has efficient penetration capabilities and multi-mission capabilities, and has attracted much attention in recent years.

[0003] Amphibious cross-medium unmanned aerial vehicles (UAVs) can be categorized into three types based on their operational methods and workspace: surface UAVs, cross-medium surface-launching UAVs, and underwater UAVs. Surface UAVs, also known as sea-skimming UAVs, are high-performance aircraft that utilize the ground effect to navigate at high speeds in the ground effect zone close to the sea surface. Their performance falls between that of aircraft and ships, offering advantages such as safety, reliability, high speed, economy, and practicality. Cross-medium surface-launching UAVs are carried by an underwater platform to facilitate their surface emergence. They are amphibious unmanned systems capable of aerial reconnaissance, target location and surveillance, communication relay, and auxiliary attack missions. They achieve specific speeds through both dry and wet methods. Underwater UAVs are unmanned systems capable of both underwater navigation and aerial flight, with an operational range extending underwater. They possess high independence and autonomous operation capabilities. Research on these amphibious cross-medium UAVs has received considerable attention in recent years, demonstrating their wide range of applications.

[0004] However, current experimental technologies for accelerating small aircraft to specific speeds for water entry or glide jumps primarily utilize rotating aircraft. When non-rotating aircraft are involved, such as the aforementioned reciprocating cross-medium aircraft and amphibious cross-medium unmanned aerial vehicles (UAVs), conventional cylindrical motion acceleration devices are no longer suitable, or their model size and operational space are limited. Due to the special geometric configuration of non-rotating aircraft, the required acceleration device must meet greater space requirements. Compared to rotating aircraft, non-rotating aircraft cannot achieve effective speed acceleration using cylindrical acceleration devices, thus significantly increasing the axial space occupancy of their water acceleration devices. Therefore, it is essential to develop a rotary acceleration system capable of simultaneously accelerating both non-rotating and rotating aircraft in water, without making significant modifications to existing conventional cylindrical motion acceleration devices. Summary of the Invention

[0005] In order to solve the above-mentioned technical problems, the present invention provides a motion simulation and acceleration device for a non-rotating waterborne aircraft.

[0006] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows: A motion simulation and acceleration device for a non-rotating waterborne aircraft includes a motion transmission device and a power unit and a push-and-rebound device arranged on one side of the motion transmission device. The power unit and the push-and-rebound device are arranged parallel to each other. The motion transmission device includes a support and a connecting shaft circumferentially mounted on the support in a horizontal direction. One end of the power unit and one end of the push-and-rebound device are respectively slidably mounted on the connecting shaft on both sides of the support along the axial direction of the connecting shaft. The other end of the power unit and the other end of the push-and-rebound device are fixedly mounted. The push-and-rebound device includes an aircraft mounting platform, a slide rail, and a connecting member. The aircraft mounting platform is slidably mounted on the slide rail, and one end of it is connected to the connecting shaft through the connecting member. The connecting member is rotatably connected to the connecting shaft. The power unit includes a piston cylinder and a piston connecting rod assembly. The piston connecting rod assembly is slidably mounted inside the piston cylinder, and one end of it is rotatably connected to the connecting shaft. The piston cylinder is fixedly mounted and filled with high-pressure gas.

[0007] Furthermore, a fixed limiting block is fixedly installed at the end of the slide rail away from the connecting part.

[0008] Furthermore, the thickness of the fixed limiting block is set to be greater than the diameter of the slide rail.

[0009] Furthermore, the connector is fixed to the upper part of one end of the aircraft platform, and the slide rail is installed through the lower part of the aircraft platform.

[0010] Furthermore, the support is located at the center of the connecting shaft.

[0011] Furthermore, the upper part of the support is a cylindrical rod structure, and two limiting members are provided on it, which are located on the upper and lower sides of the connecting shaft, respectively.

[0012] Furthermore, buffer limiters are fixed at both ends of the connecting shaft.

[0013] Furthermore, two sliding sleeves are slidably sleeved on the connecting shaft along the axial direction, and one end of the connecting member and one end of the piston connecting rod assembly are respectively rotatably connected to the two sliding sleeves.

[0014] Furthermore, each sliding sleeve is radially fixed to its exterior, and one end of the connecting member and one end of the piston rod assembly are rotatably connected to the sliding sleeve via the vertical rod.

[0015] Furthermore, the power unit and the push-base rebound device are arranged symmetrically along the support.

[0016] Compared with the prior art, the present invention has the following advantages: The motion simulation and acceleration device for a non-rotating waterborne aircraft of this invention utilizes the working principle of a crank-slider mechanism to achieve excellent motion transmission and power transmission. When the piston-connecting rod assembly slides within the piston cylinder, the piston-connecting rod assembly acts as a slider, and the piston cylinder acts as a slide rail. The connecting member and the connecting shaft, as well as the piston-connecting rod assembly and the connecting shaft, are rotatably connected. The piston-connecting rod assembly drives the motion transmission device, transmitting motion and power to the other end of the connecting shaft, thus driving the movement of the connecting member and the aircraft platform in the same manner.

[0017] The power unit and the push seat rebound device are arranged on the same side of the motion transmission device, and adopt an asymmetrical rotation structure, which effectively improves the space utilization rate. It cleverly utilizes the same-side motion transmission method, which greatly improves the overall space utilization rate of the device of the present invention. Compared with the opposite-side motion transmission method in the prior art, it ensures transmission efficiency while avoiding the disadvantage of excessive space usage area when the device is in working state due to axial motion sweeping.

[0018] The waterborne non-rotating aircraft motion simulation and acceleration device of the present invention combines the functions of non-rotating aircraft acceleration simulation with those of rotating aircraft acceleration simulation, enhancing the safety of the adjustment process and reducing the difficulty of operation. When accelerating a non-rotating aircraft, there is no need to switch the power output device, i.e., the power unit. On one hand, the rotating aircraft can be built into the piston cylinder, and the piston-connecting rod assembly drives the rotating aircraft to achieve the simulated acceleration process; on the other hand, the non-rotating aircraft can be externally mounted on the aircraft platform, with the acceleration function provided by the power unit.

[0019] The motion simulation and acceleration device for non-rotating watercraft of the present invention only adds some equipment to the original rotating motion acceleration power device, without making major modifications, and can realize the motion acceleration function of both rotating and non-rotating watercraft.

[0020] The connecting parts and the connecting shaft, as well as the piston rod assembly and the connecting shaft, have two degrees of freedom of movement: rotation and sliding, thereby enabling the adjustment of the water entry angle and the rotation arm. Attached Figure Description

[0021] Figure 1 This is a three-dimensional structural schematic diagram of the motion simulation and acceleration device for a non-rotating waterborne aircraft according to the present invention. Figure 2This is a top view schematic diagram of the motion simulation and acceleration device for a non-rotating waterborne aircraft according to the present invention. Figure 3 This is a left cross-sectional schematic diagram of the motion simulation and acceleration device for a non-rotating watercraft according to the present invention. Figure 4 This is a three-dimensional structural diagram of the motion simulation and acceleration device for a non-rotating watercraft of the present invention mounted on a vertical truss. Figure 5 This is a three-dimensional structural diagram of the waterborne non-rotating aircraft motion simulation gyroscopic acceleration device of the present invention in a gyroscopic state.

[0022] In the picture: 1. Motion transmission device; 11. Support; 12. Connecting shaft; 13. Buffer limiter; 14. Sliding sleeve; 15. Vertical rod; 2. Power unit; 21. Piston cylinder; 22. Piston connecting rod assembly; 3. Push seat rebound device; 31. Aircraft mounting platform; 32. Slide rail; 33. Connecting component; 34. Fixed limit block; 102. Vertical truss. Detailed Implementation

[0023] Specific implementation method one: Combining Figures 1-5 This description of embodiments provides a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] It should be noted that the descriptions of "left," "right," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0025] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0026] A motion simulation and acceleration device for a non-rotating waterborne aircraft includes a motion transmission device 1, a power unit 2, and a push-base rebound device 3 arranged on one side of the motion transmission device 1, wherein the power unit 2 and the push-base rebound device 3 are arranged parallel to each other. The motion transmission device 1 includes a support 11 and a connecting shaft 12 that is circumferentially mounted on the support 11 in the horizontal direction. One end of the power unit 2 and one end of the push-seat rebound device 3 are respectively slidably mounted on the connecting shaft 12 on both sides of the support 11 along the axial direction of the connecting shaft 12. The other ends of the power unit 2 and the push-seat rebound device 3 are both fixedly mounted. The push-and-rebound device 3 includes an aircraft mounting platform 31, a slide rail 32, and a connecting member 33. The aircraft mounting platform 31 is slidably mounted on the slide rail 32, and one end of the platform is connected to the connecting shaft 12 via the connecting member 33. The connecting member 33 is rotatably connected to the connecting shaft 12. The power unit 2 includes a piston cylinder 21 and a piston connecting rod assembly 22. The piston connecting rod assembly 22 is slidably installed inside the piston cylinder 21 and one end of it is rotatably connected to the connecting shaft 12. The piston cylinder 21 is fixedly installed and filled with high-pressure gas.

[0027] The device of this invention utilizes the working principle of a crank-slider mechanism to achieve excellent motion transmission and power transmission. When the piston-connecting rod assembly 22 slides within the piston cylinder 21, the piston-connecting rod assembly 22 acts as a slider, and the piston cylinder 21 acts as a slide rail. The connecting member 33 and the connecting shaft 12 are rotatably connected, as are the piston-connecting rod assembly 22 and the connecting shaft 12. The piston-connecting rod assembly 22 drives the motion transmission device 1, transmitting motion and power to the other end of the connecting shaft 12. In the same manner, it drives the movement of the connecting member 33 and the aircraft-mounted platform 31.

[0028] The power unit 2 and the push seat rebound device 3 are arranged on the same side of the motion transmission device 1, and adopt an asymmetrical rotation structure, which effectively improves the space utilization rate. By cleverly utilizing the same-side motion transmission method, the overall space utilization rate of the device of the present invention is greatly improved. Compared with the opposite-side motion transmission method in the prior art, while ensuring transmission efficiency, it effectively avoids the disadvantage of the axial motion sweeping through the space with an excessively large area when the device is in working state.

[0029] The device of this invention combines the functions of simulating acceleration for both non-rotating and rotating aircraft, enhancing the safety of the adjustment process and reducing the difficulty of operation. When accelerating a non-rotating aircraft, there is no need to switch the power output device, i.e., the power unit 2. On one hand, the rotating aircraft can be internally housed in the piston cylinder 21, with the piston-connecting rod assembly 22 driving the rotating aircraft to achieve the simulated acceleration process. On the other hand, the non-rotating aircraft can be externally mounted on the aircraft platform 31, with the acceleration function provided by the power unit 2.

[0030] The device of the present invention only adds some equipment to the original rotary motion acceleration power device 2, without making major modifications, and can realize the motion acceleration function of both rotary and non-rotary aircraft.

[0031] The motion and power are transmitted through the motion transmission device 1. The support 11 is used to install and fix the entire device on its mounting platform. The mounting platform can be an adjustable mounting platform, thereby realizing the adjustability of the aircraft's water landing angle and making the entire adjustment process simpler and safer. The connecting shaft 12 is used as the connecting rod of the entire crank-slider mechanism, and is rotatably connected to the support 11 through a shaft-embedded method.

[0032] The power unit 2 and the push-seat rebound device 3 are arranged in parallel to each other. By adjusting the distance between the power unit 2 and the central axis of the support 11 and the distance between the push-seat rebound device 3 and the central axis of the support 11, the size of the transmission lever arm can be controlled, thereby achieving controllable transmission efficiency.

[0033] The power unit 2 primarily outputs power by controlling the movement of the piston connecting rod assembly 22, and the piston cylinder 21 is fixedly installed to ensure the stability of the entire power unit 2. The piston cylinder 21 is made of a high-temperature and high-pressure resistant material and has good sealing performance.

[0034] The push-seat rebound device 3 mainly realizes the release function after the aircraft accelerates. The aircraft is installed on the aircraft mounting platform 31. The power provided by the power unit 2 is transmitted to the aircraft mounting platform 31 through the connecting shaft 12 and the connecting piece 33, so that it moves at high speed on the slide rail 32. The aircraft release function is realized above the aircraft mounting platform 31 after acceleration by rebounding after impacting the fixed end.

[0035] Support 11 is made of sturdy and thick steel to ensure its stable and reliable quality.

[0036] The working environment of the device of the present invention can be placed on a large platform or on a vertical truss 102. Since some components of the device are involved in rotational motion for a long time and are in a state of sliding friction, it is necessary to apply lubricating oil to them regularly and do a good job of rust prevention.

[0037] The connecting member 33 and the connecting shaft 12, as well as the piston rod assembly 22 and the connecting shaft 12, have two degrees of freedom of movement: rotation and sliding, thereby realizing the adjustment of the water entry angle and the rotation arm.

[0038] A fixed limiting block 34 is fixedly installed at one end of the slide rail 32 away from the connecting member 33. With this design, the other end of the push seat rebound device 3 is fixed by setting the fixed limiting block 34, and the sliding limit position of the aircraft mounting platform 31 is limited.

[0039] The thickness of the fixed limiting block 34 is greater than the diameter of the slide rail 32. This design ensures that when the aircraft platform 31 impacts the fixed limiting block 34, it has sufficient contact area, thereby ensuring the stable rebound of the aircraft platform 31.

[0040] The connector 33 is fixedly mounted on the upper part of one end of the aircraft carrier platform 31, and the slide rail 32 is disposed through the lower part of the aircraft carrier platform 31. This design avoids interference between the connector 33 and the slide rail 32 during the sliding of the aircraft carrier platform 31 along the slide rail 32.

[0041] The support 11 is located in the middle of the connecting shaft 12.

[0042] The upper part of the support 11 is a cylindrical rod structure, and two limiting members are provided on it. The two limiting members are located on the upper and lower sides of the connecting shaft 12, respectively. With this design, the cylindrical rod structure on the upper part of the support 11 realizes the limiting function of the connecting shaft 12 through the two limiting members, so that the connecting shaft 12 can rotate safely and reliably in the horizontal plane.

[0043] Both ends of the connecting shaft 12 are fixedly equipped with buffer limiters 13. This design, by setting two buffer limiters 13, limits the axial limit positions of the power unit 2 and the push seat rebound device 3 on the connecting shaft 12, preventing the power unit 2 or the push seat rebound device 3 from detaching from the connecting shaft 12 during the test, and effectively improving the overall safety of the device.

[0044] Two sliding sleeves 14 are slidably fitted along the axial direction on the connecting shaft 12. One end of the connecting member 33 and one end of the piston rod assembly 22 are respectively rotatably connected to the two sliding sleeves 14. In this design, the sliding sleeves 14 mainly serve as transmission hubs, enabling sliding connections between the power unit 2 and the motion transmission device 1, and between the push seat rebound device 3 and the motion transmission device 1. By setting the connection between one end of the connecting member 33 and the sliding sleeve 14, and between one end of the piston rod assembly 22 and the sliding sleeve 14, it is further ensured that when the connecting shaft 12 rotates circumferentially around the support 11, the sliding sleeves 14 can smoothly slide along the axial direction of the connecting shaft 12. This allows the motion transmission device 1 to drive the aircraft mounting platform 31 and its non-rotating aircraft to slide along the slide rail 32 during the extension and retraction of the piston rod assembly 22 along the piston cylinder 21. The buffer limiters 13 at both ends of the connecting shaft 12 limit the extreme positions of the two sliding sleeves 14.

[0045] In addition, the sliding function of the two sliding sleeves 14 on the connecting shaft 12 enables the adjustment of the lever arm length, giving the motion transmission device 1 a certain range of rotation lever arm adjustment function, thus making the power transmission efficiency controllable to a certain extent.

[0046] Each sliding sleeve 14 is radially fixed with a vertical rod 15. One end of the connecting member 33 and one end of the piston rod assembly 22 are rotatably connected to the sliding sleeve 14 via the vertical rod 15. This design, by setting the vertical rod 15, achieves the rotatable connection between the connecting member 33 and the sliding sleeve 14, as well as the rotatable connection between the piston rod assembly 22 and the sliding sleeve 14, enabling rotation without dead angles in the horizontal plane without being restricted by the movement of other mechanisms.

[0047] The power unit 2 and the push seat rebound device 3 are arranged symmetrically along the support 11.

[0048] Working principle: The power source, typically compressed air, is located in the piston cylinder 21 at a pressure of approximately 8-10 MPa. Both sides of the piston cylinder 21 (allowing for different driving directions) can be connected to an air compressor via hoses. Injecting compressed gas causes it to expand within the cylinder, pushing the piston rod assembly 22 and generating significant acceleration. The piston rod assembly 22 then transmits power to the connecting shaft 12 on the motion transmission device 1 through relative rotation with the sliding sleeve 14. The connecting shaft 12 rotates around the support 11, thereby driving the sliding sleeve 14 at the other end and the connecting piece 33 connected to it. This power is then transmitted to the aircraft carrier platform 31, propelling it forward along the slide rail 32. The aircraft moves along with the carrier platform. Subsequently, the aircraft carrier platform 31 rapidly impacts and rebounds with the fixed limit block 34, releasing the aircraft and completing the entire process of accelerating the model to a specific speed and releasing it into the water.

[0049] 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 equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A motion simulation and acceleration device for a non-rotating waterborne aircraft, characterized in that: The device includes a motion transmission device (1) and a power device (2) and a push-seat rebound device (3) arranged on one side of the motion transmission device (1). The power device (2) and the push-seat rebound device (3) are arranged parallel to each other. The motion transmission device (1) includes a support (11) and a connecting shaft (12) circumferentially mounted on the support (11) in the horizontal direction. One end of the power device (2) and one end of the push-seat rebound device (3) are respectively slidably arranged on the connecting shaft (12) on both sides of the support (11) along the axial direction of the connecting shaft (12). The other end of the power device (2) and the other end of the push-seat rebound device (3) are fixedly arranged. The push-seat rebound device (3) includes an aircraft mounting platform (31), a slide rail (32), and a connecting member (33). The aircraft mounting platform (31) is slidably mounted on the slide rail (32), and one end of it is connected to the connecting shaft (12) through the connecting member (33). The connecting member (33) is rotatably connected to the connecting shaft (12). The power unit (2) includes a piston cylinder (21) and a piston connecting rod assembly (22). The piston connecting rod assembly (22) is slidably mounted inside the piston cylinder (21), and one end of it is rotatably connected to the connecting shaft (12). The piston cylinder (21) is fixedly mounted, and the piston cylinder (21) is filled with high-pressure gas. When it is necessary to simulate the acceleration process of a rotating aircraft, the rotating aircraft is built into the piston cylinder and driven by the piston-connecting rod assembly; when it is necessary to simulate the acceleration process of a non-rotating aircraft, the non-rotating aircraft is placed on the aircraft platform and the acceleration function is provided by the power unit. Two sliding sleeves (14) are slidably sleeved on the connecting shaft (12) along the axial direction. One end of the connecting member (33) and one end of the piston connecting rod assembly (22) are respectively rotatably connected to the two sliding sleeves (14).

2. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: A fixed limiting block (34) is fixedly installed on one end of the slide rail (32) away from the connecting member (33).

3. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 2, characterized in that: The thickness of the fixed limiting block (34) is greater than the diameter of the slide rail (32).

4. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: The connector (33) is fixedly mounted on the upper part of one end of the aircraft carrier platform (31), and the slide rail (32) is installed through the lower part of the aircraft carrier platform (31).

5. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: The support (11) is located in the middle of the connecting shaft (12).

6. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: The upper part of the support (11) is a round rod structure, and two limiting members are provided on it. The two limiting members are located on the upper and lower sides of the connecting shaft (12), respectively.

7. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: Both ends of the connecting shaft (12) are fixed with buffer limiters (13).

8. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 7, characterized in that: Each sliding sleeve (14) is fixed with a vertical rod (15) along its radial direction. One end of the connecting member (33) and one end of the piston connecting rod assembly (22) are rotatably connected to the sliding sleeve (14) through the vertical rod (15).

9. The motion simulation and acceleration device for a non-rotating waterborne aircraft according to claim 1, characterized in that: The power unit (2) and the push seat rebound device (3) are arranged symmetrically along the support (11).

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