Floating device for aircraft underwater experiment

Abstract

The invention discloses a floating device for an aircraft underwater experiment. The floating device comprises a shell, and a connecting plug connected with a launcher projectile body is arranged at the bottom of the shell; the core body is mounted in the shell, and the top cover is arranged at the top of the shell; a locking device is arranged between the core body and the bottom of the shell; the core body is connected with the shell through a spring release assembly; an electronic control system is mounted in the core body; an antenna is also arranged in the core body; a communication quick-connection plug is also arranged in the cavity of the core body; data in the projectile body are obtained through the quick connector at the bottom of the shell, the core body for obtaining the data in the projectile body through the communication quick connector and the internal cable is arranged in the shell, the core body automatically floats upwards through cooperation of the locking device and the spring release assembly, and only the core body needs to be fished; the problems that in an existing aircraft underwater experiment, an aircraft projectile body is difficult to fish and position, and projectile body data are difficult to recover are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of underwater experiments on aircraft, and in particular to a buoyancy device for underwater experiments on aircraft. Background Art

[0002] With the widespread demand for cross-medium aircraft in underwater reconnaissance, communications, and military applications, a large number of cross-medium aircraft launch experiments have been conducted. In these experiments, the projectile is launched underwater via a launch system. However, due to the complex underwater environment, projectile positioning is difficult and the high cost of positioning equipment requires manual salvage to obtain sensor data inside the projectile. This salvage process is inefficient and requires a significant amount of manpower and resources to recover the sensor data inside the projectile.

[0003] At present, there is no effective structure to achieve autonomous surfacing of the projectile for easy recovery. Existing buoyancy-driven technologies mostly adopt a single volume control or weight control type, lacking an efficient hybrid regulation mechanism, making it difficult to achieve stable and autonomous surfacing in deep sea or cross-media environments.

[0004] Moreover, the existing buoyancy system is highly dependent on external power and has insufficient energy efficiency. For example, the use of propeller drive consumes a lot of energy, which limits the ability to perform long-term tasks. The existing system also lacks intelligent control and dynamic adjustment functions, and is difficult to adapt to changes in complex underwater environments, which may lead to structural damage during the surfacing process and affect the integrity of the recovered data.

[0005] Therefore, developing a surfacing device for underwater experiments that can achieve autonomous surfacing, reduce recovery costs, and adapt to cross-media environments, quickly recover the experimental data in the launcher body, and ensure the integrity of the recovered data has become a technical need that needs to be urgently addressed. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a buoyancy device for underwater experiments of aircraft, which can solve the problem of recovering internal data of the aircraft body due to the difficulty in salvaging and positioning the aircraft body after the aircraft body is launched.

[0007] In order to solve the above technical problems, the technical solutions adopted by the present invention are as follows.

[0008] A buoyancy device for underwater experiments of aircraft, comprising an outer shell, a connecting plug connected to a transmitter body is provided at the bottom of the outer shell; a core for receiving data inside the body is installed inside the outer shell, and a top cover for sealing the core when not buoyant is provided at the top of the outer shell; a locking device is provided between the core and the bottom of the outer shell; the core and the outer shell are connected by a spring release component that ejects the core out of the outer shell after the core is released; an electronic control system is installed inside the core, and the electronic control system includes a pressure sensor, an accelerometer, a power module and a microprocessor arranged on a circuit board; an antenna for transmitting a positioning signal obtained by the microprocessor is also provided inside the core; a communication quick-connect plug for obtaining data inside the body is also provided in the cavity of the core, the communication quick-connect plug and the connecting connector are connected by an internal cable, and the communication quick-connect plug is in communication connection with the microprocessor; the controlled ends of the locking device are respectively connected to the output ends of the microprocessor, and the output ends of the pressure sensor and the accelerometer are respectively connected to the input ends of the microprocessor.

[0009] The above-mentioned floating device for underwater experiments of aircraft, the locking device is composed of a strong magnet with electricity connecting the core and the shell, and a fuse resistor that disconnects the power circuit of the strong magnet with electricity.

[0010] The above-mentioned buoyancy device for underwater experiments of aircraft, the spring release assembly includes evenly distributed springs, one end of the spring is connected to the bottom end surface inside the shell, and the other end is in contact with the bottom end surface of the core.

[0011] In the above-mentioned buoyancy device for underwater experiments of aircraft, an inwardly concave annular groove is provided on the circumferential side of the upper portion of the core body, and an annular composite material buoyancy module is installed inside the annular groove.

[0012] In the above-mentioned buoyancy device for underwater experiments of aircraft, the composite material buoyancy module is an annular buoyancy rod made by combining hollow glass microspheres with resin.

[0013] The above-mentioned buoyancy device for underwater experiments of aircraft has a cavity provided inside the core body, a partition provided at the lower part of the cavity, and the cavity located below the partition is a buoyancy chamber; a support plate for adjusting the center of gravity of the core body to ensure stable movement of the core body is slidably provided in the cavity above the partition, and the electronic control system is provided on the support plate; an adjustment component for adjusting the position of the support plate is provided between the support plate and the partition.

[0014] The above-mentioned buoyancy device for underwater experiments of aircraft, the adjustment component includes a drive motor arranged on the support plate, the motor shaft of the drive motor is connected to the screw rod, the lower part of the screw rod passes through the partition and is threadedly connected to the nut on the partition.

[0015] The above-mentioned buoyancy device for underwater experiments of aircraft is also provided with a pressurizing port on the top of the shell for inflating air into the interior of the shell to ensure the stability of the core body in the shell.

[0016] The above-mentioned buoyancy device for underwater experiments of aircraft is also provided with a lighting lamp with strong penetrating power on the top of the core body.

[0017] The above-mentioned buoyancy device for underwater experiments of aircraft is also provided with a solar panel on the top of the core body for supplying power to the power module.

[0018] Due to the adoption of the above technical solution, the technical progress achieved by the present invention is as follows.

[0019] The present invention provides a buoyancy device for underwater experiments of aircraft. The data inside the projectile is obtained through a quick connector at the bottom of the shell. A core body is provided inside the shell for obtaining the data inside the projectile body through a communication quick connector and an internal cable. The core body realizes autonomous buoyancy through the coordinated cooperation of a locking device and a spring release assembly. There is no need to spend a lot of manpower and material resources to salvage the launcher projectile itself, only the core body needs to be salvaged. Moreover, the present invention combines an electronic control system integrating a pressure sensor, an accelerometer and a microprocessor for real-time perception and intelligent control, and can realize stable buoyancy of the aircraft efficiently and autonomously in a complex underwater environment. It can also send a positioning signal in time through an antenna to facilitate the salvage of the core body, thereby solving the problems of difficulty in salvaging and positioning the aircraft projectile body and difficulty in recovering projectile body data in current aircraft underwater experiments.

[0020] The present invention achieves autonomous floating through a hybrid buoyancy adjustment mechanism consisting of a composite material buoyancy module and a support plate capable of changing the center of gravity position. During the floating process, timely adjustments can be made according to the core state to ensure that the core always keeps its head upward during the floating process, thereby avoiding damage to the core and ensuring the integrity of the recovered data. The present invention has a simple structure and low cost. Both the outer shell and the core are made of pressure-resistant composite materials and can adapt to the high-pressure environment of the deep sea. Moreover, through the cooperation of the composite material buoyancy module, the adjustment component and the spring release component, energy utilization is optimized and dependence on external power is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the specific structure of the present invention; Figure 2 The figure is a schematic diagram of the specific structure of the present invention installed on the launcher body.

[0022] Among them: 1. Shell, 2. Core, 3. Partition, 4. Buoyancy chamber, 5. Support plate, 6. Drive motor, 7. Screw, 8. Nut, 9. Microprocessor, 10. Ring buoyancy rod, 11. Solar panel, 12. Pressurization port, 13. Antenna, 14. Communication quick connect plug, 15. Connecting plug, 16. Locking device, 17. Spring, 18. Launcher body. DETAILED DESCRIPTION

[0023] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0024] A floating device for underwater experiments on aircraft, such as Figures 1 to 2 As shown, it includes a shell 1, a connecting plug 15 connected to the launcher body 18 is provided at the bottom of the shell 1, a core 2 is installed inside the shell 1, a top cover is provided on the top of the shell 1, and a sealing ring is provided between the top cover and the shell to ensure the sealing of the entire device when the launcher body is launched. A locking device 16 is provided between the core 2 and the bottom of the shell 1 to limit the core 2 in the shell 1 and release the core 2 when it needs to float. The core 2 and the shell 1 are connected by a spring release component that ejects the core out of the shell 1 after the core 2 is released, driving the aircraft body 18 to float.

[0025] The spring release assembly includes evenly distributed springs 17, one end of which is connected to the bottom end surface inside the shell 1, and the other end is connected to the bottom end surface of the core 2. When the core 2 is inside the shell 1, the spring 17 is in a compressed state. At this time, the bottom end surface of the core contacts and compresses the spring. When the core is released, the elastic potential energy of the spring pushes the core out, and the core gradually separates from the spring and floats to the water.

[0026] A cavity is provided inside the core 2 , a partition 3 is provided at the lower part of the cavity, and the cavity below the partition 3 is a buoyancy chamber 4 .

[0027] A support plate 5 for adjusting the center of gravity of the aircraft body 18 is slidingly provided in the cavity above the partition 3. By changing the up and down positions of the support plate 5, the center of gravity of the core body is adjusted to a neutral buoyancy state, so that the head of the core body is always facing upward during the floating process, ensuring its stable operation.

[0028] An O-ring is provided between the supporting plate 5 and the inner wall of the cavity of the core body to ensure that the supporting plate fits tightly against the inner wall of the cavity.

[0029] An electronic control system is installed on the support plate 5. The electronic control system includes a pressure sensor, an accelerometer, a power module and a microprocessor 9 arranged on a circuit board. It can monitor the water pressure, depth and task status in real time and accurately control the floating process according to preset conditions.

[0030] The accelerometer is arranged near the central axis of the core 2 to monitor the changes in speed and acceleration during the floating process and to prevent structural impact.

[0031] An adjustment component for adjusting the position of the support plate is provided between the support plate 5 and the partition 3. The adjustment component includes a drive motor 6 arranged on the support plate 5. The motor shaft of the drive motor 6 is connected to the screw rod 7. The lower part of the screw rod 7 passes through the partition 3 and is threadedly connected to the nut seat 8 on the partition 3. The position of the support plate is adjusted by driving the screw rod to rotate by the drive motor.

[0032] A communication quick-connect plug 14 is also provided in the cavity of the core body 2. The communication quick-connect plug 14 is connected to the connection connector 15 through an internal cable. The communication quick-connect plug 14 is communicated with the microprocessor for collecting sensor data inside the launcher body so that the body data obtained by the core body can be recovered after the core body floats up.

[0033] The supporting plate 5 is also provided with an antenna 13 , which is provided through the top of the core 2 . The positioning signal acquired by the microprocessor can be transmitted through the antenna 13 .

[0034] A seal is provided between the antenna 13 and the top of the core 2 to ensure the sealing of the interior of the core and prevent water from entering and damaging the electronic control system and the drive motor.

[0035] An inwardly concave annular groove is provided on the upper circumference of the core 2, and a composite material buoyancy module is installed inside the annular groove to provide basic positive buoyancy to ensure that the aircraft body has a basic buoyancy margin in the initial state.

[0036] The composite material buoyancy module is an annular buoyancy rod 10 made of hollow glass microspheres and resin.

[0037] The locking device 16 consists of an energized strong magnet and a fuse resistor. When the launcher body is operating normally, the core 2 and the shell 1 are connected and locked by the energized strong magnet. When it is necessary to control the launcher body 18 to float up, the output current is increased to melt the fuse resistor. After the energized strong magnet is powered off, the magnetism disappears and the lock is quickly released. At the same time, the spring 17 releases the stored elastic potential energy, pushing the core body to open the top cover and start floating.

[0038] A pressurizing port 12 for inflating air into the interior of the shell 1 is also provided at the top of the shell 1. Air is inflated into the interior of the shell 1 through the top pressurizing port 12, and the gas diffuses between the core 2 and the shell 1. On the one hand, it plays a role in surrounding and stabilizing the core 2, so that the core is stably located inside the shell, ensuring that the core can be released stably. On the other hand, after the air pressure is increased by inflation, the high-pressure gas between the shell and the core can also play a role in pushing the core 2 to float when the core 2 is released.

[0039] The connecting plug 15 is connected to the data port on the transmitter body 18 through a cable, and is used to obtain data from the sensor inside the transmitter body 18.

[0040] A lighting lamp with strong penetrating power is also provided on the top of the core 2 to facilitate rapid salvage of the core after the core floats up.

[0041] A solar panel 11 is also provided on the top of the core 2 for supplying power to the power module to prevent power exhaustion after the core floats up and affects salvage.

[0042] The outer shell 1 and the core 2 are respectively made of pressure-resistant composite materials, which can withstand the high-pressure environment of the deep sea and ensure the safety of the structure.

[0043] The controlled ends of the driving motor 6 and the locking device 16 are respectively connected to the output ends of the microprocessor, and the output ends of the pressure sensor and the accelerometer are respectively connected to the input ends of the microprocessor.

[0044] The working principle of the present invention is as follows: When the projectile is initially launched, the outer shell is connected to the launcher body through the connecting joint, and the core is inside the outer shell and sealed by the top cover. At the same time, the core will apply a certain compression force to the spring. At this time, the internal data of the projectile body will be transmitted to the communication quick-connect plug through the connecting joint and the internal cable.

[0045] When it is necessary to float, the output current is increased to melt the fuse resistor and stop supplying power to the energized strong magnet. At this time, the magnetism of the energized strong magnet disappears, and the spring releases the stored elastic potential energy, driving the core to push open the top cover and start floating.

[0046] As the core body floats up, the cable between the communication quick-connect plug and the connecting connector is disconnected under the action of thrust, and the core body floats up with the acquired internal data of the launcher body.

[0047] During the floating process, the pressure sensor and accelerometer work in real time to detect the environmental pressure on the core, and detect the changes in speed and acceleration of the core during the floating process, and feed the detection results back to the microprocessor. The microprocessor controls the adjustment component to adjust the center of gravity of the core according to the feedback results to ensure that the core is in a stable working state during the floating process.

[0048] When the antenna inside the core surfaces, a position signal is sent through the antenna so that the core can be quickly salvaged. At the same time, a lighting lamp is set on the top of the core to facilitate the search and salvage of the core and launcher body after the core surfaces at night.

[0049] After the salvage is completed, the internal sensor data of the launcher body can be read through the communication quick-connect plug inside the core, without spending a lot of manpower and material resources to salvage the launcher body.

[0050] The present invention provides a buoyancy device for underwater experiments of aircraft. The data inside the projectile is obtained through a quick connector at the bottom of the shell. A core body is provided inside the shell for obtaining the data inside the projectile body through a communication quick connector and an internal cable. The core body realizes autonomous buoyancy through the coordinated cooperation of a locking device and a spring release assembly. There is no need to spend a lot of manpower and material resources to salvage the launcher projectile itself, only the core body needs to be salvaged. Moreover, the present invention combines an electronic control system integrating a pressure sensor, an accelerometer and a microprocessor for real-time perception and intelligent control, and can realize stable buoyancy of the aircraft efficiently and autonomously in a complex underwater environment. It can also send a positioning signal in time through an antenna to facilitate the salvage of the core body, thereby solving the problems of difficulty in salvaging and positioning the aircraft projectile body and difficulty in recovering projectile body data in current aircraft underwater experiments.

[0051] The present invention achieves autonomous floating through a hybrid buoyancy adjustment mechanism consisting of a composite material buoyancy module and a support plate capable of changing the center of gravity position. During the floating process, timely adjustments can be made according to the core state to ensure that the core always keeps its head upward during the floating process, thereby avoiding damage to the core and ensuring the integrity of the recovered data. The present invention has a simple structure and low cost. Both the outer shell and the core are made of pressure-resistant composite materials and can adapt to the high-pressure environment of the deep sea. Moreover, through the cooperation of the composite material buoyancy module, the adjustment component and the spring release component, energy utilization is optimized and dependence on external power is reduced.

Claims

1. A floating device for underwater experiments on aircraft, characterized by: The invention comprises a shell (1), wherein a connecting plug (15) connected to a launcher body (18) is provided at the bottom of the shell (1); a core (2) for receiving data inside the body is installed inside the shell (1), and a top cover for sealing the core (2) when not floating is provided at the top of the shell (1); a locking device (16) is provided between the core (2) and the bottom of the shell (1); the core (2) and the shell (1) are connected via a spring release component for ejecting the core (2) from the shell (1) after the core (2) is released; an electronic control system is installed inside the core (2), and the electronic control system includes a pressure sensor provided on a circuit board. A sensor, an accelerometer, a power module and a microprocessor (9); an antenna (13) for transmitting a positioning signal obtained by the microprocessor is also provided inside the core (2); a communication quick-connect plug (14) for obtaining data inside the projectile is also provided in the cavity of the core (2); the communication quick-connect plug (14) and the connection connector (15) are connected via an internal cable, and the communication quick-connect plug (14) is communicatively connected to the microprocessor (9); the controlled end of the locking device (16) is respectively connected to the output end of the microprocessor (9), and the output ends of the pressure sensor and the accelerometer are respectively connected to the input end of the microprocessor (9).

2. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: The locking device (16) is composed of a strong magnet connected to the core (2) and the shell (1) and a fuse resistor that disconnects the circuit of the strong magnet.

3. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: The spring release assembly comprises uniformly distributed springs (17), one end of the spring (17) is connected to the inner bottom end surface of the housing (1), and the other end is in contact with the bottom end surface of the core (2).

4. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: An inwardly concave annular groove is provided on the circumferential side of the upper portion of the core body (2), and an annular composite material buoyancy module is installed inside the annular groove.

5. The buoyancy device for underwater experiments on aircraft according to claim 4, characterized in that: The composite material buoyancy module is an annular buoyancy rod (10) made by combining hollow glass microspheres with resin.

6. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: A cavity is provided inside the core (2), a partition (3) is provided at the lower part of the cavity, and the cavity below the partition (3) is a buoyancy chamber (4); a support plate (5) for adjusting the center of gravity of the core (2) to ensure stable movement of the core is slidably provided in the cavity above the partition (3), and an electronic control system is provided on the support plate (5); an adjustment component for adjusting the position of the support plate is provided between the support plate (5) and the partition (3).

7. The buoyancy device for underwater experiments on aircraft according to claim 6, characterized in that: The adjustment assembly comprises a drive motor (6) arranged on a supporting plate (5), a motor shaft of the drive motor (6) being connected to a screw rod (7), a lower portion of the screw rod (7) passing through the partition (3) and being threadedly connected to a nut seat (8) on the partition (3).

8. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: The top of the shell (1) is also provided with a pressurizing port (12) for inflating air into the interior of the shell (1) to ensure the stability of the core (2) in the shell (1).

9. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: A lighting lamp with strong penetrating power is also provided on the top of the core (2).

10. The buoyancy device for underwater experiments on aircraft according to claim 1, characterized in that: A solar panel (11) for supplying power to the power module is also provided on the top of the core (2).

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