Rocket attitude intelligent perception device

Abstract

The application provides a rocket attitude intelligent sensing device, and relates to the technical field of rockets.The rocket attitude intelligent sensing device comprises a shell, a three-axis acceleration sensor arranged in the shell, a three-axis gyroscope arranged in the shell, a magnetometer arranged in the shell, an air pressure sensor arranged in the shell, and a buffer device arranged on one side of the shell.The buffer device can buffer the shell and the rocket when the rocket vibrates, thereby reducing the influence of the rocket vibration on the fixed connection between the shell and the rocket, improving the use effect of the multiple sensors in the shell, and further improving the use effect of the attitude intelligent sensing device.The fixed assembly can quickly fix the connecting frame to one side of the shell, and then facilitate the subsequent use of the buffer plate.The auxiliary assembly uses a rubber plate to replace the buffer plate and the rocket to contact and wear, thereby prolonging the service life of the buffer plate.

Description

Technical Field

[0001] This invention relates to the field of rockets, and in particular to an intelligent attitude sensing device for rockets. Background Technology

[0002] An intelligent posture sensing device is a technical device used to monitor and provide feedback on the posture state of an object in real time. It can accurately capture the position, orientation, and motion state of an object in three-dimensional space.

[0003] During artificial rainmaking, rockets are launched into the clouds. Before launch, an internal attitude sensing device automatically calibrates sensors and initializes the attitude baseline. After launch, a high overload triggers the sensors inside the casing to activate. A three-axis accelerometer, a three-axis gyroscope, a magnetometer, and a barometer simultaneously collect data. This data is then fused and processed by an internal control module to calculate precise attitude angles and altitude information. When the data matches a preset catalytic threshold, the agent dispensing device is automatically triggered, and the attitude data is transmitted back to the ground station in real time via a wireless module inside the casing. However, when the casing is fixed inside the rocket, it is prone to significant vibrations during rocket movement, causing the casing's fixing structure to loosen. This can affect the operation of the internal sensors, thus impacting the effectiveness of the attitude sensing device. Summary of the Invention

[0004] The technical problem to be solved by this invention is that when the outer shell is fixed inside the rocket, it is prone to large vibrations when the rocket moves and is subjected to force, and then the fixing structure of the outer shell becomes loose, which affects the use of the sensors inside the outer shell, thus affecting the performance of the attitude intelligent sensing device.

[0005] The technical solution adopted by the present invention to solve its technical problem is: a rocket attitude intelligent sensing device, including a shell, a three-axis accelerometer, a three-axis gyroscope, a magnetometer, and a pressure sensor inside the shell, and a buffer device on one side of the shell, the buffer device cushioning the force on the shell through a buffer plate and a spring.

[0006] The aforementioned components achieve the following effects: During artificial rainmaking, rockets are launched into the clouds to induce rain. Before launch, the internally installed intelligent attitude sensing device automatically completes sensor calibration and attitude baseline initialization. After launch, high overload triggers the sensors inside the outer shell to wake up. At this time, a buffer device is used to buffer and protect the outer shell from vibration when the rocket is vibrating. Then, the three-axis accelerometer, three-axis gyroscope, magnetometer, and barometer simultaneously collect data. After being fused and processed by the internal control module, accurate attitude angle and altitude information are calculated. When the data matches the preset catalytic threshold, the agent dispensing device is automatically triggered, and the attitude data is transmitted back to the ground station in real time through the wireless module inside the outer shell.

[0007] Preferably, the buffer device includes a fixing component, a connecting frame, a spring, and a buffer plate. The fixing component is disposed on one side of the outer shell and fixes the connecting frame to the side of the outer shell. The two ends of the spring are respectively connected to the connecting frame and the buffer plate. The size of the buffer plate is adapted to the size of the rocket.

[0008] The aforementioned components achieve the following effects: Before the outer shell is installed onto the rocket, a fixed assembly on the surface secures the connecting bracket to the outer shell surface. Then, buffer plates are fixed around the perimeter of the outer shell surface. After the outer shell is fixedly installed inside the rocket, the buffer plates contact the inner wall of the rocket. Springs fixed to the buffer plates and connecting brackets ensure the buffer plates fit snugly against the inner wall of the rocket. When the rocket moves and vibrates, the buffer plates shift, allowing the springs to deform and absorb the vibration force, thus buffering the force on the outer shell and reducing the impact of rocket vibration on the outer shell and internal components. By using this buffering device, when the rocket vibrates, there is a buffer between the outer shell and the rocket, reducing the impact of rocket vibration on the fixed connection between the outer shell and the rocket. This improves the effectiveness of the multiple sensors inside the outer shell, thereby enhancing the effectiveness of the attitude intelligent sensing device.

[0009] Preferably, a telescopic rod is fitted inside the spring, and the two ends of the telescopic rod are connected to the connecting frame and the buffer plate, respectively.

[0010] The above components achieve the following effects: the telescopic rod is connected and fixed to the connecting frame and the buffer plate at both ends, and the telescopic rod is sleeved inside the spring to restrict the shape of the spring and prevent the spring from bending and affecting its use. In addition, the damping setting inside the telescopic rod attenuates the high-frequency vibration energy through friction damping during the spring's extension and contraction.

[0011] Preferably, the fixing component includes a fixing block and a first bolt. The fixing block is disposed on one side of the housing, and the first bolt is inserted into one side of the fixing block and threadedly fixed to the connecting frame.

[0012] The effect achieved by the above components is as follows: when fixing the connecting frame, the connecting frame is placed inside the fixing block fixed on one side of the outer shell, and then the first bolt is rotated and inserted into the fixing block on one side to be threaded and fixed with the connecting frame. Then the position of the connecting frame on the side of the outer shell is quickly fixed. By using the fixing components, the connecting frame can be quickly fixed to the side of the outer shell, which facilitates the subsequent use of the buffer plate.

[0013] Preferably, inclined grooves are provided on both sides of the fixing block to increase the size of the fixing block entrance.

[0014] The effect achieved by the above components is that by opening inclined grooves on both sides of the fixing block, the size of the entry point of the fixing block is increased, making it easier for the connecting block to be inserted into the fixing block.

[0015] Preferably, the buffer plate has an auxiliary component on the side away from the spring. The auxiliary component includes a second bolt, a mounting plate, and a rubber plate. The second bolt is inserted into one side of the mounting plate and threadedly connected to the buffer plate. The rubber plate is disposed on one side of the mounting plate, and the size of the rubber plate is adapted to the size of the buffer plate.

[0016] The effect achieved by the above components is as follows: When using the auxiliary components, the rubber plate is moved so that the mounting plate fixed on one side of the rubber plate contacts the buffer plate. Then, the second bolt is rotated so that it is inserted into the mounting plate and threaded to the buffer plate, thus fixing the position of the rubber plate. Then, the rubber plate is used to replace the buffer plate and the rocket for wear. By using the auxiliary components, the rubber plate replaces the buffer plate and the rocket for contact wear, thereby improving the service life of the buffer plate.

[0017] Preferably, a reinforcing plate is provided on one side of the mounting plate, and one side of the reinforcing plate is connected to the rubber plate.

[0018] The effect achieved by the above components is to improve the connection strength between the mounting plate and the rubber plate by fixing the reinforcing plate to the rubber plate and the mounting plate, thereby preventing the mounting plate and the rubber plate from separating under stress.

[0019] Preferably, a positioning block is provided on one side of the buffer plate to position the mounting plate.

[0020] The effect achieved by the above components is as follows: by fixing the positioning block to one side of the buffer plate, the position of the mounting plate on the surface of the buffer plate is positioned, and then it is convenient for the operator to use the second bolt to fix the mounting plate.

[0021] In summary, the beneficial effects of the present invention are as follows: By using a buffer device, when the rocket vibrates, the outer shell and the rocket can be buffered, reducing the impact of the rocket vibration on the fixed connection between the outer shell and the rocket, thereby improving the performance of multiple sensors inside the outer shell, and thus improving the performance of the attitude intelligent sensing device.

[0022] By using the fixing components, the connecting bracket can be quickly fixed to one side of the housing, which facilitates the subsequent use of the buffer plate.

[0023] By using auxiliary components, a rubber plate is used instead of a buffer plate to avoid contact wear with the rocket, thereby extending the service life of the buffer plate. Attached Figure Description

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0025] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 For the present invention Figure 1 A schematic diagram of a partial three-dimensional structure; Figure 3 This is a three-dimensional structural diagram of the buffer device of the present invention; Figure 4 For the present invention Figure 3 A schematic diagram of a partial three-dimensional structure; Figure 5 For the present invention Figure 4 Enlarged view of point A; Figure 6 This is the control flowchart of the present invention.

[0026] Legend: 1. Housing; 2. Three-axis accelerometer; 3. Three-axis gyroscope; 4. Magnetometer; 5. Barometric pressure sensor; 6. Buffer device; 61. Fixing component; 611. Fixing block; 612. First bolt; 613. Inclined groove; 62. Connecting frame; 63. Spring; 64. Buffer plate; 65. Telescopic rod; 66. Auxiliary component; 661. Second bolt; 662. Mounting plate; 663. Rubber plate; 664. Reinforcing plate; 665. Positioning block. Detailed Implementation

[0027] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" or "linked" should be interpreted broadly. For example, it can refer to a fixed connection, a detachable connection, or an integral connection; it can refer to a mechanical connection or an electrical connection; it can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0029] Figures 1 to 6 The rocket attitude intelligent sensing device shown includes a shell 1, a three-axis accelerometer 2, a three-axis gyroscope 3, a magnetometer 4, and a pressure sensor 5 inside the shell 1. A buffer device 6 is provided on one side of the shell 1. The buffer device 6 buffers the force on the shell 1 through a buffer plate 64 and a spring 63.

[0030] Figures 1 to 6 As shown, during artificial rainmaking, rockets are launched into the clouds to induce rain. Before the rockets are launched, the internal intelligent attitude sensing device automatically completes sensor calibration and attitude baseline initialization. After launch, the high overload triggers the sensors inside the outer shell 1 to wake up. At this time, the buffer device 6 is used to buffer and protect the outer shell 1 from the rocket when it vibrates. Then, the three-axis accelerometer 2, the three-axis gyroscope 3, the magnetometer 4, and the barometer 5 simultaneously collect data. After being fused and processed by the internal control module, the accurate attitude angle and altitude information are calculated. When the data matches the preset catalytic threshold, the agent dispensing device is automatically triggered, and the attitude data is transmitted back to the ground station in real time through the wireless module inside the outer shell 1.

[0031] Figures 1 to 6 The buffer device 6 shown includes a fixing component 61, a connecting frame 62, a spring 63, and a buffer plate 64. The fixing component 61 is located on one side of the outer shell 1 and fixes the connecting frame 62 to one side of the outer shell 1. The two ends of the spring 63 are connected to the connecting frame 62 and the buffer plate 64 respectively. The size of the buffer plate 64 is adapted to the size of the rocket.

[0032] Figures 1 to 6As shown, before the outer shell 1 is installed onto the rocket, a fixing component 61 is fixed to the surface of the outer shell 1, and a buffer plate 64 is fixed around the surface of the outer shell 1. After the outer shell 1 is fixedly installed into the rocket, the buffer plate 64 contacts the inner wall of the rocket. At this time, the spring 63 fixed to the buffer plate 64 and the connecting frame 62 keeps the buffer plate 64 in close contact with the inner wall of the rocket. When the rocket moves and vibrates, the buffer plate 64 is displaced, allowing the spring 63 to deform and absorb the vibration force, thus buffering the force on the outer shell 1 and reducing the impact of rocket vibration on the outer shell 1 and internal components. By using the buffer device 6, when the rocket vibrates, the outer shell 1 and the rocket can be buffered, reducing the impact of rocket vibration on the fixed connection between the outer shell 1 and the rocket, thereby improving the performance of multiple sensors inside the outer shell 1 and thus improving the performance of the attitude intelligent sensing device.

[0033] Figures 1 to 6 The spring 63 shown has a telescopic rod 65 fitted inside it. Both ends of the telescopic rod 65 are connected to the connecting frame 62 and the buffer plate 64, respectively. The telescopic rod 65 is fixed to the connecting frame 62 and the buffer plate 64 by connecting and fixing both ends of the telescopic rod 65 to the spring 63, thus limiting the shape of the spring 63 and preventing it from bending and affecting its use. Furthermore, the damping mechanism inside the telescopic rod 65 attenuates high-frequency vibration energy through frictional damping during the extension and retraction of the spring 63.

[0034] Figures 1 to 6 The fixing component 61 shown includes a fixing block 611 and a first bolt 612. The fixing block 611 is disposed on one side of the outer casing 1, and the first bolt 612 is inserted into one side of the fixing block 611 and threadedly fixed to the connecting frame 62. When fixing the connecting frame 62, the connecting frame 62 is inserted into the fixing block 611 fixed on one side of the outer casing 1, and then the first bolt 612 is rotated, using the first bolt 612 inserted into one side of the fixing block 611 and threadedly fixed to the connecting frame 62. This quickly completes the fixing of the connecting frame 62 to one side of the outer casing 1. By using the fixing component 61, the connecting frame 62 can be quickly fixed to one side of the outer casing 1, facilitating subsequent use of the buffer plate 64. Sloping grooves 613 are formed on both sides of the fixing block 611 to increase the size of the entrance of the fixing block 611. By forming sloping grooves 613 on both sides of the fixing block 611, the size of the entrance of the fixing block 611 is increased, making it easier for the connecting block to be inserted into the fixing block 611.

[0035] Figures 1 to 6The buffer plate 64 shown is provided with an auxiliary component 66 on the side away from the spring 63. The auxiliary component 66 includes a second bolt 661, a mounting plate 662, and a rubber plate 663. The second bolt 661 is inserted into one side of the mounting plate 662 to be threadedly connected to the buffer plate 64. The rubber plate 663 is located on one side of the mounting plate 662, and the size of the rubber plate 663 is adapted to the size of the buffer plate 64. When using the auxiliary component 66, the rubber plate 663 is moved so that the mounting plate 662 fixed on one side of the rubber plate 663 contacts the buffer plate 64. Then, the second bolt 661 is rotated so that the second bolt 661 is inserted into one side of the mounting plate 662 and threadedly fixed to the buffer plate 64. This completes the fixation of the position of the rubber plate 663. Then, the rubber plate 663 is used to replace the buffer plate 64 in contact wear with the rocket. By using the auxiliary component 66, the rubber plate 663 replaces the buffer plate 64 in contact wear with the rocket, thereby improving the service life of the buffer plate 64.

[0036] Figures 1 to 6 The mounting plate 662 shown has a reinforcing plate 664 on one side, which is connected to the rubber plate 663. The reinforcing plate 664 is fixedly connected to the rubber plate 663 and the mounting plate 662 to increase the connection strength between them and prevent separation under stress. A positioning block 665 is provided on one side of the buffer plate 64 to position the mounting plate 662. The positioning block 665 is fixed to one side of the buffer plate 64 to position the mounting plate 662 on its surface, facilitating subsequent fixation of the mounting plate 662 by the operator using the second bolt 661.

[0037] Working principle: During artificial rainmaking, rockets are launched into the clouds. Before launch, the internal intelligent attitude sensing device automatically completes sensor calibration and attitude reference initialization. After launch, high overload triggers the sensors inside the outer shell 1 to wake up. At this time, the buffer device 6 is used to buffer and protect the outer shell 1 from the rocket when it vibrates. Then, the three-axis accelerometer 2, three-axis gyroscope 3, magnetometer 4, and barometer 5 simultaneously collect data. After being fused and processed by the internal control module, the accurate attitude angle and altitude information are calculated. When the data matches the preset catalytic threshold, the agent dispensing device is automatically triggered, and the attitude data is transmitted back to the ground station in real time through the wireless module inside the outer shell 1. Before the outer shell 1 is installed onto the rocket, the fixing component 61 fixed to the surface of the outer shell 1 fixes the connecting bracket 62 to the surface of the outer shell 1. Then, the buffer plate 64 is fixed around the surface of the outer shell 1. After the outer shell 1 is fixedly installed into the rocket, the buffer plate 64 contacts the inner wall of the rocket. At this time, the spring 63 fixed to the buffer plate 64 and the connecting bracket 62 keeps the buffer plate 64 in close contact with the inner wall of the rocket. When the rocket moves and vibrates, the buffer plate 64 is displaced, so that the spring 63 deforms to absorb the force of the vibration, thus buffering the force on the outer shell 1 and reducing the impact of the rocket vibration on the outer shell 1 and internal components. By using the buffer device 6, when the rocket vibrates, the outer shell 1 and the rocket can be buffered, reducing the impact of the rocket vibration on the fixed connection between the outer shell 1 and the rocket, thereby improving the use effect of multiple sensors inside the outer shell 1, and thus improving the use effect of the attitude intelligent sensing device.

[0038] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any other way. Any person skilled in the art may utilize the disclosed technical content to make changes or equivalent variations to other fields. However, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the present invention, shall still fall within the protection scope of the present invention. In the description of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" 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 mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in the present invention can be understood through specific circumstances.

Claims

1. A rocket attitude intelligent sensing device, characterized in that: Includes a housing (1), inside which is a three-axis accelerometer (2), inside which is a three-axis gyroscope (3), inside which is a magnetometer (4), inside which is a barometric pressure sensor (5), and on one side of the housing (1) is a buffer device (6), the buffer device (6) buffers the force on the housing (1) through a buffer plate (64) and a spring (63).

2. The intelligent attitude sensing device for rockets according to claim 1, characterized in that: The buffer device (6) includes a fixing component (61), a connecting frame (62), a spring (63) and a buffer plate (64). The fixing component (61) is located on one side of the outer shell (1) to fix the connecting frame (62) to one side of the outer shell (1). The two ends of the spring (63) are connected to the connecting frame (62) and the buffer plate (64) respectively. The size of the buffer plate (64) is adapted to the size of the rocket.

3. The intelligent attitude sensing device for rockets according to claim 2, characterized in that: The spring (63) is fitted with a telescopic rod (65), and the two ends of the telescopic rod (65) are connected to the connecting frame (62) and the buffer plate (64) respectively.

4. The rocket attitude intelligent sensing device according to claim 3, characterized in that: The fixing component (61) includes a fixing block (611) and a first bolt (612). The fixing block (611) is disposed on one side of the outer shell (1), and the first bolt (612) is inserted into one side of the fixing block (611) and threadedly fixed to the connecting frame (62).

5. The intelligent attitude sensing device for rockets according to claim 4, characterized in that: The fixed block (611) has inclined grooves (613) on both sides to increase the size of the entrance of the fixed block (611).

6. The intelligent attitude sensing device for rockets according to claim 5, characterized in that: The buffer plate (64) is provided with an auxiliary component (66) on the side away from the spring (63). The auxiliary component (66) includes a second bolt (661), a mounting plate (662) and a rubber plate (663). The second bolt (661) is inserted into one side of the mounting plate (662) and threadedly connected to the buffer plate (64). The rubber plate (663) is provided on one side of the mounting plate (662), and the size of the rubber plate (663) is adapted to the size of the buffer plate (64).

7. The intelligent attitude sensing device for rockets according to claim 6, characterized in that: The mounting plate (662) has a reinforcing plate (664) on one side, and the reinforcing plate (664) is connected to the rubber plate (663) on one side.

8. The intelligent attitude sensing device for rockets according to claim 7, characterized in that: The buffer plate (64) is provided with a positioning block (665) on one side, which is used to position the mounting plate (662).

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