Damping device suitable for aviation optical fiber inertial navigation

Abstract

The utility model relates to the technical field of aviation optical fiber inertial navigation, in particular to an aviation optical fiber inertial navigation damping device which comprises an IMU mounting plate, mounting holes are formed in the surface of the IMU mounting plate, and a mounting clamping groove is fixedly connected to the surface of the IMU mounting plate. The IMU mounting plate is fixedly connected with the mounting clamping groove, the first damping rubber column is arranged on the upper surface of the mounting clamping groove, the second damping rubber column is arranged on the lower surface of the mounting clamping groove, the damping pressing plate is arranged on the upper surface of the first damping rubber column, and the round hole is formed in the surface of the damping pressing plate. The lower surface of the second damping rubber column is provided with a damping supporting column, the damping supporting column is fixedly connected with the separation blade, and the upper surface of the damping pressing plate is provided with an M6 bolt. According to the novel optical fiber inertial navigation instrument, the negative influence of high-frequency vibration generated by an engine on an optical fiber gyroscope and an accelerometer in the optical fiber inertial navigation instrument when the optical fiber inertial navigation instrument is applied to the aviation field can be effectively reduced; and the navigation accuracy is influenced.

Description

Technical Field

[0001] This utility model relates to the field of fiber optic inertial navigation technology for aviation, specifically a vibration damping device suitable for aviation fiber optic inertial navigation. Background Technology

[0002] The application of fiber optic inertial navigation in the aviation field is mainly reflected in high-precision navigation and flight control. Fiber optic inertial navigation systems rely on high-precision fiber optic gyroscopes and accelerometers to measure the angular velocity and acceleration of objects, thereby determining their position and orientation. They have advantages such as high precision, long lifespan, strong anti-interference ability, small size, light weight, and fast response. These characteristics make fiber optic gyroscopes play a crucial role in aviation navigation, enabling them to accurately measure the attitude, angular velocity, and acceleration of aircraft, providing pilots with accurate flight status information, thereby achieving precise navigation and positioning of aircraft.

[0003] Currently, driven by market demand, the future development direction of fiber optic gyroscopes mainly includes high precision, miniaturization, and low cost. With continuous technological advancements, fiber optic gyroscopes are expected to achieve significant improvements in precision, performance, and cost. However, changes in the external environment, such as temperature fluctuations, vibrations, and shocks, can negatively impact the performance of these sensors, thereby affecting navigation accuracy. Therefore, it is necessary to design a shock absorption device to eliminate these negative impacts. Utility Model Content

[0004] The purpose of this invention is to provide a vibration damping device suitable for aviation fiber optic inertial navigation, in order to solve the problem mentioned in the background art that changes in the external environment, such as temperature fluctuations, vibrations and shocks, can negatively affect the performance of these sensors and thus affect the accuracy of navigation.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a vibration damping device suitable for aviation fiber optic inertial navigation, comprising an IMU mounting plate, wherein the surface of the IMU mounting plate is provided with mounting holes, and the surface of the IMU mounting plate is fixedly connected with a mounting slot, wherein a first vibration damping rubber column is provided on the upper surface of the mounting slot, and a second vibration damping rubber column is provided on the lower surface of the mounting slot, wherein a vibration damping pressure plate is provided on the upper surface of the first vibration damping rubber column, and the surface of the vibration damping pressure plate is provided with a circular hole, wherein a vibration damping support is provided on the lower surface of the second vibration damping rubber column, wherein a baffle is fixedly connected to the lower end of the vibration damping support, and an M6 bolt is provided on the upper surface of the vibration damping pressure plate.

[0006] Preferably, the IMU mounting plate is made of aluminum alloy, and the mounting holes are evenly distributed in four groups on the surface of the IMU mounting plate.

[0007] Preferably, the mounting slots are arranged in four groups evenly distributed on the side of the IMU mounting plate.

[0008] Preferably, the first and second shock-absorbing rubber posts are movably embedded in the surface of the mounting slot, and the first and second shock-absorbing rubber posts are made of silicone rubber.

[0009] Preferably, the inner surface of the shock-absorbing pressure plate is threaded, and four sets of round holes are evenly distributed on the side of a set of the shock-absorbing pressure plates. The shock-absorbing pressure plates are made of 304 stainless steel and are in the shape of round plates.

[0010] Preferably, the shock-absorbing support column is cylindrical in shape, and the shock-absorbing support column passes through the mounting slot, the first shock-absorbing rubber column and the second shock-absorbing rubber column. The shock-absorbing support column and the shock-absorbing pressure plate are threaded together. The baffle is circular in shape, and the shock-absorbing support column and the baffle are made of 304 stainless steel.

[0011] Preferably, the M6 ​​bolt passes through the mounting slot, the first damping rubber column, the second damping rubber column, the damping pressure plate, the damping support column, and the baffle, and the M6 ​​bolt and the damping support column are threaded together.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] 1. The IMU mounting plate has mounting holes on its surface, and the IMU mounting plate is fixedly connected to the mounting slot. The upper surface of the mounting slot is provided with a first shock-absorbing rubber column, and the lower surface of the mounting slot is provided with a second shock-absorbing rubber column. The upper surface of the first shock-absorbing rubber column is provided with a shock-absorbing pressure plate, and the surface of the shock-absorbing pressure plate is provided with a round hole. The lower surface of the second shock-absorbing rubber column is provided with a shock-absorbing support column, and the shock-absorbing support column is fixedly connected to the baffle. The upper surface of the shock-absorbing pressure plate is provided with an M6 bolt. This new type can effectively reduce the negative impact of high-frequency vibration generated by the engine on the fiber optic gyroscope and accelerometer in the fiber optic inertial navigation instrument when it is used in the aviation field, thereby affecting the accuracy of navigation.

[0014] 2. The IMU mounting plate has mounting holes on its surface, and the IMU mounting plate is fixedly connected to the mounting slot. The upper surface of the mounting slot is provided with a first shock-absorbing rubber column, and the lower surface of the mounting slot is provided with a second shock-absorbing rubber column. The upper surface of the first shock-absorbing rubber column is provided with a shock-absorbing pressure plate, and the surface of the shock-absorbing pressure plate is provided with a round hole. The lower surface of the second shock-absorbing rubber column is provided with a shock-absorbing support column, and the shock-absorbing support column is fixedly connected to the baffle. The upper surface of the shock-absorbing pressure plate is provided with an M6 bolt. This new structure is simple, reliable, and can be installed quickly. At the same time, it adopts a large number of hollow designs, which can reduce the overall weight while ensuring strength. Attached Figure Description

[0015] Figure 1 This is a top-view perspective view of the structure of this utility model;

[0016] Figure 2 This is a front view schematic diagram of the structure of this utility model;

[0017] Figure 3 This is an exploded three-dimensional structural diagram of the present invention;

[0018] Figure 4 This is a partial three-dimensional structural diagram of the IMU mounting plate of this utility model;

[0019] Figure 5 This is a partial three-dimensional schematic diagram of the shock-absorbing rubber column of this utility model;

[0020] Figure 6 This is a partial three-dimensional schematic diagram of the shock-absorbing pressure plate of this utility model;

[0021] Figure 7 This is a partial three-dimensional schematic diagram of the shock-absorbing support structure of this utility model.

[0022] In the diagram: 1. IMU mounting plate; 2. Mounting hole; 3. Mounting slot; 4. First damping rubber column; 5. Second damping rubber column; 6. Damping pressure plate; 7. Round hole; 8. Damping support column; 9. Baffle; 10. M6 bolt. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Please see Figure 1-7 One embodiment provided by this utility model:

[0025] A vibration damping device for aviation fiber optic inertial navigation systems includes an IMU mounting plate 1, primarily made of aluminum alloy with a hollowed-out design to reduce overall weight. Mounting holes 2 are formed on the surface of the IMU mounting plate 1 for fixing the fiber optic IMU. Mounting slots 3 are fixedly connected to the surface of the IMU mounting plate 1 for mounting a vibration damping structure. A first vibration damping rubber post 4, a second vibration damping rubber post 5, a vibration damping pressure plate 6, a vibration damping support post 8, and a baffle 9 constitute the vibration damping structure, effectively reducing the high-frequency emissions generated by the engine during the application of fiber optic inertial navigation instruments in the aviation field. To address the negative impact of vibration on fiber optic gyroscopes and accelerometers in fiber optic inertial navigation instruments, thus affecting navigation accuracy, this invention utilizes M6 bolts 10 for fixation to the outer casing. The overall structure is simple, reliable, and allows for rapid installation. The upper surface of the mounting slot 3 is equipped with a first damping rubber post 4, and the lower surface is equipped with a second damping rubber post 5. Both posts are made of silicone rubber, and their hardness can be customized according to the vibration level. Internal slots in both posts allow for insertion into the IMU mounting plate. 1. The damping pressure plate 6 and damping support column 8 are installed together to achieve the damping effect. In each damping structure, the first damping rubber column 4 and the second damping rubber column 5 are installed in two parts, upper and lower, to enhance the damping effect. The upper surface of the first damping rubber column 4 is provided with the damping pressure plate 6. The damping pressure plate 6 is mainly made of 304 stainless steel to ensure the installation strength requirements. The damping pressure plate 6 is used to compress the first damping rubber column 4, causing the first damping rubber column 4 to deform, thereby achieving the damping effect. The surface of the damping pressure plate 6 has a round hole 7, which is used for locking during installation. The second... The lower surface of the damping rubber column 5 is provided with a damping support column 8. The damping support column 8 is mainly made of 304 stainless steel to ensure the installation strength requirements. The damping support column 8 is used to connect the mounting slot 3, the first damping rubber column 4, the second damping rubber column 5 and the damping pressure plate 6 together. The lower end of the damping support column 8 is fixedly connected with a baffle 9. The baffle 9 is used to install the second damping rubber column 5, squeeze the second damping rubber column 5, and cause the second damping rubber column 5 to deform, thereby achieving the damping effect. The upper surface of the damping pressure plate 6 is provided with an M6 bolt 10. The M6 ​​bolt 10 is used to fix the device to the outer shell.

[0026] Furthermore, the IMU mounting plate 1 is made of aluminum alloy. The IMU mounting plate 1 is mainly made of aluminum alloy and adopts a hollow design in the middle to reduce the overall weight. The mounting holes 2 are evenly distributed in four groups on the surface of the IMU mounting plate 1. The mounting holes 2 are used to fix the fiber optic IMU.

[0027] Furthermore, the mounting slots 3 are evenly distributed in four groups on the side of the IMU mounting plate 1. The mounting slots 3 are used to install the shock absorption structure. The first shock absorption rubber column 4, the second shock absorption rubber column 5, the shock absorption pressure plate 6, the shock absorption support column 8, and the baffle 9 form the shock absorption structure, which effectively reduces the negative impact of the high-frequency vibration generated by the engine on the fiber optic gyroscope and accelerometer in the fiber optic inertial navigation instrument when it is used in the aviation field, thus affecting the accuracy of navigation. It is fixed to the shell with M6 bolts 10. The overall structure is simple, the performance is reliable, and it can be installed quickly.

[0028] Furthermore, the first damping rubber column 4 and the second damping rubber column 5 are movably embedded in the surface of the mounting slot 3. The first damping rubber column 4 and the second damping rubber column 5 are made of silicone rubber. The hardness of the first damping rubber column 4 and the second damping rubber column 5 can be customized according to the vibration level. The first damping rubber column 4 and the second damping rubber column 5 have slots inside, which can be used to install with the IMU mounting plate 1, the damping pressure plate 6, and the damping support column 8 to achieve the damping effect. The first damping rubber column 4 and the second damping rubber column 5 in each damping structure are installed in two parts, upper and lower, to enhance the damping effect.

[0029] Furthermore, the inner surface of the damping plate 6 is threaded, and four sets of round holes 7 are evenly distributed on the side of a set of damping plates 6. The damping plate 6 is made of 304 stainless steel and is in the shape of a round plate. The damping plate 6 is mainly made of 304 stainless steel to ensure the installation strength requirements. The damping plate 6 is used to squeeze the first damping rubber column 4, causing the first damping rubber column 4 to deform, thereby achieving the damping effect. The round holes 7 are used for locking during installation.

[0030] Furthermore, the shock absorber support 8 is cylindrical in shape and passes through the mounting slot 3, the first shock absorber rubber column 4, and the second shock absorber rubber column 5. The shock absorber support 8 and the shock absorber pressure plate 6 are threaded together. The shock absorber support 8 is mainly made of 304 stainless steel to ensure the installation strength requirements. The shock absorber support 8 is used to connect the mounting slot 3, the first shock absorber rubber column 4, the second shock absorber rubber column 5, and the shock absorber pressure plate 6 together. The baffle 9 is circular in shape. The shock absorber support 8 and the baffle 9 are made of 304 stainless steel. The baffle 9 is mainly made of 304 stainless steel to ensure the installation strength requirements. The baffle 9 is used to install the second shock absorber rubber column 5, compress the second shock absorber rubber column 5, and cause the second shock absorber rubber column 5 to deform, thereby achieving the shock absorption effect.

[0031] Furthermore, the M6 ​​bolt 10 passes through the mounting slot 3, the first shock-absorbing rubber column 4, the second shock-absorbing rubber column 5, the shock-absorbing pressure plate 6, the shock-absorbing support column 8, and the baffle 9. The M6 ​​bolt 10 and the shock-absorbing support column 8 are threaded together. The M6 ​​bolt 10 is used to fix the device to the housing.

[0032] Working principle: The first damping rubber column 4 and the second damping rubber column 5 can buffer the vibration of the instrument, which can effectively reduce the negative impact of the high-frequency vibration generated by the engine on the fiber optic gyroscope and accelerometer in the fiber optic inertial navigation instrument when it is used in the aviation field, thus affecting the accuracy of navigation. This new structure is simple, reliable, and can be quickly installed. At the same time, it adopts a large number of hollow designs, which can reduce the overall weight while ensuring strength.

[0033] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A vibration damping device suitable for aviation fiber optic inertial navigation, comprising an IMU mounting plate (1), characterized in that: The surface of the IMU mounting plate (1) is provided with mounting holes (2), and the surface of the IMU mounting plate (1) is fixedly connected with mounting slots (3). The upper surface of the mounting slots (3) is provided with a first shock-absorbing rubber column (4), and the lower surface of the mounting slots (3) is provided with a second shock-absorbing rubber column (5). The upper surface of the first shock-absorbing rubber column (4) is provided with a shock-absorbing pressure plate (6), and the surface of the shock-absorbing pressure plate (6) is provided with a round hole (7). The lower surface of the second shock-absorbing rubber column (5) is provided with a shock-absorbing support column (8), and the lower end of the shock-absorbing support column (8) is fixedly connected with a baffle plate (9). The upper surface of the shock-absorbing pressure plate (6) is provided with an M6 bolt (10).

2. The vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The IMU mounting plate (1) is made of aluminum alloy, and the mounting holes (2) are evenly distributed in four groups on the surface of the IMU mounting plate (1).

3. The vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The mounting slots (3) are evenly distributed in four groups on the side of the IMU mounting plate (1).

4. The vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The first shock-absorbing rubber column (4) and the second shock-absorbing rubber column (5) are movably embedded in the surface of the mounting slot (3), and the first shock-absorbing rubber column (4) and the second shock-absorbing rubber column (5) are made of silicone rubber.

5. A vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The inner surface of the shock-absorbing pressure plate (6) is threaded, and four sets of round holes (7) are evenly distributed on the side of a set of the shock-absorbing pressure plate (6). The shock-absorbing pressure plate (6) is made of 304 stainless steel and is in the shape of a round plate.

6. A vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The shock-absorbing support column (8) is cylindrical in shape. The shock-absorbing support column (8) passes through the mounting slot (3), the first shock-absorbing rubber column (4), and the second shock-absorbing rubber column (5). The shock-absorbing support column (8) and the shock-absorbing pressure plate (6) are threaded together. The baffle plate (9) is circular in shape. The shock-absorbing support column (8) and the baffle plate (9) are made of 304 stainless steel.

7. A vibration damping device suitable for aviation fiber optic inertial navigation according to claim 1, characterized in that: The M6 ​​bolt (10) passes through the mounting slot (3), the first shock-absorbing rubber column (4), the second shock-absorbing rubber column (5), the shock-absorbing pressure plate (6), the shock-absorbing support column (8), and the baffle (9). The M6 ​​bolt (10) and the shock-absorbing support column (8) are threaded together.

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