CN219912309U - Airborne vibration reduction platform suitable for unmanned platform gravity measurement - Google Patents
Airborne vibration reduction platform suitable for unmanned platform gravity measurement Download PDFInfo
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- CN219912309U CN219912309U CN202320608156.2U CN202320608156U CN219912309U CN 219912309 U CN219912309 U CN 219912309U CN 202320608156 U CN202320608156 U CN 202320608156U CN 219912309 U CN219912309 U CN 219912309U
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- 230000005484 gravity Effects 0.000 title claims abstract description 56
- 238000005259 measurement Methods 0.000 title claims abstract description 31
- 238000009434 installation Methods 0.000 claims abstract description 20
- 230000035939 shock Effects 0.000 claims description 33
- 238000013016 damping Methods 0.000 claims description 20
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 9
- 239000000741 silica gel Substances 0.000 claims description 9
- 229910002027 silica gel Inorganic materials 0.000 claims description 9
- 238000010521 absorption reaction Methods 0.000 description 17
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 5
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- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000012937 correction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 229910052500 inorganic mineral Inorganic materials 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
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Abstract
The utility model relates to a machine-mounted vibration reduction table suitable for unmanned platform gravity measurement, which comprises a vibration reduction module, a gyroscope structure, fixing columns and mounting pad feet, wherein the vibration reduction module is respectively fixed on the upper side and the lower side of each fixing column, the fixing columns are arranged around the vibration reduction module, a plurality of fixing columns are arranged, the gyroscope structure is arranged among the fixing columns, and the mounting pad feet are arranged on the lower side of the vibration reduction module on the lower side. The utility model creates a measuring mode for measuring the vibration parameters of the gravity installation platform; according to the utility model, the combination of the vibration reduction modules is evaluated through the measured platform vibration parameters; the vibration of the gravity meter mounting platform is reduced through the superposition installation of the vibration reduction modules.
Description
Technical Field
The utility model relates to the field of geophysical exploration, in particular to an onboard vibration reduction table suitable for unmanned platform gravity measurement.
Background
The generation of gravitational acceleration of the earth is the presence of earth mass. The gravitational acceleration varies from place to place on the earth, and the cause is that the mass distribution inside the earth is uneven, except for the ellipsoidal shape of the earth. For example, where large iron ores are stored underground, the gravity is greater than the average gravity; if petroleum is stored underground at another place of the scale, the gravity is smaller than the average gravity. The reason for the difference is the difference in density of the subsurface materials. On the ocean, the change in gravity measured on the sea surface is also apparent due to the complex topography and geology of the ocean floor. The phenomenon that the gravity field of the corresponding space changes due to uneven distribution of underground substances is important in military as well as civil mineral exploration and earth science research. Aeronautical gravity measurement is a gravity measurement method in which an aeronautical gravity measurement system is arranged on an airplane to perform continuous measurement. It is not limited by ground traffic conditions, and has higher working efficiency. The principle, method and instrument of aero gravity measurement are basically the same as that of marine gravity measurement, but the disturbance acceleration suffered by the instrument on the plane is several times to tens times larger than that on the ship, and the period is long. The measurement requirements of navigation positioning, altitude, speed and the like in the air are high, and the error of the correction in the early-stage lunar-e (early-stage lunar-e) is large; the static gravity instrument is added with stronger damping, which is easy to cause the abnormal gravity distortion; and the cost is high.
Aeronautical gravity measurement is generally used in areas where ground gravity measurement is difficult to cover, and medium wave gravity information can be obtained, so that the aeronautical gravity measurement is an important direction of gravity development.
Previous airborne gravity measurements were typically used on man-machine, with equipment weights of around 200 kg. At present, the weight of the gravity meter and the gravity meter which is developed to be miniaturized is only less than 25 kg, so that the gravity meter has the foundation which can be installed on a large unmanned plane. However, the large unmanned aerial vehicle vibrates greatly, and the gravity meter measurement technology requires a stable platform without vibration. Therefore, there is a need for a device for reducing vibration of a unmanned aerial vehicle platform suitable for gravity measurement.
The traditional method for measuring the vibration of the unmanned aerial vehicle is mainly based on the vibration attribute in the unmanned aerial vehicle flight control module, but only the vibration parameter of the position of the flight control module is measured instead of the vibration parameter of the platform of the gravity meter, so that the vibration attribute of the installation platform of the gravity meter cannot be reduced according to the vibration parameter in the flight control module, and in short, the measurement positions of the two are greatly different. Furthermore, the flight control module needs to be arranged at the center or the gravity center of the unmanned aerial vehicle and needs to be installed in a sealing mode, so that the flight control module cannot be installed on a gravity instrument carrying platform.
Disclosure of Invention
According to the technical problem, the utility model provides the airborne vibration reduction table for unmanned aerial vehicle gravity measurement, which enables the installation platform to be stable, and has no vibration or very small vibration, in order to solve the vibration of the unmanned aerial vehicle installation miniaturized gravity meter platform position.
The utility model provides an on-vehicle damping platform suitable for unmanned platform gravity measurement, includes damper module, gyroscope structure, fixed column, installation pad foot, both sides are fixed with damper module respectively about the fixed column, the fixed column sets up around damper module, the fixed column is a plurality of, installs gyroscope structure between a plurality of fixed columns, and the installation pad foot is installed to the damper module downside of downside.
The shock absorption module comprises a shock absorption pad upper fixing plate, a shock absorption pad and a shock absorption pad lower fixing plate, wherein the shock absorption pad upper fixing plate is fixed on the shock absorption pad silica gel upper side, and the shock absorption pad lower fixing plate is fixed on the shock absorption pad silica gel lower side.
The damping modules are N groups, and N is more than or equal to 2.
The shock pad is a silica gel shock pad.
The upper shock pad fixing plate, the shock pad and the lower shock pad fixing plate are connected through bolts.
The gyroscope structure comprises a gyroscope and a gyroscope mounting box, wherein the gyroscope is mounted in the gyroscope mounting box, a fixing hole is formed in the gyroscope mounting box, the rear side of the fixing hole is of a threaded structure, the fixing hole is of a T-shaped structure, a fixing bolt is arranged on the rear side of the gyroscope, and the gyroscope is screwed and fixed into the fixing hole through the bolt.
The fixed column comprises a shell and a connecting structure, wherein the shell is of a hollow structure, mounting structures are arranged on the upper side and the lower side of the shell, and the connecting structure is arranged on the upper side of the mounting structure.
The mounting structure comprises a mounting shell, a thread structure and a fixing groove, wherein the mounting shell is of a groove structure, the thread structure is arranged on the outer side of the mounting shell, and the fixing groove is formed in the mounting shell; the connecting structure comprises a damping spring and a rubber damper, wherein the damping spring is sleeved on the rubber damper, and the rubber damper is fixed in the fixing groove through a bolt structure.
The damping module, the gyroscope structure, the fixing column and the mounting pad foot are fixed by screws and structural members. The gyroscope is ensured to be at the center position during installation. The direction of the gyroscope is consistent with the direction of the gravity meter, and the gyroscope is connected with the gravity meter connector through a signal wire. Gyroscopes are important components used to calibrate the orientation of the gravity measurement data. The vibration damping frequencies of the vibration damping pad and the mounting pad foot part of the vibration damping module are required to be measured in the earlier stage to obtain the vibration frequency of the aircraft, and then the proper vibration damping material is rotated according to different vibration frequencies of each aircraft.
The beneficial effects of the utility model are as follows: the utility model creates a measuring mode for measuring the vibration parameters of the gravity installation platform; according to the utility model, the combination of the vibration reduction modules is evaluated through the measured platform vibration parameters; the vibration of the gravity meter mounting platform is reduced through the superposition mounting of the vibration reduction modules; when the gyroscope gravity measuring device is used, the gyroscope gravity meter is tightly arranged on the unmanned aerial vehicle supporting platform through the vibration reduction module, so that the influence of vibration on the gyroscope gravity measurement is reduced; after the gyroscope gravity meter is arranged on the platform and fixed, the shell of the supporting fixed column is removed, so that the weight is reduced; high-precision measurement of the unmanned plane gravity meter is realized.
The fixing column is of a hollow structure, so that the weight of the aircraft is reduced, and the flight requirement of the aircraft is met.
According to the utility model, the rubber shock absorbers are arranged on the upper part and the lower part of the fixed column, so that the shock absorption effect of the fixed column is improved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model.
Fig. 2 is an exploded view of the present utility model.
Fig. 3 is a structural diagram of a fixing column according to the present utility model.
Fig. 4 is a schematic view of an installation structure of the fixing post of the present utility model.
Fig. 5 is a graph of information about rotational vibration of an aircraft on the ground according to the present utility model.
Fig. 6 is a graph of vibration information of an aircraft while flying in the air when the present utility model is in use.
As shown in the figure, a shock pad upper fixing plate 1, a shock pad 2, a shock pad lower fixing plate 3, fixing columns 4, a gyroscope 5, a gyroscope mounting box 6 and mounting pad feet 7.
Detailed Description
The following description of the embodiments of the present utility model will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the utility model are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the description of the present utility model, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present utility model, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art. In addition, the technical features of the different embodiments of the present utility model described below may be combined with each other as long as they do not collide with each other.
Example 1
The utility model relates to a machine-mounted vibration reduction table suitable for unmanned platform gravity measurement, which comprises a vibration reduction module, a gyroscope structure, fixing columns and mounting pad feet, wherein the vibration reduction module is respectively fixed on the upper side and the lower side of each fixing column, the fixing columns are arranged around the vibration reduction module, a plurality of fixing columns are arranged, the gyroscope structure is arranged among the fixing columns, and the mounting pad feet are arranged on the lower side of the vibration reduction module on the lower side. The shock absorption module comprises a shock absorption pad upper fixing plate, a shock absorption pad and a shock absorption pad lower fixing plate, wherein the shock absorption pad upper fixing plate is fixed on the shock absorption pad silica gel upper side, and the shock absorption pad lower fixing plate is fixed on the shock absorption pad silica gel lower side. The damping modules are N groups, and N is more than or equal to 2. The shock pad is a silica gel shock pad. The upper shock pad fixing plate, the shock pad and the lower shock pad fixing plate are connected through bolts. The gyroscope structure comprises a gyroscope and a gyroscope mounting box, wherein the gyroscope is mounted in the gyroscope mounting box, a fixing hole is formed in the gyroscope mounting box, the rear side of the fixing hole is of a threaded structure, the fixing hole is of a T-shaped structure, a fixing bolt is arranged on the rear side of the gyroscope, and the gyroscope is screwed and fixed into the fixing hole through the bolt. The fixed column comprises a shell and a connecting structure, wherein the shell is of a hollow structure, mounting structures are arranged on the upper side and the lower side of the shell, and the connecting structure is arranged on the upper side of the mounting structure. The mounting structure comprises a mounting shell, a thread structure and a fixing groove, wherein the mounting shell is of a groove structure, the thread structure is arranged on the outer side of the mounting shell, and the fixing groove is formed in the mounting shell; the connecting structure comprises a damping spring and a rubber damper, wherein the damping spring is sleeved on the rubber damper, and the rubber damper is fixed in the fixing groove through a bolt structure.
After weighing, the utility model has excessive weight, so that the whole system is optimized and the weight is properly reduced. So as to meet the requirement of the aircraft on the take-off weight of less than 95 kg. The weight was eventually reduced from 94 kg to 91.5 kg. The takeoff weight of the aircraft is satisfied.
Example 2
When the vibration measuring device is used, firstly, the vibration condition of the aircraft is measured by using the vibration measuring instrument. The utility model is fixed at the center of plane plate of plane by hard screw, and records the rotation of plane on ground and vibration information curve (see figure) when flying in air.
The foregoing has shown and described the basic principles and main features of the present utility model and the advantages of the present utility model. Various components mentioned in the present utility model are common in the art, and it should be understood by those skilled in the art that the present utility model is not limited by the above embodiments, and the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications can be made in the present utility model without departing from the spirit and scope of the utility model, which is defined in the claims. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (8)
1. The utility model provides a machine carries damping platform suitable for unmanned platform gravity measurement, its characterized in that includes damper module, gyroscope structure, fixed column, installation pad foot, both sides are fixed with damper module respectively about the fixed column, the fixed column sets up around damper module, the fixed column is a plurality of, installs gyroscope structure between a plurality of fixed columns, and the installation pad foot is installed to damper module downside of downside.
2. The airborne vibration reduction table suitable for unmanned platform gravity measurement according to claim 1, wherein the vibration reduction module comprises a vibration reduction pad upper fixing plate, a vibration reduction pad and a vibration reduction pad lower fixing plate, the vibration reduction pad upper fixing plate is fixed on the upper side of the vibration reduction pad silica gel, and the vibration reduction pad lower fixing plate is fixed on the lower side of the vibration reduction pad silica gel.
3. An airborne vibration damping table suitable for unmanned platform gravity measurement according to claim 2, wherein the vibration damping modules are of N groups, N being greater than or equal to 2.
4. An airborne vibration-damping mount adapted for use in unmanned platform gravity measurement according to claim 2, wherein said shock pad is a silica gel shock pad.
5. An airborne vibration-damping bench suitable for use in unmanned platform gravity measurement according to claim 2, wherein said upper damper plate, said damper and said lower damper plate are connected by bolts.
6. The airborne vibration reduction table suitable for unmanned platform gravity measurement according to claim 1, wherein the gyroscope structure comprises a gyroscope and a gyroscope installation box, the gyroscope is installed in the gyroscope installation box, a fixing hole is formed in the gyroscope installation box, the rear side of the fixing hole is of a threaded structure, the fixing hole is of a T-shaped structure, a fixing bolt is arranged on the rear side of the gyroscope, and the gyroscope is screwed into the fixing hole through the bolt.
7. The airborne vibration reduction table suitable for unmanned platform gravity measurement according to claim 1, wherein the fixed column comprises a shell and a connecting structure, the shell is of a hollow structure, mounting structures are arranged on the upper side and the lower side of the shell, and the connecting structure is arranged on the upper side of the mounting structure.
8. The airborne vibration reduction platform suitable for unmanned platform gravity measurement according to claim 7, wherein the installation structure comprises an installation shell, a thread structure and a fixing groove, the installation shell is of a groove structure, the thread structure is arranged on the outer side of the installation shell, and the fixing groove is arranged in the installation shell; the connecting structure comprises a damping spring and a rubber damper, wherein the damping spring is sleeved on the rubber damper, and the rubber damper is fixed in the fixing groove through a bolt structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320608156.2U CN219912309U (en) | 2023-03-25 | 2023-03-25 | Airborne vibration reduction platform suitable for unmanned platform gravity measurement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320608156.2U CN219912309U (en) | 2023-03-25 | 2023-03-25 | Airborne vibration reduction platform suitable for unmanned platform gravity measurement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219912309U true CN219912309U (en) | 2023-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320608156.2U Active CN219912309U (en) | 2023-03-25 | 2023-03-25 | Airborne vibration reduction platform suitable for unmanned platform gravity measurement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219912309U (en) |
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2023
- 2023-03-25 CN CN202320608156.2U patent/CN219912309U/en active Active
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