Inertial navigation installation structure of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle inertial navigation installation structure, which comprises an installation plate, the two side walls of the installation plate are both fixedly connected with a plurality of installation seats, each installation seat is provided with an installation hole, the surface of the installation plate is provided with an installation groove, an inertial navigation system body is placed in the installation groove, and the inertial navigation system body is provided with an installation hole. Convex blocks are fixedly connected to the side walls of the bottom ends of the two sides of the inertial navigation system body, a protective shell is mounted on the mounting plate, positioning blocks are fixedly connected to the inner walls of the bottom ends of the two sides of the protective shell, and a plurality of vibration reduction parts are arranged in the protective shell. According to the utility model, the inertial navigation system body can be effectively protected so as to prevent the inertial navigation system body from being damaged due to friction and collision of an external environment, and the vibration of the inertial navigation system body can be effectively reduced so as to prevent the inertial navigation system body from bumping and loosening to influence the measurement accuracy.

Description

Technical Field

[0001] The utility model belongs to the technical field of inertial navigation installation, in particular to an inertial navigation installation structure of a drone. Background Art

[0002] Inertial navigation is a method that uses inertial measurement devices (such as accelerometers and gyroscopes) to measure the acceleration and angular velocity of an object, thereby calculating the object's position, velocity and attitude. This navigation system does not rely on external signals and is an autonomous navigation method. It is widely used in aviation, navigation, aerospace and other fields that require high-precision positioning.

[0003] Inertial navigation equipment is often installed on drones to measure the acceleration and angular velocity of the drone. By processing these data, the inertial navigation system can calculate the real-time position, speed and attitude of the drone. At present, there are some inertial navigation installation structures on the market. For example, an inertial navigation installation structure for intelligent drones is disclosed on the Chinese Patent Network, and its announcement number is CN219237408U. This installation structure facilitates the rapid installation and removal of navigation equipment, avoids wasting the time of staff maintenance, reduces the labor intensity of staff, improves the work efficiency of staff, and is conducive to the use of staff. However, there are some defects and deficiencies that need to be improved: (1) Some existing inertial navigation equipment lacks effective protection measures after being installed on drones. When the drone flies in a more complex environment such as a forest, the inertial navigation equipment is easily damaged by friction and collision from the external environment, thereby affecting the measurement of the drone; (2) The drone often generates large vibrations during flight, and some existing inertial navigation equipment is difficult to achieve a good vibration reduction effect after installation, which causes the inertial navigation system to be bumpy and loose, affecting its measurement accuracy. Therefore, in view of the above problems, the inertial navigation installation structure of a UAV provided by the utility model is of great significance. Utility Model Content

[0004] The utility model provides an inertial navigation installation structure for a drone, which can effectively protect the inertial navigation system body through a protective shell, thereby effectively preventing the inertial navigation system body from being damaged by friction and collision from the external environment when the drone flies in a complex environment such as a forest; the vibration of the inertial navigation system body can be effectively reduced through various vibration-damping parts, so as to prevent the inertial navigation system body from being shaken and loosened when the drone vibrates during flight, thereby affecting its measurement accuracy. In summary, the problems in the background technology are solved.

[0005] In order to solve the above technical problems, the utility model is realized by the following technical solutions:

[0006] The utility model discloses an inertial navigation installation structure of a drone, comprising a mounting plate, both side walls of the mounting plate are fixedly connected with a plurality of mounting seats, each of the mounting seats is provided with a mounting hole, a mounting groove is provided on the surface of the mounting plate, an inertial navigation system body is placed in the mounting groove, both bottom side walls of the inertial navigation system body are fixedly connected with protrusions, a protective shell is installed on the mounting plate, both bottom ends of the protective shell are L-shaped and provided with a plurality of positioning holes, and both bottom inner walls of the protective shell are fixedly connected with positioning blocks, a plurality of studs are fixedly connected with the top of the mounting plate, the number of the studs is the same as that of the positioning holes, the diameters are correspondingly equal, and the center of each stud corresponds to the center of each positioning hole one by one, each stud is threadedly connected with a nut matched therewith, and a plurality of vibration damping members are arranged inside the protective shell;

[0007] Each of the vibration damping parts includes a vibration damping plate, which is in an N-shape, and the width of its inner wall is equal to the length of the inertial navigation system body. A plurality of springs are fixedly connected to the top of the vibration damping plate. The springs are equidistantly linearly distributed along the length direction of the vibration damping plate, and the tops of the springs are fixedly connected to the top inner wall of the protective shell.

[0008] Furthermore, a layer of vibration-damping pad is provided on the inner wall surface of the vibration-damping plate.

[0009] Furthermore, movable blocks are fixedly connected to the outer walls on both sides of the vibration damping plate, and a number of movable grooves are provided on the side walls on both sides of the protective shell. The movable grooves are rectangular, and their number is the same as the movable blocks, and the groove width of the movable grooves is equal to the width of the movable blocks. The movable blocks pass through the movable grooves and extend outside the protective shell, and guide holes are provided on the surface of the movable blocks, and guide rods are inserted into the guide holes, and the bottom ends of the guide rods are fixedly connected to the protective shell.

[0010] Furthermore, a limit frame is arranged inside the protective shell. The limit frame is rectangular, and the length and width of its inner wall are equal to the length and width of the inertial navigation system body, and a plurality of fixed blocks are fixedly connected between the outer walls on both sides of the limit frame and the inner wall of the protective shell.

[0011] Furthermore, a layer of anti-wear ring is provided on the inner wall surface of the limiting frame.

[0012] Furthermore, pads are fixedly connected to the four corners of the mounting groove.

[0013] Compared with the prior art, the utility model has the following beneficial effects:

[0014] (1) When the inertial navigation installation structure of a drone in the utility model is in use, the protective shell can effectively protect the inertial navigation system body, thereby effectively preventing the inertial navigation system body from being damaged by friction and collision from the external environment when the drone is flying in a relatively complex environment such as a forest;

[0015] (2) When the inertial navigation installation structure of an unmanned aerial vehicle in the utility model is in use, the vibration of the inertial navigation system body can be effectively reduced through various vibration-damping parts, so as to avoid the inertial navigation system body from being shaken and loosened when the unmanned aerial vehicle vibrates during flight, thereby affecting its measurement accuracy.

[0016] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for describing the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 This is a structural schematic diagram of an inertial navigation installation structure of a UAV of the utility model;

[0019] Figure 2 This is a front cross-sectional view of an inertial navigation installation structure of an unmanned aerial vehicle of the utility model;

[0020] Figure 3 It is a structural schematic diagram of the mounting plate in the utility model;

[0021] Figure 4 It is a structural schematic diagram of the inertial navigation system body in the utility model;

[0022] Figure 5 It is a schematic diagram of the structure of the protective shell in the utility model;

[0023] Figure 6 It is a schematic diagram of the structure of the vibration damping member in the utility model;

[0024] Figure 7 It is a structural schematic diagram of the limit frame in the utility model.

[0025] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0026] 1. Mounting plate; 2. Mounting seat; 3. Mounting hole; 4. Mounting slot; 5. Inertial navigation system body; 6. Bump; 7. Protective shell; 8. Positioning hole; 9. Stud; 10. Nut; 11. Vibration damping plate; 12. Spring; 13. Vibration damping pad; 14. Movable block; 15. Movable slot; 16. Guide hole; 17. Guide rod; 18. Limit frame; 19. Fixed block; 20. Anti-wear ring; 21. Cushion block; 22. Positioning block. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0028] In the description of the present invention, it should be understood that terms such as "relative", "one end", "inside", "lateral", "end", "two ends", "both sides", "front", "one end face", "the other end face" and the like indicating orientation or positional relationship are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the components or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0029] See also Figure 1-7As shown, an inertial navigation installation structure of an unmanned aerial vehicle of the utility model comprises a mounting plate 1, and the side walls on both sides of the mounting plate 1 are fixedly connected with a plurality of mounting seats 2, each mounting seat 2 is provided with a mounting hole 3, and a fastener such as a bolt can be inserted into the mounting hole 3, and the mounting plate 1 can be fixed to the unmanned aerial vehicle through the bolt and the mounting hole 3, so as to carry out the subsequent installation of the inertial navigation system, and the surface of the mounting plate 1 is provided with a mounting groove 4, and an inertial navigation system body 5 is placed in the mounting groove 4, and the inertial navigation system body 5 is a prior art, and an inertial measurement unit, a data processing unit, a power supply and an interface module (not shown in the figure) are integrated therein, and these components are existing products that can be directly purchased on the market, and their specific structure is not repeated, and the bottom side walls on both sides of the inertial navigation system body 5 are fixedly connected with protrusions 6, and a protective shell 7 is installed on the mounting plate 1, and the bottom ends of both sides of the protective shell 7 are L-shaped and provided with a plurality of positioning holes 8, and the bottom inner walls of both sides of the protective shell 7 are fixedly connected with positioning blocks 22, and the top of the mounting plate 1 is fixedly connected with a plurality of studs 9, the number of studs 9 and positioning holes 8 is the same, the diameters are correspondingly equal, and the center of each stud 9 corresponds to the center of each positioning hole 8. Each stud 9 is threadedly connected with a nut 10 matched therewith, and each stud 9 can be aligned with and pass through the corresponding positioning hole 8. At this time, the nut 10 is threadedly connected to each stud 9 and tightened. The protective shell 7 can be fixed on the mounting plate 1 through the mutual cooperation between the stud 9 and the nut 10, and it can cover the outside of the entire inertial navigation system body 5. When the drone flies in a more complex environment such as a forest, the inertial navigation system body 5 can be effectively protected by the protective shell 7, thereby effectively preventing the inertial navigation system body 5 from being damaged by friction and collision of the external environment. When the protective shell 7 is fixed on the mounting plate 1, the positioning block 22 can be against the top of the protrusions 6 on both sides of the inertial navigation system body 5. At this time, the inertial navigation system body 5 can be positioned by the positioning block 22, so that the inertial navigation system body 5 is firmly fixed in the mounting groove 4. A plurality of vibration damping members are arranged inside the protective shell 7;

[0030] Each vibration damping member includes a vibration damping plate 11, which is in an N-shape, and the width of its inner wall is equal to the length of the inertial navigation system body 5. A plurality of springs 12 are fixedly connected to the top of the vibration damping plate 11. The springs 12 are equidistantly linearly distributed along the length direction of the vibration damping plate 11, and the top is fixedly connected to the top inner wall of the protective shell 7. When the protective shell 7 is fixed on the mounting plate 1, each vibration damping plate 11 can be tightly pressed against the top of the inertial navigation system body 5 under the elastic reset action of the spring 12. When the drone vibrates during flight, each vibration damping member can effectively reduce the vibration of the inertial navigation system body 5, so as to avoid the inertial navigation system body 5 from being shaken and loosened and affecting its measurement accuracy.

[0031] Among them, a layer of vibration-damping pad 13 is arranged on the inner wall surface of the vibration-damping plate 11. The vibration-damping pad 13 is made of elastic materials such as sponge and is fixed by glue or other means. When the vibration-damping plate 11 is against the top of the inertial navigation system body 5, the vibration-damping pad 13 can play a buffering and vibration-damping effect to prevent the surface of the inertial navigation system body 5 from directly contacting the vibration-damping plate 11 to cause collision and wear.

[0032] Among them, the outer walls on both sides of the vibration damping plate 11 are fixedly connected with movable blocks 14, and the side walls on both sides of the protective shell 7 are provided with a plurality of movable grooves 15. The movable grooves 15 are rectangular, and their number is the same as that of the movable blocks 14, and the groove width of the movable grooves 15 is correspondingly equal to the width of the movable blocks 14. The movable blocks 14 pass through the movable grooves 15 and extend to the outside of the protective shell 7, and the surface of the movable blocks 14 is provided with guide holes 16, and guide rods 17 are inserted into the guide holes 16. The bottom end of the guide rod 17 is fixedly connected to the protective shell 7. The mutual cooperation between the guide rods 17 and the guide holes 16 can be used to limit each vibration damping plate 11 to prevent the vibration damping plate 11 from shaking and displacing and affecting the vibration reduction effect.

[0033] Among them, a limit frame 18 is arranged inside the protective shell 7. The limit frame 18 is rectangular, and the length and width of its inner wall are equal to the length and width of the inertial navigation system body 5. A plurality of fixing blocks 19 are fixedly connected between the outer walls on both sides of the limit frame 18 and the inner wall of the protective shell 7. When the protective shell 7 is fixed on the mounting plate 1, the limit frame 18 can be put on the inertial navigation system body 5 and fit on the side wall of the inertial navigation system body 5. At this time, the limit frame 18 can be used to limit the inertial navigation system body 5, so as to improve the stability of the inertial navigation system body 5 after installation, thereby preventing it from loosening and displacement during the flight of the UAV.

[0034] Among them, a layer of anti-wear ring 20 is provided on the inner wall surface of the limit frame 18. The anti-wear ring 20 is made of elastic materials such as rubber and is fixed by glue or other means. When the limit frame 18 is attached to the side wall of the inertial navigation system body 5, the anti-wear ring 20 can play an anti-wear protection role to prevent the surface of the inertial navigation system body 5 from directly contacting the limit frame 18 to cause collision and wear.

[0035] Among them, pads 21 are fixedly connected at the four corners of the installation groove 4. The pads 21 are cylindrical rubber columns and are fixed by glue or other means. When the inertial navigation system body 5 is placed in the installation groove 4, each pad 21 can be placed on the bottom of the inertial navigation system body 5. At this time, the pads 21 can play a buffering and anti-wear role to avoid direct contact between the bottom of the inertial navigation system body 5 and the bottom of the installation groove 4 to cause wear. At the same time, it can also absorb part of the vibration generated by the drone, thereby further reducing the bump amplitude of the inertial navigation system body 5.

[0036] The circuits, electronic components and chip modules involved in the utility model are all existing technologies and can be fully implemented by those skilled in the art. Needless to say, the content protected by the utility model does not involve improvements to software and methods.

[0037] The standard parts used in the application documents can all be purchased from the market. All the components in this application document can be customized according to the description in the specification and drawings. The specific connection methods of each part adopt mature conventional means such as bolts, rivets, welding, etc. in the prior art. Machinery, parts and equipment all adopt conventional models in the prior art. The electrical components appearing in this article are all electrically connected to the external main controller and 220V AC power, and the main controller can be a conventional known device that controls the LED lamp body, etc.

[0038] The working principle of the utility model is:

[0039] When the utility model is used, the inertial navigation system body 5 can be first placed in the mounting groove 4 on the surface of the mounting plate 1, and then the protective shell 7 can be fixed on the mounting plate 1 through the mutual cooperation between the studs 9 and the nuts 10, and the protective shell 7 can be covered on the outside of the entire inertial navigation system body 5. At this time, the positioning blocks 22 on the inner wall of the protective shell 7 can be against the tops of the protrusions 6 on both sides of the inertial navigation system body 5. The inertial navigation system body 5 can be positioned by the positioning blocks 22 so that the inertial navigation system body 5 can be firmly fixed in the mounting groove 4. After that, fasteners such as bolts can be inserted into the mounting holes 3 on each mounting seat 2, so that the mounting plate 1 together with the inertial navigation system body 5 can be installed and fixed through the bolts and the mounting holes 3. When the UAV flies in a complex environment such as a forest, the protective shell 7 can effectively protect the inertial navigation system body 5, thereby effectively avoiding the inertial navigation system body 5 from being damaged by friction and collision in the external environment. A plurality of shock-absorbing parts are arranged inside the protective shell 7. When the protective shell 7 is fixed on the mounting plate 1, the shock-absorbing plate 11 in each shock-absorbing part can be tightly pressed against the top of the inertial navigation system body 5 under the elastic reset action of the spring 12. When the UAV vibrates during flight, the vibration of the inertial navigation system body 5 can be effectively reduced by utilizing each shock-absorbing part, so as to avoid the inertial navigation system body 5 from being shaken and loosened and affecting its measurement accuracy.

[0040] The preferred embodiments of the utility model disclosed above are only used to help explain the utility model. The preferred embodiments do not describe all the details in detail, nor do they limit the utility model to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the utility model, so that technicians in the relevant technical field can well understand and use the utility model. The utility model is limited only by the claims and their full scope and equivalents.

Claims

1. An inertial navigation installation structure for a drone, characterized in that: The invention comprises a mounting plate, wherein the side walls on both sides of the mounting plate are fixedly connected with a plurality of mounting seats, each of the mounting seats is provided with a mounting hole, a mounting groove is provided on the surface of the mounting plate, an inertial navigation system body is placed in the mounting groove, and the side walls on both sides of the bottom end of the inertial navigation system body are fixedly connected with protrusions, a protective shell is installed on the mounting plate, the bottom ends of both sides of the protective shell are L-shaped and provided with a plurality of positioning holes, and the inner walls on both sides of the bottom end of the protective shell are fixedly connected with positioning blocks, a plurality of studs are fixedly connected with the top of the mounting plate, the number of the studs is the same as that of the positioning holes, the diameters are correspondingly equal, and the center of each stud corresponds to the center of each positioning hole one by one, each stud is threadedly connected with a nut matched therewith, and a plurality of vibration damping members are arranged inside the protective shell; Each of the vibration damping parts includes a vibration damping plate, which is in an N-shape, and the width of its inner wall is equal to the length of the inertial navigation system body. A plurality of springs are fixedly connected to the top of the vibration damping plate. The springs are equidistantly linearly distributed along the length direction of the vibration damping plate, and the tops of the springs are fixedly connected to the top inner wall of the protective shell.

2. The inertial navigation installation structure of a UAV according to claim 1, characterized in that: A layer of vibration-damping pad is arranged on the inner wall surface of the vibration-damping plate.

3. The inertial navigation installation structure of a UAV according to claim 1, characterized in that: The outer walls on both sides of the vibration damping plate are fixedly connected with movable blocks, and the side walls on both sides of the protective shell are provided with a plurality of movable grooves, the movable grooves are rectangular, and the number of the movable grooves is the same as the movable blocks, and the groove width of the movable grooves is correspondingly equal to the width of the movable blocks, the movable blocks pass through the movable grooves and extend outside the protective shell, and the surface of the movable block is provided with guide holes, and guide rods are inserted into the guide holes, and the bottom ends of the guide rods are fixedly connected to the protective shell.

4. The inertial navigation installation structure of a UAV according to claim 1, characterized in that: A limit frame is arranged inside the protective shell. The limit frame is rectangular, and the length and width of its inner wall are correspondingly equal to the length and width of the inertial navigation system body. A plurality of fixing blocks are fixedly connected between the outer walls on both sides of the limit frame and the inner wall of the protective shell.

5. The inertial navigation installation structure of a UAV according to claim 4, characterized in that: The inner wall surface of the limiting frame is provided with an anti-wear ring.

6. The inertial navigation installation structure of a UAV according to claim 1, characterized in that: Pads are fixedly connected to the four corners of the installation groove.

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