CN216232979U - External structure of improved generation of unmanned aerial vehicle magnetic compass - Google Patents
External structure of improved generation of unmanned aerial vehicle magnetic compass Download PDFInfo
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- CN216232979U CN216232979U CN202123065780.2U CN202123065780U CN216232979U CN 216232979 U CN216232979 U CN 216232979U CN 202123065780 U CN202123065780 U CN 202123065780U CN 216232979 U CN216232979 U CN 216232979U
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Abstract
The utility model discloses an improved external structure of an unmanned aerial vehicle magnetic compass, relates to the technical field of unmanned aerial vehicles, and solves the problems that the flight track is deviated and even crashes caused by the fact that the current unmanned aerial vehicle is easily influenced by an external magnetic field and an internal magnetic field in the flight process, and the technical scheme is as follows: the unmanned aerial vehicle comprises an isolation shell and a wiring installation shell, wherein the isolation shell and the wiring installation shell form an unmanned aerial vehicle shell, the upper end inside the wiring installation shell is fixedly provided with a circuit board, an electromagnetic inductor and a controller respectively, the center position of the lower surface of the isolation shell is rotatably provided with a rotary ball sleeve, an electronic gyroscope is arranged inside the rotary ball sleeve, the lower surface of the rotary ball sleeve is fixedly provided with a magnetic compass, the outer walls of four sides of the unmanned aerial vehicle shell are fixedly provided with driving rods, and the tail end of each driving rod is fixedly provided with an electromagnetic detection ring; the magnetic compass has the advantages of reducing the influence of the external magnetic field and the internal magnetic field on the magnetic compass, optimizing the positioning effect of the compass and having higher use safety.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an improved external structure of a magnetic compass of an unmanned aerial vehicle.
Background
An unmanned aerial vehicle (unmanned aerial vehicle) ("UAV"), which is an unmanned aerial vehicle operated by a radio remote control device and a self-contained program control device, is a general name of unmanned aerial vehicles, and can be defined as follows from the technical point of view: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc.
Unmanned aerial vehicle is at the flight in-process, mainly can utilize the unmanned aerial vehicle compass, unmanned aerial vehicle's magnetic compass effect is revised to the gyroscope, there is the triaxial gyroscope in the flight control, the integral through the gyroscope can obtain the angle, but the gyroscope has a characteristic, along with the increase of on-time, drift also can increase, then magnetic compass just through its characteristic sensitive to magnetic field variation and inertial force, revise the deviation of gyroscope to ensure unmanned aerial vehicle's flight orbit.
Unmanned aerial vehicle is at the flight in-process, environment electromagnetic interference leads to the earth magnetism compass to become invalid, because the earth magnetism field is too weak, just easily because other radiation source disturbs the magnetic compass that flies on controlling, unmanned aerial vehicle can fly to wrong direction, unmanned aerial vehicle compass mainly installs inside the aircraft in addition, unmanned aerial vehicle is at the circular telegram flight in-process, the normal use of compass also can be disturbed to the produced magnetic field of its inside electric current that flows, lead to the skew more and more distant of unmanned aerial vehicle flight, the problem of crash even, therefore, for solving this type of problem, we propose the external structure of improved generation of unmanned aerial vehicle magnetic compass.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an improved external structure of a magnetic compass of an unmanned aerial vehicle, which reduces the influence of an external magnetic field and an internal magnetic field on the magnetic compass, optimizes the positioning effect of the compass and has higher use safety.
The technical purpose of the utility model is realized by the following technical scheme: the unmanned aerial vehicle is characterized by comprising an isolation shell and a wiring installation shell, wherein the isolation shell and the wiring installation shell form the unmanned aerial vehicle shell, the upper end inside the wiring installation shell is fixedly provided with a circuit board, an electromagnetic inductor and a controller respectively, the center position of the lower surface of the isolation shell is rotatably provided with a rotary ball sleeve, an electronic gyroscope is arranged inside the rotary ball sleeve, and the lower surface of the rotary ball sleeve is fixedly provided with a magnetic compass;
the unmanned aerial vehicle is characterized in that driving rods are fixedly mounted on the outer walls of four sides of the unmanned aerial vehicle shell, and an electromagnetic detection ring is fixedly mounted at the tail end of each driving rod.
Through adopting above-mentioned technical scheme, the installation of magnetic compass is located and is in isolated state between the inside circuit structure of unmanned aerial vehicle casing, so the influence of the inside magnetic field of unmanned aerial vehicle to the magnetic compass has been reduced, and set up the electromagnetic detection ring on the actuating lever position of unmanned aerial vehicle casing, at unmanned aerial vehicle flight in-process, external electromagnetic field intensity in the environment that real-time detection unmanned aerial vehicle is located, the electromagnetic field intensity in the external environment that unmanned aerial vehicle is located can direct feedback on the panel board on the unmanned aerial vehicle controller, the unmanned aerial vehicle driver can carry out the regulation and control of unmanned aerial vehicle flight orbit according to the electromagnetic field intensity.
The utility model is further configured to: and each group of driving rods is provided with a protection rod at the lower end, and the setting position of the protection rod is lower than the magnetic compass.
Through adopting above-mentioned technical scheme, unmanned aerial vehicle is at the in-process that descends, is that the fender rod contacts with ground earlier to avoid the magnetic compass to collide with ground and cause the damage.
The utility model is further configured to: fixed surface installs the slide bar that is vertical distribution under the actuating lever, sliding connection between slide bar and the fender rod, just the circumference outer wall of slide bar is provided with second buffer spring, fixed connection between second buffer spring lower extreme and the fender rod.
Through adopting above-mentioned technical scheme, at the in-process that unmanned aerial vehicle descends, through second buffer spring and sliding rod connection between fender rod and the actuating lever, so can offset the impact force of descending in-process.
The utility model is further configured to: the lower surface of the isolation shell is lower than the cross section plane of the rotary ball sleeve positioned at the center point.
Through adopting above-mentioned technical scheme, at unmanned aerial vehicle flight in-process, the ball cover that changes carries out 360 free rotations in isolated casing inside, so its inside electronic gyroscope and magnetic compass are in parallel state with the gravity field direction all the time.
The utility model is further configured to: the utility model discloses a wiring installation casing, including wiring installation casing, servo motor's output fixed mounting has connecting pin post, connecting pin post runs through the lower surface of wiring installation casing and connects for rotating, wiring installation casing lower surface is the symmetric distribution along the position that sets up of connecting pin post and is provided with the spoiler, two the one end that the spoiler is close to the magnetic compass is articulated.
Through adopting above-mentioned technical scheme, at unmanned aerial vehicle flight in-process, connect two spoilers through servo motor, can play and dredge two effects of air current and separation air current, so in-process that flight deviation appears in unmanned aerial vehicle, through the turned angle who adjusts the spoiler to cooperation electronic gyroscope and magnetic compass, calibration unmanned aerial vehicle's flight orbit.
The utility model is further configured to: and the two spoilers are in a triangular arrow shape along the direction from the servo motor to the magnetic compass.
By adopting the technical scheme, the spoilers form the triangular arrow shape, so that the air can uniformly flow along the spoilers in the flight process, and the flight stability is further ensured.
The utility model is further configured to: and the central position of the outer wall of one side, close to each other, of each spoiler is fixedly provided with a first buffer spring, and the tail end of each first buffer spring is fixedly connected with the connecting pin column.
By adopting the technical scheme, when the angle of the spoiler is adjusted, the air is blocked by the spoiler, and the wind power in the flight process can be matched according to the two first buffer springs.
Compared with the prior art, the utility model has the following beneficial effects: overall structure separately installs magnetic compass and inside circuit structure to can avoid the influence of the electromagnetic field that produces in the current flow among the internal circuit structure to magnetic compass, and all be provided with the electromagnetism in every actuating lever outside and survey the ring, the electromagnetic field intensity of certain position in can the real-time detection unmanned aerial vehicle flight orbit, and according to electromagnetic field intensity, utilize the spoiler to adjust unmanned aerial vehicle's flight orbit, with this flight stationarity who guarantees unmanned aerial vehicle.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the utility model and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the utility model and together with the description serve to explain the principles of the utility model. In the drawings:
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a cut-away view of the wiring mounting housing component of the present invention;
FIG. 3 is a cut-away view of an insulating housing component of the present invention;
FIG. 4 is a schematic diagram of a servo motor assembly according to the present invention;
fig. 5 is a schematic structural view of the driving lever member of the present invention.
Reference numbers and corresponding part names in the drawings: 1. isolating the housing; 2. a guard bar; 3. a drive rod; 4. an electromagnetic detection ring; 5. a wiring installation housing; 6. a circuit board; 7. an electromagnetic inductor; 8. a controller; 9. a servo motor; 10. a spoiler; 11. rotating the ball sleeve; 12. an electronic gyroscope; 13. a magnetic compass; 14. connecting a pin column; 15. a first buffer spring; 16. a second buffer spring; 17. a slide bar.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail with reference to the following examples and accompanying fig. 1-5, wherein the exemplary embodiments and descriptions of the present invention are only used for explaining the present invention and are not used as limitations of the present invention.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and is therefore not to be construed as limiting the utility model.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Example (b): an improved external structure of an unmanned aerial vehicle magnetic compass comprises an isolation shell 1 and a wiring installation shell 5, wherein the isolation shell 1 and the wiring installation shell 5 form the unmanned aerial vehicle shell, the upper end inside the wiring installation shell 5 is respectively and fixedly provided with a circuit board 6, an electromagnetic inductor 7 and a controller 8, the center position of the lower surface of the isolation shell 1 is rotatably provided with a rotary ball sleeve 11, an electronic gyroscope 12 is arranged inside the rotary ball sleeve 11, and the lower surface of the rotary ball sleeve 11 is fixedly provided with a magnetic compass 13;
the outer walls of four sides of the unmanned aerial vehicle shell are fixedly provided with driving rods 3, and the tail end of each driving rod 3 is fixedly provided with an electromagnetic detection ring 4.
As shown in fig. 1 and 5, a guard bar 2 is arranged at the lower end of each group of driving bars 3, the arrangement position of the guard bar 2 is lower than that of the magnetic compass 13, slide bars 17 which are vertically distributed are fixedly mounted on the lower surfaces of the driving bars 3, the slide bars 17 are slidably connected with the guard bars 2, a second buffer spring 16 is arranged on the circumferential outer wall of each slide bar 17, and the lower end of each second buffer spring 16 is fixedly connected with the guard bar 2.
As shown in fig. 2, 3 and 4, the lower surface of the isolation housing 1 is lower than the cross-sectional plane of the rotary ball sleeve 11 at the center point, the servo motor 9 is fixedly mounted at the center position of the lower end inside the wiring installation housing 5, the output end of the servo motor 9 is fixedly mounted with the connecting pin 14, the connecting pin 14 penetrates through the lower surface of the wiring installation housing 5 and is rotatably connected, the spoilers 10 are symmetrically distributed on the lower surface of the wiring installation housing 5 along the position of the connecting pin 14, one ends of the two spoilers 10 close to the magnetic compass 13 are hinged, the two spoilers 10 are in a triangular arrow shape along the direction from the servo motor 9 to the magnetic compass 13, the center positions of the outer walls at one side where the two spoilers 10 are close to each other are fixedly mounted with the first buffer springs 15, and the ends of the two first buffer springs 15 are fixedly connected with the connecting pin 14.
The working principle is as follows: constitute a complete unmanned aerial vehicle casing by isolated casing 1 and wiring installation casing 5, magnetic compass 13 is installed in isolated casing 1, so can not receive the inside influence because the electric current flows the electromagnetic field that produces of wiring installation casing 5 to drive overall structure and fly under the effect of the actuating lever 3 of unmanned aerial vehicle casing outer end, under the flight condition, divide into the following condition:
under the normal operating condition: the servo motor 9 is started to rotate the two spoilers 10, the direction of a hinge point of the two spoilers 10 is kept consistent with the flight direction, air can be uniformly separated along the spoilers 10 at the moment, and the flight stability of the unmanned aerial vehicle is guaranteed at the moment;
under the condition of abnormal operation: under the normal operation condition, the electromagnetic detection ring 4 on the driving rod 3 detects the electromagnetic field intensity of the external environment of the unmanned aerial vehicle in real time, and feeds the information of the electromagnetic field intensity back to the controller 8, and also directly feeds back to the instrument panel of the controller of the unmanned aerial vehicle, when the electromagnetic field intensity in a certain direction is larger, the driver of the unmanned aerial vehicle can input a control command into the controller 8 according to the electromagnetic field intensity displayed by the instrument panel of the controller, the controller 8 rapidly sends an electric signal to the servo motor 9 and the driving rod 3, firstly, the driving rod 3 changes the operation mode to change the flight track of the unmanned aerial vehicle, then under the action of the servo motor 9, the two spoilers 10 are driven to rotate by a certain angle, the rotation angle and the rotation direction are matched with the electromagnetic field direction under the abnormal condition, and the unmanned aerial vehicle is controlled to rapidly keep away from the area with larger electromagnetic field intensity, in the process, the spoiler 10 is rotated, so that the air flowing direction is changed, the response can be quickly made, and the flight stability of the unmanned aerial vehicle is ensured;
during the falling process, the protective rod 2 is firstly contacted with the ground, and the impact force of the falling is counteracted through the second buffer spring 16.
In addition, the comparator and the reference threshold value are added, the electromagnetic field intensity information is compared with the reference threshold value, and automatic correction control is realized when the electromagnetic field intensity information exceeds the reference threshold value.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. An improved external structure of an unmanned aerial vehicle magnetic compass is characterized by comprising an isolation shell (1) and a wiring installation shell (5), wherein the isolation shell (1) and the wiring installation shell (5) form the unmanned aerial vehicle shell, the upper end inside the wiring installation shell (5) is respectively and fixedly provided with a circuit board (6), an electromagnetic inductor (7) and a controller (8), the center position of the lower surface of the isolation shell (1) is rotatably provided with a rotary ball sleeve (11), an electronic gyroscope (12) is arranged inside the rotary ball sleeve (11), and the lower surface of the rotary ball sleeve (11) is fixedly provided with a magnetic compass (13);
the unmanned aerial vehicle is characterized in that driving rods (3) are fixedly mounted on the outer walls of four sides of the unmanned aerial vehicle shell, and an electromagnetic detection ring (4) is fixedly mounted at the tail end of each driving rod (3).
2. The improved external structure of the magnetic compass of the unmanned aerial vehicle as claimed in claim 1, wherein a guard bar (2) is disposed at the lower end of each set of the driving bars (3), and the arrangement position of the guard bar (2) is lower than that of the magnetic compass (13).
3. The improved external structure of the magnetic compass of the unmanned aerial vehicle as claimed in claim 2, wherein the lower surface of the driving rod (3) is fixedly provided with vertically distributed sliding rods (17), the sliding rods (17) are slidably connected with the protection rod (2), the outer wall of the circumference of the sliding rods (17) is provided with second buffer springs (16), and the lower ends of the second buffer springs (16) are fixedly connected with the protection rod (2).
4. The improved external structure of the magnetic compass of unmanned aerial vehicle as claimed in claim 1, wherein the lower surface of said insulating housing (1) is lower than the cross-sectional plane of the ball-rotating sleeve (11) at the center point.
5. The improved external structure of an unmanned aerial vehicle magnetic compass according to claim 1, wherein a servo motor (9) is fixedly installed at a central position of an inner lower end of the wiring installation housing (5), a connecting pin (14) is fixedly installed at an output end of the servo motor (9), the connecting pin (14) penetrates through a lower surface of the wiring installation housing (5) and is rotatably connected, spoilers (10) are symmetrically distributed on the lower surface of the wiring installation housing (5) along a setting position of the connecting pin (14), and one ends of the two spoilers (10) close to the magnetic compass (13) are hinged.
6. The improved external structure of the magnetic compass of the unmanned aerial vehicle as claimed in claim 5, wherein said two spoilers (10) are in the shape of triangle arrows along the direction from the servo motor (9) to the magnetic compass (13).
7. The improved external structure of the unmanned aerial vehicle magnetic compass according to claim 5, wherein a first buffer spring (15) is fixedly installed at the center position of the outer wall of one side of each of the two spoilers (10) close to each other, and the tail ends of the two first buffer springs (15) are fixedly connected with the connecting pins (14).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202123065780.2U CN216232979U (en) | 2021-12-08 | 2021-12-08 | External structure of improved generation of unmanned aerial vehicle magnetic compass |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202123065780.2U CN216232979U (en) | 2021-12-08 | 2021-12-08 | External structure of improved generation of unmanned aerial vehicle magnetic compass |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
| CN114858149A (en) * | 2022-07-04 | 2022-08-05 | 深圳市边界智控科技有限公司 | Calibration device of magnetic compass and unmanned aerial vehicle using same |
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2021
- 2021-12-08 CN CN202123065780.2U patent/CN216232979U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
| CN114735218B (en) * | 2022-04-12 | 2023-04-14 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
| CN114858149A (en) * | 2022-07-04 | 2022-08-05 | 深圳市边界智控科技有限公司 | Calibration device of magnetic compass and unmanned aerial vehicle using same |
| CN114858149B (en) * | 2022-07-04 | 2022-09-06 | 深圳市边界智控科技有限公司 | Calibration device of magnetic compass and unmanned aerial vehicle using same |
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