CN218481200U - Flight controller and aircraft - Google Patents

Abstract

An embodiment of the utility model provides a flight controller and aircraft relates to the flight controller field. The flight controller comprises a shell, an air pressure sensor and an elastic sealing ring, wherein the shell is provided with a through hole; the air pressure sensor detects air pressure outside the shell through the through hole and is provided with an annular groove; the annular groove is sleeved on the inner side of the elastic sealing ring, and the outer side of the elastic sealing ring is positioned in the through hole and is tightly matched with the through hole. Therefore, after the air pressure sensor is installed on the shell, the assembly gap between the air pressure sensor and the shell is provided with the elastic sealing ring, so that a better waterproof effect can be achieved. Meanwhile, the air pressure sensor can directly detect the air pressure outside the shell through the through hole, so that the detection accuracy is higher, the overall applicability is stronger, and the air pressure sensor has a wider application scene.

Description

Flight controller and aircraft

Technical Field

The utility model relates to a flight controller field particularly, relates to a flight controller and aircraft.

Background

The flight controller of the aircraft generally takes control over the various components of the aircraft, and in the prior art, the flight controller often integrates various sensing devices, such as an air pressure sensor.

However, in the prior art, after the air pressure sensor is installed on the shell of the flight controller, the technical problem of poor waterproof performance exists.

SUMMERY OF THE UTILITY MODEL

The utility model provides a flight controller and aircraft, its water-proof effects that can realize the preferred to the elastic sealing circle is difficult for droing.

The embodiment of the utility model discloses a can realize like this:

an embodiment of the utility model provides a flight controller, it includes:

a housing provided with a through hole;

the air pressure sensor detects the air pressure outside the shell through the through hole and is provided with an annular groove; and

the annular groove is sleeved on the inner side of the elastic sealing ring, and the outer side of the elastic sealing ring is located in the through hole and is in close fit with the through hole.

Optionally, the flight controller further comprises a circuit board located within the housing, the barometric pressure sensor being mounted to the circuit board.

Optionally, the barometric sensor includes a base and a sensor body, and the sensor body is connected to the base;

the base is mounted on the circuit board;

the ring channel set up in on the sensor body, the sensor body is kept away from the one end terminal surface of base forms and detects the terminal surface, it is used for passing through to detect the terminal surface the through-hole contact the outer environment of casing.

Optionally, the casing includes an outer wall surface and an inner wall surface, the through hole penetrates through the outer wall surface and the inner wall surface, and the detection end surface is flush with the outer wall surface.

Optionally, the annular groove is spaced apart from the detection end face.

Optionally, the annular groove is defined by a first inner wall surface, a second inner wall surface, and a third inner wall surface provided in this order on the sensor body;

the first inner wall surface is provided opposite to the third inner wall surface, and the first inner wall surface is close to the detection end surface relative to the third inner wall surface;

the inner side of the elastic sealing ring comprises a first surface, a second surface and a third surface which are sequentially connected, wherein the first surface, the second surface and the third surface are in one-to-one correspondence with the first inner wall surface, the second inner wall surface and the third inner wall surface and are in tight fit with the first inner wall surface, the second inner wall surface and the third inner wall surface.

Optionally, the sensor body is cylindrical, the first inner wall surface is disposed along a radial direction of the sensor body, the second inner wall surface is disposed along an axial direction of the sensor body, and the third inner wall surface is disposed along the radial direction of the sensor body.

Optionally, the outside of elastic sealing ring includes a plurality of annular sand grips of interval setting, annular sand grip with the through-hole closely cooperates.

Optionally, the housing includes a first housing and a second housing, the first housing and the second housing are detachably connected, the circuit board is disposed between the first housing and the second housing, and the through hole is opened in the first housing.

The embodiment of the utility model also provides an aircraft, it includes foretell flight control ware.

The utility model discloses flight controller and aircraft's beneficial effect includes, for example:

the flight controller comprises a shell, an air pressure sensor and an elastic sealing ring, wherein the shell is provided with a through hole; the air pressure sensor detects air pressure outside the shell through the through hole and is provided with an annular groove; the annular groove is sleeved on the inner side of the elastic sealing ring, and the outer side of the elastic sealing ring is positioned in the through hole and is tightly matched with the through hole. Like this, this baroceptor installs the back on the casing, and its fitting gap department with the casing is owing to there is the elastic sealing circle, consequently can play the water-proof effects of preferred, simultaneously, because the elastic sealing circle is assembled to the baroceptor through the ring channel on, consequently is difficult to drop, and the installation is dismantled etc. comparatively conveniently. Understandably, the air pressure sensor is matched with the through hole, so that the full utilization of space is realized, and the integration compactness of the flight controller is improved. Meanwhile, the air pressure sensor can directly detect the air pressure outside the shell through the through hole, so that the detection accuracy is higher, the overall applicability is stronger, and the air pressure sensor has a wider application scene.

The aircraft includes the flight controller, which has all of the functions of the flight controller.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic structural diagram of an aircraft provided in the present embodiment;

fig. 2 is a schematic structural diagram of the flight controller provided in this embodiment at a first viewing angle;

fig. 3 is a schematic structural diagram of the flight controller provided in this embodiment at a second viewing angle;

fig. 4 is a schematic structural diagram of the flight controller provided in this embodiment at a third viewing angle;

fig. 5 is a schematic structural diagram of internal elements of the flight controller according to the present embodiment in a first view;

fig. 6 is a schematic structural diagram of internal elements of the flight controller provided in this embodiment in a second view angle.

Icon: 100-an aircraft; 20-a fuselage; 10-a flight controller; 11-a housing; 110-a via; 111-a first housing; 112-a second housing; 114-outer wall surface; 115-inner wall face; 12-a barometric pressure sensor; 120-detecting the end face; 121-a base; 122-a sensor body; 123-an annular groove; 1231-a first inner wall surface; 1232-second inner wall surface; 1233-third interior wall surface; 13-elastic sealing ring; 131-a first surface; 132-a second surface; 133-a third surface; 134-annular ribs; 14-circuit board.

Detailed Description

To make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the attached drawings in the embodiments of the present invention are combined to clearly and completely describe the technical solution in the embodiments of the present invention, and obviously, the described embodiments are part of the embodiments of the present invention, rather than all embodiments. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.

In the description of the present invention, it should be noted that, if the terms "upper", "lower", "inner", "outer", etc. indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the products of the present invention are used, the description is only for convenience of description and simplification, but the indication or suggestion that the indicated device or element must have a specific position, be constructed and operated in a specific orientation, and thus, should not be interpreted as a limitation of the present invention.

Furthermore, the appearances of the terms "first," "second," and the like, if any, are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

It should be noted that the features of the embodiments of the present invention may be combined with each other without conflict.

The flight controller of the aircraft generally takes over the control of the various components of the entire aircraft, and in the prior art, the flight controller often integrates various sensing devices, such as an air pressure sensor. The flight controller can calculate the flight altitude of the aircraft through the air pressure measured by the air pressure sensor, and can also determine the wind field distribution and the like of the aircraft according to the air pressure. However, in the prior art, after the air pressure sensor is installed on a shell of the flight controller, the technical problem of poor waterproof performance exists.

In view of the above, referring to fig. 1, the present embodiment provides a flight controller 10 and an aircraft 100, which can effectively improve the above-mentioned technical problems. Specifically, the aircraft 100 includes a fuselage 20 and a flight controller 10, and the flight controller 10 is mounted on the fuselage 20. Generally, the flight controller 10 may include various other electrical components, such as a gyroscope, a satellite positioning module, a data transmission module, etc., which may be relatively independent components or may be integrated.

Before describing the technical solution of the present embodiment, the technical terms and application scenarios related to the present embodiment will be described and explained first.

Referring to fig. 1, the aircraft 100 shown in fig. 1 is a drone that operates automatically according to a predetermined path, flight speed, etc., or is manually controlled by an operator. In other embodiments, when the design meets the requirement, the driver can be carried, and the related operation can be manually operated in the cab by the driver. Generally, the power for flying the aircraft 100 is provided by an electric motor, although in other embodiments, power provided by a gasoline engine or a diesel engine is not excluded. Meanwhile, from the application scene, the unmanned aerial vehicle is an agricultural unmanned aerial vehicle, and various execution devices required in agriculture, such as a spraying component, a sowing component and the like, are generally mounted on the unmanned aerial vehicle, so that spraying irrigation, sowing and the like can be realized. Of course, the device can also be used in other fields such as spraying of fire extinguishing liquid in forest fires, seed sowing, aerial photography, power inspection, environmental monitoring, forest fire prevention, disaster patrol and the like. Alternatively, a game device or the like is mounted for interaction. In general, the flight controller 10 mentioned above can control various electrical components mounted on the body 20.

The flight controller 10 provided in this embodiment will be described in detail below, and it should be noted that the flight controller 10 provided in this embodiment is mainly applied to the aircraft 100, but is not limited to the aircraft 100, and for example, the flight controller 10 may be mounted on an unmanned vehicle or an unmanned ship, or applied to living goods (watches, wristbands, computers, smart glasses, smart speakers, and the like), engineering machinery, medical equipment, and the like, and in other words, any scene requiring a waterproof design for the air pressure sensor 12 on the flight controller 10 can be well applied.

Specifically, referring to fig. 2 and 3, fig. 2 is shown in an overall view of flight controller 10, and fig. 3 is shown in an exploded view of flight controller 10.

The present embodiment provides a flight controller 10, which includes:

a housing 11, the housing 11 being provided with a through hole 110;

an air pressure sensor 12, the air pressure sensor 12 detecting air pressure outside the housing 11 through the through hole 110, the air pressure sensor 12 being provided with an annular groove 123 (shown in fig. 5 and 6); and

the annular groove 123 is sleeved on the inner side of the elastic sealing ring 13, and the outer side of the elastic sealing ring 13 is located in the through hole 110 and is tightly matched with the through hole 110.

In combination with the above, after the air pressure sensor 12 is installed on the casing 11, the elastic sealing ring 13 is arranged in the assembling gap between the air pressure sensor 12 and the casing 11, so that a better waterproof effect can be achieved, and meanwhile, the elastic sealing ring 13 is assembled on the air pressure sensor 12 through the annular groove 123, so that the air pressure sensor is not easy to fall off, and the installation and the disassembly are convenient. It is understood that, since the air pressure sensor 12 is fitted to the through hole 110, sufficient use of space is also achieved, and the integration compactness of the flight controller 10 is improved. In addition, since the air pressure sensor 12 can directly detect the air pressure outside the housing 11 through the through hole 110, the detection accuracy is higher, the overall applicability is stronger, and the air pressure sensor has a wider application scene.

Referring to fig. 2 and 3, in the present embodiment, the flight controller 10 further includes a circuit board 14, the circuit board 14 is located in the housing 11, and the air pressure sensor 12 is mounted on the circuit board 14. In particular, the air pressure sensor 12 is soldered directly to the circuit board 14, the circuit board 14 optionally being a rigid circuit board, such that when the circuit board 14 is mounted on the housing 11, the mounting of the air pressure sensor 12 in place is simultaneously achieved. Of course, it is not excluded that the circuit board 14 is a flexible circuit board, or that the air pressure sensor 12 is mounted on one end of the flexible circuit board, and the other end of the flexible circuit board is fixed to a hard circuit board.

Those skilled in the art will appreciate that the various electrical components of the flight controller 10 mentioned above (e.g., gyroscope, satellite positioning module, data transmission module, etc.) may be integrated on the circuit board 14. Due to the partial structure of the air pressure sensor 12 in the through hole 110, a relatively spare space can be provided in the housing 11, which is more beneficial for installing more relevant modules suitable for flight control.

The circuit board 14 is provided with mounting holes at four corners, and the circuit board 14 can be fixed to the housing 11 (specifically, to the first housing 111) typically using bolts to fit the mounting holes. In the process of screwing the bolt into the shell 11, the elastic sealing ring 13 and the sensor body 122 are slowly inserted into the through hole 110, and in the process of slowly inserting the bolt into the through hole 110, the elastic sealing ring 13 is deformed so as to be extruded on the inner wall of the through hole 110, so that tight fit is realized.

Referring to fig. 2 and 3, the housing 11 includes a first housing 111 and a second housing 112, the circuit board 14 is disposed between the first housing 111 and the second housing 112, and the first housing 111 and the second housing 112 can be detachably connected by bolts, clamping, and the like. Specifically, the through hole 110 is provided on the first casing 111, and as shown in the relative position in the drawing, when the first casing 111 is located above the second casing 112, and is specifically mounted on the machine body 20, the first casing 111 may be located above the second casing 112, that is, the first casing 111 faces upward, or the first casing 111 may be located below the second casing 112, that is, the first casing 111 faces downward, and when the first casing 111 faces downward, the position of the through hole 110 is located at the bottom position of the whole casing 11, so that the waterproof effect can be relatively improved. Taking the first housing 111 installed downward as an example, when the aircraft 100 flies, if the flight controller 10 encounters rain weather, rain water covers the outer wall of the second housing 112, and in the process of flowing downward, the rain water is easily blown off because the aircraft 100 keeps the flying state, even if a small amount of rain water exists on the outer wall of the first housing 111, the rain water is also easily blown off, and because the first housing 111 faces downward, the rain water is more easily blown off under the action of gravity, so that the residual rain water is prevented from being gathered near the through hole 110, and the probability that the rain water enters the housing 11 through the through hole 110 can be greatly reduced.

The air pressure sensor 12 provided by the embodiment can adopt a sensor with good waterproof performance, namely, the sensor has a waterproof function, namely, external liquid is not easy to permeate through the air pressure sensor 12. Meanwhile, the elastic sealing ring 13 is sleeved on the outer wall of the air pressure sensor 12, so that external liquid can be prevented from permeating through the installation gap of the air pressure sensor 12.

In general, in the present embodiment, the "exterior" refers to the exterior of the housing 11, the "interior" refers to the interior of the housing 11, and the "infiltration" refers to the interior of the housing 11.

In combination with the above, since the air pressure sensor 12 itself has a certain waterproof function, it can directly contact with the external environment, that is, directly detect the air pressure outside the housing 11. Since the external air pressure of the housing 11 is directly detected, the measurement accuracy is high. Meanwhile, the embedded design is adopted, so that the whole volume can be made very small, and a better integration effect is realized. In other words, the design can not only realize the detection precision of the air pressure better, but also realize the waterproof effect of the better, and simultaneously, the better integration effect is realized, and the whole structure is more compact. When the flight controller 10 is used in an aircraft 100, the overall compactness greatly reduces the space occupied, providing additional space for installing more other components.

In this embodiment, the elastic sealing ring 13 is a rubber ring, but in other embodiments, a silicone ring may be used. In general, the specific material of the elastic sealing ring 13 is not limited as long as the elastic sealing ring is mounted on the air pressure sensor 12 and can achieve a sealing effect by being pressed and deformed after being assembled into the through hole 110.

Referring to fig. 4-6, fig. 4 shows the assembly of the circuit board 14, the pressure sensor 12, and the elastic sealing ring 13 with the housing 11 (the first housing 111), and fig. 5 and 6 show the circuit board 14, the pressure sensor 12, and the elastic sealing ring 13, wherein the three are shown in an exploded view.

Referring to fig. 4-6, in the present embodiment, the air pressure sensor 12 includes a base 121 and a sensor body 122, and the sensor body 122 is connected to the base 121; the base 121 is mounted to the circuit board 14; the annular groove 123 is opened on the sensor body 122, and an end face of the sensor body 122 far away from the base 121 forms a detection end face 120, and the detection end face 120 is used for contacting the environment outside the housing 11 through the through hole 110.

Generally, the base 121 is fixed to the circuit board 14 by soldering, and the base 121 has a rectangular parallelepiped structure, and a bottom surface thereof is attached to one side surface of the circuit board 14.

Referring to fig. 4, in the present embodiment, the housing 11 includes an outer wall surface 114 and an inner wall surface 115, the through hole 110 penetrates the outer wall surface 114 and the inner wall surface 115, and the detection end surface 120 is flush with the outer wall surface 114.

The design of the detection end face 120 flush with the outer wall face 114 enables the liquid to flow along the outer wall face 114 during the flight of the aircraft 100 if the liquid is largely condensed on the outer wall face 114 during the flight of the aircraft 100, and the liquid can flow rapidly without staying due to the fact that the detection end face 120 is flush with the outer wall face 114, so that the liquid is prevented from permeating into the housing 11 through the through hole 110. Of course, in other embodiments, the detection end face 120 may be protruded from the outer wall surface 114 or recessed in the through hole 110. It is generally understood that the liquid may be rain or droplets of liquid sprayed on flight controller 10 when aircraft 100 is performing a spraying operation.

Referring to fig. 5 and 6, in the present embodiment, the annular groove 123 is spaced apart from the detection end surface 120. In other words, when the detection end face 120 and the outer wall surface 114 are flush with each other, the elastic seal ring 13 is completely fitted into the through hole 110 and is not exposed. Therefore, the area of the detection end face 120 can be relatively large enough, the detection accuracy can be higher, and the area can be large enough, so that when the area is almost not large different from the area of the through hole 110, the detection end face 120 can play a certain covering role, and rainwater can be further prevented from permeating into the shell 11 through the through hole 110. Of course, other embodiments are not excluded in which the annular groove 123 is disposed adjacent to the detection end face 120, that is, after the elastic sealing ring 13 is fitted around the annular groove 123, the end face of the elastic sealing ring 13 is flush with the detection end face 120, so that when the detection end face 120 and the outer wall surface 114 are flush, the elastic sealing ring 13 and the detection end face 120 jointly cover the through hole 110.

With reference to fig. 5 and 6, in the present embodiment, the annular groove 123 is defined by a first inner wall surface 1231, a second inner wall surface 1232, and a third inner wall surface 1233 provided in this order on the sensor body 122; the first inner wall surface 1231 is provided opposite to the third inner wall surface 1233, and the first inner wall surface 1231 is close to the detection end surface 120 with respect to the third inner wall surface 1233; the inner side of the elastic sealing ring 13 includes a first surface 131, a second surface 132, and a third surface 133 connected in sequence, and the first surface 131, the second surface 132, and the third surface 133 correspond to the first inner wall surface 1231, the second inner wall surface 1232, and the third inner wall surface 1233 one to one, and are tightly fitted.

Specifically, the sensor body 122 is cylindrical, the first inner wall surface 1231 is arranged along the radial direction of the sensor body 122, the second inner wall surface 1232 is arranged along the axial direction of the sensor body 122, and the third inner wall surface 1233 is arranged along the radial direction of the sensor body 122.

In other words, the first inner wall surface 1231 and the third inner wall surface 1233 are both planar and annular in shape, and are distributed around the axial direction of the sensor body 122, and the second inner wall surface 1232 is a circumferential surface, and is also distributed around the axial direction of the sensor body 122, so that the design of the annular groove 123 facilitates selection of the type of the elastic sealing ring 13, and generally, the elastic sealing ring 13 with a large elastic coefficient can be selected, and thus, after being mounted in the annular groove 123, the elastic sealing ring 13 can be tightly fitted with the annular groove 123.

Referring to fig. 6, in the present embodiment, the outer side of the elastic sealing ring 13 includes a plurality of annular protruding strips 134 arranged at intervals, and the annular protruding strips 134 are tightly fitted with the through hole 110.

Specifically, the number of the annular ribs 134 shown in fig. 6 is three. This annular sand grip 134 is when contacting with through-hole 110, because two adjacent annular sand grips 134 intervals set up, can more be favorable to this annular sand grip 134 to warp like this, through great deflection, the inner wall of extrusion through-hole 110 that can be better to strengthen sealed effect.

The flight controller 10 provided by the present embodiment has at least the following advantages:

the air pressure sensor 12 is installed and fixed in the through hole 110 through the elastic sealing ring 13, and the elastic sealing ring 13 is sleeved on the air pressure sensor 12, and meanwhile, the outer wall of the elastic sealing ring 13 is tightly matched with the inner wall of the through hole 110, so that the waterproof effect can be improved. Specifically, the inner side of the elastic sealing ring 13 is sleeved in the annular groove 123 of the air pressure sensor 12, so that the sealing effect is good, and meanwhile, the outer side of the elastic sealing ring 13 comprises a plurality of annular convex strips 134 distributed at intervals, so that when the annular convex strips are in contact with the inner wall of the through hole 110, the sealing effect can be enhanced by increasing the deformation.

Meanwhile, when the flight controller 10 is mounted to the body 20, the through hole 110 of the housing 11 may be disposed downward, so that rainwater is not easily infiltrated into the housing 11 when the aircraft 100 encounters rainwater weather.

Moreover, since the detection end face 120 of the air pressure sensor 12 is flush with the outer wall surface 114 of the housing 11, even if rainwater exists on the outer wall surface 114 of the housing 11, the flow of the rainwater is not blocked by the flush arrangement during the flight of the aircraft 100, so that the rainwater is convenient to be blown away.

To sum up, the embodiment of the present invention provides an aircraft controller 10 and an aircraft 100, where the aircraft controller 10 includes a housing 11, an air pressure sensor 12, and an elastic sealing ring 13, and the housing 11 is provided with a through hole 110; the air pressure sensor 12 detects the air pressure outside the shell 11 through the through hole 110, and the air pressure sensor 12 is provided with an annular groove 123; the annular groove 123 is sleeved on the inner side of the elastic sealing ring 13, and the outer side of the elastic sealing ring 13 is located in the through hole 110 and is tightly matched with the through hole 110. Therefore, after the air pressure sensor 12 is mounted on the housing 11, the elastic sealing ring 13 is arranged in the assembly gap between the air pressure sensor 12 and the housing 11, so that a better waterproof effect can be achieved, and meanwhile, the elastic sealing ring 13 is assembled on the air pressure sensor 12 through the annular groove 123, so that the air pressure sensor is not easy to fall off, and is convenient to mount and dismount. It is understood that, since the air pressure sensor 12 is fitted to the through hole 110, sufficient use of space is also achieved, and the integration compactness of the flight controller 10 is improved. In addition, since the air pressure sensor 12 can directly detect the air pressure outside the housing 11 through the through hole 110, the detection accuracy is higher, the overall applicability is stronger, and the air pressure sensor has a wider application scene.

The aircraft 100 includes the flight controller 10, which has all of the functions of the flight controller 10.

The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims (10)

1. A flight controller, comprising:

a housing (11), the housing (11) being provided with a through hole (110);

the air pressure sensor (12), the air pressure sensor (12) detects the air pressure outside the shell (11) through the through hole (110), and the air pressure sensor (12) is provided with an annular groove (123); and

elastic sealing ring (13), the inboard cover of elastic sealing ring (13) is established annular groove (123), the outside of elastic sealing ring (13) is located in through-hole (110) and with through-hole (110) closely cooperate.

2. The flight controller of claim 1, wherein the flight controller (10) further comprises a circuit board (14), the circuit board (14) being located within the housing (11), the barometric pressure sensor (12) being mounted to the circuit board (14).

3. Flight controller according to claim 2, characterized in that the barometric sensor (12) comprises a base (121) and a sensor body (122), the sensor body (122) being connected with the base (121);

the base (121) is mounted to the circuit board (14);

the annular groove (123) is arranged on the sensor body (122), one end face, far away from the base (121), of the sensor body (122) forms a detection end face (120), and the detection end face (120) is used for contacting with the environment outside the shell (11) through the through hole (110).

4. The flight controller according to claim 3, wherein the housing (11) includes an outer wall surface (114) and an inner wall surface (115), the through hole (110) penetrates through the outer wall surface (114) and the inner wall surface (115), and the detection end surface (120) is flush with the outer wall surface (114).

5. Flight controller according to claim 3, characterized in that the annular groove (123) is arranged spaced apart from the detection end face (120).

6. The flight controller according to claim 3, characterized in that the annular groove (123) is defined by a first inner wall surface (1231), a second inner wall surface (1232) and a third inner wall surface (1233) provided in sequence on the sensor body (122);

the first inner wall surface (1231) is provided so as to face the third inner wall surface (1233), and the first inner wall surface (1231) is close to the detection end surface (120) with respect to the third inner wall surface (1233);

the inner side of the elastic sealing ring (13) comprises a first surface (131), a second surface (132) and a third surface (133) which are sequentially connected, wherein the first surface (131), the second surface (132) and the third surface (133) correspond to the first inner wall surface (1231), the second inner wall surface (1232) and the third inner wall surface (1233) in a one-to-one mode and are tightly matched with each other.

7. The flight controller according to claim 6, wherein the sensor body (122) has a cylindrical shape, the first inner wall surface (1231) is provided in a radial direction of the sensor body (122), the second inner wall surface (1232) is provided in an axial direction of the sensor body (122), and the third inner wall surface (1233) is provided in a radial direction of the sensor body (122).

8. Flight controller according to one of claims 1 to 7, characterized in that the outside of the elastic sealing ring (13) comprises a plurality of annular ribs (134) arranged at intervals, the annular ribs (134) mating with the through hole (110).

9. Flight controller according to any one of claims 2 to 7, characterized in that the housing (11) comprises a first housing (111) and a second housing (112), the first housing (111) and the second housing (112) being detachably connected, the circuit board (14) being arranged between the first housing (111) and the second housing (112), the through hole (110) opening onto the first housing (111).

10. An aircraft, characterized in that it comprises a flight controller (10) according to any one of claims 1 to 9.

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