WO2023142769A1

WO2023142769A1 - Aircraft

Info

Publication number: WO2023142769A1
Application number: PCT/CN2022/139735
Authority: WO
Inventors: 李治国; 戴寅; 王彦伟
Original assignee: 汉王科技股份有限公司
Priority date: 2022-01-26
Filing date: 2022-12-16
Publication date: 2023-08-03
Also published as: CN116534261A

Abstract

An aircraft, comprising a housing, wherein an inner cavity is formed in the housing, a driving mechanism (3) and a control unit (4) are provided in the inner cavity, and a camera assembly (2) is provided in the housing; an air inlet (215) is provided on the camera assembly (2), a first air outlet (121) is provided on the housing, and an airflow enters the inner cavity from the air inlet (215), flows through the driving mechanism (3) to the control unit (4), and then is discharged from the first air outlet (121). In the flight process of the aircraft, the inner cavity can form a heat dissipation airflow, and the airflow enters the inner cavity from the air inlet (215), flows through the driving mechanism (3) to the control unit (4), and then is discharged from the first air outlet (121), which facilitates heat dissipation of internal elements of the aircraft and discharge of hot airflow in the inner cavity, especially the heat dissipation speed of the driving mechanism and the control unit is accelerated, the heat dissipation effect is improved, the possibility of damaging the internal elements of the aircraft due to overheating is reduced, and the service life of the aircraft is prolonged.

Description

aircraft

This disclosure claims the priority of the Chinese patent application with the application number 2022100935827 and the title of the invention "aircraft" filed with the China Patent Office on January 26, 2022, the entire contents of which are incorporated by reference in this disclosure.

technical field

This disclosure relates to aircraft.

Background technique

In recent years, aircraft have been loved by more and more people. Existing aircraft is mainly divided into winged aircraft and wingless aircraft. Winged aircraft include fixed-wing aircraft such as airplanes and gliders, and moving-wing aircraft such as rotorcraft and orthopters.

The heat dissipation effect of traditional aircraft is relatively mediocre during use. After long-term flight, the internal heat accumulates and is difficult to dissipate. It is easy to cause overheating and damage to internal components and affect the service life of the aircraft.

Contents of the invention

(1) Technical problems to be solved

When the aircraft is in use, its heat dissipation effect is relatively average. After long-term flight, the internal heat accumulates and is difficult to dissipate, which may easily cause overheating and damage to internal components and affect the service life of the aircraft.

(2) Technical solutions

According to various embodiments disclosed herein, an aircraft is provided.

An aircraft, comprising: a housing, the housing is formed with an inner cavity, the inner cavity is provided with a drive mechanism and a control unit, and the housing is provided with a camera assembly;

Wherein, the camera assembly is provided with an air inlet, and the housing is provided with a first air outlet, and the air flow enters the inner cavity from the air inlet, passes through the driving mechanism, flows to the control unit, and then flows from the first outlet. Vent discharge.

Optionally, the first air outlet is arranged on the top of the housing;

The first air outlet is arranged opposite to the control unit, so that the air flows from the air inlet into the inner cavity, passes through the driving mechanism, flows to the control unit, and then is discharged from the first air outlet.

Optionally, both sides of the housing are provided with second air outlets;

The second air outlet is arranged on two sides of the housing corresponding to the control unit, so that the air flow enters the inner cavity from the air inlet and flows to the control unit after passing through the driving mechanism Exhausted from the second air outlet.

Optionally, the inner cavity is provided with a power supply structure, and the driving mechanism, the control unit and the power supply structure are sequentially arranged along the length direction of the housing;

Both sides of the housing are provided with a third air outlet;

The third air outlet is arranged on two sides of the casing corresponding to the power supply structure, so that the air flow enters the inner cavity from the air inlet and flows to the driving mechanism, the control unit and The power supply structure is then discharged from the third air outlet.

Optionally, the housing includes a machine head and a fuselage connected to the machine head, the connection between the machine head and the fuselage forms a neck, and the camera assembly is arranged on the neck, so The neck is provided with a mounting hole for mounting the camera assembly.

Optionally, the camera assembly includes a mounting platform, and a lens hole is opened on the outer surface of the mounting platform, and the lens hole is provided with a camera for collecting images of the surrounding environment.

Optionally, the axis of the camera forms a first included angle with the central axis in the longitudinal direction of the casing, and the first included angle α satisfies: 40°≤α≤48°.

Optionally, a hole wall at one end of the lens hole close to the outer surface is provided with a boss, the boss extends along the circumference of the lens hole, and the boss is in contact with the camera.

Optionally, the boss includes a slope intersecting the outer surface, the slope forms a second angle with the axis of the camera, and the second angle β satisfies: β≥52°.

Optionally, the installation platform is provided with an air inlet hole, the air inlet hole is located at one end of the outer surface to form the air inlet hole, and the air inlet hole communicates with the inner cavity.

Optionally, the installation platform is provided with a plurality of the air inlet holes, the plurality of the air inlet holes are arranged at intervals, and the plurality of the air inlet holes are arranged around the lens hole.

Optionally, the diameter d of the air inlet hole satisfies: 2mm≤d≤6mm.

Optionally, the camera assembly includes a protective frame, the protective frame is connected to the installation platform, and the protective frame includes a raised portion;

Along the height direction H of the housing, the lowest end of the raised portion is lower than the lowest end of the fuselage.

Optionally, the drive mechanism includes a motor, an impeller and a transmission mechanism; the impeller is connected to the motor;

Wherein, the motor includes an output shaft, the output shaft is arranged along the length direction of the housing, the impeller and the transmission mechanism are both arranged on the output shaft, and the impeller is arranged opposite to the control unit .

Optionally, the motor includes a stator and an outer rotor, and the outer rotor is sleeved on the stator;

The outer rotor, the impeller and the output shaft are of an integral structure.

Optionally, there are multiple impellers, and the multiple impellers are evenly spaced along the circumference of the output shaft.

Optionally, the control unit includes a flight controller, an electronic governor, an image controller and a wireless communication module;

The electronic governor is connected to the driving mechanism, the image controller is connected to the camera assembly, and the wireless communication module is connected to the mobile terminal;

The flight controller is respectively connected with the electronic governor, the image controller and the wireless communication module;

Wherein, the image controller is used to receive the information fed back by the camera assembly, and transmit the information fed back by the camera assembly to the flight controller, and the electronic governor is used to adjust the electronic governor to control the movement of the drive mechanism, and transmit the information fed back by the drive structure to the flight controller, and the wireless communication module is used to send the information received by the flight controller to the mobile terminal or transmit the instruction sent by the mobile terminal to the flight controller.

Optionally, the casing includes a left casing and a right casing, and the inner cavity is formed after the left casing and the right casing are closed.

Optionally, the flight controller includes a first PCB board, the electronic governor includes a second PCB board, the image controller includes a third PCB board, and the wireless communication module includes a fourth PCB board;

The third PCB board and the fourth PCB board are arranged in the left casing, and the third PCB board is connected to the fourth PCB board;

The first PCB board and the second PCB board are arranged in the right casing, and the first PCB board and the second PCB board are connected.

Optionally, the inner cavity is provided with a fuselage frame, and the fuselage frame is connected to the housing;

The driving mechanism, the power supply structure and the control unit are all arranged on the fuselage frame, and the centerlines of the driving mechanism, the power supply structure and the control unit coincide with the centerline of the fuselage frame .

Compared with the prior art, the technical solutions provided by the embodiments of the present disclosure have the following advantages:

The aircraft provided by the embodiments of the present disclosure includes a housing, the housing is formed with an inner cavity, the inner cavity is provided with a driving mechanism and a control unit, and the housing is provided with a camera assembly; wherein, the camera assembly is provided with an air inlet, and the housing is provided with a first The air outlet, the second air outlet, and the third air outlet form an airflow channel between the air inlet and the first air outlet, the second air outlet, and the third air outlet. After entering the inner cavity from the air inlet, the air flows from the first air outlet, The second air outlet and the third air outlet are discharged. During the flight of the aircraft, the inner cavity can form a heat-dissipating airflow, and the airflow enters the inner cavity from the air inlet and is discharged from the first air outlet, the second air exhaust port, and the third air exhaust port, which is convenient for the heat dissipation of the internal components of the aircraft, and the inner cavity The exhaust of the hot air in the engine especially accelerates the heat dissipation speed of the drive mechanism, control unit and power supply structure, improves the heat dissipation effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and prolongs the service life of the aircraft.

Additional features and advantages of the disclosure will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by practice of the disclosure. The objectives and other advantages of the disclosure will be realized and attained by the structure particularly pointed out in the written description, claims hereof as well as the accompanying drawings, the details of one or more embodiments of the disclosure being set forth in the accompanying drawings and the description below.

In order to make the above objects, features and advantages of the present disclosure more comprehensible, optional embodiments are given below and described in detail in conjunction with the accompanying drawings.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, for those of ordinary skill in the art, In other words, other drawings can also be obtained from these drawings without paying creative labor.

FIG. 1 is an exploded view of an aircraft according to an embodiment of the present disclosure;

FIG. 2 is a cross-sectional view of an aircraft according to an embodiment of the present disclosure;

Fig. 3 is a top view of the aircraft described in the embodiment of the present disclosure;

Fig. 4 is a side view structural schematic diagram of the aircraft described in the embodiment of the present disclosure;

FIG. 5 is a schematic structural diagram of another side view of the aircraft according to the embodiment of the present disclosure;

Fig. 6 is a schematic structural view of the aircraft described in the embodiment of the present disclosure after the shell is removed;

FIG. 7 is an exploded view of the aircraft according to the embodiment of the present disclosure after the shell is removed;

8 is a schematic structural diagram of a camera assembly in an aircraft according to an embodiment of the present disclosure;

Fig. 9 is a sectional view along A-A direction of Fig. 8;

FIG. 10 is an exploded view of a camera assembly in an aircraft according to an embodiment of the present disclosure;

FIG. 11 is a schematic structural view of the protective frame of the camera assembly in the aircraft according to the embodiment of the present disclosure;

Fig. 12 is a partially enlarged view of the camera assembly in the aircraft according to the embodiment of the present disclosure;

13 is a schematic diagram of the installation position of the camera assembly in the aircraft according to the embodiment of the present disclosure;

Fig. 14 is a schematic structural diagram of the driving mechanism in the aircraft according to the embodiment of the present disclosure;

FIG. 15 is a cross-sectional view of a driving mechanism in an aircraft according to an embodiment of the present disclosure.

Detailed ways

In order to more clearly understand the above objects, features and advantages of the present disclosure, the solutions of the present disclosure will be further described below. It should be noted that, in the case of no conflict, the embodiments of the present disclosure and the features in the embodiments can be combined with each other.

In the following description, many specific details are set forth in order to fully understand the present disclosure, but the present disclosure can also be implemented in other ways than described here; obviously, the embodiments in the description are only some of the embodiments of the present disclosure, and Not all examples.

The terms "first" and "second" and the like in the specification and claims of the present disclosure are used to distinguish different objects, rather than to describe a specific order of objects. For example, the first camera and the second camera are used to distinguish different cameras, not to describe a specific order of the cameras.

In the embodiments of the present disclosure, words such as "exemplary" or "for example" are used as examples, illustrations or illustrations. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present disclosure shall not be construed as being preferred or advantageous over other embodiments or designs. To be precise, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific manner. In addition, in the description of the embodiments of the present disclosure, unless otherwise specified, the meaning of "plurality" refers to two one or more.

As shown in FIGS. 1-6 , the aircraft provided by the embodiment of the present disclosure includes a housing, the housing is formed with an inner cavity, the inner cavity is provided with a drive mechanism 3 and a control unit 4, and the housing is provided with a camera assembly 2; wherein, the camera The component 2 is provided with an air inlet 215, and the housing is provided with a first air outlet 121. An airflow channel can be formed between the air inlet 215 and the first air outlet 121. The airflow enters the inner cavity from the air inlet 215 and flows to the control unit 4 through the drive mechanism 3. Then it is discharged from the first air outlet 121. During the flight of the aircraft, the inner cavity can form a cooling air flow. The air flow enters the inner cavity from the air inlet 215 and flows to the control unit 4 through the driving mechanism 3. After that, it is discharged from the first air outlet 121, which is convenient for the interior of the aircraft. The heat dissipation of the components discharges the hot air in the inner cavity. The airflow channel formed between the air inlet 215 and the first air outlet 121 especially accelerates the heat dissipation speed of the drive mechanism 3 and the control unit 4, improves the heat dissipation effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and prolongs the service life of the aircraft.

In addition, the airflow channel formed between the air inlet 215 and the first air outlet 121 can also reduce wind resistance.

In the embodiment of the present disclosure, the number of the air inlet 215 is at least one, and can be set in multiples as required.

There may be multiple first air outlets 121 . When two or more first air outlets 121 are provided, the two or more first air outlets 121 are arranged at intervals along the length direction of the aircraft, which further improves the heat dissipation performance of the aircraft.

In some specific embodiments, the first air outlet 121 is arranged on the top of the housing, so that the airflow can be smoothly discharged from the first air outlet 121 after entering the air inlet 215, which is convenient for the heat dissipation of the electronic components inside the aircraft, and at the same time can Reduce wind resistance. The first air outlet 121 is arranged opposite to the control unit 4 , which is beneficial to the heat dissipation of the control unit 4 . The first air outlet 121 is arranged opposite to the control unit 4 so that the air flow enters the inner cavity from the air inlet 215 and flows through the drive mechanism 3 to the control unit 4, and then is discharged from the first air outlet 121, so that the heat generated by the drive mechanism 3 and the control unit 4 can be discharged from the first air outlet 121. The air is discharged from the first air outlet 121, which reduces the possibility of damage to the driving mechanism 3 and the control unit 4 due to overheating, and prolongs the service life of the aircraft.

In some specific embodiments, both sides of the casing are provided with second air outlets 122, so that the airflow can be smoothly discharged from the second air outlets 122 after entering from the air inlet 215, which is convenient for the heat dissipation of the electronic components inside the aircraft, and at the same time Also reduces wind resistance. The second air outlet 122 is arranged on two sides of the housing corresponding to the control unit 4 , so that the air flow enters the inner cavity from the air inlet 215 and flows to the control unit 4 through the driving mechanism 3 , and then is discharged from the second air outlet 122 . During the flight of the aircraft, the inner cavity can form a heat-dissipating airflow. The airflow enters the inner cavity from the air inlet 215 and flows to the control unit 4 through the drive mechanism 3. The hot air flow in the cavity is discharged, especially the heat dissipation speed of the control unit 4 is accelerated, the heat dissipation effect is improved, the possibility of damage to the internal components of the aircraft due to overheating is reduced, and the service life of the aircraft is prolonged.

Optionally, the number of the second air outlet 122 on each side of the casing is at least one, and can be set in multiples as required. When two or more second air outlets 122 are provided, the two or more second air outlets 122 are arranged at intervals along the length direction of the aircraft, which further improves the heat dissipation performance of the aircraft.

When the casing is respectively provided with a first air outlet 121 and two sets of second air outlets 122 . The airflow enters from the air inlet 215 to form three airflows, which are respectively discharged from the first air outlet 121 and two groups of second air outlets 122, which improves the heat dissipation effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and prolongs the life of the aircraft. service life.

As shown in FIG. 1 , FIG. 2 and FIG. 6 , the inner cavity is provided with a power supply structure 5 , and the driving mechanism 3 , the control unit 4 and the power supply structure 5 are sequentially arranged along the length direction of the casing. Both sides of the housing are provided with a third air outlet 123, so that the airflow can be smoothly discharged from the third air outlet 123 after entering from the air inlet 215, which is convenient for the heat dissipation of the electronic components inside the aircraft and can also reduce wind resistance.

The third air outlet 123 is arranged on the two sides of the housing corresponding to the power supply structure 5, so that the air flow enters the inner cavity from the air inlet 215 and flows to the drive mechanism 3, the control unit 4 and the power supply structure 5, and then is discharged from the third air outlet 123 . During the flight of the aircraft, the inner cavity can form a heat-dissipating airflow, and the airflow enters the inner cavity from the air inlet 215, passes through the drive mechanism 3, flows to the control unit 4 and the power supply structure 5, and then is discharged from the third air outlet 123 on both sides, which is convenient for the internal components of the aircraft. Heat dissipation is to discharge the hot air in the inner cavity, especially to accelerate the heat dissipation speed of the power supply structure 5, improve the heat dissipation effect, reduce the possibility of damage to the internal components of the aircraft due to overheating, and prolong the service life of the aircraft.

Optionally, the number of the third air outlet 123 on each side of the casing is at least one, and can be set in multiples as required. When two or more third air outlets 123 are provided, the two or more third air outlets 123 are arranged at intervals along the length direction of the aircraft, which further improves the heat dissipation performance of the aircraft.

When the casing is respectively provided with a first air outlet 121 , two sets of second air outlets 122 and two sets of third air outlets 123 . The airflow enters from the air inlet 215 to form a plurality of airflows, which are respectively discharged from the first air outlet 121, two groups of second air outlets 122 and two groups of third air outlets 123, which improves the heat dissipation effect and reduces the internal components of the aircraft due to overheating. The possibility of damage, while reducing wind resistance, prolonging the service life of the aircraft.

The power supply structure 5 may include a battery assembly. Optionally, the casing is provided with a mounting hole for installing the battery assembly, and the battery assembly is detachably mounted on the casing through the mounting hole for supplying power to the aircraft. The battery assembly includes a battery, and the battery may be a secondary battery that can be repeatedly charged and discharged.

Optionally, the power supply structure 5 , the driving mechanism 3 , the control unit 4 and the power supply structure 5 are sequentially arranged along the central axis in the longitudinal direction of the housing.

In some specific embodiments, the casing includes a nose 11 and a fuselage 12 connected to the nose 11, the nose 11 is arranged at the front end of the aircraft, and is used to point to the flight direction of the aircraft, and the fuselage 12 is equipped with a drive mechanism 3. Control unit 4 and power supply structure 5, etc. The junction of the nose 11 and the fuselage 12 forms a neck 16 .

In some specific implementation manners, in order to obtain surrounding scenes during the flight of the aircraft, a camera component is installed on the aircraft to collect images of the surrounding environment of the aircraft. The camera assembly 2 is arranged on the neck 16 of the aircraft, and the neck 16 of the aircraft is provided with a mounting hole 111 for installing the camera assembly 2. The opening direction of the mounting hole 111 is slightly inclined downward, so that the camera assembly 2 is inclined downward during installation, which can be more Good shot of the scene below the aircraft. The camera assembly 2 includes a camera 23 installed in the installation hole 111 . When the aircraft lands on the ground, even if the aircraft leans over and tilts slightly, the camera 23 will not rub against the ground, which reduces the possibility of damage to the camera 23 . When the aircraft is flying, the camera assembly 2 is placed at the neck 16, and the acquisition angle of view of the camera assembly 2 will not be blocked. Even if the flight attitude changes, such as rolling or pitching, the shooting field of view of the camera assembly 2 will not be affected.

The neck 16 of the aircraft is arranged on the position of the fuselage 12 near the nose 11, and the camera assembly 2 arranged on the neck 16 will not rub the camera 23 with the ground when the aircraft lands on the ground. The collision caused by the camera 23 improves the service life of the camera 23 .

Specifically, as shown in FIGS. 8-13 , the camera assembly 2 includes a mounting table 21, the mounting table 21 includes an outer surface 211, the outer surface 211 is provided with a lens hole 212, and the lens hole 212 is provided with a camera 23 for collecting images of the surrounding environment. . When the camera 23 is installed, it is inclined downward, which can better photograph the environment below the aircraft, making the layout of the camera 23 more reasonable. The camera 23 may be a 360-degree panoramic camera, and in some specific embodiments, the camera 23 may also be a fixed-focus lens. The camera head 23 can be screwed, fastened, glued, etc. to the mounting table 21 at the lens hole 212 . With the above solution, the installation platform 21 has a simple structure, and the installation platform 21 is connected to the aircraft in a detachable manner, which is convenient for installation and disassembly.

As shown in FIG. 13 , the central axis in the longitudinal direction of the aircraft is located on the fuselage of the aircraft, and the first angle formed between the axis of the camera and the central axis in the longitudinal direction of the aircraft is α. When the aircraft is flying, under the action of the aerodynamic moment, the fuselage 12 will maintain a certain elevation angle, that is, the elevation angle γ formed by the central axis in the longitudinal direction of the aircraft and the horizontal direction L. Sensors are installed on the aircraft to obtain the attitude information of the aircraft. By analyzing the data collected by the sensors, it can be obtained that the range of the elevation angle γ of the aircraft during flight is 10°≤γ≤20°.

As shown in Figure 13, the angle formed by the axis of the camera and the horizontal direction L is α-γ. Therefore, when the aircraft is flying forward, when the result of satisfying 90°-(α-γ)-β is not less than 0°, That is, when the first included angle α satisfies: 40°≤α≤48°, the field of view of the camera 23 is on the left side of the vertical direction H, the range of images collected by the camera 23 is relatively wide, and the image quality is clear, which is convenient for the camera 23 Take pictures of the environment below the aircraft.

It should be noted that the above-mentioned horizontal direction L refers to a direction parallel to the ground, and the above-mentioned vertical direction refers to a direction perpendicular to the ground.

Preferably, the first included angle formed by the axis of the camera 23 and the central axis in the longitudinal direction of the aircraft is set to 45°, so that the images captured by the camera 23 are clearer, and the environment below the aircraft can be better photographed.

Further, the flying height of the aircraft is set to be no more than 50 meters, that is, the distance between the flying height of the aircraft and the ground is no more than 50 meters, the images captured by the camera 23 are clear and the aircraft can reduce damage to the aircraft and ground objects in the event of a fall . Specifically, when the flying height is 50 meters, the distance range of the horizontal direction of the ground covered by the field of view of the camera 23 is between 69 meters and 96 meters. In this range, the resolution of the image is high, and the camera 23 can collect Quality clear images. Moreover, within the flight altitude range of no more than 50 meters, when the aircraft suddenly falls and other emergencies occur during the flight, the limited flight altitude can effectively reduce the damage to ground objects and the aircraft itself due to the accidental fall of the aircraft. .

In some specific embodiments, the hole wall of the lens hole 212 near the end of the outer surface 211 is provided with a boss 213, and the boss 213 extends along the circumference of the lens hole 212, and the boss 213 is in contact with the camera 23, so that the camera 23 is accommodated In the lens hole 212, when the aircraft lands on the ground, the camera 23 can be prevented from rubbing against the ground, which can effectively solve the problem that the camera 23 is easy to break when the aircraft fails and falls.

In some specific embodiments, the boss 213 includes a slope 213a intersecting the outer surface 211, the slope 213a forms a second angle with the axis of the camera 23, and the second angle β satisfies: β≥52°, which can reduce the convexity. The occlusion of the field of view of the camera 23 by the platform 213 enables the camera 23 to adopt a wide-angle lens of 104°. When the aircraft is flying at high altitude, it can obtain a larger field of view for shooting. .

In some specific embodiments, the installation platform 21 is provided with an air inlet 214, and one end of the air inlet 214 located on the outer surface 211 forms an air inlet 215, and the air inlet 214 communicates with the inner cavity. During the flight of the aircraft, the airflow enters the air inlet 214 from the air inlet 215, and then enters the inner cavity, and takes away the heat of the driving mechanism 3, the control unit 4 or the power supply structure 5 in the inner cavity, and flows from the first air outlet 121, the second air outlet The second air outlet 122 or the third air outlet 123 is discharged to facilitate the heat dissipation of the internal components of the aircraft, and the hot air in the inner cavity can be discharged, especially the heat dissipation speed of the drive mechanism 3, the control unit 4 and the power supply structure 5 has been accelerated, and the heat dissipation has been improved. As a result, the possibility of damage to the internal components of the aircraft due to overheating is reduced, and the service life of the aircraft is extended.

In some specific embodiments, the installation platform 21 is provided with a plurality of air inlet holes 214, which can ensure that enough wind enters the inner cavity of the fuselage 12 and improves the heat dissipation effect of the aircraft. The plurality of air inlet holes 214 are arranged at intervals, and A plurality of air inlet holes 214 are arranged around the lens hole 212, so that the airflow can enter each air inlet hole 214 more evenly and enter the inner cavity from the air inlet holes 214, thereby improving the flight stability of the aircraft.

In some specific implementations, the diameter d of the air inlet hole 214 satisfies: 2mm≤d≤6mm, which can improve the heat dissipation effect of the aircraft, reduce the possibility of damage to internal components of the aircraft due to overheating, and prolong the service life of the aircraft.

Preferably, four air inlet holes 214 are uniformly arranged around the lens hole 212, and the diameter of the air inlet holes is 5mm or about 5mm, which can ensure that enough wind enters the inner cavity of the fuselage 12, and can also block larger airflow at the same time. Debris, reducing the possibility of debris entering the aircraft body and damaging the internal structure.

In some specific implementations, the camera assembly 2 includes a protective frame 22 , which is attached to the fuselage 12 to reduce the possibility of the fuselage 12 being directly collided and protect the fuselage 12 . Optionally, the shape of the protective frame 22 is adapted to the fuselage 12, so that the protective frame 22 fits better with the fuselage 12, so that when the aircraft lands, the protective frame 22 is in contact with the ground to prevent the fuselage 12 from contacting the ground. Friction damage occurs, prolonging the service life of the aircraft. The protective frame 22 is connected with the mounting table 21, and the protective frame 22 and the mounting table 21 are of an integrated structure. The protective frame 22 includes a raised portion 221; as shown in FIG. 2 , along the height direction H of the housing, the lowest end of the raised portion 221 is lower than the lowest end of the fuselage 12, so that when the aircraft lands, the raised portion 221 first landing. Therefore, when the aircraft lands, the raised portion 221 contacts the ground first, which reduces the damage of the fuselage 12 due to friction with the ground, and plays a shock absorbing function, prolonging the service life of the aircraft.

Optionally, the protective frame 22 may be made of polypropylene, which has high toughness and impact resistance. Optionally, the housing can be made of foamed plastics, which have good compression resistance and cushioning properties.

2, FIG. 9 and FIG. 10, the lowest end of the raised portion 221 is lower than the lowest end of the fuselage 12, so that the raised portion 221 is the lowest point of the aircraft, the camera 23 is installed higher than the raised portion 221, and the aircraft At the moment of landing, the raised portion 221 touches the ground first, and under the synergistic effect of the two materials of the protective frame 22 and the shell, it can effectively buffer the impact force on the camera 23, protect the camera 23, and prevent the camera 23 from being damaged when the aircraft lands.

As shown in Fig. 6, Fig. 14 and Fig. 15, the driving mechanism 3 includes a motor 31, an impeller 32 and a transmission mechanism 33; the impeller 32 is connected to the motor 31; wherein, the motor 31 includes an output shaft 311, and the output shaft 311 is along the length of the housing The direction is set, the impeller 32 and the transmission mechanism 33 are all arranged on the output shaft 311, the impeller 32 is arranged opposite to the control unit 4, so that the airflow generated by the rotation of the impeller 32 can flow backward and blow to the control unit 4. In this embodiment, the casing can form an axial air duct, and the airflow can be accelerated after passing through the impeller 32, and the accelerated airflow can perform forced convection and heat dissipation on the control unit 4 and the power supply structure 5, which improves the connection between the control unit 4 and the power supply structure 5. For heat dissipation performance, the impeller 32 is arranged on the output shaft 311 of the motor 31, which accelerates the air flow velocity in the inner cavity and improves the heat exchange efficiency of the axial air duct formed in the casing.

In some specific embodiments, the motor 31 includes a stator 312 and an outer rotor 313, and the outer rotor 313 is sleeved on the stator 312; the outer rotor 313, the impeller 32 and the output shaft 311 are integrated, so that the output shaft 311 of the motor 31 rotates When driving the impeller 32 to rotate, the consumption of electric energy will not be increased too much, the efficiency of the motor will be increased, and the air flow in the inner cavity can be increased to improve the heat dissipation efficiency during the operation of the motor 31. When energized, the stator 312 of the motor 31 does not rotate, and the outer rotor 313 of the motor 31 rotates at a high speed. The driving gear fixedly connected to the motor 31 shaft drives the wings to flutter through the power transmission assembly, and the impeller 32 fixedly connected to the motor 31 shaft A wind along the length of the housing is generated to dissipate heat for the control unit 4 and the power supply structure 5 .

In some specific embodiments, the number of impellers 32 is multiple, and the plurality of impellers 32 are evenly spaced along the circumference of the output shaft 311. When the impellers 32 rotate, the airflow can flow through the middle of the impellers 32, which is beneficial to the airflow. Circulation can improve heat dissipation efficiency, and while the motor 31 runs stably and smoothly, it prolongs the service life of each internal component.

Optionally, the transmission mechanism 33 may include the fuselage frame 15, a gear set, a connecting rod and a swing bracket. The fuselage frame 15 can be installed on the casing, and is used for fixing the transmission mechanism 33 to the casing. A gear set may be mounted to the fuselage frame 15 and driven by a motor 31 . The gear set can also be connected with the connecting rod transmission. For example, a gear in a gear set can be connected to one end of a connecting rod so that rotation of the gear moves the connecting rod with it. The other end of the connecting rod can be pivotally connected with the swing bracket, so that the swing bracket can move accordingly under the drive of the connecting rod. In addition, the swing bracket can also be pivotally connected with the fixed bracket so that the swing bracket can be supported. The wings of the aircraft can be connected with the swing bracket, so that the swing bracket drives the wing to flutter up and down.

As shown in FIG. 6 and FIG. 7, optionally, the gear set is installed on the bracket and symmetrically distributed on both sides of the fuselage frame 15, and the motor 31 is installed on the bracket of the gear set and symmetrically distributed on the fuselage both sides of the frame 15. The rear end of the fuselage frame 15 along the length direction of the housing is provided with a square hole, and the power supply structures 5 are embedded in the square hole and symmetrically distributed on both sides of the fuselage frame 15 .

Shown in conjunction with Fig. 6 and Fig. 7, control unit 4 comprises flight controller 41, electronic governor 42, image controller 43 and wireless communication module 44; Electronic governor 42 is connected with drive mechanism 3, and image controller 43 is connected with The camera assembly 2 is connected, and the wireless communication module 44 is connected with the mobile terminal; the flight controller 41 is connected with the electronic governor 42, the image controller 43 and the wireless communication module 44 respectively; wherein, the image controller 43 is used to receive feedback from the camera assembly 2 information, and the information fed back by the camera assembly 2 is transmitted to the flight controller 41, and the electronic governor 42 is used to adjust the electronic governor 42 according to the instruction sent by the flight controller 41 so as to control the movement of the driving mechanism 3, and the driving structure The feedback information is transmitted to the flight controller 41 , and the wireless communication module 44 is used to send the information received by the flight controller 41 to the mobile terminal, and transmit the instruction sent by the mobile terminal to the flight controller 41 .

The power supply structure 5 is respectively connected with the driving mechanism 3 , the image controller 43 , the camera assembly 2 and the wireless communication module 44 for supplying power to the driving mechanism 3 , the image controller 43 , the camera assembly 2 and the wireless communication module 44 .

In order to make full use of the space inside the casing, the flight controller 41 and the electronic governor 42 are arranged in the right casing 14 , and the image controller 43 and the wireless communication module 44 are arranged in the left casing 13 .

In some specific embodiments, the flight controller 41 includes a first PCB board, the electronic governor 42 includes a second PCB board, the image controller 43 includes a third PCB board, and the wireless communication module 44 includes a fourth PCB board; Three PCB boards and the fourth PCB board are arranged in the left casing 13, and the third PCB board and the fourth PCB board are connected; The first PCB board and the second PCB board are arranged in the right casing 14, and the first PCB board and the second PCB board Two PCB board connections. The first PCB board, the second PCB board, the third PCB board and the fourth PCB board are evenly arranged on both sides of the central axis of the fuselage 12, which can ensure that the center of gravity of the aircraft is located on the central axis of the fuselage 12, and prevent the aircraft from tilting left and right when flying , to ensure the smooth flight of the aircraft.

Optionally, the first PCB board and the second PCB board are electrically connected without touching each other, the flight control module is integrated on the first PCB board, and the electronic speed control module is integrated on the second PCB board, which is beneficial to avoid other components from causing damage to it. Interference, while reducing the impact of the heat emitted by the electronic speed control module on the flight control module, and improving the sensitivity of the signal transmission of the flight control module.

Optionally, the third PCB board and the fourth PCB board are electrically connected without contacting each other, the image control module is integrated on the third PCB board, and the wireless communication module 44 is integrated on the fourth PCB board, which is beneficial to avoid other components from causing damage to it. At the same time, it reduces the influence of the heat emitted by the image control module on the wireless communication module 44, improves the wireless transmission sensitivity and transmission speed of images, and prolongs the wireless transmission distance of images.

Optionally, the first PCB board and the second PCB board are connected through an electrical connector, and the third PCB board and the fourth PCB board are connected through an electrical connector.

Optionally, the camera 23 is used to take images or video images during the flight and deliver the images or video signals to the processor, after processing by the processor, the information fed back by the camera 23 is delivered to the flight controller 41, and the wireless communication module 44 is used for sending the information received by the flight controller 41 to the mobile terminal or transferring the instruction sent by the mobile terminal to the flight controller 41 . Through the mobile terminal on the ground, you can directly watch the images taken by the aircraft during flight, and it is more convenient to judge whether the aircraft is in a normal flight working state, so as to control the flight state of the aircraft.

The mobile terminal may include a dedicated remote controller of the aircraft or a mobile phone or other wireless communication equipment.

As shown in FIG. 1 , FIG. 3 and FIG. 6 , in some specific embodiments, the casing includes a left casing 13 and a right casing 14 , and the left casing 13 and the right casing 14 are closed to form an inner cavity. Optionally, a plurality of notches are provided on the left casing 13 and the right casing 14, and a plurality of protrusions are arranged on the outer edge of the fuselage frame 15, and the plurality of protrusions are clamped and fixed with corresponding plurality of notches. . The left casing 13 and the right casing 14 are fastened together. Optionally, the left casing 13 and the right casing 14 can be connected by buckle, thread, fastener or adhesive. Optionally, the left casing 13 and the right casing 14 can choose one or a combination of at least two of buckle connection, screw connection, fastener connection and bonding.

In some specific embodiments, the inner cavity is provided with a fuselage frame 15, and the fuselage frame 15 is connected to the casing; the driving mechanism 3, the power supply structure 5 and the control unit 4 are all arranged on the fuselage frame 15, and the driving mechanism 3 , the center line of the power supply structure 5 and the control unit 4 coincides with the center line of the fuselage frame 15, which can ensure that the center of gravity of the aircraft is located on the central axis of the fuselage 12, prevent the aircraft from tilting left and right, and ensure the smooth flight of the aircraft.

By arranging the driving mechanism 3, the power structure 5 and the control unit 4 on the fuselage frame 15, the driving mechanism 3, the power structure 5 and the control unit 4 can be formed into an integrated module, which is easy to install and can improve the stability of the structure.

Optionally, the fuselage frame 15 is provided with at least one hollow hole to reduce the weight of the aircraft. The driving mechanism 3 , the power supply structure 5 and the control unit 4 can be respectively arranged in the hollow holes to improve the stability of the connection between the driving mechanism 3 , the power supply structure 5 and the control unit 4 and the fuselage frame 15 .

The technical features of the above embodiments can be combined arbitrarily. To make the description concise, all possible combinations of the technical features in the above embodiments are not described. However, as long as there is no contradiction in the combination of these technical features, they should be It is considered to be within the range described in this specification.

The above examples only express several implementations of the present disclosure, and the descriptions thereof are more specific and detailed, but should not be construed as limiting the scope of the patent for the invention. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present disclosure, and these all belong to the protection scope of the present disclosure. Therefore, the scope of protection of the disclosed patent should be based on the appended claims.

Industrial Applicability

In the aircraft disclosed in the present disclosure, the camera assembly 2 is provided with an air inlet 215, and the casing is provided with a first air outlet 121, and an airflow channel can be formed between the air inlet 215 and the first air outlet 121, and the airflow enters the inner cavity from the air inlet 215 After the drive mechanism 3 flows to the control unit 4, it is discharged from the first air outlet 121. During the flight of the aircraft, the inner cavity can form a heat dissipation airflow, and the air flow enters the inner cavity from the air inlet 215, passes through the drive mechanism 3, flows to the control unit 4, and then flows from the first air outlet. The air outlet 121 is exhausted, which facilitates the heat dissipation of the internal components of the aircraft, and discharges the hot air in the inner cavity. The airflow channel formed between the air inlet 215 and the first air outlet 121 especially accelerates the heat dissipation speed of the drive mechanism 3 and the control unit 4, improves the heat dissipation effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and prolongs the The service life of the aircraft reduces the replacement cost and has strong industrial applicability.

Claims

An aircraft, characterized in that it comprises: a housing, the housing is formed with an inner chamber, the inner chamber is provided with a drive mechanism (3) and a control unit (4), and the housing is provided with a camera assembly (2 );

Wherein, the camera assembly (2) is provided with an air inlet (215), and the housing is provided with a first air outlet (121), and the air flow enters the inner cavity from the air inlet (215) and passes through the driving mechanism (3) flow to the control unit (4) and then be discharged from the first air outlet (121).
The aircraft according to claim 1, characterized in that, the first air outlet (121) is arranged on the top of the housing;

The first air outlet (121) is arranged opposite to the control unit (4), so that the air flow enters the inner cavity from the air inlet (215) and flows to the control unit through the driving mechanism (3). The unit (4) is then discharged from the first air outlet (121).
The aircraft according to claim 1, characterized in that, both sides of the housing are provided with a second air outlet (122);

The second air outlet (122) is arranged on two sides of the housing corresponding to the control unit (4), so that the airflow enters the inner cavity from the air inlet (215) and passes through the The drive mechanism (3) flows to the control unit (4) and then is discharged from the second air outlet (122).
The aircraft according to claim 1, characterized in that, the inner cavity is provided with a power supply structure (5), and the drive mechanism (3), the control unit (4) and the power supply structure (5) are arranged along the The length direction of the housing is set in sequence;

Both sides of the housing are provided with a third air outlet (123);

The third air outlet (123) is arranged on two sides of the casing corresponding to the power supply structure (5), so that the air flow enters the inner cavity from the air inlet (215) and flows toward the The drive mechanism (3), the control unit (4) and the power supply structure (5) are discharged from the third air outlet (123).
The aircraft according to any one of claims 1 to 4, wherein the housing comprises a nose (11) and a fuselage (12) connected to the nose (11), the nose ( 11) A neck (16) is formed at the joint with the fuselage (12), the camera assembly (2) is arranged on the neck (16), and the neck (16) is provided with the camera Mounting holes for component (2).
The aircraft according to claim 5, wherein the camera assembly (2) comprises a mounting platform (21), and an outer surface (211) of the mounting platform (21) is provided with a lens hole (212), so The lens hole (212) is provided with a camera (23) for collecting images of the surrounding environment.
The aircraft according to claim 6, characterized in that, the axis of the camera (23) forms a first angle with the central axis in the longitudinal direction of the housing, and the first angle α satisfies: 40°≤ α≤48°.
The aircraft according to claim 6, wherein a boss (213) is provided on the hole wall of the lens hole (212) near one end of the outer surface (211), and the boss (213) is arranged along the wall of the lens hole (213). The circumferential extension of the lens hole (212), the boss (213) is in contact with the camera (23).
The aircraft according to claim 8, characterized in that, the boss (213) includes an inclined plane (213a) intersecting with the outer surface (211), and the inclined plane (213a) is in line with that of the camera (23) The axes form a second included angle, and the second included angle β satisfies: β≧52°.
The aircraft according to claim 6, characterized in that, the mounting platform (21) is provided with an air inlet hole (214), and the air inlet hole (214) is located at one end of the outer surface (211) to form the An air inlet (215), the air inlet hole (214) communicates with the inner cavity.
The aircraft according to claim 10, characterized in that, the installation platform (21) is provided with a plurality of the air inlet holes (214), the plurality of the air inlet holes (214) are arranged at intervals, and the plurality of the air inlet holes (214) The air inlet hole (214) is arranged around the lens hole (212).
The aircraft according to claim 10, characterized in that, the aperture d of the air inlet hole (214) satisfies: 2mm≤d≤6mm.
The aircraft according to claim 5, wherein the camera assembly (2) includes a protective frame (22), the protective frame is connected to the installation platform (21), and the protective frame (22) includes a convex starting part(221);

Along the height direction (H) of the housing, the lowest end of the raised portion (221) is lower than the lowest end of the fuselage (12).
The aircraft according to any one of claims 1 to 4, characterized in that, the drive mechanism (3) comprises a motor (31), an impeller (32) and a transmission mechanism (33); the impeller (32) and the Described motor (31) is connected;

Wherein, the motor (31) includes an output shaft (311), the output shaft (311) is arranged along the length direction of the housing, and the impeller (32) and the transmission mechanism (33) are both arranged on the On the output shaft (311), the impeller (32) is arranged opposite to the control unit (4).
The aircraft according to claim 14, characterized in that, the motor (31) comprises a stator (312) and an outer rotor (313), and the outer rotor (313) is sleeved on the stator (312);

The outer rotor (313), the impeller (32) and the output shaft (311) are of an integral structure.
The aircraft according to claim 14, characterized in that the number of the impellers (32) is multiple, and the multiple impellers (32) are evenly spaced along the circumferential direction of the output shaft (311).
The aircraft according to any one of claims 1 to 4, wherein the control unit (4) includes a flight controller (41), an electronic governor (42), an image controller (43) and a wireless communication module(44);

The electronic governor (42) is connected to the drive mechanism (3), the image controller (43) is connected to the camera assembly (2), and the wireless communication module (44) is connected to a mobile terminal;

The flight controller (41) is respectively connected with the electronic governor (42), the image controller (43) and the wireless communication module (44);

Wherein, the image controller (43) is used to receive the information fed back by the camera assembly (2), and transmit the information fed back by the camera assembly (2) to the flight controller (41), and the electronic The governor (42) is used to adjust the electronic governor (42) according to the instruction sent by the flight controller (41) so as to control the movement of the driving mechanism (3), and to control the movement of the driving mechanism (3) The feedback information is delivered to the flight controller (41), and the wireless communication module (44) is used to send the information received by the flight controller (41) to the mobile terminal or send the mobile terminal The instructions are passed to the flight controller (41).
The aircraft according to claim 17, characterized in that, the casing comprises a left casing (13) and a right casing (14), and the left casing (13) and the right casing (14) are closed Then the inner cavity is formed.
The aircraft according to claim 18, wherein the flight controller (41) comprises a first PCB board, the electronic governor (42) comprises a second PCB board, and the image controller (43) Including a third PCB board, the wireless communication module (44) includes a fourth PCB board;

The third PCB board and the fourth PCB board are arranged in the left casing (13), and the third PCB board and the fourth PCB board are connected;

The first PCB board and the second PCB board are arranged in the right casing (14), and the first PCB board and the second PCB board are connected.
The aircraft according to claim 18, characterized in that, the inner cavity is provided with a fuselage frame (15), and the fuselage frame (15) is connected to the housing;

The driving mechanism (3), the power supply structure (5) and the control unit (4) are all arranged on the fuselage frame (15), and the driving mechanism (3), the power supply structure (5) And the centerline of the control unit (4) coincides with the centerline of the fuselage frame (15).