aircraft

Abstract

The present disclosure relates to the technical field of aircraft, and particularly relates to an aircraft. The aircraft provided by the present disclosure comprises a shell, the shell is formed with an inner cavity, the inner cavity is provided with a driving mechanism and a control unit, and the shell is provided with a camera assembly; wherein the camera assembly is provided with an air inlet, the shell is provided with a first air outlet, and airflow enters the inner cavity from the air inlet, flows to the control unit through the driving mechanism, and is discharged from the first air outlet. During the flight of the aircraft, the inner cavity can form a heat dissipation airflow, the airflow enters the inner cavity from the air inlet, flows to the control unit through the driving mechanism, and is discharged from the first air outlet, so as to facilitate the heat dissipation of the internal elements of the aircraft, discharge the hot airflow in the inner cavity, especially accelerate the heat dissipation speed of the driving mechanism and the control unit, improve the heat dissipation effect, reduce the possibility of damage of the internal elements of the aircraft due to overheating, and prolong the service life of the aircraft.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft technology, and more particularly to an aircraft. Background Technology

[0002] In recent years, aircraft have become increasingly popular. Existing aircraft are 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 flapping-wing aircraft.

[0003] Traditional aircraft have relatively poor heat dissipation during use. After long-term flight, internal heat accumulates and is difficult to dissipate, which can easily cause overheating and damage to internal components, affecting the service life of the aircraft. Summary of the Invention

[0004] To address the aforementioned technical problems, this disclosure provides an aircraft.

[0005] This disclosure provides an aircraft, including: a shell, the shell having an inner cavity, the inner cavity having a drive mechanism and a control unit, and the shell having a camera assembly;

[0006] The camera assembly is provided with an air inlet, and the housing is provided with a first air outlet. Airflow enters the inner cavity from the air inlet, flows through the drive mechanism to the control unit, and is then discharged from the first air outlet.

[0007] Furthermore, the first air outlet is located at the top of the housing;

[0008] The first air outlet is positioned opposite to the control unit so that the airflow enters the inner cavity from the air inlet, flows through the drive mechanism to the control unit, and is then discharged from the first air outlet.

[0009] Furthermore, a second air outlet is provided on both sides of the housing;

[0010] The second air outlet is located on both sides of the housing corresponding to the control unit, so that the airflow enters the inner cavity from the air inlet, flows through the drive mechanism to the control unit, and is discharged from the second air outlet.

[0011] Furthermore, the inner cavity is provided with a power supply structure, and the drive mechanism, the control unit, and the power supply structure are arranged sequentially along the length direction of the housing;

[0012] The housing is provided with a third air outlet on both sides;

[0013] The third air outlet is located on both sides of the housing corresponding to the power supply structure, so that the airflow enters the inner cavity from the air inlet, flows to the drive mechanism, the control unit and the power supply structure and then exits from the third air outlet.

[0014] Furthermore, the housing includes a head and a body connected to the head, the connection between the head and the body forming a neck, the camera assembly being disposed on the neck, and the neck having mounting holes for mounting the camera assembly.

[0015] Furthermore, the camera assembly includes a mounting platform, the outer surface of which has a lens hole, and the lens hole is equipped with a camera for acquiring images of the surrounding environment.

[0016] Furthermore, the axis of the camera forms a first angle with the central axis of the housing along its length, and the first angle α satisfies: 40°≤α≤48°.

[0017] Furthermore, a boss is provided on the end of the lens hole near the outer surface, the boss extends circumferentially along the lens hole, and the boss contacts the camera.

[0018] Furthermore, the boss includes an inclined surface that intersects the outer surface, and the inclined surface forms a second angle β with the axis of the camera, the second angle β satisfying: β≥52°.

[0019] Furthermore, the mounting platform is provided with an air inlet, which is located at one end of the outer surface to form the air inlet, and the air inlet communicates with the inner cavity.

[0020] Furthermore, the mounting platform has multiple air inlets, which are spaced apart and arranged around the lens hole.

[0021] Furthermore, the diameter d of the air inlet hole satisfies: 2mm≤d≤6mm.

[0022] Furthermore, the camera assembly includes a protective frame connected to the mounting platform, and the protective frame includes a protrusion.

[0023] Along the height direction H of the housing, the lowest point of the protrusion is lower than the lowest point of the fuselage.

[0024] Furthermore, the drive mechanism includes a motor, an impeller, and a transmission mechanism; the impeller is connected to the motor;

[0025] The motor includes an output shaft that is arranged along the length of the housing. The impeller and the transmission mechanism are both mounted on the output shaft, and the impeller is positioned opposite to the control unit.

[0026] Furthermore, the motor includes a stator and an outer rotor, with the outer rotor sleeved on the stator;

[0027] The outer rotor, the impeller, and the output shaft are an integral structure.

[0028] Furthermore, there are multiple impellers, which are evenly spaced along the circumference of the output shaft.

[0029] Furthermore, the control unit includes a flight controller, an electronic speed controller, an image controller, and a wireless communication module;

[0030] The electronic speed controller is connected to the drive mechanism, the image controller is connected to the camera assembly, and the wireless communication module is connected to the mobile terminal;

[0031] The flight controller is connected to the electronic speed controller, the image controller, and the wireless communication module, respectively.

[0032] The image controller is used to receive information from the camera component and transmit the information from the camera component to the flight controller. The electronic speed controller is used to adjust the electronic speed controller according to the instructions sent by the flight controller to control the movement of the drive mechanism and transmit the information from the drive mechanism to the flight controller. The wireless communication module is used to send the information received by the flight controller to the mobile terminal or transmit the instructions sent by the mobile terminal to the flight controller.

[0033] Furthermore, the housing includes a left housing and a right housing, and the left housing and the right housing are joined together to form the inner cavity.

[0034] Furthermore, the flight controller includes a first PCB board, the electronic speed controller includes a second PCB board, the image controller includes a third PCB board, and the wireless communication module includes a fourth PCB board;

[0035] The third PCB board and the fourth PCB board are disposed inside the left housing, and the third PCB board and the fourth PCB board are connected.

[0036] The first PCB board and the second PCB board are disposed inside the right housing, and the first PCB board and the second PCB board are connected.

[0037] Furthermore, the inner cavity is provided with a fuselage frame, which is connected to the housing;

[0038] The drive mechanism, power supply structure, and control unit are all mounted on the fuselage frame, and the center lines of the drive mechanism, power supply structure, and control unit coincide with the center line of the fuselage frame.

[0039] The technical solution provided in this disclosure has the following advantages compared with the prior art:

[0040] The aircraft provided in this embodiment includes a shell with an inner cavity. The inner cavity houses a drive mechanism and a control unit, and the shell also houses a camera assembly. The camera assembly has an air inlet, and the shell has a first air outlet, a second air outlet, and a third air outlet. An airflow channel is formed between the air inlet and the first, second, and third air outlets. Airflow enters the inner cavity through the air inlet and exits through the first, second, and third air outlets. During flight, the inner cavity generates a cooling airflow. This airflow enters the inner cavity through the air inlet and exits through the first, second, and third air outlets, facilitating heat dissipation for the internal components and expelling hot air from the inner cavity. This particularly accelerates the heat dissipation of the drive mechanism, control unit, and power supply structure, improving the heat dissipation effect, reducing the possibility of damage to internal components due to overheating, and extending the service life of the aircraft. Attached Figure Description

[0041] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure.

[0042] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0043] Figure 1 This is an exploded view of the aircraft described in the embodiments of this disclosure;

[0044] Figure 2 This is a cross-sectional view of the aircraft described in the embodiments of this disclosure;

[0045] Figure 3 This is a top view of the aircraft described in the embodiments of this disclosure;

[0046] Figure 4 This is a side view of the aircraft described in an embodiment of the present disclosure;

[0047] Figure 5This is a schematic diagram of another side view of the aircraft described in an embodiment of this disclosure;

[0048] Figure 6 This is a schematic diagram of the structure of the aircraft described in the embodiments of this disclosure after removing the shell;

[0049] Figure 7 This is an exploded view of the aircraft described in the embodiments of this disclosure after the shell has been removed;

[0050] Figure 8 This is a schematic diagram of the structure of the camera assembly in the aircraft described in the embodiments of this disclosure;

[0051] Figure 9 for Figure 8 Sectional view along axis AA;

[0052] Figure 10 This is an exploded view of the camera assembly in the aircraft described in the embodiments of this disclosure;

[0053] Figure 11 This is a schematic diagram of the structure of the protective frame for the camera assembly in the aircraft described in this embodiment of the present disclosure;

[0054] Figure 12 This is a partial enlarged view of the camera assembly in the aircraft described in the embodiments of this disclosure;

[0055] Figure 13 This is a schematic diagram showing the installation location of the camera assembly in the aircraft described in this embodiment of the disclosure;

[0056] Figure 14 This is a schematic diagram of the drive mechanism in the aircraft described in the embodiments of this disclosure;

[0057] Figure 15 This is a cross-sectional view of the drive mechanism in the aircraft described in the embodiments of this disclosure.

[0058] Reference numerals: 11. Nose; 111. Mounting hole; 12. Fuselage; 121. First air outlet; 122. Second air outlet; 123. Third air outlet; 13. Left fuselage; 14. Right fuselage; 15. Fuselage frame; 16. Neck; 2. Camera assembly; 21. Mounting platform; 211. Outer surface; 212. Lens hole; 213. Boss; 213a. Sloping surface; 214. Air inlet; 215. Air inlet; 22. Protective frame; 221. Protrusion; 23. Camera; 3. Drive mechanism; 31. Motor; 311. Output shaft; 312. Stator; 313. Outer rotor; 32. Impeller; 33. Transmission mechanism; 4. Control unit; 41. Flight controller; 42. Electronic speed controller; 43. Image controller; 44. Wireless communication module; 5. Power supply structure. Detailed Implementation

[0059] To better understand the above-mentioned objectives, features, and advantages of this disclosure, the solutions disclosed herein will be further described below. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0060] Numerous specific details are set forth in the following description in order to provide a full understanding of this disclosure, but this disclosure may also be implemented in other ways different from those described herein; obviously, the embodiments in the specification are only some, and not all, of the embodiments of this disclosure.

[0061] Combination Figures 1-6 As shown, the aircraft provided in this embodiment includes a shell with an inner cavity. The inner cavity is equipped with a drive mechanism 3 and a control unit 4. The shell also includes a camera assembly 2. The camera assembly 2 has an air inlet 215, and the shell has a first air outlet 121. An airflow channel can be formed between the air inlet 215 and the first air outlet 121. Airflow enters the inner cavity from the air inlet 215, flows through the drive mechanism 3 to the control unit 4, and then exits from the first air outlet 121. During flight, the inner cavity can generate a cooling airflow. This airflow, entering the inner cavity from the air inlet 215, flowing through the drive mechanism 3 to the control unit 4, and then exiting from the first air outlet 121, facilitates the cooling of the internal components of the aircraft and removes hot air from the inner cavity. The airflow channel formed between the air inlet 215 and the first air outlet 121 significantly accelerates the cooling speed of the drive mechanism 3 and the control unit 4, improves the cooling effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and extends the service life of the aircraft.

[0062] In addition, the airflow channel formed between the air inlet 215 and the first air outlet 121 can also reduce wind resistance.

[0063] In this embodiment of the disclosure, the number of air inlets 215 is at least one, and can be set to multiple as needed.

[0064] Multiple first air outlets 121 can be provided. When two or more first air outlets 121 are provided, the two or more first air outlets 121 are spaced apart along the length of the aircraft, which further improves the heat dissipation performance of the aircraft.

[0065] In some specific embodiments, the first air outlet 121 is located at the top of the housing, allowing airflow to smoothly exit from the air inlet 215 after entering through the air inlet 215. This facilitates heat dissipation for the internal electronic components of the aircraft and reduces wind resistance. The first air outlet 121 is positioned opposite the control unit 4, which is beneficial for heat dissipation of the control unit 4. The opposite positioning of the first air outlet 121 and the control unit 4 allows airflow to enter the internal cavity from the air inlet 215, pass through the drive mechanism 3, flow to the control unit 4, and exit from the first air outlet 121. This dissipates the heat generated by the drive mechanism 3 and the control unit 4, reducing the possibility of damage to the drive mechanism 3 and the control unit 4 due to overheating and extending the service life of the aircraft.

[0066] In some specific embodiments, second air outlets 122 are provided on both sides of the shell, allowing airflow to smoothly exit from the second air outlets 122 after entering from the air inlet 215. This facilitates heat dissipation for the internal electronic components of the aircraft and reduces wind resistance. The second air outlets 122 are located on both sides of the shell corresponding to the control unit 4, so that airflow enters the inner cavity from the air inlet 215, flows through the drive mechanism 3 to the control unit 4, and exits from the second air outlets 122. During flight, a cooling airflow can be formed in the inner cavity. The airflow enters the inner cavity from the air inlet 215, flows through the drive mechanism 3 to the control unit 4, and exits from the second air outlets 122 on both sides. This facilitates heat dissipation for the internal components of the aircraft, removes hot air from the inner cavity, especially accelerates the heat dissipation speed of 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 extends the service life of the aircraft.

[0067] Optionally, the number of second air outlets 122 on each side of the shell is at least one, and can be set to multiple as needed. When two or more second air outlets 122 are provided, the two or more second air outlets 122 are spaced apart along the length of the aircraft, which further improves the heat dissipation performance of the aircraft.

[0068] When the shell is provided with a first air outlet 121 and two sets of second air outlets 122, the airflow enters from the air inlet 215 and forms three airflows, which are discharged from the first air outlet 121 and the two sets of second air outlets 122 respectively. This improves the heat dissipation effect, reduces the possibility of damage to internal components of the aircraft due to overheating, and extends the service life of the aircraft.

[0069] Combination Figure 1 , Figure 2 and Figure 6As shown, the inner cavity is equipped with a power supply structure 5, and the drive mechanism 3, control unit 4, and power supply structure 5 are arranged sequentially along the length of the shell. Both sides of the shell are provided with third air outlets 123, allowing airflow to enter from the air inlet 215 and then smoothly exit from the third air outlet 123, facilitating heat dissipation of the aircraft's internal electronic components and reducing wind resistance.

[0070] The third air outlet 123 is located on both sides of the housing corresponding to the power structure 5, so that airflow enters the inner cavity from the air inlet 215, flows to the drive mechanism 3, control unit 4 and power structure 5, and then exits from the third air outlet 123. During the flight of the aircraft, a cooling airflow can be formed in the inner cavity. The airflow enters the inner cavity from the air inlet 215, flows through the drive mechanism 3 to the control unit 4 and power structure 5, and then exits from the third air outlet 123 on both sides. This facilitates the heat dissipation of the internal components of the aircraft, removes the hot airflow in the inner cavity, especially accelerates the heat dissipation speed of the power structure 5, improves the heat dissipation effect, reduces the possibility of damage to the internal components of the aircraft due to overheating, and extends the service life of the aircraft.

[0071] Optionally, the number of third air outlets 123 on each side of the shell is at least one, and can be set to multiple as needed. When two or more third air outlets 123 are provided, the two or more third air outlets 123 are spaced apart along the length of the aircraft, which further improves the heat dissipation performance of the aircraft.

[0072] When the shell is equipped with a first air outlet 121, two sets of second air outlets 122, and two sets of third air outlets 123, the airflow entering from the air inlet 215 forms multiple airflows, which are discharged from the first air outlet 121, the two sets of second air outlets 122, and the two sets of third air outlets 123 respectively. This improves the heat dissipation effect, reduces the possibility of damage to internal components of the aircraft due to overheating, and also reduces wind resistance, thus extending the service life of the aircraft.

[0073] The power supply structure 5 may include a battery assembly. Optionally, the housing is provided with mounting holes for mounting the battery assembly, which is detachably mounted to the housing through the mounting holes for supplying power to the aircraft. The battery assembly includes a battery, which may be a rechargeable secondary battery capable of repeated charging and discharging.

[0074] Optionally, the power supply structure 5, the drive mechanism 3, the control unit 4, and the power supply structure 5 are arranged sequentially along the central axis of the length direction of the housing.

[0075] In some specific embodiments, the housing includes a nose 11 and a fuselage 12 connected to the nose 11. The nose 11 is located at the front of the aircraft and is used to point the direction of flight of the aircraft. The fuselage 12 is equipped with a drive mechanism 3, a control unit 4, and a power supply structure 5, etc. The connection between the nose 11 and the fuselage 12 forms a neck 16.

[0076] In some specific embodiments, to acquire images of the surrounding environment during the aircraft's flight, a camera assembly 2 is installed on the aircraft to capture images of the surrounding environment. The camera assembly 2 is located on the neck 16 of the aircraft, which has a mounting hole 111 for mounting the camera assembly 2. The opening of the mounting hole 111 is slightly tilted downwards, allowing the camera assembly 2 to be tilted downwards during installation, thus better capturing images of the scene below the aircraft. The camera assembly 2 includes a camera 23, which is installed in the mounting hole 111. When the aircraft lands, even if the aircraft tilts slightly forward, the camera 23 will not rub against the ground, reducing the possibility of damage to the camera 23. During flight, with the camera assembly 2 positioned at the neck 16, the camera assembly 2's field of view is not obstructed, and even changes in flight attitude, such as roll or pitch, will not affect the camera assembly 2's field of view.

[0077] The neck 16 of the aircraft is located on the fuselage 12 near the nose 11. The camera assembly 2 installed on the neck 16 will not rub against the ground when the aircraft lands, so as to avoid collisions caused by the aircraft landing and improve the service life of the camera 23.

[0078] Specifically, in combination Figures 8-13 As shown, the camera assembly 2 includes a mounting platform 21, which has an outer surface 211 with a lens hole 212. The lens hole 212 houses a camera 23 for capturing images of the surrounding environment. The camera 23 is tilted downwards during installation to better capture images of the environment below the aircraft, resulting in a more rational layout. The camera 23 can be a 360-degree panoramic camera; in some specific embodiments, it can also be a fixed-focus lens. The camera 23 can be connected to the mounting platform 21 via threaded connection, fastener connection, or adhesive bonding. Using this design, the mounting platform 21 has a simple structure, and its connection to the aircraft is detachable, facilitating installation and disassembly.

[0079] like Figure 13 As shown, the central axis of the aircraft's length direction is located on the aircraft's fuselage, and the first angle α formed between the camera's axis and the central axis of the aircraft's length direction is α. During flight, under the influence of aerodynamic torque, the fuselage 12 maintains a certain angle of elevation, namely the angle γ formed by the central axis of the aircraft's length direction and the horizontal direction L. Sensors are installed on the aircraft to acquire its attitude information. Analysis of the data collected by the sensors shows that the angle of elevation γ during flight ranges from 10° to 20°.

[0080] Combination Figure 13As shown, the angle between the camera's axis and the horizontal direction L is α-γ. Therefore, when the aircraft is flying forward, when the angle obtained by 90°-(α-γ)-β is not less than 0°, that is, when the first angle α satisfies: 40°≤α≤48°, the field of view of the camera 23 is to the left of the vertical direction H. The range of the image captured by the camera 23 is relatively wide, the image quality is clear, and it is convenient for the camera 23 to capture the environment below the aircraft.

[0081] It should be noted that the horizontal direction L mentioned above refers to the direction parallel to the ground, and the vertical direction mentioned above refers to the direction perpendicular to the ground.

[0082] Preferably, the first angle formed by the axis of camera 23 and the central axis of the aircraft along its length is set to 45°, so that the images captured by camera 23 are clearer and can better capture the environment below the aircraft.

[0083] Furthermore, the aircraft's flight altitude is set to no more than 50 meters, meaning the distance between the aircraft and the ground will not exceed 50 meters. This ensures clear images captured by camera 23 and reduces damage to the aircraft and ground objects in the event of a crash. Specifically, at a flight altitude of 50 meters, the horizontal distance covered by camera 23's field of view is between 69 and 96 meters. Within this range, the image resolution is high, allowing camera 23 to capture clear images. Moreover, within a flight altitude range of no more than 50 meters, in the event of a sudden crash or other unforeseen circumstances during flight, this limited flight altitude effectively reduces the extent of damage to ground objects and the aircraft itself caused by an accidental crash.

[0084] In some specific embodiments, a boss 213 is provided on the end of the lens hole 212 near the outer surface 211. The boss 213 extends circumferentially along the lens hole 212 and contacts the camera 23, so that the camera 23 is housed 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 easily damaged when the aircraft malfunctions and falls.

[0085] In some specific embodiments, the boss 213 includes an inclined surface 213a that intersects with the outer surface 211. The inclined surface 213a forms a second angle with the axis of the camera 23. The second angle β satisfies: β≥52°. This can reduce the obstruction of the boss 213 on the field of view of the camera 23, so that the camera 23 can use a 104° wide-angle lens. When the aircraft is flying at high altitude, it can obtain a larger field of view for shooting scenes.

[0086] In some specific embodiments, the mounting platform 21 is provided with an air inlet 214, which forms an air inlet 215 at one end of the outer surface 211 and communicates with the inner cavity. During flight, airflow enters the air inlet 214 from the air inlet 215 and then enters the inner cavity, carrying away the heat from the drive mechanism 3, control unit 4, or power structure 5 in the inner cavity and discharging it from the first air outlet 121, the second air outlet 122, or the third air outlet 123. This facilitates the heat dissipation of the internal components of the aircraft, expelling hot air from the inner cavity, especially accelerating the heat dissipation of the drive mechanism 3, control unit 4, and power structure 5, improving the heat dissipation effect, reducing the possibility of damage to the internal components of the aircraft due to overheating, and extending the service life of the aircraft.

[0087] In some specific embodiments, the mounting platform 21 is provided with multiple air inlets 214, which can ensure that enough air enters the inner cavity of the fuselage 12, thereby improving the heat dissipation effect of the aircraft. The multiple air inlets 214 are spaced apart and arranged around the lens hole 212, which can make the airflow enter each air inlet 214 more evenly and enter the inner cavity from the air inlet 214, thereby improving the flight stability of the aircraft.

[0088] In some specific implementations, the diameter d of the air inlet 214 satisfies: 2mm≤d≤6mm, which can improve the heat dissipation effect of the aircraft, reduce the possibility of damage to internal components due to overheating, and extend the service life of the aircraft.

[0089] Preferably, four air inlets 214 are evenly distributed around the lens hole 212. The diameter of the air inlets is about 5mm. This ensures that enough air can enter the inner cavity of the fuselage 12, while also blocking larger debris and reducing the possibility of debris entering the aircraft body and damaging the internal structure.

[0090] In some specific embodiments, the camera assembly 2 includes a protective frame 22 that fits snugly against the fuselage 12, reducing the possibility of direct impact on the fuselage 12 and protecting it. Optionally, the shape of the protective frame 22 is adapted to the fuselage 12, allowing for a better fit. This ensures that during aircraft landing, the protective frame 22 contacts the ground, preventing damage from friction between the fuselage 12 and the ground, thus extending the aircraft's service life. The protective frame 22 is connected to the mounting platform 21, and the protective frame 22 and the mounting platform 21 are an integral structure. The protective frame 22 includes a protrusion 221; combined with... Figure 2As shown, along the height direction H of the shell, the lowest point of the protrusion 221 is lower than the lowest point of the fuselage 12, so that the protrusion 221 touches the ground first when the aircraft lands. Thus, when the aircraft lands, the protrusion 221 contacts the ground first, reducing the possibility of damage to the fuselage 12 due to friction with the ground, and also playing a shock absorption role, extending the service life of the aircraft.

[0091] Optionally, the protective frame 22 can be made of polypropylene, which has high toughness and impact resistance. Optionally, the shell can be made of foamed plastic, which has good pressure resistance and cushioning.

[0092] Combination Figure 2 , Figure 9 and Figure 10 As shown, the lowest point of the protrusion 221 is lower than the lowest point of the fuselage 12, making the protrusion 221 the lowest point of the aircraft. The camera 23 is installed above the protrusion 221. When the aircraft lands, the protrusion 221 will contact the ground first. With the combined action of the protective frame 22 and the shell, the impact force on the camera 23 can be effectively buffered, protecting the camera 23 and preventing it from being damaged when the aircraft lands.

[0093] Combination Figure 6 , Figure 14 and Figure 15 As shown, the drive mechanism 3 includes a motor 31, an impeller 32, and a transmission mechanism 33. The impeller 32 is connected to the motor 31. The motor 31 includes an output shaft 311, which is arranged along the length of the housing. The impeller 32 and the transmission mechanism 33 are both mounted on the output shaft 311. The impeller 32 is positioned opposite to the control unit 4, allowing the airflow generated by the rotation of the impeller 32 to flow backward effectively and blow towards the control unit 4. In this embodiment, the housing can form an axial air duct. The airflow is accelerated after passing through the impeller 32, and the accelerated airflow provides forced convection cooling to the control unit 4 and the power supply structure 5, improving their heat dissipation performance. The impeller 32, located on the output shaft 311 of the motor 31, accelerates the airflow velocity within the cavity, improving the heat exchange efficiency of the axial air duct formed within the housing.

[0094] In some specific embodiments, the motor 31 includes a stator 312 and an outer rotor 313, with the outer rotor 313 fitted onto the stator 312. The outer rotor 313, impeller 32, and output shaft 311 are integrated into a single structure, so that when the output shaft 311 of the motor 31 rotates, it drives the impeller 32 to rotate, without excessively increasing power consumption, thus increasing the efficiency of the motor. Furthermore, it allows for increased airflow within the motor 31's internal cavity during operation, improving heat dissipation efficiency. When energized, the stator 312 of the motor 31 does not rotate, while the outer rotor 313 rotates at high speed. The drive gear fixed to the shaft of the motor 31 drives the wings to flap via the power transmission mechanism 33. The impeller 32 fixed to the shaft of the motor 31 generates airflow along the length of the casing, thereby dissipating heat for the control unit 4 and the power supply structure 5.

[0095] In some specific embodiments, there are multiple impellers 32, which 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 conducive to airflow and can improve heat dissipation efficiency. While the motor 31 runs stably and smoothly, the service life of the internal components is extended.

[0096] Optionally, the transmission mechanism 33 may include a fuselage frame 15, a gear set, a connecting rod, and a swing bracket. The fuselage frame 15 may be mounted on a housing to secure the transmission mechanism 33 to the housing. The gear set may be mounted on the fuselage frame 15 and driven by a motor 31. The gear set may also be connected to the connecting rod. For example, one gear in the gear set may be connected to one end of the connecting rod, so that the rotation of the gear can drive the connecting rod to move accordingly. The other end of the connecting rod may be pivotally connected to the swing bracket, so that the swing bracket can move accordingly under the drive of the connecting rod. In addition, the swing bracket may also be pivotally connected to a fixed bracket so that the swing bracket can be supported. The wings of the aircraft may be connected to the swing bracket, so that the swing bracket drives the wings to flap up and down.

[0097] Combination Figure 6 and Figure 7 As shown, optionally, the gear set is mounted on the bracket and symmetrically distributed on both sides of the fuselage frame 15, and the motor 31 is mounted on the bracket of the gear set and symmetrically distributed on both sides of the fuselage frame 15. A square hole is opened at the rear end of the fuselage frame 15 along the length direction of the housing, and the power supply structure 5 is embedded in the square hole and symmetrically distributed on both sides of the fuselage frame 15.

[0098] Combination Figure 6 and Figure 7As shown, the control unit 4 includes a flight controller 41, an electronic speed controller 42, an image controller 43, and a wireless communication module 44. The electronic speed controller 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 the mobile terminal. The flight controller 41 is connected to the electronic speed controller 42, the image controller 43, and the wireless communication module 44. The image controller 43 is used to receive information from the camera assembly 2 and transmit the information from the camera assembly 2 to the flight controller 41. The electronic speed controller 42 is used to adjust the electronic speed controller 42 according to the instructions sent by the flight controller 41 to control the movement of the drive mechanism 3 and transmit the information from the drive mechanism to the flight controller 41. The wireless communication module 44 is used to send the information received by the flight controller 41 to the mobile terminal and transmit the instructions sent by the mobile terminal to the flight controller 41.

[0099] The power supply structure 5 is connected to the drive mechanism 3, the image controller 43, the camera assembly 2 and the wireless communication module 44 respectively, and is used to supply power to the drive mechanism 3, the image controller 43, the camera assembly 2 and the wireless communication module 44.

[0100] To make full use of the internal space, the flight controller 41 and electronic speed controller 42 are located on the right fuselage 14, and the image controller 43 and wireless communication module 44 are located on the left fuselage 13.

[0101] In some specific embodiments, the flight controller 41 includes a first PCB board, the electronic speed controller 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. The third and fourth PCB boards are disposed within the left fuselage 13 and are connected. The first and second PCB boards are disposed within the right fuselage 14 and are connected. The first, second, third, and fourth PCB boards are evenly arranged on both sides of the central axis of the fuselage 12, which ensures that the center of gravity of the aircraft is located on the central axis of the fuselage 12, preventing the aircraft from tilting left or right during flight and ensuring stable flight.

[0102] Optionally, the first PCB board and the second PCB board are electrically connected but do not touch 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. This helps to avoid interference from other components, reduces the heat emitted by the electronic speed control module from affecting the flight control module, and improves the sensitivity of the flight control module's signal transmission.

[0103] Optionally, the third PCB board and the fourth PCB board are electrically connected but do not touch 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. This helps to avoid interference from other components and reduces the impact of the heat emitted by the image control module on the wireless communication module 44. This improves the wireless transmission sensitivity and transmission speed of the image and extends the wireless transmission distance of the image.

[0104] Optionally, the first PCB board and the second PCB board are connected by an electrical connector, and the third PCB board and the fourth PCB board are connected by an electrical connector.

[0105] Optionally, camera 23 is used to capture images or videos during flight and transmit the image or video signals to the processor. After processing, the processor transmits the information fed back by camera 23 to flight controller 41. Wireless communication module 44 is used to send the information received by flight controller 41 to a mobile terminal or to transmit the instructions sent by the mobile terminal to flight controller 41. Through the mobile terminal on the ground, the images captured by the aircraft during flight can be viewed directly, making it easier to determine whether the aircraft is in a normal flight operating state, thereby controlling the flight status of the aircraft.

[0106] Mobile terminals may include dedicated remote controllers for aircraft, mobile phones, or other wireless communication devices.

[0107] Combination Figure 1 , Figure 3 and Figure 6 As shown, in some specific embodiments, the housing includes a left housing 13 and a right housing 14, which, when closed, form an inner cavity. Optionally, the left housing 13 and the right housing 14 have multiple slots, and the outer edge of the body frame 15 has multiple protrusions, which engage and fix with corresponding slots. The left housing 13 and the right housing 14 are interlocked. Optionally, the left housing 13 and the right housing 14 can be connected by snap-fit, threaded connection, fastener connection, or adhesive bonding. Optionally, the left housing 13 and the right housing 14 can be selected from one or a combination of at least two of the following: snap-fit ​​connection, threaded connection, fastener connection, and adhesive bonding.

[0108] In some specific embodiments, the inner cavity is provided with a fuselage frame 15, which is connected to the shell; the drive mechanism 3, the power structure 5 and the control unit 4 are all set on the fuselage frame 15, and the center lines of the drive mechanism 3, the power structure 5 and the control unit 4 coincide 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 stable flight of the aircraft.

[0109] By mounting the drive mechanism 3, power supply structure 5, and control unit 4 on the body frame 15, the drive mechanism 3, power supply structure 5, and control unit 4 can be integrated into a single module, which is convenient for installation and can improve the stability of the structure.

[0110] Optionally, the fuselage frame 15 has at least one perforation to reduce the weight of the aircraft. The drive mechanism 3, power structure 5, and control unit 4 can be respectively located at the perforation to improve the stability of the connection between the drive mechanism 3, power structure 5, and control unit 4 and the fuselage frame 15.

[0111] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0112] The above are merely specific embodiments of this disclosure, enabling those skilled in the art to understand or implement this disclosure. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not to be limited to these embodiments, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft, characterized in that, include: The housing has 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). The camera assembly (2) is provided with an air inlet (215), and the housing is provided with a first air outlet (121). Airflow enters the inner cavity from the air inlet (215), flows through the drive mechanism (3) to the control unit (4), and is discharged from the first air outlet (121). The drive mechanism (3) includes a motor (31), an impeller (32), and a transmission mechanism (33); the impeller (32) is connected to the motor (31); The motor (31) includes an output shaft (311) which is arranged along the length of the housing. The impeller (32) and the transmission mechanism (33) are both arranged on the output shaft (311). The impeller (32) is arranged opposite to the control unit (4). Among them, the drive gear fixed on the shaft of the motor (31) drives the wings to flap through the transmission mechanism (33), and the impeller (32) fixed on the shaft of the motor (31) generates wind along the length of the casing.

2. The aircraft according to claim 1, characterized in that, The first air outlet (121) is located at the top of the housing; The first air outlet (121) is arranged opposite to the control unit (4) so ​​that the airflow enters the inner cavity from the air inlet (215), flows through the drive mechanism (3) to the control unit (4), and is discharged from the first air outlet (121).

3. The aircraft according to claim 1, characterized in that, The housing is provided with a second air outlet (122) on both sides. The second air outlet (122) is provided on both sides of the housing corresponding to the control unit (4) so ​​that the airflow enters the inner cavity from the air inlet (215), flows through the drive mechanism (3) to the control unit (4), and is discharged from the second air outlet (122).

4. 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 sequentially along the length direction of the housing; The housing is provided with a third air outlet (123) on both sides. The third air outlet (123) is disposed on both sides of the housing corresponding to the power supply structure (5) so that the airflow enters the inner cavity from the air inlet (215), flows to the drive mechanism (3), the control unit (4) and the power supply structure (5) and then exits from the third air outlet (123).

5. The aircraft according to any one of claims 1 to 4, characterized in that, The housing includes a head (11) and a body (12) connected to the head (11). The connection between the head (11) and the body (12) forms a neck (16). The camera assembly (2) is disposed on the neck (16), and the neck (16) is provided with mounting holes for mounting the camera assembly (2).

6. The aircraft according to claim 5, characterized in that, The camera assembly (2) includes a mounting platform (21), on the outer surface (211) of the mounting platform (21) having a lens hole (212), and the lens hole (212) having a camera (23) for acquiring images of the surrounding environment.

7. The aircraft according to claim 6, characterized in that, The axis of the camera (23) forms a first angle with the central axis of the length direction of the housing, and the first angle α satisfies: 40°≤α≤48°.

8. The aircraft according to claim 6, characterized in that, The lens hole (212) has a boss (213) on one end of the hole wall near the outer surface (211). The boss (213) extends circumferentially along the lens hole (212) and contacts the camera (23).

9. The aircraft according to claim 8, characterized in that, The boss (213) includes an inclined surface (213a) that intersects the outer surface (211). The inclined surface (213a) forms a second angle with the axis of the camera (23). The second angle β satisfies: β≥52°.

10. The aircraft according to claim 6, characterized in that, The mounting platform (21) is provided with an air inlet (214), and the air inlet (214) is located at one end of the outer surface (211) to form the air inlet (215). The air inlet (214) is connected to the inner cavity.

11. The aircraft according to claim 10, characterized in that, The mounting platform (21) has a plurality of air inlets (214), which are spaced apart and arranged around the lens hole (212).

12. The aircraft according to claim 10, characterized in that, The diameter d of the air inlet (214) satisfies: 2mm≤d≤6mm.

13. The aircraft according to claim 6, characterized in that, The camera assembly (2) includes a protective frame (22) connected to the mounting platform (21), and the protective frame (22) includes a protrusion (221). Along the height direction (H) of the housing, the lowest end of the protrusion (221) is lower than the lowest end of the fuselage (12).

14. The aircraft according to claim 1, characterized in that, The motor (31) includes a stator (312) and an outer rotor (313), the outer rotor (313) being sleeved on the stator (312). The outer rotor (313), the impeller (32) and the output shaft (311) are an integral structure.

15. The aircraft according to claim 11, characterized in that, The number of impellers (32) is multiple, and the multiple impellers (32) are evenly spaced along the circumference of the output shaft (311).

16. The aircraft according to any one of claims 1 to 4, characterized in that, The control unit (4) includes a flight controller (41), an electronic speed controller (42), an image controller (43), and a wireless communication module (44). The electronic speed controller (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 the mobile terminal; The flight controller (41) is connected to the electronic speed controller (42), the image controller (43) and the wireless communication module (44) respectively; The image controller (43) is used to receive information fed back by the camera component (2) and transmit the information fed back by the camera component (2) to the flight controller (41). The electronic speed controller (42) is used to adjust the electronic speed controller (42) according to the instructions sent by the flight controller (41) to control the movement of the drive mechanism (3) and transmit the information fed back by the drive mechanism (3) to the flight controller (41). The wireless communication module (44) is used to send the information received by the flight controller (41) to the mobile terminal or transmit the instructions sent by the mobile terminal to the flight controller (41).

17. The aircraft according to claim 16, characterized in that, The housing includes a left housing (13) and a right housing (14), and the left housing (13) and the right housing (14) are joined together to form the inner cavity.

18. The aircraft according to claim 17, characterized in that, The flight controller (41) includes a first PCB board, the electronic speed controller (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; The third PCB board and the fourth PCB board are disposed inside the left housing (13), and the third PCB board and the fourth PCB board are connected; The first PCB board and the second PCB board are disposed inside the right housing (14), and the first PCB board and the second PCB board are connected.

19. The aircraft according to claim 17, characterized in that, The inner cavity is provided with a fuselage frame (15), which is connected to the shell. The drive mechanism (3), power supply structure (5) and control unit (4) are all mounted on the fuselage frame (15), and the center lines of the drive mechanism (3), power supply structure (5) and control unit (4) coincide with the center line of the fuselage frame (15).

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