Camera assembly, aircraft fuselage, and aircraft

Abstract

The present disclosure relates to the technical field of aircraft, in particular to a camera assembly, an aircraft fuselage and an aircraft. The camera assembly provided by the present disclosure is installed on an aircraft, and the camera assembly comprises a mounting table, a lens hole formed on the outer surface of the mounting table, and a camera arranged in the lens hole, so that the surrounding scene can be obtained when the aircraft is flying, and the image of the surrounding environment is collected. Wherein, the axis of the camera and the central axis of the length direction of the aircraft shell form a first included angle, and the first included angle alpha satisfies: 40 DEG ≤ alpha ≤ 48 DEG. When the aircraft lands on the ground, even if the aircraft slightly leans, the camera will not rub against the ground, reducing the possibility of damage to the camera.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft technology, and more particularly to a camera assembly, an aircraft fuselage, and 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 typically have their internal cameras exposed during use, making them susceptible to damage upon landing and contact with the ground. Summary of the Invention

[0004] To address the aforementioned technical problems, this disclosure provides a camera assembly, an aircraft fuselage, and an aircraft.

[0005] The first aspect of this disclosure provides a camera assembly mounted on an aircraft. The camera assembly includes: a mounting platform, a lens aperture formed on the outer surface of the mounting platform, and a camera disposed within the lens aperture; wherein the axis of the camera forms a first angle with the central axis of the aircraft housing along its length, the first angle α satisfying: 40°≤α≤48°.

[0006] 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.

[0007] 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°.

[0008] Furthermore, the camera assembly includes a protective frame, the mounting platform is connected to the protective frame, and the protective frame is used to fit against the body.

[0009] Furthermore, the protective frame includes a protrusion;

[0010] Along the height direction H of the fuselage, the lowest point of the protrusion is lower than the lowest point of the fuselage.

[0011] Furthermore, along the height direction H of the body, the lowest point of the camera is higher than the protrusion.

[0012] Furthermore, the mounting platform and the protective frame are an integrated structure.

[0013] 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.

[0014] Furthermore, the mounting platform has multiple air inlets, which are spaced apart and arranged around the lens hole.

[0015] Furthermore, the diameter d of the air inlet hole satisfies: 2mm≤d≤6mm.

[0016] A second aspect of this disclosure provides an aircraft fuselage, including a housing and the aforementioned camera assembly;

[0017] The housing includes a head unit connected to the body, and the connection between the head unit and the body forms a neck. The camera assembly is disposed in the neck, and the neck has a mounting hole.

[0018] Furthermore, the neck is located on the fuselage near the head.

[0019] Furthermore, the housing includes a left housing and a right housing, which together form an inner cavity, and the air inlet is connected to the inner cavity.

[0020] Furthermore, the top of the housing is provided with a first air outlet, so that airflow enters the inner cavity from the air inlet and then exits from the first air outlet.

[0021] Furthermore, a second air outlet is provided on both sides of the housing so that airflow enters the inner cavity from the air inlet and is discharged from the second air outlet.

[0022] Furthermore, the housing is provided with a third air outlet on both sides, so that the airflow enters the inner cavity from the air inlet and is discharged from the third air outlet.

[0023] This disclosure provides a third aspect of an aircraft, including the said aircraft fuselage;

[0024] The housing has an inner cavity, which is provided with a drive mechanism, a control unit, and a power supply structure. The drive mechanism, the control unit, and the power supply structure are arranged sequentially along the length of the housing.

[0025] Furthermore, the control unit includes a flight controller, an electronic speed controller, an image controller, and a wireless communication module;

[0026] 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;

[0027] The flight controller is connected to the electronic speed controller, the image controller, and the wireless communication module, respectively.

[0028] 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.

[0029] 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;

[0030] 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.

[0031] The first PCB board and the second PCB board are disposed inside the right casing, and the first PCB board and the second PCB board are connected.

[0032] Furthermore, the inner cavity is provided with a fuselage frame, which is connected to the housing;

[0033] 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.

[0034] The technical solution provided in this disclosure has the following advantages compared with the prior art:

[0035] The camera assembly provided in this disclosure is used for mounting on an aircraft to acquire surrounding scenes and capture images of the surrounding environment during flight. The camera assembly includes a mounting platform, a lens aperture on the outer surface of the mounting platform, and a camera disposed within the lens aperture. The camera is tilted downwards during mounting to better capture the environment below the aircraft, resulting in a more rational camera layout. The axis of the camera forms a first angle α with the central axis of the aircraft's hull along its length, satisfying 40°≤α≤48°. When the aircraft lands, even with a slight tilt, the camera will not experience friction with the ground, reducing the possibility of camera damage. Attached Figure Description

[0036] 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.

[0037] 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.

[0038] Figure 1 This is an exploded view of the aircraft described in the embodiments of this disclosure;

[0039] Figure 2 This is a cross-sectional view of the aircraft described in the embodiments of this disclosure;

[0040] Figure 3 This is a top view of the aircraft described in the embodiments of this disclosure;

[0041] Figure 4 This is a side view of the aircraft described in an embodiment of the present disclosure;

[0042] Figure 5 This is a schematic diagram of another side view of the aircraft described in an embodiment of this disclosure;

[0043] Figure 6 This is a schematic diagram of the structure of the camera assembly described in an embodiment of this disclosure;

[0044] Figure 7 for Figure 6 Sectional view along axis AA;

[0045] Figure 8 This is an exploded view of the camera assembly described in an embodiment of this disclosure;

[0046] Figure 9 This is a schematic diagram of the structure of the protective frame in the camera assembly described in this embodiment of the present disclosure;

[0047] Figure 10 This is a partial enlarged view of the camera assembly described in an embodiment of this disclosure;

[0048] Figure 11 This is a schematic diagram showing the installation position of the camera assembly according to an embodiment of this disclosure;

[0049] Figure 12 This is a schematic diagram of the structure of the aircraft described in the embodiments of this disclosure after removing the shell;

[0050] Figure 13 This is an exploded view of the aircraft described in the embodiments of this disclosure after the outer shell has been removed.

[0051] 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; 32. Impeller; 4. Control unit; 41. Flight controller; 42. Electronic speed controller; 43. Image controller; 44. Wireless communication module; 5. Power supply structure. Detailed Implementation

[0052] 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.

[0053] 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.

[0054] Combination Figures 6-11 As shown, the camera assembly 2 provided in this embodiment is used for mounting on an aircraft. The camera assembly 2 includes a mounting platform 21, a lens hole 212 formed on the outer surface 211 of the mounting platform 21, and a camera 23 disposed within the lens hole 212. The camera 23 is tilted downwards during installation, allowing for better capture of the environment below the aircraft, resulting in a more rational layout of the camera 23. The camera 23 can be a 360-degree panoramic camera; in some specific embodiments, the camera 23 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, etc. Using the above solution, the mounting platform 21 has a simple structure, and the mounting platform 21 is detachably connected to the aircraft, facilitating installation and disassembly. The axis of the camera 23 forms a first angle α with the central axis of the aircraft's shell along its length, satisfying: 40°≤α≤48°. When the aircraft lands on the ground, even if the aircraft tilts slightly downwards, the camera 23 will not rub against the ground, reducing the possibility of damage to the camera 23.

[0055] like Figure 11As shown, the axis of the aircraft's length direction is located on the fuselage of the aircraft, and the first angle α formed between the axis of the camera and the central axis of the aircraft's length direction is α. During flight, under the influence of aerodynamic torque, the fuselage 12 will maintain 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 range of the angle of elevation γ during flight is 10° ≤ γ ≤ 20°.

[0056] Combination Figure 11 As 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.

[0057] 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.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] 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 camera 23's field of view by the boss 213, allowing the camera 23 to 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.

[0062] In some specific embodiments, the camera assembly 2 includes a protective frame 22. The mounting platform 21 and the protective frame 22 are connected. The protective frame 22 is designed to fit 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, and extending the aircraft's service life.

[0063] In some specific embodiments, the protective frame 22 is connected to the mounting platform 21, and the protective frame 22 includes a protrusion 221, which is combined with... Figure 2 As shown, along the height direction H of the fuselage 12, 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. The protrusion 221 can play a shock absorption role when the aircraft lands, so that when the aircraft lands, the protrusion 221 contacts the ground, reducing the damage to the fuselage 12 due to friction with the ground, and extending the service life of the aircraft.

[0064] 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.

[0065] Combination Figure 2 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.

[0066] In some specific embodiments, along the height direction H of the fuselage 12, the lowest point of the camera 23 is higher than the protrusion 221. When the aircraft lands on the ground, even if the aircraft tilts slightly, the camera 23 will not rub against the ground, reducing the possibility of damage to the camera 23.

[0067] In some specific implementations, the mounting platform 21 and the protective frame 22 are an integrated structure, which is simple in structure, easy to install, and can reduce assembly time.

[0068] Combination Figures 1-5 As shown in the figure, the aircraft fuselage 12 provided in this embodiment includes a shell and a camera assembly 2. The shell includes a nose section 11, which is connected to the fuselage 12 and positioned at the front of the aircraft to point in the flight direction. The fuselage 12 is used to mount a drive mechanism 3, a control unit 4, and a power supply structure 5, etc. A neck section 16 is formed at the connection between the nose section 11 and the fuselage 12. The camera assembly 2 is disposed in the neck section 16, which has mounting holes 111. When the aircraft lands on the ground, even if the aircraft tilts slightly, the camera 23 will not rub against the ground, reducing the possibility of damage to the camera 23.

[0069] During flight, the camera assembly 2, positioned on the neck 16, maintains an unobstructed field of view. Even changes in flight attitude, such as roll or pitch, do not affect the camera assembly 2's field of view. The neck 16 has mounting holes 111 for the camera assembly 2, allowing it to be installed at a downward tilt, providing better imaging of the environment below the aircraft and resulting in a more rational layout. The camera assembly 2 is used to capture images of the aircraft's surroundings. During flight, the camera 23 within the camera assembly 2 continuously monitors the surrounding environment to facilitate flight trajectory determination and navigation.

[0070] In some specific embodiments, the neck 16 of the aircraft is located on the fuselage 12 near the nose 11. The camera assembly 2 located 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.

[0071] To enhance heat dissipation within the aircraft, in some specific embodiments, the mounting platform 21 is provided with an air inlet 214, which forms an air intake 215 at one end of the outer surface 211. The air inlet 214 communicates with the inner cavity formed by the aircraft shell. During flight, airflow enters the air inlet 214 from the air intake 215 and then enters the inner cavity, carrying away heat from the drive mechanism 3, control unit 4, or power supply structure 5 within the cavity. The heat is then discharged from the first air outlet 121, the second air outlet 122, or the third air outlet 123, facilitating heat dissipation of the internal components and expelling hot air from the inner cavity. This significantly accelerates the heat dissipation of the drive mechanism 3, control unit 4, and power supply structure 5, improving the heat dissipation effect, reducing the possibility of damage to internal components due to overheating, and extending the service life of the aircraft.

[0072] In some specific embodiments, the mounting platform 21 has multiple air inlets 214, which are spaced apart and arranged around the lens hole 212. This arrangement allows airflow to enter each air inlet 214 more evenly and then enter the inner cavity through the air inlets 214, thereby improving the stability of the aircraft's flight.

[0073] 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.

[0074] 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 from entering and reducing the possibility of debris entering the aircraft body and damaging the internal structure.

[0075] Combination Figures 1-5 As shown, in some specific embodiments, the housing includes a left housing 13 and a right housing 14. The left housing 13 and right housing 14, when closed, form an inner cavity, and the air inlet 214 communicates with the inner cavity. Optionally, the left housing 13 and right housing 14 have multiple slots, and the outer edge of the body frame 15 has multiple protrusions, which are engaged and fixed with corresponding slots. The left housing 13 and right housing 14 are interlocked. Optionally, the left housing 13 and right housing 14 can be connected by snap-fit, threaded connection, fastener connection, or adhesive bonding. Optionally, the left housing 13 and 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.

[0076] In some specific embodiments, to improve the heat dissipation effect inside the aircraft, the aircraft is equipped with air outlets and air inlets. Specifically, a first air outlet 121 is provided at the top of the shell, allowing airflow to enter the inner cavity through the air inlet 214 and then exit through the first air outlet 121. Airflow enters the inner cavity through the air inlet 215, passes through the electronic components within the cavity, and exits through the first air outlet 121. During flight, a cooling airflow can be formed within the inner cavity. This airflow, entering through the air inlet 215, passing through the electronic components, and exiting through the first air outlet 121, facilitates heat dissipation for the internal components of the aircraft, expelling hot air from the inner cavity. The airflow channel formed between the air inlet 215 and the first air outlet 121 particularly accelerates the heat dissipation speed of the drive mechanism 3 and the control unit 4, improving the heat dissipation effect, reducing the possibility of damage to internal components due to overheating, and extending the service life of the aircraft.

[0077] The airflow channel formed between the air inlet 215 and the first air outlet 121 can also reduce wind resistance.

[0078] In this embodiment of the disclosure, the number of air inlets 215 is at least one, and can be set to multiple as needed.

[0079] 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.

[0080] In some specific embodiments, second air outlets 122 are provided on both sides of the housing, so that airflow enters the inner cavity from the air inlet 214 and exits from the second air outlets 122, facilitating heat dissipation of the internal electronic components of the aircraft and reducing wind resistance. The second air outlets 122 are located on both sides of the housing 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 aircraft flight, a cooling airflow can be formed in the inner cavity. This 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, facilitating heat dissipation of the internal components of the aircraft, expelling hot air from the inner cavity, especially accelerating the heat dissipation speed of the control unit 4, improving the heat dissipation effect, reducing the possibility of damage to internal components due to overheating, and extending the service life of the aircraft.

[0081] 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.

[0082] 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.

[0083] In some specific embodiments, the shell is provided with a third air outlet 123 on both sides, so that the airflow enters the inner cavity from the air inlet 214 and is discharged from the third air outlet 123, so that the airflow enters from the air inlet 215 and can be discharged smoothly from the third air outlet 123, which facilitates the heat dissipation of the electronic components inside the aircraft and also reduces wind resistance.

[0084] During flight, the internal cavity can generate a cooling airflow. The airflow enters the internal cavity from the air inlet 215, flows through the drive mechanism 3 to the control unit 4, and then exits from the third air outlet 123 on both sides. This facilitates the cooling of the internal components of the aircraft, removes the hot air from the internal cavity, and especially accelerates the cooling speed of the power structure 5, 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.

[0085] 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.

[0086] 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 extends the service life of the aircraft.

[0087] The aircraft provided in this embodiment includes an aircraft fuselage 12; the shell has an inner cavity, and the inner cavity is provided with a drive mechanism 3, a control unit 4 and a power supply structure 5, which are arranged sequentially along the length of the shell.

[0088] 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.

[0089] Optionally, the power supply structure 5, drive mechanism 3, control unit 4, and power supply structure 5 are arranged sequentially along the central axis of the length direction of the housing.

[0090] The drive mechanism 3 includes a motor 31, an impeller 32, and a transmission mechanism. The impeller 32 is connected to the motor 31. The motor 31 includes an output shaft arranged along the length of the housing. The impeller 32 and the transmission mechanism are both mounted on the output shaft. The impeller 32 is positioned opposite to the control unit 4, allowing the airflow generated by the rotation of the impeller 32 to flow effectively backward and 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 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.

[0091] In some specific embodiments, the motor 31 includes a stator and an outer rotor, with the outer rotor fitted onto the stator. The outer rotor, impeller 32, and output shaft are integrated into a single structure, so that when the output shaft of the motor 31 rotates, it drives the impeller 32 to rotate, without excessively increasing power consumption, thus increasing the motor's efficiency. Furthermore, it increases airflow within the motor 31's internal cavity during operation, improving heat dissipation efficiency. When energized, the stator of the motor 31 does not rotate, while the outer rotor rotates at high speed. The drive gear fixed to the shaft of the motor 31 drives the flapping of the wings via the power transmission assembly. The impeller 32, also 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.

[0092] Optionally, the transmission mechanism 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 to the housing. The gear set may be mounted to 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 aircraft's wings may be connected to the swing bracket, so that the swing bracket drives the wings to flap up and down.

[0093] 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.

[0094] Combination Figure 12 and Figure 13 As 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 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 or transmit the instructions sent by the mobile terminal to the flight controller 41.

[0095] 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.

[0096] 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.

[0097] 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 as close as possible to the central axis of the fuselage 12, preventing the aircraft from tilting left or right and ensuring stable flight.

[0098] 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 impact of heat dissipated by the electronic speed control module on the flight control module, and improves the sensitivity of the flight control module's signal transmission.

[0099] 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.

[0100] 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.

[0101] Optionally, camera 23 is used to capture video footage during flight and transmit the video signal 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 information received by flight controller 41 to mobile terminal or to transmit instructions sent by mobile terminal to flight controller 41. Through a mobile terminal on the ground, images captured by the aircraft during flight can be viewed directly, making it easier to determine whether the aircraft is in normal flight operation and thus control the aircraft's flight status.

[0102] Mobile terminals may include dedicated remote controllers for aircraft, mobile phones, or other wireless communication devices.

[0103] 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.

[0104] 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.

[0105] 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.

[0106] 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.

[0107] 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. A camera assembly mounted on an aerial vehicle, characterized in that, The camera assembly includes: a mounting platform (21), a lens hole (212) opened on the outer surface (211) of the mounting platform (21), and a camera (23) disposed in the lens hole (212); wherein, the axis of the camera (23) forms a first angle with the central axis of the length direction of the aircraft shell, and the first angle α satisfies: 40°≤α≤48°; 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).

2. The camera assembly according to claim 1, 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°.

3. The camera assembly of claim 1, wherein, The camera assembly includes a protective frame (22), the mounting platform (21) and the protective frame (22) are connected, and the protective frame (22) is used to fit against the body (12).

4. The camera assembly of claim 3, wherein, The protective frame (22) includes a protrusion (221); Along the height direction (H) of the fuselage (12), the lowest end of the protrusion (221) is lower than the lowest end of the fuselage (12).

5. The camera assembly of claim 4, wherein, Along the height direction (H) of the body (12), the lowest point of the camera (23) is higher than the protrusion (221).

6. The camera assembly of claim 3, wherein, The mounting platform (21) and the protective frame (22) are an integrated structure.

7. The camera assembly of claim 1, wherein, 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 an air inlet (215).

8. The camera assembly of claim 7, wherein, The mounting platform (21) has a plurality of air inlets (214), which are spaced apart and arranged around the lens hole (212).

9. The camera assembly of claim 8, wherein, The diameter d of the air inlet (214) satisfies: 2mm≤d≤6mm.

10. An aircraft fuselage, characterized in that, Includes a housing and a camera assembly (2) as described in any one of claims 1 to 9; The housing includes a head (11) connected to the body (12), and 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 a mounting hole (111). The camera assembly (2) is disposed on the mounting hole (111).

11. The aircraft fuselage of Claim 10, wherein, The neck (16) is located on the fuselage (12) near the head (11).

12. The aircraft fuselage of Claim 10, wherein, The housing includes a left housing (13) and a right housing (14). The left housing (13) and the right housing (14) are joined together to form an inner cavity, and the air inlet (214) is connected to the inner cavity.

13. The aircraft fuselage of Claim 12, wherein, The top of the housing is provided with a first air outlet (121) so that airflow enters the inner cavity from the air inlet (214) and then exits from the first air outlet (121).

14. The aircraft fuselage according to claim 12, characterized in that, The housing is provided with a second air outlet (122) on both sides so that the airflow enters the inner cavity from the air inlet (214) and is discharged from the second air outlet (122).

15. The aircraft fuselage of Claim 12, wherein, The housing is provided with a third air outlet (123) on both sides so that the airflow enters the inner cavity from the air inlet (214) and is discharged from the third air outlet (123).

16. An aircraft, characterized in that Includes the aircraft fuselage as described in any one of claims 10 to 15; The housing has an inner cavity, which is provided with a drive mechanism (3), a control unit (4) and a power supply structure. The drive mechanism (3), the control unit (4) and the power supply structure are arranged sequentially along the length of the housing.

17. The aircraft of claim 16, wherein, 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).

18. The aircraft of claim 17, wherein, 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 casing (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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