Aircraft camera mount, aircraft camera device and electric vertical takeoff and landing aircraft

Abstract

This utility model relates to an aircraft camera bracket, an aircraft camera device, and an electric vertical takeoff and landing (EVTOL) aircraft. The aircraft camera bracket includes a camera base, a first camera mounting component, and a second camera mounting component. The camera base is mounted on the vertical tail of the aircraft; the first camera mounting component is mounted on the camera base for mounting a first camera; and the second camera mounting component is mounted on the camera base for mounting a second camera. This aircraft camera bracket offers a wide field of view.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to an aircraft camera bracket, an aircraft camera device, and an electric vertical take-off and landing aircraft. Background Technology

[0002] With the gradual development of the low-altitude economy, various types of electric vertical takeoff and landing (eVTOL) aircraft are being rapidly developed, and corresponding functional components for eVTOLs are also being developed, such as aircraft camera devices. Aircraft camera devices can capture and transmit images and / or video data in real time, providing safety assurance for real-time monitoring of the aircraft's flight attitude. However, the field of view of aircraft camera devices in related technologies is limited. Utility Model Content

[0003] Therefore, it is necessary to provide an aircraft camera mount with a wide field of view.

[0004] This utility model provides an aircraft camera bracket, comprising:

[0005] Camera mount, for mounting on the vertical tail of an aircraft;

[0006] A first camera mounting component, disposed on the camera base, is used to mount the first camera; and

[0007] The second camera mounting component is disposed on the camera base and is used to mount the second camera.

[0008] In one embodiment, the camera base is detachably connected to the vertical tail; and / or

[0009] The first camera mounting component is detachably connected to the camera base; and / or

[0010] The second camera mounting component is detachably connected to the camera base; and / or

[0011] The first camera mount includes a first pivot on the camera base, the first pivot being used to mount the first camera so that the first camera can rotate relative to the camera base; and / or

[0012] The second camera mount includes a second pivot on the camera base, the second pivot being used to mount the second camera so that the second camera can rotate relative to the camera base.

[0013] In one embodiment, the first camera mounting component includes an adapter mechanism and an angle adjustment mechanism. The adapter mechanism is disposed on the camera base. The angle adjustment mechanism includes a first angle adjustment lug, a first screw, and a first nut. There are multiple first angle adjustment lugs, which are spaced apart on the adapter mechanism so that the first lug of the first camera can be inserted between two adjacent first angle adjustment lugs. The first screw is used to pass through the first angle adjustment lug and the first lug so that the first lug can rotate around the first screw. The first nut cooperates with the first screw so that the first angle adjustment lug and the first lug can lock the angle of the first camera through friction.

[0014] In one embodiment, the first angle adjusting ear has a first adjusting serration, the first adjusting serration being used to engage with a first serration on the first ear to mechanically lock the first angle adjusting ear to the first ear; and / or

[0015] The adapter mechanism is fixed to the camera base with screws.

[0016] In one embodiment, the second camera mount includes a camera mounting base disposed on the camera base. The camera mounting base has a receiving cavity for accommodating the second camera. The side of the camera mounting base near the nose of the aircraft has an inlet and outlet communicating with the receiving cavity. The inlet and outlet are used for the second camera to enter and exit the receiving cavity.

[0017] In one embodiment, the first camera mount and the second camera mount are arranged in the longitudinal direction of the aircraft, and the second camera mount is closer to the nose of the aircraft relative to the first camera mount. The first camera mount includes a first pivot on the camera base, the first pivot extending in the lateral direction of the aircraft for mounting the first camera so that the first camera can rotate relative to the camera base. In the altitude direction of the aircraft, the first pivot is located above the camera mount; and / or

[0018] The camera mount has a second lug, and the camera base has multiple spaced-apart second angle adjustment lugs, allowing the second lugs to be inserted between adjacent second angle adjustment lugs. The second camera mounting component also includes a second screw and a second nut. The second screw passes through the second angle adjustment lugs and the second lugs, allowing the second lugs to rotate around the second screw. The second nut cooperates with the second screw, allowing the second angle adjustment lugs and the second lugs to lock the angle of the second camera through friction; and / or

[0019] In the left-right direction of the aircraft, the camera mounting base is provided with fixing lugs on both the left and right sides. The second camera mounting component also includes fixing screws, which are used to pass through the fixing lugs and the side walls of the camera mounting base and abut against the outer wall of the second camera.

[0020] In one embodiment, the camera base has a slot on one side for engaging with the vertical tail;

[0021] The aircraft camera bracket also includes an assembly component, which includes an assembly bolt and an assembly nut. The assembly bolt is used to pass through the two opposite groove walls of the slot and the vertical tail. The assembly nut cooperates with the assembly bolt so that the camera base can be detachably assembled onto the vertical tail.

[0022] In one embodiment, the camera base includes a housing, a first mounting protrusion, and a second mounting protrusion. The housing has the slot. Both the first mounting protrusion and the second mounting protrusion protrude from the outer surface of the housing. The first mounting protrusion and the second mounting protrusion are arranged in the longitudinal direction of the aircraft, and the second mounting protrusion is closer to the nose of the aircraft than the first mounting protrusion. In the altitude direction of the aircraft, the first mounting protrusion protrudes beyond the second mounting protrusion. The first camera mounting component is disposed on the first mounting protrusion, and the second camera mounting component is disposed on the second mounting protrusion.

[0023] The inner wall of the slot is fitted to the outer surface of the skin of the vertical tail; and / or

[0024] A shock-absorbing pad is provided between the inner wall of the slot and the outer surface of the skin of the tail; and / or

[0025] The end face of the camera base near the nose of the aircraft is teardrop-shaped; and / or

[0026] The outer surface of the camera base has at least one flow guide groove, which is spaced apart along the longitudinal direction of the aircraft, and both ends of the flow guide groove extend to both sides of the vertical tail; and / or

[0027] A boss is provided on the outer wall of the slot, and the boss has an internally threaded through hole for the assembly bolt to pass through and be screwed into; and / or

[0028] The assembly consists of two parts.

[0029] This utility model also provides an aircraft camera device, including:

[0030] Such as the aircraft camera mount mentioned above;

[0031] A first camera, detachably mounted on a first camera mounting component; and

[0032] The second camera is detachably mounted on the second camera mounting component;

[0033] The first camera is an action camera, and the second camera is an image transmission camera.

[0034] This utility model also provides an electric vertical takeoff and landing aircraft, comprising:

[0035] The aircraft body has a vertical tail; and

[0036] The aforementioned aircraft camera device has its camera base mounted on the vertical tail.

[0037] The aforementioned aircraft camera mount is mounted on the aircraft's vertical tail via a camera base, facilitating real-time image and / or video data capture and transmission by the camera mounted on the mount, thus providing a safety guarantee for real-time monitoring of the aircraft's flight attitude. Furthermore, by providing a first camera mounting component for mounting a first camera and a second camera mounting component for mounting a second camera, the aforementioned aircraft camera mount allows for the simultaneous mounting of both a first and a second camera. The first and second cameras can work collaboratively, resulting in an aircraft camera device comprising the aforementioned aircraft camera mount, the first camera, and the second camera, possessing a wide field of view. Attached Figure Description

[0038] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0039] Figure 1 This is a schematic diagram of the structure of an aircraft camera device according to an embodiment of the present invention;

[0040] Figure 2 This is a schematic diagram of the structure of an aircraft camera bracket according to an embodiment of the present invention;

[0041] Figure 3 for Figure 2 The image shows a side view of the aircraft's camera mount. Detailed Implementation

[0042] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0043] In the description of this application, it should be understood that, where they appear, the terms “center,” “longitudinal,” “lateral,” “length,” “width,” “thickness,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” “outer,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0044] Furthermore, where applicable, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0045] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., shall be interpreted broadly. For example, they may refer to a fixed connection, a detachable connection, or an integral part; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; they may refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0046] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0047] It should be noted that, if an element is described as "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is described as "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0048] like Figures 1-3 As shown, an embodiment of the present invention provides an aircraft camera device 10. The aircraft camera device 10 includes an aircraft camera bracket 200, a first camera 300, and a second camera 400. The aircraft camera device 10 is mounted on the vertical tail of the aircraft. Specifically, in this embodiment, the aircraft camera device 10 is located at the highest point of the vertical tail.

[0049] The aircraft camera mount 200 includes a camera base 210, a first camera mount 220, and a second camera mount 230. The camera base 210 is mounted on the vertical tail of the aircraft. Both the first camera mount 220 and the second camera mount 230 are mounted on the camera base 210. The first camera 300 is mounted on the first camera mount 220. The second camera 400 is mounted on the second camera mount 230.

[0050] The aforementioned aircraft camera bracket 200 is mounted on the vertical tail of the aircraft via a camera base 210, which facilitates the real-time capture and transmission of images and / or video data by the camera mounted on the aircraft camera bracket 200, providing a safety guarantee for real-time monitoring of the aircraft's flight attitude. Furthermore, by providing a first camera mounting bracket 220 for mounting the first camera 300 and a second camera mounting bracket 230 for mounting the second camera 400, the aforementioned aircraft camera bracket 200 allows for the simultaneous mounting of both the first camera 300 and the second camera 400. The first camera 300 and the second camera 400 can work collaboratively, thereby enabling the aircraft camera device 10, including the aforementioned aircraft camera bracket 200, the first camera 300, and the second camera 400, to have a wide field of view.

[0051] In this embodiment, the camera base 210 is detachably connected to the vertical stabilizer. This simplifies installation and maintenance. It is understood that in other embodiments, the camera base 210 and the vertical stabilizer may be non-detachably connected (e.g., bonded or integrally molded).

[0052] In this embodiment, the first camera mount 220 is detachably connected to the camera base 210. This simplifies installation and maintenance. It is understood that in other embodiments, the first camera mount 220 and the camera base 210 may also be non-detachably connected (e.g., bonded or integrally molded).

[0053] In this embodiment, the second camera mount 230 is detachably connected to the camera base 210. This simplifies installation and maintenance. It is understood that in other embodiments, the second camera mount 230 and the camera base 210 may also be non-detachably connected (e.g., bonded or integrally molded).

[0054] In this embodiment, the first camera 300 is detachably connected to the first camera mount 220. This simplifies installation and maintenance. It is understood that in other embodiments, the first camera 300 and the first camera mount 220 may also be non-detachably connected (e.g., bonded).

[0055] In this embodiment, the second camera 400 is detachably connected to the second camera mount 230. This simplifies installation and maintenance. It is understood that in other embodiments, the second camera 400 and the second camera mount 230 may also be non-detachably connected (e.g., bonded).

[0056] Furthermore, in the aforementioned aircraft camera bracket 200 or the aforementioned aircraft camera device 10, each component can be installed / disassembled independently. That is, the aforementioned aircraft camera bracket 200 or the aforementioned aircraft camera device 10 adopts a modular structure design, which makes installation and maintenance simple and easy.

[0057] In this embodiment, the first camera mount 220 includes a first pivot 222 disposed on the camera base 210. The first pivot 222 is used to mount the first camera 300 so that the first camera 300 can rotate relative to the camera base 210. Thus, the first camera 300 can adjust its shooting angle by rotating around the first pivot 222, making it easier to adjust the field of view of the aircraft camera device 10. It is understood that in other embodiments, the first camera 300 may also be fixed to the camera base 210, in which case the first pivot 222 may be omitted.

[0058] In this embodiment, the second camera mount 230 includes a second pivot 232 disposed on the camera base 210. The second pivot 232 is used to mount the second camera 400 so that the second camera 400 can rotate relative to the camera base 210. This makes it very convenient to adjust the shooting angle of the second camera 400. Thus, the second camera 400 can adjust its shooting angle by rotating around the second pivot 232, making it easier to adjust the field of view of the aircraft camera device 10. It is understood that in other embodiments, the second camera 400 may also be fixed to the camera base 210, in which case the second pivot 232 may be omitted.

[0059] In this embodiment, the first camera mount 220 and the second camera mount 230 are arranged in the longitudinal direction of the aircraft, with the second camera mount 230 closer to the nose of the aircraft than the first camera mount 220. The first pivot 222 extends in the lateral direction of the aircraft. Thus, the second camera mount 230 is located in front of the first camera mount 220. By adjusting the shooting angle of the first camera 300, the second camera 400, located in front of the first camera 300, can be prevented from entering the field of view of the first camera 300 and interfering with its image capture.

[0060] In this embodiment, the first pivot 222 is located above the second pivot 232 in the altitude direction of the aircraft. This facilitates the layered arrangement of the first camera 300 and the second camera 400, ensuring that the first camera 300 is at a higher position and the second camera 400 is at a lower position. This prevents the second camera 400, located in front of the first camera 300, from entering the field of view of the first camera 300 and interfering with its image capture. It is understood that in other embodiments, when the first camera mount 220 and the second camera mount 230 are not arranged in the front-rear direction of the aircraft—for example, when the first camera mount 220 is located at the left front of the aircraft and the second camera mount 230 is located at the right front of the aircraft—the first pivot 222 and the second pivot 232 can also be set at the same height.

[0061] In this embodiment, when the first camera 300 is in a vertical direction, it can swing around the first pivot 222 within a wide range (±45°), facilitating the adjustment of the shooting angle of the first camera 300. When the second camera 400 is in a vertical direction, it can swing around the second pivot 232 within a small range (±5°), facilitating fine-tuning of the relative position of the second camera 400 and the first camera 300 during installation.

[0062] In this embodiment, the second camera mounting component 230 further includes a camera mounting base 234. The camera mounting base 234 is disposed on the camera base 210. The camera mounting base 234 has a receiving cavity 234a for accommodating the second camera 400 (the size of the receiving cavity 234a matches the fuselage of the second camera 400, with a gap ≤0.5mm). The side of the camera mounting base 234 near the nose of the aircraft has an inlet and outlet 234b communicating with the receiving cavity 234a. The inlet and outlet 234b is used for the second camera 400 to enter and exit the receiving cavity 234a. In this way, the second camera 400 can be a bare unit without a mounting structure (the first camera 300 is not a bare unit; the first camera 300 has a first lug 310, which is its mounting structure), thereby making it easier for the aforementioned aircraft camera device 10 to select a camera.

[0063] In this embodiment, the first pivot 222 is located above the camera mount 234 in the altitude direction of the aircraft. This facilitates the layered arrangement of the first camera 300 and the second camera 400, placing the first camera 300 at a higher position and the second camera 400 at a lower position, thus preventing the second camera 400, located in front of the first camera 300, from entering the field of view of the first camera 300 and interfering with the first camera 300's shooting and drawing.

[0064] In this embodiment, the distance between the first rotating shaft 222 and the camera mount 234 in the altitude direction of the aircraft is greater than or equal to 50mm. This prevents the camera mount 234 from entering the field of view of the first camera 300 when it is taking pictures.

[0065] In this embodiment, the camera base 210 has a slot 210a on one side. The slot 210a is used to engage with the vertical stabilizer. The aircraft camera bracket 200 also includes an assembly. The assembly includes an assembly bolt 240 and an assembly nut. The assembly bolt 240 is used to pass through the two opposite walls of the slot 210a and the vertical stabilizer. The assembly nut cooperates with the assembly bolt 240 to allow the camera base 210 to be detachably mounted on the vertical stabilizer. This facilitates a detachable connection between the camera base 210 and the vertical stabilizer. Specifically, in this embodiment, the assembly bolt 240 is an M6 high-strength bolt.

[0066] In this embodiment, a boss 210b protrudes from the outer wall of the slot 210a. The boss 210b has an internally threaded through hole for the mounting bolt 240 to pass through and be screwed onto. This effectively disperses the stress during the tightening of the mounting bolt 240, avoids local deformation of the tail skin, and improves connection reliability. Specifically, in this embodiment, the boss 210b is cylindrical, with a diameter of 12mm, and a minimum length of 5mm protruding from the boss 210b to the outer wall of the slot 210a.

[0067] In this embodiment, there are two assemblies. The two assemblies are arranged in the fore-and-aft direction of the aircraft. This facilitates a secure connection between the camera base 210 and the vertical tail.

[0068] In this embodiment, the inner wall of the slot 210a is fitted to the outer surface of the skin of the vertical tail. This facilitates a secure connection between the camera base 210 and the vertical tail, prevents the camera base 210 from damaging the vertical tail, and also helps reduce wind resistance. Specifically, in this embodiment, the fitting accuracy is ≤0.1mm.

[0069] In this embodiment, a shock-absorbing pad is provided between the inner wall of the slot 210a and the outer surface of the vertical tail skin. This shock-absorbing pad absorbs vibration energy, effectively preventing loosening of the connection due to vibration during flight. Specifically, in this embodiment, the shock-absorbing pad is a nitrile rubber shock-absorbing pad (2mm thick, Shore A50 hardness), which can absorb more than 50% of the vibration energy, effectively preventing loosening of the connection due to vibration during flight.

[0070] In this embodiment, the end face of the camera base 210 near the nose of the aircraft is teardrop-shaped (length-to-diameter ratio 3:1). This helps to reduce wind resistance.

[0071] In this embodiment, the outer surface of the camera base 210 has at least one flow guide groove. The flow guide grooves are spaced apart along the longitudinal direction of the aircraft, with both ends extending to the sides of the vertical stabilizer. The flow guide grooves guide airflow to adhere to the outer surface of the camera base 210, preventing turbulent separation. Specifically, in this embodiment, the depth of the flow guide groove is 0.5 mm, and the spacing between two adjacent flow guide grooves is 2 mm.

[0072] In this embodiment, the camera base 210 includes a housing 212, a first mounting protrusion 214, and a second mounting protrusion 216. The shape of the housing 212 is adapted to the shape of the vertical stabilizer and is used to cover the opposite sides of the vertical stabilizer. Specifically, in this embodiment, the housing 212 has a slot 210a for engaging with the vertical stabilizer. Both the first mounting protrusion 214 and the second mounting protrusion 216 protrude from the outer surface of the housing 212. The first mounting protrusion 214 and the second mounting protrusion 216 are arranged in the longitudinal direction of the aircraft, and the second mounting protrusion 216 is closer to the nose of the aircraft than the first mounting protrusion 214. In the altitude direction of the aircraft, the first mounting protrusion 214 protrudes beyond the second mounting protrusion 216. A first camera mount 220 is disposed on the first mounting protrusion 214. A second camera mount 230 is disposed on the second mounting protrusion 216. This arrangement facilitates the layered placement of the first camera 300 and the second camera 400, placing the first camera 300 at a higher position and the second camera 400 at a lower position. This prevents the second camera 400, located in front of the first camera 300, from entering the field of view of the first camera 300 and interfering with its shooting and drawing. Furthermore, the camera base 210 with the above-described structure helps reduce wind resistance.

[0073] In this embodiment, the first camera mounting component 220 includes a connecting mechanism 220a and an angle adjustment mechanism 220b. The connecting mechanism 220a is disposed on the camera base 210 (first mounting protrusion 214). The angle adjustment mechanism 220b includes a first angle adjustment lug 224, a first screw 222, and a first nut. There are multiple first angle adjustment lugs 224. The multiple first angle adjustment lugs 224 are arranged at intervals on the connecting mechanism 220a so that the first lug 310 of the first camera 300 can be inserted between two adjacent first angle adjustment lugs 224. The first screw 222 is used to pass through the first angle adjustment lugs 224 and the first lug 310. The first pivot 222 is the first screw 222. The first nut cooperates with the first screw 222 so that the first angle adjustment lugs 224 and the first lug 310 can lock the angle of the first camera 300 through friction. This not only facilitates the detachable connection between the first camera 300 and the first camera mounting component 220, but also facilitates the rotation of the first camera 300.

[0074] In this embodiment, the first screw 222 is a hand-tightening screw (with anti-slip knurling on the surface) for easy disassembly and installation. The first nut is a nylon lock nut. In this embodiment, the thread fit accuracy between the hand-tightening screw and the nut reaches 6H / 6g level, effectively preventing loosening of the connection due to vibration during flight. Specifically, in this embodiment, the first screw 222 is an M5 hand-tightening screw. When the first screw 222 is loosened, the first camera 300 can be freely adjusted within a vertical range of ±45° around the first screw 222; after tightening the first nut, the angle is locked by the friction between the lugs. The adjustment process requires no tools and can be completed by a single person within 30 seconds.

[0075] In this embodiment, the angle adjustment mechanism 220b includes a pair of U-shaped lugs, that is, the angle adjustment mechanism 220b includes three first angle adjustment lugs 224 (lug spacing 25mm, thickness 3mm). The first camera 300 has U-shaped lugs, that is, the first camera 300 has two first lugs 310.

[0076] In this embodiment, the first angle adjusting ear 224 has a first adjusting serration (tooth height 0.3mm, tooth pitch 1mm, angle 30°). The first adjusting serration is used to engage with the first serration on the first ear 310 to mechanically lock the first angle adjusting ear 224 and the first ear 310. Thus, when the first adjusting serration engages with the first serration, mechanical locking can prevent angle deviation.

[0077] In this embodiment, the first camera mounting component 220 (adapter mechanism 220a) is fixed to the camera base 210 (first mounting protrusion 214) with screws. This facilitates the detachable connection between the first camera mounting component 220 and the camera base 210. Specifically, in this embodiment, the adapter mechanism 220a has two φ6mm mounting holes (40mm apart, symmetrically distributed), which are fixed to the first mounting protrusion 214 with M4 countersunk screws, ensuring a tight and secure fit between the adapter mechanism 220a and the first mounting protrusion 214 without any wobble.

[0078] In this embodiment, the camera mount 234 (second mounting protrusion 216) has a second lug 236. The camera base 210 has a plurality of spaced-apart second angle adjustment lugs 218, allowing the second lug 236 to be inserted between adjacent second angle adjustment lugs 218. The second camera mount 230 also includes a second screw 232 and a second nut. The second screw 232 is used to pass through the second angle adjustment lugs 218 and 236. The second pivot 232 is the second screw 232. The second nut cooperates with the second screw 232, allowing the second angle adjustment lugs 218 and 236 to lock the angle of the second camera 400 through friction. This not only facilitates the detachable connection between the second camera mount 230 and the camera base 210, but also facilitates the rotation of the camera mount 234, thereby driving the second camera 400 located within the camera mount 234 to rotate.

[0079] In this embodiment, there are three second angle adjustment lugs 218 (lug spacing 20mm). There are two second lugs 236 (thickness 4mm). The second screw 232 is a hand-tightening screw (M6 hand-tightening screw). In this embodiment, the thread fit accuracy between the hand-tightening screw and the nut reaches 6H / 6g level, effectively preventing loosening of the connection due to vibration during flight.

[0080] In this embodiment, the second angle adjusting ear 218 has a second adjusting serration. The second adjusting serration engages with the second serration on the second ear 236 to mechanically lock the second angle adjusting ear 218 and the second ear 236. Thus, when the adjusting serration engages with the second serration, angle deviation can be prevented by mechanical locking.

[0081] In this embodiment, the camera mount 234 has a notch 234c on one side of the second lug 236. The notch 234c communicates with the receiving cavity 234a and extends along the longitudinal direction of the aircraft. In the lateral direction of the aircraft, the second lug 236 is present on both the left and right sides of the notch 234c. This facilitates the entry and exit of the second camera 400 into and out of the receiving cavity 234a and improves the reliability of the connection between the camera mount 234 and the camera base 210.

[0082] In this embodiment, mounting lugs 238 are provided on both the left and right sides of the camera mount 234 in the left-right direction of the aircraft. The second camera mounting component 230 also includes a fixing screw 239 (in this embodiment, the fixing screw 239 is an M3 hex socket screw). The fixing screw 239 is used to pass through the mounting lugs 238 and the side wall of the camera mount 234 and abut against the outer wall of the second camera 400. In this way, it is very convenient for the second camera 400 to be detachably connected to the second camera mounting component 230, and it can also make the connection between the second camera 400 and the second camera mounting component 230 highly reliable, ensuring a stable connection during flight and no displacement or shaking of the second camera 400.

[0083] In this embodiment, a shock-absorbing pad is provided between the fixing lug 238 and the camera mounting base 234. This shock-absorbing pad absorbs vibration energy, effectively preventing loosening of the connection due to vibration during flight. Specifically, in this embodiment, the shock-absorbing pad is a nitrile rubber shock-absorbing pad (2mm thick, Shore A50 hardness), which can absorb more than 50% of the vibration energy, effectively preventing loosening of the connection due to vibration during flight.

[0084] In this embodiment, the first camera 300 is an action camera, and the second camera 400 is an image transmission camera. Thus, the lens of the first camera 300 mainly covers the top of the aircraft rotor and the external environment, while the lens of the second camera 400 mainly focuses on key components in the middle of the fuselage (such as the rotor connecting shaft and skin interface), achieving complementary fields of view between the two cameras. It is understood that in other embodiments, both the first camera 300 and the second camera 400 can be action cameras or image transmission cameras.

[0085] In this embodiment, the main parts of the camera base 210, the first camera mounting component 220, and the second camera mounting component 230 are all made of 6061-T6 aluminum alloy, precision machined by CNC, and anodized to improve wear resistance and corrosion resistance. 6061-T6 aluminum alloy is characterized by its low weight and high strength, effectively ensuring the stability of image / video data transmission during flight. Specifically, in this embodiment, the main load-bearing components (camera base 210, camera mounting bracket 234) are made of 6061-T6 aluminum alloy to ensure connection strength. The non-load-bearing adjustment components (first camera mounting component 220, fixing lug 238) are made of CFRP (density 1.6 g / cm³). 3 It is only 60% the weight of aluminum alloy, manufactured through a molding process, and coated with a 3μm thick conductive silver paste coating (sheet resistance ≤0.1Ω) to solve the problem of static accumulation in carbon fiber materials and avoid static interference with image transmission signals during flight.

[0086] In this embodiment, all connecting components (bolts, screws, and thumbscrews) adopt standardized specifications, and the disassembly sequence is clear: first, remove the thumbscrews of the first camera 300 → remove the first camera 300 → remove the countersunk screws of the adapter mechanism 220a → remove the adapter mechanism 220a → remove the fixing screws 239 of the fixing lug 238 of the second camera 400 → remove the second camera 400 → finally, remove the mounting bolts 240 of the camera base 210. The replacement time for a single component is ≤10 minutes, no special tools are required, and the difficulty of ground maintenance is significantly reduced.

[0087] This utility model also provides an electric vertical takeoff and landing (EVTOL) aircraft. The EVTOL aircraft has a vertical tail. The camera base 210 of the aforementioned aircraft camera device 10 is mounted on the vertical tail. It is understood that in other embodiments, the EVTOL aircraft may also be other types of aircraft.

[0088] The aforementioned aircraft camera device 10 has a stable configuration, effectively reducing wind resistance. All components are individually replaceable, and this configuration allows for adjustment of the shooting angle. This structural design, with its high-low camera positions, effectively prevents the camera mount 234 from appearing in the lens of the first camera 300 during shooting. The connections throughout the aircraft camera device 10 are reliable and robust, ensuring stable image / video transmission during flight. It allows for direct observation of the aircraft's attitude stability during flight and rapid identification of the status of each rotor, facilitating attitude adjustments during flight.

[0089] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0090] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An aircraft camera mount, comprising: include: Camera mount, for mounting on the vertical tail of an aircraft; A first camera mounting component is disposed on the camera base and is used to mount the first camera; as well as The second camera mounting component is disposed on the camera base and is used to mount the second camera.

2. The aircraft camera mount of claim 1, wherein, The camera base is detachably connected to the vertical tail; and / or The first camera mounting component is detachably connected to the camera base; and / or The second camera mounting component is detachably connected to the camera base; and / or The first camera mount includes a first pivot on the camera base, the first pivot being used to mount the first camera so that the first camera can rotate relative to the camera base; and / or The second camera mount includes a second pivot on the camera base, the second pivot being used to mount the second camera so that the second camera can rotate relative to the camera base.

3. The aircraft camera mount of claim 1, wherein, The first camera mounting component includes an adapter mechanism and an angle adjustment mechanism. The adapter mechanism is mounted on the camera base. The angle adjustment mechanism includes a first angle adjustment lug, a first screw, and a first nut. There are multiple first angle adjustment lugs, which are spaced apart on the adapter mechanism so that the first lug of the first camera can be inserted between two adjacent first angle adjustment lugs. The first screw is used to pass through the first angle adjustment lug and the first lug so that the first lug can rotate around the first screw. The first nut cooperates with the first screw so that the first angle adjustment lug and the first lug can lock the angle of the first camera through friction.

4. The aircraft camera mount of Claim 3, wherein, The first angle adjusting ear has a first adjusting serration, which engages with the first serration on the first ear to mechanically lock the first angle adjusting ear to the first ear; and / or The adapter mechanism is fixed to the camera base with screws.

5. The aircraft camera mount of claim 1, wherein, The second camera mounting component includes a camera mount, which is disposed on the camera base. The camera mount has a cavity for accommodating the second camera. The side of the camera mount near the nose of the aircraft has an inlet and outlet communicating with the cavity. The inlet and outlet are used for the second camera to enter and exit the cavity.

6. The aircraft camera mount of claim 5, wherein, The first camera mount and the second camera mount are arranged in the longitudinal direction of the aircraft, with the second camera mount being closer to the nose of the aircraft relative to the first camera mount. The first camera mount includes a first pivot on the camera base, the first pivot extending in the lateral direction of the aircraft for mounting the first camera so that the first camera can rotate relative to the camera base. In the altitude direction of the aircraft, the first pivot is located above the camera mount; and / or The camera mount has a second lug, and the camera base has multiple spaced-apart second angle adjustment lugs, allowing the second lugs to be inserted between adjacent second angle adjustment lugs. The second camera mounting component also includes a second screw and a second nut. The second screw passes through the second angle adjustment lugs and the second lugs, allowing the second lugs to rotate around the second screw. The second nut cooperates with the second screw, allowing the second angle adjustment lugs and the second lugs to lock the angle of the second camera through friction; and / or In the left-right direction of the aircraft, the camera mounting base is provided with fixing lugs on both the left and right sides. The second camera mounting component also includes fixing screws, which are used to pass through the fixing lugs and the side walls of the camera mounting base and abut against the outer wall of the second camera.

7. The aircraft camera mount of claim 1, wherein, The camera base has a slot on one side for locking onto the vertical tail. The aircraft camera bracket also includes an assembly component, which includes an assembly bolt and an assembly nut. The assembly bolt is used to pass through the two opposite groove walls of the slot and the vertical tail. The assembly nut cooperates with the assembly bolt so that the camera base can be detachably assembled onto the vertical tail.

8. The aircraft camera mount of claim 7, wherein, The camera base includes a housing, a first mounting protrusion, and a second mounting protrusion. The housing has the slot. Both the first mounting protrusion and the second mounting protrusion protrude from the outer surface of the housing. The first mounting protrusion and the second mounting protrusion are arranged in the longitudinal direction of the aircraft, and the second mounting protrusion is closer to the nose of the aircraft than the first mounting protrusion. In the height direction of the aircraft, the first mounting protrusion protrudes beyond the second mounting protrusion. The first camera mounting component is disposed on the first mounting protrusion, and the second camera mounting component is disposed on the second mounting protrusion. The inner wall of the slot is fitted to the outer surface of the skin of the vertical tail; and / or A shock-absorbing pad is provided between the inner wall of the slot and the outer surface of the skin of the tail; and / or The end face of the camera base near the nose of the aircraft is teardrop-shaped; and / or The outer surface of the camera base has at least one flow guide groove, which is spaced apart along the longitudinal direction of the aircraft, and both ends of the flow guide groove extend to both sides of the vertical tail; and / or A boss is provided on the outer wall of the slot, and the boss has an internally threaded through hole for the assembly bolt to pass through and be screwed into; and / or The assembly consists of two parts.

9. An aircraft camera device, characterized by include: The aircraft camera mount as described in any one of claims 1-8; The first camera is detachably mounted on the first camera mounting component; as well as The second camera is detachably mounted on the second camera mounting component; The first camera is an action camera, and the second camera is an image transmission camera.

10. An electric vertical take-off and landing aircraft, characterized in that, include: The aircraft body has a vertical tail; as well as The aircraft camera device of claim 9, wherein the camera base is disposed on the vertical tail.

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