Unmanned aerial vehicle undercarriage locking mechanism and unmanned aerial vehicle fixing equipment

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and provides an unmanned aerial vehicle undercarriage locking mechanism and unmanned aerial vehicle fixing equipment, the locking mechanism comprises a locking platform, a locking part and a driving piece, the locking part is movably connected to the locking platform, and the locking part is provided with a clamping part; the driving piece is arranged on the locking platform and used for driving the locking part to be switched between the locking position and the unlocking position; at the locking position, the locking part locks the supporting body, and the supporting rod is clamped to the clamping part; and at the unlocking position, the locking part unlocks the supporting body. According to the unmanned aerial vehicle undercarriage locking mechanism provided by the utility model, the locking part is driven by the driving part to be switched between the locking position and the unlocking position; and at the locking position, the supporting body is locked through the locking component, and the supporting piece is positioned through the clamping part on the locking component, so that the fixing stability of the undercarriage and the unmanned aerial vehicle is improved, and the problem that the unmanned aerial vehicle slides down and is damaged is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a UAV landing gear locking mechanism and a UAV fixing device. Background Art

[0002] Drones (UAVs) are unmanned aircraft controlled by radio remote control and self-contained programmable devices. Based on their flight platform configuration, UAVs can be categorized as fixed-wing, rotary-wing, airship, parachute, and flapping-wing. They are widely used in fields such as power inspection, agriculture, plant protection, express delivery, disaster relief, infectious disease monitoring, and surveying and mapping. The landing gear is a crucial component of a UAV, and its performance directly impacts its safety.

[0003] In the prior art, the drone landing gear is clamped by two clamps to fix the drone on the apron or the drone-mounted tools. This clamping method has poor stability, causing the drone to move or fall out of the clamps, and in severe cases, causing the drone to slip and be damaged. Utility Model Content

[0004] The utility model provides a UAV landing gear locking mechanism and a UAV fixing device, which are used to solve the defects of the prior art UAV landing gear fixing method having poor stability and being prone to UAV sliding and damage.

[0005] The utility model provides a locking mechanism for a landing gear of a UAV, wherein the landing gear comprises a supporting body and a supporting rod connected to the supporting body, and the locking mechanism comprises:

[0006] Locking the platform;

[0007] A locking component movably connected to the locking platform; the locking component has a clamping portion;

[0008] A driving member is provided on the locking platform, and is used to drive the locking member to switch between a locked position and an unlocked position; in the locked position, the locking member locks the support body, and the support rod is clamped to the clamping portion; in the unlocked position, the locking member releases the lock on the support body.

[0009] According to a UAV landing gear locking mechanism provided by the utility model, the locking platform is provided with a rotating shaft, the locking component is connected to the rotating shaft; and the output of the driving member is connected to the rotating shaft.

[0010] According to a UAV landing gear locking mechanism provided by the utility model, a first connecting member is mounted on the rotating shaft, and the first connecting member has an outwardly extending extension portion, and the output of the driving member is rotatably connected to an end of the extension portion away from the center of the rotating shaft.

[0011] According to a UAV landing gear locking mechanism provided by the utility model, the locking component includes:

[0012] a second connecting member, movably connected to the first side of the locking platform;

[0013] a locking member connected to the second connecting member;

[0014] In the locked position, at least a portion of the locking member extends to the second side of the locking platform, and a locking cavity for accommodating the support body is formed between at least a portion of the locking member and the locking platform;

[0015] In the unlocked position, at least a portion of the locking member is retracted to a first side of the locking platform.

[0016] According to a UAV landing gear locking mechanism provided by the utility model, the locking member includes a first locking pressure plate and a second locking pressure plate connected to each other, the first locking pressure plate is connected to the second connecting member, and a first preset angle is formed between the first locking pressure plate and the second locking pressure plate;

[0017] In the locking position, both the first locking pressure plate and the second locking pressure plate abut against the support body.

[0018] According to the UAV landing gear locking mechanism provided by the present invention, the clamping portion is arranged on a side of the second locking pressure plate away from the first locking pressure plate.

[0019] According to a UAV landing gear locking mechanism provided by the utility model, the clamping portion includes a first limiting surface and a second limiting surface;

[0020] In the locking position, both the first limiting surface and the second limiting surface abut against the support rod.

[0021] According to the UAV landing gear locking mechanism provided by the utility model, a second preset angle is formed between the first limiting surface and the second limiting surface.

[0022] The utility model also provides a UAV fixing device, comprising any one of the UAV landing gear locking mechanisms described above.

[0023] According to the utility model, a UAV fixing device further includes a fixing platform, on which two UAV landing gear locking mechanisms are arranged opposite to each other, and the locking platform of at least one UAV landing gear locking mechanism is in sliding cooperation with the fixing platform.

[0024] The UAV landing gear locking mechanism provided by the utility model drives the locking component to switch between a locked position and an unlocked position through a driving member; in the locked position, the supporting body is locked by the locking component, and the clamping portion on the locking component positions the supporting component to improve the stability of the landing gear and the UAV fixation, thereby avoiding the problem of the UAV slipping and being damaged. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0026] Figure 1 The utility model is a schematic diagram of the structure of the UAV landing gear locking mechanism for locking the landing gear.

[0027] Figure 2 yes Figure 1 Schematic diagram of the local enlarged structure at point A.

[0028] Figure 3 It is a structural schematic diagram of the UAV landing gear locking mechanism unlocking the landing gear provided by the utility model.

[0029] Figure 4 yes Figure 3 Schematic diagram of the local enlarged structure at point B.

[0030] Figure 5 This is one of the structural schematic diagrams of the UAV landing gear locking mechanism provided by the utility model in the locked position.

[0031] Figure 6 This is the second structural schematic diagram of the UAV landing gear locking mechanism provided by the utility model in the locked position.

[0032] Figure 7 It is a structural schematic diagram of the locking component provided by the utility model.

[0033] Figure 8 It is a structural schematic diagram of the first connecting piece provided by the utility model.

[0034] Reference numerals:

[0035] 100, UAV landing gear locking mechanism; 110, locking platform; 120, locking component; 121, clamping portion; 1211, first limiting surface; 1212, second limiting surface; 122, second connecting member; 123, locking member; 1231, first locking pressure plate; 1232, second locking pressure plate;

[0036] 130, driving member; 140, rotating shaft; 150, first connecting member; 151, extending portion;

[0037] 200. UAV; 210. Airframe; 220. Support body; 230. Support rod. DETAILED DESCRIPTION

[0038] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0039] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance.

[0040] In the description of the embodiments of the present invention, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on specific circumstances.

[0041] In the embodiments of the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, a first feature being "above," "above," or "above" a second feature may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below," "below," or "below" a second feature may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is lower in level than the second feature.

[0042] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0043] The following combination Figures 1-8 The invention describes a locking mechanism for a UAV landing gear.

[0044] The embodiment of the first aspect of the present utility model provides a UAV landing gear locking mechanism, such as Figures 1 to 4 、 Figure 7 As shown, the locking mechanism includes a locking platform 110, a locking component 120 and a driving component 130; the locking component 120 is movably connected to the locking platform 110; the locking component 120 has a clamping portion 121; the driving component 130 is arranged on the locking platform 110, and the driving component 130 is used to drive the locking component 120 to switch between a locked position and an unlocked position; in the locked position, the locking component 120 locks the support body 220, and the support rod 230 is clamped to the clamping portion 121; in the unlocked position, the locking component 120 releases the lock on the support body 220.

[0045] The drone 200 includes a body 210 and a landing gear arranged at the lower part of the body 210 . The landing gear includes a support body 220 and a support rod 230 . The upper end of the support rod 230 is connected to the body 210 , and the lower end of the support rod 230 is connected to the support body 220 .

[0046] It can be understood that the support body 220 of the landing gear is placed on the locking platform 110, and the locking component 120 is driven to move by the driving member 130 to achieve the locking of the landing gear by the locking component 120, thereby fixing the position of the drone 200 to prevent the drone 200 from slipping and being damaged.

[0047] Specifically, the driving member 130 drives the locking member 120 to switch between the locked position and the unlocked position to achieve locking and unlocking of the UAV landing gear; Figure 1 and Figure 2As shown, when the locking component 120 is in the locked position, the locking component 120 is close to the locking body to lock the support body 220, and the support rod 230 is clamped to the clamping portion 121 to achieve locking of the landing gear; when the landing gear needs to be unlocked, the driving member 130 drives the locking component 120 to move away from the locking body, and the support rod 230 is away from the clamping portion 121, so that the locking component 120 is separated from the support body 220, so that the locking component 120 releases the lock on the support body 220, as shown in FIG. Figure 3 and Figure 4 shown.

[0048] It should be noted that when the locking component 120 is in the locked position, the supporting body 220 is locked by the locking component 120, and the clamping portion 121 on the locking component 120 locks the supporting member, thereby ensuring the stability of the landing gear and the UAV 200.

[0049] The UAV landing gear locking mechanism provided by the embodiment of the present invention drives the locking component 120 to switch between a locked position and an unlocked position through the driving component 130; in the locked position, the supporting body 220 is locked by the locking component 120, and the clamping portion 121 on the locking component 120 positions the supporting component to improve the stability of the landing gear and the fixing of the UAV 200, thereby avoiding the problem of the UAV 200 slipping and being damaged.

[0050] In one embodiment of the present invention, Figure 6 and Figure 7 As shown, the locking platform 110 is provided with a rotating shaft 140 , the locking component 120 is connected to the rotating shaft 140 , and the output of the driving member 130 is connected to the rotating shaft 140 .

[0051] It is understandable that the driving member 130 drives the rotating shaft 140 to rotate, and the rotating shaft 140 drives the locking component 120 thereon to rotate, so that the locking component 120 can be switched between the locked position and the unlocked position.

[0052] Optionally, a first connecting member 150 is mounted on the rotating shaft 140 . The first connecting member 150 has an outwardly extending extension portion 151 . The output of the driving member 130 is rotatably connected to an end of the extension portion 151 away from the center of the rotating shaft 140 .

[0053] In this embodiment, the driving member 130 can adopt a driving cylinder, the cylinder body of the driving cylinder is movably installed on the locking platform 110, and the piston rod of the driving cylinder is rotatably connected to the extension part 151 through a pin shaft. The driving cylinder drives the piston rod to extend, and the piston rod drives the rotating shaft 140 to rotate forward, and the rotating shaft 140 drives the locking component 120 to rotate close to the support body 220 to achieve locking of the landing gear; when it is necessary to unlock the landing gear, the driving cylinder drives the piston rod to retract, and the piston rod drives the rotating shaft 140 to rotate in the opposite direction, and the rotating shaft 140 drives the locking component 120 to rotate away from the support body 220 to release the lock of the landing gear.

[0054] In one embodiment of the present invention, Figures 5 to 7 As shown, the driving member 130 is disposed on the first side of the locking platform 110, and the locking component 120 is movably connected to the first side of the locking platform 110. Under the action of the driving member 130, the locking component 120 can be extended to the second side of the locking platform 110 to lock the landing gear, and can be retracted to the first side of the locking platform 110. It should be noted that the second side of the locking platform 110 is the side where the landing gear is fixed.

[0055] Optionally, the locking component 120 includes a second connecting member 122 and a locking member 123, the second connecting member 122 is connected to the rotating shaft 140, the locking member 123 is connected to the second connecting member 122, the driving member 130 drives the rotating shaft 140 to rotate, and the rotating shaft 140 drives the locking member 123 to rotate; when the locking component 120 is in the locked position, at least part of the locking member 123 extends to the second side of the locking platform 110, and a locking cavity for accommodating the support body 220 is formed between at least part of the locking member 123 and the locking platform 110 to achieve locking of the support body 220; when the locking component 120 is in the unlocked position, at least part of the locking member 123 is retracted to the first side of the locking platform 110.

[0056] In one embodiment of the present invention, Figure 6 and Figure 8 As shown, the first connecting member 150 is a sleeve structure, and the first connecting member 150 has an extension portion 151 extending outward, and the extension portion 151 is arc-shaped, with one end of the extension portion 151 close to the center of the first connecting member 150 and the other end of the extension portion 151 away from the center of the first connecting member 150; the second connecting member 122 has two connecting portions, and the two connecting portions have connecting holes for cooperating with the rotating shaft 140.

[0057] The assembly process of the UAV landing gear locking mechanism in this embodiment is as follows: the first connecting member 150 is sleeved on the middle part of the rotating shaft 140, and the rotating shaft 140 is passed through the two connecting parts of the second connecting member 122, the first connecting member 150 is located in the middle of the two connecting parts, and the rotating shaft 140 is rotatably installed on the locking platform 110; the cylinder body of the movable cylinder is movably installed on the locking platform 110, and the piston rod of the driving cylinder is rotatably connected to the end of the extension part 151 away from the center of the rotating shaft 140 through a pin shaft; after determining the installation position of the first connecting member 150 and the second connecting member 122, the first connecting member 150 is connected to the rotating shaft 140 through a keyway, and the second connecting member 122 is connected to the rotating shaft 140 through a keyway; the locking member 123 is installed on the second connecting member 122.

[0058] It should be noted that by adjusting the length of the extension portion 151 and the position of the second connecting member 122 (the corresponding central angle between the connecting portion and the extension portion 151), it is possible to fix UAV landing gear of different specifications on the apron.

[0059] Further, such as Figure 5 As shown, the locking member 123 includes a first locking pressure plate 1231 and a second locking pressure plate 1232 connected to each other. The first locking pressure plate 1231 is connected to the second connecting member 122. There is a first preset angle between the first locking pressure plate 1231 and the second locking pressure plate 1232. In the locked position, the first locking pressure plate 1231 and the second locking pressure plate 1232 are both against the support body 220.

[0060] Optionally, the first preset angle between the first locking pressure plate 1231 and the second locking pressure plate 1232 can be an obtuse angle. For example, the locking platform 110 is arranged horizontally, the driving member 130 is located on the lower side of the locking platform 110, and the landing gear is located on the locking platform 110. When the locking component 120 is in the locked position, the first locking pressure plate 1231 is arranged at an angle, and the second locking pressure plate 1232 is located on the upper side of the support body 220. The second locking pressure plate 1232 is arranged at an angle, and the end of the second locking pressure plate 1232 away from the first locking pressure plate 1231 is close to the locking platform 110.

[0061] It should be noted that the locking member 123 can be a curved pressure plate to enhance the surface pressure and lateral locking function; of course, in other embodiments, the end of the locking member 123 away from the second connecting member 122 can also be in an arc hook shape to form a locking hook structure.

[0062] In one embodiment of the present invention, the clamping portion 121 is provided on a side of the second locking plate 1232 away from the first locking plate 1231 . The number of the clamping portions 121 is equal to the number of the support rods 230 of the landing gear, and the positions correspond one to one.

[0063] In this embodiment, Figure 3As shown, each landing gear includes two support rods 230 , and the second locking pressure plate 1232 is provided with two clamping portions 121 that cooperate with the two support rods 230 .

[0064] For example, the two clamping parts 121 are located at the edge of the second locking pressure plate 1232, and the clamping part 121 can be a notch opened at the edge of the second locking pressure plate 1232; in the locked position, the first locking pressure plate 1231 is arranged obliquely, the second locking pressure plate 1232 is located on the upper side of the support body 220, and the second locking pressure plate 1232 is arranged downwardly obliquely, and the end of the second locking pressure plate 1232 away from the first locking pressure plate 1231 is close to the locking platform 110, so that the first locking pressure plate 1231, the second locking pressure plate 1232 and the locking platform 110 are locked. A locking cavity is formed, and the second locking pressure plate 1232 realizes the locking of the front-to-back and up-down degrees of freedom of the support body 220; at the same time, the two support rods 230 are respectively clamped to the clamping parts 121 at the ends of the second locking pressure plate 1232, thereby realizing the locking of the left-right degrees of freedom of the landing gear. In this way, the locking component 120 of this embodiment can realize the locking of the six degrees of freedom of the landing gear in the front-to-back direction, the up-down direction, and the left-to-right direction in the locking position, thereby realizing the locking of the six degrees of freedom of the drone 200, thereby ensuring that the drone 200 is in a completely fixed state.

[0065] Optional, such as Figure 7 As shown, the engaging portion 121 includes a first limiting surface 1211 and a second limiting surface 1212. A second preset angle is defined between the first limiting surface 1211 and the second limiting surface 1212. In the locked position, the first limiting surface 1211 and the second limiting surface 1212 both abut against the support rod 230. In an example, the second preset angle can be 80° to 150°. In this embodiment, the second preset angle is 90°. The first limiting surface 1211 and the second limiting surface 1212 are connected by a circular arc transition.

[0066] It should be noted that when the landing gear includes a support rod 230, the clamping portion 121 can be arranged in the middle of the second locking pressure plate 1232, and the clamping portion 121 can be a clamping slot, and the shape of the clamping slot can be a triangle, U-shape or other shapes, as long as it can be clamped with the support rod 230.

[0067] An embodiment of the second aspect of the present invention provides a drone fixing device, which includes the drone landing gear locking mechanism 100 provided by any of the above embodiments.

[0068] In the embodiments of the present invention, the type of drone fixing device is not limited. For example, the drone fixing device can be a transport device, a carrying device, etc. In other words, as long as the drone fixing device can use the drone landing gear locking mechanism 100 of the present invention, it will be sufficient.

[0069] Optionally, the UAV fixing device further includes a fixing platform, on which a locking group is provided, and the locking group includes two UAV landing gear locking mechanisms 100 arranged opposite to each other.

[0070] It can be understood that the locking platforms 110 of the two UAV landing gear locking mechanisms 100 are set on a fixed platform, and the locking components 120 of the two UAV landing gear locking mechanisms 100 are arranged relative to each other. The two UAV landing gear locking mechanisms 100 are used to respectively realize the locking and unlocking of the two landing gears of the UAV 200, thereby realizing the locking and unlocking of the UAV 200.

[0071] Furthermore, in the locking group, the locking platform 110 of at least one UAV landing gear locking mechanism 100 slides with the fixed platform to adjust the spacing between the two UAV landing gear locking mechanisms 100, thereby achieving the fixation of UAV landing gears of different specifications. In other embodiments, two UAV landing gear locking mechanisms 100 can also slide with the fixed platform to adjust the spacing between the two UAV landing gear locking mechanisms 100.

[0072] In one embodiment of the present invention, the drone fixing device also includes a transport body, and the fixing platform is arranged on the transport body. The support body 220 is locked by the locking component 120, and the clamping part 121 on the locking component 120 positions the support member to improve the stability of the drone 200.

[0073] It should be noted that existing drone-mounted tools experience significant vibration when traveling in uneven terrain, such as mountainous terrain, resulting in unstable clamping and causing the drone 200 to slip and be damaged. However, this embodiment utilizes locking member 120 to stably lock the drone 200, thereby preventing the drone 200 from slipping and being damaged. This facilitates the transportation of larger drones 200 in complex terrain, making the transfer and deployment of drones 200 more flexible and safer.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A UAV landing gear locking mechanism, characterized in that: The landing gear includes a support body and a support rod connected to the support body, and the locking mechanism includes: Locking the platform; A locking component movably connected to the locking platform; the locking component has a clamping portion; A driving member is provided on the locking platform, and is used to drive the locking member to switch between a locked position and an unlocked position; in the locked position, the locking member locks the support body, and the support rod is clamped to the clamping portion; in the unlocked position, the locking member releases the lock on the support body.

2. The UAV landing gear locking mechanism according to claim 1, characterized in that: The locking platform is provided with a rotating shaft, the locking component is connected to the rotating shaft; the output of the driving member is connected to the rotating shaft.

3. The UAV landing gear locking mechanism according to claim 2, characterized in that: The rotating shaft is sleeved with a first connecting member, which has an extension portion extending outward, and the output of the driving member is rotationally connected to an end of the extension portion away from the center of the rotating shaft.

4. The UAV landing gear locking mechanism according to any one of claims 1 to 3, characterized in that: The locking component comprises: a second connecting member, movably connected to the first side of the locking platform; a locking member connected to the second connecting member; In the locked position, at least a portion of the locking member extends to the second side of the locking platform, and a locking cavity for accommodating the support body is formed between at least a portion of the locking member and the locking platform; In the unlocked position, at least a portion of the locking member is retracted to a first side of the locking platform.

5. The UAV landing gear locking mechanism according to claim 4, characterized in that: The locking member includes a first locking pressure plate and a second locking pressure plate connected to each other, the first locking pressure plate is connected to the second connecting member, and a first preset angle is formed between the first locking pressure plate and the second locking pressure plate; In the locking position, both the first locking pressure plate and the second locking pressure plate abut against the support body.

6. The UAV landing gear locking mechanism according to claim 5, characterized in that: The clamping portion is arranged on a side of the second locking plate away from the first locking plate.

7. The UAV landing gear locking mechanism according to claim 6, characterized in that: The clamping portion includes a first limiting surface and a second limiting surface; In the locking position, both the first limiting surface and the second limiting surface abut against the support rod.

8. The UAV landing gear locking mechanism according to claim 7, characterized in that: A second preset angle is defined between the first limiting surface and the second limiting surface.

9. A drone fixing device, characterized in that: It comprises the UAV landing gear locking mechanism as described in any one of claims 1 to 8.

10. The drone fixing device according to claim 9, characterized in that: It also includes a fixed platform, on which two relatively arranged UAV landing gear locking mechanisms are provided, and the locking platform of at least one UAV landing gear locking mechanism is slidably matched with the fixed platform.

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