An unmanned aerial vehicle assisted landing device

Abstract

The utility model relates to an unmanned plane technical field especially relates to an unmanned plane landing aid device. Including cavity, a set of buffer mechanism, drive mechanism and control mechanism, wherein cavity is used for providing installation space for buffer mechanism and other components, a set of buffer mechanism is used for absorbing landing impact force, drive mechanism is used for driving a set of buffer mechanism to draw close or vertical corresponding cavity, makes it after landing and ground contact play the buffering effect, control mechanism controls a set of buffer mechanism to draw close or vertical corresponding cavity's action. The utility model drive mechanism can accurate control buffer mechanism to unfold and shrink, make elastic assembly draw close cavity, reduce the interference of buffer structure to airflow, guarantee unmanned plane flight stability, when unmanned plane prepares to land, drive mechanism rapidly drives elastic assembly vertical corresponding cavity, lets buffer mechanism play the buffering effect, reduces landing impact force, protects unmanned plane main body, prolongs its life.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV landing aid device. Background Technology

[0002] A drone landing aid is a crucial device used to assist drones in landing safely. With the increasing prevalence of drones, ensuring a smooth and accurate landing is paramount. This drone landing aid effectively addresses landing requirements in various terrains and environments, providing reliable support and cushioning for the drone, thereby significantly improving the safety and stability of the landing.

[0003] For example, CN214165320U discloses a visual recognition-based drone landing aid device, including a shell with flanges around its perimeter and evenly distributed threaded holes on its upper surface; it also includes an outer cover with a flange welded to its upper side, which matches the lower flange of the shell. The flange and shell are connected by a screw, forming a first receiving cavity between them. A partition is welded near the upper part of the first receiving cavity, and a microcontroller is bolted to the lower part of the partition. The outer cover is a hollow hemisphere, forming a second receiving cavity with the flange, and a camera is bolted to the second receiving cavity. A shock-absorbing spring is sleeved on the screw, and a shock-absorbing pad is fixed to the lower end of the screw. This utility model effectively protects the safety of drones during takeoff and landing by setting a buffer pad; at the same time, it can be connected to various models of drones, improving the applicability of this utility model.

[0004] In summary, the existing technology suffers from the following technical problems: because the buffer structure lacks contraction capability, it causes airflow interference to the drone's flight. Especially during takeoff and low-altitude flight, this airflow interference may disrupt the drone's flight stability, making it difficult for the drone to maintain its intended flight attitude and trajectory. Therefore, we propose a drone landing aid device. Utility Model Content

[0005] The purpose of this invention is to provide a drone landing aid device to solve the technical problem mentioned in the background art, which is that the lack of contraction capacity of the buffer structure causes airflow interference to the drone flight, thereby affecting the flight stability.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0007] A drone landing aid includes a cavity fixed to the bottom of the drone body, and further includes:

[0008] A set of buffer mechanisms, each comprising a housing rotatably connected to the cavity via a first connecting seat, and an elastic component connected to the housing and whose bottom end is retractable into the housing when compressed;

[0009] The driving mechanism includes a transmission part fixed within the cavity, and a traction part connected between the housing and the transmission part in a set of buffer mechanisms. The transmission part is used to drive the elastic component to move closer to or perpendicularly correspond to the cavity via the traction part.

[0010] The control mechanism includes a rangefinder for detecting the distance between the upper cavity of the UAV and the ground, and triggering the transmission unit when the measured distance is a specified threshold.

[0011] As a preferred embodiment of the UAV landing aid device provided by this utility model, the control mechanism further includes a bracket for mounting a rangefinder and fixing it in the cavity, and a control module integrated in the cavity that can start and stop the transmission component according to the rangefinder's ranging information.

[0012] The rangefinder measures the distance between the cavity on the UAV and the ground based on laser, ultrasonic, and / or visual ranging.

[0013] As a preferred embodiment of the UAV landing aid device provided by this utility model, the transmission part includes a base fixed to the cavity, a screw rotatably connected to the base and having two oppositely helical threaded sections, a set of slides respectively threaded to the two threaded sections of the screw, and a motor for moving the set of slides in opposite directions on the base by driving the screw.

[0014] Each of the aforementioned traction components includes multiple first connecting rods, one end of which is rotatably connected to the outer shell of the buffer mechanism, and connecting plates fixed on the slide block and rotatably connected to the other end of the multiple first connecting rods;

[0015] Multiple first links work together to change the angle of the housing on the cavity under the action of the connecting plate, so that the elastic components inside the housing are brought closer to or perpendicular to the cavity.

[0016] As a preferred embodiment of the UAV landing aid device provided by this utility model, the driving mechanism further includes a set of guide parts that allow the auxiliary connecting plate to move linearly by the drive of the slide block;

[0017] Each of the guide portions includes a sliding shaft fixed within the cavity along the width direction of the cavity, and a set of sliding sleeves all sleeved outside the sliding shaft and respectively fixed to the connecting plate in the set of driving portions.

[0018] As a preferred embodiment of the UAV landing aid device provided by this utility model, the elastic component includes a foot plate for contacting the ground, a set of connecting rods arranged in opposite directions between the foot plate and the housing, and a buffer connected between the set of connecting rods and capable of restoring the distance between the foot plate and the top of the housing to the initial distance.

[0019] As a preferred embodiment of the UAV landing aid device provided by this utility model, each of the group of connecting rods includes a second connecting seat, a second connecting rod rotatably connected between the second connecting seat and the top of the housing, and a third connecting rod rotatably connected between the second connecting seat and the foot plate.

[0020] The buffer includes a tension spring or gas spring connected between second connecting seats in a set of the linkages.

[0021] It is clear without a doubt that the technical solution described above in this application can solve the technical problem that this application aims to address.

[0022] At the same time, through the above technical solutions, this utility model has at least the following beneficial effects:

[0023] This utility model provides a drone landing aid device that uses a drive mechanism to precisely control the deployment and retraction of a buffer mechanism. During takeoff and low-altitude flight, the drive mechanism can bring the elastic component closer to the cavity, greatly reducing the interference of the buffer structure on airflow, ensuring the stability of the drone's flight, and enabling it to better maintain its predetermined flight attitude and trajectory. When the drone is preparing to land, the drive mechanism can quickly move the elastic component vertically to the cavity, allowing the buffer mechanism to fully exert its buffering effect, reducing the impact force during drone landing, effectively protecting the drone body, and extending its service life.

[0024] This utility model provides a drone landing aid device that can accurately measure the distance between the drone's upper cavity and the ground through a control mechanism. When the distance reaches a specified threshold, the transmission part is immediately triggered, thereby realizing the automatic and timely response of the buffer mechanism, improving the safety and reliability of drone landing, and reducing errors and delays caused by manual operation. Attached Figure Description

[0025] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1This is a schematic diagram of the structure of a drone landing aid device in its retracted state according to the present invention;

[0027] Figure 2 This is a schematic diagram of the structure of a drone landing aid device in its working state according to this utility model;

[0028] Figure 3 This is a schematic diagram of the control mechanism of a drone landing aid device according to the present invention;

[0029] Figure 4 This is a schematic diagram of the drive mechanism of a drone landing aid device according to the present invention;

[0030] Figure 5 This is a schematic diagram of the buffer mechanism of a drone landing aid device according to the present invention.

[0031] In the diagram: 1. Cavity; 2. Buffer mechanism; 21. First connecting seat; 22. Outer shell; 3. Elastic component; 31. Foot plate; 32. Linkage member; 321. Second connecting seat; 322. Second link; 323. Third link; 33. Buffer; 4. Drive mechanism; 41. Transmission part; 411. Base; 412. Screw; 413. Slide; 414. Motor; 42. Driving part; 421. First link; 422. Connecting plate; 43. Guide part; 431. Sliding shaft; 432. Sliding sleeve; 5. Control mechanism; 51. Rangefinder; 52. Bracket. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0033] like Figure 1 As shown, this type of UAV landing aid includes a cavity 1, a set of buffer mechanisms 2, a drive mechanism 4, and a control mechanism 5. The cavity 1 serves as the basic load-bearing part of the entire device, providing a stable installation space for components such as the buffer mechanisms 2. The set of buffer mechanisms 2 is used to ensure that the UAV can accurately contact the ground when it lands, effectively absorbing the impact force during landing through its own structure, achieving a good buffering effect, and ensuring the stability of the UAV landing process.

[0034] Drive mechanism 4 drives a set of buffer mechanisms 2 to operate according to different flight stages and needs. For example, during the flight of the UAV, when the buffer mechanisms 2 do not need to work, drive mechanism 4 can bring a set of buffer mechanisms 2 closer to the cavity 1 to minimize the drag on the UAV's flight and ensure the flexibility and efficiency of the UAV's flight; while when the buffer mechanisms 2 are needed for buffer landing, drive mechanism 4 can drive a set of buffer mechanisms 2 to be perpendicular to the cavity 1, so that it can accurately contact the ground after landing and play a buffering role.

[0035] The control mechanism 5 is used to detect the distance between the cavity 1 on the UAV and the ground in real time. When the measured distance reaches a specified threshold, the control mechanism 5 can quickly and accurately trigger the corresponding command to control a set of buffer mechanisms 2 to perform actions that move closer to the cavity 1 or are perpendicular to the cavity 1, ensuring the safety and reliability of the entire landing process.

[0036] like Figure 2 As shown, a set of buffer mechanisms 2 are respectively arranged in opposite directions in the cavity 1, and each further includes a first connecting seat 21, a shell 22 and an elastic component 3; specifically, the first connecting seat 21 serves as the connection hub between the buffer mechanism 2 and the cavity 1, which can ensure that the shell 22 rotates stably in the cavity 1, while bearing forces from all directions; the shell 22 is made of high-strength material, which not only has sufficient rigidity to support the elastic component 3, but also maintains structural integrity when subjected to impact, effectively preventing damage to the internal elastic component 3;

[0037] As the core component of the buffer mechanism 2, the elastic component 3 has an elastic retraction mechanism at its bottom (see below for details). When the drone lands and generates an impact force, the structure can respond quickly and convert the impact force into elastic potential energy, effectively slowing down the drone's landing speed and thus achieving a good buffering effect.

[0038] The drive mechanism 4 further includes a transmission part 41 and a traction part 42. Specifically, the transmission part 41 is located in the center of the cavity 1 to stably output power and drive the traction part 42 to move. The traction part 42 serves as a connecting bridge between the transmission part 41 and the outer shell 22 in the buffer mechanism 2. When the drive mechanism 4 receives a trigger command from the control mechanism 5, the transmission part 41 will start immediately and drive the elastic component 3 in the outer shell 22 to move closer to the cavity 1 or perpendicular to the cavity 1 through the traction part 42. When the elastic component 3 in the outer shell 22 is perpendicular to the cavity 1, the safe landing of the UAV can be achieved.

[0039] like Figure 3 As shown, and refer to Figure 1 or Figure 2The control mechanism 5 further includes a rangefinder 51, a bracket 52, and a control module; specifically, the bracket 52 is fixed inside the cavity 1 to provide a stable and reliable mounting base for the rangefinder 51, ensuring that the rangefinder 51 can accurately measure distances;

[0040] The control module has processing capabilities. By receiving distance information from the rangefinder 51 and comparing it with a preset threshold, the control module will quickly issue a command when the distance measured by the rangefinder 51 reaches the threshold, accurately start and stop the transmission unit 41, and then drive the elastic component 3 in the outer shell 22 to vertically correspond to the cavity 1 through the traction unit 42, thereby achieving safe descent buffer.

[0041] In some embodiments, the rangefinder 51 can employ one or more combinations of various ranging technologies to adapt to different environmental conditions and usage requirements. For example, ultrasonic ranging is more reliable in environments with insufficient light or low visibility; while laser ranging is more advantageous in situations requiring high-precision measurement; and in specific scenarios, distance measurement through image recognition and analysis can achieve relatively accurate distance measurement for landing aid areas with obvious feature markings, and in complex environments, it can use preset visual models for assisted judgment, further improving the accuracy and adaptability of the measurement. By selecting or combining multiple ranging technologies, the UAV landing aid device can stably and reliably acquire distance information between the UAV and the ground in various complex environments, providing a solid data foundation for the subsequent control module to accurately control the transmission unit 41.

[0042] In some embodiments, such as Figure 4 As shown, the transmission unit 41 further includes a base 411, a screw 412, a set of slides 413, and a motor 414. Specifically, the base 411 is fixed in the cavity 1, providing a stable support foundation for the entire transmission unit 41. The screw 412, with its two sections of oppositely helical threads, enables the slides 413 to move in opposite directions. This design utilizes the rotational characteristics of the threads to convert the rotational motion of the motor 414 into the linear motion of the slides 413. Furthermore, the two slides 413 can move in opposite directions simultaneously, thereby achieving a highly efficient and precise transmission effect.

[0043] A set of slides 413 are threadedly connected to the two threaded sections of the screw 412. They move as the screw 412 rotates. This connection method ensures the stability and accuracy of the movement of the slides 413. The motor 414 serves as a power source. By driving the screw 412 to rotate, it drives a set of slides 413 to move in opposite directions on the base 411, realizing the overall function of the transmission unit 41 and providing reliable power support for the UAV landing aid device.

[0044] Each set of traction parts 42 further includes multiple first connecting rods 421 and connecting plates 422; specifically, the multiple first connecting rods 421 are evenly distributed, and one end of them is rotatably connected to the outer shell 22 in the buffer mechanism 2 through a rotating shaft. This rotatable connection method allows the first connecting rods 421 to rotate flexibly within a certain angle range to adapt to the changing angle requirements of the outer shell 22.

[0045] The connecting plate 422 is fixed on the slide block 413. When the slide block 413 moves under the drive of the screw 412, the connecting plate 422 moves synchronously. The connecting plate 422 is provided with a rotating connection structure that matches the other ends of the multiple first connecting rods 421, enabling a reliable rotating connection between the other ends of the multiple first connecting rods 421 and the connecting plate 422. During the movement of the connecting plate 422 with the slide block 413, the multiple first connecting rods 421, driven by the connecting plate 422, change the position of the outer shell 22 within the cavity. At angle 1, when the elastic component 3 needs to be close to the cavity 1, the slide 413 drives the connecting plate 422 to move, causing multiple first connecting rods 421 to pull the outer shell 22 to rotate towards the cavity 1, thereby bringing the elastic component 3 closer together; when the elastic component 3 needs to be perpendicular to the cavity 1, the slide 413 moves in the opposite direction, driving the connecting plate 422 to cause multiple first connecting rods 421 to push the outer shell 22 to rotate to a vertical position, ensuring that the elastic component 3 can be perpendicular to the cavity 1, so as to meet the buffer landing assistance of the UAV.

[0046] In some embodiments, the drive mechanism 4 further includes a set of guide portions 43 that allow the auxiliary connecting plate 422 to move linearly via the slide block 413; each set of guide portions 43 further includes a sliding shaft 431 and a set of sliding sleeves 432; specifically, the sliding shaft 431 is fixed inside the cavity 1 and arranged along its width direction, providing a stable guiding effect for the linear movement of the connecting plate 422; and the set of sliding sleeves 432 are respectively sleeved on the corresponding sliding shaft 431 and fixedly connected to the connecting plate 422, ensuring that the connecting plate 422 can move accurately along the direction of the sliding shaft 431 during the movement, without any deviation or shaking, thereby ensuring the stability and reliability of the entire drive mechanism 4, enabling the UAV landing aid device to more accurately achieve the buffer landing function.

[0047] In some embodiments, such as Figure 5 As shown, the elastic component 3 further includes a foot plate 31, a set of connecting rods 32 and a buffer 33; specifically, the foot plate 31 is made of a high-strength, wear-resistant and elastic material, and its bottom is provided with anti-slip texture, which can provide sufficient friction when in contact with the ground to prevent the UAV from sliding during the landing process, while its elastic properties can initially buffer some of the impact force.

[0048] A set of connecting rods 32 are arranged in opposite directions inside the outer shell 22 and between the foot plate 31. They can deform when subjected to landing impact force. The arrangement in opposite directions can evenly distribute the impact force from the ground and avoid damage caused by excessive local stress.

[0049] The buffer 33 is connected between a set of linkages 32. When the impact force generated by the drone landing causes the set of linkages 32 to deform, the buffer 33 can play its role, absorbing and dissipating the impact energy through its own elastic deformation, thereby restoring the distance between the foot plate 31 and the top of the inner shell 22 to the initial distance, ensuring that the elastic component 3 can return to a stable state after each impact, so as to prepare for the next landing assistance.

[0050] Continue as Figure 5 As shown, each of the connecting rods 32 includes a second connecting seat 321, a second connecting rod 322, and a third connecting rod 323; specifically, the second connecting seat 321 serves as the core connecting component of the connecting rod 32, and is used to ensure the stable rotation of the second connecting rod 322 and the third connecting rod 323;

[0051] The second link 322 is rotatably connected between the second connecting seat 321 and the top of the outer shell 22. Its rotational design allows for flexible adjustment based on the direction and magnitude of the impact force during the drone's descent, effectively dispersing the impact force. The third link 323 is rotatably connected between the second connecting seat 321 and the foot plate 31. It also has the characteristic of flexible rotation and works in conjunction with the second link 322 to form a stable structure of a set of link members 32, ensuring that the force can be evenly transmitted and deformed when subjected to impact.

[0052] In some embodiments, the buffer 33 is a tension spring (as shown in the figure) or a gas spring connected between the second connecting seats 321 in a set of connecting rods 32. For example, when it is a tension spring, it can absorb energy through its own tensile deformation when subjected to the impact force transmitted by the second connecting seat 321, and can rely on elastic restoring force to restore the connecting rods 32 as a whole to their initial shape after the impact force disappears. When it is a gas spring, it can more accurately control the movement speed and buffering force of the connecting rods 32, providing a more stable and reliable landing assistance effect for the drone. In practical applications, the appropriate type of buffer 33 can be flexibly selected according to factors such as the specific model, weight, and usage environment of the drone to achieve the best landing assistance performance.

[0053] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the present utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the present utility model, thereby enabling those skilled in the art to better understand and utilize it. The present utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A drone landing aid device, comprising a cavity (1) fixed to the bottom of the drone body, characterized in that, Also includes: A set of buffer mechanisms (2) each includes a housing (22) rotatably connected to the cavity (1) via a first connecting seat (21), and an elastic component (3) connected to the housing (22) and whose bottom end can retract into the housing (22) when pressed; The drive mechanism (4) includes a transmission part (41) fixed inside the cavity (1) and a pulling part (42) connected between the housing (22) and the transmission part (41) in a set of buffer mechanisms (2). The transmission part (41) is used to drive the elastic component (3) to move closer to the cavity (1) or perpendicularly to the cavity (1) via the pulling part (42); and The control mechanism (5) includes a rangefinder (51) for detecting the distance between the upper cavity (1) of the UAV and the ground, and triggering the transmission unit (41) when the measured distance is a specified threshold.

2. The UAV landing aid device according to claim 1, characterized in that, The control mechanism (5) also includes a bracket (52) for mounting the rangefinder (51) and fixing it in the cavity (1), and a control module integrated in the cavity (1) that can start and stop the transmission unit (41) according to the distance measurement information of the rangefinder (51); The rangefinder (51) measures the distance between the cavity (1) on the UAV and the ground based on laser, ultrasonic and / or visual ranging.

3. The UAV landing aid device according to claim 1, characterized in that, The transmission unit (41) includes a base (411) fixed to the cavity (1), a screw (412) rotatably connected to the base (411) and having two oppositely helical threaded sections, a set of slides (413) respectively threaded to the two threaded sections of the screw (412), and a motor (414) for moving the set of slides (413) in opposite directions on the base (411) by driving the screw (412). Each of the aforementioned traction parts (42) includes multiple first connecting rods (421) with one end rotatably connected to the outer shell (22) in the buffer mechanism (2), and connecting plates (422) fixed on the slide (413) and rotatably connected to the other end of the multiple first connecting rods (421). Multiple first links (421) are used together to change the angle of the housing (22) on the cavity (1) under the action of the connecting plate (422), so that the elastic component (3) inside the housing (22) is close to or perpendicular to the cavity (1).

4. The UAV landing aid device according to claim 3, characterized in that, The drive mechanism (4) also includes a set of guide parts (43) for the auxiliary connecting plate (422) to move linearly by the slide (413). Each of the guide portions (43) includes a slide shaft (431) fixed in the cavity (1) along the width direction of the cavity (1), and a set of slide sleeves (432) all sleeved outside the slide shaft (431) and fixed to the connecting plate (422) in the set of driving portions (42).

5. The UAV landing aid device according to claim 1, characterized in that, The elastic component (3) includes a foot plate (31) for contacting the ground, a set of connecting rods (32) arranged in opposite directions between the foot plate (31) and the housing (22), and a buffer (33) connected between the set of connecting rods (32) and capable of restoring the distance between the foot plate (31) and the top of the housing (22) to the initial distance.

6. The UAV landing aid device according to claim 5, characterized in that, Each of the connecting rods (32) includes a second connecting seat (321), a second connecting rod (322) rotatably connected between the second connecting seat (321) and the top of the housing (22), and a third connecting rod (323) rotatably connected between the second connecting seat (321) and the foot plate (31). The buffer (33) includes a tension spring or gas spring connected between a second connecting seat (321) in a set of the connecting rods (32).

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