Small unmanned aerial vehicle undercarriage
By designing a small drone landing gear with elastic force and damping force, the bounce problem during landing in the existing technology is solved, and the landing gear is closed, improving flight safety and stability.
Patent Information
- Application Number
- CN202411863855.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-18
- Publication Date
- 2025-04-25
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The existing drone landing gear bounces due to lack of damping force during landing, which affects flight safety and cannot be retracted to increase air resistance, affecting flight stability and handling accuracy.
A small drone landing gear is designed, including two support arms, a telescopic mechanism, a support mechanism and a buffer assembly. The landing gear not only has elastic force but also has appropriate damping force. The design of the buffer assembly effectively suppresses the bounce phenomenon during landing, and can be retracted to reduce air resistance.
It effectively suppresses the bounce phenomenon during landing of the drone, ensures flight safety, and reduces air resistance by squeezing the landing gear, improving flight stability and handling accuracy.
Smart Images
Figure CN119872870A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a small-sized unmanned aerial vehicle landing gear. Background Art
[0002] In today's era, small vertical take-off and landing drones have shown great application value in many fields with their unique advantages, especially in aerial photography, agriculture, surveying and mapping, etc., and have become a powerful assistant to promote the development of various industries. As a crucial component of the drone's take-off and landing stage, the landing gear has the key mission of absorbing and releasing the impact energy from the ground. The quality of its performance is directly related to the safety and stability of the drone. In view of this, in order to effectively protect the body and the precision equipment inside the body from damage, most drones are now equipped with specially designed landing gear.
[0003] At present, most of the existing UAV landing gears use flat springs to achieve the buffering function. Flat springs have the remarkable characteristics of simple structure, low cost and no need for complicated maintenance, which to a certain extent meet the basic needs of UAV landing gears, and thus have been widely used in the market. However, this traditional flat spring buffering method has defects that cannot be ignored. Since the flat spring can only provide a single elastic force and lacks effective damping force to suppress excessive energy release, the UAV often bounces at the moment of landing due to insufficient energy dissipation. Once this bounce occurs, the UAV is very likely to deviate from the predetermined runway, or even roll over in an unstable state, which undoubtedly poses a major threat to the flight safety of the UAV.
[0004] In addition, there is a common problem in the design of existing drone landing gear, that is, it is usually impossible to fold it up. When the drone is flying in the air, the landing gear that cannot be folded up will significantly increase the drone's air resistance, making it more susceptible to interference and influence of airflow. This will not only reduce the flight efficiency of the drone and increase energy consumption, but also affect the flight stability and control accuracy of the drone to a certain extent, limiting the performance of the drone in complex weather conditions and high-demand flight missions. Summary of the invention
[0005] The present application aims to solve one of the technical problems in the related art at least to some extent.
[0006] To this end, one purpose of the present application is to provide a small UAV landing gear, which not only has elastic force but also has appropriate damping force, which can effectively suppress the bouncing phenomenon when the UAV lands, and at the same time can retract the landing gear, greatly reducing air resistance and effectively ensuring the stability of the UAV flight.
[0007] To achieve the above-mentioned purpose, the first aspect embodiment of the present application proposes a small UAV landing gear, comprising two support arms, a retractable mechanism, a support mechanism and a buffer assembly, wherein the two support arms are arranged side by side below the UAV bracket, and one end of the support arm is pivotally connected to the UAV bracket, and a hinge ear is provided on the bottom beam of the support arm near the other end of the support arm; the retractable mechanism is located above the two support arms, and one end of the retractable mechanism is pivotally connected to the UAV bracket, and the other end of the retractable mechanism is pivotally connected to the hinge ears on the two support arms through a rotating shaft; the support mechanism is pivotally connected to the other ends of the two support arms; the buffer assembly is close to the support mechanism and fixedly arranged between the two support arms, and the buffer assembly is connected to the support mechanism.
[0008] The small UAV landing gear of the embodiment of the present application not only has elastic force but also has appropriate damping force, which can effectively suppress the bouncing phenomenon when the UAV lands. At the same time, the landing gear can be retracted, which greatly reduces air resistance and effectively ensures the stability of the UAV flight.
[0009] In addition, the small UAV landing gear proposed in the present application may also have the following additional technical features:
[0010] In one embodiment of the present application, the supporting mechanism includes a triangular box, a first piston, a first guide rod and a base, wherein the top end of the triangular box is pivotally connected to the other end of the two supporting arms through a rotating shaft, and the triangular box is filled with oil; the first piston is movably arranged in the triangular box; the first guide rod is vertically fixed on the bottom wall of the first piston, and the bottom end of the first guide rod passes through the triangular box and is fixedly connected to the base.
[0011] In one embodiment of the present application, a rubber pad with anti-slip patterns is provided on the bottom wall of the base.
[0012] In one embodiment of the present application, the buffer assembly includes a box body, a partition, a second piston, a second guide rod, a baffle, a spring and a bellows, wherein the box body is fixedly arranged between the two support arms; the partition is arranged in the box body, wherein the partition separates the box body into a first chamber and a second chamber, and a plurality of groups of side-by-side through holes are provided on the partition; the second piston is movably arranged in the second chamber; one end of the second guide rod is fixedly connected to the second piston, and the other end of the second guide rod passes through the box body and is fixedly connected to the baffle; the spring is sleeved on the second guide rod, and one end of the spring is fixedly connected to the second piston, and the other end of the spring is fixedly connected to the end wall of the second chamber; one end of the bellows is connected to the triangular box, and the other end of the bellows is connected to the first chamber.
[0013] In one embodiment of the present application, the through hole is a tapered hole, and the diameter of the tapered hole gradually decreases from the first chamber to the second chamber.
[0014] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:
[0016] Figure 1 The structure of the landing gear of a small UAV according to one embodiment of the present application is shown in FIG. Figure 1 ;
[0017] Figure 2 The structure of the landing gear of a small UAV according to one embodiment of the present application is shown in FIG. Figure 2 ;
[0018] Figure 3 The structure of the landing gear of a small UAV according to one embodiment of the present application is shown in FIG. Figure 3 ;
[0019] Figure 4 It is a cross-sectional view of a small UAV landing gear according to one embodiment of the present application.
[0020] As shown in the figure: 10, support arm; 11, drone bracket; 12, hinge ear; 20, retractable mechanism; 30, support mechanism; 31, triangular box; 32, first piston; 33, first guide rod; 34, base; 301, rubber pad; 40, buffer assembly; 41, box body; 42, partition; 43, second piston; 44, second guide rod; 45, baffle; 46, spring; 47, bellows; 401, first chamber; 402, second chamber; 403, through hole. DETAILED DESCRIPTION
[0021] Embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.
[0022] The small UAV landing gear of the embodiment of the present application is described below with reference to the accompanying drawings.
[0023] like Figure 1-Figure 4As shown, the small UAV landing gear of the embodiment of the present application may include two support arms 10, a retractable mechanism 20, a support mechanism 30 and a buffer assembly 40.
[0024] Among them, the two support arms 10 are arranged side by side below the drone bracket 11, and one end of the support arm 10 is pivotally connected to the drone bracket 11, and a hinge ear 12 is provided on the bottom beam of the support arm 10 near the other end of the support arm 10.
[0025] The retractable mechanism 20 is located above the two support arms 10 , and one end of the retractable mechanism 20 is pivotally connected to the drone bracket 11 , and the other end of the retractable mechanism 20 is pivotally connected to the hinge ears 12 on the two support arms 10 through a rotating shaft.
[0026] It should be noted that the retractable mechanism 20 described in this embodiment may be an electric retractable rod.
[0027] The support mechanism 30 is pivotally connected to the other ends of the two support arms 10 . The buffer assembly 40 is close to the support mechanism 30 and fixedly disposed between the two support arms 10 . The buffer assembly 40 is connected to the support mechanism 30 .
[0028] Specifically, when the drone needs to land, the relevant control personnel can control the output end of the retractable mechanism 20 to extend and push the two support arms 10 to drive the support mechanism 30 and the buffer assembly 40 to flip downward, so that the two support arms 10 are unfolded (that is, the support arms are changed from a state nearly parallel to the drone bracket 11 to a state nearly vertical).
[0029] When the drone lands, the support mechanism 30 will be impacted, causing the drone body to descend to a certain extent to buffer the impact force from the ground, and the buffering force buffered by the support mechanism 30 is transmitted to the buffer component 40, and is absorbed and buffered by the buffer component 40. After the drone lands, the buffer component 40 transfers part of the absorbed impact energy to the support mechanism 30, so that the drone body gradually rises to a stable height after descending. This can effectively suppress the bouncing phenomenon of the drone when it lands.
[0030] When the UAV takes off, in order to reduce air resistance and ensure the stability of the UAV flight, the operator can control the output end of the retractable mechanism 20 to retract, and pull the two support arms 10 to drive the support mechanism 30 and the buffer assembly 40 to rotate and reset.
[0031] In one embodiment of the present application, Figure 1-Figure 4 As shown, the supporting mechanism 30 may include a triangular box 31 , a first piston 32 , a first guide rod 33 and a base 34 .
[0032] The top end of the triangular box 31 is pivotally connected to the other ends of the two support arms 10 via a rotating shaft, and the triangular box 31 is filled with oil.
[0033] The first piston 32 is movably disposed in the triangular box 31 , and the first guide rod 33 is vertically fixedly disposed on the bottom wall of the first piston 32 , and the bottom end of the first guide rod 33 passes through the triangular box 31 and is fixedly connected to the base 34 .
[0034] It is understandable that the base 34 can adapt to uneven ground by pivotally connecting the top of the triangular box 31 to the other ends of the two support arms 10. That is, when the drone lands, the base 34 contacts the uneven ground (for example, inclined ground), and the base 34 can drive the triangular box 31 to deflect through the first guide rod 33 to adapt to the uneven ground.
[0035] In the embodiment of the present application, a rubber pad 301 with anti-slip grooves is provided on the bottom wall of the base 34 .
[0036] It is understandable that by providing the rubber pad 301 with anti-skid patterns, not only can a certain buffering effect be provided for the landing of the drone, but also the friction with the ground can be increased, thereby improving the stability of the drone during landing.
[0037] Further, in one embodiment of the present application, Figure 3 and Figure 4 As shown, the buffer assembly 40 may include a housing 41 , a partition 42 , a second piston 43 , a second guide rod 44 , a baffle 45 , a spring 46 and a bellows 47 .
[0038] The box body 41 is fixedly disposed between the two support arms 10, and the partition 42 is disposed in the box body 41, wherein the partition 42 separates the box body 41 into a first chamber 401 and a second chamber 402, and a plurality of groups of through holes 403 arranged side by side are provided on the partition 42. For example, the plurality of groups of through holes 403 may be 2, 3, 4, 5, 6 groups of through holes 403, etc., and each group of through holes 403 may include 4, 5, 6, 7, 8 through holes 403, etc., and the specific number of through holes 403 may be selected according to actual conditions, and is not limited here.
[0039] The second piston 43 is movably disposed in the second chamber 402 . One end of the second guide rod 44 is fixedly connected to the second piston 43 . The other end of the second guide rod 44 passes through the box body 41 and is fixedly connected to the baffle 45 .
[0040] The spring 46 is sleeved on the second guide rod 44 , and one end of the spring 46 is fixedly connected to the second piston 43 , and the other end of the spring 46 is fixedly connected to the end wall of the second chamber 402 .
[0041] One end of the bellows 47 is communicated with the triangular box 31 , and the other end of the bellows 47 is communicated with the first chamber 401 .
[0042] In order to clearly explain the above embodiment, in one embodiment of the present application, as Figure 4 As shown, the through hole 403 may be a tapered hole, and the diameter of the tapered hole gradually decreases from the first chamber 401 to the second chamber 402 .
[0043] It can be understood that by gradually decreasing the diameter of the tapered hole from the first chamber 401 to the second chamber 402, when the oil enters the second chamber 402 through the first chamber 401, the flow rate of the oil will be accelerated, thereby increasing the thrust and pushing the second piston 43 to compress the spring 46. On the contrary, when the oil flows back from the second chamber 402 to the first chamber 401, the flow rate will be slowed down, and the thrust will be reduced, so that the bouncing phenomenon of the drone during landing can be effectively suppressed.
[0044] Specifically, when the drone needs to land, the relevant control personnel can control the output end of the retractable mechanism 20 to extend and push the two support arms 10 to drive the support mechanism 30 and the buffer assembly 40 to flip downward, so that the two support arms 10 are unfolded.
[0045] When the drone lands, the base 34 contacts the ground and absorbs the impact force from the ground. At this time, the base 34 pushes the first piston 32 upward through the first guide rod 33 (that is, it is equivalent to the drone body descending). The upward first piston 32 pushes the oil in the triangular box 31 through the bellows 47 into the first chamber 401.
[0046] At this time, the oil entering the first chamber 401 flows into the second chamber 402 through multiple groups of parallel through holes 403 on the partition 42 and pushes the second piston 43 to move. The moving second piston 43 pushes the second guide rod 44 to move and compress the spring 46, and the deformation of the spring 46 buffers the impact potential energy generated when the drone lands.
[0047] When the drone lands on the ground, the second piston 43 moves back under the elastic potential energy of the spring 46. The moving second piston 43 pushes the oil in the second chamber 402 to gradually flow back to the first chamber 401 through multiple groups of parallel through holes 403, and flows back to the triangular box 31 through the bellows 47, thereby pushing the drone body to gradually rise to a certain height until the drone body is stable.
[0048] In summary, the small UAV landing gear of the embodiment of the present application not only has elastic force but also has appropriate damping force, which can effectively suppress the bouncing phenomenon when the UAV lands. At the same time, the landing gear can be retracted, which greatly reduces air resistance and effectively ensures the stability of the UAV flight.
[0049] In the description of this specification, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.
[0050] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. 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 present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0051] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and deform the above embodiments within the scope of the present application.
Claims
1. A small UAV landing gear, characterized in that: It includes two support arms, a retractable mechanism, a support mechanism and a buffer assembly, wherein: The two support arms are arranged side by side below the drone bracket, and one end of the support arm is pivotally connected to the drone bracket, and a hinge ear is provided on the bottom beam of the support arm near the other end of the support arm; The retractable mechanism is located above the two support arms, and one end of the retractable mechanism is pivotally connected to the drone bracket, and the other end of the retractable mechanism is pivotally connected to the hinge ears on the two support arms through a rotating shaft; The support mechanism is pivotally connected to the other ends of the two support arms; The buffer component is close to the supporting mechanism and fixedly arranged between the two supporting arms, and the buffer component is connected to the supporting mechanism.
2. The small UAV landing gear according to claim 1, characterized in that: The support mechanism includes a triangular box, a first piston, a first guide rod and a base, wherein: The top end of the triangular box is pivotally connected to the other ends of the two support arms via a rotating shaft, and the triangular box is filled with oil; The first piston is movably disposed in the triangular box; The first guide rod is vertically fixed on the bottom wall of the first piston, and the bottom end of the first guide rod passes through the triangular box and is fixedly connected to the base.
3. The small UAV landing gear according to claim 2, characterized in that: A rubber pad with anti-skid patterns is arranged on the bottom wall of the base.
4. The small UAV landing gear according to claim 2, characterized in that: The buffer assembly includes a box body, a partition, a second piston, a second guide rod, a baffle, a spring and a bellows, wherein: The box body is fixedly arranged between the two support arms; The partition is arranged in the box body, wherein the partition separates the box body into a first chamber and a second chamber, and the partition is provided with a plurality of groups of through holes arranged side by side; The second piston is movably disposed in the second chamber; One end of the second guide rod is fixedly connected to the second piston, and the other end of the second guide rod passes through the box body and is fixedly connected to the baffle; The spring is sleeved on the second guide rod, one end of the spring is fixedly connected to the second piston, and the other end of the spring is fixedly connected to the end wall of the second chamber; One end of the bellows is communicated with the triangular box, and the other end of the bellows is communicated with the first chamber.
5. The small UAV landing gear according to claim 4, characterized in that: The through hole is a tapered hole, and the diameter of the tapered hole gradually decreases from the first chamber to the second chamber.