Sma based unmanned aerial vehicle vibration damping landing gear

Abstract

The present disclosure provides a kind of unmanned aerial vehicle damping landing gear based on SMA, it is related to damping technical field, wherein the unmanned aerial vehicle damping landing gear includes: base;Multiple damping devices, damping device includes: first cylinder, damping rod, first elastic component, second elastic component and at least one SMA component, one end of SMA component is connected with the force end of first elastic component, and the end of SMA component away from first elastic component is connected with the force end of second elastic component.In the present disclosure, a kind of unmanned aerial vehicle damping landing gear based on SMA, SMA component cooperates first elastic component and second elastic component to be able to provide greater elastic force and damping force, to effectively improve the energy consumption capacity of damping device, to guarantee the stable support of unmanned aerial vehicle damping landing gear, meet the safe landing demand of unmanned aerial vehicle.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of vibration reduction, in particular to a SMA-based unmanned aerial vehicle (UAV) vibration reduction landing gear. BACKGROUND

[0002] An unmanned aerial vehicle (UAV) is a pilotless aircraft that is controlled by radio remote control equipment and self-provided program control device. The UAV is widely used in aerial photography, agriculture, plant protection, disaster rescue and other fields. When the UAV lands, it will be subjected to strong reaction force from the ground, which seriously affects the landing safety of the UAV. Therefore, a vibration reduction device is generally installed on the UAV landing gear to ensure the take-off and landing safety of the UAV. However, the current vibration reduction device provides small elastic force and damping force, which leads to insufficient overall energy consumption capacity, resulting in low take-off and landing stability of the UAV, and cannot meet the use requirements. SUMMARY

[0003] The present disclosure aims to at least partially solve one of the technical problems in the related art.

[0004] To this end, the purpose of the present disclosure is to provide a SMA-based unmanned aerial vehicle (UAV) vibration reduction landing gear.

[0005] To achieve the above purpose, the present disclosure provides a SMA-based unmanned aerial vehicle (UAV) vibration reduction landing gear, comprising a base, a plurality of vibration reduction devices, each vibration reduction device comprising a first cylinder, a vibration reduction rod, a first elastic component, a second elastic component and at least one shape memory alloy (SMA) component, the vibration reduction rod being slidingly arranged in the first cylinder, the first elastic component being arranged on the base, and the first elastic component being connected to one end of the first cylinder, the force receiving end of the first elastic component being in abutment with one end of the vibration reduction rod, the second elastic component being arranged at an end of the first cylinder away from the first elastic component, and the force receiving end of the second elastic component being in abutment with an end of the vibration reduction rod away from the first elastic component, one end of the SMA component being connected to the force receiving end of the first elastic component, and the other end of the SMA component being connected to the force receiving end of the second elastic component, and a support plate connected to the vibration reduction rods of the plurality of vibration reduction devices.

[0006] Optionally, the first elastic assembly comprises: an end cover arranged on the base, and the end cover is connected to one end of the first cylinder body away from the second elastic assembly, and a first accommodating cavity is formed between the end cover and the first cylinder body; a baffle arranged in the first accommodating cavity, and the baffle is in abutment with one end of the first cylinder body away from the second elastic assembly; a spring arranged in the first accommodating cavity, and one end of the spring is in abutment with one side of the baffle away from the first cylinder body, and the other end of the spring away from the baffle is in abutment with one side of the end cover close to the first cylinder body; wherein one end of the damping rod away from the second elastic assembly is in abutment with one side of the baffle close to the first cylinder body, and one end of the SMA assembly away from the second elastic assembly is connected to the baffle.

[0007] Optionally, the first elastic assembly further comprises: a first ring plate sleeved on one end of the first cylinder body away from the second elastic assembly, and one side of the first ring plate away from the first cylinder body is in abutment with the baffle; and a second ring plate sleeved on one end of the end cover close to the first cylinder body, and the second ring plate is detachably connected to the first ring plate.

[0008] Optionally, the damping device further comprises: a second cylinder body detachably connected to the second ring plate, and the second cylinder body is sleeved on the first cylinder body, and a second accommodating cavity is formed between the second cylinder body and the first cylinder body, and the SMA assembly is located in the first accommodating cavity and the second accommodating cavity.

[0009] Optionally, a limiting hole is arranged on the baffle, and a limiting pin is arranged on one end of the damping rod away from the second elastic assembly, and the limiting pin is slidingly inserted into the limiting hole.

[0010] Optionally, the first elastic assembly and the second elastic assembly are structurally identical, and the first elastic assembly and the second elastic assembly are symmetrically arranged at two ends of the first cylinder body.

[0011] Optionally, the damping device further comprises: a connecting rod slidingly arranged on the end cover of the second elastic assembly, and one end of the connecting rod close to the first elastic assembly is connected to one end of the damping rod away from the first elastic assembly, and the other end of the connecting rod away from the first elastic assembly is connected to the support plate, and the spring of the second elastic assembly is sleeved on the connecting rod.

[0012] Optionally, a plurality of grooves are arranged on the base, and the end cover of the first elastic assembly is arranged in the groove.

[0013] Optionally, the SMA assembly comprises: a first adjusting rod, which is slidingly arranged at the force receiving end of the first elastic assembly; a first adjusting sleeve, which is arranged at the force receiving end of the first elastic assembly away from the second elastic assembly, and the first adjusting sleeve is threadedly connected with one end of the first adjusting rod away from the second elastic assembly; a second adjusting rod, which is slidingly arranged at the force receiving end of the second elastic assembly; a second adjusting sleeve, which is arranged at the force receiving end of the second elastic assembly away from the first elastic assembly, and the second adjusting sleeve is threadedly connected with one end of the second adjusting rod away from the first elastic assembly; and an SMA wire, one end of which is connected with one end of the first adjusting rod close to the second elastic assembly, and the other end of the SMA wire is connected with one end of the second adjusting rod close to the first elastic assembly.

[0014] Optionally, the unmanned aerial vehicle damping landing gear further comprises: a plurality of reinforcing rods, at least one of which is arranged between adjacent damping devices.

[0015] The technical solutions provided by the present disclosure can include the following beneficial effects:

[0016] The SMA assembly can provide a larger damping force in the process of stretching and rebounding, thereby consuming the vibration impact force on the damping rod and the rebound force of the first elastic assembly, the second elastic assembly and the SMA assembly itself, and then realizing damping of the damping device in cooperation with the first elastic assembly, the second elastic assembly and the SMA assembly. Due to the super-elasticity, high damping and high recovery force of the SMA assembly, and the fact that the SMA assembly can always be in a stretching cycle state in the process of reciprocating vibration of the damping rod, the SMA assembly can provide a larger elastic force and damping force in cooperation with the first elastic assembly and the second elastic assembly, thereby effectively improving the energy consumption capacity of the damping device, and further ensuring the stable support of the unmanned aerial vehicle damping landing gear, and meeting the safe landing requirements of the unmanned aerial vehicle.

[0017] Additional aspects and advantages of the present disclosure will be in part apparent and in part pointed out hereinafter. BRIEF DESCRIPTION OF DRAWINGS

[0018] The above and / or additional aspects and advantages of the present disclosure will become apparent and be readily appreciated from the following description, taken in conjunction with the accompanying drawings, in which:

[0019] Figure 1 is a cross-sectional view of an unmanned aerial vehicle damping landing gear based on SMA according to an embodiment of the present disclosure;

[0020] Figure 2is a sectional view of a damping device in a SMA-based unmanned aerial vehicle damping landing gear according to an embodiment of the present disclosure;

[0021] Figure 3 is a sectional view of a damping device in a SMA-based unmanned aerial vehicle damping landing gear according to an embodiment of the present disclosure (when the damping rod moves along the first elastic component to the second elastic component);

[0022] Figure 4 is a sectional view of a damping device in a SMA-based unmanned aerial vehicle damping landing gear according to an embodiment of the present disclosure (when the damping rod moves along the second elastic component to the first elastic component);

[0023] As shown in the figure: 1, base;

[0024] 2, damping device;

[0025] 21, first cylinder body;

[0026] 22, damping rod, 221, limiting pin;

[0027] 23, first elastic component, 231, end cover, 232, baffle, 233, spring, 234, first accommodating cavity, 235, first ring plate, 236, second ring plate;

[0028] 2321, limiting hole;

[0029] 24, second elastic component;

[0030] 25, SMA component, 251, first adjusting rod, 252, first adjusting sleeve, 253, second adjusting rod, 254, second adjusting sleeve, 255, SMA wire;

[0031] 26, second cylinder body, 27, second accommodating cavity, 28, connecting rod;

[0032] 3, support plate, 4, groove, 5, reinforcing rod. DETAILED DESCRIPTION

[0033] The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by reference to the accompanying drawings are exemplary and are only used to explain the present disclosure and cannot be understood as a limitation of the present disclosure. On the contrary, the embodiments of the present disclosure include all changes, modifications and equivalents falling within the spirit and scope of the appended claims.

[0034] As Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, the unmanned aerial vehicle damping landing gear based on the SMA (Shape-Memory-Alloys) is provided, which comprises a base 1, a plurality of damping devices 2 and a support plate 3. The damping device 2 comprises a first cylinder 21, a damping rod 22, a first elastic component 23, a second elastic component 24 and at least one SMA component 25. The damping rod 22 is slidingly arranged in the first cylinder 21. The first elastic component 23 is arranged on the base 1 and connected to one end of the first cylinder 21. The force receiving end of the first elastic component 23 abuts against one end of the damping rod 22. The second elastic component 24 is arranged at the end of the first cylinder 21 away from the first elastic component 23, and the force receiving end of the second elastic component 24 abuts against the end of the damping rod 22 away from the first elastic component 23. One end of the SMA component 25 is connected to the force receiving end of the first elastic component 23, and the end of the SMA component 25 away from the first elastic component 23 is connected to the force receiving end of the second elastic component 24. The support plate 3 is connected to the damping rods 22 of the plurality of damping devices 2.

[0035] It can be understood that when the damping rod 22 is subjected to a vibration impact force in the direction from the first elastic component 23 to the second elastic component 24, the first elastic component 23 is not stressed, and the second elastic component 24 is compressed, while the SMA component 25 is stretched, because the force receiving end of the first elastic component 23 abuts against one end of the damping rod 22, and the force receiving end of the second elastic component 24 abuts against the end of the damping rod 22 away from the first elastic component 23, and one end of the SMA component 25 is connected to the force receiving end of the first elastic component 23, and the end of the SMA component 25 away from the first elastic component 23 is connected to the force receiving end of the second elastic component 24. At this time, the damping rod 22 is buffered by the rebound force of the second elastic component 24 and the SMA component 25.

[0036] Moreover, when the damping rod 22 is subjected to a vibration impact force in the direction from the second elastic component 24 to the first elastic component 23, the second elastic component 24 is not stressed, and the first elastic component 23 is compressed, while the SMA component 25 is stretched, at this time, the damping rod 22 is buffered by the rebound force of the first elastic component 23 and the SMA component 25.

[0037] In the process of stretching and rebounding, the SMA component 25 can provide a larger damping force, thereby consuming the vibration impact force on the damping rod 22 and the rebound force of the first elastic component 23, the second elastic component 24 and the SMA component 25, and further realizing the damping of the damping device 2 through the cooperation of the first elastic component 23, the second elastic component 24 and the SMA component 25.

[0038] Due to the super-elasticity, high-damping and high-recovery force of the SMA component 25, and the fact that the SMA component 25 can always be in a tensile cycle state during the reciprocating vibration of the damping rod 22, the SMA component 25 in cooperation with the first elastic component 23 and the second elastic component 24 can provide greater elastic force and damping force, thereby effectively improving the energy dissipation capacity of the damping device 2, and further ensuring the stable support of the unmanned aerial vehicle damping landing gear, and meeting the safe landing requirements of the unmanned aerial vehicle.

[0039] It should be noted that the base 1 is used to carry a plurality of damping devices 2, and the specific type of the base 1 can be set according to actual needs, which is not limited.

[0040] The support plate 3 is used to connect a plurality of damping devices 2, so that the plurality of damping devices 2 can synchronously and stably damp the unmanned aerial vehicle damping landing gear.

[0041] The first cylinder 21 is used to guide the damping rod 22, and the specific type of the first cylinder 21 can be set according to actual needs, which is not limited. For example, the first cylinder 21 can be a cylindrical structure with both ends through, and the inner diameter of the first cylinder 21 is greater than the outer diameter of the damping rod 22.

[0042] The damping rod 22 is used to conduct vibration impact force, and the specific type of the damping rod 22 can be set according to actual needs, which is not limited. For example, the damping rod 22 can be a cylindrical rod structure.

[0043] The first elastic component 23 and the second elastic component 24 not only can buffer the vibration impact force on the damping rod 22, but also can help the recovery of the SMA component 25 by using its own elastic force. The specific type of the first elastic component 23 and the second elastic component 24 can be set according to actual needs, which is not limited.

[0044] The SMA component 25 is used to provide elastic force and damping force. The SMA component 25 is a component including a part made of SMA material. The specific type of the SMA component 25 can be set according to actual needs, which is not limited. The SMA material is a kind of metal material that can change its shape under the condition of changes in external temperature and other environmental factors, and has reversible changes. It is an alloy metal with shape memory ability, and is also a kind of intelligent material with functions such as self-detection, self-diagnosis, self-repair and self-adaptation. It has shape memory effect, super-elasticity, high-damping and high-recovery force, and has corrosion resistance, fatigue resistance and excellent mechanical properties.

[0045] The number of the SMA assemblies 25 can be set according to actual needs, which is not limited, for example, the SMA assemblies 25 can be one, two, three, four, etc. When the SMA assemblies 25 are multiple, the multiple SMA assemblies 25 are uniformly distributed along the circumference of the first cylinder 21.

[0046] The number of the damping devices 2 can be set according to actual needs, which is not limited, for example, the damping devices 2 can be two, three, four, etc.

[0047] As shown in Figure 1 , Figure 2 , Figure 3 and Figure 4 , in some embodiments, the first elastic assembly 23 includes an end cover 231, a baffle 232 and a spring 233, the end cover 231 is arranged on the base 1, and the end cover 231 is connected to the end of the first cylinder 21 away from the second elastic assembly 24, a first containing cavity 234 is formed between the end cover 231 and the first cylinder 21, the baffle 232 is arranged in the first containing cavity 234, and the baffle 232 abuts against the end of the first cylinder 21 away from the second elastic assembly 24, the spring 233 is arranged in the first containing cavity 234, and one end of the spring 233 abuts against the side of the baffle 232 away from the first cylinder 21, the end of the spring 233 away from the baffle 232 abuts against the side of the end cover 231 close to the first cylinder 21, wherein the end of the damping rod 22 away from the second elastic assembly 24 abuts against the side of the baffle 232 close to the first cylinder 21, and the end of the SMA assembly 25 away from the second elastic assembly 24 is connected to the baffle 232.

[0048] It can be understood that when the damping rod 22 is subjected to a vibration impact force in the direction from the second elastic assembly 24 to the first elastic assembly 23, since the baffle 232 abuts against the end of the first cylinder 21 away from the second elastic assembly 24, and the end of the damping rod 22 away from the second elastic assembly 24 abuts against the side of the baffle 232 close to the first cylinder 21, the damping rod 22 pushes the baffle 232 to move in the direction close to the end cover 231, at the same time, since one end of the spring 233 abuts against the side of the baffle 232 away from the first cylinder 21, and the end of the spring 233 away from the baffle 232 abuts against the side of the end cover 231 close to the first cylinder 21, the baffle 232 exerts a pushing force on the spring 233 to compress the spring 233, and since the end of the SMA assembly 25 away from the second elastic assembly 24 is connected to the baffle 232, the baffle 232 exerts a pulling force on the SMA assembly 25 to stretch the SMA assembly 25, thereby the damping rod 22 is buffered by the rebound force of the spring 233 and the SMA assembly 25.

[0049] Moreover, the SMA assembly 25 can provide a larger damping force in the process of stretching and rebounding, so as to consume the vibration impact force on the damping rod 22 and the rebound force of the spring 233 and the SMA assembly 25 itself, and then realize the damping of the damping device 2 in cooperation of the end cover 231, the baffle 232, the spring 233 and the SMA assembly 25.

[0050] Wherein, since the baffle 232, the spring 233 and the one end of the SMA assembly 25 away from the second elastic assembly 24 are all located in the first containing cavity 234, the end cover 231 effectively protects the baffle 232, the spring 233 and the SMA assembly 25, thereby reducing the influence of the external environment on the damping device 2, ensuring the stable damping of the damping device 2 and prolonging the service life of the damping device 2.

[0051] It should be noted that the end cover 231 is used to form the first containing cavity 234 with the first cylinder 21, and to support the one end of the spring 233 away from the baffle 232, and the specific type of the end cover 231 can be set according to actual needs, which is not limited, for example, the end cover 231 can be a cylindrical structure with one end through, and the through end of the end cover 231 is connected with the first cylinder 21.

[0052] The baffle 232 is used to abut with the first cylinder 21, the damping rod 22 and the spring 233, and is used to connect with the SMA assembly 25, and the specific type of the baffle 232 can be set according to actual needs, which is not limited, for example, the baffle 232 can be a circular steel plate, and the diameter of the baffle 232 is smaller than the inner diameter of the first containing cavity 234.

[0053] The spring 233 is used to buffer the vibration impact force on the damping rod 22, and is also used to help the recovery of the SMA assembly 25, and the specific type of the spring 233 can be set according to actual needs, which is not limited.

[0054] Wherein, different springs 233 have different elastic coefficients, since the spring 233 can help the SMA assembly 25 to recover by using its own elastic force, therefore, by replacing the spring 233 with appropriate elastic coefficient, the vibration displacement of the damping rod 22 can be reduced while ensuring that the SMA assembly 25 can stretch and rebound.

[0055] As Figure 1 , Figure 2 , Figure 3 and Figure 4As shown in some embodiments, the first elastic assembly 23 further comprises a first ring plate 235 and a second ring plate 236, the first ring plate 235 is sleeved on one end of the first cylinder 21 away from the second elastic assembly 24, and the side of the first ring plate 235 away from the first cylinder 21 abuts against the baffle 232, and the second ring plate 236 is sleeved on one end of the end cover 231 close to the first cylinder 21, and the second ring plate 236 is detachably connected with the first ring plate 235.

[0056] It can be understood that, through the detachable connection between the first ring plate 235 and the second ring plate 236, the stable connection between the end cover 231 and the first cylinder 21 is realized, and the disassembly and assembly between the end cover 231 and the first cylinder 21 are facilitated, so that the maintenance of the damping device 2 is more convenient, and at the same time, since the side of the first ring plate 235 away from the first cylinder 21 abuts against the baffle 232, the baffle 232 can be compressed by the damping rod 22 to compress the spring 233 and stretch the SMA assembly 25, so as to ensure the stable damping of the damping device 2.

[0057] It should be noted that the specific type of the first ring plate 235 and the second ring plate 236 can be set according to actual needs, which is not limited, for example, the first ring plate 235 and the second ring plate 236 can be annular plate structures, the inner diameter of the first ring plate 235 is equal to the outer diameter of the first cylinder 21, the inner diameter of the second ring plate 236 is equal to the outer diameter of the end cover 231, and the first ring plate 235 and the second ring plate 236 can be fixedly connected through a plurality of bolts.

[0058] Since the side of the first ring plate 235 away from the first cylinder 21 abuts against the baffle 232, and the end of the SMA assembly 25 away from the second elastic assembly 24 is connected with the baffle 232, a through hole for the SMA assembly 25 to pass through should also be provided on the first ring plate 235.

[0059] As shown in some embodiments, Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown in some embodiments, the damping device 2 further comprises a second cylinder 26, the second cylinder 26 is detachably connected with the second ring plate 236, and the second cylinder 26 is sleeved on the first cylinder 21, a second containing cavity 27 is formed between the second cylinder 26 and the first cylinder 21, and the SMA assembly 25 is located in the first containing cavity 234 and the second containing cavity 27.

[0060] It can be understood that, since the second cylinder 26 is sleeved on the first cylinder 21, and the SMA assembly 25 is located in the first containing cavity 234 and the second containing cavity 27, the first cylinder 21 and the SMA assembly 25 can be effectively protected, thereby reducing the influence of the external environment on the damping device 2, ensuring the stable damping of the damping device 2, and prolonging the service life of the damping device 2.

[0061] Wherein, since the second cylinder body 26 is detachably connected with the second ring plate 236, the second cylinder body 26 is stably sleeved outside the first cylinder body 21, and the second cylinder body 26 is convenient to disassemble and assemble, so that the maintenance of the damping device 2 is more convenient.

[0062] It should be noted that the specific type of the second cylinder body 26 can be set according to actual needs, which is not limited, for example, the second cylinder body 26 can be a through-cylinder structure, and the inner diameter of the second cylinder body 26 is greater than the outer diameter of the second ring plate 236.

[0063] As shown in Figure 1 , Figure 2 , Figure 3 and Figure 4 , in some embodiments, the baffle 232 is provided with a limiting hole 2321, and the damping rod 22 is provided with a limiting pin 221 away from the second elastic assembly 24. The limiting pin 221 is slidingly inserted into the limiting hole 2321.

[0064] It can be understood that since the limiting hole 2321 is arranged on the baffle 232, the limiting pin 221 is arranged on the damping rod 22, and the limiting pin 221 is slidingly inserted into the limiting hole 2321, when the damping rod 22 pushes the baffle 232 to move, the limiting pin 221 can limit the baffle 232, thereby avoiding the radial deviation of the baffle 232, ensuring the stable compression of the baffle 232 to the spring 233 and the stable stretching of the SMA assembly 25, and further ensuring the stable damping of the damping device 2.

[0065] It should be noted that the limiting pin 221 is matched with the limiting hole 2321, and the specific type of the limiting pin 221 and the limiting hole 2321 can be set according to actual needs, which is not limited, for example, the diameter of the limiting pin 221 is less than the diameter of the damping rod 22, and the center axis of the limiting pin 221 coincides with the center axis of the damping rod 22, and the outer diameter of the limiting pin 221 is less than the inner diameter of the limiting hole 2321.

[0066] As shown in Figure 1 , Figure 2 , Figure 3 and Figure 4 , in some embodiments, the first elastic assembly 23 and the second elastic assembly 24 are the same structure, and the first elastic assembly 23 and the second elastic assembly 24 are symmetrically arranged at both ends of the first cylinder body 21.

[0067] It can be understood that when the vibration occurs on the damping rod 22, the end cap 231, the baffle 232 and the spring 233 in the first elastic assembly 23 and the end cap 231, the baffle 232 and the spring 233 in the second elastic assembly 24 can be matched with the SMA assembly 25 respectively, so as to realize efficient damping of the damping device 2, ensure stable support of the unmanned aerial vehicle damping landing gear, and meet the safe landing demand of the unmanned aerial vehicle.

[0068] It should be noted that, since the first elastic assembly 23 and the second elastic assembly 24 are structurally identical, the second elastic assembly 24 also includes the end cap 231, the baffle 232 and the spring 233. In addition, the second elastic assembly 24 can also include the first ring plate 235, the second ring plate 236, the limiting hole 2321, etc. Moreover, the damping rod 22 away from the first elastic assembly 23 also has a limiting pin 221.

[0069] As shown in Figure 1 , Figure 2 , Figure 3 and Figure 4 , in some embodiments, the damping device 2 further includes a connecting rod 28, which is slidingly arranged on the end cap 231 of the second elastic assembly 24. The end of the connecting rod 28 close to the first elastic assembly 23 is connected to the end of the damping rod 22 away from the first elastic assembly 23. The end of the connecting rod 28 away from the first elastic assembly 23 is connected to the support plate 3. The spring 233 of the second elastic assembly 24 is sleeved on the connecting rod 28.

[0070] It can be understood that, through the arrangement of the connecting rod 28, the damping rod 22 is connected to the support plate 3, so that the damping device 2 can utilize the cooperation of the first elastic assembly 23, the second elastic assembly 24 and the SMA assembly 25 to achieve damping, thereby meeting the damping demand of the unmanned aerial vehicle damping landing gear.

[0071] The spring 233 of the second elastic assembly 24 is sleeved on the connecting rod 28, which not only realizes the combined arrangement of the connecting rod 28 and the first elastic assembly 23, but also avoids interference between the connecting rod 28 and the first elastic assembly 23, thereby ensuring stable damping of the damping device 2.

[0072] It should be noted that the end of the connecting rod 28 close to the first elastic assembly 23 can be connected to the limiting pin 221 of the end of the damping rod 22 away from the first elastic assembly 23.

[0073] As shown in Figure 1 , a plurality of grooves 4 are arranged on the base 1, and the end cap 231 of the first elastic assembly 23 is arranged in the groove 4.

[0074] It can be understood that, through the arrangement of the grooves 4, the damping device 2 can be stably installed on the base 1, thereby ensuring stable damping of the damping device 2.

[0075] It should be noted that the specific type of the groove 4 can be set according to actual needs, and no limitation is made.

[0076] As shown in Figure 1 , Figure 2 , Figure 3 and Figure 4 , in some embodiments, the SMA assembly 25 includes a first adjusting rod 251, a first adjusting sleeve 252, a second adjusting rod 253, a second adjusting sleeve 254 and an SMA wire 255, the first adjusting rod 251 is slidingly arranged at the force receiving end of the first elastic assembly 23, the first adjusting sleeve 252 is arranged at the side of the force receiving end of the first elastic assembly 23 away from the second elastic assembly 24, and the first adjusting sleeve 252 is threadedly connected to the end of the first adjusting rod 251 away from the second elastic assembly 24, the second adjusting rod 253 is slidingly arranged at the force receiving end of the second elastic assembly 24, the second adjusting sleeve 254 is arranged at the side of the force receiving end of the second elastic assembly 24 away from the first elastic assembly 23, and the second adjusting sleeve 254 is threadedly connected to the end of the second adjusting rod 253 away from the first elastic assembly 23, one end of the SMA wire 255 is connected to the end of the first adjusting rod 251 close to the second elastic assembly 24, and the other end of the SMA wire 255 is connected to the end of the second adjusting rod 253 close to the first elastic assembly 23.

[0077] It can be understood that, since the first adjusting rod 251 is slidingly arranged at the force receiving end of the first elastic assembly 23, and the first adjusting sleeve 252 is threadedly connected to the end of the first adjusting rod 251 away from the second elastic assembly 24, the first adjusting rod 251 can be adjusted in position by screwing the first adjusting sleeve 252, since the second adjusting rod 253 is slidingly arranged at the force receiving end of the second elastic assembly 24, and the second adjusting sleeve 254 is threadedly connected to the end of the second adjusting rod 253 away from the first elastic assembly 23, the second adjusting rod 253 can be adjusted in position by screwing the second adjusting sleeve 254, and since one end of the SMA wire 255 is connected to the end of the first adjusting rod 251 close to the second elastic assembly 24, and the other end of the SMA wire 255 is connected to the end of the second adjusting rod 253 close to the first elastic assembly 23, the SMA wire 255 can be adjusted in initial strain by cooperation of the first adjusting rod 251, the first adjusting sleeve 252, the second adjusting rod 253 and the second adjusting sleeve 254, so as to adjust the elastic force and damping force of the damping device 2, so that the damping device 2 is more flexible and versatile in use, thereby meeting different damping requirements of the unmanned aerial vehicle damping landing gear.

[0078] It should be noted that the specific types of the first adjusting rod 251 and the first adjusting sleeve 252 can be set according to actual needs, and no limitation is made thereto. For example, the central axis of the first adjusting rod 251 coincides with the central axis of the damping rod 22, the baffle 232 of the first elastic assembly 23 is provided with a through hole corresponding to the first adjusting rod 251, the first adjusting rod 251 is provided with an external thread, the first adjusting sleeve 252 is located on the side of the baffle 232 of the first elastic assembly 23 away from the second elastic assembly 24, and the first adjusting sleeve 252 is provided with an internal thread. The threaded end of the first adjusting rod 251 is connected with the first adjusting sleeve 252 by screwing the external thread with the internal thread after passing through the through hole.

[0079] The specific types of the second adjusting rod 253 and the second adjusting sleeve 254 can be set according to actual needs, and no limitation is made thereto. For example, the structures of the second adjusting rod 253 and the second adjusting sleeve 254 can be the same as those of the first adjusting rod 251 and the first adjusting sleeve 252.

[0080] The SMA wire 255 refers to a wire-like structure made of SMA material.

[0081] As shown in FIG. 1, in some embodiments, the unmanned aerial vehicle damping landing gear further comprises a plurality of reinforcing rods 5, at least one reinforcing rod 5 being arranged between adjacent damping devices 2. Figure 1 It can be understood that, by arranging the reinforcing rods 5, the adjacent damping devices 2 can be stably connected, so as to ensure that the plurality of damping devices 2 can synchronously and stably damp the unmanned aerial vehicle damping landing gear.

[0082] It should be noted that the number of reinforcing rods 5 can be set according to actual needs, and no limitation is made thereto. For example, the reinforcing rods 5 can be two, three, four, etc.

[0083] The specific types of the reinforcing rods 5 can be set according to actual needs, and no limitation is made thereto. For example, the reinforcing rods 5 can be rod-like structures, and the two ends of the reinforcing rods 5 are respectively connected with the second barrels 26 of the adjacent damping devices 2.

[0084] In the description of the present disclosure, the terms “first”, “second”, etc. are only for descriptive purposes, and cannot be understood as indicating or implying relative importance. In addition, in the description of the present disclosure, the meaning of “a plurality of” is two or more, unless otherwise specified.

[0085]

[0086] ​Any procedural or methodological descriptions in flow charts or otherwise described herein can be understood to represent modules, segments, or portions of code that include executable instructions for implementing the logic functions or procedures described, and the scope of preferred embodiments of the present disclosure includes additional implementations in which the functions can be performed in an order different from that shown or discussed, including substantially simultaneously or in reverse order, as appropriate, according to the functionality involved, as will be understood by those skilled in the art to which embodiments of the present disclosure pertain.

[0087] In the description of the present specification, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present disclosure. In the present specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Also, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in an appropriate manner.

[0088] Although the embodiments of the present disclosure have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present disclosure, and those skilled in the art can make changes, modifications, replacements, and variations to the above-described embodiments within the scope of the present disclosure.

Claims

1. An SMA-based unmanned aerial vehicle (UAV) vibration damping landing gear, comprising: The utility model relates to a damping device, including: a base; a plurality of damping devices, the damping device includes: first cylinder, damping rod, first elastic component, second elastic component and at least one shape memory alloy (SMA) component, the damping rod is slidably arranged in the first cylinder, the first elastic component is arranged on the base, and the first elastic component is connected with one end of the first cylinder, the force receiving end of the first elastic component abuts against one end of the damping rod, the second elastic component is arranged at one end of the first cylinder away from the first elastic component, and the force receiving end of the second elastic component abuts against one end of the damping rod away from the first elastic component, one end of the SMA component is connected with the force receiving end of the first elastic component, and the end of the SMA component away from the first elastic component is connected with the force receiving end of the second elastic component; a support plate connected with the damping rods of the plurality of damping devices, respectively; wherein the first elastic component includes an end cap, a baffle, and a spring, the end cap is arranged on the base, and the end cap is connected with one end of the first cylinder away from the second elastic component, a first accommodating cavity is formed between the end cap and the first cylinder, the baffle is arranged in the first accommodating cavity, and the baffle abuts against one end of the first cylinder away from the second elastic component, the spring is arranged in the first accommodating cavity, and one end of the spring abuts against one side of the baffle away from the first cylinder, the end of the spring away from the baffle abuts against one side of the end cap close to the first cylinder, wherein the end of the damping rod away from the second elastic component abuts against one side of the baffle close to the first cylinder, and the end of the SMA component away from the second elastic component is connected with the baffle; a limiting hole is arranged on the baffle, and a limiting pin is arranged on the end of the damping rod away from the second elastic component, the limiting pin is slidably inserted into the limiting hole; the SMA component includes a first adjusting rod, a first adjusting sleeve, a second adjusting rod, a second adjusting sleeve, and an SMA wire, the first adjusting rod is slidably arranged at the force receiving end of the first elastic component, the first adjusting sleeve is arranged at one side of the force receiving end of the first elastic component away from the second elastic component, and the first adjusting sleeve is threadedly connected with one end of the first adjusting rod away from the second elastic component, the second adjusting rod is slidably arranged at the force receiving end of the second elastic component, the second adjusting sleeve is arranged at one side of the force receiving end of the second elastic component away from the first elastic component, and the second adjusting sleeve is threadedly connected with one end of the second adjusting rod away from the first elastic component, one end of the SMA wire is connected with one end of the first adjusting rod close to the second elastic component, and the end of the SMA wire away from the first elastic component is connected with one end of the second adjusting rod close to the first elastic component, and the SMA wire adjusts the initial strain by cooperating with the first adjusting rod, the first adjusting sleeve, the second adjusting rod, and the second adjusting sleeve.

2. The SMA-based unmanned aerial vehicle vibration damping landing gear of claim 1, wherein, the first elastic component further includes A first ring plate is sleeved on one end of the first cylinder body away from the second elastic assembly, and a side of the first ring plate away from the first cylinder body abuts against the baffle; A second ring plate is sleeved on one end of the end cover close to the first cylinder body, and the second ring plate is detachably connected with the first ring plate.

3. The SMA-based unmanned aerial vehicle vibration damping landing gear of claim 2, wherein, The damping device further comprises: A second cylinder body is detachably connected with the second ring plate, and the second cylinder body is sleeved on the first cylinder body, so that a second accommodating cavity is formed between the second cylinder body and the first cylinder body, and the SMA assembly is located in the first accommodating cavity and the second accommodating cavity.

4. The SMA-based unmanned aerial vehicle vibration damping landing gear of claim 1, wherein, The first elastic assembly and the second elastic assembly are of the same structure, and the first elastic assembly and the second elastic assembly are symmetrically arranged at two ends of the first cylinder body.

5. The SMA-based unmanned aerial vehicle vibration damping landing gear of claim 4, wherein, The damping device further comprises: A connecting rod is slidingly arranged on the end cover of the second elastic assembly, one end of the connecting rod close to the first elastic assembly is connected with one end of the damping rod away from the first elastic assembly, one end of the connecting rod away from the first elastic assembly is connected with the support plate, and the spring of the second elastic assembly is sleeved on the connecting rod.

6. The SMA-based unmanned aerial vehicle vibration damping landing gear of claim 1, wherein, A plurality of grooves are arranged on the base, and the end cover of the first elastic assembly is arranged in the groove.

7. The SMA-based unmanned aerial vehicle vibration damping landing gear according to any one of claims 1-6, wherein, The unmanned aerial vehicle damping landing gear further comprises: A plurality of reinforcing rods are arranged between adjacent damping devices.

Images