Multifunctional vibration reduction supporting leg for unmanned aerial vehicle

Abstract

The utility model discloses a multifunctional damping supporting leg for an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. Each supporting leg comprises a sleeve, a piston rod, an elastic assembly, a landing trigger inductive switch and a limiting assembly. The sleeve is vertically fixed to the bottom face of the unmanned aerial vehicle, the piston rod is coaxially inserted into the sleeve, elastically stretches out and draws back with the sleeve and is in axial limiting connection, and the lower end of the piston rod is exposed out of a lower end opening of the sleeve. The elastic assembly sleeves the piston rod and is used for elastic stretching of the piston rod relative to the sleeve. The limiting assembly is installed at the top end of the piston rod and used for preventing the piston rod from disengaging from the sleeve downwards. The landing triggering inductive switch is located over the piston rod, electrically connected with the unmanned aerial vehicle control system and used for inducting the ground touching upward movement of the piston rod and transmitting ground touching information to the unmanned aerial vehicle control system. The damping supporting foot is compact and small in structure, the double-spring series connection design is suitable for damping of landing and vehicle-mounted working conditions, the grounding signal feedback function is achieved, and the landing speed of the unmanned aerial vehicle can be conveniently adjusted in time so as to reduce impact.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a multifunctional vibration-reducing support foot for unmanned aerial vehicles. Background Art

[0002] With the continuous liberalization of low-altitude economic policies, the civilian low-altitude aircraft market has emerged, and more and more types of drones are being used in public safety maintenance, emergency search and rescue, agriculture and forestry, environmental protection, communications, aerial photography and other fields. Users have more urgent needs for the diversification of drone functions, and the demand for medium and large drones (generally referring to drones with a take-off weight of more than 25 kilograms) is gradually increasing, such as agricultural plant protection, fire fighting, short-distance transportation, etc.

[0003] As an important component of drones, the landing gear plays a role in shock absorption and buffering for drone take-off and landing. Traditional drone landing gear is designed as a fixed or automatic folding structure, such as Figure 9 As shown in the figure, the general structure is large and heavy. The main reason is that the traditional landing gear mainly relies on its structural deformation to absorb the impact energy when the drone lands and touches the ground. This design inevitably requires a relatively large structural size, which brings about a large weight of the landing gear, thus occupying the very precious load capacity of the drone.

[0004] With the diversification of drone technology and demand, higher requirements are put forward for drone load capacity, airborne time and other indicators. In particular, the development of tethered drones often requires drones to be equipped with other supporting equipment and stored together in a vehicle-mounted cabin. Tethered drones put forward more control and intervention requirements for the landing process, such as: timely feedback of drone touchdown signals, and positioning and locking of drones after landing. However, the existing tethered drones mostly use traditional landing gear, which, on the one hand, affects the load capacity of the drone, and on the other hand, because it can only play the role of landing vibration reduction and reducing the impact of touching the ground, it is impossible to achieve timely feedback of drone touchdown signals, and thus it is impossible to regulate the landing speed, which may easily lead to excessive landing impact and damage to some parts of the drone; on the other hand, the bumps in the vehicle-mounted cabin during the transportation of the drone will also cause damage to the drone. The locking of the traditional landing gear requires manual operation to complete and confirm the lock, and the process is relatively cumbersome.

[0005] Therefore, it is necessary to design a multifunctional vibration-damping support foot for UAV to solve the above problems. Summary of the invention

[0006] Technical problem to be solved: In order to avoid the shortcomings of the prior art, the present invention provides a multifunctional vibration-damping support foot for UAV, which realizes buffering and shock absorption through the elastic cooperation of a piston rod and a sleeve, and a trigger switch is arranged at the top of the sleeve to sense the support foot touching the ground, so as to solve the problem that the traditional landing gear affects the load capacity of the UAV and cannot realize the feedback of the touchdown signal.

[0007] The technical solution of the present invention is: a multi-functional shock-absorbing support leg for a drone, including a sleeve, a piston rod, an elastic component, a ground-touch trigger induction switch, and a limit component;

[0008] The sleeve is a hollow cylindrical structure with open ends at both ends. The sleeve is vertically fixed to the bottom surface of the drone body along its axis, and a flange is provided at its top for fixed connection with the drone body;

[0009] The piston rod is coaxially inserted into the sleeve, elastically telescoping with the sleeve and axially limitedly connected. The lower end of the piston rod is exposed outside the lower open end of the sleeve;

[0010] The elastic component is sleeved on the piston rod and is located inside the sleeve for the elastic telescoping of the piston rod relative to the sleeve;

[0011] The limit component is installed at the top of the piston rod to prevent the piston rod from slipping out of the sleeve downward;

[0012] The ground-touch trigger induction switch is located directly above the piston rod and is fixed to the upper open end of the sleeve through a mounting plate; the ground-touch trigger induction switch is electrically connected to the drone control system; when the piston rod touches the ground and moves upward, and the ground-touch trigger induction switch senses the upward movement of the piston rod, the ground-touch trigger induction switch transmits the ground-touch information of the support leg to the drone control system.

[0013] A further technical solution of the present invention is: the hollow inner cavity of the sleeve is a stepped structure, which is successively an axial limit cavity, a radial limit cavity, and an elastic component installation cavity from top to bottom, wherein the diameters of the axial limit cavity and the elastic component installation cavity are larger than the diameter of the radial limit cavity; a limit component is installed in the axial limit cavity to prevent the piston rod from slipping out of the sleeve downward; the radial limit cavity matches the small-diameter section of the piston rod to limit the radial movement of the piston rod relative to the sleeve; the elastic component installation cavity is used to install the elastic component.

[0014] A further technical solution of the present invention is: the main body of the piston rod is a stepped rod, including a small-diameter section, a large-diameter section, and a ground-touch joint integrally formed from top to bottom; the small-diameter section penetrates through the elastic component installation cavity and the radial limit cavity from bottom to top, and its top end extends into the axial limit cavity. An external thread is provided at the top end of the small-diameter section for connection with the limit component; the elastic component is sleeved on the small-diameter section, and a first step surface is formed between the small-diameter section and the large-diameter section for the installation and limitation of the elastic component; the upper end of the large-diameter section is embedded in the elastic component installation cavity; the ground-touch joint is located at the lower end of the large-diameter section and is exposed outside the lower open end of the sleeve, and the second step surface between the large-diameter section and the ground-touch joint is used to limit the maximum axial upward displacement of the piston rod.

[0015] A further technical solution of the present invention is that the lower end surface of the ground contact joint is a spherical structure for contacting the ground; a locking groove is provided on the outer circumferential wall of the ground contact joint for locking the support leg; the locking groove is a horizontal annular inner groove structure perpendicular to the axis of the piston rod and is used for plug-in cooperation with the locking pin of the locking mechanism.

[0016] A further technical solution of the present invention is that the elastic component includes a first spring, a second spring, and a spacer ring; the first spring, the spacer ring, and the second spring are coaxially sleeved on the small-diameter section of the piston rod from top to bottom in sequence; the upper and lower end surfaces of the spacer ring are respectively in contact with the first spring and the second spring, and the spacer ring is used to separate the first spring and the second spring to prevent dislocation during the compression of the two springs; the upper end of the first spring abuts against the top wall of the elastic component installation cavity; the lower end of the second spring abuts against the first step surface of the piston rod.

[0017] A further technical solution of the present invention is that the elastic coefficient of the first spring is less than that of the second spring.

[0018] A further technical solution of the present invention is that the limiting component includes a nut and a gasket. The gasket is sleeved on the top of the small-diameter section of the piston rod and is located in the axial limiting cavity; the nut is in threaded connection with the external thread at the top of the small-diameter section of the piston rod, and its lower end surface is in contact with the upper end surface of the gasket; when the piston rod is in a free state, the lower end surface of the gasket is in contact with the bottom wall of the axial limiting cavity.

[0019] A further technical solution of the present invention is that a plurality of connection holes are evenly distributed on the circumference of the flange at the top of the sleeve for passing through fasteners to connect with the bottom of the UAV body; a concave portion is coaxially arranged and communicated with the center position of the upper end surface of the flange for fixing the mounting plate.

[0020] A further technical solution of the present invention is that the mounting plate is coaxially embedded in the concave portion of the flange and is fixedly connected to the bottom surface of the concave portion of the flange by screws; the landing trigger induction switch is fixed at the center position of the lower end surface of the mounting plate.

[0021] A further technical solution of the present invention is that the sleeve is made of super-hard aluminum alloy 7A04; the piston rod is made of nylon 1010.

[0022] Beneficial effects

[0023] The beneficial effects of the present invention are as follows: For the multi-functional shock-absorbing landing gear of the unmanned aerial vehicle of the present invention, four shock-absorbing landing gears are uniformly arranged and fixed at the bottom of the unmanned aerial vehicle body. When the unmanned aerial vehicle approaches the takeoff and landing platform, unstable lift fluctuations will occur between the downward airflow and the takeoff and landing platform, making the unmanned aerial vehicle in an unstable state. When landing, 1 to 2 landing gears touch the ground first. Since a landing trigger induction switch is provided at the top of the sleeve directly above the piston rod, when the piston rod of one shock-absorbing landing gear moves upward, the landing trigger induction switch can transmit the ground contact information to the unmanned aerial vehicle control system, so as to control the unmanned aerial vehicle to instantaneously increase lift, thereby further reducing the ground contact impact.

[0024] The elastic component of the present invention is composed of two springs with different spring constants connected in series. The spring constant of the first spring is less than that of the second spring, which is more suitable for the two stages of the landing of the unmanned aerial vehicle of the tethered cable unmanned aerial vehicle and the vehicle-mounted driving after collection. Since the impact forces received by the shock-absorbing landing gear during the landing of the tethered cable unmanned aerial vehicle and the vehicle-mounted driving are quite different, the double-spring series design with two spring constants enables the springs to absorb impact energy with the best deformation amount at a relatively small length in these two working stages. Compared with a single spring, when dealing with two quite different impact forces simultaneously, the spring often has a huge telescopic amount. The double-spring structure can more effectively and reasonably handle the impact, save the telescopic space, and reduce the design size of the shock-absorbing landing gear.

[0025] The present invention provides a reliable locking function interface for the unmanned aerial vehicle to help the unmanned aerial vehicle achieve the safety of equipment in the carried state: By designing a locking groove in the shock-absorbing landing gear and cooperating with the locking mechanism of the takeoff and landing platform, the locking of the shock-absorbing landing gear can be triggered through the locking trigger to develop and trigger the control system of the takeoff and landing platform of the unmanned aerial vehicle after the collection is in place, which facilitates the fixation of the tethered cable unmanned aerial vehicle during collection and vehicle loading.

[0026] The overall structure of the shock-absorbing landing gear of the present invention is compact, small and light, and the appearance is neat and beautiful. It is mainly applicable to medium and large unmanned aerial vehicles with a takeoff weight of more than 25 kg, including tethered cable unmanned aerial vehicles and other traditional unmanned aerial vehicles. Brief Description of the Drawings

[0027] Figure 1 It is a schematic diagram of the internal structure of the shock-absorbing landing gear of the present invention in the free state;

[0028] Figure 2 It is a schematic diagram of the external structure of the shock-absorbing landing gear of the present invention in the state of being pressed when touching the ground;

[0029] Figure 3 It is a schematic diagram of the installation structure of the elastic component in the present invention;

[0030] Figure 4 It is a schematic diagram of the shock-absorbing landing gear installed on the unmanned aerial vehicle;

[0031] Figure 5 Schematic diagram of the locking mechanism cooperation between the shock-absorbing support foot and the takeoff and landing platform of the present invention;

[0032] Figure 6 is Figure 5 partial enlarged view of;

[0033] Figure 7 Schematic diagram of the structure of the sleeve in the present invention;

[0034] Figure 8 Schematic diagram of the structure of the piston rod in the present invention;

[0035] Figure 9 Schematic diagram of the traditional UAV landing gear and its installation structure with the UAV.

[0036] Explanation of reference numerals: 1. Sleeve, 11. Axial limiting cavity, 12. Radial limiting cavity, 13. Elastic component installation cavity, 14. Flange, 2. Piston rod, 21. Small diameter section, 22. Large diameter section, 23. Ground contact joint, 231. Locking groove, 3. Elastic component, 31. First spring, 32. Second spring, 33. Spacer ring, 4. Landing trigger induction switch, 41. Mounting plate, 5. UAV, 6. Locking mechanism, 61. Locking mechanism main body, 62. Locking pin, 63. Locking sleeve, 64. Locking trigger switch, 7. Limiting component, 71. Nut, 72. Gasket, 8. Takeoff and landing platform, 9. Traditional UAV landing gear. Detailed implementation manners

[0037] The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0038] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0039] Referring to FIGS. 1 and 4, this embodiment provides a multifunctional shock-absorbing support foot for a UAV, as Figure 4As shown, four shock-absorbing feet are provided simultaneously and installed at the bottom of the fuselage of the vertical takeoff and landing drone 5. The multi-functional shock-absorbing feet of the present invention can play a role in buffering the landing of the drone 5 and buffering the impact during vehicle-mounted transportation; at the same time, it can realize the signal feedback of the landing to the drone control system, so as to timely control the landing speed of the drone 5; in addition, it can cooperate with the locking mechanism 6 provided on the takeoff and landing platform 8 to realize the locking of the drone 5 after it is properly stored, which is convenient for fixing when the tethered cable drone is stored on the vehicle.

[0040] Referring to Figure 1 , 2 , the multi-functional shock-absorbing feet of the drone of the present invention include a sleeve 1, a piston rod 2, an elastic component 3, a landing trigger induction switch 4, and a limit component 7. The sleeve 1 is a hollow, open-ended, integrally formed cylindrical structure, and the sleeve 1 is vertically fixed to the bottom surface of the fuselage of the drone 5 along its axis, and its top end is fixedly connected to the bottom of the fuselage of the drone 5. The piston rod 2 is coaxially inserted into the hollow cylinder of the sleeve 1 and is elastically telescoped with the sleeve 1 through the elastic component 3. The elastic component 3 is sleeved on the piston rod 2 and is located inside the sleeve 1 for the elastic telescoping of the piston rod 2 relative to the sleeve 1. The piston rod 2 is axially limited by the limit component 7 at the same time, and the limit component 7 restricts the piston rod 2 from slipping out of the sleeve 1 downward during the up and down movement. The lower end of the piston rod 2 is exposed outside the lower open end of the sleeve 1 for touching the ground. The landing trigger induction switch 4 is located directly above the piston rod 2 and is fixed to the top open end of the sleeve 1 through the mounting plate 41. The landing trigger induction switch 4 is electrically connected to the drone control system. When the piston rod 2 touches the ground and moves upward to trigger the landing trigger induction switch 4, the landing trigger induction switch 4 transmits the ground-touching information of the foot to the drone control system, so as to facilitate the control of the landing speed of the drone 5. For example, at the moment when the drone 5 lands, generally one or two feet touch the ground first, and the ground-touching signal is fed back to the drone control system. The drone control system makes the drone rotor accelerate and rotate instantly to provide a short-term large lift force to slow down the landing, thereby reducing the landing impact and achieving a smooth landing.

[0041] Specifically, referring to Figure 7, a flange 14 is provided at the top of the sleeve 1, and 6 φ7 connection holes are evenly distributed around the circumference of the flange 14, which are used to pass screws to connect with the bottom of the body of the drone 5. The hollow inner cavity of the sleeve 1 is a stepped structure, which includes an axial limit cavity 11, a radial limit cavity 12, and an elastic component installation cavity 13 from top to bottom, wherein the apertures of the axial limit cavity 11 and the elastic component installation cavity 13 are larger than the apertures of the radial limit cavity 12, forming a variable diameter step surface. A limit component 7 is provided in the axial limit cavity 11, and the limit component 7 is connected with the top of the piston rod 2 to prevent the piston rod 2 from slipping out of the sleeve 1 downward. The radial limit cavity 12 matches the small diameter section 21 of the piston rod 2 to limit the radial movement of the piston rod 2 relative to the sleeve 1, that is, to avoid radial offset and shaking during the up and down movement of the piston rod 2. The elastic component installation cavity 13 accommodates the elastic component 3, and the elastic component 3 is sleeved on the piston rod 2. The center position of the upper end surface of the flange 14 is coaxial with the axial limit cavity 11 and is provided with an inner concave portion intersecting therewith, for fixing the mounting plate 41. The mounting plate 41 is coaxially embedded in the inner concave portion of the flange 14 and is fixedly connected to the bottom surface of the inner concave portion of the flange 14 by screws. The floor-triggering induction switch 4 is fixed at the center position of the lower end surface of the mounting plate 41, and the microwave induction head of the floor-triggering induction switch 4 faces the piston rod 2.

[0042] The ground-trigger induction switch 4 in this embodiment is an induction trigger switch, and its front end is a microwave induction head. When an object moves within 50 mm of its front end, the switch will send a trigger signal. When the vibration-damping foot contacts the ground, the upper end of the piston rod 2 moves upward, and the ground-trigger induction switch 4 will send a trigger signal to the drone control system in real time. The characteristics of the ground-trigger induction switch 4 ensure that the piston rod 2 moves up after touching the ground. After the trigger induction switch 4 sends a trigger signal, the piston rod 2 is allowed to continue to compress and move upward to adapt to the maximum stroke of the piston rod 2.

[0043] See also Figure 8 The main body of the piston rod 2 is a stepped rod, including a small diameter section 21, a large diameter section 22, and a ground contact joint 23 integrally formed from top to bottom. The small diameter section 21 of the piston rod 2 penetrates the elastic component installation cavity 13 and the radial limit cavity 12 of the sleeve 1 from bottom to top, and its top end extends into the axial limit cavity 11. The top end of the small diameter section 21 is provided with an external thread for connecting with the limit component 7. Specifically, as Figure 1 As shown, the limiting assembly 7 includes a nut 71 and a gasket 72. The gasket 72 is sleeved on the top of the piston rod small diameter section 21 and is located in the axial limiting cavity 11. The nut 71 is matched with the external thread on the top of the piston rod small diameter section 21, and its lower end surface contacts the upper end surface of the gasket 72. When the piston rod 2 is in a free state, the lower end surface of the gasket 72 contacts the bottom wall of the axial limiting cavity 11, thereby realizing that the piston rod 2 is suspended in the sleeve 1 to prevent it from coming out of the sleeve 1.

[0044] The elastic component 3 is sleeved on the small-diameter section 21 of the piston rod 2. A first step surface is formed between the small-diameter section 21 and the large-diameter section 22 for the installation and limitation of the elastic component 3 on the piston rod 2. The upper end of the large-diameter section 22 is embedded in the elastic component installation cavity 13, so that the upper end of the elastic component 3 abuts against the top end of the elastic component installation cavity 13, and the lower end of the elastic component 3 abuts against the first step surface. The ground contact joint 23 is located at the lower end of the large-diameter section 22 and is exposed outside the lower open end of the sleeve 1. The second step surface formed between the large-diameter section 22 and the ground contact joint 23 is used to limit the maximum upward axial displacement of the piston rod 2, that is, when the piston rod 2 is compressed to the limit position, the second step surface abuts against the end surface of the lower open end of the sleeve 1. The lower end surface of the ground contact joint 23 is of a spherical structure to ensure that it can adapt to various ground conditions when touching the ground. At the same time, in order to lock the outrigger conveniently, a locking groove 231 is provided on the ground contact joint 23. The locking groove 231 is located on the outer circumferential wall of the ground contact joint 23 and is a horizontal annular inner groove structure perpendicular to the axis of the piston rod 2.

[0045] Refer to Figure 3 , the elastic component 3 adopts a series-connected double elastic coefficient spring assembly to be applicable to two stages of the UAV landing and in-vehicle driving after storage, so that the spring can absorb the impact energy with the smallest length and the best deformation amount in the two working stages.

[0046] The elastic component 3 includes a first spring 31, a second spring 32, and a spacer ring 33. The first spring 31, the spacer ring 33, and the second spring 32 are coaxially sleeved on the small-diameter section 21 of the piston rod 2 from top to bottom in sequence and are located in the elastic component installation cavity 13 of the sleeve 1. The upper and lower end surfaces of the spacer ring 33 are in contact with the first spring 31 and the second spring 32 respectively. The spacer ring 33 is used to separate the first spring 31 and the second spring 32 to prevent dislocation during the compression of the two springs. The upper end of the first spring 31 abuts against the top wall of the elastic component installation cavity 13, and the lower end of the second spring 32 abuts against the first step surface of the piston rod 2. Among them, the elastic coefficient of the first spring 31 is less than that of the second spring 32. When the piston rod 2 touches the ground, the first spring 31 with a smaller elastic coefficient is compressed first.

[0047] The elastic coefficient of a single first spring 31 is determined based on the pressure required to compress it by half of its stroke. During the landing phase of the drone 5, when approaching the landing platform 8, unstable lift fluctuations will occur between the downward airflow and the landing platform 8, making the drone 5 in an unstable state. In the final landing phase, generally only 1 or 2 feet may contact the landing platform. At this time, the total weight of the fuselage will act on 1 or 2 feet. The magnitude of the impact force is determined. Since the drone is affected by the lift of the rotor system during this phase, the actual impact force can generally be considered according to an acceleration of 1.5g. The elastic coefficient of a single first spring 31 is calculated by this method. When the drone is driving off-road on a vehicle, the impact of the vehicle's bumps on the on-vehicle equipment is relatively large. In the double-spring assembly, the elastic coefficient of the lower second spring 32 is designed to be relatively large, mainly to reduce the equipment impact during this phase. When selecting the elastic coefficient of the second spring 32, the impact acceleration generated during driving is considered according to 4g. In the stowed state, the 4 feet basically bear the impact force evenly. That is, when each second spring 32 is compressed to 80% of its full stroke (leaving 20% margin to cope with extreme working conditions), it can bear the total weight of the drone and its load.

[0048] By adopting a series-connected double-elastic coefficient spring, it is possible to absorb excess impact energy, providing shock absorption when the drone 5 touches the ground and also providing shock absorption protection for the drone 5 and its load equipment during vehicle bumps.

[0049] Refer to Figure 5 、 6 In the design of the locking groove 231 of the piston rod 2, it is used to cooperate with the locking mechanism 6 installed on the landing platform 8 to lock the feet. For a tethered cable drone, when the drone 5 has completed landing, it is necessary to lock and fix the fuselage in the shelter. By matching the multifunctional shock-absorbing feet in the present invention to the tethered cable vertical takeoff and landing drone 5, when the drone 5 lands, according to the landing procedure, it lands on the landing platform 8 in the shelter. When it is guided to the stowed lock position, the ground contact joint 23 at the lower end of the piston rod 2 is inserted into the locking mechanism 6 on the landing platform 8 to achieve the stowing and fixing of the drone 5.

[0050] Specifically, the locking mechanism 6 includes a locking mechanism main body 61, a locking pin 62, a locking sleeve 63, and a locking trigger switch 64. The locking sleeve 63 has a cap-like structure. Its cap body opens upward and is embedded in the takeoff and landing platform 8, and its brim part is fixedly connected to the takeoff and landing platform 8. The grounding joint 23 of the piston rod 2 is inserted into the cavity of the cap body. The side wall of the cap body is provided with through holes for connecting the locking groove 231 of the grounding joint 23. The locking mechanism main body 61 is fixedly installed inside the unmanned aerial vehicle takeoff and landing platform 8. The locking pin 62 is telescopically and horizontally slidably installed on the locking mechanism main body 61. The locking trigger switch 64 is installed at the lower end of the locking sleeve 63, and its key cap is located at the bottom of the cavity of the cap body of the locking sleeve 63. Both the locking trigger switch 64 and the locking mechanism main body 61 are electrically connected to the control system of the unmanned aerial vehicle takeoff and landing platform. When the shock-absorbing foot is inserted into the locking sleeve 63 and the grounding joint 23 of its piston rod 2 triggers the locking trigger switch 64, the control system of the unmanned aerial vehicle takeoff and landing platform receives the signal that the foot has landed, thereby controlling the locking mechanism main body 61 to drive the locking pin 62 to move. The outer end of the locking pin 62 passes through the through hole of the cap body of the locking sleeve 63 and is inserted and matched with the locking groove 231 to achieve locking. Of course, only one form of the locking mechanism 6 is provided in the embodiment of the present invention, and any other locking mechanisms that can cooperate with the locking groove 231 to achieve locking are applicable.

[0051] In the design of the present invention, structural functions and part weight reduction are considered, so that under the premise of meeting the design functions, the payload capacity of the unmanned aerial vehicle is not occupied as much as possible. The sleeve 1 should meet the basic function of integral molding and bear relatively large bending and torsion forces. It is advisable to use a lightweight metal material with high tensile strength. In this embodiment, super-hard aluminum alloy 7A04 is adopted. The load of the piston rod 2 is relatively small, and it is required to slide freely inside the sleeve 1. It is advisable to use a lightweight non-metallic material with relatively low strength and self-lubricating function. In this embodiment, nylon 1010 is adopted.

[0052] The multifunctional shock-absorbing foot of the present invention is mainly applicable to medium and large unmanned aerial vehicles with a takeoff weight of more than 25 kg, and can achieve ground contact shock absorption, impact reduction, vehicle-mounted impact shock absorption, ground contact trigger signal, and convenient locking. It is especially suitable for tethered cable unmanned aerial vehicles. When applied to tethered cable vertical takeoff and landing unmanned aerial vehicles: at the moment when the unmanned aerial vehicle contacts the takeoff and landing platform, the unmanned aerial vehicle control system receives the aircraft ground contact signal transmitted from the multifunctional foot, so that the rotors of the unmanned aerial vehicle instantly accelerate and rotate to provide a short-term large lift force to resist the ground contact impact. The elastic component 3 inside the multifunctional foot absorbs the excess impact energy to make the ground contact smooth. After normal landing, the locking groove 231 provided at the lower end of the multifunctional foot provides a locking structure for the airframe. After the airframe is reliably locked and fixed in the shelter, the double-spring setting inside the multifunctional foot can provide the shock-absorbing function for the bumps of the unmanned aerial vehicle caused by the uneven road surface during the vehicle driving process.

[0053] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A multifunctional vibration-damping support for an unmanned aerial vehicle, characterized in that: It comprises a sleeve (1), a piston rod (2), an elastic component (3), a floor-triggering induction switch (4), and a limit component (7); The sleeve (1) is a hollow cylindrical structure with open ends. The sleeve (1) is vertically fixed to the bottom surface of the body of the drone (5) along its axis, and a flange (14) is provided at its top end to be fixedly connected to the body of the drone (5). The piston rod (2) is coaxially inserted into the sleeve (1), and is elastically telescopically and axially limitedly connected to the sleeve (1), and the lower end of the piston rod (2) is exposed at the lower end opening of the sleeve (1); The elastic component (3) is sleeved on the piston rod (2), is located inside the sleeve (1), and is used for elastic expansion and contraction of the piston rod (2) relative to the sleeve (1); The limiting assembly (7) is installed at the top end of the piston rod (2) and is used to prevent the piston rod (2) from falling out of the sleeve (1) downwards; The landing trigger induction switch (4) is located directly above the piston rod (2) and is fixed to the top opening of the sleeve (1) via a mounting plate (41); the landing trigger induction switch (4) is electrically connected to the drone control system. When the piston rod (2) touches the ground and moves upward to trigger the landing trigger induction switch (4), the landing trigger induction switch (4) transmits the ground contact information of the support leg to the drone control system.

2. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 1, characterized in that: The hollow inner cavity of the sleeve (1) is a stepped structure, which comprises, from top to bottom, an axial limit cavity (11), a radial limit cavity (12), and an elastic component installation cavity (13), wherein the apertures of the axial limit cavity (11) and the elastic component installation cavity (13) are larger than the apertures of the radial limit cavity (12), forming a variable diameter table; a limit cavity (7) is installed in the axial limit cavity (11); the radial limit cavity (12) matches the small diameter section (21) of the piston rod (2) and is used to limit the radial movement of the piston rod (2) relative to the sleeve (1); and the elastic component installation cavity (13) is used to install the elastic component (3).

3. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 2 is characterized in that: The piston rod (2) is a stepped rod, comprising a small diameter section (21), a large diameter section (22), and a ground contact joint (23) which are integrally formed from top to bottom; the small diameter section (21) passes through the elastic component installation cavity (13) and the radial limit cavity (12) from bottom to top, and its top end extends into the axial limit cavity (11). The top end of the small diameter section (21) is provided with an external thread for connecting with the limit cavity (7); the elastic component (3) is sleeved on the small diameter section (21), and a first step surface is formed between the small diameter section (21) and the large diameter section (22) for installation and limitation of the elastic component (3); the upper end of the large diameter section (22) is embedded in the elastic component installation cavity (13); the ground contact joint (23) is located at the lower end of the large diameter section (22) and is exposed to the lower end opening of the sleeve (1); the second step surface formed between the large diameter section (22) and the ground contact joint (23) is used to limit the maximum axial upward displacement of the piston rod (2).

4. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 3 is characterized in that: The lower end surface of the ground contact joint (23) is a spherical structure for contacting the ground; a locking groove (231) is provided on the outer circumferential wall of the ground contact joint (23) for locking the support foot; the locking groove (231) is a horizontal annular inner groove structure perpendicular to the axis of the piston rod (2) for plugging and matching with the locking pin (62) of the locking mechanism (6).

5. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 3 is characterized in that: The elastic component (3) comprises a first spring (31), a second spring (32) and a spacer ring (33); the first spring (31), the spacer ring (33) and the second spring (32) are coaxially mounted on the small diameter section (21) of the piston rod (2) in sequence from top to bottom; the upper and lower end surfaces of the spacer ring (33) are in contact with the first spring (31) and the second spring (32) respectively, and the spacer ring (33) is used to separate the first spring (31) and the second spring (32) to avoid misalignment of the two springs during compression; the upper end of the first spring (31) is in contact with the top wall of the elastic component installation cavity (13); the lower end of the second spring (32) is in contact with the first step surface of the piston rod (2).

6. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 5, characterized in that: The elastic coefficient of the first spring (31) is smaller than the elastic coefficient of the second spring (32).

7. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 2, characterized in that: The limiting assembly (7) comprises a nut (71) and a gasket (72); the gasket (72) is sleeved on the top end of the piston rod small diameter section (21) and is located in the axial limiting cavity (11); the nut (71) is connected to the external thread on the top end of the piston rod small diameter section (21), and its lower end surface contacts the upper end surface of the gasket (72); when the piston rod (2) is in a free state, the lower end surface of the gasket (72) contacts the bottom wall of the axial limiting cavity (11).

8. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 2, characterized in that: The flange (14) at the top end of the sleeve (1) is evenly distributed around a plurality of connection holes for passing fasteners through the flange (14) to connect to the bottom of the body of the drone (5); the center position of the upper end surface of the flange (14) is coaxial with the axial limit cavity (11) and is provided with an inner concave portion intersecting the axial limit cavity (11) for fixing the mounting plate (41).

9. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 8, characterized in that: The mounting plate (41) is coaxially embedded in the inner recess of the flange (14) and is fixedly connected to the bottom surface of the inner recess of the flange (14) by means of screws; the floor-triggering induction switch (4) is fixed at the center position of the lower end surface of the mounting plate (41).

10. The multifunctional vibration-damping support foot for unmanned aerial vehicles according to claim 1, characterized in that: The sleeve (1) is made of super-hard aluminum alloy 7A04; the piston rod (2) is made of nylon 1010.

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