Unmanned aerial vehicle with elastic vibration reduction undercarriage

Abstract

The invention discloses an unmanned aerial vehicle with an elastic vibration reduction undercarriage, and belongs to the technical field of unmanned aerial vehicles. An unmanned aerial vehicle with an elastic vibration reduction undercarriage comprises a vehicle body, a spring vibration reduction damper component and a foot frame component are symmetrically and detachably connected to the lower portion of the vehicle body, and the foot frame component is installed on the spring vibration reduction damper component; each of the left side spring vibration reduction damper and the right side spring vibration reduction damper comprises a cylinder barrel and a piston rod connected in the cylinder barrel in a sliding manner, a lower pressing plate is connected to the cylinder barrel, an upper pressing plate is connected to the piston rod, and a spring piece is connected to the cylinder barrel in a sleeving manner; the damping effect in the landing process of the unmanned aerial vehicle is good, damage such as structural damage, component looseness and even system faults caused by instant impact, vertical vibration and horizontal vibration during landing can be effectively reduced, the stability and safety of landing of the unmanned aerial vehicle are improved, and the use cost of the unmanned aerial vehicle is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to an unmanned aerial vehicle with an elastic shock-absorbing landing gear. Background Art

[0002] Unmanned aerial vehicles are widely used in fields such as agricultural monitoring, environmental monitoring, logistics transportation, disaster relief, film shooting, and geographical mapping.

[0003] During the landing process of an unmanned aerial vehicle, impacts and vibrations will occur, resulting in structural damage and component loosening. In severe cases, system failures will occur, reducing the reliability of the unmanned aerial vehicle in use and the safety during the landing process.

[0004] The landing gears of existing multi-rotor unmanned aerial vehicles are designed with a rigid structure, which cannot effectively absorb and disperse stress. When subjected to impacts and vibrations, they are more likely to cause cumulative damage, posing a safety hazard and increasing the use cost of the unmanned aerial vehicle. Summary of the Invention

[0005] The purpose of the present invention is to solve the problems raised in the above background art, and to propose an unmanned aerial vehicle with an elastic shock-absorbing landing gear.

[0006] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0007] An unmanned aerial vehicle with an elastic shock-absorbing landing gear, including a fuselage, and spring shock-absorbing damper members and leg members are symmetrically and detachably connected to the lower part of the fuselage, and the leg members are installed on the spring shock-absorbing damper members;

[0008] The spring shock-absorbing damper members include a left spring shock-absorbing damper and a right spring shock-absorbing damper. Both the left spring shock-absorbing damper and the right spring shock-absorbing damper include a cylinder barrel and a piston rod slidably connected in the cylinder barrel. A lower pressing plate is connected to the cylinder barrel, an upper pressing plate is connected to the piston rod, a spring member is sleeved on the cylinder barrel, and both ends of the spring member are respectively connected to the upper pressing plate and the lower pressing plate.

[0009] Preferably, the included angle between the axis of the spring shock-absorbing damper member and the axis in the vertical direction of the fuselage is 30 - 60°.

[0010] Preferably, the included angle between the axis of the spring shock-absorbing damper member and the axis in the vertical direction of the fuselage is 45°.

[0011] Preferably, the cylinder barrel is provided with a threaded groove, and the lower pressing plate is threadedly connected to the threaded groove to facilitate adjustment of the shock-absorbing elastic force.

[0012] Preferably, the leg member includes a left leg fixed to the left spring shock absorber and a right leg fixed to the right spring shock absorber. A connector is fixedly connected to the cylinder. The left leg and the left spring shock absorber are welded together through the connector, and the right leg and the right spring shock absorber are welded together through the connector.

[0013] Preferably, a left mechanical fixing lug and a right mechanical fixing lug are fixedly connected to the lower end of the fuselage. A damper fixing ring is fixedly connected to the upper pressing plate. The damper fixing ring on the left spring shock absorber is connected to the left mechanical fixing lug through a left damper fixing bolt, and the damper fixing ring on the right spring shock absorber is connected to the right mechanical fixing lug through a right damper fixing bolt.

[0014] Preferably, a driving part is installed at the upper end of the fuselage. A left carrying platform lug and a right carrying platform lug are fixedly connected to the lower end of the fuselage. A right cross bar and a left cross bar are connected between the left carrying platform lug and the right carrying platform lug. A mission carrying platform is fixedly connected to the left cross bar and the right cross bar.

[0015] Preferably, the driving part includes a left rear robotic arm installed on the fuselage. A left rear motor is installed on the left rear robotic arm, and a left rear propeller is installed at the output end of the left rear motor.

[0016] The driving part includes a left front robotic arm installed on the fuselage. A left front motor is installed on the left front robotic arm, and a left front propeller is installed at the output end of the left front motor.

[0017] Preferably, the driving part includes a right rear robotic arm installed on the fuselage. A right rear motor is installed on the right rear robotic arm, and a right rear propeller is installed at the output end of the right rear motor.

[0018] The driving part includes a right front robotic arm installed on the fuselage. A right front motor is installed on the right front robotic arm, and a right front propeller is installed at the output end of the right front motor.

[0019] Preferably, the left rear robotic arm, the left front robotic arm, the right front robotic arm, the right rear robotic arm and the fuselage are all connected through robotic arm fixing bolts.

[0020] The parts not involved in this device are the same as the prior art or can be implemented using the prior art. The present invention has a good damping effect during the landing process of the drone, and can effectively reduce hazards such as structural damage, component loosening, and system failures caused by the instantaneous impact, vertical vibration, and horizontal vibration during landing, which is beneficial to improving the stability and safety of the drone during landing and reducing the use cost of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 FIG. 1 is a schematic structural diagram of a drone with an elastic damping landing gear proposed by the present invention;

[0022] Figure 2 FIG. 2 is a left-view structural diagram of a drone with an elastic damping landing gear proposed by the present invention;

[0023] Figure 3 FIG. 3 is a right-view structural diagram of a drone with an elastic damping landing gear proposed by the present invention;

[0024] Figure 4 FIG. 4 is a top-view structural diagram of a drone with an elastic damping landing gear proposed by the present invention;

[0025] Figure 5 FIG. 5 is a schematic structural diagram of a spring damping damper component of a drone with an elastic damping landing gear proposed by the present invention.

[0026] In the figures: 1, left rear propeller; 2, left rear motor; 3, left front motor; 4, left front propeller; 5, left front robotic arm; 6, left mechanical fixing lug; 7, fuselage; 8, right mechanical fixing lug; 9, right front robotic arm; 10, right front propeller; 11, right front motor; 12, right rear motor; 13, right rear propeller; 14, right damper fixing bolt; 15, right spring damping damper; 16, right landing gear; 17, mission carrying platform; 18, left landing gear; 19, left spring damping damper; 20, left damper fixing bolt; 21, left carrying platform lug; 22, right carrying platform lug; 23, left crossbar; 24, left rear robotic arm; 25, right rear robotic arm; 26, right crossbar; 27, robotic arm fixing bolt; 28, damper fixing ring; 29, upper pressure plate; 30, piston rod; 31, spring member; 32, threaded groove; 33, lower pressure plate; 34, cylinder barrel; 35, connector. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0028] Example 1:

[0029] Referring to Figures 1-5 , a drone with an elastic shock-absorbing landing gear, which includes a fuselage 7. Symmetrically and detachably connected below the fuselage 7 are a spring shock-absorbing damper member and a leg member, and the leg member is installed on the spring shock-absorbing damper member;

[0030] Referring to Figure 5 , the spring shock-absorbing damper member includes a left spring shock-absorbing damper 19 and a right spring shock-absorbing damper 15. Both the left spring shock-absorbing damper 19 and the right spring shock-absorbing damper 15 include a cylinder barrel 34 and a piston rod 30 slidably connected in the cylinder barrel 34. A lower pressure plate 33 is connected to the cylinder barrel 34, an upper pressure plate 29 is connected to the piston rod 30, and a spring member 31 is sleeved on the cylinder barrel 34. The two ends of the spring member 31 are respectively connected to the upper pressure plate 29 and the lower pressure plate 33.

[0031] Referring to Figure 1 , in order to better damp the fuselage 7 of the drone, the included angle between the axis of the spring shock-absorbing damper member and the axis in the vertical direction of the fuselage 7 is 30 - 60°. Specifically, the included angle between the axis of the spring shock-absorbing damper member and the axis in the vertical direction of the fuselage 7 is 30°, 45° or 60°, so as to relieve the instantaneous impact, vertical vibration and horizontal vibration when the left or right side of the drone lands first.

[0032] Referring to Figure 5 , a threaded groove 32 is provided on the cylinder barrel 34, and the lower pressure plate 33 is threadedly connected to the threaded groove 32. By rotating the lower pressure plate 33, the position of the lower pressure plate 33 on the cylinder barrel 34 can be adjusted, and then the telescopic degree of the spring member 31 can be adjusted to control the elastic force during shock absorption, which is applicable to different landing grounds.

[0033] The leg member includes a left leg 18 fixedly connected to the left spring shock-absorbing damper 19 and a right leg 16 fixedly connected to the right spring shock-absorbing damper 15. A connecting head 35 is fixedly connected to the cylinder barrel 34. The left leg 18 and the left spring shock-absorbing damper 19 are welded together through the connecting head 35, and the right leg 16 and the right spring shock-absorbing damper 15 are welded together through the connecting head 35.

[0034] The present invention has a good shock-absorbing effect during the landing process of the drone, and can effectively reduce the structural damage, component loosening and even system failures and other hazards caused by the instantaneous impact, vertical vibration and horizontal vibration during landing, which is beneficial to improving the stability and safety of the drone landing and reducing the use cost of the drone.

[0035] Example 2:

[0036] Referring to Figures 1-5, A drone with an elastic shock-absorbing landing gear, which is basically the same as Embodiment 1. Further, a left mechanical fixed hanger 6 and a right mechanical fixed hanger 8 are fixedly connected to the lower end of the fuselage 7. A damper fixing ring 28 is fixedly connected to the upper pressure plate 29. The damper fixing ring 28 on the left spring shock-absorbing damper 19 is connected to the left mechanical fixed hanger 6 through a left damper fixing bolt 20, and the damper fixing ring 28 on the right spring shock-absorbing damper 15 is connected to the right mechanical fixed hanger 8 through a right damper fixing bolt 14.

[0037] A driving part is installed at the upper end of the fuselage 7. A left carrying platform hanger 21 and a right carrying platform hanger 22 are fixedly connected to the exact lower end of the fuselage 7. A right cross bar 26 and a left cross bar 23 are connected between the left carrying platform hanger 21 and the right carrying platform hanger 22. A task carrying platform 17 is fixedly connected to the left cross bar 23 and the right cross bar 26, which is used for carrying and hanging loads.

[0038] The driving part includes a left rear mechanical arm 24 installed on the fuselage 7. A left rear motor 2 is installed on the left rear mechanical arm 24, and a left rear propeller 1 is installed at the output end of the left rear motor 2;

[0039] The driving part includes a left front mechanical arm 5 installed on the fuselage 7. A left front motor 3 is installed on the left front mechanical arm 5, and a left front propeller 4 is installed at the output end of the left front motor 3.

[0040] The driving part includes a right rear mechanical arm 25 installed on the fuselage 7. A right rear motor 12 is installed on the right rear mechanical arm 25, and a right rear propeller 13 is installed at the output end of the right rear motor 12;

[0041] The driving part includes a right front mechanical arm 9 installed on the fuselage 7. A right front motor 11 is installed on the right front mechanical arm 9, and a right front propeller 10 is installed at the output end of the right front motor 11.

[0042] The left rear mechanical arm 24, the left front mechanical arm 5, the right front mechanical arm 9, the right rear mechanical arm 25 and the fuselage 7 are all connected through mechanical arm fixing bolts 27. By setting the mechanical arm fixing bolts 27, it is convenient to disassemble, install and replace each mechanical arm;

[0043] During the shock absorption process:

[0044] Such as Figure 1 , 5As shown, when the drone lands and the left landing gear 18 and the right landing gear 16 touch the ground horizontally at the same time, during the landing process, the instantaneous impact, vertical vibration, and horizontal vibration of the fuselage 7 with the ground are respectively transmitted to the spring 31 through the upper pressure plate 29 on the left spring shock absorber 19 and the lower pressure plate 33 connected to the cylinder barrel 34 based on the thread groove 32 on the right spring shock absorber 15. Then, the spring 31 absorbs its impact energy and vibration energy, thereby weakening the impact and vibration of the overall drone during the landing process and realizing the smooth landing of the overall drone;

[0045] As Figure 1 、 2 As shown in Fig. 5, when the drone lands and the left landing gear 18 touches the ground first, during the landing process, the instantaneous impact, vertical vibration, and horizontal vibration of the fuselage 7 with the ground are respectively transmitted to the spring 31 through the upper pressure plate 29 on the left spring shock absorber 19 and the lower pressure plate 33 connected to the cylinder barrel 34 based on the thread groove 32. Then, the spring 31 absorbs the impact energy and vibration energy, thereby weakening the impact and vibration generated when the left landing gear 18 touches the ground first during the landing process;

[0046] As Figure 1 、 3 As shown in Fig. 5, when the drone lands and the right landing gear 16 touches the ground first, during the landing process, the instantaneous impact, vertical vibration, and horizontal vibration of the fuselage 7 with the ground are respectively transmitted to the spring 31 through the upper pressure plate 29 on the right spring shock absorber 15 and the lower pressure plate 33 connected to the cylinder barrel 34 based on the thread groove 32. Then, the spring 31 absorbs the impact energy and vibration energy, thereby weakening the impact and vibration generated when the right landing gear 16 touches the ground first during the landing process.

[0047] As Figure 2 、 3 As shown in Fig. 5, when the drone lands and instantaneous impact and vibration occur on the front and back sides of the left landing gear 18 and the right landing gear 16, the impact force flow and vibration force flow are respectively transmitted to the spring 31 through the lower pressure plate 33 connected to the cylinder barrel 34 based on the thread groove 32 on the left spring shock absorber 19 and the right spring shock absorber 15. The spring 31 absorbs the impact energy and vibration energy generated in the front and back directions, thereby alleviating the impact and vibration generated in the front and back directions during the landing process of the drone to a certain extent and improving the landing stability.

[0048] The present invention has a good damping effect during the landing process of the drone, can effectively reduce hazards such as structural damage, component loosening, and even system failures caused by the instantaneous impact, vertical vibration, and horizontal vibration during landing, is beneficial to improving the stability and safety of the drone landing, and reducing the use cost of the drone.

[0049] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention should cover within the protection scope of the present invention any equivalent replacement or change made according to the technical solution and inventive concept of the present invention.

Claims

1. An unmanned aerial vehicle with elastic vibration-damping landing gear, comprising a fuselage (7), characterized in that: A spring vibration damper component and a foot frame component are symmetrically and detachably connected to the lower part of the fuselage (7), and the foot frame component is installed on the spring vibration damper component; The spring vibration damper component comprises a left spring vibration damper (19) and a right spring vibration damper (15), and the left spring vibration damper (19) and the right spring vibration damper (15) both comprise a cylinder (34) and a piston rod (30) slidably connected in the cylinder (34), the cylinder (34) is connected with a lower pressure plate (33), the piston rod (30) is connected with an upper pressure plate (29), the cylinder (34) is sleeved with a spring member (31), and the two ends of the spring member (31) are respectively connected to the upper pressure plate (29) and the lower pressure plate (33).

2. The UAV with elastic vibration-damping landing gear according to claim 1, characterized in that: The angle between the axis of the spring vibration damper component and the axis in the vertical direction of the fuselage (7) is 30-60 degrees.

3. The UAV with elastic vibration-damping landing gear according to claim 2, characterized in that: The angle between the axis of the spring vibration damper component and the axis in the vertical direction of the fuselage (7) is 45 degrees.

4. The UAV with elastic vibration-damping landing gear according to any one of claims 1 to 3, characterized in that: The cylinder barrel (34) is provided with a thread groove (32), and the lower pressing plate (33) is threadedly connected to the thread groove (32).

5. The UAV with elastic vibration-damping landing gear according to claim 1, characterized in that: The foot frame member comprises a left foot frame (18) fixedly connected to a left spring vibration damper (19) and a right foot frame (16) fixedly connected to a right spring vibration damper (15); a connecting head (35) is fixedly connected to the cylinder (34); the left foot frame (18) and the left spring vibration damper (19) are welded together via the connecting head (35); and the right foot frame (16) and the right spring vibration damper (15) are welded together via the connecting head (35).

6. The UAV with elastic vibration-damping landing gear according to claim 4, characterized in that: The lower end of the fuselage (7) is fixedly connected to a left mechanical fixing lug (6) and a right mechanical fixing lug (8); the upper pressure plate (29) is fixedly connected to a damper fixing ring (28); the damper fixing ring (28) on the left spring vibration damper (19) is connected to the left mechanical fixing lug (6) via a left damper fixing bolt (20); the damper fixing ring (28) on the right spring vibration damper (15) is connected to the right mechanical fixing lug (8) via a right damper fixing bolt (14).

7. The UAV with elastic vibration-damping landing gear according to claim 1, characterized in that: A driving unit is installed at the upper end of the fuselage (7); a left-side loading platform hanging ear (21) and a right-side loading platform hanging ear (22) are fixedly connected to the lower end of the fuselage (7); a right-side cross bar (26) and a left-side cross bar (23) are connected between the left-side loading platform hanging ear (21) and the right-side loading platform hanging ear (22); and a task loading platform (17) is fixedly connected to the left-side cross bar (23) and the right-side cross bar (26).

8. The UAV with elastic vibration-damping landing gear according to claim 7, characterized in that: The driving unit comprises a left rear mechanical arm (24) mounted on the fuselage (7), a left rear motor (2) being mounted on the left rear mechanical arm (24), and a left rear blade (1) being mounted on the output end of the left rear motor (2); The driving unit comprises a left front mechanical arm (5) mounted on a fuselage (7), a left front motor (3) being mounted on the left front mechanical arm (5), and a left front blade (4) being mounted on an output end of the left front motor (3).

9. The UAV with elastic vibration-damping landing gear according to claim 8, characterized in that: The driving unit comprises a right rear mechanical arm (25) mounted on the fuselage (7), a right rear motor (12) being mounted on the right rear mechanical arm (25), and a right rear blade (13) being mounted on the output end of the right rear motor (12); The driving unit comprises a right front mechanical arm (9) mounted on the fuselage (7), a right front motor (11) being mounted on the right front mechanical arm (9), and a right front blade (10) being mounted at the output end of the right front motor (11).

10. The UAV with elastic vibration-damping landing gear according to claim 9, characterized in that: The left rear mechanical arm (24), the left front mechanical arm (5), the right front mechanical arm (9), the right rear mechanical arm (25) and the fuselage (7) are all connected via mechanical arm fixing bolts (27).

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