Vibration reduction mechanism and unmanned aerial vehicle undercarriage

Abstract

The utility model provides a damping mechanism and an unmanned aerial vehicle undercarriage, and belongs to the technical field of unmanned aerial vehicles. The damping mechanism comprises a cantilever, a supporting leg is hinged to the outer end of the cantilever, the supporting leg is folded inwards into the cantilever, a ratchet mechanism is installed on the cantilever, and the ratchet mechanism is connected with an upper shaft of the supporting leg. According to the unmanned aerial vehicle, the supporting legs can be stored in the cantilevers, occupied space is reduced, the supporting legs can be unfolded to obtain a larger supporting area and improve supporting stability, due to the deflection characteristic of the supporting legs, good vibration reduction can be achieved even if the unmanned aerial vehicle lands in an inclined mode, and due to the fact that damping is achieved through the ratchet mechanism, the structural cost is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and more specifically, to a vibration reduction mechanism and a landing gear for an unmanned aerial vehicle. Background Art

[0002] The landing gear of a UAV is usually equipped with a vibration-damping structure to reduce vibration during landing in order to reduce the cost of the vibration-damping structure.

[0003] The Chinese patent application number is CN201920364600.4, which discloses a vibration reduction mechanism for a UAV landing gear. The main solution is that when the UAV lands, the space in the upper sealed chamber becomes smaller and the pressure increases, pushing the cover downward and squeezing the spring, causing the pressure in the lower sealed chamber to also increase. Subsequently, the high-pressure gases in the upper and lower sealed chambers gradually reach equilibrium through the throttling orifice plate, which imitates the principle of energy loss when the fluid flows in a pipe.

[0004] However, in the process of implementing the technical solutions in the embodiments of the present application, the inventors of the present application found that the above technology has at least the following technical problems:

[0005] 1. During vibration reduction, the second sleeve retracts into the first sleeve, and the vibration reduction direction is fixed. When the drone lands at an angle due to strong wind, the vibration reduction direction is not parallel to the extension direction of the sleeve, resulting in poor vibration reduction effect;

[0006] 2. Due to the use of pneumatic vibration reduction, it is necessary to ensure the sealing during expansion and contraction, so the processing accuracy is high, and sealing rings, lubricating oil, etc. are also required, resulting in high structural costs. Utility Model Content

[0007] In order to make up for the above deficiencies, the present application provides a vibration reduction mechanism and a UAV landing gear, aiming to improve the problems mentioned in the above background technology.

[0008] In a first aspect, an embodiment of the present application provides a vibration reduction mechanism, comprising a cantilever, wherein a leg is hingedly connected to the outer end of the cantilever, and the leg is folded inwardly into the cantilever, and a ratchet mechanism is installed on the cantilever, and the ratchet mechanism is connected to the upper shaft of the leg.

[0009] In a specific embodiment, a bent foot is provided at the outer end of the leg, and the bent foot protrudes from the cantilever.

[0010] In the above implementation process, when the legs are stored in the cantilever, the bent feet protrude from the cantilever, making it easier for fingers to buckle the legs out. When landing, the bent feet can also increase the landing area and improve the stability of the support.

[0011] In a specific embodiment, a buffer pad is fixedly connected to the supporting leg, and the buffer pad is movably pressed against the cantilever.

[0012] In the above implementation process, when the outrigger is completely buffered to the bottom, the buffer pad is clamped between the cantilever and the outrigger to serve as the final buffering and positioning.

[0013] In a specific embodiment, the ratchet mechanism includes a ratchet, and the ratchet is connected to the leg shaft.

[0014] In a specific embodiment, the ratchet mechanism further includes a pawl, and the pawl is movably engaged with the ratchet wheel.

[0015] In the above implementation process, when the outrigger is deflected, the ratchet is driven to rotate, and the engagement of the pawl and the ratchet is utilized to enable the outrigger to obtain a one-way damping deflection effect, consume the landing energy, and achieve a vibration reduction effect. When the outrigger is stored, the pawl can also engage with the ratchet to achieve a locking effect.

[0016] In a specific embodiment, the ratchet mechanism further includes a housing, the pawl is slidably connected to the housing, and a spring is provided in the housing to press against the pawl.

[0017] In a specific implementation, an adjusting screw is threaded onto the housing, and an inner end of the adjusting screw is movably pressed against the rear end of the spring.

[0018] In the above implementation process, the pre-compression degree of the spring is adjusted by using the adjusting screw, thereby adjusting the elasticity of the spring, and then adjusting the engagement degree of the pawl and the ratchet wheel, so as to adjust the magnitude of the damping.

[0019] In a second aspect, the present application further provides a UAV landing gear, including the above-mentioned vibration reduction mechanism.

[0020] Compared with the prior art, the beneficial effects of the present application are: the legs can be stored in the cantilever to reduce space occupancy, and can also be unfolded to obtain a larger support area and improve support stability. Due to the deflection characteristics of the legs, better vibration reduction can be achieved even if the drone lands at an angle. Since a ratchet mechanism is used to achieve damping, the structural cost is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the implementation methods of the present application, the drawings required for use in the implementation methods will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a schematic diagram of the structure of the vibration reduction mechanism provided in the embodiment of the present application;

[0023] Figure 2 A schematic diagram of the structure of the legs in the unfolded state provided in the embodiment of the present application;

[0024] Figure 3 A schematic diagram of the structure of the legs in the stowed state provided in the embodiment of the present application;

[0025] Figure 4 A schematic structural diagram of the connection relationship between the ratchet mechanism and the legs provided in an embodiment of the present application.

[0026] In the figure: 10-cantilever; 20-leg; 30-ratchet mechanism; 31-ratchet; 32-pawl; 33-housing; 34-spring; 35-adjusting screw; 40-bent foot; 50-buffer pad. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application.

[0028] See also Figure 1-Figure 4 The present application provides a vibration reduction mechanism, including a cantilever 10, a leg 20 is hinged at the outer end of the cantilever 10, the leg 20 is folded inwardly into the cantilever 10, a ratchet mechanism 30 is installed on the cantilever 10, and the ratchet mechanism 30 is connected to the upper shaft of the leg 20. The leg 20 can be stored in the cantilever 10 to reduce the space occupied, and can also be unfolded to obtain a larger support area and improve the support stability. Due to the deflection characteristics of the leg 20, even if the drone lands at an angle, better vibration reduction can be obtained. Since the ratchet mechanism 30 is used to achieve damping, the structural cost is reduced.

[0029] See also Figure 1-Figure 4 The outer end of the leg 20 is provided with a bent foot 40, and the bent foot 40 protrudes from the cantilever 10. When the leg 20 is stored in the cantilever 10, the bent foot 40 protrudes from the cantilever 10, which is convenient for fingers to buckle the leg 20. When landing, the bent foot 40 can also increase the landing area and improve the stability of the support.

[0030] See also Figure 1-Figure 4 The supporting leg 20 is fixedly connected with a buffer pad 50, and the buffer pad 50 is movably pressed against the cantilever 10. When the supporting leg 20 is fully buffered to the bottom, the buffer pad 50 is clamped between the cantilever 10 and the supporting leg 20 as the final buffering and positioning.

[0031] See also Figure 1-Figure 4The ratchet mechanism 30 includes a ratchet 31, which is connected to the shaft of the leg 20. The ratchet mechanism 30 also includes a pawl 32, which is movably engaged with the ratchet 31. When the leg 20 deflects, the ratchet 31 is driven to rotate, and the engagement of the pawl 32 with the ratchet 31 is used to make the leg 20 obtain a one-way damping deflection effect, consume the landing energy, and achieve a vibration reduction effect. When the leg 20 is stored, the pawl 32 can also be engaged with the ratchet 31 to achieve a locking effect.

[0032] See also Figure 1-Figure 4 The ratchet mechanism 30 further includes a housing 33, a pawl 32 is slidably connected to the housing 33, and a spring 34 is arranged in the housing 33 to press against the pawl 32. An adjusting screw 35 is threadedly connected to the housing 33, and the inner end of the adjusting screw 35 is movably pressed against the rear end of the spring 34. The adjusting screw 35 is used to adjust the pre-compression degree of the spring 34, thereby adjusting the elasticity of the spring 34, and then adjusting the engagement degree of the pawl 32 and the ratchet wheel 31, and the damping size can be adjusted.

[0033] See also Figure 1-Figure 4 The present application further provides a UAV landing gear, including the above-mentioned vibration reduction mechanism.

[0034] The working principle of the vibration reduction mechanism is as follows: when the drone needs to be used, the leg 20 is buckled out of the cantilever 10 and unfolded outward into the state of the landing gear, and then the adjusting screw 35 is screwed in to increase the elastic force of the spring 34 so that the leg 20 can support the entire drone. When the drone lands too heavy, the leg 20 deflects greatly, and the deflection drives the ratchet 31 to rotate, and the engagement of the ratchet 31 and the pawl 32, as well as the elastic collapse of the pawl 32, are used to eliminate the energy of the landing, thereby achieving a vibration reduction effect. When storing, the adjusting screw 35 is loosened, the pawl 32 is pulled back, and then the leg 20 is folded into the cantilever 10. In summary, the leg 20 can be stored in the cantilever 10 to reduce space occupancy, and can also be unfolded to obtain a larger support area and improve support stability. Due to the deflection characteristics of the leg 20, even if the drone lands at an angle, better vibration reduction can be obtained. Since the ratchet mechanism 30 is used to achieve damping, the structural cost is reduced.

[0035] The above are only embodiments of the present application and are not intended to limit the scope of protection of the present application. For those skilled in the art, the present application may have various changes and variations. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the scope of protection of the present application. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

Claims

1. A vibration reduction mechanism, characterized in that: The invention comprises a cantilever (10), wherein the outer end of the cantilever (10) is hingedly connected to a leg (20), the leg (20) is folded inwardly into the cantilever (10), and a ratchet mechanism (30) is installed on the cantilever (10), and the ratchet mechanism (30) is connected to the upper axis of the leg (20).

2. A vibration reduction mechanism according to claim 1, characterized in that: The outer end of the supporting leg (20) is provided with a bent foot (40), and the bent foot (40) protrudes from the cantilever (10).

3. A vibration reduction mechanism according to claim 2, characterized in that: A buffer pad (50) is fixedly connected to the supporting leg (20), and the buffer pad (50) is movably pressed against the cantilever (10).

4. A vibration reduction mechanism according to claim 3, characterized in that: The ratchet mechanism (30) comprises a ratchet wheel (31), and the ratchet wheel (31) is axially connected to the supporting leg (20).

5. A vibration reduction mechanism according to claim 4, characterized in that: The ratchet mechanism (30) further comprises a ratchet pawl (32), and the ratchet pawl (32) is movably engaged with the ratchet wheel (31).

6. A vibration reduction mechanism according to claim 5, characterized in that: The ratchet mechanism (30) further comprises a housing (33), the ratchet pawl (32) is slidably connected to the housing (33), and a spring (34) is arranged in the housing (33) to press against the ratchet pawl (32).

7. A vibration reduction mechanism according to claim 6, characterized in that: An adjusting screw (35) is threadedly connected to the housing (33), and the inner end of the adjusting screw (35) is movably pressed against the rear end of the spring (34).

8. A UAV landing gear, characterized in that: The invention comprises the vibration reduction mechanism as described in any one of claims 1 to 7.

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