Throttle valve device, oil cylinder and oil-gas type shock absorption structure of nose landing gear of unmanned aerial vehicle

By incorporating a porous structure and a spring collision mechanism into the throttle valve, the problem of insufficient potential energy absorption during drone front landing gear landing was solved, resulting in stronger cushioning and shock absorption capabilities and structural durability.

CN224150075UActive Publication Date: 2026-04-21微至航空科技(北京)有限公司
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
微至航空科技(北京)有限公司
Filing Date
2025-06-17
Publication Date
2026-04-21

AI Technical Summary

Technical Problem

In the existing hydropneumatic shock absorption structure of the front landing gear of drones, the throttle valve has only a single orifice, which results in limited absorption of potential energy during landing and makes it prone to damage.

Method used

Multiple throttling orifices are set on the throttling valve body, and multiple throttling springs are sleeved on the protrusion. After the hydraulic oil passes through the porous structure, it drives the springs to collide and generate vibration, thus achieving dual absorption of potential energy.

Benefits of technology

It improves the potential energy absorption capacity, enhances the shock absorption and buffering effect, and extends the service life of the shock-absorbing structure.

✦ Generated by Eureka AI based on patent content.

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Abstract

The utility model provides a throttling valve device, an oil cylinder and an oil-gas type shock absorption structure of a nose landing gear of an unmanned aerial vehicle. The throttling valve device comprises a throttling valve body, a plurality of throttling reeds and a throttling sealing ring. The throttle valve body is of a hollow cylindrical structure, the outer circumferential surface of the throttle valve body is of a threaded structure, and a sealing ring groove is formed in the inner circumferential surface of the throttle valve body; a protruding part is arranged on the top face of the throttle valve body, and a fixing part is arranged on the bottom face of the throttle valve body. A plurality of throttling holes are formed in the throttling valve body; a plurality of throttling reeds are arranged on the protruding part in a sleeved mode, and a throttling sealing ring is installed in the sealing ring groove. According to the throttle valve device, the oil cylinder and the oil-gas type shock absorption structure of the nose landing gear of the unmanned aerial vehicle provided by the embodiment of the invention, the throttle valve device has double absorption capacity on potential energy generated when the nose landing gear of the unmanned aerial vehicle lands, and the buffering and shock absorption capacity of the oil-gas type shock absorption structure of the nose landing gear of the unmanned aerial vehicle is improved; and the service life of the oil-gas type shock absorption structure of the nose landing gear of the unmanned aerial vehicle is prolonged.
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Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a throttle valve device, a hydraulic cylinder, and a hydropneumatic shock absorber structure for the front landing gear of a UAV. Background Technology

[0002] The drone's nose landing gear incorporates a hydropneumatic shock absorber to cushion the potential energy generated during landing. When the drone's nose landing gear touches down, hydraulic oil in the cylinders of this shock absorber flows at high speed through a throttle valve within the cylinder, absorbing some of the potential energy generated during landing and thus providing shock absorption. However, the throttle valve has only a single orifice and a relatively simple structure, limiting its ability to absorb the potential energy during landing and making the hydropneumatic shock absorber structure susceptible to damage. Utility Model Content

[0003] To address the aforementioned issues, the purpose of this application is to provide a throttle valve device, a hydraulic cylinder, and a hydropneumatic shock absorber structure for the front landing gear of a drone.

[0004] In a first aspect, embodiments of this application provide a throttle valve device, including: a throttle valve body, a plurality of throttle springs, and a throttle sealing ring;

[0005] The throttle valve body is a hollow cylindrical structure. The outer circumferential surface of the throttle valve body is threaded, and the inner circumferential surface of the throttle valve body is provided with a sealing ring groove.

[0006] The top surface of the throttle valve body is provided with a protrusion, and the bottom surface of the throttle valve body is provided with a fixing part;

[0007] The throttle valve body has multiple throttle orifices; wherein the axis of each throttle orifice is parallel to the axis of the throttle valve body.

[0008] Multiple throttling springs are fitted onto the protrusion, and the throttling sealing ring is installed in the sealing ring groove.

[0009] Secondly, this application also provides a hydraulic cylinder, including: a hydraulic cylinder housing, a valve fixing pipe, and the throttle valve device described in the first aspect;

[0010] The nozzle fixing tube is installed inside the cylinder housing. The top of the nozzle fixing tube is fixedly connected to the cylinder housing, and the bottom inner circumferential surface of the nozzle fixing tube is provided with a threaded part.

[0011] The nozzle fixing tube is threaded to the throttle valve device via a threaded part, and the throttle valve device is fixed to the bottom of the nozzle fixing tube by a fuse.

[0012] Thirdly, embodiments of this application also provide a hydropneumatic shock absorber structure for the front landing gear of an unmanned aerial vehicle, including: the hydraulic cylinder described in the second aspect above.

[0013] In the solution provided by the first aspect of this application embodiment, multiple throttling orifices are provided on the throttling valve body. Compared with the throttling valve in the related art, which has only a single orifice and has limited absorption of potential energy when the UAV's front landing gear lands, the throttling valve device with a multi-hole structure (i.e., multiple throttling orifices) can better absorb the potential energy generated when the UAV's front landing gear lands. Moreover, multiple throttling springs are sleeved on the protrusion of the throttling valve body, so that the hydraulic oil flows into the multiple throttling springs after passing through the throttling valve device with the multi-hole structure. The hydraulic oil will cause adjacent throttling springs to collide and generate vibration. During this process, the multiple throttling springs will absorb the potential energy generated when the UAV's front landing gear lands again, so that the throttling valve device has a dual absorption capability for the potential energy generated when the UAV's front landing gear lands. This improves the throttling valve's absorption capability for the potential energy when the UAV's front landing gear lands, increases the buffering and shock absorption capability of the UAV's front landing gear's oil-gas shock absorption structure, and extends the service life of the UAV's front landing gear's oil-gas shock absorption structure.

[0014] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A schematic diagram of the structure of a throttle valve device provided in an embodiment of this application is shown;

[0017] Figure 2 An exploded schematic diagram of the throttle valve device provided in the embodiment of this application is shown;

[0018] Figure 3 A schematic diagram of the structure of the throttle valve body provided in the embodiment of this application is shown. Figure 1 ;

[0019] Figure 4 A schematic diagram of the structure of the throttle valve body provided in the embodiment of this application is shown. Figure 2 ;

[0020] Figure 5A schematic diagram of the structure of the hydraulic cylinder provided in the embodiment of this application is shown;

[0021] Figure 6 The embodiments provided in this application are shown. Figure 5 Enlarged view of a portion of the diagram.

[0022] Icons: 1. Throttling valve body; 2. Throttling spring; 3. Washer ring; 4. Throttling sealing ring; 11. Protrusion; 12. Fixing part; 13. Sealing ring groove; 101. Cylinder housing; 102. Nozzle fixing pipe; 103. Throttling valve device; 104. Lower oil seal of nozzle fixing pipe; 105. Nozzle fixing pipe guide ring. Detailed Implementation

[0023] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0025] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0026] The drone's nose landing gear incorporates a hydropneumatic shock absorber to cushion the potential energy generated during landing. When the drone's nose landing gear touches down, hydraulic oil in the cylinders of this shock absorber flows at high speed through a throttle valve within the cylinder, absorbing some of the potential energy generated during landing and thus providing shock absorption. However, the throttle valve has only a single orifice and a relatively simple structure, limiting its ability to absorb the potential energy during landing and making the hydropneumatic shock absorber structure susceptible to damage.

[0027] Based on this, this embodiment proposes a throttle valve device, a hydraulic cylinder, and a hydropneumatic shock absorber structure for the UAV's front landing gear. Multiple throttle orifices are provided on the throttle valve body. The throttle valve device with its porous structure can better absorb the potential energy generated when the UAV's front landing gear lands. Furthermore, multiple throttle springs are fitted onto the protrusions of the throttle valve body, allowing hydraulic oil to flow into the multiple throttle springs after passing through the porous throttle valve device. The hydraulic oil causes adjacent throttle springs to collide and vibrate, further absorbing the potential energy generated when the UAV's front landing gear lands. This gives the throttle valve device a dual absorption capability for the potential energy generated when the UAV's front landing gear lands, improving its absorption capacity and increasing the cushioning and shock absorption capacity of the hydropneumatic shock absorber structure for the UAV's front landing gear, thus extending its service life.

[0028] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the application will be further described in detail below with reference to the accompanying drawings and embodiments.

[0029] Example

[0030] See Figure 1 The schematic diagram of the throttle valve device shown is provided below. Figure 2 The exploded schematic diagram of the throttle valve device shown is available in [reference]. Figure 3 The diagram shows the structure of the throttle valve body. Figure 1 And see also Figure 4 The diagram shows the structure of the throttle valve body. Figure 2 This embodiment proposes a throttle valve device, including: a throttle valve body 1, a plurality of throttle springs 2, and a throttle sealing ring 4.

[0031] The throttle valve body 1 is a hollow cylindrical structure. The outer circumferential surface of the throttle valve body 1 is threaded, and the inner circumferential surface of the throttle valve body 1 is provided with a sealing ring groove 13.

[0032] The top surface of the throttle valve body 1 is provided with a protrusion 11, and the bottom surface of the throttle valve body 1 is provided with a fixing part 12.

[0033] The throttle valve body 1 has multiple throttle holes; wherein the axis of each throttle hole is parallel to the axis of the throttle valve body 1.

[0034] Multiple throttling springs 2 are fitted onto the protrusion 11, and the throttling sealing ring 4 is installed in the sealing ring groove 13.

[0035] In one embodiment, the number of throttling sealing rings 4 is two, and correspondingly, two sealing ring grooves 13 are provided on the inner circumferential surface of the flow valve body 1. This allows one throttling sealing ring 4 to be installed in each of the two sealing ring grooves 13.

[0036] Specifically, the aforementioned fixing part 12 is provided with fixing holes.

[0037] Furthermore, the throttle valve device proposed in this embodiment also includes: a gasket 3.

[0038] A washer 3 is provided between adjacent throttling springs 2 in a plurality of throttling springs 2, and the washer 3 increases the gap between adjacent throttling springs 2.

[0039] In one embodiment, the number of washer rings 3 is one less than the number of throttling springs 2.

[0040] By increasing the gap between adjacent throttling springs 2 by using the washer ring 3, the collision force and vibration of adjacent throttling springs 2 when hydraulic oil flows through multiple throttling springs 2 can be further increased, thereby increasing the absorption effect of multiple throttling springs 2 on the potential energy generated when the UAV's front landing gear lands.

[0041] In one embodiment, the throttle orifice is a bellows orifice. By providing multiple bellows orifices in the throttle valve device, the contact area between the hydraulic oil and the throttle orifice can be further increased when the hydraulic oil flows at high speed through the throttle valve device in the cylinder. This allows the throttle valve device to absorb more of the potential energy generated when the UAV's front landing gear lands.

[0042] Optionally, the corrugated hole is an irregularly shaped hole that is larger at both ends and smaller in the middle.

[0043] In one embodiment, the throttling spring 2 is a flexible stainless steel sheet. The thickness of the throttling spring 2 is between 0.3 mm and 0.6 mm.

[0044] See Figure 5 The schematic diagram of the hydraulic cylinder shown is available in [reference]. Figure 6 shown Figure 5 The enlarged schematic diagram shows that this embodiment also proposes a hydraulic cylinder, including: a hydraulic cylinder housing 101, an air nozzle fixing pipe 102, and the aforementioned throttle valve device 103.

[0045] The nozzle fixing tube 102 is installed inside the cylinder housing 101. The top of the nozzle fixing tube 102 is fixedly connected to the cylinder housing 101, and the bottom inner circumferential surface of the nozzle fixing tube 102 is provided with a threaded part.

[0046] The nozzle fixing tube 102 is threadedly connected to the throttle valve device 103 via a threaded portion, and the throttle valve device 103 is fixed to the bottom of the nozzle fixing tube 102 via a fuse.

[0047] The throttle valve device 103 is fixed to the bottom of the nozzle fixing tube 102 by means of a fuse. Specifically, the fuse is passed through the fixing hole provided on the fixing part 12 of the throttle valve device 103, thereby fixing the throttle valve device 103 to the bottom of the nozzle fixing tube 102 by means of a fuse.

[0048] Furthermore, such as Figure 5 and Figure 6 As shown, the hydraulic cylinder proposed in this embodiment also includes: a lower oil seal 104 for the nozzle fixing tube and a guide ring 105 for the nozzle fixing tube.

[0049] The bottom outer circumferential surface of the air nozzle fixing tube 102 is provided with a guide ring groove and an oil seal groove, respectively.

[0050] The lower oil seal 104 of the air nozzle fixing tube is set in the oil seal groove, and the air nozzle fixing tube guide ring 105 is set in the guide ring groove.

[0051] This embodiment also proposes a hydropneumatic shock absorption structure for the front landing gear of an unmanned aerial vehicle, including the aforementioned hydraulic cylinder.

[0052] In summary, this embodiment provides a throttle valve device, a hydraulic cylinder, and a hydropneumatic shock absorber structure for the nose landing gear of a UAV. Multiple throttle orifices are provided on the throttle valve body. Compared to related technologies where throttle valves with only a single orifice have limited absorption of potential energy during UAV nose landing, the throttle valve device with a multi-hole structure (i.e., multiple throttle orifices) can better absorb the potential energy generated during UAV nose landing. Furthermore, multiple throttle springs are fitted onto the protrusions of the throttle valve body, allowing hydraulic oil to flow more effectively after passing through the multi-hole throttle valve device. By inserting multiple throttle springs, the hydraulic oil causes adjacent throttle springs to collide and vibrate. During this process, the multiple throttle springs absorb the potential energy generated when the drone's front landing gear lands, thus enabling the throttle valve device to have a dual absorption capability for the potential energy generated when the drone's front landing gear lands. This improves the throttle valve's ability to absorb the potential energy when the drone's front landing gear lands, increases the buffering and shock absorption capability of the drone's front landing gear's hydropneumatic shock absorption structure, and extends the service life of the drone's front landing gear's hydropneumatic shock absorption structure.

[0053] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A throttle valve device, characterized in that, include: Throttling valve body, multiple throttling springs, and throttling sealing ring; The throttle valve body is a hollow cylindrical structure. The outer circumferential surface of the throttle valve body is threaded, and the inner circumferential surface of the throttle valve body is provided with a sealing ring groove. The top surface of the throttle valve body is provided with a protrusion, and the bottom surface of the throttle valve body is provided with a fixing part; The throttle valve body has multiple throttle orifices; wherein the axis of each throttle orifice is parallel to the axis of the throttle valve body. Multiple throttling springs are fitted onto the protrusion, and the throttling sealing ring is installed in the sealing ring groove.

2. The throttle valve device according to claim 1, characterized by Also includes: Washer ring; A washer ring is provided between adjacent throttling reeds in a plurality of throttling reeds to increase the gap between adjacent throttling reeds.

3. The throttle valve device according to claim 1, characterized by The throttling orifice is a corrugated orifice.

4. The throttle valve apparatus according to claim 1, characterized by The throttling spring is made of elastic stainless steel.

5. The throttle valve apparatus according to claim 1, characterized by The thickness of the throttling reed is between 0.3 mm and 0.6 mm.

6. A cylinder, characterized by Includes: a cylinder housing, a valve fixing pipe, and a throttle valve device as described in any one of claims 1-5; The nozzle fixing tube is installed inside the cylinder housing. The top of the nozzle fixing tube is fixedly connected to the cylinder housing, and the bottom inner circumferential surface of the nozzle fixing tube is provided with a threaded part. The nozzle fixing tube is threaded to the throttle valve device via a threaded part, and the throttle valve device is fixed to the bottom of the nozzle fixing tube by a fuse.

7. The oil cylinder of claim 6, wherein, Also includes: Oil seal on nozzle fixing tube and guide ring on nozzle fixing tube; The outer circumferential surface of the bottom of the air nozzle fixing tube is provided with a guide ring groove and an oil seal groove, respectively. The oil seal of the nozzle fixing pipe is located in the oil seal groove, and the guide ring of the nozzle fixing pipe is located in the guide ring groove.

8. An oil-gas type shock absorbing structure of a UAV front landing gear, characterized in that, include: The hydraulic cylinder as described in claim 6 or 7 above.