Unmanned aerial vehicle front landing gear integrated drive control device based on micro liquid pump valve joint control

Abstract

This invention discloses an integrated drive and control device for the front landing gear of a UAV based on micro-liquid pump and valve joint control, belonging to the field of UAVs. It includes a mounting assembly, a pump and valve assembly, a plug-in assembly, and a landing assembly. The pump and valve assembly is installed and connected to the inside of the mounting assembly, the plug-in assembly is installed and connected to one side of the pump and valve assembly, and the landing assembly is installed and connected to one side of the plug-in assembly. Through the coordinated use of these devices, the micro gear pump and the reversing valve are integrated into the same housing, eliminating a large number of external pipelines, adapters, and independent supports, significantly reducing the overall installation volume and weight. The diaphragm oil tank is directly connected to the internal oil circuit of the pump body, forming a closed-loop micro-hydraulic circulation system with no exposed pipelines or redundant interfaces, structurally reducing the risk of oil leakage. Simultaneously, the diaphragm oil tank can automatically compensate for changes in hydraulic oil volume, improving operational stability in complex environments such as high and low temperatures and high altitudes.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV front landing gear integrated drive and control device based on micro-liquid pump valve linkage control. Background Technology

[0002] As a core piece of equipment for modern aerial reconnaissance, surveying, logistics, and military applications, the landing gear system of unmanned aerial vehicles (UAVs) directly determines takeoff and landing safety, site adaptability, and overall reliability. The nose landing gear, as the main load-bearing and steering component during UAV takeoff and landing, must simultaneously perform multiple functions, including extension and retraction, cushioning, steering, and locking.

[0003] Traditional devices often employ a separate arrangement of hydraulic pumps, control valves, actuators, and oil tanks, resulting in lengthy pipelines, numerous joints, and independent control of pump drive and valve reversal. This leads to delayed response to retraction and extension actions, large fluctuations in flow and pressure, and susceptibility to malfunctions such as incomplete landing gear retraction and extension or unreliable locking. Performance degrades significantly in complex environments such as high altitudes and low temperatures. Seals in traditional hydraulic systems are prone to aging and leakage, and electric drives have weak overload protection capabilities. Troubleshooting and maintenance are cumbersome, making it difficult to meet the long-endurance and high-frequency takeoff and landing requirements of UAVs.

[0004] Therefore, the present invention provides an integrated drive and control device for the front landing gear of a UAV based on micro-liquid pump valve linkage to solve the above problems. Summary of the Invention

[0005] (a) Technical problems to be solved

[0006] This invention provides an integrated drive and control device for the nose landing gear of a UAV based on micro-liquid pump valve linkage, which aims to solve the problems mentioned in the background art.

[0007] (II) Technical Solution

[0008] To achieve the above objectives, the present invention provides the following technical solution: a comprehensive drive and control device for the front landing gear of an unmanned aerial vehicle based on micro-liquid pump valve joint control, comprising a mounting component, a pump valve component, a plug-in component, and a landing component, wherein the pump valve component is mounted and connected to the inner side of the mounting component, the plug-in component is mounted and connected to one side of the pump valve component, and the landing component is mounted and connected to one side of the plug-in component.

[0009] The pump valve assembly includes a diaphragm oil tank, a housing, gears, a connecting shaft, and a reversing valve. The diaphragm oil tank is fastened to the inside of the mounting assembly. The housing is located on one side of the diaphragm oil tank. The gear is rotatably connected inside the housing. Another set of gears is located on one side of the gear and connected by serrated meshing. One end of the connecting shaft is fastened to the gear, and the other end of the connecting shaft passes through the housing and the other set of housings and is fastened to the gear. The reversing valve is located on one side of the housing, and one end of the reversing valve is plugged into the plug-in assembly.

[0010] As a preferred technical solution of this application, the plug-in assembly includes a plug shell, a limiting ring, a spring, and a pull rod. The plug shell is disposed inside the mounting assembly. The limiting ring is slidably connected to the inner side of a groove inside the plug shell. The spring is disposed inside the groove of the plug shell. One end of the spring is fastened to the plug shell, and the other end of the spring is fastened to the limiting ring. The pull rod is fastened to the outer side of the spring. The outer side of the plug shell is provided with an opening for the pull rod to move.

[0011] As a preferred technical solution of this application, the lifting assembly includes a retraction actuator, a connecting plate, a micro rotary motor, a drive shaft, and a wheel. One end of the retraction actuator is inserted into the housing and limited by a limiting ring. The connecting plate is hinged to the output end of the retraction actuator. The micro rotary motor is installed inside the connecting plate. The drive shaft is driven by the micro rotary motor. One end of the drive shaft passes through the connecting plate and is fastened to the micro rotary motor. The wheel is fastened to the other end of the drive shaft.

[0012] As a preferred technical solution of this application, the mounting assembly includes a mounting base, a mounting plate, a side guard plate, and a bottom guard plate. The mounting plate is disposed on one side of the mounting base, the side guard plate is fastened to one side edge of the mounting plate, and the bottom guard plate is disposed on one side of the side guard plate.

[0013] As a preferred technical solution of this application, the diaphragm oil tank is connected to the internal oil circuit of the outer shell to form a closed micro hydraulic circulation system. The gear is coaxially fixed with the connecting shaft, and the two sets of gears mesh to form a micro hydraulic pump drive structure, which forms a pump-valve integrated control structure with the reversing valve.

[0014] As a preferred technical solution of this application, the limiting ring realizes automatic locking and quick release of the retractable actuator under the action of the spring, and the pull rod drives the limiting ring to compress the spring to unlock.

[0015] As a preferred technical solution of this application, the connecting plate is a steering load-bearing support, and the micro rotary motor is embedded in the connecting plate to reduce the overall volume and weight of the steering mechanism. The micro rotary motor drives the wheel to rotate through the transmission shaft to realize the steering function of the UAV's front landing gear.

[0016] (III) Beneficial Effects

[0017] This invention provides a comprehensive drive and control device for the nose landing gear of a UAV based on micro-liquid pump and valve linkage. Through the coordinated use of a housing, gears, a diaphragm oil tank, and a reversing valve, the micro gear pump and the reversing valve are integrated into the same housing, eliminating the signal delay and flow fluctuation caused by the traditional separate pump and valve. This makes the landing gear retraction and extension movements smoother and more precise, eliminating a large number of external pipelines, adapters, and independent brackets, significantly reducing the overall installation volume and device weight. The diaphragm oil tank is directly connected to the internal oil circuit of the pump body, forming a closed-loop micro-hydraulic circulation system with no exposed pipelines and redundant interfaces, structurally reducing the risk of oil leakage. At the same time, the diaphragm oil tank can automatically compensate for changes in hydraulic oil volume, improving the working stability in complex environments such as high and low temperatures and high altitudes, meeting the user's needs.

[0018] This invention provides a comprehensive drive and control device for the nose landing gear of a UAV based on micro-liquid pump valve linkage. Through the coordinated use of a housing, pull rod, limit ring, and spring, the limit ring and spring achieve automatic locking. Fixing and disassembly can be completed simply by inserting and removing the housing, without tools or screwing. This significantly shortens the time required for landing gear installation, disassembly, and maintenance. The limit ring is continuously compressed under the spring force, forming a rigid limit that will not loosen under the impact of UAV takeoff and landing or flight vibration. This ensures stable oil circuit connection and a firm mechanical connection between the retraction actuator and the pump valve assembly, improving system operational safety. Pulling the pull rod causes the limit ring to compress the spring, unlocking the device. The operation requires minimal force and no special tools, meeting the user's operational needs. Attached Figure Description

[0019] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 This is a cross-sectional view of the overall structure of the present invention;

[0022] Figure 3 This is a schematic diagram of the pump and valve assembly structure of the present invention;

[0023] Figure 4 This is a schematic diagram of the plug-in assembly structure of the present invention;

[0024] Figure 5 This is a schematic diagram of the landing assembly structure of the present invention.

[0025] In the picture:

[0026] 1. Mounting components; 11. Mounting base; 12. Mounting plate; 13. Side guard plate; 14. Bottom guard plate; 2. Pump and valve assembly; 21. Diaphragm oil tank; 22. Housing; 23. Gear; 24. Connecting shaft; 25. Directional valve; 3. Plug-in assembly; 31. Insert shell; 32. Limit ring; 33. Spring; 34. Tie rod; 4. Lifting and lowering assembly; 41. Retraction and extension actuator; 42. Connecting plate; 43. Miniature rotary motor; 44. Drive shaft; 45. Wheel. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] Please see Figures 1-5 The present invention provides a technical solution: a comprehensive drive and control device for the front landing gear of a UAV based on micro-liquid pump valve joint control, including a mounting component 1, a pump valve component 2, a plug-in component 3 and a landing component 4. The pump valve component 2 is installed and connected to the inside of the mounting component 1, the plug-in component 3 is installed and connected to one side of the pump valve component 2, and the landing component 4 is installed and connected to one side of the plug-in component 3.

[0029] The pump-valve assembly 2 includes a diaphragm oil tank 21, a housing 22, a gear 23, a connecting shaft 24, and a reversing valve 25. The diaphragm oil tank 21 is fastened to the inside of the mounting assembly 1. The housing 22 is located on one side of the diaphragm oil tank 21. The gear 23 is rotatably connected inside the housing 22. Another set of gears 23 is located on one side of the gear 23 and is connected by serrated meshing. One end of the connecting shaft 24 is fastened to the gear 23, and the other end of the connecting shaft 24 passes through the housing 22 and the other set of housings 22 and is fastened to the gear 23. The reversing valve 25 is located on one side of the housing 22, and one end of the reversing valve 25 is plugged into the insertion assembly 3. The diaphragm oil tank 21 and the internal oil circuit of the housing 22 are connected to form a closed micro hydraulic circulation system. The gear 23 is coaxially fixed with the connecting shaft 24. The meshing of the two sets of gears 23 constitutes a micro hydraulic pump drive structure, which, together with the reversing valve 25, forms a pump-valve integrated control structure.

[0030] In this embodiment, the micro gear pump and the reversing valve 25 are integrated into the same housing, eliminating the signal delay and flow fluctuation caused by the separation of pumps and valves in the traditional method. This makes the landing gear retraction and extension movements smoother and more precise, eliminating a large number of external pipelines, adapters and independent brackets, significantly reducing the overall installation volume and the weight of the device. The diaphragm oil tank 21 is directly connected to the internal oil circuit of the pump body to form a closed micro hydraulic circulation system. There are no exposed pipelines and redundant interfaces, which reduces the risk of oil leakage from a structural perspective. At the same time, the diaphragm oil tank 21 can automatically compensate for changes in hydraulic oil volume, improving the working stability in complex environments such as high and low temperatures and high altitudes.

[0031] like Figures 1-5 As shown, the present invention provides a technical solution: Preferably, the plug-in assembly 3 includes a plug shell 31, a limiting ring 32, a spring 33, and a pull rod 34. The plug shell 31 is disposed inside the mounting assembly 1. The limiting ring 32 is slidably connected to the inner side of the groove inside the plug shell 31. The spring 33 is disposed inside the groove of the plug shell 31. One end of the spring 33 is fastened to the plug shell 31, and the other end of the spring 33 is fastened to the limiting ring 32. The pull rod 34 is fastened to the outer side of the spring 33. The outer side of the plug shell 31 is provided with an movable opening for the pull rod 34 to move. Under the action of the spring 33, the limiting ring 32 realizes automatic locking and quick release of the retraction actuator 41. The pull rod 34 drives the limiting ring 32 to compress the spring to unlock.

[0032] In this embodiment, the limiting ring 32 and the spring 33 work together to achieve automatic locking. Fixing and disassembly can be completed by simply plugging and unplugging, without tools or screwing. This significantly shortens the time for landing gear installation, disassembly, and maintenance. The limiting ring 32 is continuously pressed under the elastic force of the spring 33 to form a rigid limit. It will not loosen under the impact of UAV take-off and landing or flight vibration. This ensures stable oil circuit connection and firm mechanical connection between the retraction actuator 41 and the pump valve assembly 2, improving the safety of system operation. Pulling the lever 34 can drive the limiting ring 32 to compress the spring 33 to unlock. The operating force is small and no special tools are required.

[0033] like Figures 1-5As shown, the present invention provides a technical solution: Preferably, the lifting assembly 4 includes a retraction actuator 41, a connecting plate 42, a micro rotary motor 43, a drive shaft 44, and a wheel 45. One end of the retraction actuator 41 is inserted into the housing 31 and limited by a limiting ring 32. The connecting plate 42 is hinged to the output end of the retraction actuator 41. The micro rotary motor 43 is installed inside the connecting plate 42. The drive shaft 44 is driven by the micro rotary motor 43. One end of the drive shaft 44 passes through the connecting plate 42 and is fastened to the micro rotary motor 43. The wheel 45 is fastened to... Connected to the other end of the drive shaft 44, the connecting plate 42 serves as a steering support. The micro rotary motor 43 is embedded inside the connecting plate 42, reducing the overall size and weight of the steering mechanism. The micro rotary motor 43 drives the wheel 45 to rotate through the drive shaft 44, thereby realizing the steering function of the UAV's front landing gear. The mounting assembly 1 includes a mounting base 11, a mounting plate 12, a side guard plate 13, and a bottom guard plate 14. The mounting plate 12 is located on one side of the mounting base 11, the side guard plate 13 is fastened to one side edge of the mounting plate 12, and the bottom guard plate 14 is located on one side of the side guard plate 13.

[0034] like Figures 1-5 As shown, when the user needs to use the integrated drive and control device for the UAV front landing gear based on micro-hydraulic pump valve linkage, after the drive power is turned on, the connecting shaft 24 in the pump valve assembly 2 drives two sets of meshing gears 23 to rotate inside the housing 22, forming a micro hydraulic pump and generating pressurized oil. The diaphragm oil tank 21 directly supplies hydraulic oil to the pump body, forming a closed-loop micro hydraulic circulation system. At the same time, the reversing valve 25 acts synchronously with the gear pump to adjust the oil flow direction and pressure, realizing pump valve linkage control and providing stable power for landing gear retraction and extension. The pressurized oil output from the pump valve assembly 2 enters the internal oil circuit of the insert housing 31 of the insertion assembly 3 through the reversing valve 25. After the end of the retraction actuator 41 is inserted into the insert housing 31, the limiting ring 32 automatically engages with the actuator slot under the elastic force of the spring 33, completing mechanical locking and oil circuit sealing. When disassembly is required, the pull rod is pulled. The limit ring 32 is compressed by the spring 33 to quickly unlock the device. Pressurized oil enters the retraction actuator 41, pushing the piston rod to extend and retract, which in turn drives the connecting plate 42 and the wheel 45 to complete the retraction or extension of the landing gear. The reversing valve 25 can switch the oil inlet direction of the actuator, making the retraction and extension actions reversible. After reaching the position, the valve group locks to maintain the landing gear in a fixed position. After the landing gear is lowered, the micro rotary motor 43 starts and directly drives the wheel 45 to rotate through the transmission shaft 44, realizing the UAV's ground taxiing and turning. The motor is embedded in the connecting plate 42, which has a compact structure and rapid turning response. The entire pump and valve assembly 2 and the plug-in assembly 3 are installed on the mounting base 11 and are protected by the side guard plate 13 and the bottom guard plate 14 to avoid damage to the internal structure from take-off and landing impacts, dust and vibration, and to ensure stable operation of the device in complex environments.

[0035] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, 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, and therefore should not be construed as a limitation of this invention.

[0036] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features, and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A comprehensive drive and control device for the nose landing gear of an unmanned aerial vehicle based on micro-liquid pump valve joint control, comprising a mounting component (1), a pump valve component (2), a plug-in component (3), and a landing component (4), characterized in that: The pump valve assembly (2) is installed and connected to the inside of the mounting assembly (1), the plug-in assembly (3) is installed and connected to one side of the pump valve assembly (2), and the lifting assembly (4) is installed and connected to one side of the plug-in assembly (3). The pump valve assembly (2) includes a diaphragm oil tank (21), a housing (22), a gear (23), a connecting shaft (24), and a reversing valve (25). The diaphragm oil tank (21) is fastened to the inside of the mounting assembly (1). The housing (22) is located on one side of the diaphragm oil tank (21). The gear (23) is rotatably connected to the inside of the housing (22). Another set of gears (23) is provided on one side of the gear (23) and connected by sawtooth meshing. One end of the connecting shaft (24) is fastened to the gear (23). The other end of the connecting shaft (24) passes through the housing (22) and the other set of housings (22) and is fastened to the gear (23). The reversing valve (25) is located on one side of the housing (22). One end of the reversing valve (25) is plugged into the plugging assembly (3).

2. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 1, characterized in that: The plug-in assembly (3) includes a plug shell (31), a limiting ring (32), a spring (33), and a pull rod (34). The plug shell (31) is disposed inside the mounting assembly (1). The limiting ring (32) is slidably connected to the inside of the groove inside the plug shell (31). The spring (33) is disposed inside the groove of the plug shell (31), and one end of the spring (33) is fastened to the plug shell (31).

3. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 2, characterized in that: The other end of the spring (33) is fastened to the limiting ring (32), the pull rod (34) is fastened to the outside of the spring (33), and the outer side of the insert (31) is provided with an opening for the pull rod (34) to move.

4. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 3, characterized in that: The lifting assembly (4) includes a retraction actuator (41), a connecting plate (42), a micro rotary motor (43), a drive shaft (44), and a wheel (45). One end of the retraction actuator (41) is inserted into the housing (31) and limited by a limiting ring (32). The connecting plate (42) is hinged to the output end of the retraction actuator (41). The micro rotary motor (43) is installed inside the connecting plate (42). The drive shaft (44) is driven by the micro rotary motor (43). One end of the drive shaft (44) passes through the connecting plate (42) and is fastened to the micro rotary motor (43). The wheel (45) is fastened to the other end of the drive shaft (44).

5. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 1, characterized in that: The mounting assembly (1) includes a mounting base (11), a mounting plate (12), a side guard plate (13), and a bottom guard plate (14), wherein the mounting plate (12) is disposed on one side of the mounting base (11).

6. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 5, characterized in that: The side guard plate (13) is fastened to one side edge of the mounting plate (12), and the bottom guard plate (14) is disposed on one side of the side guard plate (13).

7. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 1, characterized in that: The diaphragm oil tank (21) is connected to the internal oil circuit of the outer shell (22) to form a closed micro hydraulic circulation system. The gear (23) is coaxially fixed with the connecting shaft (24). The two sets of gears (23) mesh to form a micro hydraulic pump drive structure, which forms a pump-valve integrated control structure with the reversing valve (25).

8. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 1, characterized in that: The limiting ring (32) automatically locks and quickly releases the retractable actuator cylinder (41) under the action of the spring (33), and the pull rod (34) drives the limiting ring (32) to compress the spring to unlock.

9. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 1, characterized in that: The connecting plate (42) is a steering support, and the micro rotary motor (43) is embedded in the connecting plate (42) to reduce the overall volume and weight of the steering mechanism.

10. The integrated drive and control device for UAV front landing gear based on micro-liquid pump valve linkage according to claim 9, characterized in that: The micro rotary motor (43) drives the wheel (45) to rotate via the transmission shaft (44), thereby enabling the UAV's front landing gear to turn.

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