Folding undercarriage device of low-altitude aircraft

Abstract

The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of landing gears, in particular to a foldable landing gear device for a low-altitude aircraft. Background Art

[0002] As a type of low-altitude aircraft, drones are widely used in the field of agricultural plant protection due to their high efficiency and flexibility.

[0003] However, agricultural plant protection drones in the existing technology usually use a fixed landing gear structure when performing low-altitude spraying operations. Although the structure is simple, it cannot be folded during flight, which increases air resistance, resulting in increased energy consumption of the drone and reduced endurance. Moreover, when operating at low altitude, the fixed landing gear is prone to entanglement or collision with tall crops (such as corn, sugarcane, etc.), thereby affecting flight safety. Summary of the Invention

[0004] In response to the shortcomings of the existing technology, the present invention provides a folding landing gear device for low-altitude aircraft, which solves the technical problems in the existing technology that most agricultural plant protection drones use fixed landing gear, resulting in large air resistance and high energy consumption. It has the advantages of effectively reducing wind resistance and reducing energy consumption.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions: a foldable landing gear device for a low-altitude aircraft, comprising an aircraft body, a liquid medicine spraying mechanism for fertilizing crops provided on the aircraft body, a height-adjustable landing gear mechanism provided at the lower end of the aircraft body, a landing buffer mechanism provided on the landing gear mechanism, the landing buffer mechanism being used to reduce the impact on the landing gear mechanism caused by the moment of landing, a linkage auxiliary mechanism provided on the aircraft body, during low-altitude flight, the liquid medicine spraying mechanism will automatically spray medicine on the crops, and when landing, the landing buffer mechanism will automatically inflate to achieve a soft landing, which can effectively prevent damage to the landing gear mechanism. The structure is designed to produce a larger impact, and the landing gear mechanism includes a fixed plate body, which is detachably mounted on the aircraft body, and mounting bases are symmetrically arranged on the fixed plate body, and a first-level frame is movably mounted on the two mounting bases respectively, and a second-level frame is slidably connected to the first-level frame, and a folding drive member for driving the first-level frame to rotate is provided inside the mounting base, and a supporting cross plate is provided at the lower end of the second-level frame, and a telescopic joint is provided between the supporting cross plate and the second-level frame, and when the second-level frame is extended obliquely downward, the telescopic joint will extend synchronously, and when the second-level frame is retracted toward the inside of the first-level frame, the telescopic joint will shorten synchronously, thereby ensuring that the landing gear mechanism can be retracted and folded.

[0006] Preferably, the folding drive component includes a driven gear mounted on the first-level frame, and a driving gear meshing with the driven gear is provided inside the mounting base. When the driving gear rotates, it cooperates with the driven gear to rotate the first-level frame, thereby rotating the first-level frame from a vertical state to a horizontal state.

[0007] Preferably, an electric telescopic rod for pushing the secondary frame is fixedly installed inside the primary frame. When the electric telescopic rod is extended, the secondary frame is extended outward, thereby reducing the height of the supporting horizontal plate.

[0008] Preferably, the landing buffer mechanism includes a mounting groove opened at the bottom of the supporting horizontal plate, a buffer airbag is arranged inside the mounting groove, and an inflation component is fixedly installed on the supporting horizontal plate. The inflation component is used to input gas into the buffer airbag. Initially, the buffer airbag is in a contracted state. After the inflation component is powered on, gas is automatically filled into the interior of the buffer airbag, thereby causing the buffer airbag to expand and become larger.

[0009] Preferably, a mounting circular tube is embedded in the supporting horizontal plate, a metal slider is slidably connected to the mounting circular tube, a rubber gasket is fixedly installed on the metal slider, and a force storage spring is fixedly connected between the metal slider and the mounting circular tube. Before landing, the force storage spring is in a relaxed state. After landing, the metal slider will squeeze the force storage spring, thereby cushioning the impact caused by landing.

[0010] Preferably, an electromagnet assembly is embedded on the inner wall of the mounting tube. When the electromagnet assembly is energized, the metal slider is magnetically fixed. When the electromagnet assembly is de-energized, the metal slider is quickly extended under the action of a force storage spring.

[0011] Preferably, the liquid medicine spraying mechanism includes a liquid medicine storage tank that is detachably mounted on the aircraft body, a medicine adding channel is provided on the liquid medicine storage tank, and spraying components are symmetrically provided on both sides of the liquid medicine storage tank. During the flight of the aircraft body, the spraying components will evenly spray the liquid medicine inside the liquid medicine storage tank.

[0012] Preferably, sensor components are symmetrically provided on both sides of the fixed plate, and the sensor components can monitor the flight altitude of the aircraft body in real time, thereby cooperating with the controller to adjust the state of the landing gear mechanism.

[0013] Preferably, the linkage auxiliary mechanism includes a reinforcing cross bar fixedly mounted on the primary frame, an arc-shaped rack fixedly mounted on the reinforcing cross bar, a movable rotating shaft movably mounted inside the aircraft body, a fixed gear sleeved on the outside of the movable rotating shaft, a stirring vertical shaft movably mounted inside the medicine liquid storage tank, a transmission assembly is provided between the stirring vertical shaft and the movable rotating shaft, a stirring blade is fixedly mounted on the stirring vertical shaft, and when the stirring vertical shaft rotates, the medicine liquid will be stirred and mixed by cooperating with the stirring blade, thereby ensuring the uniformity of the medicine liquid.

[0014] Preferably, the fixed gear is engaged with the arc-shaped rack, and the transmission assembly is a bevel gear set. When the arc-shaped rack moves, the movable shaft rotates, and when the movable shaft rotates, the transmission assembly is used to rotate the stirring vertical shaft.

[0015] By means of the above technical solution, the present invention provides a foldable landing gear device for a low-altitude aircraft, which has at least the following beneficial effects:

[0016] 1. The present invention adopts a dynamic folding design by providing a landing gear mechanism. After takeoff, the secondary frame retracts, shortening the telescopic joint, thereby reducing the overall height and effectively reducing air turbulence during flight. At the same time, the primary frame rotates to be parallel to the fuselage, significantly reducing the cross-sectional area of ​​the landing gear mechanism and significantly reducing windage loss during high-speed flight.

[0017] 2. The present invention realizes efficient switching under different working conditions by setting a landing gear mechanism. In the ground support mode, the first-level frame is vertically locked and the second-level frame is fully extended to form a stable configuration, ensuring uniform distribution of supporting force. In the flight storage mode, the electric telescopic rod pulls back the second-level frame, and the gear set rotates and folds the first-level frame to achieve compact storage, which can effectively avoid touching crops, significantly improving working efficiency and adaptability to complex terrain, while ensuring the stability and reliability of the landing gear mechanism.

[0018] 3. The present invention provides a landing cushioning mechanism. During landing, the inflation assembly first rapidly inflates the cushioning airbag to form the first cushioning barrier, thereby effectively absorbing the initial impact energy. After the airbag contacts the ground, the internal gas is slowly discharged through the valve, allowing the rubber gasket to contact the ground smoothly to complete the second stage of cushioning, thus achieving an intelligent soft landing of the aircraft body and effectively avoiding the damage to the landing gear caused by a traditional hard landing.

[0019] 4. The present invention provides a landing buffer mechanism. After landing, the metal slider compresses the storage spring to store energy and achieves stable locking through the electromagnet assembly. During the next takeoff, the electromagnet assembly is powered off and the energy stored in the storage spring is released instantly, providing an auxiliary upward thrust for the aircraft body. The buffer system is successfully integrated with the takeoff assistance function, optimizing energy utilization efficiency.

[0020] 5. The present invention creatively combines the landing gear folding action with the liquid medicine stirring function by setting a linkage auxiliary mechanism. No additional power source is required, and the liquid medicine stirring is automatically completed during the normal retraction and extension of the landing gear. This ensures uniform mixing of the medicine and avoids uneven spraying caused by precipitation, and realizes intelligent reuse of energy.

[0021] 6. The present invention provides a linkage auxiliary mechanism and, through the precise matching of the arc-shaped rack and the bevel gear set, efficiently converts the rotary motion of the landing gear into the vertical rotation of the stirring vertical shaft. It has the characteristics of high transmission efficiency and simple maintenance, and completely avoids the risk of failure of the electronic control system in a pesticide corrosive environment.

[0022] 7. The present invention achieves coordinated optimization of the spraying operation and the landing gear status by providing a liquid spraying mechanism. The sensor component monitors the flight altitude in real time and feeds back to the controller, enabling the landing gear mechanism to automatically adjust the folding state according to the operation scenario. This adaptive adjustment mechanism not only reduces flight wind resistance, but also avoids accidental collisions between the landing gear and crops, thereby achieving a dual improvement in the safety and economy of plant protection operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0024] Figure 1 The three-dimensional structure of the overall structure of the present invention Figure 1 ;

[0025] Figure 2 The three-dimensional structure of the overall structure of the present invention Figure 2 ;

[0026] Figure 3 It is a structural schematic diagram of the Chinese medicine liquid spraying mechanism of the present invention;

[0027] Figure 4 Schematic diagram of the structure of the landing gear mechanism of the present invention;

[0028] Figure 5 Schematic diagram of the structure of the folding drive member in the present invention;

[0029] Figure 6 Schematic diagram of the structure of the landing buffer mechanism in the present invention;

[0030] Figure 7 Schematic diagram of the structure of the cushioning airbag in the present invention;

[0031] Figure 8 This is a schematic diagram of the internal structure of the circular tube installed in the present invention;

[0032] Figure 9 Schematic diagram of the structure of the linkage auxiliary mechanism in the present invention;

[0033] Figure 10 It is a structural schematic diagram of the vertical stirring shaft in the present invention.

[0034] In the figure: 1. Aircraft body; 2. Liquid medicine spraying mechanism; 201. Liquid medicine storage tank; 202. Dosing channel; 203. Spraying assembly; 204. Sensor assembly; 3. Landing gear mechanism; 301. Fixed plate; 302. Mounting base; 303. Primary frame; 304. Secondary frame; 305. Folding drive member; 306. Supporting horizontal plate; 307. Telescopic joint; 4. Landing buffer mechanism; 401. Mounting groove; 402. Buffer airbag; 403. Inflatable assembly; 404. Mounting round tube; 405. Metal slider; 406. Rubber gasket; 407. Storage spring; 408. Electromagnet assembly; 5. Linkage auxiliary mechanism; 501. Reinforcement cross bar; 502. Arc rack; 503. Movable rotating shaft; 504. Fixed gear; 505. Transmission assembly; 506. Stirring vertical shaft; 507. Stirring blade. DETAILED DESCRIPTION

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0036] Example 1

[0037] Agricultural plant protection drones in the prior art usually use a fixed landing gear structure when performing low-altitude spraying operations. Although the structure is simple, it cannot be folded during flight, which increases air resistance, resulting in increased energy consumption and reduced endurance of the drone. Moreover, when operating at low altitude, the fixed landing gear is prone to entanglement or collision with tall crops (such as corn, sugarcane, etc.), thus affecting flight safety. In order to solve this technical defect in the prior art, Figure 1-Figure 7 As shown, this embodiment proposes a foldable landing gear device for a low-altitude aircraft, which can effectively reduce air turbulence during flight and significantly reduce windage loss during high-speed flight. The device is provided with a liquid medicine spraying mechanism 2 for fertilizing crops on the aircraft body 1, and a height-adjustable landing gear mechanism 3 is provided at the lower end of the aircraft body 1. A landing buffer mechanism 4 is provided on the landing gear mechanism 3, and the landing buffer mechanism 4 is used to reduce the impact on the landing gear mechanism 3 caused by the moment of landing. A linkage auxiliary mechanism 5 is provided on the aircraft body 1. During low-altitude flight, the liquid medicine spraying mechanism 2 will automatically spray medicine on the crops. When landing, the landing buffer mechanism 4 will automatically inflate to achieve a soft landing, which can effectively prevent a large impact on the landing gear mechanism 3.

[0038] Specifically, the landing gear mechanism 3 includes a fixed plate body 301, which is detachably mounted on the aircraft body 1, and a mounting base 302 is symmetrically provided on the fixed plate body 301. A first-level frame 303 is movably mounted on the two mounting bases 302, and a second-level frame 304 is slidably connected to the first-level frame 303. An electric telescopic rod for pushing the second-level frame 304 is fixedly mounted inside the first-level frame 303. When the electric telescopic rod is extended, the second-level frame 304 is extended outward, thereby lowering the height of the supporting cross plate 306. A folding drive member 305 for driving the first-level frame 303 to rotate is provided inside the mounting base 302. The folding drive member 305 includes a sleeve The driven gear on the first-stage frame 303 is installed with a driving gear meshing with the driven gear inside the mounting base 302. When the driving gear rotates, it will rotate the first-stage frame 303 through cooperation with the driven gear, thereby rotating the first-stage frame 303 from a vertical state to a horizontal state. The lower end of the second-stage frame 304 is provided with a supporting cross plate 306, and a telescopic joint 307 is provided between the supporting cross plate 306 and the second-stage frame 304. When the second-stage frame 304 is extended obliquely downward, the telescopic joint 307 will be extended synchronously. When the second-stage frame 304 is retracted toward the inside of the first-stage frame 303, the telescopic joint 307 will be shortened synchronously, thereby ensuring that the landing gear mechanism 3 can be retracted and folded.

[0039] According to the above content, before takeoff, if Figure 1 As shown, the primary frame 303 is in a vertical state, the secondary frame 304 is in an extended state, and the telescopic joint 307 is in an extended state, thereby providing stable support for the aircraft body 1.

[0040] After the aircraft body 1 takes off, first, the secondary frame 304 will be retracted toward the inside of the primary frame 303 under the action of the electric telescopic rod, thereby increasing the height of the supporting cross plate 306. At the same time, the telescopic joint 307 will be shortened synchronously, thereby reducing the volume of the landing gear mechanism 3, which can effectively reduce the wind resistance of the landing gear mechanism 3 during flight.

[0041] When the aircraft needs to hover at low altitude to perform liquid spraying operations, the first-stage frame 303 will rotate from a vertical state to a horizontal state parallel to the fixed plate 301 under the action of the driving gear. This can prevent the liquid from splashing onto the landing gear mechanism 3 to a certain extent, and prevent the landing gear mechanism 3 from colliding with tall-straw crops. It takes into account both the optimization of aerodynamic performance and the adaptability to field operations, greatly improving flight safety and operating efficiency.

[0042] This embodiment adopts a dynamic folding design by providing a landing gear mechanism 3. After takeoff, the secondary frame 304 retracts and drives the telescopic joint 307 to shorten, thereby reducing the overall height and effectively reducing air turbulence during flight. At the same time, the primary frame 303 rotates to be parallel to the fuselage, which greatly reduces the cross-sectional area of ​​the landing gear mechanism 3 and significantly reduces the wind resistance loss during high-speed flight. Moreover, this embodiment realizes efficient switching under different working conditions by providing the landing gear mechanism 3. In the ground support mode, the primary frame 303 is vertically locked and the secondary frame 304 is fully extended to form a stable configuration, ensuring uniform distribution of supporting force. In the flight storage mode, the electric telescopic rod pulls back the secondary frame 304, and the primary frame 303 is folded in combination with the gear group to achieve compact storage, which can effectively avoid touching crops, significantly improve operating efficiency and adaptability to complex terrain, and at the same time ensure the stability and reliability of the landing gear mechanism 3.

[0043] Example 2

[0044] In order to achieve an intelligent soft landing of the aircraft body 1 and avoid damage to the landing gear caused by a traditional hard landing, based on the first embodiment, as shown in FIG. Figure 1 、 Figure 2 、 Figure 4 as well as Figure 6-Figure 8 As shown, this embodiment is provided with a landing buffer mechanism 4. Specifically, the landing buffer mechanism 4 includes a mounting groove 401 provided at the bottom of the supporting horizontal plate 306. A buffer airbag 402 is provided inside the mounting groove 401. An inflatable component 403 is fixedly installed on the supporting horizontal plate 306. The inflatable component 403 is used to input gas into the buffer airbag 402. Initially, the buffer airbag 402 is in a contracted state. After the inflatable component 403 is powered on, gas is automatically inflated into the interior of the buffer airbag 402, thereby expanding the buffer airbag 402. A mounting round tube 404 is embedded in the supporting horizontal plate 306. The mounting round tube 404 slides up It is dynamically connected with a metal slider 405, on which a rubber gasket 406 is fixedly installed. A force storage spring 407 is fixedly connected between the metal slider 405 and the mounting tube 404. Before landing, the force storage spring 407 is in a relaxed state. After landing, the metal slider 405 will squeeze the force storage spring 407, thereby cushioning the impact caused by landing. An electromagnet assembly 408 is embedded in the inner wall of the mounting tube 404. When the electromagnet assembly 408 is energized, it will magnetically fix the metal slider 405. After the electromagnet assembly 408 is de-energized, the metal slider 405 will quickly extend under the action of the force storage spring 407.

[0045] According to the above content, before the aircraft lands, the inflatable component 403 will automatically inflate the interior of the cushioning airbag 402. Figure 7As shown, the cushioning airbag 402 will expand downward and become larger, thereby providing cushioning before the landing gear mechanism 3 touches the ground, thereby preventing the landing gear mechanism 3 from being damaged by hard contact with the ground during landing.

[0046] After the cushioning airbag 402 contacts the ground, the inflation assembly 403 stops working, and then the gas inside the cushioning airbag 402 is slowly discharged outward through the valve, so that the rubber gasket 406 can slowly and steadily contact the ground to achieve a soft landing.

[0047] After all the gas inside the cushioning airbag 402 is exhausted, the weight of the entire aircraft body 1 will be pressed on the rubber gasket 406 . Next, the metal slider 405 will slide toward the inside of the mounting tube 404 , thereby squeezing the force storage spring 407 .

[0048] Subsequently, the electromagnet assembly 408 will be energized to generate magnetism, magnetically fixing the metal slider 405, so that the force storage spring 407 is always in a compressed energy storage state. When taking off next time, the electromagnet assembly 408 will automatically be powered off. Next, the metal slider 405 will quickly extend outward under the action of the force storage spring 407, thereby giving the aircraft body 1 an upward thrust.

[0049] This embodiment provides a landing buffer mechanism 4. During landing, the inflation component 403 first inflates the buffer airbag 402 rapidly to form a first buffer barrier, thereby effectively absorbing the initial impact energy. After the airbag contacts the ground, the internal gas is slowly discharged through the valve, allowing the rubber gasket 406 to contact the ground smoothly to complete the second stage of buffering, thereby achieving an intelligent soft landing of the aircraft body 1 and effectively avoiding the damage to the landing gear caused by a traditional hard landing. Moreover, this embodiment provides a landing buffer mechanism 4. After landing, the metal slider 405 compresses the storage spring 407 to store energy, and achieves stable locking through the electromagnet component 408. When taking off next time, the electromagnet component 408 releases the energy stored in the storage spring 407 at the moment of power failure, thereby providing an upward auxiliary thrust for the aircraft body 1, successfully integrating the buffer system with the takeoff auxiliary function, and optimizing energy utilization efficiency.

[0050] Example 3

[0051] In order to monitor the flight altitude in real time and feed it back to the controller, so that the landing gear mechanism 3 can automatically adjust the folding state according to the operation scene, based on the above embodiment, as shown in FIG. Figure 1-Figure 3As shown, this embodiment is provided with a medicine liquid spraying mechanism 2. Specifically, the medicine liquid spraying mechanism 2 includes a medicine liquid storage tank 201 that can be detachably mounted on the aircraft body 1. The medicine liquid storage tank 201 is provided with a medicine adding channel 202. Spraying components 203 are symmetrically provided on both sides of the medicine liquid storage tank 201. During the flight of the aircraft body 1, the spraying component 203 will evenly spray the medicine liquid inside the medicine liquid storage tank 201. Sensor components 204 are symmetrically provided on both sides of the fixed plate 301. The sensor components 204 can monitor the flight altitude of the aircraft body 1 in real time, thereby cooperating with the controller to adjust the state of the landing gear mechanism 3.

[0052] As can be seen from the above, before takeoff, the staff will add liquid medicine into the interior of the liquid medicine storage tank 201 through the dosing channel 202. After takeoff, the liquid medicine will be automatically sprayed outward through the spraying assembly 203.

[0053] At the same time, the sensor components 204 on both sides of the fixed plate 301 will monitor the flight altitude in real time and feed the data back to the controller, thereby dynamically adjusting the folding state of the landing gear mechanism 3.

[0054] This embodiment achieves coordinated optimization of the spraying operation and the landing gear status by providing a liquid medicine spraying mechanism 2. The sensor component 204 monitors the flight altitude in real time and feeds back to the controller, so that the landing gear mechanism 3 can automatically adjust the folding state according to the operation scenario. This adaptive adjustment mechanism not only reduces flight wind resistance, but also avoids accidental collisions between the landing gear and crops, thereby achieving a dual improvement in the safety and economy of plant protection operations.

[0055] Example 4

[0056] In order to combine the landing gear folding action with the liquid medicine stirring function to realize the intelligent reuse of energy, such as Figure 2 、 Figure 9 as well as Figure 10As shown, this embodiment is provided with a linkage auxiliary mechanism 5. Specifically, the linkage auxiliary mechanism 5 includes a reinforcing cross bar 501 fixedly mounted on the primary frame 303, an arc-shaped rack 502 fixedly mounted on the reinforcing cross bar 501, a movable rotating shaft 503 movably mounted inside the aircraft body 1, a fixed gear 504 is sleeved on the outside of the movable rotating shaft 503, a stirring vertical shaft 506 movably mounted inside the liquid medicine storage tank 201, a transmission assembly 505 is provided between the stirring vertical shaft 506 and the movable rotating shaft 503, the fixed gear 504 is engaged with the arc-shaped rack 502, and the transmission assembly 505 is a bevel gear set. When the arc-shaped rack 502 moves, the movable rotating shaft 503 is rotated. When the movable rotating shaft 503 rotates, the transmission assembly 505 is used to rotate the stirring vertical shaft 506. A stirring blade 507 is fixedly mounted on the stirring vertical shaft 506. When the stirring vertical shaft 506 rotates, the liquid medicine is stirred and mixed by cooperating with the stirring blade 507, thereby ensuring the uniformity of the liquid medicine.

[0057] According to the above content, after takeoff is completed, the first-stage frame 303 will rotate to a horizontally fitted state under the action of the folding drive member 305. When the first-stage frame 303 rotates, the arc-shaped rack 502 will rotate synchronously. When the arc-shaped rack 502 rotates, it will cooperate with the fixed gear 504 to rotate the movable shaft 503.

[0058] When the movable rotating shaft 503 rotates, it will rotate the stirring vertical shaft 506 through cooperation with the transmission component 505, thereby stirring and mixing the liquid medicine inside the liquid medicine storage tank 201, avoiding precipitation and ensuring the uniformity of the liquid medicine.

[0059] This embodiment creatively combines the folding action of the landing gear with the liquid medicine stirring function by providing a linkage auxiliary mechanism 5. No additional power source is required, and the liquid medicine stirring is automatically completed during the normal retraction and extension of the landing gear, which not only ensures the uniform mixing of the medicine and avoids uneven spraying caused by precipitation, but also realizes the intelligent reuse of energy. Moreover, this embodiment provides a linkage auxiliary mechanism 5, and through the precise cooperation of the arc-shaped rack 502 and the bevel gear set, the rotational motion of the landing gear is efficiently converted into the vertical rotation of the stirring vertical shaft 506, which has the characteristics of high transmission efficiency and simple maintenance, and completely avoids the risk of failure of the electronic control system in a pesticide corrosive environment.

[0060] The control method of the present invention is automatic control through a controller. The control circuit of the controller can be implemented by simple programming by a person skilled in the art. The provision of power is also common knowledge in the art. The present invention is mainly used to protect mechanical devices, so the control method and circuit connection are not explained in detail in the present invention.

[0061] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0062] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A foldable landing gear device for a low-altitude aircraft, comprising an aircraft body (1), the aircraft body (1) being provided with a liquid spraying mechanism (2) for fertilizing crops, characterized in that: A height-adjustable landing gear mechanism (3) is provided at the lower end of the aircraft body (1); a landing buffer mechanism (4) is provided on the landing gear mechanism (3); the landing buffer mechanism (4) is used to reduce the impact on the landing gear mechanism (3) caused by the moment of landing; and a linkage auxiliary mechanism (5) is provided on the aircraft body (1); The landing gear mechanism (3) includes a fixed plate (301), which is detachably mounted on the aircraft body (1); a mounting base (302) is symmetrically arranged on the fixed plate (301); a first-stage frame (303) is movably mounted on each of the two mounting bases (302); a second-stage frame (304) is slidably connected to the first-stage frame (303); a folding drive member (305) for driving the first-stage frame (303) to rotate is arranged inside the mounting base (302); a supporting cross plate (306) is arranged at the lower end of the second-stage frame (304); and a telescopic joint (307) is arranged between the supporting cross plate (306) and the second-stage frame (304).

2. The foldable landing gear device for low-altitude aircraft according to claim 1, characterized in that: The folding driving member (305) comprises a driven gear sleeved on the primary frame (303), and a driving gear meshing with the driven gear is provided inside the mounting base (302).

3. The foldable landing gear device for a low-altitude aircraft according to claim 1, characterized in that: An electric telescopic rod for pushing the secondary frame (304) is fixedly installed inside the primary frame (303).

4. The foldable landing gear device for a low-altitude aircraft according to claim 1, characterized in that: The landing buffer mechanism (4) comprises a mounting groove (401) provided at the bottom of the supporting transverse plate (306), a buffer airbag (402) being provided inside the mounting groove (401), and an inflation component (403) being fixedly mounted on the supporting transverse plate (306), the inflation component (403) being used to input gas into the buffer airbag (402).

5. The foldable landing gear device for low-altitude aircraft according to claim 4, characterized in that: A mounting circular tube (404) is embedded in the supporting horizontal plate (306), a metal slider (405) is slidably connected to the mounting circular tube (404), a rubber gasket (406) is fixedly installed on the metal slider (405), and a force storage spring (407) is fixedly connected between the metal slider (405) and the mounting circular tube (404).

6. The foldable landing gear device for low-altitude aircraft according to claim 5, characterized in that: An electromagnet assembly (408) is embedded on the inner wall of the mounting circular tube (404).

7. The foldable landing gear device for a low-altitude aircraft according to claim 1, characterized in that: The liquid medicine spraying mechanism (2) comprises a liquid medicine storage tank (201) detachably mounted on the aircraft body (1), a medicine adding channel (202) being provided on the liquid medicine storage tank (201), and spraying assemblies (203) being symmetrically provided on both sides of the liquid medicine storage tank (201).

8. The foldable landing gear device for a low-altitude aircraft according to claim 7, characterized in that: Sensor components (204) are symmetrically arranged on both sides of the fixed plate (301).

9. The foldable landing gear device for a low-altitude aircraft according to claim 1, characterized in that: The linkage auxiliary mechanism (5) comprises a reinforcement crossbar (501) fixedly mounted on a primary frame (303), an arc-shaped rack (502) fixedly mounted on the reinforcement crossbar (501), a movable rotating shaft (503) movably mounted inside the aircraft body (1), a fixed gear (504) sleeved on the outside of the movable rotating shaft (503), a stirring vertical shaft (506) movably mounted inside the liquid medicine storage tank (201), a transmission assembly (505) disposed between the stirring vertical shaft (506) and the movable rotating shaft (503), and a stirring blade (507) fixedly mounted on the stirring vertical shaft (506).

10. The foldable landing gear device for a low-altitude aircraft according to claim 9, characterized in that: The fixed gear (504) is meshed with the arc-shaped rack (502), and the transmission assembly (505) is a bevel gear set.

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