CN117922825A - Aircraft with a plurality of aircraft body - Google Patents

Abstract

The invention is suitable for the technical field of aircrafts, and provides an aircraft. The aircraft comprises a fuselage, a liquid container connected to the fuselage, a plurality of wing assemblies arranged at intervals around the circumference of the fuselage, and a spray head which is arranged on the wing assemblies and communicated with the liquid container for spraying liquid medicine. The liquid container comprises a container body, wherein the container body comprises an upper box body and a lower box body, the upper box body is provided with a first cavity, the lower box body is provided with a second cavity communicated with the first cavity, and the first cavity and the second cavity are used for storing liquid medicine. The liquid container is detachably connected to the machine body, the upper box body is provided with a supporting part, the supporting part is used for supporting the machine body, and when the liquid container is installed on the machine body, the lower box body is inserted into the machine body, and then the upper box body is supported on the machine body. Due to the formation of the first cavity and the second cavity, the shaking of the liquid medicine stored in the first cavity and the second cavity in the moving process is reduced, so that the moving stability and reliability are ensured.

Description

Aircraft

This application is a divisional application of an invention patent application filed on April 6, 2017, with the earliest priority date being April 7, 2016, with the invention name being “Liquid Container and Aircraft” and the application number being 201710221785.9.

Technical Field

The present invention belongs to the technical field of aircraft, and in particular relates to an aircraft.

Background technique

At present, due to the improvement of automation technology, aircraft are widely used in fabric protection operations, for example, using aircraft to spray plants with liquid medicine and agricultural management. When an aircraft sprays plants with medicine, a liquid container is generally set on the fuselage of the aircraft to hold the liquid medicine to be sprayed. The aircraft uses a liquid container to carry the liquid medicine. During the flight of the aircraft, the liquid medicine in the liquid container is sprayed to the farmland, forestry and other areas to be sprayed through a spraying device.

However, during the flight of the aircraft, the liquid medicine in the existing liquid container is prone to shaking, causing the flight of the aircraft to be unstable.

Summary of the invention

The purpose of the present invention is to provide an aircraft, aiming to solve the technical problem in the prior art of how to reduce the shaking of liquid medicine in a liquid container during the movement of the liquid container.

The object of the present invention is to provide an aircraft, comprising a fuselage, a liquid container connected to the fuselage, a plurality of wing assemblies arranged circumferentially around the fuselage at intervals, and a spray head mounted on the wing assemblies and connected to the liquid container for spraying liquid medicine;

The liquid container comprises a container body, the container body comprises an upper box body and a lower box body, the upper box body is provided with a first cavity, the lower box body is provided with a second cavity communicating with the first cavity, the first cavity and the second cavity are used to store liquid medicine;

The liquid container is detachably connected to the fuselage, and the upper box body is provided with a supporting portion, which is used to support the fuselage. When the liquid container is installed on the fuselage, after the lower box body is inserted into the fuselage, the upper box body is supported on the fuselage.

Furthermore, a cross-sectional area of the lower box body in a direction of looking down at the fuselage is smaller than a cross-sectional area of the upper box body.

Furthermore, the support portion is disposed on the bottom wall of the upper box body, and is disposed at a portion of the upper box body whose cross-sectional area is larger than that of the lower box body.

Furthermore, the support portion is arranged on the bottom wall of the upper box body adjacent to the lower box body.

Furthermore, the support portion is a part of the upper box body, and the upper box body is supported on the fuselage through the support portion.

Furthermore, when the liquid container contains liquid medicine to be sprayed, the upper box body is supported on the fuselage under the action of gravity of the liquid medicine to be sprayed.

Furthermore, the upper box body and the lower box body are in an up-and-down stacking structure and roughly form a "T" shape or an inverted "L" shape.

Furthermore, the fuselage includes a frame, and the frame is a vertically through-structure to form a through-space, and the lower box is inserted into the through-space.

Furthermore, the fuselage includes a nose, the nose and the frame are arranged along the front-rear direction, the nose is located in front of the forward direction of the aircraft, and the frame is fixedly connected to the nose.

Furthermore, the machine head has a supporting plate, and the frame includes two strip-shaped mounting plates arranged at the rear end of the supporting plate and symmetrically arranged with respect to the left and right directions, and a connecting plate connected to the rear ends of the two mounting plates, and the connecting plate, the two mounting plates and the supporting plate enclose the through space.

Furthermore, the upper box body is provided with a buckling structure for being snap-connected with the fuselage.

Furthermore, the fuselage includes a head having a supporting flat plate, and the upper box is overlapped on the supporting flat plate and buckled on the supporting flat plate.

Furthermore, one of the upper box and the supporting plate is provided with a pair of snap fasteners and the other is provided with a pair of snap-fitting grooves matched with the snap fasteners.

Furthermore, the liquid outlet of the liquid container is arranged on the bottom wall of the upper box body adjacent to the connection between the upper box body and the lower box body, or is arranged on the side wall of the lower box body adjacent to the connection between the upper box body and the lower box body.

Furthermore, the liquid container also includes a counterweight component sunk at the bottom of the lower box body and an infusion hose connecting the counterweight component and the liquid outlet.

Furthermore, it also includes at least one guide rod arranged on the fuselage and close to the side of the nose, the guide rod is arranged along the insertion direction of the lower box body, and is stopped at the front surface of the lower box body when the lower box body is inserted into the through space.

Furthermore, the upper box body and the lower box body are integrally formed.

Furthermore, the lower box body extends downward from the bottom wall of the upper box body.

The technical effect of the present invention compared to the prior art is that the liquid container is provided with the upper box body and the lower box body arranged up and down, and respectively provided with the first cavity and the second cavity which are interconnected. Due to the formation of the first cavity and the second cavity, the shaking of the medicine liquid stored in the first cavity and the second cavity during the movement is reduced to ensure the stability and reliability of the movement.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments of the present invention or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

FIG1 is a schematic diagram of a structure in which a liquid container is mounted on the body in one direction according to an embodiment of the present invention;

FIG2 is a schematic diagram of the fuselage structure of an aircraft provided by an embodiment of the present invention;

FIG3 is a partial enlarged view of III in FIG2;

Fig. 4 is a partial enlarged view of IV in Fig. 2;

FIG5 is a schematic diagram of the structure of the rolling assembly in FIG2;

6 is a schematic diagram of a structure in which a liquid container is mounted on the fuselage in another direction according to an embodiment of the present invention;

FIG7 is a partial enlarged view of VII in FIG6;

FIG8 is a schematic structural diagram of a liquid container provided in an embodiment of the present invention;

FIG9 is a partial enlarged view of IX in FIG8;

FIG. 10 is a structural diagram of a liquid container provided in an embodiment of the present invention, to show the structural features inside the liquid storage cavity thereof.

Description of reference numerals:

Detailed ways

Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

In the description of the present invention, it is necessary to understand that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

Please refer to FIGS. 1 to 10 , the liquid container 10 provided in the embodiment of the present invention includes a container body 12, the container body 12 includes an upper box body 126 and a lower box body 124 extending downward from the bottom wall of the upper box body 126, the upper box body 126 is provided with a first cavity 1262, the lower box body 124 is provided with a second cavity 1242 communicating with the first cavity 1262, and the first cavity 1262 and the second cavity 1242 are used to store liquid medicine. The liquid container is provided with the upper box body 126 and the lower box body 124 arranged up and down, and is provided with the first cavity 1262 and the second cavity 1242 communicating with each other, respectively. Due to the formation of the first cavity 1262 and the second cavity 1242, the shaking of the liquid medicine stored in the first cavity 1262 and the second cavity 1242 during the movement is reduced, so as to ensure the stability and reliability of the movement.

Please refer to Figures 1 to 10. The liquid container 10 provided in the embodiment of the present invention is applied to an aircraft. The aircraft has a fuselage 30. The liquid container 10 is detachably connected to the fuselage 30. The liquid container 10 includes a container body 12 having a liquid storage cavity 120, and is provided with a liquid injection port 121 and a liquid outlet 122 located on the container body 12 and connected to the liquid storage cavity 120. The liquid storage cavity 120 is used to hold a liquid to be sprayed; the container body 12 includes a lower box body 124 inserted in the fuselage 30 and an upper box body 126 supported by the fuselage 30 and buckled on the fuselage 30. The upper box body 126 and the lower box body 124 are integrally formed and together form the liquid storage cavity 120.

The liquid container 10 provided in the embodiment of the present invention can be detachably connected to the body 30, so that the liquid container 10 can be quickly disassembled and assembled from the body 30, and is convenient to use. Specifically, the container body 12 of the liquid container 10 has the lower box body 124 and the upper box body 126 made of one piece, and the lower box body 124 and the upper box body 126 together form the liquid storage cavity 120 for containing the liquid to be sprayed, and have the liquid injection port 121 and the liquid outlet 122 that are interconnected with the liquid storage cavity 120, so that the liquid can be poured into the liquid storage cavity 120 and discharged from the liquid storage cavity 120. The liquid container 10 When installed on the fuselage 30, the lower box body 124 is inserted into the fuselage 30 to limit the freedom of lateral movement of the liquid container 10, and the upper box body 126 is buckled to the fuselage 30 to limit the freedom of vertical movement of the liquid container 10, so that the liquid container 10 is firmly installed on the fuselage 30. Since the upper box body 126 and the fuselage 30 are buckled with each other, the disassembly and assembly between the two is ensured, which is conducive to the quick disassembly and assembly and replacement of the liquid container 10.

It should be noted that the liquid injection port 121 and the liquid outlet 122 are independently arranged on the container body 12 ; or, the liquid injection port 121 and the liquid outlet 122 can be the same hole arranged on the container body 12 .

Please refer to Figures 1, 8 to 10. In this embodiment, the lower box 124 and the upper box 126 are both roughly square, such as rectangular. The upper box 126 and the lower box 124 are arranged along the up and down direction shown in the figure. When the liquid storage cavity 120 is filled with the liquid to be sprayed, the lower box 124 is inserted into the fuselage 30 and the upper box 126 is supported on the fuselage 30 by the gravity of the liquid to be sprayed and fixed to the fuselage 30 by buckling with the fuselage 30, so as to prevent the liquid container 10 from shaking during the flight of the aircraft, resulting in unstable flight.

In this embodiment, the aircraft can be used in the farming industry to spray pesticides or water on agricultural products. Of course, the aircraft can also be used to spray fire extinguishing liquid in forest fires.

When the liquid container 10 is installed on the fuselage 30, the lower box body 124 is inserted into the fuselage 30 to position the liquid container 10, and the liquid container 10 is accurately positioned at a predetermined position on the fuselage 30, and the upper box body 126 is snapped on the fuselage 30 to fix the liquid container 10, so that the liquid container 10 is installed on the fuselage 30, so that the installation and removal of the liquid container 10 are quick and convenient, thereby improving the working efficiency.

When the liquid medicine needs to be replaced after a single operation of the aircraft is completed, the liquid container 10 can be quickly removed from the fuselage 30, and the liquid container 10 pre-filled with liquid medicine can be quickly installed on the fuselage 30, thereby saving the extra time for filling liquid medicine after the aircraft lands, and the installation and removal of the liquid container 10 are also convenient and quick, thereby improving the operating efficiency of the aircraft.

1, 8 to 10, further, the upper box 126 is provided with a buckle structure 20 snap-connected with the body 30. The buckle structure 20 snap-connects the upper box 126 with the body 30 to conveniently fix the liquid container 10 on the body 30, so that the installation and removal of the liquid container 10 on the body 30 are convenient and fast.

Preferably, the buckling structure 20 can be a matching structure of a buckle 24 and a buckle slot 22, or a matching structure of a buckle and a strap, so as to limit the freedom of movement of the liquid container 10 up and down along the body 30, but is not limited thereto.

Please refer to Figures 8 to 10. Further, the cross-sectional area of the lower box 124 in the direction of looking down at the fuselage 30 is smaller than the cross-sectional area of the upper box 126. It can be understood that the direction of looking down at the fuselage 30 is the direction from top to bottom in the figure, and the cross-sectional areas of the lower box 124 and the upper box 126 in the direction of looking down at the fuselage 30 are the planes formed by the front-back and left-right directions in the figure. The lower box 124 is located below the upper box 126, and the cross-sectional area of the lower box 124 is smaller than the cross-sectional area of the upper box 126. After the lower box 124 is inserted into the fuselage 30, the upper box 126 is supported on the fuselage 30, which facilitates the installation of the liquid container 10, so that pre-batch filling can be achieved.

Compared with other liquid containers 10 of the same box volume and height, the liquid container 10 in this embodiment can reduce the movement of the unit volume of liquid in the lower box 124 due to the small cross-sectional area of the lower box 124, thereby reducing the shaking of the liquid medicine in the lower box 124 during the flight of the aircraft, ensuring that the aircraft can fly smoothly. For example, the liquid medicine in the liquid container 10 will suddenly change the center of gravity of the aircraft as the flight posture of the aircraft changes suddenly during flight, which will cause the liquid medicine in the liquid container 10 to sway.

During the flight operation of the aircraft, under the action of the gravity of the liquid medicine, the liquid medicine in the upper box of the liquid container 10 flows out of the lower box from the liquid outlet 122. That is to say, when the liquid medicine in the liquid storage cavity 120 is reduced to the lower box 124, the flight attitude of the aircraft changes significantly. Since the cross-sectional area of the lower box 124 along the liquid storage cavity 120 is small, the movement amount of the liquid medicine per unit volume is reduced. When the flight attitude of the aircraft changes, the liquid medicine in the lower box 124 can reduce the sloshing phenomenon, which is convenient for controlling the stable flight of the aircraft.

In other embodiments, interconnected grids may be provided in the container body 12 to reduce the sloshing of the liquid medicine, thereby simplifying the production process of the liquid container 10 and reducing the production cost of the liquid container 10 .

Please refer to Figures 8 and 10. Further, the upper box 126 and the lower box 124 form a "T" shape or an inverted "L" shape. The upper box 126 and the lower box 124 are stacked up and down, and roughly form a "T" shape or an inverted "L" shape. On the one hand, the lower box 124 is inserted into the fuselage 30 and the upper box 126 is supported on the fuselage 30. On the other hand, the cross-sectional area of the lower box 124 is smaller than the cross-sectional area of the upper box 126, so as to reduce the sloshing phenomenon of the liquid in the liquid storage cavity 120 during the operation of the aircraft and ensure the stability of the flight of the aircraft.

Please refer to Figure 10. Further, the bottom wall of the upper box body 126, the side wall of the lower box body 124, and the plane passing through one end of the bottom wall of the upper box body 126 away from the lower box body 124 and the bottom end of the side wall of the lower box body 124 form a receiving space (not shown), and the liquid outlet 122 is located in the receiving space. It can be understood that when the liquid container 10 is placed on the bottom surface, one end of the bottom wall of the upper box body 126 away from the lower box body 124 and the bottom end of the side wall of the lower box body 124 are supported on the ground respectively, and the liquid outlet 122 is located in the receiving space and does not directly contact the ground.

Please refer to FIGS. 1 to 10 . Further, the fuselage 30 includes a nose 32 having a support plate 34 and a frame 35 fixedly connected to the support plate 34 and enclosed with the support plate 34 to form a through space 36. The lower box 124 is inserted into the through space 36, and the upper box 126 is overlapped on the support plate 34 and buckled on the support plate 34. The upper box 126 is overlapped on the support plate 34 and buckled with the support plate 34, and the lower box 124 is inserted into the through space 36 to insert the liquid container 10 into the fuselage 30. In this way, when the aircraft lands on the ground, due to the support of the support plate 34, the liquid outlet 122 set at the bottom of the lower box 124 will not directly contact the ground, thereby protecting the liquid outlet 122.

Please refer to Figures 8 and 10. Further, the liquid outlet 122 is arranged on the side of the upper box 126 connected to the lower box 124, and the liquid container 10 also includes a counterweight 14 sunk at the bottom of the lower box 124 and a liquid infusion hose 15 connecting the counterweight 14 and the liquid outlet 122. The liquid outlet 122 and the lower box 124 are arranged on the same side of the upper box 126. Since the cross-sectional area of the lower box 124 is smaller than that of the upper box 126, the height of the lower box 124 can play a certain protective role on the liquid outlet 122, so that the liquid outlet 122 is protected during the process of lifting the liquid container 10, and the liquid outlet 122 is prevented from being deformed and causing leakage.

In order to spray all the medicine liquid in the lower box 124, the infusion hose 15 is used to connect the liquid outlet 122 and the counterweight 14 at the bottom of the lower box 124. When the medicine liquid in the liquid storage cavity 120 gradually decreases, the infusion hose 15 transports the medicine liquid at the bottom of the lower box 124 to the liquid outlet 122. The counterweight 14 is provided so that one end of the infusion hose 15 is always maintained at the bottom of the lower box 124 under the action of gravity.

In this embodiment, the weight component 14 and the infusion hose 15 are made of corrosion-resistant materials. For example, the infusion hose 15 may be made of plastic, and the component may be made of ceramic or alloy.

Please refer to Figures 8 to 10. Further, the container body 12 also includes a handle 128 integrally formed on the upper box body 126. The handle 128 and the lower box body 124 are respectively located on opposite sides of the upper box body 126, and the pulling direction of the handle 128 coincides with the center of gravity direction of the liquid storage cavity 120. The liquid container 10 is provided with the handle 128 so that the liquid container 10 can be quickly inserted into the body 30 or removed from the body 30 by pulling the handle 128, which is convenient for disassembly and assembly. The handle 128 is integrally formed with the upper box body 126, which simplifies the processing of the liquid container 10 and ensures the strength of the liquid container 10. The handle 128 is disposed at the middle position of the width direction of the upper surface of the upper box body 126, so that the pulling direction of the handle 128 coincides with the center of gravity direction of the liquid storage cavity 120 formed by the lower box body 124 and the upper box body 126, so as to ensure that the liquid container 10 can be inserted into or taken out of the body 30 along the gravity direction during the process of pulling the handle 128. The width direction refers to the left-right direction in the figure.

Please refer to Figures 8 to 10. Further, the liquid injection port 121 is provided on the same side of the upper box body 126 together with the handle 128 along the length direction of the handle 128, and the axial direction of the liquid outlet 122 coincides with the center of gravity direction of the container body 12. It can be understood that the liquid outlet 122 is provided at the middle position in the width direction of the lower surface of the upper box body 126, so that the axial direction of the liquid outlet 122 coincides with the center of gravity direction of the container body 12, and preferably, the axial direction of the liquid outlet 122 coincides with the lifting direction of the handle 128.

Preferably, when the lower box body 124 and the upper box body 126 are symmetrical structures, the handle 128, the liquid outlet 122, the lower box body 124 and the upper box body 126 have the same symmetry plane, and the symmetry plane is located in the middle position of the upper box body 126 in the width direction.

Please refer to FIG8 . Further, a first liquid level observation belt 1240 for observing the water level in the liquid storage cavity 120 is provided on one side of the lower box 124 along its height direction, and/or a second liquid level observation belt 1260 for observing the water level in the liquid storage cavity 120 is provided on one side of the upper box 126 along its height direction. It should be noted that the height direction refers to the up-down direction in the figure. The liquid container 10 is provided with the first liquid level observation belt 1240 on the lower box 124 and/or the second liquid level observation belt 1260 on the upper box 126, so as to observe the liquid level in the liquid storage cavity 120, so as to judge whether it is necessary to pour liquid medicine into the liquid storage cavity 120 when the aircraft stops operating. In addition, it can also allow the user to judge the volume of liquid medicine when pouring liquid medicine into the liquid storage cavity 120.

Preferably, a volume scale of corresponding volume is marked near the first liquid level observation tape 1240 , and similarly, a volume scale of corresponding volume is marked near the second liquid level observation tape 1260 , so as to intuitively see the remaining amount of liquid medicine in the liquid storage cavity 120 .

Please refer to Figures 8 and 10. Further, the liquid container 10 also includes a water stop valve assembly 16 screwed into the liquid injection port 121 and a water outlet valve 18 screwed onto the liquid outlet 122. The liquid container 10 is screwed onto the liquid injection port 121, and after the water stop valve assembly 16 is screwed out, the liquid storage cavity 120 can be filled with liquid medicine through the liquid injection port 121. After the liquid medicine is fully filled, the water stop valve assembly 16 is screwed onto the liquid injection port 121, which prevents the liquid medicine from flowing out of the liquid injection port 121 and maintains the balance of air pressure inside and outside the liquid storage cavity 120, thereby ensuring that the liquid medicine in the liquid storage cavity 120 can be smoothly discharged from the liquid outlet 122.

In this embodiment, the water stop valve assembly 16 includes a water stop and air permeable valve to prevent liquid leakage and a screw cap that cooperates with the liquid injection port 121. In order to ensure that the water stop and air permeable valve is fixed to the liquid injection port 121, the water stop and air permeable valve is first clamped on the screw cap, and the screw cap is then broken by the thread and screwed on the liquid injection port 121, so that the water stop and air permeable valve is set in the liquid injection port 121.

The water outlet valve 18 is screwed onto the liquid outlet 122, and can automatically close the liquid outlet 122 when the liquid container 10 is not in use, thereby preventing leakage of the liquid in the liquid storage cavity 120. Preferably, the water outlet valve 18 is an automatic water outlet and water stop valve.

Please refer to Figures 1 to 10, the aircraft provided in the embodiment of the present invention includes a fuselage 30, a liquid container 10 connected to the fuselage 30, a plurality of wing assemblies 40 circumferentially spaced around the fuselage 30, and a nozzle 50 installed on each of the wing assemblies 40 and connected to the liquid container 10 for spraying liquid medicine, the liquid container 10 is the above-mentioned liquid container 10, and the nozzle 50 is connected to the liquid outlet 122. The liquid container 10 in this embodiment has the same structure as the liquid container 10 in the above-mentioned embodiments, and has the same function, which will not be repeated here.

In this embodiment, the liquid container 10 is detachably connected to the body 30 to facilitate quick disassembly and assembly, thereby greatly improving disassembly and assembly efficiency.

The aircraft is connected to the liquid outlet 122 of the liquid container 10 through the nozzle 50 to spray the liquid in the liquid storage cavity 120 along the liquid outlet 122 and the nozzle 50 to the required spraying area to meet the liquid spraying requirements.

The aircraft is provided with the wing assembly 40 to provide lifting power. The power of the nozzle 50 can be provided by the wing assembly 40 or can be driven by a separate driving motor.

Please refer to FIG. 1, FIG. 2 and FIG. 6. Further, the fuselage 30 includes a nose 32 having a support plate 34 and a frame 35 fixedly connected to the support plate 34 and enclosed with the support plate 34 to form a through space 36. The lower box 124 is inserted into the through space 36, and the upper box 126 is overlapped on the support plate 34 and buckled on the support plate 34. It can be understood that the nose 32 and the frame 35 are arranged along the front-to-back direction in the figure, the nose 32 is located in front of the forward direction of the aircraft, and the frame 35 is arranged at the rear end of the support plate 34. The frame 35 is fixedly connected to the nose 32 and is also fixed to the support plate 34. The frame 35 is a vertically through structure to form the through space 36. The main structure of the frame 35 includes two strip-shaped mounting plates arranged at the rear end of the support plate 34 and symmetrically arranged with respect to the left and right directions, and a connecting plate connected to the rear ends of the two mounting plates. The connecting plate, the two mounting plates and the support plate 34 enclose the through space 36. The width direction of the through space 36 is slightly larger than the width of the lower box 124, so that the lower surface of the upper box 126 can overlap the support plate 34.

In this embodiment, the main circuit and main control components of the aircraft may be disposed on the nose 32 .

In this embodiment, the aircraft further includes a crossbeam erected above the through space 36 to reduce the through space 36 to a size in which the lower box 124 can be inserted, thereby preventing the liquid container 10 from shaking in the through space 36 .

Please refer to Figures 1 to 8. Further, one of the upper box 126 and the supporting plate 34 is provided with a pair of fasteners 24 and the other is provided with a pair of fastening grooves 22 that cooperate with the fasteners 24. The aircraft cooperates with the fasteners 24 through the fastening grooves 22 to mount the liquid container 10 on the fuselage 30. That is, the liquid container 10 is provided with the fasteners 24 and the fuselage 30 is provided with the fastening grooves 22, or the liquid container 10 is provided with the fastening grooves 22 and the fuselage 30 is provided with the fasteners 24.

When installing the liquid container 10 on the body 30, the liquid container 10 can be fixed on the body 30 by snapping the snap member 24 into the snap groove 22, and the liquid container 10 can be accurately installed and positioned at a predetermined position on the body 30, so that the installation and removal of the liquid container 10 are convenient and quick, thereby improving the working efficiency.

When the liquid medicine needs to be replaced after a single operation of the aircraft is completed, the liquid container 10 can be quickly removed from the fuselage 30, and the liquid container 10 pre-filled with liquid medicine can be quickly installed on the fuselage 30, thereby saving the extra time for filling liquid medicine after the aircraft lands, and the installation and removal of the liquid container 10 are also convenient and quick, thereby improving the operating efficiency of the aircraft.

Please refer to FIGS. 1 to 8 , further, each of the clamping grooves 22 has a recessed portion 220 at its bottom, and each of the clamping members 24 has a protruding strip 240 protruding toward the inside of the clamping groove 22 and embedded in the recessed portion 220. The aircraft is accommodated in the clamping groove 22 by the clamping members 24, so that the liquid container 10 is positioned on the supporting plate 34. Further, the recessed portion 220 is recessed at the bottom of the clamping groove 22, and the protruding strip 240 is protruding on the clamping member to be buckled in the recessed portion 220, so that the clamping member 24 is firmly buckled in the clamping groove 22, thereby fixing the liquid container 10 on the supporting plate 34.

Please refer to Figures 1, 2 and 8. Further, the two snap-fit grooves 22 are symmetrically arranged on opposite sides of the upper box 126, and the two snap-fit members 24 are fixedly connected to the support plate 34 and are located on both sides of the upper box 126. The snap-fit grooves 22 are arranged on opposite sides of the upper box 126 to symmetrically position the upper box 126, ensuring that the positioning force and the limit position are balanced and balanced. Similarly, the snap-fit members 24 are located on both sides of the upper box 126 and snap-fit with the snap-fit grooves 22.

Please refer to FIGS. 1 to 5 , further, the buckle 24 includes a support seat 242 fixedly connected to the support plate 34 and a support frame 244 protruding along the support seat 242 toward a side away from the support plate 34 and received in the clamping groove 22, the surface of the support frame 244 facing the upper box 126 is parallel to the outer surface of the upper box 126, and the protruding strip 240 is protruding on the surface of the support frame 244. Preferably, the support seat 242 can be locked on the support plate 34 by bolt connection, or fixed on the support plate 34 by welding, so that the support seat 242 is fixed on the support plate 34. The support frame 244 protrudes along the support seat 242 and is received in the clamping groove 22, and the protruding strip 240 is protruding on the surface of the support frame 244 to be buckled in the lower concave portion 220, so that the buckle is firmly buckled in the clamping groove 22.

Please refer to Fig. 8 and Fig. 9, further, the clamping groove 22 has an introduction port 222 for introducing the support frame 244, and an introduction surface 224 for introducing the protruding strip 240 into the concave portion 220 is formed between the introduction port 222 and the concave portion 220. The introduction port 222 is close to the lower surface of the upper box 126, so that when the support frame 244 is matched with the clamping groove 22, the end of the support frame 244 is inserted into the clamping groove 22 along the introduction port 222, and the protruding strip 240 is clamped into the concave portion 220 along the introduction surface 224, so as to ensure the smoothness of the clamping.

In this embodiment, the protruding strip 240 is strip-shaped and is arranged along the front-rear direction of the fuselage 30 , or in other words, the protruding strip 240 is arranged along a direction perpendicular to the insertion direction of the lower box body 124 .

8 and 9, further, the introduction surface 224 is an arc surface protruding outward. Protruding outward refers to a direction away from the center of the upper box body 126. The protruding strip 240 can be smoothly buckled into the lower concave portion 220 along the introduction surface 224, so that the positioning and installation of the liquid container 10 are faster and more accurate.

Referring to FIGS. 1 to 7 , the fuselage 30 further includes a pair of rolling assemblies 38 that roll with both sides of the lower box 124 when the lower box 124 is inserted into the through space 36, and each rolling assembly 38 is installed on the inner side of the frame 35 and accommodated in the through space 36. The aircraft is provided with the rolling assemblies 38 that roll with the lower box 124 to avoid friction between the lower box 124 and the frame 35 to damage the lower box 124, and can prevent the liquid container 10 from shaking during operation.

Please refer to Figures 1 to 5. Further, each rolling assembly 38 includes a fixed bracket 380 fixed to the inner side of the frame 35 and at least one roller 382 rotatably connected to the fixed bracket 380 and in rolling contact with the surface of the lower box 124, and the axial direction of the roller 382 is perpendicular to the insertion direction of the lower box 124. The fixed bracket 380 is locked and fixed to the inner side of the frame 35 by screws, and the roller 382 is rotatably connected to the fixed bracket 380 and in rolling contact with the surface of the lower box 124 to avoid friction between the lower box 124 and the frame 35.

Preferably, the entire fixed bracket 380 can be located entirely on the inner wall of the frame 35, and in this case, the roller 382 is located inside the frame 35; or the upper part of the fixed bracket 380 extends upward and is higher than the frame 35, and in this case, the roller 382 can be installed at a position higher than the frame 35, thereby achieving rolling cooperation between the roller 382 and the lower box body 124 to avoid friction between the lower box body 124 and the frame 35 and damage to the lower box body 124.

Please refer to FIG. 5 , further, the number of the rollers 382 in each rolling assembly 38 is two or more, and each roller 382 is arranged in parallel and spaced along the insertion direction of the lower box 124. It can be understood that each roller 382 is arranged in parallel and spaced along the up and down direction in the figure. The distance between the rollers 382 on the two rolling assemblies 38 is slightly larger than the size of the lower box 124 in the left and right direction, thereby facilitating the installation of the lower box 124 between the two sets of rolling assemblies 38.

Please refer to FIG. 6 and FIG. 7 . Further, the aircraft also includes at least one guide rod 60 disposed on the fuselage 30 and close to the side of the nose 32. The guide rod 60 is disposed along the insertion direction of the lower box 124, and stops at the front surface of the lower box 124 when the lower box 124 is inserted into the through space 36. Preferably, the guide rod 60 is extended along the up-down direction of the inner side of the fuselage 30. The number of the guide rods 60 can be one or more. For example, two guide rods 60 are disposed on the fuselage 30, and the two guide rods 60 are spaced apart along the left and right sides of the lower box 124, and stop at the front surface of the lower box 124 when the lower box 124 is inserted into the through space 36 from top to bottom. When the liquid container 10 filled with liquid medicine is installed on the body 30, since the lower box 124 is heavy, the lower box 124 is easy to tilt forward when the handle 128 is held. The stopping effect of the guide rod 60 can prevent the lower box 124 from tilting forward when the liquid container 10 is installed, thereby facilitating the fastener 24 to quickly and accurately cooperate with the snap-in groove 22, thereby quickly positioning and installing the liquid container 10 on the body 30.

Please refer to Figures 1, 2 and 6. Further, each of the wing assemblies 40 includes an arm 42 mounted on the fuselage 30, a rotor 44 mounted at the end of the arm 42 and a driving device 45. The driving device 45 drives the rotor 44 to rotate, and the nozzle 50 is arranged directly below the driving device 45. It can be understood that the end of each arm 42 is provided with a rotor 44 and a driving device 45 for driving the rotor 44 to rotate, such as a motor. The rotor 44 can be connected to the motor shaft of the motor so that the rotor 44 rotates to drive the aircraft to fly. Preferably, the number of the wing assemblies 40 is 4 groups, that is, the aircraft is a quad-rotor aircraft. Of course, the number of the wing assemblies 40 can also be other numbers, such as a six-rotor aircraft.

In this embodiment, the spray head 50 can be arranged on the machine arm 42 through a threaded connection structure, or the spray head 50 can also be arranged on the machine arm 42 through a snap-fit structure. In one embodiment of the present invention, the number of the spray heads 50 is the same as the number of the machine arms 42, and the plurality of spray heads 50 are respectively detachably arranged at the lower part of the ends of the plurality of machine arms 42, for example, the spray heads 50 can be arranged directly below the driving device 45. Thus, the plurality of spray heads 50 are dispersedly arranged, so the requirements for spraying the liquid medicine are met, and the liquid spraying is more uniform.

Please refer to Figures 1, 2 and 6. Further, the aircraft further includes a pair of supporting legs 70 fixedly mounted on the fuselage 30 and used to suspend the fuselage 30 above the ground. The aircraft is provided with the supporting legs 70 so that when the aircraft lands and parks on the ground, the fuselage 30 does not directly contact the ground, thereby preventing damage to the fuselage 30. The supporting legs 70 are used to support and protect the aircraft.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims (18)

1. An aircraft, comprising a fuselage, a liquid container connected to the fuselage, a plurality of wing assemblies circumferentially spaced around the fuselage, and a spray head mounted on the wing assemblies and in communication with the liquid container for spraying a liquid;

The liquid container comprises a container main body, wherein the container main body comprises an upper box body and a lower box body, the upper box body is provided with a first cavity, the lower box body is provided with a second cavity communicated with the first cavity, and the first cavity and the second cavity are used for storing liquid medicine;

The liquid container is detachably connected to the machine body, the upper box body is provided with a supporting part, the supporting part is used for supporting the machine body, and when the liquid container is installed on the machine body, the lower box body is inserted into the machine body, and then the upper box body is supported on the machine body.

2. The aircraft of claim 1, wherein the cross-sectional area of the lower tank in a top view of the fuselage is smaller than the cross-sectional area of the upper tank.

3. The aircraft of claim 2, wherein the support portion is provided at a bottom wall of the upper case and at a portion of the upper case having a larger cross-sectional area than the lower case.

4. The aircraft of claim 1, wherein the support is provided adjacent the lower tank at a bottom wall of the upper tank.

5. The aircraft of claim 1, wherein the support portion is part of the upper case, the upper case being supported to the fuselage by the support portion.

6. The vehicle of claim 1, wherein when the liquid container contains liquid medicine to be sprayed, the upper case is abutted against the body under the gravity action of the liquid medicine to be sprayed.

7. The aircraft of claim 1, wherein the upper and lower tanks are stacked one above the other and generally form a "T" shape or an inverted "L" shape.

8. The aircraft of claim 1, wherein the fuselage includes a frame that is a through-up-down structure to form a through-space, the lower box being inserted into the through-space.

9. The aircraft of claim 8, wherein the fuselage includes a nose, the nose and the frame being disposed in a fore-aft direction, the nose being forward of the direction of travel of the aircraft, the frame being fixedly coupled to the nose.

10. The aircraft according to claim 9, wherein the nose has a support plate, and the frame includes two strip-shaped mounting plates provided at the rear end of the support plate and symmetrically provided with respect to the left-right direction, and a connection plate connected to the rear ends of the two mounting plates, the connection plate, the two mounting plates, and the support plate enclosing the through space.

11. The aircraft of claim 1 wherein the upper housing is provided with a snap-fit structure for snap-fit connection with the fuselage.

12. The aircraft of claim 11, wherein the fuselage includes a nose having a support panel, and wherein the upper shell overlaps and snaps onto the support panel.

13. The aircraft of claim 12, wherein one of the upper case and the support panel is provided with a pair of snap-in members and the other is provided with a pair of snap-in grooves that mate with the snap-in members.

14. The aircraft of claim 1, wherein the liquid outlet of the liquid container is provided in a bottom wall of the upper tank adjacent to a junction of the upper tank and the lower tank or in a side wall of the lower tank adjacent to a junction of the upper tank and the lower tank.

15. The vehicle of claim 14, wherein the liquid container further comprises a weight member disposed at the bottom of the lower tank and a fluid hose communicating the weight member with the fluid outlet.

16. The aircraft of claim 1, further comprising at least one guide bar provided on the fuselage and adjacent to one side of the nose, the guide bar being provided along an insertion direction of the lower case and stopping at a front surface of the lower case when the lower case is inserted into the through space.

17. The aircraft of claim 1, wherein the upper and lower tanks are integrally formed.

18. The aircraft of claim 1, wherein the lower tank extends downwardly from a bottom wall of the upper tank.