CN210479011U - Aircraft hydraulic leveling device - Google Patents
Aircraft hydraulic leveling device Download PDFInfo
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- CN210479011U CN210479011U CN201921454816.6U CN201921454816U CN210479011U CN 210479011 U CN210479011 U CN 210479011U CN 201921454816 U CN201921454816 U CN 201921454816U CN 210479011 U CN210479011 U CN 210479011U
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Abstract
The utility model provides an aircraft hydraulic leveling device, which belongs to the technical field of aircraft and comprises a body, wherein the bottom of the body is provided with a plurality of support legs, the edge of the upper part of the body is provided with a plurality of driving loop bars, the upper part of the driving loop bars is provided with paddles, the upper part of the body is connected with a liquid storage tank through a plurality of electro-hydraulic servo cylinders, a sensor for monitoring the balance state of the body and a controller for controlling the expansion of the electro-hydraulic servo cylinders are arranged inside the body, and the sensor is electrically connected with the controller; the bottom of the liquid storage tank is provided with a first joint, and the first joint is connected with a liquid discharge pipe. The embodiment of the utility model provides an in, carry out balance adjustment to the liquid reserve tank through electronic hydraulic servo jar, the effectual aircraft of having avoided when flying, the influence liquid reserve tank that receives the air current follows the fuselage and inclines, leads to the inside liquid repacking liquid reserve tank wall of liquid reserve tank, causes the aircraft unstability, has improved the security of aircraft at the plant protection in-process.
Description
Technical Field
The utility model belongs to the technical field of the aircraft specifically an aircraft hydraulic pressure leveling device.
Background
Plant protection unmanned aerial vehicle is the unmanned aircraft who is used for agriculture and forestry plant protection operation, flies the accuse through ground remote control or navigation, realizes spraying the operation, can spray medicament, seed, powder etc..
Current plant protection unmanned aerial vehicle is carrying out the medicament when spraying, because the change of air current and unmanned aerial vehicle when the flight turns to, lead to unmanned aerial vehicle to produce the slope easily, the liquid medicine that its liquid reserve tank inside was stored then can produce and rock, leads to the striking to the liquid reserve tank wall, causes unmanned aerial vehicle unstability easily, leads to unmanned aerial vehicle to crash, consequently, current plant protection unmanned aerial vehicle has the not enough defect of security.
SUMMERY OF THE UTILITY MODEL
The technical problem to be solved by the embodiments of the present invention is to provide an aircraft hydraulic leveling device.
In order to solve the technical problem, the utility model provides a following technical scheme:
the aircraft hydraulic leveling device comprises a machine body, wherein a plurality of supporting legs are arranged at the bottom of the machine body, a plurality of driving sleeve rods are arranged at the edge of the upper part of the machine body, blades are arranged at the upper parts of the driving sleeve rods, the upper part of the machine body is connected with a liquid storage tank through a plurality of electric hydraulic servo cylinders, a sensor for monitoring the balance state of the machine body and a controller for controlling the electric hydraulic servo cylinders to stretch are arranged in the machine body, and the sensor is electrically connected with the controller; the bottom of the liquid storage tank is provided with a first joint, a liquid discharge pipe is connected to the first joint, and one end, far away from the first joint, of the liquid discharge pipe penetrates through the machine body and is connected with a second joint on the upper portion of the spraying disc.
As a further improvement of the utility model: the liquid reserve tank is the rectangle structure, electronic hydraulic servo jar sets up four groups, and the slope sets up respectively in liquid reserve tank bottom corner.
As a further improvement of the utility model: the upper part of the electric hydraulic servo cylinder is connected to the liquid storage tank through a first articulated part, and the lower part of the electric hydraulic servo cylinder is connected to the machine body through a second articulated part.
As a further improvement of the utility model: the first hinge part and the second hinge part are of the same structure and respectively comprise a rotating base and a rotating rod penetrating through the rotating base, the upper position and the lower position of the electric hydraulic servo cylinder are respectively connected with an end plate, and a through hole matched with the rotating rod is formed in the end plate.
As a further improvement of the present invention: the drain pipe is a hose, and the joint of the drain pipe and the first joint and the joint of the drain pipe and the second joint are fastened by adopting binding wires.
As a further improvement of the present invention: and a guide cylinder is also arranged outside the liquid discharge pipe.
As a further improvement of the present invention: the upper part of the spray disc is connected to the bottom of the machine body through a suspension arm.
Compared with the prior art, the beneficial effects of the utility model are that:
the embodiment of the utility model provides an in, carry out balance adjustment to the liquid reserve tank through electronic hydraulic servo jar, the effectual aircraft of having avoided when flying, the influence liquid reserve tank that receives the air current follows the fuselage and inclines, leads to the inside liquid repacking liquid reserve tank wall of liquid reserve tank, causes the aircraft unstability, has improved the security of aircraft at the plant protection in-process.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft hydraulic leveling device;
FIG. 2 is an enlarged view of a hydraulic leveling device for an aircraft at A;
FIG. 3 is an enlarged view of a hydraulic leveling device for an aircraft at B;
FIG. 4 is a schematic structural diagram of an electro-hydraulic servo cylinder in an aircraft hydraulic leveling device;
in the figure: 1-supporting leg, 2-machine body, 3-driving loop bar, 4-paddle, 5-liquid storage tank, 6-first connector, 7-binding wire, 8-liquid discharge pipe, 9-guide cylinder, 10-suspension arm, 11-second connector, 12-spraying disc, 13-rotating base, 14-rotating rod, 15-electric hydraulic servo cylinder, 16-end plate and 17-through hole.
Detailed Description
The technical solution of the present patent will be described in further detail with reference to the following embodiments.
Reference will now be made in detail to embodiments of the present patent, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present patent and are not to be construed as limiting the present patent.
In the description of this patent, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for the convenience of describing the patent and for the simplicity of description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the patent.
In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.
Example 1
Referring to fig. 1-4, the present embodiment provides an aircraft hydraulic leveling device, including a fuselage 2, where the bottom of the fuselage 2 is provided with a plurality of legs 1, the edge of the upper portion of the fuselage 2 is provided with a plurality of driving rods 3, and the upper portion of the driving rods 3 is provided with blades 4; the upper part of the machine body 2 is connected with a liquid storage tank 5 through a plurality of electro-hydraulic servo cylinders 15, a sensor for monitoring the balance state of the machine body 2 and a controller for controlling the electro-hydraulic servo cylinders 15 to stretch are arranged in the machine body 2, and the sensor is electrically connected with the controller; the bottom of the liquid storage tank 5 is provided with a first connector 6, the first connector 6 is connected with a liquid discharge pipe 8, and one end of the liquid discharge pipe 8, which is far away from the first connector 6, penetrates through the machine body 2 and is connected with a second connector 11 on the upper portion of the spray disc 12.
When the aircraft flies, the aircraft is easy to incline due to the influence of airflow, liquid in the liquid storage tank 5 is easy to shake, the aircraft is unstable in the air, the horizontal condition of the aircraft is monitored in real time through the sensor, when the aircraft inclines, the sensor transmits an inclination signal of the aircraft to the controller, the controller controls the electric hydraulic servo cylinder 15 to operate, the liquid storage tank 5 is adjusted through the electric hydraulic servo cylinder 15, the liquid storage tank 5 is kept horizontal, the stability of the liquid storage tank 5 is guaranteed, the liquid in the liquid storage tank 5 is prevented from shaking, the wall of the liquid storage tank 5 is impacted, and the stable flight of the aircraft is further guaranteed; the liquid in the liquid storage tank 5 is discharged to the spraying disc 12 through the liquid discharge pipe 8 and is sprayed out of the spraying disc 12, so that the plant protection function of the aircraft is realized; it should be noted that the types and parameters of the above sensors, controllers, and the electrohydraulic servo cylinder 15, and the control circuit for implementing signal transmission all belong to the prior art, and are not described in detail in this embodiment.
The liquid reserve tank 5 is the rectangle structure, electronic hydraulic servo cylinder 15 sets up four groups, and the slope sets up respectively in liquid reserve tank 5 bottom corner.
The upper part of the electro-hydraulic servo cylinder 15 is connected to the liquid storage tank 5 through a first hinge part, and the lower part of the electro-hydraulic servo cylinder 15 is connected to the machine body 2 through a second hinge part.
Through the arrangement of the first hinge part and the second hinge part, when the liquid storage box 5 is adjusted by the electric hydraulic servo cylinder 15, the electric hydraulic servo cylinder 15 can adapt to the change of the relative point positions of the liquid storage box 5 and the electric hydraulic servo cylinder 15, adaptive rotation is made, the adjustment range of the liquid storage box 5 is convenient to increase, and the liquid storage box 5 can be kept horizontal when the aircraft is greatly inclined.
The first hinge part and the second hinge part are of the same structure and respectively comprise a rotating base 13 and a rotating rod 14 penetrating through the rotating base 13, end plates 16 are respectively connected to the upper position and the lower position of the electric hydraulic servo cylinder 15, and through holes 17 matched with the rotating rods 14 are formed in the end plates 16.
During the installation, fix rotating basis 13 respectively in liquid reserve tank 5 bottom and fuselage 2 upper portion, place electronic hydraulic servo cylinder 15 in between liquid reserve tank 5 and the fuselage 2 again, utilize bull stick 14 to be connected rotating basis 13 and end plate 16, realize the rotation of electronic hydraulic servo cylinder 15 through bull stick 14.
The drain pipe 8 is a hose, the joint of the drain pipe 8 and the first joint 6 and the joint of the drain pipe 8 and the second joint 11 are fastened by adopting the binding wire 7, and the drain pipe 8 is a hose, so that when the liquid storage tank 5 is subjected to posture adjustment, the drain pipe 8 can be extended or shortened in adaptability, and normal liquid drainage of the aircraft is prevented from being influenced.
The upper part of the spray disk 12 is connected to the bottom of the machine body 2 through a suspension arm 10.
The working principle of the embodiment is as follows: when the aircraft flies, the aircraft is easy to incline due to the influence of airflow, liquid in the liquid storage tank 5 is easy to shake, the aircraft is unstable in the air, the horizontal condition of the aircraft is monitored in real time through the sensor, when the aircraft inclines, the sensor transmits an inclination signal of the aircraft to the controller, the controller controls the electric hydraulic servo cylinder 15 to operate, the liquid storage tank 5 is adjusted through the electric hydraulic servo cylinder 15, the liquid storage tank 5 is kept horizontal, the stability of the liquid storage tank 5 is guaranteed, the liquid in the liquid storage tank 5 is prevented from shaking, the wall of the liquid storage tank 5 is impacted, and the stable flight of the aircraft is further guaranteed; the liquid in the liquid storage tank 5 is discharged to the spraying disc 12 through the liquid discharge pipe 8 and is sprayed out of the spraying disc 12, so that the plant protection function of the aircraft is realized.
Through the arrangement of the first hinge part and the second hinge part, when the liquid storage box 5 is adjusted by the electric hydraulic servo cylinder 15, the electric hydraulic servo cylinder 15 can adapt to the change of the relative point positions of the liquid storage box 5 and the electric hydraulic servo cylinder 15, adaptive rotation is made, the adjustment range of the liquid storage box 5 is convenient to increase, and the liquid storage box 5 can be kept horizontal when the aircraft is greatly inclined.
During the installation, fix rotating basis 13 respectively in liquid reserve tank 5 bottom and fuselage 2 upper portion, place electronic hydraulic servo cylinder 15 in between liquid reserve tank 5 and the fuselage 2 again, utilize bull stick 14 to be connected rotating basis 13 and end plate 16, realize the rotation of electronic hydraulic servo cylinder 15 through bull stick 14.
Example 2
Referring to fig. 3, in the present embodiment of the hydraulic leveling device for an aircraft, compared with embodiment 1, a guide cylinder 9 is further disposed outside the drainage pipe 8, and the drainage pipe 8 is protected by the guide cylinder 9, so that the fracture of the drainage pipe 8 caused by friction between the drainage pipe 8 and the fuselage 2 is avoided.
The embodiment of the utility model provides an in, carry out balance adjustment to liquid reserve tank 5 through electronic hydraulic servo cylinder 15, effectually avoided the aircraft when flying, the influence liquid reserve tank 5 that receives the air current follows fuselage 2 and inclines, leads to 5 inside liquid repacking liquid reserve tank 5 tank walls of liquid reserve tank, causes the aircraft unstability, has improved the security of aircraft at the plant protection in-process.
Although the preferred embodiments of the present patent have been described in detail, the present patent is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present patent within the knowledge of those skilled in the art.
Claims (7)
1. The aircraft hydraulic leveling device comprises a machine body (2), wherein a plurality of supporting legs (1) are arranged at the bottom of the machine body (2), a plurality of driving loop bars (3) are arranged at the edge of the upper part of the machine body (2), and paddles (4) are arranged at the upper part of the driving loop bars (3), and the aircraft hydraulic leveling device is characterized in that the upper part of the machine body (2) is connected with a liquid storage tank (5) through a plurality of electric hydraulic servo cylinders (15), a sensor for monitoring the balance state of the machine body (2) and a controller for controlling the electric hydraulic servo cylinders (15) to stretch are arranged in the machine body (2), and the sensor is electrically connected with the controller; the liquid storage tank is characterized in that a first connector (6) is arranged at the bottom of the liquid storage tank (5), a liquid discharge pipe (8) is connected onto the first connector (6), and one end, far away from the first connector (6), of the liquid discharge pipe (8) penetrates through the machine body (2) and is connected with a second connector (11) on the upper portion of the spraying disc (12).
2. Hydraulic aircraft levelling device according to claim 1, characterized in that the tank (5) is of rectangular configuration and the electrohydraulic servo cylinders (15) are arranged in four groups, each inclined at the bottom corner of the tank (5).
3. Hydraulic levelling device for aircraft according to claim 1 or 2, characterized in that the upper part of the electrohydraulic servo cylinder (15) is connected to the tank (5) by a first articulated joint and the lower part of the electrohydraulic servo cylinder (15) is connected to the fuselage (2) by a second articulated joint.
4. The hydraulic leveling device for the aircraft according to claim 3, wherein the first hinge part and the second hinge part are the same in structure and comprise a rotating base (13) and a rotating rod (14) penetrating through the rotating base (13), the upper and lower positions of the electro-hydraulic servo cylinder (15) are connected with end plates (16), and through holes (17) matched with the rotating rod (14) are formed in the end plates (16).
5. The aircraft hydraulic leveling device according to claim 1, wherein the drain pipe (8) is a hose, and the joint of the drain pipe (8) and the first joint (6) and the joint of the drain pipe (8) and the second joint (11) are fastened by using a binding wire (7).
6. Hydraulic levelling device for aircraft according to claim 1 or 5, characterized in that the drain pipe (8) is externally provided with a guide cylinder (9).
7. Hydraulic aircraft levelling device according to claim 1, characterized in that the spray disk (12) is connected at its upper part to the fuselage (2) bottom by means of a boom (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921454816.6U CN210479011U (en) | 2019-09-03 | 2019-09-03 | Aircraft hydraulic leveling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921454816.6U CN210479011U (en) | 2019-09-03 | 2019-09-03 | Aircraft hydraulic leveling device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210479011U true CN210479011U (en) | 2020-05-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921454816.6U Active CN210479011U (en) | 2019-09-03 | 2019-09-03 | Aircraft hydraulic leveling device |
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| CN (1) | CN210479011U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114617501A (en) * | 2022-03-18 | 2022-06-14 | 北京石头世纪科技股份有限公司 | Cleaning apparatus and control method thereof |
-
2019
- 2019-09-03 CN CN201921454816.6U patent/CN210479011U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114617501A (en) * | 2022-03-18 | 2022-06-14 | 北京石头世纪科技股份有限公司 | Cleaning apparatus and control method thereof |
| CN114617501B (en) * | 2022-03-18 | 2023-09-12 | 北京石头世纪科技股份有限公司 | Cleaning apparatus and control method thereof |
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