CN214165310U - Aircraft with a flight control device - Google Patents

Abstract

An embodiment of the utility model provides an aircraft relates to plant protection unmanned aerial vehicle field. The aircraft comprises an aircraft body and a spray head connected with the aircraft body; the body is provided with at least three touchdown points for touchdown, and the touchdown surfaces are limited by the at least three touchdown points; wherein, the spray head is positioned above the ground; among the at least three touchdown points, the angle between the connecting line of the touchdown point closest to the spray head and the bottom of the spray head and the touchdown surface is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees. The aircraft can reduce the probability of spraying the agent to the body when spraying.

Description

Aircraft with a flight control device

Technical Field

The utility model relates to a plant protection unmanned aerial vehicle field particularly, relates to an aircraft.

Background

Plant protection unmanned aerial vehicle, also called unmanned vehicles, is the unmanned aircraft who is used for agriculture and forestry plant protection operation as the name implies, and it is general from taking spray mechanism, flies the accuse through ground remote control or navigation, realizes spraying the operation, can spray medicament, seed, powder etc..

In the prior art, when carrying out the medicament and spraying, spray unmanned aerial vehicle's organism easily on, when causing the medicament extravagant, still lead to the organism to be corroded by the medicament easily.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aircraft, it can reduce the probability that the medicament sprayed on the organism when spraying.

The embodiment of the utility model discloses a can realize like this:

an embodiment of the utility model provides an aircraft, it includes:

a body having at least three touchdown points for touchdown, the at least three touchdown points defining a touchdown surface; and

the spray head is connected with the machine body;

wherein the spray head is positioned above the ground contact surface; in the at least three touchdown points, the angle between the connecting line of the touchdown point closest to the spray head and the bottom of the spray head and the touchdown surface is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees.

Optionally, the spray head comprises a centrifugal atomizing disk;

the bottom of the spray head is the center of the bottom surface of the centrifugal atomizing disk.

Optionally, the body comprises:

a body;

a landing gear coupled to the fuselage, the at least three contact points being located at a bottom end of the landing gear;

one end of the horn is connected with the machine body; and

the power device is connected to the other end of the machine arm and is positioned above the machine arm;

wherein, the shower nozzle is connected to the horn, and is located the below of horn.

Optionally, the spray head is located in an area covered by a downwash of the power plant;

wherein the downwash airflow is formed by the aircraft forward process.

Optionally, the aircraft further includes a fixing rod, a first connecting end and a first mounting end are respectively formed at two ends of the fixing rod, the first connecting end is connected with the horn, and the first mounting end is connected with the spray head.

Optionally, an included angle between a connecting line of projections of the first connecting end and the first mounting end on a vertical plane and the vertical direction is alpha, and alpha is greater than or equal to 30 degrees and less than or equal to 34 degrees;

wherein the vertical plane intersects the first connection end and is a plane defined by the first connection end traveling, retreating, lifting, and descending on the aircraft.

Optionally, the fixing rod is linear, and the fixing rod is arranged obliquely forwards or backwards relative to the vertical direction;

wherein the inclination angle is alpha, and alpha is more than or equal to 30 degrees and less than or equal to 34 degrees.

Optionally, the horn includes a first horn and a second horn, and the spray head includes a first spray head and a second spray head;

the first machine arm and the second machine arm are distributed on two sides of the machine body, the first spray head is connected to the first machine arm, and the second spray head is connected to the second machine arm;

the distance between the first spray head and the second spray head is L, and L is more than or equal to 1.4m and less than or equal to 1.8 m.

Optionally, a second connecting end and a second mounting end are respectively formed at two ends of the horn, the second connecting end is connected with the machine body, and the second mounting end is connected with the power device;

wherein, the distance between the second connecting end and the grounding surface is less than the distance between the second mounting end and the grounding surface.

Optionally, an included angle between a connecting line of the second connecting end and the second mounting end and the vertical direction is γ, and γ is greater than or equal to 100 degrees and less than or equal to 120 degrees.

The utility model discloses aircraft's beneficial effect includes, for example:

the aircraft includes organism and shower nozzle, and the shower nozzle is installed on the organism, when the aircraft flies, can carry out the operation of spraying of medicament through the shower nozzle. In conventional understanding, when an aircraft lands on the ground, stable stopping is achieved by contacting the aircraft with at least three touchdown points, which may define the touchdown surface. On the basis of keeping the conventional spraying design, the position of the spray head is properly adjusted, so that the spray head and the ground contact surface meet the following requirements: the included angle between the connecting line of the contact point closest to the spray head and the bottom of the spray head and the contact surface is beta, and the beta is more than or equal to 13 degrees and less than or equal to 17 degrees. Under the condition that satisfies this design, the aircraft is spraying the operation, and the medicament is difficult to spray to the organism on, can avoid the medicament extravagant like this, can also reduce the organism simultaneously by the probability that the medicament corrodes, has improved life greatly.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic structural diagram of an aircraft according to the present embodiment at a first viewing angle;

FIG. 2 is a schematic structural diagram of the aircraft at a second perspective provided in this embodiment;

FIG. 3 is a schematic structural diagram of the aircraft at a third viewing angle according to the present embodiment;

fig. 4 is a schematic structural diagram of the aircraft provided in this embodiment at a fourth viewing angle.

Icon: 100-an aircraft; 10-body; 101-touching the ground; 11-a fuselage; 12-a landing gear; 13-a horn; 131-a second connection end; 132-a second mounting end; 133-a first horn; 134-a second horn; 14-a power plant; 15-liquid storage container; 16-a battery; 20-a spray head; 201-a first showerhead; 202-a second spray head; 21-a drive device; 22-centrifugal atomizing disk; 30-a fixing rod; 31-a first connection end; 32-first mounting end.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it should be noted that, if the terms "upper", "lower", "inner", "outer", etc. indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the products of the present invention are used, the description is only for convenience of description and simplification, but the indication or suggestion that the indicated device or element must have a specific position, be constructed and operated in a specific orientation, and thus, should not be interpreted as a limitation of the present invention.

Furthermore, the appearances of the terms "first," "second," and the like, if any, are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

It should be noted that the features of the embodiments of the present invention may be combined with each other without conflict.

Plant protection unmanned aerial vehicle, also called unmanned vehicles, is the unmanned aircraft who is used for agriculture and forestry plant protection operation as the name implies, and it is general from taking spray mechanism, flies the accuse through ground remote control or navigation, realizes spraying the operation, can spray medicament, seed, powder etc.. In the prior art, when carrying out the medicament and spraying, spray unmanned aerial vehicle's organism easily on, when causing the medicament extravagant, still lead to the organism to be corroded by the medicament easily.

Referring to fig. 1-4, the present embodiment provides an aircraft 100, which can effectively improve the above-mentioned technical problems.

Aircraft 100 in this embodiment is unmanned aerial vehicle that can not manned, specifically, is rotor unmanned aerial vehicle, of course, in other embodiments, also can be fixed wing unmanned aerial vehicle, umbrella wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle etc. or, this aircraft 100 can manned. In this embodiment, this aircraft 100 is plant protection unmanned aerial vehicle, carries out the spraying of medicament, of course, also can carry out the spraying of fertilizer, seed etc..

Fig. 1 shows a perspective view of the aircraft 100, fig. 2 shows a top view of the aircraft 100, fig. 3 shows a rear view of the aircraft 100, and fig. 4 shows a left side view of the aircraft 100. The relative positions herein are illustrated with respect to the relative positions of the aircraft 100 when it is in normal use.

Specifically, in connection with fig. 3, the aircraft 100 comprises an airframe 10 and a spray head 20 connected to the airframe 10; the body 10 is provided with at least three touchdown points for touchdown, the at least three touchdown points defining a touchdown surface 101; wherein, the spray head 20 is positioned above the grounding surface 101; among the at least three touchdown points, the angle between the connecting line between the touchdown point closest to the spray head 20 and the bottom of the spray head 20 and the touchdown surface 101 is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees.

Referring to fig. 3, generally, when the aircraft 100 lands on the ground, the ground contact surface 101 is parallel to or coincides with the horizontal plane, and is illustrated by the relative positions in fig. 3, fig. 3 shows two spray heads 20, namely a first spray head 201 and a second spray head 202, the contact point on the ground contact surface 101 closest to the first spray head 201 is the rightmost point of the bottom end of the aircraft body 10, and the contact point on the ground contact surface 101 closest to the second spray head 202 is the leftmost point of the bottom end of the aircraft body 10. When the above β satisfies 15 ° ± 2 °, the probability of spraying the medicine onto the body 10 when the medicine is sprayed from the spray head 20 can be reduced, specifically, β may be 13 °, 14 °, 15 °, 16 °, 17 °, and the like.

In this embodiment, the aircraft 100 includes an airframe 10 and a spray head 20, and the spray head 20 is mounted on the airframe 10, so that when the aircraft 100 flies, the spray head 20 can spray the medicament. In a conventional understanding, when aircraft 100 lands on the ground, stable stopping is achieved by touchdown of at least three touchdown points on aircraft 100, which may define touchdown surface 101. On the basis of keeping the conventional spraying design, the position of the spray head 20 is properly adjusted so that the spray head 20 and the ground contact surface 101 satisfy: the included angle between the connecting line of the grounding point closest to the spray head 20 and the bottom of the spray head 20 and the grounding surface 101 is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees. Under the condition that satisfies this design, aircraft 100 is spraying the operation, and the medicament is difficult to spray to organism 10 on, can avoid the medicament extravagant like this, can also reduce the probability that organism 10 is corroded by the medicament simultaneously, has improved life greatly.

Referring to fig. 1, in the present embodiment, the spray head 20 includes a centrifugal atomizing disk 22; wherein, the bottom of the spray head 20 is the center of the bottom surface of the centrifugal atomizing disk 22. Meanwhile, the spray head 20 further comprises a driving device 21 for driving the centrifugal atomizing disk 22 to rotate. Generally, the driving device 21 is a motor, and the rotation speed of the centrifugal atomizing disk 22 can be controlled by the motor. By controlling the liquid inlet amount of the spray head 20, the rotating speed of the centrifugal atomizing disk 22 and the like, the effective regulation of the spraying range, the granularity and the like can be realized. Based on prior art's regulation, the condition that the medicine sprays on the organism 10 of some liquid drops often appears, in this embodiment, carries out appropriate adjustment to the position of shower nozzle 20, according to the conventional control to feed liquor volume size and centrifugal atomizing disk 22 rotational speed, can effectively avoid the medicine to spray on the organism 10. In this embodiment, the spray head 20 is fixed, that is, the spraying direction is determined, but in other embodiments, the spray head 20 may be driven to swing by installing a motor to realize swinging spraying. Meanwhile, in other embodiments, the spraying operation may also be performed by a direct spraying manner of the spraying head 20, for example, the spraying head 20 is provided with a plurality of fine holes, and the medicine is sprayed through the fine holes to achieve the spraying operation.

With reference to fig. 1 and 2, in the present embodiment, specifically, the body 10 includes a fuselage 11, a landing gear 12, an arm 13, and a power device 14; the landing gear 12 is connected to the fuselage 11, and at least three contact points are located at the bottom end of the landing gear 12; one end of the machine arm 13 is connected with the machine body 11; the power device 14 is connected to the other end of the machine arm 13 and is positioned above the machine arm 13; the nozzle 20 is connected to the arm 13 and located below the arm 13.

In this embodiment, the number of the landing gear 12 is two, and the two landing gear 12 are fixedly distributed below the two sides of the aircraft body 11 to ensure the stability of the aircraft 100 in takeoff and landing. The number of the horn 13 is also two, and the horn is distributed on both sides of the body 11. The power device 14 provides lift for the flying of the aircraft 100, and in the embodiment, the foldable propeller is adopted as the propeller in the power device 14, so that the portability of the transportation of the whole aircraft 100 can be improved by folding when the aircraft is not used. With reference to fig. 1, an aircraft 100 comprising two arms 13 and two power units 14 may also be referred to as a twin rotor drone.

Meanwhile, the machine body 10 further includes a liquid storage container 15, a battery 16, an electronic control module (not shown), and the like mounted on the machine body 11. The liquid storage container 15 is used for containing articles to be sprayed or transported, the battery 16 is used for supplying power to various electrical components of the aircraft 100, and the electronic control module is used for controlling the flight attitude of the aircraft 100. The spray head 20 is in communication with the reservoir 15 via a line to spray the solution within the reservoir 15. Typically, the reservoir 15 and the battery 16 are mounted in either a contact or a non-contact manner, for example, by a spacer separating the two.

The above-mentioned each part of being connected with fuselage 11 can choose for use modes such as joint, bolted connection to realize with fuselage 11 fixed, it is comparatively convenient to install like this and dismantle.

In this embodiment, the spray head 20 is located in the area covered by the downwash of the power plant 14; wherein the downwash is formed by the forward course of the aircraft 100.

Referring to fig. 2, the L direction shown on the left side of the aircraft 100 is the left direction, the R direction shown on the right side of the aircraft 100 is the right direction, the B direction shown on the upper side of the aircraft 100 is the front direction, and the H direction shown on the lower side of the aircraft 100 is the rear direction, as explained with respect to the relative positions in fig. 2.

With reference to fig. 4, the relative positions in fig. 4 are illustrated such that the X1 direction shown on the left side of the aircraft 100 is the forward direction, the X2 direction shown on the right side of the aircraft 100 is the reverse direction, the Y1 direction shown on the top of the aircraft 100 is the lift direction, and the Y2 direction shown on the bottom of the aircraft 100 is the descent direction.

Generally, the aircraft 100 has multiple flight directions and multiple attitudes, but a forward direction is common (not to emphasize a certain level of forward travel, but also to allow for lifting or lowering while traveling forward). Therefore, in the present embodiment, referring to fig. 4, the shower head 20 is provided on the lower rear side of the power unit 14. As is also apparent from fig. 2, the spray head 20 is not located directly below the power unit 14, but is located at a rearward position below it. Thus, when the aircraft 100 moves forward, the downward washing air flow generated by the high-speed rotation of the propeller in the power device 14 can be fully utilized, and the uniformity of spraying the medicament can be improved, so that the spraying efficiency is improved.

For ease of understanding, the above-mentioned "downwash" is described in detail herein, and the downwash is also referred to as rotor downwash, which means that when the aircraft 100 is in a hovering state, the propeller rotates to cause the airflow to flow from above the propeller to below the propeller to generate an induced velocity, and the combined velocity of the induced velocity and the circumferential motion velocity of the lutein forms a lutein true velocity such that the air flows in a direction opposite to the pulling force. Under such conditions, the pressure on the upper surface of the propeller is small while the pressure on the lower surface is strong, a lift force is generated between the upper surface and the lower surface of the propeller, and since the height of the aircraft 100 is generally constant during flight, air with high pressure on the lower surface flows downward to form a downwash airflow.

Referring to fig. 1 and 3, in the present embodiment, the aircraft 100 further includes a fixing rod 30, two ends of the fixing rod 30 respectively form a first connecting end 31 and a first mounting end 32, the first connecting end 31 is connected to the horn 13, and the first mounting end 32 is connected to the spray head 20.

In this embodiment, the fixing rod 30 has a hollow structure, so that lines and pipes connected to the spray head 20 can be installed through the inside of the fixing rod 30, and the fixing rod 30 can effectively protect the lines and pipes. In addition, in the present embodiment, the fixing rod 30 is a rigid structure, that is, the length thereof is not adjustable, but in other embodiments, the fixing rod 30 may also be retractable, and the position of the nozzle 20 may be adjusted by the retractable, so that the included angle β may be adjusted. It will be appreciated that, illustrated in relative position in figure 3, the angle β increases when the fixation rod 30 is contracted and decreases when the fixation rod 30 is extended.

With reference to fig. 4, optionally, an angle between a connecting line of the above-mentioned first connecting end 31 and the first mounting end 32 projected on the vertical plane and the vertical direction is α, and α is greater than or equal to 30 ° and less than or equal to 34 °; wherein the vertical plane intersects the first connection end 31 and is the plane defined by the first connection end 31 traveling, backing, lifting and lowering of the aircraft 100.

It will be appreciated that the direction K shown in fig. 4 is a vertically downward direction. The vertical plane may be understood as a plane defined by the above-mentioned X1 direction, X2 direction, Y1 direction, and Y2 direction, and may also be understood as a plane of the paper in fig. 4.

Referring to fig. 4, alternatively, the fixing lever 30 is linear, and the fixing lever 30 is disposed obliquely forward or backward with respect to the vertical direction; wherein the inclination angle is alpha, and alpha is more than or equal to 30 degrees and less than or equal to 34 degrees.

Under the condition that other designs are kept in the conventional design, when the included angle alpha satisfies 32 degrees +/-2 degrees, such as 30 degrees, 31 degrees, 32 degrees, 33 degrees and 34 degrees, the downwash air flow generated by the high-speed rotation of the propeller in the power device 14 can be fully utilized, the uniformity of medicament spraying can be improved, and the spraying efficiency is improved. Specifically, in conjunction with fig. 4, the fixing lever 30 is inclined in the X2 direction, i.e., is disposed obliquely rearward. Of course, in other embodiments, the fixing rod 30 may be disposed obliquely forward.

In this embodiment, the arm 13 is linear, and the fixing rod 30 and the arm 13 are arranged at an included angle.

Specifically, referring to fig. 3, an included angle formed between the fixing rod 30 connected to the first arm 133 and the first arm 133 is Z, where Z is greater than or equal to 80 ° and less than or equal to 100 °, for example, 80 °, 85 °, 90 °, 95 °, 100 °, and when Z is 90 °, the first arm 133 and the fixing rod 30 are vertically distributed. Meanwhile, in this embodiment, an included angle formed between the fixing rod 30 connected to the second arm 134 and the second arm 134 is also Z.

Referring to fig. 3, in the embodiment, the horn 13 includes a first horn 133 and a second horn 134, and the nozzle 20 includes a first nozzle 201 and a second nozzle 202; the first arm 133 and the second arm 134 are distributed on two sides of the body 11, the first nozzle 201 is connected to the first arm 133, and the second nozzle 202 is connected to the second arm 134; wherein, the distance between the first spray head 201 and the second spray head 202 is L, L is more than or equal to 1.4m and less than or equal to 1.8 m.

In the above, when the distance L satisfies 1.4m to 1.8m, such as 1.4m, 1.5m, 1.6m, 1.7m, 1.8m, etc., the spraying range of the two nozzles 20 is reasonable, and the spraying efficiency can be improved.

In this embodiment, a second connecting end 131 and a second mounting end 132 are respectively formed at two ends of the horn 13, the second connecting end 131 is connected with the body 11, and the second mounting end 132 is connected with the power device 14; wherein, the distance between the second connecting end 131 and the ground contact surface 101 is smaller than the distance between the second mounting end 132 and the ground contact surface 101.

It will be appreciated that the arm 13 is of a tilted configuration, so that the centre of gravity of the aircraft 100 is relatively low, and at the same time the centre of gravity of the propeller of the power plant 14, which generates the pulling force, is relatively far from the centre of gravity, so that the flight of the aircraft 100 as a whole is more stable.

Referring to fig. 3, in the present embodiment, taking the second horn 134 as an example, the connection between the second horn 134 and the fuselage 11 is a pivot joint, it can be understood that the rotatable connection between the horn 13 and the fuselage 11 is realized by shaft hole fitting or the like, and the rotation direction is shown in the direction F, that is, by the rotatable connection, the folding and unfolding of the aircraft 100 can be realized. In this embodiment, the first arm 133 and the second arm 134 are both pivotally connected to the fuselage 11, so that the portability of the transportation of the aircraft 100 can be improved by the folding operation when not in use.

Referring to fig. 3, in the present embodiment, an angle between a connection line of the second connecting end 131 and the second mounting end 132 mentioned above and the vertical direction is γ, and γ is greater than or equal to 100 ° and less than or equal to 120 °. The gamma can be selected from 100 degrees, 105 degrees, 110 degrees, 115 degrees and 120 degrees.

Generally, the larger the angle γ, the lower the center of gravity of the overall aircraft 100, and the further away from the center of gravity the pull center of the propeller of the power plant 14 produces a pulling force, the more stable the flight of the aircraft 100, while keeping the other designs conventional. Similarly, a similar effect is achieved when the length of the horn 13 is longer, but this results in a larger overall size of the aircraft 100. Through the folding operation, the inconvenience caused by the large volume can be relieved.

The present embodiment provides an aircraft 100 with at least the following advantages:

through reasonable setting parameters such as alpha, beta, gamma, L, can be so that the process of spraying make full use of the downwash air current that power device 14 produced, can improve and spray the degree of consistency, improve and spray efficiency, improve flight stability, improve and spray scope etc. simultaneously, the medicament that sprays can not obviously spray on organism 10, reduces the probability that organism 10 is corroded by the medicament. Moreover, the whole aircraft 100 is low in weight and cost and wide in market prospect.

To sum up, the embodiment of the present invention provides an aircraft 100, the aircraft 100 includes the body 10 and the shower nozzle 20, the shower nozzle 20 is installed on the body 10, when the aircraft 100 flies, the operation of spraying of the medicament can be carried out through the shower nozzle 20. In a conventional understanding, when aircraft 100 lands on the ground, stable stopping is achieved by touchdown of at least three touchdown points on aircraft 100, which may define touchdown surface 101. On the basis of keeping the conventional spraying design, the position of the spray head 20 is properly adjusted so that the spray head 20 and the ground contact surface 101 satisfy: the included angle between the connecting line of the grounding point closest to the spray head 20 and the bottom of the spray head 20 and the grounding surface 101 is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees. Under the condition that satisfies this design, aircraft 100 is spraying the operation, and the medicament is difficult to spray to organism 10 on, can avoid the medicament extravagant like this, can also reduce the probability that organism 10 is corroded by the medicament simultaneously, has improved life greatly.

The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims (10)

1. An aircraft, characterized in that it comprises:

-a body (10), said body (10) being provided with at least three touchdown points for touchdown, said at least three touchdown points defining a touchdown surface (101); and

a spray head (20) connected with the machine body (10);

wherein the spray head (20) is located above the ground contact surface (101); among the at least three touchdown points, the angle between the connecting line of the touchdown point closest to the spray head (20) and the bottom of the spray head (20) and the touchdown surface (101) is beta, and beta is more than or equal to 13 degrees and less than or equal to 17 degrees.

2. The aircraft of claim 1, characterized in that the spray head (20) comprises a centrifugal atomizer disk (22);

the bottom of the spray head (20) is the center of the bottom surface of the centrifugal atomizing disk (22).

3. The aircraft of claim 1, characterized in that the airframe (10) comprises:

a body (11);

-a landing gear (12), said landing gear (12) being connected to said fuselage (11), said at least three contact points being located at a bottom end of said landing gear (12);

the machine arm (13), one end of the machine arm (13) is connected with the machine body (11); and

the power device (14) is connected to the other end of the machine arm (13), and is positioned above the machine arm (13);

wherein the spray head (20) is connected to the machine arm (13) and is positioned below the machine arm (13).

4. The aircraft of claim 3, characterized in that the spray heads (20) are located in an area covered by a downwash of the power plant (14);

wherein the downwash airflow is formed by a forward course of the aircraft (100).

5. The aircraft of claim 4, characterized in that the aircraft (100) further comprises a fixing rod (30), wherein both ends of the fixing rod (30) form a first connecting end (31) and a first mounting end (32), respectively, the first connecting end (31) being connected with the horn (13), and the first mounting end (32) being connected with the spray head (20).

6. The aircraft according to claim 5, characterized in that the angle α between the line of projection of said first connection end (31) and said first mounting end (32) on a vertical plane and the vertical is 30 ° ≦ α ≦ 34 °;

wherein the vertical plane intersects the first connection end (31) and is a plane defined by the first connection end (31) advancing, retreating, lifting and descending the aircraft (100).

7. The aircraft of claim 5, characterized in that said fixed bars (30) are rectilinear, said fixed bars (30) being disposed obliquely forwards or backwards with respect to the vertical;

wherein the inclination angle is alpha, and alpha is more than or equal to 30 degrees and less than or equal to 34 degrees.

8. The aircraft of any one of claims 3 to 7, wherein the horn (13) comprises a first horn (133) and a second horn (134), and the spray head (20) comprises a first spray head (201) and a second spray head (202);

the first horn (133) and the second horn (134) are distributed on two sides of the body (11), the first spray head (201) is connected to the first horn (133), and the second spray head (202) is connected to the second horn (134);

the distance between the first spray head (201) and the second spray head (202) is L, and L is more than or equal to 1.4m and less than or equal to 1.8 m.

9. The aircraft according to any one of claims 3 to 7, characterized in that the two ends of said horn (13) form a second connection end (131) and a second mounting end (132), respectively, said second connection end (131) being connected to said fuselage (11) and said second mounting end (132) being connected to said power unit (14);

wherein the distance between the second connecting end (131) and the grounding surface (101) is smaller than the distance between the second mounting end (132) and the grounding surface (101).

10. The aircraft of claim 9, wherein a line connecting the second connecting end (131) and the second mounting end (132) forms an angle γ with the vertical direction, 100 ° ≦ γ ≦ 120 °.

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