CN213974478U - Fuselage assembly of aircraft and aircraft with same - Google Patents

Abstract

The utility model discloses a fuselage subassembly of aircraft and aircraft that has it, the fuselage subassembly includes: a body; the plurality of the horn arms are distributed along the circumferential direction of the machine body, and one end of each horn arm is arranged on the machine body; the spraying device is arranged at one end of the machine arm, which is far away from the machine body; the driving part is arranged on the machine body and connected with the machine arm to drive the machine arm to rotate along the axial direction. The utility model discloses a fuselage subassembly can make the central axis of sprinkler and the rotatory central axis of power component's screw remain parallel or coincidence throughout, keeps the state of evenly spraying the droplet, improves spraying effect of aircraft.

Description

Fuselage assembly of aircraft and aircraft with same

Technical Field

The utility model belongs to the technical field of the technique of aircraft and specifically relates to a fuselage subassembly of aircraft and aircraft that has it are related to.

Background

In the related art, when an aircraft is used to spray liquid medicine or water and the aircraft changes a flight state (forward, backward, leftward or rightward flight) in the air, the spray device sprays non-uniform droplets, and the spraying effect of the aircraft is poor.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, an object of the utility model is to provide a fuselage subassembly of aircraft can make the central axis of sprinkler and the rotatory central axis of power component's screw remain parallel or coincidence throughout, keeps the state of evenly spraying the droplet, improves the spraying effect of aircraft.

The utility model also provides an aircraft, including foretell fuselage subassembly.

According to the utility model discloses fuselage subassembly of aircraft, include: a body; the plurality of the horn arms are distributed along the circumferential direction of the machine body, and one end of each horn arm is arranged on the machine body; the spraying device is arranged at one end of the machine arm, which is far away from the machine body; the driving part is arranged on the machine body and connected with the machine arm to drive the machine arm to rotate along the axial direction.

According to the utility model discloses fuselage subassembly of aircraft through setting up the drive division, makes the drive division establish on the fuselage and link to each other with the horn and rotate along the axial with the drive horn to the central axis of rotation that can make sprinkler's the central axis and power component's screw remains parallel or coincidence throughout, makes sprinkler spun droplet along with pushing down the even downward dispersion in wind field, keeps the state of evenly spraying the droplet, and then improves spraying effect of aircraft. Meanwhile, the structure of the machine body assembly can be simplified, and the manufacturing cost of the machine body assembly is reduced.

According to some embodiments of the utility model, the fuselage includes fixed frame, fixed frame includes fixed bolster, first plate body and second plate body are connected on the upper and lower both sides of fixed bolster, the fuselage subassembly still includes the clamping part, the clamping part cover is established on the horn, the horn is relative the axial rotation can be followed to the clamping part, the clamping part respectively with first plate body with the second plate body links to each other in order to incite somebody to action the horn is installed on the fuselage.

In some embodiments of the utility model, the clamping part includes first holder, second holder and bearing spare, first holder with the second holder sets up relatively in order to inject the fixed orifices, the bearing spare is established just the cover is established in the fixed orifices on the horn.

In some embodiments of the present invention, the first clamping member is connected to the first plate, and the second clamping member is connected to the second plate.

In some embodiments of the present invention, the clamping portion is a plurality of, and a plurality of, the clamping portion is distributed along the axial direction of the horn at intervals.

According to some embodiments of the utility model, the horn includes first arm section, second arm section and connecting portion, first arm section is established on the fuselage, connecting portion are including the first connecting piece and the second connecting piece that link to each other, first connecting piece with first arm section links to each other, the second connecting piece with the second arm section links to each other, the second connecting piece is relative first connecting piece is rotatable between first position and second position, the horn has expansion state and fold condition first position, the horn is in expansion state the second position, the horn is in fold condition.

According to some embodiments of the invention, the horn is a piece of carbon fiber material, a piece of plastic material, or a piece of aluminum alloy material.

According to some embodiments of the present invention, the driving portion is a plurality of, a plurality of the driving portion is provided with a plurality of the horn one-to-one.

According to some embodiments of the invention, the drive portion is connected with a plurality of the horn respectively in order to drive every the horn rotates along the axial.

According to the utility model discloses aircraft, include according to the utility model discloses fuselage subassembly of aircraft of above-mentioned embodiment.

According to the utility model discloses aircraft, through setting up the basis the utility model discloses the fuselage subassembly of the aircraft of above-mentioned embodiment. Thereby can make sprinkler's the central axis and the rotatory central axis of power component's screw remain parallel or coincide throughout, make sprinkler spun droplet along with pushing down the even downward dispersion of wind field, keep the state of evenly spraying the droplet, and then improve the spraying effect of aircraft. Meanwhile, the structure of the aircraft can be simplified, and the manufacturing cost of the aircraft is reduced.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic illustration of an aircraft according to some embodiments of the present invention;

fig. 2 is a schematic illustration of an aircraft according to some embodiments of the present invention;

FIG. 3 is an enlarged view of portion A of FIG. 2;

fig. 4 is a partial schematic view of a fuselage according to some embodiments of the invention;

fig. 5 is a schematic view of a horn according to some embodiments of the present invention.

Reference numerals:

100. an aircraft;

10. a fuselage assembly;

1. a body;

11. a fixing frame; 111. fixing a bracket; 112. a first plate body; 113. a second plate body;

12. a first mounting frame; 121. a fixing plate; 122. a first connecting plate; 123. a first installation space;

13. a second mounting frame; 131. a second connecting plate; 132. a third connecting plate; 133. a separator plate; 134. a second installation space;

2. a horn;

21. a first arm segment; 22. a second arm segment; 23. a connecting portion; 231. a first connecting member; 232. a second connecting member;

3. a drive section;

4. a clamping portion; 41. a first clamping member; 42. a second clamping member; 43. a bearing member;

20. a landing gear; 30. a power assembly; 40. a battery; 50. and a control module.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like 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 invention, and should not be construed as limiting the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring now to fig. 1-5, a fuselage assembly 10 of an aircraft 100 according to an embodiment of the present disclosure is described, wherein the aircraft 100 may be a drone (e.g., as shown in fig. 1 and 2, the aircraft 100 is a dual rotor drone), and the aircraft 100 may be used in agricultural operations for spraying agricultural chemicals or spraying moisture onto crops. Of course, the aircraft 100 may also be used in other fields such as spraying of fire suppression fluids in forest fires, aerial photography, power routing inspection, environmental monitoring, forest fire prevention, and disaster patrol.

The use of the aircraft 100 in the farming industry for pesticide spraying or water sprinkling for crops is described in detail below. It will be appreciated that the horn 2 of the aircraft 100 is provided with a spray device for spraying pesticide or water.

As shown in fig. 1-3, a fuselage assembly 10 of an aircraft 100 according to an embodiment of the invention comprises: fuselage 1, horn 2, sprinkler and drive division 3.

Specifically, the number of the horn 2 is plural, the plurality of horns 2 are distributed along the circumferential direction of the body 1, and one end of each horn 2 is provided on the body 1. The spraying device is arranged at one end of the machine arm 2 far away from the machine body 1. The driving part 3 is arranged on the machine body 1 and connected with the machine arm 2 to drive the machine arm 2 to rotate along the axial direction.

It can be seen that the arm 2 can be driven by the driving part 3 to rotate along the axial direction (i.e. rotate around the axis), so that the structure provided on the arm 2, such as the power assembly 30, the spraying device, etc., can rotate synchronously with the arm 2, and the relative positions of the power assembly 30 and the spraying device will not change.

As is known, the propeller of the power assembly 30 normally rotates to form a downward-pressing wind field below the propeller, the spraying device is located in the middle of the wind field, the central axis of the spraying device is generally parallel to or coincident with the rotation axis of the propeller, and the droplets sprayed from the spraying device are uniformly dispersed downward along with the downward-pressing wind field. In the prior art, when the aircraft changes the flight state (advances, retreats, flies leftwards or rightwards), the propeller is controlled to incline by the steering engine at the bottom of the propeller, and the spraying device at the bottom of the horn cannot incline synchronously with the propeller, so that an included angle is formed between the rotation axis of the propeller and the central axis of the spraying device, and the sprayed fog drops cannot be uniform. Thereby affecting the spraying effect of the aircraft.

However, in the embodiment of the utility model, when the aircraft 100 carries out the operation of spraying of pesticide spraying or moisture, no matter which direction the aircraft 100 flies towards, all can drive horn 2 through control drive division 3 and adjust the direction of the screw of power component 30 along the axial rotation, and guarantee that sprinkler and power component 30's relative position can not change, can be so that sprinkler's the central axis keeps parallel or coincidence with the central axis of rotation of power component 30's screw throughout, just so can make sprinkler be located the middle part position of the wind field that pushes down that the screw formed all the time, make sprinkler spun droplet along with pushing down the even downward dispersion in wind field, keep evenly spraying the state of droplet, and then improve aircraft 100's the effect of spraying.

Meanwhile, the driving part 3 can replace the function of an original steering engine for controlling the rotation of the propeller, so that the fuselage assembly 10 can be free from the arrangement of the steering engine for controlling the rotation of the propeller, the spraying effect of the aircraft 100 is improved, the structure of the fuselage assembly 10 can be simplified, and the manufacturing cost of the fuselage assembly 10 is reduced.

According to the utility model discloses fuselage subassembly 10 of aircraft 100 through setting up drive division 3, makes drive division 3 establish on fuselage 1 and link to each other with drive horn 2 along the axial rotation with drive horn 2 to the central axis that can make sprinkler's the central axis and the rotatory central axis of power component 30's screw remain parallel throughout or coincide, makes sprinkler spun fog drip along with pushing down the even downward dispersion in wind field, keeps evenly spraying the state of fog drip, and then improves the effect of spraying of aircraft 100. And at the same time, the structure of the body assembly 10 can be simplified, reducing the manufacturing cost of the body assembly 10.

As shown in fig. 1-3, according to some embodiments of the present invention, the fuselage 1 includes the fixed frame 11, the fixed frame 11 includes the fixed bolster 111, the first plate body 112 and the second plate body 113 are connected on the upper and lower both sides of the fixed bolster 111, the fuselage assembly 10 further includes the clamping part 4, the clamping part 4 cover is established on the horn 2, the relative clamping part 4 of the horn 2 can be rotated along the axial, the clamping part 4 links to each other with the first plate body 112 and the second plate body 113 respectively in order to install the horn 2 on the fuselage 1. It can be seen that the fixing frame 11 has a simple and reliable structure and high strength. One end of the horn 2 can be efficiently attached to the body 1 through the clamp 4, whereby the structural reliability of the body assembly 10 can also be improved. Meanwhile, the horn 2 can rotate axially relative to the clamping part 4, so that the state that the aircraft 100 sprays fog drops uniformly can be ensured, and the spraying effect of the aircraft 100 is improved.

As shown in fig. 3, in some embodiments of the present invention, the clamping portion 4 includes a first clamping member 41, a second clamping member 42 and a bearing member 43, the first clamping member 41 and the second clamping member 42 are disposed relatively to define a fixing hole, and the bearing member 43 is disposed in the fixing hole and sleeved on the horn 2. This makes it possible to provide the clamping portion 4 with a simple and reliable structure. The bearing piece 43 can improve the reliability that the horn 2 can rotate along the axial direction, reduce the resistance that the horn 2 receives when rotating along the axial direction, and then improve the reliability of the fuselage assembly 10. It should be noted that the structure of the clamping portion 4 is not limited to this, and the clamping portion 4 may also be in other forms of structures, for example, the clamping portion 4 includes a clamping fixture and a bearing member 43, the clamping fixture is an integral member, a through hole is provided on the clamping fixture, and the bearing member 43 is provided on the through hole.

In some embodiments of the present invention, the first clamping member 41 is connected to the first plate 112, and the second clamping member 42 is connected to the second plate 113. Therefore, the clamping part 4 is arranged on the fixing part in a simple and reliable mode, and is convenient to mount and dismount.

Optionally, the first clamping member 41 is detachably connected to the second clamping member 42. Thereby, the assembly and the fixation of the clamping part 4 and the machine arm 2 are more convenient, and the integral assembly mode of the machine body component 10 is more flexible. For example, the first clamping member 41 may be connected to the first plate 112, the second clamping member 42 may be connected to the second plate 113, the horn 2 may be assembled to the bearing member 43, the bearing member 43 may be assembled to the fixing hole, and the first clamping member 41 may be connected to the second clamping member 42. For example, the horn 2 and the holder 4 may be assembled first, and then the horn 2 and the holder 4 may be integrally fixed to the fixing frame 11.

As shown in fig. 2 and 3, in some embodiments of the present invention, the clamping portion 4 is plural, and the plural clamping portions 4 are spaced apart from each other in the axial direction of the horn 2. Accordingly, the robot arm 2 can be fixed by the plurality of clamping portions 4, whereby the reliability of the robot arm 2 provided to the body 1 and the reliability of the body assembly 10 can be improved.

As shown in fig. 3 and 5, according to some embodiments of the present invention, the horn 2 includes a first arm segment 21, a second arm segment 22 and a connecting portion 23, the first arm segment 21 is disposed on the fuselage 1, the connecting portion 23 includes a first connecting member 231 and a second connecting member 232 connected to each other, the first connecting member 231 is connected to the first arm segment 21, the second connecting member 232 is connected to the second arm segment 22, the second connecting member 232 is rotatable between a first position and a second position with respect to the first connecting member 231, the horn 2 has an unfolded state and a folded state, the horn 2 is in the unfolded state at the first position, and the horn 2 is in the folded state at the second position.

Therefore, in the embodiment of the present invention, the extension and the folding of the arm 2 can be realized only by adjusting the position of the second connecting member 232 relative to the first connecting member 231. Thereby when aircraft 100 is idle to be accomodate, can be through rotating second connecting piece 232 to the second position relative first connecting piece 231, and then make horn 2 be in fold condition to can reduce the occupation space of fuselage subassembly 10 to a certain extent, and then reduce aircraft 100's occupation space, be convenient for accomodating and transporting of aircraft 100. When the aircraft 100 needs to be used, the second connecting part 232 can be rotated to the first position relative to the first connecting part 231, so that the horn 2 is in the unfolded state, and the reliability of the use of the aircraft 100 can be ensured.

According to some embodiments of the invention, the horn 2 is a piece of carbon fiber material, a piece of plastic material or an aluminum alloy material. Whereby the reliability of the structure of the horn 2 can be ensured. And simultaneously contributes to the reduction of the manufacturing cost of the horn 2. Alternatively, the horn 2 may be an aluminum alloy tube made of a carbon fiber material. Of course, the horn 2 may be made of other materials as long as the reliability of the horn 2 and the reliability of the body assembly 10 are ensured.

As shown in fig. 2, according to some embodiments of the present invention, the driving portion 3 is plural, and the plural driving portions 3 are disposed in one-to-one correspondence with the plural arms 2. Therefore, the reliability of the fuselage assembly 10 can be ensured, each driving part 3 drives the corresponding horn 2 to rotate, the flying direction of the aircraft 100 can be controlled effectively and accurately, and the sensitivity and the reliability of the aircraft 100 are improved.

According to other embodiments of the present invention, the driving portion 3 is connected to the plurality of arms 2 to drive each of the arms 2 to rotate in the axial direction. This simplifies the structure of the body module 10 and reduces the manufacturing cost of the body module 10.

According to the present invention, the aircraft 100 comprises the fuselage assembly 10 of the aircraft 100 according to the above embodiments of the present invention.

According to the present invention, the aircraft 100 is provided with the fuselage assembly 10 according to the above-mentioned embodiments of the present invention. Therefore, the central axis of the spraying device and the rotating central axis of the propeller of the power assembly 30 can be always kept parallel or coincident, so that the fog drops sprayed by the spraying device are uniformly dispersed downwards along with the downward pressing wind field, the state of uniformly spraying the fog drops is kept, and the spraying effect of the aircraft 100 is improved. While simplifying the structure of the aircraft 100 and reducing the manufacturing cost of the aircraft 100.

An aircraft 100 according to a specific embodiment of the invention is described below with reference to fig. 1-5. It is to be understood that the following description is exemplary only, and is intended to be illustrative of the present invention and is not to be construed as limiting the invention. Specifically, aircraft 100 may be unmanned, and aircraft 100 may be used for carrying out operations such as pesticide spraying or moisture sprinkling irrigation to crops in the agro-farming industry. Of course, the aircraft 100 may also be used in other fields such as spraying of fire extinguishing fluid in forest fires, aerial photography, power routing inspection, environmental monitoring, forest fire prevention, and disaster patrol.

Referring to fig. 1 and 2, an aircraft 100 according to an embodiment of the invention includes: fuselage assembly 10, landing gear 20, power assembly 30, a liquid storage container, battery 40, an electrical tilt module, and a control module 50. The body assembly 10 includes: the spraying device comprises a machine body 1, two machine arms 2, a spraying device, a driving part 3 and a clamping part 4. Two horn 2 distribute along the circumference of fuselage 1, and the one end of every horn 2 is established on fuselage 1, and the one end of keeping away from fuselage 1 of every horn 2 is equipped with sprinkler. The driving parts 3 are arranged on the machine body 1, the two driving parts 3 are correspondingly connected with the two machine arms 2 one by one, and each driving part 3 is used for controlling the corresponding machine arm 2 to rotate along the axial direction thereof so as to adjust the rotation axis of the power assembly 30. The landing gear 20 is fixed below the fuselage 1 to ensure the stability of the aircraft 100 in takeoff and landing, the power assembly 30 is fixed at the end part of the horn 2 far away from the fuselage 1, the power assembly 30 provides power for the flight and flight attitude adjustment of the aircraft 100, the liquid storage container is carried on the fuselage 1 to contain objects to be sprayed or transported, the battery 40 is fixed on the fuselage 1 to provide power for the power assembly 30, and the electric regulation module and the control module 50 are fixed on the fuselage 1 to control the flight attitude of the aircraft 100.

Referring to fig. 1-2, the main body 1 includes a fixed frame 11, and a first mounting frame 12 and a second mounting frame 13 connected to the fixed frame 11, wherein the fixed frame 11 includes a fixed bracket 111, and a first plate 112 and a second plate 113 disposed on upper and lower sides of the fixed bracket 111, respectively, the first plate 112 and the second plate 113 are used for bearing an electric regulation module, a control module 50, a driving portion 3, and the like, and the liquid storage container and the battery 40 are adapted to be disposed in the first mounting frame 12 and the second mounting frame 13, respectively.

Referring to fig. 4, the first mounting frame 12 includes a fixing plate 121 fixedly coupled to the fixing frame 11 and two first coupling plates 122 coupled to both ends of the fixing plate 121, the two first coupling plates 122 being disposed opposite to each other. The second mounting frame 13 includes two second connecting plates 131 and two third connecting plates 132 and a partition plate 133. One ends of the two second connecting plates 131 are respectively connected with the ends of the two first connecting plates 122 far away from the fixing plate 121, and the two third connecting plates 132 are connected with the other ends of the two second connecting plates 131. The partition plate 133 is connected to the two second connection plates 131 on the side close to the first connection plate 122.

Referring to fig. 2 and 4, the first and second installation frames 12 and 13 define first and second installation spaces 123 and 134, respectively. The reservoir may be mounted to the first mounting space 123 and the battery 40 may be mounted to the second mounting space 134.

Referring to fig. 1-2 in combination with fig. 5, the horn 2 includes two driving portions 3, and the two driving portions 3 are disposed in one-to-one correspondence with the two horns 2. Each horn 2 includes first arm section 21, second arm section 22 and connecting portion 23, first arm section 21 is established on fuselage 1 and is linked to each other with drive division 3, connecting portion 23 includes first connecting piece 231 and the second connecting piece 232 that links to each other, first connecting piece 231 links to each other with first arm section 21, second connecting piece 232 links to each other with second arm section 22, second connecting piece 232 is rotatable between first position and second position relative first connecting piece 231, horn 2 has expansion state and fold condition, at the first position, second connecting piece 232 rotates and is in the expansion state to horn 2, at the second position, second connecting piece 232 rotates and is in fold condition to horn 2. The first arm section 21 and the second arm section 22 are formed substantially as cylindrical rod bodies. In this embodiment, the rod body is an aluminum alloy tube wrapped with a carbon fiber material.

Specifically, as shown in fig. 3, one end of the first arm segment 21 is disposed on the fuselage 1 through the clamping portion 4, the other end of the first arm segment 21 is connected with one end of the second arm segment 22 through the connecting portion 23, and the other end of the second arm segment 22 is used for fixing the power assembly 30.

Referring to fig. 1 to 3, the clamping portion 4 includes a first clamping member 41, a second clamping member 42, and a bearing member 43, the first clamping member 41 and the second clamping member 42 are disposed opposite to each other to define a fixing hole, and the bearing member 43 is disposed in the fixing hole and fitted over the horn 2 to prevent the first arm section 21 from moving in the axial direction. In this embodiment, the first arm segment 21 is connected to the fuselage 1 by means of two clamping portions 4.

The driving part 3 comprises a steering engine and a transmission device. Specifically, the steering wheel is fixed on fuselage 1, and the output shaft of steering wheel links to each other with the horn 2 that corresponds through transmission in order to drive horn 2 and rotate along its axis direction.

The following describes the principle of the driving part 3 driving the power assembly 30 to rotate:

for example, when the aircraft 100 needs to go forward or turn to change the flight state, the control module 50 controls the steering engine of the driving part 3 to rotate, the output shaft of the steering engine drives the transmission device to rotate along the axis of the horn 2, the transmission device is connected with the horn 2, and then the horn 2 can be driven to rotate along the axial direction, so that the change of the flight state of the aircraft 100 is realized. Through the arrangement, the driving part 3 is used for driving the horn 2 and the power assembly 30 on the horn 2 to rotate together with the spraying device, so that the axis of the spraying device is parallel to or coincided with the rotation axis of the propeller of the power assembly 30, the state of uniformly spraying fog drops is kept, and the spraying effect of the aircraft 100 is improved.

Other configurations and operations of the aircraft 100 according to embodiments of the present invention are known to those of ordinary skill in the art and will not be described in detail herein.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. Fuselage assembly (10) of an aircraft (100), characterized in that it comprises:

a fuselage (1);

the plurality of the horn (2) are distributed along the circumferential direction of the machine body (1), and one end of each horn (2) is arranged on the machine body (1);

the spraying device is arranged at one end, far away from the machine body (1), of the machine arm (2);

the driving part (3), establish in driving part (3) on fuselage (1) and with horn (2) link to each other in order to drive horn (2) are along axial rotation.

2. The fuselage assembly (10) of the aircraft (100) according to claim 1, characterized in that the fuselage (1) comprises a fixed frame (11), the fixed frame (11) comprising a fixed support (111), a first panel (112) and a second panel (113), the first panel (112) and the second panel (113) being connected on the upper and lower sides of the fixed support (111),

fuselage subassembly (10) still include clamping part (4), clamping part (4) cover is established on horn (2), horn (2) are relative clamping part (4) can be followed the axial and rotated, clamping part (4) respectively with first plate body (112) with second plate body (113) link to each other in order to incite somebody to action horn (2) are installed on fuselage (1).

3. The fuselage assembly (10) of the aircraft (100) according to claim 2, characterized in that the clamping portion (4) comprises a first clamping member (41), a second clamping member (42) and a bearing member (43), the first clamping member (41) and the second clamping member (42) being arranged opposite one another so as to define a fixing hole, the bearing member (43) being arranged in the fixing hole and being fitted over the horn (2).

4. The fuselage assembly (10) of the aircraft (100) according to claim 3, characterized in that the first clip (41) is connected to the first panel (112) and the second clip (42) is connected to the second panel (113).

5. The fuselage assembly (10) of the aircraft (100) according to claim 3, characterized in that the clips (4) are plural, the clips (4) being distributed at intervals in the axial direction of the horn (2).

6. The fuselage assembly (10) of the aircraft (100) according to claim 1, characterized in that the horn (2) comprises a first arm section (21), a second arm section (22) and a connection (23), the first arm section (21) being provided on the fuselage (1),

connecting portion (23) are including continuous first connecting piece (231) and second connecting piece (232), first connecting piece (231) with first arm section (21) links to each other, second connecting piece (232) with second arm section (22) link to each other, second connecting piece (232) are relative first connecting piece (231) are rotatable between primary importance and second place, horn (2) have expansion state and fold condition the primary importance, horn (2) are in the expansion state the second place, horn (2) are in fold condition.

7. The fuselage assembly (10) of the aircraft (100) according to claim 1, characterized in that the horn (2) is a piece of carbon fiber material, plastic material or aluminum alloy material.

8. The fuselage assembly (10) of the aircraft (100) according to one of claims 1 to 7, characterized in that the number of drives (3) is multiple, and a plurality of drives (3) are arranged in one-to-one correspondence with a plurality of horn arms (2).

9. The fuselage assembly (10) of the aircraft (100) according to one of the claims 1 to 7, characterized in that the drive (3) is connected to a plurality of the arms (2) in each case in order to drive each of the arms (2) in each case in an axial direction.

10. An aircraft (100) comprising a fuselage assembly (10) of the aircraft (100) according to any one of claims 1 to 9.

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