CN213735502U - Unmanned vehicles's fuselage assembly and unmanned vehicles who has it - Google Patents

Abstract

The utility model discloses an unmanned vehicles's fuselage assembly and unmanned vehicles who has it, unmanned vehicles's fuselage assembly includes: fuselage, first fixed frame and battery apron. The machine body comprises an upper shell and a lower shell, an installation space is formed between the upper shell and the lower shell, and a first groove body penetrating through the upper shell is formed on the upper shell; in installation space was located to first fixed frame, first fixed frame included: the battery mounting part corresponds to the first groove body in the vertical direction, and the battery module is detachably mounted on the battery mounting part; the battery cover plate is suitable for being matched with the first groove body and clamped on the first fixing frame or the first groove body. According to the utility model discloses unmanned vehicles's fuselage assembly, battery module get and put the convenience, can fix battery module better simultaneously, prevent that the in-process battery module of flying from droing, and structural layout is reasonable, has promoted user experience.

Description

Unmanned vehicles's fuselage assembly and unmanned vehicles who has it

Technical Field

The utility model belongs to the technical field of unmanned vehicles technique and specifically relates to an unmanned vehicles's fuselage assembly and unmanned vehicles who has it are related to.

Background

Along with the development of society, the application field of unmanned vehicles is continuously expanding, both industrial aircrafts and consumer aircrafts are greatly improved, and especially small unmanned vehicles represented by multi-propeller unmanned vehicles and fixed-wing unmanned vehicles are widely applied in various application fields, such as the fields of aerial photography detection, electric power inspection, environmental monitoring, disaster inspection and the like.

Disclosure of Invention

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 an unmanned vehicles's fuselage assembly, unmanned vehicles's fuselage assembly structural layout is reasonable, has promoted user experience.

The utility model also provides an unmanned vehicles who has unmanned vehicles's fuselage assembly.

According to the utility model discloses unmanned vehicles's fuselage assembly includes: the device comprises a machine body, a first connecting piece and a second connecting piece, wherein the machine body comprises an upper shell and a lower shell, an installation space is formed between the upper shell and the lower shell, and a first groove body penetrating through the upper shell is formed in the upper shell; first fixed frame, first fixed frame is located in the installation space, first fixed frame includes: the battery mounting part corresponds to the first groove body in the vertical direction, and a battery module is detachably mounted on the battery mounting part; the battery cover plate is suitable for being matched with the first groove body and clamped on the first fixing frame or the first groove body; be equipped with the locking part on the battery installation department, the locking part includes hasp portion and pin joint portion, pin joint portion will hasp portion rotationally locates on the battery installation department, hasp portion has unblock position and locking position on the rotation direction, battery module installs back in the battery installation department, hasp portion is suitable for the activity to the locking position, with the locking battery module, hasp portion activity extremely during the unblock position, battery module is suitable for the follow take out in the battery installation department.

According to the utility model discloses unmanned vehicles's fuselage assembly can protect the inside spare part of fuselage assembly better through last casing and lower casing, through setting up first cell body and battery installation department, can be comparatively simple realization battery module get put, through setting up the battery apron, can fix battery module better, prevents that unmanned vehicles flight in-process battery module from droing, and structural layout is reasonable, has promoted user experience.

In addition, according to the utility model discloses an unmanned vehicles's fuselage assembly can also have following additional technical characterstic:

in some embodiments of the present invention, a first mounting groove is formed on the battery mounting portion, at least a portion of the battery module is cooperatively mounted in the first mounting groove, a first protrusion protruding upward is circumferentially formed on the first mounting groove, and the first protrusion is cooperatively mounted in the first groove.

In some embodiments of the utility model, unmanned vehicles's fuselage assembly still includes the fixed frame of second, the fixed frame of second is located in the installation space, and detachably installs first fixed frame lower extreme, and first fixed frame with the cooperation of the fixed frame of second is connected the back, the upper end of first fixed frame with go up shells inner wall butt, the lower extreme of the fixed frame of second with the inner wall butt of casing down.

In other embodiments of the present invention, a matching groove is formed on the battery cover plate, a protrusion is formed on the locking portion, and when the locking portion is located at the locking position, the protrusion is adapted to fit in the matching groove.

In another embodiment of the present invention, a latch is formed on one of the battery cover plate and the upper case, and a latch groove engaged with the latch is formed on the other of the battery cover plate and the upper case.

Optionally, the fastening part comprises a first fastening part and a second fastening part, the first fastening part and the second fastening part are respectively arranged at two ends of the battery cover plate in the length direction, and a first fastening groove and a second fastening groove matched with the first fastening part and the second fastening part are respectively formed in the upper shell.

In a specific embodiment of the present invention, the fuselage assembly of the unmanned aerial vehicle further includes a control module and an aerial survey module, the control module and the aerial survey module are all detachably connected to the first fixing frame, the battery module is adjacent to the front end of the installation space, the control module is adjacent to the rear end of the installation space, the aerial survey module is located between the battery module and the control module to adjust the center of gravity of the fuselage assembly.

In another example of the present invention, the first fixing frame further includes: the wing installation department, the wing installation department is located the rear end of battery installation department, it is a plurality of first fixed parts that extend along first fixed frame width direction to be equipped with on the wing installation department, and is a plurality of first fixed part sets up along the central line symmetry, unmanned vehicles's wing is suitable for to install on the first fixed part.

The utility model also provides an unmanned vehicles of fuselage assembly with above-mentioned unmanned vehicles.

According to the utility model discloses unmanned vehicles, unmanned vehicles still includes: the machine head is detachably arranged at the front end of the machine body assembly; the second wing sections are symmetrically arranged on two sides of the fuselage assembly; the wingtip winglet is arranged at the front end of the second wing section and forms an included angle with the second wing section; the dual-rotor power assembly is symmetrically arranged on the rotor arms at the two sides of the second wing section relative to the fuselage, the empennage is of an inverted V-shaped structure, and the end part of the empennage is connected with the rotor arms through tail support rods; the fixed wing power component is arranged at the tail part of the airframe assembly.

According to the utility model discloses unmanned vehicles, through rotor power component and fixed wing power component, make unmanned vehicles can take off and land with zero speed, and have the ability of hovering, appearance design through streamlined setting, air component when having reduced the flight, flight speed has been promoted, aerial survey module can make unmanned vehicles can carry out the mapping of taking photo by plane betterly simultaneously, electric power is patrolled and examined, the investigation operation of being not convenient for people for going on such as environmental monitoring and disaster inspection, and the fuselage assembly can fix battery module betterly, the battery is got and is put the convenience simultaneously, and is more humanized, and is rational in infrastructure, flight is stable, and application scene is wide.

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 an exploded view of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural view of an upper shell side of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 3 is a schematic structural view of a lower housing side of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 4 is a schematic structural view of a battery cover plate of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 5 is a schematic structural view of a battery module of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 6 is a structural intent of a top side of a first fixed frame of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 7 is a schematic structural view of the bottom side of a first fixed frame of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 8 is a schematic structural view of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

FIG. 9 is a cross-sectional view of FIG. 8;

FIG. 10 is an enlarged view of area A of FIG. 9;

fig. 11 is a schematic structural view of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 12 is an assembly view of a first fixed frame and aerial survey module of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention.

100: fuselage assembly of unmanned aerial vehicle

1: a body; 11: an upper housing; 111: a first tank body; 12: a lower housing;

2: a first fixed frame; 21: a battery mounting portion; 211: a first mounting groove; 212: a first protrusion; 22: a locking member; 221: a locking part; 222: a pivot part; 23: a wing mounting portion; 231: a first fixed part;

3: a battery cover plate; 31: a mating groove; 32: a first fastener; 33: a second fastener;

4: a second fixed frame; 5: a battery module; 6: a control module; 7: an aerial survey module;

1000: an unmanned aerial vehicle;

101: a machine head; 102: a second wing section; 103: a wingtip winglet; 104: an aileron; 105: a rotor arm; 106: a dual rotor power assembly; 107: a fixed wing power assembly; 108: a tail wing; 109: a tail stay bar; 110: and a fixing member.

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.

The following describes the unmanned aerial vehicle fuselage assembly 100 and the unmanned aerial vehicle 1000 having the same according to an embodiment of the present invention with reference to fig. 1 to 12.

According to the embodiment of the utility model provides an unmanned vehicles's fuselage assembly 100, fuselage assembly 100 includes: the battery cover plate comprises a body 1, a first fixing frame 2 and a battery cover plate 3.

Specifically, referring to fig. 1, the body 1 includes an upper housing 11 and a lower housing 12, and an installation space is formed between the upper housing 11 and the lower housing 12, so that the installation space can better place and fix the components of the body assembly 100, and plays a certain role in protection.

As shown in fig. 1, the upper case 11 is formed with a first groove 111 penetrating the upper case 11, the first fixed frame 2 is provided in the installation space, and the first fixed frame 2 includes: the battery mounting portion 21 corresponds to the first groove 111 in the vertical direction, and the battery module 5 is detachably mounted on the battery mounting portion 21. Therefore, as shown in fig. 2, after the assembly of the body assembly 100 is completed, the battery module 5 can be taken and placed better by the cooperation of the first groove 111 and the battery mounting portion 21, and compared with the prior art in which the housing needs to be disassembled to replace the battery module 5, the structure is more reasonable.

Further, referring to fig. 1-5, the battery cover plate 3 is adapted to cooperate with the first groove body 111 and is clamped on the first fixing frame 2 or the first groove body 111, so that the battery cover plate 3 can better protect the battery located in the first mounting groove 211 through the cooperation of the first protrusion 212 and the first groove body 111, and meanwhile, the battery cover plate 3 can be easily clamped in contact with the first groove body 111, so that the battery can be conveniently taken and placed.

According to the utility model discloses unmanned vehicles's fuselage assembly 100, through last casing 11 and lower casing 12 can protect the inside spare part of fuselage 1 assembly betterly, through setting up first cell body 111 and battery installation department 21, can be comparatively simple realization battery module 5 get put, through setting up battery apron 3, can fix battery module 5 better, prevent that unmanned vehicles 1000 flies in-process battery module 5 and drops, structural layout is reasonable, has promoted user experience.

In some examples, the upper surface of the battery cover plate 3 and the upper surface of the aircraft body 1 can form a streamline structure, so that air resistance in the flight process can be effectively reduced, and the flight capability of the unmanned aerial vehicle 1000 is enhanced.

In a specific example, the fuselage 1 has a first symmetrical center line, the center of gravity of the aircraft falls on the first symmetrical center line of the fuselage 1, the balance stability of the aircraft 1000 is improved, the fuselage 1 is streamlined, the head is parabolic in shape, and the middle section and the rear section gradually shrink to the tail, so that the air resistance of the unmanned aircraft 1000 in the flying process can be well reduced, and the horizontal flying speed of the aircraft is improved.

In other examples, the fuselage 1 may have other shapes, and the streamlining may reduce the air resistance better, but is not a limitation of the present invention.

In some embodiments of the utility model, as shown in fig. 7-9, be formed with first mounting groove 211 on the battery installation department 21, at least some cooperations of battery module 5 are installed in first mounting groove 211, upwards convex first protruding 212 is formed to circumference of first mounting groove 211, first protruding 212 cooperation is installed in first cell body 111, that is to say, cooperation through first protruding 212 and first cell body 111, can fix a position between first fixed frame 2 and the last casing 11 betterly, need not pass through under the help of extra fastener such as structure such as bolt simultaneously, alright realize the assembly between first fixed frame 2 and the last casing 11, the structure is comparatively reasonable.

In one specific example, the battery module 5 may be entirely placed in the first mounting groove 211.

The utility model discloses a in a specific embodiment, refer to fig. 1, fig. 3, fuselage 1 assembly still includes the fixed frame 4 of second, the fixed frame 4 of second is located in the installation space, and detachably installs at the fixed frame 2 lower extreme of first, and after the fixed frame 2 of first and second cooperates with the fixed frame 4 and connect, the upper end and the 11 inner wall butts of last casing of the fixed frame 2 of first, the lower extreme of the fixed frame 4 of second and the inner wall butts of casing 12 down, therefore, the compact structure nature of fuselage 1 assembly has been promoted, make the structure after connecting comparatively firm.

In a specific embodiment, the first fixing frame 2 has a mounting protrusion extending from the periphery thereof, and the upper casing 11 and the lower casing 12 are fixedly connected to the upper surface and the lower surface of the mounting protrusion, respectively, and the connection manner may be gluing or the like, without limitation, so that the connection stability can be improved well.

As shown in fig. 9 and 10, the battery mounting portion 21 is provided with the locking member 22, the locking member 22 includes a locking portion 221 and a pivot portion 222, the pivot portion 222 rotatably locates the locking portion 221 on the battery mounting portion 21, the locking portion 221 has an unlocking position and a locking position in the rotating direction, after the battery module 5 is mounted in the battery mounting portion 21, the locking portion 221 is located at a movable locking position to lock the battery module 5, and when the locking portion 221 is moved to the unlocking position, the battery module 5 is suitable for being taken out of the battery mounting portion 21. Thus, the battery module 5 can be fixed in the battery mounting portion 21 well, the structure is simple and effective, and the battery can be effectively prevented from falling off in the flying process.

Further, referring to fig. 4, the battery cover plate 3 is formed with a fitting groove 31, the locking portion 221 is formed with a protrusion, and when the locking portion 221 is located at the locking position, the protrusion is adapted to fit into the fitting groove 31, that is, when the protrusion fits into the fitting groove 31, it is indicated that the locking member 22 has fixed the battery module 5 and also has fixed the battery cover plate 3, thereby further effectively preventing the battery from falling off during the flight of the unmanned aerial vehicle 1000.

In the utility model discloses a still another embodiment, be formed with the buckle on one in battery apron 3 and the last casing 11, be formed with on the other in battery apron 3 and the last casing 11 with buckle complex joint groove, can realize the assembly between battery apron 3 and the last casing 11 better through the cooperation in buckle and joint groove, promoted the stability of connecting.

Optionally, the fastener includes a first fastener 32 and a second fastener 33, the first fastener 32 and the second fastener 33 are respectively disposed at two ends of the battery cover plate 3 in the length direction, the upper housing 11 is respectively formed with a first fastening groove and a second fastening groove which are matched with the first fastener 32 and the second fastener 33, and the battery cover plate 3 can be firmly connected with the upper housing 11 through the first fastener 32 and the second fastener 33 which are respectively matched with the first fastening groove and the second fastening groove, so that after the assembly is completed, the battery cover plate 3 can better fix the battery module 5.

In some embodiments of the present invention, as shown in fig. 9, the fuselage assembly 100 further includes a control module 6 and an aerial survey module 7, the control module 6 and the aerial survey module 7 are detachably connected to the first fixing frame 2, the battery module 5 is adjacent to the front end of the installation space, the control module 6 is adjacent to the rear end of the installation space, and the aerial survey module 7 is located between the battery module 5 and the control module 6 to adjust the center of gravity of the fuselage 1 assembly. That is to say, the gravity center of the aerial survey module 7 after adjustment can better balance the stress difference of the front end and the rear end of the aircraft body assembly caused by different installation positions, weights and other factors of the battery module 5 and the control module 6, the aircraft body 1 is reasonable in structural layout, and the stability of the aircraft 1000 in the flight process is further improved.

In a specific example, the assembled battery module 5, the control module 6 and the aerial measurement module 7 all have a second symmetric center line, and the first symmetric center line and the second symmetric center line are coplanar, so that the balance of the fuselage 1 assembly is further ensured, and the unmanned aerial vehicle 1000 can fly smoothly.

In an embodiment of the present invention, as shown in fig. 6 to 8, the first fixed frame 2 further comprises: the wing installation part 23 is located at the rear end of the battery installation part 21, a plurality of first fixing parts 231 extending in the width direction of the first fixing frame 2 are arranged on the wing installation part 23, the plurality of first fixing parts 231 are symmetrically arranged along the first symmetric center line, and the wings of the unmanned aerial vehicle 1000 are suitable for being installed on the first fixing parts 231.

Therefore, the wings after assembly are symmetrical relative to the first symmetrical center line, the balance of the unmanned aerial vehicle 1000 can be well kept, the center of gravity is stable, and the structural layout is reasonable.

Preferably, the wings may be made of a lightweight material such as foam to reduce the weight of the unmanned aerial vehicle 1000, and a streamline transition is formed between the wings and the fuselage 1 to further reduce the air resistance during flight.

The utility model also provides an unmanned vehicles 1000 with above-mentioned fuselage assembly 100.

According to the utility model discloses unmanned vehicles 1000, unmanned vehicles 1000 includes: fuselage assembly 100, nose 101, second wing section 102, wingtip winglet 103, rotor arms 105, tail wing 108, dual rotor power components 106, and fixed wing power components 107.

The machine head 101 is detachably disposed at the front end of the machine body assembly 100, and preferably, a receiving cavity is formed in the machine head 101.

As shown in fig. 11, the second wing section 102 is symmetrically disposed on both sides of the fuselage assembly 100, and the winglet 103 is disposed at the front end of the second wing section 102 and forms an angle with the second wing section 102, so that the winglet 103 can better prevent the air from flowing around the upper and lower surfaces of the second wing section 102, thereby reducing the damage of the air flowing around to the lift force.

In a specific example, the fuselage 1 and the second wing section 102 are connected by a fixing member 110, an aileron 104 is further disposed at a trailing edge position of the second wing section 102, the aileron 104 can be flipped up and down relative to the fuselage 1 to control the flight attitude of the unmanned aerial vehicle 1000, the aileron 104 includes an upper surface and a lower surface opposite to each other, the upper surface is substantially flush with the top surface of the second wing section 102, and the lower surface of the aileron 104 is substantially flush with the bottom surface of the second wing section 102. Preferably, a steering engine capable of controlling the ailerons 104 to turn is arranged in the first wing section 6, so as to control the flight direction of the unmanned aerial vehicle 1000. Specifically, the steering wheel sets up in mounting 110, and the output shaft of multistage steering wheel is worn out along mounting 110's lateral wall to be connected with aileron 104 through coupling assembling and rotate in order to drive aileron 104.

In some examples, the wing includes, but is not limited to, the second wing section 102, and may include a third wing section and a fourth wing section, and may be configured according to the size of the unmanned aerial vehicle 1000, and is not limited thereto, and the connection between the wing sections is the same as the connection between the fuselage 1 and the second wing section 102.

Furthermore, rotor arms 105 perpendicular to the second wing section 102 are arranged on the second wing section 102, two dual-rotor power assemblies 106 are arranged on each rotor arm 105 and are respectively arranged on two sides of the wing, the dual-rotor power assemblies 106 are symmetrically arranged on the rotor arms 105 on two sides of the second wing section 102 relative to the fuselage 1, the tail wing 108 is in an inverted V-tail layout, and tail support rods 109 at two ends of a V shape are connected with the rotor arms 105.

In a specific example, the tail wing 108 includes two tail wing plates, the two tail wing plates are pivoted with each other, are arranged in an inverted V shape, and can be folded with each other, so that the storage space of the tail wing 108 can be reduced when the tail wing 108 is detached, and in addition, a movable control surface is installed at the rear edge of the tail wing plates, so that the inverted V-shaped tail wing 108 has the engineering of a normal fixed wing vertical tail and a normal tail, the structure weight is small, and the control efficiency is high. In some examples, tail 108 may also employ a double-droop tail or other configuration of tail.

Optionally, the fixed-wing power assembly 107 adopts a tail-push propeller layout, and a driving motor shaft is connected to a carbon fiber thrust propeller and is located at a tail portion of the fuselage assembly 100, wherein the fixed-wing power assembly 107 can provide a horizontal flight driving force for the unmanned aerial vehicle 1000, and after the unmanned aerial vehicle 1000 reaches a certain horizontal flight speed, the wings can provide sufficient lift force for the unmanned aerial vehicle 1000, so as to ensure that the unmanned aerial vehicle 1000 can normally fly.

In other examples, dual rotor power assembly 106 includes a carbon fiber propeller coupled to a brushless dc motor shaft, a brushless dc motor coupled to rotor arm 105 via a motor mount, and a motor mount, whereby dual rotor power assembly 106 provides VTOL flight capability for UAV 1000, i.e., enables UAV 1000 to better VTOL and hover.

According to the utility model discloses unmanned vehicles 1000, through bispin wing power component 106 and fixed wing power component 107, make unmanned vehicles 1000 take off and land with zero speed, and have the ability of hovering, appearance design through streamlined setting, air component when having reduced the flight, flight speed has been promoted, aerial survey module 9 can make unmanned vehicles 1000 carry out aerial photography survey and drawing betterly simultaneously, electric power is patrolled and examined, the personnel of not being convenient for the investigation operation of going on such as environmental monitoring and disaster inspection, and is rational in infrastructure, flight is stable, the application scene is wide.

Other constructions and operations of the fuselage assembly 100 of an unmanned aerial vehicle according to embodiments of the 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 terms "some embodiments," "optionally," "further," or "some examples," etc., 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 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 (9)

1. A fuselage assembly (100) of an unmanned aerial vehicle, comprising:

the novel multifunctional aircraft engine comprises an engine body (1), wherein the engine body (1) comprises an upper shell (11) and a lower shell (12), an installation space is formed between the upper shell (11) and the lower shell (12), and a first groove body (111) penetrating through the upper shell (11) is formed in the upper shell (11);

first fixed frame (2), first fixed frame (2) are located in the installation space, first fixed frame (2) include: a battery mounting part (21), wherein the battery mounting part (21) corresponds to the first groove body (111) in the vertical direction, and a battery module (5) is detachably mounted on the battery mounting part (21);

the battery cover plate (3) is suitable for being matched with the first groove body (111) and clamped on the first fixing frame (2) or the first groove body (111);

the battery locking device is characterized in that a locking piece (22) is arranged on the battery mounting part (21), the locking piece (22) comprises a locking part (221) and a pivoting part (222), the locking part (221) is rotatably arranged on the battery mounting part (21) by the pivoting part (222), the locking part (221) is provided with an unlocking position and a locking position in the rotating direction, and after the battery module (5) is mounted in the battery mounting part (21), the locking part (221) is suitable for moving to the locking position to lock the battery module (5); when the locking part (221) moves to the unlocking position, the battery module (5) is suitable for being taken out of the battery mounting part (21).

2. The unmanned aerial vehicle's fuselage assembly (100) of claim 1, characterized in that, be formed with first mounting groove (211) on battery installation department (21), at least some cooperation of battery module (5) is installed in first mounting groove (211), be formed with first arch (212) of upwards bulging on the circumference of first mounting groove (211), first arch (212) cooperation is installed in first cell body (111).

3. The unmanned aerial vehicle's fuselage assembly (100) of claim 1 or 2, characterized in that, still include the fixed frame of second (4), the fixed frame of second (4) is located in the installation space, and detachably installs first fixed frame (2) lower extreme, and after first fixed frame (2) with the cooperation of the fixed frame of second (4) is connected, the upper end of first fixed frame (2) with go up casing (11) inner wall butt, the lower extreme of the fixed frame of second (4) with the inner wall butt of casing (12) down.

4. The fuselage assembly (100) of an unmanned aerial vehicle according to claim 1, wherein the battery cover plate (3) is formed with a mating groove (31), and the locking portion (221) is formed with a projection adapted to fit into the mating groove (31) when the locking portion (221) is in the locked position.

5. The fuselage assembly (100) of the unmanned aerial vehicle according to claim 1, wherein a snap is formed on one of the battery cover plate (3) and the upper housing (11), and a snap groove that mates with the snap is formed on the other of the battery cover plate (3) and the upper housing (11).

6. The fuselage assembly (100) of the unmanned aerial vehicle according to claim 5, wherein the fastener comprises a first fastener (32) and a second fastener (33), the first fastener (32) and the second fastener (33) are respectively disposed at two ends of the battery cover plate (3) in the length direction, and a first clamping groove and a second clamping groove which are matched with the first fastener (32) and the second fastener (33) are respectively formed on the upper shell (11).

7. The fuselage assembly (100) of the unmanned aerial vehicle of claim 1, further comprising a control module (6) and an aerial survey module (7), the control module (6) and the aerial survey module (7) each being detachably connected to the first fixed frame (2), the battery module (5) being adjacent to the front end of the installation space, the control module (6) being adjacent to the rear end of the installation space, the aerial survey module (7) being located between the battery module (5) and the control module (6) to adjust the center of gravity of the fuselage assembly (100).

8. The fuselage assembly (100) of an unmanned aerial vehicle according to claim 1, wherein the first fixed frame (2) further comprises: wing installation department (23), wing installation department (23) are located the rear end of battery installation department (21), be equipped with a plurality of first fixed part (231) that extend along first fixed frame (2) width direction on wing installation department (23), it is a plurality of first fixed part (231) set up along the central line symmetry, unmanned vehicles's wing is suitable for to install on first fixed part (231).

9. An unmanned aerial vehicle (1000), comprising:

a fuselage assembly (100), the fuselage assembly (100) comprising the fuselage assembly (100) of any one of claims 1 to 8;

the machine head (101) is detachably arranged at the front end of the machine body assembly (100);

the second wing sections (102), the second wing sections (102) are symmetrically arranged on two sides of the fuselage assembly (100);

the wingtip winglet (103) is arranged at the front end of the second wing section (102), and an included angle is formed between the wingtip winglet (103) and the second wing section (102);

the double-rotor wing power assembly comprises rotor wing arms (105), a tail wing (108), double-rotor wing power assemblies (106) and fixed wing power assemblies (107), wherein the rotor wing arms (105) parallel to the second wing section (102) are arranged on the second wing section (102), two double-rotor wing power assemblies (106) are arranged on each rotor wing arm (105) and are respectively arranged on two sides of the second wing section (102), the double-rotor wing power assemblies (106) are symmetrically arranged on the rotor wing arms (105) on two sides of the second wing section (102) relative to a fuselage (1), the tail wing (108) is of an inverted V-shaped structure, and the end parts of the tail wing power assemblies are connected with the rotor wing arms (105) through tail stay bars (109); the fixed wing power component (107) is arranged at the tail part of the fuselage assembly (100).

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