CN213443067U - Unmanned vehicles's fuselage assembly and unmanned vehicles who has it - Google Patents

Abstract

The utility model provides an unmanned vehicles's fuselage assembly and unmanned vehicles who has it, the fuselage assembly includes: fuselage and first fixed frame. The machine body is provided with a first symmetrical center line and comprises an upper shell and a lower shell, and an installation space is formed between the upper shell and the lower shell; in installation space was located to first fixed frame, battery module, control module, aerial survey module all can dismantle with first fixed frame and link to each other, and the front end of the neighbouring installation space of battery module, the rear end of the neighbouring installation space of control module, aerial survey module are located between battery module and the control module to the focus of adjustment fuselage assembly, and battery module, control module and aerial survey module are relative first symmetrical center line symmetrical arrangement. According to the utility model discloses unmanned vehicles's fuselage assembly is simple, and structural layout is reasonable, and the focus is stable, has higher integrated level.

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

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 is simple, and structural layout is reasonable, and the focus is stable, has higher integrated level.

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, unmanned vehicles's fuselage assembly includes: the device comprises a machine body, a first positioning device and a second positioning device, wherein the machine body is provided with a first symmetrical center line and comprises an upper shell and a lower shell, and an installation space is formed between the upper shell and the lower shell; first fixed frame, first fixed frame is located in the installation space, battery module, control module, aerial survey module all with first fixed frame can be dismantled continuously, battery module is neighbouring the front end of installation space, control module is neighbouring the rear end of installation space, aerial survey module is located battery module with between the control module to the focus of adjustment fuselage assembly, just battery module control module with aerial survey module is relative first symmetrical center line symmetrical arrangement.

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, install electric core module, control module and aerial survey module on first fixed frame simultaneously, the focus of aerial survey module adjustment fuselage assembly after the assembly, and electric core module, control module, aerial survey module and the equal symmetry of fuselage, from this, the fuselage assembly of this application is simple, and structural layout is reasonable, and the focus is stable, has higher integrated level.

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

the utility model discloses an in some embodiments, be formed with first cell body on the upper shell body, be formed with the second cell body on the lower casing, be formed with the ascending first mounting groove of opening on the first fixed frame, battery module is suitable for to be installed in the first mounting groove, upwards convex first arch is formed with to the week of first mounting groove, first protruding cooperation is installed in first cell body.

Preferably, the fuselage assembly further comprises: the battery cover plate is suitable for being matched with the first groove body and clamped on the first groove body, and the upper surface of the battery cover plate is located in the same arc-shaped surface with the upper surface of the machine body.

In other embodiments of the present invention, the fuselage assembly further comprises: the fixed frame of second, be formed with the second mounting groove that the opening is decurrent on the fixed frame of second, the aerial survey module is suitable for to be installed in the second mounting groove, the lower surface of the fixed frame of second with the lower surface of casing is in same cambered surface down.

Optionally, the fuselage assembly of the unmanned aerial vehicle further comprises: fill the shell, the aerial survey module is installed back in the second mounting groove, fill the shell be suitable for with the cooperation of second mounting groove, in order to incite somebody to action the aerial survey module seals in the second mounting groove, just fill the lower surface of shell the lower surface of the fixed frame of second with the lower surface of casing is in same cambered surface down.

Optionally, first fixed frame with at least one in the fixed frame of second is formed with at least one spliced pole, first fixed frame with be formed with the connecting hole on another in the fixed frame of second, the fastener is suitable for to pass the connecting hole with the spliced pole cooperation, with will the fixed frame of first fixed frame and second is fixed continuous.

Optionally, the first fixed frame comprises: a battery mounting part on which the first mounting groove is formed; the wing installation department, the wing installation department is located the rear end of battery installation department, be equipped with a plurality of first fixed parts that extend along first fixed frame width direction on the wing installation department, it is a plurality of first fixed part is followed first symmetrical center line symmetry sets up, unmanned vehicles's wing is suitable for to install on the first fixed part.

Further, the fuselage assembly of unmanned vehicles still includes: first wing, two first wing is located respectively symmetrically the both sides of fuselage, first wing includes along upper and lower direction can dismantle consecutive last wing and lower wing, go up the wing with at least one in the wing down is formed with the edge the constant head tank that fuselage width direction extends, first fixed part includes: the fixing rod is suitable for being installed on the fixing hole in a matched mode, and the fixing rod exposed out of the fixing hole is suitable for being matched with the positioning groove.

According to the utility model discloses further embodiment, 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 first mounting groove, 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 first mounting groove.

Optionally, the second fixed frame comprises: the control installation part is provided with a control installation groove with an upward opening, an installation space is formed between the control installation groove and the first fixing frame, and the control module is arranged in the control installation space; the aerial survey installation department, be formed with on the aerial survey installation department the second mounting groove, in the direction from bottom to top, the sectional area of second mounting groove reduces gradually.

The utility model discloses still provide an unmanned vehicles who has unmanned vehicles fuselage assembly of above-mentioned embodiment.

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 bispin wing 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 inconvenient for going on such as environmental monitoring and disaster inspection, 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 the lower shell side of the fuselage assembly of the unmanned aerial vehicle without a filler shell according to an embodiment of the invention;

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

FIG. 6 is a cross-sectional view of FIG. 5;

FIG. 7 is an enlarged view of area A of FIG. 6;

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

fig. 9 is a schematic structural view of a top side of a second fixed frame of a fuselage assembly of an unmanned aerial vehicle according to an embodiment of the invention;

fig. 10 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. 11 is a schematic structural view of the bottom side of the first fixed frame of the fuselage assembly of the unmanned aerial vehicle according to an embodiment of the invention;

fig. 12 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. 13 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. 14 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;

fig. 15 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.

Reference numerals:

100: a fuselage assembly of the unmanned aerial vehicle;

1: a body; 11: a first center line of symmetry; 12: an upper housing; 121: a first tank body; 13: a lower housing; 131: a second tank body;

2: a first fixed frame; 21: a first mounting groove; 22: a first protrusion; 23: a locking member; 231: a locking part; 232: a pivot part; 24: a first fixed part; 241: fixing the rod; 242: a fixing hole; 25: connecting columns; 26: a battery mounting portion; 27: a wing mounting portion;

3: a second fixed frame; 31: a second mounting groove; 32: a control mounting part; 33: controlling the mounting groove; 35: connecting holes;

4: a battery cover plate; 41: a first fastener; 42: a second fastener;

5: filling the shell;

6: a first wing section; 61: an upper wing section; 62: a lower wing section; 63: a fixing member;

7: a battery module; 8: a control module; 9: 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.

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 15.

According to the utility model discloses unmanned vehicles's fuselage assembly 100 includes: a body 1 and a first fixed frame 2.

Specifically, the fuselage 1 has a first center line of symmetry 11, and the center of gravity of the aircraft falls on the first center line of symmetry 11 of the fuselage 1, so that the balance stability of the unmanned aerial vehicle 1000 is improved.

As shown in fig. 1, the body 1 includes an upper shell 12 and a lower shell 13, and an installation space is formed between the upper shell 12 and the lower shell 13, so that the installation space can better place and fix the components of the body assembly 100, and plays a certain role in protection.

Further, first fixed frame 2 is located in the installation space, and battery module 7, control module 8, aerial survey module 9 all can dismantle with first fixed frame 2 and link to each other, and battery module 7 is close to the front end of installation space, and control module 8 is close to the rear end of installation space, and aerial survey module 9 is located between battery module 7 and the control module 8 to the focus of adjustment fuselage assembly 100, and battery module 7, control module 8 and aerial survey module 9 are relative first symmetrical center line symmetrical arrangement.

That is to say, after the battery module 7, the control module 8 and the aerial survey module 9 are assembled on the first fixed frame 2, because of being symmetrical relative to the first symmetrical center line 11, the gravity center of the aerial survey module 9 after being adjusted can better balance uneven stress on the front end and the rear end of the fuselage assembly 100 caused by different installation positions, different weights and other factors of the battery module 7 and the control module 8, and further improve the stability of the flight process of the aircraft.

According to the utility model discloses unmanned vehicles's fuselage assembly 100 can protect the inside spare part of fuselage assembly 100 better through last casing 12 and lower casing 13, installs battery module 7, control module 8 and aerial survey module 9 on first fixed frame 2 simultaneously, and the focus of aerial survey module 9 adjustment fuselage assembly 100 after the assembly, and battery module 7, control module 8, aerial survey module 9 and fuselage 1 homogeneous phase are relative 11 symmetries of first symmetry central line, from this, fuselage assembly 100 of this application assembles simply, and structural layout is reasonable, and the focus is stable, has higher integrated level.

In some examples, fuselage 1 is streamlined, and the head appearance is the parabola, and well back end shrinks gradually to the afterbody, from this, can be so that can reduce the aerodynamic drag of unmanned vehicles 1000 flight in-process betterly, promotes the flying speed of aircraft, and fuselage 1 also can be for other shapes, and the streamlined is convenient for promote flight ability, but not right the utility model discloses a restriction.

In some embodiments of the present invention, the first groove 121 is formed on the upper case 12, the second groove 131 is formed on the lower case 13, the first mounting groove 21 with the upward opening is formed on the first fixing frame 2, the battery module 7 is suitable for being mounted in the first mounting groove 21, the first protrusion 22 protruding upward is formed in the circumferential direction of the first mounting groove 21, and the first protrusion 22 is cooperatively mounted in the first groove 121. Therefore, the battery can be directly installed in the first installation groove 21 through the first groove body 121, and compared with the prior art that the battery can be replaced by detaching the machine body shell, the structure is more reasonable. In addition, through the cooperation of first arch 22 with first cell body 121, can realize the installation location between first fixed frame 2 and the last casing 12 better, need not simultaneously through the help of structures such as extra fastener for example bolt under, alright in order to realize the assembly between first fixed frame 2 and the last casing 12, the structure is comparatively reasonable.

In a specific embodiment, the first fixing frame 2 has a mounting protrusion extending from the periphery thereof, and the upper casing 12 and the lower casing 13 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, which is not limited herein, so that the connection stability can be improved well.

Optionally, fuselage assembly 100 still includes battery apron 4, battery apron 4 is suitable for with the cooperation of first cell body 121, and the joint is on first cell body 121, the upper surface of battery apron 4 is in same cambered surface with the upper surface of fuselage 1, from this, through first arch 22 with the cooperation of first cell body 121, battery apron 4 can protect the battery that is located first mounting groove 21 betterly, and simultaneously, battery apron 4 can be comparatively light with first cell body 121 contact joint, the operation of getting of the battery of being convenient for, and is rational in infrastructure, user experience has been promoted.

The upper surface of the battery cover plate 4 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 capacity of the unmanned aerial vehicle 1000 is enhanced.

In an embodiment, referring to fig. 12, a first fastening part 41 and a second fastening part 42 are disposed on the battery cover plate 4, a first fastening part is formed on the first fastening part 41, a second fastening part is formed on the second fastening part 42, a fastening groove is formed on an inner side wall of the first mounting groove 21, and the first fastening part and the second fastening part cooperate to further fix the battery.

As shown in fig. 1-4, the fuselage assembly 100 further includes: the fixed frame 3 of second, the fixed frame 3 of second is formed with the second mounting groove 31 that the opening is decurrent, aerial survey module 9 is suitable for installing in second mounting groove 31, the lower surface of the fixed frame 3 of second is in same cambered surface with lower casing 13's lower surface, can keep down casing 13's streamlined from this betterly, reduce the air resistance of flight in-process, can have certain guard action to aerial survey module 9 through second mounting groove 31, it can be understood, aerial survey module 9 generally comprises comparatively fragile camera lens, therefore, second mounting groove 31 has avoided unmanned vehicles 1000 flight in-process aerial survey module 9 to receive the condition emergence of influence effectively.

Optionally, as shown in fig. 3, the fuselage assembly 100 further comprises: and after the filling shell 5 and the aerial survey module 9 are installed in the second installation groove 31, the filling shell 5 is suitable for being matched with the second installation groove 31 so as to seal the aerial survey module 9 in the second installation groove 31, and the lower surface of the filling shell 5, the second fixing frame 3 and the lower surface of the lower shell 13 are in the same arc-shaped surface.

Therefore, the filling shell 5 can well protect the aerial survey module 9 after assembly is completed, and the lower surface of the filling shell 5, the second fixing frame 3 and the lower surface of the lower shell 13 can form a streamline structure, so that aerodynamic force of the unmanned aerial vehicle 1000 can be effectively prevented from being influenced, and the flight capacity of the unmanned aerial vehicle 1000 is enhanced.

It should be noted that an opening which does not block the shooting angle of the aerial survey module 9 is formed on the lower surface of the filling shell 5, so that the aerial survey module 9 is protected and the normal operation of the aerial survey module 9 is not affected.

Alternatively, with reference to fig. 6 to 11, at least one of the first and second fixed frames 2 and 3 is formed with at least one connecting post 25, and the other of the first and second fixed frames 2 and 3 is formed with a connecting hole 35, and a fastener is adapted to pass through the connecting hole 35 to cooperate with the connecting post 25 to fixedly connect the first and second fixed frames 2 and 3. This enables the first fixed frame 2 and the second fixed frame 3 to be connected to each other well, and maintains the stability of the connection structure of the body assembly 100.

In one embodiment as shown in fig. 11, the first fixing frame 2 is formed with a plurality of connecting posts 25, and as shown in fig. 9, the second fixing frame 3 is formed with a plurality of connecting holes 35 corresponding thereto, so that the stability of connection is further improved by the cooperation of the plurality of connecting posts 25 and the plurality of connecting holes 35.

Optionally, the first fixed frame 2 comprises: a battery mount 26 and a wing mount 27.

Specifically, the first mounting groove 21 is formed on the battery mounting portion 26, the wing mounting portion 27 is located at the rear end of the battery mounting portion 26, the wing mounting portion 27 is provided with a plurality of first fixing portions 24 extending in the width direction of the first fixing frame 2, the first fixing portions 24 are symmetrically arranged along the first symmetric center line 11, and the wings of the unmanned aerial vehicle 1000 are adapted to be mounted on the first fixing portions 24. Therefore, after the wing assembly is completed, the positions of the wings are also symmetrical relative to the first symmetrical center line 11, so that the balance of the unmanned aerial vehicle 1000 can be well kept, the flight process is stable, and the structural layout is reasonable.

Further, the fuselage assembly 100 further comprises: first wing section 6, the both sides of fuselage 1 are located respectively to two first wing sections 6 symmetries, and with fuselage 1 integrated into one piece, and first wing section 6 includes can dismantle continuous last wing section 61 and lower wing section 62 along upper and lower direction, is formed with the constant head tank that extends along fuselage 1 width direction on at least one in last wing section 61 and the lower wing section 62, and first fixed part 24 includes: a fixing rod 241 and a fixing hole 242, the fixing hole 242 being formed on the wing mounting portion 27, the fixing rod 241 being adapted to be fitted to the fixing hole 242, a portion of the fixing rod 241 exposed from the fixing hole 242 being adapted to be fitted with the positioning groove.

In a specific example, as shown in fig. 5, two sets of symmetrically arranged fixing holes 242 are formed on the wing mounting portion 27, wherein the fixing rods 241 on each set of symmetrically arranged fixing holes 242 have the same length, and as shown in fig. 1, positioning grooves are formed on opposite side surfaces of the upper wing section 61 and the lower wing section 62, and after the assembly is completed, the positioning grooves are tightly abutted to the outer peripheral surface of the fixing rods 241, and the lower surface of the assembled upper wing section 61 is tightly abutted to the upper surface of the second wing section 102, so as to fix the positions of the first wing section 6 and the second wing section 102.

Preferably, the wing may be made of a light material such as foam to reduce the weight of the unmanned aerial vehicle 1000, the upper wing section 61 and the lower wing section 62 are integrally formed during production, and the upper wing section 61 and the lower wing section 62 respectively form a streamline transition with the shell and the lower shell 13, so as to further reduce the air resistance during flight.

In some examples, as shown in fig. 5 and 6, the battery mounting portion 26 is provided with a locking member 23, which includes a locking portion 231 and a pivot portion 232, the pivot portion 232 rotatably locates the locking portion 231 on the battery mounting portion 26, the locking portion 231 has an unlocking position and a locking position in the rotating direction, after the battery module 7 is mounted in the first mounting groove 21, the locking portion 231 is adapted to move to the locking position to lock the battery module 7, and when the locking portion 231 moves to the unlocking position, the battery module 7 is adapted to be taken out from the first mounting groove 21. Therefore, the battery module 7 can be well fixed in the first mounting groove 21, the structure is simple and effective, and the battery module 7 is effectively prevented from falling off.

Preferably, as shown in fig. 12, a mating groove is formed on the battery cover plate 4, the mating groove is adapted to receive the locking member 23, when the locking member 23 is mated on the mating groove, it is described that the second locking portion is already mated with the locking groove of the first mounting groove 21, and the battery cover plate 4 is fixed, so as to further effectively prevent the battery module 7 from falling off during the flight of the unmanned aerial vehicle 1000.

Optionally, the second fixed frame 3 comprises: control installation department 32 and aerial survey installation department (not marked in the figure), wherein, be formed with the ascending control mounting groove 33 of opening on the control installation department 32, be formed with installation space between control mounting groove 33 and the first fixed frame 2, control module 8 locates in the installation space, from this the protection to control module 8 can be realized better to the fixed frame 3 of first fixed frame 2 and second for unmanned vehicles 1000 can be normal receive control module 8's instruction, can not receive external factor easily and influence.

In fact, be formed with second mounting groove 31 on the aerial survey installation department, on the direction from bottom to top, the sectional area of second mounting groove 31 reduces gradually, that is to say, the internal face of second mounting groove 31 is the inclined plane for when external force collision extrusion is received at second mounting groove 31, difficult emergence deformation, and then the assurance sets up in aerial survey module 9's wherein safe in utilization.

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 still includes: a nose 101, a second wing section 102, a wingtip winglet 103, a rotor arm 105, a tail wing 108, a dual rotor power assembly 106, and a fixed wing power assembly 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. 15, 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 first wing section 6 and the second wing section 102 are connected by a fixing member 63, 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 realize controlling the flight attitude of the unmanned aerial vehicle 1000, the aileron 104 includes an upper surface and a lower surface which are opposite to each other, the upper surface is approximately flush with the top surface of the second wing section 102, and the lower surface of the aileron 104 is approximately 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 63, and the output shaft of multistage steering wheel passes through along the lateral wall of mounting 63 to be connected with aileron 104 through coupling assembling in order to drive aileron 104 and rotate.

In some examples, the wing includes, but is not limited to, the first wing panel 6 and the second wing panel 102, and may include a third wing panel and a fourth wing panel, and may be configured according to the size of the unmanned aerial vehicle 1000, and is not limited thereto, and the connection between these wing panels is the same as the connection between the first wing panel 6 and the second wing panel 102.

Furthermore, a rotor arm 105 parallel to the second wing section 102 is 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 stay 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, the rear edges of the tail wing plates are provided with movable control surfaces, so that the inverted V-shaped tail wing 108 has the functions of a normal fixed wing vertical tail and a normal tail, the structural 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, the air resistance when having reduced the flight, flight speed has been promoted, aerial survey module 9 can make unmanned vehicles 1000 carry out the mapping of taking photo by plane betterly simultaneously, electric power patrols and examines, the personnel of not being convenient for the investigation operation 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 (11)

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

the airplane body (1), wherein the airplane body (1) is provided with a first symmetrical center line (11), the airplane body (1) comprises an upper shell (12) and a lower shell (13), and an installation space is formed between the upper shell (12) and the lower shell (13);

first fixed frame (2), first fixed frame (2) are located in the installation space, battery module (7), control module (8), aerial survey module (9) all with first fixed frame (2) can be dismantled and link to each other, battery module (7) are neighbouring the front end of installation space, control module (8) are neighbouring the rear end of installation space, aerial survey module (9) are located battery module (7) with between control module (8) to the focus of adjustment fuselage assembly (100), just battery module (7) control module (8) with aerial survey module (9) are relative first symmetrical center line symmetrical arrangement.

2. The unmanned aerial vehicle's fuselage assembly (100) of claim 1, characterized in that, be formed with first cell body (121) on last casing (12), be formed with second cell body (131) on lower casing (13), be formed with the ascending first mounting groove (21) of opening on the first fixed frame (2), battery module (7) are suitable for to be installed in first mounting groove (21), be formed with the first arch (22) of upwards protrusion in the circumference of first mounting groove (21), first protruding (22) cooperation is installed in first cell body (121).

3. The fuselage assembly (100) of the unmanned aerial vehicle of claim 2, further comprising: battery apron (4), battery apron (4) be suitable for with first cell body (121) cooperation, and the joint is in on first cell body (121), the upper surface of battery apron (4) with the upper surface of fuselage (1) is in same cambered surface.

4. The fuselage assembly (100) of the unmanned aerial vehicle of claim 1, wherein the fuselage assembly (100) further comprises: the fixed frame of second (3), be formed with second mounting groove (31) that open side down on the fixed frame of second (3), aerial survey module (9) are suitable for to be installed in second mounting groove (31), the lower surface of the fixed frame of second (3) with the lower surface of lower casing (13) is in same cambered surface.

5. The fuselage assembly (100) of the unmanned aerial vehicle of claim 4, further comprising:

pack shell (5), aerial survey module (9) are installed back in second mounting groove (31), pack shell (5) be suitable for with second mounting groove (31) cooperation, with aerial survey module (9) are sealed in second mounting groove (31), just the lower surface of packing shell (5) the lower surface of the fixed frame of second (3) with the lower surface of casing (13) is in same cambered surface down.

6. The fuselage assembly (100) of an unmanned aerial vehicle according to claim 4, characterized in that at least one of the first fixed frame (2) and the second fixed frame (3) is formed with at least one connecting post (25), a connecting hole (35) is formed on the other of the first fixed frame (2) and the second fixed frame (3), a fastener is suitable for passing through the connecting hole (35) with the connecting post (25) cooperates in order to fixedly connect the first fixed frame (2) and the second fixed frame (3).

7. The fuselage assembly (100) of an unmanned aerial vehicle according to claim 2, wherein the first fixed frame (2) comprises:

a battery mounting portion (26), the first mounting groove (21) being formed on the battery mounting portion (26);

wing installation department (27), wing installation department (27) are located the rear end of battery installation department (26), be equipped with a plurality of first fixed part (24) that extend along first fixed frame (2) width direction on wing installation department (27), it is a plurality of first fixed part (24) are followed first symmetry central line (11) symmetry sets up, unmanned vehicles's wing is suitable for to install on first fixed part (24).

8. The fuselage assembly (100) of the unmanned aerial vehicle of claim 7, further comprising: first wing panel (6), two first wing panel (6) are located respectively symmetrically the both sides of fuselage (1), first wing panel (6) are including following upper and lower direction and can dismantle consecutive last wing panel (61) and lower wing panel (62), go up wing panel (61) with at least one in lower wing panel (62) is formed with the edge the constant head tank that fuselage (1) width direction extends, first fixed part (24) include: the fixing rod (241) and fixed orifices (242), fixed orifices (242) form on wing installation department (27), fixed rod (241) are suitable for the cooperation to be installed on fixed orifices (242), expose fixed orifice (242) fixed rod (241) be suitable for with the constant head tank cooperation.

9. The unmanned aerial vehicle fuselage assembly (100) of claim 7, wherein a locking piece (23) is disposed on the battery mounting portion (26), the locking piece (23) comprises a locking portion (231) and a pivoting portion (232), the pivoting portion (232) rotatably locates the locking portion (231) on the battery mounting portion (26), the locking portion (231) has an unlocking position and a locking position in a rotation direction, after the battery module (7) is mounted in the first mounting groove (21), the locking portion (231) is adapted to move to the locking position to lock the battery module (7), and when the locking portion (231) moves to the unlocking position, the battery module (7) is adapted to be taken out from the first mounting groove (21).

10. Fuselage assembly (100) of an unmanned aerial vehicle according to claim 4, wherein the second fixed frame (3) comprises:

the control installation part (32) is provided with a control installation groove (33) with an upward opening, an installation space is formed between the control installation groove (33) and the first fixed frame (2), and the control module (8) is arranged in the control installation space;

the aerial survey installation department, be formed with on the aerial survey installation department second mounting groove (31), in the direction from bottom to top, the sectional area of second mounting groove (31) reduces gradually.

11. 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 10;

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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