CN111422344A

CN111422344A - Unmanned aerial vehicle

Info

Publication number: CN111422344A
Application number: CN202010401943.0A
Authority: CN
Inventors: 李季; 王利光
Original assignee: Chengdu Zongheng Dapeng Unmanned Plane Technology Co ltd
Current assignee: Chengdu Zongheng Dapeng Unmanned Plane Technology Co ltd
Priority date: 2020-05-13
Filing date: 2020-05-13
Publication date: 2020-07-17

Abstract

The invention discloses an unmanned aerial vehicle which comprises a fuselage, a horn assembly and a rotor power assembly, wherein the fuselage comprises a shell with an accommodating cavity inside, the horn assembly is rotatably connected to a horn hinged part formed on the wall surface of the shell, and the rotor power assembly is arranged on the horn assembly. The unmanned aerial vehicle is light in structure, the bearing capacity of the unmanned aerial vehicle can be improved, the waste weight of the unmanned aerial vehicle is prevented from being increased, the bearing capacity is improved, the endurance time is prolonged, the occupied volume is effectively reduced by the foldable structure, the space utilization rate is high, the unmanned aerial vehicle is convenient to store, and transportation is facilitated.

Description

Unmanned aerial vehicle

Technical Field

The invention relates to the technical field of aircrafts, in particular to an unmanned aerial vehicle.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device or a self-contained program control device, is widely applied at present, and is well applied in the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection, disaster relief, movie and television shooting, romantic manufacturing and the like. Unmanned aerial vehicle compares with manned aircraft, has characteristics such as small, the cost is low, convenient to use, but unmanned aerial vehicle lightweight degree commonly used at present is lower, adopts structural framework to come parts such as carrier arm, mission equipment usually, but greatly increased unmanned aerial vehicle's dead weight like this, reduced the bearing capacity of aircraft, shortened flight duration.

Disclosure of Invention

The invention aims to solve the technical problems and provide a technical task of improving the prior art, and provides an unmanned aerial vehicle, which solves the problems that the unmanned aerial vehicle in the prior art adopts a structural framework to bear a machine arm and task equipment, so that the waste is heavy, the bearing capacity of the unmanned aerial vehicle is low, and the endurance time is short.

In order to solve the technical problems, the technical scheme of the invention is as follows:

the utility model provides an unmanned aerial vehicle, includes fuselage, horn subassembly and rotor power component, the fuselage including inside have the casing that holds the chamber, the horn subassembly rotate to be connected on the horn articulated portion that the wall of casing formed, rotor power component set up on the horn subassembly. The unmanned aerial vehicle is light in structure, the arm component is directly hinged to the shell, a traditional structural framework is omitted, waste weight of the unmanned aerial vehicle is prevented from being increased, bearing capacity of the unmanned aerial vehicle is improved, the shell is directly used for integrally bearing the arm component and the rotor wing power component on the arm component, waste weight of the unmanned aerial vehicle is effectively reduced, bearing capacity is improved, endurance time is prolonged, the occupied volume is effectively reduced due to the foldable structure, storage is convenient, and transportation is facilitated.

Furthermore, the horn component include main arm and folding arm, rotor power component set up in the main arm on, folding arm one end with the main arm is articulated, the other end is articulated with the casing. The folding state is more compact, the occupied space is reduced, the placement and the transportation are convenient, the unfolding and folding operation is more efficient and convenient, and the main arm is close to the machine body under the rotating action of the folding arm to realize the folding and the unfolding or is far away from the machine body to realize the unfolding.

Furthermore, folding arm be provided with a plurality of along the length direction parallel interval of main arm, it is better to connect the reliability, improves the stability that unmanned aerial vehicle expanded the state, ensures the stability of flight.

Further, folder arm structure including being used for articulated runner assembly, runner assembly include turned angle spare, for turned angle spare pivoted angle setting element and the articulated locking mechanism of action between locking position and unblock position, the turned angle spare is gone up and is rotated the interval and be provided with at least one block portion in week, the angle setting element on be provided with block portion complex location portion, articulated locking mechanism keep location portion and block portion to be in the fit state when being in the locking position. The rotating assembly adopted by the invention has the functions of angle positioning and locking, the rotating angle piece and the angle positioning piece are respectively connected with a component needing to realize hinging, the rotating angle positioning is realized by matching the clamping part on the rotating angle piece with the positioning part on the angle positioning piece, namely, when the angle positioning piece and the rotating angle piece rotate relatively until the positioning part and the clamping part are matched, the rotating angle is in place, the accuracy of the rotating angle is ensured, the excessive rotation or insufficient rotation is avoided, and the current rotating angle state is kept by using the hinging and locking mechanism when the rotating angle is in place, namely, the stable unfolding state or folding state can be kept, the situation that the unfolding state is unstable in the flying process to cause shaking and even accidental folding is avoided, and the dangerous situation that the flying state is unstable to cause crash is avoided, simultaneously also effectively ensure the stability of draw in the state in to the guarantee is placed or the stability of transportation, avoids appearing folding horn structure accident and expandes and lead to appearing colliding with impaired situation, ensures the fail safe nature that unmanned aerial vehicle placed, the transportation.

Furthermore, block portion be the recess, location portion for with recess complex arch, block portion set up on the ascending terminal surface that is close to the angle of rotation setting element along the rotation axis of angle of rotation piece, location portion correspond set up on the ascending terminal surface that is close to the angle of rotation piece along the rotation axis of angle of rotation setting element. The unmanned aerial vehicle is simple in structure, convenient to machine and low in cost, the rotation angle positioning can be accurately realized by the matching of the grooves and the protrusions, and the rotation angle positioning can be accurately realized each time, so that the stability of the flying state of the unmanned aerial vehicle after the unmanned aerial vehicle is unfolded can be ensured, the compactness of the folded state can be ensured, and the situation that the unmanned aerial vehicle is difficult to transport in a case due to the fact that the unmanned aerial vehicle is folded in and has deviation and interferes with an outer package can be avoided.

Furthermore, the hinged locking mechanism comprises a locking block which moves upwards in a direction perpendicular to the rotating shaft, a driving inclined plane which is inclined to the rotating axial direction and is used for pressing the rotating angle piece and the angle positioning piece is arranged on the locking block, the structure is simple, the locking function can be reliably realized, the implementation is convenient, the cost is low, when the locking block moves in the direction perpendicular to the rotating axial direction, the driving inclined plane on the locking block can generate a displacement amount (acting force in the rotating axial direction) in the rotating axial direction, so that the rotating angle piece and the angle positioning piece can be pressed together in the rotating axial direction, the convex positioning part is more tightly inserted into the groove-shaped clamping part, no clearance is reserved between the rotating angle piece and the angle positioning piece in the rotating axial direction, and the convex positioning part can not withdraw from the groove-shaped clamping part, thereby can't take place relative rotation between turned angle spare and the angle setting element, and then realized the current turned angle state of locking, promptly, can keep stable expansion state or furl state. When needs unblock, only need in perpendicular to rotate axial direction in the reverse movement locking piece can to remove turned angle piece and angle setting element and rotate the ascending state that compresses tightly of axial, and then can carry out relative rotation between turned angle piece and the angle setting element, promptly, unmanned aerial vehicle can be in the expansion and draw in the state between switch.

Further, the casing on be provided with task equipment coupling mechanism, it is including installing the machine of installing on unmanned aerial vehicle end and installing the equipment end on task equipment, the machine of carrying serve and be provided with the electric connector, the equipment end on be provided with the electric connector that matches with the electric connector, and the machine of carrying serve and be provided with and supply equipment end male spout to the machine carries and still be provided with the anticreep locking mechanism that prevents equipment end withdraw from the spout between end and the equipment end. The invention integrates the mechanical connection and the electrical connection of the task equipment, namely, the mechanical connection and the fixation of the task equipment on the unmanned aerial vehicle and the electrical connection of the task equipment and an electrical system of the unmanned aerial vehicle are simultaneously realized through the connection of the airborne end and the equipment end, the operation is simple and rapid, the connection reliability is good, the condition that the task equipment is accidentally separated and falls off can be avoided, and the use safety and the use reliability are improved.

Further, anticreep locking mechanism supply the elastic pin male jack including the elastic pin that sets up on the lateral wall of equipment end and set up on the lateral wall of spout, simple structure, implementation convenience, easy operation, locking reliability is high, equipment end inserts and carries automatic realization locking behind the end, effectively prevents unexpected the deviating from, need not the manual work and carries out the operation of locking again after the plug-in operation, avoids appearing forgetting to carry out the produced potential safety hazard of locking operation.

Furthermore, a flying control assembly is fixed in the accommodating cavity of the shell through a shock absorber, the shock absorber comprises a first connecting piece connected with the flying control assembly, a second connecting piece connected with the shell and a plurality of shock absorption wires, two ends of the shock absorption wires are respectively connected with the first connecting piece and the second connecting piece, a first connecting face is formed at the joint of the shock absorption wires on the first connecting piece, a second connecting face is formed at the joint of the shock absorption wires on the second connecting piece, and the first connecting face is inclined to the second connecting face. The vibration damper adopted by the invention has a multidimensional vibration damping function, and can realize vibration damping in the direction parallel to the first connecting surface and the direction vertical to the first connecting surface by taking the first connecting surface as a reference, the traditional vibration damper adopts a plurality of same vibration damping wires to be connected between the first connecting part and the second connecting part, so that the plane formed by the connecting positions of the vibration damping wires on the first connecting part is a plane formed by the connecting positions of the vibration damping wires on the second connecting part, the first connecting part and the second connecting part are mutually parallel, and the traditional vibration damper can only realize the vibration damping function in a single direction (the connecting direction of the first connecting part and the second connecting part), therefore, if the traditional vibration damper is adopted to realize the multidimensional vibration damping, additional vibration dampers are required to be arranged, for example, a group of vibration dampers in the vertical direction are arranged, and if the transverse vibration damping is required to be realized, the vibration absorber adopted by the invention has the advantages that the first connecting surface is inclined to the second connecting surface, so that the vibration absorbing wires connected between the first connecting part and the second connecting part are different in shape and length, the vibration absorbing directions of all the vibration absorbing wires are different, the vibration absorbing wires are combined together to enable the whole vibration absorber to have a good vibration absorbing effect in the multi-dimensional direction, namely, the single vibration absorber realizes multi-dimensional vibration absorption, compared with the traditional vibration absorber, the use number of the vibration absorber can be effectively reduced, the required assembly space is reduced, the structural compactness of the unmanned aerial vehicle is improved, the waste weight is reduced, and the bearing capacity is improved.

Furthermore, the included angle between the first connecting surface and the second connecting surface is 60-70 degrees, and a good vibration reduction effect can be achieved in the multi-dimensional direction.

Compared with the prior art, the invention has the advantages that:

the unmanned aerial vehicle is light in structure, the bearing capacity of the unmanned aerial vehicle can be improved, the waste weight of the unmanned aerial vehicle is prevented from being increased, the bearing capacity is improved, the endurance time is prolonged, the occupied volume is effectively reduced due to the foldable structure, the space utilization rate is high, the unmanned aerial vehicle is convenient to store and is beneficial to transportation;

the unmanned aerial vehicle folding and unfolding device has the advantages that the structure is compact, the unfolding and folding stability is good, the precision is high, the unfolding state and the folding state can be reliably locked, the flight stability and safety are guaranteed, the folding state stability is also guaranteed, and the safety and reliability of the unmanned aerial vehicle in the placing and transporting process are guaranteed;

the quick mounting and dismounting of the task equipment can be realized, different task equipment can be conveniently replaced to realize different functions, the application range is enlarged, mechanical connection and electrical connection are integrally realized, the operation is simple and quick, the connection reliability is high, the safety is high, the automatic locking function is realized, and the condition that the task equipment is accidentally disengaged and falls off can be avoided;

the damping is effectual, can realize the damping of multidimension degree, and required assembly space is little, improves compact structure nature, reduces useless heavy, improves unmanned aerial vehicle bearing capacity.

Drawings

Fig. 1 is a schematic structural diagram of an unfolding state of the unmanned aerial vehicle;

FIG. 2 is a schematic view of the bottom side structure of FIG. 1;

fig. 3 is a schematic structural view of the folded state of the unmanned aerial vehicle;

FIG. 4 is a schematic structural view of the inside of the housing;

FIG. 5 is a cross-sectional view of the articulated portion of the arm assembly and the housing;

FIG. 6 is a schematic view of the articulation of the main arm with the folding arm;

FIG. 7 is a schematic structural view of the main arm connected to the folding arm via the rotating assembly;

FIG. 8 is an exploded view of the rotating assembly;

FIG. 9 is a schematic structural view of the airborne terminal;

FIG. 10 is an exploded view of the onboard end;

FIG. 11 is a schematic diagram of the structure of the device side;

FIG. 12 is an exploded view of the device side;

FIG. 13 is a schematic view of a connection structure of the flight control assembly and the damping device;

FIG. 14 is a schematic structural view of a shock absorber;

FIG. 15 is a side view of the damper;

FIG. 16 is a schematic structural view of a damping wire;

FIG. 17 is a schematic illustration of a structure of the landing gear;

figure 18 is a schematic view of the other side of the landing gear.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The unmanned aerial vehicle disclosed by the embodiment of the invention has the advantages of light structure and high strength, effectively improves the bearing capacity, prolongs the endurance time, effectively reduces the occupied volume by the foldable structure, is convenient to store and is beneficial to transportation.

As shown in fig. 1 to 18, an unmanned aerial vehicle mainly includes a fuselage a, a horn assembly b and a rotor power assembly c, wherein the fuselage a includes a housing 1 having an accommodating cavity therein, the housing 1 is formed by splicing an upper portion and a lower portion, the horn assembly b is rotatably connected to a horn hinge portion formed on a wall surface of the housing 1 so as to form a folding horn structure, and the rotor power assembly c is disposed on the horn assembly b;

in the embodiment, the rear side of the top of the shell 1 is provided with an empennage, the front end of the top of the shell 1 and the empennage are provided with differential positioning antennas, the empennage is also provided with a backup GPS (global positioning system) and a magnetic compass module, the shell 1 and the horn component b are made of plate-shaped materials, and the shell and the horn component b are specifically made of carbon fiber composite materials, so that the carbon fiber composite materials are excellent in mechanical property, small in specific gravity, good in rigidity, high in strength, high in specific strength and high in specific modulus comprehensive index, and accordingly the shell 1 and the horn component b are guaranteed to have excellent structural strength, the fuselage a and the horn component b are only of thin shell structures and do not need to be provided with reinforcing ribs, the horn component b is directly hinged to the shell 1, a structural framework does not need to be arranged in the fuselage;

as shown in fig. 4 and 5, the arm hinge portion formed on the wall surface of the casing 1 is a cavity groove 11 formed by the wall surface of the casing 1 being recessed inwards, and the cavity groove formed by the recessed wall surface can effectively improve the structural strength of the cavity groove, specifically, the cavity groove 11 has two parallel side walls, through holes are formed on the two side walls, the rotating shaft 2 is inserted into the through holes, the rotating shaft 2 is hollow inside, and power supply wires of the rotor power assembly c are routed from the hollow inside of the rotating shaft 2, in this embodiment, the arm assembly b is fixedly connected to the rotating shaft 2, i.e. the arm assembly b does not rotate relative to the rotating shaft 2, and the rotating shaft 2 is rotatably disposed in the through holes on the side walls of the cavity groove 11, and in order to further improve the structural stability and the stability of rotation, a casing hinge seat 12 for the rotating shaft 2 to pass through is attached to the two side walls, the shell hinge base 12 is a metal hinge base;

in addition, the rotating shaft 2 is provided with a rotating damping adjusting mechanism, which improves the rotating stability of the horn assembly b relative to the machine body a and avoids the unstable shaking condition in the unfolding state and the folding state, specifically, the rotating damping adjusting mechanism comprises a nut 21, a friction plate 22 and a damping gasket 23, the friction plate 22 is sleeved on the rotating shaft 2 and is connected and fixed with the housing hinge seat 12, the nut 21 is screwed on the rotating shaft 2 and presses the damping gasket 23 sleeved on the rotating shaft 2 on the friction plate 22, in this embodiment, the damping gasket 23 is respectively provided with one, specifically, steps with variable diameters are arranged on the rotating shaft 2, the friction plate 22, the damping gasket 23, the friction plate 22 and the nut 21 are sequentially sleeved on the steps, and the nut 21 is used for adjusting the pressing force between the friction plate 22 and the damping gasket 23, therefore, the rotation damping is adjusted, so that the machine arm component b can stably rotate; further, a plurality of spring washers 24 are arranged between the friction plate 22 close to the nut 21 and the nut 21, the spring washers 24 can be overlapped, the nut 21 locked on the rotating shaft 2 limits the spring washers 24 on the rotating shaft 2, and the spring washers 24 apply elastic pressing acting force on the friction plate 22, the damping washer 23 and the friction plate 22, so that stable rotation damping is guaranteed, and stable and smooth rotation can be realized;

in this embodiment, as shown in fig. 1 to 3, the boom assembly b includes a main arm b1 and a folding arm b2, the main arm b1 and the folding arm b2 are both made of carbon fiber composite material and have a hollow cylindrical structure, which is light in weight and high in structural strength, a rotor power assembly c is disposed on the main arm b1, one end of the folding arm b2 is hinged to the main arm b1, the other end of the folding arm b2 is hinged to the cavity 11 of the housing 1, specifically, the main arm b1 is a long rod shape along the fore-and-aft direction of the fuselage a, the folding arm b2 is disposed in parallel and spaced two along the length direction of the main arm b1 to form a parallelogram folding boom structure, the structural stability in the unfolded state is good to ensure the stability and safety of flight, the rotor power assemblies c are disposed at both ends of the main arm b1, the left and right sides of the fuselage a are symmetrically disposed with the cavity 11 for connecting the boom assembly b, thereby at the left and right sides symmetric connection organic arm subassembly b of fuselage a, thereby constitute four rotor's unmanned aerial vehicle, folding arm rotate along the fore-and-aft direction of fuselage, namely, the both sides wall that is parallel to each other of chamber groove 11 is along the horizontal direction, the main arm is then keeping away from or being close to the left and right sides of fuselage in the horizontal direction, the main arm is the state of expanding when keeping away from the fuselage left and right sides, the main arm is the state of drawing in when being close to the fuselage left and right sides, the space length that unmanned aerial vehicle occupies in the fuselage fore-and-aft direction is main arm length when expanding state and draw in the state, and because the horn subassembly b folds along the fore-and-aft direction, thereby can not increase the occupation space of direction of height when draw; in the traditional unmanned aerial vehicle, each horn is provided with a rotor power assembly, and each horn is independently connected with the fuselage, so that each horn needs to be independently rotated in the unfolding and folding processes, the operation times are multiple, and the efficiency is low;

in order to strengthen fuselage a's bulk strength, still be provided with the bracing piece 13 of connecting between left and right side chamber groove 11 in casing 1, it is concrete, bracing piece 13 is connected with friction disc 22 through the bolt, and friction disc 22 is connected fixedly with the articulated seat 12 of casing, the articulated seat 12 of casing is again attached to be fixed on chamber groove 11's lateral wall, thereby be fixed relation of connection between bracing piece 13 and the casing 1, the overall structure intensity of casing 1 can be strengthened to bracing piece 13, make the stable machine arm component b that bears of casing 1 ability, and bracing piece 13 make by carbon fiber composite, the light-duty intensity of structure is high, reduces useless weight, improves unmanned aerial vehicle's bearing capacity.

In this embodiment, as shown in fig. 6, the folding arm structure is hinged between the main arm b1 and the folding arm b2 through the rotating assembly 3, and the rotating assembly 3 has the functions of positioning and locking the rotating angle, so that the folding arm structure can be accurately rotated to a set angle position and maintain the stability of the current state, and the folding arm structure is prevented from changing states in the flying process or the transportation process, so that the flying stability and the transportation stability are ensured, and the flying safety and the transportation integrity of the unmanned aerial vehicle are ensured;

specifically, as shown in fig. 7 and 8, the rotating assembly 3 includes a rotating angle member 31, an angle positioning member 32 rotating relative to the rotating angle member 31, and a hinge locking mechanism acting between a locking position and an unlocking position, the rotating angle member 31 and the angle positioning member 32 are respectively connected to two components to be hinged, in this embodiment, the rotating angle member 31 is fixedly connected to a folding arm b2, and the angle positioning member 32 is fixedly connected to a main arm b1, so that the folding arm b2 and the main arm b1 can rotate relative to each other through the connection of the rotating assembly 3, for an aircraft, the most important rotating state is an unfolding state and a folding state, therefore, two sets of engaging portions 311 are provided on the rotating angle member 31 at intervals in the rotating circumferential direction, one set is an angular position of the folding state, the other set is an angular position of the unfolding state, a positioning portion 321 engaged with the engaging portion 311 is provided on the angle positioning member 32, when the rotating angle member 31 and the angle positioning member 32 rotate relatively, the positioning portion 321 is matched with the engaging portion 311 at different angle positions to realize rotating angle positioning;

when the rotating angle piece 31 and the angle positioning piece 32 relatively rotate to the positioning part 321 to be matched with the clamping part 311 in the folded state, the arm assembly b rotates to the folded state, and when the rotating angle piece 31 and the angle positioning piece 32 relatively rotate to the positioning part 321 to be matched with the clamping part 311 in the unfolded state, the arm assembly b rotates to the unfolded state;

in the process of rotating the horn assembly b, the hinge locking mechanism is in an unlocked position, so that the rotating angle member 31 and the angle positioning member 32 can rotate relatively; and when rotating when targetting in place, promptly, when location portion 321 and block portion 311 reached the fit state, the operation articulated locking mechanism switch to the locking position, articulated locking mechanism keeps location portion 321 and block portion 311 to be in the fit state and makes unable emergence relative rotation between turned angle spare 31 and the angle location spare 32 this moment to can make unmanned aerial vehicle keep firm expansion state and the folded state through articulated locking mechanism, guarantee unmanned aerial vehicle flight's stability, avoid unmanned aerial vehicle's fold condition to take place unexpected switching, improve the reliability.

In this embodiment, the engaging portion 311 is a groove, the positioning portion 321 is a protrusion engaged with the groove, and two sides of the groove along the rotation circumferential direction are inclined slopes, correspondingly, two sides of the protrusion along the rotation circumferential direction are also inclined slopes, or two sides of only one of the groove and the protrusion along the rotation circumferential direction are inclined slopes, the inclined slopes are used for guiding to improve the smoothness of engagement between the engaging portion 311 and the positioning portion 321, so that during the rotation process, the protruding positioning portion 321 can be smoothly inserted into the groove-shaped engaging portion 311 or withdrawn from the engaging portion 311, the protruding positioning portion 321 and the groove-shaped engaging portion 311 are engaged with each other with high reliability and high precision, thereby ensuring the precision and stability of the unmanned aerial vehicle in the folded state and the unfolded state, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 are simple in structure, the processing is convenient, the cost is low, and the realization is easy;

further, in this embodiment, the engaging portion 311 is disposed on the end surface of the angle positioning member 31 near the angle positioning member 32 in the axial direction of rotation, and the positioning portion 321 is correspondingly disposed on the end surface of the angle positioning member 32 near the angle positioning member 31 in the axial direction of rotation, so that the structure is more compact, and the engaging portion 311 and the positioning portion 321 do not occupy the space in the circumferential direction of rotation; when the engaging portion 311 and the positioning portion 321 of this structure are adopted, as long as there is a certain mobility in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32, which may be a gap in the rotation axis direction, or the rotation angle member 31 and the angle positioning member 32 are elastically deformed, the rotation angle member 31 and the angle positioning member 32 can relatively rotate, and when the mobility in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32 is eliminated, the gap in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32 can be eliminated, or the rotation angle member 31 and the angle positioning member 32 are pressed to avoid elastic deformation, the rotation angle member 31 and the angle positioning member 32 can not relatively rotate, so that when the hinge locking mechanism is in the locking position, it can apply an acting force in the rotation axis direction to press the rotation angle member 31 and the angle positioning member 32 together, the function of keeping the positioning part 321 and the clamping part 311 in the matching state can be realized;

specifically, the hinge locking mechanism includes a locking block 33 moving upward perpendicular to the rotation axis, the locking block 33 is provided with a driving inclined plane 331 inclined to the rotation axis direction and used for compressing the rotation angle member 31 and the angle positioning member 32, when the locking block moves in the direction perpendicular to the rotation axis direction, the driving inclined plane on the locking block can generate displacement in the rotation axis direction, so that the rotation angle member 31 and the angle positioning member 32 are compressed in the rotation axis direction, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 are more tightly matched together, at this time, the protruding positioning portion 321 is difficult to withdraw from the groove-shaped engaging portion 311, thereby playing a function of a locking state, so that the unmanned aerial vehicle can be locked and maintained in a furled state or an unfolded state, and avoid the furled state or unfolded state from being displaced accidentally, when the state of the unmanned aerial vehicle needs to be switched, the locking block only needs to be moved reversely.

In this embodiment, the rotating assembly 3 further includes a rotating shaft 34, the inside of the rotating shaft 34 is hollow for routing, that is, the power supply line of the rotor power assembly c is routed from the inside of the rotating shaft 34, the rotating angle component 31 is non-rotatably disposed on the rotating shaft 34, the angle positioning component 32 is rotatably sleeved on the rotating shaft 34, because the rotating angle component 31 is fixed on the folding arm b2, the rotating shaft 34 and the folding arm b2 are non-rotatably fixed and connected, the folding arm b2 is provided with a through hole penetrating up and down, the rotating shaft 34 penetrates into the through hole, a folding arm hinge seat b21 for the rotating shaft 34 to penetrate is disposed on the lower side of the through hole in an attaching manner, so as to improve the structural strength, ensure that the rotating shaft 34 can be stably connected with the folding arm b2, the rotating angle component 31 is disposed on the upper side of the through hole and sleeved on the rotating shaft 34, the lower side of the main, the angle positioning element 32 is fixedly arranged on the lower surface of the through hole of the main arm b1, so that the rotating angle element 31 and the angle positioning element 32 can be attached to each other in the rotating shaft direction, so that the convex positioning part 321 and the concave clamping part 311 can be matched to play a role in positioning the rotating angle, the main arm b1 is of a hollow structure, and a main arm hinge seat b11 for the rotating shaft 34 to penetrate through is arranged in the main arm b1, so that the structural strength of the main arm b1 is improved, and the stability of the rotating connection of the folding arm b2 and the main arm b1 is enhanced;

in order to ensure that the locking block 33 can move stably along the direction vertical to the rotating axial direction, a channel assembly 35 fixed on a main arm hinge seat b11 is arranged in the main arm b1, the path direction of the channel assembly 35 is perpendicular to the axial direction of rotation, specifically, the channel assembly 35 is composed of a pressing seat 351 and a pressing plate 352 sleeved on the rotating shaft 34, the pressing seat 351 and the pressing plate 352 are fixed on the main arm hinge seat b11 through bolts, and the pressing plate 352 is in a structure of being arched in the middle, so that a passage for the movement of the locking block 33 is formed between the pressing seat 351 and the pressing plate 352 in a path direction perpendicular to the rotation axial direction, in this embodiment, the locking block 33 is provided with a through hole, the locking block 33 is also sleeved on the rotating shaft 34, the locking block 33 is located in the channel formed between the pressing seat 351 and the pressing plate 352, the locking block 33 penetrates through the wall surface of the main arm b1, so that the locking block 33 can be conveniently operated to switch between the locking position and the unlocking position;

further, in this embodiment, the locking block 33 is formed by connecting two parts, and both the two parts respectively penetrate through the wall surface of the main arm b1, one end of the locking block 33 penetrating through the main arm b1 is pressed towards the inner side of the main arm b1 to switch from the locking position to the unlocking position, and the other end of the locking block 33 penetrating through the main arm b1 is pressed towards the inner side of the main arm b1 to switch from the unlocking position to the locking position, so that two ends of the locking block 33 can be respectively defined as a locking end and an unlocking end, and the locking end and the unlocking end are in different colors, for example, the unlocking end is green and the locking end is red, which facilitates accurate locking and unlocking operations; in the embodiment, two parallel folding arms b2 are hinged to one main arm b1 at intervals, so that a parallelogram folding arm structure is formed, the main arm b1 is connected with one folding arm b2 by the rotating component 3 with the hinged locking mechanism, and the main arm b1 is connected with the other folding arm b2 by the rotating component without the hinged locking mechanism, so that the whole parallelogram folding arm structure can be locked by locking the hinged position of the main arm b1 and one folding arm b2, the stable mechanism state of the folding arm structure is maintained, the rotation and displacement are avoided, the unmanned aerial vehicle is enabled to be kept in a stable unfolding state and folding state, and the flying stability of the unmanned aerial vehicle is guaranteed;

in this embodiment, the driving inclined plane 331 of the locking block 33 faces upward, the rotating shaft 34 is further sleeved with a pressing block 36 located above the locking block 33, the pressing plate 352 is provided with a through hole through which the pressing block 36 can freely pass along the axial direction of the rotating shaft, the rotating shaft 34 is screwed with a nut 37, the pressing block 36 is locked and abutted on the locking block 33 by the nut 37, in order to ensure that the locking block 33 drives the pressing block 36 smoothly without retardation, the contact position of the pressing block 36 and the locking block 33 is an inclined plane matched with the driving inclined plane 331, when the locking block 33 moves from the unlocking position to the locking position along the direction perpendicular to the axial direction of rotation, the locking block 33 pushes the pressing block 36 to move upward through the driving inclined plane 331, the movement of the locking block 33 along the direction perpendicular to the axial direction of rotation is converted into the movement of the pressing block 36 along the axial direction of rotation through the driving inclined plane 331, so that the pressing block 36 drives the rotating shaft 34 to move, the folding arm b2 is also driven to move upwards to be more close to the main arm b1, the rotating angle piece 31 and the angle positioning piece 32 are pressed together along the rotating axial direction, the protruding positioning part 321 is tightly matched with the groove-shaped clamping part 311 and cannot be separated and withdrawn, and therefore the unmanned aerial vehicle is locked in an unfolding state or a folding state; when the locking block 33 moves from the locking position to the unlocking position along the direction perpendicular to the rotation axial direction, the additional axial acting force applied to the rotation angle piece 31 and the angle positioning piece 32 is released, the pressure between the rotation angle piece 31 and the angle positioning piece 32 is reduced, the rotation angle piece 31 and the angle positioning piece 32 are reset to a state that the rotation angle piece and the angle positioning piece can rotate relatively, the protruding positioning part 321 can withdraw from the groove-shaped clamping part 311, and therefore the unmanned aerial vehicle can be freely switched between a folded state and an unfolded state;

the rotating assembly 3 is further provided with an elastic member 38 with an acting force along the rotating axial direction for pre-pressing the rotating angle member 31 and the angle positioning member 32, in this embodiment, the elastic member 38 is a plurality of spring washers sleeved on the rotating shaft 34, the spring washers are located between the second nut 37 and the pressing block 36, the pressing block 36 is freely movable along the rotating shaft 34 in the axial direction, the spring washers elastically press the pressing block 36 on the locking block 33, and simultaneously, the acting force of the spring washers is utilized to elastically press the rotating angle member 31 and the angle positioning member 32 together in the rotating axial direction, so that when the rotating angle member 31 and the angle positioning member 32 rotate relatively, there is an elastically avoiding space between the two, and during the rotating process, when the protruding positioning portion 321 is not inserted into the groove-shaped engaging portion 311, the protruding positioning portion 321 abuts against the surface of the rotating angle member 31, that is, the gap between the rotating angle piece 31 and the angle positioning piece 32 in the rotating axial direction is increased, and at the moment, the elastic piece 38 is further compressed to realize elastic avoidance, so that the relative rotation between the rotating angle piece 31 and the angle positioning piece 32 can be ensured; and when the locking piece 33 moves from the unlocking position to the locking position along the direction perpendicular to the axial direction of rotation, the locking piece 33 pushes the pressing piece 36 to move upwards through the driving inclined plane 331 so as to further compress the elastic piece 38, and in turn, the elastic piece 38 can generate larger acting force, so that the rotation angle piece 31 and the angle positioning piece 32 are pressed together more tightly in the direction of rotation axis, the protruding positioning part 321 is ensured to be incapable of exiting from the groove-shaped clamping part 311, and the stability of the unmanned aerial vehicle in the folding state and the unfolding state is ensured.

As shown in fig. 2, 9 to 12, the housing 1 is provided with a task device connecting mechanism 4, which mainly includes an onboard end 41 installed on the unmanned aerial vehicle and a device end 42 installed on the task device, the onboard end 41 is provided with an electrical connector 43, the device end 42 is provided with an electrical connector 44 matching with the electrical connector 43, the onboard end 41 is provided with a chute 45 into which the device end 42 is inserted, and an anti-drop locking mechanism for preventing the device end 42 from dropping out of the chute 45 is further provided between the onboard end 41 and the device end 42, the task device connecting mechanism of the present embodiment can be used to conveniently and quickly connect the task device and the unmanned aerial vehicle main body, and integrate the mechanical connection and the electrical connection of the task device into a whole, so that the installation operation is simpler and quicker, and different types of task devices can be conveniently replaced, thereby can be applied to the demand of difference with unmanned aerial vehicle, increase application scope.

Specifically, the electrical connector 43 and the electrical connector 44 are 40pin electrical connectors, which can meet the use requirements of most task devices;

in order to improve the assembly and disassembly efficiency, when the task equipment is mechanically fixed on the body of the unmanned aerial vehicle and the electric connecting port 43 and the electric connector 44 are connected, the insertion and extraction directions of the electric connecting port 43 and the electric connector 44 are set to be that the machine-mounted end 41 moves along the sliding groove 45, specifically, the electric connecting port 43 is arranged at the tail end of the sliding direction of the sliding groove 45, the electric connector 44 is arranged at the front end of the insertion direction of the equipment end 42, so that the electric connecting port 43 and the electric connector 44 are inserted while the equipment end 42 is inserted along the sliding groove 45, the electric connecting port 43 and the electric connector 44 are separated while the equipment end 42 is extracted along the sliding groove 45, thereby simplifying the assembly and disassembly operation of the task equipment and improving the assembly and disassembly efficiency, the electric connecting port 43 is arranged at the tail end of the sliding groove 45, and the electric connector 44 is arranged at the front end of the equipment end 42, after the installation is finished, the electric connection port 43 and the electric connector 44 are blocked by the equipment end 42, and due to the existence of the anti-falling locking mechanism, the equipment end 42 cannot withdraw from the sliding groove 45, so that the electric connection stability of the electric connection port 43 and the electric connector 44 can be ensured, the condition of poor electric connection contact can be avoided, and when the equipment end 42 is inserted into the sliding groove 45 in place, the electric connection port 43 and the electric connector 44 are wrapped inside the equipment end 42 and the task end, the electric connection port 43 and the electric connector 44 can be effectively protected, the electric connection can be prevented from being damaged due to exposure outside, the reliability of electric connection can be further ensured, and the task equipment can stably work;

in this embodiment, the left and right side walls of the sliding slot 45 in the sliding direction are provided with the guide rails 451 along the sliding direction, the side wall of the equipment end 42 is provided with the guide grooves 452 matched with the guide rails 451, so that the accuracy of inserting and pulling the equipment end 42 into and out of the sliding slot is improved, the electrical connection port 43 and the electrical connector 44 can be accurately butted, and the situation that the electrical connector 44 is difficult to be inserted into the electrical connection port 43 is avoided;

the anti-falling and locking mechanism mainly comprises an elastic pin 46 arranged on the side wall of the side where the guide groove 452 of the equipment end 42 is arranged and a jack 47 for inserting the elastic pin 46 is arranged on the side wall of the side where the guide rail 451 of the sliding groove 45 is arranged, the elastic pin 46 is similar to a latch structure, the front end side facing the inserting direction of the equipment end 42 is a guide inclined surface, the rear end side facing the inserting direction of the equipment end 42 is a right-angled surface, the elastic pin 46 comprises a pin and a spring for pushing the pin to protrude out of the equipment end 42, when the equipment end 42 is inserted into the vehicle-mounted end 41 along the sliding groove 45, the elastic pin 46 is squeezed by the side wall of the sliding groove 45 and retracted into the equipment end 42 when the elastic pin 46 does not reach the jack 47 position, and when the equipment end 42 is inserted into the place, the elastic pin 46 just reaches the jack 47 position, so that the elastic pin 46 is reset to pop out and insert into the jack 47 to, the equipment end 42 is prevented from reversely exiting the chute 45, so that the task equipment is reliably connected to the unmanned aerial vehicle, and the dangerous condition that the task equipment is separated from the unmanned aerial vehicle is avoided;

furthermore, the anti-disengagement locking mechanism further comprises a key 48 movably inserted into the insertion hole 47 for unlocking, and the key 48 is pushed to push the elastic pin 46, so that the elastic pin 46 retracts towards the inside of the equipment end 42, and the locking state of the equipment end 42 and the machine-mounted end 41 is released, and the operation is simple and rapid; in this embodiment, the anti-falling locking mechanism is provided one on each of the left and right sides of the sliding direction of the sliding chute 45, the insertion hole 47 penetrates through the side wall of the sliding chute 45 in the left and right directions of the sliding chute 45, the button 48 is provided on the left and right sides of the sliding chute 45, and unlocking can be achieved by pressing the button 48 toward the center of the sliding chute 45;

in order to facilitate the separation of the equipment end 42 and the onboard end 41, an elastic pushing mechanism 49 for pushing the equipment end 42 out of the chute 45 is further arranged in the chute 45, that is, when the button 48 is pressed to press the elastic pin 46 back into the equipment end 42 so that the locking state of the insertion hole 47 of the elastic pin 46 is released, the elastic pushing mechanism 49 pushes the equipment end 42 to move out of the chute 45, specifically, the elastic pushing mechanism 49 is arranged at the end of the sliding direction of the chute 45, the elastic pushing mechanism 49 is composed of a pushing block and a pushing spring, when the equipment end 42 is inserted along the chute 45, the equipment end 42 will push the elastic pushing mechanism 49 so that the pushing spring of the elastic pushing mechanism 49 is compressed to store elastic potential energy, and when the elastic pin 46 is inserted into the locking state of the insertion hole 47, the elastic pushing mechanism 49 is always in the state of storing elastic potential energy, when the elastic pin 46 is out of the insertion hole 47 to become the unlocking state, the elastic pushing mechanism 49 releases the elastic potential energy to push the equipment end 42 outwards along the sliding slot 45, so as to improve the convenience of disassembly, and, because the onboard end 41 and the equipment end 42 adopt a chute plugging connection mode, a certain fit clearance exists, and the fit clearance can generate larger vibration in the flight process, namely, the task equipment can generate larger vibration to seriously affect the working reliability of the task equipment, the elastic thrusting mechanism 49 plays a role of generating a pre-tightening force when the equipment end 42 is inserted into the airborne end 41, the acting force of the elastic thrusting mechanism faces the exit direction of the chute, the fit clearance between the airborne end 41 and the equipment end 42 can be filled and eliminated, the elastic pin 46 is tightly matched with the jack 47, so that the vibration problem is solved, and the working stability and reliability of task equipment are guaranteed.

As shown in fig. 4, the accommodating cavity of the housing 1 is used for placing a flight control assembly 5 and the like, one of the important factors affecting the flight state of the unmanned aerial vehicle is that an inertial sensor used for attitude calculation can generate adverse effects due to vibration, and resonance or random vibration can cause data errors of the sensor, thereby causing fatal errors of attitude calculation, so that technical means are usually adopted to reduce the error effects caused by low-frequency vibration in the flight process of the unmanned aerial vehicle, and the general technical means is to indirectly install the flight control assembly in the fuselage through a vibration damping device;

as shown in fig. 13 to 16, the vibration damper includes a plurality of vibration dampers 6 disposed at intervals in the circumferential direction of the flight control assembly 5, in this embodiment, four vibration dampers 6 are adopted and distributed at four corners of the flight control assembly 5, the vibration dampers 6 adopted in this embodiment have a multi-dimensional vibration damping function, and can realize horizontal and vertical vibration damping in the flight process of the unmanned aerial vehicle, so that it is not necessary to separately provide vertical vibration dampers and horizontal vibration dampers as in the prior art, the number of vibration dampers can be reduced, the structural compactness of the vibration damper is improved, the required assembly space is reduced, the waste weight is reduced, and the bearing capacity is improved;

specifically, the damper 6 mainly includes a first connecting member 61 connected to the flight control assembly 5, a second connecting member 62 connected to the housing 1, and a plurality of damper wires 63, both ends of the damper wires 63 are respectively connected to the first connecting member 61 and the second connecting member 62, a first connecting surface 64 is formed at a joint of the damper wires 63 on the first connecting member 61, a second connecting surface 65 is formed at a joint of the damper wires 63 on the second connecting member 62, the first connecting surface 64 is inclined to the second connecting surface 65, the damper wires 63 connected between the first connecting member 61 and the second connecting member 62 are in a plurality of different shapes and lengths, so that the first connecting surface 64 is inclined to the second connecting surface 65, the damper wires 63 in different shapes and lengths have different damping directions, and after the damper wires 63 in different shapes and lengths are combined together, a multi-dimensional damping function of a single damper 6 is finally realized, thereby improving the vibration damping effect while reducing the use amount of the vibration damper;

the included angle between the first connecting surface 64 and the second connecting surface 65 is 60-70 degrees, preferably, the included angle between the first connecting surface 64 and the second connecting surface 65 is 66.5 degrees, so that the vibration reduction effects of the vibration reducer 6 in different directions are balanced, and the overall vibration reduction effect is improved; the damping wires 63 are steel wire cables with the diameters of 1-1.5 mm, preferably 1.2mm steel wire cables, the diameters of the damping wires 63 can be selected according to flight control assemblies with different weights, and the damping effect of the flight control assemblies with different weights can meet requirements;

in this embodiment, the first connecting member 61 is a flat plate parallel to the first connecting surface 64, the second connecting member 62 is a flat plate parallel to the second connecting surface 65, the structure is simple, the manufacturing is convenient, and the first connecting member 61 and the second connecting member 62 can also be designed to be in a special-shaped structure, for example, the first connecting member 61 and the second connecting member 62 are triangular prisms, L-shaped plates, and can be set to be in a specific shape according to actual connecting requirements;

in this embodiment, four damping wires 63 are provided, two of the damping wires 63 are bent into a C shape, the other two damping wires are bent into a spiral shape, and the damper 6 is of a symmetrical structure, that is, two damping wires 63 in a C shape are symmetrically connected to a first connecting piece 61 and a second connecting piece 62, two damping wires 63 in a spiral shape are also symmetrically connected to the first connecting piece 61 and the second connecting piece 62, the damping direction of the damping wire 63 in a C shape is mainly the direction of the connecting line of the two ends of the damping wire 63 in a C shape, and the damping direction of the damping wire 63 in a spiral shape is mainly the spiral axial direction of the damping wire 63 and the direction perpendicular to the spiral axial direction, so that the damping wires 63 in different shapes and lengths are combined to make the first connecting surface 64 inclined to the second connecting surface 65 and realize a better damping function in a multi-dimensional direction;

furthermore, all the damping wires 63 connected to the first connecting piece 61 and the second connecting piece 62 are formed by bending a long steel wire, the first connecting piece 61 and the second connecting piece 62 are provided with connecting through holes for the long steel wires to pass through, and the long steel wires are fixed in the connecting through holes, so that the stability of the whole structure of the damper 6 can be improved, the situation that the damping wires 63 are separated from the first connecting piece 61 and the second connecting piece 62 and fall off is reduced, the damper 6 can work stably for a long time, and the stable damping effect is guaranteed;

in this embodiment, a connecting piece 61 is direct to be connected with flying to control subassembly 5, and two 62 connecting pieces with fix the mount pad fixed connection on casing 1, and connect a face 64 and be on a parallel with the horizontal plane, and connect two 65 slope in the horizontal plane of face, need not to set up again and bear the adapter that flies to control subassembly 5, then a connecting piece 61 is connected with the adapter again, the structure is compacter, reduce required fitting space, reduce useless heavy, when assembling, a connecting piece 61 of shock absorber 6, two 62 connecting pieces all face in the focus that flies to control, ensure that four 6 synergistic effects of shock absorber can effectively subdue the vibration of multiple direction and multiple frequency, improve the damping effect, improve the stability of unmanned aerial vehicle flight.

As shown in fig. 1 to 3, 17 and 18, the arm assembly b of the unmanned aerial vehicle is further provided with landing gear d, specifically, the landing gear d is fixed at the lower sides of the two ends of the main arm b1, the landing gear d mainly comprises a mounting seat d1 fixed on the main arm b1 and a landing gear body d2 hinged on the mounting seat d1, that is, the landing gear d is of a foldable structure, the landing gear d is made of ABS material and can be unfolded when needed to be used, so as to support the unmanned aerial vehicle well, avoid the arm assembly, the fuselage portion and the like of the unmanned aerial vehicle from being collided, ensure the integrity, and be folded and folded when the landing gear is needed to be used, so as to reduce the occupied space and facilitate placement and transportation, a holding locking mechanism for holding the state of the landing gear body d2 is arranged between the mounting seat d1 and the landing gear body d2, and an antenna d3 is arranged on the landing gear body d2, so, the signal strength can be guaranteed;

in this embodiment, the holding locking mechanism includes a lock catch d4 hinged to the landing gear body d2 and a clamping portion d5 arranged on the mounting seat d1 and matched with the lock catch d4, when the landing gear body d2 is unfolded in place, the lock catch d4 and the clamping portion d5 are buckled to lock and hold the unfolded state of the landing gear body d2, so that the landing gear is prevented from being folded and retracted accidentally, and the landing gear is ensured to play a role in supporting the whole unmanned aerial vehicle reliably and stably;

in order to further guarantee the reliability of the locking of the unfolding state of the landing gear body d2, the locking mechanism is further provided with an elastic piece for driving the lock catch d4 to keep the locking state, the elastic piece is specifically a torsion spring, the acting force direction of the torsion spring is the buckling direction of the locking catch d4 and the clamping part d5, and further guarantee is provided for the landing gear body d2 to be locked in the unfolding state;

in this embodiment, the landing gear body d2 is a hollow structure, so that the weight can be reduced, the waste weight can be reduced, and the carrying capacity of the unmanned aerial vehicle can be improved, the antenna d3 is arranged in the hollow interior of the landing gear body d2, does not occupy the external space, can effectively protect the antenna d3, and ensures the long-term stable operation of the antenna d3, and the landing gear body d2 is provided with a cover plate d6 for opening and closing the hollow interior of the landing gear body d6, so that the antenna d3 can be conveniently taken and placed, and the operation convenience can be improved;

undercarriage main part d2 bottom still be provided with shock pad d7, shock pad d7 specifically can adopt the shock attenuation bubble cotton, improves the buffering stationarity when undercarriage d supports unmanned aerial vehicle, reduces the impact to the inside flight control subassembly of fuselage etc. when unmanned aerial vehicle descends to the ground, the equal efficient and stable work such as guarantee flight control subassembly.

In the flight process of the unmanned aerial vehicle, the flight control assembly 5 and the like in the shell generate heat, the working stability of the unmanned aerial vehicle is seriously affected when the temperature is too high, and the service life of the unmanned aerial vehicle is also shortened;

specifically, as shown in fig. 4, the heat dissipation mechanism includes an air inlet 14, an air outlet 15 and a heat dissipation fan 16 disposed at the air inlet 14, the heat dissipation fan 16 introduces external air into the housing 1 from the air inlet 14, and the air absorbs heat of each component in the housing and then is discharged from the air outlet 15, in this embodiment, the air inlet 14 is disposed at the front end of the housing 1, the air outlet 15 is disposed at the left and right sides of the housing 1, and the air inlet 14 is disposed at the windward side of the unmanned aerial vehicle during flying, so as to facilitate air entering the housing from the air inlet and being discharged from the air outlet, and improve the heat dissipation effect The efficient heat dissipation effect is guaranteed, the proper working temperature of each part is ensured, and the working stability is improved;

the unmanned aerial vehicle is further provided with a navigation light, specifically, the navigation light is arranged on a main arm b1 of the arm component b, the main arm is of a hollow columnar structure made of carbon fiber composite materials, the navigation light is arranged in the hollow interior of the main arm b1, a transparent light guide cover b3 for light transmission of the navigation light is arranged on the bottom side of the main arm b1, the navigation light is effectively protected by the transparent light guide cover b3, and long-term stable operation of the navigation light is guaranteed;

in this embodiment, horn subassembly b be the parallelogram beta structure that main arm b1 and folding arm b2 constitute, main arm b1 is the stock form along fuselage a fore-and-aft direction, horn subassembly b sets up at casing 1's bilateral symmetry, the navigation light leans on the bottom at both ends at main arm b1, can directly take the light source as the navigation light with rotor power component c's electricity accent certainly, and different navigation lights show different colours and are used for discerning unmanned aerial vehicle's fore-and-aft direction, it is concrete, can adopt the navigation light that leans on unmanned aerial vehicle aircraft nose one side and the different mode of navigation light colour that leans on unmanned aerial vehicle tail one side, thereby the aircraft nose direction that can be very convenient accurate discernment unmanned aerial vehicle, be convenient for ground personnel can be convenient judgement unmanned aerial vehicle's fore-and-aft direction through the mode of observing, be favorable to accurate control.

As shown in fig. 2, the avionic component 7 is arranged at the rear end of the housing 1, the avionic component 7 includes a battery compartment 72 specifically provided at the rear end of the housing for inserting the battery 71, the battery compartment 72 is open, that is, the mouth of the battery compartment 72 is exposed outside the housing 1, a quick plug-in structure is adopted between the battery 71 and the battery compartment 72, instead of the traditional method of opening the housing first and then replacing the battery, so as to improve the efficiency of replacing the battery, the battery is provided with a lock catch, when the battery is inserted into the battery compartment, the lock catch of the battery can automatically extend into a hole on the side wall of the battery compartment to complete locking, so as to ensure the stability and quickness of battery installation, when the battery 71 needs to be replaced, the battery can be pulled out of the battery compartment only by pulling a handle provided on the battery, so;

the battery 71 is an intelligent battery, a heating sheet is arranged in the battery 71, the heating sheet is powered by the battery, external power supply is not needed, and an integrated design structure is adopted, so that the battery is heated and insulated by heating after the heating sheet is powered on in a low-temperature environment, the discharge rate of the battery is guaranteed, the output current of the battery is stabilized, and the unmanned flight stability is guaranteed; and battery 71 still is provided with the communication interface that is used for with unmanned aerial vehicle real-time communication, but the residual capacity of real-time accurate discernment battery, guarantee unmanned aerial vehicle's duration directly perceived controllable.

The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the spirit and scope of the invention, and these modifications and adaptations should be considered within the scope of the invention.

Claims

1. The utility model provides an unmanned aerial vehicle, its characterized in that includes fuselage (a), horn subassembly (b) and rotor power component (c), fuselage (a) including inside casing (1) that hold the chamber, horn subassembly (b) rotate to be connected on the horn articulated portion that the wall of casing (1) formed, rotor power component (c) set up on horn subassembly (b).

2. A drone according to claim 1, characterised in that the horn assembly (b) comprises a main arm (b1) and a folding arm (b2), the rotor power assembly (c) being arranged on the main arm (b1), the folding arm (b2) being hinged at one end to the main arm (b1) and at the other end to the housing (1).

3. A drone according to claim 2, characterised in that the folding arms (b2) are arranged in parallel and at intervals along the length of the main arm (b 1).

4. The unmanned aerial vehicle of claim 1, wherein the folding arm structure comprises a rotating assembly (3) for hinging, the rotating assembly (3) comprises a rotating angle piece (31), an angle positioning piece (32) rotating relative to the rotating angle piece (31) and a hinged locking mechanism acting between a locking position and an unlocking position, at least one clamping part (311) is arranged on the rotating angle piece (31) at intervals in the rotating circumferential direction, a positioning part (321) matched with the clamping part (311) is arranged on the angle positioning piece (32), and the hinged locking mechanism keeps the positioning part (321) and the clamping part (311) in a matched state when in the locking position.

5. The unmanned aerial vehicle of claim 4, wherein the engaging portion (311) is a groove, the positioning portion (321) is a protrusion engaged with the groove, the engaging portion (311) is disposed on an end surface of the angle positioning member (31) close to the angle positioning member (32) in the axial direction of rotation, and the positioning portion (321) is correspondingly disposed on an end surface of the angle positioning member (32) close to the angle positioning member (31) in the axial direction of rotation.

6. A drone according to claim 5, characterised in that the articulation locking mechanism comprises a locking block (33) moving in the direction perpendicular to the rotation axis, the locking block (33) being provided with a driving ramp (331) inclined to the rotation axis for pressing the rotation angle member (31) against the angle positioning member (32).

7. The unmanned aerial vehicle of claim 1, wherein the housing (1) is provided with a task device connecting mechanism (4) which comprises an onboard end (41) mounted on the unmanned aerial vehicle and a device end (42) mounted on the task device, the onboard end (41) is provided with an electrical connector (43), the device end (42) is provided with an electrical connector (44) matched with the electrical connector (43), the onboard end (41) is provided with a sliding groove (45) for the device end (42) to be inserted, and an anti-dropping locking mechanism for preventing the device end (42) from dropping out of the sliding groove (45) is further arranged between the onboard end (41) and the device end (42).

8. The task equipment connecting mechanism according to claim 7, characterized in that the anti-disengagement locking mechanism comprises an elastic pin (46) provided on a side wall of the equipment end (42) and an insertion hole (47) provided on a side wall of the slide groove (45) for inserting the elastic pin (46).

9. The unmanned aerial vehicle of claim 1, wherein the flight control assembly (5) is fixed in the accommodating cavity of the housing (1) through a damper (6), the damper (6) comprises a first connecting part (61) connected with the flight control assembly (5), a second connecting part (62) connected with the housing (1) and a plurality of damping wires (63), two ends of each damping wire (63) are respectively connected with the first connecting part (61) and the second connecting part (62), a first connecting surface (64) is formed at the connecting part of each damping wire (63) on the first connecting part (61), a second connecting surface (65) is formed at the connecting part of each damping wire (63) on the second connecting part (62), and the first connecting surface (64) is inclined to the second connecting surface (65).

10. An unmanned aerial vehicle according to claim 9, wherein the angle between the first connecting surface (64) and the second connecting surface (65) is 60-70 °.