A drone

Abstract

The present invention discloses an unmanned aerial vehicle, comprising a fuselage, an arm assembly and a rotor power assembly, wherein the fuselage comprises a shell having a receiving cavity therein, the arm assembly is rotatably connected to an arm hinge formed on the wall of the shell, and the rotor power assembly is arranged on the arm assembly. The unmanned aerial vehicle of the present invention has a light structure, can improve the carrying capacity of the unmanned aerial vehicle, avoid increasing the waste weight of the unmanned aerial vehicle, improve the carrying capacity, and extend the flight time, and the foldable structure effectively reduces the occupied volume, has a high space utilization rate, is convenient for storage, and is conducive to transportation.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an unmanned aerial vehicle. Background Art

[0002] Drones are unmanned aircraft that are controlled by radio remote control equipment or self-provided program control devices. Currently, drones are widely used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance, etc. Compared with manned aircraft, drones have the characteristics of small size, low cost, and easy use. However, the commonly used drones are less lightweight and usually use structural frames to carry components such as arms and mission equipment. However, this greatly increases the waste weight of drones, reduces the carrying capacity of the aircraft, and shortens the flight endurance. Summary of the invention

[0003] The technical problem to be solved and the technical task proposed by the present invention are to improve the existing technology and provide a drone to solve the problem that drones in current technology use a structural skeleton to carry arms and mission equipment, which is heavy and bulky, resulting in low drone carrying capacity and short flight time.

[0004] In order to solve the above technical problems, the technical solution of the present invention is:

[0005] A drone includes a fuselage, an arm assembly and a rotor power assembly, wherein the fuselage includes a shell having a receiving cavity therein, the arm assembly is rotatably connected to an arm hinge formed on the wall of the shell, and the rotor power assembly is arranged on the arm assembly. The drone structure of the present invention is light, the arm assembly is directly hinged on the shell, the traditional structural skeleton is omitted, the increase of the waste weight of the drone is avoided, and the carrying capacity of the drone is improved. In addition, the present invention directly uses the shell to integrally carry the arm assembly and the rotor power assembly on the arm assembly, effectively reducing the waste weight of the drone, improving the carrying capacity, and extending the endurance time. The foldable structure effectively reduces the occupied volume, is convenient for storage, and is conducive to transportation.

[0006] Furthermore, the arm assembly includes a main arm and a folding arm, the rotor power assembly is arranged on the main arm, one end of the folding arm is hinged to the main arm, and the other end is hinged to the shell. The folded state is more compact, the occupied space is reduced, and it is convenient to place and transport. The unfolding and folding operation is more efficient and convenient. The main arm is folded close to the fuselage or unfolded away from the fuselage under the rotation of the folding arm.

[0007] Furthermore, a plurality of folding arms are arranged in parallel and at intervals along the length direction of the main arm, so that the connection reliability is better, the stability of the unfolded state of the UAV is improved, and the flight stability is ensured.

[0008] Furthermore, the folding arm structure includes a rotating assembly for articulation, the rotating assembly includes a rotating angle member, an angle positioning member rotating relative to the rotating angle member, and an articulated locking mechanism that moves between a locked position and an unlocked position, the rotating angle member is provided with at least one engaging portion spaced apart in the circumferential direction of rotation, the angle positioning member is provided with a positioning portion cooperating with the engaging portion, and the articulated locking mechanism keeps the positioning portion and the engaging portion in a mating state when the articulated locking mechanism is in the locked position. The rotating assembly adopted in the present invention has the functions of angle positioning and locking. The rotating angle member and the angle positioning member are respectively connected to the parts that need to be hinged. The present invention uses the clamping part on the rotating angle member to cooperate with the positioning part on the angle positioning member to realize the rotating angle positioning, that is, when the angle positioning member and the rotating angle member rotate relative to each other until the positioning part and the clamping part are matched, it means that the rotation is in place, thereby ensuring the accuracy of the rotation angle and avoiding excessive or insufficient rotation. When the rotation is in place, the hinge locking mechanism is used to maintain the current rotation angle state, that is, it can maintain a stable unfolded state or folded state, avoiding the situation that the unfolded state is unstable during flight and causes shaking or even accidental folding, and avoiding the dangerous situation that the flight state is unstable and causes a crash. At the same time, it also effectively ensures the stability of the folded state, thereby ensuring the stability of the placement or transportation process, avoiding the situation that the folded arm structure is accidentally unfolded and caused to be damaged by bumps, and ensuring the safety and reliability of the placement and transportation process of the drone.

[0009] Furthermore, the engaging portion is a groove, the positioning portion is a protrusion matched with the groove, the engaging portion is arranged on the end face of the angle-rotating member close to the angle positioning member along the rotation axis, and the positioning portion is correspondingly arranged on the end face of the angle positioning member close to the rotation axis. The present invention adopts the method of matching the groove and the protrusion, which has a simple structure, convenient processing and low cost, and the matching of the groove and the protrusion can realize the rotation angle positioning very accurately, ensuring that each rotation can accurately reach the preset angle position, thereby ensuring the stability of the flight state of the drone after unfolding, and also ensuring the compactness of the folded state, avoiding the situation where the drone has deviations in folding and interferes with the outer packaging, resulting in difficulties in packing and transportation.

[0010] Furthermore, the hinged locking mechanism includes a locking block that is movable in a direction perpendicular to the rotation axis, and the locking block is provided with a driving inclined surface inclined to the rotation axis for pressing the rotation angle member and the angle positioning member tightly. The structure is simple, and the locking function can be reliably realized. The implementation is convenient and the cost is low. When the locking block moves in a direction perpendicular to the rotation axis, the driving inclined surface on the locking block will generate a displacement along the rotation axis (a force along the rotation axis), thereby pressing the rotation angle member and the angle positioning member together along the rotation axis, thereby making the protruding positioning portion more tightly inserted into the groove-shaped clamping portion. At this time, there is no avoidance gap between the rotation angle member and the angle positioning member in the rotation axis, so that the protruding positioning portion cannot withdraw from the groove-shaped clamping portion, so that the rotation angle member and the angle positioning member cannot rotate relative to each other, thereby realizing the locking of the current rotation angle state, that is, it can maintain a stable expanded state or a retracted state. When unlocking is required, it is only necessary to move the locking block in the opposite direction perpendicular to the rotation axis, thereby releasing the compression state of the rotation angle member and the angle positioning member on the rotation axis, and then the rotation angle member and the angle positioning member can rotate relative to each other, that is, the drone can switch between the deployed and folded states.

[0011] Furthermore, the shell is provided with a mission equipment connection mechanism, which includes an airborne end installed on the drone and a device end installed on the mission equipment, the airborne end is provided with an electrical connection port, the device end is provided with an electrical connection head matching the electrical connection port, and the airborne end is provided with a slide slot for the device end to be inserted, and an anti-drop locking mechanism is also provided between the airborne end and the device end to prevent the device end from exiting the slide slot. The present invention integrates the mechanical connection and electrical connection of the mission equipment into one, that is, through the connection between the airborne end and the device end, the mechanical connection and fixation of the mission equipment to the drone and the electrical connection of the mission equipment to the drone's electrical system are simultaneously achieved, which is simple and quick to operate, has good connection reliability, can avoid the situation where the mission equipment accidentally falls out, and improves the safety and reliability of use.

[0012] Furthermore, the anti-disengagement locking mechanism includes an elastic pin arranged on the side wall of the device end and a socket for inserting the elastic pin arranged on the side wall of the slide groove. It has a simple structure, convenient implementation, simple operation, and high locking reliability. After the device end is inserted into the airborne end, it is automatically locked to effectively prevent accidental disengagement. There is no need for manual locking operation after the insertion operation, thus avoiding safety hazards caused by forgetting to perform the locking operation.

[0013] Furthermore, a flight control component is fixed in the accommodating cavity of the shell through a shock absorber, and the shock absorber includes a connector 1 connected to the flight control component, a connector 2 connected to the shell, and a plurality of shock-absorbing wires, the two ends of the shock-absorbing wires are respectively connected to the connector 1 and the connector 2, and the connection of the shock-absorbing wire on the connector 1 constitutes a connection surface 1, and the connection of the shock-absorbing wire on the connector 2 constitutes a connection surface 2, and the connection surface 1 is inclined to the connection surface 2. The vibration damper used in the present invention has a multi-dimensional vibration damping function. With the connection surface one as a reference, it can realize vibration damping in the direction parallel to the connection surface one and in the direction perpendicular to the connection surface one. The traditional vibration damper adopts a plurality of identical vibration damping wires connected between the connection piece one and the connection piece two, so that the plane formed by the connection of the vibration damping wire on the connection piece one is parallel to the plane formed by the connection of the vibration damping wire on the connection piece two, and the connection piece one and the connection piece two are parallel to each other. Therefore, the traditional vibration damper can only realize the vibration damping function in a single direction (the direction of the connection line between the connection piece one and the connection piece two). Therefore, if the traditional vibration damper is used to realize multi-dimensional vibration damping, it is necessary to set up additional vibration dampers. For example, if a group of vibration dampers for vertical vibration damping are set up, if lateral vibration damping is also to be realized, In order to reduce vibration, a group of shock absorbers for lateral vibration reduction need to be set up, which requires a large additional installation space, and the large number of components also brings additional waste weight, which seriously affects the structural compactness and carrying capacity of the UAV. The shock absorber adopted in the present invention has a connection surface one that is inclined to the connection surface two, so that the vibration-damping wires connected between the connecting member one and the connecting member two are of different shapes and lengths, so that the vibration-damping direction of each vibration-damping wire is different. After these vibration-damping wires are combined together, the overall shock absorber has a better vibration-damping effect in multiple dimensions, that is, a single shock absorber realizes multi-dimensional vibration reduction. Compared with traditional shock absorbers, it can effectively reduce the number of shock absorbers used, reduce the required assembly space, improve the structural compactness of the UAV, reduce waste weight, and improve the carrying capacity.

[0014] Furthermore, the angle between the connecting surface 1 and the connecting surface 2 is 60-70°, which can achieve a good vibration reduction effect in multiple dimensions.

[0015] Compared with the prior art, the present invention has the advantages of:

[0016] The drone of the present invention has a light structure, which can improve the carrying capacity of the drone, avoid increasing the waste weight of the drone, improve the carrying capacity, and extend the flight time. The foldable structure effectively reduces the occupied volume, has high space utilization, is convenient for storage, and is conducive to transportation.

[0017] The structure is compact, the unfolding and folding stability is good, the precision is high, and the unfolding and folding state can be reliably locked to ensure the flight stability and safety. At the same time, the stability of the folded state is also guaranteed, and the safety and reliability of the drone placement and transportation process are guaranteed.

[0018] It can realize the rapid installation and disassembly of mission equipment, facilitate the replacement of different mission equipment to realize different functions, expand the scope of application, and realize the mechanical connection and electrical connection in one. The operation is simple and fast, the connection reliability and safety are high, and it has an automatic locking function to avoid the accidental fall of mission equipment.

[0019] It has good vibration reduction effect and can realize multi-dimensional vibration reduction. It requires small assembly space, improves structural compactness, reduces waste weight, and improves the carrying capacity of UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the structure of the UAV in its unfolded state;

[0021] Figure 2 for Figure 1 Schematic diagram of the bottom structure;

[0022] Figure 3 This is a schematic diagram of the structure of the drone in the folded state;

[0023] Figure 4 is a schematic diagram of the structure inside the shell;

[0024] Figure 5 It is a schematic diagram of the cross-sectional structure of the hinge between the arm assembly and the shell;

[0025] Figure 6 Schematic diagram of the articulation of the main arm and the folding arm;

[0026] Figure 7 A schematic diagram of a structure in which the main arm and the folding arm are connected via a rotating assembly;

[0027] Figure 8 It is a schematic diagram of the exploded structure of the rotating assembly;

[0028] Fig. 9 It is a structural diagram of the airborne end;

[0029] Fig.10 Schematic diagram of the decomposed structure of the airborne terminal;

[0030] Fig.11 It is a structural diagram of the device side;

[0031] Fig.12 This is a schematic diagram of the decomposition structure of the device side;

[0032] Fig.13 It is a schematic diagram of the connection structure between the flight control component and the vibration reduction device;

[0033] Fig.14 is a schematic diagram of the structure of the shock absorber;

[0034] Fig.15 is a schematic diagram of the side structure of the shock absorber;

[0035] Fig.16 It is the structural schematic diagram of the vibration damping wire;

[0036] Fig.17 It is a schematic diagram of the structure of the landing gear;

[0037] Fig.18 This is a schematic diagram of the structure on the other side of the landing gear. DETAILED DESCRIPTION

[0038] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] An unmanned aerial vehicle disclosed in an embodiment of the present invention has a light structure and high strength, which effectively improves the carrying capacity and prolongs the flight time. The foldable structure effectively reduces the occupied volume, is convenient for storage, and is conducive to transportation.

[0040] like Figures 1 to 18 As shown, a drone mainly includes a fuselage a, an arm assembly b and a rotor power assembly c, wherein the fuselage a includes a shell 1 with a receiving cavity inside, the shell 1 is composed of an upper and a lower part, the arm assembly b is rotatably connected to an arm hinge formed on the wall of the shell 1 to form a folding arm structure, and the rotor power assembly c is arranged on the arm assembly b;

[0041] In this embodiment, a tail wing is arranged at the rear side of the top of the shell 1, a differential positioning antenna is arranged at the front end of the top of the shell 1 and on the tail wing, and a backup GPS and magnetic compass module are also arranged on the tail wing. The shell 1 and the arm assembly b are formed by plate-like materials, specifically by carbon fiber composite materials. The carbon fiber composite materials have excellent mechanical properties, small specific gravity, good rigidity and high strength, and high comprehensive indicators of specific strength and specific modulus, thereby ensuring that the shell 1 and the arm assembly b have excellent structural strength, so that the fuselage a and the arm assembly b are only thin shell structures, and there is no need to set reinforcing ribs. The arm assembly b is directly hinged on the shell 1, and there is no need to set a structural skeleton in the fuselage, which effectively reduces the waste weight of the drone, improves the carrying capacity, and extends the flight time;

[0042] like Figure 4 and Figure 5As shown, the arm hinge portion formed on the wall surface of the shell 1 is a cavity 11 formed by the inward depression of the wall surface of the shell 1. The cavity formed by the inward depression of the wall surface can effectively improve the structural strength of the place. Specifically, the cavity 11 has two side walls parallel to each other, and the two side walls are provided with through holes and the rotating shaft 2 is inserted in the through holes. The interior of the rotating shaft 2 is hollow, and the power supply line of the rotor power component c and the like are routed through the internal hollow of the rotating shaft 2. In this embodiment, the arm component b is fixedly connected to the rotating shaft 2, that is, there is no relative rotation between the arm component b and the rotating shaft 2, and the rotating shaft 2 is rotatably arranged in the side wall through hole of the cavity 11. In order to further improve the structural stability and the reliability of smooth rotation, a shell hinge seat 12 for the rotating shaft 2 to pass through is fitted on the two side walls, and the shell hinge seat 12 specifically adopts a metal hinge seat;

[0043] In addition, a rotation damping adjustment mechanism is provided on the rotating shaft 2 to improve the stability of the rotation of the arm assembly b relative to the fuselage a and avoid shaking and instability in the unfolded state and the folded state. Specifically, the rotation damping adjustment mechanism includes a nut 21, a friction plate 22 and a damping gasket 23. The friction plate 22 is sleeved on the rotating shaft 2 and fixedly connected to the shell 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 onto the friction plate 22. In this embodiment, the damping gasket 23 is respectively provided with one on both sides of the axial direction of the friction plate 22. Specifically, the rotating shaft 2 is provided with a step with a changed diameter. The friction plate 22, the damping washer 23, the friction plate 22 and the nut 21 are sequentially sleeved on the step, and the nut 21 is used to adjust the pressing force between the friction plate 22 and the damping washer 23, so as to adjust the rotation damping, so that the machine arm assembly b can rotate stably; further, a spring washer 24 is arranged between the friction plate 22 and the nut 21 close to the nut 21, and a plurality of spring washers 24 can be arranged in a stacked manner, and the nut 21 locked on the rotating shaft 2 restricts the spring washer 24 on the rotating shaft 2, and the spring washer 24 applies an elastic pressing force to the friction plate 22, the damping washer 23 and the friction plate 22, so as to ensure stable rotation damping and smooth rotation;

[0044] In this embodiment, if Figures 1 to 3As shown, the arm assembly b includes a main arm b1 and a folding arm b2. Both the main arm b1 and the folding arm b2 are hollow columnar structures made of carbon fiber composite materials, which are light in weight and high in structural strength. The rotor power assembly c is arranged on the main arm b1, one end of the folding arm b2 is hinged to the main arm b1, and the other end of the folding arm b2 is hinged to the cavity 11 of the shell 1. Specifically, the main arm b1 is a long rod along the front-to-back direction of the fuselage a, and two folding arms b2 are arranged in parallel and spaced along the length direction of the main arm b1, thereby forming a parallelogram folding arm structure, and the structural stability in the unfolded state is good, thereby ensuring the stability and safety of the flight. The rotor power assembly c is respectively arranged at both ends of the main arm b1, and the cavity 11 for connecting the arm assembly b is symmetrically arranged on the left and right sides of the fuselage a, so that the arm assembly b is symmetrically connected to the left and right sides of the fuselage a, thereby forming a four-rotor drone, and the folding arm rotates along the front-to-back direction of the fuselage, that is, the two parallel side walls of the cavity 11 are along In the horizontal direction, the main arm is away from or close to the left and right sides of the fuselage in the horizontal direction. When the main arm is away from the left and right sides of the fuselage, it is in the unfolded state, and when the main arm is close to the left and right sides of the fuselage, it is in the folded state. In the unfolded state and the folded state, the length of the space occupied by the drone in the front and rear directions of the fuselage is the length of the main arm, and because the arm assembly b is folded along the front and rear directions, the occupied space in the height direction will not be increased in the folded state, which can make the folded state more compact; in the traditional drone, each arm is respectively provided with a rotor power assembly, and each arm is independently connected to the fuselage, so that each arm needs to be rotated independently during the unfolding and folding process, the number of operations is high and the efficiency is low, while the folding arm structure described in this embodiment only needs to rotate the arm assembly twice during the unfolding and folding process, and the operation of switching the unfolded state and the folded state is more convenient and efficient, the folded state is more compact, the occupied volume is reduced, the space utilization rate is improved, it is conducive to transportation, and the transportation cost is reduced;

[0045] In order to strengthen the overall strength of the fuselage a, a support rod 13 connected between the left and right side cavities 11 is also provided in the shell 1. Specifically, the support rod 13 is connected to the friction plate 22 by bolts, and the friction plate 22 is connected and fixed to the shell hinge seat 12, and the shell hinge seat 12 is attached and fixed to the side wall of the cavity 11, so that the support rod 13 and the shell 1 are in a fixed connection relationship. The support rod 13 can strengthen the overall structural strength of the shell 1, so that the shell 1 can stably support the arm assembly b, and the support rod 13 is made of carbon fiber composite material, with a light structure and high strength, which reduces waste weight and improves the carrying capacity of the UAV.

[0046] In this embodiment, if Figure 6As shown, the folding arm structure is hinged between the main arm b1 and the folding arm b2 through a rotating assembly 3, and the rotating assembly 3 has the functions of rotation angle positioning and locking, so that it can accurately rotate to the set angle position and maintain the stability of the current state, thereby avoiding the state change of the folding arm structure during flight or transportation, thereby ensuring the stability of the flight and the stability of the transportation process, and ensuring the flight safety and transportation integrity of the UAV;

[0047] Specifically, Figure 7 and Figure 8 As shown, the rotating assembly 3 includes a rotating angle member 31, an angle positioning member 32 that rotates relative to the rotating angle member 31, and a hinged locking mechanism that moves between a locked position and an unlocked position. The rotating angle member 31 and the angle positioning member 32 are respectively connected to two components that need to be hinged. In this embodiment, the rotating angle member 31 is fixedly connected to the folding arm b2, and the angle positioning member 32 is fixedly connected to the 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 rotation states are the unfolded state and the folded state. Therefore, two groups of engaging portions 311 are arranged at intervals on the rotating angle member 31 in the rotation circumferential direction, one group is the angular position of the folded state, and the other group is the angular position of the unfolded state. The angle positioning member 32 is provided with a positioning portion 321 that cooperates with the engaging portion 311. When the rotating angle member 31 and the angle positioning member 32 rotate relative to each other, the positioning portion 321 cooperates with the engaging portions 311 at different angular positions to achieve rotation angle positioning.

[0048] When the angle member 31 and the angle positioning member 32 rotate relative to each other until the positioning portion 321 cooperates with the engaging portion 311 in the folded state, the arm assembly b rotates to the folded state; and when the angle member 31 and the angle positioning member 32 rotate relative to each other until the positioning portion 321 cooperates with the engaging portion 311 in the unfolded state, the arm assembly b rotates to the unfolded state.

[0049] During the process of rotating the arm assembly b, the articulated locking mechanism is in the unlocked position, so that relative rotation can occur between the rotating angle member 31 and the angle positioning member 32; and when the rotation is in place, that is, when the positioning portion 321 and the engaging portion 311 reach a mating state, the articulated locking mechanism is operated to switch to the locked position. At this time, the articulated locking mechanism keeps the positioning portion 321 and the engaging portion 311 in a mating state so that relative rotation cannot occur between the rotating angle member 31 and the angle positioning member 32. Therefore, the articulated locking mechanism can keep the drone in a stable unfolded state and folded state, thereby ensuring the stability of the drone's flight, avoiding accidental switching of the drone's folding state, and improving reliability.

[0050] In the present embodiment, the engaging portion 311 is a groove, and the positioning portion 321 is a protrusion matched with the groove, and the two sides of the groove along the rotation circumference are inclined slopes, and correspondingly, the two sides of the protrusion along the rotation circumference are also inclined slopes, or it can be that only one of the groove and the protrusion has two inclined slopes along the rotation circumference, and the inclined slopes are used to play a guiding role, thereby improving the smoothness of the matching 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, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 have high reliability and high precision in matching, thereby ensuring the accuracy and stability of the drone in the folded state and the unfolded state, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 have a simple structure, convenient processing, low cost, and are easy to implement;

[0051] Furthermore, in the present embodiment, the engaging portion 311 is arranged on the end face of the rotating angle member 31 close to the angle positioning member 32 along the rotating axis, and the positioning portion 321 is correspondingly arranged on the end face of the angle positioning member 32 close to the rotating angle member 31 along the rotating axis. The structure is more compact, and the engaging portion 311 and the positioning portion 321 do not occupy the space in the rotating circumferential direction. When the engaging portion 311 and the positioning portion 321 of this structural mode are adopted, as long as there is a certain mobility between the rotating angle member 31 and the angle positioning member 32 in the rotating axis, there can be a gap in the rotating axis, or the rotating angle member 31 and the angle positioning member 32 themselves can undergo elastic deformation. Then the rotating angle member 31 and the angle positioning member 32 can rotate relative to each other, and when the mobility between the rotating angle member 31 and the angle positioning member 32 in the rotating axis direction is eliminated, the gap between the rotating angle member 31 and the angle positioning member 32 in the rotating axis direction can be eliminated, or the rotating angle member 31 and the angle positioning member 32 can be pressed tightly to prevent them from elastic deformation, so that the rotating angle member 31 and the angle positioning member 32 can no longer rotate relative to each other, so that when the hinge locking mechanism is in the locking position, it can apply a force along the rotating axis direction to press the rotating angle member 31 and the angle positioning member 32 together, so as to achieve the function of keeping the positioning portion 321 and the engaging portion 311 in a matching state;

[0052] Specifically, the articulated locking mechanism includes a locking block 33 movable in a direction perpendicular to the rotation axis, and the locking block 33 is provided with a driving inclined surface 331 inclined to the rotation axis for pressing the rotation angle member 31 and the angle positioning member 32. When the locking block moves in a direction perpendicular to the rotation axis, the driving inclined surface on the locking block will produce a displacement along the rotation axis, so that the rotation angle member 31 and the angle positioning member 32 are pressed in the rotation axis, so that the protruding positioning portion 321 and the groove-shaped engaging portion 311 are more tightly matched together, and at this time, the protruding positioning portion 321 is difficult to withdraw from the groove-shaped engaging portion 311, thereby playing the function of a locking state, so that the drone can be locked and maintained in a folded state or an unfolded state to avoid accidental displacement of the folded state or the unfolded state. When the state of the drone needs to be switched, it is only necessary to move the locking block in the opposite direction.

[0053] In this embodiment, the rotating assembly 3 also includes a rotating shaft 34. The internal hollow space of the rotating shaft 34 is used for wiring, that is, the power supply line of the rotor power assembly c is routed through the internal hollow space of the rotating shaft 34. The rotating angle member 31 is non-rotatably arranged on the rotating shaft 34, and the angle positioning member 32 is rotatably sleeved on the rotating shaft 34. Since the rotating angle member 31 is fixed on the folding arm b2, the rotating shaft 34 and the folding arm b2 are in a non-rotatable fixed connection relationship. The folding arm b2 is provided with a through hole running through the upper and lower parts, and the rotating shaft 34 is inserted into the through hole. A folding arm hinge seat b21 for the rotating shaft 34 to pass through is arranged on the lower side of the through hole to improve the structural strength and ensure that the rotating shaft 34 can be with The folding arm b2 is stably connected, the rotation angle member 31 is arranged on the upper side of the through hole and sleeved on the rotating shaft 34, the lower side of the main arm b1 is provided with a through hole for the rotating shaft 34 to penetrate, and the angle positioning member 32 is fixedly arranged on the lower surface of the through hole of the main arm b1, so that the rotation angle member 31 and the angle positioning member 32 can be abutted against each other in the rotation axis direction so that the convex positioning portion 321 and the groove-shaped engaging portion 311 can cooperate to play the role of rotation angle positioning, and the main arm b1 is a hollow structure, and a main arm hinge seat b11 for the rotating shaft 34 to penetrate is arranged inside, so as to improve the structural strength of the main arm b1 at this place and strengthen the stability of the rotation connection between the folding arm b2 and the main arm b1;

[0054] In order to ensure that the locking block 33 can stably move in a direction perpendicular to the rotation axis, a channel assembly 35 fixed to the main arm hinge seat b11 is provided in the main arm b1, and the path direction of the channel assembly 35 is perpendicular to the rotation axis. Specifically, the channel assembly 35 is composed of a pressure seat 351 and a pressure plate 352 sleeved on the rotating shaft 34, the pressure seat 351 and the pressure plate 352 are fixed to the main arm hinge seat b11 by bolts, and the pressure plate 352 is a structure with an arch in the middle, so that a channel for the locking block 33 to move is formed between the pressure seat 351 and the pressure plate 352, and the path direction is perpendicular to the rotation axis. In this embodiment, the locking block 33 is provided with a through hole, and the locking block 33 is also sleeved on the rotating shaft 34. The locking block 33 is located in the channel formed between the pressure seat 351 and the pressure plate 352, and the locking block 33 passes through the wall of the main arm b1, so that the locking block 33 can be conveniently operated to switch between the locked position and the unlocked position;

[0055] Furthermore, in the present embodiment, the locking block 33 is composed of two connected parts, and the two parts respectively pass through the wall surface of the main arm b1, and one end of the locking block 33 passing through the main arm b1 is pressed toward 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 passing through the main arm b1 is pressed toward the inner side of the main arm b1 to switch from the unlocking position to the locking position. The two ends of the locking block 33 can be defined as the locking end and the unlocking end, respectively, and the locking end and the unlocking end are of different colors, for example, the unlocking end is green and the locking end is red, so as to facilitate accurate locking and unlocking operations; and in the present embodiment, a main arm b 1 is hinged with two parallel folding arms b2 at intervals, thereby forming a parallelogram folding arm structure. The main arm b1 and one of the folding arms b2 are connected by the aforementioned rotating assembly 3 with a hinge locking mechanism, while the main arm b1 and the other folding arm b2 are connected by a rotating assembly without the hinge locking mechanism. It is only necessary to lock the hinge between the main arm b1 and one of the folding arms b2 to lock the entire parallelogram folding arm structure, maintain its stable mechanism state, avoid rotation displacement, and keep the UAV in a stable unfolded state and folded state, thereby ensuring the stability of the UAV flight.

[0056] The locking block 33 is locked by the second nut 37. The locking block 33 is locked by the second nut 37. The locking block 33 is locked by the second nut 37. The locking block 33 is locked by the second nut 37. The whole unit moves upward. Since the rotating shaft 34 is fixedly connected to the folding arm b2, the folding arm b2 is also driven upward to be closer to the main arm b1, and then the rotating angle member 31 and the angle positioning member 32 are pressed together along the rotating axis, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 are tightly matched and cannot be separated and withdrawn, thereby locking the drone in the unfolded state or the folded state; and when the locking block 33 moves from the locking position to the unlocking position along the direction perpendicular to the rotating axis, the additional axial force applied to the rotating angle member 31 and the angle positioning member 32 is released, the pressure between the rotating angle member 31 and the angle positioning member 32 is reduced, and the two are reset to a state where they can rotate relative to each other, and the protruding positioning portion 321 can withdraw from the groove-shaped engaging portion 311, so that the drone can freely switch between the folded state and the unfolded state.

[0057] The rotating assembly 3 is also provided with an elastic member 38 for pre-pressing the rotating angle member 31 and the angle positioning member 32 along the rotating axis. In the present embodiment, the elastic member 38 is a plurality of spring washers mounted on the rotating shaft 34, and the spring washers are located between the nut 37 and the pressure block 36. The pressure block 36 can move freely along the axial direction of the rotating shaft 34, and the spring washers elastically press the pressure block 36 onto the locking block 33. At the same time, the force of the spring washers is also used to elastically press the rotating angle member 31 and the angle positioning member 32 together in the rotating axis. Therefore, when the rotating angle member 31 and the angle positioning member 32 rotate relative to each other, there is an elastic avoidance space between the two. During the rotation process, when the convex positioning portion 321 is not inserted into the groove-shaped engaging portion 311, the convex positioning portion 3 21 abuts against the surface of the rotating angle member 31, that is, the gap between the rotating angle member 31 and the angle positioning member 32 in the rotating axis direction becomes larger. At this time, the elastic member 38 is further compressed to achieve elastic avoidance, thereby ensuring that the rotating angle member 31 and the angle positioning member 32 can achieve relative rotation; and when the locking block 33 moves from the unlocking position to the locking position along the direction perpendicular to the rotating axis, the locking block 33 drives the pressing block 36 to move upward by the driving inclined surface 331, thereby further compressing the elastic member 38. In turn, the elastic member 38 will generate a greater force, so that the rotating angle member 31 and the angle positioning member 32 are pressed more tightly together in the rotating axis direction, ensuring that the protruding positioning portion 321 cannot withdraw from the groove-shaped engaging portion 311, thereby ensuring the stability of the drone in the folded state and the unfolded state.

[0058] like Figure 2 , Figures 9 to 12 As shown, the shell 1 is provided with a mission equipment connection mechanism 4, which mainly includes an airborne end 41 installed on the UAV and a device end 42 installed on the mission equipment, the airborne end 41 is provided with an electrical connection port 43, the device end 42 is provided with an electrical connection head 44 matching the electrical connection port 43, and the airborne end 41 is provided with a slide groove 45 for the device end 42 to be inserted, and an anti-slip locking mechanism is also provided between the airborne end 41 and the device end 42 to prevent the device end 42 from exiting the slide groove 45. The mission equipment connection mechanism of this embodiment can be used to conveniently and quickly realize the connection between the mission equipment and the UAV body, and the mechanical connection and electrical connection of the mission equipment are integrated into one, the installation operation is simpler and faster, and it is convenient to replace different types of mission equipment, so that the UAV can be applied to different needs and the scope of application is increased.

[0059] Specifically, the electrical connection port 43 and the electrical connection head 44 are 40-pin electrical connectors, which can meet the use requirements of most mission equipment;

[0060] In order to improve the efficiency of assembly and disassembly, the electrical connection port 43 and the electrical connection head 44 are connected while the mission equipment is mechanically fixed to the fuselage of the UAV. The plug-in and pull-out directions of the electrical connection port 43 and the electrical connection head 44 are set to the movable direction of the airborne end 41 along the slide groove 45. Specifically, the electrical connection port 43 is set at the end of the sliding direction of the slide groove 45, and the electrical connection head 44 is set at the front end of the insertion direction of the equipment end 42. Therefore, when the equipment end 42 is inserted along the slide groove 45, the electrical connection port 43 and the electrical connection head 44 are also plugged in. When the equipment end 42 is pulled out along the slide groove 45, the electrical connection port 43 and the electrical connection head 44 are also separated, thereby simplifying the assembly and disassembly operations of the mission equipment and improving the assembly and disassembly efficiency. The efficiency of disassembly is improved, and the electrical connection port 43 is arranged at the end of the slide slot 45, and the electrical connection head 44 is arranged at the front end of the device end 42, so that after the installation is completed, the electrical connection port 43 and the electrical connection head 44 are blocked by the device end 42, and due to the existence of the anti-drop locking mechanism, the device end 42 cannot be withdrawn from the slide slot 45, thereby ensuring the electrical connection stability of the electrical connection port 43 and the electrical connection head 44, avoiding the occurrence of poor electrical connection contact, and when the device end 42 is inserted into the slide slot 45 and is in place, the electrical connection port 43 and the electrical connection head 44 are wrapped inside the device end 42 and the task end, which can effectively protect the electrical connection port 43 and the electrical connection head 44, and avoid them from being exposed to the outside and damaged, further ensuring the reliability of the electrical connection, and ensuring that the task equipment can work stably;

[0061] In this embodiment, guide rails 451 are provided along the sliding direction on the left and right side walls of the slide slot 45, and guide grooves 452 matching the guide rails 451 are provided on the side walls of the device end 42, so as to improve the accuracy of plugging the device end 42 into and out of the slide slot, thereby ensuring that the electrical connection port 43 and the electrical connection head 44 can be accurately docked, and avoiding the situation where the electrical connection head 44 is difficult to insert into the electrical connection port 43;

[0062] The anti-drop locking mechanism mainly includes an elastic pin 46 arranged on the side wall of the guide groove 452 of the device end 42 and a socket 47 for inserting the elastic pin 46 arranged on the side wall of the guide rail 451 of the slide groove 45. The elastic pin 46 is similar to the lock tongue structure, and its front end side facing the insertion direction of the device end 42 is a guiding inclined surface, and its rear end side facing the insertion direction of the device end 42 is a right-angled surface. The elastic pin 46 includes a pin and a spring that pushes the pin protruding from the surface of the device end 42. When When the device end 42 is inserted into the airborne end 41 along the slide groove 45, before the elastic pin 46 reaches the position of the insertion hole 47, the elastic pin 46 is squeezed back into the device end 42 by the side wall of the slide groove 45. When the device end 42 is inserted into place, the elastic pin 46 just reaches the position of the insertion hole 47, so that the elastic pin 46 is reset and popped out of the insertion hole 47 to achieve the effect of limit locking, preventing the device end 42 from reversely exiting the slide groove 45, ensuring that the mission equipment is reliably connected to the drone, and avoiding the dangerous situation of the mission equipment being out of place.

[0063] Furthermore, the anti-slip locking mechanism further includes a button 48 for unlocking that is movably inserted into the socket 47. By pushing the button 48 to push the elastic pin 46, the elastic pin 46 is retracted into the inside of the device end 42, thereby releasing the locking state between the device end 42 and the onboard end 41. The operation is simple and quick. In this embodiment, the anti-slip locking mechanism is provided on each of the left and right sides of the sliding direction of the slide groove 45. The socket 47 penetrates the side wall of the slide groove in the left and right directions of the slide groove 45. The button 48 is provided on the left and right sides of the slide groove 45. Unlocking can be achieved by pressing the button 48 toward the center direction of the slide groove 45.

[0064] In order to facilitate the separation of the device end 42 from the airborne end 41, an elastic pushing mechanism 49 is also provided in the slide groove 45 to push the device end 42 out of the slide groove 45, that is, when the button 48 is pressed to press the elastic pin 46 back into the device end 42 so that the locking state of the elastic pin 46 inserted into the socket 47 is released, the elastic pushing mechanism 49 pushes the device end 42 to move out of the slide groove 45. Specifically, the elastic pushing mechanism 49 is arranged at the end of the sliding direction of the slide groove 45. The elastic pushing mechanism 49 is composed of a pushing block and a pushing spring. When the device end 42 is inserted along the slide groove 45, the device end 42 will produce a pushing effect on the elastic pushing mechanism 49, so that the pushing spring of the elastic pushing mechanism 49 is compressed and elastic potential energy is stored. When the elastic pin 46 is inserted into the locking state of the socket 47, the elastic pushing mechanism 49 is always in the state of storing elastic potential energy. The state of potential energy, and when the elastic pin 46 exits the socket 47 and becomes unlocked, the elastic pushing mechanism 49 releases the elastic potential energy to push the equipment end 42 outward along the slide groove 45, thereby improving the convenience of disassembly. In addition, since the airborne end 41 and the equipment end 42 adopt a slide groove plug-in connection method, there will be a certain fitting gap, and the fitting gap will produce greater vibration during the flight process, that is, the mission equipment will produce greater vibration, which will seriously affect the working reliability of the mission equipment. The elastic pushing mechanism 49 plays a role in generating a pre-tightening force when the equipment end 42 is inserted into the airborne end 41. The action force of the elastic pushing mechanism is in the direction of the slide groove exit, which can fill and eliminate the fitting gap between the airborne end 41 and the equipment end 42, so that the elastic pin 46 and the socket 47 are tightly fitted, thereby solving the vibration problem and ensuring the working stability and reliability of the mission equipment.

[0065] like Figure 4 As shown, the accommodating cavity of the housing 1 is used to place the flight control component 5, etc. One of the important factors affecting the flight state of the drone is that the inertial sensor used for attitude solution will be adversely affected by vibration. Resonance or random vibration will cause data errors in the sensor, which will cause fatal errors in attitude solution. Therefore, technical means are usually required to reduce the error effect caused by low-frequency vibration during the flight of the drone. The usual technical means is to indirectly install the flight control component in the fuselage through a vibration reduction device;

[0066] like Figures 13 to 16 As shown, the vibration reduction device includes a plurality of vibration reducers 6 arranged at intervals in the circumferential direction of the flight control assembly 5. In this embodiment, four vibration reducers 6 are used, which are distributed and arranged at the four corners of the flight control assembly 5. The vibration reducers 6 used in this embodiment have a multi-dimensional vibration reduction function, which can achieve horizontal and vertical vibration reduction during the flight of the UAV, so there is no need to separately set vertical vibration reducers and horizontal vibration reducers as in the prior art, which can reduce the number of vibration reducers, improve the compactness of the vibration reduction device, reduce the required assembly space, reduce waste weight, and improve the bearing capacity;

[0067] Specifically, the shock absorber 6 mainly includes a connector 1 61 connected to the flight control component 5, a connector 2 62 connected to the housing 1, and a plurality of shock absorbing wires 63. The two ends of the shock absorbing wire 63 are respectively connected to the connector 1 61 and the connector 2 62, and the connection of the shock absorbing wire 63 on the connector 1 61 forms a connection surface 1 64, and the connection of the shock absorbing wire 63 on the connector 2 62 forms a connection surface 2 65. The connection surface 1 64 is inclined to the connection surface 2 65. The shock absorbing wire 63 connected between the connector 1 61 and the connector 2 62 has a plurality of different shapes and lengths, so that the connection surface 1 64 is inclined to the connection surface 2 65. The shock absorbing wires 63 of different shapes and lengths have different shock absorbing directions. After the shock absorbing wires 63 of different shapes and lengths are combined together, a single shock absorber 6 is finally realized to have a multi-dimensional shock absorbing function, thereby reducing the use of the shock absorber while improving the shock absorbing effect.

[0068] The angle between the connection surface 1 64 and the connection surface 2 65 is 60-70°, preferably, the angle between the connection surface 1 64 and the connection surface 2 65 is 66.5°, so that the vibration reduction effect of the vibration absorber 6 in different directions is balanced, and the overall vibration reduction effect is improved; and the vibration reduction wire 63 is a steel wire cable with a diameter of 1-1.5 mm, preferably a 1.2 mm steel wire cable, and the diameter of the vibration reduction wire 63 can be selected according to flight control components of different weights, ensuring that the vibration reduction effect of flight control components of different weights can meet the requirements;

[0069] In this embodiment, the connecting member 1 61 is a flat plate parallel to the connecting surface 1 64, and the connecting member 2 62 is a flat plate parallel to the connecting surface 2 65, which has a simple structure and is easy to manufacture. The connecting member 1 61 and the connecting member 2 62 can also be designed to have a special-shaped structure, for example, the connecting member 1 61 and the connecting member 2 62 are triangular prisms, L-shaped plates, etc., and can be set to a specific shape according to actual connection needs;

[0070] In the present embodiment, there are four vibration damping wires 63, two of which are bent roughly into a C shape, and the other two are bent roughly into a spiral shape, and the vibration damper 6 is symmetrically structured, that is, the two C-shaped vibration damping wires 63 are symmetrically connected to the connecting member 1 61 and the connecting member 2 62, and the two spiral vibration damping wires 63 are also symmetrically connected to the connecting member 1 61 and the connecting member 2 62. The vibration damping direction of the C-shaped vibration damping wire 63 is mainly the direction of the connecting line at both ends of the C-shaped vibration damping wire 63, and the vibration damping direction of the spiral vibration damping wire 63 is mainly the spiral axial direction of the spiral vibration damping wire 63 and the direction perpendicular to the spiral axial direction, so that the vibration damping wires 63 of different shapes and lengths are combined so that the connecting surface 1 64 is inclined to the connecting surface 2 65 and realizes a good vibration damping function in multiple dimensions.

[0071] Furthermore, all the vibration-damping wires 63 connected to the connecting piece 1 61 and the connecting piece 2 62 are formed by bending a long steel wire, and the connecting piece 1 61 and the connecting piece 2 62 are provided with connecting holes for the long steel wire to pass through, and the long steel wire is fixed in the connecting holes, which can improve the overall structural stability of the vibration absorber 6, reduce the situation of the vibration-damping wire 63 separating from the connecting piece 1 61 and the connecting piece 2 62, and ensure that the vibration absorber 6 can work stably for a long time and ensure a stable vibration reduction effect;

[0072] In this embodiment, the connector 1 61 is directly connected to the flight control assembly 5, and the connector 2 62 is fixedly connected to the mounting base fixed on the shell 1, and the connecting surface 1 64 is parallel to the horizontal plane, and the connecting surface 2 65 is inclined to the horizontal plane. There is no need to set up an adapter to carry the flight control assembly 5, and then the connector 1 61 is connected to the adapter. The structure is more compact, reducing the required assembly space and waste weight. During assembly, the connector 1 61 and the connector 2 62 of the shock absorber 6 are facing the center of gravity of the flight control, ensuring that the four shock absorbers 6 can work together to effectively reduce vibrations in multiple directions and frequencies, improve the vibration reduction effect, and improve the stability of the UAV flight.

[0073] like Figures 1 to 3 , Fig.17 , Fig.18 As shown, the arm assembly b of the UAV is also provided with a landing gear d. Specifically, the landing gear d is fixed to the lower sides of both ends of the main arm b1. The landing gear d mainly includes 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 a foldable structure. The landing gear d is made of ABS material and is unfolded when needed. It can well support the UAV and prevent the arm assembly and fuselage of the UAV from being bumped and ensured in good condition. When the landing gear is needed, it can be folded and retracted to reduce the occupied space and facilitate placement and transportation. A holding locking mechanism for maintaining the state of the landing gear body d2 is provided between the mounting seat d1 and the landing gear body d2, and an antenna d3 is provided on the landing gear body d2. There is no shielding around the landing gear body, which can ensure the signal strength.

[0074] In this embodiment, the holding locking mechanism includes a lock buckle d4 hinged on the landing gear body d2 and a clamping portion d5 provided on the mounting seat d1 and cooperating with the lock buckle d4. When the landing gear body d2 is deployed in place, the lock buckle d4 is buckled with the clamping portion d5 to lock and maintain the deployed state of the landing gear body d2, thereby preventing it from being accidentally folded and recovered, and ensuring that the landing gear can reliably and stably support the entire UAV.

[0075] In order to further ensure the reliability of locking the landing gear body d2 in the deployed state, the locking mechanism is further provided with an elastic member for driving the lock buckle d4 to maintain the locked state. The elastic member is specifically a torsion spring. The acting direction of the torsion spring is the direction of maintaining the lock buckle d4 and the clamping part d5, which further provides a guarantee for locking the landing gear body d2 in the deployed state.

[0076] In this embodiment, the landing gear body d2 is a hollow structure, which can reduce weight, reduce waste weight, and improve the carrying capacity of the UAV. The antenna d3 is arranged in the hollow interior of the landing gear body d2, does not occupy external space, can effectively protect the antenna d3, and ensure that the antenna d3 works stably and long-term. A cover plate d6 for opening and closing the hollow interior is arranged on the landing gear body d2, which is convenient for taking and placing the antenna d3, and improves the convenience of operation.

[0077] A shock-absorbing pad d7 is also provided at the bottom of the landing gear body d2. The shock-absorbing pad d7 can specifically be made of shock-absorbing foam to improve the cushioning stability when the landing gear d supports the drone, reduce the impact on the flight control components inside the fuselage when the drone lands on the ground, and ensure the long-term and stable operation of the flight control components.

[0078] During the flight of the drone, the flight control components 5 and other components inside the shell will generate heat. If the temperature is too high, it will seriously affect the working stability of the drone and shorten the service life of the drone. In this embodiment, the shell 1 is provided with a heat dissipation mechanism to ensure good heat dissipation during the flight of the drone, thereby ensuring that each component is in a suitable state and ensuring that the drone can work stably and effectively for a long time.

[0079] Specifically, Figure 4 As shown, the heat dissipation mechanism includes an air inlet 14, an air outlet 15 and a heat dissipation fan 16 arranged at the air inlet 14, which introduces external air into the housing 1 from the air inlet 14. The air is discharged from the air outlet 15 after absorbing the heat of the components in the housing. In this embodiment, the air inlet 14 is arranged at the front end of the housing 1, and the air outlet 15 is arranged on the left and right sides of the housing 1. The air inlet 14 is arranged on the windward side when the UAV is flying, which is conducive to air entering the housing from the air inlet and being discharged from the air outlet, thereby improving the heat dissipation effect. In this embodiment, the flight control component 5 is installed in the housing 1 at a position close to the nose of the UAV, and the avionics component is installed in the housing at a position close to the tail of the UAV. The airflow entering the housing 1 from the air inlet 14 at the front end of the nose can effectively take away the heat of the flight control component 5 and the avionics component during the process of flowing through the housing 1, thereby ensuring efficient heat dissipation effect, ensuring that the working temperature of each component is suitable, and improving working stability.

[0080] The drone is also provided with a navigation light. Specifically, the navigation light is provided on the main arm b1 of the arm assembly b. The main arm of the present application is a hollow columnar structure made of carbon fiber composite material. The navigation light is provided in the hollow interior of the main arm b1. A transparent light guide cover b3 for the navigation light to transmit light is provided on the bottom side of the main arm b1. The transparent light guide cover b3 is used to effectively protect the navigation light, thereby ensuring that the navigation light can work stably and effectively for a long time.

[0081] In this embodiment, the arm assembly b is a parallelogram folding structure composed of a main arm b1 and a folding arm b2. The main arm b1 is in the shape of a long rod along the front and rear direction of the fuselage a. The arm assembly b is symmetrically arranged on the left and right sides of the shell 1. The navigation lights are at the bottom of the main arm b1 at both ends. The electrically adjustable light source of the rotor power assembly c can be directly used as the navigation light, and different navigation lights display different colors to identify the front and rear directions of the UAV. Specifically, the navigation lights on the side of the UAV nose and the navigation lights on the side of the UAV tail can be different in color, so that the nose direction of the UAV can be easily and accurately identified, so that ground personnel can easily judge the front and rear directions of the UAV by observation, which is conducive to precise control of the UAV.

[0082] like Figure 2 As shown, the avionics assembly 7 is arranged at the rear end of the shell 1. The avionics assembly 7 includes a battery compartment 72 specifically arranged at the rear of the shell for inserting a battery 71. The battery compartment 72 is open, that is, the mouth of the battery compartment 72 is exposed outside the shell 1. A quick plug-in structure is adopted between the battery 71 and the battery compartment 72, replacing the traditional method of opening the shell first and then replacing the battery, thereby improving the efficiency of loading and unloading and replacing the battery. A lock is provided on the battery. When the battery is inserted into the battery compartment, the lock of the battery will automatically extend into the hole on the side wall of the battery compartment to complete the locking, thereby ensuring the stability and speed of the battery installation. When the battery 71 needs to be replaced, the battery can be pulled out of the battery compartment by pulling the handle provided on the battery, and the disassembly is convenient and simple.

[0083] Battery 71 adopts a smart battery and has a built-in heating plate. The heating plate is powered by the battery itself and does not require external power supply. The integrated design structure can heat the battery and keep it warm after the heating plate is powered on in a low temperature environment, thereby ensuring the discharge rate of the battery and stabilizing the output current of the battery, thereby ensuring the flight stability of the unmanned aircraft. Battery 71 is also provided with a communication interface for real-time communication with the drone, which can accurately identify the remaining capacity of the battery in real time, ensuring that the drone's endurance is intuitive and controllable.

[0084] The above are only preferred embodiments of the present invention. It should be noted that the above preferred embodiments should not be regarded as limiting the present invention, and the protection scope of the present invention should be based on the scope defined by the claims. For ordinary technicians in this technical field, several improvements and modifications can be made without departing from the spirit and scope of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A drone, characterized in that: The invention comprises a fuselage (a), an arm assembly (b) and a rotor power assembly (c), wherein the fuselage (a) comprises a shell (1) having a receiving cavity therein, the arm assembly (b) is rotatably connected to an arm hinge formed on the wall of the shell (1) to form a folded arm structure, and the rotor power assembly (c) is arranged on the arm assembly (b); The folding machine arm structure comprises a rotating assembly (3) for articulation, the rotating assembly (3) comprising a rotating angle member (31), an angle positioning member (32) rotating relative to the rotating angle member (31), and an articulated locking mechanism operating between a locked position and an unlocked position, the rotating angle member (31) being provided with at least one engaging portion (311) spaced apart in the rotation circumferential direction, the angle positioning member (32) being provided with a positioning portion (321) cooperating with the engaging portion (311), and the articulated locking mechanism maintaining the positioning portion (321) and the engaging portion (311) in a coordinated state when being in the locked position; The hinged locking mechanism comprises a locking block (33), the locking block (33) moves perpendicular to the rotation axis of the rotating assembly (3), and the locking block (33) is provided with a driving inclined surface (331) inclined to the rotation axis for pressing the rotating angle member (31) and the angle positioning member (32) together.

2. The drone according to claim 1, characterized in that: The arm assembly (b) comprises a main arm (b1) and a folding arm (b2); the rotor power assembly (c) is arranged on the main arm (b1); one end of the folding arm (b2) is hinged to the main arm (b1), and the other end is hinged to the shell (1).

3. The drone according to claim 2, characterized in that: A plurality of folding arms (b2) are arranged in parallel and at intervals along the length direction of the main arm (b1).

4. The drone according to claim 1, characterized in that: The engaging portion (311) is a groove, and the positioning portion (321) is a protrusion that cooperates with the groove. The engaging portion (311) is arranged on the end face of the rotating angle member (31) close to the angle positioning member (32) along the rotating axis, and the positioning portion (321) is correspondingly arranged on the end face of the angle positioning member (32) close to the rotating angle member (31) along the rotating axis.

5. The drone according to claim 1, characterized in that: The hinged locking mechanism also includes a channel assembly (35) whose path direction is perpendicular to the rotation axis. The locking block (33) slides along the path of the channel assembly (35) to switch between a locked position and an unlocked position, and is used to press the rotation angle member (31) and the angle positioning member (32) along the rotation axis.

6. The drone according to claim 5, characterized in that: The main arm (b1) is a hollow structure, and a main arm hinge seat (b11) is arranged inside the main arm. The channel component (35) is fixed on the main arm hinge seat (b11). The locking block (33) passes through the wall surface of the main arm (b1), and the two ends of the locking block (33) are respectively a locking end and an unlocking end.

7. The drone according to claim 1, characterized in that: The shell (1) is provided with a task equipment connection mechanism (4), which includes an airborne end (41) installed on the drone and a device end (42) installed on the task equipment, the airborne end (41) is provided with an electrical connection port (43), the device end (42) is provided with an electrical connection head (44) matching the electrical connection port (43), and the airborne end (41) is provided with a slide groove (45) for the device end (42) to be inserted, and an anti-slip locking mechanism is also provided between the airborne end (41) and the device end (42) to prevent the device end (42) from exiting the slide groove (45).

8. The drone according to claim 7, characterized in that: The anti-drop locking mechanism comprises an elastic pin (46) arranged on the side wall of the equipment end (42) and a socket (47) arranged on the side wall of the slide groove (45) for the elastic pin (46) to be inserted.

9. The drone according to claim 1, characterized in that: A flight control component (5) is fixed in the accommodating cavity of the shell (1) via a shock absorber (6). The shock absorber (6) comprises a first connector (61) connected to the flight control component (5), a second connector (62) connected to the shell (1), and a plurality of shock-absorbing wires (63). The two ends of the shock-absorbing wires (63) are respectively connected to the first connector (61) and the second connector (62). The connection of the shock-absorbing wires (63) on the first connector (61) forms a first connection surface (64), and the connection of the shock-absorbing wires (63) on the second connector (62) forms a second connection surface (65). The first connection surface (64) is inclined to the second connection surface (65). There are shock-absorbing wires (63) of different shapes and / or lengths between the first connector (61) and the second connector (62). Different shock-absorbing wires (63) have different shock-absorbing directions to achieve multi-dimensional shock-absorbing.

10. The drone according to claim 9, characterized in that: The angle between the first connecting surface (64) and the second connecting surface (65) is 60-70 degrees.

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