CN212448035U

CN212448035U - Lightweight unmanned aerial vehicle

Info

Publication number: CN212448035U
Application number: CN202020787313.7U
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: 2021-02-02
Anticipated expiration: 2030-05-13

Abstract

The utility model discloses a lightweight unmanned aerial vehicle, including fuselage, horn subassembly and rotor power component, the fuselage include the casing by plate material machine-shaping, the casing on be provided with the inside sunken chamber groove of wall, the horn subassembly articulate in chamber groove department and constitute beta structure, rotor power component set up on the horn subassembly. Lightweight unmanned aerial vehicle structure light-duty intensity be high, can improve unmanned aerial vehicle's bearing capacity, need not to set up the strengthening rib on the casing, avoid increasing unmanned aerial vehicle's useless heavy, improve bearing capacity, extension duration, folding structure effectively reduces and occupies the volume, convenient storage is favorable to the transportation.

Description

Lightweight unmanned aerial vehicle

Technical Field

The utility model relates to an aircraft technical field especially relates to a lightweight unmanned aerial vehicle.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and 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, and fuselage structural strength is poor, increases the structural framework usually and comes to bear parts such as horn, mission equipment, but greatly increased unmanned aerial vehicle's useless heavy like this, reduced the bearing capacity of aircraft, shortened flight duration.

SUMMERY OF THE UTILITY MODEL

The utility model discloses the technical problem that will solve and the technical task that provides improve prior art, provide a lightweight unmanned aerial vehicle, solve unmanned aerial vehicle fuselage structural strength difference among the prior art, useless great, lead to the problem that bearing capacity is low, duration is short.

For solving the above technical problem, the technical scheme of the utility model is that:

the utility model provides a lightweight unmanned aerial vehicle, includes fuselage, horn subassembly and rotor power component, the fuselage include the casing by plate material machine-shaping, the casing on be provided with the inside sunken chamber groove of wall, the horn subassembly articulate and constitute beta structure in chamber groove department, rotor power component set up on the horn subassembly. The light unmanned aerial vehicle adopts the shell which is processed and formed by the plate-shaped material, preferably the shell which is made of the carbon fiber composite material, does not need to be provided with a reinforcing rib on the shell, has high light intensity of the structure, avoids increasing the waste weight of the unmanned aerial vehicle, can improve the bearing capacity of the unmanned aerial vehicle, adopts the cavity groove which is formed in the wall surface of the shell and is concave as the hinged joint of the horn component, namely, the shell is directly utilized to integrally bear the horn component and the rotor power component on the horn component, the cavity groove formed by the concave surface can effectively improve the structural strength, and the shell is processed and formed by the plate-shaped material of the carbon fiber composite material, and the like, thereby further ensuring the structural strength of the cavity groove, avoiding the situations that the cavity groove is damaged, the horn component shakes and even falls off, and further avoiding the arrangement of a structural framework which is used for connecting and bearing the horn component in the body, and then effectively reduce unmanned aerial vehicle's useless heavy, improve bearing capacity, extension duration, folding structure effectively reduces occupation volume, and convenient storage is favorable to the transportation.

Further, fuselage, horn subassembly adopt carbon-fibre composite machine-shaping, the light-duty intensity of structure is high, need not to set up the strengthening rib on the casing, reduces unmanned aerial vehicle self gravity, improves bearing capacity.

Furthermore, the left side and the right side of the shell are symmetrically provided with a plurality of cavity grooves, the left side and the right side of the fuselage are symmetrically connected with the machine arm assembly, and the unmanned aerial vehicle is integrally in a left-right symmetric structure.

Further, still be provided with the bracing piece of connecting between left and right side chamber groove in the casing, strengthen the overall structure intensity of casing, the loader arm subassembly that can be more firm.

Furthermore, the cavity groove is provided with two parallel side walls, a rotating shaft of the machine arm assembly is inserted on the two side walls, and the rotating connection structure is simple and good in stability.

Further, the side wall that is parallel to each other of chamber groove on connect and set up the articulated seat of casing that supplies the axis of rotation to pass, the axis of rotation rotates to be connected at the articulated seat of casing, the quick-witted arm component that bears that can be more firm improves the stability when the quick-witted arm component rotates simultaneously.

Furthermore, the rotating shaft is provided with a rotating damping adjusting mechanism which can rotate stably.

Furthermore, the rotary damping adjusting mechanism comprises a nut, a friction plate and a damping gasket, the friction plate is fixedly connected with the shell hinge seat, the nut is screwed on the rotary shaft and presses the damping gasket sleeved on the rotary shaft on the friction plate, and the friction damping between the damping gasket and the friction plate is the rotary damping of the machine arm assembly, so that the rotary stability is improved.

Furthermore, the two sides of the friction plate along the rotating axial direction are respectively provided with one damping gasket, so that the mechanical arm assembly has stable rotating damping when rotating.

Furthermore, the rotary damping adjusting mechanism further comprises a spring gasket sleeved on the rotary shaft, the compression amount of the spring gasket is adjusted through a nut so as to adjust the pressing force between the friction plate and the damping gasket, and the damping during rotation of the horn assembly is conveniently and flexibly adjusted.

Compared with the prior art, the utility model discloses the advantage lies in:

lightweight unmanned aerial vehicle structure light-duty intensity be high, can improve unmanned aerial vehicle's bearing capacity, need not to set up the strengthening rib on the casing, avoid increasing unmanned aerial vehicle's useless heavy, improve bearing capacity, extension duration, folding structure effectively reduces and occupies the volume, space utilization is high, conveniently accomodates, is favorable to the transportation.

Drawings

Fig. 1 is a structural schematic diagram of a light unmanned aerial vehicle in an unfolded state;

fig. 2 is a schematic structural view of a lightweight unmanned aerial vehicle in a folded state;

FIG. 3 is a schematic structural view of the housing;

fig. 4 is a sectional view of the joint between the horn assembly and the housing.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

The embodiment of the utility model discloses a lightweight unmanned aerial vehicle, the structure is light-duty, intensity is high, effectively improves bearing capacity, extension duration, and folding structure effectively reduces occupation volume, and convenient storage is favorable to the transportation.

As shown in fig. 1 to 4, a lightweight unmanned aerial vehicle mainly comprises a body a, a horn assembly b and a rotor power assembly c, wherein the body a comprises a housing 1 which is formed by processing a plate-shaped material and is provided with a containing cavity, the housing 1 is provided with a cavity groove 11 with an inward sunken wall surface, the horn assembly b is hinged to the cavity groove 11 to form a folding horn structure, the rotor power assembly c is arranged on the horn assembly b, and the horn assembly b is further provided with a folding undercarriage d.

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 arm component b are specifically formed by processing carbon fiber composite materials, 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, so that the shell 1 and the arm component b are guaranteed to have excellent structural strength, the fuselage a and the arm component b are only thin shell structures, reinforcing ribs are not needed to be arranged, the arm component b is directly connected to the shell 1, a structural framework is not needed to be arranged in the fuselage, the waste weight of the unmanned aerial vehicle is effectively reduced;

the cavity groove formed by the inner recess of the 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 arranged on the two side walls, the rotating shaft 2 is inserted and arranged in the through holes, the inside of the rotating shaft 2 is hollow, the power supply line of the rotor power component c and the like are routed from the inside of the rotating shaft 2, in the embodiment, the machine arm component b is fixedly connected with the rotating shaft 2, the rotating shaft 2 is inserted and arranged in the through hole arranged on the machine arm component b, the two ends of the through hole of the machine arm component b are attached with the folding arm hinge seat b21 for the rotating shaft 2 to penetrate and fix, the relative rotation between the machine arm component b and the rotating shaft 2 is not generated, the rotating shaft 2 is rotatably arranged in the through hole of the side wall of the cavity groove 11, in order to further improve the structural stability and the stable and reliable rotation, the shell hinge seat, 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, 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, the weight is light, the structural strength is high, the 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 in the shape of a long rod along the fore-and-aft direction of the fuselage a, the folding arm b2 is disposed in parallel and spaced along the length direction of the main arm b1 to form a parallel folding boom structure, the unfolded state has good structural stability and quadrilateral safety, the rotor power assemblies c are disposed at both ends of the main arm b1, the cavity 11 for connecting the boom assemblies b is symmetrically disposed at both left and right sides of the fuselage a, so that the boom assemblies b are symmetrically connected at both left and right sides of the fuselage a, therefore, the folding horn structure of the embodiment only needs to carry out operation of rotating the horn assemblies twice in the unfolding and folding processes, the operation of switching the unfolding state and the folding state is more convenient and efficient, the compactness of the folding state is better, the occupied volume is reduced, the space utilization rate is improved, the transportation is facilitated, and the transportation cost is reduced;

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.

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 enhancements can be made without departing from the spirit and scope of the invention, and such modifications and enhancements are intended to be within the scope of the invention.

Claims

1. The utility model provides a lightweight unmanned aerial vehicle, its characterized in that includes fuselage (a), horn subassembly (b) and rotor power component (c), fuselage (a) include casing (1) by plate material machine-shaping, casing (1) on be provided with inside sunken chamber groove (11) of wall, horn subassembly (b) articulate and locate to constitute beta structure in chamber groove (11), rotor power component (c) set up on horn subassembly (b), the casing bears rotor power component on horn subassembly and the horn subassembly.

2. The unmanned aerial vehicle of claim 1, wherein the fuselage (a) and the arm assembly (b) are formed by machining carbon fiber composite materials.

3. The unmanned aerial vehicle with light weight as claimed in claim 1, wherein the housing (1) is provided with a plurality of cavities (11) symmetrically on left and right sides.

4. The unmanned aerial vehicle of claim 3, wherein the housing (1) is further provided with a support rod (13) connected between the left and right side cavities (11).

5. The unmanned aerial vehicle of any one of claims 1 to 4, wherein the cavity (11) has two parallel side walls, and the rotation shaft (2) of the arm assembly (b) is inserted through the two side walls.

6. The unmanned aerial vehicle with the light weight as claimed in claim 5, wherein the side walls of the cavity groove (11) which are parallel to each other are connected with a housing hinge seat (12) for the rotation shaft (2) to pass through.

7. The unmanned aerial vehicle of claim 5, wherein the rotating shaft (2) is provided with a rotating damping adjusting mechanism.

8. The unmanned aerial vehicle with the light weight as claimed in claim 7, wherein the rotation damping adjustment mechanism comprises a nut (21), a friction plate (22) and a damping washer (23), the friction plate (22) is fixedly connected with the housing hinge seat (12), the nut (21) is screwed on the rotating shaft (2) and presses the damping washer (23) sleeved on the rotating shaft (2) on the friction plate (22).

9. The unmanned aerial vehicle of claim 8, wherein the damping washer (23) is disposed on each of two sides of the friction plate (22) along the rotation axis direction.

10. The unmanned aerial vehicle of claim 8, wherein the rotary damping adjusting mechanism further comprises a spring washer (24) sleeved on the rotary shaft (2), and the compression amount of the spring washer (24) is adjusted through a nut (21) to adjust the pressing force between the friction plate (22) and the damping washer (23).