CN108058827A - A kind of unmanned plane - Google Patents

Abstract

The invention discloses an unmanned aerial vehicle, comprising: a fuselage; two arms, arranged on both sides of the fuselage, and arranged along the length direction of the fuselage; and a propeller is respectively arranged at the front and rear of the top of the arm. Two first folding arms, the two arms are respectively connected to the fuselage through one of the first folding arms; one end of the first folding arm is hinged to the arm, and the other end is hinged to the fuselage; The rotation of the first folding arm drives the arm close to the fuselage to fold the arm, or drives the arm away from the fuselage to unfold the arm. The present invention only includes two arms arranged on both sides of the fuselage. The two arms are respectively connected to the fuselage through the first folding arm. The folding of the arms is fast and convenient, and the folded UAV is small in size. , easy to store and carry.

Description

a drone

technical field

The invention relates to the technical field of unmanned aerial vehicle design, in particular to a novel unmanned aerial vehicle arm and unmanned aerial vehicle which are convenient to fold and resistant to collision.

Background technique

UAVs are widely used in agriculture, exploration, photography, border patrol and other fields because of their advantages of flexible maneuverability, fast response, unmanned flight, and low operation requirements.

Existing drones have the following disadvantages:

1. The existing drones are usually equipped with an arm for each propeller, one end of the arm is connected to the fuselage, and the propeller is installed on the other end of the arm, so most of the existing drones are equipped with four or four more than one arm. Among them, some UAVs design the arms to be foldable, but this type of UAV needs to fold the arms one by one, which is inconvenient to fold, and the volume is still large after folding, which is inconvenient to store and carry; in addition , the folding arm on the existing drone cannot be locked after being folded, which brings inconvenience to the transportation and carrying of the drone.

2. Existing UAVs are assembled from independent fuselages, arms and other components, and the fuselage and arms of existing UAVs are all made of plastic shells as strength components, which are not strong enough; This type of UAV is easily damaged during the impact process, and may even fall apart; in addition, the electrical parts on the fuselage and arm of the existing UAV are all installed on the plastic shell, and the UAV is damaged during the impact process. It will also cause damage or loss of electrical parts.

3. The heat dissipation effect of the electrical parts in the arm of the existing drone and the electrical parts in the fuselage is poor.

4. Most of the propellers of existing drones are integrated with the arms of the drone, and the blades cannot be disassembled directly. When the blades need to be repaired or replaced, the entire propeller needs to be disassembled, resulting in disassembly and maintenance of the propeller. Inconvenient; and the blades of the propellers in the prior art are always in the open state, so that the drone takes up a lot of space when it is not in use, and is not easy to carry and store.

5. There is usually only one indicator light on the existing UAV, which is usually a three-color light, which is used for real-time flight status of the UAV; but the existing indicator light cannot indicate the flight of the UAV Direction, especially when the UAV is at night or in a harsh environment, the operator cannot distinguish the flying direction of the UAV, and cannot observe the flight attitude of the UAV.

Contents of the invention

In order to solve the above technical problems, the present invention provides an unmanned aerial vehicle, including:

body;

The machine arm is arranged on one side of the fuselage, and is arranged along the length direction of the fuselage; the front and rear of the top of the machine arm are respectively provided with a propeller.

A first folding arm, the arm is connected to the fuselage through a first folding arm; one end of the first folding arm is hinged to the arm, and the other end is hinged to the fuselage; the first folding arm is hinged to the fuselage; A folding arm rotates to drive the arm close to the fuselage to fold the arm, or drives the arm away from the fuselage to unfold the arm.

Preferably, the fuselage includes an organic metal frame, the arm includes an organic metal frame, and the first folding arm includes a first folding arm metal frame; one end of the first folding arm metal frame is connected to The metal frame of the fuselage is hinged, and the other end is hinged with the metal frame of the machine arm to form a metal frame of the drone.

Preferably, the propeller is connected to the metal frame of the machine arm; the electrical parts in the machine arm are installed on the metal frame of the machine arm; the electrical parts in the fuselage are installed on the metal frame of the machine arm above; the outer side of the fuselage is provided with a pan-tilt, and the pan-tilt is connected with the metal frame of the fuselage.

Preferably, the machine arm includes an organic arm shell, and the metal frame of the machine arm is used as a part of the machine arm shell; an electric regulator board for controlling the propeller is arranged inside the machine arm shell, and the electric regulator The board is attached to the metal frame of the machine arm, and the heat generated by the electric control board is transferred to the metal frame of the machine arm for heat dissipation.

Preferably, cooling holes for the machine arm are also provided at positions corresponding to the electric control board on the machine arm shell.

Preferably, one arm is provided on both sides of the fuselage, and the front and rear ends of the two arms are provided with omnidirectional antennas for signal transmission with the remote control of the drone.

Preferably, the front end of one of the arms is provided with a 5.8G omnidirectional antenna, and the rear end is provided with a 2.4G omnidirectional antenna; the front end of the other described machine arm is provided with a 2.4G omnidirectional antenna, and the rear end is provided with a 5.8G omnidirectional antenna.

Preferably, a landing gear is provided at the front and rear of the bottom of the arm, and a foot pad is provided at the bottom of the landing gear; the foot pad is installed on the bottom of the landing gear through a buckle assembly and glue.

Preferably, the bottom of the arm is detachably provided with an anti-pinch device; the anti-pinch device is arranged between the front and rear undercarriages.

Preferably, the propeller includes:

The paddle assembly includes a paddle seat and a paddle arranged on the paddle seat, and the paddle can be rotated and folded around the joint with the paddle seat;

a fixed seat, the paddle seat is detachably mounted on the fixed seat;

The power device is installed on the arm, and the fixed device is installed on the power device; the power device drives the fixed seat to rotate, thereby driving the blade assembly to rotate.

Preferably, the detachable connection between the paddle seat and the fixed seat is achieved through a quick release assembly; a counterbore is provided at the lower end of the paddle seat, and the upper end of the fixed seat extends into the counterbore, so The quick release assembly includes a first connecting assembly for realizing the axial positioning between the fixing seat and the counterbore, and a second connecting assembly for realizing the circumferential positioning between the fixing seat and the counterbore.

Preferably, the first connection component includes:

The first clip is arranged on the side of the upper end of the fixing seat and extends radially;

The first bayonet is arranged on the inner wall of the counterbore, and the first bayonet is arranged along the circumference of the inner wall of the counterbore; the first bayonet is matched with the first clip;

The fixing seat protrudes into the counterbore, the paddle seat rotates relative to the fixing seat, and the first clamping member snaps into the first bayonet.

Preferably, the second connection assembly includes:

The lower end of the button is installed in the fixed seat, and the lower end of the button is provided with an elastic member, and the button can move axially relative to the fixed seat; a through hole is arranged in the center of the paddle seat, and the fixed seat The upper end extends into the counterbore, and the upper end of the button passes through the counterbore and the through hole in turn;

The second clip is arranged on the side wall of the lower end of the key, and one end of the second clip is located in the fixing seat, and the other end extends out of the fixing seat;

The second bayonet socket is arranged on the bottom of the counterbore at a position corresponding to the first bayonet socket;

After the first clip is snapped into the first bayonet, the second clip is snapped into the second bayonet under the action of the elastic member.

Preferably, a locking mechanism is provided at the hinges of the first folding arm, the arm and the fuselage; after the arm is unfolded or folded, the locking mechanism realizes the locking mechanism between the first folding arm and the fuselage. The joints of the machine arm and the fuselage are locked at the joints.

Preferably, the locking mechanism includes:

A rotating shaft, one end is fixedly connected to the arm/the fuselage, and the other end is rotatably connected to the first folding arm;

The first rotating wheel is sleeved on the rotating shaft, and the first rotating wheel is non-rotatable relative to the rotating shaft; one side of the first rotating wheel of the rotating shaft is provided with a circumferentially arranged slider;

The second rotating wheel is fixed on the first folding arm, and the second rotating wheel is rotatably sleeved on the rotating shaft; the second rotating wheel is on the side opposite to the first rotating wheel A circumferentially arranged chute is provided, and the slider is matched with the chute;

The first runner and the second runner are pressed together and can rotate with each other, and the rotating shaft drives the first runner to rotate relative to the second runner, and the slider snaps into the Locking is realized in the chute.

Preferably, a slider is arranged on the upper circumference of the first rotating wheel, and two sliding slots are arranged on the upper circumference of the second rotating wheel; the sliding block is turned into one of the sliding slots to realize the After unfolding and locking, the slide block is transferred into another chute to realize locking after the folding of the machine arm.

Preferably, the locking mechanism further includes an elastic assembly, which is sheathed on the rotating shaft, and presses the first runner and the second runner together; the elastic assembly includes a sleeve A plurality of elastic washers arranged on the rotating shaft, the elastic washers are pressed against one side of the first runner so that the other side of the second runner is pressed against the second runner superior.

Preferably, the locking mechanism also includes:

An upper bracket, one end of the rotating shaft is mounted on the upper bracket, and the upper bracket is fixedly mounted on the arm/the fuselage;

a lower bracket, the lower bracket is fixed on the first folding arm, the second runner is fixed on the lower bracket; one end of the rotating shaft is installed on the arm/the fuselage, and the other One end passes through the lower bracket, the second runner and the first runner in turn.

Preferably, a second folding arm is further provided between the arm and the fuselage, and the two ends of the second folding arm are respectively hinged to the arm and the fuselage.

Preferably, a circuit board module is arranged in the fuselage, and the circuit board module is installed on a heat dissipation assembly, and the heat dissipation assembly includes:

The heat sink, the circuit board module is installed on the lower end surface of the heat sink, and is attached to the lower end surface of the heat sink; the upper end surface of the heat sink is provided with a number of air guide walls;

The heat dissipation fan is installed above several of the air guide walls; a heat dissipation channel extending from the center of the heat sink to the edge is formed between the adjacent air guide walls.

Preferably, a first indicator light and a second indicator light are respectively provided on the left and right sides of the drone, a third indicator light is provided at the front or tail of the drone, and the first indicator light, the second indicator light The connecting line with the third indicator light is triangular.

Preferably, the first indicator light and the second indicator light are constant monochrome lights, and the third indicator light is a tricolor light indicating the flight state of the drone.

Compared with the prior art, the present invention has the following advantages and positive effects due to the adoption of the above technical solutions:

1. In the drone provided by the present invention, only one arm is provided on the side, and the arm is connected to the fuselage through a first folding arm, which is fast and convenient to fold. Moreover, the arm is arranged along the length direction of the fuselage. The folded arms are placed close to the sides of the fuselage and arranged in the length direction, so that the folded drone is long and narrow as a whole. Compared with the existing technology, the folded drone is more convenient for storage. carry;

At the same time, a locking mechanism is provided at the connection between the first folding arm and the machine arm and the fuselage; in the locking mechanism, a slider on the first wheel and two slide grooves on the second wheel realize that the arm is in the unfolded state. Locking in the down or folded state; specifically, when the arm is fully unfolded, the slider snaps into one of the chute to achieve locking; of course, after the arm is fully folded, the slider snaps into the other chute to achieve locking, thus ensuring The arm is always fixed relative to the fuselage regardless of whether it is unfolded or folded, so as to prevent the arm from shaking relative to the fuselage after being unfolded or folded;

2. The unmanned aerial vehicle provided by the present invention is formed by connecting the body metal frame, the first folding arm metal frame and the machine arm metal frame by being provided with a metal frame at the body part, the machine arm and the first folding arm part. A complete UAV metal frame, thus ensuring the overall firmness and high strength of the UAV, and the fuselage can also ensure the integrity of the whole machine under high-intensity impact, which has the advantage of crashworthiness;

3. The UAV provided by the present invention attaches the electric adjustment board to the metal frame of the machine arm, and directly dissipates heat through the metal frame of the machine arm, which has the advantages of simple structure, good heat dissipation effect, and fast heat dissipation; at the same time, through Set the arm cooling holes on the arm shell to enhance the cooling effect;

4. For the drone provided by the present invention, the circuit board in the fuselage realizes heat dissipation through the cooperation of the heat sink and the fan, thereby improving the heat dissipation effect of the fuselage;

5. For the drone provided by the present invention, the left and right sides of the drone are indicated by the first indicator light and the second indicator light, and the tail of the drone is indicated by the third indicator light. The cooperation of the three indicator lights is enough Indicate the flight direction of the UAV, so that the operator can observe the flight attitude of the UAV at night or in harsh environments.

Description of drawings

The above and other features and advantages of the present invention can be more clearly understood through the following detailed description in conjunction with the accompanying drawings, wherein:

Fig. 1 is the schematic diagram of the three-dimensional structure of the unmanned aerial vehicle provided by the present invention in the unfolded state;

Fig. 2 is a top view of the unmanned aerial vehicle provided by the present invention in an unfolded state;

3 is a schematic diagram of the three-dimensional structure of the UAV in a folded state provided by the present invention;

Fig. 4 is the split schematic diagram of unmanned aerial vehicle provided by the present invention;

Fig. 5 is the overall structure schematic diagram of locking mechanism in the present invention;

Fig. 6 is a disassembled schematic view of the locking mechanism in the present invention;

Fig. 7 is the structural representation of the second runner in the present invention;

Fig. 8 is a schematic structural view of the first runner in the present invention;

Fig. 9 is a schematic structural view of the metal frame of the drone in the present invention;

Fig. 10 is the structural representation of fuselage metal frame among the present invention;

Fig. 11 is the split schematic diagram of machine arm in the present invention;

Fig. 12 is a disassembled schematic diagram of the first folding arm in the present invention;

Fig. 13 is a disassembled schematic view of the fuselage in the present invention;

Fig. 14 is a structural schematic diagram of a heat dissipation assembly in the present invention;

Fig. 15 is a disassembled schematic view of the propeller in the present invention;

Fig. 16 is a disassembled schematic view of the paddle assembly in the present invention;

Fig. 17 is an internal schematic view of the blade holder in the present invention;

Fig. 18 is a schematic structural view of the fixing seat in the present invention;

Figure 19 is a schematic diagram of the connection between the blade assembly and the fixing seat in the present invention;

Fig. 20 is a schematic diagram of the distribution of three indicator lights on the drone in the present invention.

Detailed ways

The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In these drawings, the size and relative sizes of layers and regions may be exaggerated for clarity.

Example 1

Referring to Fig. 1-4, the present invention provides a kind of unmanned aerial vehicle, comprises body 1, two arms 2 and two first folding arms 3; The length direction of the body 1 is arranged, and a propeller 5 is respectively arranged at the front and back of the top of the machine arm 2; the two machine arms 2 are respectively connected with the fuselage 1 through a first folding arm 3; The fuselage 1 is hinged; the first folding arm 3 rotates to drive the machine arm 2 close to the fuselage 1 to realize the folding of the machine arm 2 (as shown in Figure 3 ), or to drive the machine arm 2 away from the fuselage 1 to realize the expansion of the machine arm 2 (as shown in Figure 1-2).

The drone provided by the present invention only includes two arms 2 arranged on both sides of the fuselage, and the two arms 2 are respectively connected to the fuselage 1 through a first folding arm 3; when the arms 2 need to be folded , you only need to hold the arm 2 and apply force in the front and rear directions, and the first folding arm 3 rotates to drive the arm 2 closer to the fuselage 1 until it reaches the side of the fuselage 1, and the folding of the arm is completed; the above-mentioned arm folding method , Folding is fast and convenient, and the folded drone is small in size, easy to store and carry.

In this embodiment, a locking mechanism is provided at the connection between the first folding arm 3 and the machine arm 2 and the fuselage 1, that is, a locking mechanism is provided at the joints of the first folding arm metal frame 301 and the machine arm metal frame 201 and the fuselage metal frame 101. locking mechanism. After the machine arm 2 is unfolded or folded, the setting of the locking mechanism enables the locking of the connection between the first folding arm 3 and the machine arm 2 and the fuselage 1, thereby preventing the machine arm from shaking after the machine arm 2 is unfolded or folded.

Specifically, referring to FIGS. 5-8 , the locking mechanism includes a rotating shaft 702 , a first rotating wheel 705 and a second rotating wheel 704 . One end of the rotating shaft 702 is fixedly connected with the machine arm 2/body 1, and the other end is rotatably connected with the first folding arm 3; both sides of the rotating shaft 702 are partially cut along its axial direction, so that the cross section of the rotating shaft 702 is formed by two relative arcs shape and two relative straight lines; the central hole of the first runner 705 is in the same rectangular shape as the section of the rotating shaft 702, and the first runner 705 is sleeved on the rotating shaft 702 so that the first runner 705 is relatively opposite to the rotating shaft. Circumferentially limited (that is, non-rotatable in the circumferential direction), the first rotating wheel 705 is movable in the circumferential direction relative to the rotating shaft 702 ; a circumferentially extending slider 7051 is arranged on one side of the first rotating wheel 705 . The second runner 704 is fixed on the first folding arm 3, the central hole of the second runner 704 is a circular hole, the second runner is sleeved on the rotating shaft 702, and the second runner 704 can rotate around the rotating shaft 702 to rotate and move axially; the second runner 704 is provided with a circumferentially arranged chute on the opposite side of the first runner 705, and the slider 7051 is matched with the chute; the first runner 705 and the second runner 705 The wheels 704 are pressed together and can rotate mutually, and the locking is realized when the slide block 7051 snaps into the chute.

Wherein, in this embodiment, one end of the rotating shaft 702 is installed on the machine arm 2/body 1 through the upper bracket 701; the upper bracket 701 is installed on the machine arm 2/body 1, and one end of the rotating shaft 702 is fixed on the upper bracket 701 on. Of course, in other embodiments, the way of fixing one end of the rotating shaft 702 is not limited to the above, and can also be adjusted in more specific situations, which is not limited here.

Wherein, in this embodiment, the second runner 704 is installed on the first folding arm 3 through the lower bracket 703; the lower bracket 703 is fixed on the first folding arm 3, and the second runner 704 is coaxially fixed by screws or the like. On one side of the lower bracket 703, the other side of the lower bracket 703 is opposite to the upper bracket 701, the other end of the rotating shaft 702 passes through the lower bracket 703, the second rotating wheel 704 and the first rotating wheel 705 in sequence, and the other end of the rotating shaft 702 A nut 708 is arranged on the top, and the lower bracket 703, the second runner 704 and the first runner 705 are sequentially connected together.

Among them, in this embodiment, the locking mechanism also includes an elastic assembly, which is sleeved on the rotating shaft 702, and the first rotating wheel 705 is pressed against the second rotating wheel 704 through the elastic assembly; moreover, when unlocking is required , the first rotating wheel 705 rotates relative to the second rotating wheel 704, and the elastic component is pressed, so that a certain distance is generated between the first rotating wheel 705 and the second rotating wheel 704, so that the slider 7051 slides out of the chute 7041, 7043 , to realize unlocking; in this embodiment, the elastic component is a plurality of elastic washers 706 sleeved on the rotating shaft, and located between the nut 708 and the first rotating wheel 705 . Of course, in other embodiments, the elastic component can also be realized by structures such as springs, which is not limited here.

Wherein, in this embodiment, a first wear-resistant gasket 709 is provided between the second runner 704 and the lower bracket 703, and a second wear-resistant gasket 710 is arranged between the first runner 705 and the elastic component. The setting of a wear-resistant pad 709 and the second wear-resistant pad 710 plays the role of including the second runner 704 and the first runner 705 on the one hand, and the first wear-resistant pad 709 and the second wear-resistant pad on the other hand The washer 710 is provided with a plurality of hole structures for adding lubricating oil, so that the rotation between the first runner 705 and the second runner 704 is smoother. A third wear-resistant gasket 707 is arranged between the nut 708 and the elastic component to protect the elastic component. Of course, in other embodiments, the first wear-resistant pad 709 , the second wear-resistant pad 710 , and the third wear-resistant pad 707 may not be provided, and there is no limitation here.

Wherein, in the present embodiment, the slider 7051 is an arc-shaped slider, and the chute is an arc-shaped chute matched with the slider 7051, so that it is arranged so that the first rotating wheel 705 and the second rotating wheel 705 During the mutual rotation of the wheels 704, the slider smoothly slides into the chute; of course, in other embodiments, the structure of the chute and the slider can also be adjusted according to specific conditions, which is not limited here.

Wherein, in this embodiment, one end of the chute is designed as a chute slope 7042, and one end of the slider 7051 is designed as a slider slope 7052, and the chute slope 7042 and the slider slope 7052 are set so that the slider can slide out smoothly chute.

Wherein, in this embodiment, as shown in Fig. 7 and Fig. 8, a slider 7051 is arranged in the circumferential direction of the first runner 705, and two slide grooves are arranged in the circumferential direction of the second runner 704. Slot 7041, second chute 7043, the central angle between the first chute 7041 and the second chute 7043 is the rotation angle of the first folding arm; when the slider 7051 is transferred into the first chute 7041 The locking after the machine arm is unfolded can be realized, and the locking after the machine arm is folded can be realized after the slide block 7051 is turned into the second chute 7043 .

In this embodiment, the locking mechanism provided above has a simple structure and is easy to operate; of course, in other embodiments, locking mechanisms of other structural forms may also be used, which is not limited here.

In this embodiment, as shown in FIG. 1 , a second folding arm 4 is provided between the arm 2 and the fuselage 1 , and the two ends of the second folding arm 4 are hinged to the arm 2 and the fuselage 1 respectively. Since the machine arm 2 in this embodiment is relatively long, if only one folding arm is used to unfold or fold the machine arm, the operation is extremely unstable, and it is easy to cause damage to the machine arm, and the connection strength of the machine arm 2 is not enough; In this embodiment, by adding the second folding arm 4, on the one hand, the connection strength between the arm 2 and the fuselage 1 is strengthened, and on the other hand, the unfolding and folding operations of the arm 2 are more stable. Of course, in other embodiments, the second folding arm 4 may not be provided, and there is no limitation here.

Further, as shown in FIG. 2 , the two ends of the second folding arm 4 are hinged to the fuselage 1 and the machine arm 2 through the rotating shaft 11 respectively; of course, in other embodiments, the second folding arm 4 is connected to the machine arm The articulation mode between the body 1 and the arm 2 is not limited to the above, and can also be adjusted according to specific conditions, which is not limited here.

Further, the length of the second folding machine arm 4 is equal to the length of the first folding machine arm 3, and the second folding machine arm 4 is always parallel to the first folding machine arm 3, thereby ensuring that the first folding machine arm 3 and the second folding machine arm Synchronization of rotation between folding arms 4.

The folding and unfolding state of the drone arm provided by the present invention will be further described below:

As shown in Figure 1-2, the machine arm 2 is in the unfolded state at this time; when the machine arm 2 is in the unfolded state, the slider 7051 in the locking mechanism at the hinge joint between the first folding arm 3 and the fuselage 1 and machine arm 2 is located at the first In the chute 7041, the mutual fixation between the first runner 705 and the second runner 704 is realized without applying external force; are fixed to each other, and the second runner 704 and the first folding arm 3 are fixed to each other, so that the first folding arm 3 is fixed to the fuselage 1 and the machine arm 2, so that when the machine arm 2 is unfolded, the machine arm 2 Locking relative to body 1.

When it is necessary to fold the machine arm 2, hold the machine arm 2 and apply force to the front of the fuselage 1, so that the first folding arm 3 rotates around the hinge with the fuselage 1/machine arm 2. Make the slider 7051 slide out of the first chute 7041, and the locking mechanism is unlocked; the first folding arm 3 rotates counterclockwise, the first folding arm 3 drives the engine arm 2 to snap into the side of the fuselage 1, and at the same time the second folding arm 3 It also rotates clockwise under the action of arm 2.

As shown in Figure 3, when the machine arm 2 leans against the side of the fuselage 1, the slider 7051 on the locking mechanism at the joint between the first folding arm and the fuselage 1 and the machine arm 2 also turns to the second At the position of the chute 7043, the slider 7051 is stuck into the second chute 7043, realizing the mutual fixing of the first folding arm 3, the fuselage 1, and the machine arm 2, thereby realizing that the machine arm 2 is in the folded state, and the machine arm 2 Locking relative to body 1.

Example 2

This embodiment is an improvement made on the basis of Embodiment 1, as follows.

In this embodiment, with reference to FIGS. 9-10 , the drone also includes a metal frame, and the metal frame includes a fuselage metal frame 101 arranged on the fuselage 1 and an arm metal frame 201 arranged on the machine arm 2. , the first folding arm metal frame 301 arranged on the first folding arm 3 and the second folding arm metal frame 401 arranged on the second folding arm 4, and one end of the first folding arm metal frame 301 is connected with the machine arm metal frame 201 is hinged, the other end is hinged with the fuselage metal frame 101, one end of the second folding arm metal frame 401 is hinged with the machine arm metal frame 201, and the other end is hinged with the fuselage metal frame 101, thereby forming a complete metal frame structure.

In this embodiment, a metal frame is arranged on the fuselage, the arm, the first folding arm, and the second folding arm, and the metal frame of the fuselage and the metal frame of the arm are connected to form a complete drone. The metal frame, the setting of the metal frame of the UAV increases the strength on the fuselage 1, the machine arm 2, the first folding arm 3, and the second folding arm 4, thereby enhancing the strength of the whole machine of the UAV; The machine arm metal frame 201 on the machine arm of the man-machine is connected with the fuselage metal frame 101 on the fuselage 1 through the first folding arm metal frame 301 and the second folding arm metal frame 401, so that When being hit, under the action of connecting the metal frame 201 of the machine arm and the metal frame 101 of the fuselage, the UAV will not be separated from the fuselage and the arm, thereby ensuring the integrity of the UAV and having a crashworthy The advantages.

In this embodiment, the arm metal frame 201, the fuselage metal frame 101, the first folding arm metal frame 301, and the second folding arm metal frame 401 are all made of high-strength, light-weight metals, so as to guarantee the strength. At the same time, avoid the UAV from being too heavy, which will affect the normal flight. Preferably, the arm metal frame 201, the fuselage metal frame 101, the first folding arm metal frame 301, and the second folding arm metal frame 401 are made of magnesium alloy, which has low density, high strength, and large elastic modulus. Good heat dissipation, good shock absorption, strong ability to withstand impact loads, and good corrosion resistance.

In this embodiment, the machine arm 1 includes an organic arm shell, and the machine arm metal frame 201 is used as a part of the machine arm shell; The outer shell portion 203 and the arm metal frame 201 are jointly formed, and the arm metal frame 201 is used as a part of the top of the arm shell, and the arm metal frame 201 is arranged along the length direction of the machine arm; wherein, the inner shell portion 202 , the outer shell portion 203 and the arm metal frame 201 can be set according to the shape of the arm, and are not limited here. In other embodiments, the metal frame 201 of the machine arm may also be directly disposed in the shell of the machine arm, which is not limited here.

In this embodiment, a propeller 5 is provided on the machine arm, and the propeller 5 is connected to the metal frame 201 of the machine arm; specifically, referring to Fig. 9 and Fig. 11 , propeller mounting parts are respectively provided on the front and rear sides of the upper end of the metal frame 201 of the machine arm In 2012, the propeller installation part 2012 is provided with a propeller installation hole, and the lower end of the propeller 5 is installed on the propeller installation hole through a connecting piece (such as a screw, etc.), so as to realize the fixed installation of the propeller 5 . Compared with the scheme of installing the propeller 5 on the plastic shell of the machine arm in the prior art, the propeller 5 on the machine arm is installed on the metal frame 201 of the machine arm in this embodiment, even if the machine arm shell Breakage occurs and falls off, and the propeller knot is firmly connected on the metal frame 201 of the machine arm, thereby preventing the propeller 5 from falling off when the machine arm encounters a collision.

In this embodiment, electrical parts are also arranged in the machine arm, and the electrical parts are installed on the metal frame 201 of the machine arm; wherein the electrical parts in the machine arm include electric boards for controlling propellers, etc., which are not limited here . Compared with the technical solution in the prior art that the electrical parts in the machine arm are installed on the plastic shell of the machine arm, the electrical parts in the machine arm in this embodiment are also connected to the metal frame 201 of the machine arm, even if the shell of the machine arm is hit by the impact opening For the problem of breakage and falling off, the electrical parts are still connected to the metal frame 201 of the machine arm, so as to prevent the electrical parts in the machine arm from falling off when the machine arm encounters an impact.

In this embodiment, referring to FIG. 12, the first folding arm 3 includes a first folding arm metal frame 301 and a plastic upper cover 302 covering the upper side of the first folding arm metal frame 301; of course, in other embodiments , the setting of the plastic upper cover 302 may also be omitted, which is not limited here.

In conjunction with Fig. 9, Fig. 10 and Fig. 12, the first folding arm fuselage mounting part 1012 is provided on both sides of the upper front end of the fuselage metal frame 101, and the first folding arm fuselage mounting part 1012 is provided with a mounting hole. One end of the arm metal frame 301 is connected with the front folding arm mounting hole 102 through a hinge, thereby realizing the hinge between the first folding arm fuselage mounting part 1012 and the fuselage metal frame 101; the machine arm metal frame 201 is provided with a second A folding arm machine arm mounting part, the other end of the first folding arm metal frame 301 is installed on the first folding arm machine arm mounting part by a hinge, thereby realizing the connection between the front folding arm metal frame 2 and the machine arm metal frame 201 hinged.

In this embodiment, the second folding arm 4 is not provided with a casing, and the metal frame 401 of the second folding arm is directly used as the second folding arm. Of course, in other embodiments, the second folding arm 4 may also be provided with a casing, which is not limited here.

Further, referring to Fig. 9 and Fig. 10, connecting columns 1011 extending downwards are arranged at the bottom of both sides of the upper rear end of the metal frame 101 of the fuselage, the bottom of the connecting columns 1011 is equipped with a fixing base 12, and one end of the metal frame 401 of the second folding arm Installed on the fixed base 12 through a hinge; the arm metal frame 201 is also provided with a second folding arm arm installation part, and the setting position of the second folding arm arm installation part is lower than the first folding arm arm installation part , the other end of the metal frame 401 of the second rear folding arm is installed on the arm mounting part of the second folding arm through a hinge. In this embodiment, through the setting of the connecting column 102 extending downwards, and limiting the setting position of the arm installation part of the second folding arm to be lower than the installation part of the first folding arm, the metal frame of the first folding arm 301 is higher than the metal frame 401 of the second folding arm, so as to avoid interference between the first folding arm and the second folding arm in the same plane during the folding process, and ensure the smooth completion of folding and unfolding of the first folding arm and the second folding arm.

In this embodiment, with reference to FIG. 13 , the fuselage 1 includes a fuselage shell, the fuselage shell is composed of an upper cover 102 and a lower shell 103, and the metal frame 101 of the fuselage is located in the fuselage shell and installed on the lower shell Body 103; fuselage metal frame 101 together with upper cover 102 and lower shell 103 constitute the main part of the fuselage to ensure the strength of the fuselage. Of course, in other embodiments, the fuselage metal frame 101 can also be directly used as a part of the fuselage, for example, the fuselage metal frame 1 can be directly used as the lower shell of the fuselage shell, which is not limited here.

Wherein, the specific structural form of the metal frame 101 of the fuselage can be set according to the shape of the fuselage, which is not limited here.

Further, the fuselage is provided with electrical components, and the electrical components are installed on the metal frame 1 of the fuselage. In this embodiment, the electrical components of the fuselage are installed on the metal frame 101 of the fuselage to prevent the fuselage from Damage or drop of electrical parts inside the fuselage.

Further, the electrical components on the fuselage include heat dissipation components, battery components 104, circuit board components 105, etc., which are not limited here.

Further, in conjunction with Fig. 1 and Fig. 10, the outer side of the front end of the fuselage is also provided with a pan-tilt 6, and the pan-tilt 6 is connected with the metal frame 1 of the fuselage; 6 is installed on the pan/tilt mounting hole 1014 through a connecting piece, so as to realize the connection between the pan/tilt 6 and the metal frame 101 of the fuselage. Compared with the technical scheme in which the pan/tilt 6 is directly installed on the fuselage shell in the prior art, the present embodiment connects the pan/tilt 6 to the metal frame 101 of the fuselage. When the drone is hit, the metal frame 101 of the fuselage is The self-strength is strong and not easy to be damaged, and because the gimbal 6 is installed on the metal frame 1 of the fuselage, the gimbal 6 is not easy to fall off from the drone.

Example 3

This embodiment is improved on the basis of embodiment 1 or embodiment 2, as follows.

In this embodiment, referring to FIG. 11 , an electric control board 209 for controlling the propeller is arranged in the arm 2 .

Specifically, referring to FIG. 11 , the electric adjustment board 209 is attached to the arm metal frame 201 , and the heat generated by the electric adjustment board 209 is transferred to the metal frame 3 for heat dissipation. In this embodiment, the electric adjustment board 209 is attached to the metal frame of the machine arm, and the heat is emitted directly through the metal frame, which has the advantages of simple structure, good heat dissipation effect, and fast heat dissipation. At the same time, the setting of the metal frame also has the effect of strengthening the strength of the machine arm. advantage.

Further, there are cooling ribs 2011 extending downwards on the inner surface of the metal frame 201 of the machine arm. The cooling ribs 2011 are plate-shaped structures extending perpendicular to the metal frame 201 of the machine arm. The electric board bracket is vertically installed in the arm shell, and the electric board 209 is closely attached to the cooling ribs 2011; further, there are multiple heat source points on the electric board 209 (every electrical component on the electric board Corresponding to form a heat source point), multiple heat source points are all bonded to the cooling ribs 2011; the heat on the ESC board 209 is first transferred to the cooling ribs 2011, and then transferred to the metal frame 201 of the machine arm through the cooling ribs 2011, the metal frame of the machine arm The frame 201 is used as a part of the arm shell to directly dissipate the heat, and the heat dissipation effect is good and the heat dissipation speed is fast.

Wherein, in this embodiment, due to the limitation of the structural form of the machine arm and in order to make full use of the space in the machine arm, the electric control board 209 is vertically arranged, and the heat transfer between the electric control board 209 and the electric control board 209 is realized by vertically extending the cooling ribs. . Of course, in other embodiments, according to the specific structural form of the machine arm, the metal frame 201 of the machine arm may not be provided with heat dissipation ribs 2011, and the electric adjustment board 209 is directly attached to the inner surface of the metal frame 201 of the machine arm. Do limit.

Further, there are cooling holes on the arm shell corresponding to the position of the electric control board 209, so that the heat in the inner space of the arm shell is directly discharged through the cooling holes on the arm, thereby enhancing the heat dissipation effect. Preferably, the top and the bottom of the arm housing are respectively provided with a first heat dissipation hole and a second heat dissipation hole, and the first heat dissipation hole and the second heat dissipation hole are both located at the position of the electric adjustment board 209; Both the top and the bottom are equipped with cooling holes to form convection channels to enhance the cooling effect. Of course, in other embodiments, the location and number of cooling holes on the machine arm can be adjusted according to specific conditions, and there is no limitation here.

In this embodiment, referring to FIGS. 13-14 , the electrical components in the fuselage 1 include a circuit board module 105 , and the circuit board module 105 is installed on a heat dissipation assembly for dissipating heat for the circuit board module 105 . Further, the heat dissipation assembly includes a heat sink 106 and a heat dissipation fan 10; the circuit board module 105 is installed on the lower end surface of the heat sink 106, and is attached to the lower end surface of the heat sink 1; Between the walls 1061 and the adjacent air guiding walls 1061 , a heat dissipation air channel extending from the center of the heat sink to the edge is formed; the cooling fan 107 is installed above several air guiding walls 1061 through the link 108 and is located in the middle. The heat generated by the circuit board module 105 is transferred to the heat sink 106 , and under the blowing of the heat dissipation fan 107 , the heat on the heat sink 106 is diffused to the surrounding through each air duct, thereby achieving the effect of heat dissipation.

Example 4

This embodiment is improved on the basis of embodiment 1 or embodiment 2 or embodiment 3, as follows.

In this embodiment, the propeller 5 is installed on the top of the machine arm 2 and fixed on the metal frame 201 of the machine arm.

15-19, the propeller 5 includes a blade assembly, a fixed seat 503 and a power device 506 (such as a motor assembly, etc.), the blade assembly is detachably connected to the fixed seat 503, and the fixed seat 503 is installed on the power device 506. Device 506 is mounted on the arm.

Wherein, the blade assembly includes a blade base 501 and a blade 508 arranged on the blade base 501, and the blade 508 can rotate around the joint with the blade base 501, thereby realizing the folding of the blade; the blade base 501 It is detachably installed on the fixing base 503 . In the propeller provided by the present invention, the blade assembly is detachable, so that the disassembly and maintenance of the blade is convenient, and the disassembly and assembly are convenient; in addition, the blade in the present invention can be rotated and folded relative to the blade seat, so that it is convenient for no one to Store and carry the computer when it is not in use.

Wherein, the outer wall of the upper end of the paddle seat 501 is provided with an installation port 5012 for installing the paddle, the installation port 5012 is in an inverted "U" shape, and the top and bottom of the installation port 5012 is provided with a paddle seat connecting hole 5013; A blade connection hole 5081 is also provided on the installation end, and the connection end of the blade 508 extends into the installation port 5012, and the blade connection hole 5081 is opposite to the blade seat connection hole 5013, and then the connection piece 507 is passed through the blade The connecting hole 5081 is connected to the connecting hole 5013 of the blade seat, so as to realize the connection between the blade 508 and the blade seat 501; moreover, the connecting hole 5081 of the blade and the connecting piece 507 can be rotated relatively, so as to realize the connection between the blade and the paddle. Rotatable connection between leaf seats.

Wherein, the connecting member 507 may use stepped screws, and of course other connecting members may also be used in other embodiments, which is not limited here.

Further, a limiting structure is provided between the paddle connecting hole 5081 and the outer wall of the connecting piece 507 to limit the rotation of the paddle relative to the connecting piece 507 when the blade is unfolded or folded; specifically, the limiting structure consists of The straight knurling provided on the outer wall of the connecting piece 507 and the inner wall of the paddle connecting hole 5081 is realized. The paddle 508 cannot rotate relative to the connecting piece 507 without external force, so that the paddle 508 is in the unfolded state. Or in the folded state, it cannot rotate relative to the connecting member 507 when no external force is applied.

Of course, in other embodiments, other ways can also be used to realize that the blade cannot rotate without applying external force. For example, a friction friction structure can also be added between the connection end of the blade 508 and the inner wall of the installation port 5012. Here No restrictions.

The unfolding and folding of the blades in this embodiment will be further described below:

As shown in Figure 15, the two paddles 508 are located on the same straight line at this time and are in the unfolded state; under the action of the straight grain knurling on the outer wall of the connector 507 and the inner wall of the paddle connecting hole 5081, the paddle 508 is relatively The connecting piece 507 cannot rotate, and the paddle 508 is in a fixed state.

When the paddle 508 needs to be folded, a tangential force is applied to the paddle 508 to overcome the resistance between the connecting piece 507 and the paddle connecting hole 5081, so that the paddle 508 rotates around the connecting piece 507, and one of the paddles is smooth Turn clockwise, and the other blade rotates counterclockwise, until the two blades are turned to be flat with each other, as shown in Figure 17, the folding of the blade is completed.

The paddle 508 and the paddle seat 501 are directly connected in rotation through the connecting piece, and the positioning after unfolding or folding is realized directly through the setting of the ruled knurling, which has a simple structure and is easy to operate.

Of course, in other embodiments, the connection manner between the blade 508 and the blade seat 501 is not limited to the above, and can also be adjusted according to specific conditions, which is not limited here.

In this embodiment, the blade seat 501 and the fixed seat 503 are detachably connected through the quick release assembly 2 . The lower end of the paddle seat 501 is provided with a counterbore 5014, and the upper end of the fixed seat 503 extends into the counterbore 5014. The quick release assembly includes a first connection assembly for realizing the axial positioning between the fixed seat 503 and the counterbore 5014 and the realization of the fixed seat 503. Circumferentially positioned second connection assembly with counterbore 5014.

The first connection assembly includes a first clip 5031 and a first bayonet 5015; a step is provided on the upper end surface of the fixing seat 503, and the first clip 5031 is arranged on the side wall of the step and extends radially, as shown in Figure 15 As shown in FIG. 14 , the inner wall of the counterbore 5014 is provided with a first bayonet 5015 matching the first clip 5031 , and the first bayonet 5015 is provided along the circumferential direction of the sidewall of the counterbore 5014 .

The second connection assembly includes a button 504, a second clip 509, and a second bayonet 5016; the lower end of the button 504 is installed in the fixed seat 503, and an elastic member 505 (such as a spring) is arranged between the lower end of the button 504 and the fixed seat 503. etc.), the button 504 is located at the center of the step; the second clip 509 is arranged on the outer wall of the button 504, and the upper end of the second clip 509 stretches out from the upper end face of the step; when the button 504 is pressed, the button 504 overcomes the The elastic force of the elastic member 505 moves downward axially, thereby driving the second clamping member 509 to move down and retract into the step; the bottom surface of the counterbore 5014 is provided with a second bayonet socket 5016 at a position corresponding to the first bayonet socket 5015, and the second bayonet socket 5016 is arranged on the bottom surface of the counterbore 5014. The opening 5016 matches with the second clip 509 .

Wherein, in this embodiment, four first clips are evenly distributed in the axial direction on the upper end of the fixed seat 503, and four first bayonets are arranged on the corresponding blade seat 501; The number of one card can also be 2, 3..., at least two, and there is no limitation here. Wherein, in this embodiment, the button 204 is evenly distributed with two second clips in the circumferential direction, and the corresponding paddle seat 501 is provided with two second bayonet slots; of course, in other embodiments, the second clip on the fixing seat 503 The number of pieces can also be 3, 4, 5..., at least two, which is not limited here.

The disassembly and assembly between the blade seat 501 and the fixing seat 503 will be described in detail below:

When connecting, the paddle seat 501 is fastened to the fixed seat 503, and the upper end of the button 504 passes through the counterbore 5014 and the through hole 304 in sequence, and extends out of the upper end surface of the paddle seat 501; the upper end of the fixed seat 503 extends into the counterbore 5014 Inside, the bottom of the counterbore 5014 is pressed against the second clip 509 first, the paddle seat 302 moves down and presses the second clip 509, and the second clip 509 moves down to drive the button 504 to overcome the elasticity of the elastic part 505. Move down; until the first clip 5031 touches the bottom of the counterbore 5014, then turn the paddle seat 501 so that the first clip 205 snaps into the first buckle 3011, so as to realize the shaft between the paddle seat and the fixed seat At the same time, under the action of the resilient force of the elastic member 505, the second clip 509 snaps into the second buckle 3012, thereby realizing the circumferential positioning between the blade seat and the fixed seat, thereby realizing the alignment between the blade seat and the fixed seat. A fixed connection between the fixed seats;

When detaching, press down the button 204, thereby driving the second clip 509 to move down, and the second clip 509 moves down to break away from the second buckle 3012, and the circumferential positioning is released; then rotate the paddle seat 501, so that the first clip The member 5031 is screwed out of the first bayonet 5015, and the axial positioning is released, so that the lock between the blade seat 501 and the fixing seat 503 is released, and the blade assembly can be taken out directly.

Referring to the above description, it can be seen that the quick release assembly provided by this embodiment has a simple and compact structure and is easy to operate. Of course, in other embodiments, the quick release method between the blade assembly and the fixing seat is not limited to the above, and can also be adjusted according to specific conditions, which is not limited here.

Example 5

This embodiment is improved on the basis of embodiment 1 or embodiment 2 or embodiment 3 or embodiment 4, as follows.

In this embodiment, with reference to FIG. 4 and FIG. 11 , the bottoms of the two arms 2 are respectively provided with landing gears 212 at the front and back, which are used to support the UAV when the UAV lands. Foot pads 205 are also provided at the bottom of the landing gear 212 for protecting the landing gear.

Further, the foot pad 205 is a rubber body structure, and the foot pad 205 is installed on the bottom of the landing gear 212 through a buckle assembly and glue. Specifically, the foot pad 205 is a cover-like structure, and its cover is arranged on the bottom end of the landing gear 212; A plurality of clamping holes on the side wall of the lower end of the landing gear 212; the foot pad 205 is set on the bottom of the landing gear 212, and the clamps are respectively clamped into each clamping hole to realize the connection; the colloid is a double-sided adhesive 204, which is arranged on the bottom of the inner side of the foot pad 205 Between the bottom of the undercarriage 212, paste connection is realized. In this embodiment, the connection between the foot pad 205 and the undercarriage 212 is realized through the buckle assembly and the colloid, the connection effect is better, and the foot pad 205 can be effectively prevented from falling off.

In this embodiment, referring to Fig. 1 and Fig. 11, an anti-pinch device 207 is provided at the bottom of the machine arm 2, and is located between the two landing gears 212; 207, so that the grip position is moved down relative to the machine arm 2, thereby preventing the operator’s hand from being caught between the fuselage and the machine arm, thereby facilitating the user to use; at the same time, the setting of the anti-pinch device can strengthen the machine arm 2 The strength to prevent damage to the arm during the folding process.

Wherein, the anti-pinch device 207 is detachably connected with the machine arm 2 by a connector (such as a screw 208), and the anti-pinch device 207 can be disassembled from the machine arm when flying, so as to avoid the damage of the anti-pinch device to the unmanned aerial vehicle. impact on flight.

Wherein, the two ends of the anti-pinch device 207 respectively extend to the positions of the two lifting feet 3, and the shape of the upper edge of the anti-pinch device 207 is consistent with the shape of the gap formed between the bottom of the machine arm 2 and the two lifting feet 3; The present invention ensures the integrity and consistency of the appearance of the machine arm and the aesthetic effect of the drone through the limitation of the above structure.

Example 6

This embodiment is improved on the basis of embodiment 1 or embodiment 2 or embodiment 3 or embodiment 4 or embodiment 5, as follows.

In this embodiment, referring to FIG. 11 , an omnidirectional antenna 210 , 211 for signal transmission with the remote control of the drone is also provided at the front and rear ends of the two arms 2 . Specifically, one of the arms is equipped with a 5.8G omnidirectional antenna at the front end and a 2.4G omnidirectional antenna at the rear end; the other arm is equipped with a 2.4G omnidirectional antenna at the front end and a 5.8G omnidirectional antenna at the rear end . In this embodiment, the antenna is set in the above way, so that when the drone is flying, no matter which direction is facing the remote control, there is a 5.8G omni-directional antenna and a 2.4G omni-directional antenna facing the remote control, so that the remote control is better. Take control of the drone.

Example 7

This embodiment is improved on the basis of embodiment 1 or embodiment 2 or embodiment 3 or embodiment 4 or embodiment 5 or embodiment 6, as follows.

In this embodiment, referring to Fig. 20, three indicator lights are arranged on the UAV, including the first indicator light 8 and the second indicator light 9 arranged on the two arms, and the third indicator light arranged on the tail of the fuselage 10. The connecting line of the first indicator light 8 , the second indicator light 9 and the third indicator light 10 is triangular. The present invention indicates the left and right sides of the drone through the first indicator light 8 and the second indicator light 9, and indicates the tail or front end of the drone through the third indicator light 10, and the cooperation of the three indicator lights can indicate no one. The flight direction of the drone is convenient for operators to observe the flight attitude of the drone at night or in harsh environments.

When in use, the first indicator light 8 and the second indicator light 9 are on the front side of the third indicator light 10, and the direction of the first indicator light 8 and the second indicator light 9 relative to the third indicator light 10 is the direction of the drone. flight direction. Wherein, preferably, the first indicator lights 8 and the second indicator lights 9 are symmetrically arranged left and right. Wherein, preferably, the first indicator light 8 and the second indicator light 9 are arranged at the bottom of the machine arm 2, and the third indicator light is arranged at the bottom of the tail of the fuselage 1. This setting method is conducive to the operator to see more clearly Indicator light, to prevent parts on the fuselage from covering the indicator light.

In other embodiments, the third indicator light 10 can also be arranged at the front end of the fuselage 2. At this time, the third indicator light 10 is located in front of the first indicator light 8 and the second indicator light 9, and the third indicator light 10 is opposite to each other. The direction of the first indicator light 8 and the second indicator light 9 is the flying direction of the drone.

Further, the first indication lamp 8 and the second indication lamp 9 adopt constant-on single-color lamps, and the third indication lamp 10 adopts three-color lamps; wherein, the light colors of the first indication lamp 8 and the second indication lamp 9 can be the same or It can be different, and can be adjusted according to the specific situation, and there is no limit here; among them, the three-color light is the light commonly used on the existing drones to indicate the status of the drone aircraft, which uses different combinations of the three-color lights The lights show the real-time status of the aircraft.

In other embodiments, the first indicator light 8 and the second indicator light 9 can also be blinking monochrome lights, and the third indicator light can also be multi-color lights for prompting the state of the aircraft in other structural forms. Do limit.

In this embodiment, the first indicator light 8 and the second indicator light 9 have the same structure. Specifically, with reference to Fig. 11 and Fig. 20, the structure of the first indicator light 8 is taken as an example for further description. The first indicator light 8 includes a light-emitting part and a lampshade 206. The light-emitting part is installed on the bottom 2 of the machine arm, and the lampshade The 206 cover is arranged on the luminous part, and is detachably connected with the machine arm, and the lamp cover 206 plays the role of guiding light.

In this embodiment, referring to FIG. 13 and FIG. 20 , the third indicator lamp 10 is directly arranged in the tail of the fuselage 1, and the third indicator lamp also includes a luminous body 109 and a lampshade 110; the luminous body 109 is installed on the fuselage, The lampshade 110 covers the reflector 109 and is detachably connected with the fuselage.

Of course, in other embodiments, the specific structural form of the three indicator lamps can also be adjusted according to specific needs, which is not limited here.

Those skilled in the art will appreciate that the present invention may be embodied in many other specific forms without departing from its own spirit or scope. Although the embodiments of the present invention have been described, it should be understood that the present invention should not be limited to these embodiments, and that changes and modifications can be made by those skilled in the art within the spirit and scope of the invention as defined by the appended claims.

Claims (22)

1. A kind of unmanned aerial vehicle, is characterized in that, comprises: body; The machine arm is arranged on one side of the fuselage, and is arranged along the length direction of the fuselage; the front and rear of the top of the machine arm are respectively provided with a propeller. A first folding arm, the arm is connected to the fuselage through a first folding arm; one end of the first folding arm is hinged to the arm, and the other end is hinged to the fuselage; the first folding arm is hinged to the fuselage; A folding arm rotates to drive the arm close to the fuselage to fold the arm, or drives the arm away from the fuselage to unfold the arm. 2. The unmanned aerial vehicle according to claim 1, wherein the fuselage includes an organic metal frame, the arm includes an organic metal frame, and the first folding arm includes a first folding arm Metal frame; one end of the metal frame of the first folding arm is hinged to the metal frame of the fuselage, and the other end is hinged to the metal frame of the machine arm to form a metal frame of the drone. 3. The unmanned aerial vehicle according to claim 2, wherein the propeller is connected to the metal frame of the machine arm; the electrical parts in the arm are installed on the metal frame of the machine arm; The electric parts in the body are installed on the metal frame of the fuselage; a cloud platform is arranged outside the body, and the cloud platform is connected with the metal frame of the body. 4. The unmanned aerial vehicle according to claim 2, wherein said machine arm comprises an organic arm shell, and said machine arm metal frame is used as a part of said machine arm shell; said machine arm shell is provided with a The electric control board that controls the propeller is attached to the metal frame of the machine arm, and the heat generated by the electric control board is transferred to the metal frame of the machine arm for heat dissipation. 5 . The drone according to claim 4 , wherein a heat dissipation hole for the arm is provided at a position corresponding to the electric control board on the arm shell. 6 . 6. The unmanned aerial vehicle according to claim 1, characterized in that, the two sides of the fuselage are respectively provided with a described machine arm, and the front and rear ends on the two described machine arms are all provided with a Omnidirectional antenna for signal transmission. 7. The unmanned aerial vehicle according to claim 6, wherein the front end of one of the arms is provided with a 5.8G omnidirectional antenna, and the rear end is provided with a 2.4G omnidirectional antenna; The front end is equipped with a 2.4G omnidirectional antenna, and the rear end is equipped with a 5.8G omnidirectional antenna. 8. The unmanned aerial vehicle according to claim 1, wherein a landing gear is respectively provided at the front and rear of the bottom of the arm, and a foot pad is provided at the bottom of the landing gear; the foot pad is installed through a buckle assembly and colloid on the bottom of the landing gear. 9. The drone according to claim 10, wherein the bottom of the arm is detachably provided with an anti-pinch device; the anti-pinch device is arranged between the front and rear landing gears. 10. The unmanned aerial vehicle according to claim 1 or 2, wherein the propeller comprises: The paddle assembly includes a paddle seat and a paddle arranged on the paddle seat, and the paddle can be rotated and folded around the joint with the paddle seat; a fixed seat, the paddle seat is detachably mounted on the fixed seat; The power device is installed on the arm, and the fixed device is installed on the power device; the power device drives the fixed seat to rotate, thereby driving the blade assembly to rotate. 11. The unmanned aerial vehicle according to claim 10, characterized in that, the detachable connection between the blade seat and the fixed seat is realized through a quick release assembly; the lower end of the blade seat is provided with a counterbore, so The upper end of the fixing seat extends into the counterbore, and the quick release assembly includes a first connecting component for realizing the axial positioning between the fixing seat and the counterbore and realizing the connection between the fixing seat and the counterbore. A second connection assembly positioned circumferentially therebetween. 12. The unmanned aerial vehicle according to claim 11, wherein the first connecting component comprises: The first clip is arranged on the side of the upper end of the fixing seat and extends radially; The first bayonet is arranged on the inner wall of the counterbore, and the first bayonet is arranged along the circumference of the inner wall of the counterbore; the first bayonet is matched with the first clip; The fixing seat protrudes into the counterbore, the paddle seat rotates relative to the fixing seat, and the first clamping member snaps into the first bayonet. 13. The unmanned aerial vehicle according to claim 12, wherein the second connection assembly comprises: The lower end of the button is installed in the fixed seat, and the lower end of the button is provided with an elastic member, and the button can move axially relative to the fixed seat; a through hole is arranged in the center of the paddle seat, and the fixed seat The upper end extends into the counterbore, and the upper end of the button passes through the counterbore and the through hole in sequence; The second clip is arranged on the side wall of the lower end of the key, and one end of the second clip is located in the fixing seat, and the other end extends out of the fixing seat; The second bayonet socket is arranged on the bottom of the counterbore at a position corresponding to the first bayonet socket; After the first clip is snapped into the first bayonet, the second clip is snapped into the second bayonet under the action of the elastic member. 14. The unmanned aerial vehicle according to claim 1 or 2, wherein a locking mechanism is provided at the hinge of the first folding arm, the arm and the fuselage; the arm is unfolded or folded Finally, the locking mechanism locks the joints of the first folding arm, the arm, and the fuselage. 15. The drone according to claim 14, wherein the locking mechanism comprises: A rotating shaft, one end is fixedly connected to the arm/the fuselage, and the other end is rotatably connected to the first folding arm; The first rotating wheel is sleeved on the rotating shaft, and the first rotating wheel is non-rotatable relative to the rotating shaft; one side of the first rotating wheel of the rotating shaft is provided with a circumferentially arranged slider; The second rotating wheel is fixed on the first folding arm, and the second rotating wheel is rotatably sleeved on the rotating shaft; the second rotating wheel is on the side opposite to the first rotating wheel A circumferentially arranged chute is provided, and the slider is matched with the chute; The first runner and the second runner are pressed together and can rotate with each other, and the rotating shaft drives the first runner to rotate relative to the second runner, and the slider snaps into the Locking is realized in the chute. 16. The unmanned aerial vehicle according to claim 15, wherein a slide block is arranged circumferentially on the first runner, and two chutes are arranged circumferentially on the second runner; The slider is transferred into one of the chute to realize the locking after the arm is deployed, and the slider is transferred into the other chute to realize the locking after the arm is folded. 17. The unmanned aerial vehicle according to claim 15, wherein the locking mechanism further includes an elastic component, the elastic component is sleeved on the rotating shaft, and the first wheel, the second wheel The runners are pressed together; the elastic assembly includes a plurality of elastic gaskets sleeved on the shaft, and the elastic gaskets are pressed against one side of the first runner, so that the second runner The other side is pressed against the second runner. 18. The drone according to claim 15, wherein the locking mechanism further comprises: An upper bracket, one end of the rotating shaft is mounted on the upper bracket, and the upper bracket is fixedly mounted on the arm/the fuselage; a lower bracket, the lower bracket is fixed on the first folding arm, the second runner is fixed on the lower bracket; one end of the rotating shaft is installed on the arm/the fuselage, and the other One end passes through the lower bracket, the second runner and the first runner in turn. 19. The unmanned aerial vehicle according to claim 1 or 2, wherein a second folding arm is also provided between the arm and the fuselage, and the two ends of the second folding arm are respectively connected to the Described machine arm, described fuselage are hinged. 20. The unmanned aerial vehicle according to claim 1 or 2, wherein a circuit board module is arranged in the fuselage, and the circuit board module is installed on a heat dissipation assembly, and the heat dissipation assembly includes: The heat sink, the circuit board module is installed on the lower end surface of the heat sink, and is attached to the lower end surface of the heat sink; the upper end surface of the heat sink is provided with a number of air guide walls; The heat dissipation fan is installed above several of the air guide walls; a heat dissipation channel extending from the center of the heat sink to the edge is formed between the adjacent air guide walls. 21. The UAV according to claim 1, characterized in that, the left and right sides of the UAV are respectively provided with a first indication light and a second indication light, and the front end or tail of the UAV is provided with a third indication light lights, the connecting line of the first indicator light, the second indicator light and the third indicator light is triangular. 22. The unmanned aerial vehicle according to claim 21, wherein the first indication light and the second indication light are constant monochromatic lights, and the third indication light is a three-color indicator indicating the flying state of the drone. colored lights.