Quadrotor unmanned aerial vehicle capable of prolonging endurance time

Abstract

The invention discloses a quad-rotor unmanned aerial vehicle capable of prolonging the endurance time. The quad-rotor unmanned aerial vehicle comprises a vehicle body, vehicle arms, rotors, a battery and a circuit board, wherein the battery and the circuit board are installed on the top face and the bottom face of the vehicle body in an embedded mode respectively. A heat dissipation space is clamped between the circuit board and the battery, the heat dissipation space is communicated with two heat dissipation openings which are arranged in the machine body and communicated with the outside of the machine body, and a through heat dissipation channel is formed in the machine body. When the unmanned aerial vehicle works, heat generated by the circuit board is discharged from the heat dissipation channel, and the working heat of the circuit board is taken away by means of air flowing during flight. The vehicle arms comprise two groups of lower loading vehicle arms and two groups of upper loading vehicle arms located above the lower loading vehicle arms, the lower loading vehicle arms are mounted upwards, the upper loading vehicle arms are mounted downwards, and a distribution structure with an upper layer and a lower layer is formed on the vehicle body, so that the resistance during flight is reduced, the stress of the unmanned aerial vehicle during flight is more stable, and the unmanned aerial vehicle is more stable in flight. The sensitivity of flight control of the unmanned aerial vehicle is improved, and the endurance time is prolonged.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a four-rotor UAV with improved flight time. Background Art

[0002] With the development of quad-rotor drone technology, the application of quad-rotor drones has expanded to aerial photography, agriculture, industry, and military. Although the quad-rotor drone industry is relatively mature, how to improve the endurance of quad-rotor drones has always been a major problem in the industry. Quad-rotor drones mainly rely on lithium batteries for power, but the energy density of lithium batteries is relatively low. Therefore, in order to increase the endurance, more batteries have to be carried. However, the increase in battery volume and weight further increases the weight of the drone itself, which in turn leads to increased power consumption, forming a vicious circle. Combined with the above factors, how to effectively balance the relationship between load and endurance is an urgent problem that the quad-rotor drone industry needs to solve. Summary of the invention

[0003] The purpose of the present invention is to provide a quad-rotor unmanned aerial vehicle with improved flight time, comprising a fuselage, an arm, a rotor, a circuit board and a battery.

[0004] The circuit board is embedded in the bottom of the fuselage.

[0005] The battery is embedded in the body through the top surface of the body and is located above the circuit board.

[0006] The interior of the fuselage is provided with two heat dissipation openings, and the heat dissipation openings are connected to the exterior of the fuselage.

[0007] A heat dissipation space is sandwiched between the circuit board and the battery, and the heat dissipation space is connected with the two heat dissipation ports to form a through heat dissipation channel inside the fuselage.

[0008] Four sets of machine arms are installed on the machine body at intervals.

[0009] The machine arms include two groups of upper machine arms and two groups of lower machine arms. The lower machine arms are installed below the upper machine arms, and the installation direction of the lower machine arms is upward, while the installation direction of the upper machine arms is downward, forming an upper and lower layer distribution structure on the fuselage.

[0010] A rotor is installed on one end of the arm away from the fuselage.

[0011] The rotation centers of the rotors are in the same horizontal plane.

[0012] Furthermore, the lower mounting arm and the upper mounting arm are relatively mounted on the fuselage.

[0013] Furthermore, the number of installed lower mounting arms is the same as the number of installed upper mounting arms.

[0014] Furthermore, the upper mounting arm includes an upper mounting arm I and an upper mounting arm II.

[0015] The lower installation arm comprises a lower installation arm I and a lower installation arm II.

[0016] The upper mounting arm I and the upper mounting arm II are relatively installed on both sides of the fuselage, and the lower mounting arm I and the lower mounting arm II are also relatively installed on both sides of the fuselage. The upper mounting arm I and the lower mounting arm II are located on the same side of the fuselage, and the upper mounting arm II and the lower mounting arm I are located on the same side of the fuselage.

[0017] The rotors include an upper rotor group I, an upper rotor group II, a lower rotor group I and a lower rotor group II.

[0018] The upper mounted rotor group I and the upper mounted rotor group II are respectively installed on the upper mounted machine arm I and the upper mounted machine arm II, and the installation direction of the upper mounted rotor group I and the upper mounted rotor group II is downward.

[0019] The lower mounted rotor group I and the lower mounted rotor group II are respectively mounted on the lower mounted machine arm I and the lower mounted machine arm II, and the mounting direction of the lower mounted rotor group I and the lower mounted rotor group II is upward.

[0020] Furthermore, the fuselage and the arm are connected via a folding mechanism, one end of the folding mechanism is fixed to the fuselage, and the other end is connected to the arm.

[0021] The machine arm realizes the folding and contracting function of the machine arm through the folding mechanism.

[0022] Furthermore, a rotating shaft is installed on one end of the machine arm away from the fuselage, the rotating shaft on the lower machine arm is installed in an upward direction, and the rotating shaft on the upper machine arm is installed in a downward direction. The rotor is installed on the rotating shaft.

[0023] Furthermore, the rotation center of the rotor is on the same horizontal plane as the center of gravity of the drone.

[0024] Furthermore, when the UAV is flying, the blades of the rotor rotate in the air to form a rotating track, and the diameter of the rotating track is at least 1.5 times the length of the fuselage.

[0025] Furthermore, the drone is arranged in a spatial rectangular coordinate system O-XYZ.

[0026] The X-axis of the spatial rectangular coordinate system O-XYZ is parallel to the horizontal direction of the fuselage, the Y-axis is parallel to the longitudinal direction of the fuselage, and the Z-axis is parallel to the vertical direction.

[0027] The rotating surface of the rotor is deflected around the rotating center of gravity toward the plumb plane where the center of gravity of the drone is located. After the deflection, the angle between the rotating surface of the rotor and the X-axis is 0° to 15°, and the angle between the rotating surface of the rotor and the Y-axis is 0° to 15°.

[0028] The angles between the rotating planes of the plurality of rotors and the X-axis and the Y-axis are equal.

[0029] Furthermore, the heat dissipation openings are arranged along the length direction of the fuselage, one opening is arranged at the front of the fuselage, and the other opening is arranged at the rear of the fuselage.

[0030] The technical effect of the present invention is unquestionable, and the beneficial effects of the present invention are as follows:

[0031] 1. The present invention adopts a method of placing the battery from the top of the drone, which is conducive to the installation and removal of large-volume and heavy-weight batteries, and to a certain extent reduces the difficulty of the fuselage shell structure design. Under the premise of the same battery weight, this installation method can more efficiently and conveniently remove and install the battery, and can use larger-volume and larger-capacity batteries to increase the flight time of the drone.

[0032] 2. The present invention adopts a structure in which the battery is on top and the circuit board is on the bottom, and cooperates with the front and rear openings at the bottom of the fuselage to form a closed heat dissipation channel in the area where the circuit board is located. When the drone is operating, the heat generated by the circuit board will be discharged from front to back. This method uses the flow of air when the drone is flying to naturally take away the working heat of the circuit board. On the one hand, it avoids the drone from malfunctioning due to excessive temperature, and on the other hand, it avoids the extra energy consumption caused by the external heat dissipation module, so that the battery can supply energy to the rotor for a longer time, thereby improving the flight time.

[0033] 3. The present invention adopts a distribution method in which the arms are layered up and down, the rotors are installed facing each other, and the rotors are tilted at a certain angle to the center of the UAV, so that the rotation centers of the four sets of rotors are on the same horizontal plane, which can reduce the resistance caused during flight and make the force of the UAV more stable during flight, which is beneficial to improving the sensitivity of the UAV flight control and reducing the energy consumption required to resist resistance to increase the flight time of the UAV.

[0034] 4. The present invention adopts large-sized blades. When providing the same lift, the required motor speed is relatively reduced, which can improve the working efficiency of the motor, improve the energy utilization rate of the battery, and effectively increase the flight time of the drone.

[0035] 5. The present invention designs a quad-rotor drone with improved flight time, increases the battery volume, and maximizes the propeller blade size, thereby increasing the battery capacity and improving the motor working efficiency, thereby improving the flight time. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1This is a schematic diagram of the axonometric structure of the UAV in flight;

[0037] Figure 2 This is a schematic diagram of the structure of the drone when it is flying from a bird's-eye view;

[0038] Figure 3 This is a schematic diagram of the structure when the drone is folded up from a bird's-eye view;

[0039] Figure 4 This is a side view schematic diagram of the structure of the drone when it is folded;

[0040] Figure 5 This is a schematic diagram of the front view of the UAV during flight.

[0041] Figure 6 This is a side view schematic diagram of the UAV structure when it is flying.

[0042] In the figure: 1-fuselage; 2-arm; 21-upper-mounted arm I; 22-upper-mounted arm II; 23-lower-mounted arm I; 24-lower-mounted arm II; 25-folding mechanism; 3-rotor; 31-upper-mounted rotor group I; 32-upper-mounted rotor group II; 33-lower-mounted rotor group I; 34-lower-mounted rotor group II; 4-circuit board; 5-battery; 6-rotation trajectory. DETAILED DESCRIPTION

[0043] The present invention is further described below in conjunction with the embodiments, but it should not be understood that the above subject matter of the present invention is limited to the following embodiments. Without departing from the above technical ideas of the present invention, various substitutions and changes are made according to the common technical knowledge and customary means in the art, which should all be included in the protection scope of the present invention.

[0044] Embodiment 1:

[0045] A four-rotor unmanned aerial vehicle with improved flight time comprises a fuselage 1, an arm 2, a rotor 3, a circuit board 4 and a battery 5.

[0046] The circuit board 4 is embedded in the bottom of the body 1 .

[0047] The battery 5 is embedded in the body 1 through the top surface of the body 1 and is located above the circuit board 4 .

[0048] The body 1 has two heat dissipation openings inside, and the heat dissipation openings are connected to the outside of the body 1.

[0049] A heat dissipation space is sandwiched between the circuit board 4 and the battery 5 , and the heat dissipation space is connected with the two heat dissipation ports to form a through heat dissipation channel inside the body 1 .

[0050] Four sets of arms 2 are installed on the fuselage 1 at intervals.

[0051] The arms 2 include two groups of upper mounting arms and two groups of lower mounting arms. The lower mounting arms are installed below the upper mounting arms, and the installation direction of the lower mounting arms faces upward, while the installation direction of the upper mounting arms faces downward, forming an upper and lower layer distribution structure on the fuselage 1.

[0052] A rotor 3 is mounted on one end of the arm 2 away from the fuselage 1 .

[0053] The rotation centers of the rotors 3 are in the same horizontal plane.

[0054] Embodiment 2:

[0055] The main structure of this embodiment is the same as that of Embodiment 1. Furthermore, the lower mounting arm and the upper mounting arm are relatively mounted on the fuselage 1.

[0056] Embodiment 3:

[0057] The main structure of this embodiment is the same as any one of Embodiments 1 to 2. Furthermore, the number of installed lower mounting arms is the same as the number of installed upper mounting arms.

[0058] Embodiment 4:

[0059] The main structure of this embodiment is the same as any one of Embodiments 1 to 3. Furthermore, the upper mounting arm includes an upper mounting arm I21 and an upper mounting arm II22.

[0060] The lower loading arm includes a lower loading arm I23 and a lower loading arm II24.

[0061] The upper mounting arm I21 and the upper mounting arm II22 are relatively installed on both sides of the fuselage 1, and the lower mounting arm I23 and the lower mounting arm II24 are also relatively installed on both sides of the fuselage 1, and the upper mounting arm I21 and the lower mounting arm II24 are located on the same side of the fuselage 1, and the upper mounting arm II22 and the lower mounting arm I23 are located on the same side of the fuselage 1.

[0062] The rotor 3 includes an upper rotor group I31, an upper rotor group II32, a lower rotor group I33 and a lower rotor group II34.

[0063] The upper mounted rotor group I31 and the upper mounted rotor group II32 are respectively installed on the upper mounted machine arm I21 and the upper mounted machine arm II22, and the installation direction of the upper mounted rotor group I31 and the upper mounted rotor group II32 is downward.

[0064] The lower mounted rotor group I33 and the lower mounted rotor group II34 are respectively mounted on the lower mounted machine arm I23 and the lower mounted machine arm II24, and the installation direction of the lower mounted rotor group I33 and the lower mounted rotor group II34 is upward.

[0065] Embodiment 5:

[0066] The main structure of this embodiment is the same as any one of Embodiments 1 to 4. Furthermore, the body 1 and the arm 2 are connected via a folding mechanism 25. One end of the folding mechanism 25 is fixed to the body 1, and the other end is connected to the arm 2.

[0067] The arm 2 realizes the folding and contracting function of the arm through the folding mechanism 25 .

[0068] Embodiment 6:

[0069] The main structure of this embodiment is the same as any one of Embodiments 1 to 5. Further, a rotating shaft is installed on one end of the arm 2 away from the fuselage 1, the rotating shaft on the lower arm is installed upward, and the rotating shaft on the upper arm is installed downward. The rotor 3 is installed on the rotating shaft.

[0070] Embodiment 7:

[0071] The main structure of this embodiment is the same as any one of Embodiments 1 to 6. Furthermore, the rotation center of the rotor 3 and the center of gravity of the drone are on the same horizontal plane.

[0072] Embodiment 8:

[0073] The main structure of this embodiment is the same as any one of Embodiments 1 to 7. Furthermore, when the UAV is flying, the blades of the rotor 3 rotate in the air to form a rotating track 6, and the diameter of the rotating track 6 is at least 1.5 times the length of the fuselage 1.

[0074] Embodiment 9:

[0075] The main structure of this embodiment is the same as any one of Embodiments 1 to 8. Furthermore, the drone is arranged in a spatial rectangular coordinate system O-XYZ.

[0076] The X-axis of the spatial rectangular coordinate system O-XYZ is parallel to the horizontal direction of the fuselage, the Y-axis is parallel to the longitudinal direction of the fuselage, and the Z-axis is parallel to the vertical direction.

[0077] The rotating surface of the rotor 3 deflects around the rotating center of gravity toward the plumb plane where the center of gravity of the drone is located. After the deflection, the angle between the rotating surface of the rotor 3 and the X-axis is 0° to 15°, and the angle between the rotating surface of the rotor 3 and the Y-axis is 0° to 15°.

[0078] The included angles between the rotating planes of the plurality of rotors 3 and the X-axis and the Y-axis are equal.

[0079] Embodiment 10:

[0080] The main structure of this embodiment is the same as any one of Embodiments 1 to 9. Furthermore, the heat dissipation ports are arranged along the length direction of the fuselage 1, one is arranged at the front of the fuselage 1, and the other is arranged at the rear of the fuselage 1.

[0081] Embodiment 11:

[0082] The main structure of this embodiment is the same as any one of embodiments 1 to 10. Further, a quad-rotor drone with improved flight time includes a fuselage 1, an arm 2, a rotor 3, a circuit board 4, a battery 5, a rotation track 6 and related layout methods;

[0083] The body 1 includes a circuit board 4 and a battery 5 .

[0084] The bottom of the body 1 is closed on the left and right sides and open on the front and back sides, forming a heat dissipation channel that runs through the front and back sides.

[0085] The battery 5 is installed into the body 1 from top to bottom.

[0086] The circuit board 4 is installed into the body 1 from below.

[0087] The battery 5 is located above the circuit board 4 in space.

[0088] The arm 2 is connected to the fuselage 1 .

[0089] There are four arms 2, namely, upper mounting arm I21, upper mounting arm II22, lower mounting arm I23 and lower mounting arm II24. Among them, upper mounting arm I21 and upper mounting arm II22 are located at the upper end of the front half of the fuselage 1, and the other two lower mounting arms I23 and lower mounting arm II24 are located at the lower end of the rear half of the fuselage 1, forming a distribution mode of upper and lower layered installation.

[0090] The machine arms 2 are installed in pairs facing each other.

[0091] The two sets of arms 2 are installed facing each other so that the rotation centers of the four sets of rotors 3 are in the same horizontal plane.

[0092] The rotor 3 is installed at the tail end of the arm 2.

[0093] There are four groups of rotors 3, namely, upper rotor group I31, upper rotor group II32, lower rotor group I33 and lower rotor group II34, all of which have the same deflection angle toward the center of the UAV.

[0094] Furthermore, the fuselage 1, the circuit board 4, and the battery 5 form a specific spatial distribution relationship:

[0095] The battery 5 is installed into the fuselage 1 from the top of the drone from top to bottom, and is spatially located at the upper part of the fuselage 1. The circuit board 4 is installed into the fuselage 1 from the tail or bottom of the drone, and is spatially located at the bottom of the fuselage 1. A certain space is left between the circuit board 4 and the battery 5. The fuselage 1 is closed on the left and right, and the space left between the circuit board 4 and the battery 5 is open at the front and back. When the drone is flying, air can naturally flow through the channel between the circuit board 4 and the battery 5 to play a heat dissipation role.

[0096] Furthermore, the arm 2 is installed in a specific manner:

[0097] The arms 2 can be divided into two groups: one group is an upper mounting arm I21 and an upper mounting arm II22, and the other group is a lower mounting arm I23 and a lower mounting arm II24. The upper mounting arm I21 and the upper mounting arm II22 are installed at the upper end of the outer body 1, and the lower mounting arm I23 and the lower mounting arm II24 are installed at the lower end of the outer body 1, and the two groups of arms form a layered distribution structure.

[0098] The upper mounting arms I21 and II22 are installed downward, and the lower mounting arms I23 and II24 are installed upward, so that the two sets of arms are installed in opposite directions, and the rotation center points of the four pairs of rotors 3 are in the horizontal plane where the center of gravity of the UAV is located.

[0099] Furthermore, the rotor 3 has the following characteristics: the rotation trajectory of the rotor has a large diameter, and the diameter is at least 1.5 times the length of the fuselage.

[0100] Furthermore, the rotor 3 and the fuselage 1 form a specific distribution relationship:

[0101] The rotors 3 can be divided into two groups: one group of rotors is the upper rotor group I31 and the upper rotor group II32, which are installed at the ends of the upper machine arms I21 and II22; the other group of rotors is the lower rotor group I33 and the lower rotor group II34, which are installed at the ends of the lower machine arms I23 and II24. The four groups of rotors are all deflected at a certain angle around the rotation center of gravity toward the vertical plane of the center of gravity where the battery is located, and the deflection angles of the four groups of rotors are the same.

[0102] Embodiment 12:

[0103] The main structure of this embodiment is the same as any one of Embodiments 1 to 10. Furthermore, a quad-rotor drone with improved flight time includes a battery, a circuit board, a fuselage, an arm, and a rotor.

[0104] The battery is the central part of the entire drone. When a large battery is used, it will account for most of the weight of the entire drone. Therefore, the subsequent layout plan also needs to be designed around the battery.

[0105] The circuit board includes flight control, image transmission, core processing and other main boards. All main boards are installed centrally below the battery and keep a certain distance from the battery.

[0106] The fuselage is the main connecting structure of the quad-rotor drone, and contains batteries and circuit boards. The batteries are installed into the fuselage from directly above the drone, and the circuit boards are installed into the fuselage from the tail of the drone, and are spatially located directly below the batteries.

[0107] The bottom of the fuselage is provided with a gap in the front-to-back direction, and a ventilation passage is formed with the gap between the circuit board and the fuselage, which is conducive to more effectively discharging the heat generated by the circuit board when working from the inside of the fuselage.

[0108] There are four arms in total, which are distributed in upper and lower layers, two of which are installed at the upper end of the front half of the fuselage, and the other two are installed at the lower end of the rear half of the fuselage.

[0109] The rotor is installed on a rotating shaft at the end of the arm, and the length of a single rotor is longer than that of a traditional UAV.

[0110] The layout of the arms and rotors is as follows: the arms are distributed in upper and lower layers and are installed oppositely, so that the rotation centers of the four sets of rotors are in the same horizontal plane, and the four sets of rotors are inclined at the same angle toward the center of the drone.

[0111] Embodiment 13:

[0112] The main structure of this embodiment is the same as any one of Embodiments 1 to 10. Figure 1 The UAV includes a fuselage 1, an arm 2, a rotor 3, a circuit board 4, a battery 5 and a rotating track 6.

[0113] The battery 5 is directly installed into the fuselage 1 from the top of the drone.

[0114] The arms 2 of the quad-rotor drone include: an upper mounting arm I21, an upper mounting arm II22, a lower mounting arm I23 and a lower mounting arm II24.

[0115] The rotor 3 is composed of four groups of propeller blades including: an upper rotor group I31, an upper rotor group II32, a lower rotor group I33, and a lower rotor group II34, and is installed on the rotating shaft at the end of the arm 2 in a centrally symmetrical form.

[0116] The rotor rotation track 6 has a relatively large diameter, which is at least 1.5 times the length of the fuselage 1 from head to tail.

[0117] One end of the folding module 25 is fixed on the fuselage 1, and the other end is connected to the arm 2. The upper mounting arm I21, the upper mounting arm II22, the lower mounting arm I23 and the lower mounting arm II24 are all connected to the fuselage 1 through the folding mechanism 25, thereby realizing the folding and contraction function of the arm.

[0118] The upper loading arm I21, upper loading arm II22, lower loading arm I23 and lower loading arm II24 adopt an upper and lower layered distribution structure, wherein the upper loading arm I21 and upper loading arm II22 are located at the upper head end of the fuselage 1, and the lower loading arm I23 and lower loading arm II24 are located at the lower tail end of the fuselage 1.

[0119] The upper mounting arm I21, upper mounting arm II22, lower mounting arm I23 and lower mounting arm II24 are arranged in a layout manner of opposite installation, wherein the upper mounting arm I21 and upper mounting arm II22 are located at the upper part of the fuselage 1, and the installation direction of the upper mounting rotor group I31 and upper mounting rotor group II32 is downward; the lower mounting arm I23 and lower mounting arm II24 are located at the lower part of the fuselage 1, and the installation direction of the lower mounting rotor group I33 and lower mounting rotor group II34 is upward, forming a face-to-face installation manner of two sets of rotor groups.

[0120] The circuit board 4 is installed at the bottom of the fuselage 1, and the battery 5 is placed on the top of the fuselage 1. There is a large space between the circuit board 4 and the battery 5. The front and rear fuselages 1 at the position of the space have openings, which is conducive to the air flow inside the space when the drone is flying, thereby forming a left and right closed heat dissipation channel.

[0121] Since the arms 2 are installed in opposite directions, the rotation centers of the upper rotor groups I31, II32 and the lower rotor groups I33, II34 are located in the same horizontal plane, and the center of gravity of the UAV is also in the same horizontal plane.

[0122] The upper rotor group I31, the upper rotor group II32 and the lower rotor group I33, the lower rotor group II34 are all inclined at a certain angle to the vertical plane where the center of gravity of the drone is located.

[0123] Embodiment 14:

[0124] The main structure of this embodiment is the same as any one of embodiments 1 to 10. Furthermore, the present invention relates to the field of industrial manufacturing technology, and in particular to a quad-rotor drone with improved endurance. A quad-rotor drone with improved endurance includes a fuselage, an arm, a rotor, a circuit board, a battery, and a rotor rotation trajectory; the fuselage contains a battery and a circuit board, and the three have a specific spatial distribution relationship; the battery is installed in an up-and-down manner, and for batteries of the same size, the up-and-down installation method is more efficient and convenient, so a larger capacity battery can be considered; the battery and the circuit board are respectively located on the upper and lower sides of the fuselage, forming a closed heat dissipation channel between the battery and the circuit board; the arm is installed on the outside of the fuselage, and is a layered distribution structure, and a counter-mounting method is adopted to ensure that the rotation center of the rotor is still in the same horizontal plane; the rotation diameter of the rotor is relatively large, at least 1.5 times the length of the drone, and the four sets of rotors are all deflected to the same angle to the vertical plane of the center of the drone.

[0125] The present invention adopts the method of installing the batteries up and down, so that larger capacity batteries can be used to provide longer flight time; the use of a large rotating diameter rotor can reduce the motor speed while providing the same lift, improve energy utilization, reduce energy consumption, and increase flight time; by installing the arms in layers and opposite directions, the maneuverability of the drone during flight can be improved, and the resistance generated when the drone changes its attitude can be reduced, thereby reducing battery energy consumption and achieving the effect of increasing flight time; the closed heat dissipation channel formed by the specific distribution among the fuselage, the battery, and the circuit board can achieve a natural heat dissipation effect through air flow when the drone is flying, avoiding the extra energy consumption caused by the installation of a heat dissipation module, thereby increasing the flight time.

Claims

1. A quad-rotor drone with improved flight time, characterized in that: It comprises a fuselage (1), an arm (2), a rotor (3), a circuit board (4) and a battery (5); The circuit board (4) is embedded in the bottom of the body (1); The battery (5) is embedded in the body (1) through the top surface of the body (1) and is located above the circuit board (4); The body (1) has two heat dissipation openings inside, and the heat dissipation openings are connected to the outside of the body (1); A heat dissipation space is sandwiched between the circuit board (4) and the battery (5), and the heat dissipation space is connected to the two heat dissipation ports to form a continuous heat dissipation channel inside the body (1); Four sets of machine arms (2) are installed at intervals on the machine body (1); The machine arms (2) include two groups of upper machine arms and two groups of lower machine arms, wherein the lower machine arms are installed below the upper machine arms, and the installation direction of the lower machine arms is upward, while the installation direction of the upper machine arms is downward, so as to form an upper and lower layer distribution structure on the machine body (1); A rotor (3) is mounted on one end of the arm (2) away from the fuselage (1); The rotation centers of the rotors (3) are located in the same horizontal plane.

2. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The lower mounting arm and the upper mounting arm are relatively mounted on the fuselage (1).

3. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The number of installed lower mounting arms is the same as the number of installed upper mounting arms.

4. A quad-rotor drone with improved flight time according to claim 1 or 2, characterized in that: The upper loading arm comprises an upper loading arm I (21) and an upper loading arm II (22); The lower loading arm comprises a lower loading arm I (23) and a lower loading arm II (24); The upper mounting arm I (21) and the upper mounting arm II (22) are relatively mounted on two sides of the fuselage (1), and the lower mounting arm I (23) and the lower mounting arm II (24) are also relatively mounted on two sides of the fuselage (1), and the upper mounting arm I (21) and the lower mounting arm II (24) are located on the same side of the fuselage (1), and the upper mounting arm II (22) and the lower mounting arm I (23) are located on the same side of the fuselage (1); The rotor (3) comprises an upper rotor group I (31), an upper rotor group II (32), a lower rotor group I (33) and a lower rotor group II (34); The upper mounted rotor group I (31) and the upper mounted rotor group II (32) are respectively mounted on the upper mounted machine arm I (21) and the upper mounted machine arm II (22), and the mounting direction of the upper mounted rotor group I (31) and the upper mounted rotor group II (32) is downward; The lower mounted rotor group I (33) and the lower mounted rotor group II (34) are respectively mounted on the lower mounted machine arm I (23) and the lower mounted machine arm II (24), and the mounting direction of the lower mounted rotor group I (33) and the lower mounted rotor group II (34) is upward.

5. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The fuselage (1) and the arm (2) are connected via a folding mechanism (25); one end of the folding mechanism (25) is fixed on the fuselage (1), and the other end is connected to the arm (2). The machine arm (2) realizes the folding and contracting function of the machine arm through the folding mechanism (25).

6. The quad-rotor drone with improved flight time according to claim 1, characterized in that: A rotating shaft is installed on one end of the machine arm (2) away from the fuselage (1); the installation direction of the rotating shaft on the lower machine arm is upward, and the installation direction of the rotating shaft on the upper machine arm is downward; the rotor (3) is installed on the rotating shaft.

7. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The rotation center of the rotor (3) and the center of gravity of the drone are on the same horizontal plane.

8. The quad-rotor drone with improved flight time according to claim 1, characterized in that: When the unmanned aerial vehicle is flying, the blades of the rotor (3) rotate in the air to form the rotation track (6), and the diameter of the rotation track (6) is at least 1.5 times the length of the fuselage (1).

9. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The drone is arranged in a spatial rectangular coordinate system O-XYZ; The X-axis of the spatial rectangular coordinate system O-XYZ is parallel to the horizontal direction of the fuselage, the Y-axis is parallel to the longitudinal direction of the fuselage, and the Z-axis is parallel to the vertical direction; The rotating surface of the rotor (3) deflects around the rotating center of gravity toward the plumb plane where the center of gravity of the drone is located. After the deflection, the angle between the rotating surface of the rotor (3) and the X-axis is 0° to 15°, and the angle between the rotating surface of the rotor (3) and the Y-axis is 0° to 15°. The included angles between the rotating surfaces of the plurality of rotors (3) and the X-axis and the Y-axis are equal.

10. The quad-rotor drone with improved flight time according to claim 1, characterized in that: The heat dissipation openings are arranged along the length direction of the fuselage (1), one opening is arranged at the front part of the fuselage (1), and the other opening is arranged at the rear part of the fuselage (1).

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