A rotor unmanned aerial vehicle general load platform and a take-off and landing method thereof

Abstract

The application discloses a general load platform of a rotor unmanned aerial vehicle and a taking-off and landing method thereof. The general load platform of the rotor unmanned aerial vehicle comprises a four-rotor unmanned aerial vehicle and at least one set of mechanical and electrical integrated quick-release load interfaces, each set of the quick-release load interfaces comprises two quick-release load interfaces, the quick-release load interface comprises a quick-release female seat and a quick-release male seat, the quick-release female seat is fixedly installed on the fuselage of the four-rotor unmanned aerial vehicle, and the quick-release male seat is detachably connected with a load support. The general load platform of the rotor unmanned aerial vehicle can quickly and accurately complete mechanical and electrical connection between the rotor unmanned aerial vehicle and the load through the mechanical and electrical integrated quick-release load interface, solves the problem that the existing rotor unmanned aerial vehicle cannot quickly and accurately mount the load, saves a large amount of manpower and improves the mounting connection yield; and the load support is detachably connected with the quick-release male seat, the load support can carry different types of loads, realizes one machine with multiple uses and achieves the purpose of saving cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, and particularly relates to a general load platform of a rotor unmanned aerial vehicle and a take-off and landing method thereof. BACKGROUND

[0002] At present, the rotor performance unmanned aerial vehicles on the market are mainly used for light performance, lantern performance and fireworks performance, wherein the unmanned aerial vehicles for light performance are relatively mature, but the rotor unmanned aerial vehicles for lantern performance and fireworks performance cannot quickly and accurately mount loads, for example, when the rotor unmanned aerial vehicle mounts fireworks, it needs to perform complicated steps such as fixing the fireworks, adjusting the angle of the fireworks and connecting the ignition circuit of the fireworks, which not only consumes a long time, but also has the risk of connection error. SUMMARY

[0003] The technical problem to be solved by the present application is to provide a general load platform of a rotor unmanned aerial vehicle and a take-off and landing method thereof, so as to solve the problem that the existing rotor unmanned aerial vehicle cannot quickly and accurately mount loads.

[0004] To solve the above technical problem, the present application adopts the technical solution as follows:

[0005] In one aspect, the present application provides a general load platform of a rotor unmanned aerial vehicle, which comprises a quad-rotor unmanned aerial vehicle and at least one set of mechanical and electrical integrated quick-release load interface, each set of quick-release load interface comprises two quick-release load interfaces, the two quick-release load interfaces of each set are correspondingly installed on two opposite sides of the fuselage of the quad-rotor unmanned aerial vehicle, the quick-release load interface comprises a quick-release female seat and a quick-release male seat which is detachably connected with the quick-release female seat, the quick-release female seat is fixedly installed on the fuselage of the quad-rotor unmanned aerial vehicle, and the quick-release male seat is detachably connected with a load support.

[0006] In another aspect, the present application provides a take-off and landing method of a general load platform of a rotor unmanned aerial vehicle, which is used for controlling the take-off and landing of the general load platform of the rotor unmanned aerial vehicle, each arm of the quad-rotor unmanned aerial vehicle of the general load platform of the rotor unmanned aerial vehicle extends outward to form an arm extension segment, and the take-off and landing method of the general load platform of the rotor unmanned aerial vehicle comprises the following steps: opening an aircraft box and unfolding the storable legs on the upper and lower surfaces of the aircraft box to build a take-off and landing platform on the ground; placing the quad-rotor unmanned aerial vehicle with mounted loads in the hollow area of the aircraft box, and placing the arm extension segment of the quad-rotor unmanned aerial vehicle in the arm extension segment accommodating groove of the aircraft box; executing a take-off command to control the quad-rotor unmanned aerial vehicle to take off; executing a landing command to control the quad-rotor unmanned aerial vehicle to fall into the hollow area of the aircraft box, and to control the arm extension segment of the quad-rotor unmanned aerial vehicle to fall into the arm extension segment accommodating groove of the aircraft box; unloading the loads, clamping the arm extension segment of the quad-rotor unmanned aerial vehicle into the clamping groove in the arm extension segment accommodating groove, and closing the aircraft box.

[0007] The beneficial technical effect of the present application is that the rotor unmanned aerial vehicle universal load platform can quickly and accurately complete the mechanical and electrical connection of the rotor unmanned aerial vehicle and the load through the mechanical and electrical integrated quick-release load interface, solves the problem that the existing rotor unmanned aerial vehicle cannot quickly and accurately mount the load, saves a lot of manpower and improves the mounting connection yield; and the load support and the quick-release male seat are detachably connected, the load support can carry different types of loads, realizes one machine with multiple uses, and achieves the purpose of saving cost. BRIEF DESCRIPTION OF DRAWINGS

[0008] Figure 1 The structure schematic diagram of the rotor unmanned aerial vehicle universal load platform in embodiment one in another direction when not mounting the load;

[0009] Figure 2 The structure schematic diagram of the rotor unmanned aerial vehicle universal load platform in embodiment one in another direction when not mounting the load;

[0010] Figure 3 The structure schematic diagram of the rotor unmanned aerial vehicle universal load platform in embodiment one when the battery and the battery compartment are separated;

[0011] Figure 4 The three-dimensional structure schematic diagram of the first quick-release load interface in embodiment one;

[0012] Figure 5 The split structure schematic diagram of the first quick-release load interface in embodiment one in one direction;

[0013] Figure 6 The split structure schematic diagram of the first quick-release load interface in embodiment one in another direction;

[0014] Figure 7 The partial sectional view of the first quick-release load interface and the first load support in embodiment one when assembling;

[0015] Figure 8 The first state schematic diagram of the first quick-release load interface and the first load support in embodiment one when assembling;

[0016] Figure 9 The second state schematic diagram of the first quick-release load interface and the first load support in embodiment one when assembling;

[0017] Figure 10 The third state schematic diagram of the first quick-release load interface and the first load support in embodiment one when assembling;

[0018] Figure 11The schematic view of the split structure of the second quick-release load interface in the first embodiment of the present application;

[0019] Figure 12 The partial sectional view of the second quick-release load interface in the first embodiment of the present application when assembled;

[0020] Figure 13 The first state schematic view of the second quick-release load interface and the second load support when assembled in the first embodiment of the present application;

[0021] Figure 14 The second state schematic view of the second quick-release load interface and the second load support when assembled in the first embodiment of the present application;

[0022] Figure 15 The structure schematic view of the rotor unmanned aerial vehicle general load platform when mounting a load in the first embodiment of the present application;

[0023] Figure 16 The structure schematic view of the rotor unmanned aerial vehicle general load platform when mounting a load in the second embodiment of the present application;

[0024] Figure 17 The structure schematic view of the rotor unmanned aerial vehicle general load platform when mounting a load in the third embodiment of the present application;

[0025] Figure 18 The mechanism schematic view of the aircraft landing platform of the present application;

[0026] Figure 19 The landing method flowchart schematic view of the rotor unmanned aerial vehicle general load platform of the present application.

[0027] Explanation of reference signs:

[0028] 10-robot arm, 11-robot arm extension section, 12-antenna box, 20-paddle, 21-motor, 22-motor base, 30-battery, 31-battery compartment, 32-LED light, 40-first quick release load interface, 41-first quick release female seat, 411-first female seat groove, 412-female buckle, 42-first quick release male seat, 421-first male seat protrusion, 422-male buckle clamp, 423-rotation shaft, 424-bracket mounting hole, 4241-spring limiting step, 425-positioning clamping groove, 43-first load bracket, 431-load bracket rotation shaft, 432-spring, 433-pivot, 50-second quick release load interface, 51-second quick release female seat, 511-second female seat groove, 512-buckle column, 52-second quick release male seat, 521-second male seat protrusion, 522-C-shaped buckle, 523-buckle rotation shaft, 524-hand knob, 53-second load bracket, 61-quick release female seat circuit connector, 62-quick release male seat circuit connector, 70-load, 100-airplane box, 101-storable support leg, 102-hollow area, 103-robot arm extension section containing groove, 104-clamping groove. DETAILED DESCRIPTION

[0029] In order to make ordinary skilled in the art more clearly understand the purpose, technical scheme and advantages of the present application, the present application is further described below in conjunction with the drawings and examples.

[0030] The present application provides a general load platform for a rotor unmanned aerial vehicle, which comprises a quadrotor unmanned aerial vehicle and at least one set of mechanical and electrical integrated quick release load interface. Each set of quick release load interface comprises two quick release load interfaces, and the two quick release load interfaces of each set are installed on two opposite sides of the fuselage of the quadrotor unmanned aerial vehicle. The quick release load interface comprises a quick release female seat and a quick release male seat which is detachably connected with the quick release female seat. The quick release female seat is fixedly installed on the fuselage of the quadrotor unmanned aerial vehicle, and the quick release male seat is detachably connected with a load bracket. The general load platform for the rotor unmanned aerial vehicle can quickly and accurately complete the mechanical and electrical connection between the rotor unmanned aerial vehicle and the load through the mechanical and electrical integrated quick release load interface, solves the problem that the existing rotor unmanned aerial vehicle cannot quickly and accurately mount the load, saves a lot of manpower and improves the mounting connection yield; and the load bracket is detachably connected with the quick release male seat, the load bracket can carry different types of loads, realizes one machine with multiple uses, and achieves the purpose of saving cost.

[0031] Example 1:

[0032] As Figures 1 to 3As shown, in this embodiment of the invention, the universal payload platform for rotary-wing drones includes a quadcopter drone and two sets of quick-release payload interfaces. The quadcopter drone includes four arms 10, each arm 10 is equipped with a propeller 20 and a motor 21 for driving the propeller 20 to rotate. The motor 21 is fixed to the arm 10 by a motor mount 22, and the propeller 20 is fixedly connected to the shaft of the motor 21. Each arm 10 extends outward to form an arm extension section 11, which can be used as a support part for take-off, landing, and storage. An antenna box 12 is installed at the end of the arm extension section 11. The quadcopter drone has a battery compartment 31 at the bottom, which contains a pluggable battery 30. An LED light 32 is installed at the bottom of the battery compartment 31 for use in light show performances.

[0033] In this embodiment, the two sets of quick-release load interfaces include a first quick-release load interface 40 and a second quick-release load interface 50. The two first quick-release load interfaces 40 of the first quick-release load interface are respectively installed on two opposite sides of the fuselage of the quadcopter drone, and the two second quick-release load interfaces of the second quick-release load interface are respectively installed on the other two opposite sides of the fuselage of the quadcopter drone.

[0034] like Figures 4 to 6 As shown, the first quick-release load interface 40 includes a first quick-release female connector 41, a first quick-release male connector 42 detachably connected to the first quick-release female connector 41, and a first load bracket 43. The first quick-release female connector 41 is fixedly mounted on the fuselage of the quadcopter drone. The first quick-release male connector 42 is detachably connected to the first load bracket 43. The load 70 mounted on the first load bracket 43 can be fireworks, lanterns, pods, or other types of loads. The first quick-release male connector 42 can be quickly connected to the first quick-release female connector 41. The first quick-release male connector 42 can be pre-operated without location restrictions before quickly connecting to the first quick-release female connector 41 on the fuselage. For example, when the load is fireworks, the first quick-release male connector 42 can perform pre-operations such as binding the fireworks, adjusting the fireworks angle, and connecting the fireworks ignition wire before connecting to the first quick-release female connector 41.

[0035] The first quick release female seat 41 is provided with a first female seat groove 411 on the side away from the quadrotor, the first quick release male seat 42 is provided with a first male seat protrusion 421 on the upper end, the first female seat groove 411 is provided with a quick release female seat circuit connector 61, the first male seat protrusion 421 is provided with a quick release male seat circuit connector 62, the first quick release female seat 41 is provided with female buckles 412 on both sides, and the first quick release male seat 42 is provided with male buckle clamps 422 on both sides of the upper end. The male buckle clamps 422 are rotatably installed on both sides of the first quick release male seat 42 through a rotating shaft 423, and the rotating shaft 423 is provided with a torsional spring for providing a torque for the inward rotation of the male buckle clamps 422. The side wall of the first female seat groove 411 is a slope, so that the cross section of the first female seat groove 411 gradually decreases from the opening to the bottom; the side of the first male seat protrusion 421 is a slope, so that the cross section of the first male seat protrusion 421 gradually increases from the end to the other end; the side wall of the first female seat groove 411 and the side of the first male seat protrusion 421 are designed as slopes, so that the first male seat protrusion 421 can be more conveniently inserted into the first female seat groove 411.

[0036] When the first quick release male seat 42 is connected with the first quick release female seat 41, the first male seat protrusion 421 is inserted into the first female seat groove 411, and the cooperation between the first male seat protrusion 421 and the first female seat groove 411 can realize the up-down and left-right displacement limitation of the first quick release male seat 42 after being connected with the first quick release female seat 41. The male buckle clamps 422 are buckled with the female buckles 412 under the action of the rotating torque provided by the torsional spring, so as to limit the front-back displacement of the first quick release male seat 42 and the first quick release female seat 41. At the same time, the quick release female seat circuit connector 61 in the first female seat groove 411 is electrically connected with the quick release male seat circuit connector 62 on the first male seat protrusion 421, so as to realize the electrical connection between the quadrotor and the load, and further realize the control of the load. For example, when the load is fireworks, the quick release female seat circuit connector 61 and the first male seat protrusion 421 can be used to realize the ignition control of the fireworks; when the load is other devices that need to be controlled, the quick release female seat circuit connector 61 and the first male seat protrusion 421 can also be used to transmit signals and power.

[0037] As Figures 7 to 8As shown, the first load support 43 is provided with a load support rotating shaft 431, and a compression spring 432 is sleeved on the load support rotating shaft 431. The lower end of the first quick-release male seat 42 is provided with a support mounting hole 424, and a compression spring limiting step 4241 is arranged in the support mounting hole 424. A pin shaft 433 is fixedly installed at the end of the load support rotating shaft 431 after the load support rotating shaft 431 penetrates through the support mounting hole 424. The end of the support mounting hole 424 away from the first load support 43 is provided with a plurality of positioning clamping grooves 425 for the pin shaft. During assembly, the load support rotating shaft 431 is inserted into the support mounting hole 424, and the load support rotating shaft 431 is connected with the support mounting hole 424 to realize cylindrical pair connection. At this time, the compression spring 432 is in a compressed state, so that the first load support 43 and the first quick-release male seat 42 exist an action force in the direction of the axis of the load support rotating shaft 431. The pin shaft 433 is fixedly installed at the end of the load support rotating shaft 431 after the load support rotating shaft 431 penetrates through the support mounting hole 424. The pin shaft 433 is in interference fit with the load support rotating shaft 431. The pin shaft 433 is arranged in the corresponding positioning clamping groove 425, and the positioning clamping groove 425 can limit the movement of the pin shaft 433 and limit the rotation movement of the first load support 43 in the radial direction of the load support rotating shaft 431 and the sliding movement of the first load support 43 in the axis direction of the load support rotating shaft 431. The positioning clamping groove 425 is provided with a plurality of groups, and each group is spaced apart by a certain angle, so as to limit the installation angle of the first load support 43. For example, the installation angle of the first load support 43 can be adjusted to 45° (as shown in Figure 9 ), or the installation angle of the first load support 43 can be adjusted to 0° (as shown in Figure 10 ). Through different installation angles, more rich performance effects can be realized.

[0038] As shown in Figures 11 to 12 , the second quick-release load interface 50 includes a second quick-release female seat 51, a second quick-release male seat 52 detachably connected with the second quick-release female seat 51, and a second load support 53. The second quick-release female seat 51 is fixedly installed on the body of the quadrotor unmanned aerial vehicle. The second quick-release male seat 52 is detachably connected with the second load support 53. The load 70 installed on the second load support 53 can be fireworks, or can be lanterns, pods or other types of loads. The second quick-release male seat 52 can be quickly connected with the second quick-release female seat 51. For example, when the load is fireworks, the second quick-release male seat 52 can be connected with the second quick-release female seat 51 after preliminary operations such as bundling fireworks, adjusting the angle of the fireworks, connecting the ignition line of the fireworks, etc.

[0039] The second quick release female seat 51 is provided with a second female seat groove 511 at the upper end, the second quick release male seat 52 is provided with a second male seat protrusion 521 at the lower end, the second female seat groove 511 is provided with a quick release female seat circuit connector 61, the second male seat protrusion 521 is provided with a quick release male seat circuit connector 62, the second quick release female seat 51 is provided with a buckle column 512 away from the four-rotor unmanned aerial vehicle, the second quick release male seat 52 is provided with a deformable C-shaped buckle 522 away from the four-rotor unmanned aerial vehicle, the C-shaped buckle 522 is made of a material with good toughness, such as nylon. The C-shaped buckle 522 is installed on the second quick release male seat 52 through a buckle shaft 523, and the C-shaped buckle 522 can rotate around the buckle shaft 523. The side wall of the second female seat groove 511 is inclined, so that the cross section of the second female seat groove 511 gradually decreases from the opening to the bottom; the side of the second male seat protrusion 521 is inclined, so that the cross section of the second male seat protrusion 521 gradually increases from the end to the other end; the side wall of the second female seat groove 511 and the side of the second male seat protrusion 521 are designed to be inclined, so that the second male seat protrusion 521 can be more conveniently inserted into the second female seat groove 511.

[0040] When the second quick release male seat 52 is connected with the second quick release female seat 51, the second male seat protrusion 521 is inserted into the second female seat groove 511, and the second male seat protrusion 521 and the second female seat groove 511 can realize the front-back and left-right displacement limitation of the second quick release male seat 52 after being connected with the second quick release female seat 51; the C-shaped buckle 522 rotates clockwise around the buckle shaft 523, so that the C-shaped buckle 522 cooperates with the buckle column 512, and the elastic force generated by deformation presses the second quick release male seat 52 and the second quick release female seat 51 tightly. At the same time, the quick release female seat circuit connector 61 in the second female seat groove 511 is electrically connected with the quick release male seat circuit connector 62 on the second male seat protrusion 521, realizing the electrical connection between the unmanned aerial vehicle and the load, and further realizing the control of the load. For example, when the load is fireworks, the quick release female seat circuit connector 61 can realize the ignition control of the fireworks together with the first male seat protrusion 421; when the load is other devices that need to be controlled, the quick release female seat circuit connector 61 can also transmit signals and power together with the first male seat protrusion 421.

[0041] The second load support 53 is detachably connected with the second quick release male seat 52 through a hand knob 524. The hand knob 524 is provided with a screw rod, and rotating the hand knob 524 can compress or loosen the second load support 53 and the second quick release male seat 52. In the loosened state, the second load support 53 can rotate around the screw rod shaft of the hand knob 524 to adjust the angle, and after the angle is determined, the hand knob 524 is tightened, so that the second load support 53 is fixed with the second quick release male seat 52 at the corresponding angle, thereby adjusting the installation angle of the second load support 53, for example, the second load support 53 is inclined upward, vertically upward, as shown in Figure 13 、 14

[0042] Figure 15 The structure schematic diagram of the rotor unmanned aerial vehicle universal load platform in the embodiment of the application when mounting a load is shown. As shown in Figure 15 , the four-rotor unmanned aerial vehicle is mounted with loads around the fuselage, wherein, two first quick release load interfaces 40 of the first quick release load interface group are correspondingly installed on two sides of the fuselage of the four-rotor unmanned aerial vehicle parallel to the battery insertion and extraction direction, so as to install downward loads on the two sides parallel to the battery insertion and extraction direction; two second quick release load interfaces 50 of the second quick release load interface group are correspondingly installed on two sides of the fuselage of the four-rotor unmanned aerial vehicle perpendicular to the battery insertion and extraction direction, so as to install upward loads on the two sides perpendicular to the battery insertion and extraction direction; such installation does not affect the insertion and extraction of the battery, and facilitates the replacement of the battery during performance. Of course, in other embodiments of the application, the installation positions of the first quick release load interface 40 and the second quick release load interface 50 can be transposed.

[0043] Embodiment two:

[0044] In the embodiment of the application, the rotor unmanned aerial vehicle universal load platform comprises a four-rotor unmanned aerial vehicle and a first quick release load interface group 40. The four-rotor unmanned aerial vehicle comprises four arms 10, each arm 10 is provided with a propeller 20 and a motor 21 for driving the propeller 20 to rotate, the motor 21 is fixed on the arm 10 through a motor seat 22, the propeller 20 is fixedly connected with the rotating shaft of the motor 21, each arm 10 extends outward to form an arm extension segment 11, which can be used as a support part during take-off and landing and storage, and an antenna box 12 is installed at the end of the arm extension segment 11. The four-rotor unmanned aerial vehicle is provided with a battery compartment 31 at the bottom, a pluggable battery 30 is installed in the battery compartment 31, and an LED lamp 32 is installed at the bottom of the battery compartment 31, which can be used for light show performance.

[0045] ​The difference between the rotor unmanned plane general load platform in the embodiment of the application and the rotor unmanned plane general load platform in the first embodiment is that only a group of two first quick-release load interfaces 40 are included, and a group of second quick-release load interfaces 50 are omitted.

[0046] The rotor unmanned plane general load platform in the embodiment of the application is provided with two downward loads on two opposite sides of the fuselage of the quad-rotor unmanned plane through two first quick-release load interfaces 40, as shown in the figure. Figure 16

[0047] Embodiment three:

[0048] In the embodiment of the application, the rotor unmanned plane general load platform comprises a quad-rotor unmanned plane and a group of second quick-release load interfaces 50, the quad-rotor unmanned plane comprises four arms 10, each arm 10 is provided with a paddle 20 and a motor 21 for driving the paddle 20 to rotate, the motor 21 is fixed on the arm 10 through a motor seat 22, the paddle 20 is fixedly connected with a rotating shaft of the motor 21, each arm 10 extends outward to form an arm extension segment 11, the arm extension segment 11 can be used as a support part during take-off and landing and storage, and an antenna box 12 is installed at the end of the arm extension segment 11. The bottom of the quad-rotor unmanned plane is provided with a battery compartment 31, a pluggable battery 30 is installed in the battery compartment 31, and an LED lamp 32 is installed at the bottom of the battery compartment 31 and can be used for light show performance.

[0049] The difference between the rotor unmanned plane general load platform in the embodiment of the application and the rotor unmanned plane general load platform in the first embodiment is that only a group of two second quick-release load interfaces 50 are included, and a group of first quick-release load interfaces 40 are omitted.

[0050] The rotor unmanned plane general load platform in the embodiment of the application is provided with two upward loads on two opposite sides of the fuselage of the quad-rotor unmanned plane through two second quick-release load interfaces 50, as shown in the figure. Figure 17

[0051] Embodiment four:

[0052] ​​In the embodiment of the present application, the rotor unmanned aerial vehicle general load platform comprises a four-rotor unmanned aerial vehicle and two groups of second quick-release load interfaces 50, the four-rotor unmanned aerial vehicle comprises four arms 10, each arm 10 is provided with a propeller 20 and a motor 21 for driving the propeller 20 to rotate, the motor 21 is fixed on the arm 10 through a motor seat 22, the propeller 20 is fixedly connected with the rotating shaft of the motor 21, each arm 10 extends outward to form an arm extension segment 11, the arm extension segment 11 can be used as a support part during take-off and landing, and an antenna box 12 is installed at the end of the arm extension segment 11. The bottom of the four-rotor unmanned aerial vehicle is provided with a battery compartment 31, a pluggable battery 30 is installed in the battery compartment 31, and an LED lamp 32 is installed at the bottom of the battery compartment 31 and can be used for light show performance.

[0053] The difference between the rotor unmanned aerial vehicle general load platform in the embodiment of the present application and the rotor unmanned aerial vehicle general load platform in the first embodiment is that the two groups of quick-release load interfaces are both second quick-release load interfaces 50.

[0054] The rotor unmanned aerial vehicle general load platform in the embodiment of the present application is provided with four upward loads through two groups of four second quick-release load interfaces 50 around the fuselage of the four-rotor unmanned aerial vehicle.

[0055] Embodiment five:

[0056] In the embodiment of the present application, the rotor unmanned aerial vehicle general load platform comprises a four-rotor unmanned aerial vehicle and two groups of first quick-release load interfaces 40, the four-rotor unmanned aerial vehicle comprises four arms 10, each arm 10 is provided with a propeller 20 and a motor 21 for driving the propeller 20 to rotate, the motor 21 is fixed on the arm 10 through a motor seat 22, the propeller 20 is fixedly connected with the rotating shaft of the motor 21, each arm 10 extends outward to form an arm extension segment 11, the arm extension segment 11 can be used as a support part during take-off and landing, and an antenna box 12 is installed at the end of the arm extension segment 11. The bottom of the four-rotor unmanned aerial vehicle is provided with a battery compartment 31, a pluggable battery 30 is installed in the battery compartment 31, and an LED lamp 32 is installed at the bottom of the battery compartment 31 and can be used for light show performance.

[0057] The difference between the rotor unmanned aerial vehicle general load platform in the embodiment of the present application and the rotor unmanned aerial vehicle general load platform in the first embodiment is that the two groups of quick-release load interfaces are both first quick-release load interfaces 40.

[0058] The rotor unmanned aerial vehicle general load platform in the embodiment of the present application is provided with four downward loads through two groups of four first quick-release load interfaces 40 around the fuselage of the four-rotor unmanned aerial vehicle.

[0059] The application also provides a take-off and landing method of the rotor unmanned aerial vehicle general load platform, which is used for controlling the take-off and landing of the rotor unmanned aerial vehicle general load platform in any one of the first embodiment to the fifth embodiment. Figure 19 As shown in the figure, the take-off and landing method of the rotor unmanned aerial vehicle general load platform comprises steps S1 to S5.

[0060] S1, open the aircraft box, and unfold the storable legs on the upper and lower surfaces of the aircraft box to build a take-off and landing platform on the ground.

[0061] As shown in the figure, Figure 18 The aircraft box 100 adopts a 2-part split design, comprising an upper box body and a lower box body, and the upper box body top surface and the lower box body bottom surface are both provided with storable legs 101, and the upper box body and the lower box body are both provided with a plurality of hollow areas 102, and the hollow areas 102 are provided with a machine arm extension section accommodating groove 103 around, and the machine arm extension section accommodating groove 103 is provided with a clamping groove 104.

[0062] When the rotor unmanned aerial vehicle general load platform is to take off, the aircraft box 100 is opened, and the storable legs 101 on the upper and lower surfaces of the aircraft box 100 (the upper box body top surface and the lower box body bottom surface) are unfolded, so that the aircraft box 100 forms a higher height difference with the ground, thereby building a take-off and landing platform on the ground for the rotor unmanned aerial vehicle general load platform.

[0063] S2, place the four-rotor unmanned aerial vehicle with the mounted load in the hollow area of the aircraft box, and place the machine arm extension section of the four-rotor unmanned aerial vehicle in the machine arm extension section accommodating groove of the aircraft box.

[0064] Place the four-rotor unmanned aerial vehicle with the mounted load in the hollow area 102 of the aircraft box 100, and place the machine arm extension section of the four-rotor unmanned aerial vehicle in the machine arm extension section accommodating groove 103 of the aircraft box 100, and support the four-rotor unmanned aerial vehicle in the hollow area 102 through the support of the machine arm extension section, so that the four-rotor unmanned aerial vehicle is hung in the hollow area 102, and due to the height difference between the aircraft box 100 and the ground, even if the four-rotor unmanned aerial vehicle is installed with a lower load with a longer height, such as fireworks, it can also ensure that the load will not contact the ground.

[0065] S3, execute the take-off command to control the four-rotor unmanned aerial vehicle to take off.

[0066] S4, execute the landing command to control the four-rotor unmanned aerial vehicle to fall into the hollow area of the aircraft box, and control the machine arm extension section of the four-rotor unmanned aerial vehicle to fall into the machine arm extension section accommodating groove of the aircraft box.

[0067] When landing, the quadcopter is controlled to fall into the hollow area 102 of the aircraft box 100, and the arm extension section of the quadcopter is controlled to fall into the arm extension section accommodating groove 103 of the aircraft box, so that the quadcopter is hung in the hollow area 102 by the support of the arm extension section, and since the height difference between the aircraft box 100 and the ground, even if the quadcopter is installed with a lower load with a relatively high height, such as fireworks, the load can be ensured not to contact the ground.

[0068] S5, unload the load, clamp the arm extension section of the quadcopter into the clamping groove in the arm extension section accommodating groove, and close the aircraft box.

[0069] After the quadcopter landed on the aircraft box 100 is unloaded, the arm extension section of the quadcopter is clamped into the clamping groove 104 in the arm extension section accommodating groove 103, the movement of the aircraft is limited, and the transportation is facilitated.

[0070] The landing and taking-off method of the quadcopter universal load platform provided by the embodiment of the application ensures that the quadcopter universal load platform does not contact the ground when landing and taking off by constructing a landing and taking-off platform, and solves the problem that the quadcopter with a lower load with a relatively high height cannot be stably placed on the ground.

[0071] The above description is only the preferred embodiment of the application, and does not limit the application in any form. Those skilled in the art can make various equivalent changes and improvements on the basis of the above-described embodiments, and any equivalent changes or modifications made within the scope of the claims shall fall within the protection scope of the application.

Claims

1. A general purpose load platform for a rotorcraft unmanned aerial vehicle, characterized by: The rotor unmanned plane general load platform comprises a four-rotor unmanned plane and at least one set of mechanical and electrical integrated quick-release load interface, each set of quick-release load interface comprises two quick-release load interfaces, the two quick-release load interfaces of each set are correspondingly installed on two opposite sides of the fuselage of the four-rotor unmanned plane, the quick-release load interface comprises a quick-release female seat and a quick-release male seat which is detachably connected with the quick-release female seat, the quick-release female seat is fixedly installed on the fuselage of the four-rotor unmanned plane, and the quick-release male seat is detachably connected with a load support. The rotor unmanned plane general load platform comprises two sets of quick-release load interfaces, the two quick-release load interfaces of one set are correspondingly installed on two opposite sides of the fuselage of the four-rotor unmanned plane, and the two quick-release load interfaces of the other set are correspondingly installed on the other two opposite sides of the fuselage of the four-rotor unmanned plane. The two sets of quick-release load interfaces comprise a first set of quick-release load interfaces and a second set of quick-release load interfaces, the first set of quick-release load interfaces comprises a first quick-release female seat, a first quick-release male seat and a first load support, the first quick-release female seat is fixedly installed on the fuselage of the four-rotor unmanned plane, and the first quick-release male seat is detachably connected with the first load support, the first quick-release female seat is provided with a first female seat groove away from one side of the four-rotor unmanned plane, the upper end of the first quick-release male seat is provided with a first male seat protrusion, the first female seat groove is provided with a quick-release female seat circuit connector, the first male seat protrusion is provided with a quick-release male seat circuit connector, the two sides of the first quick-release female seat are provided with female buckles, the upper end of the first quick-release male seat is provided with male buckle clamps, after the first male seat protrusion is connected with the first female seat groove in a matched mode, the quick-release female seat circuit connector in the first female seat groove is electrically connected with the quick-release male seat circuit connector on the first male seat protrusion, and the male buckle clamps are buckled with the female buckles. The first load support is provided with a load support rotating shaft, a compression spring is sleeved on the load support rotating shaft, the first quick-release male seat is provided with a support mounting hole, the support mounting hole is provided with a compression spring limiting step, the load support rotating shaft is fixedly installed with a pin shaft after penetrating through the support mounting hole, and the end of the support mounting hole away from the first load support is provided with a plurality of positioning clamping grooves for the pin shaft.

2. The rotor drone universal load platform of claim 1, wherein: The male buckle clamp is installed on the first quick-release male seat in a mode that the male buckle clamp can rotate around the rotating shaft, and the rotating shaft is provided with a torsional spring for providing a torque for the male buckle clamp to rotate inward.

3. The rotor drone universal load platform of claim 1, wherein: The second quick release load interface comprises a second quick release female seat, a second quick release male seat and a second load support, the second quick release female seat is fixedly installed on the body of the quadrotor, and the first quick release male seat and the second load support are detachably connected; a second female seat groove is formed in the upper end of the second quick release female seat, a second male seat protrusion is arranged at the lower end of the second quick release male seat, a quick release female seat circuit connector is arranged in the second female seat groove, a quick release male seat circuit connector is arranged on the second male seat protrusion, a buckle column is arranged on the side of the second quick release female seat away from the quadrotor, a deformable C-shaped buckle is arranged on the side of the second quick release male seat away from the quadrotor, after the second male seat protrusion is connected with the second female seat groove, the quick release female seat circuit connector in the second female seat groove is electrically connected with the quick release male seat circuit connector on the second male seat protrusion, and the C-shaped buckle is matched with the buckle column.

4. The rotor drone universal load platform of claim 3, wherein: The second load support is detachably connected with the second quick release male seat through a hand screw knob.

5. The rotor drone universal load platform of any one of claims 1-4, wherein: The bottom of the body of the quadrotor is provided with a battery compartment, a pluggable battery is arranged in the battery compartment, an LED lamp is arranged at the bottom of the battery compartment, two first quick release load interfaces of the first quick release load interface group are arranged on two sides of the body of the quadrotor, which are parallel to the plugging direction of the battery, and two second quick release load interfaces of the second quick release load interface group are arranged on two sides of the body of the quadrotor, which are perpendicular to the plugging direction of the battery.

6. The rotor drone universal load platform of claim 5, wherein: The quadrotor comprises four arms, each arm is provided with a paddle, and each arm is outwardly extended to form an arm extension segment, and an antenna box is arranged at the end of the arm extension segment.

7. A method for controlling the take-off and landing of a rotorcraft universal load platform as claimed in any one of claims 1 to 5, characterized in that: The quadrotor of the general load platform of the rotor unmanned aerial vehicle is outwardly extended to form an arm extension segment, and the take-off and landing method of the general load platform of the rotor unmanned aerial vehicle comprises the following steps: Open the aircraft box, and unfold the storable supporting legs on the upper and lower sides of the aircraft box to build a take-off and landing platform on the ground; Place the quadrotor with the mounted load in the hollow area of the aircraft box, and place the arm extension segment of the quadrotor in the arm extension segment accommodating groove of the aircraft box; Execute a take-off command to control the quadrotor to take off; Execute a landing command to control the quadrotor to fall into the hollow area of the aircraft box, and control the arm extension segment of the quadrotor to fall into the arm extension segment accommodating groove of the aircraft box; Unload the load, and clamp the arm extension segment of the quadrotor into the clamping groove in the arm extension segment accommodating groove, and close the aircraft box.

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