Multifunctional flying platform with A-plane and B-plane flying capabilities and control method

Abstract

The present invention relates to a multifunctional flight platform with A-side and B-side flight capabilities and a control method, using a multifunctional flight platform with A-side and B-side flight capabilities; the control method is specifically as follows: before the flight, the flight mode selection switch is used to select the flight to take off in the A-side or B-side mode of the body according to the mission requirements, and when the flight mode is changed, the current positive and negative pole converter is controlled by the flight mode selection switch to control the power system to rotate forward or reverse. The current positive and negative pole converter of the mode selection device of the present invention is connected to the power system of the aircraft, and the power system of the aircraft is controlled to rotate forward and reverse by changing the current direction, so that the aircraft can take off in the A-side or B-side mode of the body, or adjust from the A-side of the body to the B-side mode of the body to fly, or adjust from the B-side of the body to the A-side mode of the body to fly, thereby completing different types of work task requirements and meeting the all-round, multi-angle, and three-dimensional one-machine multi-purpose use needs.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a multifunctional flying platform with A-plane and B-plane flying capabilities and a control method thereof. Background Art

[0002] Drones are now widely used in all walks of life and bring new ideas to the development of all walks of life. The drone systems currently in use are all single-person single-machine or special-purpose models, and have not truly achieved multi-purpose or even multi-purpose use. Although the existing drone system can improve the efficiency of the original pure manual work, it has limitations. The original mode is only point-to-point, and face-to-face problem solving does not consider solving problems from a three-dimensional perspective. To this end, the present invention proposes a mother-and-child multi-purpose drone flight platform with A and B-side flight capabilities. Summary of the invention

[0003] The present invention aims to solve the above-mentioned problems and proposes a multi-rotor functional mother UAV flight platform with the ability to fly on both A and B sides. When flying normally with the A side facing upward, multiple sub-machines can be placed on the belly. In the mission area, the sub-machines can take off and land in the belly of the mother machine, and the mother machine can be linked to realize multi-machine operations. When flying with the B side facing upward, the lifting platform can be hung on large equipment or placed on cargo. The present invention realizes the multi-purpose use of unmanned aerial vehicles through the concept of multi-purpose and multi-angle, providing new ideas for the development of the UAV industry.

[0004] The technical solution of the present invention is:

[0005] The present invention provides a multifunctional flying platform with A-plane and B-plane flying capabilities.

[0006] A multifunctional flying platform with A-side and B-side flying capability comprises an unmanned mother aircraft, wherein the unmanned mother aircraft comprises an aircraft and an intelligent control system; the aircraft body comprises an A-side and a B-side; the intelligent control system comprises a mode selection device, wherein the mode selection device is arranged on the side of the aircraft body; the mode selection device comprises a current positive and negative electrode converter and a flight mode selection switch connected to each other; and the current positive and negative electrode converter is linked to the power system of the aircraft.

[0007] The intelligent control system also includes a central control system and a monitoring device, and the mode selection device and the monitoring device are both connected to the central control system; the monitoring device includes a signal transceiver and a positioning device, a gyroscope, an acceleration sensor, a barometer and a wind speed sensor respectively connected to the signal transceiver, and the signal transceiver is connected to the central control system; wherein the positioning device and the signal transceiver are arranged on the aircraft arm; the gyroscope, the acceleration sensor and the barometer are arranged inside the aircraft body; and the wind speed sensor is arranged on the A surface of the body.

[0008] The device also includes a remote control device, which is connected to the signal transceiver.

[0009] The body A side is provided with a folding cover, and the belly opening of the body A side is provided with a carrying platform, and the carrying platform has a built-in lifting and stopping platform; the lifting and stopping platform is provided with a sub-machine; the body A side is also provided with a first expansion platform; the first expansion platform is provided with monitoring equipment; the body B side is also provided with a second expansion platform; the folding cover, power system, lifting and stopping platform, the first expansion platform and the second expansion platform are all connected to the central control system.

[0010] The four corners of the aircraft body are provided with telescopic tripods.

[0011] The power system is a motor, the number of which is greater than 1; the motor is a rainproof motor and is provided with a rotor.

[0012] The folding cover is a two-stage opening and closing folding cover.

[0013] There are 4 lifting platforms, and each lifting platform is equipped with a sub-machine.

[0014] The present invention provides a control method for a multi-rotor functional mother-type UAV with A-plane and B-plane flight capabilities.

[0015] A control method for a multi-rotor functional mother UAV with A-side and B-side flight capabilities uses the multifunctional flight platform with A-side and B-side flight capabilities as described above; the control method is specifically as follows: before flight, the flight mode selection switch is used to select flight takeoff in the A-side or B-side mode according to mission requirements. When changing the flight mode, the current positive and negative pole converter is controlled by the flight mode selection switch to control the forward or reverse rotation of the power system.

[0016] The technical effects of the present invention are:

[0017] 1. The current positive and negative converter of the mode selection device of the present invention is connected to the power system of the aircraft, and controls the forward and reverse rotation of the power system of the aircraft by changing the current direction, so that the aircraft can take off in the body A surface or body B surface mode, or adjust from the body A surface to the body B surface mode or adjust from the body B surface to the body A surface mode, so as to complete the requirements of different types of work tasks, and meet the needs of all-round, multi-angle and three-dimensional one-machine multi-purpose use;

[0018] 2. The present invention controls the attitude of the aircraft through a positioning device, a gyroscope, an acceleration sensor and a barometer to monitor the aircraft's safe and rapid arrival at the mission location, and uses a wind speed sensor to detect whether the environment in which the aircraft is located allows the folding cover to be opened to complete the aerial take-off and landing operation;

[0019] 3. The aircraft is also equipped with a first expansion platform on the A side of the fuselage and a second expansion platform on the B side of the fuselage to achieve all-round and multi-angle processing mission requirements;

[0020] 4. The sub-machine carried on the aircraft can work in coordination with the mother drone to achieve multi-tasking. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of the multifunctional flying platform with A-plane and B-plane flying capabilities of the present invention.

[0022] Figure 2 This is a front view of the multifunctional flying platform with A-side and B-side flying capability of the present invention, with the A-side of the body facing upward.

[0023] Figure 3 It is a top view of the multifunctional flying platform with A-side and B-side flying capability with the A-side of the body facing upward.

[0024] Figure 4 This is a front view of the multifunctional flying platform with A- and B-side flying capabilities of the present invention with the B-side of the body facing upward.

[0025] Figure 5 It is a top view of the multifunctional flying platform with A- and B-plane flying capability with the B-plane of the body facing upward.

[0026] Figure 6 It is a system connection diagram of the multifunctional flying platform with A-plane and B-plane flying capabilities of the present invention.

[0027] Figure numerals: 1. aircraft; 2. folding cover; 3. carrying platform; 4. first lifting platform; 5. second lifting platform; 6. third lifting platform; 7. fourth lifting platform; 8. first expansion platform; 9. second expansion platform; 10. telescopic tripod; 11. positioning device; 12. signal transceiver; 13. wind speed sensor; 14. motor; 15. rotor; 16. flight mode selection switch. DETAILED DESCRIPTION

[0028] Example 1

[0029] A multifunctional flying platform with A- and B-surface flying capabilities comprises an unmanned mother aircraft, wherein the unmanned mother aircraft comprises an aircraft 1 and an intelligent control system; the body of the aircraft 1 comprises a body A-surface and a body B-surface; the intelligent control system comprises a mode selection device, which is arranged on the side of the fuselage of the aircraft 1; the mode selection device comprises a current positive and negative converter and a flight mode selection switch 16 connected to each other; the current positive and negative converter is linked to the power system of the aircraft 1.

[0030] The specific implementation process of this embodiment is as follows:

[0031] The current positive and negative pole converter of the mode selection device of the present invention is connected to the power system of the aircraft 1, and controls the forward and reverse rotation of the power system of the aircraft 1 by changing the current direction, so that the aircraft 1 can take off in the body A surface mode or the body B surface mode, or adjust from the body A surface to the body B surface mode for flight, or adjust from the body B surface to the body A surface mode for flight, thereby completing the requirements of different types of work tasks and achieving the needs of all-round, multi-angle, and three-dimensional multi-purpose use of one machine.

[0032] Example 2

[0033] On the basis of Example 1, it also includes:

[0034] The intelligent control system also includes a central control system and a monitoring device, and the mode selection device and the monitoring device are both connected to the central control system; the monitoring device includes a signal transceiver 12 and a positioning device 11, a gyroscope, an acceleration sensor, a barometer and a wind speed sensor 13 respectively connected to the signal transceiver 12, and the signal transceiver 12 is connected to the central control system; wherein the positioning device 11 and the signal transceiver 12 are arranged on the arm of the aircraft 1; the gyroscope, the acceleration sensor and the barometer are arranged inside the body of the aircraft 1; and the wind speed sensor 13 is arranged on the A surface of the body.

[0035] Example 3

[0036] On the basis of Example 2, the invention further comprises:

[0037] It also includes a remote control device, which is connected to the signal transceiver 12 and is a handheld remote control device.

[0038] Example 4

[0039] On the basis of Example 3, the invention further includes:

[0040] The body A is provided with a folding cover 2, and a carrying platform 3 is provided at the opening of the belly of the body A. The carrying platform 3 has a built-in lifting platform; a sub-machine is provided on the lifting platform; the body A is also provided with a first expansion platform 8; the first expansion platform 8 is provided with a monitoring device; the body B is also provided with a second expansion platform 9. The folding cover 2, the power system, the lifting platform, the first expansion platform 8 and the second expansion platform 9 are all connected to the central control system. The four corners of the body of the aircraft 1 are provided with a telescopic tripod 10. The power system is a motor 14, the number of motors 14 is greater than 1; the motor 14 is a rainproof motor 14 and is provided with a rotor 15. The folding cover 2 is a two-stage opening and closing folding cover 2. There are 4 lifting platforms, namely the first lifting platform 4, the second lifting platform 5, the third lifting platform 6 and the fourth lifting platform 7, each of which is provided with a sub-machine.

[0041] The specific implementation process of this embodiment is as follows:

[0042] The unmanned mother aircraft includes an aircraft 1 and an intelligent control system. Before the flight, the flight mode selection switch 16 is used to select the aircraft 1 to take off in the A-plane or B-plane mode according to the mission requirements. The positive and negative current converter is connected to the power system of the aircraft 1, and the power system of the aircraft 1 is controlled to rotate forward and reverse by changing the current direction. After that, the gyroscope monitors the real-time posture of the aircraft 1, and the real-time posture is judged by the central control system whether the posture of the aircraft 1 is consistent with the preset mode. The task instruction is sent through the remote control device. After the signal transceiver device receives the task instruction, the central control system allocates the motor 14 to drive the rotor 15 to rotate so that the aircraft 1 is lifted off to the mission area. After that, the positioning device 11, the gyroscope, the acceleration sensor and the barometer work together to monitor the position and flight attitude of the aircraft 1 in real time. The real-time monitoring data is uploaded to the central control system, and the central control system corrects the navigation at any time and allocates the motor 14 to make the aircraft 1 arrive at the mission area safely and efficiently.

[0043] 1. Aircraft body A side flight mode

[0044] After arriving at the mission area in the body A-surface flight mode, the wind speed sensor 13 monitors the external wind speed of the aircraft 1 in real time, and the central control system determines whether the aerial take-off and landing operation of the sub-machine is allowed to be completed, and transmits the judgment result back to the remote control device through the signal transceiver device. The remote control device can also send a mission instruction to the signal transceiver device to command the central control system whether to perform the aerial take-off and landing operation. After allowing the aerial take-off and landing operation, the central control system controls the folding cover 2 to open automatically, and then controls the lifting platform to rise to the outside of the belly of the aircraft to complete the launch of the sub-machine. After that, the central control system controls the lifting platform to descend to the belly of the aircraft and close the folding cover 2. During the mission flight, the central control system controls the first expansion platform 8 and the second expansion platform 9 to operate the carried equipment according to the preloaded mission. The central control system can also send a mission instruction to the signal transceiver 12 through the remote control device to instruct the central control system to complete the operation of the first expansion platform 8 and the second expansion platform 9;

[0045] After the mission is completed, the sub-machine can automatically return to the area where the unmanned mother machine is located according to the mission settings. At this time, the monitoring device will monitor the real-time posture of the aircraft 1 in real time, and then the central control system will control the aircraft 1 to hover in the air. The wind speed sensor 13 monitors the external wind speed and uploads it to the central control system. The central control system determines whether to open the folding cover 2 to allow the sub-machine to land. When landing, the central control system controls the folding cover 2 to open, and the lifting platform is raised to complete the recovery of the sub-machine. After that, the central control system controls the lifting platform to retract and the folding cover 2 to close to complete the recovery of the sub-machine. When the conditions for landing in the air are not met, the remote control device can send a command to the sub-machine to remotely land by itself.

[0046] 2. Aircraft B side flight mode

[0047] After arriving at the mission area in the B-side flight mode of the fuselage, the central control system controls the first expansion platform 8 and the second expansion platform 9 to operate the carried equipment according to the preset mission, and at the same time controls the lifting platform to hoist the equipment or deliver the cargo. The remote control device can also send a mission instruction to the signal transceiver 12 to command the central control system to complete the control operation of the first expansion platform 8, the second expansion platform 9, the folding cover 2 and the carrying platform 3.

Claims

1. A multifunctional flying platform with A-plane and B-plane flying capabilities, comprising an unmanned mother aircraft, wherein the unmanned mother aircraft comprises an aircraft (1) and an intelligent control system; characterized in that: The body of the aircraft (1) comprises a body A surface and a body B surface; the intelligent control system comprises a mode selection device, which is arranged on the side of the body of the aircraft (1); the mode selection device comprises a current positive and negative polarity converter and a flight mode selection switch (16) connected to each other; the current positive and negative polarity converter is connected to the power system of the aircraft (1); The intelligent control system further comprises a central control system and a monitoring device, wherein the mode selection device and the monitoring device are both connected to the central control system; the monitoring device comprises a signal transceiver (12) and a positioning device (11), a gyroscope, an acceleration sensor, a barometer and a wind speed sensor (13) respectively connected to the signal transceiver (12), and the signal transceiver (12) is connected to the central control system; wherein the positioning device (11) and the signal transceiver (12) are arranged on the arm of the aircraft (1); the gyroscope, the acceleration sensor and the barometer are arranged in the body of the aircraft (1); and the wind speed sensor (13) is arranged on the A surface of the body; It also includes a remote control device, which is connected to the signal transceiver (12); The machine body A side is provided with a folding cover (2), the machine body A side is provided with a carrying platform (3) at the opening of the machine belly, the carrying platform (3) is provided with a lifting platform; the lifting platform is provided with a submachine; the machine body A side is also provided with a first expansion platform (8); the first expansion platform (8) is provided with a monitoring device; the machine body B side is also provided with a second expansion platform (9); the folding cover (2), the power system, the lifting platform, the first expansion platform (8) and the second expansion platform (9) are all connected to the central control system; Among them, the flight mode of the A side of the aircraft is: After arriving at the mission area in the A-plane flight mode, the wind speed sensor (13) monitors the wind speed outside the aircraft (1) in real time, and the central control system determines whether to allow the completion of the aerial take-off and landing operation of the sub-machine, and transmits the judgment result back to the remote control device through the signal transceiver (12), or sends a mission instruction to the signal transceiver (12) through the remote control device to command the central control system whether to perform the aerial take-off and landing operation; after allowing the aerial take-off and landing operation, the central control system controls the folding cover (2) to open automatically, and then controls the lifting platform to rise to the outside of the belly of the aircraft to complete the flight of the sub-machine, and then the central control system controls the lifting platform to descend to the belly of the aircraft and close the folding cover (2); during the mission flight, the central control system controls the first expansion platform (8) and the second expansion platform (9) to operate the equipment carried by them according to the pre-loaded mission, or sends a mission instruction to the signal transceiver (12) through the remote control device to instruct the central control system to complete the operation of the first expansion platform (8) and the second expansion platform (9); After the mission is completed, the sub-machine can automatically return to the area where the unmanned mother machine is located according to the mission settings. At this time, the monitoring device will monitor the real-time posture of the aircraft (1) in real time, and then the central control system will control the aircraft (1) to hover in the air. The wind speed sensor (13) monitors the external wind speed and uploads it to the central control system. The central control system determines whether to open the folding cover (2) to allow the sub-machine to land. When landing, the central control system controls the folding cover (2) to open, and the lifting platform is raised to complete the recovery of the sub-machine. After that, the central control system controls the lifting platform to retract and the folding cover (2) to close to complete the recovery of the sub-machine; when the conditions for landing in the air are not met, the remote control device sends a command to the sub-machine to remotely land automatically; The flight modes of the B side of the aircraft are: After arriving at the mission area in the B-side flight mode of the aircraft body, the central control system controls the first expansion platform (8) and the second expansion platform (9) to operate the equipment carried thereon according to the preset mission, and at the same time controls the lifting platform to hoist equipment or drop cargo, or sends a mission instruction to the signal transceiver (12) through the remote control device to command the central control system to complete the control operation of the first expansion platform (8), the second expansion platform (9), the folding cover (2) and the carrying platform (3).

2. The multifunctional flying platform with A-plane and B-plane flying capability according to claim 1, characterized in that: Telescopic tripods (10) are provided at the four corners of the aircraft (1).

3. The multifunctional flying platform with A-plane and B-plane flying capability according to claim 2, characterized in that: The power system is a motor (14), the number of the motor (14) is greater than 1; the motor (14) is a rainproof motor (14) and is provided with a rotor (15).

4. The multifunctional flying platform with A-plane and B-plane flying capability according to claim 3, characterized in that: The folding cover (2) is a two-stage opening and closing folding cover (2).

5. The multifunctional flying platform with A-plane and B-plane flying capability according to claim 4, characterized in that: There are 4 lifting platforms, and each lifting platform is equipped with a sub-machine.

6. A control method for a multi-rotor functional mother drone with A-plane and B-plane flight capabilities, characterized in that: A multifunctional flying platform with A-side and B-side flying capability as described in claim 1 is used; the control method is as follows: before flight, the flight mode selection switch (16) is used to select the take-off mode in the A-side or B-side mode according to the mission requirements; when changing the flight mode, the current positive and negative pole converter is controlled by the flight mode selection switch (16) to control the forward or reverse rotation of the power system.

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