22-axis vertical take-off and landing aircraft and control method thereof

Abstract

The invention discloses a twenty-two-axis vertical take-off and landing aircraft and a control method thereof. The twenty-two-axis vertical take-off and landing aircraft mainly comprises a parachute bag, a cabin and a power device. The twenty-two shafts comprise ten propellers, eight rotating shafts and four movable wings which are powered by independent power devices. The attitude, the position, the speed, the height and the course parameters of the aircraft are set on a computer according to the use requirements, and the attitude, the position, the speed, the height and the course parameters of the aircraft are calculated through sensors installed on twenty-two axes and an inertial reference system / attitude course reference system, an atmospheric data system, a global navigation satellite system, a course assisting and correcting system, a radio altimeter and an atmospheric temperature sensor in a cabin. A computer carries out data fusion and sends instruction signals to a power device for controlling ten propellers, eight rotating shafts and four movable wings, so that state control of the aircraft is realized, flight environment safety is intelligently diagnosed, and risk early warning and active avoidance are provided.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to a 22-axis vertical takeoff and landing aircraft and its control method. Background Technology

[0002] Most existing general-purpose helicopters still use the traditional single-rotor configuration with a tail rotor, but they are constantly being optimized in details, such as expanding the manufacturing materials to composite materials, introducing ducted design for the tail rotor, developing intelligent avionics and flight control systems, and adopting diversified power plants to adapt to market demands.

[0003] Among the existing general-purpose helicopter technologies mentioned above, their large size, high noise, high manufacturing difficulty, complex operation, high requirements for pilots, high purchase cost, high maintenance cost, limited parking area, and poor maneuverability make them unsuitable for widespread application. Summary of the Invention

[0004] The purpose of this invention is to provide a 22-axis vertical takeoff and landing aircraft and its control method to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a 22-axis vertical takeoff and landing aircraft, comprising a parachute, a cabin, and a power unit. The power unit includes a first fixed base, on which four sets of support columns are fixedly connected. A second fixed base is fixedly connected to the upper part of the support columns. A pair of parallel dual engines with dual generators is fixedly connected to one side of the first fixed base. The power ends of the parallel dual engines with dual generators penetrate the second fixed base and are fixedly connected to concentric dual shafts. Two sets of first propellers are fixedly connected to the outer sides of the concentric dual shafts. Fixed rods are evenly distributed and fixedly connected around the second fixed base. A first... The system comprises a rotating shaft, with a second rotating shaft rotatably connected to the outer side of the first rotating shaft. One end of the second rotating shaft is fixedly connected to a connecting rod, and the other end of the connecting rod is fixedly connected to a mirror-arranged dual motor. The power ends of the mirror-arranged dual motors are respectively fixedly connected to two sets of second propellers. Support seats are fixedly connected to both sides below the fixed rods, and movable wings are rotatably connected between the two sets of support seats on the same side. Drive motors are evenly fixedly connected to the four sides below the second fixed seat. The power ends of the four sets of drive motors are fixedly connected to the movable wings. The four sets of first and second rotating shafts, two sets of first propellers, eight sets of second propellers, and four sets of movable wings constitute twenty-two shafts.

[0006] Preferably, the two sets of first propellers rotate in opposite directions, and the eight sets of second propellers rotate in opposite directions.

[0007] Preferably, a first fairing is fixedly connected to the upper outer side of the fixed rod, the first fairing is sleeved on the outside of the first propeller, and a second fairing is fixedly connected to the outside of the connecting rod, the second fairing is sleeved on the outside of the second propeller.

[0008] Preferably, a docking base is fixedly connected to the top of the cabin, the docking base is fixedly connected to the first fixed seat, observation windows are provided at the front and rear of the cabin, cabin doors and mounting holes are provided on the left and right sides of the cabin, an energy box and electric drive wheels are provided at the bottom of the cabin, and a spraying device, a cleaning device, a lifting device, an impact device, a passage device, a lighting device and a honeycomb device are provided inside the cabin.

[0009] Preferably, the spraying device includes a storage tank located inside the cabin, with a first connecting pipe fixedly connected to one side of the storage tank, and a nozzle fixedly connected to the first connecting pipe through a hole; the cleaning device includes a cleaning brush, with a second connecting pipe fixedly connected to one end of the cleaning brush, and the other end of the second connecting pipe fixedly connected to a hole; the lifting device includes a crane located inside the cabin, with a third connecting pipe fixedly connected to one side of the crane, and a pulley fixedly connected to the third connecting pipe through a hole, a safety rope being fitted around the pulley, with one end of the safety rope fixedly connected to the crane, and the other end of the safety rope fixedly connected to the pulley. The device includes a lifebuoy fixedly connected to one end; the impact device includes a motor, which is located inside the cabin, with a fourth connecting pipe at one end and a hole fixedly connected to the other end of the fourth connecting pipe; an impact hammer is fixedly connected to the power end of the motor; the passage device includes a telescopic passage, with one end fixedly connected to a door, and a slide rail fitted inside the telescopic passage; the lighting device includes a lamp, with a fifth connecting pipe fixedly connected to one end of the lamp and a hole fixedly connected to the other end of the fifth connecting pipe; the honeycomb device includes a honeycomb box, which is located inside the cabin, and an electrode slide rail is fixedly connected to each cell of the honeycomb box.

[0010] A control method for a 22-axis vertical takeoff and landing aircraft, wherein the energy tank provides fuel energy for two parallel engines equipped with two generators, and provides electrical energy for the 22 axes, the power unit of the electric drive wheels, various sensors and computers;

[0011] Sensors are distributed on the twenty-two axes. The sensors are used to detect the rise and fall of the first propeller at the center position, and the rise, fall, forward, backward, left, right and rotation of the first rotating axis, the second rotating axis, the second propeller and the movable wing around the perimeter. The attitude, position, speed, altitude and heading parameters of the aircraft are set on the computer according to the usage requirements.

[0012] The aircraft's status is controlled by a computer that integrates data from sensors mounted on the 22 axes and the inertial reference system / attitude and heading reference system, atmospheric data system, global navigation satellite system, heading assist and correction system, radio altimeter, and atmospheric temperature sensor. The computer then sends command signals to the power units that control the first rotating axis, the second rotating axis, the second propeller, and the movable wing.

[0013] Preferably, the power generated by the parallel dual engines and dual generators is used to first satisfy the power needs of each electrical device, and the surplus power can be used to supplement the power of the batteries in the energy box, all of which is controlled by a computer.

[0014] Preferably, the energy box provides electrical energy to the spraying device, cleaning device, lifting device, impact device, passage device, lighting device, and honeycomb device.

[0015] Compared with the prior art, the beneficial effects of the present invention are:

[0016] 1. This invention supports three control modes: manual, intelligent, and remote. It combines multi-sensor data fusion with computer intelligent control, eliminating the need for complex training for professional drivers. Ordinary people can operate it with simple guidance, lowering the barrier to entry and making driving easy.

[0017] 2. This invention also reduces the rotational speed of a single propeller through a multi-axis distributed power design, avoiding the high-decibel noise generated by the high-speed rotation of a traditional single rotor. It can operate in noise-sensitive areas such as residential areas, hospitals, and schools, with strong environmental compatibility, low noise, and wide applicability.

[0018] 3. The present invention also features 22 axes driven by independent power units, combined with anti-rotation and anti-torque design, each propeller, rotating shaft and movable wing can be independently controlled, the aircraft can flexibly complete multi-directional movements such as take-off, landing, forward and backward, left and right, and rotation, the maneuverability and flexibility are greatly improved compared with traditional helicopters, and the maneuverability and flexibility are high. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0020] Figure 2 This is a top view of the power unit of a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0021] Figure 3 This is a bottom view of the power unit of a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0022] Figure 4 This is a schematic diagram of the cockpit of a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0023] Figure 5This is a schematic diagram of a jet device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0024] Figure 6 This is a schematic diagram of a cleaning device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0025] Figure 7 This is a schematic diagram of a lifting device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0026] Figure 8 This is a schematic diagram of an impact device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0027] Figure 9 This is a schematic diagram of a channel device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0028] Figure 10 This is a schematic diagram of a lighting device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0029] Figure 11 This is a schematic diagram of a honeycomb device for a 22-axis vertical takeoff and landing aircraft according to the present invention;

[0030] Figure 12 This is a partial attitude diagram of a 22-axis vertical take-off and landing aircraft according to the present invention.

[0031] In the diagram: 1. Parachute pack; 2. Support column; 3. Second mounting base; 4. Side-by-side dual engines with dual generators; 5. Concentric dual shafts; 6. First propeller; 7. Mounting rod; 8. First fairing; 9. First rotating shaft; 10. Second rotating shaft; 11. Connecting rod; 12. Mirror-arranged dual motors; 13. Second propeller; 14. Support base; 15. Movable wing; 16. Drive motor; 17. Second fairing; 18. First mounting base; 19. Window; 20. Power tank; 21. Door ; 22. Electric drive wheel; 23. Hole; 24. Hull; 25. Docking base; 26. Storage box; 27. First connecting pipe; 28. Nozzle; 29. ​​Second connecting pipe; 30. Cleaning brush; 31. Crane; 32. Third connecting pipe; 33. Pulley; 34. Safety rope; 35. Life ring; 36. Fourth connecting pipe; 37. Motor; 38. Impact hammer; 39. Slide rail; 40. Telescopic passage; 41. Light; 42. Fourth connecting pipe; 43. Electrode slide rail; 44. Honeycomb box. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Please see Figure 1-12 This invention provides a technical solution: a 22-axis vertical takeoff and landing aircraft, including a parachute pack 1, a cabin 24, and a power unit. The power unit includes a first fixed base 18, with four sets of support columns 2 bolted to the upper part of the first fixed base 18. A second fixed base 3 is bolted to the upper part of the support columns 2. A pair of parallel dual engines with dual generators 4 are bolted to one side of the first fixed base 18. The power ends of the parallel dual engines with dual generators 4 penetrate the second fixed base 3 and are fixedly connected to concentric dual shafts 5 via couplings. Two sets of first propellers 6 are bolted to the outer side of the concentric dual shafts 5 to provide main lift. Fixed rods 7 are evenly distributed around the second fixed base 3 and fixedly connected by welding. A first rotating shaft 9 is rotatably connected to the outer side of the fixed rods 7 via bearings. A second rotating shaft 10 is rotatably connected to the outer side of the first rotating shaft 9 via bearings. One end of the second rotating shaft 10 is fixedly connected to a connecting rod 11 by welding. The other end of the connecting rod 11 is fixedly connected to a mirror-arranged dual motor 12 by bolts. The power ends of the mirror-arranged dual motor 12 are fixedly connected to two sets of second propellers 13 by couplings. Support seats 14 are fixedly connected to both sides below the fixed rod 7 by bolts. Movable wings 15 are rotatably connected between the two sets of support seats 14 on the same side via bearings. Drive motors 16 are evenly fixedly connected to the four sides below the second fixed seat 3 by bolts. The power ends of the four sets of drive motors 16 are fixedly connected to the movable wings 15 by couplings. The four sets of first rotating shafts 9 and second rotating shafts 10, two sets of first propellers 6, eight sets of second propellers 13, and four sets of movable wings 15 constitute twenty-two shafts.

[0034] The two sets of first propellers 6 rotate in opposite directions, and the eight sets of second propellers 13 rotate in opposite directions; the opposite rotation eliminates torque.

[0035] The upper side of the fixed rod 7 is fixedly connected to the first fairing 8 by bolts. The first fairing 8 is sleeved on the outside of the first propeller 6. The outer side of the connecting rod 11 is fixedly connected to the second fairing 17 by bolts. The second fairing 17 is sleeved on the outside of the second propeller 13.

[0036] The bottom of the cabin 24 is fixedly connected to the docking base 25 by bolts. The docking base 25 is fixedly connected to the first fixed seat 18 by bolts. The cabin 24 has a circular streamlined structure. The cabin 24 is provided with observation windows 19 at the front and rear. The cabin 24 is provided with doors 21 and mounting holes 23 on the left and right sides. The bottom of the cabin 24 is fixedly connected to the energy box 20 and electric drive wheels 22 by bolts. The cabin 24 is equipped with a spray device, a cleaning device, a lifting device, an impact device, a passage device, a lighting device, and a honeycomb device.

[0037] The spraying device includes a storage tank 26, which is placed inside the cabin 24. A first connecting pipe 27 is fixedly connected to one side of the storage tank 26 by bolts. A nozzle 28 is fixedly connected to the first connecting pipe 27 through a hole 23 by bolts. It is used for spraying water, spraying pesticides, spraying rain enhancers, and aerial refueling.

[0038] The cleaning device includes a cleaning brush 30, one end of which is fixedly connected to a second connecting pipe 29 by bolts, and the other end of the second connecting pipe 29 is fixedly connected to a hole 23 by bolts. It is used for cleaning photovoltaic power stations and urban buildings.

[0039] The lifting device includes a crane 31, which is placed inside the cabin 24. A third connecting pipe 32 is fixedly connected to one side of the crane 31 by bolts. A pulley 33 is fixedly connected to the third connecting pipe 32 through a hole 23 by bolts. A safety rope 34 is fitted on the outside of the pulley 33. One end of the safety rope 34 is fixedly connected to the crane 31 by bolts. A life ring 35 is fixedly connected to the other end of the safety rope 34 for water rescue.

[0040] The impact device includes a motor 37, which is placed inside the cabin 24. One end of the motor 37 is connected to a fourth connecting pipe 36 by bolts, and the other end of the fourth connecting pipe 36 is fixedly connected to the hole 23 by bolts. The power end of the motor 37 is fixedly connected to an impact hammer 38 by a coupling for high-altitude de-icing.

[0041] The access device includes a telescopic channel 40, one end of which is fixed to the door 21 by bolts. The telescopic channel 40 is fitted with a slide rail 39 inside, which is used for emergency rescue in high-rise buildings and as a maintenance platform for high-altitude facilities.

[0042] The lighting device includes a lamp 41, one end of which is fixedly connected to a fifth connecting pipe 42 by bolts, and the other end of the fifth connecting pipe 42 is fixedly connected to a hole 23 by bolts, for use as rescue lighting;

[0043] The cellular device includes a cellular box 44, which is placed inside the cabin 24. Each cell in the cellular box 44 is fixedly connected to an electrode rail 43 by bolts for charging and directional guidance of the drone.

[0044] A control method for a 22-axis vertical takeoff and landing (VTOL) aircraft: An energy tank 20 provides fuel energy to the parallel twin engines equipped with twin generators 4. The energy tank 20 also provides power to the first rotating shaft 9, the second rotating shaft 10, the second propeller 13, the movable wing 15, functional devices, the electric drive wheel 22, various sensors, and a computer. Sensors are distributed along the 22 axes. These sensors detect the ascent and descent of the first propeller 6 at the center position, and the ascent, descent, forward, backward, left, right, and rotation of the surrounding first rotating shaft 9, second rotating shaft 10, second propeller 13, and movable wing 15. Flight parameters are set on the computer according to usage requirements. The attitude, position, speed, altitude, and heading parameters of the aircraft are fused by a computer through sensors installed on the 22 axes and an inertial reference system / attitude and heading reference system, an atmospheric data system, a global navigation satellite system, a heading assist and correction system, a radio altimeter, and an atmospheric temperature sensor inside the cabin 24. The computer then sends command signals to the power unit that controls the first rotating shaft 9, the second rotating shaft 10, the second propeller 13, and the movable wing 15 to achieve state control of the aircraft. The aircraft can be manually controlled, intelligently controlled, or remotely controlled. At the same time, the aircraft can intelligently diagnose flight environment safety and provide risk warnings and active avoidance.

[0045] The power generated by the parallel dual engines and dual generators 4 is prioritized to meet the power needs of each electrical device. The surplus power can be used to supplement the battery in the energy box 20. All of this is controlled by a computer.

[0046] The energy tank 20 provides electrical energy for the spraying device, cleaning device, lifting device, impact device, passage device, lighting device and honeycomb device.

[0047] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0048] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A 22-axis vertical takeoff and landing aircraft, comprising a parachute pack (1), a cabin (24), and a power unit, characterized in that: The power unit includes a first fixed base (18), with four sets of support columns (2) fixedly connected to the upper part of the first fixed base (18). A second fixed base (3) is fixedly connected to the upper part of the support columns (2). A pair of parallel dual engines with dual generators (4) is fixedly connected to one side of the first fixed base (18). The power end of the pair of parallel dual engines with dual generators (4) penetrates the second fixed base (3) and is fixedly connected to a concentric dual shaft (5). Two sets of first propellers (6) are fixedly connected to the outside of the concentric dual shafts (5). Fixed rods (7) are evenly distributed and fixedly connected around the second fixed base (3). A first rotating shaft (9) is rotatably connected to the outside of the fixed rods (7). A second rotating shaft (10) is rotatably connected to the outside of the first rotating shaft (9). (10) One end is fixedly connected to a connecting rod (11), and the other end of the connecting rod (11) is fixedly connected to a mirror-arranged dual motor (12). The power end of the mirror-arranged dual motor (12) is fixedly connected to two sets of second propellers (13). The two sides below the fixed rod (7) are fixedly connected to support seats (14). The two sets of support seats (14) on the same side are rotatably connected to movable wings (15). The four sides below the second fixed seat (3) are evenly fixedly connected to drive motors (16). The power ends of the four sets of drive motors (16) are fixedly connected to the movable wings (15). The four sets of first rotating shafts (9) and second rotating shafts (10), two sets of first propellers (6), eight sets of second propellers (13), and four sets of movable wings (15) constitute twenty-two axes.

2. A 22-axis vertical takeoff and landing aircraft according to claim 1, characterized in that: The two sets of first propellers (6) rotate in opposite directions, and the eight sets of second propellers (13) rotate in opposite directions.

3. A 22-axis vertical takeoff and landing aircraft according to claim 1, characterized in that: The first fairing (8) is fixedly connected to the upper side of the fixed rod (7). The first fairing (8) is sleeved on the outside of the first propeller (6). The second fairing (17) is fixedly connected to the outside of the connecting rod (11). The second fairing (17) is sleeved on the outside of the second propeller (13).

4. A 22-axis vertical takeoff and landing aircraft according to claim 1, characterized in that: The top of the cabin (24) is fixedly connected to a docking base (25), which is fixedly connected to a first fixed seat (18). The cabin (24) has observation windows (19) at the front and rear. The cabin (24) has doors (21) and mounting holes (23) on the left and right sides. The bottom of the cabin (24) is equipped with an energy box (20) and electric drive wheels (22). The cabin (24) is equipped with a spraying device, a cleaning device, a lifting device, an impact device, a passage device, a lighting device, and a honeycomb device.

5. A 22-axis vertical takeoff and landing aircraft according to claim 4, characterized in that: The spraying device includes a storage tank (26) placed inside the cabin (24). A first connecting pipe (27) is fixedly connected to one side of the storage tank (26), and a nozzle (28) is fixedly connected to the first connecting pipe (27) through a hole (23). The cleaning device includes a cleaning brush (30). A second connecting pipe (29) is fixedly connected to one end of the cleaning brush (30), and the other end of the second connecting pipe (29) is fixedly connected to the hole (23). The lifting device includes a crane (31) placed inside the cabin (24). A third connecting pipe (32) is fixedly connected to one side of the crane (31). A pulley (33) is fixedly connected to the third connecting pipe (32) through a hole (23). A safety rope (34) is fitted around the pulley (33). One end of the safety rope (34) is fixedly connected to the crane (31), and the other end of the safety rope (34) is fixedly connected to the crane (31). The end is fixedly connected to a life ring (35); the impact device includes a motor (37), which is placed inside the cabin (24), one end of the motor (37) has a fourth connecting pipe (36), the other end of the fourth connecting pipe (36) is fixedly connected to a hole (23), and the power end of the motor (37) is fixedly connected to an impact hammer (38); the passage device includes a telescopic passage (40), one end of the telescopic passage (40) is fixedly connected to a door (21), and a slide rail (39) is sleeved inside the telescopic passage (40); the lighting device includes a lamp (41), one end of the lamp (41) is fixedly connected to a fifth connecting pipe (42), and the other end of the fifth connecting pipe (42) is fixedly connected to a hole (23); the honeycomb device includes a honeycomb box (44), which is placed inside the cabin (24), and each honeycomb box (44) has an electrode slide rail (43) fixedly connected inside each honeycomb cell.

6. A control method for a 22-axis vertical takeoff and landing aircraft according to any one of claims 1-5, characterized in that: The energy box (20) provides fuel energy for the parallel dual engines equipped with dual generators (4), and the energy box (20) provides electrical energy for the power unit of the twenty-two shafts, electric drive wheels (22), sensors, and computers; Sensors are distributed on the twenty-two axes. The sensors are used to detect the rise and fall of the first propeller (6) at the center position, and the rise, fall, forward, backward, left, right and rotation of the first rotating shaft (9), the second rotating shaft (10), the second propeller (13) and the movable wing (15) around it. According to the usage requirements, the attitude, position, speed, altitude and heading parameters of the aircraft are set on the computer. The computer performs data fusion through the sensors installed on the twenty-two axes and the inertial reference system / attitude and heading reference system, atmospheric data system, global navigation satellite system, heading assistance and correction system, radio altimeter and atmospheric temperature sensor in the cabin (24), and sends command signals to the power unit that controls the first rotating axis (9), the second rotating axis (10), the second propeller (13) and the movable wing (15) to realize the state control of the aircraft.

7. The control method for a 22-axis vertical takeoff and landing aircraft according to claim 6, characterized in that: The power generated by the parallel dual engines and dual generators (4) is used to meet the needs of each electrical device first. The surplus power can be used to supplement the battery in the energy box (20). All of this is controlled by a computer.

8. The control method for a 22-axis vertical takeoff and landing aircraft according to claim 6, characterized in that: The energy box (20) provides electrical energy for the spraying device, cleaning device, lifting device, impact device, passage device, lighting device and honeycomb device.

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