A manned aircraft

Abstract

The application discloses a manned aircraft and relates to the technical field of aircrafts, which comprises a body, a plurality of machine arms, a plurality of servo motors, a plurality of rotor mechanisms and a parachute mechanism one. The body is cylindrical and has a parachute mounting chamber one near the upper end of the body. One end of the plurality of machine arms is connected to the outer peripheral wall of the body and is arranged around the outer periphery of the body. The other end of the plurality of machine arms is provided with the plurality of servo motors. The rotation shafts of the plurality of servo motors are perpendicular to the body axial direction and are parallel to each other. The fixed end of the plurality of rotor mechanisms is fixed on the rotation shaft of the plurality of servo motors one by one. The rotation shaft of each rotor mechanism is perpendicular to the rotation shaft of the corresponding servo motor. The rotation shaft of each rotor mechanism is provided with a rotor. The plurality of rotors are symmetrically arranged relative to the body axial line. The parachute mechanism one is arranged in the parachute mounting chamber one. The cabin is connected to the lower part of the body. The application can make the cabin fly horizontally to ensure the riding comfort of the passengers and has reliable parachute safety guarantee function.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a manned aircraft. Background Technology

[0002] With technological advancements, lightweight manned aircraft have become more portable, efficient, and safe. The multi-rotor aircraft currently popular on the market maintain a tilted fuselage during forward flight, acceleration, and turns. This is achieved by adjusting the rotational speeds of different rotors to create thrust differences, causing the fuselage to tilt and decompose the horizontal component of rotor thrust as forward propulsion. This tilted flight configuration can cause discomfort for pilots and passengers, potentially leading to motion sickness, which hinders the widespread adoption of manned aircraft. Furthermore, a crucial technical challenge for the widespread adoption of manned aircraft is safety. Whether meeting travel needs or addressing rescue operations in complex environments such as cities, mountains, and forests, as well as performing special missions, safety is paramount.

[0003] For example, the safety measures of the EHang EH216-S manned aircraft mainly include real-time monitoring and dynamic scheduling; it has 8 axes and up to 16 rotors, and through a multi-backup design concept, even if some rotors fail, the others can still provide lift and thrust to ensure safe and stable flight; it is unmanned, with all operations during flight controlled by the ground command and dispatch system, reducing the risk of human error; it has an automatic obstacle avoidance function during flight, which can automatically adjust the flight path when encountering obstacles to ensure safety; in addition, flight safety is ensured through redundancy in the control system, sensors, and battery system. However, it is still not equipped with a parachute safety structure to cope with major system failures.

[0004] Therefore, how to design a manned aircraft that can achieve level flight to ensure passenger comfort and has reliable parachute safety features is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, the present invention proposes a manned aircraft, which aims to solve the technical problems of poor passenger comfort and lack of reliable parachute protection function in traditional light manned aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] This invention provides a manned aircraft, comprising:

[0008] The body is cylindrical and has a parachute mounting chamber near the upper opening of the cylindrical cavity.

[0009] Multiple robotic arms, one end of which is connected to the outer peripheral wall of the machine body and arranged around the outer periphery of the machine body; the other end of each of the multiple robotic arms is equipped with a servo motor; the rotation shafts of the multiple servo motors are perpendicular to the axis of the machine body and parallel to each other;

[0010] Multiple rotor mechanisms, with their fixed ends fixed one-to-one on the rotating shafts of multiple servo motors; the rotating shaft of each rotor mechanism is perpendicular to the rotating shaft of the corresponding servo motor; each rotor mechanism has a rotor mounted on its rotating shaft, and the multiple rotors are arranged symmetrically with respect to the axis of the fuselage.

[0011] Parachute mechanism one, wherein parachute mechanism one is disposed in parachute installation chamber one;

[0012] The cabin, the upper part of which is connected to the lower part of the fuselage.

[0013] In a manned aircraft according to the present invention, during flight, a servo motor drives the rotor mechanism to rotate. The servo motor can flexibly adjust the rotation axis of the corresponding rotor mechanism to be vertical, tilted, or horizontal, thereby changing the rotor orientation. When the rotor mechanism's rotation axis is vertical, the rotor can drive the entire aircraft to ascend and descend; when the rotor mechanism's rotation axis is tilted, the horizontal component of the rotor thrust can be used as forward or turning power; with a constant rotor speed, as the tilt angle of the rotor mechanism's rotation axis increases, the rotor thrust will increase. In other words, during flight, the manned aircraft of the present invention can both generate thrust differences by adjusting the rotation speeds of different rotors through conventional control methods, causing the fuselage to tilt and using the horizontal component of the rotor thrust as forward or turning power, and can also drive the corresponding rotor mechanism to rotate via a servo motor to adjust the orientation of multiple rotors, thereby adjusting the propulsion direction and speed. The present invention uses rotor orientation adjustment to control aircraft flight, ensuring the cabin does not tilt and maintains a level flight state, thus better guaranteeing passenger comfort. The present invention arranges the cabin below the fuselage and sets the parachute mechanism on the upper part of the fuselage. In the event of a dangerous situation and loss of control of the aircraft, the parachute mechanism will be activated to ensure the overall slow descent of the aircraft, thereby ensuring the safety of the aircraft and its passengers.

[0014] As a further improvement to the above technical solution, the parachute mechanism includes a parachute pack, a spring, and a launch cover. The launch cover is located at the upper end of the body. The parachute pack is placed inside the parachute mounting chamber, and one end of the parachute ropes of the parachute pack is fixed to the body. The spring is installed at the bottom of the parachute mounting chamber and its upper end abuts against the lower end of the parachute pack, thereby causing the parachute pack to press against the lower surface of the launch cover and ejecting the parachute pack to the outside of the parachute mounting chamber when the launch cover is opened.

[0015] The beneficial effects of the above technical solution are: by controlling the opening of the launch cover, the first parachute pack can be released; after the launch cover is opened, the spring can eject the first parachute pack out of the first parachute installation chamber; after the first parachute pack is opened, the aircraft body can be suspended by its parachute lines, thereby ensuring the overall slow descent of the aircraft and ensuring reliable safety.

[0016] As a further improvement to the above technical solution, a control room for arranging the battery pack and flight control board is located below the parachute mounting chamber inside the body; a partition is fixed between the parachute mounting chamber and the control room inside the body; the lower end of the spring abuts against the upper surface of the partition.

[0017] The beneficial effects of the above technical solution are: the partition can isolate the battery pack in the control room from the parachute pack in the parachute installation room, preventing the parachute pack from being damaged or rendered ineffective due to fire or explosion of the battery pack, and ensuring that the start-up cover can still be opened to release the parachute pack after the battery pack is at high temperature, fire or explosion.

[0018] As a further improvement to the above technical solution, the parachute mechanism one also includes an electrically controlled pin one, and the start cover is coaxially inserted into the upper end cylinder opening of the body; the electrically controlled pin one is installed on the upper outer peripheral wall of the body, and the telescopic pin end of the electrically controlled pin one can sequentially penetrate the upper outer peripheral wall of the body and the outer peripheral wall of the start cover to lock the two.

[0019] The beneficial effects of the above technical solution are: the opening of the start cover is controlled by the electronically controlled pin, which is safer and more reliable; when the electronically controlled pin is opened, the spring ejects and pushes the parachute pack, which will push open the start cover and be ejected to the outside.

[0020] As a further improvement to the above technical solution, a second parachute mechanism is also included; the second parachute mechanism includes a second parachute pack and a strap fixed to one end of the parachute ropes of the second parachute pack for passengers to wear.

[0021] An escape tube is vertically fixed to the upper part of the cabin; the upper part of the escape tube is coaxially and detachably connected to the lower part of the fuselage; a seat is provided inside the cabin below the escape tube; the lower end of the escape tube connects to the interior of the cabin to form an escape passage.

[0022] The body's cylindrical cavity contains a second parachute mounting chamber below the control room; a second partition is fixed between the second parachute mounting chamber and the control room within the body; the second parachute pack is placed in the second parachute mounting chamber, and the shoulder straps correspond to the seat arrangement.

[0023] The beneficial effects of the above technical solution are as follows: In order to further ensure the safety of passengers, the escape tube is designed to be separable from the aircraft body. After the escape tube is separated from the aircraft body, the second parachute pack in the second parachute installation chamber is released. The second parachute pack can pull the passengers wearing harnesses through the escape tube and escape from the cabin by the parachute lines. After the second parachute pack is opened, it can protect the safety of passengers independently, and the safety of passengers is better guaranteed.

[0024] As a further improvement to the above technical solution, the second parachute mechanism also includes a second electrically controlled pin; the upper end of the escape tube is adapted to be nested and inserted into the lower end of the body; the second electrically controlled pin is installed on the outer peripheral wall of the lower end of the body, and the telescopic pin end of the second electrically controlled pin can pass through the body wall and the escape tube wall in sequence to lock the two; the lower end of the second parachute pack abuts against the upper end of the escape tube.

[0025] The beneficial effects of the above technical solution are: the separation of the escape tube from the body is controlled by the electronically controlled pin 2, making it safer and more reliable.

[0026] As a further improvement to the above technical solution, one end of the parachute line of the second parachute pack is fixed with a hanging ring, and an automatic release device is fixed to the top of the cabin; the hanging ring can be detachably hooked onto the automatic release device so that one end of the parachute line of the second parachute pack is connected to the cabin.

[0027] The beneficial effects of the above technical solution are: when the hanging hook is connected to the automatic release device, after the second parachute pack is released, the cabin and the personnel inside can be suspended by the parachute ropes and descend slowly together.

[0028] As a further improvement to the above technical solution, an inflatable airbag is fixedly installed on the lower part of the outer wall of the cabin, and an air pump and an internal battery are provided inside the cabin; the internal battery is electrically connected to the air pump to provide power; the air outlet of the air pump is connected to the inflatable airbag through a pipeline to inflate it.

[0029] The beneficial effects of the above technical solution are: when the aircraft malfunctions and encounters danger above the water, the cabin can be suspended by parachute pack 2, and the airbags can be inflated by an air pump. The inflated airbags can play a role in cushioning and providing buoyancy, so as to ensure that the cabin can be safely suspended on the water, thereby ensuring the safety of the passengers and buying more time for rescue.

[0030] As a further improvement to the above technical solution, the number of robotic arms is four or more.

[0031] The beneficial effects of the above technical solution are: four or more arms can improve the safety and stability of flight; and can ensure sufficient power for manned aircraft, making flight more stable.

[0032] As a further improvement to the above technical solution, the rotor mechanism includes a motor mounting base, an upper rotor motor, and a lower rotor motor; the motor mounting base is fixed in the middle on the rotating shaft of the corresponding servo motor; the upper rotor motor and the lower rotor motor are symmetrically mounted on the upper and lower ends of the motor mounting base; the rotation axes of the upper rotor motor and the lower rotor motor are both perpendicular to the rotating shaft of the corresponding servo motor; rotors are mounted on the rotation axes of the upper rotor motor and the lower rotor motor.

[0033] The beneficial effects of the above technical solution are: each rotor mechanism is equipped with two rotors, which further improves the power and safety performance.

[0034] As can be seen from the above technical solution, compared with the prior art, the present invention discloses a manned aircraft with the following advantages and beneficial effects:

[0035] 1. The multiple rotor mechanisms of the present invention can be rotated individually to adjust the tilt attitude of the rotation axis. By coordinating and controlling the spatial attitude of the rotation axis of multiple rotor mechanisms, the thrust direction of multiple rotors can be controlled, and the forward movement, turning, acceleration and deceleration of the aircraft can be controlled while ensuring the cabin is in level flight, thereby ensuring the comfort of passengers.

[0036] 2. This invention designs a dual-parachute safety structure, which allows for flexible selection of parachute mechanism one and parachute mechanism two based on the actual conditions around the fault location, flight altitude, and weather conditions. Parachute mechanism one ensures the safety of the fuselage, arms, and rotor mechanism, reducing accident losses. If parachute mechanism one cannot guarantee the safety of the passengers, parachute mechanism two can effectively ensure their safety. In the event of an emergency landing on water, parachute mechanism two can suspend the cabin and inflate the airbags at the bottom of the cabin, transforming the cabin into a support vessel to maximize passenger safety. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0038] Figure 1 A schematic diagram of the fuselage and cabin internal structure of a manned aircraft according to the present invention;

[0039] Figure 2 A three-dimensional schematic diagram of the overall structure of a manned aircraft according to the present invention;

[0040] Figure 3Another perspective three-dimensional schematic diagram of the overall structure of a manned aircraft according to the present invention;

[0041] Figure 4 A top view schematic diagram of the overall structure of a manned aircraft according to the present invention;

[0042] Figure 5 A side view of the overall structure of a manned aircraft according to the present invention;

[0043] Figure 6 A front view schematic diagram of the overall structure of a manned aircraft according to the present invention;

[0044] Figure 7 A schematic diagram of the spring release state of a manned aircraft according to the present invention;

[0045] Figure 8 A schematic diagram of the spring compression state of a manned aircraft according to the present invention;

[0046] In the diagram: 1. Aircraft body; 11. Parachute installation compartment one; 12. Control room; 13. Partition one; 14. Parachute installation compartment two; 15. Partition two; 2. Arm; 21. Servo motor; 3. Rotor mechanism; 31. Motor mounting base; 32. Upper rotor motor; 33. Lower rotor motor; 34. Rotor; 4. Parachute mechanism one; 41. Parachute pack one; 42. Spring; 43. Start-up cover; 44. Electrical control pin one; 5. Cabin; 51. Escape tube; 52. Seat; 53. Inflatable airbag; 54. Inflator pump; 55. Internal battery; 6. Parachute mechanism two; 61. Parachute pack two; 62. Shoulder strap; 63. Electrical control pin two; 7. Passengers. Detailed Implementation

[0047] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0048] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0049] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0050] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0051] According to embodiments of the present invention, such as Figures 1 to 8 As shown, a manned aircraft includes: a fuselage 1, multiple arms 2, multiple rotor mechanisms 3, a parachute mechanism 4, and a cabin 5.

[0052] The fuselage 1 is cylindrical and has a parachute installation chamber 11 near the upper opening of the cylinder.

[0053] One end of each of the multiple robotic arms 2 is connected to the outer wall of the body 1 and is arranged around the outer periphery of the body 1; the other end of each of the multiple robotic arms 2 is equipped with a servo motor 21; the rotation shafts of the multiple servo motors 21 are perpendicular to the axis of the body 1 and parallel to each other.

[0054] The fixed ends of multiple rotor mechanisms 3 are fixed one-to-one on the rotating shafts of multiple servo motors 21; the rotating shaft of each rotor mechanism 3 is perpendicular to the rotating shaft of the corresponding servo motor 21; each rotor mechanism 3 has a rotor 34 mounted on its rotating shaft, and the multiple rotors 34 are arranged symmetrically with respect to the axis of the body 1.

[0055] Parachute mechanism 4 is located in parachute installation chamber 11. The upper part of cabin 5 is connected to the lower part of fuselage 1.

[0056] In this embodiment, a manned aircraft can drive the rotor mechanism 3 to rotate via a servo motor 21 during flight. The servo motor 21 can flexibly adjust the rotation axis of the corresponding rotor mechanism 3 to be vertical, tilted, or horizontal, thereby changing the orientation of the rotors 34. When the rotation axis of the rotor mechanism 3 is vertical, the rotors 34 can drive the entire aircraft to ascend and descend. When the rotation axis of the rotor mechanism 3 is tilted, the horizontal component of the rotor thrust can be used as forward or turning power. With the rotor speed remaining constant, the thrust of the rotor 34 will increase as the tilt angle of the rotor axis of the rotor mechanism 3 increases. In other words, during flight, the manned aircraft of this invention can both generate thrust differences by adjusting the rotation speed of different rotors 34 through conventional control methods, causing the fuselage to tilt and using the horizontal component of the rotor thrust as forward or turning power, and drive the corresponding rotor mechanism 3 to rotate via the servo motor 21 to adjust the orientation of multiple rotors 34, thereby adjusting the propulsion direction and speed. This invention controls the aircraft's flight by adjusting the orientation of the rotor 34, ensuring that the cabin 5 remains level and does not tilt, thus better guaranteeing the comfort of passengers. The cabin 5 is positioned below the fuselage 1, and the parachute mechanism 4 is located on the upper part of the fuselage 1. In the event of a dangerous situation and loss of control, the parachute mechanism 4 activates, ensuring a gentle descent of the entire aircraft and thus protecting the safety of the aircraft and its passengers.

[0057] In some embodiments, the parachute mechanism 4 includes a parachute pack 41, a spring 42, and an activation cover 43. The activation cover 43 is located at the upper end of the body 1. The parachute pack 41 is placed inside the parachute mounting chamber 11, and one end of the parachute rope of the parachute pack 41 is fixed to the body 1. The spring 42 is installed at the bottom of the parachute mounting chamber 11, and its upper end abuts against the lower end of the parachute pack 41, thereby pressing the parachute pack 41 against the lower surface of the activation cover 43, and ejecting the parachute pack 41 to the outside of the parachute mounting chamber 11 when the activation cover 43 is opened.

[0058] By controlling the opening of the launch cover 43, the parachute pack 41 can be released. After the launch cover 43 is opened, the spring 42 can eject the parachute pack 41 out of the parachute installation chamber 11. After the parachute pack 41 is opened, the aircraft body 1 can be suspended by its parachute lines, thereby ensuring the overall slow descent of the aircraft and ensuring reliable safety.

[0059] In some embodiments, the middle part of the cavity of the body 1 corresponds to the lower part of the parachute mounting chamber 11 as the control chamber 12 for arranging the battery pack and flight control board; a partition 13 is fixed between the parachute mounting chamber 11 and the control chamber 12 inside the body 1; the lower end of the spring 42 abuts against the upper surface of the partition 13.

[0060] The partition 13 can isolate the battery pack in the control room 12 from the parachute pack 41 in the parachute installation room 11, preventing the parachute pack 41 from being damaged or rendered ineffective due to fire or explosion of the battery pack, and ensuring that the launch cover 43 can still be opened to release the parachute pack 41 after the battery pack is at high temperature, fire or explosion.

[0061] In some embodiments, the parachute mechanism 4 further includes an electrically controlled pin 44, and the start cover 43 is coaxially inserted into the upper end of the cylinder opening of the body 1; the electrically controlled pin 44 is installed on the upper outer peripheral wall of the body 1, and the telescopic pin end of the electrically controlled pin 44 can pass through the upper outer peripheral wall of the body 1 and the outer peripheral wall of the start cover 43 in sequence to lock the two.

[0062] The opening of the start cover 43 is controlled by the electronically controlled pin 44, which is safer and more reliable. When the electronically controlled pin 44 is opened, the spring 42 ejects and pushes the parachute pack 41, which will push open the start cover 43 and be ejected to the outside.

[0063] Specifically, the control room 12 houses a battery pack and a flight control board. The battery pack serves as the aircraft's power source and is electrically connected to the flight control board for power supply. The flight control board is electrically connected to the servo motor 21, the rotor mechanism 3, and the electronically controlled pin 44 for control. The flight control board monitors the aircraft's flight status. In the event of flight loss of control, the flight control board can control the electronically controlled pin 44 to release the launch cover 43, thereby releasing the parachute pack 41. The cabin 5 is equipped with an emergency remote controller, which is wirelessly connected to the flight control board. In an emergency, the emergency remote controller can also control the electronically controlled pin 44 to release the launch cover 43, thereby releasing the parachute pack 41, allowing passengers to control the parachute mechanism 4 independently.

[0064] Specifically, spring 42 is a conical helical spring that can be compressed into a planar structure after being flattened.

[0065] In some embodiments, a second parachute mechanism 6 is also included; the second parachute mechanism 6 includes a second parachute pack 61 and a strap 62 fixed to one end of the parachute ropes of the second parachute pack 61 for the passenger 7 to wear.

[0066] An escape tube 51 is vertically fixed to the upper part of the cabin 5; the upper part of the escape tube 51 is coaxial and detachably connected to the lower part of the body 1 through a pin mechanism; a seat 52 is provided in the cabin 5 below the escape tube 51; the lower end of the escape tube 51 is connected to the interior of the cabin 5 to form an escape passage.

[0067] Inside the cylindrical cavity of the fuselage 1, below the control room 12, is a parachute installation chamber 2 14; inside the fuselage 1, a partition 2 15 is fixed between the parachute installation chamber 2 14 and the control room 12; the parachute pack 2 61 is placed in the parachute installation chamber 2 14, and the shoulder strap 62 is arranged corresponding to the seat 52.

[0068] To further ensure the safety of passengers, the escape tube 51 is designed to be separable from the fuselage 1. After the escape tube 51 is separated from the fuselage 1, the parachute pack 2 61 in the parachute installation compartment 2 14 is released. The parachute pack 2 61 can pull passengers wearing harnesses 62 through the escape tube 51 and escape from the cabin 5 by the parachute lines. After the parachute pack 2 61 is opened, it can protect the safety of passengers independently, and the safety of passengers is better guaranteed.

[0069] Specifically, the flight control board is electrically connected to the latch mechanism for switching control. In the event of flight loss of control, the flight control board can control the latch mechanism to separate the escape tube 51 from the fuselage 1, thereby releasing the second parachute pack 61. Passengers can also control the switching action of the latch mechanism via the emergency remote control inside the cabin 5.

[0070] In some embodiments, the parachute mechanism 26 further includes an electrically controlled pin 263; the upper end of the escape tube 51 is adapted to be nested and inserted into the bottom of the body 1 from the lower end of the tube opening; the electrically controlled pin 263 is installed on the lower outer peripheral wall of the body 1, and the telescopic pin end of the electrically controlled pin 263 can pass through the tube wall of the body 1 and the tube wall of the escape tube 51 in sequence to lock the two; the lower end of the parachute pack 261 abuts against the upper end of the escape tube 51.

[0071] The latch mechanism uses an electrically controlled latch 263, which controls the separation of the escape tube 51 from the body 1, making it safer and more reliable.

[0072] Specifically, the flight control board is electrically connected to the electronic control pin 263 to control its switching action.

[0073] In some embodiments, a hanging loop is fixed to one end of the parachute line of the second parachute pack 61, and an automatic release device is fixed to the top of the cabin 5; the hanging loop can be detachably hooked onto the automatic release device so that one end of the parachute line of the second parachute pack 61 is connected to the cabin 5.

[0074] With the hook engaged with the automatic release mechanism, after the parachute pack 261 is released, the cabin 5 and its occupants can be suspended by the parachute lines for a gentle descent. Activating the automatic release mechanism releases the hook. The automatic release mechanism is a readily available product.

[0075] Specifically, the lanyard is secured to one end of the parachute lines of parachute pack 261 via a connecting rope; a rope cutter or rope cutter is provided inside the cabin 5; if necessary, the connecting rope can be directly cut to allow parachute pack 261 to detach from cabin 5, and the rope cutter or rope cutter can also be used to cut the parachute lines of parachute pack 261.

[0076] In some embodiments, there are multiple electrically controlled pins 44 and 63; the multiple electrically controlled pins 44 and 63 are evenly distributed around the outer peripheral wall of the body 1; the number of electrically controlled pins 44 and 63 is preferably two or three.

[0077] A pin controller is also fixedly installed on the outer perimeter of fuselage 1. The pin controller includes a backup battery for powering the switching of electronically controlled pins 44 and 63, and a control board for remotely controlling the switching of electronically controlled pins 44 and 63. The backup battery is electrically connected to the control board for power, and the control board is electrically connected to electronically controlled pins 44 and 63 to control their switching actions. The control board is wirelessly connected to an emergency remote controller, allowing passengers in cabin 5 to send pin switch signals to the control board via the emergency remote controller, thereby remotely controlling the switching actions of electronically controlled pins 44 and / or 63. The backup battery can be charged via solar panels attached to the outer perimeter of fuselage 1. The control board is electrically connected to the flight control board, which monitors the battery's charge status. Cabin 5 is equipped with a display and control panel to monitor the aircraft's flight and overall operational status. The flight control board is wirelessly connected to the ground command and dispatch center control system to provide real-time feedback on the operating status. The ground command and dispatch center control system can also remotely control the aircraft, further improving flight safety.

[0078] In some embodiments, an inflatable airbag 53 is fixedly installed on the lower part of the outer wall of the cabin 5, and an air pump 54 and an in-cabin battery 55 are provided inside the cabin 5; the in-cabin battery 55 is electrically connected to the air pump 54 to provide power; the air outlet of the air pump 54 is connected to the inflatable airbag 53 through a pipeline to inflate it.

[0079] When the aircraft malfunctions and encounters danger above the water, the cabin 5 can be suspended by parachute pack 261, and the airbag 53 can be inflated by air pump 54. The inflated airbag 53 can act as a buffer and provide buoyancy to ensure that the cabin 5 can be safely suspended on the water, thereby ensuring the safety of the passengers and buying more time for rescue.

[0080] Specifically, the in-cabin battery 55 is electrically connected to the displays, control panels and automatic uncoupling device in the engine room 5 to provide power.

[0081] In some embodiments, the number of robotic arms 2 is four or more.

[0082] Having four or more arms can improve flight safety and stability; it can ensure sufficient power for manned aircraft and make flight more stable.

[0083] In some embodiments, the rotor mechanism 3 includes a motor mounting base 31, an upper rotor motor 32, and a lower rotor motor 33; the middle part of the motor mounting base 31 is fixed on the rotating shaft of the corresponding servo motor 21; the upper rotor motor 32 and the lower rotor motor 33 are symmetrically mounted on the upper and lower ends of the motor mounting base 31; the rotation axes of the upper rotor motor 32 and the lower rotor motor 33 are both perpendicular to the rotating shaft of the corresponding servo motor 21; rotors 34 are mounted on the rotation axes of the upper rotor motor 32 and the lower rotor motor 33.

[0084] Each rotor mechanism 3 is equipped with two rotors 34, further improving power and safety performance.

[0085] Specifically, this embodiment provides a six-axis twelve-rotor manned aircraft, with its six arms 2 symmetrically arranged on the left and right sides of the fuselage 1 or cabin 5. The rotation shafts of the servo motors 21 installed at the ends of the six arms 2 are all arranged along the left and right direction of the cabin 5. The rotation shafts of the six upper rotor motors 32 and the six lower rotor motors 33 are evenly distributed on the circumference with the center line of the fuselage 1 as the central axis.

[0086] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0087] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A manned aircraft, characterized in that, include: The body (1) is cylindrical and has a parachute mounting chamber (11) near the upper opening of the cylinder cavity; Multiple robotic arms (2), one end of each robotic arm (2) is connected to the outer peripheral wall of the body (1) and is arranged around the outer periphery of the body (1); the other end of each robotic arm (2) is equipped with a servo motor (21); the rotation shafts of each servo motor (21) are perpendicular to the axis of the body (1) and parallel to each other; Multiple rotor mechanisms (3) are provided, and the fixed ends of the multiple rotor mechanisms (3) are fixed one-to-one on the rotating shafts of the multiple servo motors (21); the rotating shaft of each rotor mechanism (3) is perpendicular to the rotating shaft of the corresponding servo motor (21); a rotor (34) is installed on the rotating shaft of each rotor mechanism (3), and the multiple rotors (34) are arranged symmetrically with respect to the axis of the body (1); Parachute mechanism 1 (4) is disposed in the parachute installation chamber 1 (11); Cabin (5), the upper part of which is connected to the lower part of the body (1); The parachute mechanism (4) includes a parachute pack (41), a spring (42), and a start-up cover (43). The start-up cover (43) is installed on the upper end of the body (1). The parachute pack (41) is placed inside the parachute installation chamber (11), and one end of the parachute rope of the parachute pack (41) is fixed to the body (1). The spring (42) is installed at the bottom of the parachute installation chamber (11), and its upper end abuts against the lower end of the parachute pack (41), thereby causing the parachute pack (41) to press against the lower surface of the start-up cover (43), and being able to eject the parachute pack (41) to the outside of the parachute installation chamber (11) when the start-up cover (43) is opened. Inside the cylindrical cavity of the body (1), below the parachute mounting chamber (11), is a control room (12) for arranging the battery pack and flight control board; inside the body (1), a partition (13) is fixed between the parachute mounting chamber (11) and the control room (12); the lower end of the spring (42) abuts against the upper surface of the partition (13); The parachute mechanism (4) further includes an electrically controlled pin (44), and the start cover (43) is coaxially inserted into the upper end of the body (1); the electrically controlled pin (44) is installed on the upper outer peripheral wall of the body (1), and the telescopic pin end of the electrically controlled pin (44) can pass through the upper outer peripheral wall of the body (1) and the outer peripheral wall of the start cover (43) in sequence to lock the two together; It also includes a second parachute mechanism (6); the second parachute mechanism (6) includes a second parachute pack (61) and a strap (62) for passengers to wear, which is fixed to one end of the parachute rope of the second parachute pack (61); An escape tube (51) is vertically fixed at the upper end of the cabin (5); the upper part of the escape tube (51) is coaxially and detachably connected to the lower part of the body (1); a seat (52) is provided inside the cabin (5) corresponding to the lower part of the escape tube (51); the lower end of the escape tube (51) is connected to the interior of the cabin (5) to form an escape passage. The body (1) has a parachute installation chamber two (14) inside the cylindrical cavity corresponding to the control room (12) below it; a partition two (15) is fixed between the parachute installation chamber two (14) and the control room (12) inside the body (1); the parachute pack two (61) is placed in the parachute installation chamber two (14), and the shoulder strap (62) is arranged corresponding to the seat (52); The second parachute mechanism (6) further includes an electrically controlled pin (63); the upper end of the escape tube (51) is adapted to be nested and inserted into the lower end of the body (1); the electrically controlled pin (63) is installed on the lower outer peripheral wall of the body (1), and the telescopic pin end of the electrically controlled pin (63) can pass through the cylinder wall of the body (1) and the cylinder wall of the escape tube (51) in sequence to lock the two; the lower end of the second parachute pack (61) abuts against the upper end of the escape tube (51); One end of the parachute line of the second parachute pack (61) is fixed with a hanging ring, and an automatic release device is fixed on the top of the cabin (5); the hanging ring can be detachably hooked onto the automatic release device so that one end of the parachute line of the second parachute pack (61) is connected to the cabin (5). An inflatable airbag (53) is fixedly installed on the lower part of the outer wall of the cabin (5). An air pump (54) and an in-cabin battery (55) are provided inside the cabin (5). The in-cabin battery (55) is electrically connected to the air pump (54) to supply power. The air outlet of the air pump (54) is connected to the inflatable airbag (53) through a pipeline to inflate it.

2. The manned aircraft according to claim 1, characterized in that, The number of the robotic arms (2) is four or more.

3. The manned aircraft according to claim 1, characterized in that, The rotor mechanism (3) includes a motor mounting base (31), an upper rotor motor (32), and a lower rotor motor (33); the middle part of the motor mounting base (31) is fixed on the rotating shaft of the corresponding servo motor (21); the upper rotor motor (32) and the lower rotor motor (33) are symmetrically mounted on the upper and lower ends of the motor mounting base (31); the rotation axes of the upper rotor motor (32) and the lower rotor motor (33) are both perpendicular to the rotating shaft of the corresponding servo motor (21); rotors (34) are mounted on the rotation axes of the upper rotor motor (32) and the lower rotor motor (33).

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