A load bearing skeleton for a manned multicopter and said multicopter

Abstract

The present application relates to the technical field of manned aircraft, and discloses a carrying framework of a manned multi-rotor aircraft and the aircraft. The carrying framework comprises two first connecting beams arranged symmetrically, a second connecting beam and a third connecting beam arranged between two ends of the two first connecting beams respectively, and a plurality of mounting beams, and first, second and third mounting seats are arranged on the corresponding first connecting beams according to the set angle and position. The rotors loads, the passenger loads and the cabin loads are transmitted to the carrying framework through the arms fixed by the mounting seats, so that the rotors loads, the passenger loads and the cabin loads are dispersed and absorbed by the connecting beams of the carrying framework, the carrying framework is taken as the core of the unified load, the structure of the load-bearing components of the whole aircraft is reduced, and the loads generated by the rotor assemblies are not directly applied to the side walls of the cabin, so that the risk of deformation, cracking or loose connection of the cabin is reduced.

Description

Technical Field

[0001] This invention relates to the field of manned aircraft technology, and in particular to a load-bearing frame for a manned multirotor aircraft and a manned multirotor aircraft having the load-bearing frame. Background Technology

[0002] With the development of applications such as low-altitude economy, urban air traffic, short-distance air travel, and emergency rescue, manned multirotor aircraft are gradually becoming an important type of low-altitude flight equipment. Compared with fixed-wing aircraft, manned multirotor aircraft have the advantages of vertical take-off and landing, low requirements for take-off and landing sites, flexible structural layout, and strong hovering ability, making them suitable for scenarios such as low-altitude commuting, aerial sightseeing, inspection assistance, and emergency transfer.

[0003] Existing multirotor aircraft typically have rotor arms directly fixed to the fuselage shell, center plate, or simple support frame, causing the lift, vibration, and bending moment generated by the rotor power assembly to act directly on the fuselage shell. For manned aircraft, due to the significantly increased overall load, this load-bearing method presents prominent hidden dangers: Firstly, the fuselage shell is not designed as a primary load-bearing component, and long-term exposure to concentrated loads can easily lead to structural fatigue, deformation, or even damage. If the fuselage shell fails due to load-bearing capacity, it will directly endanger the safety of the occupants. Secondly, with rotor arms connected to various parts of the fuselage shell, it is difficult to uniformly control the height deviation between the rotor thrust plane and the aircraft's center of gravity. Excessive deviation will introduce additional pitch or roll moments, increasing the difficulty of flight control and further affecting flight stability and safety.

[0004] Meanwhile, in the existing structural layout, the rotor load-bearing path and the platform load-bearing path are separated, usually requiring separate support frames for the rotor system and the fuselage-crew structure. This separate design leads to redundant load-bearing components and unclear force transmission paths, which not only increases the overall structural weight and hinders lightweight design, but also complicates assembly processes and makes maintenance difficult, making it hard to meet the high integration and high reliability requirements of manned multi-rotor aircraft. Summary of the Invention

[0005] (1) Technical problems to be solved To address the technical problems in existing manned multirotor aircraft, such as poor occupant safety, insufficient flight stability, large structural weight, and complex assembly and maintenance caused by the rotor load acting directly on the fuselage shell and the rotor load path being separate from the platform load path, this invention provides a load-bearing frame for a manned multirotor aircraft and a manned multirotor aircraft having the load-bearing frame.

[0006] (2) Technical solution The first aspect of the present invention provides a load-bearing frame for a manned multi-rotor aircraft, comprising: The base for mounting the cockpit includes four connecting beams: two first connecting beams arranged symmetrically, each with a straight section at one end that is parallel to each other and an inclined section at the other end that is inclined towards each other; a second connecting beam that connects to the free ends of the two inclined sections at both ends; and a third connecting beam that connects to the free ends of the two straight sections at both ends. Each pair consists of three symmetrically arranged mounting seats: one end of the first mounting seat is fixed to one of the two inclined sections, and the other end is also inclined, with the extension lines of the inclined ends intersecting the extension line of the second connecting beam; one end of the second mounting seat is fixed to one of the two straight sections and is close to the bend between the corresponding straight and inclined sections, with the second mounting seat perpendicular to the corresponding straight section; one end of the third mounting seat is fixed to the connection between the third connecting beam and the free ends of the two straight sections, and the other end is inclined away from the third connecting beam; all connecting beams and all mounting seats are located on the same plane; each mounting seat is used to mount one boom; Multiple mounting beams are fixed at both ends to two straight segments and are divided into two evenly distributed groups located on opposite sides of the pair of second mounting seats; the multiple mounting beams are used to jointly mount the seat.

[0007] As a further improvement to the above scheme, the tilt angle u of the inclined section ranges from 15° to 22.5°.

[0008] As a further improvement to the above scheme, the tilt angle of the first mounting base ranges from 30° to 45°.

[0009] As a further improvement to the above scheme, the tilt angle of the tilting section is half the tilt angle of the first mounting base.

[0010] As a further improvement to the above scheme, multiple mounting beams are parallel to each other.

[0011] As a further improvement to the above scheme, the middle part of each mounting beam protrudes downward from the plane, making each mounting beam U-shaped.

[0012] As a further improvement to the above scheme, the ratio of the length of the inclined segment to the length of the straight segment is in the range of 1:1.2 to 1:1.8.

[0013] As a further improvement to the above scheme, the tilt angle of the third mounting base is greater than the tilt angle of the tilt section.

[0014] As a further improvement to the above scheme, the tilt angle of the third mounting base is equal to the tilt angle of the first mounting base.

[0015] As a further improvement to the above scheme, all mounting seats are inserted into the corresponding connecting beams in an interlocking manner.

[0016] As a further improvement to the above scheme, all mounting bases are inserted and fixed on the corresponding connecting beams.

[0017] As a further improvement to the above solution, each mounting base is further secured to the corresponding connecting beam by several fasteners at the position where it is sleeved or plugged into the corresponding connecting beam.

[0018] The second aspect of the present invention provides a manned multi-rotor aircraft, which includes a support frame, a cockpit mounted on the support frame, a seat and multiple arms. The support frame adopts the support frame as described above. The cockpit is mounted on a base, each mounting seat is mounted on an arm, and the seat is mounted on multiple mounting beams.

[0019] As a further improvement to the above scheme, it includes: As described above, the load-bearing frame; The cockpit is covered on the outside of the supporting frame; three pairs of mounting seats with corresponding connection holes are opened on opposite sides of the cockpit, and each mounting seat is set through the corresponding connection hole to fix the cockpit to the supporting frame. The seats are installed in the cabin and are fixedly connected to multiple mounting beams of the load-bearing frame; Multiple arms correspond one-to-one with three pairs of mounting bases. One end of each arm is fitted onto the corresponding mounting base, and the other end is fixedly connected to a rotor assembly.

[0020] As a further improvement to the above scheme, the manned multi-rotor aircraft also includes a power supply module for providing kinetic energy to the aircraft, a flight controller for controlling the adjustment of the aircraft, an electrical control module for cooperating with the power supply module to perform electrical adjustment of the equipment, and a communication module for communicating with the outside world; the power supply module, flight controller, electrical control module and communication module are all located inside the cockpit.

[0021] As a further improvement to the above solution, the rotor assembly includes a mounting structure for connecting the arm, multiple blades for driving the aircraft to fly, and a drive motor for driving the multiple blades to rotate. The multiple blades and the drive motor are all mounted on the mounting structure.

[0022] As a further improvement to the above scheme, the cockpit includes a transparent canopy and an equipment canopy. The transparent canopy is located on one side of the seat, and the equipment canopy is installed at the bottom of the transparent canopy, so that the transparent canopy and the equipment canopy together enclose the external covering structure and occupant protection space of the manned aircraft.

[0023] (3) Beneficial effects 1. This invention employs two symmetrical first connecting beams, each with one end being a straight, parallel segment and the other end an inclined segment facing each other. A second connecting beam connects to the free ends of the two inclined segments, and a third connecting beam connects to the free ends of the two straight segments. Each pair has three symmetrically arranged mounting seats, and all connecting beams and mounting seats are located on the same plane. Therefore, the two first connecting beams, the second connecting beam, and the third connecting beam form a ring-shaped base, which serves as the main load-bearing structure of the load-bearing frame. This improves the bending and torsional stiffness inside the manned multi-rotor aircraft, thus enhancing the overall structural reliability. Each mounting seat, used to fix the arm, transfers the rotor load to the base via the mounting seat. Multiple mounting beams, used to fix the seats, transfer the occupant load to the base via the mounting beams. The cockpit load is directly transferred to the base, ensuring that the rotor load, occupant load, and cockpit load are all distributed and absorbed by the connecting beams of the base. Therefore, the load-bearing frame, as the core of the unified load, not only reduces the structure of the entire aircraft's load-bearing components, but also avoids the load generated by the rotor assembly from acting directly on the side wall of the cockpit, reducing the risk of cockpit deformation, cracking, or loosening of connections. This solves the technical problems in existing manned multi-rotor aircraft, such as poor crew safety, insufficient flight stability, large structural weight, and complex assembly and maintenance, caused by the rotor load acting directly on the fuselage shell and the rotor load path being separated from the platform load path.

[0024] 2. The cockpit of this invention is mainly used for rectification, protection and enclosure, and is not used as a major load-bearing component. Therefore, the cockpit cover can be designed to be lightweight and modular, which facilitates disassembly, maintenance and replacement.

[0025] 3. This invention transfers the load of the seat, cockpit, and rotor assembly to the load-bearing frame in a concentrated manner, making the structure of the manned multi-rotor aircraft simpler and more reliable, and suitable for the safety and maintainability requirements of manned aircraft. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of the aircraft in Embodiment 1 of the present invention; Figure 2 This is a schematic diagram of the load-bearing frame in Embodiment 1 of the present invention; Figure 3 This is a schematic diagram of the cockpit structure in Embodiment 1 of the present invention; Figure 4 This is a schematic diagram of the structure of the support frame with an arm in Embodiment 1 of the present invention.

[0027] Figure Labels 11. Cockpit; 12. Seat; 13. Load-bearing frame; 14. Rotor assembly; 15. Arm; 21. First connecting beam; 22. Second connecting beam; 23. Third connecting beam; 24. First mounting base; 25. Second mounting base; 26. Third mounting base; 27. Mounting beam; 28. Mounting hole; 29. ​​Socket cavity; 31. Transparent canopy; 32. Equipment cover; 33. Connecting hole. Detailed Implementation

[0028] The technical solutions in the embodiments of the present invention will be clearly and completely described below. 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.

[0029] It should be noted that when a component is said to be "installed on" another component, it can be directly on the other component or it may be in a component that is centered on it. When a component is said to be "set on" another component, it can be directly set on the other component or it may also be in a component that is centered on it. When a component is said to be "fixed to" another component, it can be directly fixed to the other component or it may also be in a component that is centered on it.

[0030] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "or / and" as used herein includes any and all combinations of one or more of the associated listed items.

[0031] Example 1 This embodiment introduces a manned multirotor aircraft with an integrated load-bearing frame 13. The load-bearing frame 13 serves as the main load-bearing structure for the rotor, crew, and cockpit 11, allowing the aircraft to maintain a simple structure while improving load-bearing reliability, assembly convenience, and maintenance ease. It is suitable for low-altitude manned flight, short-distance air commuting, aerial sightseeing, and related manned multirotor flight scenarios. The manned multirotor aircraft includes, for example,... Figure 1The shown frame 13, cockpit 11, seat 12, multiple arms 15, and multiple rotor assemblies 14 may also include a power supply module, flight controller, electrical control module, and communication module. The power supply module, flight controller, electrical control module, and communication module are all located inside the cockpit 11 and mounted on the frame 13. The power supply module, such as a battery pack, provides kinetic energy to the aircraft. The flight controller controls the aircraft's adjustments, including flight direction and other structural uses. The electrical control module works in conjunction with the power supply module to perform electrical adjustments for the equipment. The communication module is used for communication with the outside world. The power supply module, flight controller, electrical control module, and communication module are all common components in aircraft and are used as existing technology; their installation methods and working principles are well-known to those in the industry and will not be elaborated upon here.

[0032] The load-bearing frame 13, as the main load-bearing structure, supports the cockpit 11, seat 12, multiple arms 15, and multiple rotor assemblies 14 during flight. The load-bearing frame 13 includes a base, three pairs of mounting bases, and multiple mounting beams 27. The base, as the main load-bearing structure of the load-bearing frame 13, absorbs and distributes the load from the rotors, occupants, and the cockpit 11, thereby increasing the stability of the entire aircraft. The base includes two first connecting beams 21, a second connecting beam 22, and a third connecting beam 23. These four connecting beams are fixedly connected end-to-end, forming a ring-shaped base that serves as the foundation of the load-bearing frame 13. The two first connecting beams 21 are symmetrically arranged, with one end being a straight, parallel section and the other end being an inclined section facing each other. The inclination angle of the inclined sections ranges from 15° to 22.5°, and the ratio of the length of the curved section to the length of the parallel section of each first connecting beam 21 is between 1:1.2 and 1:1.8, allowing the first connecting beams 21 to bear the load more evenly. The second connecting beam 22 is fixedly connected between the ends of the curved sections of the two first connecting beams 21 that are away from their parallel sections, that is, the two ends of the second connecting beam 22 are respectively connected to the free ends of the two inclined sections. The third connecting beam 23 is fixedly connected between the ends of the parallel sections of the two first connecting beams 21 that are away from their curved sections, that is, the two ends of the third connecting beam 23 are respectively connected to the free ends of the two straight sections.

[0033] It should be noted that, in addition, multiple pre-drilled holes are provided on the two first connecting beams 21, the second connecting beam 22, and the third connecting beam 23 in the load-bearing frame 13. This not only reduces the overall weight but also provides multiple types of mounting positions for functional expansion of the entire machine. The load-bearing frame 13 is hollow in the middle, which can provide wiring channels for the aircraft's electrical components and can also be used to fix wiring harnesses, improving assembly efficiency.

[0034] Three pairs of mounting seats are symmetrically arranged on the two first connecting beams 21. The three pairs of mounting seats consist of two first mounting seats 24, two second mounting seats 25, and two third mounting seats 26. Each first connecting beam 21 has one first mounting seat 24, one second mounting seat 25, and one third mounting seat 26 inserted into it for subsequent installation of the rotor assembly 14. All mounting seats on the two first connecting beams 21 are located in the same horizontal plane. In this embodiment, one end of each pair of first mounting seats 24 is fixed to one of the two inclined sections, and the other end is inclined, with the extension lines of the inclined ends intersecting the extension line of the second connecting beam 22. One end of each pair of second mounting seats 25 is fixed to one of the two straight sections, near the bend between the corresponding straight and inclined sections, and the second mounting seat 25 is perpendicular to the corresponding straight section. One end of each pair of third mounting seats 26 is fixed to the connection between the third connecting beam 23 and the free ends of the two straight sections, and the other end is inclined away from the third connecting beam 23. All connecting beams and all mounting seats are located in the same plane. Each mounting seat is used to install one arm 15.

[0035] It should be noted that the tilt angle of the third mounting base 26 is greater than the tilt angle of the tilted segment, and the tilt angle of the third mounting base 26 is equal to the tilt angle of the first mounting base 24. In this embodiment, all mounting bases can be inserted onto the corresponding connecting beams in an interlocking manner, and each mounting base and the corresponding connecting beam can be further fixed by several fasteners. All mounting bases can also be inserted and fixed onto the corresponding connecting beams. The insertion and fixing method can be to provide two plugs for each mounting base, with the corresponding connecting beam disconnected at the mounting position of the mounting base, and two plug holes for inserting the two plugs are opened on the cross section. Alternatively, each mounting base can be provided with two plug holes, with the corresponding connecting beam disconnected at the mounting position of the mounting base, and two plugs for inserting the two plug holes are opened on the cross section.

[0036] In different embodiments, the first mounting base 24 may also be disposed in the middle of the curved section of the first connecting beam 21, with one end for mounting the machine arm 15 inclined to the curved section. The inclination angle between the end of the first mounting base 24 for mounting the machine arm 15 and the curved section is 30° to 45°, and the inclination angle of the inclined section is half the inclination angle of the first mounting base 24. The second mounting base 25 may also be disposed on the side of the parallel section of the first connecting beam 21 near the curved section, with one end for mounting the machine arm 15 perpendicular to the parallel section. The third mounting base 26 may also be disposed at the connection between the first connecting beam 21 and the third connecting beam 23, with one end for mounting the machine arm 15 extending outward along the bisector of the angle between the first connecting beam 21 and the third connecting beam 23. The outer ends of the first mounting base 24, the second mounting base 25, and the third mounting base 26 are all provided with a sleeve cavity 29 for mounting the machine arm 15, and the top of the sleeve cavity 29 is provided with a mounting hole 28 for fixing the machine arm 15.

[0037] Multiple mounting beams 27 are fixed at both ends to two straight segments and are divided into two evenly distributed groups located on opposite sides of the pair of second mounting seats 25. The mounting beams 27 can also be evenly spaced between the parallel segments of the two first connecting beams 21 and evenly distributed on both sides of the second mounting seats 25. All mounting beams 27 are recessed away from the first connecting beams 21 for subsequent installation and fixation of the seat 12, and can reinforce the entire load-bearing frame 13 (similar to the function of reinforcing ribs). The mounting beams 27 can be connected by welding, bolting, riveting, or integral molding. Figure 2 As shown, in this embodiment, multiple mounting beams 27 are installed in the middle of two connecting beams equipped with mounting seats. In other different embodiments, multiple mounting beams 27 may also be installed in the middle of connecting beams without mounting seats. The middle part of each mounting beam 27 protrudes downward from the plane, making each mounting beam 27 U-shaped.

[0038] It should be noted that the two sides of the multiple mounting beams 27 in the load-bearing frame 13 are designated as mounting areas for installing power supply modules, flight controllers, electrical control modules, and communication modules. Furthermore, the overall center of gravity of the aircraft can be optimized based on the weight of other components, bringing it closer to the area where the load-bearing frame 13 is located. In this embodiment, multiple arms 15 can be arranged on the same or approximately the same load-bearing plane. This load-bearing plane is located in the mid-height region of the aircraft, close to the height of the overall center of gravity. Multiple rotor assemblies 14 are positioned at the ends of the corresponding arms 15 furthest from the mounting base; therefore, the lift application positions of the multiple rotor assemblies 14 are also distributed near the mid-height load-bearing plane of the aircraft. By arranging the arms 15 and rotor assemblies 14 in the mid-height region of the aircraft, the height difference between the rotor lift application plane and the overall center of gravity can be reduced, thereby reducing the additional pitch and roll moments generated by the thrust height difference during flight and improving the attitude stability of the manned multi-rotor aircraft.

[0039] Seat 12 is mounted on multiple mounting beams 27 for occupant seating, allowing the occupant's weight (and load) to be transferred via seat 12 and the mounting beams 27 to a closed-loop base formed by four connecting beams. Thus, seat 12 uses a load-bearing frame 13 as its primary load-bearing foundation. The robust structure of the load-bearing frame 13 enhances the installation strength of seat 12 and the safety of occupant seating. Seat 12 can be secured to the mounting beams 27 using bolts or other fastening methods, facilitating subsequent disassembly and maintenance.

[0040] The cockpit 11 is fitted over the outside of the load-bearing frame 13 to cover and protect the load-bearing frame 13 and the seat 12. For example... Figure 3As shown, the cockpit 11 includes a transparent canopy 31, an equipment canopy 32, and multiple connection holes 33 on the equipment canopy 32. The transparent canopy 31 is located on one side of the seat 12, providing the occupants with a field of vision and forming a forward protective space. The equipment canopy 32 is installed at the bottom of the transparent canopy 31, together with the transparent canopy 31, forming the external enclosure structure and occupant protective space of the manned aircraft, used to cover and protect the seat 12, the load-bearing frame 13, and other components on the aircraft within the cockpit 11. These other components include, as mentioned above, the power supply module, flight controller, electrical control module, and communication module. The multiple connection holes 33 on the equipment canopy 32 correspond one-to-one with multiple mounting seats, and each mounting seat passes through its corresponding connection hole 33 and is fixed together, so that the entire cockpit 11 is fixed to the load-bearing frame 13, allowing the load of the cockpit 11 to be directly transferred to the load-bearing frame 13. During assembly, the cockpit 11 can be fixed to the load-bearing frame 13 by passing bolts, screws, clips or other connectors through the connecting holes 33.

[0041] Please see Figure 4 Multiple arms 15 correspond one-to-one with two first mounting seats 24, two second mounting seats 25, and two third mounting seats 26. Each mounting seat has one arm 15 attached to its protruding portion from the cockpit 11, serving as a transmission rod to transfer the torque generated by the rotor assembly 14 to the load-bearing frame 13. The arms 15 can be tubular beam structures, such as round tubes or square tubes. Different types of structures can be used in different embodiments; this embodiment uses a structure such as... Figure 2 The circular tubular structure is shown. The arm 15 can be made of carbon fiber, aluminum alloy, or composite materials. Furthermore, at the connection points of the arm 15, the strength and rigidity of the structure can be increased by increasing the wall thickness, making the aircraft's flight more reliable.

[0042] Multiple rotor assemblies 14 correspond one-to-one with multiple arms 15, and each rotor assembly 14 is mounted on the end of its corresponding arm 15 away from the mounting base, used to generate lift and attitude control torque for the aircraft. Each rotor assembly 14 includes a drive motor, multiple blades, and a mounting structure for connecting the drive motor and the arm 15. The drive motor drives the blades to rotate. The lift generated by the rotor assembly 14 during operation is transmitted through the arm 15 to the load-bearing frame 13, allowing the load-bearing frame 13 to bear the main lift reaction load and the bending moment load of the arm 15 during flight. The load generated by the rotor assembly 14 does not directly act on the cockpit 11. In this embodiment, the mounting structure is not used as an innovative structure; existing mounting structures that can connect the arm 15 and fix the drive motor are sufficient.

[0043] It should be noted that the mounting base is provided with a socket 29. The inner end of the arm 15 is inserted into the corresponding socket 29 and fixedly connected to the arm 15 by bolts, pins, or rivets passing through the mounting holes 28 on the mounting base. Through the cooperation of the socket 29 and the mounting holes 28, a plug-in reinforced connection structure is formed between the arm 15 and the load-bearing frame 13. This connection method can increase the contact length and connection area between the end of the arm 15 near the mounting base and the load-bearing frame 13, so that the lift and vibration load generated by the rotor assembly 14 and the bending moment generated by the arm 15 can be more evenly transmitted to the load-bearing frame 13, reducing stress concentration at the end of the arm 15 near the mounting base and improving the reliability of the connection between the arm 15 and the load-bearing frame 13.

[0044] The force process in this embodiment is as follows: When the aircraft is in takeoff, hovering, or flight, multiple rotor assemblies 14 generate lift and attitude control torque. The lift generated by each rotor assembly 14 first acts on the end of the corresponding arm 15 furthest from the mounting base, and is then transferred to the end of the arm 15 closest to the corresponding mounting base. Subsequently, this load is transferred to the load-bearing frame 13 through the connection area formed by the socket 29 and the connecting hole 33. The two first connecting beams 21, the second connecting beam 22, and the third connecting beam 23 in the load-bearing frame 13 jointly bear and distribute this load.

[0045] When the occupant is seated in seat 12, the occupant's weight is transferred through seat 12 to multiple mounting beams 27, then from these beams to multiple mounting beams 27 connected to them, and further distributed to multiple mounting beams 27 not connected to them. The weight generated by the power supply module, flight controller, electrical control module, and communication module also directly acts on the load-bearing frame 13. Thus, the occupant load, component load, arm 15 load, and flight load generated by the rotor assembly 14 are all concentrated in the load-bearing frame 13 for transfer and distribution.

[0046] Through the above structure, this embodiment forms a load-bearing system for a manned multi-rotor aircraft with the load-bearing frame 13 as its core. This load-bearing system makes the load transfer paths of the seat 12, arms 15, multiple rotor assemblies 14, and other components clearer, reduces the main structural load borne by the cockpit 11, and improves the overall bending stiffness, torsional stiffness, and connection reliability of the aircraft. At the same time, the arms 15 and rotor assemblies 14 are arranged in the middle of the aircraft, so that the rotor lift plane is close to the height of the aircraft's center of gravity, which helps to reduce additional attitude moments and improve flight stability.

[0047] Therefore, the Type 13 manned multirotor aircraft with a load-bearing frame in this embodiment can improve the load-bearing reliability, assembly convenience, and maintenance convenience of manned aircraft while maintaining a simple structure. It is suitable for low-altitude manned flight, short-distance air commuting, aerial sightseeing, and related manned multirotor flight scenarios.

[0048] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0049] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

Claims

1. A load-bearing frame for a manned multi-rotor aircraft, characterized in that, It includes: The base for mounting the cockpit (11) includes four connecting beams: two first connecting beams (21) arranged symmetrically, one end of which is a straight segment and parallel to each other, and the other end of which is an inclined segment and inclined towards each other; a second connecting beam (22) that connects the free ends of the two inclined segments respectively; and a third connecting beam (23) that connects the free ends of the two straight segments respectively. Each pair consists of three symmetrically arranged mounting seats: one end of the first mounting seat (24) is fixed to the two inclined sections respectively, and the other end is inclined with the extension lines of the inclined ends intersecting the extension line of the second connecting beam (22); one end of the second mounting seat (25) is fixed to the two straight sections respectively and is close to the bend of the corresponding straight section and the corresponding inclined section, and the second mounting seat (25) is perpendicular to the corresponding straight section; one end of the third mounting seat (26) is fixed to the connection between the third connecting beam (23) and the free ends of the two straight sections respectively, and the other end is inclined in a direction away from the third connecting beam (23); all connecting beams and all mounting seats are located on the same plane; each mounting seat is used to install one arm (15). Multiple mounting beams (27) are fixed at both ends to two straight segments and are divided into two groups of equal number located on opposite sides of the pair of second mounting seats (25); the multiple mounting beams (27) are used to jointly mount the seat (12).

2. The load-bearing frame according to claim 1, characterized in that, The tilt angle of the inclined section ranges from 15° to 22.5°; And / or, the tilt angle of the first mounting base (24) ranges from 30° to 45°; And / or, the tilt angle of the tilt segment is half the tilt angle of the first mounting base (24); And / or, multiple mounting beams (27) are parallel to each other; And / or, the middle part of each mounting beam (27) protrudes downward from the plane, making each mounting beam (27) U-shaped; And / or, the ratio of the length of the inclined segment to the length of the straight segment is in the range of 1:1.2 to 1:1.

8.

3. The load-bearing frame according to claim 1, characterized in that, The tilt angle of the third mounting base (26) is greater than the tilt angle of the tilt segment.

4. The load-bearing frame according to claim 3, characterized in that, The tilt angle of the third mounting base (26) is equal to the tilt angle of the first mounting base (24).

5. The load-bearing frame according to claim 1, characterized in that, All mounting brackets are interlocked onto the corresponding connecting beams; And / or, all mounting brackets are inserted and secured on the corresponding connecting beams.

6. The load-bearing frame according to claim 5, characterized in that, The position where each mounting base is sleeved or plugged into the corresponding connecting beam is further secured to the corresponding connecting beam by several fasteners.

7. A manned multi-rotor aircraft, comprising a support frame (13), a cockpit (11) mounted on the support frame (13), a seat (12), and multiple arms (15), characterized in that, The load-bearing frame (13) is as described in any one of claims 1 to 6, the cockpit (11) is mounted on the base, each mounting base is equipped with an arm (15), and the seat (12) is mounted on multiple mounting beams (27).

8. The manned multi-rotor aircraft according to claim 7, characterized in that, It includes: The load-bearing frame (13) as described in any one of claims 1 to 6; the load-bearing frame (13) includes a base, three pairs of mounting seats and multiple mounting beams (27); The cabin (11) is covered on the outside of the supporting frame (13); three pairs of mounting seats are provided on its opposite sides, with corresponding connection holes (33), and each mounting seat is provided through the corresponding connection hole (33), so that the cabin (11) is fixed on the supporting frame (13); Seat (12) is installed in the cabin (11) and fixedly connected to multiple mounting beams (27) of the load-bearing frame (13); Multiple arms (15) correspond one-to-one with three pairs of mounting bases. One end of each arm (15) is fitted onto the corresponding mounting base, and the other end is fixedly connected to a rotor assembly (14).

9. The manned multi-rotor aircraft according to claim 8, characterized in that, The manned multi-rotor aircraft also includes a power supply module for providing kinetic energy to the aircraft, a flight controller for controlling the adjustment of the aircraft, an electrical control module for cooperating with the power supply module to perform electrical adjustment of the equipment, and a communication module for communicating with the outside world; the power supply module, flight controller, electrical control module and communication module are all located inside the cockpit (11); And / or, the rotor assembly (14) includes a mounting structure for connecting the arm (15), multiple blades for driving the aircraft to fly, and a drive motor for driving the multiple blades to rotate, with the multiple blades and the drive motor mounted on the mounting structure.

10. The manned multi-rotor aircraft according to claim 8, characterized in that, The cockpit (11) includes a transparent canopy (31) and an equipment cover (32). The transparent canopy (31) is located on one side of the seat (12), and the equipment cover (32) is installed at the bottom of the transparent canopy (31) so that the transparent canopy (31) and the equipment cover (32) together enclose the external covering structure and occupant protection space of the manned aircraft.

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