Manned annular six-rotor independent aircraft

Abstract

The invention provides a manned annular six-rotor independent aircraft, and belongs to the technical field of helicopter structure design, the manned annular six-rotor independent aircraft comprises a support arm, an annular support piece, a connector, a battery system mounting hole and a battery mounting platform; the six supporting arms are connected through the connecting joints, the supporting arms are connected through the annular supporting pieces, the ends of the supporting arms provide installation space for a battery electric control system, the two ends of each annular supporting piece can be provided with a battery system, the upper portion of the central joint can provide an installation platform for a flight control system, the structural form is simple, and a high-efficiency force transmission path is achieved; and good maintainability and interchangeability are achieved, and meanwhile the purpose of efficiently carrying people or goods can be achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of helicopter structure design, and in particular relates to a manned annular six-rotor independent aircraft. Background Art

[0002] At present, electric multi-rotor aircraft are mainly unmanned aerial vehicles, and most of their structures are mainly lightweight frame structures with low load-bearing capacity and low structural load transfer efficiency, which cannot meet the strength and stiffness requirements of manned aircraft. In addition, most aircraft have complex structures, poor maintainability, interchangeability and economy, and other disadvantages.

[0003] Therefore, it is necessary to optimize the aircraft structure, improve the load-bearing capacity and force transmission efficiency, and improve the safety and stability of the aircraft structure. Summary of the invention

[0004] In order to optimize the aircraft structure, improve the bearing capacity and force transmission efficiency, and improve the safety and stability of the aircraft structure, the present invention provides a circular six-rotor aircraft structure, which connects six arms through a connecting joint, and the arms are connected to each other through a circular support. The end of the arm provides an installation space for the battery electronic control system, and the battery system can be installed at both ends of the circular support. The upper part of the central joint can provide an installation platform for the flight control system. The structure is simple, and a high-efficiency force transmission path is realized. It has good maintainability and interchangeability, and can achieve the purpose of high-efficiency manned or cargo carrying. The technical solution is as follows:

[0005] A manned annular six-rotor independent aircraft, comprising: a support arm 1, an annular support member 2, a connecting joint 3, a battery system mounting hole 16, and a battery mounting platform 17;

[0006] A connecting joint 3 is inserted into one side of the root of the support arm 1, and the two ends of the annular support 2 are respectively connected to one side of the end of two adjacent support arms 1 through connecting angle materials 4 to form the entire annular six-rotor structure body; a battery mounting platform 17 for installing the battery and a battery system mounting hole 10 for fixing the battery are provided at both ends of each annular support 2; a motor and a rotor system are installed on one side of the end of each support arm 1 close to the annular support 2, the motor is connected to the battery, and the bottom of the connecting joint 3 is connected to the cabin or cargo hold.

[0007] Optionally, the bottom of the connecting joint 3 is connected to the cabin or cargo hold by means of a second bolt 7, a second gasket 8 and a cylindrical nut 34, so that the lower cabin can be quickly disassembled and replaced, thereby realizing the switching between carrying people and cargo.

[0008] Optionally, the support arm 1 is a cylindrical structure made of all-carbon fiber composite materials, and a ply thickening area 11 is provided at a position with greater stress to achieve lightweight while meeting strength requirements; the end of the support arm 1 close to the annular support 2 is a cup-shaped structure, and a motor mounting hole 14 is provided on the upper surface of the cup-shaped structure to provide space and interface for the installation of the motor and rotor; a motor wire hole 13 is provided on the side of the cup-shaped structure to pass through the cable connecting the battery and the motor; an equipment mounting surface 12 for installing the electric control system equipment is provided on the front end surface of the cup-shaped structure, and a sensor mounting hole 15 is provided on the bottom plane of the cup-shaped structure for installing the sensor; all connecting cables pass through the inside of the support arm 1 and are connected to the central flight control system.

[0009] Optionally, the annular support member 2 is a full carbon fiber composite material structure; the annular member is provided with heat dissipation holes 18 for dissipating heat for the battery.

[0010] Optionally, in the connecting joint 3, the thickness of the area with greater stress is a preset thickness, and the thickness of the area with less stress is less than the preset thickness. The effect of this is that the structure is strengthened by adding the thickened area, and the thickness of the area with less stress is reduced to reduce the weight, thereby achieving efficient load transmission of the connecting joint while reducing the weight of the connecting joint.

[0011] Optionally, the connection joint 3 includes: an upper connection plate 19, a lower connection plate 20, a middle support member 21

[0012] The upper connecting plate 19 and the lower connecting plate 20 adopt a centrally symmetrical structure. The upper connecting plate 19, the six middle support members 21 and the lower connecting member 20 are connected by a first bolt 5, a first gasket 6 and an open thick nut 22, and are prevented from loosening by a cotter pin; after the upper connecting plate 19, the middle support member 21 and the lower connecting plate 20 are connected together, the cross-section along the radial direction of each support arm 1 is an I-shaped structure, which effectively improves the bending coefficient and can effectively transmit the bending moment from the support arm 2.

[0013] Optionally, a T-shaped reinforcing rib 23 is provided on the upper connecting plate 19 along the axial direction of each arm, the function of which is to improve the bending coefficient of the entire part and resist the bending moment from the arm 1. The upper connecting plate 19 is provided with a plurality of second bolt holes 25, which are evenly distributed at 60° on the bottom surface of the upper connecting plate 19 for connecting the arm 1; a plurality of first bolt holes 24 are evenly distributed in the central area of ​​the upper connecting plate 19 for connecting the middle support member 21; a hexagonal reinforcing flange 26 is provided on the outer ring of the upper connecting plate 19 for increasing the torsion resistance system and resisting the torque from the arm; a rectangular thickening area 27 and a hexagonal thickening area 28 are provided on the upper connecting plate 19 at a location with greater stress; a triangular lightening hole 29 is provided on the bottom surface of the upper connecting plate 19 for reducing weight, and a plurality of connecting lugs 30 are arranged on the upper connecting plate 19 for installing the equipment installation platform;

[0014] The first bolt holes 24 are arranged on the upper and lower surfaces of the middle support member 33 for connecting the upper connection plate 19 and the lower connection plate 20. The outer ring is provided with a rectangular reinforcement flange 31, the inner ring is provided with an oblong reinforcement flange 32, a conical thickening area 33 is added where the stress is larger, and an oblong relief hole 34 is provided in the middle position;

[0015] A T-shaped reinforcing rib 23 is provided along the axial direction of each arm at the bottom of the lower connecting plate 20, and its function is to improve the bending coefficient of the entire part and resist the bending moment from the arm 1; the lower connecting plate 20 is provided with a second bolt hole 25, which is evenly distributed at 60° on the bottom surface of the lower connecting plate 20 and is used to connect the arm 1; the first bolt holes 24 are evenly distributed in the central area of ​​the lower connecting plate 20 and are used to connect the middle support 21; the outer ring of the lower connecting plate 20 is provided with a hexagonal reinforcing flange 26, which is used to increase the anti-torsion system and resist the torque from the arm; the upper connecting plate 20 is provided with a rectangular thickened area 27, a hexagonal thickened area 28 and a reinforcing rib 35 at the stress greater than the upper connecting plate 20; a circular mounting hole 36 for mounting a cylindrical nut 34 is provided on the T-shaped reinforcing rib 23, and a triangular lightening hole 29 is provided on the upper surface of the lower connecting plate 20 to reduce weight.

[0016] Optionally, the support arm 1 and the connecting joint 3 are connected by a second bolt 7, a second gasket 8 and a second support plate nut 10. Through the disassembly and assembly of the bolts, quick disassembly can be easily achieved, thereby achieving interchangeability and maintainability of the connecting joint, the support arm and the ring member, and convenient road transportation.

[0017] Optionally, the ring member 2 is connected to the support arm 1 by means of a first bolt 5, a first gasket 6, and a first support plate nut 7. By disassembling and assembling the bolts, quick disassembly can be easily achieved, thereby achieving interchangeability and maintainability of the connecting joint, the support arm, and the ring member, and convenient road transportation.

[0018] The beneficial effects of the present invention are at least:

[0019] The annular six-rotor aircraft structure connects the arms through joints and is connected to each other through annular supports to form a centrally symmetrical structure. The structure is simple and efficient, has a high structural bearing capacity, and has high safety and stability. The structures are connected by simple bolts, have good disassembly and maintenance, and interchangeability, and can easily meet the requirements of road transportation.

[0020] The support arm, annular support and connecting joint of the present invention can serve as load-bearing structures and provide installation space and interfaces for various equipment of the system, thereby realizing the function of independent flight. At the same time, the lower part of the connecting joint can provide an installation interface for the cabin and cargo hold, so that switching between manned or flying can be realized at any time. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the structure of a circular six-rotor aircraft;

[0022] Figure 2 for Figure 1 Middle I partial schematic diagram;

[0023] Figure 3 for Figure 1 middle Partial schematic diagram;

[0024] Figure 4 It is a schematic diagram of the support arm structure;

[0025] Figure 5 for Figure 4 Schematic diagram of the structure of medium III;

[0026] Figure 6 It is a schematic diagram of the motor system and the rotor system;

[0027] Figure 7 is an isometric view of the annular support;

[0028] Figure 8 is a top view of the annular support;

[0029] Fig. 9 is a schematic diagram of the connection joint;

[0030] Fig.10 is a schematic diagram of the upper connection plate;

[0031] Fig.11 is a schematic diagram of the middle support member;

[0032] Fig.12 Schematic diagram of the lower connecting plate ((flipped 180°)). DETAILED DESCRIPTION

[0034] The present invention is further described in detail below through specific implementation modes and drawings.

[0035] The invention provides a six-rotor aircraft structure which can carry people or cargo and is easy to disassemble, assemble and maintain.

[0036] See also Figure 1 An embodiment of the present invention provides a manned annular six-rotor independent aircraft, including a support arm 1, an annular support member 2, a connecting joint 3, a connecting angle 4, a first bolt 5, a first gasket 6, a first support plate nut 7, a second bolt 8, a second gasket 9, and a second support plate nut 10.

[0037] See also Figure 2 The support arm 1 includes a ply thickening area 11, an equipment mounting surface 12, a battery wire passing hole 13, a motor mounting hole 14, and a sensor mounting hole 15.

[0038] See also Figure 4 The annular support 2 includes a battery system mounting hole 16, a battery mounting platform 17, and a heat dissipation hole 18.

[0039] See also Figure 5 The connecting joint includes an upper connecting plate 19, a lower connecting plate 20, a middle support member 21, a first bolt 5, a first gasket 6, a first support plate nut 7, a second bolt 8, a second gasket 9, an open thick nut 22 and a cylindrical nut 37.

[0040] See also Figure 6 The upper connecting plate 19 includes a T-shaped reinforcing rib 23, a first bolt hole 24, a second bolt hole 25, a hexagonal reinforcing flange 26, a rectangular thickened area 27, a hexagonal thickened area 28, a triangular lightening hole 29, and a connecting ear 30.

[0041] See also Figure 7 The middle support member 21 includes a rectangular reinforcement flange 31 , an oblong reinforcement flange 32 , a conical thickened area 33 , and an oblong lightening hole 34 .

[0042] See also Figure 8 The lower connecting plate 20 includes a T-shaped reinforcing rib 23, a first bolt hole 24, a second bolt hole 25, a hexagonal reinforcing flange 26, a rectangular thickened area 27, a hexagonal thickened area 28, a triangular lightening hole 29, a connecting ear 30, a reinforcing rib 35, and a circular mounting hole 36.

[0043] Please refer to detail II, insert one side of the root of the support arm 1 into the connection joint 3, and connect it with the second bolt 8, the second gasket 8 and the second support plate nut 10. Please refer to detail I, one side of the end of the support arm 1 is connected to the two ring parts 2 through the angle material 4, and connected through the first bolt 5, the first gasket 6, and the first support plate nut 7, completing the installation of the entire annular six-rotor structure body. The entire structure is axially symmetrical and centrally symmetrical, which can ensure that the bending moments from the symmetrical position of the support arms offset each other, and transmit torque through the connection of the ring parts. The structure is simple and efficient, and can be easily disassembled by disassembling and assembling the bolts, thereby realizing the interchangeability and maintainability of the connection joint, the support arm and the ring parts, and can be conveniently transported by road.

[0044] See also Figure 2 The arm 1 is the main load-bearing structure, which adopts a full carbon fiber composite cylindrical structure. It mainly bears the tension, bending moment, torque and deadweight of the system equipment generated by the rotor. The end where the root equipment with greater stress is installed has a thickened layer area 11. The stress at the connection between the arm 1 and the connecting joint 3 is greater. Multiple devices are installed at the cup-shaped structure at the end of the arm 1. The thickened layer area 11 is added to meet the stiffness requirements. The layers in other parts are reduced to achieve lightweight on the basis of meeting the strength requirements. Please refer to the details. Figure IIIThe cup-shaped structure provides space and interfaces for the installation of equipment systems. The motor installation hole 14 is used to install the motor and rotor system. The front end of the cup-shaped structure is provided with an equipment installation surface 12 for installing the electric control system equipment. The bottom plane of the cup-shaped structure is provided with a sensor installation hole 15 for installing the sensor. The motor wire hole 13 is used to pass the cable connecting the battery and the motor. Finally, all cables are connected to the central flight control system through the internal passage of the support arm. For installation form, please refer to Figure 3 .

[0045] See also Figure 4 The annular support 2 is a secondary load-bearing structure, which adopts a full carbon fiber composite material structure. It mainly bears the bending moment and torque from the rotor, as well as the deadweight of the battery system, and provides installation space and interface for the battery system. The battery mounting platforms 17 at both ends of each annular support 2 are used to install batteries and are fixed through the battery system mounting holes 16. The entire annular structure can install multiple batteries, which can provide sufficient endurance for flight. The upper part of the annular member provides heat dissipation for the battery through the heat dissipation holes 15. Since the entire structure can be installed with complete batteries, motors, rotors, flight control and other systems, independent flight capabilities can be achieved.

[0046] See also Figure 5 , the connection joint 3 is the main load-bearing structure, which mainly bears the bending moment and tension from the support arm, as well as the deadweight of the lower cabin and cargo compartment, and provides an installation platform for the flight control system. The connection joint 3 is an axisymmetric and centrally symmetrical structure, which can ensure that the bending moments from the symmetrical position support arms offset each other, and more efficiently transmit the load from the support arm. The area with greater stress is reinforced by adding thickening areas, and the thickness of other areas is reduced, so as to achieve efficient load transmission of the connection joint and reduce the weight of the connection joint. The lower part is connected to the lower cabin and the cargo compartment through the second bolt 7, the second gasket 8 and the cylindrical nut 37, which can realize the rapid disassembly and replacement of the lower cabin, thereby realizing the switching between manned and cargo. The upper connection plate 19, the lower connection plate 20 and the middle support member 21 are connected with the first bolt 5, the first gasket 6 and the open thick nut. Through the disassembly and assembly of the bolts, quick disassembly can be easily achieved, thereby realizing faster inspection and maintenance of the connection joint and the interchangeability and maintainability of the six support arms.

[0047] See also Figure 6-8The upper connecting plate 19 and the lower connecting plate 20 are respectively provided with T-shaped reinforcing ribs 23 to increase the bending rigidity of the entire structure and more efficiently transmit the load from the support arm. The upper connecting plate 19 and the lower connecting plate 20 are provided with hexagonal reinforcing flanges 26 to increase the torsional rigidity of the structure and resist the torsion from the support arm 1. The junction between the upper connecting plate 19 and the middle support member 21, the junction between the lower connecting plate 20 and the middle support member 21, and the central area of ​​the upper connecting plate 19 and the lower connecting plate 20 are areas with relatively large stress. The structure is strengthened by adding thickened areas, and lightening holes are added to the remaining areas with relatively small stress, so as to realize efficient load transmission of the connection joint and reduce the weight of the connection joint.

[0048] The annular six-rotor independent aircraft of the present invention has a simple and efficient structure, high bearing capacity, and is connected to each other through bolts, so it can be quickly disassembled and installed, convenient for maintenance, convenient for transportation, and interchangeable; at the same time, it can provide installation space and interfaces for various systems, so as to realize independent flight capability; the lower part can be optionally equipped with a cockpit and a cargo hold to realize the function switching of manned flight and cargo transportation.

[0049] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A manned annular six-rotor independent aircraft, characterized in that: include: Support arm (1), annular support member (2), connecting joint (3), battery system mounting hole (16), battery mounting platform (17); A connecting joint (3) is inserted into one side of the root of the support arm (1), and the two ends of the annular support member (2) are respectively connected to one side of the end of two adjacent support arms (1) through connecting angle bars (4), so as to form the entire annular six-rotor structure body; a battery installation platform (17) for installing a battery and a battery system installation hole (10) for fixing the battery are provided at both ends of each annular support member (2); a motor and a rotor system are installed on one side of the end of each support arm (1) close to the annular support member (2), and the motor is connected to the battery, and the bottom of the connecting joint (3) is connected to the cabin or the cargo hold.

2. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The bottom of the connecting joint (3) is connected to the cabin or cargo hold via a second bolt (7), a second gasket (8) and a barrel nut (34).

3. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The support arm (1) is a cylindrical structure made of all carbon fiber composite materials, and a ply thickening area (11) is provided at a position with greater stress; one end of the support arm (1) close to the annular support member (2) is a cup-shaped structure, and a motor mounting hole (14) is provided on the upper surface of the cup-shaped structure; a motor wire passing hole (13) is provided on the side of the cup-shaped structure; an equipment mounting surface (12) for mounting electric control system equipment is provided on the upper front end surface of the cup-shaped structure, and a sensor mounting hole (15) for mounting a sensor is provided on the bottom plane of the cup-shaped structure; all connecting cables pass through the inside of the support arm (1) and are connected to the central flight control system.

4. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The annular support member (2) is a full carbon fiber composite material structure; the annular member is provided with heat dissipation holes (18) for dissipating heat for the battery.

5. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The thickness of the connecting joint (3) in the area with greater stress is a preset thickness, and the thickness of the area with less stress is less than the preset thickness.

6. The manned annular six-rotor independent aircraft according to claim 5, characterized in that: The connecting joint (3) comprises: an upper connecting plate (19), a lower connecting plate (20), and a middle supporting member (21). The upper connecting plate (19) and the lower connecting plate (20) adopt a central symmetrical structure. The upper connecting plate (19), six middle supporting members (21) and the lower connecting member (20) are connected by a first bolt (5), a first gasket (6) and an open thick nut (22), and are prevented from loosening by a cotter pin. After the upper connecting plate (19), the middle supporting member (21) and the lower connecting plate (20) are connected together, the cross-section along the radial direction of each support arm (1) is an I-shaped structure.

7. The manned annular six-rotor independent aircraft according to claim 6, characterized in that: The upper connecting plate (19) is provided with a T-shaped reinforcing rib (23) along the axial direction of each support arm; the upper connecting plate (19) is provided with a plurality of second bolt holes (25) which are evenly distributed at 60 degrees on the bottom surface of the upper connecting plate (19) for connecting the support arm (1); a plurality of first bolt holes (24) are evenly distributed in the central area of ​​the upper connecting plate (19) for connecting the middle support member (21); the outer ring of the upper connecting plate (19) is provided with a hexagonal reinforcing flange (26); the upper connecting plate (19) is provided with a rectangular thickening area (27) and a hexagonal thickening area (28) at a location with greater stress; the bottom surface of the upper connecting plate (19) is provided with a triangular lightening hole (29); the upper connecting plate (19) is arranged with a plurality of connecting lugs (30); The first bolt holes (24) are arranged on the upper and lower surfaces of the middle support member (33) for connecting the upper connection plate (19) and the lower connection plate (20). The outer ring is provided with a rectangular reinforcement flange (31), the inner ring is provided with an oblong reinforcement flange (32), a conical thickening area (33) is added at a location with greater stress, and an oblong lightening hole (34) is provided in the middle position; A T-shaped reinforcing rib (23) is provided at the lower side of each support arm in the axial direction of the lower connecting plate (20); the lower connecting plate (20) is provided with a second bolt hole (25) which is evenly distributed at 60 degrees on the bottom surface of the lower connecting plate (20) for connecting the support arm (1); a first bolt hole (24) is evenly distributed in the central area of ​​the lower connecting plate (20) for connecting the middle support member (21); a hexagonal reinforcing flange (26) is provided on the outer ring of the lower connecting plate (20); a rectangular thickened area (27), a hexagonal thickened area (28) and a reinforcing rib (35) are provided at a location with greater stress on the upper connecting plate (20); a circular mounting hole (36) for mounting a cylindrical nut (34) is provided on the T-shaped reinforcing rib (23), and a triangular lightening hole (29) is provided on the upper surface of the lower connecting plate (20).

8. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The support arm (1) and the connecting joint (3) are connected via a second bolt (7), a second gasket (8) and a second support plate nut (10).

9. The manned annular six-rotor independent aircraft according to claim 1, characterized in that: The annular member (2) is connected to the support arm (1) via a first bolt (5), a first gasket (6) and a first support plate nut (7).

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