A multi-rotor aircraft

Abstract

This utility model relates to a multi-rotor aircraft, including a first arm and a second arm. The second arm is located above the first arm, and the middle parts of the first and second arms are rotatably connected via a folding pivot. This allows the aircraft to have a folded state where the first and second arms are parallel, and an unfolded state where the first and second arms are not parallel. Lower rotors are located at both ends of the first arm, and upper rotors are located at both ends of the second arm. In this utility model, two integral arms are arranged vertically and rotatably connected, allowing the aircraft to be folded into a slender structure for easy loading and transportation. The arm structure is complete, allowing rotor drive mechanisms to be arranged along the arms. In the folded state, these rotor drive mechanisms do not need to be disassembled, greatly improving the ease of use and reliability of the multi-rotor aircraft. Furthermore, the complete load-bearing structure of the arms facilitates the support of higher loads.

Description

Technical Field

[0001] This utility model relates to a multi-rotor aircraft. Background Technology

[0002] With the development of vertical takeoff and landing (VTOL) aircraft technology, electric multirotor aircraft using distributed propulsion have become mainstream. These aircraft use multiple small electric power units combined to generate lift, and their arms are often folded during transport to reduce their size. This method is mainly suitable for small multirotor aircraft. When the rotor arms are too large or contain mechanical transmission structures, the load-bearing structures and mechanical transmission structures need to be removed from the arms before folding. After transport, these structures are then reinstalled on the arms, resulting in poor usability. Furthermore, the frequent disassembly and reassembly of the load-bearing and mechanical transmission structures affects the aircraft's structural performance. Utility Model Content

[0003] This utility model relates to a multi-rotor aircraft, which can at least solve some of the defects of the prior art.

[0004] This utility model relates to a multi-rotor aircraft, including a first arm and a second arm. The second arm is located above the first arm. The middle part of the first arm and the middle part of the second arm are rotatably connected by a folding pivot, so that the aircraft has a folded state in which the first arm and the second arm are parallel and an unfolded state in which the first arm and the second arm are not parallel. The two ends of the first arm are respectively provided with lower rotors, and the two ends of the second arm are respectively provided with upper rotors.

[0005] As one embodiment, at least one end of the first arm is provided with a vertical tail; and / or, at least one end of the second arm is provided with a vertical tail.

[0006] As one implementation method, the length of the second arm is less than the length of the first arm.

[0007] As one embodiment, both sets of lower rotors include a rotor shaft connected to the first arm and blades connected to the rotor shaft, and the length of the second arm is less than the distance between the two rotor shafts.

[0008] As one embodiment, the two ends of the first arm are symmetrically distributed with respect to the folding axis; and / or, the two ends of the second arm are symmetrically distributed with respect to the folding axis.

[0009] As one implementation method, in the unfolded state, the first arm is perpendicular to the second arm.

[0010] As one implementation method, the first arm is provided with a lower rotor drive mechanism, and the two sets of lower rotors are respectively connected to the lower rotor drive mechanism.

[0011] As one implementation method, the first arm is a truss arm.

[0012] As one implementation method, the second arm is provided with an upper rotor drive mechanism, and the two sets of upper rotors are respectively connected to the upper rotor drive mechanism.

[0013] As one implementation method, the second arm is a truss-type arm.

[0014] This utility model has at least the following beneficial effects:

[0015] The multi-rotor aircraft provided by this utility model adopts two integral arms arranged vertically and rotatably connected. The first arm and the second arm can rotate relative to each other until they are parallel, folding into a slender structure for easy loading and transportation. The arm structure is complete, and the rotor drive mechanism can be arranged along the arm. In the folded state, there is no need to disassemble these rotor drive mechanisms, avoiding the disassembly of the load-bearing structure and rotor drive mechanism on the arm during transportation and the reassembly work after transportation. Therefore, it can greatly improve the ease of use of the multi-rotor aircraft, and at the same time avoid the impact of frequent disassembly and reassembly of the load-bearing structure and rotor drive mechanism on the structural performance of the aircraft, thus improving the reliability of the multi-rotor aircraft.

[0016] In this invention, the multi-rotor aircraft uses two integral arms with a complete load-bearing structure, which is conducive to bearing higher loads and can correspondingly improve the reliability of the multi-rotor aircraft. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A schematic diagram of the deployed state of a multi-rotor aircraft provided in an embodiment of this utility model;

[0019] Figure 2 A schematic diagram of the folded state of the multi-rotor aircraft provided in this embodiment of the utility model. Detailed Implementation

[0020] The technical solutions in the embodiments of this utility model are described clearly and completely below. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0021] like Figure 1 and Figure 2 This utility model provides a multi-rotor aircraft, including a first arm 11 and a second arm 21. The second arm 21 is located above the first arm 11. The middle part of the first arm 11 and the middle part of the second arm 21 are rotatably connected by a folding pivot 3, so that the aircraft has a folded state in which the first arm 11 and the second arm 21 are parallel and an unfolded state in which the first arm 11 and the second arm 21 are not parallel. The two ends of the first arm 11 are respectively provided with lower rotors 12, and the two ends of the second arm 21 are respectively provided with upper rotors 22.

[0022] The first arm 11 and the second arm 21 are both integral arms. When the first arm 11 and the second arm 21 rotate relative to each other, the first arm 11 rotates as a whole and / or the second arm 21 rotates as a whole.

[0023] Preferably, such as Figure 1 In the deployed state, the first arm 11 and the second arm 21 are perpendicular. In another embodiment, in the deployed state, the first arm 11 and the second arm 21 may also intersect in an X-shape.

[0024] Generally, in the deployed state, it is necessary to ensure the positional stability of the first arm 11 and the second arm 21, that is, to lock the deployed state. Accordingly, a locking unit can be provided on the first arm 11 to lock the second arm 21 in the deployed state, and / or a locking unit can be provided on the second arm 21 to lock the first arm 11 in the deployed state. The above-mentioned locking units include, but are not limited to, locking structures such as electric locking pins, the specific structures of which will not be described in detail here.

[0025] Preferably, the two ends of the first arm 11 are symmetrically distributed with respect to the folding pivot 3, and / or the two ends of the second arm 21 are symmetrically distributed with respect to the folding pivot 3, which can realize stable, controllable, safe and efficient flight of the aircraft, including but not limited to improving hovering balance performance, torque balance performance, decoupling control reliability and flight control efficiency.

[0026] In one embodiment, the length of the second arm 21 is less than the length of the first arm 11. This structure facilitates the folding of the aircraft and avoids interference between the upper and lower rotor structures 12 and between the lower rotor 12 on the first arm 11 and the second arm 21 in the folded state. Furthermore, both sets of lower rotors 12 include a rotor shaft connected to the first arm 11 and blades connected to the rotor shaft. The length of the second arm 21 is less than the distance between the two rotor shafts. In the folded state, the second arm 21 is located between the two rotor shafts, and there is no interference between the lower rotor 12 and the second arm 21, thus achieving better folding of the aircraft.

[0027] The multi-rotor aircraft provided in this embodiment adopts two integral arms arranged vertically and rotatably connected. The first arm 11 and the second arm 21 can rotate relative to each other until they are parallel, folding into a slender structure, which is convenient for loading and transportation. The arm structure is complete, and the rotor drive mechanism can be arranged along the arm. In the folded state, there is no need to disassemble these rotor drive mechanisms, avoiding the disassembly of the load-bearing structure and rotor drive mechanism on the arm during transportation and the reassembly work after transportation. Therefore, it can greatly improve the ease of use of the multi-rotor aircraft, and at the same time avoid the impact of frequent disassembly and reassembly of the load-bearing structure and rotor drive mechanism on the structural performance of the aircraft, thus improving the reliability of the multi-rotor aircraft.

[0028] In addition, since the aforementioned multi-rotor aircraft uses two integral arms with a complete load-bearing structure, it is better able to carry higher loads and correspondingly improve the reliability of the multi-rotor aircraft.

[0029] As described above, the rotor drive mechanism can be arranged along the arm; therefore, preferably, as shown below. Figure 1 and Figure 2 The first arm 11 is provided with a lower rotor drive mechanism 13, and the two sets of lower rotors 12 are respectively connected to the lower rotor drive mechanism 13. The lower rotor drive mechanism 13 can drive the two sets of lower rotors 12 to rotate.

[0030] The lower rotor drive mechanism 13 can be electrically driven. When one electric power unit drives two sets of lower rotors 12 simultaneously, the two sets of lower rotors 12 are respectively connected to the electric power unit through a drive shaft. When two electric power units drive two sets of lower rotors 12 respectively, one electric power unit is connected to one set of lower rotors 12 through a drive shaft, and the other electric power unit is connected to the other set of lower rotors 12 through a drive shaft. Preferably, the two electric power units are symmetrically distributed with respect to the folding pivot 3 to ensure the hovering balance performance and torque balance performance of the aircraft.

[0031] As described above, the rotor drive mechanism can be arranged along the arm; therefore, preferably, as shown below. Figure 1 and Figure 2 The second arm 21 is provided with an upper rotor drive mechanism 23. The two sets of upper rotors 22 are respectively connected to the upper rotor drive mechanism 23, and the upper rotor drive mechanism 23 can drive the two sets of upper rotors 22 to rotate.

[0032] The upper rotor drive mechanism 23 can be electrically driven. When one electric power unit drives two sets of upper rotors 22 simultaneously, the two sets of upper rotors 22 are respectively connected to the electric power unit through a drive shaft. When two electric power units drive two sets of upper rotors 22 respectively, one electric power unit is connected to one set of upper rotors 22 through a drive shaft, and the other electric power unit is connected to the other set of upper rotors 22 through a drive shaft. Preferably, the two electric power units are symmetrically distributed relative to the folding pivot 3 to ensure the hovering balance performance and torque balance performance of the aircraft.

[0033] Preferably, such as Figure 1 and Figure 2 The first arm 11 is a truss arm, which can give the first arm 11 a high strength-to-weight ratio and load capacity, as well as ensure that the first arm 11 has excellent bending and torsional stiffness, effectively improving the flight stability and flight control accuracy of the aircraft, and is especially suitable for large multi-rotor aircraft.

[0034] Furthermore, the use of a truss-type arm for the first arm 11 facilitates the arrangement of the lower rotor drive mechanism 13 and the like.

[0035] Similarly, as Figure 1 and Figure 2 The second arm 21 is also preferably a truss arm.

[0036] In one embodiment, at least one end of the first arm 11 is provided with a vertical tail 4; and / or, at least one end of the second arm 21 is provided with a vertical tail 4. Figure 1 In the illustrated embodiment, a vertical tail 4 is provided only at one end of the first arm 11, which is sufficient to meet the directional control and other related requirements of a large multi-rotor aircraft.

[0037] like Figure 2 As shown, both the upper rotor 22 and the lower rotor 12 are foldable; when a vertical tail 4 is provided, preferably, the vertical tail 4 can also be folded to further facilitate the folding and transportation of the above-mentioned aircraft.

[0038] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A multi-rotor aircraft, characterized in that, The aircraft includes a first arm and a second arm, with the second arm located above the first arm. The middle parts of the first arm and the second arm are rotatably connected by a folding pivot, so that the aircraft has a folded state in which the first arm and the second arm are parallel and an unfolded state in which the first arm and the second arm are not parallel. The first arm has a lower rotor at each end, and the second arm has an upper rotor at each end.

2. The multi-rotor aircraft as described in claim 1, characterized in that, The first arm has a vertical tail at at least one end; and / or the second arm has a vertical tail at at least one end.

3. The multi-rotor aircraft as described in claim 1, characterized in that, The length of the second arm is less than the length of the first arm.

4. The multi-rotor aircraft as described in claim 3, characterized in that, Both sets of lower rotors include a rotor shaft connected to the first arm and blades connected to the rotor shaft. The length of the second arm is less than the distance between the two rotor shafts.

5. The multi-rotor aircraft as described in claim 1, characterized in that, The two ends of the first arm are symmetrically distributed with respect to the folding axis; and / or, the two ends of the second arm are symmetrically distributed with respect to the folding axis.

6. The multi-rotor aircraft as described in claim 1, characterized in that, In the deployed state, the first arm is perpendicular to the second arm.

7. The multi-rotor aircraft as described in claim 1, characterized in that, The first arm is equipped with a lower rotor drive mechanism, and the two sets of lower rotors are respectively connected to the lower rotor drive mechanism.

8. The multi-rotor aircraft as described in claim 1 or 7, characterized in that, The first arm is a truss arm.

9. The multi-rotor aircraft as described in claim 1, characterized in that, The second arm is equipped with an upper rotor drive mechanism, and the two sets of upper rotors are respectively connected to the upper rotor drive mechanism.

10. The multi-rotor aircraft as described in claim 1 or 9, characterized in that, The second arm is a truss arm.

Images