Joint type rotor manned aircraft

Abstract

The utility model discloses a linkage type rotor manned aircraft which comprises a rack and a seat, a power source is arranged on the rack, a control area is arranged on the rack, a flight controller is installed in the control area, the power source is connected with the flight controller, and the seat is connected with the flight controller. A front folding machine arm structure and a rear folding machine arm structure are arranged on the machine frame, rotor wing structures are arranged at the two ends of the front folding machine arm structure and the two ends of the rear folding machine arm structure correspondingly, and the rotor wing structures are connected with the power source and the flight controller correspondingly. And the front folding arm structure and the rear folding arm structure have a folding state and an unfolding state. On the basis of keeping multiple rotor wings, the unmanned aerial vehicle can conveniently rise and take off, and can be folded when not needed on the basis of not long and high-quality running, so that the unmanned aerial vehicle has better transportation and placement, is more beneficial to meeting the use requirements of users, and has higher market value.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft, especially a connecting type rotor manned aircraft. BACKGROUND

[0002] At present, the traditional low-altitude aircraft is mainly small aircraft and helicopter, which needs airport or take-off site, needs professional pilot, has strict requirements on airspace use, and is often affected by high-altitude airflow to limit its use. The previous manned aircraft generally adopts fixed-wing mode, such as the manned aircraft disclosed in the Chinese utility model patent with the authorization announcement number CN210592420U. This kind of aircraft has long take-off distance and requires high-quality runway. Therefore, a fixed-wing rotor hybrid aircraft appears, such as the fixed-wing rotor hybrid aircraft disclosed in the Chinese utility model patent with the authorization announcement number CN216783850U. This kind of aircraft has the advantages of high flight efficiency, long flight time and long flight distance, but has the disadvantages of high cost, large size and the need for airport and runway. Therefore, a multi-rotor electric manned aircraft appears, such as the multi-rotor electric manned aircraft disclosed in the Chinese utility model patent with the authorization announcement number CN218229407U. This kind of aircraft completely avoids the requirements of long take-off distance and high-quality runway by designing a top-mounted multi-rotor, but the overall length does not change when it is not needed. This requires a large space for placement, which is inconvenient for users to place and transport. Therefore, it is necessary to improve the existing technology. SUMMARY

[0003] (I) Technical problems to be solved

[0004] In view of the deficiencies in the prior art, the utility model provides a connecting type rotor manned aircraft, which can ascend and take off conveniently on the basis of maintaining multiple rotors, and can be folded when not needed on the basis of not needing long and high-quality runway. It has good transportation and placement, is more conducive to meeting the use requirements of users, and has great market value.

[0005] (II) Technical solutions to be taken

[0006] In order to achieve the above-mentioned purpose, the technical solution adopted by the utility model is:

[0007] The application discloses a kind of linkable rotor manned aircraft, including frame and the seat for passenger arranged on the frame, and power source is arranged on the frame, control area is arranged on the frame, flight controller is installed in the control area, the power source is connected with the flight controller, front folding arm structure and rear folding arm structure are arranged on the frame, rotor structure is arranged on the both ends of the front folding arm structure and rear folding arm structure, the power source and flight controller are connected with the rotor structure respectively, and the front folding arm structure and rear folding arm structure have folding state and extension state.

[0008] Preferably, the front folding arm structure includes a front fixed arm arranged in front of the frame, a front movable arm is arranged at both ends of the front fixed arm, the front movable arm is connected with the front fixed arm through a front folding structure, and the rotor structure is arranged at the other end of the front movable arm; the rear folding arm structure includes a rear fixed arm arranged at the rear of the frame, a rear movable arm is arranged at both ends of the rear fixed arm, and the rear movable arm is connected with the rear fixed arm through a rear folding structure.

[0009] Preferably, the front folding structure and the rear folding structure are both folding arm parts.

[0010] Preferably, the front fixed arm, the front movable arm, the rear fixed arm and the rear movable arm are hollow structures, wires are arranged in the front fixed arm, the front movable arm, the rear fixed arm and the rear movable arm of the hollow structure, and the rotor structure is connected with the power source and the flight controller through the wires.

[0011] Preferably, the wing structure includes a rotor motor arranged at both ends of the front folding arm structure and the rear folding arm structure, a rotor blade is arranged on the rotor motor, the rotor blade is connected with the rotor motor, an electronic speed controller is arranged at both ends of the front folding arm structure and the rear folding arm structure, and the power source is electrically connected with the electronic speed controller and the rotor motor.

[0012] Preferably, the rotor blade can be a folding rotor.

[0013] Preferably, the rotor blade horizontal plane on the rear folding arm structure has a height difference with the rotor blade horizontal plane on the front folding arm structure.

[0014] Preferably, the height of the rotor blade horizontal plane on the rear folding arm structure is slightly higher than the height of the rotor blade horizontal plane on the front folding arm structure.

[0015] Preferably, the power source is arranged on the frame below the seat.

[0016] Preferably, the power source comprises two battery seats arranged on the frame, and each of the battery seats is arranged with a battery, and each of the batteries is connected with the flight controller and the rotor structure respectively.

[0017] (Three) technical effects to be achieved

[0018] Compared with the prior art, the utility model has the advantages of:

[0019] Firstly, the frame is provided with a front folding arm structure and a rear folding arm structure, both ends of the front folding arm structure and the rear folding arm structure are provided with rotor structures, the rotor structures are connected with power sources and flight controllers respectively, and the front folding arm structure and the rear folding arm structure have folding and stretching states, which can facilitate take-off on the basis of maintaining multi-rotors, do not need a long and high-quality runway, and can be folded when not needed, thereby having good transportation and placement and being more conducive to meeting the use requirements of users and having great market value.

[0020] Secondly, the front folding arm structure comprises a front fixed arm arranged at the front of the frame, both ends of the front fixed arm are provided with front movable arms, the front movable arms and the front fixed arm are connected through a front folding structure, and both ends of the front movable arms are provided with rotor structures; the rear folding arm structure comprises a rear fixed arm arranged at the rear of the frame, both ends of the rear fixed arm are provided with rear movable arms, the rear movable arms and the rear fixed arm are connected through a rear folding structure, and this structure is simpler, facilitates production and manufacturing, is conducive to reducing production and manufacturing costs, and facilitates large-area batch production and assembly.

[0021] Thirdly, the front folding arm structure comprises a front fixed arm arranged at the front of the frame, both ends of the front fixed arm are provided with front movable arms, the front movable arms and the front fixed arm are connected through a front folding structure, and both ends of the front movable arms are provided with rotor structures; the rear folding arm structure comprises a rear fixed arm arranged at the rear of the frame, both ends of the rear fixed arm are provided with rear movable arms, the rear movable arms and the rear fixed arm are connected through a rear folding structure, and this connecting structure is conducive to folding and unfolding, can reduce the occupied space when not needed, facilitates storage and transportation, and is more conducive to meeting the use requirements. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a whole schematic view of the utility model.

[0023] Figure 2 It is a whole schematic view of the utility model in the stretching state.

[0024] Figure 3 It is a schematic view in the side direction of the utility model in the stretching state.

[0025] Figure 4 It is the overall schematic view under the folding state of the utility model.

[0026] Figure 5 It is the side view direction schematic view under the folding state of the utility model.

[0027] Figure 6 It is the schematic view of the front folding structure of the utility model.

[0028] Figure 7 It is the schematic view of the rear folding structure of the utility model.

[0029] In the drawing: 1, frame; 2, seat; 3, power source; 4, control area; 5, front folding arm structure; 6, rear folding arm structure; 7, rotor structure; 31, machine seat; 32, battery; 51, front fixed arm; 52, front movable arm; 53, front folding structure; 61, rear fixed arm; 62, rear movable arm; 63, rear folding structure; 71, rotor motor; 72, rotor blade; 73, electric governor. DETAILED DESCRIPTION

[0030] In the description of the utility model, it needs to be explained that when an element is called "fixed to" or "set to" another element, it can be directly on another element or indirectly on another element. When an element is called "connected to" another element, it can be directly connected to another element or indirectly connected to another element.

[0031] In the description of the utility model, it needs to be explained that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawing, or the orientation or positional relationship commonly used when the utility model product is used, which is only for the convenience of describing the utility model and simplifying the description, and is not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", "third" and the like are only used for differentiation, and cannot be understood as indicating or implying relative importance. Therefore, the features limited by "first", "second" can explicitly or implicitly include one or more features. In the description of the utility model, the meaning of "multiple" is two or more, unless otherwise specifically limited. The meaning of "several" is one or more, unless otherwise specifically limited.

[0032] In the description of the utility model, still need to explain, unless another explicit provision and limitation, term "arrangement", "installation", "link", "connection" should do broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected;Can be mechanical connection, also can be electrical connection;Can be directly connected, also can be indirectly connected through the intermediate medium, can be two elements inside the communication. For ordinary skilled in the art, the above-mentioned terms can be understood in the utility model according to specific circumstances.

[0033] In order to make the purpose, technical scheme and advantage of the utility model more clear and obvious, below, through the drawing and example, the utility model is further detailed. But it should be understood that the specific embodiments described here are only used to explain the utility model, and are not used to limit the scope of the utility model. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the utility model.

[0034] Example one: refer to Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 And Figure 5 A kind of linking rotor manned aircraft, including frame 1 and the seat 2 for carrying person arranged on frame 1, and power source 3 is arranged on frame 1, control area 4 is arranged on frame 1, flight controller (while not shown in the figure) is installed in control area 4, flight controller is connected with power source 3, and the aircraft is driven and controlled by flight controller, front folding machine arm structure 5 and rear folding machine arm structure 6 are arranged on frame 1, rotor structure 7 is arranged on both ends of front folding machine arm structure 5 and rear folding machine arm structure 6, rotor structure 7 is connected with power source 3 and flight controller respectively, not only to provide power supply, power source 3 is used to drive rotor structure 7 to rotate, to realize the take-off and landing of the whole aircraft under the action of power source 3 driving rotor structure 7 to rotate, but also can control and speed regulation, and front folding machine arm structure 5 and rear folding machine arm structure 6 have folding state and extension state, which can facilitate take-off on the basis of maintaining multi-rotor, without long and high quality running basis, and can be folded when not needed, with good transportation and placement, more conducive to meet the use requirements of users, with great market value.

[0035] Example two: can be based on example one, as Figure 2 、 Figure 4 、 Figure 5 、 Figure 6 And Figure 7As shown, the front folding arm structure 5 includes a front fixed arm 51 arranged at the front of the frame 1, both ends of the front fixed arm 51 are provided with a front movable arm 52, and the front movable arm 52 and the front fixed arm 51 are connected through a front folding structure 53, and both ends of the front movable arm 52 are provided with a rotor structure 7; the rear folding arm structure 6 includes a rear fixed arm 61 arranged at the rear of the frame 1, both ends of the rear fixed arm 61 are provided with a rear movable arm 62, and the rear movable arm 62 and the rear fixed arm 61 are connected through a rear folding structure 63, and the front folding structure 53 realizes the folding and stretching between the front movable arm 52 and the front fixed arm 51, and the rear folding structure 63 realizes the folding and stretching between the rear movable arm 62 and the rear fixed arm 61, which not only can keep normal flight utility in the stretched state, but also can have good transportation and placement in the folded state, reduce the occupied space, and also is beneficial to reduce the cost investment, and has greater practical value. Further description is as follows: Figure 6 and Figure 7 As shown, the front folding structure 53 and the rear folding structure 63 are both folding arm parts, and such a connecting structure is beneficial to realize the folding (beneficial to reduce the occupied space) and the unfolding.

[0036] As shown in Figure 2 , Figure 4 and Figure 5 The front fixed arm 51, the front movable arm 52, the rear fixed arm 61 and the rear movable arm 62 are hollow structures, wires are installed in the hollow structure of the front fixed arm 51, the front movable arm 52, the rear fixed arm 61 and the rear movable arm 62, the rotor structure 7 is connected with the power source 3 and the flight controller through the wires, and the distribution of the wires is avoided, and the safety of use is also improved.

[0037] Example three: on the basis of example one or example two, as shown in Figure 2 , Figure 4 and Figure 5 The rotor structure 7 includes a rotor motor 71 arranged at both ends of the front folding arm structure 5 and the rear folding arm structure 6, the rotor motor 71 is provided with a rotor blade 72, the rotor blade 72 is connected with the rotor motor 71, and an electronic speed regulator 73 is arranged at both ends of the front folding arm structure 5 and the rear folding arm structure 6, the electronic speed regulator is used for adjusting the rotating speed of the rotor motor 71, the power source 3 is electrically connected with the electronic speed regulator 73 and the rotor motor 71, and drives the rotor motor 71 and the electronic speed regulator 73 to work under the action of the power source 3. The rotating speed of the corresponding rotor blade 72 is adjusted through the electronic speed regulator 73, the steering is controlled by adjusting the differential speed of the four first wheel groups and the stretching amount of the folding wings on both sides of the fuselage, and the stability during steering is improved.

[0038] As shown in Figure 4 andFigure 5 As shown, the rotor blade 72 horizontal plane on the rear folding arm structure 6 is different in height from the rotor blade 72 horizontal plane on the front folding arm structure 5, which is beneficial to the rear folding arm structure 6 and the front folding arm structure 5 to overlap each other after folding, and is beneficial to reduce the occupied space, and in the embodiment, the height of the rotor blade 72 horizontal plane on the rear folding arm structure 6 is slightly higher than the height of the rotor blade 72 horizontal plane on the front folding arm structure 5, which is beneficial to realize the rear folding arm structure 6 and the front folding arm structure 5 to be staggered up and down, and is beneficial to better folding and reduce the occupied space. Further, the height of the rotor blade 72 horizontal plane on the rear folding arm structure 6 is 3cm-10cm, preferably 5cm, which not only maintains better normal use, but also is beneficial to stagger up and down after folding and reduce the occupied space. Or, wherein, the rotor blade 72 can adopt a folding rotor, which is beneficial to reduce the actual space.

[0039] Embodiment three: based on embodiment one or embodiment two or embodiment three, as shown, Figure 1 As shown, the power source 3 is arranged on the frame 1 below the seat 2, and in the embodiment, it is symmetrically arranged along the front and rear direction of the seat 2, which is reasonable and is more beneficial to save internal space. Further, the power source 3 includes two machine seats 31 arranged on the frame 1, and each machine seat 31 is provided with a battery 32, and each battery 32 is respectively connected with a flight controller and a rotor structure 7, which is beneficial to provide stable power support for the device.

[0040] In the utility model, the front folding arm structure 5 and the rear folding arm structure 6 and the front folding arm structure 5 and the rear folding arm structure 6 are all provided with a rotor structure 7 (can vertically take off and land, does not need runway, load capacity and load ratio are higher, take-off site demand is small, flight space requirement is small), and the flight personnel is located on the seat 2 in the middle of the frame 1 (is wrapped with safety protection), plays a safety protection role, the front folding arm structure 5 and the rear folding arm structure 6 are foldable, are unfolded during flight, are folded compactly when not needed, the structure size is small, is convenient to place and transport, and the overall cost of the utility model is 10% of the general aviation aircraft, which is convenient for more people to use.

[0041] The standard parts used in the present application file can be purchased from the market, the specific connection mode of each part adopts the conventional means such as folding machine arm in the prior art, the flight controller (an element for assisting or fully autonomously controlling other systems and components of the aircraft during take-off, cruising, landing and other stages, usually used together with inertial measurement unit (IMU), barometer, magnetic compass and other components to form a flight control system), battery and internal components of electronic speed controller adopt conventional models in the prior art, and the internal structure belongs to the prior art structure, workers can complete normal operation according to the existing technical manual, plus the circuit connection adopts the conventional connection mode in the prior art, which will not be described in detail here.

[0042] It should be noted that although the above embodiments have been described in this paper, the patent protection scope of the present application is not limited thereby. Therefore, based on the innovative concept of the present application, the changes and modifications of the embodiments described in this paper, or the equivalent structure or equivalent process transformation made by using the content of the present application specification and drawings, directly or indirectly apply the above technical solutions to other related technical fields, which are all included in the protection scope of the present application patent.

Claims

1. A manned aircraft with articulated rotors, comprising a frame (1) and a seat (2) for a person arranged on the frame (1), and a power source (3) arranged on the frame (1), a control area (4) is arranged on the frame (1), a flight controller is installed on the control area (4), and the flight controller is connected with the power source (3), characterized in that: The frame (1) is provided with a front folding arm structure (5) and a rear folding arm structure (6), both ends of the front folding arm structure (5) and the rear folding arm structure (6) are provided with a rotor structure (7), the rotor structure (7) is respectively connected with the power source (3) and the flight controller, and the front folding arm structure (5) and the rear folding arm structure (6) have a folding state and an extended state. ​ 2. The articulated rotorcraft of claim 1, wherein: The front folding arm structure (5) comprises a front fixed arm (51) arranged at the front of the frame (1), both ends of the front fixed arm (51) are provided with a front movable arm (52), the front movable arm (52) and the front fixed arm (51) are connected through a front folding structure (53), and both ends of the front movable arm (52) are provided with the rotor structure (7); the rear folding arm structure (6) comprises a rear fixed arm (61) arranged at the rear of the frame (1), both ends of the rear fixed arm (61) are provided with a rear movable arm (62), and the rear movable arm (62) and the rear fixed arm (61) are connected through a rear folding structure (63).

3. The articulated rotorcraft of claim 2, wherein: The front folding structure (53) and the rear folding structure (63) are both folding arm parts.

4. The articulated rotorcraft of claim 2 or 3, wherein: The front fixed arm (51), the front movable arm (52), the rear fixed arm (61) and the rear movable arm (62) are hollow structures, wires are installed in the front fixed arm (51), the front movable arm (52), the rear fixed arm (61) and the rear movable arm (62), and the rotor structure (7) is respectively connected with the power source (3) and the flight controller through the wires.

5. The articulated rotor manned flying vehicle of claim 1 or 2 or 3, wherein: The wing structure (7) comprises a rotor motor (71) arranged at both ends of the front folding arm structure (5) and the rear folding arm structure (6), the rotor motor (71) is provided with a rotor blade (72), the rotor blade (72) is connected with the rotor motor (71), and an electronic speed controller (73) is arranged at both ends of the front folding arm structure (5) and the rear folding arm structure (6), and the power source (3) is electrically connected with the electronic speed controller (73) and the rotor motor (71).

6. The articulated rotorcraft of claim 5, wherein: The rotor blade (72) on the rear folding arm structure (6) has a height difference with the rotor blade (72) on the front folding arm structure (5).

7. The articulated rotorcraft of claim 5, wherein: The rotor blade (72) can be a folding rotor.

8. The tethered rotary wing personal flight vehicle as claimed in claim 1 or 2 or 3 or 6 or 7, wherein: The power source (3) is arranged on the frame (1) below the seat (2).

9. The articulated rotorcraft of claim 8, wherein: The power source (3) comprises two machine seats (31) arranged on the frame (1), a battery (32) is installed in each machine seat (31), and each battery (32) is respectively connected with the flight controller and the rotor structure (7).

Images