Manned aircraft with three shafts and six propellers

Abstract

The utility model relates to the technical field of aircrafts, and particularly discloses a three-shaft six-propeller manned aircraft which comprises a fuselage main body, a mounting frame fixedly connected to the bottom of the back of the fuselage main body, a battery pack fixedly connected to the inner wall of the mounting frame, and an anti-rolling frame fixedly connected to one side of the back of the fuselage main body. Mounting frames are fixedly connected to the two sides of the mounting frame and the back face of the anti-rolling frame, a protective frame is fixedly connected to one side of the surface of each mounting frame, a connecting column is fixedly connected to the middle of the inner wall of each protective frame, motors are fixedly connected to the upper end and the lower end of each connecting column, and rotors are mounted at the output ends of the motors; forces in the X direction, the Y direction and the Z direction are generated through the rotating speed difference of the rotors to control the aircraft to move in any direction, lift force and balance can be still kept in the three-shaft six-paddle mode under the condition that one motor loses efficacy, and therefore the purpose of continuous flight is achieved, the weight of the aircraft can be reduced through the semi-open type cabin space, and the space of the aircraft is saved. And a corresponding anti-rolling framework is arranged, so that the safety of a driver is effectively protected.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft, and in particular relates to a three-axis six-propeller manned aircraft. Background Art

[0002] With the rapid development of science and technology, especially breakthroughs in aviation, automobiles, new materials, automatic control and artificial intelligence, the integration of aircraft and ground transportation has become possible. Manned aircraft, as a product of this integration trend, is developed to solve problems such as urban traffic congestion and environmental pollution, while providing a more convenient and efficient way of travel.

[0003] In the Chinese patent with publication number CN106218879B, a split low-altitude manned aircraft is mentioned, including a manned flight platform, a cable, and a battery pack movably placed on the ground or floating on the water surface, the manned flight platform is connected to the battery pack through the cable, one end of the power supply line is connected to the power supply end of the manned flight platform through a first plug-in connector, and the other end is connected to the power output end of the battery pack through a second plug-in connector, one end of the tension rope is fixedly connected to the battery pack, and the other end is connected to the manned flight platform through an automatic unhooking mechanism, and a tension sensor connected to the flight control system of the manned flight platform is arranged in the automatic unhooking mechanism, when the tension sensor detects that the tension on the tension rope is greater than the tension threshold value, the automatic unhooking mechanism automatically unhooks, so that the manned flight platform is separated from the battery pack. The manned aircraft of the present invention prevents the manned flight platform from taking the battery pack off the ground, thereby ensuring the safety of manned flight.

[0004] However, when the above technical solution is in use, the manned flying device is separated from the battery pack. Although this can ensure the safety of manned flight, the use of the manned flying device is relatively simple. It is difficult to achieve the function of convenient flight control in existing use, and it is difficult to mass-produce the whole device. Therefore, the staff needs to improve it. Utility Model Content

[0005] The purpose of the utility model is to provide a three-axis six-propeller manned aircraft to solve the problems raised in the above background technology.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A three-axis six-propeller manned aircraft, comprising:

[0008] The main body of the fuselage;

[0009] A mounting frame is fixedly connected to the bottom of the back of the fuselage body, a battery pack is fixedly connected to the inner wall of the mounting frame, and a roll cage is fixedly connected to one side of the back of the fuselage body;

[0010] Mounting frames are fixedly connected to both sides of the mounting frame and the back of the roll cage, a protective frame is fixedly connected to one side of the mounting frame surface, a connecting column is fixedly connected to the middle of the inner wall of the protective frame, a motor is fixedly connected to the upper and lower ends of the connecting column, and a rotor is installed at the output end of the motor.

[0011] Preferably, a backrest is fixedly connected to one side of the top of the mounting frame, a flight controller is fixedly connected to the top of the back of the backrest, and a parachute is fixedly connected to one side of the bottom of the flight controller.

[0012] Preferably, lap plates are fixedly connected to both sides of the inner wall of the roll cage, and a control rod is fixedly connected to one side of the top of the lap plate.

[0013] Preferably, a touch panel body is fixedly connected to one side of the top of the roll cage, and the touch panel body and the control rod are electrically connected to each other.

[0014] Preferably, both sides of the bottom of the installation frame are fixedly connected with supporting feet, and both sides of the surface of the supporting feet are fixedly connected with fixing sleeves.

[0015] Preferably, a connecting column is fixedly connected to one side of the inner wall of the fixed sleeve, a connecting box is inserted into one side of the bottom of the fixed sleeve, and the inner wall of the connecting box is sleeved on the surface of the connecting column.

[0016] Preferably, multiple groups of limit sliders are fixedly connected to both sides of the connection box, and the multiple groups of limit sliders are slidably connected to the inner wall of the fixed sleeve, and one side of the bottom of the connection box is fixedly connected to an anti-slip base plate.

[0017] Preferably, a plurality of groups of shock-absorbing springs are inserted into one side of the inner wall of the connection box, a damping shock absorber is inserted into the inner wall of the shock-absorbing spring, and the top end of the shock-absorbing spring is overlapped with the bottom of the connecting column.

[0018] Compared with the prior art, the beneficial effects of the utility model are:

[0019] (1) The aircraft can be controlled to move in any direction by using the speed difference of the rotors to generate forces in the X, Y, and Z directions. The three-axis six-propeller structure can maintain lift and balance even if one motor fails, thereby achieving the purpose of continuing to fly. The semi-open cockpit space can reduce the weight of the aircraft and is equipped with a corresponding anti-roll frame to effectively protect the safety of the driver.

[0020] (2) By arranging the supporting feet, the fixed sleeve, the connecting column, the connecting box, the limit slider, the anti-skid bottom plate, the shock-absorbing spring and the damping shock absorber, the aircraft contacts the ground through the anti-skid bottom plate when landing, and multiple groups of shock-absorbing springs and damping shock absorbers are arranged on the inner wall of the connecting box. The shock-absorbing springs and the damping shock absorbers contact the connecting column inside the fixed sleeve, and the connecting column and the shock-absorbing springs and the damping shock absorbers are buffered and damped, thereby achieving the effect of protecting the aircraft when landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is one of the three-dimensional diagrams of the utility model;

[0022] Figure 2 This is the second stereogram of the utility model;

[0023] Figure 3 A three-dimensional diagram of the roll cage of the utility model;

[0024] Figure 4 A three-dimensional diagram of the support foot of the utility model;

[0025] In the figure: 1. fuselage body; 2. mounting frame; 3. roll cage; 4. mounting frame; 5. protection frame; 6. connecting column; 7. motor; 8. rotor; 9. backrest; 10. flight controller; 11. lap plate; 12. touch panel body; 13. support foot; 14. fixing sleeve; 15. connecting column; 16. connecting box; 17. limit slider; 18. anti-slip bottom plate; 19. shock-absorbing spring; 20. damping shock absorber. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0027] Embodiment 1:

[0028] See also Figures 1 to 4 As shown, a three-axis six-propeller manned aircraft comprises:

[0029] Body 1;

[0030] The bottom of the back of the fuselage body 1 is fixedly connected with a mounting frame 2, the inner wall of the mounting frame 2 is fixedly connected with a battery pack, and one side of the back of the fuselage body 1 is fixedly connected with a roll cage 3;

[0031] Mounting frames 4 are fixedly connected to both sides of the mounting frame 2 and the back of the roll cage 3, a protective frame 5 is fixedly connected to one side of the surface of the mounting frame 4, a connecting column 6 is fixedly connected to the middle of the inner wall of the protective frame 5, a motor 7 is fixedly connected to the upper and lower ends of the connecting column 6, a rotor 8 is installed at the output end of the motor 7, a backrest 9 is fixedly connected to one side of the top of the mounting frame 2, a flight controller 10 is fixedly connected to the top of the back of the backrest 9, a parachute is fixedly connected to one side of the bottom of the flight controller 10, a lap plate 11 is fixedly connected to both sides of the inner wall of the roll cage 3, a joystick is fixedly connected to one side of the top of the lap plate 11, a touch panel body 12 is fixedly connected to one side of the top of the roll cage 3, and the touch panel body 12 and the joystick are electrically connected to each other.

[0032] Two sets of symmetrical rotors 8 are arranged on both sides and the tail of the aircraft, so that the lift of the aircraft is provided by six sets of rotors 8. Each two sets of rotors 8 are coaxial and distributed at three vertices of an equilateral triangle. Each set of coaxial rotors 8 rotates in opposite directions to resist the anti-torque generated by the rotors 8. All the upper rotors 8 rotate clockwise, and all the lower rotors 8 rotate counterclockwise. The speed difference of the rotors 8 is used to generate forces in the three directions of X, Y, and Z to control the movement of the aircraft in any direction.

[0033] The three-axis six-propeller form can maintain lift and balance even if one motor 7 fails, thereby achieving the purpose of continuing to fly. In the case of a layout with flight safety redundancy, the most streamlined layout is the three-axis six-propeller form. As a manned aircraft, it is the lightest aircraft with safety redundancy.

[0034] If one of the motors 7 stops, the flight controller 10 will control the other motor 7 to stop as well, and the three-axis six-propeller mode will become a three-axis four-propeller mode, that is, one axis still maintains the coaxial counter-propeller mode, and the other two axes become single motors 7, but the rotation directions are opposite. This is also a stable mode. In this mode, the aircraft continues to fly until landing.

[0035] The cockpit space formed inside the roll cage 3 is about 1.7 meters long and 0.7 meters wide, which can provide a comfortable single-person riding experience and a large-capacity cargo space. A parachute is installed at the tail, which plays a key protective role in emergencies. Due to the low flight altitude, the semi-open cockpit space can reduce the weight of the aircraft, and a corresponding roll cage is provided to effectively protect the safety of the driver.

[0036] Embodiment 2:

[0037] See also Figures 1 to 4As shown, both sides of the bottom of the installation frame 2 are fixedly connected with supporting feet 13, both sides of the surface of the supporting feet 13 are fixedly connected with fixed sleeves 14, one side of the inner wall of the fixed sleeve 14 is fixedly connected with a connecting column 15, one side of the bottom of the fixed sleeve 14 is plugged with a connecting box 16, and the inner wall of the connecting box 16 is sleeved on the surface of the connecting column 15, both sides of the connecting box 16 are fixedly connected with multiple groups of limit sliders 17, and the multiple groups of limit sliders 17 are slidably connected to the inner wall of the fixed sleeve 14, one side of the bottom of the connecting box 16 is fixedly connected with an anti-slip bottom plate 18, and the connecting box A plurality of shock absorbing springs 19 are inserted into one side of the inner wall of 16, and a damping shock absorber 20 is inserted into the inner wall of the shock absorbing spring 19, and the top end of the shock absorbing spring 19 is overlapped with the bottom of the connecting column 15, and contacts the ground through the anti-skid bottom plate 18, and a plurality of shock absorbing springs 19 and damping shock absorbers 20 are arranged on the inner wall of the connecting box 16, and the connecting column 15 inside the fixed sleeve 14 is contacted by the shock absorbing spring 19 and the damping shock absorber 20, and the connecting column 15 and the shock absorbing spring 19 and the damping shock absorber 20 are buffered and damped, thereby achieving the effect of protecting the aircraft when landing.

[0038] In the description of the present utility model, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. The meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0039] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0040] In the drawings of the embodiments disclosed in the present utility model, only the structures related to the embodiments disclosed in the present utility model are involved, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present utility model can be combined with each other.

[0041] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A three-axis six-propeller manned aircraft, characterized in that: include: The main body of the fuselage (1); The bottom of the back side of the fuselage main body (1) is fixedly connected to a mounting frame (2), the inner wall of the mounting frame (2) is fixedly connected to a battery pack, and one side of the back side of the fuselage main body (1) is fixedly connected to an anti-roll cage (3); Both sides of the installation frame (2) and the back of the anti-roll cage (3) are fixedly connected with installation frames (4), one side of the surface of the installation frame (4) is fixedly connected with a protection frame (5), the middle of the inner wall of the protection frame (5) is fixedly connected with a connecting column (6), the upper and lower ends of the connecting column (6) are fixedly connected with a motor (7), and the output end of the motor (7) is equipped with a rotor (8).

2. A three-axis six-propeller manned aircraft according to claim 1, characterized in that: A backrest (9) is fixedly connected to one side of the top of the installation frame (2), a flight controller (10) is fixedly connected to the top of the back of the backrest (9), and a parachute is fixedly connected to one side of the bottom of the flight controller (10).

3. A three-axis six-propeller manned aircraft according to claim 1, characterized in that: Both sides of the inner wall of the anti-roll cage (3) are fixedly connected with lap plates (11), and one side of the top of the lap plate (11) is fixedly connected with a control rod.

4. The three-axis six-propeller manned aircraft according to claim 1, characterized in that: A touch panel body (12) is fixedly connected to one side of the top of the anti-roll cage (3), and the touch panel body (12) and the control rod are electrically connected to each other.

5. The three-axis six-propeller manned aircraft according to claim 1, characterized in that: Support legs (13) are fixedly connected to both sides of the bottom of the installation frame (2), and fixed sleeves (14) are fixedly connected to both sides of the surface of the support legs (13).

6. A three-axis six-propeller manned aircraft according to claim 5, characterized in that: A connecting column (15) is fixedly connected to one side of the inner wall of the fixed sleeve (14), a connecting box (16) is inserted into one side of the bottom of the fixed sleeve (14), and the inner wall of the connecting box (16) is sleeved on the surface of the connecting column (15).

7. A three-axis six-propeller manned aircraft according to claim 6, characterized in that: Multiple groups of limit sliders (17) are fixedly connected to both sides of the connection box (16), and the multiple groups of limit sliders (17) are slidably connected to the inner wall of the fixed sleeve (14), and one side of the bottom of the connection box (16) is fixedly connected to an anti-slip bottom plate (18).

8. The three-axis six-propeller manned aircraft according to claim 6, characterized in that: A plurality of groups of shock absorbing springs (19) are inserted into one side of the inner wall of the connection box (16), a damping shock absorber (20) is inserted into the inner wall of the shock absorbing spring (19), and the top end of the shock absorbing spring (19) is overlapped with the bottom of the connection column (15).

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