Air-ground amphibious aircraft

Abstract

The utility model discloses an air-ground amphibious aircraft, which belongs to the technical field of vehicles, and comprises a rack, and a pavement power system, an energy module, an undercarriage system, a flight power system, a lead screw control system and a control module which are arranged on the rack, the undercarriage system comprises undercarriage auxiliary wheels and a driving mechanism; the flight power system comprises a propeller, a motor and an electronic speed controller; the lead screw control system comprises a servo driver, a servo motor and a lead screw mechanism. The control module comprises a switcher and a hub motor controller, an undercarriage controller, a flight controller and a screw rod pushing controller which are electrically connected with the switcher, the hub motor controller is electrically connected with the road surface power system, the undercarriage controller is electrically connected with the undercarriage system, the flight controller is electrically connected with the flight power system, and the screw rod pushing controller is electrically connected with the screw rod pushing controller. And the screw rod pushing controller is electrically connected with the screw rod control system.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of vehicle technology, in particular to a kind of amphibious aircraft. BACKGROUND

[0002] With the emergence of road congestion and vehicle congestion in big cities more and more, the traditional ground traffic route is continuously developed to space three-dimensional traffic, but only through underground subway passage or road overpass construction cannot effectively solve the problem, at present, in order to better utilize the air area to reduce congestion, air vehicle gradually enters people's field of vision.

[0003] Chinese patent CN208881509U proposes a flying motorcycle, although it can travel on road and in the air respectively, but still has the following problems:

[0004] (1) when driving in the air, the frame form of motorcycle makes the driver bear excessive wind and airflow, which affects driving safety;

[0005] (2) the device lacks landing auxiliary device, and there is a safety hazard when landing;

[0006] (3) the number of propellers is less, and the flying power is insufficient.

[0007] Therefore, a new amphibious aircraft is needed to solve the above problems. SUMMARY

[0008] In view of the above problems, the purpose of the present application is to provide an amphibious aircraft with sufficient power, safe driving and safe landing.

[0009] In order to achieve the above purpose, the present application provides the following technical scheme: an amphibious aircraft, comprising a frame, a road power system, a flight power system, a landing gear system, a lead screw control system, an energy module and a control module; the road power system, the flight power system, the landing gear system, the lead screw control system, the energy module and the control module are fixedly arranged on the frame.

[0010] As a preferred structure of the present application, the landing gear system comprises landing gear auxiliary wheels and a driving mechanism; the flight power system comprises propellers, motors and electronic governors; the lead screw control system comprises servo drives, servo motors and lead screw mechanisms; the control module comprises a switch and a hub motor controller, a landing gear controller, a flight controller and a lead screw pushing controller electrically connected with the switch, the hub motor controller and the road power system are electrically connected, the landing gear controller and the landing gear system are electrically connected, the flight controller and the flight power system are electrically connected, and the lead screw pushing controller and the lead screw control system are electrically connected.

[0011] As a preferred structure of the present application, the propeller is provided with four groups of eight, each group of propeller is movably connected with a motor, the flight controller can control the motor to make the propeller retract inward.

[0012] As a preferred structure of the present application, the two propellers of each group are symmetrically arranged up and down.

[0013] As a preferred structure of the present application, the landing gear auxiliary wheel is two, symmetrically arranged left and right.

[0014] As a preferred structure of the present application, the servo driver drives the screw rod mechanism through the servo motor.

[0015] As a preferred structure of the present application, the rack is designed as a closed carriage type, the top of the roof is fixedly connected with a screw rod control system, a car cover is arranged above the screw rod control system, and the roof and the car cover are detachably connected.

[0016] Compared with the prior art, the present application has the following advantages:

[0017] (1) The rack of the present application is designed as a closed carriage type, which can avoid the influence of wind and airflow on the driver even when flying in the air;

[0018] (2) The landing gear system of the present application is provided with two landing gear auxiliary wheels arranged symmetrically, which can make the driving more stable on the road and make the aircraft landing more safely, and the buffer mechanism provides landing buffer to avoid excessive pressure when landing;

[0019] (3) The present application is provided with four groups of eight propellers to provide greater flight power. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is an overall structure diagram of the amphibious aircraft of the present application Figure One .

[0021] Figure 2 It is an overall structure diagram of the amphibious aircraft of the present application Figure Two .

[0022] Figure 3 It is a flight power structure diagram of the amphibious aircraft of the present application.

[0023] Figure 4 It is a screw rod pushing structure diagram of the amphibious aircraft of the present application.

[0024] Figure 5 It is a landing gear structure diagram of the amphibious aircraft of the present application.

[0025] Figure 6The block diagram of the road power system of the amphibious aircraft.

[0026] Figure 7 The block diagram of the landing gear system of the amphibious aircraft.

[0027] Figure 8 The block diagram of the flight power system of the amphibious aircraft.

[0028] Figure 9 The block diagram of the lead screw control system of the amphibious aircraft.

[0029] Figure 10 The block diagram of the control module of the amphibious aircraft.

[0030] In the figure: 1, frame; 2, road power system; 3, energy module; 4, landing gear system; 5, flight power system; 6, lead screw control system; 7, control module; 11, roof; 12, cover; 21, wheel hub motor; 22, front wheel; 23, rear wheel; 41, landing gear auxiliary wheel; 42, driving mechanism; 43, buffer mechanism; 51, propeller; 52, motor; 53, electronic speed controller; 61, servo driver; 62, servo motor; 63, lead screw mechanism; 71, switch; 72, wheel hub motor controller; 73, landing gear controller; 74, flight controller; 75, lead screw push controller. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the present application clearer, the present application is further described in detail below in combination with the drawings and examples.

[0032] REFERENCE Figures 1 to 10The amphibious aircraft comprises a frame 1, a road power system 2, an energy module 3, a landing gear system 4, a flight power system 5, a screw rod control system 6 and a control module 7 which are arranged on the frame 1; the road power system 2 comprises a hub motor 21, a front wheel 22 and a rear wheel 23; the landing gear system 4 comprises a landing gear auxiliary wheel 41, a driving mechanism 42 and a buffer mechanism 43; the flight power system 5 comprises a propeller 51, a motor 52 and an electronic speed controller 53; the screw rod control system 6 comprises a servo driver 61, a servo motor 62 and a screw rod mechanism 63; the control module 7 comprises a switch 71 and a hub motor controller 72, a landing gear controller 73, a flight controller 74 and a screw rod pushing controller 75 which are electrically connected with the switch 71, the hub motor controller 72 is electrically connected with the road power system 2, the landing gear controller 73 is electrically connected with the landing gear system 4, the flight controller 74 is electrically connected with the flight power system 6, and the screw rod pushing controller 75 is electrically connected with the screw rod control system 6; the energy module 3 comprises a lithium battery which supplies power for the road power system 2, the landing gear system 4, the flight power system 5, the screw rod control system 6 and the control module 7.

[0033] As a preferred structure of the embodiment, the propeller 51 is provided with four groups of eight, each group of propeller is movably connected with a motor 52, and the flight controller 74 can control the motor 52 to make the propeller 51 retract inward.

[0034] As a preferred structure of the embodiment, the two propellers in each group are symmetrically arranged upward and downward.

[0035] As a preferred structure of the embodiment, the landing gear auxiliary wheel 41 is two, which are symmetrically arranged left and right.

[0036] As a preferred structure of the embodiment, the servo driver 61 drives the screw rod mechanism 63 through the servo motor 62.

[0037] As a preferred structure of the embodiment, the frame 1 is designed in a closed carriage type, the screw rod control system 6 is fixedly connected to a roof 11, a car cover 12 is arranged above the screw rod control system 6, and the roof 11 and the car cover 12 are detachably connected.

[0038] The above only describes the preferred embodiments of the present application, and it should be pointed out that those skilled in the art can make some improvements and refinements without departing from the principles of the present application, and these improvements and refinements should also be considered as the protection scope of the present application.

Claims

1. An amphibious aircraft, characterized in that: The land-air amphibious aircraft comprises a frame (1), a road power system (2), an energy module (3), a landing gear system (4), a flight power system (5), a lead screw control system (6) and a control module (7) arranged on the frame (1); the road power system (2) comprises a hub motor (21), a front wheel (22) and a rear wheel (23); the landing gear system (4) comprises a landing gear auxiliary wheel (41), a driving mechanism (42) and a buffer mechanism (43); the flight power system (5) comprises a propeller (51), a motor (52) and an electronic governor (53); the lead screw control system (6) comprises a servo driver (61), a servo motor (62) and a lead screw mechanism (63); the control module (7) comprises a switch (71) and a hub motor controller (72), a landing gear controller (73), a flight controller (74) and a lead screw pushing controller (75) electrically connected with the switch (71); the hub motor controller (72) is electrically connected with the road power system (2), the landing gear controller (73) is electrically connected with the landing gear system (4), the flight controller (74) is electrically connected with the flight power system (5), and the lead screw pushing controller (75) is electrically connected with the lead screw control system (6).

2. The land-air amphibious aircraft according to claim 1, wherein: the energy module (3) comprises a lithium battery, which supplies power to the road power system (2), the landing gear system (4), the flight power system (5), the lead screw control system (6) and the control module (7).

3. The land-air amphibious aircraft according to claim 1, wherein: the propeller (51) is provided with four groups of eight propellers, each group of propellers is movably connected with a motor (52), and the flight controller (74) can control the motor (52) to make the propeller (51) retract inward.

4. The land-air amphibious aircraft according to claim 3, wherein: the two propellers in each group are symmetrically arranged up and down.

5. The land-air amphibious aircraft according to claim 1, wherein: the landing gear auxiliary wheel (41) is two, which are symmetrically arranged left and right.

6. The land-air amphibious aircraft according to claim 1, wherein: the servo driver (61) drives the lead screw mechanism (63) through the servo motor (62).

7. The land-air amphibious aircraft according to claim 1, wherein: the frame (1) is designed in a closed carriage type, the lead screw control system (6) is fixedly connected to a roof (11), a car cover (12) is arranged above the lead screw control system (6), and the roof (11) and the car cover (12) are detachably connected.

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