Three-split flying car

Abstract

The utility model provides a three-split flying car. The flying efficiency of the hovercar is mainly improved. According to the scheme, the aircraft comprises an aircraft body, a cockpit and an automobile chassis; the aircraft, the cockpit and the automobile chassis are sequentially connected and fixed from top to bottom; the aircraft comprises a fuselage, working wings and a duct structure. The working wings and the duct structure are used for providing power for the aircraft; according to the hovercar, the overall structure and aerodynamic layout of the hovercar are optimized, the flying efficiency, safety and reliability of the hovercar are improved, and the energy consumption ratio of the hovercar is reduced.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of flying cars, and particularly relates to a three-part flying car. BACKGROUND

[0002] At present, with the acceleration of urbanization, the aggravation of traffic congestion and the increasingly serious environmental problems, the fusion of flying vehicles and cars will become an important solution for future urban travel. As a key innovation of low-altitude economy, flying cars that integrate vertical take-off and landing technology can take off and fly flexibly and quickly in urban airspace, greatly relieving traffic pressure and reducing carbon emissions.

[0003] Therefore, in recent years, the research on flying cars has been focused on the three-part flying car, which can realize ground driving and air flight, and switch according to the two motion states. However, the existing three-part flying car has the following problems: ① When a four-rotor three-part is used, the flying car is a simple coupling of a four-rotor flying vehicle and a car. During flight, only four rotors provide flight lift and thrust, resulting in high energy consumption and low flight efficiency. Any propeller failure will cause a safety accident. ② When a multi-rotor design is used for flight, the number of propellers is increased, so that the flying car has a certain robustness. However, the structure has low flight efficiency, especially during cruise flight and long-distance flight, the energy consumption ratio is relatively high, and the endurance is insufficient. ③ When a compound wing of rotors and fixed wings is used, the aerodynamic force is used during cruise flight, which greatly improves the flight safety. However, the thrust is insufficient during flight, resulting in low flight efficiency. Therefore, the existing three-part flying car has the problem of low flight efficiency, and the overall structure and aerodynamic layout of the flying car need to be optimized. SUMMARY

[0004] In order to overcome the shortcomings of the prior art and improve the flight efficiency of the flying car, the present application provides a three-part flying car.

[0005] A three-part flying car, comprising a flying vehicle 1, a cockpit 2 and a car chassis 3; the flying vehicle 1, the cockpit 2 and the car chassis 3 are connected and fixed in sequence from top to bottom;

[0006] The cockpit 2 is a cuboid; the windward surface and the leeward surface of the cockpit 2 are curved surfaces; the top surface of the cockpit 2 is provided with a first docking device 21; the bottom surface of the cockpit 2 is provided with a second docking device 22; the side surface of the cockpit 2 is provided with a cabin door; the first docking device 21 and the second docking device 22 are both long strip-shaped sliding grooves; the sliding groove cross section of the first docking device 21 and the second docking device 22 is a “concave” shape;

[0007] The aircraft 1 includes a fuselage 11, a working wing, a duct structure 13 and a landing gear 14; the fuselage 11 is a cuboid; the top surface of the fuselage 11 is streamlined in the chord direction; the leeward surface of the fuselage 11 is provided with the duct structure 13; the two sides of the fuselage 11 in the chord direction are provided with the working wing; the bottom surface of the fuselage 11 is provided with the first docking slide rail; after the first docking slide rail is connected with the first docking device 21 in sliding mode, the aircraft 1 and the cockpit 2 are fixed; the bottom surface of the fuselage 11 is provided with the landing gear 14;

[0008] The top surface of the automobile chassis 3 is provided with the second docking slide rail; the second docking slide rail is connected with the second docking device in sliding mode.

[0009] Further, the working wing includes a front wing, a main wing, a support rod and a plurality of lift propellers 124; the front wing includes a left front wing 121 and a right front wing 121'; the left front wing 121 and the right front wing 121' are respectively arranged symmetrically on the two sides of the fuselage 11 in the forward direction; the main wing includes a left main wing 122 and a right main wing 122'; the left main wing 122 and the right main wing 122' are respectively arranged symmetrically on the two sides of the fuselage 11 in the chord direction; the front wing is forward-swept; the main wing is backward-swept, forming an X-shaped tandem wing layout; the X-shaped tandem wing layout optimizes lift and aerodynamic efficiency, improves stability and controllability;

[0010] The support rod includes a left support rod 123 and a right support rod 123'; the left support rod 123 and the right support rod 123' are respectively arranged symmetrically on the two sides of the fuselage 11 in the forward direction; the left support rod 123 and the right support rod 123' are both long strips; the top surface of the left support rod 123 and the right support rod 123' is fixedly connected with the bottom surface of the main wing; the side surface of the left support rod 123 is provided with a first through hole; the side surface of the right support rod 123' is provided with a second through hole; the wing tip of the left front wing 121 passes through the first through hole and is fixed with the left support rod 123; the wing tip of the right front wing 121' passes through the second through hole and is fixed with the right support rod 123';

[0011] The bottom surface of the left support rod 123 and the right support rod 123' is provided with a plurality of lift propellers 124; the lift propellers are symmetrically distributed along the chord direction of the fuselage 11;

[0012] The inside of the left support rod 123 is provided with a first driving motor set; the first driving motor set includes a plurality of driving motors; the number of driving motors of the first driving motor set is the same as the number of lift propellers of the left support rod; the driving motors of the first driving motor set are connected with the lift propellers of the left support rod one by one, for providing power;

[0013] The second driving motor set is arranged inside the right support rod 123', and comprises a plurality of driving motors. The number of the driving motors of the second driving motor set is the same as the number of the lift propellers of the right support rod. The driving motors of the second driving motor set are connected with the lift propellers of the right support rod one by one, and are used for providing power.

[0014] The driving motors of the first driving motor set and the second driving motor set are connected with a controller respectively. The controller is arranged inside the fuselage 11.

[0015] Further, the duct structure 13 comprises a thrust fan 131, a thrust fan fairing 132 and a driving device. The thrust fan fairing 132 is arranged on the leeward surface of the fuselage 11. The thrust fan 131 is arranged inside the thrust fan fairing 132. The thrust fan 131 is connected with a third driving motor. The third driving motor is arranged inside the fuselage 11. The third driving motor is connected with the controller. The number of the thrust fans 131 is even, and the thrust fans 131 are symmetrically arranged along the chord direction of the fuselage. The thrust fan fairing 132 is provided with a spoiler 133. The spoiler 133 is arranged at the air outlet of the thrust fan 131. The spoiler 133 is a long rectangular thin plate. The spoiler 133 is used for improving the stability of airflow, enhancing the aerodynamic performance, and enhancing the flight stability and controllability.

[0016] Further, the tail of the spoiler 133 along the forward direction is provided with a rudder 134. The rudder 134 is a long rectangular thin plate.

[0017] Further, a plurality of hinge holes are arranged on the first docking slide rail and the first docking device correspondingly, and a plurality of hinge holes are arranged on the second docking slide rail and the second docking device correspondingly, so as to improve the reliability of connection.

[0018] Further, the wing tips of the main wings are respectively provided with heading stabilizers 127, so as to provide the static stability of heading control, and improve the flight stability of the flying car.

[0019] Further, the trailing edge of the left front wing 121 is provided with a first elevator 125. The trailing edge of the right front wing 121' is provided with a second elevator 125'. The first elevator 125 is arranged between the wing root and the left support rod. The second elevator 125' is arranged between the wing root and the right support rod.

[0020] The trailing edge of the left main wing 122 is provided with a first aileron 126. The trailing edge of the right main wing 122' is provided with a second aileron 126'. The positions of the first aileron 126 and the second aileron 126' are close to the wing tips of the left main wing 122 and the right main wing 122' respectively.

[0021] Further, the cockpit bottom is provided with a high-speed connector pin; the automobile chassis 3 is provided with a high-speed connector socket; the high-speed connector is used for transmitting power and control signals, and adopts CAN FD protocol to transmit steering wheel angle and throttle depth signals.

[0022] Further, the cockpit top is provided with a fiber-optic communication ring; when the cockpit is connected with the aircraft 1, an optical communication link is established through the fiber-optic communication ring, and FlexRay protocol is used to transmit lift propeller and thrust duct fan rotating speed, pitch / roll angle instructions.

[0023] The beneficial effects of the present application are:

[0024] In the present application, the first and second docking devices are introduced into the cockpit to facilitate the switching between the ground driving mode and the flight mode, wherein the first docking device is used for slidingly connecting the aircraft, and the second docking device is used for slidingly connecting the automobile chassis; when an electronic locking structure such as an electronic bolt is further introduced, the safety and docking reliability of the flying car structure are greatly enhanced; in addition, the aircraft of the present application comprises a fuselage, working wings and a duct structure, wherein the working wings are arranged on both sides of the fuselage, and the duct structure is arranged at the tail of the fuselage, thereby realizing the optimization of the overall structure and aerodynamic layout of the flying car; the working wings are used to provide power in the vertical take-off and landing stage, and the working wings and the duct structure are used to jointly provide power in the cruising stage, thereby improving the flight efficiency, safety and reliability of the flying car, and reducing the energy consumption ratio of the flying car. Preferably, in the duct structure, the rudder is integrated with the thrust fan, so that the rudder is in the slipstream of the propeller, thereby improving the control efficiency of the rudder. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is an overall structure schematic view when the aircraft, the cockpit and the automobile chassis are connected in the present flying car;

[0026] Figure 2 It is a three-dimensional structure schematic view of the present aircraft;

[0027] Figure 3 It is a top view structure schematic view of the present aircraft;

[0028] Figure 4 It is a structure schematic view of the cockpit top provided with the first docking device;

[0029] Figure 5 It is a structure schematic view of the cockpit bottom provided with the second docking device;

[0030] Figure 6 It is a flight mode structure schematic view of the present flying car;

[0031] Figure 7The structure schematic diagram of the ground driving mode of the present flying automobile;

[0032] 1, the aircraft; 2, the cockpit; 3, the automobile chassis; 11, the fuselage; 13, the duct structure; 14, the landing gear; 21, the first docking device; 22, the second docking device; 121, the left front wing; 121', the right front wing; 122, the left main wing; 122', the right main wing; 123, the left strut; 123', the right strut; 124, the lift propeller; 125, the first elevator; 125', the second elevator; 126, the first aileron; 126', the second aileron; 127, the heading stabilizer; 131, the thrust fan; 132, the thrust fan fairing; 133, the spoiler; 134, the rudder. DETAILED DESCRIPTION

[0033] A three-part flying automobile, comprising an aircraft 1, a cockpit 2 and an automobile chassis 3; the aircraft 1, the cockpit 2 and the automobile chassis 3 are sequentially connected and fixed from top to bottom;

[0034] The cockpit 2 is a cuboid; the windward surface and the leeward surface of the cockpit 2 are curved surfaces; the top surface of the cockpit 2 is provided with a first docking device 21; the bottom surface of the cockpit 2 is provided with a second docking device 22; the side surface of the cockpit 2 is provided with a cabin door; the first docking device 21 and the second docking device 22 are both long strip-shaped sliding grooves; the sliding groove cross section of the first docking device 21 and the second docking device 22 is a "concave" shape;

[0035] The aircraft 1 comprises a fuselage 11, working wings, a duct structure 13 and a landing gear 14; the fuselage 11 is a cuboid; the top surface of the fuselage 11 is a streamlined cross section along the chord direction; the leeward surface of the fuselage 11 is provided with a duct structure 13; the two side surfaces of the fuselage 11 along the chord direction are provided with working wings; the bottom surface of the fuselage 11 is provided with a first docking sliding rail; after the first docking sliding rail is slidingly connected with the first docking device 21, the aircraft 1 and the cockpit 2 are fixed; the bottom surface of the fuselage 11 is provided with a landing gear 14;

[0036] The working wings comprise front wings, main wings, struts and a plurality of lift propellers 124; the front wings comprise left front wings 121 and right front wings 121'; the left front wings 121 and the right front wings 121' are respectively symmetrically arranged on the two sides of the forward direction of the fuselage 11; the main wings comprise left main wings 122 and right main wings 122'; the left main wings 122 and the right main wings 122' are respectively symmetrically arranged on the two sides of the fuselage 11 along the chord direction; the front wings are forward-swept; the main wings are backward-swept, forming an X-shaped tandem wing layout; in the X-shaped tandem wing layout, the front wings are forward-swept and the main wings are backward-swept, optimizing the lift and aerodynamic efficiency and improving the stability and controllability;

[0037] The support rod comprises a left support rod 123 and a right support rod 123'; the left support rod 123 and the right support rod 123' are symmetrically arranged on the two sides of the front direction of the fuselage 11 respectively; the left support rod 123 and the right support rod 123' are both long strips; the top surface of the left support rod 123 and the right support rod 123' is fixedly connected with the bottom surface of the main wing; the side surface of the left support rod 123 is provided with a first through hole; the side surface of the right support rod 123' is provided with a second through hole; the wing tip of the left front wing 121 passes through the first through hole and is fixed with the left support rod 123; the wing tip of the right front wing 121' passes through the second through hole and is fixed with the right support rod 123';

[0038] The bottom surface of the left support rod 123 and the right support rod 123' is provided with a plurality of lift propellers 124; the lift propellers are symmetrically distributed along the chord direction of the fuselage 11; in this structure, the working wing adopts a combined structure of fixed wings and lift propellers 124, and the flight anti-stall characteristics are far superior to those of fixed-wing flying cars, ducted flying cars, multi-modal rotor flying cars or composite wing split flying cars, the flight efficiency is greatly improved, the structural integration is realized, and excellent aerodynamic efficiency is also considered;

[0039] The inside of the left support rod 123 is provided with a first driving motor set; the first driving motor set comprises a plurality of driving motors; the number of driving motors of the first driving motor set is the same as the number of lift propellers of the left support rod, and the driving motors of the first driving motor set are connected with the lift propellers of the left support rod one by one for providing power;

[0040] The inside of the right support rod 123' is provided with a second driving motor set; the second driving motor set comprises a plurality of driving motors; the number of driving motors of the second driving motor set is the same as the number of lift propellers of the right support rod; the driving motors of the second driving motor set are connected with the lift propellers of the right support rod one by one for providing power;

[0041] The driving motors of the first driving motor set and the second driving motor set are respectively connected with a controller; the controller is arranged inside the fuselage 11;

[0042] A plurality of hinged holes are correspondingly arranged on the slide rail and the slide groove to improve the reliability of connection;

[0043] The wing tip positions of the main wing are respectively provided with heading stabilizers 127 to provide static stability for heading control and improve the flight stability of the flying car;

[0044] The duct structure 13 comprises a thrust fan 131, a thrust fan fairing 132 and a driving device; the thrust fan fairing 132 is arranged on the leeward surface of the fuselage 11; the thrust fan 131 is arranged in the thrust fan fairing 132; the thrust fan 131 is connected with a third driving motor; the third driving motor is arranged inside the fuselage 11; the third driving motor is connected with the controller;

[0045] The number of the thrust fans 131 is even, and they are symmetrically arranged left and right along the chord direction of the fuselage;

[0046] The thrust fan cowl 132 is provided with a spoiler 133; the spoiler 133 is arranged at the air outlet of the thrust fan 131; the spoiler 133 is a long rectangular thin plate; the spoiler 133 is used to improve the stability of airflow, enhance aerodynamic performance, and enhance flight stability and controllability;

[0047] The tail of the spoiler 133 in the forward direction is provided with a rudder 134, which is a long rectangular thin plate; the rudder 134 facilitates the control of the air car to perform yaw movement;

[0048] In this structure, the heading control adopts the composite form of the thrust fan 131 and the spoiler 133, instead of the traditional rudder surface, which increases the control efficiency, increases the flight thrust, realizes power redundancy, and greatly improves the safety of the aircraft; the thrust fan cowl 132 and the spoiler 133 work together to adjust and guide the airflow, reduce noise, reduce airflow vortex and turbulence, and improve flight efficiency;

[0049] The trailing edge of the left front wing 121 is provided with a first elevator 125; the trailing edge of the right front wing 121' is provided with a second elevator 125'; the first elevator 125 is arranged between the wing root and the left strut; the second elevator 125' is arranged between the wing root and the right strut;

[0050] The trailing edge of the left main wing 122 is provided with a first aileron 126; the trailing edge of the right main wing 122' is provided with a second aileron 126'; the positions of the first aileron 126 and the second aileron 126' are close to the wing tips of the left main wing 122 and the right main wing 122' respectively;

[0051] The elevator controls the pitch movement of the air car, and the aileron controls the roll movement of the air car, which facilitates the control of the air car;

[0052] The top surface of the car chassis 3 is provided with a second docking slide rail; the second docking slide rail is in sliding connection with the second docking device;

[0053] The bottom of the cockpit is provided with a high-speed connector pin; the car chassis 3 is provided with a high-speed connector socket; the high-speed connector is used to transmit power and control signals, and adopts CAN FD protocol to transmit the steering wheel angle and throttle depth signals;

[0054] The cockpit top is provided with a fiber optical communication ring; when the cockpit is connected with the aircraft 1, an optical communication link is established through the fiber optical communication ring, and the rotation speed of the lift propeller and the thrust duct fan, the pitch / roll angle command are transmitted by using the FlexRay protocol;

[0055] The application will be further described below in conjunction with the drawings and embodiments.

[0056] As Figure 1 shown, a three-part flying car includes an aircraft 1, a cockpit 2 and a car chassis 3, wherein the aircraft 1 is used to drive the cockpit 2 to fly in the flight mode, the car chassis 3 is used to drive the cockpit 2 to drive on the ground in the ground driving mode, and the car chassis 3 can be provided with wheels for ground driving; the cockpit 2 can be unmanned or manned. When it is unmanned, intelligent unmanned driving can be realized through the intervention of the control system.

[0057] As Figure 4 and Figure 5 shown, the cockpit 2 is provided with a first docking device 21 and a second docking device 22, the first docking device 21 is used to slide connect the aircraft 1, and the second docking device 22 is used to slide connect the car chassis 3. The aircraft 1 includes a fuselage 11, working wings and a duct structure 13, the working wings are arranged on both sides of the fuselage 11, the duct structure 13 is arranged at the tail of the fuselage 11, and the working wings and the duct structure 13 are used to provide power for the aircraft 1.

[0058] In the utility model, on the one hand, the aircraft 1 adopts the combined form of working wings and a duct structure 13, realizes the optimization of the overall structure and the aerodynamic layout of the flying car, uses the working wings to provide power in the vertical take-off and landing stage, uses the working wings and the duct structure 13 to jointly provide power in the cruising stage, improves the flight efficiency, safety and reliability of the flying car, and reduces the energy consumption ratio of the flying car; on the other hand, the cockpit 2 is slide connected through the first docking device 21 and the second docking device 22, ensures the connection convenience and reliability between the three-part modules, and facilitates the switching between the ground driving mode and the flight mode. In addition, the overall application of the three-part flying car solves the dead weight problem existing in the ground driving, and increases the flexibility of the overall structure.

[0059] As Figure 2 and Figure 3As shown, in order to make the specific structure of the working wing clear, the working wing comprises a front wing 121 and a main wing 122, a strut 123 is arranged between the front wing 121 and the main wing 122, and a plurality of lift propellers 124 are arranged at the bottom of the strut 123. In this structure, the working wing adopts a combined structure of fixed wings and lift propellers 124, the flight stall-resistant performance is far superior to that of a fixed-wing flying car, a ducted flying car, a multi-modal rotor flying car or a compound wing split flying car, the flight efficiency is greatly improved, the structural integration is realized, and excellent aerodynamic efficiency is taken into account.

[0060] In the above structure, the lift propellers 124 on the strut 123 are arranged in multiple, for example, four on the left and right, to ensure that sufficient power is provided.

[0061] In the present flying car, in order to reduce the size of the aircraft 1 and reduce the wet area and fuselage resistance of the aircraft 1, the front wing 121 is swept forward and the main wing 122 is swept backward to form an X-shaped tandem wing layout. In the X-shaped tandem wing layout, the front wing 121 is swept forward and the main wing 122 is swept backward, which optimizes the lift and aerodynamic efficiency and improves the stability and controllability.

[0062] In order to facilitate the control of the flying car, an elevator 125 is arranged on the front wing 121 and an aileron 126 is arranged on the main wing 122, the elevator 125 controls the pitching motion of the flying car, and the aileron 126 controls the rolling motion of the flying car.

[0063] In order to improve the flight stability of the present flying car, a directional stabilizer 127 is arranged at both ends of the main wing 122 to provide static stability for directional control and improve the flight stability of the flying car.

[0064] In the present flying car, in order to make the specific structure of the duct structure 13 clear, the duct structure 13 comprises a thrust fan 131, a thrust fan fairing 132 and a driving device, the thrust fan fairing 132 is arranged at the tail of the fuselage 11, the thrust fan 131 is arranged in the thrust fan fairing 132, the driving device is arranged on the aircraft 1, and the driving device is electrically connected with the thrust fan 131.

[0065] Among them, the thrust fan 131 can be two, and the left and right are symmetrically arranged.

[0066] Preferably, to increase the control efficiency, the outer side of the thrust fan cowl 132 is connected with a spoiler 133 and a rudder 134, wherein: the spoiler 133 is used to improve the stability of the airflow, enhance the aerodynamic performance, enhance the flight stability and controllability; the rudder 134 facilitates the control of the flying car to perform the yaw movement. In the structure, the heading control adopts the composite form of the thrust fan 131 and the spoiler 133, instead of the traditional rudder surface, which increases the control efficiency, increases the flight thrust, realizes the power redundancy, and greatly improves the safety of the flying vehicle; and the thrust fan cowl 132 and the spoiler 133 jointly act to adjust and guide the airflow, reduce the noise, reduce the airflow vortex and turbulence, and improve the flight efficiency.

[0067] To support the take-off and landing of the flying car, landing gears 14 are arranged on both sides of the fuselage 11.

[0068] To clearly show the specific structure of the first docking device 21 and the second docking device 22, the first docking device 21 and the second docking device 22 are both in sliding connection with the slide rail and the slide groove. The cross section of the slide groove can be concave.

[0069] Further, a plurality of hinge holes are correspondingly arranged on the slide rail and the slide groove to improve the reliability of the connection.

[0070] As shown in Figure 4 and Figure 5 To clearly show the setting form of the slide rail and the slide groove, the top and the bottom of the cockpit 2 are respectively provided with the slide groove, and at this time, the bottom of the fuselage 11 of the flying vehicle 1 is provided with a slide rail connected with the top slide groove of the cockpit 2, and the top of the automobile chassis 3 is provided with a slide rail connected with the bottom slide groove of the cockpit 2.

[0071] In addition, when the cockpit 2 is provided with the slide rail, the slide groove can be arranged at the corresponding connection position of the flying vehicle 1 and the automobile chassis 3.

[0072] To enhance the safety redundancy and reliability between the structure connections, the first docking device 21 and the second docking device 22 are both provided with an electromagnetic latch, the slide rail and the slide groove are provided with a latch hole through which the electromagnetic latch passes, the electromagnetic latch is provided with a mounting base, and the mounting base is fixedly connected to a preset mounting position of the cockpit 2. The preset mounting position can be determined according to the docking position, that is, after the electromagnetic latch is installed, the electromagnetic latch can pass through the latch hole on the slide rail and the slide groove.

[0073] In addition, the two sides of the cockpit 2 can be provided with cabin doors for passengers to get on and off.

[0074] The preferred working mode of the flying car is described as follows:

[0075] As shown in Figure 6As shown, the flying mode structure diagram of the flying car, the top of the cockpit 2 is connected to the aircraft 1 through the first docking device 21. Among them: in the vertical take-off and landing stage, mainly rely on multiple lift propellers 124 to provide main lift; in the cruising stage, rely on the thrust fan 131 to provide thrust, the front wing 121 and the main wing 122 generate aerodynamic lift, through the rudder 134, the front wing 121 and the main wing 122 to control the attitude of the rudder surface.

[0076] As shown, the flying mode structure diagram of the flying car, the top of the cockpit 2 is connected to the aircraft 1 through the first docking device 21. Among them: in the vertical take-off and landing stage, mainly rely on multiple lift propellers 124 to provide main lift; in the cruising stage, rely on the thrust fan 131 to provide thrust, the front wing 121 and the main wing 122 generate aerodynamic lift, through the rudder 134, the front wing 121 and the main wing 122 to control the attitude of the rudder surface. Figure 7

[0077] The cockpit as the control center, can be through the reserved independent circuit interface, and use multi-protocol communication channel respectively with the aircraft and chassis connection, realize instruction distribution and accurate control.

[0078] The cockpit bottom deployment high-speed data pin, with the chassis through the electromagnetic locking mechanism docking, transmission power and control signal, using CAN FD protocol transmission steering wheel angle, accelerator depth and other signals.

[0079] The cockpit top configuration fiber communication ring, when docking with the aircraft, synchronous establishment of optical communication link (delay <0.1ms), using FlexRay protocol, can quickly transmit the lift propeller and thrust duct fan speed, pitch / roll angle instruction.

[0080] At the same time, dual-channel Wi-Fi 6E wireless link (6GHz frequency band) is used as a backup channel to form a transmission channel redundancy.​

Claims

1. A tri-copter aerocar, characterized by: The utility model provides an aircraft, cockpit and automobile chassis, the aircraft, cockpit and automobile chassis are connected from top to bottom in proper order, the cockpit is cuboid, the windward surface and the leeward surface of cockpit are curved surface, the top surface of cockpit is provided with first docking device (21), the bottom surface of cockpit is provided with second docking device (22), the side surface of cockpit is provided with cabin door, first docking device (21) and second docking device (22) are all long strip shape, the sliding groove section of first docking device (21) and second docking device (22) is '' concave '' character, the aircraft includes fuselage (11), working wing, duct structure (13) and landing gear (14), the fuselage (11) is cuboid, the top surface of fuselage (11) is along the chord direction section and is streamline, the leeward surface of fuselage (11) is provided with duct structure (13), the two side surfaces of fuselage (11) are along the chord direction and are provided with working wing, the bottom surface of fuselage (11) is provided with first docking sliding rail, after first docking sliding rail and first docking device (21) sliding connection, aircraft (1) and cockpit (2) fixed connection, the bottom surface of fuselage (11) is provided with landing gear (14), the top surface of automobile chassis (3) is provided with second docking sliding rail, second docking sliding rail and second docking device (22) sliding connection.

2. The tri-copter air car of claim 1, wherein: The working wing includes front wing, main wing, support rod and several lift propellers (124), the front wing includes left front wing (121) and right front wing (121'), left front wing (121) and right front wing (121') are respectively arranged on the two sides of fuselage (11) in the forward direction, the main wing includes left main wing (122) and right main wing (122'), left main wing (122) and right main wing (122') are respectively arranged on the two sides of fuselage (11) along the chord direction, the front wing is forward swept, the main wing is backward swept, and X-shaped tandem wing layout is formed, The support rod includes left support rod (123) and right support rod (123'), left support rod (123) and right support rod (123') are respectively arranged on the two sides of fuselage (11) in the forward direction, left support rod (123) and right support rod (123') are both long strip shape, the top surface of left support rod (123) and right support rod (123') is fixedly connected with the bottom surface of main wing, the side surface of left support rod (123) is provided with first through hole, the side surface of right support rod (123') is provided with second through hole, the wing tip of left front wing (121) passes through first through hole and is fixed with left support rod (123), the wing tip of right front wing (121') passes through second through hole and is fixed with right support rod (123'), The bottom surface of left support rod (123) and right support rod (123') is provided with several lift propellers (124), the lift propellers are symmetrically distributed along the chord direction of fuselage (11). The inside of the left support rod (123) is provided with a first driving motor group; the first driving motor group includes a plurality of driving motors; the number of driving motors of the first driving motor group is the same as the number of lift propellers of the left support rod, and the driving motors of the first driving motor group are connected one by one with the lift propellers of the left support rod for providing power; The inside of the right support rod (123') is provided with a second driving motor group; the second driving motor group includes a plurality of driving motors; the number of driving motors of the second driving motor group is the same as the number of lift propellers of the right support rod; The driving motors of the second driving motor group are connected one by one with the lift propellers of the right support rod for providing power; The driving motors of the first driving motor group and the second driving motor group are connected with a controller respectively; the controller is arranged inside the fuselage (11).

3. The tri-copter air car of claim 2, wherein: The wing tip positions of the main wings are respectively provided with heading stabilizers (127) to provide static stability of heading control and improve the flight stability of the flying car.

4. The tri-copter air car of claim 2, wherein: The trailing edge of the left front wing (121) is provided with a first elevator (125); the trailing edge of the right front wing (121') is provided with a second elevator (125'); the first elevator (125) is arranged between the wing root and the left support rod; the second elevator (125') is arranged between the wing root and the right support rod. The trailing edge of the left main wing (122) is provided with a first aileron (126); the trailing edge of the right main wing (122') is provided with a second aileron (126'); the positions of the first aileron (126) and the second aileron (126') are close to the wing tip of the left main wing (122) and the wing tip of the right main wing (122') respectively.

5. The tri-copter air car of claim 1, wherein: The duct structure (13) includes a thrust fan (131), a thrust fan fairing (132) and a driving device; the thrust fan fairing (132) is arranged on the leeward surface of the fuselage (11); the thrust fan (131) is arranged in the thrust fan fairing (132); the thrust fan (131) is connected with a third driving motor; the third driving motor is arranged inside the fuselage (11); the third driving motor is connected with the controller; the number of the thrust fans (131) is even and they are symmetrically arranged left and right along the chord direction of the fuselage; the thrust fan fairing (132) is provided with a spoiler (133); the spoiler (133) is arranged at the air outlet of the thrust fan (131); the spoiler (133) is a rectangular thin plate; the spoiler (133) is used to improve the stability of airflow, enhance the aerodynamic performance, and enhance the flight stability and controllability.

6. The tri-copter air car of claim 5, wherein: The trailing part of the spoiler (133) along the forward direction is provided with a rudder (134); the rudder (134) is a rectangular thin plate.

7. The tri-copter air car of claim 1, wherein: A plurality of hinge holes are correspondingly arranged on the first docking slide rail and the first docking device, and a plurality of hinge holes are correspondingly arranged on the second docking slide rail and the second docking device to improve the reliability of the connection.

8. The tri-copter air car of claim 1, wherein: A high-speed connector pin is arranged at the bottom of the cockpit; a high-speed connector socket is arranged on the automobile chassis (3); the high-speed connector is used to transmit power and control signals, and the steering wheel angle and throttle depth signals are transmitted by using the CAN FD protocol.

9. The tri-copter air car of claim 1, wherein: The cockpit top is provided with a fiber-optic communication ring; when the cockpit is connected with the aircraft (1), an optical communication link is established through the fiber-optic communication ring, and the rotation speed of the lift propeller, the rotation speed of the duct structure, the pitch angle and the roll angle instructions are transmitted by using the FlexRay protocol.

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