WO2012010021A1

WO2012010021A1 - Air-ground double-purpose aircraft

Info

Publication number: WO2012010021A1
Application number: PCT/CN2011/075684
Authority: WO
Inventors: 杨朝习
Original assignee: Yang zhaoxi
Priority date: 2010-07-19
Filing date: 2011-06-13
Publication date: 2012-01-26
Also published as: CN101885295A

Abstract

An air-ground double-purpose aircraft comprises an aircraft body (47), an aircraft controller (1), an engine (38) and an undercarriage. Wherein a front ducted fan (9) which faces the wind at upper front is connected with the lower part of the front end of the aircraft body (47). A rear ducted fan (19) which faces the wind at upper front is connected with the upper part of the rear end of the aircraft body (47). The front ducted fan and the rear ducted fan form a Z-shaped structure with the aircraft body. The front ducted fan and the rear ducted fan are respectively connected with guide plates (23) and guide grids (24). A pull rod (27) for pulling the guide grids is connected with a pull rod motor (7). The undercarriage comprises a front bracket (11) and a rear bracket (33) which are arranged on the frond and the rear ends of the aircraft body (47). A front wheel (12) is connected with the lower end of the front bracket (11) and a rear wheel (32) is connected with the lower end of the rear bracket (33). The front wheel or the rear wheel is driven by a wheel shaft motor (31) or a motorcycle engine. The air-ground double-purpose aircraft can land vertically, fly horizontally, and can work normally on the ground. The aircraft is simple in structure and light in weight, and has high safety performance.

Description

Land and air vehicle

Technical field

The present invention relates to a small aircraft, and more particularly to an air-to-air aircraft.

Background technique

CN200910038258.X Patent Application discloses a double-ducted propeller vertical take-off and landing flying vehicle, which is constructed with two ducted fans facing upward in the wind on the front and rear bodies of the flying vehicle; The four-wheeled car of the car also serves as the landing gear for the aircraft. At the time of take-off and landing, the flying car relies on the rising thrust provided by two ducted fans provided on the vehicle body to achieve vertical take-off and landing. When flying in the air, the front part of the flying car should be tilted to a certain angle (like a helicopter), so that the two ducted fans can provide a certain horizontal component to promote the aircraft to achieve horizontal flight. The main disadvantages of its existence are:

1. Since the two ducted fans are all installed on the vehicle body, the total length of the car body is inevitably lengthened, and the excessively long car body will increase the weight of the car and is not conducive to the ground.

2. Since the windward side of the two ducted fans on the car body is oriented in the vertical direction, if there is no air tilting of the car body, the flying car cannot achieve horizontal flight in the air, just like a fixed-wing aircraft. Flying at the same speed. Therefore, this type of flying car is actually an aircraft that is the same as a helicopter and can take off and land vertically but cannot fly horizontally.

3. Two ducted fans are installed on the body of the flying car, which will inevitably generate a lot of vibration and vibration noise during the flight, which will make the driver and the passenger in the car feel very uncomfortable.

Summary of the invention

The object of the present invention is to provide an air-to-air dual-purpose aircraft to solve the problem that the aircraft is bulky, heavy, and has large vibration and vibration noise, and realizes vertical take-off and landing and horizontal flight of the aircraft in a simple structure and manner.

The invention is realized by the invention: an air-to-air aircraft, comprising an organism, an aircraft controller, an engine and a landing gear, and a front ducted fan facing the front side of the windward side is connected at a lower end of the front end of the body, in the body The rear end of the rear end is connected with a windward facing front upper rear ducted fan, the front ducted fan, the rear ducted fan and the body form a Z-shaped structure; the front ducted fan and the rear culvert The longitudinal fan is respectively connected with a longitudinal baffle and a lateral flow guiding grating, and the pulling rod for pulling the guiding grating is connected with the pulling rod motor; the landing gear includes a front and a rear end respectively disposed on the body and The body maintains a front bracket and a rear bracket with a front high rear and a low posture, a front wheel is connected at a lower end of the front bracket, and a rear wheel is connected at a lower end of the rear bracket, and the front wheel or the rear wheel is Wheel motor or motorcycle engine drive.

The invention comprises a front and a rear ducted fan which are arranged on the front side and the front side of the wind body, respectively, to form a Z-shaped zigzag body structure, which uses the engine to drive the propellers in the front and rear ducted fans. Rotation, thereby generating the driving power of the aircraft. At the same time, the deflection bar in the front and rear ducted fans is driven by the pull rod to perform deflection control to guide the high-speed airflow generated in the front and rear ducted fans—when the airflow is directed in a vertically downward direction. The vertical downward thrust is generated to cause the aircraft to take off and land vertically; when the airflow is directed in a horizontally rearward direction, a horizontal backward thrust is generated to propel the aircraft forward. During the horizontal flight of the aircraft, the flight direction of the aircraft can be controlled by adjusting the deflection direction of the deflector in the front and rear ducted fans. Moreover, since the front ducted fan is located at the lower part of the front of the body, and the rear ducted fan is located at the upper rear part of the body, and the upper and lower surface shapes of the body are designed according to aerodynamics, the body of the aircraft can naturally produce a pneumatic The lift of the effect is thus conducive to the flight of the aircraft.

In addition, the present invention provides a landing gear composed of front and rear brackets. On the one hand, the landing gear allows the aircraft to maintain a front high and a low posture in a normal state, so that the front and rear ducted fans are also maintained. The direction of the wind facing the front upper side, only when the front and rear ducted fans are in such an orientation, the thrust generated by the front and rear ducted fans can have a downward and backward component, so that the aircraft can Air flight; Moreover, only in such an orientation, the deflection angle of the diversion grille can be adjusted to adjust the vertical thrust and horizontal thrust of the front and rear ducted fans, thereby realizing the verticality of the aircraft. The dual purpose of takeoff and landing and horizontal flight. The key to the invention lies in this. On the other hand, by providing an axle motor or a motorcycle engine to drive the front and rear wheels on the landing gear, the purpose of the aircraft's land travel can be achieved, thereby realizing the purpose of the aircraft for both land and air.

The front ducted fan and the rear ducted fan are respectively connected to the body through a pipe girder, and the pipe girder is vertically connected to the front and rear ends of the body respectively. The structure of the right angle connection allows the axial lines of the propellers in the front and rear ducted fans to be parallel with the axis line of the body. In this way, when the air body is in the horizontal state, the diversion grille in the front and rear ducted fans can be completely in the horizontal maximum opening state, so that the resistance is minimized and the consumption is minimized. It is conducive to improving the long-term capability of the aircraft. Moreover, the implementation of the power transmission mechanism in the right angle connection structure is the simplest, and therefore, the reliability of the aircraft is also the highest.

The front ducted fan and the rear ducted fan are respectively one or two arranged side by side. That is, the setting of the front and rear ducted fans may be either one or both of the front and rear, or may be the opposite arrangement of the front one rear two or the front two rear ones. The front ducted fan and the rear ducted fan are driven by the same engine through a transmission system or respectively driven by respective engines to form an aircraft structure having single, double or multiple launches.

A pitch changing mechanism and a fairing are respectively disposed on the propeller of the front ducted fan and the rear ducted fan. The fairing can reduce the airflow resistance through the ducts; and the setting of the variable pitch mechanism facilitates the thrust adjustment of the front and rear ducted fans.

Providing a wing on each side of the outer wall of the duct of the front ducted fan and/or the rear ducted fan; the wing is a flat wing fixedly connected to the outer wall of the duct, or A curved wing that is coupled to the outer wall of the duct by a wingfold. For a single-mounted aircraft with a front ducted fan and/or a rear ducted fan, it is necessary to provide a wing on the outer wall of the duct. This is a necessary guarantee for the aircraft to achieve horizontal flight. The fixed flat wing has a relatively simple structure but a large footprint, which affects the ground. The folding wing needs to be equipped with a wing folder, and the structure is slightly complicated, but after the wing is folded and folded, it is very suitable for driving on the ground. For the two front ducted fans and/or the two rear ducted fans arranged side by side, either the wing may be provided or not, or two single wings may be provided on the two outer sides; A reinforcing plate is added between the road fans to combine some functions of the wing.

Two of the rear ducted fans are connected to both ends of a transverse transmission shaft tube, and the transverse transmission shaft tube is connected to the upper end of the pipeline girder by a tilting mechanism, and the lower end of the duct girder is The rear ends of the body are connected vertically. This facilitates the formation of the overall tilting structure of the rear ducted fan, which is advantageous for reducing the adjustment angle of the flow guiding grid, reducing the airflow resistance, and increasing the thrust.

The front bracket is in a standing position, the upper portion is penetrated and connected to the body, and the lower end is connected with 1-2 front wheels, and the front portion is connected with a front shock absorber; the rear bracket is in a lying position, and the front end thereof is movable. a joint is connected to the rear end of the body, and a rear end is connected with 1-2 rear wheels; a support rod is connected between the middle portion of the rear bracket and the pipe girder at the rear end of the machine body, and the support rod is There is a rear shock absorber attached to it.

A C-shaped seat and an ankle plate are disposed on the body, and a transverse lever is attached to an upper end of the front bracket, and the aircraft controller is disposed at a middle portion of the joystick. The seat surface of the C-shaped structure is convenient for the driver to adjust the sitting posture by the angle change of the random body during the take-off and landing of the aircraft, to achieve the purpose of comfort and convenient flight observation, and to improve flight comfort and safety. For the aircraft structure of the front and rear ducted fans, because the thrust is relatively small, only one seat can be set on the body; for the aircraft structure with increased front and rear ducted fans, due to the increased thrust, Two seats are set on the body for two-person flight. The driver grasps the horizontally operated joystick with both hands, which makes it easier to observe and control the aircraft controller installed in the middle of the joystick, and also facilitates driving and handling during land driving. The C-shaped seat is combined with the Z-shaped structure of the body and the front and rear ducted fans to form a ZC type aircraft unique to the present invention.

A cabin is provided on the body, and the aircraft controller is disposed in the cabin. This structure is suitable for large thrust aircraft, which can improve the ride comfort and flight safety of the driver.

A nacelle is disposed on the body, and an automatic flight device is disposed in the nacelle. This will enable unmanned flight and expand the field of application of the aircraft.

The advantage of the aircraft of the present invention is that, firstly, the vertical take-off and landing and horizontal flight of the aircraft can be achieved by the arrangement of a minimum of two oblique ducted fans, which cannot be achieved by any existing ducted aircraft. Efficacy, and in the process of vertical take-off or horizontal flight, all ducted fans are in working condition, overcoming the "dead weight" problem of existing multi-ducted aircraft; followed by the Z-shaped zigzag structure design of the aircraft, effective The length of the body is shortened, so that the total length of the aircraft can be designed within the length of a normal car, saving space for the aircraft, facilitating the ground travel of the aircraft, and allowing vertical take-off and landing in a standard parking space; The two ducted fans are arranged outside the body, which reduces the vibration and vibration noise of the aircraft, improves the safety and wind resistance, and is beneficial to the physical and mental health and driving comfort of the aircraft driver. The fourth is the front and rear columns. The layout of the ducted fan increases the range of the center of gravity of the aircraft, and there is no aerodynamic interference between the front and rear rotors of the tandem double rotor layout; The fifth is the Z-shaped structure of the aircraft. When the airflow passes through the front and rear ducted fans and the upper and lower surfaces of the aerodynamically designed body, the air pressure difference between the upper and lower sides of the body can be increased, and the lift can be effectively increased.

The aircraft of the invention can carry 2 people plus 20 kilograms of cargo, the flying speed can reach 180 km/h, the flying height is 1000 meters, the fuel consumption per 100 kilometers is less than 20 liters, and the voyage is 300-400 kilometers. The invention has reasonable structure, simple operation and high reliability; and can realize reliable air manned flight and land mobile driving, which is necessary for rushing to land traffic interruption (such as a highway) or inconvenient traffic (such as a deep mountain jungle, a plateau lake). The accident or crime scene is very important for the timely placement of public servants or armed personnel who perform emergency response tasks in areas where roads are blocked, as well as for alleviating urban transportation pressure and improving the efficiency of use of low-altitude space. The practical significance. The invention can also be made into an unmanned aerial vehicle to perform tasks such as low-altitude reconnaissance and disaster observation, so as to provide important, accurate and real-time intelligence information for staff decision-making under the premise of avoiding casualties.

DRAWINGS

Figure 1 is a schematic view of the structure of the present invention.

Fig. 2 is a view taken along the line A in Fig. 1;

Figure 3 is a B-direction view of Figure 1.

Figure 4 is a schematic view showing the structure of a transmission system of the present invention.

5 and 6 are schematic structural views of two embodiments using a double rear ducted fan.

7-10 are schematic views of the structure of two double aircraft embodiments.

Figure 11 is a schematic view showing the structure of an embodiment of a drone.

12 and 13 are schematic views showing the structure of an embodiment of a minicomputer.

The components and numbers in the figure are: aircraft controller 1, gearbox 2, drive shaft 3, universal joint 4, pipe girder 5, tie rod motor 7, fairing 8, front ducted fan 9, front shock absorber 10, front bracket 11, front wheel 12, fuel tank 13, oil pump 15, oil pipe 16, seat 17, parachute 18, rear duct fan 19, tool trunk 21, paddle 22, deflector 23, diversion grille 24, strut sleeve 26, tie rod 27, rear shock absorber 28, support rod 29, movable joint 30, axle motor 31, rear wheel 32, rear bracket 33, bracket movable joint 34, output shaft 35, generator 37, engine 38, ankle board 39, reinforcing plate 40, cabin 41, wing 43, wing folder 44, lever 45, body 47, connecting rod 48, blade center shaft 49, transverse drive shaft tube 50, tilting mechanism 51.

detailed description

Example 1:

As shown in FIG. 1 to FIG. 3, a basic structural form of the air-to-air aircraft is that a front and a rear end of the body 47 are respectively connected with a pipe girder 5 which is perpendicular to the body and protrudes downward and upward respectively. A front ducted fan 9 is connected to the lower end of the pipe girder 5 at the front end of the body 47; and a rear ducted fan 19 is connected to the upper end of the duct girder 5 at the rear end of the body 47. The axial lines of the propellers in the front and rear ducted fans are parallel to the axis of the body 47, respectively. Of course, the angle between the pipe girder 5 and the body 47 may also vary slightly, or the axial line of the front and rear ducted fans maintains a small angle with the axis of the body 47, but the front and rear ducts The fan is preferably held in a longitudinal column (Fig. 3). In short, the windward side of the front and rear ducted fans of the aircraft under normal conditions should be in a forward-upward posture (Fig. 1).

In Fig. 1, a longitudinal baffle 23 is respectively connected to the front ducted fan 9 and the rear ducted fan 19, and a lateral diversion grille is respectively hinged at the rear ports of the ducts of the front and rear ducted fans. 24, the flow guiding grid 24 can be deflected up and down under the control of the tie rod 27, and one end of the pull rod 27 is connected with the rod motor 7. During flight, the heading and pitch changes of the aircraft are controlled by the deflector 23 and the deflector 24, respectively. A fairing 8 and a conventional variable pitch mechanism are respectively installed on the propellers in the front and rear ducted fans.

In Fig. 2, a folding wing 43 is respectively disposed on both sides of the outer wall of the duct of the front ducted fan 9 and the rear ducted fan 19, and the wing 43 has a curved surface structure, and is connected with the outer wall of the duct through the wing folder. together. The lateral elongation of the curved wing is about 1/4 of the circumference of the duct, so that it can be attached to the surface of the duct when the wing is folded. When the wing 43 is in the deployed state, it is in a horizontal state. The wingfolder can be either manually mounted or a conventional electric control structure.

In Fig. 1, an engine 38 is mounted in the inner rear portion of the body 47, which is advantageous in reducing the center of gravity of the aircraft. A tank 13 is provided at the front of the body 47, and the tank 13 is connected to the engine 38 via an oil pump 15 and a tubing 16. A generator 37 is also attached to the rear of the engine 38 to provide operating power to the aircraft and to charge the onboard battery. The propellers in the front ducted fan 9 and the rear ducted fan 19 are respectively connected to the output shaft 35 of the engine 38 through the transmission system, and are driven to rotate by the engine 38, and the rotation of the blades 22 in the front and rear ducted fans should be ensured. Reverse direction to counteract torque.

Figure 4 shows an implementation of the drive system used for the front and rear ducted fans. The output shaft 35 is a power output shaft of the engine 38. The two ends of the output shaft 35 are connected to the blade center shaft 49 through a plurality of universal joints 4, a transmission shaft 3 and a gear transmission box 2, respectively, and are respectively realized by the engine 38. Power transmission of the front ducted fan 9 and the rear ducted fan 19.

Of course, it is also possible to use a dual engine form in which two engines 38 are directly mounted behind the propellers in the front ducted fan 9 and the rear ducted fan 19 to separately drive the propeller rotation in the front and rear ducted fans. .

The power unit of the aircraft can use either an oil machine (such as a piston engine or a jet engine) or an electric motor.

In Fig. 1, a seat surface 17 is provided on the top surface of the central portion of the body 47, and a seat 17 having a C-shaped surface is mounted. On the body 47 at the rear of the seat, a parachute 18 with an automatic ejection device, a seat belt and The tool trunk 21 and the like are provided with an ankle plate 39 on both sides of the body 47 at the lower portion of the seat.

The landing gear of the aircraft of the present invention includes a front bracket 11 and a rear bracket 33. The front and rear brackets are arranged to maintain the front body high and the low state of the body 47, and the parking angle of the body 47 can be generally controlled in the range of 10 - 75 degrees. For aircraft with hovering function, the parking angle should be large; for aircraft with horizontal flight, the parking angle should be small. The parking angle of the aircraft in this embodiment is about 37°. The front bracket 11 is in a standing position, the upper portion thereof is penetrated and connected to the front portion of the body 47, and a front wheel 12 is attached to the lower end thereof, and the front shock absorber 10 is connected to the middle portion. The rear bracket 33 is in a lying position, the front end of which is connected to the rear end of the body 47 through the movable joint 34, and the rear end thereof is connected with two rear wheels 32 (Fig. 3), and one end of the support rod 29 is connected to the rear bracket through the movable joint 30. In the middle of the 33, the other end of the support rod 29 is connected to the pipe girder 5 at the rear end of the body 47 via the movable joint 30. A rear shock absorber 28 is attached to the support rod 29. The front wheel 12 functions as a guide wheel, and an axle motor 31 is mounted on the axle of the rear wheel 32, which doubles as a ground drive wheel. It is also possible to provide two front wheels and one rear wheel, or a four-wheel combination of two front wheels and two rear wheels.

In Fig. 3, a transverse lever 45 is attached to the upper end of the front bracket 11, and the aircraft controller 1 is mounted at the center of the lever 45 and at the top of the front bracket 11. An instrument panel, a switch button, and the like are disposed on the aircraft controller 1; the joystick 45 is provided with a throttle handle and an operating handle, similar to a control structure of a motorcycle or an electric motorcycle. The aircraft controller 1 is electrically connected to the engine 38, the whip motor 7, the axle motor 31, and the wing folder, respectively, to control the operation of these working mechanisms. A gyroscope can also be incorporated in the aircraft controller 1 to improve the flight stability of the aircraft.

The working process of the present invention is that the driver straddles the C-shaped seat 17 on the aircraft body 47, fastens the seat belt, holds the handle of the operating lever 45, starts the engine 38, and the engine 38 can pass the universal joint 4 The propeller shaft 3 and the gear transmission box 2 respectively drive the propellers in the front and rear ducted fans to rotate and generate thrust. Thereafter, the aircraft controller 1 is operated, the front and rear wings 43 are opened by the wing folder, and the tie rod motor 7 is driven to pull the rod 27 so that the flow guiding grid 24 on the front and rear ducted fans is vertically downward On the ground, let the airflow in the front and rear ducted fans go straight down; then gradually increase the thrust of the front and rear ducted fans, and the aircraft can slowly rise vertically. After the aircraft is lifted to a certain height, the pitch changing mechanism is adjusted to increase the thrust of the rear duct fan 19, so that the front end of the body 47 is gradually lowered, the body 47 is slowly tilted horizontally, and the rear culvert is driven by the drawbar motor 7. The flow guide grille 24 on the duct fan 19 slowly guides the airflow generated by the rear duct fan 19 to the horizontal direction to generate a rearward thrust. When the aircraft reaches a certain speed and the lift generated by the wing and the duct is large enough, the aircraft can fly forward horizontally. During this process, the driver can adjust the body sitting posture (the upper body is tilted back and forth) by changing the pitch angle of the random body 47, and maintain a comfortable state for facilitating the manipulation of the aircraft. When the aircraft is flying in the air, it depends on the deflector 23 and the diversion grille 24 to control the heading and pitch changes of the aircraft, respectively.

When the aircraft arrives at the destination and prepares to land, the traction motor 24 is first deflected by the drawbar motor 7 to a certain angle (complementary to the parking angle), and then the thrust and direction of the front and rear ducted fans are adjusted to gradually convert the airflow into Vertically downward and the thrust is gradually reduced, so that the aircraft can slowly land to the ground, and the front and rear wings are folded after the machine is stopped.

The invention can also perform the horizontal take-off and landing by short-distance running without deflecting the flow guiding grille on the front and rear ducted fans.

When the aircraft of the present invention needs to travel on the ground, by switching the switching button on the aircraft controller 1 to switch to the ground driving mode, and by adjusting the throttle handle and the operating handle on the operating lever 45, the conventional motorcycle or The electric motorcycle is controlled to perform ground driving, and the axle motor 31 on the rear wheel 32 provides ground driving power of the aircraft, and the battery 20 on the body 47 supplies electric power.

Once the aircraft of the present invention is in an accidental situation in the air, pressing the control button on the aircraft controller 1 causes the parachute 19 to be ejected and automatically opened, thereby allowing the aircraft and the flight crew to land safely. If there is an unplanned shutdown or damage to a ducted fan on the aircraft, the parachute 19 can also be automatically ejected and used to fly with the thrust provided by another ducted fan. The aircraft at this time actually became a paramotor.

The aircraft of the present invention can also be used as a ground effect aircraft, and uses ground effect flying when flying on a calm ice surface. The flying height is less than or equal to half of the wingspan.

Example 2:

As shown in FIG. 5, the basic structure of this embodiment is the same as that of Embodiment 1, except that the rear ducted fan 19 is changed to two side by side, and the folding wing 43 is provided only on the front ducted fan 9, and the rear duct is provided. Instead of a single wing, the fan 19 is connected to a reinforcing plate 40 at the top of the two rear ducted fans 19 to define the ducts of the reinforcing plate and the rear ducted fan as the quasi-wings. The two rear ducted fans 19 side by side are supported by two pipe girder 5s and transmit power. The two pipe girders 5 are arranged in a V-shape and are vertically connected to the body 47.

Example 3:

As shown in Fig. 6, the basic structure of this embodiment is the same as that of the first embodiment, and the rear ducted fan 19 is also two in parallel. A folding wing 43 is disposed on both sides of the duct of the front ducted fan 9, and no reinforcing plate is disposed between the two rear ducted fans 19, but is disposed on the outer end sides of the two rear ducted fans. One wing 43. Two rear duct fans 19 are respectively disposed at both ends of the transverse transmission shaft tube 50, and the transverse transmission shaft tube 50 is connected to the upper end of the duct beam 5 through the tilting mechanism 51. Thus, the two rear ducted fans 19 can be tilted at a certain angle by the rotation of the transverse transmission shaft tube 50 to constitute a power (ducted fan) tilting structure.

In the present embodiment, a fixed connection mechanism is also provided at the position of the tilting mechanism 51 so that the two rear ducted fans 19 are not rotated to form a body tilting structure similar to that of the second embodiment.

Example 4:

As shown in FIG. 7 and FIG. 8 , the main structure of the embodiment is the same as that of the first embodiment, and the front and rear ducted fans are both side by side. No wing is provided on the front and rear ducted fans, and a reinforcing plate 40 is respectively disposed between the two front ducted fans 9 and the two rear ducted fans 19. The two front ducted fans 9 are supported by the two duct girders 5 arranged in a V-shape and transmit power; the two rear ducted fans 19 are also supported and connected by the two duct girders 5 arranged in a V-shape, respectively.

Since the thrust of such an aircraft is significantly increased, the present embodiment can be configured as a two-person aircraft, that is, two front and rear C-shaped seats 17 are provided on the body 47 for use by two people.

The front and rear ducted fans can also be connected by the connection of the embodiment 3 to form a power (ducted fan) tilting structure.

Example 5:

As shown in FIG. 9 and FIG. 10, the present embodiment is to perform lateral side-by-side mechanical connection of two single-body aircrafts substantially the same as the main body structure of Embodiment 1, that is, two front ducted fans 9 and two rear culverts. A reinforcing plate 40 is disposed between the duct fans 19, and a connecting rod 48 is disposed between the two bodies 47, thereby forming a combination of a two-person aircraft. In order to ensure the uniformity and coordination of the operation of the aircraft, the aircraft controller 1 is preferably disposed only on the front bracket 11 of one of the aircraft bodies, and the aircraft controller 1 controls the air flight and the ground driving motion of the two aircraft units.

Example 6

As shown in Figs. 11 and 12, the main structure of this embodiment is the same as that of the first embodiment, except that a cabin 41 is provided on the body 47, and the aircraft controller 1 is disposed in the cabin 41. In this way, the driver can control the flight in the cockpit. Since the person is in the machine and isolated from the outside, in order to improve the flight power of the aircraft, the front and rear ducted fans can be replaced by jet engines, or other high-power propellers can be used to improve the flight performance of the aircraft. The aircraft is actually turned into a small machine, so its wings can be designed as fixed wings, and preferably fixed to the fuselage.

Example 7

Figure 13 As shown in the present embodiment, a nacelle is provided on the body 47, and an automatic flight device and a gyroscope are disposed in the nacelle. The aircraft is transformed into a drone. In this embodiment, both a folding wing and a straight fixed wing can be used. The wing can be fixedly connected to the outer wall of the ducts of the front and rear ducted fans, or directly to the fuselage.

Claims

An aircraft-to-air aircraft, comprising an organism (47), an aircraft controller (1), an engine (38) and a landing gear, characterized in that a windward facing front upper portion is connected to a lower portion of the front end of the body (47). The front ducted fan (9) is connected with a rear ducted fan (19) facing the front of the wind in the upper part of the rear end of the body (47), the front ducted fan (9) and the rear ducted fan. (19) forming a Z-shaped structure with the body (47); a longitudinal baffle (23) and a lateral direction are respectively connected to the front ducted fan (9) and the rear ducted fan (19) a guide grid (24), a pull rod (27) for pulling the flow guide grille is connected to the pull rod motor (7); the landing gear includes a front and a rear end respectively disposed on the body (47) and the said The body (47) maintains a front bracket (11) and a rear bracket (33) in a front high rear and a low posture, and a front wheel (12) is attached to a lower end of the front bracket (11), and the rear bracket (33) is attached to the rear bracket (33) A rear wheel (32) is attached to the lower end, and the front wheel (11) or the rear wheel (33) is driven by an axle motor (31) or a motorcycle engine.
The air-to-air aircraft according to claim 1, wherein the front ducted fan (9) and the rear ducted fan (19) pass through a pipe beam (5) and the body (47), respectively. In connection, the pipe girders (5) are vertically connected to the front and rear ends of the body (47), respectively.
The air-to-air aircraft according to claim 1 or 2, wherein the front ducted fan (9) and the rear ducted fan (19) are respectively one or two arranged side by side; The front ducted fan (9) and the rear ducted fan (19) are driven by the same engine (38) through a transmission system or by respective engines.
The air-to-air aircraft according to claim 1 or 2, wherein a variable pitch mechanism is mounted on the propellers in the front ducted fan (9) and the rear ducted fan (19), respectively Fairing (8).
The air-to-air aircraft according to claim 1 or 2, characterized in that the two sides of the outer wall of the duct of the front ducted fan (9) and/or the rear ducted fan (19) are respectively provided The organic wing (43); the wing (43) is a flat wing fixedly connected to the outer wall of the duct, or a curved wing connected to the outer wall of the duct through a wing folder.
The air-to-air aircraft according to claim 3, wherein the two rear ducted fans (19) are connected to both ends of a transverse transmission shaft tube (50), and the transverse transmission shaft tube (50) is connected to the upper end of the pipe girder (5) by a tilting mechanism (51), and the lower end of the pipe girder (5) is perpendicularly connected to the rear end of the body (47).
The air-to-air aircraft according to claim 1 or 2, wherein the front bracket (11) is in a standing position, the upper portion thereof is penetrated and connected to the body (47), and the lower end is connected with 1-2 a front wheel (12) having a front shock absorber (10) connected thereto; the rear bracket (33) being in a lying position, the front end of which is connected to the rear end of the body (47) via a movable joint (34) , the rear end is connected with 1-2 rear wheels (32); a support rod (29) is connected between the middle portion of the rear bracket (33) and the pipe beam (5) at the rear end of the body (47), A rear shock absorber (28) is attached to the support rod (29).
The air-to-air aircraft according to claim 7, wherein a C-shaped seat (17) and an ankle plate (39) are provided on the body (47), and the front bracket (11) The upper end is connected with a transverse lever (45), and the aircraft controller (1) is disposed in the middle of the joystick (45).
The air-to-air aircraft according to claim 8, characterized in that a cabin (41) is provided on the body (47), and the aircraft controller (1) is disposed in the cabin (41).
The air-to-air aircraft according to claim 1, wherein a nacelle is provided on the body (47), and an automatic flight device is disposed in the nacelle.