Aircraft and control method thereof

Abstract

The invention belongs to the technical field of aircraft design, and particularly relates to an aircraft and a control method thereof, and the aircraft comprises N identical fan-shaped body units; each fan-shaped body unit comprises a main body cabin, a rotating shaft, a rotor ring and a fairing; the main body cabin is connected with the fairing through a rotating shaft; the fairing is annular, and a rotor ring is arranged in the fairing; the main body cabin provides electrical and control connection for the fairing through the rotating shaft; the fairing drives the rotor ring to rotate; the left end face and the right end face of the main body cabin are completely symmetrical and provided with annular connectors respectively. And the N main body cabins are connected and combined through annular interfaces.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft design, and in particular relates to an aircraft and a control method thereof. Background Art

[0002] Almost all early aircraft used aviation piston engines and propellers as aircraft power devices. Aviation piston power devices consist of aviation piston engines and propellers. The function of aviation piston engines is to convert thermal energy into mechanical energy, and the function of propellers is to generate pulling force. After the fuel and air are mixed, they are burned in the cylinder, so that the thermal energy of the fuel is converted into mechanical work through the cylinder, piston, connecting rod, crankshaft, etc., and then the mechanical work is transferred to the propeller through the reducer; driven by the engine, the propeller rotates in the air to exert force on the air, and the air generates power for the propeller to drive the aircraft forward. With the development of power batteries, motors, and electronic control technologies, electric aircraft are also increasingly developed.

[0003] Currently common aircraft include fixed-wing aircraft, rotor plus tail rotor aircraft, quadrotor aircraft, etc.

[0004] With the development of technology, especially the diversity, harshness and high reliability of military use, there is an urgent need for aircraft that can meet the needs of future wars. Summary of the invention

[0005] Purpose of the invention: In order to solve the problems of high reliability of existing aircraft, an aircraft and a control method thereof are proposed.

[0006] Technical solution:

[0007] An aircraft, comprising N identical fan-shaped units;

[0008] The fan-shaped unit includes: a main cabin, a rotating shaft, a rotor ring and a fairing;

[0009] The main cabin is connected to the fairing through a rotating shaft; the fairing is annular, and a rotor ring is arranged inside the fairing;

[0010] The main cabin provides electrical and control connections for the fairing through a rotating shaft; the fairing drives the rotor ring to rotate;

[0011] The left and right end surfaces of the main cabin are completely symmetrical and are respectively provided with an annular interface;

[0012] N main cabins are connected and combined via a ring interface.

[0013] Furthermore, the fairing generates a magnetic field through electric current to drive the rotor ring to rotate;

[0014] The rotor ring comprises a ring body and a plurality of blades; the plurality of blades are evenly distributed inside the ring body and the outer edges of the blades are connected to the inner wall of the ring body.

[0015] Furthermore, the rotating shaft is also used to drive the fairing and the rotor ring to tilt.

[0016] Furthermore, the annular interface is a telescopic structure; the annular interface is used for mechanical and electrical connection with other fan-shaped units.

[0017] Furthermore, an energy storage unit and a flight control unit are arranged inside the main cabin, and a solar panel is arranged on the surface.

[0018] Furthermore, the N fan-shaped body units of the aircraft are connected in a straight line or in a ring shape through an annular interface.

[0019] Furthermore, 3≤N≤16.

[0020] A method for controlling an aircraft, the method being used to control the aircraft, the method comprising:

[0021] When N sector-shaped units are all fully functional, they are combined into a ring through a ring interface;

[0022] When it is necessary to pass through a narrow space, two adjacent fan-shaped units are rotated 180 degrees around the annular interface to form a straight line.

[0023] Furthermore, when no more than N / 2 faults occur in the sector unit, the sector unit with faults is discarded and the configuration is maintained unchanged;

[0024] When the number of faults in the fan-shaped unit exceeds N / 2, the aircraft is transformed into a straight line.

[0025] Furthermore, the direction and speed of travel of the aircraft are controlled by controlling the rotation direction and tilt angle of the rotor ring in each fan-shaped unit.

[0026] Beneficial Effects

[0027] a) The aircraft adopts a ring circuit. When there is damage somewhere, the entire system can work normally, and the reliability of the entire system is higher;

[0028] b) Use the method of discarding useless parts to effectively reduce the useless load of the system;

[0029] c) Adopt a decentralized approach, focus on tasks, and respond faster;

[0030] d) It can change from a circular shape to a straight shape, which is conducive to adapting to movement in a narrow space;

[0031] e) The fairing not only has a fairing effect, but also has a silent effect, which can effectively improve the concealment of the aircraft;

[0032] f) The building blocks are used in a splicing manner, which makes it more flexible to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a structural diagram of the aircraft;

[0034] Figure 2 is the axial view of the aircraft;

[0035] Figure 3 It is a structural diagram of a fan-shaped body;

[0036] Figure 4 is the tilt diagram of the rotation axis;

[0037] Figure 5 It is the view of the interface;

[0038] Figure 6 It is a structural diagram of the rotor ring;

[0039] Figure 7 It is a diagram showing the power principle;

[0040] Figure 8 It is the state of the aircraft with one sector missing;

[0041] Fig. 9 It is the state of the aircraft with three less sectors;

[0042] Fig.10 It is a straight aircraft state;

[0043] Fig.11 It is a schematic diagram of the electrical interface channel. DETAILED DESCRIPTION

[0044] An aircraft 1. The aircraft is composed of 16 fan-shaped units, and the fan-shaped unit is mainly composed of a main cabin, a rotating shaft, a rotor ring, a fairing, etc.

[0045] Main cabin: It is the main structure of the fan-shaped body, realizing mechanical and electrical connection with other fan-shaped bodies, storing flight control unit, energy storage unit, mission unit, and the surface is covered with solar panels. The interface of the main cabin is an axisymmetric figure ( Figure 5 ), which is conducive to the complete docking of the interface after deformation and flipping. With a ring interface, it is conducive to flipping and deformation. The ring interface has a telescopic function, extending from the main cabin when needed and retracting into the main cabin when not needed. Various lines are laid on the ring road along the ring interface to ensure the smooth flow of various lines during the flipping and deformation process.

[0046] Rotating shaft: Through its own rotation, it can drive the rotor ring and fairing to tilt, thereby changing the flow direction of the gas, such as Figure 4As shown; in addition, it can also serve as a channel to transfer energy to the rotor ring to make the rotor ring rotate.

[0047] Rotor ring: The interaction between the current of the rotor ring and the strong magnetic field of the fairing makes the rotor ring body generate power and rotate; according to the task requirements, the direction of the current can be controlled to achieve clockwise or counterclockwise rotation of the rotor ring body, such as Figure 6 , Figure 7 shown.

[0048] Fairing: It can straighten the airflow in and out of the rotor ring to ensure better power effect. It can also absorb the noise generated during the movement of the rotor ring, especially the noise between the contact surface of the fairing and the rotor ring, effectively reducing the noise impact on the external environment.

[0049] Preferably, the aircraft is usually used in a complete original state, with the main body presenting a ring shape, such as Figure 1 , Figure 2 shown.

[0050] Preferably, when a certain fan-shaped body is damaged and cannot be used, the fan-shaped body can be removed, and the main body presents a fan shape, and the overall control system continues to perform the flight mission according to the adjusted state, such as Figure 8 shown.

[0051] Preferably, when multiple fan-shaped bodies are damaged and cannot be used, these fan-shaped bodies can be removed and reassembled, and the main body presents a fan shape. The overall control system continues to perform the flight mission according to the adjusted state. Fig. 9 shown.

[0052] Preferably, each adjacent sector can be relatively rotated 180 degrees, and the shape of the aircraft changes from a ring to a straight line, such as Fig.10 The advantage of the straight line is that normal flight can be guaranteed even when there are at least three fan-shaped bodies.

[0053] Preferably, when deformation is required, jump to a higher place before deformation, and use the time of rising and falling to complete the deformation;

[0054] Preferably, when deformation is required, if the interface between two sector-shaped bodies needs to be disconnected, the annular interface is disconnected first, and then the annular interface is retracted into the sector-shaped body;

[0055] Preferably, when deformation is required, if two sector-shaped bodies need to be flipped relative to each other, the annular interfaces complete the flipping action by rotating relative to each other.

[0056] Preferably, the various main electrical interface channels of the aircraft form a ring path, so that when there is damage somewhere, the entire system can work normally, such as Fig.11 As shown;

[0057] Preferably, when a certain fan-shaped body is excessively damaged, the fan-shaped body can be discarded in time to reduce the invalid load of the aircraft;

[0058] Preferably, a decentralized control logic is adopted, that is, there is no central control unit, and the control logic relationship can be formulated according to the real-time task, and the response speed is faster. When the left flight is changed to the right flight, it does not need to be rotated by the aircraft body, and it can be achieved directly by changing the logic relationship;

[0059] Preferably, a mode without fixed upper and lower distinction is adopted, that is, the aircraft has no upper and lower parts, and both annular surfaces can be used as the upper part, so that the aircraft has higher flexibility in use;

[0060] Preferably, when multiple aircraft are damaged, the fan-shaped body units can be reassembled.

Claims

1. An aircraft, characterized in that: The aircraft comprises N identical fan-shaped units; The fan-shaped unit includes: a main cabin, a rotating shaft, a rotor ring and a fairing; The main cabin is connected to the fairing through a rotating shaft; the fairing is annular, and a rotor ring is arranged inside the fairing; The main cabin provides electrical and control connections for the fairing through a rotating shaft; the fairing drives the rotor ring to rotate; The left and right end surfaces of the main cabin are completely symmetrical and are respectively provided with an annular interface; N main cabins are connected and combined via a ring interface.

2. The aircraft according to claim 1, characterized in that: The fairing generates a magnetic field through electric current to drive the rotor ring to rotate; The rotor ring comprises a ring body and a plurality of blades; the plurality of blades are evenly distributed inside the ring body and the outer edges of the blades are connected to the inner wall of the ring body.

3. The aircraft according to claim 2, characterized in that: The rotating shaft is also used to drive the fairing and the rotor ring to tilt.

4. The aircraft according to claim 3, characterized in that: The annular interface is a telescopic structure; the annular interface is used for mechanical and electrical connection with other fan-shaped units.

5. The aircraft according to claim 4, characterized in that: An energy storage unit and a flight control unit are arranged inside the main cabin, and a solar panel is arranged on the surface.

6. The aircraft according to claim 5, characterized in that: The N fan-shaped body units of the aircraft are connected in a straight line or in a ring shape through an annular interface.

7. The aircraft according to claim 6, characterized in that: 3≤N≤16。 8. An aircraft control method, the method being used to control the aircraft according to any one of the preceding claims, characterized in that: The control method comprises: When N sector-shaped units are all fully functional, they are combined into a ring through a ring interface; When it is necessary to pass through a narrow space, two adjacent fan-shaped units are rotated 180 degrees around the annular interface to form a straight line.

9. The method according to claim 8, characterized in that: When there are no more than N / 2 faults in the sector unit, the faulty sector unit is discarded and the configuration remains unchanged; When the number of faults in the fan-shaped unit exceeds N / 2, the aircraft is transformed into a straight line.

10. The method according to claim 9, characterized in that: The direction and speed of the aircraft are controlled by controlling the rotation direction and tilt angle of the rotor ring in each fan-shaped unit.

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