CN115675847A

CN115675847A - Single-shaft aircraft and control method thereof

Info

Publication number: CN115675847A
Application number: CN202211259832.6A
Authority: CN
Inventors: 彭延云; 史涛瑜; 朱旭耀; 赵小涵; 刘蝉; 米颖
Original assignee: Beijing Machinery Equipment Research Institute
Current assignee: Beijing Machinery Equipment Research Institute
Priority date: 2022-10-14
Filing date: 2022-10-14
Publication date: 2023-02-03

Abstract

The invention discloses a single-shaft aircraft and a control method thereof. The wing has a supporting rod, the supporting rod is connected with the fuselage, a ribbed plate is arranged on the supporting rod, the supporting rod and the ribbed plate form a wing frame, and a skin is sleeved on the wing frame. The supporting leg is connected with the machine body in an adhesive mode. And the flight control hardware is arranged in the machine body. And the power system is connected with the flight control hardware and is in a coaxial double-propeller structure or a fixed duct structure. And the control system is connected with the flight control hardware and comprises a steering engine and a rudder sheet, and the steering engine controls the rudder sheet to control the attitude of the aircraft. The aircraft has the advantages of strong attitude control capability, simple control structure and high flight efficiency.

Description

Single-shaft aircraft and control method thereof

Technical Field

The invention relates to the technical field of machine manufacturing and unmanned aerial vehicles, in particular to a single-shaft aircraft and a control method thereof.

Background

The existing unmanned aircraft with the vertical take-off and landing function is always the hot direction of the research in the aviation field, has low dependence on the take-off and landing environment, can be suitable for various flight environments, and is widely applied to the military and civil fields. Many rotors, compound wings (VTOL fixed wings) and helicopters all belong to VTOL type unmanned aerial vehicle. The single-shaft aircraft is a vertical take-off and landing unmanned aerial vehicle with a special structure, has the advantages of a common vertical take-off and landing unmanned aerial vehicle, has unique advantages, and is simple and reliable in structure compared with a helicopter. Compare in many rotor unmanned aerial vehicle, its size is compacter, uses the scene more nimble.

In the prior art, the invention patents: a single-axis aircraft and a control method (CN 113104204B) are provided, the single-axis aircraft and the control method adopt positive and negative paddles to offset a reaction torque, meanwhile, a connecting arm is arranged on the single-axis aircraft, the connecting arm comprises an electromagnetic coil, a track, a counterweight and the like, and the counterweight position is controlled through the magnetic field of the electromagnetic coil, so that the center and the attitude of the aircraft are adjusted, and the purpose of controlling the aircraft is realized. The attitude adjustment of the aircraft is limited by the balance weight and the position of the balance weight, the adjustment range is limited, the maneuverability of the aircraft is weak, and the efficiency is low. A single-shaft aircraft (CN 105480406B) discloses a single-shaft aircraft, which adopts positive and negative propellers to offset the reaction torque, and is simultaneously designed with a wing driving device, the middle part of the wing driving device is provided with an annular wing extending out of the wing driving device, and the annular wing can move horizontally under the driving of the wing driving device, thereby changing the wind resistance area and achieving the purpose of controlling the attitude of the aircraft. The propeller of the aircraft is exposed, the safety is low, and the attitude control method also has the problem of low efficiency.

To sum up, single-axis aircraft only possesses rotor class unmanned aerial vehicle vertical flight mode usually, lacks fixed wing class unmanned aerial vehicle's cruise operating mode, makes the flying speed and the flight efficiency of aircraft all restrict, and control capability is weak, control structure is complicated, the flight efficiency is low.

Disclosure of Invention

The invention mainly aims to provide a single-shaft aircraft to solve the problems that the single-shaft aircraft in the prior art is only provided with a vertical flight mode of a rotor wing type unmanned aerial vehicle and lacks a cruise working mode of a fixed wing type unmanned aerial vehicle, so that the flight speed and the flight efficiency of the aircraft are limited, the control capability is weak, the control structure is complex, and the flight efficiency is low.

To achieve the above object, according to one aspect of the present invention, there is provided a single-axis aircraft including:

the bullet machine comprises a machine body, a machine body and a machine body, wherein the machine body is provided with a bullet head and a bullet body, and the bullet head is connected with the bullet body.

The wing has a supporting rod, the supporting rod is connected with the fuselage, a ribbed plate is arranged on the supporting rod, the supporting rod and the ribbed plate form a wing frame, and a skin is sleeved on the wing frame.

The supporting legs are connected with the machine body in an adhesive manner.

And the flight control hardware is arranged in the machine body.

And the power system is connected with the flight control hardware and is in a coaxial double-propeller structure or a fixed duct structure.

And the control system is connected with the flight control hardware and comprises a steering engine and a rudder sheet, and the steering engine controls the rudder sheet to control the attitude of the aircraft.

Preferably, the body further comprises:

the battery mounting plate is arranged at one end of the bullet body close to the bullet head;

the flight control mounting plate is arranged in the bullet body close to the battery mounting plate;

the operating mechanism mounting plate is arranged in the bullet body far away from one end of the bullet head;

the power system mounting plate is arranged in the bullet body close to the operating mechanism mounting plate;

the stiffener is glued with battery mounting panel, flight control mounting panel, operating device mounting panel and power mounting panel.

Preferably, the supporting legs adopt the carbon fiber plate material, be equipped with the hole on the supporting leg, supporting leg quantity is four, is the cross and arranges.

Preferably, when the power system is a coaxial double-paddle structure, the power system comprises:

a battery mounted on the battery mounting plate;

one motor is arranged on the power system mounting plate, the other motor is arranged on the operating mechanism mounting plate, and the two motors are arranged oppositely;

the paddle is arranged inside the machine body, is installed on a shaft of the motor and is fixed through the nut, and the paddle rotates reversely to reduce disturbance of air flow to the machine body.

The battery mounting plate, the flight control mounting plate, the operating mechanism mounting plate and the power system mounting plate are arranged in parallel.

Preferably, when the power system is a fixed ducted structure, the power system includes:

fixing grooves;

the fixed duct is connected with the fixed groove;

the ducted fan is arranged in the fixed ducted.

Preferably, the manipulation system comprises:

the steering engine is connected with the flight control system through a cable;

the rudder sheet rotates to enable the aircraft to generate deflection torque and control the attitude of the aircraft, the rudder sheet forms four rudder surfaces, the rudder surfaces are arranged in a cross shape, two pairs of rudder surfaces rotate to generate pitching and rolling torque, and the four rudder surfaces rotate to generate yawing torque;

the steering engine rudder piece connecting piece is connected with the steering engine and the rudder piece.

Preferably, the manipulation system comprises:

the steering engine is arranged on the outer side of the machine body and is fixed with the machine body through screws;

and the rudder sheet is connected with the steering engine through a steering engine rudder sheet connecting piece and a screw.

Preferably, the airfoil is configured as a lifting airfoil.

According to another aspect of the invention there is provided a single-axis aircraft control method comprising:

step (1): and controlling the power system to generate power through flight control hardware.

Step (2): the steering engine of the control system is controlled through flight control hardware, the steering engine controls the rudder sheet, the rudder sheet forms a control surface, the control surface can correspondingly generate pitching and rolling moments through rotation respectively, the four control surfaces can generate yawing moments through rotation simultaneously, and vertical flight and horizontal flight of the single-shaft aircraft are achieved.

And (3): when the wings are used, the aircraft has two modes of vertical flight and horizontal flight, can be freely switched, when the wings are not used, the wings are detached, and the aircraft has a vertical flight mode.

By applying the technical scheme of the invention,

the single-shaft aircraft is provided with four control surfaces in a wake flow area to complete attitude control, the four control surfaces are arranged in a cross shape, two pairs of control surfaces can correspondingly generate pitching and rolling moments through respective rotation, and the four control surfaces can generate yawing moments through simultaneous rotation. The structure is simple and direct, stable and reliable, and the adjustable attitude angle range is large.

The aircraft body is provided with a pair of wings, so that the aircraft is convenient to disassemble and assemble, and when the wings are used, the aircraft has two modes of vertical flight and horizontal flight and can be freely switched. In the horizontal flight mode, the aircraft has higher cruising speed and lower power consumption, and is suitable for executing a large-range reconnaissance and striking task. And the vertical flight mode is used for finishing the tasks of taking off and landing and fixed-point hovering. When the aircraft does not use wings, the aircraft uses a vertical flight mode, the overall structure is more compact, vertical take-off and landing can be completed in a narrower space, and cluster launching can also be completed.

The head of the machine body can be modularized to replace a guide head, a photoelectric pod, killing gunpowder and rescue goods and materials to complete various different tasks.

The aircraft power paddle is installed inside, and the security is higher.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 shows a schematic structural view of a single-axis aircraft according to the invention;

FIG. 2 shows a cross-sectional view of the single-axis aircraft of FIG. 1;

FIG. 3 shows a view of the warhead and body configuration of the single-axis aircraft of FIG. 1;

FIG. 4 illustrates a structural view of the single-axis aircraft stiffener and mounting plate of FIG. 1;

FIG. 5 shows a mask structure view of the single-axis aircraft of FIG. 1;

FIG. 6 shows a structural view of a wing frame of the single-axis aircraft of FIG. 1;

FIG. 7 illustrates a view of the wing-free structure of the uni-axial aircraft of FIG. 1;

FIG. 8 shows a coaxial twin-bladed structural view of the single-axis aircraft of FIG. 1;

FIG. 9 shows a structural view of a steering system of the single-axis aircraft of FIG. 1;

figure 10 shows a fixed ducted structural view of the single-axis aircraft of figure 1.

Wherein the figures include the following reference numerals:

a machine body 1; a bullet 101; a body 102; a battery mounting plate 103; a flight control mounting plate 104; a power system mounting plate 105; the operating system mounting plate 106; a reinforcing rod 107; a wing 2; a skin 201; a rib plate 202; a support rod 203; support legs 3; flight control hardware 4; a connecting rod 5; a power system 6; a battery 601; a motor 602; a paddle 603; a handling system 7; a steering engine 701; a steering engine rudder blade connection 702; a rudder blade 703.

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1 to 10, an embodiment of the present invention provides a single-axis aircraft, including:

the body 1 is provided with a bullet head 101 and a bullet body 102, and the bullet head 101 is connected with the bullet body 102. The wing 2 is provided with a support rod 203, the support rod 203 is connected with the fuselage, the support rod 203 is provided with a ribbed plate 202, the support rod 203 and the ribbed plate 202 form a wing frame, and the wing frame is sleeved with a skin 201. The supporting legs 3 are connected with the machine body 1 in an adhesive mode. And flight control hardware 4 arranged in the body 1. And the power system 6 is connected with the flight control hardware 4 and is in a coaxial double-propeller structure or a fixed duct structure. And the control system 7 is connected with the flight control hardware 4 and comprises a steering engine 701 and a rudder piece 703, and the steering engine 701 controls the rudder piece 703 to control the attitude of the aircraft. The aircraft body 1 and the supporting legs 3 are connected together through glue joint, the wings 2 are fixedly connected with the aircraft body 1 through connecting rods 5, and the flight control hardware 4, the power system 6 and the operating system 7 are installed on an installation plate inside the aircraft body 1 through screws.

The single-axis aircraft is provided for solving the problems that the attitude control capability of the current single-axis aircraft is weak, the control structure is complex, the flying efficiency is low and the like. The aircraft adopts the upper and lower pair of positive and negative blades 603 as flight power, can offset the reaction torque, has small flight noise, small power consumption and longer endurance time by adopting the positive and negative blades 603, and is suitable for low-speed long-time flight. The electric ducted fan can also be used as flying power, the flying noise is large, the power consumption is also large, but the power supply is larger, and the electric ducted fan is suitable for short-time high-speed flying.

Four steering engines 701 are used at the bottoms of the blades 603 to drive four rudder pieces 703, and the aircraft can generate deflection torque by the rotation of the rudder pieces 703, so that the attitude control of the aircraft is realized. Meanwhile, a lifting wing surface can be added on the aircraft, so that the aircraft has vertical flight and horizontal flight capabilities, the cruising speed of the aircraft is increased, and the cruising duration is improved. Photoelectric reconnaissance loads can be installed on the head of the aircraft, and the head of the aircraft can be modularly replaced by hard damage loads, material rescue loads and the like, so that the application scenes of the equipment in the military and civil fields are enriched.

Example 1

In this embodiment, the body 1 has a bullet 101 and a bullet body 102, and the bullet 101 is connected to the bullet body 102. The body 1 further comprises: and a battery mounting plate 103 arranged at one end of the bullet body 102 close to the bullet head 101. And a flight control mounting plate 104 arranged in the bullet body 102 near the battery mounting plate 103. And a handling system mounting plate 106 is arranged in the bullet body 102 at the end far away from the bullet head 101. A power system mounting plate 105 is disposed in the body 102 adjacent to the operating system mounting plate 106. And the reinforcing rod 107 is glued with the battery mounting plate 103, the flight control mounting plate 104, the control system mounting plate 106 and the power mounting plate. The battery mounting plate 103, the flight control mounting plate 104, the steering system mounting plate 106, and the power system mounting plate 105 are arranged in parallel with each other.

Specifically, the machine body 1 mainly includes a bullet 101, a bullet body 102, a battery mounting plate 103, a flight control mounting plate 104, a power system mounting plate 105, a control system mounting plate 106, and a reinforcing rod, the bullet 101 and the bullet body 102 are connected by screws to form a basic shape, and the position of the bullet 101 can be subjected to loads of various functions, such as photoelectric detection load, damage load, and the like. The battery mounting plate 103, the flight control mounting plate 104, the power system mounting plate 105 and the operating system mounting plate 106 are connected with the bullet body 102 in a gluing mode, the reinforcing rod 107, the battery mounting plate 103, the flight control mounting plate 104, the power system mounting plate 105 and the operating system mounting plate 106 are connected together in a gluing mode, the use of screws can be effectively reduced by adopting gluing fixation, the purpose is to reduce weight, and the operating system 7 also plays a role in fixing the power system 6.

In this embodiment, the wing 2 has a support rod 203, the support rod 203 is connected to the fuselage, the support rod 203 is provided with a rib plate 202, the support rod 203 and the rib plate 202 form a wing frame, and the wing frame is sleeved with a skin 201. The wing 2 may be arranged as a lifting airfoil.

Specifically, the wing 2 mainly comprises a skin 201, a rib plate 202 and a support rod 203, the rib plate 202 is used for forming the appearance of the wing 2, the support rod 203 is used for improving the strength of the wing 2, and the rib plate 202, the support rod 203 and the skin 201 are connected through gluing, so that the structure is simplified, and the weight is reduced as much as possible. The wing 2 provides the aircraft with lift during flat flight and at the same time, in cooperation with the handling system 7, counteracts disturbances of the air flow during flat flight. The wings 2 are detachable modules, and the aircraft is not provided with the wings 2, so that the overall structure of the aircraft is more compact, and the aircraft only has vertical flight capability and is suitable for tasks such as reconnaissance in narrow space. The wing 2 is loaded, the aircraft is larger in size, vertical flight and horizontal flight capabilities are achieved, flight mode switching can be completed independently, the flight has high-speed cruising capability, the endurance of the aircraft is improved, and other specific flight tasks can be completed.

In this embodiment, the support legs 3 are glued to the body 1. Supporting leg 3 adopts the carbon fiber board material, is equipped with the hole on the supporting leg 3, and supporting leg 3 quantity is four, is the cross and arranges.

Specifically, supporting leg 3 adopts the carbon fiber plate processing to form, is connected to together through gluing with organism 1, plays the effect of supporting whole aircraft, and supporting leg 3 digs the hole under the condition that does not influence intensity simultaneously and subtracts weight, and the 3 cross of four supporting legs are arranged, guarantee that the aircraft has sufficient stability before taking off.

In this embodiment, the flight control hardware 4 is provided in the body 1. The flight control hardware 4 is connected with the power system 6 and the control system 7 through cables, the flight control hardware (controller) 4 sends out instructions, and the power system 6 and the control system 7 run to realize vertical take-off and landing of the aircraft. The connecting rods 5 connect the pair of wings 2 to the airframe 1 in a simple and reliable manner.

In this embodiment, the power system 6 is connected to the flight control hardware 4 and has a coaxial double-propeller structure or a fixed duct structure. When the power system 6 is a coaxial double-paddle structure, the power system comprises: battery 601 is mounted on battery mounting board 103. The motors 602, one of the motors 602 is mounted on the power system mounting plate 105, the other motor 602 is mounted on the steering system mounting plate 106, and the two motors 602 are arranged oppositely. The paddle 603 is arranged inside the machine body, is installed on a shaft of the motor 602 and is fixed through a nut, and the paddle 603 rotates reversely to reduce disturbance of air flow to the machine body 1.

Specifically, the power system 6 is a coaxial double-paddle structure, and basically includes a battery 601, a motor 602, and a paddle 603, where the battery 601 is mounted on the battery mounting plate 103 by screws, the motor 602 is mounted on the power system mounting plate 105 by screws, and the paddle 603 is mounted on a shaft of the motor 602 and fixed by nuts. Another motor 602 is mounted to the operating system mounting plate 106 by screws. The two motors 602 are arranged oppositely, and the blades 603 rotate reversely, so that the influence of airflow disturbance on the aircraft body 1 is reduced, and the difficulty of aircraft control is reduced to a certain extent.

In this embodiment, when the power system 6 is a fixed duct structure, it includes: the fixed slot, the fixed slot sets up on the fuselage. And the fixed duct is connected with the fixed groove. The ducted fan is arranged in the fixed ducted.

In this embodiment, the control system 7 is connected to the flight control hardware 4, and includes a steering engine 701 and a rudder piece 703, where the steering engine 701 controls the rudder piece 703 to control the attitude of the aircraft. The manipulation system includes: and the steering engine 701 is connected with the flight control hardware 4 through a cable. The rudder sheet 703 rotates to enable the aircraft to generate a deflection torque and control the attitude of the aircraft, the rudder sheet 703 forms four control surfaces, the control surfaces are arranged in a cross shape, two pairs of the control surfaces rotate to generate pitching and rolling torques, and the four control surfaces rotate to generate a yaw torque. The steering engine rudder piece connecting piece 702 is connected with the steering engine 701 and the rudder piece 703.

Specifically, the steering mechanism is composed of a steering engine 701, a steering engine rudder piece connector 702 and a rudder piece 703. The control mechanism (control system 7) is fixed on the control system mounting plate 106 through screws, the steering engine 701 is communicated with the flight control hardware 4 through cables, and when the aircraft flies, the steering engine 701 and the rudder piece 703 act to control the aircraft to stably hang up and land and keep the attitude of the aircraft body 1 stable.

Example 2

The power system 6 of the aircraft can be replaced by a fixed ducted fan structure, and the model selection of the steering engine 701 is also changed as shown in fig. 10. Compared with a coaxial double-paddle power mode, the ducted fan power has larger thrust and faster flight speed of the aircraft. Therefore, a fixing groove is designed on the machine body 1 of the scheme, a duct is fixed through screws, and the steering engine 701 is arranged on the outer side of the machine body 1 and is also fixed through screws. The rudder piece 703 is connected with the steering engine 701 through a steering engine rudder piece connecting piece 702 by a screw, and the rest of the structure is similar to the first scheme of the aircraft.

Example 3

The manipulation system 7 is improved on the basis of the embodiment 1, and the manipulation system in the embodiment comprises: the steering engine 701 is arranged on the outer side of the machine body 1 and is fixed with the machine body 1 through screws. And the rudder sheet 703 is connected with the steering engine 701 through a steering engine rudder sheet connecting piece 702 and a screw.

Example 4

In another embodiment of the present invention, a control method for a single-axis aircraft is provided, which includes the following steps:

step (1): the power system 6 is controlled by the flight control hardware 4 to generate power.

Step (2): the steering engine 701 of the control system 7 is controlled by the flight control hardware 4, the steering engine 701 controls the control sheet 703, the control sheet 703 forms a control surface, the control surfaces respectively rotate to correspondingly generate pitching and rolling moments, the four control surfaces simultaneously rotate to generate yawing moments, and the vertical flight and the horizontal flight of the single-shaft aircraft are realized.

And (3): when the wings 2 are used, the aircraft has two modes of vertical flight and horizontal flight, and can be freely switched, when the wings 2 are not used, the wings 2 are detached, and the aircraft has a vertical flight mode, and when the wings are not used, the aircraft is used for executing a large-range reconnaissance and striking task, and when the wings are not used, the aircraft has a vertical flight mode, and the vertical flight mode is used for completing a take-off and landing task and a fixed-point hovering task.

The method comprises the following specific steps:

step (1): the motor 602 of the power system 6 is controlled by the flight control hardware 4 to rotate, and the motor 602 drives the blades 603 to rotate or the power system 6 is controlled by the flight control hardware 4 to control the rotation of the electric ducted fan, so as to generate power.

Step (2): the steering engine 701 of the control system 7 is controlled through the flight control hardware 4, the steering engine 701 controls the rudder sheet 703, a control surface is formed through the rudder sheet 703, the control surfaces can correspondingly generate pitching and rolling moments through respective rotation, the four control surfaces can generate yawing moments through simultaneous rotation, and vertical flight and horizontal flight of the single-shaft aircraft are realized.

And (3): when the wings 2 are used, the aircraft has two modes of vertical flight and horizontal flight, and can be freely switched, when the wings 2 are not used, the aircraft has a vertical flight mode, and when the wings are not used, the aircraft is used for executing a large-range reconnaissance and batting task, and the vertical flight mode is used for completing a take-off and landing task and a fixed-point hovering task.

According to the aircraft, the structure of the whole system and the interconnection of all parts are adopted, the control plane of the wake area is used for controlling the aircraft, and the structures of the steering engine 701 and the control plane are adopted, so that two flight modes can be realized when the aircraft has the wings 2, and the aircraft can independently fly when the aircraft does not have the wings 2.

From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects: the single-shaft aircraft is provided with four control surfaces in a wake flow area to complete attitude control, the four control surfaces are arranged in a cross shape, two pairs of control surfaces rotate respectively to generate pitching and rolling moments correspondingly, and the four control surfaces rotate simultaneously to generate yawing moments. The structure is simple and direct, stable and reliable, and the adjustable attitude angle range is large. The machine body 1 is provided with a pair of wings 2, so that the machine body is convenient to disassemble and assemble. When using the wing 2, the aircraft has both vertical flight and horizontal flight modes and can be freely switched. In the horizontal flight mode, the aircraft has higher cruising speed and lower power consumption, and is suitable for executing a large-range reconnaissance and striking task. And the vertical flight mode is used for finishing the tasks of taking off and landing and fixed-point hovering. When the aircraft does not use the wings 2, the aircraft uses a vertical flight mode, the whole structure is more compact, vertical take-off and landing can be completed in a narrower space, and cluster launching can also be completed. The head of the machine body 1 can be modularized to replace a guide head, a photoelectric pod, killing gunpowder and rescue goods and materials to complete various different tasks. The aircraft power paddle 603 is installed inside, and the safety is higher.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made without departing from the spirit and principle of the present invention shall fall within the protection scope of the present invention.

Claims

1. A single-axis aircraft, comprising:

the bullet comprises a body, a bullet head and a bullet tail, wherein the bullet head is connected with the bullet body;

the wing is provided with a supporting rod, the supporting rod is connected with the fuselage, a ribbed plate is arranged on the supporting rod, the supporting rod and the ribbed plate form a wing frame, and a skin is sleeved on the wing frame;

the supporting legs are glued with the machine body;

the flight control hardware is arranged in the machine body; and

the power system is connected with the flight control hardware and is of a coaxial double-propeller structure or a fixed duct structure;

2. The single-axis aircraft as recited in claim 1, wherein said airframe further comprises:

the operating system mounting plate is arranged in the bullet body far away from one end of the bullet;

the power system mounting plate is arranged in the bullet body close to the operating system mounting plate;

the first reinforcing rod is glued with the battery mounting plate, the flight control mounting plate, the control system mounting plate and the power mounting plate.

3. The single-shaft aircraft as claimed in claim 1, wherein the support legs are made of carbon fiber plates, holes are provided on the support legs, and the number of the support legs is four, and the support legs are arranged in a cross shape.

4. The single-axis aircraft as claimed in claim 1, wherein the power system, when in a coaxial twin-oar configuration, comprises:

a battery mounted on the battery mounting plate;

one motor is arranged on the power system mounting plate, the other motor is arranged on the control system mounting plate, and the two motors are arranged oppositely;

5. The single-axis aircraft as claimed in claim 1, wherein the power system, when in a fixed ducted configuration, comprises:

a fixing groove;

the fixed duct is connected with the fixed groove;

the ducted fan is arranged in the fixed ducted.

6. The single-axis aircraft as claimed in claim 1, wherein the battery mounting plate, flight control mounting plate, steering system mounting plate, and power system mounting plate are disposed parallel to one another.

7. The single-axis aircraft as recited in claim 1, wherein the maneuvering system comprises:

and the steering engine rudder piece connecting piece is connected with the steering engine and the rudder piece.

8. The single-axis aircraft as claimed in claim 1, wherein the maneuvering system comprises:

the steering engine is arranged on the outer side of the machine body and is fixed with the machine body through a screw;

9. The single axis aircraft as set forth in claim 1, wherein said wing is configured as a lifting airfoil.

10. A method of controlling a single-axis aircraft, the single-axis aircraft according to any one of claims 1 to 9, comprising the steps of:

step (1): controlling a power system to generate power through flight control hardware;

step (2): the steering engine of the control system is controlled through flight control hardware, the steering engine controls a rudder sheet, a control surface is formed through the rudder sheet, the control surface can correspondingly generate pitching and rolling moments through respective rotation, the four control surfaces can generate yawing moments through simultaneous rotation, and vertical flight and horizontal flight of the single-shaft aircraft are realized;