Tailstock type electric vertical cruise aircraft

Abstract

The utility model discloses a tailstock type electric vertical cruise aircraft which comprises an aircraft body, a main wing, an aileron rudder, a power device, a power source, a rudder, an elevator and an aircraft body base, the pair of main wings are symmetrically connected to the middle section area of the fuselage; the two sets of machine body bases are symmetrically installed in the tail section area of the machine body in an X shape. The four sets of power devices are installed at the four ends of the X-shaped machine body base respectively, each power device is composed of a direct-current brushless motor and a propeller, and the propellers are connected to the direct-current brushless motors. According to the tailstock type electric vertical cruise aircraft provided by the utility model, the defects that the fuselage structure of the traditional vertical take-off and landing aircraft is relatively large in dead weight, large in flight resistance, high in motor power consumption and poor in control precision are effectively optimized.

Description

Technical Field

[0001] The utility model relates to the technical field of general electric aviation, and particularly provides a tail-seat type electric vertical take-off and cruise aircraft. Background Art

[0002] In recent years, with the development of UAV technology, the vertical take-off and landing fixed-wing UAV combines the advantages of rotor UAVs and traditional fixed-wing UAVs, integrating the advantages of traditional multi-rotor aircraft, such as small requirements for take-off and landing sites, vertical take-off and landing capabilities, and the ability to hover in the air, with the advantages of traditional fixed-wing aircraft, such as high speed, long range, and large payload.

[0003] However, currently, the common vertical take-off and landing fixed-wing UAVs on the market are mainly compound-wing UAVs, but the disadvantages brought by compound-wing UAVs are becoming more and more obvious. Since the compound-wing UAV directly installs a multi-rotor system on the fixed-wing aircraft body, there are many disadvantages such as large dead weight of the fuselage structure, large flight resistance, large motor power consumption, and decreased control accuracy.

[0004] Based on this situation, it is very necessary to provide a tail-seat type electric vertical take-off and landing aircraft based on rudder surface control to solve the above problems. Content of the Utility Model

[0005] In view of the above problems, the utility model provides an electric vertical take-off and cruise aircraft.

[0006] To achieve the above object, the utility model provides a tail-seat type electric vertical take-off and cruise aircraft, including: a fuselage, a main wing, aileron rudders, a power device, a power source, a rudder, an elevator, and a fuselage base; a pair of main wings are symmetrically connected to the middle section area of the fuselage;

[0007] Two groups of fuselage bases are symmetrically installed in an "X" shape in the tail section area of the fuselage;

[0008] Four groups of power devices are respectively installed at the four ends of the fuselage base in an "X" shape. The power device is composed of a DC brushless motor and a propeller, and the propeller is connected to the DC brushless motor;

[0009] Two aileron rudders are respectively connected to the outer sides of the trailing edges of the wingtips of the main wings through rotating shafts; the rudder and the elevator are connected to the tail section area of the fuselage, and the rudder and the elevator are arranged in a "cross" shape. The rudder, the elevator, and the fuselage base are cross-distributed on the same circumferential surface; the torsion required for the deflection of the rudder bodies on the aileron rudders, the rudder, and the elevator is provided by DC servo rudders; the power source is used to supply power to the DC servo rudders of the power device, the aileron rudders, the rudder, and the elevator.

[0010] Further, the power device is used to provide power for the vertical take-off and landing and horizontal flight of the aircraft; the rudder and elevator are used to provide the pitch and yaw moments required for the flight mode conversion and level flight stage of the aircraft.

[0011] Further, in the vertical take-off and landing flight mode, by controlling the differential speed of the DC brushless motor, the aircraft performs lifting, pitching, and yawing actions; in the horizontal flight mode, the aileron rudder is opened and closed up and down to deflect and control the aircraft to perform rolling motion, and the maximum opening and closing angle of the aileron rudder is plus or minus 25 degrees;

[0012] The aircraft performs yawing motion by deflecting the rudder left and right, and the maximum opening and closing angle of the rudder (5) is plus or minus 45 degrees; the aircraft performs pitching motion by deflecting the elevator up and down, and the maximum opening and closing angle of the elevator is plus or minus 30 degrees.

[0013] Further, the DC brushless motor is powered by a polymer lithium battery, and the speed of the DC brushless motor is adjusted by an ESC electronic speed controller.

[0014] Further, the layout method of the main wing is: the main beam carbon tube is arranged at 27%-29% of the wing chord length, and the number of wing ribs is 14.

[0015] Further, the wing and the aileron rudder are connected by a composite skin.

[0016] Further, the power device is installed at the four ends of the fuselage base through studs.

[0017] Further, the propeller is made of carbon fiber structure, its size is 10 inches, and the hub radius is 12 mm.

[0018] Further, the fuselage is a cylindrical structure. The front section inside the fuselage is an electronic equipment storage area, the middle section is the placement area of the flight controller, and the rear section is a mission payload storage area; several frames are installed on the inner side of the wall panels in the middle section and rear section areas inside the fuselage, and partitions are fixed on the frames. The partitions run through the entire inside of the fuselage and are used to carry electronic equipment, flight controllers, and mission payloads.

[0019] Further, the main wing is connected to the fuselage through carbon tubes and screws, and the fuselage base is connected to the fuselage through bolts.

[0020] The tail-sitting electric vertical take-off and cruise aircraft provided by the present utility model effectively optimizes the disadvantages of the traditional vertical take-off and landing aircraft, such as large dead weight of the fuselage structure, large flight resistance, large motor power consumption, and poor control accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The following further describes the present utility model in detail in conjunction with the drawings and embodiments:

[0022] Figure 1 Schematic diagram of the structure of the tail-sitter electric vertical takeoff and cruise aircraft provided by the present utility model;

[0023] Figure 2 Schematic diagram of the fuselage structure provided by the present utility model;

[0024] Figure 3 Schematic diagram of the wing structure provided by the present utility model;

[0025] Figure 4 Schematic diagram of the airframe base structure provided by the present utility model. Detailed implementation manners

[0026] The present utility model will be further explained below in conjunction with specific implementation schemes, but the present utility model is not limited thereto.

[0027] To solve the problems of the current traditional vertical takeoff and landing aircraft, such as complex structure, large dead weight of the fuselage structure, large flight resistance, large motor power consumption, and poor control accuracy, and at the same time, to enrich the usage scenarios of electric aircraft and simplify the usage process of vertical takeoff and landing aircraft, the present invention provides a tail-sitter electric vertical takeoff and landing aircraft with a control surface control function, including a fuselage, wings, aileron rudders, a power device, a rudder, an elevator, and an airframe base. Among them, the fuselage 1, as Figure 1 shown. The wing 2, as Figure 2 shown. The airframe base 7, as Figure 3 shown. Among them, the wing 2 is connected to the fuselage through a carbon tube and screws, and the airframe base 7 is connected to the fuselage 1 through bolts;

[0028] That is, the present utility model provides a tail-sitter electric vertical takeoff and cruise aircraft, including: a fuselage 1, a main wing 2, an aileron rudder 3, a power device, a power source, a rudder 5, an elevator 6, and an airframe base 7;

[0029] A pair of the main wings 2 are symmetrically connected to the middle section area of the fuselage 1;

[0030] Two sets of the airframe bases 7 are symmetrically installed in an "X" shape in the tail section area of the fuselage 1;

[0031] Four sets of the power devices are respectively installed at the four ends of the airframe base 7 in an "X" shape. The power device is composed of a DC brushless motor and a propeller, and the propeller is connected to the DC brushless motor;

[0032] Two aileron rudders 3 are respectively connected to the outer side of the trailing edge of the wingtips of the main wing 2 through rotating shafts;

[0033] The rudder 5 and elevator 6 are connected to the tail section of the fuselage 1. The rudder 5 and elevator 6 are arranged in a "cross" shape, and the rudder 5, elevator 6, and body base 7 are cross - distributed on the same circumferential plane;

[0034] The torsion required for the deflection of the aileron rudder 3 and the rudder bodies on the rudder 5 and elevator 6 is provided by a DC servo actuator;

[0035] The power plant 4 uses a DC brushless motor and uses a polymer lithium battery as the power source, which is powered through an ESC electronic speed controller. The propeller uses a two - blade propeller with a size of 10 inches and a hub radius of 12 mm, made of carbon fiber;

[0036] The wing 2 adopts a high - aspect - ratio single - wing layout. The main beam carbon tube is arranged near 28% of the wing chord length. The number of wing ribs is 14. The connection between the wing 2 and the aileron rudder 3 is made by using a composite skin;

[0037] The wing ribs of the wing use carbon fiber materials, and the skin is made of composite materials. The layup is in the sandwich sequence of fiberglass - carbon fiber - fiberglass, and is directly bonded to the wing ribs to form a box - type structure. The main beam carbon tube is arranged near 28% of the wing chord length. It is connected to the fuselage through the carbon tube, screws;

[0038] The composite skin of the aileron rudder 3 is connected to the wing 2 and is placed outside the trailing edge of the wingtip at the left and right ends of the wing 2.

[0039] The rudder 5 and elevator 6 are connected to the fuselage 1 by bolts and are placed in a "cross" shape at the bottom of the aircraft.

[0040] The power source is a polymer lithium battery, which powers the power system and the DC servo actuators that control the aileron rudder 3, rudder 5, and elevator 6.

[0041] Among them, the power plant placed in an "X" shape at the bottom of the aircraft provides the power required for vertical take - off and horizontal flight, and the DC servo actuator provides the torsion required for the deflection of the aileron rudder 3, rudder 5, and elevator 6.

[0042] Among them, the rudder 5 and elevator 6 placed in a "cross" shape at the bottom of the aircraft provide the pitch and yaw moments required for the flight mode conversion and the level flight stage of the aircraft, thereby changing the flight attitude of the aircraft.

[0043] The power plant 4 is installed on the body base 7 and is installed in an "X" shape at the tail of the fuselage through studs. The rudder 5 and elevator 6 are installed in a "cross" shape at the tail of the fuselage through studs

[0044] The power source is used to power the power plant, the DC servo actuators of the aileron rudder 3, rudder 5, and elevator 6.

[0045] The power device is used to provide power for the vertical takeoff and landing and horizontal flight of the aircraft;

[0046] The rudder 5 and elevator 6 are used to provide the pitch and yaw moments required for the flight mode conversion and level flight stage of the aircraft.

[0047] In the vertical takeoff and landing flight mode, by controlling the differential speed of the DC brushless motor, the aircraft performs lifting, pitching, and yawing actions;

[0048] In the horizontal flight mode, the aileron rudder 3 is controlled to open and close up and down to deflect to control the aircraft to perform roll motion, and the maximum opening and closing angle of the aileron rudder is plus or minus 25 degrees;

[0049] The rudder 5 is controlled to open and close left and right to deflect to control the aircraft to perform yaw motion, and the maximum opening and closing angle of the rudder (5) is plus or minus 45 degrees;

[0050] The elevator 6 is controlled to open and close up and down to deflect to control the aircraft to perform pitch motion, and the maximum opening and closing angle of the elevator (6) is plus or minus 30 degrees.

[0051] The aircraft of the present utility model has a reasonable design structure, is simple in structure, the power device is installed on the body base, is installed in an "X" shape at the tail of the fuselage, and the rudder and elevator are installed in a "cross" shape at the tail of the fuselage, so that the aircraft has the advantages of low center of gravity, stable structure, and strong controllability. At the same time, it also forms a stable takeoff and landing support point, does not require a separate additional support part, reduces the extra weight, and makes it more concise and lightweight.

[0052] By adding the aileron rudder 3, rudder 5, and elevator 6 to the rudder surface control system, the efficiency of the aircraft in flight mode conversion can be greatly improved, the adjustment time can be shortened, the thrust loss of the power device due to differential speed can be reduced, and the course stability of the aircraft in the vertical takeoff and landing stage and the course and horizontal stability in the horizontal flight stage can also be greatly improved. At the same time, the added rudder surface can also increase the lift characteristics of the aircraft, thereby increasing the flight distance and cruise time of the aircraft, and can also greatly improve the flight quality and operating performance of the aircraft.

[0053] The fuselage 1 is of a cylindrical structure. The front section inside the fuselage 1 is an electronic equipment storage area, the middle section is the placement area of the flight controller, and the rear section is the mission payload storage area;

[0054] A number of frames 111 are installed on the inner side of the wall plates in the middle section and rear section areas inside the fuselage 1. A partition plate is fixed on the frame 111, and the partition plate 112 runs through the entire inside of the fuselage 1. The partition plate is used to carry electronic equipment, flight controllers, and mission payloads. The aircraft fuselage is of a carbon fiber structure. In terms of structural layout, the front section of the fuselage uses frames and partition plates for shaping, and the middle and rear sections use wall plates and partition plates in cooperation with frames to support sufficient internal space.

[0055] A brief description of the working process of the above-mentioned aircraft is as follows:

[0056] S1: Assemble the fuselage, main wing and the body base. After installing each system, connect the battery for power supply. The aircraft conducts self-check and is vertically placed on the ground. It takes off vertically according to the method of an "X"-type multi-rotor aircraft, that is, the aircraft takes off, pitches and yaws by controlling the differential speed of the power device.

[0057] S2: After vertical takeoff, activate the rudder 5 and the elevator 6 placed in a "plus" shape at the bottom of the aircraft. The elevator 6 starts to deflect downward to generate a nose-down moment for the aircraft. At the same time, it cooperates with the up and down thrust difference generated by the differential speed of the power device to convert the aircraft from the vertical takeoff mode with the nose up to the horizontal flight mode with the nose forward.

[0058] S3: Turn on the horizontal flight mode. In this mode, the power device only provides the thrust required for flight and no longer needs to generate a thrust difference. The attitude change is provided by the moments generated by the deflection of the aileron rudder 3, the rudder 5 and the elevator 6.

[0059] S4: When the horizontal flight ends, activate the rudder 5 and the elevator 6 placed in a "plus" shape at the bottom of the aircraft. The elevator 6 starts to deflect upward to generate a nose-up moment for the aircraft. At the same time, it cooperates with the up and down thrust difference generated by the differential speed of the power device to convert the aircraft from the horizontal flight mode with the nose forward to the vertical flight mode with the nose up.

[0060] S5: The aircraft switches to the vertical flight mode and lands vertically according to the method of an "X"-type multi-rotor aircraft, that is, the aircraft lands, pitches and yaws by controlling the differential speed of the power device. After landing, the DC brushless motor automatically locks and the propeller stops rotating, and the flight ends.

[0061] The specific embodiments of the present utility model are written in a progressive manner, emphasizing the differences between each embodiment. The similar parts can be referred to each other.

[0062] The above has described in detail the embodiments of the present utility model with reference to the drawings. However, the present utility model is not limited to the above embodiments. Within the scope of knowledge possessed by those of ordinary skill in the art, various changes can be made without departing from the gist of the present utility model.

Claims

1. Tailstock-type electric vertical takeoff and cruise aircraft, characterized in that, Comprising: Fuselage (1), main wings (2), aileron rudders (3), power plant, power source, rudder (5), elevator (6), airframe base (7); A pair of main wings (2) are symmetrically connected to the middle section area of the fuselage (1). Two sets of the airframe base (7) are symmetrically installed in an "X" shape in the tail section area of the fuselage (1). Four sets of the power plant are respectively installed at the four ends of the airframe base (7) in an "X" shape. The power plant is composed of a DC brushless motor and a propeller, and the propeller is connected to the DC brushless motor. Two aileron rudders (3) are respectively connected to the outer side of the trailing edge of the wingtips of the main wings (2) through rotating shafts; The rudder (5) and elevator (6) are connected to the tail section area of the fuselage (1). The rudder (5) and elevator (6) are arranged in a "plus" shape. The rudder (5), elevator (6), and airframe base (7) are cross-distributed on the same circumferential plane; The torsion required when the rudder bodies on the aileron rudders (3), rudder (5), and elevator (6) deflect is provided by DC servo rudders. The power source is used to supply power to the DC servo rudders of the power plant, aileron rudders (3), rudder (5), and elevator (6).

2. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The power plant is used to provide power for the vertical takeoff and landing and horizontal flight of the aircraft; The rudder (5) and elevator (6) are used to provide the pitch and yaw moments required for the flight mode conversion and level flight stage of the aircraft.

3. The tailstock type electric vertical takeoff and cruise aircraft according to claim 2, characterized in that, In the vertical takeoff and landing flight mode, by controlling the differential speed generated by the DC brushless motor, the aircraft performs ascending, descending, pitching, and yawing actions; In the horizontal flight mode, the aircraft performs rolling motion by controlling the up and down opening and deflection of the aileron rudders (3). The maximum opening angle of the aileron rudders (3) is plus or minus 25 degrees. The aircraft performs yawing motion by controlling the left and right opening and deflection of the rudder (5). The maximum opening angle of the rudder (5) is plus or minus 45 degrees; The aircraft performs pitching motion by controlling the up and down opening and deflection of the elevator (6). The maximum opening angle of the elevator (6) is plus or minus 30 degrees.

4. The tailstock type electric vertical takeoff and cruise aircraft according to claim 3, wherein, The DC brushless motor is powered by a polymer lithium battery, and the speed of the DC brushless motor is adjusted by an ESC electronic speed controller.

5. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The layout method of the main wings (2) is: The main beam carbon tube is arranged at 27% - 29% of the wing chord length, and the number of wing ribs is 14.

6. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, wherein, The main wings (2) and aileron rudders (3) are connected by a composite skin.

7. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The power plant is installed at the four ends of the airframe base (7) through studs.

8. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The propeller is a carbon fiber structure, with a size of 10 inches and a hub radius of 12 mm.

9. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The fuselage (1) is a cylindrical structure. The front section inside the fuselage (1) is an electronic equipment storage area, the middle section is the placement area of the flight controller, and the rear section is the mission payload storage area; A number of frames (111) are installed on the inner side of the wall plates in the middle section area and rear section area inside the fuselage (1). Partition plates are fixed on the frames (111). The partition plates (112) run through the entire inside of the fuselage (1), and the partition plates are used to carry electronic equipment, flight controllers, and mission payloads.

10. The tailstock type electric vertical takeoff and cruise aircraft according to claim 1, characterized in that, The main wing (2) is connected to the fuselage (1) through carbon tubes and screws, and the body base (7) is connected to the fuselage (1) through bolts.

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