Vertical take-off and landing aircraft adopting special fixed wings

Abstract

The invention relates to a vertical take-off and landing aircraft adopting special fixed wings, which belongs to the technical field of vertical take-off and landing airplanes, and comprises an aircraft body, and a set of coaxial reverse propeller power device is arranged at the front end of the aircraft body. A front upper rudder wing and a front lower rudder wing are symmetrically arranged on the front portion of the aircraft body up and down, a left wing and a right wing are symmetrically arranged on the left side and the right side of the middle of the aircraft body, a left empennage and a right empennage are arranged on the left side and the right side of the rear portion of the aircraft body, and an upper empennage and a lower empennage are arranged on the upper side and the lower side of the rear portion of the aircraft body. A left anti-lift wing is arranged in the middle of the upper portion of the left wing, a right anti-lift wing is arranged in the middle of the upper portion of the right wing, and during vertical take-off and landing, lateral thrust f2 generated when the left anti-lift wing and the right anti-lift wing synchronously open by a certain angle can counteract lateral thrust f1 generated by the left wing and the right wing, so that the aircraft can keep balanced during vertical take-off and landing.

Description

Technical Field

[0001] The invention belongs to the technical field of vertical take-off and landing aircraft, and in particular relates to a vertical take-off and landing aircraft adopting special fixed wings. Background Art

[0002] Conventional lift wings can effectively provide the main lift, which is beneficial to reduce power consumption and increase range. However, if a front propeller-powered, tail-seat vertical take-off and landing aircraft uses conventional lift wings, the lift wings in a vertical posture during vertical take-off and landing will produce lateral thrust, making it difficult to balance the fuselage and easily causing rollover accidents. In order to overcome the lateral thrust generated by the lift wings, a vertical take-off and landing aircraft using special fixed wings is proposed. Summary of the invention

[0003] The present invention discloses a vertical take-off and landing aircraft using special fixed wings. In order to save energy consumption, the aircraft is provided with special fixed wings. When the aircraft is flying horizontally, the special fixed wings can provide the main lift like conventional lift wings, which is beneficial to reducing power consumption and increasing the range. When taking off and landing vertically, the special fixed wings can offset the lateral thrust, which is beneficial to the safe take-off and landing of the aircraft. In order to provide a vertical take-off and landing aircraft with a relatively long range and capable of safe take-off and landing, the present invention provides the following technical solutions: The invention provides a vertical take-off and landing aircraft adopting special fixed wings, comprising an airframe, wherein a set of coaxial reverse propeller power devices are arranged at the front end of the airframe, and the generation of reverse torque can be avoided as much as possible during the operation of the coaxial reverse propellers.

[0004] Preferably, a left wing and a right wing are symmetrically provided on the left and right sides of the middle part of the fuselage. The left wing and the right wing are designed according to the shape and angle of attack of conventional lift wings. During level flight, the high-speed airflow flowing from front to back will generate upward lift, and during vertical take-off and landing, the downward high-speed airflow generated by the coaxial counter-propeller power device will generate lateral thrust f1.

[0005] Preferably, the trailing edge of the left wing is provided with a left aileron and a left flap, and the trailing edge of the right wing is provided with a right aileron and a right flap.

[0006] Preferably, a left anti-lift wing is provided at the middle upper part of the left wing, and a right anti-lift wing is provided at the middle upper part of the right wing. During vertical take-off and landing, the lateral thrust f2 generated by the left anti-lift wing and the right anti-lift wing opening synchronously at a certain angle can offset the lateral thrust f1 generated by the left wing and the right wing. Since the left anti-lift wing and the right anti-lift wing are provided at the middle upper part of the wings, the lateral thrust f2 generated by them is equal in strength to the lateral thrust f1, but opposite in direction, and their vertical center points basically coincide with each other. Since the vertical center points of the generated lateral thrust f2 and the lateral thrust f1 basically coincide with each other, no harmful torque is generated on the fuselage, which is beneficial for maintaining the balance of the aircraft during vertical take-off and landing.

[0007] Preferably, a dual-axis tilt sensor is provided in the body to assist in adjusting the vertical posture of the body.

[0008] Preferably, a front upper rudder wing and a front lower rudder wing are symmetrically provided at the upper and lower parts of the front part of the fuselage, the front upper rudder wing is provided with a front upper rudder wing rotation axis, and the front lower rudder wing is provided with a front lower rudder wing rotation axis.

[0009] Preferably, a left tail and a right tail are provided on the left and right sides of the rear part of the fuselage, a left elevator is provided on the rear edge of the left tail, a No. 3 supporting foot is provided on the outer edge of the left tail, a No. 3 pressure sensor is provided at the rear end of the No. 3 supporting foot, a right elevator is provided on the rear edge of the right tail, a No. 1 supporting foot is provided on the outer edge of the right tail, and a No. 1 pressure sensor is provided at the rear end of the No. 1 supporting foot.

[0010] Preferably, an upper tail wing and a lower tail wing are provided on the upper and lower sides of the rear part of the fuselage, an upper rudder is provided on the rear edge of the upper tail wing, a No. 2 supporting foot is provided on the outer edge of the upper tail wing, a No. 2 pressure sensor is provided at the rear end of the No. 2 supporting foot, a lower rudder is provided on the rear edge of the lower tail wing, a No. 4 supporting foot is provided on the outer edge of the lower tail wing, and a No. 4 pressure sensor is provided at the rear end of the No. 4 supporting foot.

[0011] Preferably, when the machine body is in a vertical state, the first pressure sensor, the second pressure sensor, the third pressure sensor, and the fourth pressure sensor are on the same horizontal plane, serving as four supporting points for supporting the weight of the entire machine.

[0012] Preferably, the right flap is provided with a flap rotation axis, and the right anti-lift wing is provided with an anti-lift wing rotation axis.

[0013] Preferably, the aircraft is bilaterally symmetrical, and vertically symmetrical except for the left wing and the right wing.

[0014] The beneficial effects of the present invention are: Conventional lift wings can effectively provide the main lift, which is beneficial to reduce power consumption and increase range. However, if a front propeller-powered, tail-seat vertical take-off and landing aircraft uses conventional lift wings, the lift wings in the vertical posture during vertical take-off and landing will produce lateral thrust, making it difficult to balance the fuselage, which can easily cause rollover accidents. This type of vertical take-off and landing aircraft with special fixed wings uses specially designed lift wings to overcome the lateral thrust generated by conventional lift wings, reduce power consumption and increase range, and solve the problem of difficulty in balancing the fuselage during vertical take-off and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0016] In the attached picture: Figure 1 Schematic diagram of the structure above the aircraft Figure 2 Schematic diagram of the structure below the aircraft Figure 3 for Figure 1 Schematic diagram of the vertical section structure when the right anti-lift wing is closed at A in the middle Figure 4 for Figure 1 Schematic diagram of the vertical section structure when the right anti-lift wing is opened at A in the middle Figure 5 Schematic diagram of the right side of the aircraft Figure 6 Schematic diagram of the aircraft in level flight Figure 7 Schematic diagram of the aircraft taking off, level flight, and landing posture changes In the figure: 1, fuselage 2, coaxial reverse propeller power device 3, dual-axis tilt sensor 4, front upper rudder wing 5, front upper rudder wing rotation axis 6, left wing 7, left anti-lift wing 8, left aileron 9, left flap 10, right wing 11, right anti-lift wing 12, right aileron 13, right flap 14, right tail 15, right elevator 16, No. 1 support foot 17, No. 1 pressure sensor 18, upper tail 19, No. 2 support foot 20, No. 2 pressure sensor 21, left tail 22, No. 3 support foot 23, No. 3 pressure sensor 24, left elevator 25, front lower rudder wing 26, front lower rudder wing rotation axis 27, lower tail 28, No. 4 support foot 29, No. 4 pressure sensor 30, anti-lift wing rotation axis 31, flap rotation axis 32, upper rudder 33, lower rudder DETAILED DESCRIPTION

[0017] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0018] Example: Figure 1 Figure 5 Figure 7 As shown, when the special fixed-wing vertical take-off and landing aircraft takes off vertically, the coaxial reverse propeller power device 2 is started to generate an upward pulling force, and the front upper rudder wing 4 and the front lower rudder wing 25 are controlled according to the signal of the dual-axis tilt sensor 3 so that the pressure of the No. 1 pressure sensor 17 is the same as that of the No. 3 pressure sensor 23; the left aileron 8 and the right aileron 12, the left flap 9 and the right flap 13 are controlled, and the left anti-lift wing 7 and the right anti-lift wing 11 are gradually opened at the same time so that the pressure of the No. 2 pressure sensor 20 is the same as that of the No. 4 pressure sensor 29.

[0019] Further, if Figure 1 Figure 5 Figure 7As shown, the coaxial reverse propeller power device 2 is controlled to increase the lifting force. During the process, the pressure of the No. 1 pressure sensor 17 and the No. 3 pressure sensor 23 are kept at the same pressure, and the pressure of the No. 2 pressure sensor 20 and the No. 4 pressure sensor 29 are kept at the same pressure. When the upward lifting force is greater than the overall gravity of the aircraft, the aircraft leaves the ground and moves vertically upward.

[0020] Further, if Figure 1 Figure 5 Figure 7 As shown, the right elevator 15 and the left elevator 24 are manipulated to deflect the downward airflow generated by the coaxial counter-propeller power device 2, so that the tail of the aircraft is gradually raised, and the aircraft will also gradually accelerate to level flight.

[0021] Further, if Figure 1 Figure 5 Figure 7 As shown, when the aircraft reaches a horizontal attitude, the left anti-lift wing 7 and the right anti-lift wing 11 are closed.

[0022] Further, if Figure 1 Figure 5 Figure 7 As shown, the flight attitude is adjusted by manipulating the rudder wings so that the aircraft enters a level flight cruising state, during which the left wing 6 and the right wing 10 provide the main lift.

[0023] Further, if Figure 1 Figure 5 Figure 7 As shown, when flying forward to a high altitude close to the destination, the right elevator 15 and the left elevator 24 are manipulated to deflect the backward airflow generated by the coaxial counter-propeller power device 2, so that the tail of the aircraft gradually droops and the fuselage 1 is gradually transformed into a vertical posture. During this period, the left aileron 8 and the right aileron 12, the left flap 9 and the right flap 13 are manipulated to reduce the lateral thrust f1 generated by the left wing 6 and the right wing 10. During this period, the left anti-lift wing 7 and the right anti-lift wing 11 are gradually opened to generate a lateral thrust f2 to offset the lateral thrust f1 generated by the left wing 6 and the right wing 10.

[0024] Further, if Figure 1 Figure 5 Figure 7 As shown, when the aircraft is completely transformed into a vertical posture, the coaxial counter-propeller power device 2 is controlled to make the upward pulling force generated equal to the overall gravity of the aircraft, and then fine-tuned to make the aircraft hover vertically in the air.

[0025] Further, if Figure 1 Figure 5 Figure 7As shown, the right elevator 15 and the left elevator 24, the upper rudder 32 and the lower rudder 33 are manipulated to slightly change the attitude of the aircraft so that the aircraft moves horizontally to just above the landing point.

[0026] Further, if Figure 1 Figure 5 Figure 7 As shown, the coaxial counter-propeller power device 2 is controlled so that the upward pulling force generated is slightly smaller than the overall gravity of the aircraft, so that the aircraft begins to descend. At this time, the coaxial counter-propeller power device 2 is controlled to adjust the pulling force to slowly descend the aircraft.

[0027] Further, if Figure 1 Figure 5 Figure 7 As shown, when the aircraft is about to reach the ground, the coaxial reverse propeller power device 2 is controlled to slightly increase the lift force to offset the falling inertia of the aircraft and land smoothly on the landing point. At this time, the landing operation is completed.

[0028] Further, if Figure 1 Figure 5 Figure 7 As shown, after the aircraft is stabilized, the coaxial counter-propeller power device 2 is shut down and the flight process ends.

[0029] The above description is only a specific embodiment of the present invention, and the present invention is described in detail. The parts not described in detail are conventional technologies, but the protection scope of the present invention is not limited to this. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. The protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A vertical take-off and landing aircraft using special fixed wings, characterized in that: The invention comprises a body 1, wherein a coaxial reverse propeller power device 2 is provided at the front end of the body 1, and the reverse torque can be avoided as much as possible during the operation of the coaxial reverse propeller. A left wing 6 and a right wing 10 are symmetrically provided on the left and right sides of the middle part of the body 1. The left wing 6 and the right wing 10 are designed according to the shape and angle of attack of conventional lift wings. When flying horizontally, the high-speed airflow flowing from front to back will generate an upward lift. When taking off and landing vertically, the downward high-speed airflow generated by the coaxial reverse propeller power device 2 will generate a lateral thrust f1. A left anti-lift wing 7 is provided in the middle part above the left wing 6, and a right anti-lift wing 11 is provided in the middle part above the right wing 10. When taking off and landing vertically, the left anti-lift wing 7 and the right anti-lift wing 11 are synchronously opened at a certain angle to generate a lateral thrust f2. The lateral thrust f1 generated by the left wing 6 and the right wing 10 can be offset. Since the left anti-lift wing 7 and the right anti-lift wing 11 are arranged at the upper middle part of the wing, the lateral thrust f2 generated by them is equal to the lateral thrust f1 in strength, opposite in direction, and the vertical center points basically coincide with each other. Since the generated lateral thrust f2 basically coincides with the vertical center points of the lateral thrust f1, no harmful moment is generated on the fuselage, which is beneficial to keeping the aircraft balanced during vertical take-off and landing. The front upper rudder wing 4 and the front lower rudder wing 25 are symmetrically arranged at the upper and lower parts of the front of the fuselage 1, and the left tail wing 21 and the right tail wing 14 are arranged on the left and right sides of the rear of the fuselage 1, and the upper tail wing 18 and the lower tail wing 27 are arranged on the upper and lower sides of the rear.

2. A vertical take-off and landing aircraft using special fixed wings according to claim 1, characterized in that: A dual-axis tilt sensor 3 is provided in the machine body to assist in adjusting the vertical posture of the machine body.

3. A vertical take-off and landing aircraft using special fixed wings according to claim 1, characterized in that: A left elevator 24 is provided at the rear edge of the left tail 21, a No. 3 supporting foot 22 is provided at the outer edge of the left tail 21, and a No. 3 pressure sensor 23 is provided at the rear end of the No. 3 supporting foot 22; a right elevator 15 is provided at the rear edge of the right tail 14, a No. 1 supporting foot 16 is provided at the outer edge of the right tail 14, and a No. 1 pressure sensor 17 is provided at the rear end of the No. 1 supporting foot 16; an upper rudder 32 is provided at the rear edge of the upper tail 18, a No. 2 supporting foot 19 is provided at the outer edge of the upper tail 18, and a No. 2 pressure sensor 20 is provided at the rear end of the No. 2 supporting foot 19; a lower rudder 33 is provided at the rear edge of the lower tail 27, a No. 4 supporting foot 28 is provided at the outer edge of the lower tail 27, and a No. 4 pressure sensor 29 is provided at the rear end of the No. 4 supporting foot 28.

4. A vertical take-off and landing aircraft using special fixed wings according to claim 1, characterized in that: When the machine body 1 is in a vertical state, the first pressure sensor 17, the second pressure sensor 20, the third pressure sensor 23, and the fourth pressure sensor 29 are on the same horizontal plane, serving as four supporting points for supporting the weight of the entire machine.

5. A vertical take-off and landing aircraft using special fixed wings according to claim 1, characterized in that: The left wing 6 is provided with a left aileron 8 and a left flap 9 at its rear edge, and the right wing 10 is provided with a right aileron 12 and a right flap 13 at its rear edge.

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