Variable-pitch lift wing for vertical take-off and landing level flight cruise aircraft

Abstract

The invention relates to a variable-pitch lift wing for a vertical take-off and landing level flight cruise aircraft, and belongs to the technical field of vertical take-off and landing aircraft wings, the variable-pitch lift wing comprises an aircraft body, 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, and the left wing and the right wing are designed according to the shape of a conventional lift wing; the left wing and the right wing are connected in the mode that a variable-pitch shaft penetrates through the aircraft body, a left positioning bearing and a right positioning bearing are fixedly arranged on the two sides, in the aircraft body, of the variable-pitch shaft respectively, a sector gear is arranged in the middle of the variable-pitch shaft, a worm is arranged at the tooth end of the sector gear, and a worm gear is arranged at the tooth end of the worm. A positive and negative rotation servo motor is arranged at one end of the worm to provide power, the servo motor is fixed in the machine body, the worm is used for driving the sector gear to rotate, and the sector gear rotates to drive the left wing and the right wing to rotate synchronously through the variable pitch shaft. The incidence angle of the wing can be changed through forward and reverse rotation of the servo motor.

Description

Technical Field

[0001] The invention belongs to the technical field of vertical take-off and landing aircraft wings, and in particular relates to a variable-pitch lift wing for a vertical take-off and landing level-flying cruise aircraft. Background Art

[0002] Conventional lift wings can effectively provide the main lift, which is beneficial to reduce power consumption and increase the range. However, if a front propeller-powered, tail-seat vertical take-off and landing aircraft adopts 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 aircraft body and easily causing rollover accidents. In order to overcome the lateral thrust generated by the lift wings, a variable-pitch lift wing for vertical take-off and landing and level flight cruise aircraft is proposed. Summary of the invention

[0003] The present invention discloses a variable-pitch lift wing for a vertical take-off and landing level-flying cruise aircraft. In order to save energy consumption, the aircraft is provided with a variable-pitch lift wing. When the aircraft is in level flight, the variable-pitch lift wing can provide the main lift like a conventional lift wing, which is beneficial to reducing power consumption and increasing the range. When the aircraft is in vertical take-off and landing, the variable-pitch lift wing can change the wing angle of attack by a variable pitch, eliminate lateral thrust, and is beneficial to the safe take-off and landing of the aircraft. In order to ensure the safe take-off and landing of the vertical take-off and landing level-flying cruise aircraft, the present invention provides the following technical solutions: The invention provides a variable pitch lift wing for a vertical take-off and landing level flight cruise aircraft, 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, and the left wing and the right wing are designed in the shape of a conventional lift wing.

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

[0006] Preferably, the left wing and the right wing are connected by a variable pitch shaft passing through the fuselage, and the wing roots of the left wing and the right wing are not directly connected to the fuselage.

[0007] Preferably, a left locating bearing and a right locating bearing are fixedly provided on both sides of the pitch variable shaft in the machine body respectively.

[0008] Preferably, a sector gear is provided in the middle of the pitch-changing shaft, and a worm is provided at the tooth end of the sector gear.

[0009] Preferably, a forward and reverse servo motor is provided at one end of the worm to provide power, and the servo motor is fixed in the machine body.

[0010] Preferably, the worm gear is used to drive the sector gear to rotate, and the rotation of the sector gear drives the left wing and the right wing to rotate synchronously through the pitch shaft. The angle of attack of the wing can be changed by the forward and reverse rotation of the servo motor, so that the wing can generate appropriate lift when the aircraft is cruising in level flight, and can eliminate the lateral thrust generated by the lift effect during vertical take-off and landing.

[0011] Preferably, the tail seat of the aircraft is provided with an upper pressure sensor and a lower pressure sensor.

[0012] Preferably, a dual-axis tilt sensor is provided in the body.

[0013] 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 the range. However, if a front propeller-powered, tail-mounted 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, which can easily cause rollover accidents. This variable-pitch lift wing used for vertical take-off and landing and level flight cruise aircraft can avoid the lateral thrust generated by conventional lift wings, reduce power consumption and increase the range, and solve the problem of difficulty in balancing the fuselage during vertical take-off and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] 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.

[0015] In the attached picture: Figure 1 Schematic diagram of the structure above the aircraft Figure 2 for Figure 1 Schematic diagram of vertical cutting structure at A in the middle Figure 3 for Figure 1 Schematic diagram of vertical cutting structure at B in the middle Figure 4 Schematic diagram of the wing attitude of the aircraft during vertical takeoff and landing Figure 5 Schematic diagram of the wing attitude of the aircraft during level flight cruise In the figure: 1, coaxial reverse propeller power device 2, sector gear 3, servo motor 4, worm 5, left wing 6, right wing 7, left aileron 8, right aileron 9, left positioning bearing 10, right positioning bearing 11, variable pitch shaft 12, upper pressure sensor 13, lower pressure sensor 14, fuselage 15, dual-axis tilt sensor DETAILED DESCRIPTION

[0016] 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.

[0017] Example: Figure 1 , Figure 2 , Figure 4 As shown, this type of variable pitch lift wing for vertical take-off and landing and level flight cruise aircraft, when the aircraft takes off vertically, the downward high-speed airflow generated by the coaxial counter-propeller power device 1 flows through the variable pitch lift wing to generate lateral thrust, and at this time the servo motor 3 is started, and the left wing 5 and the right wing 6 are synchronously rotated through the worm 4, the fan gear 2, and the variable pitch shaft 11 to adjust the angle of attack and change the lateral thrust, so that the pressures of the upper pressure sensor 12 and the lower pressure sensor 13 are the same, and at this time the lateral thrust has been eliminated and take-off can be achieved.

[0018] like Figure 1 , Figure 2 , Figure 5 As shown, when the aircraft is cruising horizontally, the servo motor 3 is started, and the left wing 5 and the right wing 6 are synchronously rotated through the worm 4, the sector gear 2, and the pitch-variable shaft 11, so that the left wing 5 and the right wing 6 have a suitable positive angle of attack to generate a suitable lift, and the aircraft enters a level flight cruising state in which the lift is mainly provided by the wings.

[0019] like Figure 1 , Figure 2 , Figure 4 As shown, when the aircraft lands vertically, the servo motor 3 is started, and the left wing 5 and the right wing 6 are synchronously rotated through the worm 4, the sector gear 2, and the pitch shaft 11 to adjust the angle of attack and change the lateral thrust. At the same time, other rudders and wings are adjusted, and the dual-axis tilt sensor 15 and the aircraft attitude are observed. When the body is vertical and does not move horizontally, the aircraft can land.

[0020] 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 variable pitch lift wing for a vertical take-off and landing cruise aircraft, characterized in that: The invention comprises a fuselage, wherein a left wing and a right wing are symmetrically arranged on the left and right sides of the middle part of the fuselage, the left wing and the right wing are designed in the shape of a conventional lift wing, the left wing and the right wing are connected by a pitch-variable shaft penetrating the fuselage, the wing roots of the left wing and the right wing are not directly connected to the fuselage, the pitch-variable shaft is respectively fixed with a left locating bearing and a right locating bearing on both sides of the fuselage, a sector gear is arranged in the middle part of the pitch-variable shaft, a worm is arranged at the tooth end of the sector gear, a forward and reverse servo motor is arranged at one end of the worm to provide power, the servo motor is fixed in the fuselage, the worm is used to drive the sector gear to rotate, the rotation of the sector gear drives the left wing and the right wing to rotate synchronously through the pitch-variable shaft, the angle of attack of the wing can be changed by the forward and reverse rotation of the servo motor, so that the wing can generate appropriate lift when the aircraft is cruising in level flight, and can eliminate the lateral thrust generated by the lift effect during vertical take-off and landing.

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