Tilting rotor wing

Abstract

The utility model discloses a tilting wing which comprises a fixed section wing and a tilting section wing, and a transmission assembly is arranged between the fixed section wing and the tilting section wing. A power device is arranged at the front end of the tilting section wing; ailerons are arranged on the side sections of the tilting section wings, and the ailerons are movably hinged in connecting grooves formed in the tilting section wings; the tilting section wing is provided with a resistance-increasing stabilizing mechanism, the resistance-increasing stabilizing mechanism is composed of two first spoilers and a second spoiler, the two first spoilers are symmetrically hinged and fixed to the lower bottom surface of the tilting section wing, and the second spoiler is hinged and fixed to the upper wing surface of the tilting section wing; in the vertical take-off and landing stage of the tilting wing aircraft, the flow direction of the propeller slip flow on the upper wing surfaces of the tilting wings is changed by controlling the ailerons of the wings of the tilting section, and the resistance generated by the propeller slip flow can be reduced, so that the tilting wing aircraft is more stable in hovering and taking-off and landing.

Description

Technical Field

[0001] The utility model relates to the technical field of tilt-rotor takeoff and landing, in particular to a tilt-rotor wing. Background Art

[0002] The tilt-rotor wing configuration is an improvement on the tilt-rotor configuration, which mainly solves the fountain effect and weight gain effect caused by the aerodynamic interference between the rotor and the wing of the tilt-rotor configuration aircraft. At the same time, it also has the vertical takeoff and landing and in-air hovering capabilities similar to a helicopter, and is a special configuration aircraft with high flight speed, large load capacity, and large range close to that of a fixed-wing aircraft.

[0003] During the vertical takeoff and landing of existing tilt-rotor wing aircraft, the high-speed slipstream of the propeller will flow through the upper and lower surfaces of the tilt section wing. When the high-speed slipstream passes through the wing surface of the tilt section, a horizontal resistance will be generated due to the Bernoulli effect, reducing the takeoff and landing stability of the tilt-rotor wing aircraft. Therefore, this application designs a tilt-rotor wing to solve the above problems. Summary of the Utility Model

[0004] The purpose of the utility model is to solve the technical problems existing in the prior art and provide a tilt-rotor wing.

[0005] To achieve the above purpose, the technical solution provided by the utility model is: a tilt-rotor wing, including a fixed-section wing and a tilt-section wing. There is a transmission assembly between the fixed-section wing and the tilt-section wing. Through the setting of the transmission assembly, the fixed-section wing and the tilt-section wing can be better connected and drive the rotation of the tilt-section wing. A power device is provided at the front end of the tilt-section wing. Ailerons are provided on the side section of the tilt-section wing, and the ailerons are movably hinged in a connection groove opened on the tilt-section wing.

[0006] A drag-increasing and stabilizing mechanism is provided on the tilt-section wing. The drag-increasing and stabilizing mechanism is composed of two first spoiler plates and one second spoiler plate. The two first spoiler plates are symmetrically hinged and fixed to the lower bottom surface of the tilt-section wing, and the second spoiler plate is hinged and fixed to the upper wing surface of the tilt-section wing.

[0007] Preferably, two second installation grooves for installing and placing the first spoiler plates are symmetrically opened on the lower bottom surface of the tilt-section wing, and a first installation groove for installing and placing the second spoiler plate is opened on the upper wing surface of the tilt-section wing.

[0008] Preferably, the power device is composed of a nacelle, a fairing, and a propeller. A motor is provided in the nacelle, and the propeller and the fairing are fixedly connected to the motor shaft of the motor.

[0009] Preferably, the transmission assembly is composed of a transmission rotating shaft and multiple equally spaced stable support plates, and the stable support plates are fixedly connected to the transmission rotating shaft.

[0010] Preferably, a hydraulic slewing drive device for driving parts to rotate is connected to both the transmission assembly and the resistance increasing and stabilizing mechanism.

[0011] The present invention also discloses a control method for a tilt-rotor wing, which is applied to the above-mentioned tilt-rotor wing. The specific control method is as follows: First, connect the valve and pipeline to the hydraulic slewing drive device, then connect the power supply to the electrical components, and then start the tilt-rotor wing aircraft. When the aircraft takes off and lands vertically, the transmission assembly drives the transmission rotating shaft to rotate through the connected hydraulic slewing drive device, and the stable support plate on the transmission rotating shaft drives the tilt-section wing to rotate until the tilt-section wing is perpendicular to the fixed-section wing. At this time, the propeller in the power device rotates, and the rotation of the propeller will cause the propeller slipstream to pass through the upper and lower wing surfaces of the tilt-section wing at a high speed. When the pressure on both wing surfaces of the tilt-section wing is uneven, according to Bernoulli's principle, a horizontal force is generated on the aircraft, reducing the takeoff, landing, and hovering stability of the aircraft. At this time, control the aileron to deflect to reduce the resistance generated by the tilt-section wing, and then open the first spoiler and the second spoiler to balance the pressure difference on both sides of the tilt-section wing, finally eliminating the above resistance, enabling the aircraft to hover stably during takeoff and landing.

[0012] Advantages of the present invention:

[0013] In the present invention, during the vertical takeoff and landing stage of the tilt-rotor wing aircraft, through the deflection cooperation of the tilt-section wing and the aileron, it is convenient to change the airflow on the upper wing surface of the tilt-section wing, reduce the horizontal force on the tilt-section wing in the vertical state, and thus enable the aircraft to be more stable during the hovering takeoff and landing stage. Then, through the deflection cooperation of the first spoiler and the second spoiler, it is convenient to balance the airflow velocities on both sides of the tilt-section wing, ensuring the pressure difference on both sides of the tilt-section wing, and thus enabling the situation of unbalanced force on the tilt-section wing to be eliminated as much as possible, finally solving the problem of slip during takeoff and landing of the tilt-rotor wing aircraft. Description of the Drawings

[0014] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0015] Figure 1 It is a schematic diagram of the first perspective of the aircraft during cruise flight in the present invention;

[0016] Figure 2 It is a schematic diagram of the first perspective of the aircraft during vertical takeoff and landing in the present invention;

[0017] Figure 3 It is a schematic diagram of the second perspective of the aircraft during cruise flight in the present invention;

[0018] Figure 4Schematic diagram of the three-dimensional structure of the transmission component in the present utility model;

[0019] Figure 5 Schematic diagram of the three-dimensional structure of the resistance increasing and stabilizing mechanism in the present utility model.

[0020] Reference numerals in the attached drawings:

[0021] 1. Fixed-section wing; 2. Tilting-section wing; 3. Nacelle; 4. Fairing; 5. Propeller; 6. First spoiler; 7. Aileron; 8. Transmission rotating shaft; 9. Stable support plate; 10. Second spoiler; 11. First installation groove; 12. Second installation groove. Detailed implementation manners

[0022] This part will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the attached drawings. The role of the attached drawings is to supplement the description in the text part of the specification, enabling people to intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but it should not be construed as a limitation on the protection scope of the present utility model.

[0023] In the description of the present utility model, it should be understood that for the orientation description, such as the orientation or positional relationship indicated by up, down, front, back, left, right, etc. is based on the orientation or positional relationship shown in the attached drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the present utility model.

[0024] In the description of the present utility model, the meaning of several is one or more, the meaning of multiple is two or more, greater than, less than, exceeding, etc. are understood as not including the present number, and above, below, within, etc. are understood as including the present number. If the first and second are described only for the purpose of distinguishing technical features, they should not be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or the sequence relationship of the indicated technical features.

[0025] In the description of the present utility model, unless otherwise clearly defined, words such as setting, installing, connecting, etc. should be understood in a broad sense. Those skilled in the art can reasonably determine the specific meanings of the above words in the present utility model in combination with the specific content of the technical solution.

[0026] Embodiment 1

[0027] See Figures 1 - 5A tilt-rotor wing in the utility model comprises a fixed-section wing 1 and a tilt-section wing 2. A transmission assembly is provided between the fixed-section wing 1 and the tilt-section wing 2. The transmission assembly consists of a transmission shaft 8 and a plurality of equidistantly distributed stable support plates 9. The stable support plates 9 are fixedly connected to the transmission shaft 8. Through the arrangement of the transmission assembly, the fixed-section wing 1 and the tilt-section wing 2 can be better connected and the rotation of the tilt-section wing 2 can be driven.

[0028] Furthermore, the side section of the tilting section wing 2 is provided with ailerons 7, and the ailerons 7 are movably hinged in the connecting grooves provided on the tilting section wing 2. Through the arrangement of the ailerons 7 and the power device, the tilting wing aircraft can be made to hover and take off more stably.

[0029] Furthermore, a drag-increasing stabilization mechanism is provided at the upper and lower ends of the tilt-section wing 2, and the drag-increasing stabilization mechanism is composed of two first spoilers 6 and one second spoiler 10. The two first spoilers 6 are symmetrically hinged and fixed on the lower wing surface of the tilt-section wing 2, and the second spoiler 10 is hinged and fixed on the upper wing surface of the tilt-section wing 2. Through the setting of the drag-increasing stabilization mechanism, the first spoiler 6 and the second spoiler 10 can be deployed to offset the pressure difference on both sides of the tilt-section wing 2 caused by high-speed airflow passing through the asymmetric wing.

[0030] Furthermore, the lower wing surface of the tilting section wing 2 is symmetrically provided with two second mounting grooves 12 for mounting and placing the first spoiler 6, and the upper wing surface of the tilting section wing 2 is provided with a first mounting groove 11 for mounting and placing the second spoiler 10. Through the arrangement of the first mounting groove 11 and the second mounting groove 12, the first spoiler 6 and the second spoiler 10 can be better accommodated;

[0031] In this embodiment, a power device is provided at the front end of the tilting section wing 2, and the power device includes a nacelle 3, a fairing 4 and a propeller 5. A motor is provided in the nacelle 3, and a motor is provided in the nacelle 3. The propeller 5 and the fairing 4 are fixedly connected to the motor shaft of the motor. The fixed connection of the two makes the operation of the power device more stable.

[0032] In this embodiment, the transmission assembly and the resistance-increasing stabilization mechanism are both connected with a hydraulic rotary transmission device for driving the parts to rotate. The hydraulic rotary transmission device of the utility model is a prior art, and those skilled in the art can flexibly select it according to their needs, which is not described in detail here.

[0033] Preferably, the model of the hydraulic rotary transmission device is WKH2.5-3. Through the setting of the hydraulic rotary transmission device, the rotating parts can be better driven to rotate and the parts can withstand a larger reaction force.

[0034] The present utility model also discloses a control method for a tilt wing. The specific control method is as follows: First, connect the valve and pipeline for the hydraulic slewing drive device, then connect the power supply for the electrical components, and subsequently start the tilt wing aircraft. When the aircraft takes off and lands vertically, the transmission assembly drives the transmission rotating shaft 8 to rotate through the connected hydraulic slewing drive device. The stable support plate 9 on the transmission rotating shaft 8 drives the tilt section wing 2 to rotate to be perpendicular to the fixed section wing 1. At this time, the propeller 5 in the power device rotates. The rotation of the propeller 5 causes the propeller slipstream to pass through the upper and lower wing surfaces of the tilt section wing 2 at high speed. When the pressure on both wing surfaces of the tilt section wing 2 is uneven, according to Bernoulli's principle, a horizontal force is generated on the aircraft, reducing the takeoff, landing, and hovering stability of the aircraft. At this time, control the aileron 7 to deflect to reduce the horizontal resistance generated by the propeller slipstream. Then, open the first spoiler 6 and the second spoiler 10 to balance the pressure difference on both sides of the tilt section wing 2 and finally eliminate the above resistance, enabling the aircraft to hover stably during takeoff and landing.

[0035] In the utility model, during the vertical takeoff and landing stage of the tilt wing aircraft, through the deflection cooperation of the tilt section wing and the aileron, it is convenient to change the airflow on the upper wing surface of the tilt section wing, reduce the horizontal force on the tilt section wing in the vertical state, and thus enable the aircraft to be more stable during the hovering takeoff and landing stage. Then, through the deflection cooperation of the first spoiler and the second spoiler, it is convenient to balance the airflow speeds on both sides of the tilt section wing, ensure the pressure difference on both sides of the tilt section wing, and thus enable the situation of unbalanced force on the tilt section wing to be eliminated as much as possible, ultimately solving the problem of slip during takeoff and landing of the tilt wing aircraft.

[0036] On the premise of no conflict, those skilled in the art can freely combine and superimpose the above-mentioned additional technical features.

[0037] The above is only the preferred implementation mode of the present utility model. As long as the technical solutions that achieve the purpose of the present utility model by basically the same means are within the protection scope of the present utility model.

Claims

1. A tilt-rotor wing, characterized in that: The invention comprises a fixed section wing (1) and a tilting section wing (2), wherein a transmission assembly is arranged between the fixed section wing (1) and the tilting section wing (2), and a power device is arranged at the front end of the tilting section wing (2); ailerons (7) are arranged at the side sections of the tilting section wing (2), and the ailerons (7) are movably hinged in a connection groove provided on the tilting section wing (2); A drag-increasing stabilization mechanism is provided on the tilting section wing (2), and the drag-increasing stabilization mechanism consists of two first spoilers (6) and a second spoiler (10), the two first spoilers (6) are symmetrically hinged and fixed on the lower bottom surface of the tilting section wing (2), and the second spoiler (10) is hinged and fixed on the upper wing surface of the tilting section wing (2).

2. A tilt-rotor wing according to claim 1, characterized in that: The lower bottom surface of the tilting section wing (2) is symmetrically provided with two second installation grooves (12) for installing and placing the first spoiler (6), and the upper wing surface of the tilting section wing (2) is provided with a first installation groove (11) for installing and placing the second spoiler (10).

3. A tilt-rotor wing according to claim 1, characterized in that: The power device is composed of a nacelle (3), a fairing (4) and a propeller (5). A motor is arranged in the nacelle (3), and the propeller (5) and the fairing (4) are fixedly connected to the motor shaft of the motor.

4. A tilt-rotor wing according to claim 1, characterized in that: The transmission assembly consists of a transmission shaft (8) and a plurality of equidistantly distributed stable support plates (9), wherein the stable support plates (9) are fixedly connected to the transmission shaft (8).

5. The tilt-rotor wing according to claim 1, characterized in that: The transmission assembly and the resistance-increasing stabilizing mechanism are both connected with a hydraulic rotary transmission device for driving the parts to rotate.

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