CN218022154U

CN218022154U - Tilt wing aircraft with novel control structure

Info

Publication number: CN218022154U
Application number: CN202222020836.0U
Authority: CN
Inventors: 贾记柯; 何国毅; 黄卿晋; 于沨; 刘荣谦
Original assignee: Nanchang Hangkong University
Current assignee: Nanchang Hangkong University
Priority date: 2022-08-02
Filing date: 2022-08-02
Publication date: 2022-12-13
Anticipated expiration: 2032-08-02

Abstract

The utility model discloses a wing aircraft verts with novel control structure, which comprises a fuselage, the fuselage both sides all are provided with the wing subassembly, the wing subassembly includes canned paragraph wing and canned paragraph wing, the canned paragraph wing is located the outside of canned paragraph wing, the place ahead of canned paragraph wing is provided with driving system, be provided with the control mechanism that verts of control canned paragraph wing in the cabin of fuselage, the control mechanism that verts includes fixing support and the axle that verts, the last steering wheel that is provided with of fixing support, be provided with steering wheel horn arm on the steering wheel, be provided with the steering wheel dish on the steering wheel horn arm, install the driving gear on the steering wheel dish, it is provided with driven gear to vert epaxially, driven gear and driving gear meshing, the utility model discloses an inside control mechanism that verts of cabin carries out vector differential control with canned paragraph wing both sides's wing and driving system to have better flight performance, it is good to reach the anti-wind performance, control is simple and the good purpose of mobility.

Description

Tilt wing aircraft with novel control structure

Technical Field

The utility model relates to an aircraft technical field especially relates to a wing aircraft verts with novel control structure.

Background

The vertical take-off and landing technology was originally proposed in the second war period, and during the past war, the airplane was greatly limited in the war due to the way of running take-off, and people also recognized the shortage of running take-off. In the cold war period, the vertical take-off and landing technology is rapidly developed, and under the condition that the nuclear war is extremely likely to occur at that time, people worry about that the war damages an airport, so that the phenomenon that a conventional airplane cannot take off is caused, and the technology combining a fixed-wing aircraft and the vertical take-off and landing is created. The vertical take-off and landing aircraft reduces the dependence on a runway, can take off and land in a smaller flat field, is convenient for scattered distribution, transfer and concealment of the aircraft, can hit flexibly, reduces the threat and greatly improves the survival rate. Because the demand on the flying field is not high, the construction cost of an airport can be reduced, and the flying field can be lifted and landed under the severer climate environment, thereby reducing the use cost. The development of the vertical take-off and landing technology continues to the present, and the technology is intensively studied in all countries.

Under the high-speed development of military use, the rapid development of civil aircrafts is also driven, and the common aircrafts at present are mainly divided into a multi-rotor type and a fixed-wing type. The multi-rotor aircraft has higher flexibility, and can finish vertical takeoff, landing and hovering only by using a smaller and flat ground. At least, the power arrangement of more than two rotors makes it possess the redundancy design, and security and stability are also great promotion, nevertheless because of its structure and energy problem, can't accomplish the flight of long distance long voyage heavy load. The common fixed wing aircraft is limited to take-off and landing, and often cannot be used in practical application, or can be normally used only when taking-off and landing are achieved under certain conditions. The advantages of the two are combined, so that another vertical take-off and landing aircraft is produced, the aircraft has relatively long time and large load, and simultaneously has better energy economy and flexibility of flight control, the safety of the aircraft is greatly improved, and the aircraft has the take-off and landing capability of complex terrains.

The vertical take-off and landing aircraft commonly used at present can be roughly divided into: aft-seated, hybrid (compound), tilt-wing. Compared with other types of aircrafts, the tilting wing type aircraft has the advantages of better pneumatic layout, good control performance, high efficiency, better load capacity and the like, and can be widely applied to various fields, such as shipboard take-off and landing, electric power line patrol, exploration surveying and mapping, film and television shooting, fire fighting and disaster relief, material transportation and the like.

At present, the tilt wing type aircraft has a tilt integral wing type and a tilt partial wing type, a power system is fixed on wings, and no matter which aircraft, the wings and the power system tilt together, and the flight from a multi-rotor mode to a fixed wing mode is completed. This kind of control structure mode of verting wing aircraft relies on driving system on the wing to provide the pulling force when taking off perpendicularly, cooperates with the flaperon below the wing to accomplish attitude control. The structural control mode has poor wind resistance, in vertical take-off, wings are vertical to the airplane body, the windward area is increased, the wing is easily influenced by inflow airflow, the generated downwash airflow acts on the flaperon right below by utilizing the rotation of a propeller of a power system, and the deflection of the flaperon is utilized, so that the attitude control is realized. The aircraft with the control structure has poor wind resistance, is easily influenced by airflow, has higher difficulty in the control mode, is usually in accident in recent years as large as the osprey V22, and is almost not available in the control mode of the existing finished unmanned aircraft.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve the technical problem who exists among the prior art, provide a wing aircraft verts with novel control structure.

In order to achieve the above purpose, the utility model provides a technical scheme is: the utility model provides a wing aircraft verts with novel control structure, includes the fuselage, the fuselage both sides all are provided with the wing subassembly, the wing subassembly includes canned paragraph wing and movable section wing, the movable section wing is located the outside of canned paragraph wing, the place ahead of movable section wing is provided with driving system, be provided with control in the cabin of fuselage the control mechanism that verts of movable section wing, the control mechanism that verts includes fixing support and the axle that verts, the last steering wheel that is provided with of fixing support, be provided with steering wheel horn on the steering wheel, be provided with the steering wheel horn on the steering wheel horn, be provided with the steering wheel dish on the steering wheel horn, install the driving gear on the steering wheel dish, it is provided with driven gear to vert epaxially, driven gear with driving gear engagement.

Preferably, the tilting shaft is further provided with a U-shaped groove, and the steering engine disc, the driving gear and the driven gear are all located in the U-shaped groove.

Preferably, an undercarriage is arranged below the machine body, a V-shaped tail is arranged at the tail of the machine body, and a control surface is arranged on the V-shaped tail.

Preferably, the rear part of the fixed section wing is provided with a flap, and the lower part of the movable section wing is provided with an aileron.

Preferably, the power system comprises a motor arranged on the movable section wing, and a propeller is arranged on the motor.

The utility model discloses beneficial effect:

the utility model discloses an inside tilting control mechanism of cabin carries out vector differential control with the active section wing and the driving system of wing both sides, can be at VTOL, hover in the air and high-speed steady flat between two kinds of modes of flying interconversion to have better flight performance, it is good to reach the anti-wind performance, controls the purpose simple and mobility is good.

Drawings

The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.

FIG. 1 is a schematic structural view of the vertical take-off and landing device of the present invention;

FIG. 2 is a schematic structural view of the cruise device of the present invention;

fig. 3 is a schematic structural view of the tilting mechanism of the present invention.

The attached drawings are marked as follows:

the aircraft comprises a fuselage 1, a fixed section wing 3, a flap 4, a movable section wing 5, a motor 6, a propeller 7, an aileron 8, a V-shaped tail 9, a control surface 10, an undercarriage 11, a fixed support 12, a steering engine 13, a steering engine disk 14, a driving gear 15, a driven gear 16, a tilting shaft 17, a U-shaped groove 18 and a steering engine arm.

Detailed Description

This section will describe in detail the embodiments of the present invention, the preferred embodiments of which are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can visually and vividly understand each technical feature and the whole technical solution of the present invention, but it cannot be understood as a limitation to the scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of meanings are one or more, a plurality of meanings are two or more, and the terms greater than, smaller than, exceeding, etc. are understood as excluding the number, and the terms greater than, lower than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the terms such as setting, installing, connecting, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meaning of the terms in the present invention by combining the specific contents of the technical solution.

Referring to fig. 1-3, the utility model discloses a preferred embodiment, a wing aircraft verts with novel control structure, including fuselage 1, fuselage 1 both sides all are provided with the wing subassembly, the wing subassembly includes fixed section wing 2 and movable section wing 4, movable section wing 4 is located the outside of fixed section wing 2, movable section wing 4 top is provided with driving system, be provided with control in the cabin of fuselage 1 the control mechanism that verts of movable section wing 4, it is two to vert control mechanism, is used for controlling movable section wing 4 of fuselage 1 both sides respectively, it includes fixed support 11 and vert axle 16 to vert control mechanism, and vert axle 16 is used for the support of fixed section wing 2, is used for the helm of movable section wing 4 again, be provided with 12 on the fixed support 11, fixed support 11 is used for the position of fixed steering wheel 12, be provided with steering wheel arm 18 on 12, be provided with steering wheel dish 13 on the helm axle 18, install driving gear 14 on the helm dish 13, be provided with driven gear 15 on the helm axle 16, driven gear 15 with the driving gear meshes with the driving gear 14 the same with the steering wheel 15 specifications.

As a preferred embodiment of the present invention, it may also have the following additional technical features:

in this embodiment, still be provided with U-shaped recess 17 on the axle 16 that verts, rudder machine dish 13, driving gear 14 and driven gear 15 all are located in U-shaped recess 17 for fix and fix rudder machine dish 13, driving gear 14 and driven gear 15.

In this embodiment, the undercarriage 10 is arranged below the fuselage 1, the tail of the fuselage 1 is provided with the V-shaped tail 8, and the V-shaped tail 8 is provided with the control surface 9, so that the control surface 9 can be used as an elevator and a rudder.

In the embodiment, a flap 3 is arranged at the rear part of the fixed section wing 2, and an aileron 7 is arranged at the lower part of the movable section wing 4.

In this embodiment, the power system includes a motor 5 disposed on the movable section wing 4, and a propeller 6 is disposed on the motor 5.

If the movable section wing 4 and the fixed section wing 2 are specified to be in the same horizontal position, namely in a fixed wing mode, and the tilting angle is 0 degrees, the tilting angle of the tilting control mechanism can reach 0 degrees to 125 degrees.

When the movable section wing 4 and the fixed section wing 2 are in a relative vertical state, and the vertical angle is 90 degrees as a center, the movable section wing 4 can tilt forwards within a range of 45 degrees or tilt backwards within a range of 35 degrees, and the mode is a vertical take-off and landing mode.

The utility model discloses under the VTOL mode, movable section wing 4 and driving system through verting control mechanism, can carry out vector differential control, and movable section wing 4 and driving system are through the different angle that verts to control flight gesture.

Specifically, the two movable section wings 4 tilt forwards or backwards together with the power system, so as to control the pitch attitude of the aircraft; when the movable section wings 4 on the two sides and the power system tilt forwards on one side and tilt backwards on the other side, the yaw attitude of the aircraft is controlled; the movable section wings 4 and the power system on the two sides mainly depend on the power system, and the rolling attitude of the aircraft is controlled through the rotating speed difference of the motor 5; thereby accomplish through this kind of vector differential control the utility model discloses, attitude control under the vertical take-off and landing mode, and hover etc. in the air.

Under the transition of verting, the flap 3 combined action of movable section wing 4 and fixed segment wing 2 gets to vert more fast and flat of transition state, through movable section wing 4 and driving system, verts to 0 forward, can be in same horizontal position with fixed segment wing 2 movable section wing 4 to accomplish and vert excessively.

Under the fixed wing mode, a power system and the wings 2 jointly provide lift force, namely the movable section wings 4 and the fixed section wings 2 jointly act, and the tail wings of the wing flaps 3, the ailerons 7 and the V-shaped tails 8 all take off and control, so that the control of various postures of the aircraft under the fixed wing mode is completed.

The utility model discloses a with the wing subassembly and the driving system that can vert in both sides, carry out vector differential control, through the test, the utility model discloses the anti-wind performance is good, and flight control is simple, and is quick more and the conversion is flat when converting into the fixed wing mode, and convenient the use of coming into use with low costs moreover.

The above additional technical features can be freely combined and used in addition by those skilled in the art without conflict.

The above is only the preferred embodiment of the present invention, as long as the technical solution of the purpose of the present invention is realized by the substantially same means, all belong to the protection scope of the present invention.

Claims

1. A tilting wing aircraft with a novel control structure is characterized in that: including fuselage (1), fuselage (1) both sides all are provided with the wing subassembly, the wing subassembly includes canned paragraph wing (2) and movable section wing (4), movable section wing (4) are located the outside of canned paragraph wing (2), the place ahead of movable section wing (4) is provided with driving system, be provided with control in the cabin of fuselage (1) the tilting control mechanism of movable section wing (4), tilting control mechanism includes fixing support (11) and tilting shaft (16), be provided with steering wheel (12) on fixing support (11), be provided with steering wheel arm (18) on steering wheel (12), be provided with steering wheel dish (13) on steering wheel arm (18), install driving gear (14) on steering wheel dish (13), be provided with driven gear (15) on tilting shaft (16), driven gear (15) with driving gear (14) meshing.

2. The tilt wing aircraft with the novel control structure of claim 1, wherein: still be provided with U-shaped recess (17) on tilting shaft (16), steering engine dish (13), driving gear (14) and driven gear (15) all are located in U-shaped recess (17).

3. The tiltrotor aircraft with the novel control structure of claim 1, wherein: an undercarriage (10) is arranged below the machine body (1), a V-shaped tail (8) is arranged at the tail of the machine body (1), and a control surface (9) is arranged on the V-shaped tail.

4. The tilt wing aircraft with the novel control structure of claim 1, wherein: the rear part of the fixed section wing (2) is provided with a flap (3), and the lower part of the movable section wing (4) is provided with an aileron (7).

5. The tiltrotor aircraft with the novel control structure of claim 1, wherein: the power system comprises a motor (5) arranged on the movable section wing (4), and a propeller (6) is arranged on the motor (5).