CN212243812U

CN212243812U - Tilting duck type layout aircraft

Info

Publication number: CN212243812U
Application number: CN202020436482.6U
Authority: CN
Inventors: 华杰; 王强; 王朝阳
Original assignee: Nanjing Zhifei Aviation Technology Co ltd
Current assignee: Nanjing Zhifei Aviation Technology Co ltd
Priority date: 2020-03-30
Filing date: 2020-03-30
Publication date: 2020-12-29
Anticipated expiration: 2030-03-30

Abstract

The utility model discloses a duck formula overall arrangement aircraft verts, including fuselage, the main wing, the outer wing that verts, the aileron, the elevator, first driving system, second driving system, the duck wing. The main wing is arranged at the rear half part of the fuselage, and the two tilting outer wings are symmetrically arranged at two sides of the main wing and can rotate for 0 to 90 degrees along the axial direction of the main wing; the canard wing is arranged at the front half part of the fuselage and can rotate for 0 to 90 degrees around the rotating shaft; two first power systems are symmetrically installed on the two tilting outer wings, and the distance from the central axis of the first power system to the wing tips of the tilting outer wings is smaller than the radius of the propeller. The utility model discloses the control mode of four rotors is adopted to the vertical phase, and control is simple, increases the auxiliary control of aileron and elevator simultaneously, and it is vertical only to vert the outer wing and duck wing moreover, reduces the windward area, solves the four rotor aircraft stability problems that vert. The outer wing and the canard wing always solve the problem of the interference of the blades on the airflow of the wing under the slipstream of the propeller.

Description

Tilting duck type layout aircraft

Technical Field

The utility model relates to a VTOL aircraft, especially a duck formula overall arrangement aircraft verts.

Background

The tilting aircraft can vertically take off and land and can fly at high speed. The tilting aircraft can be divided into two categories of tilting rotors and tilting wings, a power system is arranged at a wing tip in the market of the tilting rotors, only the tilting power system is adopted, the mechanism is complex, and the rotors have serious aerodynamic interference on the wings; the tilting wing tilts the whole wing, and has large windward side, poor stability and large tilting moment in the vertical stage. The tilting aircraft is basically a two-axis aircraft, and is difficult to control vertically and is not stable.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects of the prior art, the utility model provides a VTOL aircraft.

The utility model discloses a following technical scheme can realize.

The utility model provides a duck formula overall arrangement aircraft verts includes fuselage 1, main wing 2, verts outer wing 3, aileron 4, elevator 5, first driving system 6, second driving system 7, duck wing 8.

The main wing 2 is arranged at the rear half part of the machine body 1, and the duck wing 8 is arranged at the front half part of the machine body; the duck wing 8 can rotate around the rotating shaft 11 by 0 to 90 degrees; preferably, the main wing 2 and the canard are both rectangular wings.

Preferably, the tilting outer wing 3 is a right trapezoid, the long side is a wing root, the short side is a wing tip, and the wing root is consistent with the wing tip of the main wing 2.

The two tilting outer wings 3 are symmetrically arranged on two sides of the main wing 2 and can rotate for 0 to 90 degrees along the axial direction of the main wing; the power system 6 comprises a motor 9 and a propeller 10, and the propeller 10 is arranged on the motor 9; and two power systems 6 are symmetrically arranged on the two tilting outer wings 3.

The distance from the central axis of the first power system 6 to the wingtip of the tilting outer wing 3 is smaller than the radius of the propeller 10; the length of the tilting outer wing 3 is greater than the sum of the radius of the propeller 10 and the distance from the central axis of the power system 6 to the wing tip of the tilting outer wing 3; preferably, the length of the tilted outer wing 3 is 0.8 times the diameter of the propeller 10; the central axis of the power system 7 reaches the wing root distance of the tilting outer wing 3 is the length of the tilting outer wing 3.

The ailerons 4 are arranged at the rear part of the tilting outer wing 3, the elevators 5 are arranged at the rear part of the canard wing 8, and both of the ailerons and the elevators participate in controlling the attitude of the aircraft in the whole flight process; preferably, the aileron width is 25% of the chord length of the tilt outer wing 3, and the length is equal to the length of the tilt outer wing 3; preferably, the width of the elevator rudder is 25% of the chord length of the duck wing, and the length of the elevator rudder is equal to the spread length of the duck wing 8.

The second power system 7 comprises a motor 12 and a propeller 13, and the propeller 13 is arranged on the motor 12; the two second power systems 7 are symmetrically arranged on the duck wing 8; the distance from the central axis of the second power system 7 to the wing tip of the duck wing 8 is smaller than the radius of the propeller 13; preferably, the distance from the central axis of the second power system 7 to the tip of the duck wing 8 is 0.

In the vertical take-off and landing stage, a four-rotor control mode is adopted, an elevator 5 and an aileron 4 are used for auxiliary control, the two tilting outer wings 3 and the canard wings 8 are vertical, and the two first power systems 6 and the two second power systems 7 jointly provide vertical lifting force; in the transition stage, the two tilting outer wings 3 and the canard wing 8 rotate anticlockwise; and in the cruising stage, a fixed wing control mode is adopted, the inclined outer wing 3 is integrated with the main wing 2, the canard wing 8 is horizontal, and the two first power systems 6 and the two second power systems 7 jointly provide the front flying pulling force.

The utility model has the advantages that: the control mode of four rotors is adopted in the vertical stage, the control is simple, the auxiliary control of the ailerons and the elevator is added, and the vertical stability is enhanced. Perpendicular stage is only verted outer wing and the duck wing is vertical, and the windward area that reduces further increases stability. The first power system tilts along with the tilting outer wing, aerodynamic interference is not generated on the main wing, the outer wing always slides down on the propeller, lift force can be generated under the condition that no incoming flow exists, and stall is not easy to occur. The second power system and the canard wing tilt together, and the stability of the airflow of the canard wing is ensured. The ailerons and the elevator are always kept under the slip of the propeller, so that the steering effect is improved, and the steering effect can be generated in the vertical stage to participate in the control of the vertical stage.

Drawings

Fig. 1 is a schematic diagram of a horizontal flight phase of the tilt duck type aircraft of the present invention;

fig. 2 is a schematic view of an installation structure of a tilting outer wing of the tilting duck type aircraft of the present invention;

fig. 3 is a schematic view of a duck wing installation structure of the tilt duck type aircraft of the present invention;

fig. 4 is a schematic diagram of a transition stage of a wing of the aircraft with a tilted duck layout according to the present invention;

fig. 5 is a vertical stage schematic diagram of the tilting duck type aircraft.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

It should be noted that, in this document, the term "comprises/comprising" or any other variation thereof is intended to cover a non-exclusive inclusion, so that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus. The terms "rear half," "horizontal," "front half," "counterclockwise," and the like are used for the purpose of describing the present invention only and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the present invention.

As shown in fig. 1, the aircraft with the tilting canard layout comprises a fuselage 1, a main wing 2, a tilting outer wing 3, an aileron 4, an elevator 5, a first power system 6, a second power system 7 and canard wings 8.

The main wing 2 is arranged at the rear half part of the fuselage 1, further, the main wing 2 is a rectangular wing, the wing profile is selected from clark-y, and preferably, the chord ratio of the main wing 2 is 6.92.

Further, the outer wing 3 that verts is right trapezoid, and right angle ladder height is the length of the outer wing 3 that verts, and the right angle limit is the leading edge, and the long limit is that the wing tip of wing root and main wing 2 is unanimous, and the minor face is wing tip chord length does, and the wing section is selected unanimously with main wing 2, and is further, and the root tip ratio is 1.25.

The canard wing 8 is arranged on two sides of the front half part of the fuselage through a rotating shaft, and the rotating shaft 11 is connected with a tilting mechanism 14, so that the canard wing 8 can rotate for 0-90 degrees around the rotating shaft 11; further, the rotating shaft 11 is a carbon tube, the canard wing 8 is a rectangular wing, the airfoil is NACA0018, and preferably, the aspect ratio of the canard wing 8 is 5.63.

The ailerons 4 are arranged at the rear part of the tilting outer wing 3, the elevators 5 are arranged at the rear part of the canard wing 8, and both the ailerons and the elevators participate in controlling the attitude of the airplane in the whole flight process; preferably, the aileron 4 is 25% wide of the chord length of the tilt outer wing 3 and has a length equal to 0.8 times the length of the tilt outer wing 3; preferably, the width of the elevator 5 is 25% of the chord length of the canard 8, and the length is equal to 0.8 times of the spread length of the canard 8.

As shown in fig. 1 and 2, the two tilting outer wings 3 are symmetrically installed on both sides of the main wing 2 through the carbon tube 15, and the carbon tube 15 is connected to the tilting mechanism 16 so that it can rotate 0 to 90 degrees around the axis of the carbon tube 14; the first power system 6 comprises a motor 9 and a propeller 10, wherein the propeller 9 is arranged on the motor 8, and a fairing 17 is added outside the power system for reducing resistance; the two power systems 6 are symmetrically arranged on the two tilting outer wings 3; the length of the tilting outer wing 3 is greater than the sum of the radius of the propeller 10 and the distance from the central axis of the power system 6 to the wing tip of the tilting outer wing 3; preferably, the length of the tilted outer wing 3 is 0.8 times the diameter of said propeller 9; the distance from the central axis of the power system 7 to the root of the tilting outer wing 3 is the length of the tilting outer wing 3.

As shown in fig. 1 and 3, the second power system 7 comprises a motor 12 and a propeller 13, wherein the propeller 13 is arranged on the motor 12, and a fairing 18 is added outside the power system for reducing resistance; the two second power systems 7 are symmetrically arranged on the duck wing 8; the distance from the central axis of the second power system 7 to the wing tip of the duck wing 8 is smaller than the radius of the propeller 13; preferably, the distance from the central axis of the second power system 7 to the tip of the duck wing 8 is 0.

As shown in fig. 1, 4 and 5, in the vertical take-off and landing stage, a four-rotor control mode is adopted, an elevator 5 and an aileron 4 are used for auxiliary control, two tilting outer wings 3 and two canard wings 8 are vertical, and two first power systems 6 and two second power systems 7 jointly provide vertical lifting force; in the transition stage, the two tilting outer wings 3 and the canard wing 8 rotate anticlockwise; and in the cruising stage, a fixed wing control mode is adopted, the inclined outer wing 3 is integrated with the main wing 2, the canard wing 8 is horizontal, and the two first power systems 6 and the two second power systems 7 jointly provide the front flying pulling force.

Claims

1. An aircraft with a tilting canard layout is characterized by comprising an aircraft body (1), a main wing (2), a tilting outer wing (3), an aileron (4), an elevator (5), a first power system (6), a second power system (7) and canard wings (8); the main wing (2) is arranged at the rear half part of the machine body (1); the two tilting outer wings (3) are symmetrically arranged on two sides of the main wing (2) and can rotate for 0-90 degrees along the axial direction of the main wing; the first power system (6) comprises a motor (9) and a propeller (10), and the propeller (10) is installed on the motor (9); the two first power systems (6) are symmetrically arranged on the two tilting outer wings (3); the distance from the central axis of the first power system (6) to the wingtip of the tilting outer wing (3) is smaller than the radius of the propeller (10); the length of the tilting outer wing (3) is greater than the sum of the distances from the radius of the propeller (10) and the central axis of the power system (6) to the wing tip of the tilting outer wing (3).

2. Aircraft according to claim 1, characterised in that said canard wing (8) is rotatable, in the front half of the fuselage, by 0 to 90 degrees about a rotation axis (11).

3. The aircraft according to claim 1, characterized in that said ailerons (4) are in the rear part of the tilt outer wing and said elevators (5) are in the rear part of the canard wing; the ailerons (4) and the elevators (5) participate in controlling the attitude of the aircraft during the whole flight.

4. The aircraft of claim 1, wherein the second power system (7) comprises an electric motor (12) and a propeller (13), the propeller (13) being mounted on the electric motor (12); the two second power systems (7) are symmetrically arranged on the duck wing (8); the distance from the central axis of the second power system (7) to the wing tip of the duck wing (8) is smaller than the radius of the propeller (13).

5. The aircraft with the tilting duck type layout according to claim 1, characterized in that in the vertical take-off and landing stage, a four-rotor control mode is adopted, an elevator (5) and an aileron (4) are used for auxiliary control, two tilting outer wings (3) and two duck wings (8) are vertical, and two first power systems (6) and two second power systems (7) jointly provide vertical lifting force; in the transition stage, the two tilting outer wings (3) and the canard wing (8) rotate anticlockwise; and in the cruising stage, a fixed wing control mode is adopted, the inclined outer wing (3) is integrated with the main wing (2) horizontally, the canard wing (8) is horizontal, and two first power systems (6) and two second power systems (7) jointly provide the pulling force for flying ahead.