CN217416106U - Vertical take-off and landing aircraft with partially-tilted propellers - Google Patents

Abstract

The utility model relates to an urban air traffic field, in particular to vertical take-off and landing aircraft of screw partially verts. The vertical take-off and landing aircraft with the partially tilted propellers comprises wings, an empennage, a first propeller arranged on the front side of the wings, a second propeller arranged on the rear side of the wings and a third propeller arranged on the empennage; when first screw, second screw and third screw were all up, the height of the plane of rotation of first screw and second screw was inequality, and the plane of rotation of second screw and the plane of rotation of third screw highly inequality. The third propeller is arranged at the position of the tail wing and is mainly used for improving the pitching control capability of the whole machine. The height of the rotating surface of the first propeller and the height of the rotating surface of the second propeller are different, and the height of the rotating surface of the second propeller and the height of the rotating surface of the third propeller are different, so that the first propeller, the second propeller and the third propeller can be prevented from being exploded to hurt people or main parts of an airplane.

Description

Vertical take-off and landing aircraft with partially-tilted propellers

Technical Field

The utility model relates to an urban air traffic field, in particular to vertical take-off and landing aircraft of screw partially verts.

Background

In order to make up for the short board of the existing ground traffic, the urban air traffic system is popularized. An ideal aircraft for urban air traffic has the characteristics of safety, high efficiency, environmental protection, low noise, low cost, capability of taking off and landing vertically and the like. The vertical take-off and landing aircraft with the partially tilted propellers, as an aircraft suitable for urban air traffic, has the capabilities of high-efficiency hovering and low-speed flying similar to the traditional helicopter and high-efficiency cruising and flying similar to a fixed-wing aircraft. However, the related art vertical take-off and landing aircraft with partially tilted propellers has a problem of poor pitch handling stability.

SUMMERY OF THE UTILITY MODEL

In view of this, the present invention is directed to a vertical take-off and landing aircraft with partially tilted propellers, so as to solve or partially solve the problem that the existing aircraft has poor pitching operation stability.

In order to achieve the above purpose, the technical scheme of the utility model is realized as follows:

a vertical take-off and landing aircraft with partially tilted propellers comprises wings, an empennage, a first propeller arranged on the front side of the wings, a second propeller arranged on the rear side of the wings, and a third propeller arranged on the empennage; when the first propeller, the second propeller and the third propeller are all upward, the height of the rotating surface of the first propeller is different from that of the rotating surface of the second propeller, and the height of the rotating surface of the second propeller is different from that of the rotating surface of the third propeller.

Further, the height of the rotating surface of the first propeller is greater than that of the rotating surface of the second propeller, and the height of the rotating surface of the first propeller is less than that of the rotating surface of the third propeller.

Further, the VTOL aircraft of partial screw that verts still includes the fuselage, and is a plurality of first screw equipartition arrange in the both sides of fuselage, orientation the projection is done to the fore-and-aft direction of fuselage, is located the fuselage is with adjacent two of one side the projection of first screw does not coincide.

Further, when the first propeller faces upwards, the first propeller deflects towards the direction far away from the machine body.

Further, when the first propeller faces upwards, an included angle alpha is formed between the axis of the first propeller and the height direction, and the included angle alpha is more than 45 degrees and more than 0 degree.

Further, the included angle alpha satisfies 15 degrees > alpha > 10 degrees.

Furthermore, the second screw includes two, arranges respectively in the both sides of fuselage, the second screw with the two in the outermost side first screw one-to-one sets up.

Further, the vertical take-off and landing aircraft with the partially tilted propellers further comprises a tilting mechanism, the first propeller is connected with the wing through the tilting mechanism, and the tilting mechanism enables the first propeller to be converted between the front side and the upper side.

Further, the first propeller has four; and/or the third propellers are provided with two third propellers which are respectively arranged on two sides of the tail wing.

Further, the first propeller comprises at least three blades; and/or, the second propeller comprises a double-bladed propeller or a stacked propeller; and/or, the third propeller comprises a double-bladed propeller or a stacked propeller.

Compared with the prior art, the VTOL aircraft of screw that verts of part have following advantage:

the vertical take-off and landing aircraft with the partially tilted propellers, provided by the third propeller, can improve the pitching operation stability of the vertical take-off and landing aircraft with the partially tilted propellers; when first screw, second screw and third screw were all up, because the high inequality of the plane of rotation of first screw and the plane of rotation of second screw, the plane of rotation of second screw and the plane of rotation of third screw are inequality, can prevent that first screw, second screw and third screw blasting from bringing harm, for example, the blasting appears and hurts people or damages the aircraft major component.

The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented in accordance with the contents of the description, and in order to make the above and other objects, features, and advantages of the present invention more clearly understood, the following description will particularly refer to specific embodiments of the present invention.

Drawings

The accompanying drawings, which form a part hereof, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without undue limitation. In the drawings:

fig. 1 is a schematic structural diagram of a vertical take-off and landing aircraft with partially tilted propellers according to an embodiment of the invention in a first use state;

fig. 2 is a schematic structural diagram of a vertical take-off and landing aircraft with partially tilted propellers according to an embodiment of the invention in a second use state;

FIG. 3 is a schematic top plan view of the partially tilted propeller VTOL aerial vehicle of FIG. 1;

FIG. 4 is a schematic top view of the partially tilted propeller VTOL aerial vehicle of FIG. 2;

FIG. 5 is a schematic front view of the partially tilted propeller VTOL aerial vehicle of FIG. 2;

fig. 6 is a schematic diagram of the arrangement position of the first propeller in the left side view of the partially tilted propeller vtol aircraft shown in fig. 2.

Description of reference numerals:

1-an airfoil; 2-a fuselage; 3-tail fin; 4-a first propeller; 41-a first paddle; 5-a second propeller; 51-a second paddle; 6-a third propeller; 61-a third paddle; 7-tilting mechanism.

Detailed Description

It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.

In addition, the front and the back mentioned in the embodiments of the present invention refer to the front and the back of the course of the vertical take-off and landing aircraft with partially tilted propellers.

The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

Referring to fig. 1 to 6, the present embodiment provides a partially tilted propeller vertical take-off and landing aircraft, including a wing 1 and a tail fin 3, and a first propeller 4 disposed on a front side of the wing 1, a second propeller 5 disposed on a rear side of the wing 1, and a third propeller 6 disposed on the tail fin 3; when first screw propeller 4, second screw propeller 5 and third screw propeller 6 were all up, the height of the plane of rotation of first screw propeller 4 and the plane of rotation of second screw propeller 5 was inequality, and the height of the plane of rotation of second screw propeller 5 and the plane of rotation of third screw propeller 6 was inequality.

In particular, the wing 1 is one of the important components of a partially tilted propeller vtol aircraft, mounted on the fuselage 2 of the partially tilted propeller vtol aircraft. The main function of the wing 1 is to generate lift, which together with the empennage 3 of a partially tilt-rotor vtol aircraft results in good stability and maneuverability.

The empennage 3 is a device which is arranged at the tail part of a vertical take-off and landing aircraft with partial tilt propellers and can enhance the stability of flight, the empennage 3 plays a role in stabilizing the course and the longitudinal direction, and the empennage 3 is one of important components of a flight control system. Referring to fig. 1 and 2, the vtol aircraft with partial tilt propellers in the embodiment of the present invention is a V-shaped empennage, but it should be understood that, in practical applications, the empennage 3 may also be a conventional empennage, a T-shaped empennage, a cross-shaped empennage, etc., which is not limited by the embodiment of the present invention.

The propeller is a device which rotates in the air by means of blades and converts the rotating power of an engine into propelling force, and can be a propeller which is connected with a propeller hub by two or more blades, wherein the backward surface of each blade is a helicoid or a propeller similar to the helicoid. In the vertical take-off and landing aircraft with the partially tilted propellers of the embodiment of the application, the propellers comprise a first propeller 4, a second propeller 5 and a third propeller 6. The front side of the wing 1 is connected with a first propeller 4, the rear side of the wing 1 is connected with a second propeller 5, and the tail wing 3 is connected with a third propeller 6. The front side of the wing 1 is the side of the wing 1 facing the front side of the vertical take-off and landing aircraft with the partial tilt propellers, and the rear side of the wing 1 is the side of the wing 1 facing the rear side of the vertical take-off and landing aircraft with the partial tilt propellers, that is, as shown in fig. 1 and fig. 2, the front side of the wing 1 is the left side of the wing 1, and the rear side of the wing 1 is the right side of the wing 1.

In the vertical take-off and landing aircraft with the partially tilted propellers, the third propeller 6 is arranged, so that the pitching operation stability of the vertical take-off and landing aircraft with the partially tilted propellers can be improved; and referring to fig. 5, when the first propeller 4, the second propeller 5 and the third propeller 6 are all upward, because the height of the rotating surface of the first propeller 4 is different from that of the rotating surface of the second propeller 5, and the height of the rotating surface of the second propeller 5 is different from that of the rotating surface of the third propeller 6, it is possible to prevent the first propeller 4, the second propeller 5 and the third propeller 6 from being exploded to cause damage, for example, explosion to hurt people or main parts of an airplane.

The first propeller 4, the second propeller 5, and the third propeller 6 are all facing upward, which means that the rotating surfaces of the first propeller 4, the second propeller 5, and the third propeller 6 are all facing upward, i.e., refer to the state of the first propeller 4, the second propeller 5, and the third propeller 6 in fig. 5.

The height of the rotation surface of the first propeller 4, the height of the rotation surface of the second propeller 5, and the height of the rotation surface of the third propeller 6 refer to the height in the height direction of the partially tilted propeller vtol aircraft, and specifically refer to the Z-axis direction in fig. 5 and 6.

Referring to fig. 5, in an embodiment, the height of the plane of rotation of the first propeller 4 is greater than the height of the plane of rotation of the second propeller 5, and the height of the plane of rotation of the first propeller 4 is less than the height of the plane of rotation of the third propeller 6.

The vertical take-off and landing aircraft with the partially tilted propellers has the advantages that the rotating surfaces of the propellers of the vertical take-off and landing aircraft with the partially tilted propellers are sequentially increased in height, the rotating surfaces of the second propeller 5, the first propeller 4 and the third propeller 6 are different in height, and the first propeller 4, the second propeller 5 and the third propeller 6 of the vertical take-off and landing aircraft with the partially tilted propellers can be effectively prevented from being exploded to hurt people or main parts of the aircraft.

Referring to fig. 1 to 4, in an embodiment, the vertical take-off and landing aircraft with partially tilted propellers further includes a fuselage 2, a plurality of first propellers 4 are uniformly distributed on two sides of the fuselage 2, and are projected in the front-rear direction of the fuselage 2, and the projections of two adjacent first propellers 4 located on the same side of the fuselage 2 are not overlapped.

The fuselage 2 is a part of a partially tiltrotor VTOL aircraft for loading people, cargo, weapons, and onboard equipment. The fuselage 2 connects the wings 1, the empennage 3, the landing gear and other parts into a whole. The fore-aft direction of the fuselage 2 is the fore-aft direction of the partially tilt-rotor vtol aircraft, i.e., the X-axis direction shown in fig. 3 to 5.

Because the projection is done towards the fore-and-aft direction of fuselage 2, the projection that lies in fuselage 2 and two adjacent first screw 4 with one side does not coincide, then lie in fuselage 2 and two adjacent first screw 4 with one side for the setting of discrepancy, prevent that arbitrary first screw 4 from taking place to explode and influence other first screw 4's normal work.

The rotating surfaces of the first propellers 4 are shown by dashed lines in fig. 3, and two adjacent first propellers 4 positioned on the same side of the body 2 are arranged in a staggered manner, so that the rotating surfaces of two adjacent first propellers 4 positioned on the same side of the body 2 are not overlapped. When the vertical take-off and landing aircraft with the partially tilted propellers is in a state shown in fig. 1 and 3, the rotating surfaces of two adjacent first propellers 4 positioned on the same side of the aircraft body 2 are not overlapped, and cabin personnel and main parts of the aircraft are avoided, so that the normal work of other first propellers 4 is effectively prevented from being influenced by the explosion of any first propeller 4.

Referring to fig. 6, in one embodiment, the first propeller 4 is deflected away from the fuselage 2 when the first propeller 4 is facing upwards.

When the vertical take-off and landing aircraft with the partially tilted propellers is in the state shown in fig. 2, 5 and 6, the first propeller 4 and the fuselage 2 form an angle with each other, so that the first propeller 4 can be prevented from exploding and hurting people or damaging main parts of the aircraft.

Further, as shown in fig. 6, the yaw control of the partially tilted propeller vtol aircraft can be improved by deflecting the first propeller 4 on the left side of the body 2 to the left side and deflecting the first propeller 4 on the right side of the body 2 to the right side.

Referring to fig. 6, in one embodiment, when the first propeller 4 is upward, the axis of the first propeller 4 has an angle α with the height direction, and 45 ° > α > 0 ° is satisfied.

In another embodiment, the included angle α satisfies 15 ° > α > 10 °. And when the included angle α satisfies the above range, the effect of preventing the first propeller 4 from blasting or damaging a person or main parts of the aircraft is better, and the steering stability and reliability are better, for example, when α is 13 ° or 14 ° or the like.

Referring to fig. 3 and 4, in an embodiment, the second propellers 5 include two, which are respectively disposed at both sides of the body 2, and the second propellers 5 are disposed in one-to-one correspondence with the two outermost first propellers 4.

Referring to fig. 5, in an embodiment, the partially tilted-propeller vtol aircraft further includes a tilt mechanism 7, the first propeller 4 is connected to the wing 1 through the tilt mechanism 7, and the tilt mechanism 7 shifts the first propeller 4 between toward the front side and toward the upper side.

The tilt mechanism 7 can adjust the position of the rotation surface of the first propeller 4 so that the first propeller 4 satisfies the flight condition of the partially tilted propeller vtol aircraft. It is understood that the tilting mechanism 7 may be selected from the prior art, and the embodiment of the present application is not described in detail.

In one embodiment, referring to fig. 1, arm beams are arranged at both ends of the wing 1, the tilting mechanism 7 is installed inside the arm beams, and the first propeller 4 is connected with the wing 1 through the tilting mechanism 7 and the arm beams in sequence. And the second propeller 5 is also connected with the wing 1 through an arm beam. The first propeller 4 and the second propeller 5 are respectively located at both ends of the arm beam.

Referring to fig. 1 to 4, in one embodiment, the first propeller 4 has four; and/or the third propellers 6 have two, the third propellers 6 being arranged on either side of the tail fin 3.

It can be understood that, in practical applications, the number of the first propeller 4, the second propeller 5, and the third propeller 6 may be adjusted accordingly, for example, six first propellers 4 and four second propellers 5 are provided, and the embodiment of the present invention is not limited thereto.

Two third propellers 6 are arranged on the tail wing 3, the two third propellers 6 are far away from the gravity center of the vertical take-off and landing aircraft with the partially tilted propellers, the force arm is increased, and therefore the pitching control characteristic is improved on the premise of ensuring stability.

Referring to fig. 1 to 4, in an embodiment, the first propeller 4 comprises at least three blades; and/or the second propeller 5 comprises a double-bladed propeller or a stacked propeller; and/or the third propeller 6 comprises a double-bladed propeller or a stacked propeller.

Referring to fig. 1 to 4, in an embodiment, the first propeller 4 has four first blades 41; the second propeller comprises two second blades 51 when it is a double-bladed propeller, and the third propeller 6 comprises two third blades 61 when it is a double-bladed propeller.

In one embodiment, the second propeller 5 and/or the third propeller 6 are stacked propellers, wherein the stacked propellers have better performance and generate lower noise.

Referring to fig. 2 and 4, the first propeller 4 includes five blades.

It can be understood that, in practical applications, the number and the structure of the blades in the first propeller 4, the second propeller 5 and the third propeller 6 may be adjusted accordingly, and the embodiment of the present invention is not limited thereto.

The utility model provides a VTOL aircraft of partial screw that verts, adopt the many redundant designs of power, the VTOL aircraft of partial screw that verts includes four first screws 4, two second screws 5 and two third screws 6, and adopt four first screws 4 of wing 1 front side, two second screws 5 of rear side, and 3 two third screws 6's of fin layout mode, the handling characteristic and the security of the VTOL aircraft of partial screw that verts have been improved, the VTOL aircraft of partial screw that verts has guaranteed the security of the VTOL aircraft of partial screw that verts when taking place the blasting from three dimensionality. That is, the rotor layout of the vertical take-off and landing aircraft with partially tilted propellers improves pitching control and yaw control, and greatly improves the safety of the aircraft.

The partially tilted propeller vertical take-off and landing aircraft has the following flight phases:

vertical take-off and landing: referring to fig. 2 and 4, the first propeller 4, the second propeller 5, and the third propeller 6 each provide lift, and at this time, the first propeller 4 is turned to a state in which the rotation surface faces upward by controlling the tilt mechanism 7.

Climbing stage: the first propeller 4 is in the transition between the two states of fig. 1 and 2, the first propeller 4 providing part of the lift and part of the forward-flight pulling force, and the lift being provided by the wing 1, the second propeller 5 and the third propeller 6.

And (3) cruising: referring to fig. 1, the first propeller 4 provides a pulling force and the second propeller 5 and the third propeller 6 are locked in a heading position, i.e. the two second blades 51 of the second propeller 5 and the two third blades 61 of the third propeller 6 are both arranged in the fore-and-aft direction of the fuselage 2, wherein the second propeller 5 and the third propeller 6 can also be activated in an emergency and provide a lift force during a cruise phase emergency.

A hovering stage: referring to fig. 2 and 4, the first propeller 4, the second propeller 5, and the third propeller 6 each provide lift, and at this time, the first propeller 4 is turned to a state in which the rotation surface faces upward by controlling the tilt mechanism 7.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the present invention.

Claims (10)

1. The vertical take-off and landing aircraft with the partially tilted propellers is characterized by comprising wings (1), a tail wing (3), a first propeller (4) arranged on the front side of the wings (1), a second propeller (5) arranged on the rear side of the wings (1), and a third propeller (6) arranged on the tail wing (3);

the first propeller (4), the second propeller (5) and the third propeller (6) are all up, the height of the rotating surface of the first propeller (4) is different from that of the rotating surface of the second propeller (5), and the height of the rotating surface of the second propeller (5) is different from that of the rotating surface of the third propeller (6).

2. The vertical takeoff and landing aircraft of partially tilted propellers according to claim 1, characterized in that the height of the plane of rotation of the first propeller (4) is greater than the height of the plane of rotation of the second propeller (5), the height of the plane of rotation of the first propeller (4) being less than the height of the plane of rotation of the third propeller (6).

3. The aircraft of claim 1, characterized in that it further comprises a fuselage (2) and a plurality of said first propellers (4) are uniformly distributed on both sides of said fuselage (2) and projected in the fore-aft direction of said fuselage (2), and the projections of said first propellers (4) adjacent to each other on the same side of said fuselage (2) do not coincide.

4. The partially tilt-rotor vtol aerial vehicle according to claim 3, characterized in that the first rotor (4) is deflected away from the fuselage (2) when the first rotor (4) is facing upwards.

5. The vertical take-off and landing aircraft with partially tilted propellers according to claim 4, characterized in that the axis of the first propeller (4) is at an angle α to the height direction when the first propeller (4) is facing upwards, and that 45 ° > α > 0 °.

6. The vertical take-off and landing aircraft with partially tilted propellers of claim 5, characterized in that the angle α satisfies 15 ° > α > 10 °.

7. The aircraft according to claim 3, characterized in that said second propellers (5) comprise two, respectively arranged on both sides of said fuselage (2), said second propellers (5) being arranged in one-to-one correspondence with the outermost two of said first propellers (4).

8. The partially tilted-propeller vtol aerial vehicle according to claim 1, characterized in that it further comprises a tilt mechanism (7), by means of which tilt mechanism (7) the first propeller (4) is connected with the wing (1), the tilt mechanism (7) shifting the first propeller (4) between a forward facing side and an upward facing side.

9. The partially tiltrotor propeller VTOL aerial vehicle of claim 1,

the first propellers (4) have four; and/or the presence of a gas in the atmosphere,

the number of the third propellers (6) is two, and the third propellers (6) are respectively arranged on two sides of the tail wing (3).

10. The partially tiltrotor propeller VTOL aerial vehicle of claim 1,

the first propeller (4) comprises at least three blades; and/or the presence of a gas in the gas,

the second propeller (5) comprises a double-bladed or stacked propeller; and/or the presence of a gas in the gas,

the third propeller (6) comprises a double-bladed propeller or a stacked propeller.

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