CN112623183A

CN112623183A - Portable vertical take-off and landing inclined wing aircraft

Info

Publication number: CN112623183A
Application number: CN202011602373.8A
Authority: CN
Inventors: 马超; 武旭; 叶志鸿; 李承朴; 吴旭; 安邦
Original assignee: Civil Aviation University of China
Current assignee: Civil Aviation University of China
Priority date: 2020-12-29
Filing date: 2020-12-29
Publication date: 2021-04-09
Anticipated expiration: 2040-12-29
Also published as: CN112623183B

Abstract

The invention provides a portable vertical take-off and landing inclined wing aircraft, which comprises wings, an aircraft body and an empennage, wherein the wings are arranged on the top of the aircraft body through a rotating mechanism and a fixed support; the rotating mechanism is arranged in a mechanism box, and the mechanism box is connected with the fixed support in a sliding manner through sliding rods arranged on two sides of the mechanism box; the rotary mechanism comprises a wing rotary shaft and a rotary component, the wing rotary shaft is vertically arranged in the mechanism box, a boss bearing is arranged at the top end of the wing rotary shaft, the outer ring of the boss bearing is fixedly arranged on a support plate of the wing, the wing rotary shaft is rotatably connected with a steering engine fixed on the mechanism box through the rotary component, and the bottom end of the wing rotary shaft is fixedly arranged in the mechanism box; the fixed support is fixedly arranged in the machine body. The invention adopts the shape of asymmetric wings to provide the oblique layout lift force during flight, the oblique angle can be changed along with the speed during flight, the aircraft body is more adaptive to the change of the environment than the traditional fixed wing, and the lift fan is arranged on the belly of the aircraft body to realize short-distance takeoff and vertical landing.

Description

Portable vertical take-off and landing inclined wing aircraft

Technical Field

The invention belongs to the field of aircrafts, and particularly relates to a portable vertical take-off and landing inclined wing aircraft.

Background

Researches on aerodynamics and power of an inclined wing aircraft have been carried out at home and abroad, the inclined wing aircraft has good aerodynamic characteristics, is different from a fixed wing aircraft, and can change an included angle between a wing and a fuselage along with the change of the environment so as to change the lift-drag ratio to adapt to the environment; compared with the variable sweepback wing, the inclined wing has the advantages of simple structure, constant aerodynamic center and stronger task capability.

The existing inclined wing technology is a large aircraft researched on the premise of subsonic speed, but related research shows that the inclined wing technology still has a certain speed-increasing advantage under low-speed flight, but the inclined wing is still in a fixed wing state during taking off and landing, and compared with a rotor aircraft, the inclined wing technology is poor in flexibility, long in taking off and landing process and needs a long runway.

Disclosure of Invention

In view of the above, the present invention is directed to a portable vertical take-off and landing inclined wing aircraft, so as to solve the problems of inconvenience in carrying, time-consuming assembly, and poor take-off and landing performance of a fixed wing aircraft.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

a portable vertical take-off and landing inclined wing aircraft comprises wings, an aircraft body and an empennage, wherein the wings are arranged on the top of the aircraft body through a rotating mechanism and a fixed support;

the rotating mechanism is arranged in a mechanism box, and the mechanism box is connected with the fixed support in a sliding manner through sliding rods arranged on two sides of the mechanism box;

the rotary mechanism comprises a wing rotary shaft and a rotary component, the wing rotary shaft is vertically arranged in the mechanism box, a boss bearing is arranged at the top end of the wing rotary shaft, the outer ring of the boss bearing is fixedly arranged on a support plate of the wing, the wing rotary shaft is rotatably connected with a steering engine fixed on the mechanism box through the rotary component, and the bottom end of the wing rotary shaft is fixedly arranged in the mechanism box;

the fixed support is fixedly arranged in the machine body.

Furthermore, the rotating assembly comprises an internal tooth slewing bearing, an external boss gear and a steering engine gear; the internal tooth slewing bearing rotary bearing is fixedly arranged in a notch of a mechanism box bottom plate, the boss outer gear is fixedly arranged at the bottom end of the wing rotating shaft, the internal tooth slewing bearing rotary bearing is internally meshed with the boss outer gear, and the boss outer gear is externally meshed with a steering gear fixedly arranged on a steering engine.

Furthermore, the fixed support comprises a fixed base plate and side plates fixedly arranged on two sides of the fixed base plate, wing slideways are arranged on the side plates on two sides, and fixing grooves used for clamping the sliding rods are formed in the wing slideways.

Furthermore, the number of the slide bars is two, the two slide bars are arranged in parallel, one slide bar penetrates through the mechanism box and is arranged in the wing slideway, the other slide bar penetrates through the mechanism box and is arranged in a fixed groove arranged on the wing slideway, and two end parts of the slide bars extending to the outer side of the wing slideway are respectively provided with a limiting block.

Furthermore, the wings are integrally inclined, and the shapes of the wings are arranged at the front edge and the rear edge of a wing with an asymmetric geometric shape and a slightly elliptical shape;

and one side of the wing, which is far away from the nose, is also provided with ailerons, which are asymmetrically arranged and controlled by a steering engine.

Further, two strip-shaped columns are fixedly arranged between wing ribs of the wing, the two strip-shaped columns are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns, and the support plate is correspondingly arranged in the strip-shaped grooves;

the support plate is provided with a mounting hole for mounting the boss bearing.

Further, a machine body duct is arranged in the machine body, an air inlet is formed in the end portion, close to the machine head, of the machine body duct, a machine body duct engine is arranged in the machine body duct, and a spray pipe air outlet is formed in the end portion, close to the tail, of the machine body duct.

Furthermore, a vector device is arranged on the outer side of the air outlet of the spray pipe of the tail.

Furthermore, the empennage comprises a vertical empennage and a horizontal empennage, wherein the vertical empennage is provided with a rudder, and the horizontal empennage is provided with an elevator.

Further, the lifting device is vertically arranged on the belly of the fuselage;

an abdomen ducted engine is arranged in the lift device and provides power for the aircraft;

the lift device is also provided with an annular air inlet which is symmetrically distributed in a fan shape.

Compared with the prior art, the portable vertical take-off and landing inclined wing aircraft has the following advantages:

(1) the portable vertical take-off and landing inclined wing aircraft adopts an asymmetric wing shape, provides inclined layout lift force during flight, can change an inclined angle along with speed during flight, is more adaptive to environmental change than the traditional fixed wing, and is provided with a lift fan at the belly part of the aircraft body to realize short take-off and vertical landing;

(2) the portable vertical take-off and landing inclined wing aircraft adopts the design of the rotating shafts of the wings and the aircraft body, so that when the aircraft is stored, the rotating wings and the aircraft body are in a straight line and are convenient to carry;

(3) the portable vertical take-off and landing inclined wing aircraft overcomes the defects of inconvenience in carrying and time-consuming assembly of the conventional fixed wing aircraft, and simultaneously improves the take-off and landing performance of the fixed wing aircraft by the aid of the additional fuselage abdominal lifting fan.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a schematic view of an overall structure of a portable VTOL oblique wing aircraft according to an embodiment of the present invention;

FIG. 2 is a left side view of a portable VTOL oblique wing aircraft according to an embodiment of the present invention;

FIG. 3 is a schematic view of an inverted structure of a portable VTOL oblique wing aircraft rotation mechanism according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a local wing and a fixed support of a portable VTOL oblique wing aircraft according to an embodiment of the present invention;

FIG. 5 is a rear view of a portable VTOL tilt-wing aircraft according to an embodiment of the present invention;

fig. 6 is a front view of a portable VTOL oblique wing aircraft according to an embodiment of the invention.

Description of reference numerals:

1-an airfoil; 101-ribs; 102-ailerons; 2-a fuselage; 3-tail fin; 301-vertical tail; 302-horizontal tail; 303-rudder; 304-elevators; 4-fuselage ducted engines; 5-a fuselage duct; 6-an air inlet; 7-spray pipe air outlet; 8-abdominal ducted engine; 9-annular air inlet; 10-a rotating mechanism; 11-a wing glide slope; 12-an internal tooth slewing bearing swivel bearing; 13-wing shaft; 14-boss outer gear; 15-mechanism box; 16-a slide bar; 1601-a limiting block; 17-a fixed support; 18-a support plate; 19-a bar column; 20-elevator; 21-a steering gear; 22-boss bearings; 23-vector means.

Detailed Description

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

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

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

Referring to fig. 1 to 6, the aircraft comprises a wing 1, a fuselage 2 and an empennage 3, wherein the wing 1 is installed on the top of the fuselage 2 through a rotating mechanism 10 and a fixed support 17;

the rotating mechanism 10 is arranged in a mechanism box 15, and the mechanism box 15 is connected with a fixed support 17 in a sliding manner through sliding rods 16 arranged on two sides;

the rotating mechanism 10 comprises a wing rotating shaft 13 and a rotating assembly, the wing rotating shaft 13 is vertically arranged in a mechanism box 15, a boss bearing 22 is arranged at the top end of the wing rotating shaft 13, the outer ring of the boss bearing 22 is fixedly arranged on a support plate 18 of the wing 1, the wing rotating shaft 17 is rotatably connected with a steering engine fixed on the mechanism box 15 through the rotating assembly, and the bottom end of the wing rotating shaft 17 is fixedly arranged in the mechanism box 15;

the fixed support 17 is fixedly arranged in the machine body 2.

The rotating assembly comprises an inner tooth slewing bearing 12, an outer boss gear 14 and a steering engine gear 21; the internal tooth slewing bearing rotary bearing 12 is fixedly arranged in a notch of a bottom plate of the mechanism box 15, the boss outer gear 14 is fixedly arranged at the bottom end of the wing rotating shaft 13, the internal tooth slewing bearing rotary bearing 12 is internally meshed with the boss outer gear 14, and the boss outer gear 14 is meshed with a steering gear 21 fixedly arranged on a steering engine.

The fixed support 17 comprises a fixed base plate and side plates fixedly arranged on two sides of the fixed base plate, wing slideways 11 are arranged on the side plates on two sides, and fixing grooves used for clamping the sliding rods 16 are formed in the wing slideways 11.

The number of the slide bars 16 is two, the two slide bars 16 are arranged in parallel, one slide bar 16 penetrates through the mechanism box 15 and is arranged in the wing slideway 11, the other slide bar 16 penetrates through the mechanism box 15 and is arranged in a fixing groove formed in the wing slideway 11, and two end parts of the slide bars 16 extending to the outer side of the wing slideway 11 are respectively provided with a limiting block 1601.

The wing 1 is an integral oblique wing, and the shape of the wing 1 is arranged by adopting the front edge and the rear edge of a wing with an asymmetric geometric shape which is slightly elliptical;

the aircraft is characterized in that ailerons 102 are further arranged on one side, away from the aircraft nose, of the wing 1, the ailerons 102 are arranged asymmetrically, the ailerons 102 are controlled by a steering engine and used for twisting the ailerons 102, and a flier observes and adjusts the twisting angle of the ailerons 102 during flight so as to adjust the attitude of the aircraft stably.

Strip-shaped columns 19 are fixedly arranged between wing ribs 101 of the wing 1, the number of the strip-shaped columns 19 is two, the two strip-shaped columns 19 are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns 19, and the support plate 18 is correspondingly arranged in the strip-shaped grooves;

the support plate 18 is provided with a mounting hole for mounting the boss bearing 22.

The aircraft is characterized in that an aircraft body duct 5 is arranged in the aircraft body, an air inlet 6 is arranged at the end part of the aircraft body duct 5 close to the aircraft nose, an aircraft body duct engine 4 is arranged in the aircraft body duct 5, and a spray pipe air outlet 7 is arranged at the end part of the aircraft body duct 5 close to the aircraft tail.

And a vector device 23 is arranged on the outer side of the spray pipe air outlet 7 of the tail.

The empennage comprises a vertical empennage 301 and a horizontal empennage 302, a rudder 303 is arranged on the vertical empennage 301, an elevator 304 is arranged on the horizontal empennage 302, and the rudder 303 and the vector device 23 share one steering engine for control.

The lifting device is vertically arranged at the belly of the machine body 2;

an abdomen ducted engine 8 is arranged in the lift device, and the abdomen ducted engine 8 provides power for the aircraft;

the lift device is also provided with an annular air inlet 9, and the annular air inlets 9 are symmetrically distributed in a fan shape; when the aircraft accelerates forwards, the front part of the annular air inlet 9 is used for air inlet, the lift force of the aircraft is increased, and the takeoff distance of the aircraft is shortened.

The aircraft is provided with eight receiver channels; wherein, two sets of power systems arranged on the aircraft occupy two receiver channels; two receiver channels are occupied by the wing ailerons on two sides controlled by the steering engine; elevators of the horizontal rear wings 302 on both sides controlled by the steering engine occupy one receiver channel; a vertical tail 301 and a vector device 23 controlled by a steering engine occupy one receiver channel; a rotating mechanism 10 controlled by a steering engine occupies a receiver channel; a steering engine for controlling the steering of the front wheels occupies a receiver channel;

the eight receiver channels are controlled by six rockers of the remote control.

In the implementation of the scheme, during takeoff, the aircraft is accelerated by taking the fuselage ducted engine 4 as the main power, after the aircraft starts to slide, the belly ducted engine 8 mainly uses the front part of the annular air inlet to intake air to generate upward thrust to increase the lift force of the aircraft and shorten the takeoff distance of the aircraft, and in the process, an operator of the aircraft observes the attitude of the aircraft and adjusts the states of the vector devices 23 at the vertical tail wing 301 and the air outlet 7 of the tail end spray pipe of the aircraft body to enable the aircraft to take off stably;

in the flying process, an aircraft operator properly adjusts the states of the ailerons 102, the elevators 304, the rudder 303, the vector device 23 of the nozzle air outlet 7 at the tail end of the aircraft body and the belly ducted engine 8 by observing the attitude of the aircraft, controls the steering engine of the rotating mechanism 10 to rotate the wings 1 anticlockwise for 20 degrees when the flying speed reaches the fastest speed so as to increase the speed, and adjusts the wings 1 to be in a normal state when the aircraft is ready for deceleration landing.

When the aircraft is close to the ground and is ready to land, the power of the fuselage ducted engine 4 is gradually reduced to zero, meanwhile, the power of the belly ducted engine 8 is increased, the air inlet at the rear part of the annular air inlet 9 is gradually increased in the deceleration process, the work efficiency of the belly ducted engine 8 is controlled while the aircraft is decelerated, the aircraft is approximately landed vertically to shorten the braking distance, in the process, an aircraft operator observes the attitude of the aircraft, and the states of the vector devices 23 of the vertical tail wing 301 and the tail end spray pipe air outlet 7 of the aircraft body are adjusted, so that the aircraft lands stably.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims

1. The utility model provides a portable VTOL's oblique wing aircraft that puts, includes wing (1), fuselage (2) and fin (3), its characterized in that: the wing (1) is arranged on the top of the fuselage (2) through a rotating mechanism (10) and a fixed support (17);

the rotating mechanism (10) is arranged in a mechanism box (15), and the mechanism box (15) is connected with a fixed support (17) in a sliding manner through sliding rods (16) arranged on two sides;

the rotating mechanism (10) comprises a wing rotating shaft (13) and a rotating assembly, the wing rotating shaft (13) is vertically arranged in a mechanism box (15), a boss bearing (22) is arranged at the top end of the wing rotating shaft (13), the outer ring of the boss bearing (22) is fixedly arranged on a support plate (18) of the wing (1), the wing rotating shaft (13) is rotatably connected with a steering engine fixed on the mechanism box (15) through the rotating assembly, and the bottom end of the wing rotating shaft (13) is fixedly arranged in the mechanism box (15);

the fixed support (17) is fixedly arranged in the machine body (2).

2. The portable VTOL oblique wing aircraft of claim 1, wherein: the rotating assembly comprises an inner tooth slewing bearing (12), an outer boss gear (14) and a steering engine gear (21); internal tooth slewing bearing rotating bearing (12) set firmly in the notch at mechanism box (15) bottom plate, boss external gear (14) set firmly in the bottom of wing pivot (13), internal tooth slewing bearing rotating bearing (12) and boss external gear (14) internal gearing, boss external gear (14) with set firmly the steering wheel gear on the steering wheel outside (21) the meshing.

3. The portable VTOL oblique wing aircraft of claim 1, wherein: the fixed support (17) comprises a fixed base plate and side plates fixedly arranged on two sides of the fixed base plate, wing slideways (11) are arranged on the side plates, and fixing grooves used for clamping sliding rods (16) are formed in the wing slideways (11).

4. The portable VTOL oblique wing aircraft of claim 1, wherein: the number of the sliding rods (16) is two, the two sliding rods (16) are arranged in parallel, one sliding rod (16) penetrates through the mechanism box (15) and is arranged in the wing slideway (11), the other sliding rod (16) penetrates through the mechanism box (15) and is arranged in a fixing groove formed in the wing slideway (11), and two end parts, extending to the outer side of the wing slideway (11), of the sliding rods (16) are respectively provided with a limiting block 1601.

5. The portable VTOL oblique wing aircraft of claim 1, wherein: the wing (1) is an integral inclined wing, and the shape of the wing (1) is arranged by adopting the front edge and the rear edge of a wing with an asymmetric geometric shape which is slightly elliptical;

the aircraft nose is kept away from in wing (1) one side still is equipped with aileron (102), aileron (102) are asymmetric setting, aileron (102) are by steering engine control.

6. The portable VTOL oblique wing aircraft of claim 5, wherein: strip-shaped columns (19) are fixedly arranged between wing ribs (101) of the wing (1), the number of the strip-shaped columns (19) is two, the two strip-shaped columns (19) are arranged in parallel, strip-shaped grooves are formed in the two strip-shaped columns (19), and the support plates (18) are correspondingly arranged in the strip-shaped grooves;

and the support plate (18) is provided with a mounting hole for mounting a boss bearing (22).

7. The portable VTOL oblique wing aircraft of claim 1, wherein: the aircraft is characterized in that an aircraft body duct (5) is arranged in the aircraft body, an air inlet (6) is arranged at the end part, close to the aircraft nose, of the aircraft body duct (5), an aircraft body duct engine (4) is arranged in the aircraft body duct (5), and a spray pipe air outlet (7) is arranged at the end part, close to the aircraft tail, of the aircraft body duct (5).

8. The portable VTOL oblique wing aircraft of claim 7, wherein: and a vector device (23) is arranged on the outer side of a spray pipe air outlet (7) of the tail.

9. The portable VTOL oblique wing aircraft of claim 1, wherein: the empennage (3) comprises a vertical empennage (301) and a horizontal empennage (302), a rudder (303) is arranged on the vertical empennage (301), and an elevator (304) is arranged on the horizontal empennage (302).

10. The portable VTOL oblique wing aircraft of claim 1, wherein: the lifting device is vertically arranged at the belly of the machine body (2);

an abdomen ducted engine (8) is arranged in the lift device, and the abdomen ducted engine (8) provides power for the aircraft;

the lift device is also provided with an annular air inlet (9), and the annular air inlets (9) are symmetrically distributed in a fan shape.