CN112623183B - A portable vertical take-off and landing tilt-wing aircraft - Google Patents

Abstract

The invention provides a portable vertical take-off and landing tilt-wing aircraft, comprising a wing, a fuselage and an empennage, the wing is installed on the top of the fuselage through a rotating mechanism and a fixed support; In the box, the mechanism box is slidably connected with the fixed support through the slide bars provided on both sides; The top end is provided with a boss bearing, the outer ring of the boss bearing is fixed on the support plate of the wing, and the wing shaft is connected to the steering gear fixed on the mechanism box through a rotating assembly. The bottom end is fixed in the mechanism box; the fixed support is fixed in the fuselage. The invention adopts an asymmetrical wing shape to provide lift in an oblique layout during flight, and the oblique angle can be changed with the speed during flight, which is more adaptable to changes in the environment than traditional fixed wings. landing.

Description

A portable vertical take-off and landing tilt-wing aircraft

technical field

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

Background technique

Research on the aerodynamics and dynamics of inclined-wing aircraft has been carried out at home and abroad. The inclined-wing aircraft has good aerodynamic characteristics. Unlike fixed-wing aircraft, its wings can change the angle with the fuselage as the environment changes. , and then change the lift-to-drag ratio to adapt to the environment; compared with the variable-sweep wing, the oblique wing has a simple structure and the aerodynamic center remains unchanged, and its task capability is stronger.

Existing oblique wing technologies are all large-scale aircraft researched on the premise of subsonic speed, but relevant studies have shown that it still has a certain speed-up advantage in low-speed flight, but the oblique wing is still in a fixed-wing state during take-off and landing, unlike the rotor. Compared with the aircraft, the flexibility is poor, the take-off and landing process takes a long time, and requires a long runway.

Contents of the invention

In view of this, the present invention aims to propose a portable vertical take-off and landing inclined-wing aircraft to solve the problems of inconvenient portability, time-consuming assembly, and poor take-off and landing performance of fixed-wing aircraft.

In order to achieve the above object, technical solution of the present invention is achieved in that way:

A portable tilt-wing aircraft for vertical take-off and landing comprises wings, a fuselage and an empennage, and the wings are installed on the top of the fuselage through a rotating mechanism and a fixed support;

The rotating mechanism is arranged in the mechanism box, and the mechanism box is slidably connected with the fixed support through the sliding rods provided on both sides;

The rotating mechanism includes a wing shaft and a rotating assembly, the wing shaft is vertically arranged in the mechanism box, the top of the wing shaft is provided with a boss bearing, and the outer ring of the boss bearing is fixed on the support of the wing. On the board, the wing shaft is rotationally connected with the steering gear fixed on the mechanism box through the rotating assembly, and the bottom end of the wing shaft is fixed in the mechanism box;

The fixed support is fixed in the fuselage.

Further, the rotating assembly includes an internal-tooth slewing bearing rotary bearing, a boss external gear, and a steering gear; the internal-tooth slewing bearing rotary bearing is fixed in a recess on the bottom plate of the mechanism box, and the boss external gear is fixed It is arranged at the bottom end of the wing shaft, and the internal tooth slewing support rotary bearing is internally meshed with the external gear of the boss, and the external gear of the boss is externally meshed with the steering gear fixed on the steering gear.

Further, the fixed support includes a fixed bottom plate and side plates fixed on both sides of the fixed bottom plate, the side plates on both sides are provided with wing slideways, and the wing slideways are provided with sliding rods. Fixed slot.

Further, the number of the sliding rods is two, and the two sliding rods are arranged in parallel, wherein, one of the sliding rods passes through the mechanism box and is arranged in the wing slideway, and the other one of the sliding rods passes through the The mechanism box is arranged in the fixing groove provided on the wing slideway, and the two ends of the slide bar extending to the outside of the wing slideway are respectively provided with limit blocks.

Further, the wing is an integral oblique wing, and the shape of the wing is set with a slightly elliptical front and rear edges of an asymmetric geometric shape;

The side of the wing away from the nose is also provided with an aileron, which is asymmetrically arranged and controlled by a steering gear.

Further, bar columns are fixed between the ribs of the wing, the number of the bar columns is two, the two bar columns are arranged in parallel, and both of the bar columns are provided with a strip-shaped groove, and the support plate is correspondingly arranged in the strip-shaped groove;

Mounting holes for mounting boss bearings are provided on the support plate.

Further, a fuselage duct is arranged inside the fuselage, an air inlet is provided at the end of the fuselage duct near the nose, a fuselage duct engine is arranged in the fuselage duct, and the fuselage duct The end of the duct near the tail is provided with a nozzle air outlet.

Further, a vectoring device is provided on the outside of the air outlet of the nozzle of the tail.

Further, the empennage includes a vertical empennage and a horizontal empennage, the vertical empennage is provided with a rudder, and the horizontal empennage is provided with an elevator.

Further, it also includes a lifting device, and the lifting device is vertically arranged on the abdomen of the fuselage;

An abdominal ducted engine is provided in the lift device, and the abdominal ducted engine provides power for the aircraft;

The lifting device is also provided with an annular air inlet, and the annular air inlet is fan-shaped and symmetrically distributed.

Compared with the prior art, a kind of portable vertical take-off and landing tilt-wing aircraft of the present invention has the following advantages:

(1) A portable tilt-wing aircraft for vertical take-off and landing according to the present invention adopts an asymmetrical wing shape to provide lift when flying, and the tilt angle can be changed with the speed during flight, which is more adaptable than traditional fixed wings In case of environmental changes, a lift fan is installed on the belly of the fuselage to achieve short-distance take-off and vertical landing;

(2) a kind of portable tilt-wing aircraft of vertical take-off and landing of the present invention adopts the design of the rotating shaft of wing, fuselage, makes aircraft when storing, and rotating wing is in line with fuselage, is easy to carry;

(3) a kind of portable tilt-wing aircraft of vertical take-off and landing of the present invention has improved conventional fixed-wing aircraft to carry inconvenience, the shortcoming of time-consuming assembling, the fuselage abdomen lift fan that adds has improved the take-off and landing of fixed-wing aircraft simultaneously performance.

Description of drawings

The drawings constituting a part of the present invention are used to provide a further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention. In the attached picture:

Fig. 1 is a schematic diagram of the overall structure of a portable vertical take-off and landing tilt-wing aircraft according to an embodiment of the present invention;

Fig. 2 is a left side view of a portable vertical take-off and landing tilt-wing aircraft according to an embodiment of the present invention;

Fig. 3 is a schematic diagram of an inverted structure of a rotary mechanism of a portable vertical take-off and landing tilt-wing aircraft according to an embodiment of the present invention;

Fig. 4 is a schematic structural diagram of a partial wing and a fixed support of a portable vertical take-off and landing inclined-wing aircraft according to an embodiment of the present invention;

Fig. 5 is a rear view of a portable vertical take-off and landing tilt-wing aircraft according to an embodiment of the present invention;

Fig. 6 is a front view of a portable vertical take-off and landing tilt-wing aircraft according to an embodiment of the present invention.

Explanation of reference signs:

1-wing; 101-rib; 102-aileron; 2-fuselage; 3-tail; 301-vertical tail; 302-horizontal tail; 303-rudder; 304-elevator; 4-fuselage ducted engine; 5-fuselage duct; 6-air intake; 7-nozzle outlet; 8-abdomen ducted engine; 9-circular air intake; 10-rotary mechanism; 11-wing slide; 12-internal teeth Slewing bearing; 13-wing shaft; 14-boss external gear; 15-mechanism box; 16-slider; 1601-limit block; 17-fixed support; ; 20-elevator; 21-rudder gear; 22-boss bearing; 23-vector device.

detailed description

It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and thus should not be construed as limiting the invention. In addition, the terms "first", "second", etc. are used for descriptive purposes only, and should not be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, a feature defined as "first", "second", etc. may expressly or implicitly include one or more of that feature. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it may be mechanically connected or electrically connected; it may be directly connected or indirectly connected through an intermediary, and it may be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention based on specific situations.

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

Please refer to shown in Fig. 1 to Fig. 6, comprise wing 1, fuselage 2 and empennage 3, described wing 1 is installed on the top of fuselage 2 by rotating mechanism 10 and fixed support 17;

The rotating mechanism 10 is arranged in the mechanism box 15, and the mechanism box 15 is slidably connected with the fixed support 17 through the sliding rods 16 provided on both sides;

Described rotating mechanism 10 comprises wing rotating shaft 13, rotating assembly, and wing rotating shaft 13 is vertically arranged in mechanism box 15, and the top of described wing rotating shaft 13 is provided with boss bearing 22, and the outer ring of described boss bearing 22 Fixed on the support plate 18 of the wing 1, the wing shaft 17 is rotationally connected with the steering gear fixed on the mechanism box 15 through a rotating assembly, and the bottom end of the wing shaft 17 is fixed in the mechanism box 15 ;

The fixed support 17 is fixed inside the fuselage 2 .

The rotating assembly includes an internal tooth slewing bearing 12, a boss external gear 14, and a steering gear 21; the internal tooth slewing bearing 12 is fixed in a notch on the bottom plate of the mechanism box 15, and the boss outside The gear 14 is fixed on the bottom end of the wing shaft 13, and the internal tooth slewing bearing 12 is internally meshed with the outer gear 14 of the boss, and the outer gear 14 of the boss is connected with the outer gear 21 of the steering gear fixed on the steering gear. engage.

The fixed support 17 includes a fixed bottom plate and side plates fixed on both sides of the fixed bottom plate, the side plates on both sides are provided with wing slides 11, and the wing slides 11 are provided with slide bars for engaging 16 fixing slots.

The quantity of described slide bar 16 is two, and two described slide bars 16 are arranged in parallel, and wherein, one described slide bar 16 is arranged in the wing slideway 11 through mechanism box 15, and another described slide bar 16 The rod 16 passes through the mechanism box 15 and is arranged in the fixing groove provided on the wing slide 11 , and the two ends of the slide rod 16 extending to the outside of the wing slide 11 are respectively provided with limiting blocks 1601 .

The wing 1 is an integrated inclined wing, and the shape of the wing 1 adopts an asymmetric geometric shape with slightly elliptical front and rear edges;

The side of the wing 1 far away from the nose is also provided with an aileron 102, the aileron 102 is asymmetrically arranged, and the aileron 102 is controlled by a steering gear to twist the aileron 102, and the pilot observes it during flight Adjust the twisting angle of the aileron 102 to adjust the attitude of the aircraft smoothly.

The ribs 101 of the wing 1 are fixed with bar columns 19, the number of the bar columns 19 is two, the two bar columns 19 are arranged in parallel, and the two bar columns 19 All are provided with strip-shaped grooves, and the support plates 18 are correspondingly arranged in the strip-shaped grooves;

Mounting holes for mounting boss bearings 22 are provided on the support plate 18 .

Fuselage duct 5 is established in the fuselage, and the end of said fuselage duct 5 near the nose is provided with an air inlet 6, and said fuselage duct 5 is provided with a fuselage duct engine 4, said machine Body duct 5 is provided with nozzle air outlet 7 near the end of the tail.

A vector device 23 is provided on the outside of the nozzle air outlet 7 of the tail.

The empennage comprises a vertical empennage 301 and a horizontal empennage 302. The vertical empennage 301 is provided with a rudder 303, and the horizontal empennage 302 is provided with an elevator 304. The rudder 303 and the vectoring device 23 are controlled by a common steering gear.

It also includes a lift device, which is vertically arranged on the abdomen of the fuselage 2;

An abdominal ducted engine 8 is provided in the lift device, and the abdominal ducted engine 8 provides power for the aircraft;

Also be provided with annular air inlet 9 on described lift device, described annular air inlet 9 is fan-shaped symmetrical distribution; , shorten the take-off distance of the aircraft, and when the aircraft decelerates and lands, the air intake efficiency at the rear of the annular air inlet 9 increases gradually, helping the aircraft decelerate while controlling the working efficiency of the abdominal ducted engine 8, so that the aircraft lands approximately vertically to shorten the braking time distance.

The aircraft has a total of eight receiver channels; among them, the two sets of power systems on the aircraft occupy two receiver channels; the wing ailerons on both sides controlled by the steering gear occupy two receiver channels; The elevators on both sides of the horizontal tail 302 occupy a receiver channel; the vertical tail 301 and the vector device 23 controlled by the steering gear occupy a receiver channel; the rotating mechanism 10 controlled by the steering gear occupies a receiver channel; The steering gear for wheel steering occupies a receiver channel;

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

When this program was implemented, when taking off, the fuselage ducted engine 4 was the main power to accelerate the aircraft. After the start of taxiing, the abdominal ducted engine 8 mainly used the front part of the annular air inlet to generate upward thrust to increase the lift of the aircraft. , shorten the take-off distance of the aircraft. In this process, the aircraft operator observes the attitude of the aircraft, adjusts the state of the vector device 23 at the vertical tail 301 and the nozzle air outlet 7 at the tail end of the fuselage, so that the aircraft takes off smoothly;

During the flight, the aircraft operator properly adjusts the states of the aileron 102, the elevator 304, the rudder 303, the vector device 23 of the nozzle air outlet 7 at the tail end of the fuselage, and the state of the abdominal ducted engine 8 by observing the attitude of the aircraft. When reaching the fastest, control the steering gear of the rotating mechanism 10 to make the wing 1 rotate 20 degrees counterclockwise to increase the speed. When preparing to slow down and land, the wing 1 is adjusted back to the normal state.

When the aircraft approached the ground and prepared to land, the power of the fuselage ducted engine 4 was gradually reduced to zero, and the power of the abdominal ducted engine 8 was increased, and the rear air intake of the annular air inlet 9 gradually increased in the deceleration process to help While the aircraft decelerates, the operating efficiency of the abdominal ducted engine 8 is controlled so that the aircraft lands approximately vertically to shorten the braking distance. The vector device 23 is in a state to make the aircraft land smoothly.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of the present invention. within the scope of protection.

Claims (5)

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);

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 a mechanism box (15), the boss outer gear (14) is fixedly arranged at the bottom end of a 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 externally meshed with a steering gear (21) fixedly arranged on a steering engine;

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;

an aileron (102) is further arranged on one side of the wing (1) far away from the nose, the ailerons (102) are arranged asymmetrically, and the ailerons (102) are controlled by a steering engine;

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;

the fixed support (17) comprises a fixed bottom plate and side plates fixedly arranged on two sides of the fixed bottom plate, wing slideways (11) are arranged on the side plates on two sides, and fixing grooves used for clamping the sliding rods (16) are arranged on the wing slideways (11);

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.

2. The portable VTOL oblique wing aircraft of claim 1, 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).

3. 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 formed in the end portion, 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 formed in the end portion, close to the aircraft tail, of the aircraft body duct (5).

4. The portable VTOL oblique wing aircraft of claim 3, wherein: and a vector device (23) is arranged on the outer side of a spray pipe air outlet (7) of the tail.

5. 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).

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