CN217754097U

CN217754097U - Vertical take-off and landing aircraft

Info

Publication number: CN217754097U
Application number: CN202221866010.XU
Authority: CN
Inventors: 许兴; 邴富强
Original assignee: Xiamen Tengxi Aviation Technology Co ltd
Current assignee: Xiamen Tengxi Aviation Technology Co ltd
Priority date: 2022-07-13
Filing date: 2022-07-13
Publication date: 2022-11-08
Anticipated expiration: 2032-07-13

Abstract

The utility model relates to a vertical take-off and landing aircraft, which comprises an aircraft body, wherein the aircraft body is provided with a first compound wing, a second compound wing, a duct tilting device and a tail wing in sequence from the front part to the rear part; the tail wing is a V-shaped component; the first composite wing and the second composite wing are provided with a plurality of ducted propellers capable of providing lift force in the vertical direction; the duct tilting device is connected with a multi-mode duct which can perform tilting movement relative to the fuselage so as to switch between a vertical take-off and landing mode and a level flight cruise mode. The utility model provides a VTOL aircraft VTOL is quick and stable more, and the aircraft takes off and land safelyr. The aircraft has the advantage of duck formula overall arrangement, and mobility is better, easily control, and lift is stronger, difficult stall, just the utility model discloses a shortcoming such as traditional duck formula overall arrangement landing performance has been eliminated in the lift design.

Description

Vertical take-off and landing aircraft

Technical Field

The utility model relates to an aircraft technical field, especially a VTOL aircraft.

Background

With the development of aircrafts, various aircraft schemes capable of achieving vertical take-off and landing and cruise while flying are available, such as an oil-driven tilt rotor scheme, represented by a hawk helicopter, such as a composite rotor scheme.

However, in the existing aircraft, the scheme of oil-driven tilting rotors is used in mode switching of vertical take-off, landing and flying cruising, the control difficulty is high, and safety accidents are easy to generate.

And the aircraft adopting the composite rotor scheme depends on the rotor during vertical take-off and landing, and depends on the fixed wing and the propeller generating thrust to the rear of the aircraft during flat flight, and the rotor does not work at the moment. This means that the power sections of the aircraft of this solution are not fully functional. Therefore, all parts of the aircraft are idle in the sequence time of the flight mode, and the weight of the aircraft body is increased. And the rotor wing is easy to generate resistance in the horizontal flying process, and the flying efficiency is reduced.

SUMMERY OF THE UTILITY MODEL

In order to solve the above problems, the present invention provides a vertical take-off and landing aircraft, which can safely and efficiently take off vertically and cruise in peaceful flight.

The technical solution of the utility model is that: a vertical take-off and landing aircraft comprises an aircraft body, wherein a first composite wing, a second composite wing, a duct tilting device and a tail wing (7) are sequentially arranged on the aircraft body from the front part to the rear part; the tail wing is a V-shaped component;

the first composite wing and the second composite wing are provided with a plurality of ducted propellers capable of providing lift force in the vertical direction;

the multi-mode duct can perform tilting motion relative to the fuselage so as to switch between a vertical take-off and landing mode and a level flight cruise mode, wherein in the vertical take-off and landing mode, the multi-mode duct is driven by the duct tilting device to rotate so that air flow sprayed by the multi-mode duct is vertically downward; under the level flight cruise mode, the duct tilting device drives the multi-mode duct to rotate, so that the airflow sprayed by the multi-mode duct is horizontal and faces the rear part of the aircraft body.

Preferably, the second composite wing is mounted to the fuselage at a higher position than the first composite wing.

Preferably, the duct tilting device comprises a body partition frame, a bearing seat, a duct rotating shaft and a branch steering engine, wherein the body partition frame is vertically arranged in the body, the bearing seat is a protrusion arranged on the body partition frame, a hole for the duct rotating shaft to pass through is formed in the bearing seat, the duct rotating shaft consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the multi-mode duct, and two ends of the branch steering engine are respectively hinged to the body partition frame and the rocker arm of the duct rotating shaft; the branch steering engine stretches out and draws back during operation, and the branch steering engine pushes the rocker arm to enable the duct rotating shaft to rotate so as to drive the multi-mode duct to tilt.

Preferably, the duct screw includes duct wall, first dead lever and fixed rotor, and a plurality of duct walls are seted up respectively symmetrically on first composite wing and second composite wing, and duct wall intercommunication wing is from top to bottom, and fixed rotor passes through first dead lever setting in duct wall.

Preferably, the multi-mode duct includes duct shell, connecting block, second dead lever and rotates the rotor, and the duct shell passes through the connecting block to be connected with the duct device of verting, and the second dead lever will rotate the fixed setting of rotor inside the duct shell.

Preferably, the wingtips at both ends of the first composite wing are provided with a forked winglet, and the wingtips at both ends of the second composite wing are provided with an arc winglet.

The utility model has the advantages that: the utility model provides a VTOL aircraft compares in prior art, the utility model discloses following technological effect has at least:

1. the utility model provides a VTOL aircraft VTOL is quick and stable more, and the aircraft takes off and land safelyr.

2. The aircraft has the advantage of duck formula overall arrangement, and mobility is better, easily control, and the lift is stronger, difficult stall, just the utility model discloses a lift design has eliminated shortcomings such as traditional duck formula overall arrangement landing performance of taking off.

3. The V-shaped component empennage is adopted, so that the aircraft is more stable in the working states of a vertical take-off and landing mode and a cruise control mode, and the weight of the aircraft body is further controlled by the V-shaped component empennage.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

fig. 2 is a top view of the present invention;

fig. 3 is a side view of the present invention;

fig. 4 is a front view of the present invention;

FIG. 5 is a schematic view of the vertical take-off and landing of the present invention;

fig. 6 is a first schematic structural view of the duct tilting device of the present invention;

fig. 7 is a schematic structural diagram of the duct tilting device of the present invention.

Description of the symbols: the airplane comprises an airplane body-1, a first composite wing-2, a second composite wing-3, a duct tilting device-4, a duct propeller-5, a multi-mode duct-6, an airplane body bulkhead-41, a bearing seat-42, a duct rotating shaft-43, a branch line steering engine-44, a duct wall-51, a first fixing rod-52, a fixed rotor-53, a duct shell-61, a connecting block-62, a second fixing rod-63, a rotating rotor-64, a forked winglet-21, an arc winglet-31 and an empennage-7.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and specific embodiments.

Referring to fig. 1 to 5, a vertical take-off and landing aircraft includes a fuselage 1, where the fuselage 1 is provided with a first compound wing 2, a second compound wing 3, a duct tilting device 4 and a tail 7 in sequence from the front to the rear; the tail 7 is a V-shaped component;

the first composite wing 2 and the second composite wing 3 are provided with a plurality of ducted propellers 5 which can provide lift force in the vertical direction; the ducted propeller 5 is embedded in the first composite wing 2 and the second composite wing 3, and compared with the general design, the air resistance of the aircraft is greatly reduced.

The duct tilting device 4 is connected with a multi-mode duct 6, the multi-mode duct 6 can perform tilting motion relative to the fuselage 1 so as to switch between a vertical take-off and landing mode and a level flight cruise mode, wherein in the vertical take-off and landing mode, the duct tilting device 4 drives the multi-mode duct 6 to rotate so that air flow sprayed by the multi-mode duct 6 is vertically downward; under the level flight cruise mode, the duct tilting device 4 drives the multi-mode duct 6 to rotate, so that the airflow sprayed out by the multi-mode duct 6 is horizontal and faces the rear part of the airplane body 1. In the vertical take-off and landing mode, the ducted propellers 5 and the multi-mode ducts 6 both eject vertically downward airflow to enable the aircraft to take off or land quickly. And a plurality of duct propellers 5 and multi-mode duct carry out the multiple spot atress to the aircraft, make the aircraft take off and land more stable, have improved the security of aircraft take off and land. In the flat flight cruise mode, the multi-mode duct 6 generates thrust backwards, and the duct propeller 5 generates downward thrust, so that the lift of the aircraft is maintained, and the aircraft can obtain better maneuverability than a common fixed wing aircraft. Therefore, the utility model provides a VTOL aircraft compares in current scheme, and VTOL is quick and stable more, and the aircraft takes off and land safelyr. And in the process of the horizontal flight of the aircraft, the ducted propeller 5 continuously provides partial lift force for the aircraft, so that the aircraft can be conveniently and flexibly controlled.

The provision of the V-shaped member empennage 7, which further controls body weight, makes the aircraft more stable in the vertical take-off and landing mode and the cruise mode of operation. The V-shaped tail wing has the functions of a vertical tail wing and a horizontal tail wing at the same time, can play a role in stabilizing the longitudinal direction and the heading direction at the same time, and plays a role in lifting the rudder when the rudder surfaces on the two sides deflect towards the same direction; on the contrary, when the aircraft deflects to different directions, the V-shaped tail wing plays a role of a rudder, so that the controllability of the large elevation angle of the V-shaped tail wing is good, and the stealth performance of the aircraft is improved.

And the working mode of the ducted propeller 5 in the multi-mode ducted 6 level flight cruise mode can be various, except that the ducted propeller 5 mentioned above continues to provide lift, increasing the maneuverability of the aircraft. The ducted propeller 5 can also reduce the lift force, and the ducted propeller 5 keeps a low-lift working state so as to stabilize the flow field on the surfaces of the first composite wing 2 and the second composite wing 3, so that the flight of the aircraft is quieter and more stable.

The second compound wing 3 is arranged at the position of the fuselage 1 higher than the position of the first compound wing 2 arranged at the fuselage 1. The first compound wing 2 and the second compound wing 3 form a duck-type layout, the maneuverability is good, the aircraft is easy to control, the lifting force is stronger, the aircraft is not easy to stall, and the aircraft is beneficial to simplifying the aircraft driving and ensuring the flight safety. Although traditional duck formula overall arrangement has a lot of advantages, still have "take-off landing performance is not good" and "when the duck wing is impaired, the stall problem takes place easily", and the utility model discloses a lift design has eliminated the shortcoming of traditional duck formula overall arrangement, makes the utility model discloses both have good mobility, the nature controlled and also have better take off and land the performance. And the utility model discloses a splitlevel wing design, 2 mounted positions of the 1 anterior first compound wing of fuselage are low, and 3 mounted positions of the second compound wing at rear portion in the fuselage are high, and this design reduces the focus of aircraft, and the aircraft flight is more stable.

Referring to fig. 6 to 7, the structure of the bypass tilting device 4 may be various, and may be a gear link structure or a chain transmission structure. The duct tilting device 4 comprises a body bulkhead 41, a bearing seat 42, a duct rotating shaft 43 and a branch steering engine 44, wherein the body bulkhead 41 is vertically arranged inside the body 1, the bearing seat 42 is a bulge arranged on the body bulkhead 41, a hole for the duct rotating shaft 43 to pass through is formed in the bearing seat 42, the duct rotating shaft 43 consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the multi-mode duct 6, and two ends of the branch steering engine 44 are respectively hinged to the rocker arms of the body bulkhead 41 and the duct rotating shaft 43; the branch steering engine 44 extends and retracts during operation, and the branch steering engine 44 pushes the rocker arm to rotate the duct rotating shaft 43 so as to drive the multi-mode duct 6 to tilt.

The ducted propeller 5 comprises a plurality of ducted walls 51, a first fixing rod 52 and a fixed rotor 53, wherein the ducted walls 51 are symmetrically arranged on the first composite wing 2 and the second composite wing 3 respectively, the ducted walls 51 are communicated with the upper surface and the lower surface of the wing, and the fixed rotor 53 is arranged in the ducted walls 51 through the first fixing rod 52.

The multi-mode duct 6 comprises a duct shell 61, a connecting block 62, a second fixing rod 63 and a rotary rotor 64, the duct shell 61 is connected with the duct tilting device 4 through the connecting block 62, and the rotary rotor 64 is fixedly arranged inside the duct shell 61 through the second fixing rod 63.

The utility model discloses in, equal symmetry is provided with 4 duct screw 5 on first composite wing 2 and the second composite wing 3

And two forked winglets 21 are arranged at the wingtips of the two ends of the first composite wing 2. The bifurcated winglet 21 serves to reduce tip vortices in the first composite wing 2 and reduce noise generated by the wing.

And the wingtips at two ends of the second composite wing 3 are provided with arc winglets 31. The curved winglet 31 serves to reduce tip vortices of the second composite wing 3.

In addition, the present invention relates to a problem in which the components such as the undercarriage do not relate to a problem, and therefore, are not specified.

The working process comprises the following steps:

preparation before takeoff: and checking each part of the aircraft, and carrying out takeoff check.

Taking off: the aircraft starts, and duct propeller 5 and multi-mode duct 6 are all opened, and fixed rotor 53 rotates in order to produce the air current with rotating rotor 64 high-speed, and the duct verts device 4 and drives multi-mode duct 6 rotatory to the vertical downwards of multi-mode duct 6, and multi-mode duct 6 spun air current is vertical downwards this moment. The multi-mode duct 6 is in a vertical take-off and landing mode. The aircraft gradually ascends due to the lift provided by the ducted propellers 5 and the multi-mode duct 6.

Cruising: after the aircraft ascends to a certain height, the multi-mode duct 6 is driven by the duct tilting device 4 to rotate to the horizontal direction of the multi-mode duct 6, so that the airflow sprayed out by the multi-mode duct 6 is horizontal and faces the rear part of the aircraft body 1, and the multi-mode duct 6 is in a flat flight cruise mode. At this time, the fixed rotor 53 in the ducted propeller 5 can keep a high rotating speed, so as to provide a larger lift force for the aircraft, thereby facilitating the motion control of the aircraft. The fixed rotor 53 in the ducted propeller 5 can also perform low-speed rotation to stabilize the flow field on the surface of the first and second composite wings 2 and 3.

Landing: when the aircraft descends, the culvert verts the device 4 and drives the rotation of multi-mode culvert 6, and multi-mode culvert 6 is rotatory to vertical downwards from the horizontal direction, and the culvert verts the device 4 and switches to the VTOL mode from the level and flies the mode of cruising. Both the stationary rotor 53 and the rotary rotor 64 rotate at high speed to generate a vertically downward airflow, and as the aircraft altitude descends, the stationary rotor 53 and the rotary rotor 64 gradually decrease in speed until the aircraft descends to the ground.

The points to be explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, "upper," "lower," "left," and "right," and the like are only used to indicate a relative positional relationship, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed.

Secondly, in the utility model discloses in the embodiment drawings, only relate to the structure that involves with this disclosed embodiment, other structures can refer to common design, under the conflict-free condition, the utility model discloses same embodiment and different embodiments can the intercombination.

Finally, it is only above the preferred embodiment of the present invention, the protection scope of the present invention is not limited to the above embodiments, all belong to the technical scheme of the present invention under the thought all belong to the protection scope of the present invention.

It should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. A VTOL aircraft, its characterized in that: the aircraft comprises an aircraft body (1), wherein the aircraft body (1) is sequentially provided with a first composite wing (2), a second composite wing (3), a duct tilting device (4) and a tail wing (7) from the front part to the rear part; the tail wing (7) is a V-shaped component;

a plurality of ducted propellers (5) capable of providing lift force in the vertical direction are arranged on the first composite wing (2) and the second composite wing (3);

the multi-mode duct (6) is connected to the duct tilting device (4), the multi-mode duct (6) can perform tilting movement relative to the fuselage (1) so as to switch between a vertical take-off and landing mode and a level flight cruise mode, wherein in the vertical take-off and landing mode, the duct tilting device (4) drives the multi-mode duct (6) to tilt so that air flow sprayed by the multi-mode duct (6) vertically faces downwards; under the level flies the mode of cruising, duct tilting device (4) drive multi-mode duct (6) incline to make multi-mode duct (6) spun air current level and towards fuselage (1) rear portion.

2. The VTOL aerial vehicle of claim 1, wherein: the position of the second composite wing (3) installed on the fuselage (1) is higher than the position of the first composite wing (2) installed on the fuselage (1).

3. The VTOL aerial vehicle of claim 1, wherein: the duct tilting device (4) comprises a body partition frame (41), a bearing seat (42), a duct rotating shaft (43) and a branch steering gear (44), wherein the body partition frame (41) is vertically arranged inside the body (1), the bearing seat (42) is a protrusion arranged on the body partition frame (41), a hole for the duct rotating shaft (43) to pass through is formed in the bearing seat (42), the duct rotating shaft (43) consists of a rod piece and a rocker arm connected to one end of the rod piece, the other end of the rod piece is fixedly connected with the multi-mode duct (6), and two ends of the branch steering gear (44) are respectively hinged to the rocker arms of the body partition frame (41) and the duct rotating shaft (43); the branch steering engine (44) stretches during operation, and the branch steering engine (44) pushes the rocker arm to enable the duct rotating shaft (43) to rotate so as to drive the multi-mode duct (6) to tilt.

4. The VTOL aerial vehicle of claim 1, wherein: the ducted propeller (5) comprises a plurality of ducted walls (51), first fixing rods (52) and fixed rotors (53), the ducted walls (51) are symmetrically arranged on the first composite wing (2) and the second composite wing (3) respectively, the ducted walls (51) are communicated with the upper surface and the lower surface of the wing, and the fixed rotors (53) are arranged in the ducted walls (51) through the first fixing rods (52).

5. The VTOL aerial vehicle of claim 1, wherein: multi-mode duct (6) are including duct shell (61), connecting block (62), second dead lever (63) and rotate rotor (64), and duct shell (61) are connected with duct tilting device (4) through connecting block (62), and second dead lever (63) will rotate rotor (64) and fix the setting inside duct shell (61).

6. The vtol aerial vehicle of claim 1, wherein: the wingtips of the two ends of the first composite wing (2) are respectively provided with a forked winglet (21), and the wingtips of the two ends of the second composite wing (3) are respectively provided with a circular arc winglet (31).