CN218786082U

CN218786082U - Modularized wing aircraft

Info

Publication number: CN218786082U
Application number: CN202223111070.3U
Authority: CN
Inventors: 许兴; 李治宏; 邴富强
Original assignee: Xiamen Tengxi Aviation Technology Co ltd
Current assignee: Xiamen Tengxi Aviation Technology Co ltd
Priority date: 2022-11-04
Filing date: 2022-11-04
Publication date: 2023-04-04
Anticipated expiration: 2032-11-04

Abstract

The utility model relates to a modularized wing aircraft, which comprises an aircraft body, wherein composite wing modules which can be disassembled and arranged extend from two sides of the aircraft body, each composite wing module comprises a wing main body and a duct arranged in the middle of the wing main body, the wing main body is a rectangular component with a wing-shaped section, connecting mechanisms are arranged on the left side and the right side of the wing main body, and the aircraft body and the other composite wing module are selected to be connected through the connecting mechanisms; the duct is communicated with the upper wing surface and the lower wing surface of the wing main body, and a composite power module capable of providing lift force is arranged in the duct. The utility model discloses set up the power pack of aircraft in the wing of module, make wing subassembly and power component highly combine, promote the degree of integrating of aircraft. The modularized wing assembly is convenient for quickly adjusting the flight performance of the aircraft, and when the performance requirement of the aircraft needs to be adjusted, only the corresponding composite wing modules need to be assembled according to requirements.

Description

Modularized wing aircraft

Technical Field

The utility model relates to a fixed wing aircraft technical field, especially a modularization wing aircraft.

Background

Wings are important components of fixed-wing aircraft. In previous designs, the wings provided lift to the aircraft primarily during cruise flight of the aircraft.

With the continuous progress of science and technology, the aircrafts with various functions are more and more. In order to meet the design of aircrafts with different functions, engineers propose various detachable and combined aircraft wings.

The chinese patent with application number "CN201821172033.4" proposes a quick release wing and unmanned aerial vehicle, which uses a plug-in structure to detachably combine a part of wings with another fixed wing.

The Chinese patent with the application number of CN201821783870.0 provides an unmanned aerial vehicle modular wing, and a plurality of wing sub-modules are connected together through a plurality of groups of module interfaces with the same two sides of the modular wing.

It can be seen that the modular wing itself has the advantage of quickly adjusting the flight performance of the aircraft. However, these modular wings can only provide lift when the aircraft is cruising and flying, and have a single function.

SUMMERY OF THE UTILITY MODEL

In order to solve the problem, the utility model aims at providing a modularization wing aircraft, the modularization degree is high.

The embodiment of the utility model provides an in adopt following scheme to realize: a modularized wing aircraft comprises an airframe, composite wing modules which are detachably arranged extend from two sides of the airframe,

the composite wing module comprises a wing main body and a duct arranged in the middle of the wing main body, the wing main body is a rectangular component with a wing-shaped section, the left side and the right side of the wing main body are both provided with a connecting mechanism, and one of the connecting mechanisms is selected to connect a fuselage and the other composite wing module;

the duct is communicated with the upper wing surface and the lower wing surface of the wing main body, and a composite power module capable of providing lift force is arranged in the duct.

Preferably, the machine body comprises cabin partition frames and connecting rods, the cabin partition frames are arranged in parallel, and the connecting rods penetrate through the cabin partition frames and fix the cabin partition frames;

and side mounting plates for mounting the composite wing modules are further arranged on two sides of the cabin partition frame and are connected with the cabin partition frame.

Preferably, the machine body is further provided with an extension mounting frame, and the side mounting plate is connected with the cabin partition plate frame through the extension mounting frame; the extension mounting frame comprises a front rod, a rear rod and a reinforcing rod, the front rod and the rear rod are respectively arranged on two adjacent cabin partition frames, a plurality of holes for installing the cabin partition frames are formed in the front rod and the rear rod, and the reinforcing rod is connected to the middle of the front rod and the middle of the rear rod.

Preferably, hole sites for mounting the front rod and the rear rod are formed in the upper portion, the middle portion and the lower portion of the cabin partition plate frame.

Preferably, the wing main body comprises side skeletons, inner trusses, a duct frame and a skin, wherein the inner trusses are erected between the two side skeletons, the duct frame is arranged between the inner trusses and the two side skeletons, the duct frame is an annular component for the internal composite power module, and the skin is laid inwards along the two side skeletons, is arranged outside the inner trusses and is attached to the inner side of the duct frame in a surrounding manner.

Preferably, the front side and the rear side of the side frame are both provided with a boss, and a mounting hole penetrating through the boss and the side frame is horizontally arranged in the boss; the connecting mechanism is composed of the bosses, and two adjacent composite wing modules are installed through inserting pins in the installation holes.

Preferably, the composite power module is a lift fan module, the lift fan module comprises a cross mounting frame, a lift fan and a first electronic speed regulator, the cross mounting frame is erected in the duct, the lift fan is mounted in the middle of the cross mounting frame, the first electronic speed regulator is arranged inside the wing main body, and the first electronic speed regulator is electrically connected with the lift fan.

Preferably, the composite power module is the tilting power module, the tilting power module includes tilting mounting bracket, power fan, tilting module, control panel and second electronic speed regulator, the tilting mounting bracket can be erected in the duct through the tilting module with tilting, the power fan is installed on the tilting mounting bracket, and control panel and second electronic speed regulator set up inside the wing main body, and power fan is connected to second electronic speed regulator electricity, and the tilting module is connected to the control panel electricity.

Preferably, the two sides of the side frame are provided with line openings for the connection wire harness to pass through.

Preferably, at least two composite wing modules are arranged on two sides of the fuselage.

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

the utility model discloses set up the power pack of aircraft in the wing of module, make wing subassembly and power component highly combine, promote the degree of integrating of aircraft. The modularized wing assembly is convenient for quickly adjusting the flight performance of the aircraft, and when the performance requirement of the aircraft needs to be adjusted, only the corresponding composite wing modules need to be assembled according to requirements.

The utility model discloses a set up the installation hole site of a plurality of heights on the inside skeleton of fuselage, supply to extend the front mast and the back pole installation of mounting bracket, realize the structure of last single wing, well single wing and lower single wing of aircraft in proper order to can switch over the aircraft structure fast in several kinds of designs.

In order to improve the performance and the safety of the aircraft, at least two composite wing modules are arranged on two sides of the aircraft body.

Drawings

Fig. 1 is a first perspective view of the present invention;

fig. 2 is a first perspective view of the composite wing module of the present invention;

fig. 3 is a first internal structure diagram of the composite wing module of the present invention;

fig. 4 is a second perspective view of the composite wing module of the present invention;

fig. 5 is a second internal structure diagram of the composite wing module of the present invention;

FIG. 6 is an internal structure view of the body of the present invention;

fig. 7 is a first connecting structure of the fuselage and the composite wing module of the invention;

fig. 8 is a second drawing of the connection structure of the fuselage and the composite wing module of the present invention;

fig. 9 is a third diagram of the connection structure of the fuselage and the composite wing module of the present invention;

fig. 10 is a second perspective view of the present invention;

fig. 11 is a third perspective view of the present invention.

Description of reference numerals: the aircraft comprises a fuselage-1, a composite wing module-2, a wing body-3, a duct-4, a composite power module-40, a connecting mechanism-5, a cabin partition frame-11, a connecting rod-12, a side mounting plate-13, an extension mounting frame-6, a front rod-61, a rear rod-62, a reinforcing rod-63, a side skeleton-21, an inner truss-22, a duct frame-23, a skin-24, a boss-25, a mounting hole-26, a line opening-27, a lift fan module-7, a cross mounting frame-71, a lift fan-72, a first electronic speed regulator-73, a tilting rotating force module-8, a tilting mounting frame-81, a power fan-82, a tilting module-83, a control panel-84 and a second electronic speed regulator-85.

Detailed Description

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

Referring to fig. 1 to 11, a modular wing aircraft comprises a fuselage 1, composite wing modules 2 extending from two sides of the fuselage 1,

the composite wing module 2 comprises a wing main body 3 and a duct 4 arranged in the middle of the wing main body 3, the wing main body 3 is a rectangular component with a wing-shaped section, the left side and the right side of the wing main body 3 are both provided with connecting mechanisms 5, and one of the connecting mechanisms 5 is selected to be connected with the fuselage 1 and the other composite wing module 2;

the duct 4 is communicated with the upper wing surface and the lower wing surface of the wing main body 3, and a composite power module 40 capable of providing lift force is arranged in the duct 4.

The utility model discloses set up the power pack of aircraft in the wing of module, make wing subassembly and power component highly combine, promote the degree of integrating of aircraft. The modularized wing assembly is convenient for quickly adjusting the flight performance of the aircraft, and when the performance requirement of the aircraft needs to be adjusted, only the corresponding composite wing modules 2 need to be assembled as required. The section of the wing main body 3 is a wing airfoil, the shape of the wing airfoil is the shape of a wing generating lift force for an aircraft, and the wing is generally in the shape of an airfoil with a curved upper wing surface and a straight lower wing surface.

The aircraft body 1 comprises cabin partition frames 11 and connecting rods 12, wherein the cabin partition frames 11 are arranged in parallel, and the connecting rods 12 penetrate through the cabin partition frames 11 and fix the cabin partition frames 11;

and side mounting plates 13 for mounting the composite wing modules 2 are further arranged on two sides of the cabin partition frame 11, and the side mounting plates 13 are connected with the cabin partition frame 11. The cabin bulkhead 11 and the connecting rods 12 are arranged in the aircraft fuselage 1 in order to further increase the modularity of the aircraft.

The aircraft body 1 is also provided with an extension mounting frame 6, and a side mounting plate 13 is connected with the cabin partition plate frame 11 through the extension mounting frame 6; the extension mounting frame 6 comprises a front rod 61, a rear rod 62 and a reinforcing rod 63, the front rod 61 and the rear rod 62 are respectively arranged on two adjacent cabin partition frames 11, a plurality of holes for mounting the cabin partition frames 11 are formed in the front rod 61 and the rear rod 62, and the reinforcing rod 63 is connected to the middle portions of the front rod 61 and the rear rod 62.

The extension mounting frame 6 is used for erecting the composite wing module 2 which is originally directly arranged on the fuselage 1 outside the fuselage 1, and the fuselage 1 is connected through the extension mounting frame 6, so that the steps of detaching the composite wing module 2 from the fuselage 1 are simplified. Because, when the composite wing module 2 is directly connected with the fuselage 1, the fuselage 1 needs to disassemble the shell on the fuselage and embed the composite wing module 2 on the fuselage 1; and through setting up extension mounting bracket 6, it is little to extend mounting bracket 6 and dismantle the number of times, and composite wing module 2 is direct to be connected with extension mounting bracket 6.

Hole sites for installing the front rod 61 and the rear rod 62 are formed in the upper portion, the middle portion and the lower portion of the cabin partition plate frame 11.

The utility model discloses a set up the installation hole site of a plurality of heights on 1 inside skeleton of fuselage, supply to extend the installation of front mast 61 and back pole 62 of mounting bracket 6, realize the structure of the last single wing of aircraft, well single wing and lower single wing in proper order to can switch over the aircraft structure fast in several kinds of designs. As shown in fig. 11, the aircraft now adopts a lower single wing configuration.

The wing main body 3 comprises side skeletons 21, inner trusses 22, duct frames 23 and skins 24, wherein the inner trusses 22 are erected between the two side skeletons 21, the duct frames 23 are arranged between the inner trusses 22 and the two side skeletons 21, the duct frames 23 are annular members for internally providing the composite power modules 40, and the skins 24 are inwards laid on the outer parts of the inner trusses 22 along the two side skeletons 21 and are attached to the inner sides of the duct frames 23 in a surrounding manner.

Bosses 25 are arranged on the front side and the rear side of the side frame 21, and mounting holes 26 penetrating through the bosses 25 and the side frame 21 are horizontally arranged in the bosses 25; the connecting mechanism 4 is formed by the bosses 25, and two adjacent composite wing modules 2 are installed through inserting pins into the installation holes 26.

The combined power module 40 is a lift fan module 7, the lift fan module 7 comprises a cross mounting frame 71, a lift fan 72 and a first electronic governor 73, the cross mounting frame 71 is erected in the duct 4, the lift fan 72 is mounted in the middle of the cross mounting frame 71, the first electronic governor 73 is arranged inside the wing main body 3, and the first electronic governor 73 is electrically connected with the lift fan 72. In this case, the main function of the lift fan module 7 is to provide the aircraft with lift for taking off and landing and hovering, and the lift fan module 7 may also provide partial lift when the aircraft is cruising.

Composite power module 40 is tilting power module 8, tilting power module 8 includes tilting mounting bracket 81, power fan 82, tilting module 83, control panel 84 and second electronic governor 85, tilting mounting bracket 81 can erect in duct 4 through tilting module 83 tilting, power fan 82 installs on tilting mounting bracket 81, and control panel 84 and second electronic governor 85 set up inside wing main body 3, and power fan 82 is connected to second electronic governor 85 electricity, and control panel 84 electricity is connected tilting module 83. The tilting power module 8 provides lift force at various angles through the tilting module 83, when the tilting module 83 is not tilted to the tilting mounting frame 81, the tilting mounting frame 81 is in a horizontal position, and the power fan 82 arranged on the tilting mounting frame 81 provides lift force for the aircraft; when the tilt module 83 rotates the tilt mount 81 90 degrees to the wing back side, the power fan 82 provided on the tilt mount 81 provides a lift force for the aircraft that is horizontal backward, and more specifically, this lift force is thrust. The powered fan 82 provides both thrust and lift to the aircraft between 0 and 90 degrees when the tilt module 83 tilts the tilt mount 81 to the rear of the wing.

The hybrid module 40 may be designed as a lift fan module 7 and a tiltable power module 8, which may provide lift and thrust for the aircraft. In addition, the hybrid power module 40 can be further designed in a differentiated manner to be designed into various devices with different structures for providing power for the aircraft, so that the flying mode of the aircraft is increased.

Two sides of the side frame 21 are provided with a line opening 27 for the connection wire harness to pass through. The utility model provides an inside pencil of compound wing module 2 can adopt series connection or parallel mode to be connected to the inside avionics equipment of fuselage 1.

At least two composite wing modules 2 are arranged on two sides of the machine body 1.

When the two sides of the aircraft fuselage 1 are respectively provided with the tiltable power module 8, the aircraft can realize vertical take-off and landing and cruise with flying, but in order to further improve the performance and the safety of the aircraft, the two sides of the aircraft fuselage 1 are respectively provided with at least two composite wing modules 2. The safety redundancy degree formed by the four composite wing modules 2 is high. When the flight force of the aircraft is further improved, three composite wing modules 2 can be arranged on two sides of the aircraft body 1.

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," "connecting," and "connecting" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be directly connected, and "upper," "lower," "left," and "right" are used only to indicate a relative positional relationship, and when an absolute position of an object to be described is changed, the relative positional relationship may be changed.

Secondly, the method comprises the following steps: the utility model discloses in the embodiment drawing, only involve 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.

Claims

1. A modular wing aircraft comprising a fuselage (1), characterized in that: the two sides of the machine body (1) are respectively extended with a detachable composite wing module (2),

the composite wing module (2) comprises a wing main body (3) and a duct (4) arranged in the middle of the wing main body (3), the wing main body (3) is a rectangular component with a wing section, the left side and the right side of the wing main body (3) are respectively provided with a connecting mechanism (5), and one of the left side and the right side of the wing main body (3) is connected with the fuselage (1) and the other composite wing module (2) through the connecting mechanism (5);

the duct (4) is communicated with the upper wing surface and the lower wing surface of the wing main body (3), and a composite power module (40) capable of providing lift force is arranged in the duct (4).

2. A modular wing aircraft according to claim 1, wherein: the aircraft body (1) comprises cabin partition frames (11) and connecting rods (12), the cabin partition frames (11) are arranged in parallel, and the connecting rods (12) penetrate through the cabin partition frames (11) and fix the cabin partition frames (11);

and side mounting plates (13) for mounting the composite wing modules (2) are further arranged on two sides of the cabin partition frame (11), and the side mounting plates (13) are connected with the cabin partition frame (11).

3. A modular wing aircraft according to claim 2, wherein: the aircraft body (1) is also provided with an extension mounting rack (6), and a side mounting plate (13) is connected with the cabin partition plate rack (11) through the extension mounting rack (6); extend mounting bracket (6) and include preceding pole (61), back pole (62) and stiffener (63), preceding pole (61) and back pole (62) set up respectively on two adjacent cabin septum shelves (11), all set up a plurality of holes of installing with cabin septum shelf (11) on preceding pole (61) and back pole (62), stiffener (63) are connected in the middle part of preceding pole (61) and back pole (62).

4. A modular wing aircraft according to claim 3, wherein: hole sites for installing a front rod (61) and a rear rod (62) are formed in the upper portion, the middle portion and the lower portion of the cabin partition frame (11).

5. A modular wing aircraft according to claim 1, wherein: wing main part (3) include side skeleton (21), inner truss (22), duct frame (23) and skin (24), and several inner truss (22) erect between two side skeleton (21), and between inner truss (22) and two side skeleton (21) duct frame (23) set up, and duct frame (23) are the inside annular member that supplies compound power module (40) to set up, inside laying of inner truss (22) outside and surrounding the laminating to duct frame (23) are inboard along two side skeleton (21) in skin (24).

6. A modular wing aircraft according to claim 5, wherein: bosses (25) are arranged on the front side and the rear side of the side frame (21), and a mounting hole (26) penetrating through the bosses (25) and the side frame (21) is horizontally arranged in the bosses (25); the connecting mechanism (5) is composed of the bosses (25), and two adjacent composite wing modules (2) are installed through inserting pins into the installation holes (26).

7. A modular wing aircraft according to claim 1, wherein: the combined power module (40) is a lift fan module (7), the lift fan module (7) comprises a cross mounting frame (71), a lift fan (72) and a first electronic speed regulator (73), the cross mounting frame (71) is erected in the duct (4), the middle of the cross mounting frame (71) is used for installing the lift fan (72), the first electronic speed regulator (73) is arranged inside the wing main body (3), and the lift fan (72) is electrically connected with the first electronic speed regulator (73).

8. A modular wing aircraft according to claim 1, wherein: composite power module (40) is tilting power module (8), tilting power module (8) is including tilting mounting bracket (81), power fan (82), tilting module (83), control panel (84) and second electronic governor (85), tilting mounting bracket (81) erects in duct (4) through tilting module (83) tilting, power fan (82) are installed on tilting mounting bracket (81), and control panel (84) and second electronic governor (85) set up inside wing main body (3), and power fan (82) are connected to second electronic governor (85) electricity, and control panel (84) electricity is connected tilting module (83).

9. A modular wing aircraft according to claim 5, wherein: and two sides of the side frame (21) are provided with line openings (27) for connecting wiring harnesses to pass through.

10. A modular wing aircraft according to claim 1, wherein: the aircraft body (1) both sides all are provided with two at least compound wing modules (2).