CN115783234A - Modularized wing angle aircraft - Google Patents
Modularized wing angle aircraft Download PDFInfo
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- CN115783234A CN115783234A CN202211431937.5A CN202211431937A CN115783234A CN 115783234 A CN115783234 A CN 115783234A CN 202211431937 A CN202211431937 A CN 202211431937A CN 115783234 A CN115783234 A CN 115783234A
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- 239000002131 composite material Substances 0.000 claims abstract description 35
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 230000005611 electricity Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims 1
- 238000010030 laminating Methods 0.000 claims 1
- 238000005192 partition Methods 0.000 description 11
- 230000002787 reinforcement Effects 0.000 description 3
- 230000010354 integration Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention relates to a modularized wing angle aircraft, which comprises an aircraft body, wherein an extension mounting frame module is detachably arranged on the aircraft body, a plurality of composite wing modules are detachably arranged on two sides of the extension mounting frame module, each composite wing module comprises a wing main body and a duct arranged in the middle of the wing main body, connecting mechanisms are arranged on the left side and the right side of each wing main body, and one of the connecting mechanisms is used for connecting the extension mounting frame module 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; the extension mounting frame module comprises a front rod, a rear rod and a side mounting plate; the front rod and the rear rod are arranged on the machine body side by side in a front-back manner, two sides of the front rod and two sides of the rear rod are both connected with one side mounting plate, and the side mounting plates are connected with the connecting mechanism; along with the length of the front rod is longer than/equal to/shorter than that of the rear rod, a positive angle/zero degree/negative angle is formed between the side mounting plates arranged on the two sides of the front rod and the rear rod and the machine body.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a modularized wing angle 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 aircraft that the function is various is more and more. In order to meet the design of aircrafts with different functions, engineers propose various detachable and combined aircraft wings.
Chinese patent application No. CN201821172033.4, which proposes a quick-release wing and an unmanned aerial vehicle, wherein a plug-in structure is used to detachably combine a part of wings with another fixed wing.
Chinese patent application No. CN201821783870.0 proposes a modular wing for unmanned aerial vehicle, in which a plurality of wing sub-modules are connected together through "a plurality of groups of module interfaces" with the same two sides.
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 single function.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a modularized wing angle aircraft, which can be used for providing modularized aircraft with different wing angles.
The embodiment of the invention is realized by adopting the following scheme: a modularized wing angle aircraft comprises an airframe, an extension mounting frame module detachably arranged on the airframe, a plurality of composite wing modules detachably arranged on two sides of the extension mounting frame module,
the composite wing module comprises a wing main body and a duct arranged in the middle of the wing main body, wherein 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 the extending installation frame module 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;
the extension mounting frame module comprises a front rod, a rear rod and a side mounting plate; the front rod and the rear rod are arranged on the machine body side by side in a front-back manner, two sides of the front rod and two sides of the rear rod are both connected with one side mounting plate, and the side mounting plates are connected with the connecting mechanism; along with the length of the front rod is longer than/equal to/shorter than that of the rear rod, a positive angle/zero degree/negative angle is formed between the side mounting plates arranged on the two sides of the front rod and the rear rod and the machine body.
Preferably, the fuselage includes cabin partition rack and connecting rod, several cabin partition rack parallel arrangement, and several connecting rods are worn to establish on the cabin partition rack and are fixed the cabin partition rack, and two adjacent cabin partition racks in front and back supply preceding pole and back pole setting respectively.
Preferably, the extension mount further comprises a reinforcement bar connected at a mid-portion of the front and rear bars.
Preferably, the wing main part includes side skeleton, inner truss, duct frame and covering, and several inner trusses erect between two side skeletons, and between truss and two side skeletons, the duct frame is the inside annular member that supplies the setting of composite power module including the duct frame sets up, the covering inwards lays at the inner truss outside and encircles and laminate to the duct frame inboard along two side skeletons.
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 rack, a lift fan and a first electronic speed regulator, the cross mounting rack is erected in the duct, the lift fan is mounted in the middle of the cross mounting rack, 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.
Compared with the prior art, the modularized wing angle aircraft provided by the invention at least has the following technical effects:
the power unit of the airplane is arranged in the wings of the module, so that the wing assembly and the power assembly are highly combined, and the integration degree of the airplane is improved. 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 extension mounting frame module is convenient for mounting the composite wing module, and the length of the front rod and the length of the rear rod inside the extension mounting frame module are adjusted, so that the side mounting plates connected to the two sides of the front rod and the rear rod are at a certain angle with the body, and can be at a positive angle/zero angle/negative angle. At the moment, the wings of the aircraft are sweepback wings, straight wings and forward swept wings.
Drawings
FIG. 1 is a first perspective view of the present invention;
FIG. 2 is a second perspective view of the present invention;
FIG. 3 is a third perspective view of the present invention;
FIG. 4 is a perspective view of the airfoil of the present invention;
FIG. 5 is an internal structural view of the wing of the present invention;
FIG. 6 is an internal block diagram of the fuselage and wing installation of the present invention;
FIG. 7 is a perspective view of a composite wing module of the present invention employing a lift fan module;
FIG. 8 is a view of the internal structure of a composite wing module incorporating a lift fan module according to the present invention;
FIG. 9 is a perspective view of a composite wing module of the present invention employing a tiltable force module;
fig. 10 is an internal structural view of a composite wing module using a tiltable force module according to the present invention.
Description of reference numerals: the aircraft comprises a fuselage-1, an extension mounting frame module-6, a composite wing module-2, a wing body-3, a duct-4, a composite power module-40, a front rod-61, a rear rod-62, a side mounting plate-13, a cabin partition frame-11, a connecting rod-12, 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 lift fan module-7, a cross mounting frame-71, a lift fan-72, a first electronic speed regulator-73, a tilting power 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 invention is further described with reference to the following figures and specific embodiments.
Referring to fig. 1 to 10, a modularized wing angle aircraft comprises a fuselage 1, an extension mount module 6 detachably disposed on the fuselage 1, a plurality of composite wing modules 2 detachably disposed on two sides of the extension mount module 6,
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 left side and the right side of the wing main body 3 are both provided with a connecting mechanism 5, and one of the connecting mechanisms 5 is connected with an extension mounting frame module 6 and the other composite wing module 2;
the duct 4 is communicated with the upper airfoil surface and the lower airfoil surface of the wing main body 3, and a composite power module 40 capable of providing lift force is arranged in the duct 4; according to the invention, the power unit of the airplane is arranged in the wings of the module, so that the wing assembly and the power assembly are highly combined, and the integration degree of the aircraft is improved. 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 module 2 needs to be assembled according to the requirement.
The extension mount module 6 includes a front bar 61, a rear bar 62, and side mounting plates 13; the front rod 61 and the rear rod 62 are arranged on the machine body 1 side by side in a front-back manner, two sides of the front rod 61 and the rear rod 62 are both connected with one side mounting plate 13, and the side mounting plates 13 are connected with the connecting mechanism 5; the side mounting plates 13 disposed at both sides of the front and rear bars 61 and 62 form a positive/zero/negative angle with the body 1 as the length of the front bar 61 is longer/equal/shorter than the length of the rear bar 62. As shown in fig. 1 to 3, the extension mount module 6 facilitates installation of the composite wing module 2, and adjusts the lengths of the front rod 61 and the rear rod 62 inside the extension mount module 6 so that the side mounting plates 13 connected to both sides of the front rod 61 and the rear rod 62 form a positive angle/zero angle/negative angle with respect to the fuselage 1. At the moment, the wings of the aircraft are sweepback wings, straight wings and forward swept wings. The wings at different angles can exert different maneuvering performances of the aircraft.
Fuselage 1 includes cabin partition frame 11 and connecting rod 12, several cabin partition frame 11 parallel arrangement, and several connecting rod 12 wear to establish on cabin partition frame 11 and fixed cabin partition frame 11, and two adjacent cabin partition frames 11 around supply preceding pole 61 and back pole 62 setting respectively.
The extension mount 6 further comprises a reinforcement bar 63, the reinforcement bar 63 being connected at the middle of the front and rear bars 61, 62.
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.
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. The main function of the lift fan module 7 is to provide the aircraft with lift for taking off and landing and hovering of the aircraft, and the lift fan module 7 may also provide part of the lift when the aircraft is cruising.
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, the method comprises the following steps: in the drawings of the disclosed embodiments of the invention, only the structures related to the disclosed embodiments are referred to, other structures can refer to common designs, and the same embodiment and different embodiments of the invention can be combined mutually without conflict.
Finally, the above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention.
Claims (7)
1. A modular wing angle aircraft comprising a fuselage (1), characterized in that: an extension mounting rack module (6) is detachably arranged on the fuselage (1), a plurality of composite wing modules (2) are detachably arranged on two sides of the extension mounting rack module (6),
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), wherein 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 connecting mechanisms (5) is connected with the extension mounting frame module (6) 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 extension mount module (6) comprises a front bar (61), a rear bar (62) and a side mounting plate (13); the front rod (61) and the rear rod (62) are arranged on the machine body (1) side by side in a front-back mode, two sides of the front rod (61) and two sides of the rear rod (62) are connected with one side mounting plate (13), and the side mounting plates (13) are connected with the connecting mechanism (5); as the length of the front rod (61) is longer/equal/shorter than the length of the rear rod (62), the side mounting plates (13) arranged on both sides of the front rod (61) and the rear rod (62) form a positive angle/zero angle/negative angle with the body (1).
2. A modular wing angle flying machine according to claim 1, wherein: fuselage (1) includes cabin septum frame (11) and connecting rod (12), several cabin septum frame (11) parallel arrangement, and several connecting rod (12) are worn to establish on cabin septum frame (11) and fixed cabin septum frame (11), and two adjacent cabin septum frames (11) around supply preceding pole (61) and back pole (62) respectively and set up.
3. A modular wing angle flying machine according to claim 1, wherein: the extension mounting frame (6) further comprises a reinforcing rod (63), and the reinforcing rod (63) is connected to the middle portions of the front rod (61) and the rear rod (62).
4. A modular wing angle flying machine 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).
5. A modular wing angle flying machine according to claim 4, 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 (4) is composed of the bosses (25), and two adjacent composite wing modules (2) are installed through inserting pins into the installation holes (26).
6. A modular wing angle flying machine 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).
7. A modular wing angle flying machine 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 speed regulator (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 speed regulator (85) set up inside wing main part (3), and power fan (82) are connected to second electronic speed regulator (85) electricity, and control panel (84) electricity is connected tilting module (83).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211431937.5A CN115783234A (en) | 2022-11-04 | 2022-11-04 | Modularized wing angle aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211431937.5A CN115783234A (en) | 2022-11-04 | 2022-11-04 | Modularized wing angle aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115783234A true CN115783234A (en) | 2023-03-14 |
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ID=85438054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211431937.5A Pending CN115783234A (en) | 2022-11-04 | 2022-11-04 | Modularized wing angle aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115783234A (en) |
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2022
- 2022-11-04 CN CN202211431937.5A patent/CN115783234A/en active Pending
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| DD01 | Delivery of document by public notice |
Addressee: Zhu Yongxian Document name: Notification of Entering the Substantive Examination Phase of an Invention Patent Application |
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| DD01 | Delivery of document by public notice | ||
| CB02 | Change of applicant information |
Address after: Tengxi Airlines, 4th Floor, Building A, International Air Material Center, No. 6 Gaoqi South 7th Road, Xiamen City, Fujian Province, 361006 Applicant after: Xiamen tengxi Aviation Technology Co.,Ltd. Address before: Room 504, No. 7-11, East Building, Guangye, Torch Park, Huli District, Xiamen City, Fujian Province, 361006 Applicant before: Xiamen tengxi Aviation Technology Co.,Ltd. |
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