CN110422313B - Aircraft with folding wings - Google Patents
Aircraft with folding wings Download PDFInfo
- Publication number
- CN110422313B CN110422313B CN201910814692.6A CN201910814692A CN110422313B CN 110422313 B CN110422313 B CN 110422313B CN 201910814692 A CN201910814692 A CN 201910814692A CN 110422313 B CN110422313 B CN 110422313B
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- Prior art keywords
- main
- auxiliary
- lever
- sliding block
- oil cylinder
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- 230000006978 adaptation Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses an aircraft with folding wings, which comprises a main body, wherein the tail part of the main body is provided with an aileron and is connected with a propeller; the two sides of the main body are respectively connected with a wing, the wings are provided with a first hinge point and a second hinge point, the wings are hinged with the main body through the first hinge point, the second hinge point of the wings is hinged with the tail end of the main lever, and the head end of the main lever is hinged with the main sliding block; the main sliding block slides along the length direction of the main body and drives the wing to swing around the first hinge point through the main lever. According to the aircraft with the folding wings, the wings on two sides of the main machine body can swing, so that the occupied area of the aircraft when the aircraft is idle can be reduced.
Description
Technical Field
The present invention relates to an aircraft, and more particularly to an aircraft having a folding wing.
Background
An aircraft is an aircraft that is capable of controlled flight within the atmosphere. Any aircraft must generate a lift greater than its own weight to fly. Aircraft are various in variety, and common main types are balloons, airships, airplanes, gliders, gyroplanes, helicopters and the like. The lift of an aircraft is according to the bernoulli principle: the greater the flow rate, the less the pressure; the smaller the flow rate, the greater the pressure. The wing of the aircraft is shaped so that the flow velocity below the wing is lower than the flow velocity above the wing, thereby generating a pressure difference above and below the wing and obtaining lift. Thus, the wings on both sides of the aircraft are the main components that provide lift. But an aircraft with a wing-like shape of an aircraft is parked on a floor or in storage, which requires more space.
Disclosure of Invention
The invention aims to: in order to overcome the defects in the prior art, the invention provides an aircraft with folding wings, so that the occupied space of the aircraft during parking is reduced.
The technical scheme is as follows: in order to achieve the above object, the aircraft with folding wings of the present invention comprises a main body, wherein an aileron is arranged at the tail of the main body, and a propeller is connected with the aileron; the two sides of the main body are respectively connected with a wing, the wings are provided with a first hinge point and a second hinge point, the wings are hinged with the main body through the first hinge point, the second hinge point of the wings is hinged with the tail end of the main lever, and the head end of the main lever is hinged with the main sliding block; the main sliding block slides along the length direction of the main body and drives the wing to swing around the first hinge point through the main lever.
Further, the auxiliary lever is hinged between the head end of the main lever and the tail end of the main lever, the head end of the auxiliary lever is hinged with the auxiliary sliding block, and the auxiliary sliding block slides along the sliding direction of the main sliding block.
Further, the hydraulic control system further comprises a main oil cylinder, wherein the fixed end of the main oil cylinder is connected to a main beam fixed on the main body, and the telescopic end of the main oil cylinder is connected with a main sliding block.
Further, a main chute is arranged on the main beam, and the main sliding block is slidably connected in the main chute.
Further, the device also comprises a secondary oil cylinder, wherein the fixed end of the secondary oil cylinder is connected to a main beam fixed on the main body, and the telescopic end of the secondary oil cylinder is connected with a secondary sliding block.
Further, an auxiliary sliding groove is formed in the main beam, and the auxiliary sliding block is connected in the auxiliary sliding groove in a sliding mode.
Further, a plurality of auxiliary connecting plates are arranged at the tail end of the auxiliary lever at intervals along the vertical direction, and auxiliary connecting holes are formed in the auxiliary connecting plates; a plurality of protruding main connecting plates are arranged between the head end and the tail end of the main lever at intervals along the vertical direction, and the main connecting plates are provided with main connecting holes; the main connecting plates and the auxiliary connecting plates are sequentially overlapped with each other, and the main connecting holes and the auxiliary connecting holes are coaxially opposite to each other.
Further, an arc-shaped auxiliary machine body is arranged above the front part of the main machine body, the head end of the auxiliary machine body and the main machine body are integrally formed, and the tail end of the auxiliary machine body extends backwards and is opposite to the main machine body from top to bottom.
The beneficial effects of the invention are as follows: an aircraft having a folding wing, the wings on both sides being retractable: the telescopic end of the main oil cylinder is extended, the telescopic end of the auxiliary oil cylinder is contracted, the main lever drives the wing to rotate around the first hinge point, the tail end of the wing is close to the aileron, the wing is accommodated, and the occupied area of the parked aircraft is shortened; the main oil cylinder is shortened, the auxiliary oil cylinder is extended, and the main lever drives the wing to rotate to extend to two sides, so that normal use of the aircraft is not affected.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of the connection structure of the main lever, the auxiliary lever, the main sliding block, the auxiliary sliding block, the main oil cylinder and the auxiliary oil cylinder;
fig. 3 is a schematic view of the connection of the main lever and the auxiliary lever according to the present invention.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
An aircraft with folding wings as described in figures 1 to 3, comprising a main fuselage 1, the tail of said main fuselage 1 being provided with ailerons 2 and being connected with propellers 18; the number of the ailerons 2 is 3, the ailerons 2 are respectively connected to the two sides and the upper part of the tail part of the main body 1, the three ailerons 2 are distributed in a triangle shape, and the propeller 18 is a three-wing propeller with a horizontal axis. The two sides of the main body 1 are respectively connected with a wing 3, the head end of the wing 3 is hinged with the main body 1, and the tail end of the wing 3 swings backwards to be close to the aileron 2, so that the wing is stored, and the occupied area of an aircraft during parking is reduced. The wing 3 should be provided with a landing plate 17. The bottom of the main body 1 is provided with a lifting frame 19.
Specifically, one end of the wing 3 is provided with two different hinge points, a first hinge point 4 and a second hinge point 5, respectively. The first hinge point 4 is hinged with the main body 1, the second hinge point 5 is hinged with the tail end of the main lever 6, and the head end of the main lever 6 is hinged with the main sliding block 7; the main sliding block 7 slides along the length direction of the main body 1, and drives the wing 3 to swing around the first hinge point 4 through the main lever 6. The main slider 7 is connected with the telescopic end of the main oil cylinder 10, and the fixed end of the main oil cylinder 10 is fixedly connected to the main beam of the main machine body 1. In order to effectively control the motion track of the main sliding block 7 and reduce the shaking of the main lever 6, a main sliding groove is arranged on the main beam 1 along the length direction of the main body, so that the main sliding block 7 slides along the main sliding groove. The auxiliary lever 8 is also hinged between the head end and the tail end of the main lever 6, and the other end of the auxiliary lever 8 is hinged with the auxiliary sliding block 9. The auxiliary slide block 9 also slides along the length direction of the main body 1, and the sliding track of the main slide block and the sliding track of the auxiliary slide block 9 are the same straight line. The auxiliary sliding block 9 is connected to the telescopic end of the auxiliary oil cylinder 11, and the fixed end of the auxiliary oil cylinder 11 is connected to the main beam. Similarly, in order to ensure the sliding track of the auxiliary sliding block 9 and reduce the shake of the auxiliary lever, an auxiliary sliding groove is also arranged on the main beam, so that the auxiliary sliding block 9 slides along the auxiliary sliding groove.
A plurality of auxiliary connecting plates 12 are arranged at the tail end of the auxiliary lever 8 at intervals along the vertical direction, and auxiliary connecting holes 13 are formed in the auxiliary connecting plates 12; a plurality of protruding main connecting plates 14 are arranged between the head end and the tail end of the main lever 6 at intervals along the vertical direction, and the main connecting plates 14 are provided with main connecting holes 15; the main connecting plates 14 and the auxiliary connecting plates 12 are sequentially overlapped with each other, and the main connecting holes 15 and the auxiliary connecting holes 13 are coaxially opposite.
An arc-shaped auxiliary body 16 is arranged above the front part of the main body 1, the head end of the auxiliary body 16 is integrally formed with the main body 1, and the tail end of the auxiliary body 16 extends backwards and is opposite to the main body 1 up and down.
The specific storage method of the wing comprises the following steps: when the aircraft needs to be stored, the main oil cylinder is lengthened, the auxiliary oil cylinder is shortened, the main lever rotates along the hinge point of the main sliding block, and meanwhile, the wing is driven to rotate around the first hinge point, so that the tail end of the wing is close to the aileron, and the storage is completed; when the aircraft needs to take off, the main oil cylinder is shortened, the auxiliary oil cylinder grows, the main lever rotates along the hinge point with the main sliding block, and meanwhile, the wing is driven to rotate around the first hinge point, so that the tail end of the wing is far away from the aileron, and the extension is completed.
The foregoing is only a preferred embodiment of the invention, it being noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (2)
1. An aircraft having a folding wing, characterized by: the aircraft comprises a main body (1), wherein an aileron (2) is arranged at the tail part of the main body (1) and is connected with a propeller (18); the two sides of the main body (1) are respectively connected with a wing (3), the wings (3) are provided with a first hinge point (4) and a second hinge point (5), the wings (3) are hinged with the main body (1) through the first hinge point (4), the second hinge point (5) of the wings (3) is hinged with the tail end of a main lever (6), and the head end of the main lever (6) is hinged with a main sliding block (7); the main sliding block (7) slides along the length direction of the main body (1) and drives the wing (3) to swing around the first hinge point (4) through the main lever (6);
The auxiliary lever (8) is hinged between the head end of the main lever (6) and the tail end of the main lever (6), the head end of the auxiliary lever (8) is hinged with the auxiliary sliding block (9), and the auxiliary sliding block (9) slides along the sliding direction of the main sliding block (7);
The hydraulic control system further comprises a main oil cylinder (10), wherein the fixed end of the main oil cylinder (10) is connected to a main beam fixed on the main body (1), and the telescopic end of the main oil cylinder (10) is connected with a main sliding block (7);
the main beam is provided with a main chute, and the main sliding block (7) is connected in the main chute in a sliding way;
the auxiliary oil cylinder (11) is characterized by also comprising an auxiliary oil cylinder (11), wherein the fixed end of the auxiliary oil cylinder (11) is connected to a main beam fixed on the main body (1), and the telescopic end of the auxiliary oil cylinder (11) is connected with an auxiliary sliding block (9);
the main beam is provided with an auxiliary chute, and the auxiliary sliding block (9) is connected in the auxiliary chute in a sliding way;
A plurality of auxiliary connecting plates (12) are arranged at the tail end of the auxiliary lever (8) at intervals along the vertical direction, and auxiliary connecting holes (13) are formed in the auxiliary connecting plates (12); a plurality of protruding main connecting plates (14) are arranged between the head end and the tail end of the main lever (6) at intervals along the vertical direction, and the main connecting plates (14) are provided with main connecting holes (15); the main connecting plates (14) and the auxiliary connecting plates (12) are sequentially overlapped with each other, and the main connecting holes (15) and the auxiliary connecting holes (13) are coaxially opposite.
2. An aircraft with a folding wing according to claim 1, characterized in that: the auxiliary machine body (16) is arranged above the front part of the main machine body (1), the head end of the auxiliary machine body (16) and the main machine body (1) are integrally formed, and the tail end of the auxiliary machine body (16) extends backwards and is opposite to the main machine body (1) up and down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910814692.6A CN110422313B (en) | 2019-08-30 | 2019-08-30 | Aircraft with folding wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910814692.6A CN110422313B (en) | 2019-08-30 | 2019-08-30 | Aircraft with folding wings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110422313A CN110422313A (en) | 2019-11-08 |
| CN110422313B true CN110422313B (en) | 2024-07-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910814692.6A Active CN110422313B (en) | 2019-08-30 | 2019-08-30 | Aircraft with folding wings |
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| Country | Link |
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| CN (1) | CN110422313B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111169620B (en) * | 2020-01-14 | 2020-11-24 | 浙江大学 | Telescopic wing mechanism with slotted flap and continuously variable wingspan |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101767647A (en) * | 2010-03-02 | 2010-07-07 | 北京航空航天大学 | Self-locking 90-degree full-wing variable sweepback transmission mechanism |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
| ES2289932B1 (en) * | 2006-07-03 | 2009-03-01 | INSTITUTO NACIONAL DE TECNICA AEROESPACIAL "ESTEBAN TERRADAS" | AIRCRAFT WITH CONVERTIBLE FLIGHT SYSTEM. |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| CN104176237B (en) * | 2014-07-25 | 2016-05-18 | 哈尔滨工业大学深圳研究生院 | Deformable wing installation and apply its aircraft |
| CN105923158B (en) * | 2016-04-23 | 2018-01-05 | 西安京东天鸿科技有限公司 | A kind of municipal afforestation folding wings unmanned plane |
| CN106114835A (en) * | 2016-06-29 | 2016-11-16 | 南京航空航天大学 | A kind of compound un-manned aerial helicopter |
| WO2019125198A1 (en) * | 2017-12-19 | 2019-06-27 | Валерий Туркубеевич ПЧЕНТЛЕШЕВ | Aircraft |
| CN108190003B (en) * | 2017-12-28 | 2022-07-15 | 陕西中科博亿电子科技有限公司 | Unmanned aerial vehicle with buffer gear |
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2019
- 2019-08-30 CN CN201910814692.6A patent/CN110422313B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101767647A (en) * | 2010-03-02 | 2010-07-07 | 北京航空航天大学 | Self-locking 90-degree full-wing variable sweepback transmission mechanism |
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| Publication number | Publication date |
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| CN110422313A (en) | 2019-11-08 |
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