CN112009668A - Aircraft - Google Patents
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- Publication number
- CN112009668A CN112009668A CN202011126663.XA CN202011126663A CN112009668A CN 112009668 A CN112009668 A CN 112009668A CN 202011126663 A CN202011126663 A CN 202011126663A CN 112009668 A CN112009668 A CN 112009668A
- Authority
- CN
- China
- Prior art keywords
- wing
- folding
- aircraft
- fuselage
- supporting part
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
Abstract
The invention relates to an aircraft, belongs to the technical field of aircrafts, and aims to solve the technical problems that a driving device required by folding wings of the existing variable wing aircraft is large in output power and complex in structure and the technical problem that part of the variable wing aircraft cannot be folded in the air. The aircraft comprises a fuselage, folding wings and a supporting part, wherein the two sides of the fuselage are respectively provided with one folding wing, one end of the supporting part is hinged with the fuselage, and the other end of the supporting part is hinged with the folding wings; the folding wing folding device further comprises a driving device for driving the folding wing to fold. By adopting the structure, the supporting part is utilized to bear partial stress when the folding wing is folded, so that the energy required when the folding wing is deformed is reduced, and thus, a driving device with smaller output power can be selected for driving the folding wing to deform, so that the structure is simpler, the cost is reduced, and when the aircraft flies, the folding wing does not need to be locked by using a locking pin, so that the aircraft can be folded and deformed in the air, and the flexibility and the controllability are higher.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an aircraft.
Background
The wing-changing aircraft can better adapt to unstable airflow in flight by locally or integrally changing the shape of the aircraft, and can reduce flight energy consumption by means of gust, so that the aircraft is efficient, high-performance and real-time to adapt to various flight environments and task requirements, and the wing-changing aircraft can be used more and more along with the continuous improvement of the aircraft automatic control technology.
In the prior art, because the folding position of the folding wing of the wing-changing aircraft has large stress, a driving device capable of outputting large power is needed to drive the folding, such as a hydraulic driving device, so that the weight of the whole fuselage is heavy, the structure is more complex, the cost is higher, and when part of the wing-changing aircraft flies in the air, the unfolded wing is kept stable through a locking pin, so that the wing cannot be folded in the air, and the controllability and the flexibility of the wing in the air are low.
Disclosure of Invention
The invention provides an aircraft, which is used for solving the technical problems that a driving device required by folding of folding wings of the existing wing-changing aircraft is large in output power and complex in structure and the technical problem that part of the wing-changing aircraft cannot be folded in the air.
The invention is realized by the following technical scheme: an aircraft comprises a fuselage, folding wings and a supporting part, wherein the two sides of the fuselage are respectively provided with one folding wing, one end of the supporting part is hinged with the fuselage, and the other end of the supporting part is hinged with the folding wings;
the folding wing folding device further comprises a driving device for driving the folding wing to fold.
Further, in order to better realize the invention, the driving device is a steering engine.
Further, in order to better implement the present invention, the supporting portion is a rod-shaped structure or a sheet-shaped structure.
Further, in order to better implement the present invention, the folding wing includes an inner wing and an outer wing, the outer wing is rotatably mounted on one end of the inner wing, the other end of the inner wing is hinged to the fuselage, and the support portion is connected between the outer wing and the fuselage.
Further, in order to better realize the invention, the steering engine is arranged at the position where the inner side wing and the outer side wing are connected.
Furthermore, in order to better implement the invention, the folding aircraft further comprises a fixed wing, wherein the fixed wing is fixedly connected to the aircraft body, two ends of the fixed wing respectively extend out of two sides of the aircraft body, and inner side wings of the two folding wings are respectively hinged to two ends of the fixed wing.
Further, in order to better implement the present invention, an installation beam parallel to the fuselage is installed at one end of the fixed wing close to the inner side wing, and a propeller is installed on the installation beam.
Further, in order to better implement the present invention, the outer wing is provided with an installation beam parallel to the body, the installation beam is provided with a propeller, and a position where the installation beam is in contact with the outer wing is opposite to a position where the support portion is in contact with the outer wing.
Further, in order to better implement the invention, the folding wing comprises a first rod, a second rod, a propeller and a mounting beam parallel to the fuselage, the propeller is mounted on the mounting beam, the first rod and the second rod are hinged together to form a folding rod, one end of the first rod, far away from the second rod, is hinged on the fuselage, one end of the second rod, far away from the first rod, is hinged on the mounting beam, and one end of the supporting part, far away from the fuselage, is hinged on the mounting beam.
Further, in order to better implement the present invention, the number of the supporting parts of one side of the body is plural.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides an aircraft, which comprises a fuselage, folding wings, supporting parts and a driving device, wherein the two sides of the fuselage are respectively provided with the folding wings and the supporting parts, the folding wings are rotatably arranged on the fuselage, the two ends of the supporting parts are respectively hinged on the fuselage and the corresponding folding wings, the driving device is used for driving the folding wings to fold, by adopting the structure, the folding wings are folded and supported by the supporting parts, so that the supporting parts bear partial stress when the folding wings are folded and deformed, the energy required when the folding wings are deformed can be reduced, namely, the output power of the driving device can be reduced, in this way, the driving device with smaller output power can be selected to drive the folding wings to be deformed, the structure is simpler, the cost is reduced, and in the flying process, by virtue of the supporting function of the supporting parts, the folding wings are not required to be locked by locking pins, so that the aircraft provided by the invention can be folded and deformed in the air, and the flexibility and controllability of the aircraft in the air are further improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of an aircraft in embodiment 2 of the invention;
FIG. 2 is a schematic view of an aircraft according to embodiment 2 of the present invention from another perspective;
fig. 3 is a schematic structural view of an aircraft in embodiment 3 of the invention;
FIG. 4 is a schematic view of another perspective structure of the aircraft in embodiment 3 of the invention;
FIG. 5 is a schematic structural view of an aircraft in embodiment 4 of the invention;
FIG. 6 is a schematic structural view of an aircraft in embodiment 5 of the invention;
fig. 7 is a schematic structural view of an aircraft in embodiment 6 of the present invention.
In the figure:
1-a fuselage;
2-inner wing;
3-outer flank;
4-a first rod;
5-a second rod;
6-a support part;
7-a steering engine;
8-fixed wing;
9-mounting a beam;
10-propeller.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
Example 1:
the embodiment provides an aircraft, which is used for solving the technical problems that in the prior art, when a folding wing of a variable wing aircraft is folded and deformed, a driving device required by the folding wing is large in output power and complex in structure, and the technical problem that part of the variable wing aircraft cannot be folded in the air.
The aircraft comprises a fuselage 1, folding wings and a supporting part 6, wherein the two sides of the fuselage 1 are respectively provided with one folding wing and one supporting part 6. Specifically, the fuselage 1 is a main body of the aircraft, the folding wing is rotatably mounted on the fuselage 1 so that the folding wing can rotate in a vertical plane relative to the fuselage 1, and two ends of the support part 6 are respectively hinged to the folding wing and the fuselage 1, so that the support part 6 can support or fix a form formed by folding deformation or deformation of the folding wing.
The folding wing folding device further comprises a driving device, and the driving device is used for driving the folding wing to fold.
By adopting the structure, the folding wing is folded by using the supporting part 6, so that the supporting part 6 is utilized to bear partial stress when the folding wing is folded and deformed, the energy required when the folding wing is deformed can be reduced, namely, the output power of the driving device can be reduced, in this way, the driving device with smaller output power can be selected to drive the folding wing to deform, the structure is simpler, the cost is reduced, and in the flying process, the folding wing does not need to be locked by using a locking pin under the supporting action of the supporting part 6, so that the aircraft provided by the invention can be folded and deformed in the air, and the flexibility and the controllability of the aircraft in the air are improved.
As a best mode of the embodiment, the driving device in the embodiment is a steering engine 7, such as a type Futaba S3003 steering engine or a type RobotBase RB-150MG steering engine.
As a more preferable embodiment of the present embodiment, the supporting portion 6 in the present embodiment is a rod-shaped structure or a sheet-shaped structure, and when the supporting portion 6 is a sheet-shaped structure, the supporting portion 6 is a supporting wing.
Example 2:
this embodiment is a specific implementation manner of embodiment 1, and provides an aircraft in which the above-mentioned folding wing includes an inner side wing 2 and an outer side wing 3, the above-mentioned outer side wing 3 is hinged at one end of the inner side wing 2, that is, the outer side wing 3 is rotatably mounted at one end of the inner side wing 2, and the other end of the above-mentioned inner side wing 2 is hinged on the fuselage 1. At this time, the outer wing 3 is folded with respect to the inner wing 2 and the inner wing 2 is folded with respect to the fuselage 1 to form a flapping wing, and when the outer wing 3 is folded with respect to the inner wing 2 or the inner wing 2 is folded with respect to the fuselage 1, the folding wing is extended or retracted with respect to the fuselage, when extended, the folding wing is extended to form a wing, and when retracted, the folding wing is folded for portability.
In the present embodiment, the position where the support portion 6 contacts the fuselage 1 is defined as point a, the position where the inner wing 2 contacts the fuselage 1 is defined as point B, the point where the outer wing 3 contacts the inner wing 2 is defined as point C, and the point where the support portion 6 contacts the outer wing 3 is defined as point D. When folded, points A, B, C, D are located at the four vertices of a deformable quadrilateral. When unfolded, the points C and D are collinear, and at the moment, the points A, B, D are respectively positioned on three vertexes of a triangle, and the supporting part 6 supports the outer side wing 3.
In the deployed state, the stress at the points B and C is smaller, and therefore the drive device only needs to be provided as the steering gear 7. Specifically, the steering engine 7 may be set at any one of A, B, C, D points, and optimally, the steering engine 7 is set at point C to obtain better driving effect.
In the present embodiment, the sum of the distance between the points a and B and the distance between the points a and D is L1, and the sum of the distance between the points B and C and the distance between the points C and D is L2. As an embodiment of this embodiment, L1 — L2, the folding wing can be fully folded. As another embodiment of this embodiment, L1 ≠ L2, where the folding wings are capable of being partially folded.
Example 3:
as a more preferable embodiment of embodiment 2, the aircraft provided in this embodiment further includes a fixed wing 8, the fixed wing 8 is fixedly connected to the fuselage 1, and two ends of the fixed wing 8 respectively extend out of two sides of the fuselage 1, and most preferably, the fixed wing 8 is fixedly connected to the top of the fuselage 1 and is perpendicular to the fuselage 1. The inner side wings 2 of the folding wings at the two sides of the fuselage 1 are respectively hinged at the two ends of the fixed wing 8. With this structure, when the folding wing is unfolded, the distance between the end of the outer wing 3 and the fuselage 1 is larger.
Example 4:
in this embodiment, as a more preferable embodiment of embodiment 3, in this embodiment, an installation beam 9 is installed at one end of the fixed wing 8 close to the inner wing 2, the installation beam 9 is a bearing beam, the length direction of the installation beam 9 is parallel to the length direction of the fuselage 1, a propeller 10 is installed on the installation beam 9, that is, the propeller 10 is installed on the fixed wing 8 at the point B, so that the aircraft provided by this embodiment can realize vertical take-off and landing. The propeller 10 in this embodiment may be mounted on top of the mounting beam 9.
Of course, the propeller 10 in this embodiment may also be installed at the front end of the mounting beam 9, and in this case, the aircraft provided in this embodiment may be bilaterally balanced.
Example 5:
in this embodiment, as a more preferable mode of the above embodiment, in this embodiment, an attachment beam 9 parallel to the body 1 is attached to the outer wing 3, and a propeller 10 is attached to the attachment beam 9, specifically, a position where the attachment beam 9 contacts the outer wing 3 is directly opposite to a position where the support portion 6 contacts the outer wing 3, that is, the attachment beam 9 is attached to the outer wing 3 directly opposite to the position of the D point. At this time, the aircraft provided by the embodiment is a spiral wing aircraft, and by means of the supporting portion 6, more flexible folding deformation can be realized.
The propeller 10 in this embodiment may be mounted at the top or front end of the mounting beam 9.
Example 6:
this embodiment provides, as another implementation mode of the above embodiment, an aircraft folding wing comprising a first rod 4, a second rod 5, a propeller 10 and a mounting beam 9 parallel to the fuselage 1, wherein the propeller 10 is mounted on the mounting beam 9, the first rod 4 and the second rod 5 are hinged together to form a folding rod, one end of the first rod 4 away from the second rod 5 is hinged to the fuselage 1, one end of the second rod 5 away from the first rod 4 is hinged to the mounting beam 9, and one end of the support part 6 away from the fuselage 1 is hinged to the mounting beam 9. At this time, the aircraft provided in this embodiment is a spiral wing aircraft, the folding rod can draw the mounting beam 9, at this time, the steering engine 7 is disposed between the first rod 4 and the second rod 5, and when the first rod 4 is folded relative to the second rod 5, the mounting beam 9 can be easily moved closer to or away from the fuselage 1 by the support portion 6 to be folded. It is to be noted that the first bar 4 and the second bar 5 are straight bars, but the first bar 4 and the second bar 5 may also be plate-like structures.
The propeller 10 in this embodiment may be mounted at the top or front end of the mounting beam 9.
As a best mode of the present embodiment, the number of the supporting parts 6 on one side of the fuselage 1 in the present embodiment is plural, so that the folding and unfolding of the folding wing in the present embodiment can be made more smooth.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. An aircraft, characterized in that: the airplane comprises an airplane body, folding wings and a supporting part, wherein one folding wing is respectively arranged on each of two sides of the airplane body, one end of the supporting part is hinged with the airplane body, and the other end of the supporting part is hinged with the folding wings;
the folding wing folding device further comprises a driving device for driving the folding wing to fold.
2. The aircraft of claim 1, wherein: the driving device is a steering engine.
3. An aircraft according to claim 2, characterized in that: the supporting part is of a rod-shaped structure or a sheet-shaped structure.
4. An aircraft according to claim 3, characterized in that: the folding wing comprises an inner side wing and an outer side wing, the outer side wing is rotatably arranged at one end of the inner side wing, the other end of the inner side wing is hinged to the fuselage, and the supporting part is connected between the outer side wing and the fuselage.
5. The aircraft according to claim 4, characterized in that: the steering engine is installed in the position where the inner side wing and the outer side wing are connected.
6. The aircraft according to claim 5, characterized in that: the folding wing is characterized by further comprising fixed wings, wherein the fixed wings are fixedly connected to the body, two ends of each fixed wing extend out of two sides of the body respectively, and the inner side wings of the two folding wings are hinged to two ends of each fixed wing respectively.
7. The aircraft according to claim 6, characterized in that: the fixed wing is close to the one end of medial flank install with the parallel installation roof beam of fuselage, install the screw on the installation roof beam.
8. The aircraft according to any one of claims 4 to 6, wherein: the outer side wing is provided with an installation beam parallel to the body, the installation beam is provided with a propeller, and the position where the installation beam is connected with the outer side wing is just opposite to the position where the supporting part is connected with the outer side wing.
9. The aircraft according to any one of claims 1 to 3, characterized in that: folding wing include first pole, second pole, screw and with the parallel installation roof beam of fuselage, the screw is installed on the installation roof beam, first pole with the second pole articulates together and forms folding rod, first pole is kept away from the one end of second pole articulates on the fuselage, the second pole is kept away from the one end of first pole articulates on the installation roof beam, the supporting part is kept away from the one end of fuselage articulates on the installation roof beam.
10. The aircraft according to claim 9, characterized in that: the number of the supporting parts on one side of the machine body is multiple.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2019110587664 | 2019-11-01 | ||
| CN201911058766.4A CN110758716A (en) | 2019-11-01 | 2019-11-01 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112009668A true CN112009668A (en) | 2020-12-01 |
Family
ID=69335587
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911058766.4A Pending CN110758716A (en) | 2019-11-01 | 2019-11-01 | Aircraft |
| CN202011126663.XA Pending CN112009668A (en) | 2019-11-01 | 2020-10-20 | Aircraft |
| CN202022347057.2U Active CN212448044U (en) | 2019-11-01 | 2020-10-20 | Aircraft |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911058766.4A Pending CN110758716A (en) | 2019-11-01 | 2019-11-01 | Aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022347057.2U Active CN212448044U (en) | 2019-11-01 | 2020-10-20 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN110758716A (en) |
-
2019
- 2019-11-01 CN CN201911058766.4A patent/CN110758716A/en active Pending
-
2020
- 2020-10-20 CN CN202011126663.XA patent/CN112009668A/en active Pending
- 2020-10-20 CN CN202022347057.2U patent/CN212448044U/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN212448044U (en) | 2021-02-02 |
| CN110758716A (en) | 2020-02-07 |
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| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20210609 Address after: 730087 no.240, group 2, Xiaoheng road village, Qinchuan Town, Lanzhou New District, Lanzhou City, Gansu Province Applicant after: Lanzhou Shanhe Intelligent Technology Co.,Ltd. Address before: No. 888, South Tianfu Avenue, Huayang street, Tianfu New District, Chengdu, Sichuan 610000 Applicant before: Chengdu wingspan Technology Co.,Ltd. |