CN211223864U - Supersonic aircraft with folding wing - Google Patents
Supersonic aircraft with folding wing Download PDFInfo
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- CN211223864U CN211223864U CN201921562960.1U CN201921562960U CN211223864U CN 211223864 U CN211223864 U CN 211223864U CN 201921562960 U CN201921562960 U CN 201921562960U CN 211223864 U CN211223864 U CN 211223864U
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Abstract
The application belongs to the technical field of the aerodynamic layout design of supersonic aircraft, concretely relates to supersonic aircraft with folding wing, include: a central body; two inner wings with large sweep angle; each inner wing is correspondingly arranged on one side of the central machine body; two outer wings with a medium sweep angle; each outer wing is correspondingly arranged on the outer side of one inner wing and can rotate upwards relative to the inner wing, so that the outer wing and the inner wing have different angles.
Description
Technical Field
The application belongs to the technical field of aerodynamic layout design of supersonic aircraft, and particularly relates to a supersonic aircraft with folding wings.
Background
The prior supersonic aircraft mostly adopts a pneumatic layout with a fixed sweepback angle or a pneumatic layout with a variable sweepback angle, wherein the pneumatic layout with the variable sweepback angle is mostly provided with a large sweepback angle on the designed wings so as to reduce the supersonic wave resistance and meet the requirement of the aircraft for supersonic flight, but the large sweepback angle ensures that the lift-drag of the aircraft is low in a subsonic flight stage and the requirement of the aircraft in the subsonic flight stage is difficult to adapt; the wing of the aerodynamic layout with the variable sweep angle is changed into a large sweep angle state only when the aircraft is in a supersonic speed aircraft, and the change of the wing further worsens the problem of aerodynamic focus backward movement of the aircraft caused by the supersonic speed, brings extra trimming resistance and puts forward higher trimming requirements on the trimming capability of the empennage.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a supersonic aircraft having folding wings that overcomes or alleviates at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
a supersonic aircraft having a folding wing, comprising:
a central body;
two inner wings with large sweep angle; each inner wing is correspondingly arranged on one side of the central machine body;
two outer wings with a medium sweep angle; each outer wing is correspondingly arranged on the outer side of one inner wing and can rotate upwards relative to the inner wing, so that the outer wing and the inner wing have different angles.
According to at least one embodiment of the present application, the supersonic aircraft has an angle of 180 ° at a flight speed less than mach 0.9;
when the flight speed of the supersonic aircraft is in Mach 0.9-1.3, the angle is 150 degrees;
when the flight speed of the supersonic aircraft is at Mach 1.3-1.6, the angle is 120 degrees;
when the flight speed of the supersonic aircraft is greater than Mach 1.3-1.6, the angle is 90 degrees.
According to at least one embodiment of the application, the device further comprises two vertical tail wings which are oppositely arranged at the tail part of the central machine body; each vertical tail is inclined outward.
According to at least one embodiment of the application, an engine is arranged in the central body, which engine is located in a corresponding range between the two vertical stabilizers.
According to at least one embodiment of the application, the aircraft further comprises two horizontal tail wings, and each horizontal tail wing is correspondingly arranged on one side of the tail part of the central airframe.
According to at least one embodiment of the present application, the two horizontal rear wings and the two inner wings are in the same plane.
According to at least one embodiment of the application, the trailing edge of each outer wing is provided with an outer wing control surface.
According to at least one embodiment of the application, the wing structure further comprises two rotating shafts, wherein each rotating shaft is correspondingly arranged on the outer side of one inner wing;
each outer wing is correspondingly connected with one rotating shaft and can rotate upwards around the rotating shaft.
According to at least one embodiment of the application, the large sweep angle is located above 60 °.
In accordance with at least one embodiment of the present application, the medium sweep angle is within 40-50.
Drawings
FIG. 1 is a top view of a supersonic aircraft having folded wings provided in embodiments of the present application;
FIG. 2 is a side view of a supersonic aircraft having folded wings provided in embodiments of the present application;
FIG. 3 is an elevation view of a supersonic aircraft having a folding wing provided in embodiments of the present application;
wherein:
1-central body; 2-inner wing; 3-outer wing; 4-vertical tail; 5-horizontal tail wing; 6-rotating shaft.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 3.
A supersonic aircraft having a folding wing, comprising:
a central body 1;
two inner wings 2 having a large sweep angle; each inner wing 2 is correspondingly arranged on one side of the central machine body;
two outer wings 3 having a medium sweep angle; each outer wing 3 is disposed outside one inner wing 2 and can be rotated upward with respect to the inner wing 2 to have a different angle from the inner wing 2.
For the supersonic aircraft with the folding wings disclosed in the above embodiments, those skilled in the art can easily understand that the wings are composed of the inner wing 2 and the outer wing 3, and the inner wing 2 has a large sweep angle, and the outer wing 3 has a medium sweep angle, so as to form double sweep of the wings, thereby being capable of improving the aerodynamic profile of the supersonic aircraft, and considering the requirements of the supersonic aircraft in the subsonic flight stage and the supersonic flight stage.
In some alternative embodiments, the supersonic aircraft has an angle of 180 ° at a flight speed less than mach 0.9;
when the flight speed of the supersonic aircraft is in Mach 0.9-1.3, the angle is 150 degrees;
when the flight speed of the supersonic aircraft is at Mach 1.3-1.6, the angle is 120 degrees;
when the flight speed of the supersonic aircraft is greater than Mach 1.3-1.6, the angle is 90 degrees.
For the supersonic aircraft with the folding wings disclosed in the above embodiments, it is easily understood by those skilled in the art that an angle formed between upward rotation of the outer wing 3 relative to the inner wing 2 is related to a flight speed of the supersonic aircraft, and can be adjusted according to the flight speed of the supersonic aircraft, the faster the flight speed of the supersonic aircraft is, the larger the upward rotation angle of the outer wing 3 is adjusted, when the supersonic aircraft is flying at supersonic speed, a wing focus position moves backwards to reduce a vertical tail and a horizontal tail moment arm, and a larger rudder deflection angle is required when the aircraft is operated, thereby bringing larger trim resistance and lift loss of the whole aircraft, at this time, by upward rotation of the outer wing 3, the wing focus can be moved forwards to offset the wing focus backward movement amount, thereby effectively reducing the trim resistance and lift-drag ratio of the whole aircraft; in addition, when the supersonic aircraft flies at supersonic speed, the outer wing 3 rotates upwards to become a vertical tail, the area of the vertical stabilizer is increased, and the vertical stability during high-speed flight can be improved.
In some optional embodiments, the device further comprises two vertical tail wings 4 which are oppositely arranged at the tail part of the central body 1; each vertical rear wing 4 is inclined to the outside.
In some alternative embodiments, an engine is arranged in the central body 1, which engine is located in the corresponding range between the two vertical tails 4.
In some alternative embodiments, two horizontal rear wings 5 are further included, and each horizontal rear wing 5 is correspondingly disposed at one side of the tail of the central body 1.
In some alternative embodiments, the two horizontal rear wings 5 are in the same plane as the two inner wings 2.
In some alternative embodiments, the trailing edge of each outer wing 3 is provided with an outer wing control surface.
With respect to the supersonic aircraft with folded wings disclosed in the above embodiments, it is easily understood by those skilled in the art that the outer wing control surface provided at the trailing edge of the outer wing segment 3 can be used as a horizontal tail or vertical tail control surface after the outer wing segment 3 is rotated upwards, and can be used as a supplement to the tail control surface in flight control, so as to further reduce trim resistance.
In some optional embodiments, the wind turbine further comprises two rotating shafts 6, and each rotating shaft 6 is correspondingly arranged on the outer side of one inner wing 2;
each outer wing 3 is connected to a corresponding rotating shaft 6, and can rotate upwards around the rotating shaft 6.
In some alternative embodiments, the large sweep angle is above 60 °.
In some alternative embodiments, the medium sweep angle is within 40-50.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A supersonic aircraft having a folding wing, comprising:
a central body (1);
two inner wings (2) having a large sweep angle; each inner wing (2) is correspondingly arranged on one side of the central machine body;
two outer wings (3) having a medium sweep angle; each outer wing (3) is correspondingly arranged on the outer side of one inner wing (2) and can rotate upwards relative to the inner wing (2) so as to form different angles with the inner wing (2).
2. The supersonic aircraft of claim 1,
when the flight speed of the supersonic aircraft is less than Mach 0.9, the angle is 180 degrees;
when the flight speed of the supersonic aircraft is in Mach 0.9-1.3, the angle is 150 degrees;
when the flight speed of the supersonic aircraft is at Mach 1.3-1.6, the angle is 120 degrees;
the angle is 90 ° when the supersonic aircraft flight speed is greater than mach 1.3-1.6.
3. The supersonic aircraft of claim 2,
the two vertical tail wings (4) are oppositely arranged at the tail part of the central machine body (1); each of the vertical rear wings (4) is inclined outward.
4. The supersonic aircraft of claim 3,
an engine is arranged in the central body (1) and is positioned in a corresponding range between the two vertical tail wings (4).
5. The supersonic aircraft of claim 1,
the aircraft is characterized by further comprising two horizontal tail wings (5), wherein each horizontal tail wing (5) is correspondingly arranged on one side of the tail of the central airframe (1).
6. The supersonic aircraft of claim 5,
the two horizontal tail wings (5) and the two inner wings (2) are in the same plane.
7. The supersonic aircraft of claim 1,
the trailing edge of each outer wing (3) is provided with an outer wing control surface.
8. The supersonic aircraft of claim 1,
the wing structure also comprises two rotating shafts (6), wherein each rotating shaft (6) is correspondingly arranged on the outer side of one inner wing (2);
each outer wing (3) is correspondingly connected with one rotating shaft (6) and can rotate upwards around the rotating shaft (6).
9. The supersonic aircraft of claim 1,
the large sweep angle is above 60 °.
10. The supersonic aircraft of claim 1,
the medium sweep angle is within 40-50.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921562960.1U CN211223864U (en) | 2019-09-19 | 2019-09-19 | Supersonic aircraft with folding wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921562960.1U CN211223864U (en) | 2019-09-19 | 2019-09-19 | Supersonic aircraft with folding wing |
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| Publication Number | Publication Date |
|---|---|
| CN211223864U true CN211223864U (en) | 2020-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921562960.1U Active CN211223864U (en) | 2019-09-19 | 2019-09-19 | Supersonic aircraft with folding wing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
-
2019
- 2019-09-19 CN CN201921562960.1U patent/CN211223864U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
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