阅读说明：本技术 一种超音速飞机 (Supersonic aircraft ) 是由 李士途 马泽孟 艾俊强 于 2019-09-03 设计创作，主要内容包括：本申请属于超音速飞机气动外形设计技术领域,具体涉及一种超音速飞机,包括：中央体；两个内翼段,前缘具有大后掠角,其中,一个内翼段设置在中央体的一侧,另一内翼段设置在中央体的另一侧；两个外翼段,前缘具有中等后掠角,其中,一个外翼段设置在一个内翼段上,另一个外翼段设置在另一个内翼段上。(the application belongs to the technical field of the aerodynamic configuration design of supersonic aircraft, concretely relates to supersonic aircraft, include: a central body; two inner wing sections, the leading edge of which has a large sweep angle, wherein one inner wing section is arranged on one side of the central body, and the other inner wing section is arranged on the other side of the central body; two outer panels, the leading edge having a medium sweep, wherein one outer panel is disposed on one inner panel and the other outer panel is disposed on the other inner panel.)

1. a supersonic aircraft, comprising:

A central body (1);

Two inner wing sections (2) with a leading edge having a large sweep angle, wherein one of the inner wing sections (2) is arranged on one side of the central body (1) and the other inner wing section (2) is arranged on the other side of the central body (1);

Two outer wing segments (3) with a leading edge having a medium sweep, wherein one of the outer wing segments (3) is arranged on one of the inner wing segments (2) and the other outer wing segment (3) is arranged on the other inner wing segment (2).

2. the supersonic aircraft of claim 1,

The trailing edges of the two inner wing sections (2) have a small forward sweep angle.

3. The supersonic aircraft of claim 2,

The small forward sweep angle of the trailing edges of the two inner wing sections (2) is below 15 degrees.

4. the supersonic aircraft of claim 1,

The large sweep angle of the leading edges of the two inner wing sections (2) is more than 60 degrees.

5. the supersonic aircraft of claim 1,

The trailing edges of the two outer wing sections (3) have a small sweep angle.

6. The supersonic aircraft of claim 5,

the small sweep angle of the trailing edges of the two outer wing sections (3) is below 15 degrees.

7. the supersonic aircraft of claim 1,

The intermediate sweepback angle of the leading edges of the two outer wing sections (3) is within 40-50 degrees.

8. the supersonic aircraft of claim 1,

The central body (1) has a lift profile.

9. The supersonic aircraft of claim 1,

Each inner wing section (2) and the central body (1) are smoothly transited and fused into a whole.

Technical Field

The application belongs to the technical field of aerodynamic configuration design of supersonic aircrafts, and particularly relates to a supersonic aircraft.

Background

at present, the aerodynamic shape of the airplane is mostly heavier than supersonic flight of the airplane or subsonic flight of the airplane, and the supersonic flight and the subsonic flight of the airplane cannot be effectively considered. For example, the conventional layout of fuselage-wing-empennage is adopted by the prior aircraft, in order to realize the supersonic flight, the wing leading edge is designed to have a considerable sweep angle, and the very slender fuselage is designed to be adopted, and the aerodynamic profile layout of the supersonic aircraft has the following defects:

1) The large sweepback angle of the front edge of the wing leads to low efficiency of the airplane flying at subsonic speed and poor take-off and landing performance of the airplane;

2) The use of the effective inner space of the airplane is limited due to the narrow inner space of the slender fuselage;

3) The empennage needs to be designed in a matching mode to balance the moment of the airplane, so that the weight of the airplane is increased.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one 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 an arrow-like profile to overcome or mitigate at least one of the above-mentioned disadvantages.

The technical scheme of the application is as follows:

A supersonic aircraft comprising:

a central body;

Two inner wing sections, the leading edge of which has a large sweep angle, wherein one inner wing section is arranged on one side of the central body, and the other inner wing section is arranged on the other side of the central body;

Two outer panels, the leading edge having a medium sweep, wherein one outer panel is disposed on one inner panel and the other outer panel is disposed on the other inner panel.

according to at least one embodiment of the present application, the trailing edges of the two inner panels have a small forward sweep.

According to at least one embodiment of the application, the small sweep angle of the trailing edges of the two inner panels is below 15 °.

According to at least one embodiment of the application, the large sweep angle of the leading edges of the two inner panels is above 60 °.

According to at least one embodiment of the present application, the trailing edges of the two outer wing sections have a small sweep angle.

according to at least one embodiment of the application, the small sweep angle of the trailing edges of the two outer panels is below 15 °.

According to at least one embodiment of the present application, the intermediate sweep angle of the leading edges of the two outer panels is within 40-50.

According to at least one embodiment of the present application, the central body has a lift profile.

according to at least one embodiment of the present application, each inner wing section blends into a smooth transition with the central body.

drawings

FIG. 1 is a schematic illustration of a configuration of a supersonic aircraft provided in an embodiment of the present application;

wherein:

1-body; 2-inner wing panel; 3-outer wing section.

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.

A supersonic aircraft comprising:

a central body 1;

two inner wing sections 2, the leading edges of which have a large sweep angle, wherein one inner wing section 2 is arranged on one side of the central body 1, and the other inner wing section 2 is arranged on the other side of the central body 1;

Two outer panels 3, the leading edge of which has a medium sweep, wherein one outer panel 3 is arranged on one inner panel 2 and the other outer panel 3 is arranged on the other inner panel 2.

As for the supersonic aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the central body 1 is a fuselage of the aircraft, the interior of which is mainly divided into an equipment cabin, a cockpit, a passenger cabin, etc., and each inner wing section 2 is correspondingly connected to one side of the central body 1 at the inner side and is correspondingly connected to one outer wing section at the outer side to form a wing of the aircraft, wherein,

the front edge of the inner wing section 1 has a large sweepback angle, so that a larger lift force can be provided for the airplane, and the shock resistance of the airplane in supersonic flight is reduced;

The front edge of the outer wing section 2 has a medium sweepback angle, so that the aspect ratio of the airplane can be effectively increased, the aerodynamic characteristics of the airplane during pressure-sound-speed flight are improved, the subsonic flight efficiency of the airplane is improved, and the taking-off, landing and climbing performances of the airplane are improved;

The inner wing section 2 and the outer wing section 3 are combined with the central body to form an arrow-shaped appearance with a large sweepback angle at the inner side and a medium sweepback angle at the outer side, and the flight performance of the aircraft at supersonic speed and pressure-sound speed is considered.

In some alternative embodiments, the trailing edges of the two inner panels 2 have a small forward sweep to control the outboard chord length of the inner panels 2.

in some alternative embodiments, the small sweep angle of the trailing edges of the two inner panels 2 is below 15 °.

in some alternative embodiments, the large sweep angle of the leading edges of the two inner panels 2 is above 60 °.

in some alternative embodiments, the trailing edges of the two outer panels 3 have a small sweep angle to give the outer panels 3 a reasonable root to tip ratio to enable a refined lift distribution.

In some alternative embodiments, the small sweep angle of the trailing edges of the two outer panels 3 is below 15 °.

In some alternative embodiments, the intermediate sweep angle of the leading edges of the two outer panels 3 is within 40-50.

In some alternative embodiments, the central body 1 has a lifting profile.

As for the supersonic aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the central body 1 is designed to be a lift component of the aircraft, so as to provide lift for the aircraft during flight of the aircraft, thereby improving the lift characteristic of the aircraft, and it is not necessary to design an empennage, thereby avoiding drag generated by the empennage, avoiding interference drag among the fuselage, wings and empennage, and reducing the weight of the aircraft. The design of the lift profile of the central body 1 can be chosen within the limits that will be readily imaginable to the person skilled in the art.

In alternative embodiments, each inner panel 2 blends into a smooth transition with the central body 1.

with respect to the supersonic aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the central body 1 and the two inner wing sections 2 connected thereto are smoothly transited and merged into one body, so that the aircraft has the characteristic of wing-body merging, thereby effectively improving the lift force of the aircraft, reducing or even avoiding the interference resistance, and significantly increasing the internal space of the aircraft. The smooth transition of the inner panel 2 into the central body can be carried out by means of technical measures and processes known to those skilled in the art and readily conceivable.

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.