CN210258830U - High-speed aircraft with side air inlet - Google Patents
High-speed aircraft with side air inlet Download PDFInfo
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- CN210258830U CN210258830U CN201921202889.6U CN201921202889U CN210258830U CN 210258830 U CN210258830 U CN 210258830U CN 201921202889 U CN201921202889 U CN 201921202889U CN 210258830 U CN210258830 U CN 210258830U
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Abstract
The utility model relates to a side air inlet high-speed aircraft, which comprises an aircraft body, wherein a lower wing surface is arranged below the aircraft body, a high-pressure capturing wing is arranged above the aircraft body, an air suction type engine is arranged inside the aircraft body, and the front end of the air suction type engine is provided with an air inlet; a cone and a gas flow passage are sequentially arranged from front to back below the lower airfoil surface; the cone extends from the front of the aircraft to the rear and the lower part of the aircraft, and the width of the cone is smaller than that of the corresponding lower airfoil surface; the gas flow channel is positioned at two sides of the cone, and the air inlet of the air suction type engine is positioned at the rear part of the gas flow channel; the air inlets are arranged on two sides of the front end of the aircraft, the design of the wave rider forebody can be adopted, the uniform compression characteristic of the wave rider is fully utilized, on one hand, the performance of the engine can be effectively improved, and on the other hand, the lift-drag ratio characteristic of the whole aircraft can also be effectively improved by adopting the wave rider forebody.
Description
Technical Field
The embodiment of the utility model provides a relate to high-speed aircraft technical field, concretely relates to side high-speed aircraft that admits air.
Background
The high-speed aircraft mainly refers to various supersonic or hypersonic aircrafts. Generally, the flight with the Mach number M of 1.2-5.0 is called supersonic flight; flights with a mach number M greater than 5.0 are referred to as hypersonic flights. The design of a novel high-speed aircraft configuration is a hot problem in the current aircraft development, in particular to a powered high-lift-ratio configuration design.
In the prior art, one type is an unpowered gliding aircraft, and the lift-drag ratio can be effectively improved by arranging an overhead capturing wing above the aircraft, such as CN103350750A, which is provided with a high-pressure capturing wing above the aircraft body; for another example CN104354852A discloses a high speed aircraft with overhead wings, which are also essentially high pressure capture wings. However, the high-pressure capturing wing of the above patent is basically of a circular arc structure, is not easy to mount and fix, is easy to deform, and requires relatively high machining precision. The other type of high-speed aircraft is mainly provided with an engine, but although the engine can provide power, the capacity of the aircraft is limited due to the self weight and the large volume, and the requirement for long-distance, quick and large-capacity transportation is difficult to meet. At present, the research of simultaneously using a high-pressure trapping wing and an air suction engine for a high-speed aircraft does not exist, and particularly, the arrangement mode of the air suction engine has important influence on the performance of the whole aircraft.
On the other hand, the structural design of the high-pressure capture wing itself also directly affects the performance of the aircraft, and although it can provide lift compensation under certain conditions, it also increases the resistance and weight of the body. Therefore, the airfoil design of the high pressure capture foil is critical. The utility model discloses a configuration of catching wing has been proposed, in academic paper "Hypersonic I-shaped airborne configurations, Science Chinese Physics, mechanics & Astronomy, vol.61 No.2, 2018" figure 1, has shown the roughly shape of a catching wing, and its front side adopts the sweepback formula design, and the afterbody has big holding surface, and for high-speed aircraft, near the afterbody of high pressure catching wing is the low-pressure zone, not only can not produce lift, still can bring certain frictional resistance owing to self moist area, therefore, its aerodynamic performance is not high. For a hypersonic aircraft, because of the existence of strong shock waves, the pressure difference resistance is increased sharply, so that the lift-drag ratio performance is reduced, and therefore, the wings of the high-speed aircraft generally adopt a large-sweep design.
SUMMERY OF THE UTILITY MODEL
Therefore, the embodiment of the utility model provides a high-speed aircraft is admitted air to the side to because the existence of strong shock wave leads to the problem of lift-drag ratio performance decline among the solution prior art.
In order to achieve the above object, the embodiment of the present invention provides the following technical solutions:
a side air inlet high-speed aircraft comprises an aircraft body, wherein a lower wing surface is arranged below the aircraft body, a high-pressure capturing wing is arranged above the aircraft body, an air suction type engine is arranged inside the aircraft body, and an air inlet is formed in the front end of the air suction type engine; a cone and a gas flow passage are sequentially arranged below the lower airfoil surface from front to back;
the cone extends from the front of the aircraft to the rear and the lower part of the aircraft, and the width of the cone is smaller than that of the corresponding lower airfoil surface; the gas flow channel is positioned on two sides of the cone, and the gas inlet of the air suction type engine is positioned behind the gas flow channel.
The embodiment of the utility model provides a characterized in that still, follow the side of organism is seen, the outside of the air inlet of air-breathing type engine converges gradually, is triangle-shaped on the whole, just the rear and the smooth transition of lower flank of air inlet are connected.
The embodiment of the utility model provides a characterized in that still, the below of airfoil still is provided with down the casing down, the casing wraps up the gas flow path inside the organism completely down.
The utility model discloses the characteristic still lies in, the aircraft front end forms the compression shock wave, the air inlet of air-breathing type engine is located behind the compression shock wave.
The embodiment of the utility model provides a characterized in that still, air-breathing type engine is ramjet.
The embodiment of the present invention is further characterized in that the high pressure capturing wing has a symmetrical configuration, its projection on the horizontal plane has a symmetry axis along the fore-and-aft direction, on the symmetry axis, the foremost end of the high pressure capturing wing is defined as point a, from point a, sweepback to both sides along the smooth curve, the farthest point B point of the side is reached, the line between point a and point B is the first included angle α with the included angle of the horizontal line, and 30 ° < α <50 °.
The embodiment of the utility model provides a characterized in that still, the back portion that the wing was caught to high pressure adopts the sweepback formula design of dovetail, and the wing lateral part is caught from the most distant point B point to extend backward to the C point along the straight line to high pressure, and the most extreme point definition on the axis of symmetry is the D point, and the line between C point and the D point is second contained angle β with the contained angle of axis of symmetry, 45 < β < 90.
The embodiment of the utility model provides a have following advantage:
(1) the utility model arranges the air-breathing engine under the lower wing surface, the belly space of the engine body can be released, and the engine body can be completely used as a lifting surface; the air inlets are arranged on two sides of the front end of the aircraft, the design of the wave rider forebody can be adopted, and the uniform compression characteristic of the wave rider is fully utilized, so that on one hand, the performance of the engine can be effectively improved, and on the other hand, the lift-drag ratio characteristic of the whole aircraft can also be effectively improved by adopting the wave rider forebody;
(2) the utility model discloses a sweepback angle 30 degrees < α <50 degrees, sweepback degree is less for the high pressure of traditional hypersonic aircraft catches the wing, can catch high pressure district as much as possible, and the afterbody of high pressure catches the wing and also adopts the sweepback formula design of similar dovetail shape, can utilize high pressure district more effectively;
(3) the utility model combines the air-breathing engine and the high-pressure capturing wing to be applied to the high-speed aircraft, on one hand, the lift-drag ratio of the aircraft is improved due to the installation of the high-pressure capturing wing, so that the design of the large-size high-speed aircraft becomes possible to accommodate the air-breathing engine and the fuel; on the other hand, the installation of the air suction type engine effectively improves the speed and the range of the aircraft, thereby meeting the requirement on remote rapid transportation.
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 should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structure, ratio, size and the like shown in the present specification are only used for matching with the content disclosed in the specification, so as to be known and read by people familiar with the technology, and are not used for limiting the limit conditions which can be implemented by the present invention, so that the present invention has no technical essential significance, and any structure modification, ratio relationship change or size adjustment should still fall within the scope which can be covered by the technical content disclosed by the present invention without affecting the efficacy and the achievable purpose of the present invention.
FIG. 1 is a schematic view of the overall structure of the aircraft of the present invention;
fig. 2 is a schematic three-dimensional structure diagram of the aircraft of the present invention;
FIG. 3 is a schematic side view of the aircraft of the present invention;
FIG. 4 is a schematic bottom view of the aircraft of the present invention;
fig. 5 is a schematic front structural view of the aircraft of the present invention;
fig. 6 is a schematic top view of the high-pressure capturing wing of the aircraft of the present invention.
In the figure:
1-body; 2-lower airfoil surface; 3-high voltage capture wing; 5-an air-breathing engine; 6-an air inlet; 7-axis of symmetry;
21-cone; 22-gas flow channel; 23-lower shell.
Detailed Description
The present invention is described in terms of specific embodiments, and other advantages and benefits of the present invention will become apparent to those skilled in the art from the following disclosure. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
As shown in fig. 1 to 5, the side air intake high-speed aircraft includes an aircraft body 1, a lower wing surface 2 is arranged below the aircraft body 1, a high-pressure capturing wing 3 is arranged above the aircraft body 1, an air-breathing engine 5 is arranged inside the aircraft body 1, and an air inlet 6 is arranged at the front end of the air-breathing engine 5. The air-breathing engine 5 is preferably a ramjet engine. The air-breathing engines (5) are distributed symmetrically along a symmetry axis (7). And the aircraft nose forms a compression shock 4, the air intake 6 of the air-breathing engine 5 being located behind the compression shock 4.
A cone 21 and a gas flow passage 22 are sequentially arranged below the lower airfoil surface 2 from front to back; the cone 21 extends from the front of the aircraft to the rear and the lower part of the aircraft, and the width of the cone 21 is smaller than that of the corresponding lower wing surface 2; the gas flow passage 22 is located on both sides of the cone 21, and the intake port 6 of the air-breathing engine 5 is located behind the gas flow passage 22.
The air inlets 6 are arranged on the two sides of the front end of the aircraft, the design of the wave rider forebody can be adopted, the uniform compression characteristic of the wave rider is fully utilized, on one hand, the performance of the engine can be effectively improved, and on the other hand, the lift-drag ratio characteristic of the whole aircraft can also be effectively improved by adopting the wave rider forebody.
Preferably, as for the shape of the air intake duct, as shown in fig. 3 and 4, the outer side of the air intake duct gradually converges as viewed from the side of the machine body, forming a triangular shape as a whole.
Preferably, the rear part of the air inlet channel is smoothly and excessively connected with the lower wing surface 2, and the air inlet channel is provided with a lower shell 23, so that the flow channel in the air suction type engine 5 is completely wrapped in the engine body 1, the abdominal space of the engine body 1 is released, and the air inlet channel can be completely used as a lifting surface.
Fig. 6 is a top view of the high pressure capturing wing 3, which is also a projection on a horizontal plane, and the front end and the rear end of the high pressure capturing wing are designed in a sweepback manner, as shown in the figure, the whole high pressure capturing wing 3 has a symmetrical structure, and has a symmetrical line 7 along the front-rear direction, on the symmetrical line, the foremost end of the high pressure capturing wing 3 is defined as point a, and sweepback to both sides along a smooth curve from point a, and reaches the farthest point B of the side, and the angle between the connecting line between A, B and the horizontal line is a first angle α, i.e. sweepback angle, and finally extends backwards along the straight line to point C, and the distance between A, C two points forms the maximum length of the high pressure capturing wing 3, the rearmost end point on the symmetrical line is defined as point D, and the angle between the connecting line between 36.
For the hypersonic aircraft, because of the existence of strong shock waves, the pressure difference resistance is increased sharply, so that the lift-drag ratio performance is reduced, therefore, the general swept-back wing α is more than 50 degrees, and the high-pressure capturing wing 3 is different from the conventional wing and increases the lift force by utilizing the high pressure generated by the compression of the upper surface of the body, therefore, the front edge line of the high-pressure capturing wing 3 not only needs to comprehensively consider to reduce the wave resistance, but also needs to consider to capture the high-pressure area as much as possible, so that the swept-back degree is smaller than that of the conventional hypersonic aircraft, in the embodiment, the wing adopts the swept-back form, 30 degrees < α <50 degrees, not only can effectively reduce the wave resistance, but also can effectively capture the high-pressure area, compared with the prior art, the tail of the high-pressure capturing wing 3 also adopts the swept-back design similar to the tail shape, 45 degrees β <90 degrees has the advantages that the near the symmetrical surface of the tail is a low-pressure area, not only can not generate the lift force, but also can effectively utilize the high-pressure swallow tail, the tail can be more effectively, the high-pressure tail can be more symmetrically removed, the high-pressure tail can be more easily realized by adopting the high-pressure swallow structure, and the high-pressure tail area can be more easily reduced, and the high-drag.
Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (7)
1. The utility model provides a side high-speed aircraft that admits air, includes organism (1), the below of organism (1) is equipped with down airfoil (2), the top of organism (1) is provided with high pressure and catches wing (3), its characterized in that: an air suction type engine (5) is arranged in the engine body (1), and an air inlet (6) is formed in the front end of the air suction type engine (5); a cone (21) and a gas flow passage (22) are sequentially arranged from front to back below the lower airfoil surface (2);
the cone (21) extends from the front of the aircraft to the rear and the lower part of the aircraft, and the width of the cone (21) is smaller than that of the corresponding lower wing surface (2); the gas flow channel (22) is located on two sides of the cone (21), and the gas inlet (6) of the air suction type engine (5) is located behind the gas flow channel (22).
2. A side-entry high-speed aircraft according to claim 1, wherein: the outer side of an air inlet (6) of the air suction type engine (5) gradually converges when seen from the side surface of the engine body (1), the whole air suction type engine is in a triangular shape, and the rear part of the air inlet (6) is in smooth transition connection with the lower airfoil surface (2).
3. A side-entry high-speed aircraft according to claim 1, wherein: a lower shell (23) is further arranged below the lower airfoil surface (2), and the gas flow channel (22) is completely wrapped inside the machine body (1) by the lower shell (23).
4. A side-entry high-speed aircraft according to claim 1, wherein: the aircraft front end forms a compression shock wave (4), and an air inlet (6) of the air suction type engine (5) is positioned behind the compression shock wave (4).
5. A side-entry high-speed aircraft according to claim 1, wherein: the air-breathing engine (5) is a ramjet engine.
6. The high-speed air vehicle with side air intake according to claim 1, wherein the high-pressure capturing wing (3) has a symmetrical configuration, the projection on the horizontal plane has a symmetry axis (7) along the fore-and-aft direction, on the symmetry axis (7), the foremost end of the high-pressure capturing wing (3) is defined as point A, and the point A is swept backward along a smooth curve to both sides from the point A to the point B of the farthest point of the side, the connecting line between the point A and the point B forms a first included angle α with the horizontal line, and 30 ° < α <50 °.
7. A side-air inlet high-speed aircraft according to claim 6, wherein the rear part of the high-pressure capturing wing (3) is designed in a dovetail-shaped sweepback manner, the side part of the high-pressure capturing wing (3) extends from a point B which is the farthest point to a point C along a straight line, the most end point on the symmetry axis (7) is defined as a point D, and the connecting line between the point C and the point D forms a second included angle β with the symmetry axis (7), and the included angle is 45 degrees < β <90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921202889.6U CN210258830U (en) | 2019-07-29 | 2019-07-29 | High-speed aircraft with side air inlet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921202889.6U CN210258830U (en) | 2019-07-29 | 2019-07-29 | High-speed aircraft with side air inlet |
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| Publication Number | Publication Date |
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| CN210258830U true CN210258830U (en) | 2020-04-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921202889.6U Withdrawn - After Issue CN210258830U (en) | 2019-07-29 | 2019-07-29 | High-speed aircraft with side air inlet |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| CN115556945A (en) * | 2022-10-14 | 2023-01-03 | 西安近代化学研究所 | Aircraft with scramjet engine based on polyborane compound fuel |
-
2019
- 2019-07-29 CN CN201921202889.6U patent/CN210258830U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| CN110406671B (en) * | 2019-07-29 | 2024-07-02 | 中国科学院力学研究所 | Side air inlet high-speed aircraft |
| CN115556945A (en) * | 2022-10-14 | 2023-01-03 | 西安近代化学研究所 | Aircraft with scramjet engine based on polyborane compound fuel |
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