CN113071689A - Air inlet channel of subsonic aircraft - Google Patents
Air inlet channel of subsonic aircraft Download PDFInfo
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- CN113071689A CN113071689A CN202110498558.7A CN202110498558A CN113071689A CN 113071689 A CN113071689 A CN 113071689A CN 202110498558 A CN202110498558 A CN 202110498558A CN 113071689 A CN113071689 A CN 113071689A
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- air inlet
- machine body
- face
- intake duct
- channel
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- 230000006835 compression Effects 0.000 claims abstract description 24
- 238000007906 compression Methods 0.000 claims abstract description 24
- 230000010354 integration Effects 0.000 claims description 4
- 238000005192 partition Methods 0.000 abstract description 8
- 238000011084 recovery Methods 0.000 abstract description 3
- 230000004927 fusion Effects 0.000 abstract 1
- 238000004088 simulation Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 210000002345 respiratory system Anatomy 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a subsonic aircraft air inlet, which comprises an air inlet opening surface, wherein the bottom of the air inlet opening surface is connected with a machine body and integrated with the machine body, the rear end of the air inlet opening surface is communicated with an inner channel of the air inlet, a flow partition plate is supported and fixed in the inner channel of the air inlet, a lip cover is surrounded on the air inlet opening surface, a triangle-like step compression surface is arranged on the front side of the air inlet opening surface and fixed on the machine body, and the lip cover is smoothly connected with the machine body and the triangle-like step compression surface. The structure eliminates a boundary layer separating channel independently arranged on the machine body, and replaces a bulge protruding out of the surface of the machine body with a triangle-like step compression surface; meanwhile, through the integrated fusion of the sweepback lip cover, the inlet port surface, the triangle-like step compression surface and the body, the boundary layer of the body can be effectively eliminated, the higher total pressure recovery coefficient and the lower flow field distortion index of the inlet channel are kept, and the characteristics of the attack angle and the sideslip angle of the inlet channel can be considered.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to an air inlet channel of a subsonic aircraft.
Background
As a respiratory tract of an air-breathing propulsion system, the air inlet shoulder has the important functions of capturing, compressing, rectifying and the like of airflow, and the design characteristics and the working characteristics of the air inlet shoulder have obvious influence on the working efficiency of an engine. The subsonic aircraft is the most widely applied aircraft among air-breathing aircrafts, and the air inlet of a power system of the subsonic aircraft generally has the forms of a skin-support type air inlet, an S-bend air inlet, an embedded air inlet and the like. For the reasons of engine installation, air inlet performance and the like, the S-shaped air inlet is mostly selected for modern advanced subsonic aircrafts.
In order to avoid the intake of the air intake duct into the low energy flow in the boundary layer of the fuselage surface, the conventional S-turn air intake duct generally lifts the inlet of the air intake duct away from the fuselage surface by providing a special boundary layer partition and baffle, thereby discharging the low energy flow from the partition. Obviously, the boundary layer partitions increase the frontal area of the aircraft and form the corner reflectors of the radar waves, so that the aerodynamic drag of the aircraft is increased, the stealth performance of the radar is reduced, and the weight and the structural complexity are increased.
An air Inlet without an isolated channel, also called a Bump air Inlet, is a novel Supersonic air Inlet which is designed by Rockschid Martin company and successfully applied to an F-35 airplane, namely a Supersonic air Inlet without boundary layer isolated channels (DSI), and has the characteristics of drag reduction, weight reduction and invisibility. The air inlet of the air inlet channel is not provided with a conventional fixed boundary layer partition channel, but is designed with a three-dimensional curved protruding block (or bulge) through a computer, the bulge plays a role in compressing air flow and generating pressure distribution for pushing boundary layer air flow away from the air inlet channel, and the pressure distribution has the same function of eliminating an incoming flow boundary layer as the boundary layer partition channel. Because of the excellent comprehensive performance of the air inlet without the boundary layer separating channel, the air inlet applied to the subsonic aircraft is widened at present, particularly, unmanned aircraft paying attention to stealth and drag reduction, such as American X-45A, X-45C and the like, but because of the absence of the boundary layer separating channel, the air inlet cannot completely eliminate an incoming flow boundary layer, and the performance of the air inlet is not provided with the air inlet with the separating channel generally. For the aircraft X-45A, X-45C, the inlet is arranged above the fuselage near the nose, and the front boundary layer of the inlet is thin, so the working condition is not bad, the performance is not low in general, but the performance is poor when the angle of attack exists. If the inlet of the air inlet channel is positioned in the middle or the middle rear part of the machine body, the performance of the air inlet channel is poorer and is influenced by the attack angle and the sideslip angle more greatly because the boundary layer of the machine body increases along with the increase of the length of the machine head.
Disclosure of Invention
The invention aims to provide a subsonic aircraft air inlet to solve the problems mentioned in the background art. In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a subsonic aircraft intake duct, includes intake duct face, the fuselage is connected to intake duct face bottom, and fuses with the fuselage integration, intake duct face rear end intercommunication intake duct inner channel, the inside support of intake duct inner channel is fixed with the flow divider, it has the lip cover to enclose on the intake duct face, intake duct face front side is equipped with class triangle-shaped step compression face, class triangle-shaped step compression face is fixed in on the fuselage, the lip cover is smoothly connected with fuselage and class triangle-shaped step compression face.
Preferably, the leading edge of the lip shroud is of a swept back design in both the bottom and side view.
Preferably, the triangle-like step compression surface is smoothly connected with the machine body and protrudes out of the machine body.
Preferably, the air inlet inner channel comprises an inner pipeline extending towards the interior of the fuselage in a bending manner, the rear end of the inner pipeline is connected with the air inlet outlet face, and the front end of the inner pipeline is connected with the air inlet outlet face.
Preferably, the shape of the air inlet port surface is determined according to the shape of the fuselage, and the air inlet port surface and the fuselage are integrally designed.
The invention has the technical effects and advantages that: the structure eliminates a boundary layer separating channel independently arranged on the machine body, and replaces a bulge protruding out of the surface of the machine body with a triangle-like step compression surface; meanwhile, through the integration of the sweepback lip cover, the inlet port face, the triangle-like step compression face and the body, the structure can effectively eliminate a body boundary layer, keep higher total pressure recovery coefficient and lower flow field distortion index of the inlet and simultaneously take into account the characteristics of an attack angle and a sideslip angle of the inlet.
Drawings
FIG. 1 is a three-dimensional isometric schematic of the present invention;
FIG. 2 is a bottom view of the present invention;
FIG. 3 is a top view of the present invention;
FIG. 4 is a schematic view of an inlet outlet face of the present invention.
In the figure: 1-inlet port surface, 2-body, 3-inlet channel, 4-flow baffle, 5-lip cover, 6-triangular step compression surface, 7-inner pipeline and 8-inlet outlet surface.
Detailed Description
In the description of the present invention, it should be noted that unless otherwise specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements.
Example 1
As shown in figure 1, a subsonic aircraft intake duct, including intake duct face 1, fuselage 2 is connected to intake duct face 1 bottom, and fuses with fuselage 2 integration, the passageway 3 in the 1 rear end intercommunication intake duct of intake duct face, 3 inside supports of passageway are fixed with flow divider 4 in the intake duct, it has lip cover 5 to enclose on the intake duct face 1, intake duct face 1 front side is equipped with class triangle-shaped step compression face 6, class triangle-shaped step compression face 6 is fixed in on the fuselage 2, lip cover 5 and fuselage 2 and 6 smooth connections of class triangle-shaped step compression face.
Example 2
The subsonic aircraft air inlet shown in fig. 1-4 comprises an air inlet port surface 1, the bottom of the air inlet port surface 1 is connected with a machine body 2, the shape of the air inlet port surface 1 is determined according to the appearance of the machine body 2 and is integrated with the machine body 2, the rear end of the air inlet port surface 1 is communicated with an air inlet inner channel 3, the air inlet inner channel 3 comprises an inner channel 7 which is bent and extended towards the interior of the machine body, the rear end of the inner channel 7 is connected with an air inlet outlet surface 8, the front end of the inner channel is connected with the air inlet port surface 1, a flow partition plate 4 is supported and fixed inside the air inlet inner channel 3, the flow partition plate 4 not only increases the structural strength of the air inlet inner channel 3, but also can divide the air flow captured by the air inlet port surface 1 into two air flows inside the air inlet inner channel 2, the two air flows are respectively supplied to corresponding engines, thereby reduce the distortion degree of 8 air currents of intake duct outlet face, it has lip cover 5 to enclose on intake duct face 1, intake duct face 1 front side is equipped with class triangle-shaped step compression face 6, class triangle-shaped step compression face 6 is fixed in on the fuselage 2, class triangle-shaped step compression face 6 and fuselage 2 are smooth to be connected and are outstanding in fuselage 2, and the height that class triangle-shaped step compression face 6 is outstanding in fuselage 2 can come the nimble selection according to intake duct face 1 preceding local boundary layer height, lip cover 5 and fuselage 2 and class triangle-shaped step compression face 6 are smooth to be connected, and the front edge of lip cover 5 all takes the sweepback design in looking up and looking aside two directions, and the combined action of sweepback lip cover 5 and class triangle-shaped step compression face 6, intake duct face 1 can form certain exhibition to pressure gradient before intake duct face 1, under the combined action of intake duct pressure gradient, the boundary layers are arranged and moved to two sides, in addition, the sweepback lip cover 5 can give the boundary layers which are deviated to two sides space for outflow, and if the straight lip cover 5 is adopted, the boundary layers on two sides cannot be discharged.
Design instance analysis
A semi-embedded air inlet scheme of the subsonic aircraft with a single air inlet and double-engine layout for belly air intake is designed by taking the flight Mach number of 0.7 as a cruise point, and is used as a comparison scheme, the performance of the semi-embedded air inlet scheme is analyzed by adopting a three-dimensional numerical simulation technology, and the aerodynamic performance parameters of the semi-embedded air inlet scheme are listed in a table 1.
TABLE 1 aerodynamic Performance of the subsonic aircraft inlet scheme of the present invention (simulation results)
The simulation results in table 1 show that the design intention provided by the invention is better embodied, and the attack angle characteristic and the sideslip angle characteristic of the air inlet channel are considered while the higher total pressure recovery coefficient and the lower flow field distortion index of the air inlet channel are kept.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.
Claims (5)
1. The utility model provides a subsonic aircraft intake duct, includes the intake duct oral area, its characterized in that: the fuselage is connected to intake duct face bottom, and fuses with the fuselage integration, intake duct face rear end intercommunication intake duct inner channel, the inside support of intake duct inner channel is fixed with the flow divider, it has the lip cover to enclose on the intake duct face, intake duct face front side is equipped with class triangle-shaped step compression face, class triangle-shaped step compression face is fixed in on the fuselage, the lip cover is connected with fuselage and class triangle-shaped step compression face are smooth.
2. The subsonic vehicle inlet duct of claim 1, characterized by: the front edge of the lip cover adopts a backswept design in both the upward view direction and the side view direction.
3. The subsonic vehicle inlet duct of claim 1, characterized by: the triangle-like step compression surface is smoothly connected with the machine body and protrudes out of the machine body.
4. The subsonic vehicle inlet duct of claim 1, characterized by: the air inlet channel comprises an inner pipeline which is bent and extended towards the interior of the machine body, the rear end of the inner pipeline is connected with an outlet face of the air inlet channel, and the front end of the inner pipeline is connected with an inlet face of the air inlet channel.
5. The subsonic vehicle inlet duct of claim 1, characterized by: the shape of the air inlet port surface is determined according to the shape of the machine body, and the air inlet port surface and the machine body are integrated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110498558.7A CN113071689A (en) | 2021-05-08 | 2021-05-08 | Air inlet channel of subsonic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110498558.7A CN113071689A (en) | 2021-05-08 | 2021-05-08 | Air inlet channel of subsonic aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN113071689A true CN113071689A (en) | 2021-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110498558.7A Pending CN113071689A (en) | 2021-05-08 | 2021-05-08 | Air inlet channel of subsonic aircraft |
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| CN (1) | CN113071689A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115571351A (en) * | 2022-11-21 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Flying wing layout backpack air inlet channel with high-low speed performance and stealth performance |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120031501A1 (en) * | 2010-08-09 | 2012-02-09 | Yen Tuan | Aviation engine inlet with tangential blowing for buzz saw noise control |
| CN111942600A (en) * | 2020-08-06 | 2020-11-17 | 四川航天中天动力装备有限责任公司 | Boundary layer-free partition air inlet channel |
-
2021
- 2021-05-08 CN CN202110498558.7A patent/CN113071689A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120031501A1 (en) * | 2010-08-09 | 2012-02-09 | Yen Tuan | Aviation engine inlet with tangential blowing for buzz saw noise control |
| CN111942600A (en) * | 2020-08-06 | 2020-11-17 | 四川航天中天动力装备有限责任公司 | Boundary layer-free partition air inlet channel |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115571351A (en) * | 2022-11-21 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Flying wing layout backpack air inlet channel with high-low speed performance and stealth performance |
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Application publication date: 20210706 |
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