CN112027097A - Low-speed static pressure type air inlet channel suitable for flying wing layout aircraft - Google Patents
Low-speed static pressure type air inlet channel suitable for flying wing layout aircraft Download PDFInfo
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- CN112027097A CN112027097A CN202010921767.3A CN202010921767A CN112027097A CN 112027097 A CN112027097 A CN 112027097A CN 202010921767 A CN202010921767 A CN 202010921767A CN 112027097 A CN112027097 A CN 112027097A
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- static pressure
- air inlet
- inlet channel
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- 230000003068 static effect Effects 0.000 title claims abstract description 33
- 230000001788 irregular Effects 0.000 claims abstract description 4
- 230000007704 transition Effects 0.000 claims description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The application belongs to the field of aircraft inlet design, and particularly relates to a low-speed static pressure type inlet suitable for a flying wing layout aircraft. The intake duct includes: lips and internal ducts. The lip is in an irregular pentagon shape and comprises a front edge (101), a left side edge (102), a right side edge (103), a left rear edge (104) and a right rear edge (105); the inner pipeline comprises an inlet section (1) and an inlet main section (2). The application is suitable for low-speed static pressure formula intake duct of all-wing aircraft overall arrangement aircraft through designing novel oral surface form, has weakened the pair whirlpool structure that intake duct lip incline was curled up by a wide margin, has avoided leading to the too big distortion of flow field and total pressure loss behind the intake duct to whirlpool suction to intake duct performance has been promoted. Meanwhile, in order to solve the problem of difficult air intake, the shape of the inner pipeline is carefully designed, so that the counter pressure gradient of the inner pipeline of the air inlet channel is reduced to the maximum extent, the separation inside the air inlet channel is weakened, and the problem of difficult air intake of the static pressure type air inlet channel is relieved.
Description
Technical Field
The application belongs to the field of aircraft inlet design, and particularly relates to a low-speed static pressure type inlet suitable for a flying wing layout aircraft.
Background
The air inlet can be divided into two categories, dynamic pressure type air inlet and static pressure type air inlet. The inlet of the dynamic pressure type air inlet channel is perpendicular to the incoming flow direction, incoming flow stamping air inlet can be effectively utilized, and the existing aircraft air inlet channel is mostly of a dynamic pressure type. The inlet of the static pressure type air inlet channel is parallel to the incoming flow direction, and the air inlet channel is not provided with a protruding skin part and is fused with the profile height of an aircraft. However, because the static pressure type air inlet channel cannot effectively utilize incoming flow stamping, the problems of total pressure loss and overlarge flow field distortion exist, the application range of the static pressure type air inlet channel is greatly limited, and the static pressure type air inlet channel is only used as an auxiliary air inlet or a cruise missile air inlet channel for a long time and is greatly limited as the application of a main air inlet channel of a flying wing layout aircraft. In the prior art, a static pressure type air inlet design method which can be applied to a flying wing layout aircraft is not available.
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
The present application is directed to a low velocity static pressure air scoop for a flying wing aircraft configuration that solves at least one of the problems of the prior art.
The technical scheme of the application is as follows:
a low velocity static pressure air scoop adapted for use with a flying wing aircraft, the air scoop comprising: a lip and an inner pipe, wherein,
the lip is in an irregular pentagon shape and comprises a front edge, a left side edge, a right side edge, a left rear edge and a right rear edge;
the inner pipeline comprises an air inlet channel inlet section and an air inlet channel main section, the air inlet channel inlet section and the air inlet channel main section are in second-order continuous curved surface transition, and the central line of the inner pipeline is calculated by adopting the following formula:
wherein Y is a function of the longitudinal coordinate of the central line, x is the transverse coordinate of the central line, L is the total length of the central line, and A, B, C, D, E is a constant.
Optionally, the left and right lateral edges have an camber angle α, each of which is 4 °.
Optionally, the left and right trailing edges have a forward sweep angle β, both β being equal to 12 °.
Alternatively,
the left side edge is connected with the front edge through a chamfer, and the right side edge is connected with the front edge through a chamfer;
the left side edge is connected with the left rear edge through a chamfer, and the right side edge is connected with the right rear edge through a chamfer.
Optionally, the camber angle near the inlet lip is less than 2 °.
The invention has at least the following beneficial technical effects:
the low-speed static pressure type air inlet channel suitable for the flying wing layout aircraft improves the aerodynamic performance of the static pressure type air inlet channel and reduces the total pressure loss and flow field distortion of the air inlet channel by optimizing the air inlet and the molded surface of the inner pipeline, so that the low-speed static pressure type air inlet channel can be applied to the flying wing layout aircraft.
Drawings
FIG. 1 is a schematic view of a low velocity static pressure air scoop suitable for use in an aircraft having a flying wing configuration according to one embodiment of the present disclosure;
FIG. 2 is a schematic cross-sectional view of a low velocity static pressure inlet for an aircraft having a flying wing configuration, according to one embodiment of the present disclosure.
Wherein:
1-inlet section of air inlet channel; 101-leading edge; 102-left lateral edge; 103-right lateral edge; 104-left rear edge; 105-a right rear edge; 2-main section of air inlet channel.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
A low velocity static pressure air scoop for a flying wing aircraft, the air scoop comprising: lips and internal ducts.
Specifically, as shown in fig. 2, the lip has an irregular pentagon shape, and includes a front edge 101, a left side edge 102, a right side edge 103, a left rear edge 104, and a right rear edge 105; the inner pipeline comprises an inlet section 1 of the air inlet and a main section 2 of the air inlet, and the inlet section 1 of the air inlet and the main section 2 of the air inlet are in second-order continuous curved surface transition; the central lines of the inlet section 1 and the main section 2 of the inlet of the inner pipeline are calculated by adopting the following formulas:
wherein Y is a function of the longitudinal coordinate of the central line, x is the transverse coordinate of the central line, L is the total length of the central line, and A, B, C, D, E is a constant.
In the low velocity static pressure type inlet duct for an aircraft having a flying wing configuration of the present application, the left side edge 102 and the right side edge 103 have camber angles α, which are each 4 ° in one embodiment of the present application.
In the low-velocity static pressure type air inlet duct suitable for the flying wing layout aircraft of the present application, the left rear edge 104 and the right rear edge 105 have forward sweep angles β, which in one embodiment of the present application are both equal to 12 °.
Advantageously, in one embodiment of the present application, the left side edge 102 is connected to the front edge 101 by a chamfer, and the right side edge 103 is connected to the front edge 101 by a chamfer; the left side edge 102 and the left rear edge 104 are connected by a chamfer, and the right side edge 103 and the right rear edge 105 are connected by a chamfer.
In one embodiment of the present application, the upper surface of the flying wing layout is preferably modified to ensure that the camber angle near the inlet lip is less than 2 °.
The application is suitable for low-speed static pressure formula intake duct of all-wing aircraft overall arrangement aircraft through designing novel oral surface form, has weakened the pair whirlpool structure that intake duct lip incline was curled up by a wide margin, has avoided leading to the too big distortion of flow field and total pressure loss behind the intake duct to whirlpool suction to intake duct performance has been promoted. Meanwhile, in order to solve the problem of difficult air intake, the shape of the inner pipeline is carefully designed, so that the counter pressure gradient of the inner pipeline of the air inlet channel is reduced to the maximum extent, the separation inside the air inlet channel is weakened, and the problem of difficult air intake of the static pressure type air inlet channel is relieved.
The application is suitable for low-speed static pressure formula intake duct of all-wing aircraft overall arrangement aircraft, can reduce the total pressure loss in static pressure formula intake duct flow field and intake duct export distortion index by a wide margin, is showing and promotes static pressure formula intake duct performance, makes the static pressure formula intake duct become possible as low-speed all-wing aircraft overall arrangement aircraft to can reduce all-wing aircraft intake duct windward resistance, alleviate structure weight, save space, further promote the stealthy performance of all-wing aircraft overall arrangement aircraft.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A low velocity static pressure air scoop adapted for use in a flying wing aircraft configuration, the air scoop comprising: a lip and an inner pipe, wherein,
the lip is in an irregular pentagon shape and comprises a front edge (101), a left side edge (102), a right side edge (103), a left rear edge (104) and a right rear edge (105);
the inner pipeline comprises an air inlet channel inlet section (1) and an air inlet channel main section (2), the air inlet channel inlet section (1) and the air inlet channel main section (2) are in second-order continuous curved surface transition, and the central line of the inner pipeline is calculated by adopting the following formula:
wherein Y is a function of the longitudinal coordinate of the central line, x is the transverse coordinate of the central line, L is the total length of the central line, and A, B, C, D, E is a constant.
2. The low-velocity static pressure type air intake duct for an all-wing aircraft according to claim 1, wherein the left side edge (102) and the right side edge (103) have an camber angle α, and the camber angle α is 4 °.
3. The low-velocity static pressure type air intake duct for an aircraft with an all-wing aircraft configuration according to claim 1, wherein the left rear edge (104) and the right rear edge (105) have a forward sweep angle β, each of which is equal to 12 °.
4. The low-velocity static pressure type air intake duct for an aircraft having a flying wing configuration according to claim 1,
the left side edge (102) is connected with the front edge (101) through a chamfer, and the right side edge (103) is connected with the front edge (101) through a chamfer;
the left side edge (102) is connected with the left rear edge (104) through a chamfer, and the right side edge (103) is connected with the right rear edge (105) through a chamfer.
5. The low static pressure air scoop according to claim 1 wherein the angle of incidence of the curved surface adjacent the scoop lip is less than 2 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010921767.3A CN112027097A (en) | 2020-09-04 | 2020-09-04 | Low-speed static pressure type air inlet channel suitable for flying wing layout aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010921767.3A CN112027097A (en) | 2020-09-04 | 2020-09-04 | Low-speed static pressure type air inlet channel suitable for flying wing layout aircraft |
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Application publication date: 20201204 |