CN105752347A - Airplane air inlet structure - Google Patents
Airplane air inlet structure Download PDFInfo
- Publication number
- CN105752347A CN105752347A CN201610112180.1A CN201610112180A CN105752347A CN 105752347 A CN105752347 A CN 105752347A CN 201610112180 A CN201610112180 A CN 201610112180A CN 105752347 A CN105752347 A CN 105752347A
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- China
- Prior art keywords
- air inlet
- aircraft
- extra
- airplane
- cavity
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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; 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
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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
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
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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
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
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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)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses an airplane air inlet structure.The airplane air inlet structure comprises a main air inlet structure installed above an airplane cabin and an auxiliary air inlet structure installed above an airplane wing.The main air inlet structure comprises a plurality of main air inlets, main air inlet cavities and an air outlet.The main air inlets are distributed at the upper portion of the airplane cabin.The air outlet is formed in the airplane tail.The main air inlets and the air outlet are communicated through the main air inlet cavities.The auxiliary air inlet structure comprises a plurality of auxiliary air inlets and auxiliary air inlet cavities.The auxiliary air inlets are evenly distributed at the upper portion of the airplane wing.The auxiliary air inlets are communicated to the air outlet through the auxiliary air inlet cavities.The airplane air inlet structure is simple in structure.Due to the air inlet cavities evenly and densely distributed in the upper portion of the airplane cabin and the airplane wing, when an airplane takes off, the air flow velocity over the airplane is greatly enhanced, the airplane can take off with no need of a long track or the airplane can take off and be lifted off directly on site on the condition that power of an engine is enough, the takeoff distance is greatly shortened, and the takeoff time is shortened.
Description
Technical field
The present invention relates to airplane design technical field, be specifically related to a kind of aircraft inlet structure.
Background technology
Since aircraft is born, the position of its air inlet is different, and its position selects to be the performance requirement of overall aircraft and determines；By its position aboard, it is broadly divided into frontal inlet and non-frontal air inlet, 1. frontal inlet: air inlet is positioned at fuselage or engine nacelle head, advantage is simple structure, and before air inlet, air is interference-free, and shortcoming is also apparent from, head air inlet, aircraft cannot install Large Radar Antenna, and inlet channel is also oversize simultaneously, and unfavorable interior of aircraft equipment is installed；2. non-frontal air inlet: it includes under both sides air inlet, wing root air inlet, abdominal part air inlet, the wing under air inlet, rib and back air inlet etc., the shortcoming that these air inlet location arrangements overcome frontal inlet, especially under abdominal part and the wing, the advantage of air inlet is obvious, take full advantage of the favourable bridging effect of fuselage and wing, improve the working condition of air inlet；In tactical maneuver performance, aircraft engine behavior when At High Angle of Attack is motor-driven is steady；Air inlet is also different at aeroperformance produced by diverse location and different shapes, and abdominal part air inlet and the air inlet of fuselage both sides can shorten air intake duct length, reserve Handpiece Location to airborne radar, but makes complete machine resistance increase；And aircraft is breakked away very sensitive by both sides air inlet.Performance parameter according to air inlet, it is possible to be divided into subsonic speed air inlet, supersonic speed air inlet etc., intake port shape selects also to be the needs according to aircraft actual performance；Therefore, more or less all there is certain defect in current aircraft air inlet, and owing to the existence of defect makes aircraft need substantial amounts of storage power in take-off process, therefore runway is often very long, and this brings very big inconvenience to a certain extent.
Summary of the invention
It is an object of the invention to provide a kind of aircraft inlet structure, solve one or more in above-mentioned prior art problem.
A kind of aircraft inlet structure according to the present invention, including the primary air inlet structure being installed on above aircraft cabin and be installed on the extra-air inlet structure above aircraft wing；Described primary air inlet structure includes some primary air inlets, main air inlet cavity and gas outlet, and described primary air inlet is distributed in aircraft cabin top, and described gas outlet is located at aircraft tail place, described primary air inlet and described gas outlet and is connected by main air inlet cavity；Described extra-air inlet structure includes some extra-air inlets and secondary air inlet cavity, and described extra-air inlet is distributed in aircraft wing top, and described extra-air inlet is communicated in described gas outlet by secondary air inlet cavity.
A kind of aircraft inlet structure provided by the present invention, simple in construction, by increasing, on aircraft cabin top and aircraft wing top, the air inlet cavity uniformly gathered, when taking off, air velocity above aircraft is greatly enhanced, just can make without very long runway to take off or can rolling takeoff lift-off in original place when engine power is enough, being greatly shortened the stroke that takes off, saved the departure time.
In some embodiments, described primary air inlet and described extra-air inlet pars intermedia are equipped with defroster, it is connected by cutter cutting apparatus between described defroster with described primary air inlet, being connected also by cutter cutting apparatus between described defroster and extra-air inlet, described cutter cutting apparatus linearly shape disperses distribution.When high airflight, temperature is often very low, and defroster is possible to prevent air inlet place condensation vapor to solidify, it is to avoid air inlet is plugged, thus affecting flight.
In some embodiments, described primary air inlet and described extra-air inlet are circular, oval or rectangle setting.Different intake port shapes can be selected according to the actual requirements.
In some embodiments, the air inlet angle of described primary air inlet and described extra-air inlet compared with horizontal plane in acute angle.Air inlet can be made to be constantly in air-suction state.
In some embodiments, described cutter cutting apparatus is blade, and the place of putting the first edge on a knife or a pair of scissors of blade is positioned at and locates against the wind, and the two ends of blade are provided with bearing pin, and blade carries out axle rotation centered by bearing pin, for controlling the opening and closing of primary air inlet or extra-air inlet.By blade by inlet close, aircraft can be made to be in normal flight after taking off.
In some embodiments, described defroster connects antifreeze collector, and described antifreeze collector extends respectively in described main air inlet cavity and described secondary inlet chamber body.Prevent in inlet chamber body firmly freezing by ice, affect aircraft flight.
In some embodiments, also including heating duct, described heating duct is wound on described main air inlet cavity and the described secondary air inlet cavity whole body respectively.Prevent in inlet chamber body firmly freezing by ice, affect aircraft flight.
In some embodiments, the inside cavity perisporium of described main air inlet cavity and described secondary air inlet cavity all extending and is provided with wind deflector, the bearing of trend of described wind deflector is identical with airflow direction.Air-flow is made to pass through the flow velocity of air inlet cavity faster.
Accompanying drawing explanation
Fig. 1 is the perspective view of a kind of aircraft inlet structure of one embodiment of the present invention；
Fig. 2 is the side structure schematic diagram of a kind of aircraft inlet structure of one embodiment of the present invention；
Fig. 3 is the wing extra-air inlet structural representation of a kind of aircraft inlet structure of one embodiment of the present invention；
Fig. 4 is the structural representation of the primary air inlet of a kind of aircraft inlet structure of one embodiment of the present invention or extra-air inlet；
Fig. 5 be the present invention Fig. 1 in the sectional view of A-A；
Fig. 6 is the schematic diagram of the primary air inlet structure of the present invention.
Detailed description of the invention
Below in conjunction with Figure of description, the present invention is described in more detail.
As shown in Figure 1 to Figure 2, a kind of aircraft inlet structure, including the primary air inlet structure 3 being installed on above aircraft cabin 1 be installed on the extra-air inlet structure 4 above aircraft wing 2；Primary air inlet structure 3 includes some primary air inlets 31, main air inlet cavity 33 and gas outlet 32, primary air inlet 31 is distributed in aircraft cabin 1 top, primary air inlet 31 can be regular uniform arrangement, can also irregular arranging, gas outlet 32 is installed on aircraft tail 10 place, primary air inlet 31 and gas outlet 32 and is connected by main air inlet cavity 33, main air inlet cavity 33 is installed on aircraft cabin 1 top, air enters from primary air inlet 31, by main air inlet cavity 33, then discharges from gas outlet 32；As it is shown on figure 3, extra-air inlet structure 4 includes some extra-air inlets 41 and secondary air inlet cavity 42, extra-air inlet 41 is distributed in aircraft wing 2 top, and extra-air inlet 41 is communicated in gas outlet 32 by secondary air inlet cavity 42.
Primary air inlet 31 and extra-air inlet 41 are circular, oval or rectangle is arranged, different intake port shapes can be selected according to the actual requirements, the air inlet angle of primary air inlet 31 and extra-air inlet 41 compared with horizontal plane in acute angle, generally, angle be 30 ° as well, air inlet can be made to be in quick air-suction state.
As shown in Figure 4 and Figure 6, primary air inlet 31 and extra-air inlet 41 pars intermedia are installed with defroster 6 each through bolt, it is connected by cutter cutting apparatus 7 between defroster 6 with primary air inlet 31, it is connected also by cutter cutting apparatus 7 between defroster 6 with extra-air inlet 41, cutter cutting apparatus 7 linearly shape disperses distribution, when high airflight, temperature is often very low, defroster is possible to prevent in air inlet and inlet chamber body condensation vapor and solidifies, air inlet and air inlet cavity is avoided to be plugged, thus affecting flight.
As shown in Figure 4, cutter cutting apparatus 7 forms for blade 71, the place of putting the first edge on a knife or a pair of scissors of blade 71 is positioned at and locates against the wind, so maximum minimizing windage, the two ends of blade 71 are provided with bearing pin, blade 71 carries out axle rotation centered by bearing pin, for controlling primary air inlet 31 or the opening and closing of extra-air inlet 41, blade 71 two ends are movably connected in by bearing pin on primary air inlet 31 or extra-air inlet 41, by blade by inlet close, aircraft can be made to be in normal flight after taking off, when taking off, blade 71 is opened, and air can enter air inlet, so that aircraft quickly takes off.
Defroster 6 connects antifreeze collector 61, and antifreeze collector 61 extends respectively in main air inlet cavity 33 and secondary air inlet cavity 42, and antifreeze collector 61 is electrical heated pipings, it is prevented that firmly freezing by ice in inlet chamber body, affects aircraft flight；Heating duct 8 is also included in main air inlet cavity 33 and secondary air inlet cavity 42, heating duct 8 is wound in main air inlet cavity 33 and secondary air inlet cavity 42 inwall week respectively, heating duct 8 is also adopted by Electric heating, it is prevented that firmly freezing by ice in inlet chamber body, affects aircraft flight；In main air inlet cavity 33 and secondary air inlet cavity 42, induction apparatus is installed, for observing and controlling wind speed, gas pressure intensity and gas temperature etc..
As shown in Figure 5, the inside cavity perisporium of main air inlet cavity 33 and secondary air inlet cavity 42 all extends and is provided with wind deflector 9, the bearing of trend of wind deflector 9 is identical with airflow direction, wind deflector 9 fixes uniform being distributed on main air inlet cavity 33 and secondary air inlet cavity 42 internal perisporium by welding or bolt so that air-flow is by the flow velocity of air inlet cavity faster.
A kind of aircraft inlet structure provided by the present invention, simple in construction, by increasing, on aircraft cabin top and aircraft wing top, the air inlet cavity uniformly gathered, when taking off, air velocity above aircraft is greatly enhanced, just can make without very long runway to take off or can rolling takeoff lift-off in original place when engine power is enough, being greatly shortened the stroke that takes off, saved the departure time.
The above is only the optimal way of the present invention, it is noted that to those skilled in the art, without departing from the concept of the premise of the invention, it is also possible to making some similar deformation and improvement, these also should be regarded as within protection scope of the present invention.
Claims (8)
1. an aircraft inlet structure, it is characterised in that include being installed on the primary air inlet structure (3) of aircraft cabin (1) top and being installed on the extra-air inlet structure (4) of aircraft wing (2) top；Described primary air inlet structure (3) includes some primary air inlets (31), main air inlet cavity (33) and gas outlet (32), described primary air inlet (31) is distributed in aircraft cabin (1) top, aircraft tail (10) place is located in described gas outlet (32), and described primary air inlet (31) is connected by main air inlet cavity (33) with described gas outlet (32)；Described extra-air inlet structure (4) includes some extra-air inlets (41) and secondary air inlet cavity (42), described extra-air inlet (41) is distributed in aircraft wing (2) top, and described extra-air inlet (41) is communicated in described gas outlet (32) by secondary air inlet cavity (42).
2. a kind of aircraft inlet structure according to claim 1, it is characterized in that, described primary air inlet (31) and described extra-air inlet (41) pars intermedia are equipped with defroster (6), it is connected by cutter cutting apparatus (7) between described defroster (6) with described primary air inlet (31), being connected also by cutter cutting apparatus (7) between described defroster (6) with extra-air inlet (41), described cutter cutting apparatus (7) linearly shape disperses distribution.
3. a kind of aircraft inlet structure according to claim 2, it is characterised in that described primary air inlet (31) and described extra-air inlet (41) are circular, oval or rectangle is arranged.
4. a kind of aircraft inlet structure according to claim 3, it is characterised in that the air inlet angle of described primary air inlet (31) and described extra-air inlet (41) compared with horizontal plane in acute angle.
5. a kind of aircraft inlet structure according to claim 2, it is characterized in that, described cutter cutting apparatus (7) is blade (71), the place of putting the first edge on a knife or a pair of scissors of blade (71) is positioned at and locates against the wind, the two ends of described blade (71) are provided with bearing pin, blade (71) carries out axle rotation centered by bearing pin, is used for the opening and closing controlling primary air inlet (31) or extra-air inlet (41).
6. a kind of aircraft inlet structure according to claim 2, it is characterized in that, described defroster (6) connects antifreeze collector (61), and described antifreeze collector (61) extends respectively in described main air inlet cavity (33) and described secondary air inlet cavity (42).
7. a kind of aircraft inlet structure according to claim 1, it is characterized in that, also including heating duct (8), described heating duct (8) is wound in described main air inlet cavity (33) and described secondary air inlet cavity (42) week respectively.
8. a kind of aircraft inlet structure according to claim 1, it is characterized in that, all extending on the inside cavity perisporium of described main air inlet cavity (33) and described secondary air inlet cavity (42) and be provided with wind deflector (9), the bearing of trend of described wind deflector (9) is identical with airflow direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610112180.1A CN105752347B (en) | 2016-02-29 | 2016-02-29 | A kind of aircraft inlet structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610112180.1A CN105752347B (en) | 2016-02-29 | 2016-02-29 | A kind of aircraft inlet structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105752347A true CN105752347A (en) | 2016-07-13 |
| CN105752347B CN105752347B (en) | 2017-07-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610112180.1A Active CN105752347B (en) | 2016-02-29 | 2016-02-29 | A kind of aircraft inlet structure |
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| CN (1) | CN105752347B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050869A (en) * | 2018-07-17 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of ram-air bleed structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB639117A (en) * | 1945-09-28 | 1950-06-21 | Svenska Turbinfab Ab | Improvements in boundary layer control in aircraft |
| GB881785A (en) * | 1958-08-01 | 1961-11-08 | Bmw Triebwerkbau Gmbh | Power plant for short forward or vertical take-off aircraft |
| GB979221A (en) * | 1960-11-18 | 1965-01-01 | English Electric Co Ltd | Improvements in and relating to short or vertical take-off aircraft |
| US6412731B1 (en) * | 1999-12-23 | 2002-07-02 | Edwin Zenith Gabriel | Simplified buoyancy system for avoiding aircraft crashes |
| CN103318411A (en) * | 2012-03-19 | 2013-09-25 | 陈永春 | Fixed wing vertical takeoff and landing aircraft |
-
2016
- 2016-02-29 CN CN201610112180.1A patent/CN105752347B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB639117A (en) * | 1945-09-28 | 1950-06-21 | Svenska Turbinfab Ab | Improvements in boundary layer control in aircraft |
| GB881785A (en) * | 1958-08-01 | 1961-11-08 | Bmw Triebwerkbau Gmbh | Power plant for short forward or vertical take-off aircraft |
| GB979221A (en) * | 1960-11-18 | 1965-01-01 | English Electric Co Ltd | Improvements in and relating to short or vertical take-off aircraft |
| US6412731B1 (en) * | 1999-12-23 | 2002-07-02 | Edwin Zenith Gabriel | Simplified buoyancy system for avoiding aircraft crashes |
| CN103318411A (en) * | 2012-03-19 | 2013-09-25 | 陈永春 | Fixed wing vertical takeoff and landing aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050869A (en) * | 2018-07-17 | 2018-12-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of ram-air bleed structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105752347B (en) | 2017-07-21 |
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