CN110406671A - A kind of side air inlet high-speed aircraft - Google Patents
A kind of side air inlet high-speed aircraft Download PDFInfo
- Publication number
- CN110406671A CN110406671A CN201910689158.7A CN201910689158A CN110406671A CN 110406671 A CN110406671 A CN 110406671A CN 201910689158 A CN201910689158 A CN 201910689158A CN 110406671 A CN110406671 A CN 110406671A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- point
- wing
- aircraft
- cone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000013461 design Methods 0.000 claims abstract description 11
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 230000035939 shock Effects 0.000 claims description 8
- 241000397426 Centroberyx lineatus Species 0.000 claims description 7
- 238000004080 punching Methods 0.000 claims description 3
- 230000003187 abdominal effect Effects 0.000 abstract description 3
- 238000005056 compaction Methods 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- 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
-
- 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
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
-
- 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
- B64D2033/0266—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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of side air inlet high-speed aircraft, including body, the lower section of body is equipped with lower aerofoil, and the high pressure capture wing is provided with above body, and body is internally provided with airbreathing motor, and the front end of airbreathing motor is equipped with air inlet；The lower section of lower aerofoil has been sequentially arranged cone and gas flow from front to back；Cone extends from the front direction aircraft rear of aircraft and lower section, and the width of cone is less than the width of corresponding lower aerofoil；Gas flow is located at the two sides of cone, and the air inlet of airbreathing motor is located at the rear of gas flow, and airbreathing motor is mounted on the lower section of lower aerofoil by the present invention, and body abdominal space is released, and can use entirely as lifting surface；Air inlet is placed in aircraft front end two sides, waverider forebody derived design can be used, make full use of the homogeneous compaction characteristic of Waverider, on the one hand can effectively promote the performance of engine, complete machine lift resistance ratio characteristic can also effectively on the other hand be promoted using waverider forebody derived.
Description
Technical field
The present embodiments relate to high-speed aircraft engineering device technique fields, and in particular to a kind of side air inlet high-speed flight
Device.
Background technique
High-speed aircraft refers mainly to all kinds of supersonic speed or hypersonic vehicle.It is usually 1.2~5.0 Mach number M
Flight is known as supersonic flight；Flight of the Mach number M greater than 5.0 is known as hypersonic flight.Novel high speed aircraft configurations are set
Meter is the high lift-drag ratio configuration design of the hot issue of current aircraft development, especially drive.
In the prior art, one kind is motorless glide vehicle, captures the wing by side's arrangement overhead on board the aircraft,
Lift resistance ratio, such as CN103350750A can be effectively promoted, the high pressure capture wing is provided with above aircraft body；Compare again
If CN104354852A discloses a kind of high-speed aircraft, have and above set the wing, essence is also that high pressure captures the wing.But it is above-mentioned special
The high pressure capture wing of benefit is essentially arc structure, fixation not easy to install, and easily deformable, needs relatively high machining accuracy.Separately
A kind of high-speed aircraft then mainly configures engine, however although engine is capable of providing power, but due to self weight and volume
It is larger, cause aircraft capacity limited, it is difficult to meet long-range, quick, large capacity transportation demand.Currently, not yet by high pressure
The capture wing and airbreathing motor are used for the research of high-speed aircraft simultaneously, especially for the arrangement of aspirated engine,
There is important influence for the performance of entire aircraft.
On the other hand, the structure design of the high pressure capture wing itself also directly affects the performance of aircraft, although it is one
It is capable of providing lift compensation under fixed condition, but also the resistance of body and weight can simultaneously increased.Therefore, the wing of the high pressure capture wing
Type design is most important.Inventor is it is proposed that a kind of configuration for capturing the wing, in academic paper " Hypersonic I-shaped
Aerodynamic configurations, Science China Physics, mechanics&Astronomy, vol.61
In No.2,2018 " Fig. 1, a kind of general shape for capturing the wing is illustrated, front side uses swept design, and tail portion has big
Supporting surface, and for high-speed aircraft, the tail portion that high pressure captures the wing is nearby low-pressure area, cannot not only generate lift,
Also certain frictional resistance can be brought due to the wetted area of itself, aeroperformance is not high.Fly for hypersonic
For row device, due to the presence of intense shock wave, pressure drag is sharply increased, and causes lift resistance ratio performance to decline, therefore high-speed aircraft
Wing generally using big sweepback design.
Summary of the invention
For this purpose, the embodiment of the present invention provides a kind of side air inlet high-speed aircraft, to solve in the prior art due to swashing by force
The presence of wave, cause lift resistance ratio performance decline the problem of.
To achieve the goals above, the embodiment of the present invention provides the following technical solutions:
A kind of side air inlet high-speed aircraft, including body, the lower section of the body are equipped with lower aerofoil, the body it is upper
Side is provided with the high pressure capture wing, and the body is internally provided with airbreathing motor, and the front end of the airbreathing motor is set
There is air inlet；The lower section of the lower aerofoil has been sequentially arranged cone and gas flow from front to back；
The cone extends from the front direction aircraft rear of aircraft and lower section, and the width of the cone is less than correspondence
Lower aerofoil width；The gas flow is located at the two sides of cone, and the air inlet of the airbreathing motor is located at gas stream
The rear in road.
The embodiment of the present invention is further characterized in that, in terms of the side of the body, the air inlet of the airbreathing motor
Outside gradually restrain, triangular shape on the whole, and the rear of the air inlet smoothly transits with lower aerofoil and connect.
The embodiment of the present invention is further characterized in that, lower case is additionally provided with below the lower aerofoil, and the lower case will
Gas flow is fully wrapped around in internal body.
The embodiment of the present invention is further characterized in that the aircraft front end forms compression shock, the airbreathing motor
Air inlet be located at after the compression shock.
The embodiment of the present invention is further characterized in that the airbreathing motor is punching engine.
The embodiment of the present invention is further characterized in that the high pressure capture wing has symmetrical configurations, throwing in the horizontal plane
Shadow has the axis of symmetry along front-rear direction, and on the axis of symmetry, the front end of the high pressure capture wing is defined as A point, from
A point starts to reach the farthest point B point of side, line and horizontal line between A point and B point to two sides sweepback along smooth curve
Angle be the first angle α, and 30 ° < α < 50 °.
The embodiment of the present invention is further characterized in that the rear portion of the high pressure capture wing uses the swept design of swallow-tail form,
High pressure captures flank portion and extends to C point backward along straight line from farthest point B point, and the end point on the axis of symmetry is defined as D point,
The angle of line and the axis of symmetry between C point and D point is the second angle β, 45 ° < β < 90 °.
The embodiment of the present invention has the advantages that
(1) airbreathing motor is mounted on the lower section of lower aerofoil by the present invention, and body abdominal space is released, can be complete
It is used entirely as lifting surface；Air inlet is placed in aircraft front end two sides, can be designed using waverider forebody derived, make full use of rider
On the one hand the homogeneous compaction characteristic of body can effectively promote the performance of engine, on the other hand can also be effective using waverider forebody derived
Promote complete machine lift resistance ratio characteristic；
(2) 30 ° < α < 50 ° in angle of sweep of the invention, sweepback degree are caught relative to the high pressure of traditional hypersonic aircraft
It is smaller to obtain the wing, higher-pressure region can be captured as much as possible；And the tail portion of the high pressure capture wing also uses the swept-back of similar swallow-tail form
Design, can more effectively utilize higher-pressure region；It can reduce architecture quality after plane of symmetry tail portion is cut out, wing area reduces, can make
Structural strength increases；Using swallow-tail form, so that higher-pressure region is more concentrated on high pressure capture wing middle position, makes to press heart position forward,
More easily realize trim；
(3) present invention is applied in high-speed aircraft by combining airbreathing motor and the high pressure capture wing, and one
Aspect, due to being mounted with that the high pressure capture wing improves the lift resistance ratio of aircraft, so that the design of large scale high-speed aircraft
It is possibly realized, to accommodate airbreathing motor and fuel；On the other hand, the installation of airbreathing motor is effectively promoted again
The speed and voyage of aircraft, to meet the demand to long-range fast transportation.
Detailed description of the invention
It, below will be to embodiment party in order to illustrate more clearly of embodiments of the present invention or technical solution in the prior art
Formula or attached drawing needed to be used in the description of the prior art are briefly described.It should be evident that the accompanying drawings in the following description is only
It is merely exemplary, it for those of ordinary skill in the art, without creative efforts, can also basis
The attached drawing of offer, which is extended, obtains other implementation attached drawings.
Structure depicted in this specification, ratio, size etc., only to cooperate the revealed content of specification, for
Those skilled in the art understands and reads, and is not intended to limit the invention enforceable qualifications, therefore does not have technical
Essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size are not influencing the function of the invention that can be generated
Under effect and the purpose that can reach, should all still it fall in the range of disclosed technology contents obtain and can cover.
Fig. 1 is the overall structure diagram of aircraft of the present invention；
Fig. 2 is the three dimensional structure diagram of aircraft of the present invention；
Fig. 3 is the side structure schematic diagram of aircraft of the present invention；
Fig. 4 is the present invention looks up structural representation of aircraft of the present invention；
Fig. 5 is the positive structure schematic of aircraft of the present invention；
Fig. 6 is that the high pressure of aircraft of the present invention captures the overlooking structure diagram of the wing.
In figure:
1- body；2- lower aerofoil；3- high pressure captures the wing；5- airbreathing motor；6- air inlet；The 7- axis of symmetry；
21- cone；22- gas flow；23- lower case.
Specific embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book is understood other advantages and efficacy of the present invention easily, it is clear that described embodiment is the present invention one
Section Example, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art are not doing
Every other embodiment obtained under the premise of creative work out, shall fall within the protection scope of the present invention.
As shown in Figures 1 to 5, side air inlet high-speed aircraft includes body 1, and the lower section of the body 1 is equipped with lower aerofoil
2, the top of the body 1 is provided with the high pressure capture wing 3, is provided with airbreathing motor 5 in the inside of the body 1, described
The front end of airbreathing motor 5 is equipped with air inlet 6.Airbreathing motor 5 is preferably punching engine.The airbreathing motor
(5) for along symmetrical several of the axis of symmetry (7).And aircraft front end forms compression shock 4, airbreathing motor 5
Air inlet 6 be located at after compression shock 4.
The lower section of the lower aerofoil 2 has been sequentially arranged cone 21 and gas flow 22 from front to back；The cone 21 from fly
The front direction aircraft rear of row device and lower section extend, and the width of the cone 21 is less than the width of corresponding lower aerofoil 2；Institute
The two sides that gas flow 22 is located at cone 21 are stated, the air inlet 6 of the airbreathing motor 5 is located at the rear of gas flow 22.
Air inlet 6 is placed in aircraft front end two sides, can be designed using waverider forebody derived, make full use of the uniform of Waverider
On the one hand compression property can effectively promote the performance of engine, on the other hand can also effectively promote complete machine using waverider forebody derived
Lift resistance ratio characteristic.
Preferably for the shape of air intake duct, as shown in Figure 3 and Figure 4, in terms of the side of body, the outside of air intake duct by
It tapers and holds back, on the whole at triangle.
Preferably, the rear of air intake duct and the smooth excessive connection of lower aerofoil 2 have lower case 23, by airbreathing motor 5
Inner flow passage is fully wrapped around inside body 1, and 1 abdominal space of body is released, and can use entirely as lifting surface.
Fig. 6 is the top view that high pressure captures the wing 3, and projection in the horizontal plane, front end rear end are all made of swept-back and set
Meter.As shown, the entire high pressure capture wing 3 has symmetrical constitutive character, there is line of symmetry 7 along front-rear direction, it, will on line of symmetry
The front end of the high pressure capture wing 3 is defined as A point, reaches the farthest point of side to two sides sweepback along smooth curve since A point
B point, line and horizontal angle between A, B are the first angle α namely angle of sweep, extend to C backward finally along straight line
Point, the distance of A, C two o'clock constitute the maximum length of the high pressure capture wing 3, and the end point on line of symmetry is defined as D point, D, C it
Between line and the angle of line of symmetry be the second angle β.
For hypersonic aircraft, due to the presence of intense shock wave, pressure drag is sharply increased, and leads to lift resistance ratio
It can decline, therefore general aft swept wings, α > 50 °.And the high pressure capture wing 3 is different from conventional airfoil, it is using on body
High pressure caused by surface compression increases lift, and therefore, the high pressure capture wing 3 costa will not only comprehensively consider reduction wave resistance,
Also to consider to capture higher-pressure region as much as possible, thus sweepback degree relative to traditional hypersonic aircraft wing compared with
It is small.In present embodiment, wing uses sweepback form, 30 ° < α < 50 °, can both effectively reduce wave resistance, can also effectively capture
Higher-pressure region.In addition, compared with the existing technology, the tail portion of the high pressure capture wing 3 also uses the swept design of similar swallow-tail form, 45 ° <
β<90°.It has the advantage that the tail portion plane of symmetry is nearby low-pressure area, cannot not only generate lift, it can also moistening due to itself
Area brings certain frictional resistance, can more effectively utilize higher-pressure region using this swallow-tail form；Plane of symmetry tail portion is cut out
After can reduce architecture quality, wing area reduces, and structural strength can be made to increase；Using swallow-tail form, higher-pressure region is made more to concentrate on height
Pressure capture 3 middle position of the wing, makes to press heart position forward, it is easier to realize trim.
Although above having used general explanation and specific embodiment, the present invention is described in detail, at this
On the basis of invention, it can be made some modifications or improvements, this will be apparent to those skilled in the art.Therefore,
These modifications or improvements without departing from theon the basis of the spirit of the present invention are fallen within the scope of the claimed invention.
Claims (7)
1. the lower section of a kind of side air inlet high-speed aircraft, including body (1), the body (1) is equipped with lower aerofoil (2), described
The high pressure capture wing (3) is provided with above body (1), it is characterised in that: the air suction type that is internally provided with of the body (1) starts
The front end of machine (5), the airbreathing motor (5) is equipped with air inlet (6)；The lower section of the lower aerofoil (2) is from front to back sequentially
It is provided with cone (21) and gas flow (22)；
The cone (21) extends from the front direction aircraft rear of aircraft and lower section, and the width of the cone (21) is less than
The width of corresponding lower aerofoil (2)；The gas flow (22) is located at the two sides of cone (21), the airbreathing motor (5)
Air inlet (6) be located at the rear of gas flow (22).
2. a kind of side air inlet high-speed aircraft according to claim 1, it is characterised in that: from the side of the body (1)
Face sees that the outside of the air inlet (6) of the airbreathing motor (5) is gradually restrained, triangular shape, and the air inlet on the whole
The rear of mouth (6) smoothly transits with lower aerofoil (2) to be connect.
3. a kind of side air inlet high-speed aircraft according to claim 1, it is characterised in that: under the lower aerofoil (2)
Side is additionally provided with lower case (23), and the lower case (23) is fully wrapped around internal in body (1) by gas flow (22).
4. a kind of side air inlet high-speed aircraft according to claim 1, it is characterised in that: the aircraft front end is formed
The air inlet (6) of compression shock (4), the airbreathing motor (5) is located at after the compression shock (4).
5. a kind of side air inlet high-speed aircraft according to claim 1, it is characterised in that: the airbreathing motor
It (5) is punching engine.
6. a kind of side air inlet high-speed aircraft according to claim 1, it is characterised in that: the high pressure captures the wing (3)
With symmetrical configurations, projection in the horizontal plane has the axis of symmetry (7) along front-rear direction, in the axis of symmetry (7)
On, the front end of the high pressure capture wing (3) is defined as A point, reaches side to two sides sweepback along smooth curve since A point
Farthest point B point, line between A point and B point and horizontal angle are the first angle α, and 30 ° < α < 50 °.
7. a kind of side air inlet high-speed aircraft according to claim 6, it is characterised in that: the high pressure captures the wing (3)
Rear portion use the swept design of swallow-tail form, high pressure captures the wing (3) side and from farthest point B point extends to C backward along straight line
Point, the end point on the axis of symmetry (7) are defined as D point, and the angle of the line between C point and D point and the axis of symmetry (7) is the
Two angle β, 45 ° < β < 90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910689158.7A CN110406671A (en) | 2019-07-29 | 2019-07-29 | A kind of side air inlet high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910689158.7A CN110406671A (en) | 2019-07-29 | 2019-07-29 | A kind of side air inlet high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110406671A true CN110406671A (en) | 2019-11-05 |
Family
ID=68363751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910689158.7A Pending CN110406671A (en) | 2019-07-29 | 2019-07-29 | A kind of side air inlet high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110406671A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1818257A2 (en) * | 2006-02-14 | 2007-08-15 | Lockheed Martin Corporation | Integrated inward turning inlets and nozzles for hypersonic air vehicles |
| US20070252028A1 (en) * | 2003-07-03 | 2007-11-01 | Morgenstern John M | Passive aerodynamic sonic boom suppression for supersonic aircraft |
| CN101384486A (en) * | 2005-12-15 | 2009-03-11 | 湾流航空公司 | Isentropic compression inlet for supersonic aircraft |
| CN103350750A (en) * | 2012-12-20 | 2013-10-16 | 中国科学院力学研究所 | Lift compensation type high speed aircraft |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| CN104964610A (en) * | 2015-06-29 | 2015-10-07 | 华中科技大学 | Wave-rider configuration unmanned target drone |
| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN109850180A (en) * | 2019-01-23 | 2019-06-07 | 中国人民解放军国防科技大学 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
| CN210258830U (en) * | 2019-07-29 | 2020-04-07 | 中国科学院力学研究所 | High-speed aircraft with side air inlet |
-
2019
- 2019-07-29 CN CN201910689158.7A patent/CN110406671A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070252028A1 (en) * | 2003-07-03 | 2007-11-01 | Morgenstern John M | Passive aerodynamic sonic boom suppression for supersonic aircraft |
| CN101384486A (en) * | 2005-12-15 | 2009-03-11 | 湾流航空公司 | Isentropic compression inlet for supersonic aircraft |
| EP1818257A2 (en) * | 2006-02-14 | 2007-08-15 | Lockheed Martin Corporation | Integrated inward turning inlets and nozzles for hypersonic air vehicles |
| CN103350750A (en) * | 2012-12-20 | 2013-10-16 | 中国科学院力学研究所 | Lift compensation type high speed aircraft |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
| CN104964610A (en) * | 2015-06-29 | 2015-10-07 | 华中科技大学 | Wave-rider configuration unmanned target drone |
| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN109850180A (en) * | 2019-01-23 | 2019-06-07 | 中国人民解放军国防科技大学 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
| CN210258830U (en) * | 2019-07-29 | 2020-04-07 | 中国科学院力学研究所 | High-speed aircraft with side air inlet |
Non-Patent Citations (1)
| Title |
|---|
| 李广利: "高压捕获翼位置设计方法研究", 《力学学报》, vol. 48, no. 03, pages 576 - 584 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2494008C2 (en) | High-efficiency supersonic wing with laminar flow | |
| EP2281747A3 (en) | Aircraft | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| CN108639339B (en) | Pneumatic layout of unmanned aerial vehicle | |
| CN107867387B (en) | Outflow Waverider aircraft layout in a kind of | |
| CN109612340A (en) | A kind of high stealthy target drone of high speed high maneuver | |
| CN109050918A (en) | A kind of low speed target drone aerodynamic arrangement | |
| CN106043668A (en) | Aerodynamic configuration of three-surface aircraft | |
| CN110341933A (en) | A kind of air suction type high-speed aircraft with the high pressure capture wing | |
| CN109367795A (en) | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement | |
| CN210258830U (en) | High-speed aircraft with side air inlet | |
| CN210258809U (en) | High-speed aircraft based on high-pressure capture wing appearance | |
| CN105564638A (en) | Special airplane pneumatic configuration | |
| CN102642613B (en) | Low-resistance fairing of corrugate sheath | |
| US20240124121A1 (en) | Aviation turbofan engine and fan duct nozzle | |
| CN110406671A (en) | A kind of side air inlet high-speed aircraft | |
| CN110341932A (en) | A kind of high-speed aircraft based on high pressure capture contour of flange | |
| CN210258810U (en) | Air suction type high-speed aircraft with high-pressure capture wings | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN203714171U (en) | High-efficient and stable oblique inverter wing | |
| CN109263855B (en) | Pneumatic layout of ultra-large aspect ratio aircraft adopting trailing edge supporting wings | |
| CN108502138A (en) | A kind of buzzard-type wing expanded letter high subsonic flight device aerodynamic arrangement using leading edge braced wing | |
| JP2622670B2 (en) | Supersonic aircraft wing | |
| CN115924059A (en) | Single sweepback flying wing horizontal tail fusion pneumatic layout aircraft | |
| CN214057884U (en) | Combined aircraft layout |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |