CN109367795A - Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement - Google Patents
Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement Download PDFInfo
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- CN109367795A CN109367795A CN201811229915.4A CN201811229915A CN109367795A CN 109367795 A CN109367795 A CN 109367795A CN 201811229915 A CN201811229915 A CN 201811229915A CN 109367795 A CN109367795 A CN 109367795A
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- 230000002146 bilateral effect Effects 0.000 title description 8
- 239000002243 precursor Substances 0.000 claims abstract description 32
- 238000009434 installation Methods 0.000 claims abstract description 10
- 230000035939 shock Effects 0.000 claims abstract description 9
- 230000006835 compression Effects 0.000 claims abstract description 7
- 238000007906 compression Methods 0.000 claims abstract description 7
- 238000007789 sealing Methods 0.000 claims abstract description 4
- 238000002955 isolation Methods 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 229910003460 diamond Inorganic materials 0.000 claims 1
- 239000010432 diamond Substances 0.000 claims 1
- 210000001015 abdomen Anatomy 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 2
- 241000211181 Manta Species 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- NFGXHKASABOEEW-LDRANXPESA-N methoprene Chemical compound COC(C)(C)CCCC(C)C\C=C\C(\C)=C\C(=O)OC(C)C NFGXHKASABOEEW-LDRANXPESA-N 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangement 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—Arrangement 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of high-speed aircraft aerodynamic arrangement structures, Vehicle nose, that is, precursor (1) is designed as axisymmetric centrum, air intake duct (2) are installed in the two sides of the precursor (1), angle (19) are installed and choose 150 °~180 °, the air intake duct (2) compresses air intake duct using binary, carries out two dimensional inlet quasi spline by oblique shock wave theoretical relationship according to " compression shock system (18) sealing " principle.Radar wave transparent performance of the present invention is good, has enough installation spaces, improves the lift resistance ratio of aircraft.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design fields, and in particular to a kind of fuselage bilateral air inlet high-speed flight
Device aerodynamic arrangement structure.
Background technique
Since the 1950s proposes high-speed flight concept, many countries have carried out using Tres Haute Vitesse. Ammunition as using mesh
The research of target air suction type high speed technology.By the effort of decades, in scramjet engine and air suction type high-speed aircraft skill
Art etc. achieves important breakthrough.But current air suction type high-speed aircraft be more for the purpose of technical identification, it is practical
Property consider it is less.By taking X-43, X-51 aircraft in the U.S. as an example, in order to guarantee the performance of scramjet engine, using abdomen
Aerodynamic arrangement's scheme of portion's air inlet, aircraft precursor are especially flat.The major defect of this kind of aerodynamic configuration of aircraft scheme has:
(1) wave transparent for not being able to satisfy radar for flat precursor requires and loading space requirement, the precursor equipped with radar are usually all set
It is calculated as axial symmetry or close to axisymmetric type face；(2) the lip cover inner surface of air intake duct is higher-pressure region, for the layout of abdomen air inlet
Scheme, lip cover higher-pressure region produce the effect of negative lift, reduce the lift resistance ratio of aircraft；(3) placement scheme of abdomen air inlet,
For super burn engine runner close to lower section, leading to jet pipe is asymmetric expansion, may generate negative lift, further decrease flight
The lift resistance ratio of device；(4) this kind of aerodynamic arrangement's the ratio of width to height is smaller, so that it is poor to rise resistive energy.This kind of layout lift resistance ratio is small to be caused to fly
Row voyage is shorter, and radar, undercarriage can not be installed etc., seriously reduce the practical value of such high-speed aircraft.Although beautiful
State's Manta aircraft is double side air inlet placement schemes, but the aircraft precursor is directly as air intake duct compressing surface, equally more
Flat practicability is poor.
Summary of the invention
The present invention need to solve technical problem and be to provide that a kind of radar wave transparent performance is good, has enough installation spaces and lift resistance ratio high
High-speed aircraft aerodynamic arrangement structure.
To solve the above problems, a kind of high-speed aircraft aerodynamic arrangement provided by the invention, takes technical solution as follows:
25000~30000mm of the aircraft overall length, Vehicle nose, that is, precursor design is axisymmetric centrum, in institute
The two sides installation air intake duct of precursor is stated, installation angle chooses 150 °~180 °, and the air intake duct compresses air intake duct using binary, presses
Two dimensional inlet quasi spline, input condition are carried out by oblique shock wave theoretical relationship according to " sealing of compression shock system " principle are as follows:
The Mach number and the angle of attack of the capture area, cruising condition that are determined according to indicators of overall performance；First of compressing surface angle of air intake duct
The semi-cone angle of precursor should be not less than, take 15 °~20 °；The width of air intake duct takes 1000~1200mm.
As a further improvement of that present invention, the cone angle of the precursor takes 30 °~50 °, forebody length according to radar, preceding rise and fall
The loading space of frame determines that precursor bus is using the lesser Feng's karman curve design of wave resistance.
As a further improvement of that present invention, a baffle is designed in the top of the air intake duct, improves air intake duct under positive incidence
Traffic capture characteristic.Baffle leading edge one end takes air intake duct second compressing surface starting point as starting point, and the other end takes air intake duct
Lip cover leading edge is starting point.
As a further improvement of that present invention, the engine is arranged in juxtaposition in fuselage two sides, and the engine includes isolation
Section, combustion chamber and jet pipe, wherein isolation segment length takes 5000~7500mm, and distance piece outlet and axial angle take 5 °~
10°。
As a further improvement of that present invention, it lives engine envelope to form fuselage using smooth surface, the fuselage is maximum
Cross-section location is placed on aircraft bottom, and keeps maximum transversal area minimum.
As a further improvement of that present invention, 2500~3000mm of the fuselage height, 5000~6500mm of width.
As a further improvement of that present invention, the jet pipe length takes 5000~7000mm, jet pipe discharge area with enter
Open area ratio, i.e., expansion ratio takes 5~6.
As a further improvement of that present invention, wing uses double wedge, is made of strake wing and big sweepback tapered airfoil, edge strip
For the wing since the side peak of fuselage, angle of sweep takes 75 °~80 °, with tapered airfoil contact of a curve transition；Tapered airfoil leading-edge sweep
Angle takes 55 °~60 °, and rear sweepforward angle takes 10 °~20 °, and root chord length takes the 40%~50% of aircraft overall length；The length of wing takes
The 70%~90% of fuselage width.
As a further improvement of that present invention, the installation site of V-type vertical fin is close to fuselage tail end, and rudder root spacing takes 3500~
Angle takes 90 ° between 4000mm, V rudder, and leading edge sweep takes 65 °~75 °, and trailing sweep takes 20 °~30 °, and root chord length takes flight
The 12%~15% of device overall length, length takes 2500~3000mm.
As a further improvement of that present invention, in the wing design trailing edge rudder, rudder face width takes 2000~2500mm,
Rudder face length takes the 80%~100% of half length of wing.
As a further improvement of that present invention, vertical fin rear rudder can be designed on the V-type vertical fin, rudder face length takes V-type to hang down
The 70%~80% of tail length, rudder face width take 25% vertical fin root chord length.
The invention has the advantages that:
1. the Forebody/Inlet integrated programme that the present invention proposes a kind of fuselage bilateral air inlet.Precursor is led according to radar etc.
Leader requires the precursor for being designed as an approximate cone, ensure that the wave transparent performance and requirements of installation space of radar.In the two sides of cone
Arrange that binary compresses air intake duct.For the placement scheme of abdomen air inlet, the higher-pressure region of the inner surface of air intake duct lip cover is generated negative
Lift causes lift resistance ratio smaller, air intake duct side arrangement, and what lip cover higher-pressure region generated is lateral force, and being arranged symmetrically can be with
It cancels out each other, will not have a negative impact to aircraft.
2. engine is installed on two sides by the present invention side by side, so that fuselage the ratio of width to height increases very with respect to abdomen air inlet scheme
It is more, improve vehicle lift-drag.Since air inlet scheme fuselage height in two sides is smaller, based on jet pipe is expanded with width direction,
Width direction expansion will not generate negative lift, be conducive to improve vehicle lift-drag.
3. the present invention increases highly sweptback wing, while improving shipping-direction stability using V-type vertical fin, wing, V-type vertical fin can
Rear rudder is designed, vehicle lift-drag is further improved or adjusts longitudinal stability.
Detailed description of the invention
The present invention shares 6 width attached drawings.
Fig. 1 is fuselage bilateral air inlet high-speed aircraft proposed by the present invention aerodynamic arrangement schematic diagram；
Fig. 2 is the top view of bilateral air inlet proposed by the present invention aerodynamic arrangement；
Fig. 3 is the schematic diagram of binary compression air intake duct proposed by the present invention；
Fig. 4 is the front view of bilateral air inlet proposed by the present invention aerodynamic arrangement；
Fig. 5 is the structural schematic diagram of wing of the present invention；
Fig. 6 is V-type vertical fin structural schematic diagram of the present invention.
Wherein: 1 is precursor, and 2 be air intake duct, and 3 be air intake duct baffle, and 4 be fuselage, and 5 be wing, and 6 be trailing edge rudder, 7
For V-type vertical fin, 8 be vertical fin rear rudder, and 9 be radar, and 10 be the cone angle of precursor, and 11 be the bus of precursor, and 12 be nose-gear, 13
It is rear undercarriage for engine, 14,15 be jet pipe, and 16 be isolation segment length, and 17 be distance piece outlet and axial angle, and 18 are
First of compressing surface angle of air intake duct, 19 compression shock systems, 20 be bilateral air intake duct established angle, and 21 be air intake duct width, and 22 be V
The distance between type vertical fin rudder root, 23 angle between V-type vertical fin, 24 be strake wing, and 25 be tapered airfoil, and 26 be strake wing sweepback
Angle, 27 be tapered airfoil leading edge sweep, and 28 be tapered airfoil rear sweepforward angle, and 29 be the rudder root long of tapered airfoil, and 30 be wingspan length,
31 be the width of trailing edge rudder, and 32 be the length of trailing edge rudder, and 33 be V-type vertical fin leading edge sweep, and 34 is after V-type vertical fins
Edge angle of sweep, 35 be rudder root long, and 36 be V-type vertical fin length, and 37 be the length of vertical fin rear rudder, and 38 be the width of vertical fin rear rudder
Degree.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
In one preferred embodiment, 25000~30000mm of aircraft overall length.Vehicle nose's type face two sides master
To be used as air intake duct compressing surface.According to the visual field of radar 9 and sufficient head loading space demand, Vehicle nose, that is, precursor 1
It is designed as axisymmetric cone.
Air intake duct 2 is installed in the two sides of the precursor 1, installation angle 20 chooses 150 °~180 °, and the air intake duct 2 uses
Binary compresses air intake duct, carries out two dimensional inlet type face by oblique shock wave theoretical relationship according to " 19 sealing of compression shock system " principle
Design, input condition have: the Mach number and the angle of attack of the capture area, cruising condition that are determined according to indicators of overall performance；Air intake duct 2
First of compressing surface angle 18 should be not less than the semi-cone angle of precursor 1, take 15 °~20 °, it is ensured that air intake duct 2 merges rear side with precursor 1
Face can maintain always compression, reduce pitot loss；The width 20 of air intake duct 2 takes 1000~1200mm.
Further, in one preferred embodiment, the cone angle 9 of the precursor 1 takes 30 °~50 °, 1 length of precursor
5000~7500mm meets the loading space requirement of radar 9, nose-gear 12, and precursor bus 11 is using the lesser Feng's card of wave resistance
Door curve, expression are as follows:
Wherein, L is curved section theoretical length, and Rd is curved section maximum radius, and x is axial distance, and r is the height under corresponding x
Degree.
After air intake duct 2 is merged with precursor 1, an air intake duct baffle 3 is designed in the top of air intake duct 2, improves air intake duct 2 just
Traffic capture characteristic when the angle of attack.The starting point of 4 one end of baffle leading edge fuselage takes the second compressing surface starting point of air intake duct 2, into
3 outboard end starting point of air flue baffle takes 2 lip leading edge of air intake duct.
For realize precursor 1 and air intake duct 2 type face Combined design, according to CFD (Fluid Mechanics Computation) numerical result
Integrated optimization design further is realized to precursor 1, air intake duct 2.
Further, in one preferred embodiment, engine 13 is arranged in juxtaposition in 4 two sides of fuselage, and engine 13 wraps
Include distance piece, combustion chamber and jet pipe 15.Wherein isolation segment length 16 takes 5000~7500mm, and distance piece outlet is pressed from both sides with axial
Angle 17 takes 5 °~10 °, the installation space of undercarriage 14 after guarantee.Engine, undercarriage envelope are lived into the machine that formed using flat face
Body 4, the 4 maximum cross section position of fuselage are placed on aircraft bottom, and keep maximum transversal area minimum, so that fuselage hinders
Power is minimum.Since 13 two sides of engine are installed side by side, the height of fuselage 4 2500~3000mm, 5000~6500mm of width, the ratio of width to height
Opposite abdomen air inlet scheme increases very much, improves vehicle lift-drag.
Two sides air inlet scheme 4 the ratio of width to height of fuselage are larger, based on jet pipe 15 is expanded with width direction.15 length of jet pipe takes
5000~7000mm, 15 discharge area of jet pipe and inlet area ratio, i.e., expansion ratio takes 5~6.
Further, in one preferred embodiment, since wing 5 is to determine that aircraft longitudinal stability and cruise fly
The important component of galassing weighing apparatus is risen when row, wing 5 uses double wedge, is made of strake wing 24 and big sweepback tapered airfoil 25.Edge strip
For the wing 24 since the side peak of fuselage 4, angle of sweep 26 takes 75 °~80 °, with tapered airfoil contact of a curve transition.Tapered airfoil 25
Leading edge sweep 27 takes 55 °~60 °, and rear sweepforward angle 28 takes 10 °~20 °, root chord length 29 take aircraft overall length 40%~
50%.The length 30 of wing 5 takes the 70%~90% of fuselage width.
The important component of the decision aircraft course stability of V-type vertical fin 7.By optimization design, V-type vertical fin 7 is arranged in machine
4 tail end of body, rudder root spacing 22 take 3500~4000mm, and angle 23 takes 90 ° between V rudder, and leading edge sweep 33 takes 65 °~75 °, rear
Angle of sweep 34 takes 20 °~30 °, and root chord length 35 takes the 12%~15% of aircraft overall length, and length 36 takes 2500~3000mm, meets
Shipping-direction stability determines.
Further, in one preferred embodiment, since rudder face is the important component for determining aircraft control ability,
Trailing edge rudder 6 can be designed in wing 5, rudder face width 31 takes 2000~2500mm, and rudder face length 32 takes 5 half length of wing
80%~100%, meet longitudinally, laterally maneuvering capability demand.Vertical fin rear rudder 8, rudder face length can be designed on V-type vertical fin 7
37 take the 70%~80% of V-type vertical fin length, and rudder face width 38 takes 25% vertical fin root chord length, meets directional control ability need
It asks.
Claims (10)
1. a kind of high-speed aircraft aerodynamic arrangement, which is characterized in that 25000~30000mm of the aircraft overall length, aircraft head
Portion, that is, precursor (1) is designed as axisymmetric centrum, installs air intake duct (2) in the two sides of the precursor (1), installation angle (19) choosing
150 °~180 ° are taken, the air intake duct (2) compresses air intake duct using binary, according to " compression shock system (18) sealing " principle by oblique
Shock theory relational expression carries out two dimensional inlet quasi spline, input condition are as follows: the capture determined according to indicators of overall performance
The Mach number and the angle of attack of area, cruising condition；First of the compressing surface angle (17) of air intake duct (2) should be not less than the half of precursor (1)
Cone angle takes 15 °~20 °；The width (20) of air intake duct (2) takes 1000~1200mm.
2. a kind of high-speed aircraft aerodynamic arrangement according to claim 1, which is characterized in that the cone angle of the precursor (1)
(9) 30 °~50 ° are taken, precursor (1) length is determined according to the loading space of radar (8), nose-gear (11), precursor (1) bus
(10) using the lesser Feng's karman curve design of wave resistance.
3. a kind of high-speed aircraft aerodynamic arrangement according to claim 2, which is characterized in that engine (12) is arranged in juxtaposition
In fuselage (3) two sides, the engine (12) includes distance piece, combustion chamber and jet pipe (14), wherein isolation segment length (15)
5000~7500mm is taken, and distance piece outlet takes 5 °~10 ° with axial angle (16).
4. a kind of high-speed aircraft aerodynamic arrangement according to claim 3, which is characterized in that will be started using smooth surface
Machine (12) envelope lives to be formed fuselage (3), and fuselage (3) the maximum cross section position is placed on aircraft bottom, and makes maximum cross
The area cut is minimum.
5. a kind of high-speed aircraft aerodynamic arrangement according to claim 4, which is characterized in that fuselage (3) height
2500~3000mm, 5000~6500mm of width.
6. a kind of high-speed aircraft aerodynamic arrangement according to claim 5, which is characterized in that jet pipe (14) length takes
5000~7000mm, jet pipe (14) discharge area and inlet area ratio, i.e., expansion ratio takes 5~6.
7. a kind of high-speed aircraft aerodynamic arrangement according to claim 1 or 6, which is characterized in that wing (4) uses diamond shape
Aerofoil profile is made of strake wing (23) and big sweepback tapered airfoil (24), strake wing (23) since the side peak of fuselage (3), after
Sweep angle (25) takes 75 °~80 °, with tapered airfoil contact of a curve transition；Tapered airfoil (24) leading edge sweep (26) takes 55 °~60 °,
Rear sweepforward angle (27) takes 10 °~20 °, and root chord length (28) takes the 40%~50% of aircraft overall length；The length (29) of wing (4)
Take the 70%~90% of fuselage width.
8. a kind of high-speed aircraft aerodynamic arrangement according to claim 7, which is characterized in that the installation position of V-type vertical fin (6)
Nearly fuselage (3) tail end is rested against, rudder root spacing (21) takes 3500~4000mm, and angle (22) takes 90 ° between V rudder, leading edge sweep
(32) 65 °~75 ° are taken, trailing sweep (33) takes 20 °~30 °, and root chord length (34) takes the 12%~15% of aircraft overall length, exhibition
Long (35) take 2500~3000mm.
9. a kind of high-speed aircraft aerodynamic arrangement according to claim 8, which is characterized in that designed in the wing (4)
Trailing edge rudder (5), rudder face width (30) take 2000~2500mm, rudder face length (31) take (4) half length of wing 80%~
100%.
10. a kind of high-speed aircraft aerodynamic arrangement according to claim 9, which is characterized in that in the V-type vertical fin (6)
On can design vertical fin rear rudder (7), rudder face length (36) takes the 70%~80% of V-type vertical fin length, and rudder face width (37) takes
25% vertical fin root chord length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811229915.4A CN109367795A (en) | 2018-10-22 | 2018-10-22 | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811229915.4A CN109367795A (en) | 2018-10-22 | 2018-10-22 | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109367795A true CN109367795A (en) | 2019-02-22 |
Family
ID=65400751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811229915.4A Pending CN109367795A (en) | 2018-10-22 | 2018-10-22 | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127076A (en) * | 2019-05-22 | 2019-08-16 | 中国空气动力研究与发展中心 | A kind of flat roof type Horizontal Take-off and Landing two-stage enters orbit aerocraft level-one aerodynamic arrangement design method |
| CN111003160A (en) * | 2019-11-28 | 2020-04-14 | 中国运载火箭技术研究院 | Self-adaptive high-speed aircraft layout based on wing tip deformation |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
| CN112678206A (en) * | 2020-12-29 | 2021-04-20 | 中国航天空气动力技术研究院 | Pneumatic layout structure and design method of reusable carrier |
| CN112960123A (en) * | 2021-03-26 | 2021-06-15 | 中国商用飞机有限责任公司 | Air inlet valve device of airplane auxiliary power unit |
| CN115507707A (en) * | 2022-09-30 | 2022-12-23 | 西安航天动力研究所 | Aerodynamic layout of a supersonic large maneuvering stealth target |
| CN118728556A (en) * | 2024-05-30 | 2024-10-01 | 南京航空航天大学 | A parametric design method for axisymmetric precooling inlet |
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| US4232515A (en) * | 1978-03-06 | 1980-11-11 | The Boeing Company | Supersonic cruise airplane and engine |
| CN101549758A (en) * | 2009-05-13 | 2009-10-07 | 南京航空航天大学 | Intake and exhaust device of air breathing supersonic/hypersonic aerocraft |
| CN205738058U (en) * | 2016-07-06 | 2016-11-30 | 中国人民解放军海军航空工程学院 | A kind of aerodynamic arrangement of three-control aircraft |
| CN106516086A (en) * | 2016-10-19 | 2017-03-22 | 戈晓宁 | High-invisibility lifting-body configuration aircraft without horizontal tail |
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2018
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4232515A (en) * | 1978-03-06 | 1980-11-11 | The Boeing Company | Supersonic cruise airplane and engine |
| CN101549758A (en) * | 2009-05-13 | 2009-10-07 | 南京航空航天大学 | Intake and exhaust device of air breathing supersonic/hypersonic aerocraft |
| CN205738058U (en) * | 2016-07-06 | 2016-11-30 | 中国人民解放军海军航空工程学院 | A kind of aerodynamic arrangement of three-control aircraft |
| CN106516086A (en) * | 2016-10-19 | 2017-03-22 | 戈晓宁 | High-invisibility lifting-body configuration aircraft without horizontal tail |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127076A (en) * | 2019-05-22 | 2019-08-16 | 中国空气动力研究与发展中心 | A kind of flat roof type Horizontal Take-off and Landing two-stage enters orbit aerocraft level-one aerodynamic arrangement design method |
| CN111003160A (en) * | 2019-11-28 | 2020-04-14 | 中国运载火箭技术研究院 | Self-adaptive high-speed aircraft layout based on wing tip deformation |
| CN111380409A (en) * | 2020-03-30 | 2020-07-07 | 航天神舟飞行器有限公司 | Stealthy rudder face mounting structure of all-wing aircraft overall arrangement target drone aircraft |
| CN112678206A (en) * | 2020-12-29 | 2021-04-20 | 中国航天空气动力技术研究院 | Pneumatic layout structure and design method of reusable carrier |
| CN112960123A (en) * | 2021-03-26 | 2021-06-15 | 中国商用飞机有限责任公司 | Air inlet valve device of airplane auxiliary power unit |
| CN112960123B (en) * | 2021-03-26 | 2023-11-07 | 中国商用飞机有限责任公司 | Intake valve device of auxiliary power unit of airplane |
| CN115507707A (en) * | 2022-09-30 | 2022-12-23 | 西安航天动力研究所 | Aerodynamic layout of a supersonic large maneuvering stealth target |
| CN118728556A (en) * | 2024-05-30 | 2024-10-01 | 南京航空航天大学 | A parametric design method for axisymmetric precooling inlet |
| CN118728556B (en) * | 2024-05-30 | 2025-04-01 | 南京航空航天大学 | A parametric design method for axisymmetric precooling inlet |
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