CN108995803A - A kind of folding Waverider aerodynamic arrangement of supersonic airliner - Google Patents
A kind of folding Waverider aerodynamic arrangement of supersonic airliner Download PDFInfo
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- CN108995803A CN108995803A CN201810587782.1A CN201810587782A CN108995803A CN 108995803 A CN108995803 A CN 108995803A CN 201810587782 A CN201810587782 A CN 201810587782A CN 108995803 A CN108995803 A CN 108995803A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
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- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention principally falls into Waverider aerodynamic arrangement technical field, and in particular to a kind of folding Waverider aerodynamic arrangement of supersonic airliner.Folding Waverider aerodynamic arrangement, including fuselage, main wing, strake wing, vertical fin, the buzzard-type wing on the main wing, canard and power device, the sweepforward angle of the angle of sweep of the canard and the buzzard-type wing can be adjusted；It can make the Waverider aerodynamic arrangement that deployed configuration or folding configuration be presented by the angle of sweep of the adjusting canard and the sweepforward angle of the buzzard-type wing；The deployed configuration has high aspect ratio, takes off, lands and suitable for transonic speed cruising suitable for low subsonic speed；The folding configuration is the configuration of Waverider, is suitable for supersonic cruising.The folding Waverider aerodynamic arrangement has taken into account landing, the transonic speed advantage of flight and supersonic cruising.
Description
Technical field
The present invention principally falls into Waverider aerodynamic arrangement technical field, and in particular to a kind of folding of supersonic airliner
Waverider aerodynamic arrangement.
Background technique
Improving cruising speed is always pursuing a goal for passenger plane travelling flight, and global economy, Fusion of Culture degree are very high at present,
Intercontinental travelling is not rarely seen, even if most fast jet airliner is also required to just be able to achieve intercontinental travelling in more than ten hour at present,
Comfort level, timeliness are all unsatisfactory, and supersonic airliner becomes the focus of people's research again.
In recent years, researcher proposes the imagination that lift is generated using shock wave two-way pressure difference, and this nowed forming claims
Be shock wave-dilatational wave flow pattern.Using the aircraft of this flow pattern " rider aircraft ", i.e. Waverider, flight Mach number is most
Height can achieve 20.The shape of this aircraft is streamlined, and all leading edges all have attached shock, can be applied to ultrasound
The aircraft of speed.Its principle is that the high-pressure fluid after shock wave is limited in the lower surface of aircraft, and shock wave is attached to aircraft
Lower surface, it just looks like that riding is flown on shock wave.It avoids shock wave around leading edge in design as far as possible, is leaked to upper surface, thus
In design angle-of-attack range, the lift resistance ratio more much higher than normal configuration is obtained.This aircraft can satisfy people and fly to supersonic speed
The demand of row device realizes the ideal of rapid journey.
Military Waverider aircraft has already appeared, Luo Keweier company of the U.S. when studying XB-70 supersonic bomber, if
The huge wedge-shaped air intake duct of enging cabin and one is placed in the belly of XB-70 aircraft by meter teacher, when aircraft is with Mach number 3
When speed flight, the shock wave issued by wedge-shaped air intake duct top concentrates the lower surface for acting on wing, makes the pressure of wing lower surface
Power increases suddenly, then produces additional lift.This lift newly increased becomes compression lift or shock wave lift, and the value is about
The 30% of full machine lift is accounted for, does not increase corresponding resistance at this time, so that aircraft supersonic speed lift resistance ratio increases, to improve super
The economy when velocity of sound is cruised.
Since Waverider proposes, about the research of waverider-derived, the especially research in supersonic flight field
Through relatively mature.But in wide Mach number field, traditional Waverider, which is applied, has intrinsic limitation, especially low speed
Flight, the aircraft of Waverider cannot play its advantage, presently, there are main problem have:
(1) since Waverider layout is primarily adapted for use in the supersonic flight stage, in subsonic speed even transonic speed state
Under, since aspect ratio is lower, cause Waverider passenger plane slope of lift curve at this time very low, and induction with higher hinders
Power further reduced the lift resistance ratio under its low speed；
(2) the aircraft length of Waverider layout is smaller, is difficult to arrange the high lift device of sufficient size, landing shape in rear
Aeroperformance under state is poor, needs biggish landing head that can just meet the requirements；
(3) low aspect ratio causes slope of lift curve to reduce, therefore the landing of Waverider layout needs biggish take-off attitude angle,
The undesirable pneumatic phenomenons such as air-flow separation are easily caused in Waverider leeward at this time.
Based on above-mentioned analysis, therefore to obtain the aircraft of preferable aeroperformance in wide fast domain, it is necessary to further grind
Study carefully, design the novel aircraft with high low speed pneumatic design matching effect of one kind also needs other than meeting supersonic cruising
Take into account the flying quality under takeoff and landing performance and subsonic speed.
Summary of the invention
In view of the above technical problems, the present invention provides a kind of folding Waverider aerodynamic arrangement of supersonic airliner.Its
Main design idea is concluded are as follows: is deployed configuration when low subsonic speed takeoff and anding and transonic speed cruise (if any), is used at this time
Buzzard-type wing on small sweepback canard and main wing improves takeoff and landing performance to improve lift resistance ratio；It is folding structure when supersonic cruising
Type, the buzzard-type wing on main wing rotates around the axis to change sweepforward angle at this time, is tightly attached to fuselage two sides, while small sweepback canard is also opened
Beginning, which becomes sweepback rotation, increases its angle of sweep, and final canard, main wing form the configuration of a Waverider with fuselage, is very suitable to surpass
Velocity of sound cruise.The aerodynamic arrangement is other than meeting supersonic cruising, additionally it is possible to take into account the flight under takeoff and landing performance and subsonic speed
Performance.
The present invention is achieved by the following technical solutions:
A kind of folding Waverider aerodynamic arrangement of supersonic airliner, including fuselage, main wing, strake wing, vertical fin, be located at it is described
The sweepforward angle of buzzard-type wing, canard and power device on main wing, the angle of sweep of the canard and the buzzard-type wing can be adjusted；
It can make the Waverider aerodynamic arrangement that exhibition be presented by the angle of sweep of the adjusting canard and the sweepforward angle of the buzzard-type wing
Open configuration or folding configuration；
The aspect ratio of the deployed configuration can reach 6.0 or more, takes off, lands and is suitable for transonic speed suitable for low subsonic speed
Cruise；
The folding configuration is the configuration of Waverider, is suitable for supersonic cruising.
Further, the canard is connect with the fuselage, particular by the pivot machine that the canard wing root is arranged in
The reinforcing frame of structure and the fuselage is attached, and shaft hole and shaft are arranged on the hinge mechanism, can pass through described turn
Axis adjusts the canard angle of sweep.
Further, the Waverider aerodynamic arrangement from the deployed configuration variation be the folding configuration during,
The canard angle of sweep increases to 70 ° ~ 78 ° leading edge sweeps of folded state from 15 ° ~ 22 ° leading edge sweeps of unfolded state,
The final rear for realizing canard is parallel with the leading edge of main wing, completes the variation at canard angle of sweep in folding process；
Further, the buzzard-type wing is connect with the main wing, particular by the pivot machine that the buzzard-type wing wing root is arranged in
Structure is connect with the front spar of the main wing, and shaft hole and shaft are arranged on the hinge mechanism, can pass through the shaft tune
Save the sweepforward angle of the buzzard-type wing.
Further, the Waverider aerodynamic arrangement from the deployed configuration variation be the folding configuration during,
The sweepforward angle of the buzzard-type wing increases to 85 ° ~ 90 ° of folded state from 37 ° ~ 47 ° of unfolded state, final realization buzzard-type wing
Leading edge fits with fuselage, completes the variation of the sweepforward angle of buzzard-type wing in folding process, in folded state, sweepforward nose of wing and machine
Body does not have any connection, and buzzard-type wing is connected on main wing always.
The connection type of main wing and fuselage: main wing is hinged by front and back spar and fuselage reinforcing frame；
Strake wing and fuselage connection type: the strake wing and fuselage are in semi-fusion state, pass through the rib and fuselage at wing root
Frame is hingedly attached.
A kind of change of configuration method of the folding Waverider aerodynamic arrangement of supersonic airliner, the method use described in
Folding Waverider aerodynamic arrangement, the method can realize deployed configuration and folding configuration according to the demand of state of flight
Phase co-conversion, to realize optimal flying quality under different flight state.
Further, the up-front angle of sweep of canard is adjusted to gradually increase, until the rear of canard is parallel with the leading edge of main wing,
And the sweepforward angle for adjusting buzzard-type wing gradually increases, until the leading edge of buzzard-type wing fits with fuselage；At this point, the same machine of canard, main wing
Body forms the configuration of a Waverider, that is, completes the transformation from deployed configuration to folding configuration.
Further, method of converting of the realization folding configuration to deployed configuration are as follows: adjust the up-front angle of sweep of canard gradually
Reduce, until the canard angle of sweep reaches 15 ° ~ 22 ° of range, and the sweepforward angle for adjusting buzzard-type wing is gradually reduced, until before
The sweepforward angle for plunderring the wing reaches 37 ° ~ 47 ° of range, completes the transformation from folding configuration to deployed configuration.
Advantageous effects of the invention:
(1) under low subsonic speed, folding Waverider aerodynamic arrangement is in expansion structure for Waverider aerodynamic arrangement of the present invention
Type has biggish aspect ratio, gives full play to buzzard-type wing and the aerodynamic advantages of canard under the low speed, thus its low speed landing is maximum
Lift coefficient is apparently higher than traditional Waverider, can reach 1.2 or more, is suitble to take-off and landing；
(2) Waverider aerodynamic arrangement of the present invention transonic speed when, the deployed configuration of folding Waverider aerodynamic arrangement is opposite
It is laid out in traditional Waverider, there is good low speed aerodynamic characteristic, stalling angle is suitble to transonic speed cruise up to 16 ° or more.
(3) under Waverider aerodynamic arrangement of the present invention supersonic speed, folding Waverider aerodynamic arrangement is punctured into tradition
Waverider aerodynamic arrangement.
(4) folding Waverider of the present invention aerodynamic arrangement taken into account landing, transonic speed flight and supersonic speed patrol
The advantage of boat is a kind of seating plane aerodynamic arrangement that can be used for high low speed aerodynamic characteristic matched design, can be supersonic speed visitor
Machine design provides reference.
(5) folding Waverider of the present invention aerodynamic arrangement combines compared with high aspect ratio canard, buzzard-type wing and multiplies
The advantages of wave body, it is contemplated that the compromise of high low speed aerodynamic characteristic has unique change sweepback canard and open-close type buzzard-type wing, is one
Aerodynamic arrangement's form of the novel wide area Mach number of kind (the cruise Mach number scope of application is 0.78 ~ 3.0) seating plane.
Detailed description of the invention
Figure 1A is the deployed configuration (perspective view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Figure 1B is the deployed configuration (top view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 1 C is the deployed configuration (front view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 1 D is the deployed configuration (side view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 2A is the folding configuration (perspective view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 2 B is the folding configuration (top view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 2 C is the folding configuration (front view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention；
Fig. 2 D is the folding configuration (side view) of folding Waverider aerodynamic arrangement described in the embodiment of the present invention.
Fig. 3 is that the slave deployed configuration of folding Waverider aerodynamic arrangement described in the embodiment of the present invention is changed into folding structure
The schematic diagram of type.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is explained in further detail.It should be appreciated that specific embodiment described herein is used only for explaining the present invention, and
It is not used in the restriction present invention.
On the contrary, the present invention covers any substitution done on the essence and scope of the present invention being defined by the claims, repairs
Change, equivalent method and scheme.Further, in order to make the public have a better understanding the present invention, below to of the invention thin
It is detailed to describe some specific detail sections in section description.Part without these details for a person skilled in the art
The present invention can also be understood completely in description.
Embodiment 1:
The present embodiment provides a kind of folding Waverider aerodynamic arrangement of supersonic airliner, including fuselage, main wing, strake wing,
Before vertical fin, the buzzard-type wing on the main wing, canard and power device, the angle of sweep of the canard and the buzzard-type wing
Sweep angle can be adjusted；It can make the Waverider gas by the angle of sweep of the adjusting canard and the sweepforward angle of the buzzard-type wing
Deployed configuration or folding configuration is presented in dynamic layout (as shown in Figure 1A-D and Fig. 2A-D)；
The deployed configuration aspect ratio reaches 6.0 or more, takes off, lands and suitable for transonic speed patrolling suitable for low subsonic speed
Boat；
The folding configuration is the configuration of Waverider, is suitable for supersonic cruising.
The canard is connect with the fuselage, particular by the hinge mechanism and the machine that the canard wing root is arranged in
The reinforcing frame of body is attached, and shaft hole and shaft are arranged on the hinge mechanism, can be by described rotation shaft regulated described
Canard angle of sweep.
The Waverider aerodynamic arrangement from the deployed configuration variation be the folding configuration during, after the canard
Sweep angle increases to 70 ° ~ 78 ° leading edge sweeps of folded state from 15 ° ~ 22 ° leading edge sweeps of unfolded state, finally realizes duck
The rear of the wing and the leading edge of main wing are parallel, complete the variation at canard angle of sweep in folding process；
The buzzard-type wing is connect with the main wing, particular by the hinge mechanism and the master that the buzzard-type wing wing root is arranged in
The front spar of the wing connects, and shaft hole and shaft are arranged on the hinge mechanism, can pass through the rotation shaft regulated sweepforward
The sweepforward angle of the wing.
The Waverider aerodynamic arrangement from the deployed configuration variation be the folding configuration during, the buzzard-type wing
Sweepforward angle increase to 85 ° ~ 90 ° of folded state from 37 ° ~ 47 ° sweepforward angles of unfolded state, the final leading edge for realizing buzzard-type wing
It fits with fuselage, completes the variation of the sweepforward angle of buzzard-type wing in folding process, in folded state, sweepforward nose of wing does not have with fuselage
There is any connection, buzzard-type wing is connected on main wing always.
The connection type of main wing and fuselage: main wing is hinged by front and back spar and fuselage reinforcing frame；
Strake wing and fuselage connection type: the strake wing and fuselage are in semi-fusion state, pass through the rib and fuselage at wing root
Frame is hingedly attached.
A kind of change of configuration method of the folding Waverider aerodynamic arrangement of supersonic airliner, the method use described in
Folding Waverider aerodynamic arrangement, the method can realize deployed configuration and folding configuration according to the demand of state of flight
Phase co-conversion, to realize optimal flying quality under different flight state.
It adjusts the up-front angle of sweep of canard to gradually increase, until the rear of canard is parallel with the leading edge of main wing, and before adjusting
The sweepforward angle for plunderring the wing gradually increases, until the leading edge of buzzard-type wing fits with fuselage；At this point, canard, main wing form one with fuselage
The configuration of a Waverider completes the transformation from deployed configuration to folding configuration.
Method of converting of the realization folding configuration to deployed configuration are as follows: it adjusts the up-front angle of sweep of canard and is gradually reduced, until
The canard angle of sweep reaches 15 ° ~ 22 ° of range, and the sweepforward angle for adjusting buzzard-type wing is gradually reduced, until the sweepforward of buzzard-type wing
Angle reaches 37 ° ~ 47 ° of range.
By design, calculating and analysis, it is applied to using folding Waverider provided in this embodiment aerodynamic arrangement super
When velocity of sound passenger plane:
(1) it in low subsonic speed (H=0km, Ma=0.2) takeoff and anding, according to the deployed configuration of folding Waverider, fills
Buzzard-type wing and the aerodynamic advantages of canard under the low speed are waved in distribution, and slope of lift curve and the more traditional waverider-derived of lift resistance ratio have larger
Raising, takeoff and landing performance can be obviously improved, be suitble to takeoff and anding；
(2) pneumatic special according to the deployed configuration of folding Waverider when transonic speed (H=10km, Ma=0.8) cruises
Property be better than traditional waverider-derived, including improve stalling angle and compared with high lift-drag ratio etc.；
(3) good Longitudinal Aerodynamic Characteristics fully demonstrated the folding Waverider in this research can by change canard
And the shape of main wing obtains the optimum pneumatic performance under friction speed range, development potentiality is huge；This research can be to wide area speed
The layout type selecting work for spending the seating plane of flight provides reference.
Folding Waverider provided in this embodiment aerodynamic arrangement includes deployed configuration and folding configuration, major design
Thought is concluded are as follows: is deployed configuration when low subsonic speed takeoff and anding and transonic speed cruise (if any), is used small sweepback duck at this time
Buzzard-type wing on the wing and main wing improves takeoff and landing performance to improve lift resistance ratio；It is folding configuration when supersonic cruising, leads at this time
Buzzard-type wing on the wing rotates around the axis to change sweepforward angle, is tightly attached to fuselage two sides, while small sweepback canard also starts to become sweepback
Rotation increases its angle of sweep, and final canard, main wing form the configuration of a Waverider with fuselage, is very suitable to supersonic speed and patrols
Boat.Two kinds of typical mission configurations of the layout are as follows: low subsonic speed and transonic speed under small sweepback canard add buzzard-type wing configuration and
Waverider-derived under supersonic speed.
A kind of change of configuration method of the folding Waverider aerodynamic arrangement of supersonic airliner, the method use described in
Folding Waverider aerodynamic arrangement, the method can realize deployed configuration and folding configuration according to the demand of state of flight
Phase co-conversion (transformational relation between both configurations is as shown in Figure 3), with realize under different flight state it is optimal fly
Row performance.
Method of converting of the realization deployed configuration to folding configuration are as follows: it adjusts the up-front angle of sweep of canard and gradually increases, until
The rear of canard and the leading edge of main wing are parallel, and the sweepforward angle for adjusting buzzard-type wing gradually increases, until the leading edge and machine of buzzard-type wing
Body fits；At this point, canard, main wing form the configuration of a Waverider with fuselage, that is, complete from deployed configuration to folding configuration
Transformation.
Method of converting of the realization folding configuration to deployed configuration are as follows: it adjusts the up-front angle of sweep of canard and is gradually reduced, until
The canard angle of sweep reaches 15 ° ~ 22 ° of range, and the sweepforward angle for adjusting buzzard-type wing is gradually reduced, until the sweepforward of buzzard-type wing
Angle reaches 37 ° ~ 47 ° of range.
Claims (8)
1. a kind of folding Waverider aerodynamic arrangement of supersonic airliner, including fuselage, main wing, strake wing, vertical fin, it is located at institute
State buzzard-type wing, canard and the power device on main wing, which is characterized in that before the angle of sweep of the canard and the buzzard-type wing
Sweep angle can be adjusted；It can make the Waverider gas by the angle of sweep of the adjusting canard and the sweepforward angle of the buzzard-type wing
Deployed configuration or folding configuration is presented in dynamic layout；
The aspect ratio of the deployed configuration can reach 6.0 or more, take off, land and be suitable for across sound suitable for low subsonic speed
Speed cruise；
The folding configuration is the configuration of Waverider, is suitable for supersonic cruising.
2. the folding Waverider aerodynamic arrangement of a kind of supersonic airliner according to claim 1, which is characterized in that described
Canard is connect with the fuselage, particular by be arranged in the canard wing root hinge mechanism and the fuselage reinforcing frame into
Row connection, shaft hole and shaft are arranged on the hinge mechanism, can pass through the angle of sweep of the rotation shaft regulated canard.
3. the folding Waverider aerodynamic arrangement of a kind of supersonic airliner according to claim 2, which is characterized in that described
Waverider aerodynamic arrangement from the deployed configuration variation be the folding configuration during, the canard angle of sweep from expansion shape
15 ° of state ~ 22 ° of leading edge sweeps increase to 70 ° ~ 78 ° leading edge sweeps of folded state, the final rear for realizing canard and master
The leading edge of the wing is parallel, completes the variation at canard angle of sweep in folding process.
4. the folding Waverider aerodynamic arrangement of a kind of supersonic airliner according to claim 1, which is characterized in that described
Buzzard-type wing is connect with the main wing, particular by the front wing for the hinge mechanism and the main wing that the buzzard-type wing wing root is arranged in
Beam connection, shaft hole and shaft are arranged on the hinge mechanism, can pass through the sweepforward of the rotation shaft regulated buzzard-type wing
Angle.
5. the folding Waverider aerodynamic arrangement of a kind of supersonic airliner according to claim 4, which is characterized in that described
During Waverider aerodynamic arrangement is the folding configuration from deployed configuration variation, the sweepforward angle of the buzzard-type wing is from exhibition
37 ° of open state ~ 47 ° of sweepforward angles increase to 85 ° ~ 90 ° of folded state, and the final leading edge for realizing buzzard-type wing is affixed with fuselage
It closes, completes the variation of the sweepforward angle of buzzard-type wing in folding process, in folded state, sweepforward nose of wing and fuselage do not have any company
It connects, buzzard-type wing is connected on main wing always.
6. a kind of change of configuration method of the folding Waverider aerodynamic arrangement of supersonic airliner, the method are wanted using right
Ask any one of 1-5 folding Waverider aerodynamic arrangement, which is characterized in that the method can be according to the need of state of flight
It asks, realizes the phase co-conversion of deployed configuration and folding configuration, to realize the optimal flying quality under different flight state.
7. method according to claim 6, which is characterized in that the method for converting of realization deployed configuration to folding configuration are as follows: adjust
The section up-front angle of sweep of canard gradually increases, until the rear of canard is parallel with the leading edge of main wing, and adjusts the sweepforward of buzzard-type wing
Angle gradually increases, until the leading edge of buzzard-type wing fits with fuselage；At this point, canard, main wing form a Waverider with fuselage
Configuration completes the transformation from deployed configuration to folding configuration.
8. method according to claim 6, which is characterized in that the method for converting of realization folding configuration to deployed configuration are as follows: adjust
The section up-front angle of sweep of canard is gradually reduced, until the canard angle of sweep reaches 15 ° ~ 22 °, and adjusts the sweepforward angle of buzzard-type wing
It is gradually reduced, until the sweepforward angle of buzzard-type wing reaches 37 ° ~ 47 °, completes the transformation from folding configuration to deployed configuration.
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| CN110027704A (en) * | 2019-05-14 | 2019-07-19 | 厦门大学 | The fast domain Hypersonic waveriders aircraft of the width of variable-geometry and its design method |
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| CN117208194A (en) * | 2023-11-09 | 2023-12-12 | 清华大学 | Wing-hair reconfiguration type variant aircraft |
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| RU196130U1 (en) * | 2019-11-25 | 2020-02-18 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Passenger Aircraft |
| RU196671U1 (en) * | 2019-11-25 | 2020-03-11 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Supersonic Passenger Aircraft |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
| CN111516871A (en) * | 2020-04-30 | 2020-08-11 | 浙江大学 | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design |
| CN112319813A (en) * | 2020-12-01 | 2021-02-05 | 李勇霖 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
| CN112606995A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Wide-speed-range pneumatic stability control characteristic structure for flying wing layout |
| CN113184165A (en) * | 2021-05-28 | 2021-07-30 | 西北工业大学 | Hypersonic aircraft wing small wing folding mechanism and hypersonic aircraft |
| CN114313253A (en) * | 2022-03-03 | 2022-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high lift-drag ratio air-breathing hypersonic aircraft |
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| CN114537636A (en) * | 2022-03-25 | 2022-05-27 | 西北工业大学 | Low-sonic-explosion low-resistance pneumatic layout configuration for large supersonic civil aircraft |
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| CN117208194A (en) * | 2023-11-09 | 2023-12-12 | 清华大学 | Wing-hair reconfiguration type variant aircraft |
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