CN109677587A - A kind of control method of oblique wing aircraft that taking into account high low-speed operations - Google Patents
A kind of control method of oblique wing aircraft that taking into account high low-speed operations Download PDFInfo
- Publication number
- CN109677587A CN109677587A CN201910050708.0A CN201910050708A CN109677587A CN 109677587 A CN109677587 A CN 109677587A CN 201910050708 A CN201910050708 A CN 201910050708A CN 109677587 A CN109677587 A CN 109677587A
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- speed
- oblique
- control method
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of aircraft advance aerodynamic configuration design fields, are specifically a kind of oblique wing aircrafts that can take into account the low-speed operations of aircraft height.Aircraft layout of the present invention is anury Flying-wing, includes wing and fuselage two parts, and in aircraft central axes Position Design vertical pivots rotating mechanism, two half wings of left and right are integral and can pivot, after wing rotation, port wing sweepback, starboard wing sweepforward；When aircraft flight, the rotatable different angle of wing is optimal the aeroperformance of different phase, and after this oblique wing aircraft is rotated due to wing, side wing sweepback, side wing sweepforward make full machine aerodynamic center variation less, and flight control is relatively easy to.Oblique wing aircraft wing wingtip of the invention is designed as cruise efficiency when ellipse further improves transonic speed and supersonic speed；Wing, which is opened up, makes rolling moment reduction caused by the mal-distribution of two sides lift after the rotation of wing around the pivot to the asymmetrical design with taper ratio, improves flight safety.
Description
Technical field
It is specifically that one kind can take into account aircraft height the present invention relates to a kind of aircraft advance aerodynamic configuration design field
The tilting aircraft of low-speed operations.
Background technique
In the aviation development course of last 100 years, people never stopped the effort of design high-performance cruise aircraft no matter
It is that the requirement of civil field or military domain to high-performance cruise aircraft is all very urgent.The study found that wing setting can have
Performance when effect improves aircraft high-speed flight delays shock wave to occur because angle of sweep can reduce the local speed of wing, improves
Drag divergence Mach number.
After swept back wing occurs, many scholars have researched and analysed the superiority-inferiority of sweepforward and sweepback.For the two of identical size
Kind wing, buzzard-type wing can promote higher lift and generate lesser induced drag, and buzzard-type wing can also improve aileron
Operating efficiency preferably controls stall and keeps with swept back wing identical high speed performance.But the wing tip of buzzard-type wing is located at
Before airfoil root, under the action of aerodynamic loading, wing tip increases the local angle of attack of wing tip with respect to the torsional deflection that wing root generates
Greatly, angle of attack increase can cause aerodynamic loading to further increase, and the development of this vicious circle makes wing structure that aeroelasticity occur
It dissipates and causes to destroy, and swept back wing is stable in structure, and provides additional horizontal shipping-direction stability.However, this
The design of fixed wing setting, can only meet under design cruising condition that pneumatic efficiency is optimal, cannot combine low speed landing,
Subsonic cruise, transonic speed cruise and supersonic cruise.
The it is proposed of variable swept back wing is so that aircraft all obtains preferably aerodynamic characteristic, variable swept back wing in subsonic speed and supersonic speed
I.e. aircraft can change wing setting with flying speed change automatically.The sixties to the seventies, the development of variable sweep aircraft
It reaches a climax, each state all produces the military aircraft of a large amount of variable swept back wings, and comes into operation.Become the process of sweepback aircraft in development
In, it is main problem is encountered that the problem of in terms of operation stabilization, because wing setting variation can cause aerodynamic center to occur very
Big movement.Become " Aerodynamic Derivatives for an of the research in R. E. Maine of sweepback aircraft
Oblique Wing Aircraft Estimated from Flight Data by Using a Maximum
As it can be seen that the document is incorporated herein by reference herein in Likelihood Technique ", NASA TP 1336,1978.
The appearance of oblique wing solves the problems, such as the variation of variable swept back wing aerodynamic center very greatly.There are mainly two types of shapes for oblique wing
Formula, oblique wing body combine (Oblique Wing Aircraft, OWA) form and oblique flying wing (Oblique Flying
Wing, OFW) form.The sixties, people started to study the oblique wing aircraft that wing body combines, and had carried out a large amount of
Theory analysis and practical work, the results showed that oblique wing body Combined toy plane fuselage interferes especially severe, it is pneumatic it is sympathetic result in it is non-
Linear stability features, more significant under High Angle of Attack, aeroelasticity phenomenon is also due to quality excessively concentrates on wing center
Aggravation.Although it is simpler than variable-sweep wing to turn shaft design, there is also technical challenge, while the main group of Zhan Quanji resistance
It cannot be well controlled at the fuselage wave resistance of part, so that oblique wing body Combined toy plane is reducing the advantage in wave resistance
Become intensely dark." An of the tilting multi-wall interference aircraft research in D. Terry and A. Weisshaar
Investigation of Supersonic Characteristics of Oblique Winged Aircraft”, NASA
As it can be seen that the document is incorporated herein by reference herein in Ames Grant NSG 2016,1976.
In summary, it is optimal that pneumatic design may be implemented in oblique flying wing.The concept of oblique flying wing was most mentioned early in 1958
It arrives, the designing draft of G. H. Lee in 1962 is disclosed, but is never paid close attention to.Until active digital control technology
It is widely applied, oblique flying wing research is just further developed.Theoretical research shows that the wing with elliptical load distribution has
The smallest wave drag due to lift and induced drag, therefore, oval oblique flying wing can effectively reduce aircraft in high transonic speed and supersonic speed
When flight resistance, improve aircraft high-speed flight pneumatic efficiency.Oblique flying wing also has the advantages that anury Flying-wing, more
It is realized simply for sweepback mechanism is become, while the advantages such as little is influenced on aerodynamic center.
Summary of the invention
For the above technical background, the invention proposes the controlling parties that one kind can take into account the oblique wing aircraft of high low-speed operations
Method.The technical solution of the invention is as follows, and it includes fuselage and wing two parts, in aircraft that aircraft layout, which is inaction Flying-wing,
Central axes Position Design vertical pivots rotating mechanism, left and right wing, which is integral, to be pivoted, after wing rotation, port wing
It is sweepforward for sweepback, starboard wing.
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to
It is as follows:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
The high subsonic speed or transonic speed cruising speed are 0.8~1.2 Mach.
The oblique wing aircraft wing wingtip is designed as shock wave resistance of the ellipse to reduce transonic speed or supersonic flight when
Power and induced drag.
The oblique wing aircraft wing opens up, taper ratio anti-in anti-, buzzard-type wing parabolic type to being designed as under swept-back wing parabolic type
Swept-back wing taper ratio is designed as less than buzzard-type wing.
This wing open up to and taper ratio design be in order to reduce due to wing around the pivot rotation after two sides lift not
Rolling control problem caused by symmetrical.
Beneficial effects of the present invention:
The present invention can effectively solve straight fixed wing aircraft high speed performance difference and big angle of sweep aircraft low speed takeoff and landing performance is poor
The problem of, aerodynamic center will not be varied widely with flying speed, and control is relatively easy to.
Side wing sweepback, side wing sweepforward after the present invention is rotated due to wing, with the increase of rotation angle, aircraft
Aerodynamic center will not vary widely, and automatic control is relatively easy to.
Detailed description of the invention
Fig. 1 is the tilting aircraft that can take into account high low-speed operations；
Fig. 2 is the schematic diagram that oblique wing aircraft takes into account high low-speed operations；
Fig. 3 is oblique wing aircraft wingtip plan view；
Fig. 4 is that oblique wing aircraft wing is opened up to bending figure；
Fig. 5 is left and right sides taper plan view.
Appended drawing reference
1. vertical pivots, 2. swept-back wings, 3. buzzard-type wings, 4. first oval wingtips, 5. second oval wingtips.
Specific embodiment:
Embodiment 1:
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
Embodiment 2:
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
The oblique wing aircraft wing wingtip is designed as shock wave resistance of the ellipse to reduce transonic speed or supersonic flight when
Power and induced drag.
The oblique wing aircraft wing opens up, taper ratio anti-in anti-, buzzard-type wing parabolic type to being designed as under swept-back wing parabolic type
Swept-back wing taper ratio is designed as less than buzzard-type wing.
This wing open up to and taper ratio design be in order to reduce due to wing around the pivot rotation after two sides lift not
Rolling control problem caused by symmetrical.
Embodiment 3:
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
The high subsonic speed or transonic speed cruising speed are 0.8~1.2 Mach.
The oblique wing aircraft wing opens up, taper ratio anti-in anti-, buzzard-type wing parabolic type to being designed as under swept-back wing parabolic type
Swept-back wing taper ratio is designed as less than buzzard-type wing.
This wing open up to and taper ratio design be in order to reduce due to wing around the pivot rotation after two sides lift not
Rolling control problem caused by symmetrical.
Embodiment 4:
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
The high subsonic speed or transonic speed cruising speed are 0.8~1.2 Mach.
The oblique wing aircraft wing wingtip is designed as shock wave resistance of the ellipse to reduce transonic speed or supersonic flight when
Power and induced drag.
Embodiment 5:
A kind of control method of oblique wing aircraft that taking into account high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
The high subsonic speed or transonic speed cruising speed are 0.8~1.2 Mach.
The oblique wing aircraft wing wingtip is designed as shock wave resistance of the ellipse to reduce transonic speed or supersonic flight when
Power and induced drag.
The oblique wing aircraft wing opens up, taper ratio anti-in anti-, buzzard-type wing parabolic type to being designed as under swept-back wing parabolic type
Swept-back wing taper ratio is designed as less than buzzard-type wing.
This wing open up to and taper ratio design be in order to reduce due to wing around the pivot rotation after two sides lift not
Rolling control problem caused by symmetrical.
Embodiment 6:
Oblique wing aircraft of the invention is shown in Fig. 1, and aircraft layout is anury Flying-wing, includes fuselage and wing two parts, is flying
Machine central axes Position Design vertical pivots rotating mechanism (1), wing or so two halves, which are integral, to be rotated with around the pivot (1).
The principle that the oblique wing aircraft takes into account high low-speed operations is shown in Fig. 2, when aircraft flies to high-performance cruise from low speed
When, according to the difference of flying speed, from basic status around the pivot (1), rotation changes its angle relative to air-flow to wing counterclockwise
Degree, after wing rotation, left and right wing is divided into rear wing (2) and front wing (3) two parts, and wherein port wing is that sweepback is known as rear wing (2),
Starboard wing is that sweepforward is known as front wing (3).Specific implementation method are as follows: in low-speed operations, wing is in basic status, i.e. around the pivot
(1) without spin, aircraft entire in this way is exactly a straight wing aircraft, can give full play to the low-speed performance of straight wing；To height
When subsonic speed or transonic speed (M=0.8 ~ 1.2) flight, in order to improve drag divergence Mach number, wing around the pivot (1) turns counterclockwise
It is 30 ° ~ 50 ° dynamic, reach high subsonic speed or transonic speed cruising condition, rotates angle depending on flying speed, flying speed is bigger
It is bigger to rotate angle, is optimal cruise efficiency when high subsonic speed or transonic speed；When supersonic flight, in order to break through sound
Barrier reduces drag due to shock wave, and wing rotation angle will continue to increase to 60 ° ~ 80 °, reaches supersonic cruise state；When speed reduces
When to high subsonic speed or low-speed operations, wing around the pivot (1) rotates clockwise is returned to high subsonic speed state or low speed shape again
State.This oblique wing aircraft can by performance boost of the aircraft under each speed envelope curve to highest, including low speed landing, it is sub- across
Subsonic cruise or supersonic cruise.Compared to variable sweep aircraft, oblique wing aircraft is due to the sweepforward of wing side, side sweepback, rotation
When gyration increases, it not will lead to aerodynamic center and larger change occur.
The oblique wing aircraft wing wingtip, open up it is as follows to bending, the design of asymmetric taper ratio:
A. wing wingtip designs
Oblique wing aircraft wingtip plan view of the invention is shown in that Fig. 3, wingtip are designed as oval wingtip (4), (5), can have in this way
Effect reduces resistance of the aircraft in transonic speed or supersonic flight, improves flight efficiency, because of the machine with elliptical load distribution
The wing has the smallest wave drag due to lift and induced drag.
B. wing is opened up to curved design
Oblique wing aircraft wing of the invention, which is opened up to bending, sees that Fig. 4, swept-back wing (2) are carried out under parabolic type instead to reduce additional rise
Power, buzzard-type wing (3) carry out making aircraft sweepback under cruising condition instead to increase the lift due to washing reduction under induction in parabolic type
The lift distribution almost symmetry that the wing (4) and buzzard-type wing (5) generate, so that wing rolling moment after around the pivot (1) rotates reaches
Self-balancing.This is because not opening up to curved wing, with the increase of flying speed, wing around the pivot (1) rotates certain
After angle, left and right sides wing setting and sweepforward angle increase, cause to extend induce caused by the rear under wash increase, thus
Wing two sides produce asymmetric lift distribution, and swept-back wing (2) lift increases, and buzzard-type wing (3) lift reduces, this will generate one
Fixed rolling moment causes buzzard-type wing (3) to sink, and it is unfavorable to be promoted to flight control and cruise efficiency.
C. the asymmetrical taper ratio design of wing
Left and right sides wing taper ratio plan view is shown in that Fig. 5, swept-back wing (2) taper ratio are less than buzzard-type wing (3), i.e. swept-back wing (2)
Local chord reduces, and further reduces the lift coefficient of aerofoil profile, further ensures symmetrical point of left and right sides lift
Cloth.
Claims (4)
1. the control method that one kind can take into account the oblique wing aircraft of high low-speed operations, it is characterised in that the rate-determining steps being related to are such as
Under:
A. when aircraft is in low speed landing, it is 0 ° that wing, which pivots,；I.e. without spin, entire wing is equivalent to one and puts down wing
The straight wing has played the low-speed performance of its straight wing to greatest extent；
B. when aircraft is when high subsonic speed or transonic speed are cruised, reach cruise efficiency most to improve drag divergence Mach number
Excellent, according to the difference of flying speed, for wing using flight attitude plane as benchmark face, around the pivot rotates counterclockwise 30 ° ~ 50 °；
C. when aircraft is in supersonic cruise, in order to reduce drag due to shock wave, improve cruise efficiency, wing rotation angle will continue to increase
Add to 60 ° ~ 80 °；When aircraft is from supersonic condition to lower-speed state, according to flying speed difference, wing can around the pivot up time
Needle is rotated back to 0 °.
2. one kind according to claim 1 can take into account the control method of the oblique wing aircraft of high low-speed operations, feature exists
In: the high subsonic speed or transonic speed cruising speed be 0.8~1.2 Mach.
3. one kind according to claim 1 can take into account the control method of the oblique wing aircraft of high low-speed operations, feature exists
In: the oblique wing aircraft wing wingtip is designed as drag due to shock wave of the ellipse to reduce transonic speed or supersonic flight when and lures
Lead resistance.
4. one kind according to claim 1 can take into account the control method of the oblique wing aircraft of high low-speed operations, feature exists
Opened up in: the oblique wing aircraft wing anti-in anti-, buzzard-type wing parabolic type to being designed as under swept-back wing parabolic type, taper ratio is designed as
Swept-back wing taper ratio is less than buzzard-type wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910050708.0A CN109677587B (en) | 2019-01-20 | 2019-01-20 | Control method of oblique wing aircraft capable of flying at high and low speeds |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910050708.0A CN109677587B (en) | 2019-01-20 | 2019-01-20 | Control method of oblique wing aircraft capable of flying at high and low speeds |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109677587A true CN109677587A (en) | 2019-04-26 |
| CN109677587B CN109677587B (en) | 2022-01-25 |
Family
ID=66193620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910050708.0A Active CN109677587B (en) | 2019-01-20 | 2019-01-20 | Control method of oblique wing aircraft capable of flying at high and low speeds |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109677587B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112347553A (en) * | 2020-09-30 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Design method for variation of longitudinal static stability margin of airplane along with attack angle |
| CN115636079A (en) * | 2022-12-21 | 2023-01-24 | 中国航空工业集团公司沈阳空气动力研究所 | High-altitude long-endurance unmanned aerial vehicle layout with ultrahigh lift-drag ratio |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4132374A (en) * | 1976-12-30 | 1979-01-02 | The Boeing Company | Wing pivot location and structure for oblique wing airplane |
| CN102149599A (en) * | 2008-06-20 | 2011-08-10 | 航空伙伴股份有限公司 | Curved wing tip |
| CN102167152A (en) * | 2011-03-11 | 2011-08-31 | 中国商用飞机有限责任公司 | Airplane wingtip device with aligned front edge |
| CN102975851A (en) * | 2012-07-17 | 2013-03-20 | 江闻杰 | Multifunction wing tip turbine engine having fore-lying impellers |
| US20140239117A1 (en) * | 2013-02-27 | 2014-08-28 | Northrop Grumman Systems Corporation | Canard-locked oblique wing aircraft |
| US20180086445A1 (en) * | 2016-09-29 | 2018-03-29 | Ampaire, Inc. | Oblique rotor-wing aircraft |
-
2019
- 2019-01-20 CN CN201910050708.0A patent/CN109677587B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4132374A (en) * | 1976-12-30 | 1979-01-02 | The Boeing Company | Wing pivot location and structure for oblique wing airplane |
| CN102149599A (en) * | 2008-06-20 | 2011-08-10 | 航空伙伴股份有限公司 | Curved wing tip |
| CN102167152A (en) * | 2011-03-11 | 2011-08-31 | 中国商用飞机有限责任公司 | Airplane wingtip device with aligned front edge |
| CN102975851A (en) * | 2012-07-17 | 2013-03-20 | 江闻杰 | Multifunction wing tip turbine engine having fore-lying impellers |
| US20140239117A1 (en) * | 2013-02-27 | 2014-08-28 | Northrop Grumman Systems Corporation | Canard-locked oblique wing aircraft |
| US20180086445A1 (en) * | 2016-09-29 | 2018-03-29 | Ampaire, Inc. | Oblique rotor-wing aircraft |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112347553A (en) * | 2020-09-30 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Design method for variation of longitudinal static stability margin of airplane along with attack angle |
| CN112347553B (en) * | 2020-09-30 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Design method for variation of longitudinal static stability margin of airplane along with attack angle |
| CN115636079A (en) * | 2022-12-21 | 2023-01-24 | 中国航空工业集团公司沈阳空气动力研究所 | High-altitude long-endurance unmanned aerial vehicle layout with ultrahigh lift-drag ratio |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109677587B (en) | 2022-01-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4671473A (en) | Airfoil | |
| US4674709A (en) | Airframe design | |
| US4545552A (en) | Airframe design | |
| CN111959816B (en) | Pneumatic design method for improving high-low speed performance of flying wing layout aircraft | |
| CN108639339B (en) | Pneumatic layout of unmanned aerial vehicle | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| CN210235305U (en) | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet | |
| CN105857575A (en) | Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane | |
| CN110979682A (en) | Variable-area duck-type forward-swept wing variant aircraft | |
| CN105129090A (en) | Low resistance and low sonic boom layout supersonic aircraft | |
| CN103057695B (en) | A kind of combination rudder face of tailless aircraft | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN106043684B (en) | A kind of connectible combined type aircraft of rotor wing | |
| CN108750073B (en) | Variable wing leading edge with both subsonic and supersonic aerodynamic performance | |
| CN109677587A (en) | A kind of control method of oblique wing aircraft that taking into account high low-speed operations | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN203740120U (en) | Aerodynamic structure of morphing aircraft with wide flight envelope | |
| CN106927021A (en) | Fan wing unmanned plane | |
| Jacobellis et al. | A physics-based approach to trim optimization of coaxial helicopters in high-speed flight | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| JP2622670B2 (en) | Supersonic aircraft wing | |
| WO2018233651A1 (en) | Device integrating tip of rotary blade with flight ring | |
| CN110844064B (en) | Low reynolds number rotor blade |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |