CN107804469A - aircraft - Google Patents
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- CN107804469A CN107804469A CN201710874106.8A CN201710874106A CN107804469A CN 107804469 A CN107804469 A CN 107804469A CN 201710874106 A CN201710874106 A CN 201710874106A CN 107804469 A CN107804469 A CN 107804469A
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- wing
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- high mounted
- support bar
- outer section
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- 210000001015 abdomen Anatomy 0.000 claims abstract description 5
- 210000004209 hair Anatomy 0.000 claims description 3
- 230000008450 motivation Effects 0.000 claims description 2
- 239000000446 fuel Substances 0.000 abstract description 7
- 238000004880 explosion Methods 0.000 description 4
- 230000035939 shock Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 241000272517 Anseriformes Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000000873 masking effect Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
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- 239000003381 stabilizer Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
Abstract
The invention discloses a kind of aircraft.The aircraft of the present invention includes the fuselage of tubular, also include the complete dynamic front wing, the engine being arranged above fuselage endpiece and the wing for being arranged at fuselage posterior segment for being arranged at nosing, the wing uses the high mounted wing with support bar, and one end of the support bar is connected to belly, the other end is connected to the high mounted wing.The aircraft of the present invention, possesses low-resistance, the characteristic of low noise, can significantly improve the fuel economy of aircraft, and significantly reduces interior noise, while also has outstanding navigability and stability.
Description
Technical field
The present invention relates to the aerodynamic arrangement of aircraft, more particularly to the aircraft using novel aerodynamic arrangement.
Background technology
The aerodynamic arrangement of the civil aircraft of active service is referred to as Conventional pneumatic layout.It is mainly characterized by lower single-blade, the wing is hung greatly
Bypass ratio turbofan (also has minority still to hang distribution engine using tail), and its vertical tail and tailplane are in mostly
Existing " T " shapes or "T"-shaped.By the differentiation of many decades, the performance and economy of the civil aircraft of such Conventional pneumatic layout
Bottleneck period is had evolved to, it is difficult to lifted.Therefore, unconventional aerodynamic arrangement's civil aircraft, which becomes, seeks airplane synthetic
The important directions that can be broken through.In the research and development of unconventional aerodynamic arrangement, various countries' Aviation Enterprise has had some to attempt.
The SUGAR volt transonic speeds that the subsonic speed green Aircraft Project of progress proposes for example, NASA and Boeing take the lead
The civil aircraft of truss support wing configurations.But the program is in the laminar flow zone for maintaining wing and the peace of engine rotor explosion
There are still clearly disadvantageous for control of full property and interior noise etc..
In another example the P180 aircrafts of Italian Piaggio Co., Ltd use three-surface configuration, the CN1525920A of Boeing
Patent is equally designed using three-surface configuration, but the two is in fuel economy and related to the security of engine rotor explosion
Also all there is clearly disadvantageous for aspect.
Therefore, need a kind of aircraft aerodynamic arrangement of innovation badly, to which the fuel economy of aircraft can be significantly improved, carry simultaneously
For low noise characteristic, the navigability and stability of aircraft are taken into account.
The content of the invention
The technical problem to be solved in the present invention is that aircraft overall resistance of the prior art is larger, fuel-economy in order to overcome
In the bad, cabin of property and the defects of outfield noise is larger, a kind of aircraft is proposed.
The present invention is that solve above-mentioned technical problem by following technical proposals：
The invention provides the fuselage of a kind of aircraft, including tubular, its feature is, the aircraft also includes being arranged at machine
The complete dynamic front wing of body leading portion, the engine being arranged above fuselage endpiece and the wing for being arranged at fuselage posterior segment, the machine
The wing uses the high mounted wing with support bar, and one end of the support bar is connected to belly, the other end is connected to the high mounted wing.
It is preferred that link position and the nearest upper list of the other end of described support bar with the high mounted wing
The spacing of the end points of the wing is between the 55%-75% of the semispan length of the high mounted wing.
It is preferred that the engine is open rotor engine.
It is preferred that the high mounted wing includes the stage casing wing and the outer section of wing, the outer section of wing is tapered airfoil, before the outer section of wing
Edge has bigger angle of sweep compared to trailing edge, and the difference at the angle of sweep of the two is no more than 10 °.
It is preferred that the parting surface of the outer section of wing and the stage casing wing is nearby hung with streamlined oil storage chamber, the support
The other end of bar is connected to the shell of the streamlined oil storage chamber.
It is preferred that the support bar uses zero camber symmetrical laminar flow airfoil of the relative thickness between 10%-13%.
It is preferred that the stage casing wing uses laminar flow airfoil of the relative thickness between 12%-13%, the outer section of wing uses
Laminar flow airfoil of the relative thickness between 9%-12%.
It is preferred that the stage casing wing is in straight rectangular shape, the upper counterangle of the stage casing wing is 0 °.
It is preferred that the upper counterangle of the outer section of wing is between 6 ° -10 °.
It is preferred that the taper ratio of the outer section of chord-length is between 0.45-0.75.
It is preferred that the aspect ratio of the high mounted wing is more than 15.
It is preferred that the aircraft also includes tailplane, the open rotor engine blade is rearmounted, the open rotor
Engine arrangement is on the top airfoil of the tailplane, and the Plane of rotation of the blade is in the trailing edge of the tailplane
After.
It is preferred that the left and right taper in the tailplane is separately installed with vertical tail.
It is preferred that the tailplane is using negative camber or the laminar flow airfoil of zero camber.
It is preferred that the entirely dynamic front wing uses tapered airfoil of the angle of sweep within 10 °.
It is preferred that the entirely dynamic front wing uses laminar flow airfoil of the relative thickness between 12%-13%.
It is preferred that the complete dynamic front wing is arranged to lower single-blade and with the upper counterangle between 3 ° -7 °.
Or the complete dynamic front wing is arranged to midsetwing or high mounted wing and with 0 ° of the upper counterangle.
It on the basis of common sense in the field is met, above-mentioned each optimum condition, can be combined, it is each preferably real to produce the present invention
Example.
The positive effect of the present invention is：
The aircraft of the present invention, possesses low-resistance, the characteristic of low noise, fuel economy is significantly improved compared to prior art,
And interior noise is significantly reduced, while the aircraft of the present invention also has outstanding navigability and stability.
Brief description of the drawings
Fig. 1 is the stereogram of the aircraft of a preferred embodiment of the present invention.
Fig. 2 is another stereogram of the aircraft of a preferred embodiment of the present invention.
Fig. 3 is the top view of the aircraft of a preferred embodiment of the present invention, and it illustrates high mounted wing plane figure shape.
Fig. 4 is the top view of the aircraft of another preferred embodiment of the present invention, and it illustrates high mounted wing plane figure shape.
Fig. 5 is the front view of the aircraft of a preferred embodiment of the present invention.
Fig. 6 is the high mounted wing, midsetwing, the configuration of lower single-blade of the complete dynamic front wing in the aircraft of the better embodiment of the present invention
Schematic diagram.
Embodiment
With reference to Figure of description, further the preferred embodiments of the present invention are described in detail, following description
To be exemplary, not limitation of the present invention, other any are still fallen among protection scope of the present invention similar to situation.
In following specific descriptions, the term of directionality, such as "left", "right", " on ", " under ", "front", "rear", etc.,
Direction described in refer to the attached drawing uses.The part of embodiments of the invention can be placed in a variety of different directions, directionality
Term is for illustrative purposes and nonrestrictive.
With reference to shown in figure 1-2, according to the fuselage 1 of a kind of aircraft of a preferred embodiment of the present invention, including tubular, in addition to
The complete of nosing is arranged to move front wing 3, the open rotor engine 9 being arranged above fuselage endpiece and be arranged at fuselage
The wing of posterior segment, wing use the high mounted wing 2 with support bar 6, and one end of support bar 6 is connected to belly, other end company
It is connected to high mounted wing 2.
The present invention is in the outstanding open rotor engine 9 of afterbody installation fuel economy, and wing no longer needs hanging to send out
Motivation.Using support bar 6, the moment of flexure in wing stage casing reduces so as to which wing thickness is thinned when being able to be greatly lowered flight
Drag due to shock wave in-flight, and high aspect ratio wing helps to reduce induced drag, tail, which hangs distribution engine, then to be contributed to mitigate
Interior noise.Quiet indoor environment can also be obtained.Using complete dynamic front wing 3, help to improve longitudinal control and stability of aircraft,
Further improve full machine performance.
It should be appreciated that the present invention is equally applicable to open rotor engine for the character of innovation of aircraft layout
Be changed to the power set of the types such as big Bypass Ratio Turbofan Engine, turbo oar engine, electric propulsion ducted fan, and obtain due to
The economy and performance of prior art.Certainly, illustrated herein by taking open rotor engine as an example, while be also able to highlight out
Extremely superior combustion of the own characteristic of formula rotary engine achieved by with the combination of the aircraft layout designs of the present invention
Oily economy and original full machine performance.
The combination of this braced wing and open rotor engine configures used by the aircraft layout of the present invention, it may be said that is
The horizontal highest wing profile of lift-drag ratio and the horizontal minimum propeller for turboprop of oil consumption have been organically combined in subsonic aircraft field
Machine.
Specifically, support bar can play a part of reducing wing the unloading of moment of flexure in a manner of diagonal brace, thus make
Obtain wing to be able to use the design with following resemblance, such as：Super large aspect ratio, relative thickness are smaller, wing it is overall compared with
To be elongated slim.The above-mentioned resemblance of wing is alternative in the present invention to be applicable, and can also be had both at the same time.Machine as described above
Contour of flange feature is extremely beneficial to the lift-drag ratio of aircraft.The high aspect ratio of wing can cause the induced drag of wing into anti-
Ratio declines；The thinner wing profile of relative thickness can cause wing to be set using straight or angle of sweep with very little
Meter, just can drop to conventional levels by drag due to shock wave；Also, the wingpiston of the design at angle of sweep straight or with very little
Profile matches with laminar flow airfoil just, and this helps further significantly to reduce windage resistance.
According to some preferred embodiments of the present invention, on the link position and high mounted wing of support bar and high mounted wing recently
Spacing between end points, between the 55%-75% of the semispan length of high mounted wing, or the connection position of support bar and high mounted wing
Put the centre position for the semispan for being generally in high mounted wing.In some preferred embodiments, one end of support bar is connection
On radome fairing under to high mounted wing, i.e. one end of support bar is connected to high mounted wing via radome fairing, in such cases, above-mentioned company
Connect position and can be regarded as radome fairing relative to high mounted wing aerofoil present position.
, can be further on the basis of the aircraft of present pre-ferred embodiments as described above based on above-mentioned technical factor
By it is specific some be related to the design of aerofoil surface, draw some embodiments being more highly preferred to of the present invention, it is able to reality
Now more remarkable full machine performance and efficiency in-flight.
On the other hand, although open rotor engine is horizontal with extremely low oil consumption, because its own is multiple at other
The defects of aspect is present, it does not obtain the most abundant, application the most appropriate.Specifically, open rotor engine blade
It is relatively large in diameter, engine weight is heavier, and vibration and noise level are higher, and has the problems such as security that rotor explosion is brought.
Therefore, open rotor engine is arranged on wing according to the engine arrangement mode of routine, on the one hand can destroys machine
The more clean aerodynamic configuration of the wing and large stretch of laminar flow zone, bring the Structural Dynamics risk of flutter, it is also possible to pay wing knot
The cost of structure weightening, the cabin interior noise near another aspect blade Plane of rotation will be influenceed by engine and become very big,
The blade fragment thrown away during rotor explosion is again in the presence of the latent of the critical system pipeline endangered in cabin in personal security and airframe
In danger.
The present invention is directed to many advantage and disadvantage of open rotor engine, employs the form of afterbody installation, not only pole
The drawbacks described above of open rotor engine, but also the design that can be more highly preferred to by some are avoided in big degree, such as is hung down
The masking of fin is set, and reduces the outfield influence of noise that engine is brought.
In the aircraft of example is performed as described above, fuselage can use traditional tubular, high-fineness ratio fuselage, and fuselage section is using just
Circular or multistage tangential approximate circular, streamlined head, fusiform shrink shape tail, mainly meet loading space
It is required that.The inner space of wing can meet the requirement of fuel tank arrangement, while trailing edge flap, the trailing edge flap can be provided with wing
The active face such as aileron and aileron.According to some preferred embodiments, wing uses high aspect ratio wing, i.e. the exhibition of high mounted wing 2
String ratio can be more than 15.
In some preferred embodiments of the present invention, open rotor engine is mountable to tailplane top, open type
Rotary engine is because diameter of propeller blade is big, it is necessary to the engine mount that overhang is larger, structure is heavier, and this mounting means is fine
Ground make use of the design feature of horizontal tail itself it is also served as engine mount, improve structure efficiency.
Further, because the present invention uses open rotor engine at extreme rear scheme, this is inclined by the center of gravity for causing aircraft
Afterwards, the horizontal tail arm of force is relatively short, and thus horizontal tail stabilization can not design and help dynamic shape because horizontal tail also serves as engine mount
Formula, this can cause longitudinal control and stability of aircraft and the decline of trim ability to a certain extent.Therefore, according to the present invention preceding
Fuselage is additionally arranged dynamic front wing entirely, to solve aircraft insufficient existing for longitudinal control and stability and trim ability.
It is to be further understood that although the attached aircraft configuration scheme that three hairs are shown in the figure, but the above-mentioned wound of the present invention
New layout is equally applicable to the aircraft configuration scheme of double hairs.
In some preferred embodiments of the present invention, further innovative design is done for aircraft wing, to enter
One step improves aeroplane performance.The plane figure shape of high mounted wing 2 of some preferred embodiments of the present invention is referred to shown in Fig. 3,
Wherein, the stage casing wing 21 is straight RECTANGULAR WINGS, and the outer section of wing 22 is that trailing edge is straight, and leading edge has the ladder of low sweep angle (being no more than 10 °)
The shape wing, and streamlined low-resistance wingtip can be coordinated.
According to other preferred embodiments of the present invention, further to reduce the transonic shock wave resistance of wing, reduce
Pneumatic design difficulty, can be on the basis of the above-mentioned stage casing wing 21 is the embodiment of straight RECTANGULAR WINGS, by the plane of above-mentioned wing
Shape integrally increases the angle of sweep no more than 10 °, with reference to shown in figure 4.
Preferably, the taper ratio of the outer section of chord length of the wing 22 is 0.45-0.75, and the aerofoil profile of the wing stage casing wing 21 uses 12%-
The laminar flow airfoil of 13% relative thickness, the outer section of aerofoil profile of the wing 22 use the laminar flow airfoil of 9%-12% relative thicknesses.Wherein, stage casing machine
The root of the wing, can be above Fuselage liner part section in the projection of aircraft front view, and passes through wing body radome fairing and machine
Body contour merges.
According to some preferred embodiments of the present invention, with reference to shown in figure 1 and Fig. 5, point of the outer section of wing 22 and the stage casing wing 21
Streamlined oil storage chamber nearby is hung with from face, the other end of support bar 6 is connected to the shell of streamlined oil storage chamber.Oil storage therein
Cabin can be nacelle.Parting surface said here, i.e., the joint portion of outer the section wing 22 and the stage casing wing 21, but it should be noted that this
Described outer the section wing 22 and the stage casing wing 21 are only to describe the diverse location on aerofoil surface in invention, and it is phase not necessarily to represent it
Mutually independent part.
Preferably, nacelle shell is connected with support bar by joint, and the design, which avoids strut and is joined directly together with wing, to be led
The excessively narrow aerodynamic interference problem of the gas channel of cause.Oil storage nacelle also has the unloading work(for reducing stage casing wing bending moment simultaneously
Energy.According to the control and stability demand of aircraft, the upper counterangle of the stage casing wing 21 of aircraft is 0 °, and the outer section of upper counterangle of the wing 22 is 6 ° -10 °.Enter
Preferably, laminar flow airfoil of the stage casing wing 21 using relative thickness between 12%-13%, the outer section of wing 22 uses relative thickness to one step
Laminar flow airfoil between 9%-12%.
Alternatively, with reference to shown in figure 1 and Fig. 5, the one end of support bar 6 is connected on the mechanism joint of belly, the other end
It is connected under the wing on the structural joint of oil storage nacelle, thus, support bar 6 forms a triangular truss structure with wing stage casing,
Moment of flexure and stress when can effectively reduce the flight of wing stage casing.Support bar 6 can use the zero curved of 10%-13% relative thicknesses
Spend symmetrical laminar flow airfoil.
With reference to shown in figure 1-2, according to some currently preferred embodiments of the present invention, aircraft also includes tailplane 4, open rotor
The blade of engine 9 is rearmounted, and open rotor engine 9 is arranged on the top airfoil of tailplane 4, and the Plane of rotation of blade is in
After the trailing edge of tailplane 4.Also, vertical tail 5 can be separately installed with the left and right taper of tailplane 4.
Wherein, tailplane 4 includes horizontal stabilizer and elevator, and tailplane 4 is installed on fuselage endpiece both sides, and can
Preferably by negative camber or the laminar flow airfoil of zero camber, for longitudinal trim of aircraft, manipulation and stably, while conduct is played
The function of engine mount, engine is made to can be directly mounted in the structure of tailplane 4, and elevator is arranged in engine nacelle
The trailing edge of tailplane 4 of inner side.Vertical tail 5 includes fixed fin and rudder, is installed on the taper of tailplane 4.Hang down
The trailing edge of fin 5 is disposed with rudder.Vertical tail 5 is used for the course trim of aircraft, manipulation and stably.Meanwhile vertical tail 5
The scope of open rotor engine blower blade Plane of rotation more than 60% can be effectively blocked, so as to effectively shield fan
Influence of noise, play noise reduction effect.In addition, left and right vertical fin backups each other, moreover it is possible to reduces engine blower blade and flies out and injures
Influence of the vertical tail 5 to flight safety.
Also, tail hangs the fanjet that open rotor engine 9 compares equal thrust grade, improving fuel economy
Possess larger potentiality with CO2 emission aspect is reduced, can realize that high theoretical bypass ratio is set by removing fan housing
Meter, its fuel consumption can reduce 25-30% on the basis of fanjet.
According to some preferred embodiments of the present invention, entirely dynamic front wing 3 (alternatively referred to as dynamic canard entirely) can use it is straight or
The tapered airfoil of low sweep angle within 1/4 10 ° of the string of a musical instrument, and low-resistance wingtip can be housed, dynamic front wing 3 uses relative thickness in 12%- entirely
Laminar flow airfoil between 13%.It is further preferred that dynamic front wing 3 is arranged to lower single-blade and has the upper counterangle between 3 ° -7 ° entirely,
Or it is arranged to midsetwing or high mounted wing and there is 0 ° of the upper counterangle.Complete dynamic front wing 3 helps further to improve bowing for aircraft
Face upward trim and handling characteristic.Front wing is moved in High Angle of Attack prior to main wing stall using above-mentioned configuration entirely, improves the big of aircraft
Angle of attack aeroperformance so that aircraft has more rational longitudinal stability.
According to some preferred embodiments of the present invention, complete dynamic front wing 3 can use with respect to the height and position of nosing
Lower single-blade, midsetwing, three kinds of high mounted wing selections, as shown in fig. 6, respectively illustrate from top to bottom using high mounted wing, midsetwing,
The entirely dynamic front wing 3 of lower single-blade configuration.According to lower single-blade, then front wing should have 3 ° -7 ° of the upper counterangle, and remaining height and position can use
0 ° of upper counterangle.It can wherein be melted for the configuration of lower single-blade and high mounted wing, the root of complete dynamic front wing 3 using radome fairing with fuselage appearance
Close transition.
With reference to shown in figure 1-2, trailing edge high lift device 7 and aileron 8 are installed in the trailing edge of the high mounted wing 2 of wing, used
Roll guidance and trim when lift-rising and the flight in the landing stage of aircraft.
According to some preferred embodiments of the present invention, Landing Gear System uses tricycle landing gear 10, nose-gear
Below nosing, main landing gear is located at below the bulge of ventral landing gear compartment wheel.Landing gear compartment bulge both provides master and risen and fallen
The space of frame folding and unfolding, while be connected with wing support bar 6.
Although the foregoing describing the embodiment of the present invention, it will be appreciated by those of skill in the art that these
It is merely illustrative of, protection scope of the present invention is defined by the appended claims.Those skilled in the art is not carrying on the back
On the premise of principle and essence from the present invention, various changes or modifications can be made to these embodiments, but these are changed
Protection scope of the present invention is each fallen within modification.
Claims (14)
1. a kind of aircraft, include the fuselage of tubular, it is characterised in that the aircraft also include being arranged at nosing it is complete dynamic before
The wing, the engine being arranged above fuselage endpiece and the wing for being arranged at fuselage posterior segment, the wing use band support bar
High mounted wing, one end of the support bar is connected to belly, the other end is connected to the high mounted wing.
2. aircraft as claimed in claim 1, it is characterised in that the other end of described support bar and the high mounted wing
The spacing of link position and the end points of the nearest high mounted wing the 55%-75% of the semispan length of the high mounted wing it
Between.
3. aircraft as claimed in claim 1, it is characterised in that the engine is open rotor engine.
4. aircraft as claimed in claim 1, it is characterised in that the high mounted wing includes the stage casing wing and the outer section of wing, described outer section
The wing is tapered airfoil, and the leading edge of the outer section of wing has bigger angle of sweep compared to trailing edge, and the difference at the angle of sweep of the two does not surpass
Cross 10 °.
5. aircraft as claimed in claim 4, it is characterised in that the parting surface of the outer section of wing and the stage casing wing is nearby hung
There is streamlined oil storage chamber, the other end of the support bar is connected to the shell of the streamlined oil storage chamber.
6. aircraft as claimed in claim 5, it is characterised in that the support bar is using relative thickness between 10%-13%
The symmetrical laminar flow airfoil of zero camber.
7. aircraft as claimed in claim 4, it is characterised in that the stage casing wing is using relative thickness between 12%-13%
Laminar flow airfoil, the outer section of wing use laminar flow airfoil of the relative thickness between 9%-12%.
8. aircraft as claimed in claim 4, it is characterised in that the stage casing wing is in straight rectangular shape, the stage casing wing
The upper counterangle be 0 °, the upper counterangle of the outer section of wing is between 6 ° -10 °, and the taper ratio of the outer section of chord-length is in 0.45-0.75
Between.
9. aircraft as claimed in claim 1, it is characterised in that the aspect ratio of the high mounted wing is more than 15.
10. aircraft as claimed in claim 3, it is characterised in that the aircraft also includes tailplane, the open rotor hair
Motivation blade is rearmounted, and the open rotor engine arrangement is on the top airfoil of the tailplane, and the rotation of the blade
Plane is in after the trailing edge of the tailplane.
11. aircraft as claimed in claim 1, it is characterised in that be separately installed with the left and right taper of the tailplane vertical
Fin.
12. aircraft as claimed in claim 1, it is characterised in that the tailplane is using the laminar flow for bearing camber or zero camber
Aerofoil profile.
13. aircraft as claimed in claim 1, it is characterised in that the entirely dynamic front wing is trapezoidal within 10 ° using angle of sweep
The wing, the entirely dynamic front wing use laminar flow airfoil of the relative thickness between 12%-13%.
14. aircraft as claimed in claim 1, it is characterised in that the entirely dynamic front wing be arranged to lower single-blade and with 3 ° -7 ° it
Between the upper counterangle, or, be arranged to midsetwing or high mounted wing and with 0 ° of the upper counterangle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710874106.8A CN107804469B (en) | 2017-09-25 | 2017-09-25 | Aircraft |
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|---|---|---|---|
| CN201710874106.8A CN107804469B (en) | 2017-09-25 | 2017-09-25 | Aircraft |
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| CN107804469A true CN107804469A (en) | 2018-03-16 |
| CN107804469B CN107804469B (en) | 2024-04-19 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018302A (en) * | 2018-08-14 | 2018-12-18 | 晨龙飞机（荆门）有限公司 | A kind of scalable modular unmanned plane wing that can regulate and control on demand |
| CN111319775A (en) * | 2018-12-14 | 2020-06-23 | 庞巴迪公司 | Forward swept wing aircraft with boundary layer suction and distributed electric propulsion system |
| CN112478157A (en) * | 2019-09-11 | 2021-03-12 | 北京京东尚科信息技术有限公司 | Freight unmanned aerial vehicle |
| CN113654882A (en) * | 2021-06-18 | 2021-11-16 | 中国商用飞机有限责任公司 | Experimental loading device of horizontal tail |
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