CN103538716B - A kind of efficient and stable oblique inversion wing - Google Patents
A kind of efficient and stable oblique inversion wing Download PDFInfo
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- CN103538716B CN103538716B CN201310364744.7A CN201310364744A CN103538716B CN 103538716 B CN103538716 B CN 103538716B CN 201310364744 A CN201310364744 A CN 201310364744A CN 103538716 B CN103538716 B CN 103538716B
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Abstract
The invention discloses a kind of efficient and stable oblique inversion wing, including the left wing and the right flank that are positioned at aircraft both sides, left and right wing structure is identical and symmetrical, it is characterized in that: before and after aerodynamic configuration of aircraft, width is inconsistent, the composite entity of both sides wing is sweepforward or sweepback trend, the fore-end of the left and right contacted at first at air-flow is respectively equipped with guide vane, and the end section of the left and right finally contacted at air-flow is respectively equipped with row's wing；Described aircraft both sides wing is when just overlooking, and the wing of both sides wing extends axis angle and points to and both wings curling axis angle sensing contrary.Owing to using above-mentioned wing configurations structure, reduce resistance and improve usefulness, therefore the vertical fin that the aircraft of this patent can use less area even removes vertical fin from, thus simplify and fly to control parts and control method, this patent both may be used for high-speed aircraft and improved its high-speed maneuverability, it is also possible to improve its low speed elevation performance for high heavy burden aircraft.
Description
Technical field
The present invention relates to the topology layout of a kind of aircraft wing, for blended wing-body aircraft, half side fuselage is i.e. equivalent to its side wing, so being directed to the overall aerodynamic arrangement of aircraft.
Background technology
Present aircraft wing design typically has canard, main wing, empennage and vertical fin (or V-arrangement tail), for providing lift and flight to control for aircraft, but separating due to each wing body, cause aircraft flow perturbation to be strengthened, add the energy consumption of aircraft, reduce Vehicle Structure Strength.
Patent Office of the People's Republic of China discloses Publication No. CN1636827 on July 13rd, 2005, patent name is the patent of invention that the wing that a kind of lift-drag ratio is high and angle of stall(ing) is big adds rectifying wings aerodynamic arrangement, this patent is mainly collectively formed with rectifying wings by wing, it is characterized in that: above the wing of airframe two side, use and have certain intervals distance with wing, and lower surface is the most parallel with wing slightly to be upwarped with rear portion, and the method that forward edge moves about the two spacing left and right distance the most afterwards relative to the leading edge of a wing, install one same or like with wing profile, but generally width and area are significantly less than the rectifying wings of wing, and make it together with the wing of lower section, form from front and back with left and right directions in terms of time be all the wing combined pneumatic layout structure of two shape.It is high little with flight resistance that the combination of such wing will have lift, and available flying angle is big, and during High Angle of Attack, induced drag is little and is not likely to produce flight stability advantages of higher under stall, normal flight and bad-weather condition, but it exists the defect that usefulness is low.
Patent Office of the People's Republic of China discloses Publication No. CN102267557A on December 7th, 2011., patent name is the patent of invention that a kind of canard sweepforward becomes the telescopic wing aerodynamic arrangement of length wing area, this patent includes fuselage, canard, wing and vertical fin, wing includes wing and the scalable outer wing of sweepforward in sweepforward, the scalable outer wing of sweepforward is connected by telescoping mechanism and wing in sweepforward are internal, when unmanned plane Mach 2 ship 0.2, telescoping mechanism stretches and scalable for sweepforward outer wing reaches airfoil outer in sweepforward, when unmanned plane Mach 2 ship 0.4, telescoping mechanism shrinks and is contracted in by scalable for sweepforward outer wing in sweepforward inside wing, wherein the scalable outer wing of sweepforward is 0.25～0.45 with the area ratio of wing in sweepforward.The present invention uses the telescopic wing layout becoming length wing area, makes unmanned plane in different spatial domains, different speed regime all has good aeroperformance, improves mobility and the flexibility of unmanned plane；The present invention is in Ma=0.2 and 0.4 scope, during low-speed operations, high aspect ratio aerodynamic arrangement cruise lift-drag ratio is higher by more than 20% than low aspect ratio, during high-speed flight, low aspect ratio aerodynamic arrangement cruise lift-drag ratio is higher by about 15% than high aspect ratio, possesses the ability of Ma0.2 and Ma0.4 cruising flight, but in this patent, vertical fin is also that critically important flying controls parts, exist and fly to control parts complexity, unhandy defect.
Summary of the invention
It is an object of the invention to provide a kind of efficient and stable oblique inversion wing, this wing can significantly improve mobility and the cylinder block strength of super speed vehicle, also can significantly improve stability and the lifting performance of the high aircraft that bears a heavy burden, also simplify aircraft flies control parts and control method.
For solving above-mentioned technical problem, the technical solution adopted in the present invention is as follows:
A kind of efficient and stable oblique inversion wing, including the topology layout being positioned at aircraft left and right sides wing, blended wing-body aircraft is then referred to the left and right sides fuselage of aircraft, the left and right sides wing structure layout of aircraft is identical and symmetrical, it is characterized in that: before and after aerodynamic configuration of aircraft, width is inconsistent, wing total arrangement has the trend of sweepforward or sweepback, guide vane can be respectively equipped with in aircraft front part sides, and/or in aircraft aft both sides can the row's of being respectively equipped with wing, control the flight attitude of aircraft and track by guide vane and/or row's wing；When just overlooking, the wing of described aircraft both sides wing extends axis angle and points to and wing curling axis angle sensing contrary.
The aerodynamic arrangement of aircraft generally forward swept surfaces or the swept-back wing, when using swept-back wing aerodynamic arrangement, aircraft is beloid, and during each airfoil portion stretched flat, wing leading edge has sweepback trend；When using buzzard-type wing aerodynamic arrangement, aircraft is front wide and rear narrow, and during each airfoil portion stretched flat, airfoil trailing edge has sweepforward trend；For blended wing-body aircraft, above-described both sides wing then refers to both sides fuselage.
Secondary guide vane it is provided with in described guide vane；Secondary row's wing it is provided with in described row's wing；Guide vanes at different levels and row the wing straight launch time, each several part wing body in homonymy wing the most in the same plane, and each several part wing body flush edge engage.A kind of efficient and stable oblique inversion wing according to claim 1, it is characterized in that: as unilateral wing is open and flat open time be similar to triangle or quadrangle, and when being provided with obvious sweepforward or sweepback trend of double-vane, then guide vane or row's wing are by the symmetrical inner side being arranged at wing or outside；If being simultaneously provided with guide vane and row's wing, when guide vane is positioned at inboard, row's wing is then positioned at outside wing, and vice versa.
On unilateral wing, described secondary guide vane or secondary row's wing, all when stretched flat state, when guide vane and row's wing action, can form three kinds of curved surfaces with the standing part of wing, be respectively " ∧ " shape, "～" shape or " " shape curved surface；When forming " ∧ " shape curved surface, surface intersection line was both neither perpendicular to nor parallel to fuselage axis；Formed "～" shape or " " shape curved surface and when just overlooking, the fuselage outer side extended line angle of two surface intersection lines is not more than 90 degree.
Four kinds of curve forms of aerofoil formation during described unilateral wing action: concave shape, convex shaped, the most gradually lifting shape, the most gradually lifting shape；Wing various curved surface in both sides coordinates and may be constructed following aerodynamic arrangement: first, and when both sides wing is all concave shape or convex shaped, both sides wing constitutes spoon shape aerodynamic arrangement；Second, when both sides wing is all lifting shape forward or backward, both sides wing constitutes the aerodynamic arrangement that inclined-plane raises forward or backward；3rd, when both sides wing is side lifting shape forward, and opposite side is lifting shape backward, both sides wing constitutes helical form aerodynamic arrangement.4th, when side wing is concave shape, and opposite side is convex shaped, both sides wing constitutes decelerating barrier aerodynamic arrangement.
The aerodynamic arrangement of described both sides wing entirety is swept-back wing, two guide vanes are positioned at inboard near head, two row's wings are positioned at wingtip near tail cone, the back edge of guide vane and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepforward trend, the leading edge of row's wing and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepforward trend.
The aerodynamic arrangement of described both sides wing entirety is buzzard-type wing, two guide vanes are positioned at outside near front fuselage, two row's wings are positioned at inboard near tail, the back edge of guide vane and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepback trend, the leading edge of row's wing and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepback trend.
Described aircraft is if blended wing-body, i.e. fuselage and wing is one-body molded, then both sides fuselage is both sides wing.
The shape of described guide vane and row's wing self is all approximately triangle or quadrangle.
Describe this patent for convenience, need to define a conventional visual angle, in addition it is also necessary on the unilateral wing of aircraft, define both direction and two straight lines.Owing to when flight, fuselage also can be by the active force of air-flow, so the half side fuselage of aircraft is also a part for homonymy wing in theory, to blended wing-body aircraft then using half side fuselage as its unilateral wing.If being simply divided into blended wing-body and wing body to have two classes in obvious boundary line in aircraft, for blended wing-body class aircraft, five definition are then to make with the theoretic unilateral the most half side fuselage of wing for object below, having obvious boundary line class aircraft for wing body, five definition are to make on the unilateral wing do not include fuselage below.
Just overlook: when aircraft both sides wing stretches expansion and horizontal linear flies at a constant speed, a straight line a identical with heading is made through aircraft center of gravity, the midpoint of the both sides wing wing tip of aircraft is connected and makees a line segment b, move in parallel line segment b to make its midpoint overlap with aircraft center of gravity point to obtain a plane, on that plane, with b line as x-axis, with a line as y-axis, with aircraft direction of advance for y-axis positive direction, it is referred to as just overlooking with this view aircraft.
Wing curl direction: for theoretic unilateral wing, if there being the air stream that one direction and size are all fixed, the no matter movable wing of this side wing how action, minimum to its active force produced when this air-flow flows through wing, the direction of this strand of air stream is wing curl direction.
Wing bearing of trend: for theoretic unilateral wing, if there being the air stream that one direction and size are all fixed, when each movable wing of this side wing stretches expansion, minimum to its active force produced when this air-flow flows through wing, the direction of this strand of air stream is wing bearing of trend.
Wing curling axis: in the case of unilateral wing stretches expansion, makees one direction identical with wing curl direction and pass the boost line of aircraft center of gravity, and this boost line is the wing at the projection line of the plane representated by this side wing and crimps axis.This axis can be used to approximate and changes through the interception direction of air-flow when representing unilateral wing action.
The wing extends axis: in the case of unilateral wing stretches expansion, makees one direction identical with wing bearing of trend and pass the boost line of aircraft center of gravity, and this boost line is wing extension axis at the projection line of the plane representated by this side wing.This axis can be used to approximate the flow direction being directed through air-flow when representing unilateral wing stretching, extension.
When just overlooking the aircraft double-vane using this patent, during expansion that double-vane each several part is straight, entirety is the tilted shape of sweepforward or sweepback, each row's wing and guide vane are when straight expansion, the flush edge of each several part of unilateral wing engages and becomes the whole wing in a plane, two wings of two flanks extend axis and will intersect at a point formation angle, article two, wing curling axis also will intersect at a point formation angle, and the sensing of the two angle must be contrary.Described sensing contrary includes the wing and extends in axis angle or wing curling axis angle, the situation having angle to be 180 degree.
In homonymy wing, the transformable degree of wing curved surface is the biggest, and wing curl direction and wing bearing of trend are closer to orthogonal, and the motor-driven usefulness of wing is the best.When using this patent, the aircraft pursuing high speed high maneuverability energy typically uses beloid swept-back wing aerodynamic arrangement, and engine is typically located on the axis of aircraft；The aircraft pursuing low speed height lifting performance typically uses front wide and rear narrow buzzard-type wing aerodynamic arrangement, on the generally symmetrical both wings limit being arranged in aircraft of engine.
Beneficial effects of the present invention: owing to using above-mentioned wing structure layout, make when just overlooking aircraft, wing curling axis angle points to and the wing extends axis angle and points to contrary, therefore the vertical fin that the aircraft of this patent can use less area even removes vertical fin from, thus simplify aircraft fly control parts and control method, for super speed vehicle, its high-speed maneuver performance can be optimized, for height heavy burden aircraft, its low speed elevation performance can be optimized.
Accompanying drawing explanation
The present invention is described in further detail below in conjunction with the accompanying drawings, and every width figure is all positive depression angle.
Fig. 1 is the structural representation of the embodiment of the present invention 1；
Fig. 2 is the structural representation of the embodiment of the present invention 2；
Fig. 3 is the structural representation of the embodiment of the present invention 3；
Fig. 4 is the structural representation of the embodiment of the present invention 4；
Fig. 5 is the structural representation of the embodiment of the present invention 5；
In figure: 1, left wing；2, right flank；3, guide vane；4, row's wing；5, wing curling axis；6, the wing extends axis；7, canard；8, empennage；9, secondary guide vane；10, secondary row's wing；11, fixing wing section；B, the wing extend axis angle；A, wing curling axis angle.
Detailed description of the invention
Embodiment 1: as shown in Figure 1, a kind of efficient and stable oblique inversion wing, this wing is mainly used in wing body the transporter in obvious boundary line, it includes left wing 1 and the right flank 2 being positioned at fuselage both sides, described left wing 1 and right flank 2 use front wide and rear narrow forward swept to tilt aerodynamic arrangement's structure of wing, left wing 1 is identical and symmetrical with the structure of right flank 2, fuselage is for being approximately post strip, wing is sheet and has more apparent boundary line with fuselage, it is respectively equipped with guide vane 3 in the leading section of left wing 1 and right flank 2, two guide vanes 3 are symmetrical, for fixing wing section 11 after guide vane, it is provided with symmetrical swept fin 8 in tail cone part, each guide vane and empennage are by overturning certain angle, flight attitude and flight path to aircraft are controlled；Described guide vane is bordered on fixing wing section near a side of fixing wing section all the time when upset；The sensing of the included angle A of the curling axis 5 of described double-vane 1,2 and the wing extend the sensing contrary of the included angle B of axis 6；Described every side guide vane 3 constitutes a plane whole wing when straight deployed condition with fixing airfoil portion.
Embodiment 2: as shown in Figure 2, a kind of efficient and stable oblique inversion wing, this wing is mainly used in wing body the fighter plane in obvious boundary line, it includes left wing 1 and the right flank 2 being positioned at fuselage both sides, described left wing 1 and right flank 2 use beloid swept-back to tilt aerodynamic arrangement's structure of wing, left wing 1 is identical and symmetrical with the structure of right flank 2, fuselage is for being approximately post strip, wing is sheet and has more apparent boundary line with fuselage, it is provided with symmetrical sweepforward canard 7 in front fuselage part, it is respectively equipped with row's wing 4 at wing end section, two row's wings 4 are symmetrical, for fixing wing section 11 before row's wing, canard and each row's wing are by overturning certain angle, flight attitude and flight path to aircraft are controlled；Described row's wing is bordered on fixing wing section near a side of fixing wing section all the time when upset；The sensing of the included angle A of the curling axis 5 of described double-vane 1,2 and the wing extend the sensing contrary of the included angle B of axis 6；Described every side row's wing 4 constitutes a plane whole wing when straight deployed condition with fixing airfoil portion.
nullEmbodiment 3: as shown in Figure 3，A kind of efficient and stable oblique inversion wing，This wing is mainly used in high heavy burden anury wing blended wing-body aircraft，It includes left wing 1 integrated with fuselage and right flank 2，Described left wing 1 and right flank 2 use front wide and rear narrow forward swept to tilt the aerodynamic arrangement of wing，Left wing 1 is identical and symmetrical with the structure of right flank 2，It is all the sheet the most thinning to edge by centre，It is respectively equipped with guide vane 3 in face of airflow direction in the leading section of the left wing 1 that air-flow contacts at first and right flank 2，Two guide vanes 3 are symmetrical，The wing end section finally contacted at air-flow is respectively equipped with row's wing 4 with the dispersal direction of air-flow，Two row's wings 4 are symmetrical，For fixing wing section 11 between guide vane and row's wing，Guide vane and row's wing are by overturning certain angle，Flight attitude and flight path to fuselage are controlled，Described guide vane or row's wing are bordered on fixing wing section near a side of fixing wing section all the time when upset；The sensing of the included angle A of described wing curling axis 5 and the wing extend the sensing contrary of the included angle B of axis 6；Described each guide vane 3 or row's wing 4 constitute a plane whole wing when straight deployed condition with the fixing airfoil portion of homonymy wing.
nullEmbodiment 4: as shown in Figure 4，A kind of efficient and stable oblique inversion wing，This wing is mainly used in anury wing blended wing-body aircraft at high speed，It includes left wing 1 integrated with fuselage and right flank 2，Described left wing 1 and right flank 2 use beloid swept-back to tilt the aerodynamic arrangement of wing，Left wing 1 is identical and symmetrical with the structure of right flank 2，It is all the sheet the most thinning to edge by centre，It is respectively equipped with guide vane 3 in face of airflow direction in the leading section of the left wing 1 that air-flow contacts at first and right flank 2，Two guide vanes 3 are symmetrical，The wing end section finally contacted at air-flow is respectively equipped with row's wing 4 with the dispersal direction of air-flow，Two row's wings 4 are symmetrical，For fixing wing section 11 between guide vane and row's wing，Guide vane and row's wing are by overturning certain angle，Flight attitude and flight path to fuselage are controlled；Described guide vane or row's wing are bordered on fixing wing section near a side of fixing wing section all the time when upset；The sensing of the included angle A of described wing curling axis 5 and the wing extend the sensing contrary of the included angle B of axis 6.Described each guide vane 3 or row's wing 4 constitute a plane whole wing when straight deployed condition with the fixing airfoil portion of homonymy wing.
nullEmbodiment 5: as shown in Figure 2，A kind of efficient and stable oblique inversion wing，This wing have employed multistage guide vane and row's wing structure，It includes left wing 1 and the right flank 2 being positioned at fuselage both sides，Described left wing 1 and right flank 2 use beloid swept-back to tilt aerodynamic arrangement's structure of wing，Left wing 1 is identical and symmetrical with the structure of right flank 2，Fuselage is for being approximately post strip，Wing is triangle sheet and has obvious boundary line with fuselage，Symmetrical two-stage guide vane 3 and 9 it is respectively equipped with in the leading section of left wing 1 and right flank 2，The guide vane 3 that wherein area is maximum is provided with secondary guide vane 9，It is respectively equipped with symmetrical two-stage row's wing 4 and 10 at wing end section，Row's wing 4 that area is maximum is provided with secondary row's wing 10，For fixing wing section 11 between guide vane and row's wing，Guide vane 3 its lower side when action is bordered on wing standing part all the time，Secondary guide vane 9 its lower side remainder with guide vane 3 all the time when action is bordered，Same，Main row's wing 4 its upper side edge when action is bordered on wing standing part all the time，Secondary row's wing 10 its upper side edge when action is bordered with the remainder arranging the wing 4 all the time；Guide vanes at different levels and row's wing at different levels are by overturning certain angle, and flight attitude and flight path to aircraft are controlled；The sensing of the included angle A of the curling axis 5 of described wing and the wing extend the sensing contrary of the included angle B of axis 6.Described every side guide vane at different levels 3,9 and row's wing at different levels 4,10 constitute a plane whole wing when straight deployed condition with fixing airfoil portion.
Operation principle: the function of guide vane is to control the sensing of aircraft stem, swings up and down by controlling both sides guide vane respectively, the independent air flow changed on front side of both wings, make a concerted effort change of flight device drag direction and the anterior attitude of generation.The function of row's wing is to control aircraft afterbody to be flapped toward, and swings up and down by controlling both sides row's wing respectively, and the independent air row changing both wings end is to, make a concerted effort change of flight device thrust direction and the afterbody attitude of generation.
The above is the exemplary embodiment of the present invention, certainly can not limit the interest field of the present invention with this.It should be pointed out that, that the unspecified part of the present invention belongs to those skilled in the art of the present technique's common knowledge, to those of ordinary skill in the art, technical scheme is modified or equivalent, without departure from protection scope of the present invention.
Claims (2)
1. an efficient and stable oblique inversion wing, including the topology layout being positioned at aircraft left and right sides wing, blended wing-body aircraft is then referred to the left and right sides fuselage of aircraft, the left and right sides wing structure layout of aircraft is identical and symmetrical, it is characterized in that: before and after aerodynamic configuration of aircraft, width is inconsistent, wing total arrangement has the trend of sweepforward or sweepback, it is respectively equipped with guide vane in aircraft front part sides, and/or in aircraft aft both sides can the row's of being respectively equipped with wing, control the flight attitude of aircraft and track by guide vane and/or row's wing；When just overlooking, the wing of described aircraft both sides wing extends axis angle and points to and wing curling axis angle sensing contrary；
Secondary guide vane it is provided with in described guide vane；Secondary row's wing it is provided with in described row's wing；When guide vanes at different levels and the straight expansion of row's wing, each several part wing body in homonymy wing is the most in the same plane；
As unilateral wing is open and flat open time be similar to triangle or quadrangle, and when being provided with obvious sweepforward or sweepback trend of double-vane, then guide vane or row's wing are by the symmetrical inner side being arranged at wing or outside；If being simultaneously provided with guide vane and row's wing, when guide vane is positioned at inboard, row's wing is then positioned at outside wing, and vice versa；
On unilateral wing, described secondary guide vane or secondary row's wing, all when stretched flat state, when guide vane and row's wing action, can form three kinds of curved surfaces with the standing part of wing, be respectively " ∧ " shape, "～" shape or " " shape curved surface；When forming " ∧ " shape curved surface, surface intersection line was both neither perpendicular to nor parallel to fuselage axis；Formed "～" shape or " " shape curved surface and when just overlooking, the fuselage outer side extended line angle of two surface intersection lines is not more than 90 degree；
During unilateral wing action, aerofoil forms four kinds of curve forms: concave shape, convex shaped, the most gradually lifting shape, the most gradually lifting shape；Wing various curved surface in both sides coordinates and may be constructed following aerodynamic arrangement: first, and when both sides wing is all concave shape or convex shaped, both sides wing constitutes spoon shape aerodynamic arrangement；Second, when both sides wing is all lifting shape forward or backward, both sides wing constitutes the aerodynamic arrangement that inclined-plane raises forward or backward；3rd, when both sides wing is side lifting shape forward, and opposite side is lifting shape backward, both sides wing constitutes helical form aerodynamic arrangement；4th, when side wing is concave shape, and opposite side is convex shaped, both sides wing constitutes decelerating barrier aerodynamic arrangement.
A kind of efficient and stable oblique inversion wing the most according to claim 1, it is characterized in that: the aerodynamic arrangement of aircraft generally forward swept surfaces or the swept-back wing, when using swept-back wing aerodynamic arrangement, aircraft is beloid, and during each airfoil portion stretched flat, wing leading edge has sweepback trend；When using buzzard-type wing aerodynamic arrangement, aircraft is front wide and rear narrow, and during each airfoil portion stretched flat, airfoil trailing edge has sweepforward trend；For blended wing-body aircraft, above-described both sides wing then refers to both sides fuselage；
The aerodynamic arrangement of both sides wing entirety is swept-back wing, two guide vanes are positioned at inboard near head, two row's wings are positioned at wingtip near tail cone, the back edge of guide vane and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepforward trend, the leading edge of row's wing and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepforward trend；
The aerodynamic arrangement of both sides wing entirety is buzzard-type wing, two guide vanes are positioned at outside near front fuselage, two row's wings are positioned at inboard near tail, the back edge of guide vane and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepback trend, the leading edge of row's wing and the smooth splicing of fixing wing section, splicing line is straight outside or has sweepback trend；
Fuselage and the wing of aircraft are one-body molded, and both sides fuselage is both sides wing；
The shape of guide vane and row's wing self is all approximately triangle or quadrangle.
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| CN201310364744.7A CN103538716B (en) | 2013-08-21 | 2013-08-21 | A kind of efficient and stable oblique inversion wing |
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| CN201310364744.7A CN103538716B (en) | 2013-08-21 | 2013-08-21 | A kind of efficient and stable oblique inversion wing |
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| CN103538716B true CN103538716B (en) | 2016-09-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118753493B (en) * | 2024-09-05 | 2024-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Fixed wing supersonic aircraft capable of reducing transonic resistance |
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| EP1531126A1 (en) * | 2003-11-11 | 2005-05-18 | Airbus UK Limited | Wing tip device |
| CN101547829A (en) * | 2006-10-18 | 2009-09-30 | Aerion公司 | Highly efficient supersonic laminar flow wing |
| CN103209892A (en) * | 2010-07-28 | 2013-07-17 | 航空集团联合控股公司 | Aircraft with an integral aerodynamic configuration |
| CN203714171U (en) * | 2013-08-21 | 2014-07-16 | 林仕华 | High-efficient and stable oblique inverter wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8083185B2 (en) * | 2007-11-07 | 2011-12-27 | The Boeing Company | Aircraft wing tip having a variable incidence angle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| EP1531126A1 (en) * | 2003-11-11 | 2005-05-18 | Airbus UK Limited | Wing tip device |
| CN101547829A (en) * | 2006-10-18 | 2009-09-30 | Aerion公司 | Highly efficient supersonic laminar flow wing |
| CN103209892A (en) * | 2010-07-28 | 2013-07-17 | 航空集团联合控股公司 | Aircraft with an integral aerodynamic configuration |
| CN203714171U (en) * | 2013-08-21 | 2014-07-16 | 林仕华 | High-efficient and stable oblique inverter wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
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