CN101830280A - Aerodynamic configuration of aircraft - Google Patents
Aerodynamic configuration of aircraft Download PDFInfo
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- CN101830280A CN101830280A CN 201010163685 CN201010163685A CN101830280A CN 101830280 A CN101830280 A CN 101830280A CN 201010163685 CN201010163685 CN 201010163685 CN 201010163685 A CN201010163685 A CN 201010163685A CN 101830280 A CN101830280 A CN 101830280A
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Abstract
The invention relates to an aerodynamic configuration of an aircraft. The aircraft comprises two parts, wherein the front part comprises a sweepforward wing edge-sharpening wing body syzygy and an outer wing section and the rear part comprises a triangular wing edge-sharpening wing body syzygy and an outer wing section. Left and right sweepforward wings arranged at the front part and left and right triangular wings arranged at the rear part are connected in series on the same horizontal plane; and wing roots of the left and right sweepforward wings and the left and right triangular wings are connected in parallel and then connected in series. Front edges and rear edges of the sweepforward wings and the triangular wings are respectively jointed together. Front edges of the sweepforward wings are jointed at an aircraft head part; rear edges of the sweepforward wings are combined with inner wing sections of the front edges of the triangular wings together; and the rear edges of the triangular wings are jointed at the aircraft tail. The sweepforward wings are connected with the triangular wings, so that the structure is firmer. Meanwhile, the invention has the advantages of a sweepforward wing airplane and a triangular wing airplane, complements the defects of the sweepforward wing airplane and the triangular wing airplane and has better performances.
Description
Technical field
The present invention relates to a kind of aerodynamic arrangement of aircraft, the aerodynamic arrangement of this aircraft is applicable to aircraft and ground effect vehicle.
Background technology
Biplane, buzzard-type wing, delta wing, wing body merges all-wing aircraft, and the buzzard-type wing bending is dispersed, ground effect airworthiness.
Buzzard-type wing has flight high maneuverability energy, short take-off and landing (STOL), the high controllability four big advantages of low-speed operations in pneumatic structure layout, the subsonic.There are the serious problems of configuration aspects in buzzard-type wing.Buzzard-type wing when supersonic speed, produce the flexural deformation meeting make outside wing incidence increase, thereby the lift of outer wing is increased, further cause wing flexural deformation.Under enough big speed, this phenomenon can form vicious circle, fractures until the wing bending, is called as bending and disperses.For tackling this problem, need to increase wing structure weight increasing counter-bending ability, but will offset the benefit that buzzard-type wing brings like this.Therefore, buzzard-type wing is not widely adopted all the time.After the seventies in 20th century, people begin to utilize the bending distortion coupling effect of composite structure to overcome the bending divergence problem.New material and The Application of Technology make swept forward wing plane draw attention again.On December 14th, 1984, U.S. X-29 buzzard-type wing proof machine goes up to the air first.On September 25th, 1997, Muscovite Soviet Union-37 Forward Swept Wing Fighter is taken a flight test.Indicate that swept forward wing plane has stepped into new development phase.But can not be the same, so the i.e. different balance in roll ability of two limit lift when reaching bending when distortion two aerofoil deformation angles.
In light weight, the good rigidity of delta wing wing helps placing alighting gear, lays fuel oil and other equipment.Delta wing supersonic speed resistance is little, and amount of movement is little backward in the wing center of pressure when subsonic velocity carries out the transition to supersonic speed, and this is particularly important for the poor aircraft of rudder face balanced capacity, so tailless aircraft and aircraft all adopt delta wing basically.The supersonic speed aircraft is the form of delta wing commonly used also, but because supersonic speed delta-winged aircraft aspect ratio is less, the 1ift-drag ratio during subsonic velocity flight is low, so the subsonic velocity cruising characteristics are bad.The delta wing of low aspect ratio only has enough lift coefficient under the big angle of attack, because of the angle of attack before the aircraft landing can not be very big, so its landing data is relatively poor.
Because aircraft, fighter plane use the structure of single host wing because of factors such as aerodynamic drag, structural weights, and can not perfection take into account low speed and supersonic speed performance.Adopt the variable swept back wing technology though have, but realize, can also reduce stability causing difficulty in the structure of wing, materials used, design, the manufacturing with aerodynamic arrangement and the form that changes whole host wing.By changing material, the structure of buzzard-type wing, can only postpone the generation speed that bending is dispersed, not too big leap; And increase the structural weight of whole wing, to increase counter-bending ability, also can increase body weight, and offset the bigger advantage of buzzard-type wing lift.
Summary of the invention
The present invention is a kind of aerodynamic arrangement of course of new aircraft.Have high low-speed operations and certain ground effect flight concurrently,, improve the task adaptive capacity of aircraft to improve manoevreability.
Technical scheme of the present invention is: two bottom wing fringing sharpening wing bodies merged all-wing aircraft (interior wing panel), low aspect ratio wing (outer panel), no empennage, no vertical fin layout before and after this aircraft adopted vertical integration.This aircraft is divided into anterior buzzard-type wing edge sharpening blended wing-body adds outer panel and rear portion delta wing edge sharpening blended wing-body adds the outer panel two large divisions.Its composition mode is to add the left and right sides, rear portion delta wing with anterior left and right sides buzzard-type wing to be connected in same horizontal surface, and left and right sides buzzard-type wing links to each other parallel series together side by side with left and right sides delta wing wing root.The leading edge of buzzard-type wing and delta wing joins respectively with trailing edge is in the same place.The leading edge of buzzard-type wing joins in the head place, and wing panel combines in trailing edge and the delta wing leading edge, and the trailing edge of delta wing joins in tail.The front and back wing span is wide equally.Buzzard-type wing and delta wing are divided into outer panel and interior wing panel again.Outer panel is a wing, all adopts corner cut triangle aerofoil, and anterior outer panel is because of the buzzard-type wing sweepforward, and the rear portion outer panel is because of the delta wing sweepback.The outer panel of buzzard-type wing can change sweepforward angle, and the delta wing outer panel is a fixed type.
Buzzard-type wing is characterized as: left and right sides buzzard-type wing is divided into outer panel and interior wing panel by line segment 1, makes leading edge be divided into inner segment and outer section, and more than inner segment sweepforward 35 degree, outer section is initial the same with the inner segment sweepforward number of degrees, but changes the sweepforward number of degrees (35 °-0 °) with the outer panel sweepforward.Trailing edge sweepback 40 degree.The wing root junction of its left and right sides buzzard-type wing is on the longitudinal central axis line of this aircraft.The tip string of general buzzard-type wing is in the front of root string, but the sweepforward of this buzzard-type wing leading edge, trailing edge sweepback and again in delta wing leading edge inner segment, trailing edge length is shorter than leading edge; Make wing tip chord from the trailing edge end of sweepback to the terminal sweepforward of its leading edge, form the root string in the middle of tip string.This moment, wingtip was cut point backward at the leading edge end, formed one from the wing tip of leading edge end to sweepback.Left and right sides buzzard-type wing top plan view is a butterfly's wing shape.
Delta wing is characterized as: left and right sides delta wing is divided into outer panel and interior wing panel by line segment 2, makes leading edge and trailing edge also be divided into inside and outside leading edge and inside and outside trailing edge.Leading edge inner segment sweepback 40 degree (buzzard-type wing trailing edge), outer section sweepback 45 degree, the trailing edge internal and external section is straight to connect.Its left and right sides wing root links together and with the series connection of buzzard-type wing wing root, forms the longitudinal central axis line of this aircraft.Its wingtip is marginal lappet vertical cut angle backward.
Interior wing panel is that edge sharpening wing body fusion all-wing aircraft is characterized as: it is that plane base forms by interior wing panel exactly that wing panel and outer panel in anterior buzzard-type wing and rear portion delta wing are divided into by line segment 1 and 2, edge sharpening wing body merge all-wing aircraft.Because interior wing panel is big than outer panel of shared area in the base integral blade area of this aircraft, it is very wide to make the edge sharpening wing body that is formed by interior wing panel merge the all-wing aircraft horizontal area, in order to reduce aerodynamic drag, smooth surface transition, the effect that fuselage adds wing with outer panel, need reduce fuselage thickness and make its edge thickness very thin equally sharp-pointed, merge all-wing aircraft so be called edge sharpening wing body to the edge of a knife.
The composition mode is: the edge sharpening blended wing-body that the edge sharpening blended wing-body of the interior wing panel of anterior buzzard-type wing adds wing panel in the delta wing of rear portion is combined into all-wing aircraft.Adopting lower wing and anterior buzzard-type wing to add the rear portion delta wing is connected on same horizontal surface and the axis.Wing panel fuses and forms a plane in before and after making, and it is that plane base forms at an upper portion thereof with interior wing panel just that edge sharpening wing body merges all-wing aircraft.Because of the sweepforward of buzzard-type wing inner segment leading edge also joins head is in the shape of the letter V, line segment 3 and left and right sides buzzard-type wing leading edge interface point 11, the vertical direction that tilts to arrive the junction of buzzard-type wing trailing edge interface point and delta wing inner segment leading edge interface point with direction back upper place, axis is the highest point of this aircraft, and promptly interface point 13.Line segment 4 is also from the interface point 12 of left and right sides buzzard-type wing leading edge internal and external section and line segment 1, connects to the highest point interface point 13 of aircraft.So the aerofoil between its trailing edge interface point 13 forms indent and to the vee shape aerofoil of back upper place sweepback from head along the axis to merge the all-wing aircraft front portion at edge sharpening wing body.Trailing edge (the leading edge inner segment of the delta wing) direction that line segment 6 is pressed buzzard-type wing from interface point 13 is connected with interface point 14 vertically downward, and interface point 14 is the interface point of buzzard-type wing trailing edge, inner segment wingtip and delta wing leading edge internal and external section, line segment 2.Line segment 7 longitudinally axis tilts to line segment 8, forms at delta wing edge sharpening blended wing-body top to line segment 8 plane inclined, and the aerofoil in line segment 2 and the line segment 6 also tilts to line segment 7, forms line segment 9 and line segment 10.In the line segment 8,9,10 is nozzle.It is obtuse-angled triangle that whole edge sharpening wing body merges all-wing aircraft square section basic design, and promptly the edge is an acute angle.Anterior owing to form indent vee shape aerofoil, its square section is divided into the little triangle in obtuse angle, the left and right sides by the big triangle in an obtuse angle.The rear portion is because line segment 6,7,8 forms one to back lower place nozzle plane inclined, makes the square section remove the obtuse angle, top by obtuse-angled triangle and becomes trapezium structure and dwindle to nozzle gradually.
Outer panel is that wing is characterized as: then be that interior wing panel is the extension that edge sharpening wing body merges the all-wing aircraft aerofoil, and be connected with edge sharpening wing body fusion all-wing aircraft smooth surface, form complete buzzard-type wing and delta wing.
Advantage of the present invention is: the combination that anterior buzzard-type wing adds the rear portion delta wing makes wing panel forms in it edge sharpening wing body merge all-wing aircraft and gathers around good connectivity, more strong design, bigger inside usage space, littler aerodynamic drag form and aeroperformance, and the aeroperformance merits and faults is complementary and improved each other to have buzzard-type wing and delta wing.Have high low-speed operations and certain ground effect airworthiness concurrently,, improve the task adaptive capacity of aircraft to improve manoevreability.Buzzard-type wing is as the single host wing of aircraft but make up and be used with another host wing (delta wing), can make it oversimplify and solve the bending that buzzard-type wing causes in pneumatic action, aeroperformance, pneumatic form, pneumatic structure, materials used, production and use and disperse technical scheme.
Description of drawings
Fig. 1 is the birds-eye view of normal state.
Fig. 2 is the upward view of normal state.
Fig. 3 is the birds-eye view of buzzard-type wing sweepforward state.
Fig. 4 is the upward view of buzzard-type wing sweepforward state.
Fig. 5 is a front elevation.
Fig. 6 is a back view.
Fig. 7 is a lateral plan.
The specific embodiment
A kind of later-model aerodynamic configuration of aircraft is the basis by the left and right sides delta wing 2 at two buzzard-type wings 1 about the front portion and rear portion, forms wing fringing sharpening wing body and merges the all-wing aircraft layout.The leading edge handing-over of two anterior buzzard-type wings forms the vee shape head together, and trailing edge links to each other with the leading edge inner segment of rear portion delta wing; The leading edge of delta wing also joins respectively with trailing edge is in the same place.Buzzard-type wing and delta wing are divided into outer panel and interior wing panel again, and outer panel is a wing, and interior wing panel is then to merge all-wing aircraft from form edge sharpening wing body at an upper portion thereof as plane base.The outer panel of buzzard-type wing is variable sweepforward buzzard-type wing, and the same anti-0-2 degree down with the delta wing outer panel.This aircraft is merged in the continuous wing area that all-wing aircraft forms by wing fringing sharpening wing body, and the shared area of the wing area more shared than edge sharpening wing body fusion all-wing aircraft is little.
The effect of buzzard-type wing outer panel: main rise with its in wing panel form complete buzzard-type wing and assistant edge sharpening wing body and merge that a difficult problem is dispersed in all-wing aircraft generation bending so that the whole buzzard-type wing high Mach flight of low speed and ground effect flight aeroperformance, postponement and elimination to be provided, aerodynamic drag when reducing the aircraft high speed.Be variable sweepforward outer panel, when aircraft speed improves gradually gradually forward sweepforward bending take place when postponing and solving the buzzard-type wing high speed gradually disperse to reach.When forming whole buzzard-type wing, produce low speed and ground effect flight aeroperformance jointly with forward edge sharpening wing body fusion all-wing aircraft.The current leading edge that is swept to left and right sides outer panel links to each other together side by side, be that the outer panel sweepforward is arrived below head the place ahead, by changing the pneumatic form of its outer panel is the sweepforward angle, change with outer panel small size aerofoil makes whole buzzard-type wing become sweepback by sweepforward, solve the bending that whole buzzard-type wing causes with among a small circle change and disperse a difficult problem, and merging all-wing aircraft with edge sharpening wing body, to form top plan view jointly be that the pneumatic form of triangle reduces the aerodynamic drag of aircraft high-speed flight and increases the high speed pneumatic performance.
The effect of delta wing outer panel: form complete delta wing and merge all-wing aircraft with wing panel in it and play the stability of aircraft, various maneuvering performance, high speed pneumatic performance, horizontal tail effect jointly and play the wing effect jointly with the buzzard-type wing outer panel with edge sharpening wing body.
Edge sharpening wing body merges the effect of all-wing aircraft: buzzard-type wing edge sharpening blended wing-body and delta wing edge sharpening blended wing-body are better combined together.Edge sharpening wing body merges all-wing aircraft and forms a plane at ventral, make the square section be the obtuse-angled triangle structure firmer, reduce aerodynamic drag, aeroperformance is better, internal volume is bigger.This buzzard-type wing edge sharpening blended wing-body is bigger than the wing area of outer panel, has reduced the span length of outer panel and has dispersed critical speed to postpone outer panel generation bending.By the little triangular structure in obtuse angle, the left and right sides that the vee shape head forms, there are enough spaces and better structure to reduce outer panel and produce flexural deformation and the wheel word of outer panel sweepforward is installed.Rear portion delta wing edge sharpening blended wing-body is a machinery space, the square section cuts the obtuse angle, top by obtuse-angled triangle and becomes trapezoidal, the bottom is wide and upwards dwindle gradually, the right and left aerofoil is sloped inwardly and have certain altitude, form the aerofoil that aerofoil introversion similar tail in the left and right sides hangs down, and be used for installing the comings and goings aerofoil with outer panel, so that aircraft stability and manoevreability to be provided.
The delta wing edge sharpening blended wing-body that the buzzard-type wing edge sharpening blended wing-body in the place ahead adds outer panel and rear adds outer panel at grade and combine together, because of front and back all are main wings, buzzard-type wing is than delta wing lift height when low speed, can improve the lift of delta wing, add that the delta wing resistance is little, amount of movement is little backward in the wing center of pressure when subsonic velocity carries out the transition to supersonic speed, therefore before and after the wing bear a heavy burden than being 4: 3.This buzzard-type wing mainly is provided by size, the resistance when reducing supersonic speed that increases the each several part performance and promptly provide aeroperformance, low-speed maneuver performance, load carrying ability, the outer panel of low-speed operations to play change lift, the effect that increases low-speed performance, high load capability.Delta wing mainly plays the effect of aeroperformance that flight is provided, supersonic speed performance, motor-driven controller performance, rudder face balanced capacity, certain load-carrying capacity.It is big that preposition buzzard-type wing has lift in subsonic flight, have extraordinary aeroperformance, thereby improve its manoevreability under the state of the elevation angle greatly, the low-speed control performance is good, shorten the distance of landing run that takes off, with the compensation delta wing in the subsonic velocity cruising characteristics the bad and relatively poor shortcoming of landing data.Add in light weight, the good rigidity of rearmounted delta wing wing, help placement devices, resistance is little, and amount of movement is little backward in the wing center of pressure when subsonic velocity carries out the transition to supersonic speed, and the rudder face balanced capacity is good, so maneuvering performance significantly improves.To reach the compensation of shortcoming separately between preposition buzzard-type wing and the rearmounted delta wing.
Aircraft take off, when landing, low speed and ground effect flight.The outer panel sweepforward number of degrees of anterior buzzard-type wing are between the 35-0 degree, and outer panel and edge sharpening wing body fusion this moment all-wing aircraft forms complete buzzard-type wing, plays and embodies its buzzard-type wing low speed aeroperformance to improve the deficiency of delta wing low speed aeroperformance.This moment, delta wing provided aeroperformance and pneumatic control action jointly.Buzzard-type wing and delta wing are used in combination can be provided high lift and improve the various performances of delta wing when low speed.
When aircraft entered supersonic speed, the outer panel sweepforward of anterior buzzard-type wing was to the head front (the sweepforward number of degrees be 0 degree), and the buzzard-type wing outer panel becomes delta wing at head and merges with edge sharpening wing body fusion all-wing aircraft.This moment buzzard-type wing to be mainly top plan view be that triangle morphological Edge sharpening wing body merges all-wing aircraft, reducing aerodynamic drag and aeroperformance is provided jointly, delta wing then becomes main wing and plays its high speed pneumatic performance of embodiment and pneumatic control action.The change of pneumatic form of buzzard-type wing and aerodynamic arrangement has reduced aerodynamic drag, and forms the bending divergence problem when having solved high speed.This layout has improved the high speed performance of this aircraft, is similar to the aerodynamic arrangement of guided missile.When aircraft flew in the ground effect, anterior outer panel and edge sharpening wing body merged all-wing aircraft and form complete buzzard-type wing and make windstream flow to wing root to form downward purling, change the sweepforward angle by outer panel, play the effect of control purling size; Discharge after when flowing through delta wing, increasing its low speed aeroperformance and rectification.Exert law according to uncle this moment, and the front and back air-flow velocity is slow, and the middle air flow flow velocity is fast, makes the aerofoil fusion directly produce lift and ground effect.
Claims (2)
1. aerodynamic configuration of aircraft, include buzzard-type wing and delta wing, it is characterized in that: this aircraft is divided into that anterior buzzard-type wing edge sharpening blended wing-body adds outer panel and rear portion delta wing edge sharpening blended wing-body adds the outer panel two large divisions, its composition mode is to add the left and right sides, rear portion delta wing with anterior left and right sides buzzard-type wing to be connected in same horizontal surface, left and right sides buzzard-type wing links to each other parallel series together side by side with left and right sides delta wing wing root, the leading edge of buzzard-type wing and delta wing joins respectively with trailing edge is in the same place, the leading edge of buzzard-type wing joins in the head place, wing panel combines in trailing edge and the delta wing leading edge, the trailing edge of delta wing joins in tail, and the front and back wing span is wide equally.
2. a kind of aerodynamic configuration of aircraft according to claim 1 is characterized in that: buzzard-type wing and delta wing are divided into outer panel and interior wing panel again, and the outer panel of buzzard-type wing can change sweepforward angle, and the delta wing outer panel is a fixed type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010163685A CN101830280B (en) | 2010-05-06 | 2010-05-06 | Aerodynamic configuration of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010163685A CN101830280B (en) | 2010-05-06 | 2010-05-06 | Aerodynamic configuration of aircraft |
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| Publication Number | Publication Date |
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| CN101830280A true CN101830280A (en) | 2010-09-15 |
| CN101830280B CN101830280B (en) | 2012-10-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201010163685A Expired - Fee Related CN101830280B (en) | 2010-05-06 | 2010-05-06 | Aerodynamic configuration of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436290A (en) * | 2018-12-20 | 2019-03-08 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of aircraft aerofoil fold mechanism |
Citations (5)
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|---|---|---|---|---|
| US2293644A (en) * | 1939-06-29 | 1942-08-18 | United Aircraft Corp | Tailless airplane |
| CN1143589A (en) * | 1995-08-18 | 1997-02-26 | 梁富泉 | Combined wing aircraft |
| US5984231A (en) * | 1998-06-19 | 1999-11-16 | Northrop Grumman Corporation | Aircraft with variable forward-sweep wing |
| CN201023653Y (en) * | 2007-04-24 | 2008-02-20 | 江西洪都航空工业集团有限责任公司 | Large aspect ratio sweep forward wings airplane pneumatic distribution |
| CN201647122U (en) * | 2010-05-06 | 2010-11-24 | 张伟 | Pneumatic distribution of aircraft |
-
2010
- 2010-05-06 CN CN201010163685A patent/CN101830280B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2293644A (en) * | 1939-06-29 | 1942-08-18 | United Aircraft Corp | Tailless airplane |
| CN1143589A (en) * | 1995-08-18 | 1997-02-26 | 梁富泉 | Combined wing aircraft |
| US5984231A (en) * | 1998-06-19 | 1999-11-16 | Northrop Grumman Corporation | Aircraft with variable forward-sweep wing |
| CN201023653Y (en) * | 2007-04-24 | 2008-02-20 | 江西洪都航空工业集团有限责任公司 | Large aspect ratio sweep forward wings airplane pneumatic distribution |
| CN201647122U (en) * | 2010-05-06 | 2010-11-24 | 张伟 | Pneumatic distribution of aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 《航空计算技术》 20080331 王虎峰等 飞翼布局无人攻击机气动设计研究 30-33 1-2 第38卷, 第2期 * |
| 《飞行力学》 20080831 刘文法等 变前掠翼气动布局纵向性能研究 4-7 1-2 第26卷, 第4期 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436290A (en) * | 2018-12-20 | 2019-03-08 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of aircraft aerofoil fold mechanism |
| CN109436290B (en) * | 2018-12-20 | 2023-08-22 | 中国航空工业集团公司沈阳空气动力研究所 | Aircraft airfoil folding mechanism |
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| CN101830280B (en) | 2012-10-10 |
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