CN103552682A - Airplane with combined-wing layout of flying wing and forward-swept wings - Google Patents
Airplane with combined-wing layout of flying wing and forward-swept wings Download PDFInfo
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- CN103552682A CN103552682A CN201310525116.2A CN201310525116A CN103552682A CN 103552682 A CN103552682 A CN 103552682A CN 201310525116 A CN201310525116 A CN 201310525116A CN 103552682 A CN103552682 A CN 103552682A
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Abstract
The invention provides an airplane with a combined-wing layout of a flying wing and forward-swept wings. The airplane is characterized in that thin-wing type vertical columns A and B are additionally arranged at the 70% wingspan positions of the outer sides of two side wings of a flying-wing airplane with backward-swept wings, a thin-wing type vertical column C is additionally arranged at the tail part of the flying-wing airplane, and horizontal forward-swept wings are additionally arranged at the top ends of the three thin-wing type vertical columns A, B and C so as to form the combined-wing layout of the flying wing and the forward-swept wings; elevators are arranged on the horizontal forward-swept wings and a rudder is arranged on the vertical column C; a duct type air inlet channel is adopted on the upper wing surface of the flying wing, and cracking type drag rudders are distributed at the thin-wing type vertical columns A and B. The airplane provided by the invention has the advantages that under the condition that the structure strength is effectively guaranteed, the effective aspect ratio of the wings is increased, the induced drag is reduced, the lift-drag characteristics of the airplane are improved, the stealth performance of the airplane is improved, direct-force control of the airplane in the vertical direction is realized and the detecting accuracy under the maneuvering condition is improved.
Description
Technical field
The invention belongs to the course of new aircraft field that relates to a kind of novel configuration design and aerodynamic characteristics, be specially the type aircraft layout of utilizing Flying-wing to combine with the buzzard-type wing connection wing.
Background technology
At present, commercial aircraft mostly is conventional single-blade cylindrical shape fuselage arrangement, in military affairs, attempting and successfully utilizing Flying-wing to form good stealth effect, but traditional all-wing aircraft adopts swept wing, first its stall occur at wing tip, cause that centre of lift reach and head raise up, and further deepen stall.The aerodynamic lift poor effect of the aircraft of Flying-wing when flight, while causing flight, its maneuvering performance and flying speed are very restricted, and are unfavorable for HAE flight, occur waste of fuel situation.There is the problem of aeroelastic divergence in present swept forward wing plane, is embodied in the local angle of attack increase of wing tip and can causes local lift to increase, and further strengthens the local angle of attack, until reverse, causes structural failure.Although, the aircraft of existing connecting wing at present, it is all on the basis of normal arrangement, to increase the distribution form of the wing one-tenth of connection, so its alighting gear layout can be had any problem.
Summary of the invention
In order to overcome the pneumatic problem of dispersing of the pneumatic poor effect of existing Flying-wing aircraft and buzzard-type wing, pursue better 1ift-drag ratio, the invention provides a kind of all-wing aircraft and buzzard-type wing connection wing layout aircraft.The present invention is the novel pneumatic layout aircraft that swept wing all-wing aircraft is combined with buzzard-type wing connection wing layout, and this aircraft can not only be realized certain Stealth Fighter, and better aerodynamic lift can be provided, and improves steady state stability.Meanwhile, roomy especially all-wing aircraft type fuselage can provide the larger interior space of machine and better alighting gear arrangement form.Make alighting gear there is enough spacing, the lateral stability while being conducive to take off, land.
All-wing aircraft provided by the invention and buzzard-type wing connection wing layout aircraft, in the both sides of the flying wing aircraft of swept wing, thin airfoil column A and B are added in 70% span place of wing outside, at flying wing aircraft afterbody, add thin airfoil column C, horizontal buzzard-type wing is added on top at three thin airfoil column A, B and C, forms all-wing aircraft and buzzard-type wing connection wing layout.Elevating rudder is arranged on horizontal buzzard-type wing, increases pitch control moment.Yaw rudder is arranged on the column C that is added on all-wing aircraft tail.The thin airfoil column A and the B place that in both sides wing span place, add, be all furnished with cracking drag rudder.Inlet channel adopts top airfoil duct form, is conducive to the raising of aircraft Stealth Fighter.The deflection that is coupled in the time of by all-wing aircraft and buzzard-type wing, realizes aircraft direct force is in vertical direction controlled.
The invention has the beneficial effects as follows, in the situation that effectively guaranteeing structural strength, increased effective aspect ratio of wing, reduced induced drag, thereby improved the lifting resistance characteristic of aircraft; Body top airfoil culvert type inlet channel is conducive to aircraft Stealth Fighter and improves; Direct force yaw rudder is controlled and is conducive to keep the stable of flying platform attitude, thereby improves the detection accuracy under maneuvering condition.
Accompanying drawing explanation
Fig. 1 is the whole composition of all-wing aircraft of the present invention and buzzard-type wing connection wing layout aircraft;
Fig. 2-a, Fig. 2-b, Fig. 2-c are respectively the three-view diagrams of aircraft shown in Fig. 1;
Fig. 3 is the cutaway view of top airfoil culvert type inlet channel;
Fig. 4-a and Fig. 4-b are the constructionals drawing of cracking drag rudder;
In figure: 1.. all-wing aircraft, 2.. the top connection wing, 3.. and left and right connects cabane, 4.. tail cabane, 5.. culvert type inlet channel,
6.. cracking drag rudder, 7.. elevating rudder, 8.. flaperon, 9.. yaw rudder.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
Shown in as shown in Figure 1, Figure 2-a, Fig. 2-b and Fig. 2-c, for of all-wing aircraft provided by the invention and buzzard-type wing connection wing layout aircraft realizes example.All-wing aircraft of the present invention and buzzard-type wing connection wing layout aircraft, at swept wing all-wing aircraft, 1. on fuselage, improve, in 70% span place of both sides wing outside, add left and right and connect cabane 3., at airplane tail group adding machine fin post 4., 4. 3. left and right connects cabane is thin airfoil column with tail cabane, at the top of three the column top fixing horizontals connection wing 2., 2. the top connection wing is the buzzard-type wing of horizontal positioned, has so formed the distribution form of swept wing all-wing aircraft and the buzzard-type wing connection wing.7. elevating rudder is arranged on horizontal buzzard-type wing, and 9. yaw rudder is arranged in tail cabane and 4. goes up, and 8. flaperon is arranged in the 1. top airfoil of fuselage of all-wing aircraft.The connection wing overlaps swept wing and buzzard-type wing at wing tip, makes the stressed mutual compensation of swept wing and buzzard-type wing, the Design and manufacture of simplified structure; Join the wing simultaneously and can realize the control effect of vertical tail.
In the embodiment of the present invention, 1. all-wing aircraft, adopts 30 degree sweepback angle, and all-wing aircraft aspect ratio is 4; The outer panel taper ratio of all-wing aircraft is 1, adopts intermediate gauge aerofoil profile, and relative thickness is 10%; The interior wing panel of all-wing aircraft adopts thick wing type, and relative thickness is 17%; 3. left and right between upper bottom wing connects cabane, is added on 70% all-wing aircraft span place, be highly the span grow 10%, to make structural weight reach minimum obtaining on the basis of required pneumatic effect; Connect cabane aerofoil profile and adopt symmetrical airfoil, connection wing relative thickness 2. in top is 8%～10%.For improving stealth, connection wing front and rear edge 2. in top is parallel with all-wing aircraft, adopts 30 degree sweepforward angles, and aspect ratio is 7.5.When aircraft aloft flies, because all-wing aircraft is high lift body, can produce compared with high lift, 2. the connection wing in top has increased lifting area simultaneously, can further improve lift; In addition, because left and right connects cabane blocking-up 3., can effectively suppress the formation in wing tip whirlpool, greatly reduce induced drag, thereby realize high 1ift-drag ratio.
Adopt wing layout of the present invention can greatly increase the static stability of aircraft, the center of gravity layout of aircraft is more prone to, be described as follows: when aircraft is subject to fitful wind effect and produces while coming back, 1. all-wing aircraft increases with the connection wing angle of attack 2., so lift increases, but due to the connection wing 2. focus to the distance of former aircraft focus be greater than all-wing aircraft 1. focus to the distance of former aircraft focus, so join the nose-down pitching moment that 2. wing produce, be greater than the nose-up pitching moment that 1. main wing produces, make aircraft recover original state.
In order not affect the pneumatic usefulness of aircraft, 5. employing culvert type inlet channel of the present invention, usings duct driving engine as power.Shown in as shown in Figure 1, Figure 2-a and Fig. 3,5. culvert type inlet channel is positioned at all-wing aircraft 1. on top airfoil, and engine location is arranged near the center of gravity of airplane, so that trim, horizontal position is arranged in freight house both sides.For improving duct efficiency, exhaust duct adopts the angle of flare of 5 degree.
Left and right connects cabane and 3. utilizes cracking drag rudder to produce resistance, forms yawing moment, realizes new maneuverability pattern.As shown in Fig. 4-a and Fig. 4-b, the cracking drag rudder adopting 6., being arranged in left and right connection cabane 3. locates, when 6. cracking drag rudder is opened, only produce yawing moment, can not produce rolling moment, when driftage, produce resistance and realize the control of direct force direction, avoided the coupling in manipulation, be conducive to improve the maneuvering performance of aircraft.
Simultaneously, because 2. 1. all-wing aircraft gone up and arranged controlsurface with the top connection wing simultaneously, and full mechanical coke point all-wing aircraft 1. and top join the wing 2. between, when two aerofoils are simultaneously in the same way during deflection, can in the situation that the angle of attack is constant, realize rising and the decline of aircraft, realize the direct force of vertical direction and control, thereby be conducive to keep the stable of flying platform attitude, improve the detection accuracy under maneuvering condition.
Claims (5)
1. an all-wing aircraft and buzzard-type wing connection wing layout aircraft, it is characterized in that, in the both sides of the flying wing aircraft of swept wing, thin airfoil column A and B are added in 70% span place of wing outside, at flying wing aircraft afterbody, add thin airfoil column C, horizontal buzzard-type wing is added on top at thin airfoil column A, B and C, forms all-wing aircraft and buzzard-type wing connection wing layout; Elevating rudder is arranged on horizontal buzzard-type wing, and yaw rudder is arranged on column C; Described thin airfoil column A and B place are all furnished with cracking drag rudder.
2. all-wing aircraft according to claim 1 and buzzard-type wing connection wing layout aircraft, is characterized in that, the top airfoil of described flying wing aircraft is furnished with two duct type inlet channels.
3. all-wing aircraft according to claim 1 and 2 and buzzard-type wing connection wing layout aircraft, is characterized in that described all-wing aircraft and horizontal buzzard-type wing, by the deflection that is coupled simultaneously, are realized aircraft direct force is in vertical direction controlled.
4. all-wing aircraft according to claim 1 and 2 and buzzard-type wing connection wing layout aircraft, is characterized in that, described buzzard-type wing is symmetrical airfoil, and the front and rear edge of buzzard-type wing is parallel with all-wing aircraft.
5. all-wing aircraft according to claim 4 and buzzard-type wing connection wing layout aircraft, is characterized in that, described all-wing aircraft adopts 30 degree sweepback angle, and aspect ratio is 4; The outer panel taper ratio of all-wing aircraft is 1, adopts intermediate gauge aerofoil profile, and relative thickness is 10%; The interior wing panel of all-wing aircraft adopts thick wing type, and relative thickness is 17%; Described column A and the height of B are 10% of span length; The relative thickness of described buzzard-type wing is 8%～10%, adopts 30 degree sweepforward angles, and aspect ratio is 7.5.
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| CN201310525116.2A CN103552682B (en) | 2013-10-30 | 2013-10-30 | A kind of all-wing aircraft and buzzard-type wing connection wing airplane |
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| CN201310525116.2A CN103552682B (en) | 2013-10-30 | 2013-10-30 | A kind of all-wing aircraft and buzzard-type wing connection wing airplane |
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| CN103552682A true CN103552682A (en) | 2014-02-05 |
| CN103552682B CN103552682B (en) | 2016-07-06 |
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|---|---|---|---|---|
| CN104176232A (en) * | 2014-08-18 | 2014-12-03 | 张文艳 | Three-wing glider |
| CN104443344A (en) * | 2014-11-13 | 2015-03-25 | 南京航空航天大学 | Passenger plane with joined-wing configuration |
| CN104554707A (en) * | 2015-01-14 | 2015-04-29 | 西北工业大学 | Novel flying wing unmanned aerial vehicle and heading control method thereof |
| CN105235889A (en) * | 2015-10-16 | 2016-01-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Self-adaptive rhombic wing layout of air vehicles |
| CN105366034A (en) * | 2015-11-25 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for shielding gap of unmanned aerial vehicle motion structure |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN105564638A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Special airplane pneumatic configuration |
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN106741947A (en) * | 2017-02-08 | 2017-05-31 | 杨宇腾 | A kind of Flying-wing of company structure of flying wing |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN108016617A (en) * | 2018-01-10 | 2018-05-11 | 苏州华鹏无人机科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN108557081A (en) * | 2018-03-23 | 2018-09-21 | 西北工业大学 | A kind of solar united wing unmanned plane and its control method |
| CN109649628A (en) * | 2018-12-11 | 2019-04-19 | 中国特种飞行器研究所 | A kind of long endurance wind resistance dirigible system |
| CN109835463A (en) * | 2019-04-16 | 2019-06-04 | 李则熙 | A kind of culvert type self-balancing stealth unmanned plane |
| CN110282123A (en) * | 2019-07-17 | 2019-09-27 | 高峰 | It is a kind of for natural calamity situation inspection can VTOL the electronic unmanned plane of composite wing |
| CN110341933A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of air suction type high-speed aircraft with the high pressure capture wing |
| CN110341932A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of high-speed aircraft based on high pressure capture contour of flange |
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flaperon for improving large attack angle pitching characteristic of airplane |
| CN113859514A (en) * | 2021-11-11 | 2021-12-31 | 沈阳航空航天大学 | Split type all-wing aircraft |
| CN113911318A (en) * | 2021-09-22 | 2022-01-11 | 重庆理工大学 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
| CN116451343A (en) * | 2023-03-20 | 2023-07-18 | 西北工业大学 | Wing section design method of flying wing layout aircraft considering influence of backpack type air inlet channel |
| CN112537445B (en) * | 2020-12-16 | 2024-04-23 | 北京航空航天大学合肥创新研究院 | Flying wing layout tilting rotor aircraft |
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| CN104176232A (en) * | 2014-08-18 | 2014-12-03 | 张文艳 | Three-wing glider |
| CN105564638A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Special airplane pneumatic configuration |
| CN104443344A (en) * | 2014-11-13 | 2015-03-25 | 南京航空航天大学 | Passenger plane with joined-wing configuration |
| CN104554707A (en) * | 2015-01-14 | 2015-04-29 | 西北工业大学 | Novel flying wing unmanned aerial vehicle and heading control method thereof |
| CN105235889A (en) * | 2015-10-16 | 2016-01-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Self-adaptive rhombic wing layout of air vehicles |
| CN105235889B (en) * | 2015-10-16 | 2017-04-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Self-adaptive rhombic wing layout of air vehicles |
| CN105564633A (en) * | 2015-10-22 | 2016-05-11 | 龙川 | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers |
| CN105366034B (en) * | 2015-11-25 | 2018-07-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A method of for blocking unmanned plane motion structure gap |
| CN105366034A (en) * | 2015-11-25 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for shielding gap of unmanned aerial vehicle motion structure |
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN106741947A (en) * | 2017-02-08 | 2017-05-31 | 杨宇腾 | A kind of Flying-wing of company structure of flying wing |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN107521695B (en) * | 2017-08-04 | 2020-11-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing body fusion connection wing aircraft |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN111315655B (en) * | 2017-11-02 | 2023-10-27 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for an air, water, land or space vehicle |
| CN108016617A (en) * | 2018-01-10 | 2018-05-11 | 苏州华鹏无人机科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN108557081A (en) * | 2018-03-23 | 2018-09-21 | 西北工业大学 | A kind of solar united wing unmanned plane and its control method |
| CN109649628A (en) * | 2018-12-11 | 2019-04-19 | 中国特种飞行器研究所 | A kind of long endurance wind resistance dirigible system |
| CN109835463A (en) * | 2019-04-16 | 2019-06-04 | 李则熙 | A kind of culvert type self-balancing stealth unmanned plane |
| CN110282123A (en) * | 2019-07-17 | 2019-09-27 | 高峰 | It is a kind of for natural calamity situation inspection can VTOL the electronic unmanned plane of composite wing |
| CN110341933A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of air suction type high-speed aircraft with the high pressure capture wing |
| CN110341932A (en) * | 2019-07-29 | 2019-10-18 | 中国科学院力学研究所 | A kind of high-speed aircraft based on high pressure capture contour of flange |
| CN110406671A (en) * | 2019-07-29 | 2019-11-05 | 中国科学院力学研究所 | A kind of side air inlet high-speed aircraft |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
| CN112537445B (en) * | 2020-12-16 | 2024-04-23 | 北京航空航天大学合肥创新研究院 | Flying wing layout tilting rotor aircraft |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN113022846A (en) * | 2021-05-27 | 2021-06-25 | 北京航空航天大学 | Mixed mode aircraft |
| CN113022846B (en) * | 2021-05-27 | 2021-08-03 | 北京航空航天大学 | Mixed mode aircraft |
| CN113562162A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flaperon for improving large attack angle pitching characteristic of airplane |
| CN113562162B (en) * | 2021-08-07 | 2023-12-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for using wing trailing edge flap for improving pitching characteristic of large incidence angle of aircraft |
| CN113911318A (en) * | 2021-09-22 | 2022-01-11 | 重庆理工大学 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
| CN113859514B (en) * | 2021-11-11 | 2024-04-02 | 沈阳航空航天大学 | Split type allies oneself with wing overall arrangement aircraft |
| CN113859514A (en) * | 2021-11-11 | 2021-12-31 | 沈阳航空航天大学 | Split type all-wing aircraft |
| CN116451343A (en) * | 2023-03-20 | 2023-07-18 | 西北工业大学 | Wing section design method of flying wing layout aircraft considering influence of backpack type air inlet channel |
| CN116451343B (en) * | 2023-03-20 | 2024-01-26 | 西北工业大学 | Wing section design method of flying wing layout aircraft considering influence of backpack type air inlet channel |
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