CN202279235U - Variant canard tailless aerodynamic configuration - Google Patents
Variant canard tailless aerodynamic configuration Download PDFInfo
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- CN202279235U CN202279235U CN2011203304655U CN201120330465U CN202279235U CN 202279235 U CN202279235 U CN 202279235U CN 2011203304655 U CN2011203304655 U CN 2011203304655U CN 201120330465 U CN201120330465 U CN 201120330465U CN 202279235 U CN202279235 U CN 202279235U
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Abstract
The utility model belongs to the technical field of the design of unmanned aerial vehicles, and relates to variant canard tailless aerodynamic configuration, which can realize flight with a high subsonic lift-to-drag ratio and a high supersonic lift-to-drag ratio simultaneously. Canards are arranged at the front of an airplane body, and can be folded and unfolded, wings are arranged on the rear of the airplane body, wing tips of the wings can deflect vertically, an air inlet channel is disposed at the front of the upper surface of the airplane body, a tail nozzle is arranged at the tail of the airplane body, and control surfaces are arranged on the rear edge of the airplane body and the rear edges of the wings. The variant canard tailless aerodynamic configuration adopts the design, the left and the right of the variant canard tailless aerodynamic configuration are symmetric, requirements of cruise at a high subsonic lift-to-drag ratio and supersonic penetration on aerodynamic force are efficiently met by the aid of the variation technology that the foldable wing tips and the foldable canards are combined, and contradiction of subsonic stealth cruise and supersonic flight heading stability on aerodynamic configuration is coordinately solved. The variant canard tailless aerodynamic configuration can be applied to the aerodynamic configuration design for various unmanned supersonic aircrafts.
Description
Technical field
The utility model belongs to the unmanned plane design field, relates to a kind of variant canard anury that can take into account subsonic high lift-drag ratio and the flight of hyprsonic high lift-drag ratio
Background technology
For conventional aerodynamic arrangement aircraft, subsonic flight and supersonic flight are difficult to satisfy simultaneously to the demand of aerodynamic force, and be stealthy also very difficult satisfied simultaneously to the requirement of aerodynamic arrangement with supersonic flight.
Conventional needle all adopts high aspect ratio wing and big wing area to subsonic high lift-drag ratio flight design-calculated aircraft, and the supersonic flight poor performance of this type aircraft does not even possess the supersonic flight ability.This is because when supersonic flight, increases greatly because of drag due to shock wave on the one hand, and 1ift-drag ratio reduces greatly; On the other hand, owing to move behind the supersonic gas oving foci, make aircraft trim resistance increase, 1ift-drag ratio also will reduce.The aircraft flight 1ift-drag ratio sharply reduces makes that keeping the required thrust of flight increases greatly, and fuel oil consumption increases, thus the hyprsonic acceleration capability of the aircraft that deteriorates significantly and hyprsonic duration performance.Even more serious situation is that aircraft supersonic flight resistance is increased to greater than the thrust of starting function to provide, and makes that aircraft can not supersonic flight.
Conventional needle all adopts low aspect ratio wing and less wing area to the high flight of hyprsonic design-calculated aircraft, and the subsonic flight 1ift-drag ratio of this type aircraft is lower, therefore all realizes supersonic flight to sacrifice subsonic performance.
In addition; From the high invisbile plane of present various countries institute design-calculated; Mostly the aerodynamic arrangement's form that adopts is that the wing body of no vertical fin merges lifting body layout (X-45A) or all-wing aircraft layout (B2, X-45C, X-47A, X47B, neuron, raven, ray); These aircrafts are the subsonic flight device, can not supersonic flight.Its major cause is not have the vertical fin layout and when subsonic flight, can combines the ACTIVE CONTROL mode to improve course stability and course control ability through ftracture aileron, drag direction rudder of wing tip; But when hyprsonic; Course stability meeting rapid deterioration; The cracking rudder face also can increase flight resistance greatly, is not suitable for supersonic flight so there is the vertical fin layout.
Summary of the invention
The purpose of the utility model is to propose a kind of subsonic flight and stealthy cruising ability that can make aircraft both possess high lift-drag ratio, possesses the variant canard anury aerodynamic arrangement of higher supersonic flight performance again.The technical solution of the utility model is, the upper surface of fuselage is divided into two zones, and its inside region projects upwards, and exterior lateral area is mild, fuselage upper surface inside region and exterior lateral area corresponding circle of sensation smooth transition; Canard is arranged in forebody, and the root leading edge of canard accounts for 20%～40% of fuselage length apart from the distance of head, has on the fuselage and the corresponding canard groove of canard shape; The canard rotating shaft is arranged on the fuselage of fuselage canard leading edge root, and the canard rotating shaft is vertical with the standard of fuselage face; Wing is arranged in fuselage afterbody; Wing is divided into inner wing and wing tip two parts; The burbling area of inner wing and wing tip places the wing wing root to the arbitrary position between the wingtip, near burbling area on the inner wing, arranges rotating shaft, and rotating shaft is parallel with the interior wingchordpiston and the fuselage plane of symmetry; Inlet channel places the fuselage upper surface anterior, and nozzle places afterbody; Fuselage trailing edge and trailing edge are furnished with primary control surface.
Described canard rotates around the afterbody of canard rotating shaft to fuselage, and rotational angle is adjustable, in the canard groove of income fuselage.
The inner wing of said wing and the burbling area of wing tip expose span place apart from the distance of wing wing root 40%～80%.
The deflection up or down around the shaft of described wing wing tip, deflection angle is adjustable in 0 to ± 90 degree scopes.
Advantage that the utlity model has and beneficial effect; The utility model adopts the pneumatic topological design of variant canard anury; Whole layout left-right symmetric; Through the variant technology that folding wing tip combines with the folding and unfolding canard, efficiently taken into account the subsonic high lift-drag ratio and cruised and the demand of supersonic penetration aerodynamic force, also coordinated to have solved subsonic stealthy cruise and supersonic flight course stability to the contradiction between aerodynamic arrangement's requirement.The utility model can be applicable to aerodynamic arrangement's design of all kinds of unmanned supersonic vehicles.
Description of drawings
Fig. 1 is a variant canard tailless aircraft schematic layout pattern.
Fig. 2 is near the local enlarged diagram canard.
Fig. 3 is near the local enlarged diagram wing wing tip.
Fig. 4 is wing wing tip and canard full expand configuration scheme drawing.
Fig. 5 is for the wing wing tip is turned up, canard stowed configuration scheme drawing.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the utility model is further specified.
The upper surface of fuselage 1 is divided into two zones, and its inside region 2 projects upwards, and exterior lateral area 3 is mild, fuselage 1 upper surface inside region 2 and exterior lateral area 3 corresponding circle of sensation smooth transition; Canard 5 is arranged in fuselage 1 front portion, and the root leading edge of canard 5 accounts for 20%～40% of fuselage length apart from the distance of head, has on the fuselage 1 and the corresponding canard groove 14 of canard shape; Canard rotating shaft 6 is arranged on the fuselage of fuselage canard leading edge root, and canard rotating shaft 6 is vertical with fuselage 1 horizontal surface; Wing 7 is arranged in fuselage 1 rear portion; Wing 7 is divided into inner wing 8 and wing tip 9 two parts; The burbling area of inner wing 8 and wing tip 9 places wing 7 wing roots to the arbitrary position between the wing tip, near wing tip burbling area on the inner wing, arranges rotating shaft 10, and rotating shaft 10 is parallel with the inner wing 8 string planes and fuselage 1 plane of symmetry; Inlet channel 11 places the fuselage upper surface anterior, and nozzle 12 places afterbody; Fuselage trailing edge and trailing edge are furnished with primary control surface 13.
In Fig. 1～3, the whole lower surface of fuselage 1 is milder, is the lifting body fuselage; Fuselage upper surface inside region 2 projects upwards; Fuselage upper surface exterior lateral area 3 is relatively milder; Fuselage upper surface inside region and exterior lateral area are through corresponding circle of sensation 4 smooth transition; Canard 5 is arranged in fuselage 1 front portion, and canard 5 root leading edges account for 20%～40% of fuselage length apart from the distance of head; Canard rotating shaft 6 is arranged on the fuselage near the canard leading edge root, and is vertical with the standard of fuselage face, and canard 5 can be around canard rotating shaft 6 back to rotation to fuselage, and rotational angle is adjustable, in the canard groove 14 on the income fuselage; Wing 7 is arranged in fuselage afterbody; Wing 7 is divided into inner wing 8 and wing tip 9 two parts; On the situation theory of inner wing 8 and wing tip 9 burbling areaes can for the wing wing root to the arbitrary position between the wing tip, expose span place apart from the distance of wing root 40%～80% at this burbling area of selecting inner wing 8 and wing tip 9; Near wing tip burbling area on the inner wing, arrange rotating shaft 10, rotating shaft 10 is parallel with the inner wing 8 string planes and fuselage 1 plane of symmetry, 10 deflections up or down around the shaft of the wing tip 9 of wing 7, and deflection angle is adjustable in 0 to ± 90 degree scopes; Inlet channel 11 places the fuselage upper surface anterior; Nozzle 12 places fuselage upper surface rear portion; Arrange primary control surface 13 at fuselage trailing edge and trailing edge.
When aircraft was done subsonic flight, the wing tip 9 and the canard 5 of wing 7 all launched, and see Fig. 4.This moment, aeroplane span and wing area were all maximum, had the very high 1ift-drag ratio that cruises; Simultaneously, owing to there is not vertical fin, stealth effect is best.
When aircraft was done supersonic flight, the wing tip 9 of wing 7 was turned up and is plumbness, simultaneously, in the canard 5 income fuselages, saw Fig. 5.Wing tip 9 is turned up and has been prevented the retrofocus under the hyprsonic, reduces the trim resistance, improves the flight 1ift-drag ratio; Simultaneously, wing tip 9 is turned up and is become vertical fin, course stability when having significantly improved supersonic flight and driftage control ability.Canard 5 folding and unfoldings can be adjusted the lift before the center of gravity, thereby play the effect of regulating full mechanical coke point, and focus excessively moved forward when the inhibition wing tip was turned up.
Claims (4)
1. a variant canard anury aerodynamic arrangement is characterized in that the upper surface of fuselage (1) is divided into two zones, and its inside region (2) projects upwards, and exterior lateral area (3) is mild, fuselage (1) upper surface inside region (2) and exterior lateral area (3) corresponding circle of sensation smooth transition; Canard (5) is arranged in fuselage (1) front portion, and the root leading edge of canard (5) accounts for 20%～40% of fuselage length apart from the distance of head, has on the fuselage (1) and the corresponding canard groove of canard shape (14); Canard rotating shaft (6) is arranged near the fuselage the fuselage canard leading edge root, and canard rotating shaft (6) is vertical with fuselage (1) horizontal surface; Wing (7) is arranged in fuselage (1) rear portion; Wing (7) is divided into inner wing (8) and wing tip (9) two parts; The burbling area of inner wing (8) and wing tip (9) places wing (7) wing root to the arbitrary position between the wingtip, near burbling area on the inner wing, arranges rotating shaft (10), and rotating shaft (10) is parallel with inner wing (8) the string plane and fuselage (1) plane of symmetry; Inlet channel (11) places the fuselage upper surface anterior, and nozzle (12) places afterbody; Fuselage trailing edge and trailing edge are furnished with primary control surface (13).
2. variant canard anury according to claim 1 aerodynamic arrangement is characterized in that, described canard (5) rotates around the afterbody of canard rotating shaft (6) to fuselage, and rotational angle is adjustable, in the canard groove (14) of income fuselage.
3. variant canard anury according to claim 1 aerodynamic arrangement is characterized in that, the inner wing (8) of said wing (7) and the burbling area of wing tip (9) expose span place apart from the distance of wing wing root 40%～80%.
4. variant canard anury according to claim 1 aerodynamic arrangement is characterized in that described wing wing tip is (10) deflection up or down around the shaft, and deflection angle is adjustable in 0 to ± 90 degree scopes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203304655U CN202279235U (en) | 2011-09-06 | 2011-09-06 | Variant canard tailless aerodynamic configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203304655U CN202279235U (en) | 2011-09-06 | 2011-09-06 | Variant canard tailless aerodynamic configuration |
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| Publication Number | Publication Date |
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| CN202279235U true CN202279235U (en) | 2012-06-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011203304655U Expired - Lifetime CN202279235U (en) | 2011-09-06 | 2011-09-06 | Variant canard tailless aerodynamic configuration |
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| CN103010454A (en) * | 2012-11-27 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Wave rider aircraft with redundant pneumatic distribution and control method thereof |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN104548612A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model airship and aerofoil |
| CN104548611A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model airship wing with movable front end |
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105228901A (en) * | 2013-02-14 | 2016-01-06 | 湾流航空航天公司 | For controlling the system and method for sonic boom amplitude |
| CN106516083A (en) * | 2016-08-01 | 2017-03-22 | 西北农林科技大学 | Winglet rotation device of minitype fixed wing unmanned aerial vehicle |
| CN106864731A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业集团公司成都飞机设计研究所 | A kind of Aircraft at High Angle of Attack pitch control method |
| CN107985626A (en) * | 2017-10-27 | 2018-05-04 | 南京航空航天大学 | A kind of aerodynamic arrangement's design method based on variable configuration re-entry space vehicle |
| CN108516091A (en) * | 2018-04-02 | 2018-09-11 | 南京航空航天大学 | A kind of novel changable aerodynamic arrangement aircraft |
| CN109050918A (en) * | 2018-09-20 | 2018-12-21 | 四川垚磊科技有限公司 | A kind of low speed target drone aerodynamic arrangement |
| CN109153440A (en) * | 2016-07-06 | 2019-01-04 | 空中客车德国运营有限责任公司 | Aircraft with the wing elements for reducing load |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
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| CN112141323A (en) * | 2019-06-28 | 2020-12-29 | 灵翼飞航（天津）科技有限公司 | Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof |
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2011
- 2011-09-06 CN CN2011203304655U patent/CN202279235U/en not_active Expired - Lifetime
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103010454A (en) * | 2012-11-27 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Wave rider aircraft with redundant pneumatic distribution and control method thereof |
| CN105228901A (en) * | 2013-02-14 | 2016-01-06 | 湾流航空航天公司 | For controlling the system and method for sonic boom amplitude |
| CN105228901B (en) * | 2013-02-14 | 2017-04-12 | 湾流航空航天公司 | Systems and methods for controlling a magnitude of a sonic boom |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN103879556B (en) * | 2014-03-31 | 2016-03-02 | 冯加伟 | Wide flight envelope morphing aircraft |
| CN104548611A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model airship wing with movable front end |
| CN104548612B (en) * | 2014-12-24 | 2017-05-24 | 苏州原点工业设计有限公司 | Model airship and aerofoil |
| CN104548612A (en) * | 2014-12-24 | 2015-04-29 | 苏州原点工业设计有限公司 | Model airship and aerofoil |
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
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| CN108516091B (en) * | 2018-04-02 | 2022-01-07 | 南京航空航天大学 | Novel variable aerodynamic layout aircraft |
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| TWI727335B (en) * | 2019-06-05 | 2021-05-11 | 李世平 | An aircraft with stealth double wings |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| CN112141323A (en) * | 2019-06-28 | 2020-12-29 | 灵翼飞航（天津）科技有限公司 | Unmanned aerial vehicle and drive arrangement of fracture formula aileron thereof |
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| CN110589033A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
| CN112173067A (en) * | 2020-09-11 | 2021-01-05 | 北京凌空天行科技有限责任公司 | Space flight vehicle |
| CN112407245A (en) * | 2020-12-14 | 2021-02-26 | 中国科学院工程热物理研究所 | Aircraft |
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| CN115653780A (en) * | 2022-12-13 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | Fluid thrust vectoring nozzle suitable for tailless overall arrangement |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120620 |