CN105235889A - Self-adaptive rhombic wing layout of air vehicles - Google Patents
Self-adaptive rhombic wing layout of air vehicles Download PDFInfo
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- CN105235889A CN105235889A CN201510665447.5A CN201510665447A CN105235889A CN 105235889 A CN105235889 A CN 105235889A CN 201510665447 A CN201510665447 A CN 201510665447A CN 105235889 A CN105235889 A CN 105235889A
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Abstract
The invention provides a self-adaptive rhombic wing layout of air vehicles. According to the self-adaptive rhombic wing layout of the air vehicles, a nose, a tail, four wings, an engine, a task bin, four connecting arms, hinges and control vanes are involved. The four wings are arranged in a rhombic mode from front to back. The four connecting arms can be telescoped and are transversely or longitudinally arranged in a crisscross mode. The nose and the wings are connected through the hinges, the tail and the wings are connected through the hinges, and the engine and the wings are connected through the hinges. The task bin is connected with the nose, the tail and the engine through the telescopic connecting arms and can be changed according to task requirements. The wings are provided with the control vanes used for controlling flight attitudes. The sweepback angle and the sweep-forward angle of the wings can be changed by telescoping the connecting arms so as to obtain rhombic wing layouts adapting to different flight speeds and improve the aerodynamic performance. The self-adaptive rhombic wing layout of the air vehicles has the advantages of being simple and reliable in structure, low in cost and multiple in function.
Description
Technical field
The invention belongs to flight vehicle aerodynamic configuration design technical field, be specifically related to a kind of aircraft self-adaptive rhombic wing layout.
Background technology
No matter at military, civil area, the requirement of economy, oceangoing voyage journey all proposes higher requirement to flight vehicle aerodynamic efficiency.Can take into account low, across the fast territory of, supersonic speed difference flight, possess total arrangement's form of excellent pneumatic efficiency, be the eternal pursuing of goal of Flight Vehicle Design always.High aspect ratio wing has less sweepback angle, have good aeroperformance, but during high-speed flight, wave resistance is larger when low-speed operations; Back sweeping, the wave resistance reducing when aspect ratio can reduce supersonic speed, but its low-speed performance also can be made to decline simultaneously.Becoming sweepback angle is a kind of effective ways taking into account high, low speed aeroperformance, but current change sweepback angle aircraft is generally the change being realized wing planform and sweepback angle on the basis of conventional airplane by the mechanism of complexity, this makes, and structural weight increases, capacity weight reduces, operation and maintenance cost increases; Also have the scheme adopting the advanced material such as memorial alloy to realize becoming sweepback angle, but be limited to the factors such as the deformation range of material and reliability, temporarily also failing to realize sweepback angle in a big way changes, and it does not still have the thinking of aberrant layout.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of aircraft self-adaptive rhombic wing layout.
Aircraft self-adaptive rhombic wing layout of the present invention, is characterized in, described self-adaptive rhombic wing layout comprises head, tail, wing, driving engine, mission module, connecting arm, hinge and control vane.Described wing is provided with wing after two front wings and two, and front and back assume diamond in shape arrangement.Described head is connected respectively by hinge one end with front wing I, front wing II.The other end of front wing I is connected with driving engine I by hinge.The other end of front wing II is connected with driving engine II by hinge.Described tail is connected respectively by hinge one end with rear wing I, rear wing II.The other end of rear wing I is connected with driving engine I by hinge.The other end of rear wing II is connected with driving engine II by hinge.Described connecting arm is provided with four, and four connecting arms, in the arrangement of horizontal, longitudinal right-angled crossing, are connected with mission module respectively, wherein, connecting arm I is fixedly connected with driving engine I, and connecting arm II is fixedly connected with driving engine II, and another two connecting arms are fixedly connected with head, tail respectively.
The variation range at described front wing I, the sweepback angle of front wing II is 10 degree to 70 degree; The variation range of the sweepforward angle of rear wing I (13), rear wing II is 10 degree to 70 degree.
Described wing is provided with the control vane controlled for flight attitude.
Two front wings in the present invention and the angle between the connecting arm of transverse direction are sweepback angle, and sweep range is 10 degree to 70 degree; Angle after two between wing and the connecting arm of transverse direction is sweepforward angle, and sweepforward angle variation range is 10 degree to 70 degree.
Mission module in the present invention is set to modular member, can change according to mission requirements.
Wing in the present invention is furnished with control vane, may be used for the control of flight attitude.
Aircraft self-adaptive rhombic wing layout of the present invention is different from traditional aircraft layout.Aircraft self-adaptive rhombic wing layout of the present invention achieves wing setting by telescopic connecting arm and rotatable hinge and sweepforward angle changes in a big way, obtain the rhombus wing layout adapted from different flying speed, take into account the high, low speed performance of aircraft self-adaptive rhombic wing layout, reach the object reducing flight resistance, improve 1ift-drag ratio, and achieved the multifunctional and multipurpose of aircraft by removable modular mission module.Aircraft self-adaptive rhombic wing layout of the present invention has simple and reliable for structure, that cost is low, purposes is various advantage.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft self-adaptive rhombic wing layout of the present invention in low-speed condition;
Fig. 2 is the structural representation of aircraft self-adaptive rhombic wing layout of the present invention in high-speed flight state;
In figure, 1. rear wing I 14. driving engine II 16. connecting arm II of wing I 4. driving engine I 5. mission module 6. connecting arm I 7. hinge 8. control vane 13. before head 2. tail 3..
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described.
embodiment 1
Fig. 1 is the structural representation of aircraft self-adaptive rhombic wing layout of the present invention in low-speed condition, in Fig. 1, direction shown in arrow is air flow line, aircraft self-adaptive rhombic wing layout of the present invention, comprises head 1, tail 2, wing, driving engine, mission module 5, connecting arm, hinge and control vane.Described wing is provided with wing after two front wings and two, and front and back assume diamond in shape arrangement.Described head 1 is connected respectively by hinge one end with front wing I 3, front wing II.The other end of front wing I 3 is connected with driving engine I 4 by hinge.The other end of front wing II is connected with driving engine II 14 by hinge.Described tail 2 is connected respectively by hinge one end with rear wing I 13, rear wing II.The other end of rear wing I 13 is connected with driving engine I 4 by hinge.The other end of rear wing II is connected with driving engine II 14 by hinge.Described connecting arm is provided with four, four connecting arms are in the arrangement of horizontal, longitudinal right-angled crossing, be connected with mission module 5 respectively, wherein, connecting arm I 6 is fixedly connected with driving engine I 4, connecting arm II 16 is fixedly connected with driving engine II 14, and another two connecting arms are fixedly connected with head 1, tail 2 respectively.
Described front wing I 3, the sweepback angle of front wing II are 10 degree.The sweepforward angle of rear wing I 13, rear wing II is 10 degree.Four described wings are provided with the control vane controlled for flight attitude.
In the present embodiment, connecting arm is provided with four, and connecting arm I 6 is one of them; Wing is provided with two front wings, wing after two, and front wing I 3 is one of them, and rear wing I 13 is one of them; Hinge is provided with four, and hinge 7 is one of them; Control vane is provided with 12, and control vane 8 is one of them.
embodiment 2
The present embodiment is identical with the structure of embodiment 1, Fig. 2 is the structural representation of the high-speed flight state of aircraft self-adaptive rhombic wing layout of the present invention, direction shown in arrow in Fig. 2 is air flow line, extend when longitudinally former and later two connecting arms compare low-speed condition, shorten when laterally left and right two connecting arms compare low-speed condition, thus the sweepforward angle of wing is all increased to 70 degree after making the sweepback angle of two front wings and two, be conducive to reducing the wave resistance of aircraft self-adaptive rhombic wing layout of the present invention when supersonic speed, improve aeroperformance.
embodiment 3
The present embodiment is identical with the structure of embodiment 1,2, and difference is, after the sweepback angle of two front wings and two, the sweepforward angle of wing is 30 degree.
Claims (3)
1. an aircraft self-adaptive rhombic wing layout, is characterized in that: described self-adaptive rhombic wing layout comprises head (1), tail (2), wing, driving engine, mission module (5), connecting arm, hinge and control vane; Described wing is provided with wing after two front wings and two, and front and back assume diamond in shape arrangement; Described head (1) is connected respectively by hinge one end with front wing I (3), front wing II; The other end of front wing I (3) is connected with driving engine I (4) by hinge; The other end of front wing II is connected with driving engine II (14) by hinge; Described tail (2) is connected respectively by hinge one end with rear wing I (13), rear wing II; The other end of rear wing I (13) is connected with driving engine I (4) by hinge; The other end of rear wing II is connected with driving engine II (14) by hinge; Described connecting arm is provided with four, four connecting arms are in the arrangement of horizontal, longitudinal right-angled crossing, be connected with mission module (5) respectively, wherein, connecting arm I (6) is fixedly connected with driving engine I (4), connecting arm II (16) is fixedly connected with driving engine II (14), and another two connecting arms are fixedly connected with head (1), tail (2) respectively.
2. aircraft self-adaptive rhombic wing layout according to claim 1, is characterized in that, the variation range at described front wing I (3), the sweepback angle of front wing II is 10 degree to 70 degree; The variation range of the sweepforward angle of rear wing I (13), rear wing II is 10 degree to 70 degree.
3. aircraft self-adaptive rhombic wing layout according to claim 1, is characterized in that, described wing is provided with the control vane controlled for flight attitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510665447.5A CN105235889B (en) | 2015-10-16 | 2015-10-16 | Self-adaptive rhombic wing layout of air vehicles |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510665447.5A CN105235889B (en) | 2015-10-16 | 2015-10-16 | Self-adaptive rhombic wing layout of air vehicles |
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| CN105235889A true CN105235889A (en) | 2016-01-13 |
| CN105235889B CN105235889B (en) | 2017-04-12 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN109703746A (en) * | 2019-01-09 | 2019-05-03 | 西北工业大学 | A kind of boxlike has hung down Fixed Wing AirVehicle |
| CN112638770A (en) * | 2018-08-31 | 2021-04-09 | Wing航空有限责任公司 | Safe unmanned aerial vehicle |
| CN113148141A (en) * | 2021-04-14 | 2021-07-23 | 中国空气动力研究与发展中心空天技术研究所 | Novel intelligence variant aircraft |
| CN115367097A (en) * | 2022-10-24 | 2022-11-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Novel large-scale variant aircraft |
| CN116395124A (en) * | 2023-06-07 | 2023-07-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wing surface deformation mechanism based on shape memory alloy wire drive |
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| CN203283375U (en) * | 2013-04-16 | 2013-11-13 | 赵嘉珩 | Aircraft wing layout structure |
| CN103552682A (en) * | 2013-10-30 | 2014-02-05 | 北京航空航天大学 | Airplane with combined-wing layout of flying wing and forward-swept wings |
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| CN104443344A (en) * | 2014-11-13 | 2015-03-25 | 南京航空航天大学 | Passenger plane with joined-wing configuration |
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| CN101028866A (en) * | 2007-03-30 | 2007-09-05 | 哈尔滨工业大学 | Aircraft with wing sweepback angle change |
| US20120325957A1 (en) * | 2009-12-22 | 2012-12-27 | Astrium Sas | Ultra-rapid air vehicle and related method for aerial locomotion |
| CN102530238A (en) * | 2012-02-23 | 2012-07-04 | 北京理工大学 | Unmanned aerial vehicle with variable sweepbacks and spans of wings |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN112638770A (en) * | 2018-08-31 | 2021-04-09 | Wing航空有限责任公司 | Safe unmanned aerial vehicle |
| CN112638770B (en) * | 2018-08-31 | 2022-05-17 | Wing航空有限责任公司 | Safe unmanned aerial vehicle |
| CN109703746A (en) * | 2019-01-09 | 2019-05-03 | 西北工业大学 | A kind of boxlike has hung down Fixed Wing AirVehicle |
| CN113148141A (en) * | 2021-04-14 | 2021-07-23 | 中国空气动力研究与发展中心空天技术研究所 | Novel intelligence variant aircraft |
| CN115367097A (en) * | 2022-10-24 | 2022-11-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Novel large-scale variant aircraft |
| CN116395124A (en) * | 2023-06-07 | 2023-07-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wing surface deformation mechanism based on shape memory alloy wire drive |
| CN116395124B (en) * | 2023-06-07 | 2023-08-11 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wing surface deformation mechanism based on shape memory alloy wire drive |
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| CN105235889B (en) | 2017-04-12 |
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