CN211252992U - Light flexible wing with variable trailing edge camber - Google Patents
Light flexible wing with variable trailing edge camber Download PDFInfo
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- CN211252992U CN211252992U CN201921736214.XU CN201921736214U CN211252992U CN 211252992 U CN211252992 U CN 211252992U CN 201921736214 U CN201921736214 U CN 201921736214U CN 211252992 U CN211252992 U CN 211252992U
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Abstract
A lightweight flexible variable trailing edge camber wing, comprising: the flexible rear wing comprises a front edge ribbed plate (1), a front wing beam (2), a middle ribbed plate (3), a rear wing beam (4), a flexible rear edge (5), a motor support (6), a linear motor (7), a motor and flexible rear edge connecting rod (8), a flexible rear edge and guide rail connecting plate (9), a sliding block (10), a guide rail (11), a sliding block and flexible rear edge connecting plate (12), a pull ring (13) and a skin; the linear motor (7) is electrified to pull or push the pull ring (13) on the flexible rear edge (5), and under the action of the push-pull force, the pull ring (13) makes linear motion and pulls the upper side and the lower side of the flexible rear edge (5) to make bending deformation. The utility model discloses to the limitation of traditional wing flap and current adaptive wing flap, make whole structure can take place great deformation and have better stability, and have the quality and do not occupy the characteristics in extra wing space gently.
Description
Technical Field
The utility model relates to a flexible variable trailing edge camber wing of light belongs to the aerospace field.
Background
In the flying process of the airplane, because the flying speed is constantly changed, the wings with fixed areas cannot meet the requirements of different lift-drag ratios of the airplane in the takeoff and cruising flight processes, and therefore the flaps are produced at the same time. The trailing edge flap can deflect backwards and downwards around an axis, and is a high lift device which mainly increases the lift by increasing the camber of the wing. The method aims to provide higher lifting coefficient when the airplane takes off and lands, reduce the taking off and landing speed and shorten the running distance.
Flaps were first proposed by george keli and developed continuously over the next hundred years. At present, they are mainly divided into leading-edge flaps and trailing-edge flaps.
Trailing edge flaps are the earliest and most widely used flap family, and the flap structure of the trailing edge flaps is positioned at the trailing edge of a wing and mainly comprises the following components: simple flaps, slotted flaps, fuller flaps, split flaps, and the like. The current flap systems have been developed relatively mature.
However, the conventional flap system has two main disadvantages:
1. the structure and drive of conventional flaps are often achieved by complex mechanical structures. These complex mechanical structures are incompatible with the light weight sought by the aviation industry today. Although there are many flap systems available for improving the lift coefficient, the overall trend of flap development is towards structural complications, such as the later appearance of multi-slot flaps. The complex transmission structure not only increases the fuselage mass and increases the manufacturing and flight costs, but also the complexity of the structure increases the potential failure rate and reduces flight safety.
2. Conventional flaps do not have smooth aerodynamic surfaces. The mission and the design starting point only aim at the requirement of increasing the lift coefficient in the low-speed takeoff and landing process. The increase in aerodynamic lift comes at the expense of an increase in aerodynamic drag and a decrease in aerodynamic efficiency. Conventional flap systems therefore do not function during aircraft cruise and cannot accommodate the requirements of an aircraft to obtain optimum aerodynamic performance in the face of different flight altitudes and flight speeds during cruise.
With the continuous development of the aviation industry, the requirements of people on the overall pneumatic performance, the economy, the comfort and the fuel utilization rate of the airplane are continuously improved. The concept of an adaptive flap is proposed. In 1985, NASA combined with the united states air force initiated a plan for "mission adaptive wings", but the plan was not further developed because the structure was complicated, the linkages were heavy and required large space, and the advantages gained in aerodynamics were offset. The Sridhar Kota professor obtained a patent for a variable camber wing in 1999, in which Kota professor made a monolithic wing frame from a flexible material, but was unable to deform significantly due to the driving force limitations. Hans Peter Monner proposed a rib type variable camber wing based on traditional structure in 2001, the wing body consisted of a piece of movable rib, the structure weight was too big, also had certain limitation.
SUMMERY OF THE UTILITY MODEL
The technical solution problem of the utility model is that: limitation to traditional wing flap and current adaptive wing flap, the utility model provides a flexible variable trailing edge camber wing of light uses flexible construction and linear transmission mechanism's combination, makes overall structure can take place great deformation and have better stability, and has the light characteristics that do not occupy extra wing space of quality.
The utility model adopts the technical proposal that: a lightweight flexible variable trailing edge camber wing, comprising: the flexible rear edge and guide rail connecting plate comprises a front edge rib plate, a front wing beam, a middle rib plate, a rear wing beam, a flexible rear edge, a motor support, a linear motor, a motor and flexible rear edge connecting rod, a flexible rear edge and guide rail connecting plate, a sliding block, a guide rail, a sliding block and flexible rear edge connecting plate, a pull ring and a skin;
the front wing beam is parallel to the rear wing beam, the front edge ribbed plate is connected with the middle ribbed plate through the front wing beam, the middle ribbed plate is connected with the flexible rear edge through the rear wing beam, and the front edge ribbed plate, the middle ribbed plate and the flexible rear edge form a wing airfoil and are arranged along the longitudinal direction of the wing beam to form a wing framework;
the linear motors are respectively arranged at two ends of the wing beam and positioned between the two parallel middle rib plates; the front end of the linear motor is fixed on the front wing beam through a motor support, and the rear end of the linear motor passes through the rear wing beam and is bridged on pull rings of two flexible rear edges through flexible rear edge connecting rods arranged at the end parts; the front end of the guide rail connecting plate is fixed at the front end of the flexible rear edge, and the rear end of the guide rail connecting plate is connected with the guide rail; the guide rail is provided with an opening matched with the sliding block, the sliding block and the flexible rear edge connecting plate are arranged at the lower side deformation part of the flexible rear edge, and the sliding block is arranged on the flexible rear edge connecting plate; the flexible rear edge swings up and down under the pushing of the linear motor; covering the wing framework.
The flexible rear edge is of a wedge-shaped frame structure, the pull ring is connected with the tip of the flexible rear edge through the connecting rod, and the upper side and the lower side of the flexible rear edge can be bent and deformed.
The flexible rear edge and the guide rail connecting plate are square frames with one sides opened, the square frames are positioned in the flexible rear edge, and the rear ends of the lower sides are connected with the guide rails.
The wing airfoil formed by the front edge ribbed plate, the middle ribbed plate and the flexible trailing edge is provided with groups, and the two ends of the wing beam are respectively provided with the groups.
The front end of the flexible trailing edge is mounted on the rear spar by a stiffener.
The linear motor is electrified to pull or push the pull ring on the flexible rear edge, and under the action of the push-pull force, the pull ring makes linear motion and pulls the upper side and the lower side of the flexible rear edge to make bending deformation.
The material of the leading edge rib plate, the middle rib plate, the flexible trailing edge and the skin is 7075 aluminum alloy.
The front wing beam and the rear wing beam are made of 7075 aluminum alloy.
The motor and flexible rear edge connecting rod, the flexible rear edge and guide rail connecting plate, the sliding block, the guide rail, the sliding block and flexible rear edge connecting plate and the pull ring are made of 7075 aluminum alloy.
The push-pull force range of the linear motor is 0-1000N.
Compared with the prior art, the utility model the advantage as follows:
(1) the utility model discloses can promote the aircraft totality, pneumatics and flight performance under various different flight conditions, except lift coefficient and lift-drag ratio when effectively promoting to take off and descend, can promote the adaptation scope between the operating mode of cruising maximum lift-drag ratio and the different lift coefficients by a wide margin.
(2) The utility model discloses the variable trailing edge camber structure that adopts compares in other mechanical type structural style with the drive form to and based on intelligent material's structural style, have structure light in weight, advantages such as realizability is strong.
(3) The utility model discloses compare in traditional fixed shape wing, the utility model provides a flexible variable trailing edge camber wing of light can realize that unmanned aerial vehicle all can obtain good overall aerodynamic performance under different flying height and speed condition through extending the adaptation scope between maximum lift-drag ratio and the lift coefficient by a wide margin. The speed range and the airspace range of the traditional fixed-wing unmanned aerial vehicle are greatly expanded.
(4) The utility model discloses compare in traditional aircraft through increasing the angle of attack or the mode that traditional wing flap improved the coefficient of lift, the utility model discloses a trailing edge camber that deflects in succession when obtaining required coefficient of lift, reduces the coefficient of resistance by a wide margin. The aerodynamic overall performance of the aircraft can be effectively improved, fuel oil in the whole flight process of the aircraft is saved, the flight cost is saved, the voyage range is improved, and the overall performance is improved.
Drawings
FIG. 1 is a schematic view of the flexible trailing edge structure of the present invention;
FIG. 2 is a top view of the wing assembly of the present invention;
FIG. 3 is a schematic view of the wing assembly of the present invention;
FIG. 4 is an enlarged view of the wing assembly of the present invention;
fig. 5 is a schematic diagram of the flexible trailing edge structure of the present invention before and after deformation.
Detailed Description
The present invention will be described with reference to the accompanying drawings.
As shown in fig. 1-5, the utility model provides a flexible variable trailing edge camber wing of light, including leading edge ribbed slab 1, preceding spar 2, middle ribbed slab 3, back spar 4, flexible trailing edge 5, motor support 6, linear electric motor 7, motor and flexible trailing edge connecting rod 8, flexible trailing edge and guide rail connecting plate 9, slider 10, guide rail 11, slider and flexible trailing edge connecting plate 12, pull ring 13, covering;
the front edge ribbed plate 1 and the middle ribbed plate 3 are connected through a front wing beam 2 and fixed together; the middle rib plate 3 and the flexible rear edge 5 are connected through a rear wing beam 4 and fixed together; the front end of a linear motor 7 is fixed on the front wing beam 2 through a motor support 6, and the rear end of the linear motor passes through the rear wing beam 4 and is connected with a pull ring 13 through a flexible rear edge connecting rod 8;
the flexible rear edge 5 is of a wedge-shaped frame structure, the pull ring 13 is connected with the tip end of the flexible rear edge 5 through a connecting rod, and in order to ensure that the variable camber wing is convenient to assemble and maintain, two connecting pieces are designed, namely a flexible rear edge and guide rail connecting plate 9 and a slider and flexible rear edge connecting plate 12; the flexible rear edge and the guide rail connecting plate 9 are independently manufactured so as to avoid the situation that the slider 10 cannot be installed due to the fact that the flexible rear edge and the flexible rear edge 5 are processed into a whole, the flexible rear edge and the guide rail connecting plate 9 are square frames with one open side, the front ends of the flexible rear edge 5 are fixed at the front end of one side, the rear end of one side is connected with the guide rail 11, and the flexible rear edge and the guide rail connecting plate 9 are located in the flexible rear edge 5; an opening is formed in the guide rail 11 to be matched with the sliding block 10, the sliding block and the flexible rear edge connecting plate 12 are convenient to be connected with the skin, the sliding block and the flexible rear edge connecting plate 12 are installed at the lower side deformation part of the flexible rear edge 5, because the thin plate at the lower side deformation part of the flexible rear edge 5 is too thin and is connected with the sliding block 10, after the sliding block and the flexible rear edge connecting plate 12 are used, the sliding block and the flexible rear edge connecting plate 12 are connected with the sliding block 10 through threads, and the sliding block and the flexible rear edge connecting plate 12 are riveted with the skin; the guide rail 11 and the slider 10 are designed for ensuring the linearity of the movement of the lower side of the rear edge and compensating the instability of the motor movement, and play roles in connecting and improving the stability; the two wing spars play a role in fixing and connecting and bear most of the load of the whole wing.
The front end of the flexible rear edge 5 is mounted on the rear wing beam 4 through a reinforcing plate, and the front edge rib plate 1, the front wing beam 2, the middle rib plate 3, the rear wing beam 4, the flexible rear edge 5, the motor support 6, the motor and flexible rear edge connecting rod 8, the flexible rear edge and guide rail connecting plate 9, the sliding block 10, the guide rail 11, the sliding block and flexible rear edge connecting plate 12, the pull ring 13 and the skin are all made of 7075 aluminum alloy.
The push-pull force range of the linear motor 7 is 0-1000N.
The linear motor 7 is electrified, the motion of the motor can be remotely controlled, the pull ring 13 on the flexible rear edge 5 is pulled or pushed, under the action of the push-pull force, the pull ring 13 linearly moves, the upper side and the lower side of the flexible rear edge 5 are dragged to generate bending deformation, and the lower side is restrained by the guide rail 11 and the slide block 10. The deformation of the upper side and the lower side of the structure is in a certain proportion, and the integral bending deformation can be realized (figure 3). In order to determine the relationship between the deformation and the push-pull distance of the linear motor, the relationship between the deformation and the push-pull distance of the linear motor can be obtained through test calibration, namely, the deformation angle of the flexible rear edge 5 is measured and recorded every moving unit distance of the push rod motor 7, and a function relation between the moving distance and the deformation of the pull ring 13 is obtained, so that accurate control is realized, and the deformation angle of the flexible rear edge can be controlled through the motion of the push rod of the motor when the pull ring is used.
The utility model is suitable for a fighter, unmanned aerial vehicle and various civil aviation airliners, when the aircraft takes off, through making the trailing edge camber deflect downwards, increase the air velocity of wing upper surface, reduce the air velocity of lower surface to realize the quick lift-off of aircraft, especially on fighter's application, can make fighter occupy the advantage in the air in time. When the airplane lands, the safety of the airplane landing can be improved in the mode.
The present invention has not been described in detail as is known to those skilled in the art.
Claims (10)
1. A lightweight flexible variable trailing edge camber wing, comprising: the flexible rear wing comprises a front edge ribbed plate (1), a front wing beam (2), a middle ribbed plate (3), a rear wing beam (4), a flexible rear edge (5), a motor support (6), a linear motor (7), a motor and flexible rear edge connecting rod (8), a flexible rear edge and guide rail connecting plate (9), a sliding block (10), a guide rail (11), a sliding block and flexible rear edge connecting plate (12), a pull ring (13) and a skin;
the front wing beam (2) is parallel to the rear wing beam (4), the front edge rib plate (1) is connected with the middle rib plate (3) through the front wing beam (2), the middle rib plate (3) is connected with the flexible rear edge (5) through the rear wing beam (4), and the front edge rib plate (1), the middle rib plate (3) and the flexible rear edge (5) form a wing airfoil shape and are arranged along the longitudinal direction of the wing beams to form a wing framework;
the linear motors (7) are respectively arranged at two ends of the wing beam and positioned between the two parallel middle rib plates (3); the front end of a linear motor (7) is fixed on the front wing beam (2) through a motor support (6), and the rear end of the linear motor passes through the rear wing beam (4) and is bridged on pull rings (13) of two flexible rear edges (5) through flexible rear edge connecting rods (8) arranged at the end parts; the front end of the guide rail connecting plate (9) is fixed at the front end of the flexible rear edge (5), and the rear end is connected with a guide rail (11); an opening is formed in the guide rail (11) and is matched with the sliding block (10), the sliding block and the flexible rear edge connecting plate (12) are arranged at the lower side deformation part of the flexible rear edge (5), and the sliding block (10) is arranged on the flexible rear edge connecting plate (12); the flexible rear edge (5) swings up and down under the pushing of the linear motor (7); covering the wing framework.
2. A lightweight flexible variable trailing edge camber wing according to claim 1, characterized in that the flexible trailing edge (5) is a wedge frame structure, the tab (13) is connected to the tip of the flexible trailing edge (5) via a connecting rod, and the upper and lower sides of the flexible trailing edge (5) can be subjected to bending deformation.
3. A lightweight flexible variable trailing edge camber wing according to claim 1 or 2, characterized in that the flexible trailing edge and the guide rail connection plate (9) are a square frame with an open side, which is located inside the flexible trailing edge (5), and the rear end of the lower side is connected with the guide rail (11).
4. A lightweight flexible variable trailing edge camber wing according to claim 3, wherein the leading edge rib (1), the intermediate rib (3) and the flexible trailing edge (5) form a wing profile having 4 sets, and 2 sets are mounted at each end of the spar.
5. A lightweight flexible variable trailing edge camber wing according to claim 4, characterized in that the leading end of the flexible trailing edge (5) is mounted on the rear spar (4) by means of a stiffening plate.
6. A lightweight flexible variable trailing edge camber wing according to claim 5, characterized in that the linear motor (7) is energized to pull or push the tab (13) on the flexible trailing edge (5), and under the action of the pushing and pulling force, the tab (13) moves linearly and drags the upper and lower sides of the flexible trailing edge (5) to bend and deform.
7. A lightweight flexible variable trailing edge camber airfoil according to claim 1, characterized in that the material of the leading edge rib (1), the intermediate rib (3), the flexible trailing edge (5) and the skin is 7075 aluminium alloy.
8. A lightweight flexible variable trailing edge camber wing according to claim 7, wherein the material of the front and rear spars (2, 4) is 7075 aluminium alloy.
9. A lightweight flexible variable trailing edge camber airfoil according to claim 8, characterized in that the material of the motor and flexible trailing edge connecting rod (8), the flexible trailing edge and guide rail connecting plate (9), the slider (10), the guide rail (11), the slider and flexible trailing edge connecting plate (12), and the pull ring (13) is 7075 aluminum alloy.
10. A lightweight flexible variable trailing edge camber wing according to claim 9, characterized in that the linear motor (7) has a push-pull force in the range of 0 to 1000N.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921736214.XU CN211252992U (en) | 2019-10-16 | 2019-10-16 | Light flexible wing with variable trailing edge camber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921736214.XU CN211252992U (en) | 2019-10-16 | 2019-10-16 | Light flexible wing with variable trailing edge camber |
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| Publication Number | Publication Date |
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| CN211252992U true CN211252992U (en) | 2020-08-14 |
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| CN201921736214.XU Active CN211252992U (en) | 2019-10-16 | 2019-10-16 | Light flexible wing with variable trailing edge camber |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110834714A (en) * | 2019-10-16 | 2020-02-25 | 中国航天空气动力技术研究院 | Light flexible wing with variable trailing edge camber |
| CN112319771A (en) * | 2020-11-05 | 2021-02-05 | 西北工业大学 | Variable trailing edge camber rib based on flexible driver |
| CN113173243A (en) * | 2021-05-10 | 2021-07-27 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
| WO2022104769A1 (en) * | 2020-11-23 | 2022-05-27 | 西湖大学 | Airfoil structure, wing structure and ornithopter |
| GB2605151A (en) * | 2021-03-24 | 2022-09-28 | Airbus Operations Ltd | An aircraft wing trailing edge section assembly |
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2019
- 2019-10-16 CN CN201921736214.XU patent/CN211252992U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110834714A (en) * | 2019-10-16 | 2020-02-25 | 中国航天空气动力技术研究院 | Light flexible wing with variable trailing edge camber |
| CN112319771A (en) * | 2020-11-05 | 2021-02-05 | 西北工业大学 | Variable trailing edge camber rib based on flexible driver |
| CN112319771B (en) * | 2020-11-05 | 2024-04-26 | 西北工业大学 | Flexible driver-based variable trailing edge camber rib |
| WO2022104769A1 (en) * | 2020-11-23 | 2022-05-27 | 西湖大学 | Airfoil structure, wing structure and ornithopter |
| GB2605151A (en) * | 2021-03-24 | 2022-09-28 | Airbus Operations Ltd | An aircraft wing trailing edge section assembly |
| US11878794B2 (en) | 2021-03-24 | 2024-01-23 | Airbus Operations Limited | Aircraft wing trailing edge section assembly |
| CN113173243A (en) * | 2021-05-10 | 2021-07-27 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
| CN113173243B (en) * | 2021-05-10 | 2023-02-28 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
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