CN111409816B - Variable camber wing leading edge structure - Google Patents
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- CN111409816B CN111409816B CN202010323678.9A CN202010323678A CN111409816B CN 111409816 B CN111409816 B CN 111409816B CN 202010323678 A CN202010323678 A CN 202010323678A CN 111409816 B CN111409816 B CN 111409816B
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- 239000011152 fibreglass Substances 0.000 claims 1
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
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Abstract
The application belongs to aircraft wing leading edge structure flap, slat design field, in particular to become camber wing leading edge structure, includes: a wing front spar; the flexible skin is fixed to the top and the top of the front beam of the wing; the fixed support is fixed on one side of the front beam of the wing and is provided with a through hole; the driving shaft is movably arranged in the through hole; the driving inclined rod is hinged on the shaft body of the driving shaft; one end of the main driving lever extends into the inner cavity of the wing, and the other end of the main driving lever is hinged with the fixed support and is hinged with the driving inclined rod in a universal mode; the flexible skin is fixedly arranged on the inner side surface of the flexible skin at intervals, one end of the connecting rod is hinged with the main driving lever, and the other end of the connecting rod is hinged with the reinforcing stringers; and the driving device is used for providing power for the driving shaft. The variable camber wing leading edge structure can simultaneously meet the functions of accurate deformation and high pneumatic bearing, can reduce landing and approach noise generated by gaps, and effectively improves the comprehensive performance of civil aircrafts.
Description
Technical Field
The application belongs to the field of design of flaps and slats of wing leading edge structures of aircrafts, and particularly relates to a variable camber wing leading edge structure.
Background
A "variable camber leading edge" is a deformable aircraft structure based on conventional leading edge flaps and slats, with seamless continuous smooth deformable aerodynamic surfaces. The traditional wing design can only ensure the optimal aerodynamic efficiency under the cruising state. In order to meet the aerodynamic requirements under other working conditions, the traditional wing realizes the change and adjustment of the aerodynamic profile through a leading edge and a trailing edge high lift device based on rigid hinges.
However, the conventional leading edge high lift device based on the rigid hinge has various problems: 1. rigid hinge based leading edge high lift devices result in a gap between the leading edge structure and the main wing box structure making the aerodynamic surface discontinuous. The sharp parts of the structures between the gaps are easy to generate friction with air, and the noise of takeoff and approach landing is greatly increased. 2. Under the cruising condition, the traditional front edge device is in a retraction state, but the discontinuous pneumatic surface still cannot meet the laminar flow flight requirement of the laminar flow large civil aircraft, so that pneumatic separation is easily caused, and the flight efficiency is reduced. 3. The high-lift device based on the rigid hinge can only carry out the pneumatic appearance adjustment of 2-3 discrete working conditions, cannot realize the real-time accurate deformation control of the pneumatic appearance of the full-flight envelope curve, and cannot meet the purpose of the real-time optimization of the pneumatic appearance.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a leading edge structure of a variable camber airfoil.
The application discloses variable camber wing leading edge structure includes:
the middle position of the wing front beam is provided with an opening in a penetrating way;
the flexible skin is bent to be in the shape of an airfoil, and the end parts of the two ends of the flexible skin are respectively fixed to the top of the front beam of the airfoil and the top of the front beam of the airfoil so as to form an airfoil inner cavity;
the fixed support is fixedly arranged on one side surface of the wing front beam, which is back to the flexible skin, and a through hole is formed in the fixed support in a penetrating manner along the span direction of the aircraft wing;
the driving shaft is arranged in the through hole of the fixed support, can controllably move in the through hole along the span direction of the aircraft wing, and can rotate around the axis of the driving shaft in the through hole;
one end of the driving inclined rod is hinged to the shaft body of the driving shaft, and the projection of the driving inclined rod on the driving shaft is parallel to or coincident with the axis of the driving shaft;
one end of the main driving lever extends into the inner cavity of the wing from the opening of the front wing beam, the other end of the main driving lever is hinged to the fixed support at a first hinge point, the rotation axis of the main driving lever is parallel to the unfolding direction of the wing, and in addition, the end part of the other end of the main driving lever is hinged to the end part of the other end of the driving inclined rod in a universal mode;
a plurality of stiffening stringers located within the wing cavity and fixedly disposed at intervals on an inner side of the flexible skin;
the number of the connecting rods is the same as that of the reinforcing stringers, one end of each connecting rod is hinged to the rod body of the main driving lever, a hinged point is located on the rod body of the main driving lever extending from the first hinged point to the inner cavity of the wing, and the other end of each connecting rod is hinged to the corresponding reinforcing stringer;
the driving device is arranged outside the wing inner cavity and used for driving the driving shaft to move along the wing span direction so as to drive the main driving lever to rotate around a first hinge point of the main driving lever through the driving inclined rod; wherein
The plurality of reinforcing stringers and the corresponding plurality of connecting rods are configured such that, in the rotation process of the main driving lever, the plurality of connecting rods respectively control the reinforcing stringers to drive the flexible skin at the corresponding position to perform global sagging deformation, thereby realizing deformation of the whole wing.
According to at least one embodiment of the present application, the opening formed in the front spar of the wing is rectangular.
According to at least one embodiment of the present application, the flexible skin is made of a variable stiffness composite material.
According to at least one embodiment of the present application, the variable stiffness composite is a glass fiber reinforced composite or a hybrid type composite.
According to at least one embodiment of the present application, the stiffening stringers and the flexible skin are integrally bonded together using a composite material.
According to at least one embodiment of this application, fixing support's cross-section is L shape, including mutually perpendicular's bottom plate and vertical board, the bottom plate with the wing front-axle beam is fixed, wherein, first hinge point and through-hole all set up on its vertical board.
According to at least one embodiment of this application, the drive shaft body of rod is gone up and is run through the drive hole of seting up the bar along the axis direction, the drive down tube passes through the round pin axle and articulates in the drive hole, just the drive down tube is in drive epaxial projection with the axis coincidence of drive shaft.
According to at least one embodiment of the present application, the number of stiffening stringers is 4, wherein a first stiffening stringer is located at the top of the wing cavity, a second stiffening stringer is located at the tip of the wing, and a third stiffening stringer and a fourth stiffening stringer are located at the bottom of the wing cavity and sequentially arranged from the second stiffening stringer toward the wing front spar;
the number of the connecting rods is 4, and the extending directions from the first hinge point to the inner cavity of the wing are a first connecting rod, a fourth connecting rod, a third connecting rod and a second connecting rod in sequence, wherein,
one end of the first connecting rod is hinged with the main driving lever, and the other end of the first connecting rod is hinged with the first reinforcing stringer; one end of the fourth connecting rod is hinged with the main driving lever, and the other end of the fourth connecting rod is hinged with the fourth reinforcing stringer; one end of the third connecting rod is hinged with the main driving lever, and the other end of the third connecting rod is hinged with the third reinforcing stringer; one end of the second connecting rod is hinged to the main driving lever, and the other end of the second connecting rod is hinged to the second reinforcing stringer.
According to at least one embodiment of the application, the drive means is a linear motor.
The application has at least the following beneficial technical effects:
the variable camber wing leading edge structure can simultaneously meet the functions of accurate deformation and high aerodynamic bearing; in addition, the method can realize seamless, smooth and continuous shape change of the continuous front edge aerodynamic shape, can realize real-time optimization of wing airfoil profile, reduces landing and approach noise generated by gaps, and can effectively improve the comprehensive performance of the civil aircraft; furthermore, the driving scheme that linear displacement of the driving shaft is converted into rotary displacement of the main driving lever is adopted, the required driving force can be effectively reduced, and the situation that a single driving bearing drives the three-dimensional wing to drive a plurality of driving ribs in the unfolding direction is facilitated, so that the complexity of the variable camber wing leading edge mechanism is reduced, and the weight is reduced.
Drawings
FIG. 1 is a schematic view of a leading edge structure of a variable camber airfoil according to the present application from one perspective;
FIG. 2 is a schematic structural view of another view of the variable camber airfoil leading edge structure of the present application (flexible skin not shown);
FIG. 3 is a flow chart of an optimized design of a leading edge structure of a camber airfoil according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be understood that the terms "center," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like in the description of the present application may be used in a generic and descriptive sense only and not for purposes of limitation, as indicating or implying that a particular device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the scope of the present application.
The leading edge structure of the variable camber airfoil of the present application is described in further detail below with reference to fig. 1 and 3.
The application discloses variable camber wing leading edge structure can include parts such as wing front beam 14, flexible skin 6, fixing support 3, drive shaft 1, drive down tube 2, main drive lever 11, reinforcement stringer, connecting rod and drive arrangement.
Specifically, the wing front spar 14 can be set into various suitable structural shapes according to the appearance of the wing and the matching requirement of the wing front spar and the flexible skin 6, and an opening is formed in the middle of the wing front spar; in this embodiment, the front spar 14 is preferably approximately C-shaped in cross-section, having a center panel and upper and lower flanges (or upper and lower side panels) disposed vertically at opposite ends of the center panel. Wherein the opening is opened on the middle plate, and the shape of the opening can be needed to be set in various shapes, such as rectangle, strip, ellipse, etc., in one embodiment of the present application, the opening is preferably rectangular.
The flexible skin 6 is bent into the shape of an airfoil, and both ends thereof are respectively fixed (e.g., riveted) to the top and the top of the front spar 14 (i.e., the upper and lower edge strips) of the airfoil to form an airfoil cavity. Similarly, the flexible skin 6 may be selected as a plurality of suitable materials according to needs, in an embodiment of the present application, it is preferable that the flexible skin 6 is made of a variable stiffness composite material, and at this time, the variable stiffness of the flexible skin 6 is realized by the variation of the ply thickness (which may also include the ply angle); further, the variable stiffness composite material may preferably be a glass fiber reinforced composite material or a hybrid composite material.
The fixed support 3 is fixedly arranged on one side surface of the wing front beam 14, which is back to the flexible skin 6, and a through hole is formed in the fixed support 3 in a penetrating manner along the span-wise direction. Similarly, the fixing support 3 may have any suitable shape, and in this embodiment, the fixing support 3 preferably has an L-shaped cross section and includes a bottom plate and a vertical plate perpendicular to each other, the bottom plate and the wing front beam 14 are fixed by bolts or rivets, wherein the first hinge point 31 and the through hole are both opened on the vertical plate.
The drive shaft 1 is arranged in the through hole of the fixed support 3, can move along the span direction of the machine wing in the through hole in a controlled manner (namely driven by a corresponding driving device), and can rotate around the axis of the drive shaft in the through hole.
One end of the driving diagonal rod 2 is hinged on the shaft body of the driving shaft 1, and the projection of the driving diagonal rod 2 on the driving shaft 1 is parallel to or coincided with the axis of the driving shaft 1. Similarly, the driving diagonal rod 2 and the driving shaft 1 can have a plurality of combination modes, in this embodiment, preferably, a strip-shaped driving hole is formed on the rod body of the driving shaft 1 along the axis direction, one end of the driving diagonal rod 2 extends into the driving hole, and is hinged in the driving hole through a pin shaft, and the forming position of the driving hole ensures that the projection of the driving diagonal rod 2 on the driving shaft 1 coincides with the axis of the driving shaft 1.
One end (left end in fig. 1) of the main driving lever 11 extends into the inner cavity of the wing from the opening of the wing front beam 14, and the other end (right end in fig. 1) of the main driving lever 11 is hinged with the fixed support 3 at a first hinge point 31, in addition, the rotation axis of the main driving lever 11 rotating around the first hinge point 31 is parallel to the span direction of the wing, and further, the other end (right end in fig. 1) of the main driving lever 11 is in universal hinge joint with the other end (top end in fig. 1) of the driving inclined rod 2.
Furthermore, the number of the reinforcing stringers and the connecting rods is the same, and the reinforcing stringers and the connecting rods can be arranged into a plurality of reinforcing stringers according to requirements; the plurality of reinforcing stringers are positioned in the inner cavity of the wing and fixedly arranged on the inner side surface of the flexible skin 6 at intervals; it should be noted that the stiffening stringers and the flexible skin 6 may be fixed in a variety of suitable manners, and in this embodiment, when the flexible skin 6 is made of the above-mentioned variable stiffness composite material, it is preferable that the stiffening stringers and the flexible skin 6 are integrally bonded and formed by using the composite material.
Further, one end of each connecting rod is hinged to the rod body of the main driving lever 11, and the hinge point is located on the rod body of the main driving lever 11 extending from the first hinge point 31 to the inner cavity of the wing (i.e. in the direction extending from the first hinge point 31 to the left in fig. 1), and the other end of each connecting rod is hinged to the corresponding stiffening stringer.
It should be noted that the specific number of the stiffening stringers and the tie bars may be selected according to the control requirement and the corresponding optimization design result, and in this embodiment, the number of the stiffening stringers and the tie bars is preferably 4.
Specifically, of the 4 stiffening stringers, a first stiffening stringer 5 is located at the top of the wing cavity, a second stiffening stringer 7 is located at the tip of the wing, and a third stiffening stringer 10 and a fourth stiffening stringer 12 are located at the bottom of the wing cavity and sequentially arranged from the second stiffening stringer 7 to the front wing girder 14 (i.e., from left to right in fig. 1); correspondingly, the extending direction from the first hinge point 31 to the inner cavity of the wing (i.e. from right to left in fig. 1) of the 4 connecting rods are the first connecting rod 4, the fourth connecting rod 13, the third connecting rod 9 and the second connecting rod 8 in sequence.
Wherein, one end of the first connecting rod 4 is hinged with the main driving lever 11, and the other end is hinged with the first strengthening stringer 5; one end of a fourth connecting rod 13 is hinged with the main driving lever 11, and the other end is hinged with a fourth reinforcing stringer 12; one end of a third connecting rod 9 is hinged with a main driving lever 11, and the other end is hinged with a third reinforcing stringer 10; one end of the second connecting rod 8 is hinged to the main driving lever 11 and the other end is hinged to the second stiffening stringer 7.
Further, the driving device is arranged outside the inner cavity of the wing and used for driving the driving shaft 1 to move along the span direction of the wing so as to drive the main driving lever 11 to rotate around the first hinge point 31 of the main driving lever by driving the inclined rod 2; the arrangement positions and the connection positions of the plurality of reinforcing stringers and the corresponding plurality of connecting rods are configured, in the rotation process of the main driving lever 11, the plurality of connecting rods respectively control the reinforcing stringers to drive the flexible skin 6 at the corresponding positions to carry out global drooping deformation, and therefore deformation of the whole wing is achieved. Likewise, the drive mechanism may be of any suitable drive configuration, and in this embodiment, the drive mechanism is preferably a linear motor.
The front edge structure of the variable camber wing of the application utilizes a driving device (a linear motor) as a driver of the whole front edge structure of the variable camber wing, can drive a driving shaft 1 to generate displacement along a spanwise direction (see the spanwise direction in fig. 1), and allows the driving shaft 1 to rotate around an axis; the driving shaft 1 pushes the driving oblique rod 2 to move in the process of moving in the unfolding direction, and finally the main driving lever 11 rotates around the first hinge point 31; further, the rotation of the main actuation lever 11 forces all the connecting rods connected to the main actuation lever 11 to move and eventually produces a global sagging deformation of the skin, thus varying the wing camber.
In addition, in order to accurately match the appearance of the deflected skin with the target appearance required by aerodynamics, firstly, the rigidity distribution of the skin along the circumferential direction and the position distribution of the stiffening stringer along the circumferential direction of the skin need to be subjected to collaborative optimization design, and secondly, the position of a hinge point for connecting an internal connecting rod with a main driving lever needs to be optimized; specifically, as shown in fig. 3, the following optimization design steps may be included:
1) The aerodynamic performance requirements of wings of the airplane under the flying conditions of cruising, taking-off, landing and the like are given according to the overall requirements of the airplane;
2) According to the aerodynamic performance requirement of the wing, giving the optimal initial shape and target shape of the wing leading edge through aerodynamic optimization design;
3) Taking the target appearance as the target of optimization design, and performing collaborative optimization design on design variables such as the position of the variable-stiffness skin stringer, the skin stiffness distribution (the number of layers and the layer angle), the magnitude and the direction of the transmission force of a stringer connecting point and the like;
4) Taking the integrated skin obtained by the optimization in the step 3 as input, taking the motion track of the connecting hinge point of the reinforcing stringer and the flexible skin as an optimization target, and performing topology optimization design on an internal driving mechanism so as to determine the connecting hinge point position of the connecting rod and the main driving rod, the fixed point position of the main driving rod and the fixed support and the rotation angle of the main driving rod;
5) Taking the initial design results obtained in the step 3 and the step 4 as input, carrying out detailed design on the leading edge of the variable camber wing, and carrying out design and check on a drive bearing and the like;
6) Designing a test bench and testing the leading edge structure of the variable camber wing to determine whether the deformation meets the target appearance requirement.
After the cooperative optimization design of the structure is adopted, the front edge structure can accurately realize the target appearance under the displacement drive of the linear motor. An outer flexible skin is used to maintain an accurate target profile, and mechanisms such as an inner connecting rod and a main driving lever are used to transmit an external pneumatic load while transmitting a driving force of a linear motor. Under the three-dimensional condition of the actual wing, a single driving bearing can be connected with a plurality of driving ribs, so that synchronous driving is realized.
To sum up, the variable camber wing leading edge structure of this application compares with current variable camber wing leading edge device, can satisfy accurate deformation and high aerodynamic bearing's function simultaneously. Firstly, the method can realize seamless, smooth and continuous shape change of the continuous front edge aerodynamic shape, can realize real-time optimization of wing airfoil, reduces landing and approach noise generated by gaps, and can effectively improve the comprehensive performance of the civil aircraft. Secondly, the application provides a scheme of adopting a variable-rigidity composite material (such as a glass fiber reinforced composite material or a hybrid composite material) seamless smooth flexible skin, and the scheme of the skin can meet the requirement of bearing high aerodynamic load and can realize accurate target appearance through the optimal design of rigidity cutting. Finally, the driving scheme that linear displacement of the driving bearing is converted into rotary displacement of the main driving lever is adopted, the required driving force can be effectively reduced, and meanwhile the situation that a single driving bearing drives the three-dimensional wing to drive a plurality of driving ribs in the unfolding direction is facilitated, so that the complexity of a variable-camber wing leading edge mechanism is reduced, and the weight is reduced.
Finally, the invention provides a variable-camber leading edge structure scheme based on variable-stiffness flexible skins and an internal link mechanism, and the comprehensive optimization design of the structure is carried out with the aim of realizing the accurate pneumatic appearance of the leading edge skin structure.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A variable camber airfoil leading edge structure, comprising:
the middle position of the wing front beam (14) is provided with an opening in a penetrating way;
the flexible skin (6) is bent to be in the shape of an airfoil, and the end parts of the two ends of the flexible skin (6) are respectively fixed to the top of the front wing beam (14) and the top of the front wing beam to form an airfoil inner cavity;
the fixed support (3) is fixedly arranged on one side surface, back to the flexible skin (6), of the wing front beam (14), and a through hole penetrates through the fixed support (3) along the span-wise direction;
the driving shaft (1) is arranged in a through hole of the fixed support (3), can be controlled to move along the span direction of the machine wing in the through hole and can rotate around the axis of the driving shaft in the through hole;
one end of the driving inclined rod (2) is hinged to the shaft body of the driving shaft (1), and the projection of the driving inclined rod (2) on the driving shaft (1) is parallel to or coincident with the axis of the driving shaft (1);
one end of the main driving lever (11) extends into the inner cavity of the wing from the opening of the front wing beam (14), the other end of the main driving lever (11) is hinged to the first hinge point (31) with the fixed support (3), the rotation axis of the main driving lever (11) is parallel to the span direction of the wing, and in addition, the other end of the main driving lever (11) is hinged to the other end of the driving inclined rod (2) in a universal mode;
a plurality of stiffening stringers located within the wing cavity and fixedly arranged at intervals on the inner side of the flexible skin (6);
the number of the connecting rods is the same as that of the reinforcing stringers, one end of each connecting rod is hinged with the rod body of the main driving lever (11), a hinged point is located on the rod body of the main driving lever (11) extending from the first hinged point (31) to the inner cavity of the wing, and the other end of each connecting rod is hinged with the corresponding reinforcing stringer;
the driving device is arranged outside the inner cavity of the wing and used for driving the driving shaft (1) to move along the span direction of the wing so as to drive the main driving lever (11) to rotate around a first hinge point (31) of the main driving lever through the driving inclined rod (2); wherein
The plurality of the stiffening stringers and the corresponding plurality of the connecting rods are configured to respectively control the stiffening stringers to drive the flexible skin (6) at the corresponding position to carry out global drooping deformation through the plurality of the connecting rods in the rotating process of the main driving lever (11), thereby realizing the deformation of the whole wing.
2. The leading edge structure of a variable camber airfoil according to claim 1, characterized in that the opening formed in the front spar (14) is rectangular.
3. A variable camber airfoil leading edge structure according to claim 1, wherein the flexible skin (6) is made of a variable stiffness composite material.
4. The camber airfoil leading edge structure of claim 3, wherein the variable stiffness composite is a fiberglass reinforced composite or a hybrid composite.
5. The variable camber airfoil leading edge structure of claim 3, wherein the stiffening stringers and the flexible skin (6) are integrally bonded together using a composite material.
6. The variable camber airfoil leading edge structure according to claim 1, wherein the fixed support (3) is L-shaped in cross section and comprises a bottom plate and a vertical plate which are perpendicular to each other, the bottom plate is fixed with the airfoil front beam (14), and the first hinge point (31) and a through hole are formed in the vertical plate.
7. The leading edge structure of the variable camber wing according to claim 1, wherein a strip-shaped driving hole is formed in a body of the driving shaft (1) in a penetrating manner along an axial direction, the driving diagonal rod (2) is hinged in the driving hole through a pin shaft, and a projection of the driving diagonal rod (2) on the driving shaft (1) coincides with the axial line of the driving shaft (1).
8. The variable camber airfoil leading edge structure of claim 1, wherein the number of the stiffening stringers is 4, wherein a first stiffening stringer (5) is located at the top of the airfoil cavity, a second stiffening stringer (7) is located at the tip of the airfoil, and a third stiffening stringer (10) and a fourth stiffening stringer (12) are located at the bottom of the airfoil cavity and are arranged in sequence from the second stiffening stringer (7) to the airfoil front spar (14);
the number of the connecting rods is 4, the extending directions of the connecting rods from the first hinge point (31) to the inner cavity of the wing are sequentially a first connecting rod (4), a fourth connecting rod (13), a third connecting rod (9) and a second connecting rod (8), wherein,
one end of the first connecting rod (4) is hinged with the main driving lever (11), and the other end of the first connecting rod is hinged with the first reinforcing stringer (5); one end of the fourth connecting rod (13) is hinged with the main driving lever (11), and the other end of the fourth connecting rod is hinged with the fourth reinforcing stringer (12); one end of the third connecting rod (9) is hinged with the main driving lever (11), and the other end of the third connecting rod is hinged with the third reinforcing stringer (10); one end of the second connecting rod (8) is hinged with the main driving lever (11), and the other end of the second connecting rod is hinged with the second reinforcing stringer (7).
9. The leading edge structure of a variable camber airfoil of claim 1, wherein the drive device is a linear motor.
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| CN202010323678.9A CN111409816B (en) | 2020-04-22 | 2020-04-22 | Variable camber wing leading edge structure |
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| CN202010323678.9A CN111409816B (en) | 2020-04-22 | 2020-04-22 | Variable camber wing leading edge structure |
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| CN113120220B (en) * | 2021-03-31 | 2023-11-28 | 中国飞机强度研究所 | Three-dimensional single-shaft driving system for rigid-flexible coupling variable camber wing front edge |
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| CN113551891B (en) * | 2021-06-17 | 2022-04-26 | 北京航空航天大学 | Design and loading method of a flexible skin test platform with variable camber |
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