CN111008433B - Method for determining rigidity of flexible airfoil surface suitable for distributed parabolic crankshaft drive - Google Patents
Method for determining rigidity of flexible airfoil surface suitable for distributed parabolic crankshaft drive Download PDFInfo
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Abstract
The application provides a method for determining the rigidity of a flexible airfoil surface suitable for distributed parabolic crankshaft driving, which comprises the following steps: setting preset conditions and giving a known quantity; obtaining a movable trailing edge central line parabola analytic expression according to a movable trailing edge central line parabola equation; calculating the average driving force of a single shaft according to the parabola analytic expression of the central line of the movable trailing edge; substituting the bending moment equation into a deflection line approximate differential equation, obtaining a corner equation after integration, and obtaining a corner formula by the corner equation; determining unknown quantity in the corner formula, and substituting the unknown quantity into the corner formula to obtain the elastic modulus of the flexible skin; and determining the rigidity of the flexible airfoil according to the elastic modulus. The method for determining the rigidity of the flexible airfoil driven by the distributed parabolic crankshaft provided by the embodiment of the application has the advantages of high efficiency, concise process and small error range.
Description
Technical Field
The application relates to the technical field of airplanes, and particularly provides a method for determining rigidity of a flexible airfoil suitable for distributed parabolic crankshaft driving.
Background
The geometry of a conventional fixed wing is designed according to the specific flight mission, flight altitude, flight conditions of the aircraft, which is usually optimized for only one design point and traded off for the other design points. In a complete flight process, flight parameters corresponding to different flight phases are continuously changed, and the geometric shape of the fixed wing cannot be optimized under most conditions. If the aerodynamic shape of the wing can be changed along with the change of the external flying environment, the aircraft always keeps the optimal aerodynamic characteristic in the whole flying process, and the applicability and the utilization rate of the aircraft can be greatly improved. The morphing aircraft can change the geometrical parameters of the wings, thereby solving the problems of the traditional fixed wing aircraft, ensuring that the aircraft keeps the optimal aerodynamic characteristics all the time in the whole voyage and leading the aircraft to execute various flight tasks.
For aircraft, wings are the main sources of lift and handling forces, and are the primary subject of aircraft design. The performance of the wings directly affects the flight performance of the airplane. Therefore, much of the research on new flexible morphing aircraft has focused on the research on morphing wings of the aircraft. The deformable wing needs to deform in the flight process without the support of two key technologies, namely a deformable flexible skin and a deformation driving mechanism. The deformable flexible skin is mainly used for bearing and transferring aerodynamic load during deformation, so that the surface of the wing is smooth, and the wing has good air tightness. The deformation driving mechanism needs to provide enough deformation power when the deformation wing deforms, and directly influences the wing configuration and the aerodynamic shape, so that the efficiency and the performance of the airplane are influenced.
Meanwhile, the rigidity of the deformable flexible skin must be matched with the driving force of the deformation driving mechanism. After the driving mechanism is determined, when the rigidity of the flexible skin is too high, the driving mechanism cannot drive the trailing edge of the wing; when the flexible skin is too low in rigidity, the flexible skin cannot bear aerodynamic load. Therefore, in order to ensure that the flexible skin bears the maximum pneumatic load, the maximum rigidity of the flexible skin when the flexible skin can be driven by the driving mechanism is the design rigidity, the relation between the rigidity of the flexible skin and the driving force of the driving mechanism is explored, and the size of the obtained design rigidity of the flexible skin is the key step of the design of the variant aircraft. Based on the scheme in the prior art, the design rigidity of the flexible wing trailing edge skin is directly related to the model size, the motor output torque, the crankshaft shape, the number of the motors and the number of the crankshafts, an efficient and simple calculation method is explored, and the calculation of the design rigidity is a very necessary work.
Disclosure of Invention
To address at least one of the above-identified problems, the present application provides a method for determining a stiffness of a compliant airfoil that accommodates a distributed parabolic crankshaft drive.
The application provides a method for determining the rigidity of a flexible airfoil surface suitable for distributed parabolic crankshaft driving, which comprises the following steps:
setting preset conditions and giving known quantities, wherein the known quantities comprise wing chord length, wing span, skin thickness, movable trailing edge percentage, crankshaft number, crankshaft torque, crankshaft spring clamping point percentage and crankshaft maximum downward deflection angle;
obtaining a movable trailing edge central line parabola analytic expression according to a movable trailing edge central line parabola equation;
calculating the average driving force of a single shaft according to the parabola analytic expression of the central line of the movable trailing edge;
substituting the bending moment equation into a deflection line approximate differential equation, obtaining a corner equation after integration, and obtaining a corner formula by the corner equation;
determining unknown quantity in the corner formula, and substituting the unknown quantity into the corner formula to obtain the elastic modulus of the flexible skin;
from the modulus of elasticity, the stiffness of the flexible airfoil is determined.
In some embodiments, the preset conditions include:
the torsion force output by the parabolic crankshaft is a linearly-changed concentrated force;
the deformation rear edge is a variable cross-section cantilever beam, the variable cross-section cantilever beam is equivalent to a uniform cross-section beam, and the moment of inertia at the thinnest part with concentrated acting force is taken as the moment of inertia of the uniform cross-section cantilever beam;
the driving force applied to the skin is limited force.
In some embodiments, obtaining a moving trailing edge centerline parabola equation from the moving trailing edge centerline parabola equation comprises:
let the movable trailing edge centerline parabolic equation be:
y＝Ax 2 +Bx+C；
the midline must pass through (0,0), to obtain C ═ 0,
from the curvature formula:
where x is 0, and k is the maximum value when B is 0, where the curvature of the crankshaft is the maximum and the efficiency is the highest, B is 0,
from the maximum declination angle alpha, the necessary passing point (l multiplied by n) of the central line is obtained 1 ％,l×n 1 Percent multiplied by tan alpha) into a movable trailing edge centerline parabola equation to obtain a movable trailing edge centerline parabola analytical formula as follows:
wherein l is the wing chord length, n 1 % is the movable trailing edge percentage, α is the maximum downward deflection angle of the crankshaft, k is the crankshaft curvature, and A, B, C is a constant.
In some embodiments, calculating the uniaxial average driving force according to a movable trailing edge centerline parabola analysis comprises:
when the crankshaft just starts to rotate, the downward driving force to the skin is as follows:
when the crankshaft moves to the centrifugal distance with the initial length n 2 % downward driving force on the skin is:
the average driving force is then:
wherein, F danzhou To average driving force, F 1 、F 2 Is the downward driving force of the skin, n 1 % is the percent of the movable trailing edge, n 2 % of crankshaft springThe percentage of the clamping points, i, is the wing chord length, alpha is the maximum downward deflection angle of the crankshaft, and T is the torque of the crankshaft.
In some embodiments, substituting the bending moment equation into the deflection line approximation differential equation and integrating to obtain the corner equation comprises:
the bending moment equation is:
M (x) ＝F(L-x)；
substituting the flexible line approximates a differential equation:
obtaining a rotation angle equation after integration:
wherein M is (x) Bending moment borne by the flexible airfoil; f is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<L); w is a chord-wise deflection line of the flexible trailing edge in the flexible airfoil; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
In some embodiments, and deriving the rotation angle formula from the rotation angle equation, comprises:
substituting x as 0 and theta as 0 into the rotation angle equation to obtain C as 0, namely the rotation angle equation is
Wherein F is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x < ═ L); w is a chord-wise deflection line of the flexible trailing edge in the flexible airfoil; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
In some embodiments, determining the unknowns in the corner equation comprises:
the unknowns in the corner equations are determined by the following system of equations:
wherein F is the total driving force provided by the crankshaft; g is the number of crankshafts; f danzhou Is the average driving force of a single crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<＝L)；n 1 % is the movable trailing edge percentage; theta is the corner of any cross section of the flexible trailing edge in the flexible airfoil; l is the chord length of the flexible engine, and alpha is the maximum downward deflection angle of the crankshaft; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; b is the width of the flexible trailing edge in the spanwise direction in the flexible airfoil; and t is the thickness of the flexible skin.
In some embodiments, determining the stiffness of the flexible airfoil from the modulus of elasticity comprises:
the stiffness of the flexible airfoil is determined by the following equation:
K＝E*t
wherein K is the rigidity of the flexible skin, E is the elastic modulus, and t is the thickness of the flexible skin.
The method for determining the rigidity of the flexible airfoil driven by the distributed parabolic crankshaft provided by the embodiment of the application has the advantages of high efficiency, concise process and small error range.
Drawings
FIG. 1 is a schematic flow chart diagram illustrating a method for determining stiffness of a flexible airfoil adapted for distributed parabolic crankshaft drive according to an embodiment of the present disclosure.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic flow chart of a method for determining a stiffness of a flexible airfoil adapted to a distributed parabolic crankshaft drive according to an embodiment of the present disclosure.
As shown in fig. 1, the method comprises the steps of:
step 1, setting preset conditions and giving known quantity.
The known quantities comprise wing chord length, wing span, skin thickness, movable trailing edge percentage, crankshaft number, crankshaft torque, crankshaft spring clamping point percentage and crankshaft maximum downward deflection angle.
The preset conditions include: the torsion force output by the parabolic crankshaft is a linearly-changed concentrated force; the deformation trailing edge is a variable cross-section cantilever beam, the variable cross-section cantilever beam is equivalent to an equal cross-section beam, and the moment of inertia at the thinnest part with concentrated acting force is taken as the moment of inertia of the equal cross-section cantilever beam; the driving force applied to the skin is limited force.
It should be noted that, the motor drives the crankshaft, the driving force output by the crankshaft is mainly concentrated at the tip, the force output by the crankshaft can be assumed to be concentrated force, meanwhile, the shape of the crankshaft is generally in a parabolic or hyperbolic shape close to the curvature of the trailing edge of the wing, and when the crankshaft rotates at a constant speed, the force output by the tip can be further assumed to be uniformly and linearly transformed, so that the torsion force output by the crankshaft is linearly changed concentrated force.
The deformable part of the wing trailing edge deflects under the driving of a crankshaft, and the trailing edge is from thick to thin, so the deformable trailing edge is assumed to be a deformed section cantilever beam, meanwhile, the moment of inertia of each part of the variable section is different along with the different thickness, the variable section beam is assumed to be a uniform section beam for simplifying operation, and the moment of inertia of the thinnest part where acting force is concentrated is taken as the moment of inertia of the uniform section.
In the motion process of the crankshaft, the driving force borne by the skin is continuously increased along with the reduction of the distance between the centers of the crankshafts, when the crankshafts rotate to be close to the maximum deflection angle, the driving force is infinite, and the driving force is not in accordance with reality, so that when the crankshafts are close to the maximum deflection angle, the crankshafts are clamped by the springs, the spring force is equal to the sum of other forces of the skin on the crankshafts in the vertical direction, and therefore the driving force borne by the skin can be changed into a limited force.
And 2, obtaining a movable trailing edge central line parabola analytic expression according to the movable trailing edge central line parabola equation.
The movable trailing edge centerline parabolic equation is:
y＝Ax 2 +Bx+C；
the midline must pass through (0,0), to obtain C ═ 0,
from the curvature formula:
where x is 0, and k is the maximum value when B is 0, where the curvature of the crankshaft is the maximum and the efficiency is the highest, B is 0,
from the maximum declination angle alpha, the necessary passing point (l multiplied by n) of the central line is obtained 1 ％,l×n 1 Percent multiplied by tan alpha) into a movable trailing edge centerline parabola equation to obtain a movable trailing edge centerline parabola analytical formula as follows:
wherein l is the wing chord length, n 1 % is the movable trailing edge percentage, α is the maximum downward deflection angle of the crankshaft, k is the crankshaft curvature, and A, B, C is a constant.
And 3, calculating the uniaxial average driving force according to the parabola analytical formula of the movable trailing edge centerline.
When the crankshaft just starts to rotate, the downward driving force to the skin is as follows:
when the crankshaft moves to the centrifugal distance with the initial length n 2 % downward driving force on the skin is:
the average driving force is then:
wherein, F danzhou To average driving force, F 1 、F 2 For downward driving force of the skin, n 1 % is the percent of the movable trailing edge, n 2 % is the percentage of the clamping point of the crankshaft spring, l is the length of the wing chord, alpha is the maximum downward deflection angle of the crankshaft, and T is the torque of the crankshaft.
And 4, substituting the bending moment equation into a deflection line approximate differential equation, integrating to obtain a corner equation, and obtaining a corner formula by the corner equation.
The bending moment equation is:
M (x) ＝F(L-x)；
substituting the deflection line approximate differential equation:
obtaining a rotation angle equation after integration:
wherein M is (x) Bending moment borne by the flexible airfoil; f is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<L); w is a flexible wingA chordal deflection line in the face of the flexible trailing edge; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
Substituting x as 0 and theta as 0 into the rotation angle equation to obtain C as 0, namely the rotation angle equation is
Wherein F is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length of the flexible trailing edge along the chord direction in the flexible airfoil (x < ═ L); w is a chord-wise deflection line of the flexible trailing edge in the flexible airfoil; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
And 5, determining unknown quantity in the corner formula, and substituting the unknown quantity into the corner formula to obtain the elastic modulus of the flexible skin.
The unknowns in the corner formula are determined by the following system of equations:
wherein F is the total driving force provided by the crankshaft; g is the number of crankshafts; f danzhou Is the average driving force of a single crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<＝L)；n 1 % is the movable trailing edge percentage; theta is a corner of any cross section of the flexible trailing edge in the flexible airfoil; l is the chord length of the flexible engine, and alpha is the maximum downward deflection angle of the crankshaft; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; b is the width of the flexible trailing edge in the chord direction in the flexible airfoil; and t is the thickness of the flexible skin.
And 6, determining the rigidity of the flexible airfoil according to the elastic modulus.
The stiffness of the flexible airfoil is determined by the following equation:
K＝E*t；
wherein K is the rigidity of the flexible skin, E is the elastic modulus, and t is the thickness of the flexible skin.
The method for determining the stiffness of the flexible airfoil of the distributed parabolic crankshaft drive according to the embodiment of the present application is described in detail with reference to a specific example.
For example, the length of the wing chord is 0.7m, the span is 0.6m, the thickness of the skin is 0.002m, the percentage of the movable trailing edge is 30%, the number of crankshafts is 4, the torque of the crankshaft is 4.6 N.m, the percentage of the clamping point of the crankshaft is 20%, and the maximum downward deflection angle of the crankshaft is 20 °.
The known quantities described above are substituted into a moving trailing edge centerline parabolic analytic equation to yield:
by the following formula:
it is possible to obtain,
F 1 ≈60.18N；
F 2 ≈300.91N；
F danzhou ≈180.55N；
is formed by the following equation system
It is possible to obtain,
substituting the above results into the following equation:
the available modulus of elasticity:
E＝7.9GPa；
substituting the elastic modulus into the formula:
K＝E*t；
it can be seen that the stiffness of the flexible airfoil is:
as described above, only the specific embodiments of the present application are provided, and it can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the system, the module and the unit described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again. It should be understood that the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present application, and these modifications or substitutions should be covered within the scope of the present application.
Claims (6)
1. A method for determining a stiffness of a flexible airfoil adapted for distributed parabolic crankshaft drive, comprising:
setting preset conditions and giving known quantities, wherein the known quantities comprise wing chord length, wing span, skin thickness, movable trailing edge percentage, crankshaft number, crankshaft torque, crankshaft spring clamping point percentage and crankshaft maximum downward deflection angle;
obtaining a movable trailing edge central line parabola analytic expression according to a movable trailing edge central line parabola equation;
calculating the average driving force of a single shaft according to the parabola analytic expression of the central line of the movable trailing edge;
substituting the bending moment equation into a deflection line approximate differential equation, obtaining a corner equation after integration, and obtaining a corner formula by the corner equation;
determining unknown quantity in the corner formula, and substituting the unknown quantity into the corner formula to obtain the elastic modulus of the flexible skin;
determining the rigidity of the flexible airfoil according to the elastic modulus;
obtaining a movable trailing edge centerline parabola analytic expression according to a movable trailing edge centerline parabola equation, wherein the movable trailing edge centerline parabola analytic expression comprises the following steps:
let the equation of the movable trailing edge midline parabola be:
y＝Ax 2 +Bx+C；
the midline must pass through (0,0), to obtain C ═ 0,
from the curvature formula:
where x is 0, and k is the maximum value when B is 0, where the curvature of the crankshaft is the maximum and the efficiency is the highest, B is 0,
from the maximum declination angle alpha, the necessary passing point (l multiplied by n) of the central line is obtained 1 ％,l×n 1 Percent multiplied by tan alpha) into a movable trailing edge centerline parabola equation to obtain a movable trailing edge centerline parabola analytical formula as follows:
wherein l is the wing chord length, n 1 % is movable trailing edge percentage, alpha is maximum downward deflection angle of the crankshaft, k is crankshaft curvature, A, B, C is constant;
calculating a uniaxial average driving force according to a movable trailing edge centerline parabola analytical formula, comprising:
when the crankshaft just starts to rotate, the downward driving force to the skin is as follows:
when the crankshaft moves to the centrifugal distance with the initial length n 2 % downward driving force on the skin is:
the average driving force is then:
wherein, F danzhou To average driving force, F 1 、F 2 Is the downward driving force of the skin, n 1 % is the percent of the movable trailing edge, n 2 % is the percentage of the clamping point of the crankshaft spring, l is the length of the engine wing chord, alpha is the maximum downward deflection angle of the crankshaft, and T is the torque of the crankshaft.
2. The method for determining a stiffness of a flexible airfoil compliant with a distributed parabolic crankshaft drive as set forth in claim 1, wherein said predetermined conditions comprise:
the torsion force output by the parabolic crankshaft is a linearly-changed concentrated force;
the deformation trailing edge is a variable cross-section cantilever beam, the variable cross-section cantilever beam is equivalent to an equal cross-section beam, and the moment of inertia at the thinnest part with concentrated acting force is taken as the moment of inertia of the equal cross-section cantilever beam;
the driving force applied to the skin is limited force.
3. The method for determining the stiffness of a flexible airfoil adapted to a distributed parabolic crankshaft drive according to claim 1, wherein substituting a bending moment equation into a deflection line approximation differential equation and integrating to obtain a rotation angle equation comprises:
the bending moment equation is:
M (x) ＝F(L-x)；
substituting the flexible line approximates a differential equation:
obtaining a rotation angle equation after integration:
wherein M is (x) Bending moment borne by the flexible airfoil; f is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<L); w is a chord-wise deflection line of the flexible trailing edge in the flexible airfoil; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
4. The method for determining the stiffness of a flexible airfoil adapted for a distributed parabolic crankshaft drive of claim 3, wherein the angle of rotation equation is derived from an angle of rotation equation comprising:
substituting x as 0 and theta as 0 into the rotation angle equation to obtain C as 0, namely the rotation angle equation is
Wherein F is the total driving force provided by the crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x < -L); w is a chord-wise deflection line of the flexible trailing edge in the flexible airfoil; e is the Young's modulus of the material; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; theta is the angle of rotation of any cross section of the flexible trailing edge in the flexible airfoil.
5. The method for determining a stiffness of a flexible airfoil compliant with a distributed parabolic crankshaft drive as in claim 1 wherein determining the unknowns in the corner equation comprises:
the unknowns in the corner formula are determined by the following system of equations:
wherein F is the total driving force provided by the crankshaft; g is the number of crankshafts; f danzhou Is the average driving force of a single crankshaft; l is the length of the flexible trailing edge in the chord direction in the flexible airfoil; x is the length from any cross section of the flexible trailing edge to the fixed end along the chord direction in the flexible airfoil (x)<＝L)；n 1 % is the movable trailing edge percentage; theta is a corner of any cross section of the flexible trailing edge in the flexible airfoil; l is the chord length of the flexible engine, and alpha is the maximum downward deflection angle of the crankshaft; i is the moment of inertia of the flexible trailing edge in the flexible airfoil; b is the width of the flexible trailing edge in the spanwise direction in the flexible airfoil; and t is the thickness of the flexible skin.
6. The method for determining the stiffness of a compliant airfoil compliant with a distributed parabolic crankshaft drive as in claim 1, wherein determining the stiffness of the compliant airfoil based on the elastic modulus comprises:
the stiffness of the flexible airfoil is determined by the following equation:
K＝E*t
wherein K is the rigidity of the flexible skin, E is the elastic modulus, and t is the thickness of the flexible skin.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108090273A (en) * | 2017-12-13 | 2018-05-29 | 中国飞机强度研究所 | A kind of flexible wing trailing edge formations and flexible wing trailing edge formations design method |
| CN108216572A (en) * | 2018-01-23 | 2018-06-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of more bent shaft-driven flexible aerofoil component and with its wing |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108090273A (en) * | 2017-12-13 | 2018-05-29 | 中国飞机强度研究所 | A kind of flexible wing trailing edge formations and flexible wing trailing edge formations design method |
| CN108216572A (en) * | 2018-01-23 | 2018-06-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of more bent shaft-driven flexible aerofoil component and with its wing |
Non-Patent Citations (1)
| Title |
|---|
| 可变后缘弯度机翼柔性蒙皮的变形特性分析;尹维龙等;《南京航空航天大学学报》;20120815(第04期);全文 * |
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