CN112224440A - High-precision simulation method for aerodynamic characteristics of flapping wings - Google Patents
High-precision simulation method for aerodynamic characteristics of flapping wings Download PDFInfo
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- CN112224440A CN112224440A CN202011128377.7A CN202011128377A CN112224440A CN 112224440 A CN112224440 A CN 112224440A CN 202011128377 A CN202011128377 A CN 202011128377A CN 112224440 A CN112224440 A CN 112224440A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a high-precision simulation method for aerodynamic characteristics of flapping wings, and relates to the field of aircrafts; the method comprises the following steps: the movement of the wing to be simulated is considered as the composition of 2 movements; designing a wing convenient to simulate according to the wing to be simulated, wherein the wing convenient to simulate comprises a wing spar, a wing surface and a counterweight; establishing a virtual wind tunnel in simulation software, fixing a base in the virtual wind tunnel, placing wings convenient for simulation in the virtual wind tunnel, adding a spherical pair, and constraining a wing spar, a wing surface and a counterweight; the wing beam, the wing surface and the counterweight are respectively provided with proper density, and the center of mass of the wing beam is applied with restoring force, restoring moment and driving force, so that the simulated wing can be conveniently forced to vibrate; obtaining aerodynamic characteristics of the wings convenient for simulation when forced vibration is carried out in simulation software; the method reflects the influence of inertia force on the motion rule of the wings, can predict the aerodynamic characteristics of the flapping wings and reflects the influence of the plane shape of the wings on the aerodynamic characteristics of the flapping wings.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a high-precision simulation method for aerodynamic characteristics of flapping wings.
Background
The flapping wings are adopted by insects, birds and bats which can fly in nature, and the flapping wings have the characteristics of high maneuverability and low energy consumption. The flapping wing aircraft is different from fixed wing aircraft and rotor aircraft, is an aircraft adopting insect, bird and bat flying modes, and has wide prospect in military and civil fields. Various flapping wing aircraft have been developed, such as "KUBeetle" flapping wing aircraft, university of Korean construction.
The existing flapping wing aerodynamic characteristic simulation method has the following problems:
1. the existing flapping wing aerodynamic characteristic simulation method is difficult to reflect the influence of inertia force on the motion rule of the wings.
2. The conventional flapping wing aerodynamic characteristic simulation method is difficult to predict the flapping wing aerodynamic characteristic.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides a high-precision simulation method for aerodynamic characteristics of a flapping wing.
The invention relates to a high-precision simulation method of aerodynamic characteristics of flapping wings, which comprises the following stages:
stage 1:
the movement of the wing to be simulated is considered as a composite of 2 movements:
(a) the whole wing to be simulated rotates around an axis in the wingspan direction to change the attack angle;
(b) the entire wing to be simulated flaps about an axis perpendicular to the axis about which the angle of attack is changed.
The planform of the wing to be simulated is determined. The range of flapping about an axis of flapping, the range of rotation about an axis of changing angle of attack, the period of flapping to be simulated is determined.
And (2) stage:
according to the wing to be simulated, the wing convenient to simulate is designed. The movements of the wing that facilitate simulation are synthesized from 2 movements:
(a) the whole wing convenient for simulation rotates around the axis of the changed attack angle;
(b) the entire airfoil, which facilitates simulation, slams about an axis about which the slap is made.
A wing for facilitating simulation comprising:
(a) a spar having a center of mass on an axis about which the angle of attack changes and a center of mass not on an axis about which the flapping occurs when the density of the spar is uniform;
(b) the plane shape of the airfoil is consistent with that of the airfoil to be simulated, the airfoil is provided with a cavity, and the cavity is filled by a wing beam;
(c) a counterweight sandwiched between the leading edges of the airfoils.
And (3) stage:
and establishing a virtual wind tunnel in simulation software, and performing aerodynamic characteristic simulation in the virtual wind tunnel. The base is fixed in the virtual wind tunnel. And (4) placing the wings convenient for simulation in a virtual wind tunnel. The origin of the coordinate system of the wing beam, the wing surface and the counterweight can be placed on the axis of the attack angle change, and the origin of the coordinate system of the wing beam, the wing surface and the counterweight can not be placed on the axis of the flapping.
Add spherical pair, include:
(a) a spherical pair is used for connecting the base and the wing beam;
(b) a spherical pair is used for connecting the base and the wing surface;
(c) a spherical pair is used for connecting the base and the counterweight.
The spherical centers of the spherical pairs are overlapped, the spherical centers of the spherical pairs are on the axis of the attack angle changing mechanism, and the spherical centers of the spherical pairs are on the axis of the flapping mechanism. The spar, the airfoil and the counterweight can rotate around the spherical center of the spherical pair, and the distance from the spar, the airfoil and the counterweight to the spherical center of the spherical pair is not variable. The spars, airfoils, and weights are constrained so that the origin of the spar, airfoils, and weights coordinate system can move in a plane passing through the center of the spherical pair and perpendicular to the axis about which the flapping occurs.
And (4) stage:
the spar, airfoil, and counterweight are each provided with a suitable density.
A restoring force is exerted on the centre of mass of the spar, which restoring force may return the spar to the equilibrium position when the spar is flapping away from the equilibrium position about the flapping axis. A restoring moment is exerted on the centre of mass of the spar, which restoring moment makes it possible to return the spar to the rest position when the spar is rotated away from the rest position about the axis of changing angle of attack. A periodic external force, namely a driving force, is applied to the mass center of the wing beam, so that the wing convenient to simulate is forced to vibrate under the action of the driving force. The restoring force, the restoring moment and the driving force are respectively adjusted, so that when the forced vibration reaches a stable state, the period of the forced vibration is consistent with the period of flapping to be simulated, the flapping range of the simulated wings around the axis of the flapping motion is convenient to be consistent with the flapping range of the simulated wings around the axis of the flapping motion, the rotation range of the simulated wings around the axis of the changing attack angle is convenient to be consistent with the rotation range of the simulated wings around the axis of the changing attack angle.
And (5) stage:
the aerodynamic characteristics of the wings convenient for simulation when forced vibration is carried out are obtained in simulation software. The aerodynamic characteristics of the simulated wings can be reflected conveniently when forced vibration is carried out on the simulated wings.
Compared with the prior art, the invention has the following beneficial effects:
1. the wing convenient for simulation comprises the wing beam, the wing surface and the balance weight, and the wing beam, the wing surface and the balance weight are respectively provided with proper densities, so that the influence of inertia force on the motion rule of the wing is reflected, and the precision of a simulation result is improved.
2. The high-precision simulation method for the aerodynamic characteristics of the flapping wings can predict the aerodynamic characteristics of the flapping wings.
3. The high-precision simulation method for the aerodynamic characteristics of the flapping wings reflects the influence of the plane shape of the wings on the aerodynamic characteristics of the flapping wings.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
Figure 1 shows the movement of a wing to be simulated.
Figure 2 is an isometric view of a wing for ease of simulation.
Figure 3 is an isometric view of the spar.
FIG. 4 is an isometric view of an airfoil.
Fig. 5 is an isometric view of a counterweight.
FIG. 6 is a virtual wind tunnel, pedestal, airfoil for facilitating simulation.
Fig. 7 is a spherical pair.
In the figure, 1 is the wing to be simulated, 2 is the axis about which the angle of attack is changed, 3 is the axis about which flapping is performed, 4 is the wing for convenience of simulation, 5 is the wing spar, 6 is the wing surface, 7 is the counterweight, 8 is the cavity, 9 is the virtual wind tunnel, 10 is the base, and 11 is the sphere center of the spherical pair.
Detailed Description
The present invention will be described in further detail with reference to the following examples and the accompanying drawings. The examples herein are provided for the purpose of illustration only and are not intended to be limiting.
The high-precision simulation method for the aerodynamic characteristics of the flapping wings comprises the following stages:
stage 1:
the movement of the wing 1 to be simulated is considered as a composite of 2 movements:
(a) the whole wing 1 to be simulated rotates around an axis in the wingspan direction to change the attack angle;
(b) the entire wing 1 to be simulated flaps about an axis perpendicular to the axis 2 about which the angle of attack is changed.
The movement of the wing 1 to be simulated is shown in figure 1. The plan shape of the wing 1 to be simulated is determined. The range of flapping about the axis 3 of flapping, the range of rotation about the axis 2 of changing angle of attack, the period of flapping to be simulated is determined.
And (2) stage:
depending on the wing 1 to be simulated, a wing 4 is designed which facilitates the simulation. The movements of the wing 4 that facilitate the simulation are synthesized from 2 movements:
(a) the entire airfoil 4, which is convenient for simulation, rotates about the axis 2 about which the angle of attack changes;
(b) the entire airfoil 4, which facilitates simulation, slams about the slap motion axis 3.
A wing 4 facilitating simulation is shown in figure 2. The wing 4 facilitating simulation comprises:
(a) a spar 5, the centre of mass of the spar 5 being on the axis 2 about which the angle of attack changes and the centre of mass of the spar 5 not being on the axis 3 about which flapping occurs when the density of the spar 5 is uniform; spar 5 is shown in fig. 3;
(b) the plane shape of the airfoil 6 is consistent with that of the wing 1 to be simulated, the airfoil 6 is provided with a cavity 8, and the cavity 8 is filled by the spar 5; the airfoil 6 is shown in FIG. 4;
(c) a counterweight 7, the counterweight 7 being clamped at the leading edge of the airfoil 6; the counterweight 7 is shown in fig. 5.
And (3) stage:
a virtual wind tunnel 9 is established in the simulation software, and the aerodynamic characteristic simulation is carried out in the virtual wind tunnel 9. The base 10 is fixed in the virtual wind tunnel 9. The wings 4, which facilitate the simulation, are placed in a virtual wind tunnel 9. The origin of the coordinate system of the spar 5, the airfoil 6, the counterweight 7 is placed on the axis 2 about which the angle of attack is changed, and the origin of the coordinate system of the spar 5, the airfoil 6, the counterweight 7 cannot be placed on the axis 3 about which the flapping occurs. The virtual wind tunnel 9, the base 10, and the wings 4 facilitating simulation are shown in fig. 6.
Add spherical pair, include:
(a) a spherical pair is used for connecting the base 10 and the wing beam 5;
(b) a spherical pair is used for connecting the base 10 and the airfoil 6;
(c) the base 10 and the counterweight 7 are connected by a spherical pair.
The centres 11 of the spherical pairs coincide, the centre 11 of the spherical pair being on the axis 2 about which the angle of attack is changed, and the centre 11 of the spherical pair being on the axis 3 about which the flapping is performed. The spar 5, the airfoil 6 and the counterweight 7 can rotate around the spherical center 11 of the spherical pair, and the distance from the spar 5, the airfoil 6 and the counterweight 7 to the spherical center 11 of the spherical pair is not variable. The spars 5, the airfoils 6, and the weights 7 are constrained such that the origin of the coordinate system of the spars 5, the airfoils 6, and the weights 7 can move in a plane passing through the center 11 of the spherical pair and perpendicular to the axis 3 about which the flapping is intended. The spherical pair is shown in fig. 7.
And (4) stage:
the spar 5, the airfoil 6, the counterweight 7 are provided with a suitable density, respectively.
A restoring force is exerted on the centre of mass of the spar 5, which restoring force can return the spar 5 to the rest position when the spar 5 flaps away from the rest position about the flapping axis 3. A restoring moment is exerted on the centre of mass of the spar 5, which restoring moment makes it possible to return the spar 5 to the rest position when the spar 5 is rotated away from the rest position about the axis 2, about which the angle of attack changes. A periodic external force, i.e. a driving force, is applied to the center of mass of the spar 5, so that the wing 4 convenient for simulation is forced to vibrate under the action of the driving force. The restoring force, the restoring moment and the driving force are respectively adjusted, so that when the forced vibration reaches a stable state, the period of the forced vibration is consistent with the period of flapping to be simulated, the flapping range of the simulated wings 4 around the axis 3 of flapping is consistent with the flapping range of the simulated wings to be simulated around the axis 3 of flapping, and the rotating range of the simulated wings 4 around the axis 2 of changing the angle of attack is consistent with the rotating range of the simulated wings to be simulated around the axis 2 of changing the angle of attack.
And (5) stage:
the aerodynamic characteristics of the simulated wing 4 which are convenient to simulate when forced vibration is obtained in the simulation software. The aerodynamic characteristics of the wing 1 to be simulated can be reflected by the aerodynamic characteristics of the wing 4 to be simulated when forced vibration is applied.
The foregoing is only a preferred embodiment of the present invention, and it will be apparent to those skilled in the art that various modifications and substitutions can be made without departing from the principle of the present invention, and these modifications and substitutions should also be considered as the protection scope of the present invention.
Claims (4)
1. A high-precision simulation method for aerodynamic characteristics of flapping wings is characterized by comprising the following steps:
stage 1):
the movement of the wing (1) to be simulated is considered as a composite of 2 movements:
a) the whole wing (1) to be simulated rotates around a spanwise axis to change the attack angle;
b) the entire wing (1) to be simulated flapping around an axis perpendicular to the axis (2) about which the angle of attack is changed;
determining the planar shape of the wing (1) to be simulated; determining a range of flapping about an axis (3) of flapping, a range of rotation about an axis (2) of changing angle of attack, a period of flapping to be simulated;
stage 2):
designing a wing (4) convenient for simulation according to the wing (1) to be simulated; the movements of the wing (4) which facilitate the simulation are composed of 2 movements:
a) the whole wing (4) convenient for simulation rotates around the axis (2) for changing the attack angle;
b) the whole wing (4) convenient for simulation beats around the flapping axis (3);
the wing (4) convenient for simulation comprises a wing beam (5), a wing surface (6) and a counterweight (7);
stage 3):
establishing a virtual wind tunnel (9) in simulation software, and simulating aerodynamic characteristics in the virtual wind tunnel (9); fixing the base (10) in the virtual wind tunnel (9); the wings (4) convenient for simulation are placed in a virtual wind tunnel (9); placing the origin of the coordinate systems of the wing beam (5), the wing surface (6) and the counterweight (7) on the axis (2) about which the attack angle is changed, and not placing the origin of the coordinate systems of the wing beam (5), the wing surface (6) and the counterweight (7) on the axis (3) about which the flapping motion occurs;
add spherical pair, include:
a) a spherical pair is used for connecting the base (10) and the wing beam (5);
b) a spherical pair is used for connecting the base (10) and the airfoil (6);
c) a spherical pair is used for connecting the base (10) and the counterweight (7);
the centers (11) of the spherical pairs are overlapped, the center (11) of the spherical pair is on the axis (2) of the angle of attack change, and the center (11) of the spherical pair is on the axis (3) of the flapping; the wing beam (5), the wing surface (6) and the counterweight (7) can rotate around the spherical center (11) of the spherical pair, and the distances from the wing beam (5), the wing surface (6) and the counterweight (7) to the spherical center (11) of the spherical pair are invariable; constraining the spar (5), the airfoil (6) and the counterweight (7) so that the origin of the coordinate system of the spar (5), the airfoil (6) and the counterweight (7) can move in a plane passing through the centre of sphere (11) of the spherical pair and perpendicular to the axis (3) about which the flapping is about;
stage 4):
the wing beam (5), the wing surface (6) and the counterweight (7) are respectively provided with proper density;
exerting a restoring force on the centre of mass of the spar (5) which makes it possible to return the spar (5) to the rest position when the spar (5) is flapped away from the rest position about the axis (3) about which the flapping occurs; exerting a restoring moment on the centre of mass of the spar (5), which restoring moment makes it possible to return the spar (5) to the rest position when the spar (5) is rotated away from the rest position about the axis (2) about which the angle of attack changes; a periodic external force, namely a driving force, is applied to the mass center of the wing beam (5), so that the wing (4) convenient for simulation is forced to vibrate under the action of the driving force; respectively adjusting restoring force, restoring moment and driving force to ensure that when the forced vibration reaches a stable state, the period of the forced vibration is consistent with the period of flapping to be simulated, the flapping range of the simulated wing (4) around the flapping axis (3) is convenient to be consistent with the flapping range of the flapping axis (3) to be simulated, and the rotating range of the simulated wing (4) around the axis (2) for changing the attack angle is convenient to be consistent with the rotating range of the simulating wing (2) around the axis (2) for changing the attack angle;
stage 5):
obtaining aerodynamic characteristics of the wings (4) convenient for simulation when forced vibration is carried out in simulation software; the aerodynamic characteristics of the wings (1) to be simulated can be reflected by the aerodynamic characteristics of the wings (4) convenient for simulation when forced vibration is carried out.
2. The high-precision simulation method of aerodynamic characteristics of flapping wings of claim 1, wherein when the density of the spar (5) is uniform, the center of mass of the spar (5) is on the axis (2) about which the angle of attack changes and the center of mass of the spar (5) is not on the axis (3) about which flapping occurs.
3. High-precision simulation method of the aerodynamic characteristics of flapping wings according to claim 1, wherein the plane shape of the airfoil (6) and the plane shape of the wing (1) to be simulated are identical, the airfoil (6) is provided with a cavity (8), and the cavity (8) is filled with the spar (5).
4. The high-precision simulation method of the aerodynamic characteristics of the flapping wing of claim 1, wherein the counterweight (7) is clamped at the leading edge of the airfoil (6).
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