CN211001795U - Wing, deformation device and aircraft - Google Patents
Wing, deformation device and aircraft Download PDFInfo
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- CN211001795U CN211001795U CN201921408791.6U CN201921408791U CN211001795U CN 211001795 U CN211001795 U CN 211001795U CN 201921408791 U CN201921408791 U CN 201921408791U CN 211001795 U CN211001795 U CN 211001795U
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Abstract
The utility model provides a wing, a deformation device and an airplane, wherein the wing comprises a first wing and a second wing; the first wing comprises a connecting piece and an air bag; the connecting piece is arranged at one end of the first wing, and the air bag is arranged in the connecting piece, so that the connecting piece is extended and deformed along with the inflation of the air bag or contracted and deformed along with the deflation of the air bag; one end of the second wing is connected with the first wing through the connecting piece, so that when the connecting piece is extended and deformed, the first wing moves away from a horizontal plane determined by the second wing along with the extension deformation of the connecting piece or moves close to the horizontal plane determined by the second wing along with the contraction deformation of the connecting piece when the connecting piece is contracted and deformed. Adopt the utility model provides a wing, deformation device and aircraft can realize the quick deformation of wing with light and handy structure.
Description
Technical Field
The utility model relates to a space flight field particularly, relates to a wing, deformation device and aircraft.
Background
With the rapid development of aerospace technology, the deformation of airplane wings has become a research and development hotspot. In the prior art, there are two main ways for the deformation of the wing, the first way is to lay a piezoelectric material film actuator in the wing, and although this way can achieve high-rate deformation, the amount of strain that can be generated by a single piezoelectric actuator is too small, and the piezoelectric stack actuator causes problems such as increased structural weight and increased control difficulty. The second is to arrange a shape memory alloy driver in the wing to realize the deformation control of the wing, and although large deformation can be realized, the deformation rate is very low, and the practical application is limited to a certain extent.
In view of this, how to provide a morphing wing with a light structure and a large morphing rate is a problem to be solved by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
The utility model provides a wing, deformation device and aircraft.
In a first aspect, the present invention provides a wing, comprising a first wing and a second wing;
the first wing comprises a connecting piece and an air bag;
the connecting piece is arranged at one end of the first wing, and the air bag is arranged in the connecting piece, so that the connecting piece can be extended and deformed along with the inflation of the air bag or contracted and deformed along with the deflation of the air bag;
one end of the second wing is connected with the first wing through the connecting piece, so that when the connecting piece is subjected to extension deformation, the first wing moves away from the horizontal plane determined by the second wing along with the extension deformation of the connecting piece or moves close to the horizontal plane determined by the second wing along with the contraction deformation of the connecting piece when the connecting piece is subjected to contraction deformation.
Optionally, the connecting member comprises a deformation structure and a flexible skin;
the deformation structure comprises a first supporting piece, a second supporting piece and a supporting plate;
the first supporting piece and the second supporting piece are arranged on one side of the supporting plate and are used for forming an accommodating cavity for accommodating the air bag;
one end of the flexible skin is connected with one end, far away from the supporting plate, of the first supporting piece, the other end of the flexible skin is connected with one end, far away from the supporting plate, of the second supporting piece, so that when the air bag in the accommodating cavity is inflated to cause the first supporting piece and the second supporting piece to move far away from the air bag, the flexible skin stretches, and when the air bag in the accommodating cavity is deflated to cause the first supporting piece and the second supporting piece to move close to the air bag, the flexible skin retracts.
Optionally, the connecting member includes a plurality of deformation structures and a plurality of airbags arranged in each of the deformation structures, wherein the plurality of deformation structures are connected end to end;
and each deformation structure controls the air bag in each deformation structure to inflate or deflate according to a control instruction.
Optionally, the first wing comprises a third wing and a rotor;
the third wing is rotatably arranged at one end of the first wing, which is far away from the second wing, through the rotating piece, so that the third wing can be folded to one side of the first wing.
Optionally, the first wing includes a first side and a second side;
one end of the first side surface is connected with one end of the second side surface, and the other end of the first side surface is connected with one end, close to the first side surface, of the flexible skin;
the other end of the second side surface is connected with one end, close to the second side surface, of the supporting plate;
the included angle formed by the end connected with the first side surface and the second side surface ranges from 0 degree to 30 degrees.
Optionally, the flexible skin is made of an elastic rubber material.
Optionally, the support plate is made of spring steel.
In a second aspect, the present invention provides a wing deformation device, comprising a controller, an electrical proportional control valve, an air compressor and the wing of the first aspect;
the controller is respectively connected with the wings and the electric proportional regulating valve;
the air compressor is connected with the electric proportional regulating valve;
the controller is used for sending a control command to the electric proportional regulating valve;
and the electric proportional control valve is used for controlling the air compressor to inflate or deflate the air bag according to the control instruction.
Optionally, the wing deformation device further comprises a strain gauge;
the strain gauge is arranged in the connecting piece so as to feed back the deformation state of the connecting piece.
In a third aspect, the present invention provides an aircraft comprising an aircraft body and a wing according to the first aspect;
the wings are arranged on two sides of the airplane and used for providing the lifting force for the airplane to fly.
The utility model provides a wing, a deformation device and an airplane, wherein the wing comprises a first wing and a second wing; the first wing comprises a connecting piece and an air bag; the connecting piece is arranged at one end of the first wing, and the air bag is arranged in the connecting piece, so that the connecting piece is extended and deformed along with the inflation of the air bag or contracted and deformed along with the deflation of the air bag; one end of the second wing is connected with the first wing through the connecting piece, so that when the connecting piece is extended and deformed, the first wing moves away from a horizontal plane determined by the second wing along with the extension deformation of the connecting piece or moves close to the horizontal plane determined by the second wing along with the contraction deformation of the connecting piece when the connecting piece is contracted and deformed. Adopt the utility model provides a wing, deformation device and aircraft can be through the ingenious setting to gasbag and connecting piece, solve the problem that the wing warp slowly, the structure is complicated.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below. It is appreciated that the following drawings depict only certain embodiments of the invention and are therefore not to be considered limiting of its scope. For a person skilled in the art, it is possible to derive other relevant figures from these figures without inventive effort.
Fig. 1 is a schematic structural diagram of a wing according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a wing provided in an embodiment of the present invention in a deformed state;
fig. 3 is a schematic structural diagram of a connecting member according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a wing deformation device according to an embodiment of the present invention.
Icon: 1-an airfoil; 10-a first airfoil; 100-a connector; 101-a flexible skin; 102-a first support; 103-a second support; 104-a support plate; 110-an air bag; 20-a second airfoil; 2-a controller; 3-electric proportional control valve; 4-air compressor.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings in the embodiments of the present invention are combined below to clearly and completely describe the technical solutions in the embodiments of the present invention. It is to be understood that the embodiments described are only some of the embodiments of the present invention, and not all of them. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inner", "outer", "left", "right", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally placed when the products of the present invention are used, or orientations or positional relationships that are conventionally understood by those skilled in the art, and are merely for convenience of description of the present invention and simplifying the description, but do not indicate or imply that the device or element that is referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be further noted that, unless explicitly stated or limited otherwise, the terms "disposed" and "connected" are to be interpreted broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
The following describes in detail embodiments of the present invention with reference to the accompanying drawings.
Please refer to fig. 1 and fig. 2 in combination. Fig. 1 is the structural schematic diagram of the wing 1 provided by the embodiment of the present invention, and fig. 2 is the structural schematic diagram of the wing 1 provided by the embodiment of the present invention under the deformation state. The wing 1 comprises a first wing 10 and a second wing 20;
the first wing 10 includes a connecting member 100 and an airbag 110.
The connecting member 100 is disposed at one end of the first wing 10, and the airbag 110 is disposed inside the connecting member 100, so that the connecting member 100 is deformed by extension with the inflation of the airbag 110 or deformed by contraction with the deflation of the airbag 110.
One end of the second wing 20 is connected to the first wing 10 through the connection member 100, so that the first wing 10 moves away from the horizontal plane defined by the second wing 20 along with the extension deformation of the connection member 100 when the connection member 100 is extended or moves closer to the horizontal plane defined by the second wing 20 along with the contraction deformation of the connection member 100 when the connection member 100 is contracted.
In this embodiment, a connecting piece 100 may be disposed on the first wing 10 for connecting the second wing 20, and an airbag 110 may be disposed in the connecting piece 100, so that inflation and deflation of the airbag 110 causes deformation of the connecting piece 100, and further causes deformation of the first wing 10 relative to the second wing 20. When the airbag 110 is inflated, one side of the connecting member 100 is relatively fixed, the other side of the connecting member extends and deforms as the airbag 110 is inflated, one side of the connecting member is relatively fixed, and the other side of the connecting member extends, so that the first wing 10 moves away from a horizontal plane defined by the second wing 20, that is, the first wing is deformed in a deviating manner. When the air bag 110 is deflated, one side of the connection is relatively fixed, the other side of the connection is contracted and deformed along with the deflation and shrinkage of the air bag 110, one side of the connection is relatively fixed, and the other side of the connection is contracted, so that the first wing 10 can move close to the horizontal plane determined by the second wing 20 until the first wing is reset. In this embodiment, the offset direction of the first wing 10 relative to the second wing 20 during deformation may be downward, and in other embodiments, the offset direction of the first wing 10 relative to the second wing 20 during deformation may also be upward.
It should be noted that the use of a pressure increase or decrease within bladder 110 to provide the force for deformation of connecting member 100 is more convenient than the use of hydraulic force to provide the force. The wing 1 operates in an environment where the air is very abundant and therefore there is no need to worry about the problem of insufficient inflation pressure of the bladder 110.
It will be appreciated that by inflating the bladder 110 to deform the wing 1, the rate of deformation of the wing 1 is faster than by hydraulics, etc. and the device is lighter and thus assists in the flight of the aircraft.
Referring to fig. 3, fig. 3 is a schematic structural diagram of a connecting member 100 according to an embodiment of the present invention. The connection 100 includes a deformation structure and a flexible skin 101.
The deformation structure includes a first support 102, a second support 103, and a support plate 104.
The first support member 102 and the second support member 103 are disposed at one side of the support plate 104 to form a receiving chamber for receiving the airbag 110.
One end of the flexible skin 101 is connected with one end of the first support member 102 far away from the support plate 104, and the other end is connected with one end of the second support member 103 far away from the support plate 104, so that when the air bag 110 in the accommodating cavity of the flexible skin 101 is inflated to cause the first support member 102 and the second support member 103 to move away from the second wing 20, the flexible skin 101 is stretched, and when the air bag 110 in the accommodating cavity is deflated to cause the first support member 102 and the second support member 103 to move close to the second wing 20, the flexible skin 101 is retracted.
In this embodiment, the flexible skin 101 may be fixed to the ends of the first support 102 and the second support 103 away from the support plate 104, when the airbag 110 inflates, the volume of the airbag 110 increases with the increase of the pressure inside the airbag 110, the increased airbag 110 gradually starts to press the first support 102 and the second support 103, and the ends of the first support 102 and the second support 103 connected to the support plate 104 are relatively fixed, so that the ends of the first support and the second support 103 away from the support plate 104 may start to move away from the airbag 110. The distance between the ends of the first support 102 and the second support 103 connected to the support plate 104 is constant, the distance between the ends far away from the support plate 104 is gradually increased, the flexible skin 101 connected to the ends of the first support and the second support 103 far away from the support plate 104 is stretched, the length of one side (the side where the support plate 104 is located) is basically constant for the first wing 10, the length of the other side (the side where the flexible skin 101 is located) is increased, and the end of the first wing 10 far away from the second wing 20 starts to move in a plane determined away from the second wing 20, wherein the moving direction is the direction from the flexible skin 101 to the support plate 104.
Further, the connecting member 100 includes a plurality of deformation structures and a plurality of airbags 110 disposed in each of the deformation structures, wherein the plurality of deformation structures are connected end to end.
And controlling the air bag 110 in each deformation structure to inflate or deflate according to the control instruction by each deformation structure.
In this embodiment, the number of the deformation structures provided in the connecting member 100 may be multiple, and the connection manner between the deformation structures may be an initial connection, and it should be understood that, when there are multiple deformation structures, the first supporting member 102 and the second supporting member 103 of each deformation structure both move away from each other when the airbag 110 inflates, so as to ensure that the flexible skin 101 provided in the deformation structures is stretched, and further, the first wing 10 moves away from the horizontal plane defined by the second wing 20. It should be understood that the control command may include a command for controlling each deformation structure individually, or may include a command for controlling all deformation structures simultaneously.
In another embodiment of this embodiment, the deformation structures may have different sizes, and may be connected end to end in a manner that the sizes of the deformation structures decrease from the second wing 20 to the first wing 10, and the sizes of the airbags 110 disposed in the deformation structures may also be set according to the sizes of the deformation structures. It will be appreciated that the larger the deformation structure, the larger the air cell 110, the greater the influence of the displacement of the first wing 10 when the air cell 110 is inflated, and vice versa when the air cell 110 is deflated. The smaller the deformation structure, the smaller the air cell 110, the less the influence of the air cell 110 on the displacement of the first wing 10 when the air cell 110 is inflated, and vice versa when the air cell 110 is deflated. Through the deformation structures with different sizes, the movement of the first wing 10 relative to the second wing 20 can be controlled more accurately and rapidly. For example, when the first wing 10 needs to make a large displacement relative to the second wing 20, a control instruction may be sent first to control the airbag 110 with the larger deformation structure to inflate, so as to reach the preset position range quickly, and then the control instruction is sent to control the airbag 110 with the smaller deformation structure to inflate, so as to adjust the first wing 10 to reach the preset position.
Further, in the present embodiment, the bending angle of the support plate 104 of a single deformed structure can be obtained by the following formula:
wherein, theta1The bending angle of the supporting plate 104 of a single deformation structure, M is the bending moment borne by the supporting plate 104 of a single deformation structure, E1The Young's modulus of the wing 1, I is the bending stiffness of the support plate 104 in a single deformed configuration, q is the pressure applied by the bladder 110 to the first support member 102 and the second support member 103, and H is the firstThe heights of the supports 102 and 103, w being the widths of the first support 102 and the second support 103 (the length of the sides of the first support 102 and the second support 103 defining the direction of advance of the wing 1), f being the force exerted by the flexible skin 101, wherein,
h is the thickness of the support plate 104.
Further, the force of the flexible skin 101 may be expressed by the following formula:
wherein E is2The young's modulus of the flexible skin 101, t is the thickness of the flexible skin.
Further, according to the above formula, the bending rotation angle of the single deformation structure can be:
where l is the distance between the first support 102 and the second support 103, θ2The bending rotation angle of a single deformation structure.
In this embodiment, when there are N deformation structures, the angle of bending and rotating of the whole wing 1 can be expressed by the following formula:
wherein, theta3The angle of the overall bending rotation of the wing 1.
Also, in the present embodiment, the inventors have proved through finite element analysis that when the number N of the deformation structures is 6, and the pressure of each airbag 110 is provided at 0.4Mpa, the offset displacement of the end of the first wing 10 away from the second wing 20 may be 24.8 mm.
Further, the flexible skin 101 is made of an elastic rubber material.
In this embodiment, the flexible skin 101 may be made of an elastic rubber material, and in other embodiments of this embodiment, the flexible skin 101 may also be made of other materials having elasticity, such as silicone.
Further, the support plate 104 is made of spring steel.
In this embodiment, in order to ensure that the distance between the first support member 102 and the second support member 103 at the end connected to the support plate 104 is kept substantially constant when the airbag 110 inflates and the distance between the other ends away from the support members is gradually increased, the support plate 104 may be made of a material having both rigidity and elasticity, and the shape of the support plate 104 may be slightly changed when the connecting member 100 is deformed, so that spring steel may be used as the material for making the support plate 104.
Further, the first wing 10 includes a third wing and a rotating member.
The third wing is rotatably disposed at an end of the first wing 10 away from the second wing 20 through the rotating member, so that the third wing can be folded to a side of the first wing 10.
In this embodiment, the first wing 10 may further include a third wing and a rotating member, where the third wing may be a section of the first wing 10 away from the second wing 20, and is rotatably disposed on the first wing 10 through the rotating member, and when the wing 1 needs to be transported or stored, the third wing may be rotated around the rotating member to fold the wing 1.
Further, the first wing 10 includes a first side and a second side.
One end of the first side surface and one end of the second side surface are connected, and the other end of the first side surface and the other end of the second side surface are connected with one end, close to the first side surface, of the flexible skin 101.
The other end of the second side is connected to an end of the support plate 104 near the second side.
The included angle formed by the end connected with the first side surface and the second side surface ranges from 0 degree to 30 degrees.
In this embodiment, the first side surface and the second side surface may be combined to form an exoskeleton of the first wing 10, and the included angle between the first side surface and the second side surface may be 0 ° to 30 °, and when the included angle between the first side surface and the second side surface is 0 ° to 30 °, the flight performance of the wing 1 is better.
Referring to fig. 4, fig. 4 is a schematic structural diagram of a wing deformation device according to an embodiment of the present invention. The wing deformation device comprises a controller 2, an electrical proportion regulating valve 3, an air compressor 4 and the wing 1.
The controller 2 is respectively connected with the wing 1 and the electric proportional control valve 3.
The air compressor 4 is connected to the electric proportional control valve 3.
The controller 2 is used for sending a control command to the electric proportional control valve 3.
The electrical proportional control valve 3 is used for controlling the air compressor 4 to inflate or deflate the air bag 110 according to the control instruction.
Further, the wing deformation device also comprises a strain gauge.
The strain gauge is provided in the connection member 100 to feed back a deformation state of the connection member 100.
The embodiment of the utility model provides a still provide an aircraft, including aircraft main part and aforementioned wing 1.
The wings 1 are arranged on both sides of the airplane and used for providing the lifting force for the airplane to fly.
To sum up, adopt the utility model provides a pair of wing, deformation device and aircraft can realize the quick deformation to the wing with comparatively light and handy structure.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An airfoil comprising a first airfoil and a second airfoil;
the first wing comprises a connecting piece and an air bag;
the connecting piece is arranged at one end of the first wing, and the air bag is arranged in the connecting piece, so that the connecting piece can be extended and deformed along with the inflation of the air bag or contracted and deformed along with the deflation of the air bag;
one end of the second wing is connected with the first wing through the connecting piece, so that when the connecting piece is subjected to extension deformation, the first wing moves away from the horizontal plane determined by the second wing along with the extension deformation of the connecting piece or moves close to the horizontal plane determined by the second wing along with the contraction deformation of the connecting piece when the connecting piece is subjected to contraction deformation.
2. The wing of claim 1, wherein the connection comprises a morphing structure and a flexible skin;
the deformation structure comprises a first supporting piece, a second supporting piece and a supporting plate;
the first supporting piece and the second supporting piece are arranged on one side of the supporting plate and are used for forming an accommodating cavity for accommodating the air bag;
one end of the flexible skin is connected with one end, far away from the supporting plate, of the first supporting piece, the other end of the flexible skin is connected with one end, far away from the supporting plate, of the second supporting piece, so that when the air bag in the accommodating cavity is inflated to cause the first supporting piece and the second supporting piece to move far away from the air bag, the flexible skin stretches, and when the air bag in the accommodating cavity is deflated to cause the first supporting piece and the second supporting piece to move close to the air bag, the flexible skin retracts.
3. The wing of claim 2, wherein the connection comprises a plurality of the morphing structures and a plurality of the bladders disposed in each of the morphing structures, wherein the plurality of morphing structures are connected end to end;
and each deformation structure controls the air bag in each deformation structure to inflate or deflate according to a control instruction.
4. The airfoil of claim 1, wherein the first airfoil includes a third airfoil and a rotor;
the third wing is rotatably arranged at one end of the first wing, which is far away from the second wing, through the rotating piece, so that the third wing can be folded to one side of the first wing.
5. The airfoil of claim 2, wherein the first airfoil includes a first side and a second side;
one end of the first side surface is connected with one end of the second side surface, and the other end of the first side surface is connected with one end, close to the first side surface, of the flexible skin;
the other end of the second side surface is connected with one end, close to the second side surface, of the supporting plate;
the included angle formed by the end connected with the first side surface and the second side surface ranges from 0 degree to 30 degrees.
6. The wing as claimed in claim 2, characterized in that the flexible skin is made of an elastic rubber material.
7. The wing as claimed in claim 2, characterized in that the support plate is made of spring steel.
8. An airfoil morphing device, wherein the airfoil morphing device comprises a controller, an electrical proportional control valve, an air compressor and the airfoil of any of claims 1 to 7;
the controller is respectively connected with the wings and the electric proportional regulating valve;
the air compressor is connected with the electric proportional regulating valve;
the controller is used for sending a control command to the electric proportional regulating valve;
and the electric proportional control valve is used for controlling the air compressor to inflate or deflate the air bag according to the control instruction.
9. The wing shape changing device of claim 8, further comprising strain gauges;
the strain gauge is arranged in the connecting piece so as to feed back the deformation state of the connecting piece.
10. An aircraft comprising an aircraft body and a wing as claimed in any one of claims 1 to 7;
the wings are arranged on two sides of the airplane and used for providing the lifting force for the airplane to fly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921408791.6U CN211001795U (en) | 2019-08-27 | 2019-08-27 | Wing, deformation device and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921408791.6U CN211001795U (en) | 2019-08-27 | 2019-08-27 | Wing, deformation device and aircraft |
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| CN211001795U true CN211001795U (en) | 2020-07-14 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110341934A (en) * | 2019-08-27 | 2019-10-18 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of wing, deformation apparatus and aircraft |
| CN113443119A (en) * | 2021-06-15 | 2021-09-28 | 中国科学院力学研究所 | Novel high-speed aircraft based on rocket range extension and control method thereof |
-
2019
- 2019-08-27 CN CN201921408791.6U patent/CN211001795U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110341934A (en) * | 2019-08-27 | 2019-10-18 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of wing, deformation apparatus and aircraft |
| CN113443119A (en) * | 2021-06-15 | 2021-09-28 | 中国科学院力学研究所 | Novel high-speed aircraft based on rocket range extension and control method thereof |
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