CN111152912B - Rigidity compensation device for flexible wing and working method thereof - Google Patents
Rigidity compensation device for flexible wing and working method thereof Download PDFInfo
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- CN111152912B CN111152912B CN202010021686.8A CN202010021686A CN111152912B CN 111152912 B CN111152912 B CN 111152912B CN 202010021686 A CN202010021686 A CN 202010021686A CN 111152912 B CN111152912 B CN 111152912B
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- 230000036316 preload Effects 0.000 claims description 16
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The invention discloses a rigidity compensation device for a flexible wing and a working method thereof, belonging to the technical field of aviation structure design. After the thrust is transmitted to the preloading device by using the motion conversion device, the preloading device is used for realizing the compensation of the torsional rigidity of the flexible wing and the active torsion control; the device can avoid aeroelasticity divergence, and can actively control the torsion deformation of the wing through the device to enhance the aerodynamic performance.
Description
Technical Field
The invention belongs to the technical field of aviation structure design, and relates to a rigidity compensation device for a flexible wing and a working method thereof.
Background
In recent years, with the continuous development of scientific technology, the emergence of new intelligent materials and the improvement of structural design ideas, scientists begin to integrate the technologies of intelligent materials, novel structures, efficient actuators, advanced sensors and the like into the airframe structure of an airplane, and a morphing airplane also enters an intelligent flexible deformation stage from a rigid deformation stage.
Compared with rigid wing deformation, flexible wings deform faster and have larger deformation capacity, and can change shapes smoothly and continuously, so intelligent flexible deformation gradually becomes a research hotspot. Due to the adoption of the flexible wing, the torsional rigidity of the wing is greatly reduced, the aeroelasticity of the wing is easily dispersed, and the flutter of the wing is caused. The invention is developed in order to solve the problem of insufficient torsional rigidity of the flexible wing.
Disclosure of Invention
The invention provides a method for compensating torsional rigidity of a flexible wing through a rigidity compensation device in order to solve the problem of insufficient torsional rigidity of the flexible wing, the torsional rigidity of the wing is designed, the torsional rigidity of the flexible wing is effectively increased, and meanwhile, the device can be used for actively controlling torsional deformation of the wing to enhance the aerodynamic performance.
The invention is realized by the following steps:
a rigidity compensation device for a flexible wing comprises a fuselage, wherein the fuselage is provided with the rigidity compensation device, and the rigidity compensation device comprises a preloading application device and a motion conversion device fixedly arranged on the top of the preloading application device. The motion conversion device is used for converting linear motion and rotary motion. The preload application means provides stiffness compensation on the one hand and pretension on the other hand. The bottom of the motion conversion device is sleeved on the top of the preload application device, and the motion conversion device and the preload application device are tightly matched together and fixed through screws.
The motion conversion device comprises an outer cylinder, a threaded sleeve is arranged at the top end of the outer cylinder, a thrust bearing is arranged at an opening at the top end of the outer cylinder, and the axial displacement of the threaded sleeve is limited through the matching of the outer cylinder and the thrust bearing; a screw rod is arranged in the internal thread of the screw sleeve;
an upper piston plate and a lower piston plate are respectively arranged in the preloading device; a spring is arranged between the upper piston plate and the lower piston plate, and a positioning pin and a positioning hole are arranged between the upper piston plate and the lower piston plate to ensure that the axes of the upper piston plate and the lower piston plate are superposed; the space formed by the lower piston plate and the bottom of the preloading applying device is filled with oil liquid; the motion conversion device is connected with the upper piston plate in the preloading application device through a screw rod, so that force transmission is realized.
Furthermore, the rigidity compensation device is connected with a plurality of wing ribs by utilizing hollow composite pipes; the rib at the wing root is connected with the motion conversion device of the rigidity compensation device; one end of the hollow composite pipe is connected with the threaded sleeve of the motion conversion device, and the other end of the hollow composite pipe is connected with the wing rib adjacent to the wing rib at the root part. The rigidity compensation device is arranged at the joint of the fuselage and the wing root, and the outer cylinder of the rigidity compensation device is fixedly connected with the root wing rib.
Further, the top of the preload applying device is sleeved at the bottom of the motion conversion device, and the preload applying device is fixedly connected with the outer cylinder of the motion conversion device through a screw.
Furthermore, the preloading applying device is provided with an oil inlet nozzle outside the oil filled with the oil, and the oil inlet nozzle adjusts the hydraulic pressure of the oil through connecting an oil conveying pipe.
Furthermore, the screw is provided with a guide plate and a guide groove, and the rotary motion of the screw is limited through the guide plate and the guide groove.
The invention also discloses a working method of the rigidity compensation device for the flexible wing, which is characterized in that the rigidity compensation and the active control of torsional deformation are realized by the cooperation of the preloading applying device and the motion conversion device in the method, and the method comprises the following specific steps:
the motion conversion device mainly realizes the mutual conversion of rotary motion and linear motion, the torque received between adjacent wing ribs of the wing is converted into thrust, the torque is transmitted to the stiffness compensation device of the wing root through the hollow composite pipe and then is transmitted to the motion conversion device firstly, the torque acts on the screw sleeve and drives the screw sleeve to rotate, and the screw cannot rotate because the screw is limited by the guide plate and the guide groove, so that the thrust along the axial direction is generated between the screw and the screw sleeve; the screw sleeve is limited by the outer cylinder and the thrust bearing in axial displacement, and the thrust pushes the screw rod to generate axial displacement, so that the conversion of rotary motion and linear motion is realized, and the conversion of torque on the wing into thrust is also realized.
In the process of motion conversion, the thread lead angle of the screw pair is designed to avoid screw self-locking, so that the moment generated by twisting the wing at a certain angle corresponds to the thrust generated by each axial displacement of the screw.
The working method of the preloading applying device comprises the following steps: after the motion conversion device transmits the thrust to the preloading application device, the thrust is transmitted to the upper piston plate, the upper piston plate transmits the thrust to the spring, the spring is compressed, the torque generated by the unit torsion angle of the flexible wing corresponds to the thrust generated by the unit displacement of the spring, and the torsional rigidity of the flexible wing corresponds to the compressive rigidity of the spring. In order to ensure that the thrust generated by the unit displacement of the spring is equivalent to the torque generated by the unit torsion angle of the wing, a certain pretightening force needs to be applied to the spring, and the hydraulic pressure needs to be adjusted through an oil delivery port at the bottom so as to adjust the thrust generated by the unit displacement of the spring. Meanwhile, the rigidity of the spring is reasonably designed according to factors such as required compensation rigidity, lead angle and the like.
When the wing needs rigidity compensation, the lower piston plate is in contact with oil, the amount of the oil is adjusted by increasing hydraulic pressure, the lower piston plate is driven to compress the spring, the generated elastic force is transmitted to the screw rod through the upper piston plate, then the elastic force is converted into torque through the motion conversion device, the torque is balanced with the torque generated between adjacent wing ribs under the action of aerodynamic force, the thrust generated by the unit displacement of the spring corresponds to the torque generated by the unit torsion angle of the wing, the torsional rigidity of the flexible wing corresponds to the compressive rigidity of the spring, and therefore the torsional rigidity of the flexible wing is compensated;
when active torsion control is needed to be carried out on the wing, the axes of the upper piston plate and the lower piston plate are always coincident by adjusting the hydraulic pressure of oil liquid through the positioning pins and the positioning holes, then the upper piston plate and the lower piston plate are gradually close to each other and finally contact each other, the piston plate is pushed by the hydraulic pressure and is transmitted to the motion conversion device, linear motion is converted into rotary motion by the motion conversion device, thrust is converted into torque and is transmitted to the hollow composite pipe, relative torsion is generated between adjacent wing ribs, and therefore the wing torsion is actively controlled.
The beneficial effects of the invention and the prior art are as follows:
the invention provides a device for compensating torsional rigidity of a flexible wing through a rigidity compensation device, realizing rigidity compensation and actively controlling torsional deformation through the rigidity compensation device, which mainly comprises two parts, namely a motion conversion device and a preloading application device, and realizing mutual conversion of rotary motion and linear motion through the motion conversion device so as to convert torque applied between adjacent wing ribs of the wing into thrust. After the thrust is transmitted to the preloading device by using the motion conversion device, the preloading device is used for realizing the compensation of the torsional rigidity of the flexible wing and the active torsion control; the device can avoid aeroelasticity divergence, and can actively control the torsion deformation of the wing through the device to enhance the aerodynamic performance.
Drawings
FIG. 1 is a schematic view of a wing structure in a stiffness compensation device for a flexible wing according to the present invention;
FIG. 2 is a schematic diagram of a motion conversion device in a stiffness compensation device for a flexible wing according to the present invention;
FIG. 3 is a schematic view of a preload application apparatus for use in a stiffness compensation apparatus for a flexible wing according to the present invention;
the device comprises a machine body 1, a stiffness compensation device 2, a thread sleeve 3, a hollow composite pipe 4, a wing rib 5, an oil conveying pipe 6, a thrust bearing 7, an outer cylinder 8, a screw rod 9, a guide plate 10, a guide groove 11, a screw 12, a preload applying device 13, an upper piston plate 14, a lower piston plate 15, an oil inlet nozzle 16, oil 17, a positioning pin 18, a positioning hole 19 and a spring 19.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention more clear, the present invention is further described in detail by the following examples. It should be noted that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1, the invention comprises a fuselage 1, wherein a stiffness compensation device 2 is arranged in the fuselage 1, and a plurality of wing ribs 5 are connected behind the stiffness compensation device 2 by using hollow composite pipes 4; the rib 5 at the wing root is connected to the motion conversion means of the stiffness compensation means 2.
As shown in fig. 2 to 3, the stiffness compensation device 2 of the present invention includes a preload application device 13 and a motion conversion device fixedly installed on top of the preload application device 13.
The motion conversion device is composed of a threaded sleeve 3, a thrust bearing 7, a screw rod 9, a guide plate 10, a guide groove 11 and the like and is responsible for converting linear motion and rotary motion; the preload applying device comprises an upper piston plate 14, a lower piston plate 15, a spring 19, oil 17 and the like, and the motion conversion device provides rigidity compensation on one hand and can provide pre-tightening force on the other hand. The top of the preload application device fits over the bottom of the motion conversion device and the two fit together tightly and are secured by screws 12.
In order to reduce the load of the wing, the rigidity compensation device 2 can be arranged at the joint of the fuselage 1 and the wing root, and the outer cylinder 8 of the rigidity compensation device is fixedly connected with the root rib. One end of the hollow composite pipe 4 is connected with the threaded sleeve 3 of the rigidity compensation device, and the other end of the hollow composite pipe is connected with the adjacent wing ribs of the wing ribs at the root part and used for transmitting torque between the adjacent wing ribs. Because the wing pressure center and the rigid center are not overlapped, when the wing is subjected to external aerodynamic force, torque can be generated between adjacent wing ribs, and in order to prevent the wing from twisting under the action of the torque, the torque is balanced by the rigidity compensation device, so that the torsional rigidity compensation of the flexible wing is realized. The working method of the rigidity compensation device for the flexible wing comprises the following specific steps:
in the preload application device, by increasing the amount of hydraulic pilot oil, the lower piston plate 15 is brought to compress the spring 19 and transmit the generated elastic force to the screw 9 of the motion conversion device through the upper piston plate 14. Because the screw 9 is connected with the screw sleeve 3 through thread matching, the screw sleeve 3 is limited in axial displacement, and the screw 9 is limited in rotary motion by the guide plate 10 and the guide groove 11, under the action of thrust, the screw sleeve can reversely rotate through thread matching to output torsional moment, and the torsional moment is transmitted to adjacent wing ribs through the hollow composite material pipe 4, so that the thrust generated by the unit displacement of the spring corresponds to the torque generated by the unit torsion angle of the wing, the torsional rigidity of the flexible wing corresponds to the compressive rigidity of the spring, and the compensation of the torsional rigidity of the flexible wing is realized.
By adjusting the amount of oil, the bottom piston plate can be driven to compress the spring, so that the adjustment of the anti-torsion rigidity compensation is realized, for example: because the elastic force generated when the spring is compressed at the beginning is smaller, the thrust generated by unit displacement is smaller, and the thrust generated by unit displacement is possibly insufficient to balance the torque generated by unit rotation angle, the spring can be pre-compressed by increasing hydraulic pressure, so that the thrust generated by unit displacement of the spring at the beginning is increased, and the rigidity compensation capacity of the spring is enhanced; similarly, the rigidity compensation capacity of the device can be adjusted at the later stage by adjusting the hydraulic pressure.
When active torsion control is needed to be carried out on the wing, through increasing the hydraulic pressure of the preloading device, the piston rods of the upper piston plate and the lower piston plate can be ensured to be always coincident through the positioning pins and the positioning holes 18, so that the upper piston rod and the lower piston rod can be gradually close to each other and finally contact with each other, the hydraulic pressure is continuously increased, the oil liquid can push the piston plates to transmit thrust to the motion conversion device, axial displacement is limited by the outer cylinder 8 and the thrust bearing 7 through the threaded sleeve 3, the threaded rod 9 is limited by the guide plate 10 and the guide groove 11 and cannot rotate, the threaded sleeve 3 can reversely rotate through threaded matching under the action of the thrust, torsion moment is output, the torque is transmitted to adjacent wing ribs through the hollow composite material pipe 4, the adjacent wing ribs of the wing are relatively twisted, and active control on the torsion deformation of the wing is realized.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.
Claims (6)
1. A rigidity compensation device for a flexible wing comprises a fuselage (1), and is characterized in that a rigidity compensation device (2) is arranged in the fuselage (1), and the rigidity compensation device (2) comprises a preloading application device (13) and a motion conversion device fixedly arranged on the top of the preloading application device (13);
the motion conversion device comprises an outer cylinder (8), a threaded sleeve (3) is arranged at the top end of the outer cylinder (8), a thrust bearing (7) is arranged at an opening at the top end of the outer cylinder (8), and the axial displacement of the threaded sleeve (3) is limited through the matching of the outer cylinder (8) and the thrust bearing (7); a screw rod (9) is arranged in the internal thread of the screw sleeve (3);
an upper piston plate (14) and a lower piston plate (15) are respectively arranged in the preloading device (13); a spring (19) is arranged between the upper piston plate (14) and the lower piston plate (15), and a positioning pin and a positioning hole (18) are arranged between piston rods of the upper piston plate (14) and the lower piston plate (15) to ensure that the axes of the upper piston plate (14) and the lower piston plate (15) are superposed; the space formed by the lower piston plate (15) and the bottom of the preloading applying device (13) is filled with oil (17);
the motion conversion device is connected with an upper piston plate (14) in a preloading device (13) through a screw rod (9) to realize force transmission.
2. A stiffness compensation device for a flexible wing according to claim 1, characterized in that the stiffness compensation device (2) is installed at the connection of the fuselage (1) and the wing root, and the outer cylinder (8) of the stiffness compensation device is fixedly connected with the root rib; the rigidity compensation device (2) is connected with a plurality of wing ribs (5) by hollow composite pipes (4); the rib (5) at the wing root is connected with the motion conversion device of the rigidity compensation device (2); one end of the hollow composite pipe (4) is connected with the threaded sleeve (3) of the motion conversion device, and the other end of the hollow composite pipe is connected with the wing rib adjacent to the wing rib at the root part.
3. A stiffness compensation device for a flexible wing according to claim 1, wherein the top of the preload application device (13) is fitted over the bottom of the motion conversion device and the preload application device (13) is fixedly connected to the outer cylinder (8) of the motion conversion device by means of screws (12).
4. A stiffness compensating device for a flexible wing according to claim 1, characterised in that the preload application means (13) is provided with an oil inlet nipple (16) on the outside filled with oil (17), the oil inlet nipple (16) being adapted to regulate the oil pressure by connecting an oil delivery pipe (6).
5. A stiffness compensating device for a flexible wing according to claim 1, characterised in that the screw (9) is provided with a guide plate (10) and a guide groove (11).
6. The method for operating the stiffness compensation device for the flexible wing according to any one of claims 1 to 5, wherein the stiffness compensation and the active control of the torsional deformation are realized by the cooperation of the preload application device and the motion conversion device, and the method comprises the following steps:
the motion conversion device mainly realizes the mutual conversion of rotary motion and linear motion, the torque received between adjacent wing ribs of the wing is converted into thrust, the torque is transmitted to the stiffness compensation device of the wing root through the hollow composite pipe (4), and then is transmitted to the motion conversion device firstly, and acts on the threaded sleeve (3) to drive the threaded sleeve (3) to rotate, and because the screw rod (9) is limited by the guide plate (10) and the guide groove (11), the screw rod (9) cannot rotate, the thrust along the axial direction is generated between the screw rod (9) and the threaded sleeve (3); the screw sleeve (3) is limited by the outer cylinder (8) and the thrust bearing (7) to move axially, and the thrust pushes the screw rod (9) to move axially, so that the conversion of rotary motion and linear motion is realized, and the conversion of the torque borne by the wing into the thrust is also realized;
the working method of the preloading application device comprises the following steps: after the motion conversion device transmits the thrust to the preloading application device, the thrust is transmitted to the upper piston plate (14) firstly, the upper piston plate (14) is transmitted to the spring, the spring (19) is compressed, the torque generated by the unit torsion angle of the flexible wing corresponds to the thrust generated by the unit displacement of the spring, and the torsional rigidity of the flexible wing corresponds to the compressive rigidity of the spring;
when the wing needs rigidity compensation, the lower piston plate (15) is in contact with oil (17), the amount of the oil is adjusted by increasing hydraulic pressure, the lower piston plate (15) is driven to compress the spring, the generated elastic force is transmitted to the screw (9) through the upper piston plate (14), then the elastic force is converted into torque through the motion conversion device, the torque is balanced with the torque generated between adjacent wing ribs under the action of aerodynamic force, the thrust generated by the unit displacement of the spring corresponds to the torque generated by the unit torsion angle of the wing, and the torsional rigidity of the flexible wing corresponds to the compressive rigidity of the spring, so that the torsional rigidity of the flexible wing is compensated;
when active torsion control is needed to be carried out on the wing, the hydraulic pressure of oil (17) is adjusted, the upper piston plate (14) and the lower piston plate (15) ensure that the axes of the upper piston plate and the lower piston plate are always coincident through the positioning pin and the positioning hole (18), then the upper piston plate and the lower piston plate are gradually close to each other and finally contact with each other, the piston plates are pushed by the hydraulic pressure and transmitted to the motion conversion device, linear motion is converted into rotary motion through the motion conversion device, thrust is converted into torque and transmitted to the hollow composite pipe (4), relative torsion is generated between adjacent wing ribs, and therefore the wing torsion is actively controlled.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010021686.8A CN111152912B (en) | 2020-01-09 | 2020-01-09 | Rigidity compensation device for flexible wing and working method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010021686.8A CN111152912B (en) | 2020-01-09 | 2020-01-09 | Rigidity compensation device for flexible wing and working method thereof |
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| CN111152912B true CN111152912B (en) | 2022-06-10 |
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| CN112550664B (en) * | 2020-12-09 | 2022-10-18 | 西北工业大学 | Variable camber wing structure based on shape memory alloy drive |
| CN112572763B (en) * | 2020-12-09 | 2022-10-18 | 西北工业大学 | Reversing mechanism for bidirectional variable trailing edge wing |
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| CN106741845B (en) * | 2017-02-10 | 2019-01-18 | 哈尔滨工业大学 | A kind of empty amphibious aircraft wing distressed structure of water |
| CN109131835A (en) * | 2018-09-07 | 2019-01-04 | 佛山皖和新能源科技有限公司 | A kind of adjustable wing structure of fixed-wing unmanned plane |
| CN109484625A (en) * | 2019-01-02 | 2019-03-19 | 南昌航空大学 | A kind of aircraft of wing variable rigidity |
| CN110294101B (en) * | 2019-05-20 | 2022-06-10 | 南京航空航天大学 | Auxiliary driving mechanism for folding wing and using method thereof |
| CN110294099B (en) * | 2019-05-20 | 2022-04-22 | 南京航空航天大学 | Folding wing auxiliary driving device based on solid-liquid mixed spring |
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