CN109606630B - Intelligent wing composite material trailing edge system - Google Patents
Intelligent wing composite material trailing edge system Download PDFInfo
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- CN109606630B CN109606630B CN201811306119.6A CN201811306119A CN109606630B CN 109606630 B CN109606630 B CN 109606630B CN 201811306119 A CN201811306119 A CN 201811306119A CN 109606630 B CN109606630 B CN 109606630B
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- trailing edge
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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
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
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Abstract
The invention relates to an intelligent wing composite material trailing edge system, which is characterized in that a trailing edge sensing and controlling system consists of a fiber grating sensor (18) and driving software; two ends of a pneumatic muscle driver in the rear edge driving mechanism are respectively installed and fixed on a front beam (11) and a rear beam (9) of a wing stabilizing surface, a limiting column (7) is fixed on a composite material substrate (3), and two ends of a steel cable (6) are respectively connected with the pneumatic muscle driver (13) and a rear edge strip (4) after passing through a hole of the limiting column (7); the control computer (15) is connected with the pneumatic muscle driver (13) through the electromagnetic proportional valve (21) to realize the driving of the deformation of the trailing edge structure. The invention can improve the aerodynamic efficiency of the wing structure, reduce the noise generated by the wing aerodynamics, change the camber of the wing according to the requirement of the flight state, and realize the intelligent perception and control of the wing. The realization of the invention lays an important practical foundation for the engineering verification of the trailing edge of the flexible variable camber airfoil.
Description
Technical Field
The invention belongs to the technology of a morphing aircraft structure or an intelligent airplane structure, and relates to an intelligent wing composite material trailing edge system.
Background
In recent years, with the requirements of civil aircraft on energy reduction and aircraft noise reduction and the rapid development of materials and structural technologies, which are provided by green aviation technologies, the trailing edge active surface of the aircraft wing has been gradually developed from a traditional rigid structure into a flexible structure which is seamlessly connected with the main wing, can be deformed and bears load, and is called a variable camber trailing edge structure. If the variable camber trailing edge structure also has sensing and control functions, the variable camber trailing edge structure is called an intelligent trailing edge structure, an intelligent variable camber trailing edge structure or an intelligent wing variable camber trailing edge structure. The variable camber trailing edge enables seamless, continuous, smooth, flexible, and load bearing between the wing's mainplane to the trailing edge airfoil.
For an unmanned aerial vehicle, the variable-camber trailing edge can improve the cruising ability and reduce RCSRadar cross radar scattering cross section; for a fighter, the variable camber trailing edge can improve the maneuverability, increase the range, reduce the noise during take-off and landing and reduce the RCS; for large aircraft, a variable camber trailing edge may increase its payload, increase range, etc. Therefore, the variable camber trailing edge technology has important military significance and wide application prospect.
For this reason, the flexible adaptive wing technology was listed as one of the key technologies for guaranteeing the lead position of the army in the next century in the united states as early as 80 s in the last century. The NASA implements a series of research plans such as a task Adaptive Wing MAWMission Adaptive Wing, an active Flexible Wing AFWActive Flexible Wing, an active Aeroelastic Wing AAWActive Aeroelastic Wing, an intelligent Wing SWSmart Wing, a variant Aircraft Structure MASMorphering Aircraft Structure and the like in sequence, and fully verifies the importance and the criticality of the Flexible Adaptive Wing in improving the aerodynamic performance of the Aircraft. In 2008-2015, the European Union initiated and completed the "Smart High Lift Devices for the Next Generation WingSADE" project. The feasibility of the application of the SADE plan on an airplane was verified. The project verifies the self-adaptive leading edge, the deformed trailing edge flap and the active wing tip trailing edge structure technology of civil aircraft wings in the aspect of deformed structure technology. The principle and feasibility research of the flexible structure of the wing is developed in some scientific research institutes and universities in China, and a great deal of pioneering work is done. But there is not a small distance compared to abroad. With the deep advance of civil aircraft scientific research and model work in China, advanced aviation scientific research technology is developed, and further research on the flexible trailing edge of the variable camber wing and the flexible trailing edge of the intelligent wing becomes very necessary work.
Disclosure of Invention
The invention aims to overcome the defects of the traditional deflection type wing trailing edge, improve the aerodynamic efficiency of the wing and reduce the aerodynamic noise, and provides an intelligent wing composite material trailing edge system to realize seamless, smooth and continuous deformation and bearing of the wing trailing edge.
The technical solution of the invention is as follows:
an intelligent wing composite material trailing edge system is composed of a trailing edge structure, a trailing edge driving mechanism and a trailing edge sensing and controlling system 3; the trailing edge structure comprises a composite material substrate 3, a large deformation skin 1 and a flexible honeycomb 2, wherein the composite material substrate 3 is arranged on a rear beam 9 of the wing stabilizer; the trailing edge driving mechanism comprises a pneumatic muscle driver 13, a steel cable 6 and an air source 22; the trailing edge sensing and control system consists of a fiber grating sensor 18 and driving software; two ends of a pneumatic muscle driver in the rear edge driving mechanism are respectively installed and fixed on a front beam 11 and a rear beam 9 of a wing stabilizing surface, a limiting column 7 is fixed on a composite material substrate 3, and two ends of a steel cable 6 are respectively connected with a pneumatic muscle driver 13 and a rear edge strip 4 after passing through a hole of the limiting column 7, so that the installation of a rear edge driving structure is realized; the control computer 15 is connected with the pneumatic muscle driver 13 through an electromagnetic proportional valve 21 to drive the deformation of the trailing edge structure.
Preferably, the overall layout of the trailing edge system is that the trailing edge structure is positioned at the rear part of the wing and is seamlessly connected with the wing stabilizer 19; the rear edge structure is a full-height honeycomb structure with a substrate; the pneumatic muscle driver 13 is positioned in the stabilizing surface 19, the steel cable 6 is connected with the rear edge strip 4, the position of the steel cable 6 is controlled by each limit column 7, and the pneumatic muscle driver is matched with the control computer 15 to drive the rear edge structure; the fiber grating sensor 18 is positioned in the composite material substrate 3 to realize the deformation sensing of the rear edge.
Preferably, the composite material substrate 3 is a composite material laminated plate with the fiber grating sensor 18 embedded inside, the flexible honeycomb 2 is glued on the composite material substrate 3, and the large deformation skin 1 is glued on the flexible honeycomb 2.
Preferably, the large deformation skin 1 is formed by molding spandex fibers and silicone rubber at normal temperature; wherein the mass ratio of the spandex fiber to the silicone rubber is 1:2, and the volume ratio is 1: 2.5.
Preferably, the flexible honeycomb 2 is used for supporting the large deformation skin 1, and simultaneously transmitting the aerodynamic load on the trailing edge to the substrate, the flexible honeycomb 2 generates chord-wise deformation and no span-wise deformation or generated span-wise deformation in the trailing edge structure: chordwise deformation < 0.01.
Preferably, the flexible honeycomb 2 is a 4-sided overstretched honeycomb. The mark is AC-NH, and the flexible honeycomb 2 is provided with a slot for limiting the limiting column 7.
Preferably, the composite material substrate 1 is a composite material laminated plate with the fiber grating sensor 18 embedded in the trailing edge structure or with the fiber grating sensor 18 adhered on the surface.
Preferably, the trailing edge driving mechanism utilizes the gas output by the gas source 22 to drive the pneumatic muscle driver 13 to contract, so as to drive the steel cable 6 to generate a pulling force, thereby realizing the driving function of the trailing edge driving mechanism.
The present invention has the advantages and advantageous effects that,
the invention adopts the parts of the large-deformation skin 1, the flexible honeycomb 2, the composite material substrate 3, the fiber bragg grating sensor 18, the cable connection, the pneumatic muscle driver 13 and the like, and the parts are fixed on the wing back beam 9 after being assembled and are in seamless connection with the wing stabilizing surface 19 structure, so that the wing composite material back edge structure can not only smoothly deform flexibly, but also bear the external load of the structure, and the intelligent wing composite material back edge structure is realized. The intelligent wing composite material trailing edge structure realized by the invention realizes the functions of a flexible trailing edge structure: can smooth flexible deformation can bear the external load of structure again, realized the intelligent function at flexible trailing edge simultaneously: the deformation position of the trailing edge is sensed through the fiber bragg grating, and a control signal is fed back to the control computer 15, so that the driving of the trailing edge structure is realized. The invention can improve the aerodynamic efficiency of the wing structure, reduce the noise generated by the wing aerodynamics, change the camber of the wing according to the requirement of the flight state, and realize the intelligent perception and control of the wing. And an important practical foundation is laid for the engineering verification of the trailing edge of the flexible variable camber wing.
Drawings
FIG. 1 is a schematic view of the trailing edge structure of the intelligent wing composite of the present invention.
FIG. 2 is a schematic view of an intelligent wing composite trailing edge structure and control system of the present invention.
Detailed Description
The invention is described in detail below with reference to the attached drawing figures:
1 intelligent wing composite trailing edge overall layout
The intelligent wing composite material trailing edge overall layout is that the trailing edge is positioned at the rear part of the wing and is in seamless connection with the wing stabilizer 19; the rear edge structure is a full-height honeycomb structure with a substrate; the driver is positioned in the stabilizing surface 19, the steel cable 6 is connected with the end part of the rear edge, the position of the steel cable 6 is controlled by each limit column 7, and the driver is matched with the control computer 15 to drive the rear edge; the fiber bragg grating is positioned in the composite material substrate 3 to realize the deformation perception of the rear edge.
2 trailing edge structure
The rear edge structure consists of a large deformation skin 1, a flexible honeycomb 2, a composite material substrate 3, a limiting column 7, a hoop 5, a rear edge strip 4, an angle material 8, a rear beam 9 and connecting screws and nuts.
The large deformation skin 1 is a key part of the flexible trailing edge structure. To accommodate the large deformation requirements of the flexible trailing edge, the skin is required to have a strain capacity of more than 10%. The large deformation skin 1 is formed by die pressing spandex fibers 30D and silicon rubber HT-802 at normal temperature. The mass ratio of the spandex fiber to the silicone rubber reaches 1:2, and the volume ratio reaches 1: 2.5. The strain capacity of the formed composite material large-deformation skin 1 is tested by tests and reaches about 30 percent. The modulus is 15 MPa.
The flexible honeycomb 2 is used for supporting the large deformation skin 1 and transmitting the pneumatic load on the rear edge to the substrate, and the common honeycomb cannot meet the deformation requirement of the rear edge due to the requirement of the rear edge to have larger deformation capacity. The invention adopts 4-edge overstretched honeycombs. The trade mark is AC-NH. Because the limiting columns 7 are fixed on the base plate and used for the transmission of the steel cable 6, the flexible honeycomb 2 needs to be processed and grooved, and because the flexible honeycomb 2 is difficult to process, the invention adopts an independent die and is specially used for processing and grooving the flexible honeycomb 2.
The substrate is made of carbon fiber epoxy composite material T700/BA9916, the single-layer thickness is 0.15mm, and the design thickness of the substrate is 2.0 mm. The base plate is fixed to a back beam 9 by an angle 8. The end of the base plate has a clip 5 feature for securing a wire rope 6 within the clip 5. The wire 6 carries and transmits the load of the pneumatic muscle drive 13 so that the flexible trailing edge achieves a smooth continuous deformation. A plurality of fiber grating sensors 18 are embedded in the middle of the composite material substrate 3.
The limiting columns 7 are used for limiting the position of the steel cable 6, so that the steel cable 6 is always controlled in the honeycomb processing groove when the flexible rear edge deforms. The trailing edge strip 4 may be fabricated as a metal or composite structure for maintaining the airfoil shape of the wing. The honeycomb and the skin are connected by glue joint, the connection of the flexible rear edge to the back beam 9 is mixed connection, some are connected by screws and some are connected by glue joint according to needs, and the pulley component 14, the pneumatic muscle driver 13 and the wing stabilizer 19 are connected by screws.
3 trailing edge drive mechanism
The rear edge driving part is composed of a steel cable 6, one end of which is fixed on a hoop 5 of a rear edge strip 4, and the other end of which passes through a hole of a limiting column 7 and is connected with a pneumatic muscle driver 13, a pulley component 14, the pneumatic muscle driver 13, an air flow pipeline 20, an electromagnetic proportional valve 21 and an air source 22.
The pneumatic muscle driver 13 is the key component of the trailing edge to achieve driving. The pneumatic muscle driver 13 operates on the principle that the pneumatic muscle driver 13 contracts under the pressure of the external air source 22, and the amount of contraction is related to the air pressure and the performance of the driver. The relationship between the amount of shrinkage deformation and the driving load can be determined by experiment. This relationship is generally non-linear. The air flow of the air source 22 enters the pneumatic muscle driver 13 through the electromagnetic proportional valve 21 and the air flow pipeline 20, the pneumatic muscle driver 13 contracts under the action of pressure, the steel cable 6 pulls the hoop 5 through the limiting column 7 to drive the composite material substrate 3, and downward deflection of the variable-camber flexible rear edge is realized. In the same manner, upward deflection of the variable camber flexible trailing edge can be achieved by pressurizing the upper pneumatic muscle driver 13 with air supply 22. Thereby realizing the driving function of the variable-camber flexible trailing edge.
4 trailing edge sensing and control system
The trailing edge sensing and controlling part consists of a fiber grating sensor 18, a signal collector 24, a fiber grating demodulator 25 and a control computer 15.
The deformation signal of the bending degree rear edge is collected by the signal collector 24, demodulated by the fiber grating demodulator 25, and the demodulated signal is sent to the control computer 15. And after conversion, displaying the deformation state of the trailing edge on a software interface. Further, the user controls the pneumatic muscle driver 13 through software interface input, changes the input air pressure, and realizes the adjustment control of the deformation of the trailing edge.
Corresponding parts and standard parts are produced or purchased according to the drawings and standards for assembly of the variable camber flexible trailing edge of the present invention. These parts include, on the trailing edge: the composite material comprises a composite material substrate 3, angle bars 8, limiting columns 7, a rear edge strip 4, a hoop 5, a flexible honeycomb 2 and a large-deformation composite material skin. On the stabilizer 19: pulley assembly 14, front beam 11, rear beam 9, stabilizer skin 12, rib 10, for actuation: pneumatic muscle driver 13, steel cable 6, regulating valve, air supply 22. For deformation perception: a fiber grating sensor 18, an optical fiber, a fiber signal demodulator 25, a deformation controller or a computer.
During assembly, a plurality of fiber grating sensors 18 are embedded in the middle of the composite material substrate 3 in the chord direction at equal intervals and are positioned below the uppermost first layer. The outlet of the optical fibers exits from above the faceplate. The led optical fiber is connected to the optical fiber signal demodulator 25 and the control computer 15.
A limiting column 7 is arranged on the composite material substrate 3, and a hoop 5 and a rear edge strip 4 are arranged at one end of the composite material substrate 3. An angle member 8 is attached to the other end of the composite substrate 3. The angle 8 with the composite material substrate 3 is fixed to the back beam 9.
One end of a steel cable 6 is fixed in the hoop 5, and the other end of the steel cable passes through a hole of the limiting column 7 and is led out to the outside. The optical fiber is led out to the outside, and the protection is taken. The flexible honeycomb 2 is glued and positioned on the substrate by gluing, and is placed in an autoclave for curing and molding.
And (3) connecting the large deformation skin 1 with the flexible honeycomb 2 through glue joint, and curing and molding in an oven.
The composite flexible trailing edge with the back beam 9 is thus already assembled.
The gas flow line 20 from the gas source 22 is connected to the input interface of the pneumatic muscle driver 13. The optical fiber is connected to the optical fiber signal demodulator 25, the optical fiber signal demodulator 25 is connected to the control computer 15, and the electromagnetic proportional valve 21 is connected to the control computer 15.
Thus, the intelligent wing composite material trailing edge structure with sensing and control functions is assembled.
In the course of operation,
the deformation position of the trailing edge can be displayed in real time on a trailing edge control platform or a computer. The method comprises the deformation angle, the pneumatic muscle pressure and the strain value corresponding to the fiber bragg grating.
When the trailing edge angle needs to be adjusted, the control deformation angle of the trailing edge is directly input, the electromagnetic proportional valve 21 is controlled and adjusted through software, the deformation of the trailing edge of the intelligent wing composite material can reach the specified angle, and the error is about 0.5 degrees.
Claims (5)
1. An intelligent wing composite material trailing edge system is characterized in that the trailing edge system is composed of a trailing edge structure, a trailing edge driving mechanism and a trailing edge sensing and controlling system 3; the trailing edge structure comprises a composite material substrate (3), a large deformation skin (1) and a flexible honeycomb (2), wherein the composite material substrate (3) is arranged on a rear beam (9) of the wing stabilizing surface; the rear edge driving mechanism comprises a pneumatic muscle driver (13), a steel cable (6) and an air source (22); the trailing edge sensing and control system consists of a fiber bragg grating sensor (18) and driving software; two ends of a pneumatic muscle driver in the rear edge driving mechanism are respectively installed and fixed on a front beam (11) and a rear beam (9) of a wing stabilizing surface, a limiting column (7) is fixed on a composite material substrate (3), and two ends of a steel cable (6) are respectively connected with the pneumatic muscle driver (13) and a rear edge strip (4) after passing through a hole of the limiting column (7), so that the installation of a rear edge driving structure is realized; the control computer (15) is connected with the pneumatic muscle driver (13) through an electromagnetic proportional valve (21) to realize the driving of the deformation of the trailing edge structure;
the general layout of the trailing edge system is that the trailing edge structure is positioned at the rear part of the wing and is in seamless connection with a wing stabilizer (19); the rear edge structure is a full-height honeycomb structure with a substrate; the pneumatic muscle driver (13) is positioned in the stabilizing surface (19), the steel cable (6) is connected with the rear edge strip (4), the position of the steel cable (6) is controlled by each limit column (7), and the pneumatic muscle driver is matched with the control computer (15) to drive the rear edge structure; the fiber bragg grating sensor (18) is positioned in the composite material substrate (3) to realize deformation sensing of the rear edge;
the composite material substrate (3) is a composite material laminated plate with a fiber grating sensor (18) embedded inside, the flexible honeycomb (2) is glued on the composite material substrate (3), and the large deformation skin (1) is glued on the flexible honeycomb (2); the rear edge driving mechanism utilizes the gas output by the gas source (22) to drive the pneumatic muscle driver (13) to contract, and drives the steel cable (6) to generate tension, thereby realizing the driving function of the rear edge driving mechanism.
2. The intelligent wing composite trailing edge system as claimed in claim 1, wherein the large deformation skin (1) is formed by molding spandex fibers and silicon rubber under a normal temperature condition; wherein the mass ratio of the spandex fiber to the silicone rubber is 1:2, and the volume ratio is 1: 2.5.
3. The intelligent wing composite trailing edge system according to claim 1, wherein the flexible honeycomb (2) is used for supporting a large deformation skin (1) and simultaneously transmitting aerodynamic load on the trailing edge to the substrate, and the flexible honeycomb (2) generates chord-wise deformation and no span-wise deformation or generated span-wise deformation in a trailing edge structure: chordwise deformation < 0.01.
4. The intelligent wing composite trailing edge system according to claim 3, wherein the flexible honeycomb (2) is a 4-sided polygon, the brand is AC-NH, and the flexible honeycomb (2) is provided with a slot for limiting the limit post (7).
5. The intelligent wing composite trailing edge system according to claim 1, wherein the composite substrate (3) is a composite laminate having fiber grating sensors (18) embedded in the trailing edge structure or having fiber grating sensors (18) adhered to the surface thereof.
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| CN201811306119.6A CN109606630B (en) | 2018-11-02 | 2018-11-02 | Intelligent wing composite material trailing edge system |
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| CN201811306119.6A CN109606630B (en) | 2018-11-02 | 2018-11-02 | Intelligent wing composite material trailing edge system |
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| CN109606630B true CN109606630B (en) | 2021-03-26 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111268092B (en) * | 2020-02-19 | 2023-01-06 | 南京航空航天大学 | Structure for improving torsional rigidity of trailing edge structure of flexible wing |
| CN111409816B (en) * | 2020-04-22 | 2023-02-28 | 中国飞机强度研究所 | Variable camber wing leading edge structure |
| CN111661312B (en) * | 2020-05-20 | 2022-03-29 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN113173243B (en) * | 2021-05-10 | 2023-02-28 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
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