阅读说明：本技术 一种用于旋翼桨叶的埋入式传感器的粘接方法及旋翼桨叶 (Bonding method of embedded sensor for rotor blade and rotor blade ) 是由 周国臣 韩东 刘政 林长亮 于 2020-06-09 设计创作，主要内容包括：本发明实施例公开了一种用于旋翼桨叶的埋入式传感器的粘接方法及旋翼桨叶,涉及旋翼桨叶动载荷技术领域,能够提高旋翼桨叶动载荷测试数据的可靠性,且易于长时间使用。本发明包括：采用上层胶膜(3)和下层胶膜(5)夹持光纤光栅传感器(2),其中,上层胶膜(3)和下层胶膜(5)中嵌入有支撑载体；将光纤光栅传感器(2)固定在旋翼桨叶(1)的内部,且对应桨叶表面蒙皮(4)下方的指定位置；调整上层胶膜(3)和下层胶膜(5),与光纤光栅传感器(2)在旋翼桨叶(1)内部的铺放轨迹相同；将旋翼桨叶(1)通过加温模压固化成形。本发明适用于旋翼桨叶动载荷测试。(The embodiment of the invention discloses a bonding method of an embedded sensor for a rotor blade and the rotor blade, which relate to the technical field of dynamic load of the rotor blade, can improve the reliability of the test data of the dynamic load of the rotor blade and are easy to use for a long time. The invention comprises the following steps: the fiber grating sensor (2) is clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5), wherein a support carrier is embedded in the upper-layer adhesive film (3) and the lower-layer adhesive film (5); fixing the fiber bragg grating sensor (2) in the rotor blade (1) and corresponding to a designated position below the blade surface skin (4); adjusting an upper-layer adhesive film (3) and a lower-layer adhesive film (5) to be the same as the laying track of the fiber grating sensor (2) in the rotor blade (1); the rotor blade (1) is formed by heating, mould pressing and curing. The invention is suitable for testing the dynamic load of the rotor blade.)

1. A method of bonding a buried sensor for a rotor blade, comprising:

the fiber grating sensor (2) is clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5), wherein a support carrier is embedded in the upper-layer adhesive film (3) and the lower-layer adhesive film (5);

fixing the fiber bragg grating sensor (2) in the rotor blade (1) and corresponding to a designated position below the blade surface skin (4);

adjusting an upper-layer adhesive film (3) and a lower-layer adhesive film (5) to be the same as the laying track of the fiber grating sensor (2) in the rotor blade (1);

the rotor blade (1) is formed by heating, mould pressing and curing.

2. Method according to claim 1, characterized in that the rotor blade (1) is made of a composite material, and that the upper adhesive film (3) and the lower adhesive film (5) are made of the same matrix resin system as the composite material of the rotor blade (1) and have the same curing temperature and time characteristics.

3. The method according to claim 1, wherein said curing the rotor blade (1) by warm compaction comprises:

in the process of heating and mould pressing of the rotor blade (1), solid resin contained in the upper adhesive film (3) and the lower adhesive film (5) is melted into glue solution;

and a local poor glue area near the fiber grating sensor (2) is filled by the melted glue solution.

4. A method as claimed in claim 3, characterised in that the internal supporting carriers of the upper adhesive film (3) and of the lower adhesive film (5) are of cotton material;

the support carriers are woven into a grid shape.

5. A method as claimed in claim 4, characterized in that the support carriers in the upper adhesive film (3) and the lower adhesive film (5) are present in an amount of less than 5% by weight of each adhesive film.

6. The method according to claim 4, wherein the adjusting of the upper adhesive film (3) and the lower adhesive film (5) is the same as the laying trajectory of the fiber grating sensor (2) inside the rotor blade (1), and comprises:

after surface skin cloth of a rotor blade (1) is laid in a blade forming die, a fiber grating sensor (2) clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5) is laid at a specified position below the corresponding blade surface skin (4) according to a specified track path;

and continuously laying the composition structure of the rotor blade (1), and then heating, molding, curing and forming.

7. A rotor blade, comprising:

the fiber bragg grating sensor (2) is fixed inside the rotor blade (1) and corresponds to a designated position below the blade surface skin (4);

the fiber grating sensor (2) is covered by solid resin formed by heating, mould pressing and curing the upper adhesive film (3) and the lower adhesive film (5);

the upper adhesive film (3) and the lower adhesive film (5) adopt a matrix material resin system which is the same as that of the composite material of the rotor blade (1) and have the same curing temperature and time characteristics.

8. The method according to claim 7, characterized in that the internal supporting carriers of the upper adhesive film (3) and the lower adhesive film (5) are of cotton material.

9. The method according to claim 8, wherein the support carriers in the upper adhesive film (3) and the lower adhesive film (5) are present in an amount of less than 5% by weight of each adhesive film.

Technical Field

The invention relates to the technical field of rotor blade dynamic load testing, in particular to a bonding method of an embedded sensor for a rotor blade and the rotor blade.

Background

The method is an important basis for making a load spectrum of the rotor blade and determining the service life of the blade, and is also an effective method for monitoring the use state of the rotor blade of the helicopter. At present, the traditional strain gauge type sensor measuring method is used for measuring the dynamic load of the helicopter rotor blade, the strain gauge is pasted at the designated position on the surface of the blade, and the structural load borne by the specific position of the helicopter rotor blade is obtained by monitoring the resistance value change of the strain gauge in the flight process of a helicopter.

In practical application, the strain gauge sensor is adhered to the outer surface of a blade, a quick-drying adhesive is generally adhered to a position, needing load measurement, of the blade, the strain gauge sensor transmits power and signals through a metal wire, in order to reduce power damage and distortion of a connecting wire, the diameter of the connecting metal wire (including a plastic protective layer) of a common strain gauge sensor is larger than 1mm, the strain gauge connecting wire needs to form a bundle and is converged to the root of the blade along the expansion direction of the blade, vibration is generated in the flying process of the blade, in order to ensure reliable adhesion and communication of the strain gauge and the connecting wire, the strain gauge and the connecting wire are generally completely covered by structural adhesive and are firmly fixed on the outer surface of the rotor blade, and the strain gauge and the connecting wire are ensured not to be separated and fall off in the flying measurement process.

However, the addition of the strain gauge, the connecting wire and the structural adhesive on the surface of the blade has certain influence on the aerodynamic appearance of the rotor blade, and the mass distribution characteristic of the rotor blade is slightly changed. The change of the aerodynamic shape and the mass characteristic of the rotor blade can lead to the accuracy of the actual measurement load of the rotor blade in flight to be reduced to a certain extent. Therefore, in the long-time test process, the deformation of the strain gauge and the connecting wire on the surface is caused by the rotation of the paddle, so that the error of test data is finally increased, and after the long-time test, the phenomena of looseness and falling of the strain gauge, the connecting wire and the structural adhesive can also occur, so that the test for a longer time is difficult to realize.

Disclosure of Invention

The embodiment of the invention provides a bonding method of an embedded sensor for a rotor blade and the rotor blade, which can improve the reliability of dynamic load test data of the rotor blade and are easy to use for a long time.

In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:

in a first aspect, an embodiment of the present invention provides a method, including:

the fiber grating sensor (2) is clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5), wherein a support carrier is embedded in the upper-layer adhesive film (3) and the lower-layer adhesive film (5); fixing the fiber bragg grating sensor (2) in the rotor blade (1) and corresponding to a designated position below the blade surface skin (4); adjusting an upper-layer adhesive film (3) and a lower-layer adhesive film (5) to be the same as the laying track of the fiber grating sensor (2) in the rotor blade (1); the rotor blade (1) is formed by heating, mould pressing and curing.

The rotor blade (1) is made of composite materials, and the upper-layer adhesive film (3) and the lower-layer adhesive film (5) are made of resin systems which are the same as the matrix materials of the composite materials of the rotor blade (1) and have the same curing temperature and time characteristics.

The rotor blade (1) is formed by heating, mould pressing and curing, and the method comprises the following steps: in the process of heating and mould pressing of the rotor blade (1), solid resin contained in the upper adhesive film (3) and the lower adhesive film (5) is melted into glue solution; and a local poor glue area near the fiber grating sensor (2) is filled by the melted glue solution.

Placing a blade forming mold on a vibration table and carrying out heating mold pressing; after the solid resin contained in the upper adhesive film (3) and the lower adhesive film (5) is melted into adhesive liquid, the vibration table is triggered to vibrate or rotate according to a specified inclination angle.

The internal supporting carriers of the upper adhesive film (3) and the lower adhesive film (5) are made of cotton materials; the support carriers are woven into a grid shape.

The supporting carriers in the upper adhesive film layer (3) and the lower adhesive film layer (5) account for less than 5% of each adhesive film layer by weight.

Adjust upper rubber film (3) and lower floor's rubber film (5), it is the same with fiber grating sensor (2) at the inside track of laying of rotor blade (1), include: after surface skin cloth of a rotor blade (1) is laid in a blade forming die, a fiber grating sensor (2) clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5) is laid at a specified position below the corresponding blade surface skin (4) according to a specified track path; and continuously laying the composition structure of the rotor blade (1), and then heating, molding, curing and forming.

In a second aspect, embodiments of the present invention provide a rotor blade comprising:

the fiber bragg grating sensor (2) is fixed inside the rotor blade (1) and corresponds to a designated position below the blade surface skin (4); the fiber grating sensor (2) is covered by solid resin formed by heating, mould pressing and curing the upper adhesive film (3) and the lower adhesive film (5); the upper adhesive film (3) and the lower adhesive film (5) adopt a matrix material resin system which is the same as that of the composite material of the rotor blade (1) and have the same curing temperature and time characteristics.

Wherein, the internal supporting carriers of the upper adhesive film (3) and the lower adhesive film (5) are made of cotton materials. The supporting carriers in the upper adhesive film layer (3) and the lower adhesive film layer (5) account for less than 5% of each adhesive film layer by weight.

The embodiment of the invention provides a bonding method for an embedded sensor of a rotor blade and the rotor blade, and a positioning bonding method for the embedded fiber bragg grating sensor for measuring the dynamic load of the composite material rotor blade, wherein the method comprises the following steps: the fiber grating sensor is clamped in the middle by the upper layer and the lower layer of adhesive films with certain widths and provided with supporting carriers, and is accurately positioned at the specified position inside the composite material rotor blade of the helicopter by the characteristics of the adhesive films, so that the fiber grating sensor keeps an ideal shape, and the reliable measurement of the dynamic load of the composite material rotor blade of the helicopter is realized. Therefore, in practical application, the fiber grating sensors can be well positioned and embedded in the rotor blades of the helicopter, the dynamic load test data of the rotor blades are real and reliable, and the rotor blades are easy to use for a long time.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic view of a helicopter composite rotor blade with embedded fiber grating sensors according to an embodiment of the present invention;

FIG. 2 is an exploded view of a composite fiber grating sensor embedded rotor blade of a helicopter according to an embodiment of the present invention;

FIG. 3 is a schematic view of a partial explosion at the root of a composite material rotor blade of a helicopter embedded with a fiber grating sensor according to an embodiment of the present invention;

FIG. 4 is an exploded view of a typical cross-section of a composite fiber grating sensor embedded rotor blade of a helicopter in accordance with an embodiment of the present invention;

wherein, 1 represents the rotor blade, 2 represents the fiber grating sensor, 3 represents the upper rubber coating, 4 represents blade top skin, and 5 represents the lower rubber coating.

Detailed Description

In order to make the technical solutions of the present invention better understood, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention. As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. It will be understood that when an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may also be present. Further, "connected" or "coupled" as used herein may include wirelessly connected or coupled. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

The design purpose of the embodiment of the invention is as follows: the method can ensure that the embedded fiber bragg grating sensor is accurately positioned in the blade, keeps the shape closest to a straight line, and monitors and measures the load of the rotor blade when the helicopter flies more truly and accurately.

An embodiment of the present invention provides a method for bonding an embedded sensor for a rotor blade, as shown in fig. 1 to 4, including:

the fiber grating sensor (2) is clamped by an upper adhesive film (3) and a lower adhesive film (5), wherein a support carrier is embedded in the upper adhesive film (3) and the lower adhesive film (5).

The fiber bragg grating sensor (2) is fixed inside the rotor blade (1) and corresponds to a designated position below the blade surface skin (4).

And adjusting the upper-layer adhesive film (3) and the lower-layer adhesive film (5) to be the same as the laying track of the fiber grating sensor (2) in the rotor blade (1).

The rotor blade (1) is formed by heating, mould pressing and curing.

The fiber grating sensor detects changes in physical quantities such as temperature and strain by detecting changes in wavelength. The fiber grating sensor consists of a fiber core, a cladding and a coating layer, wherein the main component of the fiber core of the fiber is silicon dioxide, in addition, the fiber core contains trace germanium dioxide and is used for improving the refractive index of the fiber core, the fiber core and the cladding form a total internal reflection condition to limit light in the fiber core, the diameter of the fiber core of the single-mode fiber used for writing the grating is 9 micrometers, the main component of the cladding is also silicon dioxide, and the diameter of the cladding is 125 micrometers. The coating layer is generally made of high polymer materials such as epoxy resin, polyimide, silicon rubber and the like, has an outer diameter of 250 micrometers, and is used for enhancing the flexibility, mechanical strength and ageing resistance of the optical fiber. The fiber grating sensor takes optical signals as a measurement signal source, the anti-electromagnetic interference capability is strong, the measurement precision is high, and the single optical fiber can realize the online measurement of the strain of a plurality of nodes. Fiber grating sensors have a wide range of uses and usage requirements. Fiber grating strain sensors have great advantages over conventional resistive strain sensors.

In this embodiment, the rotor blade (1), the upper adhesive film (3), the blade surface skin (4) and the lower adhesive film (5) are all made of conforming materials. The rotor blade (1) is made of composite materials, and the upper-layer adhesive film (3) and the lower-layer adhesive film (5) are made of resin systems which are the same as the matrix materials of the composite materials of the rotor blade (1) and have the same curing temperature and time characteristics. For example: the glue films (3) (5) have the same matrix material resin system as the composite material used for the composite material rotor blade (1) and have the same curing temperature and time characteristics. During the heating, mould pressing and curing process of the composite material rotor blade (1), the contained solid resin can be melted into glue liquid flowing and forms a stable solid form together with the reinforced fiber material when the curing process is finished, and in the process, the poor glue phenomenon with little local glue liquid often appears in the composite material rotor blade (1), which is a common phenomenon of composite material products.

Further, the rotor blade (1) is solidified and formed by heating and mould pressing, and the method comprises the following steps: in the process of heating and mould pressing of the rotor blade (1), solid resins contained in the upper-layer adhesive film (3) and the lower-layer adhesive film (5) are melted into adhesive liquid, and the local adhesive-poor area near the fiber grating sensor (2) is filled.

Specifically, in the heating and die pressing process of the composite material rotor blade (1), solid resin contained in the upper-layer adhesive film (3) and the lower-layer adhesive film (5) can be melted into adhesive liquid to flow, and a local poor adhesive area of the composite material near the fiber grating sensor (2) embedded in the composite material rotor blade (1) is filled, so that the manufacturing quality of the composite material rotor blade (1) at the load measuring position of the fiber grating sensor (2) is improved, the optimal adhesive effect of the composite material structure of the fiber grating sensor (2) and the composite material rotor blade (1) is ensured, and the load of the composite material rotor blade (1) is measured really and effectively through monitoring.

The upper-layer glue film (3) and the lower-layer glue film (5) are provided with supporting carriers, in the heating, die pressing and curing process of the composite material rotor blade (1), solid resin of the upper-layer glue film (3) and the lower-layer glue film (5) can become glue solution and flow, but the supporting carriers contained in the glue films (3) (5) cannot move, and the relative positions between the supporting carriers of the glue films (3) (5) and the fiber grating sensor (2) can be kept unchanged, so that the glue films (3) (5) with the supporting carriers can ensure the positioning of the fiber grating sensor (2) in the heating, die pressing and curing process of the composite material rotor blade (1).

In a preferable scheme, the internal supporting carriers of the upper adhesive film layer (3) and the lower adhesive film layer (5) are made of cotton materials. The support carrier is woven into a grid shape. The supporting carriers in the upper adhesive film layer (3) and the lower adhesive film layer (5) account for less than 5% of each adhesive film layer by weight. Wherein, the weight content in the adhesive films (3) and (5) is less than 5 percent, thus the influence on the local section characteristics of the composite material rotor blade (1), such as rigidity, mass characteristics and the like, can be almost ignored.

Further, the glue films (3) and (5) have a certain width, so that the glue melting liquid of the glue films (3) and (5) can sufficiently fill up the poor glue defect of the composite material in the composite material rotor blade (1), and the positioning and bonding of the fiber grating sensor (2) are ensured. For example: an SD-24 YIII type epoxy resin medium-temperature adhesive film with a supporting carrier is adopted, a long strip-shaped 2 strips with the width of 10mm are cut according to the specified position and track path, and the fiber grating sensor is respectively clamped at the upper part and the lower part.

In this embodiment, the adjusting upper rubber film (3) and the lower rubber film (5) are the same as the laying track of the fiber grating sensor (2) inside the rotor blade (1), and include:

after surface skin cloth of a rotor blade (1) is laid in a blade forming die, a fiber grating sensor (2) clamped by an upper-layer adhesive film (3) and a lower-layer adhesive film (5) is laid at a specified position below the corresponding blade surface skin (4) according to a specified track path. And continuously laying the composition structure of the rotor blade (1), and then heating, molding, curing and forming.

In the process of heating and molding the composite material rotor blade, after a first layer of surface covering cloth is laid in a blade molding die, the fiber grating sensor clamped by a glue film is laid at a specified position in the blade according to a specified track path. And then continuously laying other structures of the paddle, heating, molding, co-curing and forming to finish the positioning and bonding of the embedded fiber grating sensor.

This embodiment can use in the scene that fiber grating strain transducer measured helicopter rotor blade dynamic load, and the general thinking lies in: the positioning and bonding method of the embedded fiber grating sensor for measuring the dynamic load of the helicopter composite material rotor blade is provided, and the method comprises the following steps: the fiber grating sensor is clamped in the middle by the upper layer and the lower layer of adhesive films with certain widths and provided with supporting carriers, and is accurately positioned at the specified position inside the composite material rotor blade of the helicopter by the characteristics of the adhesive films, so that the fiber grating sensor keeps an ideal shape, and the reliable measurement of the dynamic load of the composite material rotor blade of the helicopter is realized.

By the above method, a rotor blade, as shown in fig. 1-4, can be manufactured, comprising:

the fiber bragg grating sensor (2) is fixed in the rotor blade (1) and corresponds to a designated position below the blade surface skin (4).

The fiber grating sensor (2) is covered by solid resin formed by heating, mould pressing and curing the upper layer rubber film (3) and the lower layer rubber film (5).

The upper adhesive film (3) and the lower adhesive film (5) adopt a matrix material resin system which is the same as that of the composite material of the rotor blade (1) and have the same curing temperature and time characteristics.

Wherein, the internal supporting carriers of the upper adhesive film (3) and the lower adhesive film (5) are made of cotton materials. The supporting carriers in the upper adhesive film layer (3) and the lower adhesive film layer (5) account for less than 5% of each adhesive film layer by weight.

The advantages of this embodiment are: the rubber film clamping fiber grating sensor with the supporting carrier is embedded inside the composite material rotor blade of the helicopter, so that the fiber grating sensor can be well bonded with the composite material inside the composite material rotor blade, and the fiber grating sensor can be accurately positioned. The accuracy and the authenticity of monitoring and measuring the load of the composite material rotor blade of the helicopter are ensured.

Meanwhile, the glue film with the supporting carrier is used as an intermediate material for embedding the composite material rotor blade of the helicopter into the fiber grating sensor, so that the important section characteristics of the composite material rotor blade, such as rigidity and quality, are hardly influenced, and the inherent characteristics of the measured object are not changed while the fiber grating sensor is used for effectively measuring the load.

The fiber grating sensor is pre-buried inside the helicopter rotor blade, does not influence the rotor blade surface shape and the aerodynamic characteristics of the rotor blade, and the measured rotor blade flight load is more accurate. And the fiber grating sensor is pre-buried inside the rotor blade and can work for a long time, can realize the long-term monitoring measurement to the paddle performance, can improve the life of combined material rotor blade to in time feed back to the unexpected condition, guarantee safe in utilization.

Therefore, in practical application, the embedded fiber grating sensor can be well positioned in the rotor blade of the helicopter, the dynamic load test data of the rotor blade is real and reliable, and the embedded fiber grating sensor is easy to use for a long time.

The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the apparatus embodiment, since it is substantially similar to the method embodiment, it is relatively simple to describe, and reference may be made to some descriptions of the method embodiment for relevant points. The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.