Laser processing method for carbon fiber partition plate of unmanned aerial vehicle

Abstract

The invention discloses a laser processing method for an unmanned aerial vehicle carbon fiber partition plate, and relates to the technical field of laser cutting. The machining method comprises the following steps that a laser machining system is built, according to the path of a laser beam, the laser machining system at least comprises an infrared laser millisecond pulse laser, a reflector and a laser cutting head in sequence, and the laser cutting head comprises a lens, an auxiliary gas inlet and a nozzle; and the carbon fiber partition plate is placed at the working position, and the infrared laser millisecond pulse laser is started for cutting. And high-precision cutting is realized by accurately controlling laser paths and parameters, so that a machined surface is smoother.

Description

Technical Field

[0001] The invention relates to the field of laser cutting, and in particular to a laser processing method for a carbon fiber partition of an unmanned aerial vehicle. Background Art

[0002] Carbon fiber composite material is a new type of composite material that is solidified and formed by carbon fiber as reinforcement and resin as matrix. It has the advantages of high stiffness, high modulus, high strength and light weight, and is widely used in aerospace, transportation, energy industry, sporting goods and other fields. However, the processing of carbon fiber composite materials mainly adopts traditional mechanical processing methods. Common processing methods of carbon fiber composite materials mainly include high-speed milling, water jet cutting, ultrasonic cutting, etc. Due to the difference in physical properties between resin and carbon fiber in carbon fiber composite materials, the use of traditional mechanical processing methods is prone to problems such as tool wear, composite material delamination, performance deterioration after processing, and dust generated during processing that is harmful to the environment and human body, which seriously restricts the application of carbon fiber composite materials.

[0003] Laser cutting is a new carbon fiber composite material processing technology, which irradiates a high-energy laser beam onto the surface of the material to be processed, thereby melting, gasifying the material or changing the physical properties of the material to achieve the purpose of material removal. Compared with traditional mechanical processing methods, since the laser cutting process does not directly contact the material surface, there are no problems such as tool wear, mechanical vibration, and processing defects caused by cutting force.

[0004] However, since the mechanism of action between laser and material is to locally heat the material through Joule heating to reach the melting temperature or vaporization temperature of the material to complete the material removal, thermal damage cannot be avoided. In addition, the difference in physical properties such as thermal conductivity and vaporization temperature between carbon fiber and resin leads to heat-affected zone, fiber pullout, fiber end expansion and other damages when laser cutting carbon fiber composites, which seriously affect the processing quality of carbon fiber composites. Summary of the invention

[0005] The present invention is made in view of the above-mentioned problems and provides a laser processing method for unmanned aerial vehicle carbon fiber partitions, aiming to solve the current problem of damage to carbon fiber materials caused by laser cutting.

[0006] The laser processing method of the carbon fiber partition of the unmanned aerial vehicle of the present invention comprises the following steps: building a laser processing system, wherein the laser processing system comprises at least: an infrared laser millisecond pulse laser, a reflector and a laser cutting head in sequence according to the path of the laser beam, wherein the laser cutting head comprises a lens, an auxiliary gas inlet and a nozzle; placing the carbon fiber partition of the unmanned aerial vehicle in a working position, and starting the infrared laser millisecond pulse laser for cutting.

[0007] In some embodiments of the present invention, the scanning rate of the infrared laser millisecond pulse laser is 0.8 mm / s to 1.6 mm / s.

[0008] In some embodiments of the present invention, the pulse width of the infrared laser millisecond pulse laser is 1 ms to 1.2 ms.

[0009] In some embodiments of the present invention, the frequency of the infrared laser millisecond pulse laser is 50 Hz to 55 Hz.

[0010] In some embodiments of the present invention, the single pulse energy of the infrared laser millisecond pulse laser is 1J to 1.5J.

[0011] In some embodiments of the present invention, the pressure of the auxiliary gas in the laser cutting head is 0.3 MPa to 0.4 MPa.

[0012] In some embodiments of the present invention, the auxiliary gas is a mixed gas of nitrogen and oxygen, and the volume ratio of oxygen in the mixed gas is 12% to 17%.

[0013] In some embodiments of the present invention, the UAV carbon fiber partition is an epoxy resin-based composite carbon fiber partition, and the mass ratio of epoxy resin to carbon fiber in the epoxy resin-based composite carbon fiber partition is 1:(15-25).

[0014] In some embodiments of the present invention, the K number of the carbon fibers in the epoxy resin-based composite carbon fiber separator is 1K to 5K.

[0015] In some embodiments of the present invention, the thickness of the carbon fiber partition of the drone is 1.5 mm to 2.5 mm.

[0016] The beneficial effects that can be achieved by the present invention are:

[0017] The present invention provides a laser processing method for a carbon fiber partition for a UAV. By precisely controlling the laser path and parameters, high-precision cutting is achieved, which can meet the application requirements of the carbon fiber partition for a UAV that require high precision, and can effectively improve the adverse effects of fiber pullout on the cutting surface on the workpiece. Auxiliary gas is provided, and the area of ​​the heat-affected zone is effectively reduced by adjusting the oxygen content and gas pressure of the auxiliary gas, making the processed surface smoother. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Schematic diagram of a laser processing system for a carbon fiber partition of a drone according to an embodiment of the present invention; Explanation of reference numerals: 1 infrared laser millisecond pulse laser; 2 laser beam; 3 reflector; 4 laser cutting head; 401 lens; 402 auxiliary gas inlet; 403 nozzle; 5 drone carbon fiber partition;

[0019] Figure 2 These are scanning electron microscope images of the front plan view (a) and the cross-section (b) of the processed carbon fiber partition of the drone in Example 1 of the present invention.

[0020] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0021] The accompanying drawings and the following description are provided to enable those skilled in the art to fully understand the present invention, and are not intended to limit the subject matter described in the claims.

[0022] The "range" disclosed in the present invention is defined in the form of a lower limit and an upper limit, and a given range is defined by selecting a lower limit and an upper limit, and the selected lower limit and upper limit define the boundaries of the particular range. The range defined in this way can be inclusive or exclusive of the end values, and can be arbitrarily combined, that is, any lower limit can be combined with any upper limit to form a range. For example, if a range of 60 to 120 and 80 to 110 is listed for a particular parameter, it is understood that a range of 60 to 110 and 80 to 120 is also expected. In addition, if the minimum range values ​​1 and 2 are listed, and if the maximum range values ​​3, 4 and 5 are listed, the following ranges can all be expected: 1 to 3, 1 to 4, 1 to 5, 2 to 3, 2 to 4 and 2 to 5. In the present invention, unless otherwise specified, the numerical range "a to b" represents an abbreviation of any real number combination between a and b, wherein a and b are both real numbers. For example, the numerical range "0-5" means that all real numbers between "0-5" are listed in this document, and "0-5" is just an abbreviation of these numerical combinations. In addition, when a parameter is expressed as an integer ≥ 2, it is equivalent to disclosing that the parameter is, for example, an integer of 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, etc.

[0023] If not otherwise specified, all embodiments and optional embodiments of the present invention can be combined with each other to form a new technical solution.

[0024] Unless otherwise specified, all technical features and optional technical features of the present invention can be combined with each other to form a new technical solution.

[0025] If not otherwise specified, all steps of the present invention may be performed sequentially or randomly, preferably sequentially. For example, the method includes steps (a) and (b), which means that the method may include steps (a) and (b) performed sequentially, or may include steps (b) and (a) performed sequentially. For example, the method may further include step (c), which means that step (c) may be added to the method in any order, for example, the method may include steps (a), (b) and (c), or may include steps (a), (c) and (b), or may include steps (c), (a) and (b), etc.

[0026] Since the mechanism of action between laser and material is to locally heat the material through Joule heating to reach the melting temperature or vaporization temperature of the material to complete the material removal, thermal damage cannot be avoided. In addition, the difference in physical properties such as thermal conductivity and vaporization temperature between carbon fiber and resin leads to heat-affected zone, fiber pullout, fiber end expansion and other damages when laser cutting carbon fiber composites, which seriously affect the processing quality of carbon fiber composites.

[0027] In view of this, the present invention proposes a laser processing method for a carbon fiber partition of an unmanned aerial vehicle, referring to Figure 1 , building a laser processing system, according to the path of the laser beam 2, the laser processing system sequentially includes at least: an infrared laser millisecond pulse laser 1, a reflector 3 and a laser cutting head 4, the laser cutting head includes a lens 401, an auxiliary gas inlet 402 and a nozzle 403;

[0028] The unmanned aerial vehicle carbon fiber partition 5 is placed in the working position, and the infrared laser millisecond pulse laser 1 is started for cutting.

[0029] In this solution, the laser beam 2 generated by the infrared laser millisecond pulse laser 1 is accurately guided to the laser cutting head 4 through the reflector 3. The lens 401 of the laser cutting head 4 focuses the laser beam 2 onto the workpiece. After the laser beam 2 is focused by the lens 401, the energy distribution becomes more concentrated. The high-quality laser beam 2 helps to achieve more precise cutting. The auxiliary gas blows away the slag and heat in the cutting area through the nozzle 403, reduces the heat-affected zone, and keeps the cutting surface clean. The laser processing system achieves efficient and accurate cutting of the carbon fiber partition by precisely controlling the path and energy of the laser beam, as well as the flow rate and pressure of the auxiliary gas. The cutting path can be arranged in directional order according to the distribution of each structure of the carbon fiber product, or it can be arranged according to the shortest processing path. The design of this system takes into account various key factors of laser processing, including the selection of the laser source, the transmission and focusing of the beam, and the use of auxiliary gas during the cutting process, ensuring the efficiency and processing quality of the processing process.

[0030] This solution solves the problem of thermal damage that is easy to occur during laser processing by using an infrared laser millisecond pulse laser cutting method with high repetition frequency, single pulse operation, high single pulse energy, and high single pulse energy consistency. In addition, the output high-energy single pulse is unique in the time domain. The specific position point of the workpiece material processing surface during cutting is very accurate and will not drift in space. The processing time is fast, the timing matching is precise, the laser processing process is consistent, there is no repeated irradiation, and the characteristic parameters of the carbon fiber material of the drone, such as mechanical properties or electromagnetic shielding properties, are almost not changed.

[0031] In some embodiments, the scanning rate of the infrared laser millisecond pulse laser is 0.8mm / s to 1.6mm / s. The scanning rate is one of the important factors affecting the width of the heat-affected zone of laser cutting carbon fiber composite materials. A higher scanning speed can minimize the width of the heat-affected zone. A fast scanning rate means that the laser is in contact with the material for a shorter time, thereby reducing the accumulation and diffusion of heat in the material. However, too high a scanning rate may result in the material not being completely cut, while too low a scanning rate may increase the heat-affected zone, affecting the cutting edge quality and mechanical properties of the material.

[0032] In some embodiments, the frequency of the infrared laser millisecond pulse laser is 50 Hz to 55 Hz. The frequency and scanning rate work together. A higher frequency means a shorter interaction time between the laser and the material. A higher frequency may also reduce the energy of a single pulse, thereby affecting the depth and quality of cutting.

[0033] In some embodiments, the single pulse energy of the infrared laser millisecond pulse laser is 1 J to 1.5 J. The higher the single pulse energy, the greater the energy that can be transferred when the laser beam interacts with the material, thereby achieving deeper cutting on the material.

[0034] In the system of the present invention, the scanning rate, frequency and single pulse energy are within the above ranges, which, together with other settings, can ensure that the material is effectively cut while maintaining a small heat-affected zone.

[0035] In some embodiments, the pressure of the auxiliary gas in the laser cutting head is 0.3Mpa to 0.4Mpa. The auxiliary gas can also timely blow away the material vapor generated during the processing, reduce the shielding effect of the material vapor on the laser, and enable the laser to be smoothly coupled with the workpiece.

[0036] In some embodiments, the auxiliary gas is a mixture of nitrogen and oxygen, and the volume ratio of oxygen in the mixture is 12% to 17%. Oxygen can promote gasification and degradation of materials, thereby obtaining a higher quality processed surface.

[0037] In some embodiments, the UAV carbon fiber partition is an epoxy resin-based composite carbon fiber partition, and the mass ratio of epoxy resin to carbon fiber in the epoxy resin-based composite carbon fiber partition is 1:(15-25).

[0038] In some embodiments, the K number of the carbon fiber in the epoxy resin-based composite carbon fiber separator is 1K to 5K. The K number of the carbon fiber is combined with the mass ratio of the epoxy resin to obtain a tightly bonded UAV carbon fiber separator with good surface uniformity, high surface flatness and good overall impact resistance. The UAV carbon fiber separator with parameters within the above range can better adapt to the cutting process of this solution to obtain a flat section.

[0039] In some embodiments, the thickness of the carbon fiber partition of the drone is 1.5 mm to 2.5 mm. The thickness of the carbon fiber partition of the drone is 1.5 mm to 2.5 mm. The carbon fiber partition of this thickness range can provide excellent mechanical properties for the drone and is more suitable for the cutting process of this solution to obtain a smooth section.

[0040] The technical solution of the present invention is further described in detail below in conjunction with specific embodiments. It should be understood that the following specific embodiments are only used to explain the present invention, and are not used to limit the present invention.

[0041] Example 1

[0042] The infrared laser millisecond pulse laser used is the JK702Nd:YAG millisecond pulse laser produced by a British company. It can provide an average power of 350 watts, a maximum pulse energy of 50 joules, a maximum peak power of 4.5 kilowatts, a pulse width range from 0.5 milliseconds to greater than 50 milliseconds, a repetition frequency of 0.2 to 500 Hz, a positioning accuracy of up to ±0.01mm, a maximum positioning speed of 140m / min, a machine tool volume of 2900mm×1300mm×1850mm, a processing format (length×width) of 2000mm×600mm, auxiliary gas is nitrogen, the operating environment is room temperature, and the maximum cutting thickness is 5mm.

[0043] The scanning rate of the infrared laser millisecond pulse laser is set to 1.2mm / s, the pulse width is 1.1ms, the frequency is 50Hz, the single pulse energy is 1.5J, the pressure of the auxiliary gas in the laser cutting head is 0.4Mpa, the auxiliary gas is a mixture of nitrogen and oxygen, and the volume ratio of oxygen is 14%. The carbon fiber partition matrix is ​​selected as 9A-16 epoxy resin matrix, the reinforcement carbon fiber is Toray T300, the K number of carbon fiber is 5K, and the thickness of the carbon fiber partition is 2mm.

[0044] Example 2

[0045] The infrared laser millisecond pulse laser used is the JK702Nd:YAG millisecond pulse laser produced by a British company. It can provide an average power of 350 watts, a maximum pulse energy of 50 joules, a maximum peak power of 4.5 kilowatts, a pulse width range from 0.5 milliseconds to greater than 50 milliseconds, a repetition frequency of 0.2 to 500 Hz, a positioning accuracy of up to ±0.01mm, a maximum positioning speed of 140m / min, a machine tool volume of 2900mm×1300mm×1850mm, a processing format (length×width) of 2000mm×600mm, auxiliary gas is nitrogen, the operating environment is room temperature, and the maximum cutting thickness is 5mm.

[0046] The scanning rate of the infrared laser millisecond pulse laser is set to 1.6mm / s, the pulse width is 1.0ms, the frequency is 55Hz, the single pulse energy is 1.0J, the pressure of the auxiliary gas in the laser cutting head is 0.4Mpa, the auxiliary gas is a mixture of nitrogen and oxygen, and the volume ratio of oxygen is 14%. The carbon fiber partition matrix is ​​selected as 9A-16 epoxy resin matrix, the reinforcement carbon fiber is Toray T300, the K number of carbon fiber is 5K, and the thickness of the carbon fiber partition is 2mm.

[0047] Example 3

[0048] The infrared laser millisecond pulse laser used is the JK702Nd:YAG millisecond pulse laser produced by a British company. It can provide an average power of 350 watts, a maximum pulse energy of 50 joules, a maximum peak power of 4.5 kilowatts, a pulse width range from 0.5 milliseconds to greater than 50 milliseconds, a repetition frequency of 0.2 to 500 Hz, a positioning accuracy of up to ±0.01mm, a maximum positioning speed of 140m / min, a machine tool volume of 2900mm×1300mm×1850mm, a processing format (length×width) of 2000mm×600mm, auxiliary gas is nitrogen, the operating environment is room temperature, and the maximum cutting thickness is 5mm.

[0049] The scanning rate of the infrared laser millisecond pulse laser is set to 1.6mm / s, the pulse width is 1.0ms, the frequency is 55Hz, the single pulse energy is 1.0J, the pressure of the auxiliary gas in the laser cutting head is 0.3Mpa, the auxiliary gas is a mixture of nitrogen and oxygen, and the volume ratio of oxygen is 17%. The carbon fiber partition matrix is ​​selected as 9A-16 epoxy resin matrix, the reinforcement carbon fiber is Toray T300, the K number of carbon fiber is 5K, and the thickness of the carbon fiber partition is 2mm.

[0050] Comparative Example 1

[0051] The infrared laser millisecond pulse laser used is the JK702Nd:YAG millisecond pulse laser produced by a British company. It can provide an average power of 350 watts, a maximum pulse energy of 50 joules, a maximum peak power of 4.5 kilowatts, a pulse width range from 0.5 milliseconds to greater than 50 milliseconds, a repetition frequency of 0.2 to 500 Hz, a positioning accuracy of up to ±0.01mm, a maximum positioning speed of 140m / min, a machine tool volume of 2900mm×1300mm×1850mm, a processing format (length×width) of 2000mm×600mm, auxiliary gas is nitrogen, the operating environment is room temperature, and the maximum cutting thickness is 5mm.

[0052] The scanning rate of the infrared laser millisecond pulse laser is set to 1.6mm / s, the pulse width is 1.0ms, the frequency is 55Hz, the single pulse energy is 1.0J, the pressure of the auxiliary gas in the laser cutting head is 0.5Mpa, the auxiliary gas is a mixture of nitrogen and oxygen, and the volume ratio of oxygen is 20%. The carbon fiber partition matrix is ​​selected as 9A-16 epoxy resin matrix, the reinforcement carbon fiber is Toray T300, the K number of carbon fiber is 5K, and the thickness of the carbon fiber partition is 2mm. Performance test:

[0053] The cutting surfaces obtained in the embodiment and the comparative example were tested to obtain the measurement index data. The minimum slit entrance width was ψ min , the minimum heat affected zone width is H min , the minimum cone angle is θ min , and record the results:

[0054] Table 1: Indicators of Examples 1 to 3 and Comparative Example 1

[0055]

[0056]

[0057] It can be seen from Table 1 that the laser processing method of the carbon fiber partition of the drone in this scheme achieves high-precision cutting by precisely controlling the laser path and parameters, which illustrates the importance of changing the parameter combination on the cutting quality. It can meet the application requirements of the carbon fiber partition of the drone, which has high precision requirements, and effectively improve the adverse effects of fiber pullout on the cutting surface on the workpiece, provide auxiliary gas, and effectively reduce the area of ​​the heat-affected zone by adjusting the oxygen content and gas pressure of the auxiliary gas, making the processed surface smoother.

[0058] It should be noted that the present invention is not limited to the above-mentioned embodiments. The above-mentioned embodiments are only examples, and the embodiments having the same structure as the technical idea and exerting the same effect within the scope of the technical solution of the present invention are all included in the technical scope of the present invention. In addition, without departing from the scope of the main purpose of the present invention, various modifications that can be thought of by those skilled in the art to the embodiments and other methods of combining some of the constituent elements in the embodiments are also included in the scope of the present invention.

Claims

1. A laser processing method for a carbon fiber partition of an unmanned aerial vehicle, characterized in that: The processing method comprises the following steps: Building a laser processing system, which includes at least: an infrared laser millisecond pulse laser, a reflector and a laser cutting head in sequence according to the path of the laser beam, wherein the laser cutting head includes a lens, an auxiliary gas inlet and a nozzle; The carbon fiber partition of the UAV is placed in the working position, and the infrared laser millisecond pulse laser is started for cutting.

2. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The scanning rate of the infrared laser millisecond pulse laser is 0.8 mm / s to 1.6 mm / s.

3. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The pulse width of the infrared laser millisecond pulse laser is 1 ms to 1.2 ms.

4. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The frequency of the infrared laser millisecond pulse laser is 50 Hz to 55 Hz.

5. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The single pulse energy of the infrared laser millisecond pulse laser is 1J-1.5J.

6. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The pressure of the auxiliary gas in the laser cutting head is 0.3Mpa to 0.4Mpa.

7. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The auxiliary gas is a mixed gas of nitrogen and oxygen, and the volume ratio of oxygen in the mixed gas is 12% to 17%.

8. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The unmanned aerial vehicle carbon fiber partition is an epoxy resin-based composite carbon fiber partition, and the mass ratio of epoxy resin to carbon fiber in the epoxy resin-based composite carbon fiber partition is 1:(15-25).

9. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 8 is characterized in that: The K number of the carbon fibers in the epoxy resin-based composite carbon fiber separator is 1K-5K.

10. The laser processing method of the carbon fiber partition of the unmanned aerial vehicle according to claim 1 is characterized in that: The thickness of the carbon fiber partition of the drone is 1.5 mm to 2.5 mm.

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