摘要：【中文】本发明提出一种预浸料及其制备方法，由树脂基体和纤维采用热熔法工艺制备得到，预浸料由上、下浸润层和中部的部分浸润层构成，中部的部分浸润层由不连续的非浸润纤维区域和浸润纤维区域构成，预浸料浸润度为70～90％。本发明上下完全浸润、中部部分浸润的预浸料，将干纤维留在预浸料内部，可以保证预浸料与常规预浸料相同的铺覆性，铺层时也不需要特别区分预浸料的表面状态，铺覆工艺性好，施工方便。 【EN】The invention provides a prepreg and a preparation method thereof, wherein the prepreg is prepared from a resin matrix and fibers by a hot melting process, the prepreg is composed of an upper soaking layer, a lower soaking layer and a middle partial soaking layer, the middle partial soaking layer is composed of a discontinuous non-soaking fiber area and a soaking fiber area, and the soaking degree of the prepreg is 70-90%. The prepreg which is completely infiltrated up and down and partially infiltrated in the middle is characterized in that the dry fibers are left in the prepreg, so that the same paving property of the prepreg and the conventional prepreg can be ensured, the surface state of the prepreg does not need to be particularly distinguished during paving, the paving manufacturability is good, and the construction is convenient.

摘要：【中文】本发明涉及一种氧化铝纤维布纤维界面改性的方法及由此制得的改性氧化铝纤维布。所述方法为：(1)制备温度不大于5℃的磷酸镧前驱体溶液；(2)在真空以及温度不大于10℃的条件下，采用所述磷酸镧前驱体溶液对氧化铝纤维布进行真空浸渍；(3)将经过真空浸渍后的氧化铝纤维布在室温下放置10～15h或在50～70℃下保温1～2h，然后依次经过清洗、干燥和高温处理的步骤，由此完成氧化铝纤维布纤维界面改性。本发明方法工艺简单，无需复杂设备及试剂，成本低廉；采用本发明工艺改性后纤维织物制备的氧化铝纤维增强氧化铝复合材料长时高温处理后仍有较高的强度。 【EN】The invention relates to a method for modifying a fiber interface of alumina fiber cloth and modified alumina fiber cloth prepared by the method. The method comprises the following steps: (1) preparing a lanthanum phosphate precursor solution with the temperature not higher than 5 ℃; (2) under the conditions of vacuum and temperature not higher than 10 ℃, adopting the lanthanum phosphate precursor solution to carry out vacuum impregnation on the alumina fiber cloth; (3) and (3) placing the alumina fiber cloth subjected to vacuum impregnation at room temperature for 10-15 h or insulating at 50-70 ℃ for 1-2 h, and then sequentially carrying out the steps of cleaning, drying and high-temperature treatment, thereby finishing the interface modification of the alumina fiber cloth. The method has simple process, does not need complex equipment and reagents, and has low cost; the alumina fiber reinforced alumina composite material prepared by the fiber fabric modified by the process has higher strength after long-term high-temperature treatment.

摘要：【中文】本发明涉及一种反向气流加速雾化的离心涂料喷嘴，包括进料腔、导流腔、储料腔、旋流室、导流管和反向气流帽，导流腔固连在进料腔底部，储料腔固连在导流腔底部，旋流室固连在储料腔底端中部，导流管架设在导流腔与储料腔之间，反向气流帽架设在导流管上，反向气流帽位于旋流室的出料口处，导流管内通入气体并从反向气流帽处反向流入旋流室内，本发明具有提高了喷嘴的雾化效果，同时可以控制雾化锥角，增加了适用工况的优点。 【EN】The invention relates to a centrifugal paint nozzle for accelerating atomization by reverse airflow, which comprises a feeding cavity, a flow guide cavity, a material storage cavity, a cyclone chamber, a flow guide pipe and a reverse airflow cap, wherein the flow guide cavity is fixedly connected to the bottom of the feeding cavity, the material storage cavity is fixedly connected to the bottom of the flow guide cavity, the cyclone chamber is fixedly connected to the middle part of the bottom end of the material storage cavity, the flow guide pipe is erected between the flow guide cavity and the material storage cavity, the reverse airflow cap is erected on the flow guide pipe, the reverse airflow cap is positioned at a discharge port of the cyclone chamber, and gas is introduced into the flow guide pipe and reversely flows into the cyclone chamber from the reverse airflow cap.

摘要：【中文】本发明涉及一种弱刚性薄壁复合材料构件型面轮廓测量系统及方法，属于型面测量技术领域，解决了现有弱刚性薄壁复合材料构件易变形，型面轮廓难以测量的技术问题。本发明的弱刚性薄壁复合材料构件型面轮廓测量系统，包括模具单元、固定单元、密封单元和抽真空单元；模具单元用于固定并矫正待测构件；固定单元设置于模具单元与待测构件贴合的轮廓，用于固定待测构件；密封单元用于密封待测构件，将待测构件密封在密封空间里；抽真空单元用于将待测构件所在的密封空间抽真空，以矫正待测构件，再对待测构件进行型面测量。本发明的弱刚性薄壁复合材料构件型面轮廓测量系统及方法能够对待测构件型面进行矫正，进而精确的测量型面轮廓。 【EN】The invention relates to a system and a method for measuring the profile of a weak-rigidity thin-wall composite material member, belongs to the technical field of profile measurement, and solves the technical problems that the existing weak-rigidity thin-wall composite material member is easy to deform and the profile of the profile is difficult to measure. The invention discloses a system for measuring the profile of a weak-rigidity thin-wall composite material member, which comprises a mould unit, a fixing unit, a sealing unit and a vacuumizing unit, wherein the mould unit is used for fixing the mould unit; the die unit is used for fixing and correcting the component to be measured; the fixing unit is arranged on the contour of the die unit attached to the component to be tested and used for fixing the component to be tested; the sealing unit is used for sealing the component to be tested and sealing the component to be tested in the sealed space; the vacuumizing unit is used for vacuumizing the sealed space where the component to be measured is located so as to correct the component to be measured, and then profile measurement is carried out on the component to be measured. The system and the method for measuring the profile of the weak-rigidity thin-wall composite material member profile can correct the profile of the member to be measured, so that the profile of the profile can be accurately measured.

摘要：【中文】本发明涉及一种泡沫夹层结构壁板及其成型方法。所述方法为：铺覆多层下蒙皮预浸料，每铺覆3～5层下蒙皮预浸料通过抽真空进行预压实处理直至达到下蒙皮预浸料的预定层数，然后经过固化，得到下蒙皮预制件；将一泡沫芯材的表面包覆一层胶膜和两层预浸料，再经抽真空预压，得到泡沫预硬化件；将泡沫预硬化件置于下蒙皮预制件中，然后在泡沫预硬化件的表面铺覆多层上蒙皮预浸料，每铺覆3～5层上蒙皮预浸料通过抽真空进行预压实处理直至达到上蒙皮预浸料的预定层数，再通过热压罐进行整体固化成型，得到泡沫夹层结构壁板。本发明方法以可靠的分步成型工艺，结合高效率的原位共固化技术，解决了复杂泡沫夹层结构壁板的高质量高效率成型问题。 【EN】The invention relates to a foam sandwich structure wallboard and a forming method thereof. The method comprises the following steps: paving a plurality of layers of lower skin prepreg, performing pre-compaction treatment on each 3-5 layers of lower skin prepreg paved by vacuumizing until the preset number of layers of the lower skin prepreg is reached, and curing to obtain a lower skin prefabricated part; coating a layer of adhesive film and two layers of prepreg on the surface of a foam core material, and then vacuumizing and pre-pressing to obtain a foam pre-hardened part; and placing the foam pre-hardened part in the lower skin prefabricated part, then paving a plurality of layers of upper skin prepreg on the surface of the foam pre-hardened part, performing pre-compaction treatment on 3-5 layers of upper skin prepreg paved each time by vacuumizing until the preset number of layers of the upper skin prepreg is reached, and performing integral curing molding through an autoclave to obtain the foam sandwich structure wallboard. The method solves the problem of high-quality and high-efficiency molding of the complex foam sandwich structure wallboard by using a reliable step-by-step molding process and combining with an efficient in-situ co-curing technology.

摘要：【中文】本发明涉及一种梯度纤维预制体的设计方法，所述梯度纤维预制体包括表层和低密度层；所述表层为长纤维材料层，所述低密度层为短切纤维材料层；根据梯度纤维预制体的密度要求和厚度要求，按照如下公式来确定表层和低密度层的结构：D＝D₀+D₁，ρ₀＞ρ₁，式中，ρ₀为表层密度，D₀为表层厚度，ρ₁为低密度层密度，D₁为低密度层厚度，ρ为梯度纤维预制体密度，D为梯度纤维预制体厚度。本发明提供的设计方法可以设计出不同形式的纤维预制体以满足复合材料的使用环境的不同需求，尤其可以满足高温高压较为严苛的使用条件的需求，为制备表面高强度和优异隔热性能的复合材料提供了良好的基础。 【EN】The invention relates to a design method of a gradient fiber preform, wherein the gradient fiber preform comprises a surface layer and a low-density layer; the surface layer is a long fiber material layer, and the low-density layer is a chopped fiber material layer; according to the density requirement and the thickness requirement of the gradient fiber preform, the structures of the surface layer and the low-density layer are determined according to the following formula:D＝D₀+D₁，ρ₀＞ρ₁in the formula, rho₀Is the skin density, D₀Is the skin thickness, rho₁Is low density layer density, D₁Is a low density layer thicknessRho is the density of the gradient fiber preform, and D is the thickness of the gradient fiber preform. The design method provided by the invention can be used for designing different forms of fiber preforms to meet different requirements of the use environment of the composite material, particularly meet the requirements of severer use conditions under high temperature and high pressure, and provide a good foundation for preparing the composite material with high surface strength and excellent heat insulation performance.

摘要：【中文】本发明涉及一种复合材料多阶梯平台及其高质量成型方法。所述方法：提供硬质模具；确定复材阶梯的各台阶的理论厚度，根据各台阶的理论厚度与实际厚度确定压缩量；选择与压缩量匹配的低模量材料作为替换材料，根据低模量材料的厚度与模量的匹配关系，确定低模量材料的厚度；根据等厚度替换原则，确定硬质模具的被替换厚度，对硬质模具进行机加；将对应厚度的低模量材料粘接在机加后的硬质模具上，制得成型模具；在所述成型模具上铺设复合材料后合模，然后经过固化和脱模，得到复合材料多阶梯平台。本发明解决了复合材料制件不同高度阶梯工况下的不均匀加压的问题，相比传统复合材料多阶梯平台硬成型，具有低成本和高成型质量等突出优势。 【EN】The invention relates to a composite material multi-step platform and a high-quality forming method thereof. The method comprises the following steps: providing a hard die; determining the theoretical thickness of each step of the composite material steps, and determining the compression amount according to the theoretical thickness and the actual thickness of each step; selecting a low-modulus material matched with the compression amount as a replacement material, and determining the thickness of the low-modulus material according to the matching relation between the thickness and the modulus of the low-modulus material; determining the replaced thickness of the hard die according to an equal thickness replacement principle, and machining the hard die; bonding the low-modulus material with the corresponding thickness on the machined hard mold to prepare a forming mold; and (3) paving the composite material on the forming die, closing the die, and then curing and demolding to obtain the composite material multi-step platform. The invention solves the problem of uneven pressurization of composite material workpieces under different height step working conditions, and has the outstanding advantages of low cost, high molding quality and the like compared with the traditional composite material multi-step platform hard molding.

摘要：【中文】本发明涉及一种复合材料翼面类夹芯结构及其成型方法。所述方法为：将泡沫芯材从翼根至翼尖机加成厚度依次递增的I、Ⅱ、Ⅲ和Ⅳ区泡沫芯材；泡沫表面粘接准备；将Ⅰ区预先切好的每块泡沫包覆4层预浸料，铺层[90/90/0/90]，再与Ⅱ～Ⅳ区泡沫芯材组合成一整体；对Ⅰ区、Ⅱ区泡沫整体包覆4层预浸料，铺层[90/0/90/90]，再对Ⅰ区、Ⅱ区、Ⅲ区整体包覆4层预浸料，铺层[90/90/0/90]，最后对Ⅰ区、Ⅱ区、Ⅲ区、Ⅳ区整体包覆4层预浸料，铺层[90/0/90/90]；泡沫增强固化成型。本发明使翼根两侧面板最厚，翼尖两侧面板最薄，能提高芯材抗压缩变形的能力，既实现了减重功能，又满足了结构强度设计要求。 【EN】The invention relates to a composite material wing surface type sandwich structure and a forming method thereof. The method comprises the following steps: adding foam core materials in areas I, II, III and IV with gradually increased thicknesses from the wing root to the wing tip; preparing for adhering the surface of the foam; each piece of foam pre-cut in the area I is coated with 4 layers of prepreg and is layered [90/90/0/90], and then is combined with foam core materials in the areas II to IV into a whole; integrally coating 4 layers of prepreg on foams in an area I and an area II, laying layers [90/0/90/90], integrally coating 4 layers of prepreg on the areas I, II and III, laying layers [90/90/0/90], and finally integrally coating 4 layers of prepreg on the areas I, II, III and IV, laying layers [90/0/90/90 ]; the foam is enhanced, cured and formed. The invention makes the two side panels of the wing root the thickest and the two side panels of the wing tip the thinnest, can improve the compression deformation resistance of the core material, realizes the weight reduction function and meets the design requirement of structural strength.

摘要：【中文】本发明涉及一种结构功能一体化复合材料机翼及其整体成型方法。所述方法：制备复合材料承载梁；干燥具有机翼前后缘形状的泡沫芯层，然后将其拼接在复合材料承载梁的前后侧；将吸波层板粘贴在泡沫芯层上，得到拼接组件；将拼接组件通过真空袋法预压实；将干态玻璃布和/或石英布粘贴在复合材料承载梁和吸波层板的表面，得到预成型体；将预成型体置于机翼成型模具中，采用RTM工艺进行制备，得到结构功能一体化复合材料机翼。本发明实现了承载梁、泡沫芯层、吸波材料、蒙皮的一次整体成型机翼；同时，将吸波材料成型在材料内部，避免了吸波层放置在最外层时易老化失效的问题，制备出了既具备承载功能又具备吸波隐身功能的结构功能一体机翼。 【EN】The invention relates to a structure function integrated composite material wing and an integral forming method thereof. The method comprises the following steps: preparing a composite material carrier beam; drying the foam core layer with the shape of the front edge and the rear edge of the wing, and then splicing the foam core layer on the front side and the rear side of the composite material load-bearing beam; adhering the wave-absorbing layer plate to the foam core layer to obtain a splicing assembly; pre-compacting the splicing assembly by a vacuum bag method; adhering dry glass cloth and/or quartz cloth to the surfaces of the composite material bearing beam and the wave-absorbing layer plate to obtain a preformed body; and (3) placing the preformed body in a wing forming mold, and preparing by adopting an RTM (resin transfer molding) process to obtain the composite material wing with the integrated structure and function. The invention realizes the one-time integral forming of the wing of the carrier beam, the foam core layer, the wave-absorbing material and the skin; meanwhile, the wave-absorbing material is molded in the material, so that the problem that the wave-absorbing layer is easy to age and lose efficacy when being placed on the outermost layer is solved, and the structural function integrated wing with the bearing function and the wave-absorbing stealth function is prepared.

摘要：【中文】本发明涉及一种长连续纤维缠绕减重结构复合材料承载梁及其整体成型的方法。该方法包括：(1)下翼面铺层的步骤：将单向预浸料按照45°、‑45°、0°、90°依次铺层，90°方向的单向预浸料尺寸比下翼面前缘和后缘均宽；(2)放置减重芯层的步骤；(3)长连续纤维缠绕铺层的步骤；(4)上翼面铺层的步骤：将单向预浸料按照90°、0、°‑45°、45°依次铺层，90°方向的单向预浸料尺寸比上翼面前缘和后缘均宽；(5)装模的步骤；和(6)加压固化的步骤。本发明通过0°碳纤维变厚度缠绕铺层和Z向增强铺层方式，解决了复合材料承载梁翼根及腹板蒙皮层间强度较低的问题，实现该结构复合材料机翼的整体成型。 【EN】The invention relates to a composite material load-bearing beam with a long continuous fiber winding weight-reducing structure and an integral forming method thereof. The method comprises the following steps: (1) laying the lower wing surface: the unidirectional prepreg is sequentially layered according to the angles of 45 degrees, -45 degrees, 0 degrees and 90 degrees, and the size of the unidirectional prepreg in the 90-degree direction is wider than that of the front edge and the rear edge of the lower airfoil surface; (2) placing the weight-reducing core layer; (3) winding and laying layers of long continuous fibers; (4) laying the upper wing surface: sequentially laying unidirectional prepreg at 90 degrees, 0 degrees, 45 degrees and 45 degrees, wherein the size of the unidirectional prepreg at 90 degrees is wider than that of the front edge and the rear edge of the upper airfoil surface; (5) a step of die filling; and (6) a step of press-curing. According to the invention, by means of the 0-degree carbon fiber variable-thickness winding layer and the Z-direction reinforcing layer, the problem of low interlayer strength of composite material load-bearing beam wing roots and web skin is solved, and the integral forming of the composite material wing with the structure is realized.