摘要：【中文】本发明提供了一种用于心理学教学实验的装置，包括：装置主体，其内设有第一腔体和第二腔体；催眠装置，安装在第一腔体；沙盘装置，放置在第二腔体；升降装置，固定连接在装置主体下端；旋转及移动装置，设置在升降装置下端，用于升降装置旋转及移动；显示器，设置在装置主体正面；控制器，分别与显示器、催眠装置、升降装置电连接。显示器用于显示教学素材，催眠装置用于催眠实验，沙盘装置，用于沙盘展示实验，从而使得本发明便于在教学的过程中进行实验。且本发明设置旋转及移动装置，用于驱动升降装置旋转及移动，从而带动升降装置上端的装置主体旋转及移动，便于移动本发明装置主体至需要的场合，更便于本发明的使用。 【EN】The invention provides a device for psychological teaching experiments, which comprises: the device comprises a device main body, a first cavity and a second cavity are arranged in the device main body; the hypnosis device is arranged in the first cavity; the sand table device is placed in the second cavity; the lifting device is fixedly connected to the lower end of the device main body; the rotating and moving device is arranged at the lower end of the lifting device and is used for rotating and moving the lifting device; a display provided on the front surface of the apparatus main body; and the controller is electrically connected with the display, the hypnosis device and the lifting device respectively. The display is used for displaying teaching materials, the hypnosis device is used for hypnosis experiments, and the sand table device is used for sand table display experiments, so that the experiment is convenient to carry out in the teaching process. The rotating and moving device is arranged and used for driving the lifting device to rotate and move, so that the device body at the upper end of the lifting device is driven to rotate and move, the device body is convenient to move to a required occasion, and the use of the device is more convenient.

摘要：【中文】本发明提供了一种微孔层、气体扩散层及其制备方法和应用；所述微孔层的制备原料包括二氧化硅溶胶、聚乙烯醇、交联剂以及石墨烯；通过聚乙烯醇与二氧化硅溶胶以及石墨烯复合形成微孔层，具有较好的疏水性能、气体渗透性以及氧的有效扩散性，并能够减少水的阻力，增加液态水的传输率，从而有效缓解水淹，其用于气体扩散层能够增加气体扩散层的疏水性能；气体扩散层用于质子交换膜燃料电池能够提高燃料电池的电化学性能，使其能够作为动力电池用于汽车中。 【EN】The invention provides a microporous layer, a gas diffusion layer, a preparation method and an application thereof; the preparation raw materials of the microporous layer comprise silicon dioxide sol, polyvinyl alcohol, a cross-linking agent and graphene; the microporous layer is formed by compounding polyvinyl alcohol, silicon dioxide sol and graphene, has good hydrophobic property, gas permeability and effective oxygen diffusivity, can reduce water resistance and increase the transmission rate of liquid water, thereby effectively relieving flooding, and can increase the hydrophobic property of the gas diffusion layer when the microporous layer is used for the gas diffusion layer; the gas diffusion layer used for the proton exchange membrane fuel cell can improve the electrochemical performance of the fuel cell, so that the gas diffusion layer can be used as a power cell in an automobile.

摘要：【中文】为了解决目前国内外均没有蒿属花粉特异性IgE抗体(sIgE)血清标准物质的问题，本发明的目的是提供一种蒿属花粉特异性IgE抗体标准血清的制备和检验，制备部分主要包括原料的筛选和标准血清的制备，检验主要包括：基质效应和互通性检测、均匀性检测、稳定性检测、定值、不确定度评定。 【EN】In order to solve the problem that no artemisia pollen specific IgE antibody (sIgE) serum standard substance exists at home and abroad at present, the invention aims to provide a preparation and a test of artemisia pollen specific IgE antibody standard serum, wherein the preparation part mainly comprises screening of raw materials and preparation of standard serum, and the test mainly comprises the following steps: matrix effect and interoperability detection, uniformity detection, stability detection, valuing, uncertainty assessment.

摘要：【中文】本发明提供了一种微孔层、气体扩散层及其制备方法和应用；所述微孔层的制备原料包括有机硅氧烷、碳纳米材料以及有机溶剂；微孔层包括有机硅氧烷和碳纳米材料，聚甲基硅氧烷在热处理条件下分解为分子量较小的物质，从而降低微孔层的表面张力，并与炭黑形成微纳结构，其用于气体扩散层中能够提高气体扩散层的粗糙度和接触角，从而提高气体扩散层的疏水性能；气体扩散层用于质子交换膜燃料电池能够提高燃料电池的电化学性能，使其能够作为动力能源用于汽车中。 【EN】The invention provides a microporous layer, a gas diffusion layer, a preparation method and an application thereof; the preparation raw materials of the microporous layer comprise organic siloxane, carbon nano material and organic solvent; the microporous layer comprises organic siloxane and a carbon nanomaterial, the polymethylsiloxane is decomposed into substances with smaller molecular weight under the heat treatment condition, so that the surface tension of the microporous layer is reduced, and the polymethylsiloxane and carbon black form a micro-nano structure; the gas diffusion layer used for the proton exchange membrane fuel cell can improve the electrochemical performance of the fuel cell, so that the gas diffusion layer can be used as a power source for automobiles.

摘要：【中文】本发明公开了Co/Mo₂C‑MOF树叶状的纳米片、制备方法及其作为电催化全分解水催化剂的应用，属于电催化分解水技术领域。本发明的制备方法，包括以下步骤：1)将Zn(NO₃)₂·6H₂O、Co(NO₃)₂·6H₂O、H₃Mo₁₂O₄₀P溶于水中，得到A溶液，将2‑甲基咪唑溶于另一份水中，得到B溶液；2)将A溶液逐滴加入到B溶液中，在室温下反应至溶液变成蓝紫色悬浮液，清洗收集下沉物，经干燥得到中间产物。3)将中间产物与可溶性钼盐混合，在惰性气氛保护下进行高温碳化得到树叶片状结构Co/Mo₂C‑MOF纳米片。本发明的产物，具有稳定的树叶片状结构，形貌良好，其上均布有空隙和颗粒，电催化活性高。 【EN】The invention discloses Co/Mo₂C-MOF leaf-shaped nanosheet and preparation methodThe method and the application thereof as the electrocatalytic full water decomposition catalyst belong to the technical field of electrocatalytic water decomposition. The preparation method comprises the following steps: 1) adding Zn (NO)₃)₂·6H₂O、Co(NO₃)₂·6H₂O、H₃Mo₁₂O₄₀Dissolving P in water to obtain solution A, and dissolving 2-methylimidazole in another part of water to obtain solution B; 2) and dropwise adding the solution A into the solution B, reacting at room temperature until the solution becomes a bluish purple suspension, washing and collecting precipitates, and drying to obtain an intermediate product. 3) Mixing the intermediate product with soluble molybdenum salt, and performing high-temperature carbonization under the protection of inert atmosphere to obtain leaf sheet structure Co/Mo₂C-MOF nanosheets. The product of the invention has stable leaf-shaped structure, good appearance, uniformly distributed gaps and particles and high electrocatalytic activity.

摘要：【中文】本发明提供了一种基于混合粒度注意力机制的任务型多轮对话模型构建方法，包括以下步骤：S1：对文本进行分词、去停用词、词向量编码等预处理；S2：使用输入编码器将转化后的高维向量编码成句子向量，记忆对话的细节；S3：上下文编码器对句子向量进行编码；S4：上下文编码层输出结合句子粒度的注意力机制，实现对语境编码；S5：步骤S4输出作为输出解码器第一层的输入，通过解码层第一层进行解码；S6：计算单词粒度的注意力值；S7：解码器第一层的输出结合步骤S6计算所得的单词粒度的注意力值，将解码器产生的输出映射至单词表大小的维度上，输出结果。利用本发明大大提升了在实际数据集上进行多轮对话任务生成回复的准确性。 【EN】The invention provides a task type multi-round dialogue model construction method based on a mixed granularity attention mechanism, which comprises the following steps of: s1: preprocessing the text such as word segmentation, word stop, word vector coding and the like; s2: using an input encoder to encode the converted high-dimensional vector into a sentence vector, and memorizing the details of the conversation; s3: the context encoder encodes the sentence vector; s4: the context coding layer outputs an attention mechanism combined with sentence granularity to realize the context coding; s5: step S4 outputs as input the first layer of the output decoder, decoding by decoding the first layer of the layer; s6: calculating an attention value of word granularity; s7: the output of the first layer of the decoder is combined with the attention value of the word granularity calculated in step S6, and the output generated by the decoder is mapped to the dimension of the word list size, and the result is output. The method and the device greatly improve the accuracy of generating the reply by performing multiple rounds of conversation tasks on the actual data set.

摘要：【中文】本发明属于航天发射领域与航天测控领域，公开了一种基于遥测数据的航天器动力学模型高精度动态构建方法。本发明首先根据航天器遥测弹道序列计算发射惯性坐标系的视速度序列；然后通过计算发射惯性坐标系与发射坐标系之间的方向余项矩阵，得到发射坐标系视速度序列；最后根据发射坐标系视速度序列，动态构建航天器动力学模型。本发明只需要直接应用遥测数据构建航天器动力学模型，成功地避开了所有与航天器具体结构、性能参数和控制规律相关的细节，同时又能够真实准确反映其动力学特性，是以往从来没有出现过的新方法。 【EN】The invention belongs to the field of space launching and the field of space measurement and control, and discloses a high-precision dynamic construction method of a spacecraft dynamics model based on telemetering data. Firstly, calculating an apparent velocity sequence of a launching inertial coordinate system according to a telemetering ballistic sequence of a spacecraft; then, obtaining a visual velocity sequence of the emission coordinate system by calculating a direction remainder matrix between the emission inertial coordinate system and the emission coordinate system; and finally, dynamically constructing a spacecraft dynamics model according to the apparent velocity sequence of the emission coordinate system. The invention only needs to directly apply the telemetering data to construct the spacecraft dynamics model, successfully avoids all details related to the specific structure, performance parameters and control rules of the spacecraft, and can truly and accurately reflect the dynamics characteristics, so that a new method never appears in the past.

摘要：【中文】本发明属于导航测量技术领域与卫星导航应用技术领域，公开了一种基于导航卫星信号单短基线的定向方法。本发明首先建立单测量短基线在地心坐标系中的方向矢量的估值模型；然后计算单测量短基线在地心坐标系中的方向矢量估值；最后计算单测量短基线的方位角估值和高低角估值，从而完成该基线的定向。本发明利用目标上的由两个导航卫星信号接收天线构成的单测量基线完成测量基线的定向，将测量基线的长度控制在卫星下行载波信号的半个波长之内，大幅度缩短测量基线，可以安装在小型或微型目标上。 【EN】The invention belongs to the technical field of navigation measurement and satellite navigation application, and discloses a single short baseline orientation method based on navigation satellite signals. Firstly, establishing an estimation model of a direction vector of a single-measurement short baseline in a geocentric coordinate system; then calculating the direction vector estimation value of the single-measurement short baseline in the geocentric coordinate system; and finally, calculating the azimuth angle estimation value and the elevation angle estimation value of the single-measurement short baseline so as to complete the orientation of the baseline. The invention uses the single measuring base line formed by two navigation satellite signal receiving antennas on the target to complete the orientation of the measuring base line, controls the length of the measuring base line within half wavelength of the satellite downlink carrier signal, greatly shortens the measuring base line, and can be installed on a small or miniature target.

摘要：【中文】本发明属于航天发射领域与航天测控领域，公开了一种航天发射光、雷、遥与导航卫星测量数据融合处理方法。首先，利用遥测弹道数据建立运载火箭的动力学方程；其次，建立光学、雷达与导航卫星测量系统的观测方程以及各观测方程的雅可比矩阵；然后，融合航天发射光学、雷达、遥测弹道数据与导航卫星测量数据，建立运载火箭弹道参数滤波处理方程；最后，计算融合航天发射光学、雷达、遥测弹道数据与导航卫星测量数据的运载火箭弹道参数估值。本发明充分利用各类弹道数据的优势，解决了缺乏航天发射光学、雷达、遥测弹道数据与导航卫星测量数据实时深度融合处理的技术问题。 【EN】The invention belongs to the field of space launching and the field of space measurement and control, and discloses a method for fusion processing of space launching light, thunder, remote and navigation satellite measurement data. Firstly, establishing a dynamic equation of a carrier rocket by utilizing telemetering ballistic data; secondly, establishing observation equations of an optical, radar and navigation satellite measurement system and a Jacobian matrix of each observation equation; then, integrating space launch optics, radar, telemetering ballistic data and navigation satellite measurement data, and establishing a carrier rocket ballistic parameter filtering processing equation; and finally, calculating estimated values of the launch vehicle trajectory parameters fusing the space launch optics, radar, telemetering ballistic data and navigation satellite measurement data. The invention fully utilizes the advantages of various types of ballistic data and solves the technical problem of lack of real-time deep fusion processing of space launching optics, radar, telemetering ballistic data and navigation satellite measurement data.

摘要：【中文】本发明属于航天发射领域与航天测控领域，公开了一种运载火箭导航计算与外测系统时间零点差实时估算方法。该方法将运载火箭起飞段的遥测弹道序列转换成发射坐标系的弹道序列，计算运载火箭在测量坐标系的弹道序列；利用运载火箭在测量坐标系的弹道序列，计算测速主站的斜距变化率序列以及其它副站的距离和变化率序列；然后构建遥、外测零点差估算模型，估算遥、外测零点差；最后校准遥、外测零点差。本发明利用航天发射场高精度测速雷达径向速率测量精度很高和运载火箭起飞段遥测弹道精度也很高的特点，构建遥、外测零点差估算模型，实时消除遥测弹道数据与外测数据的时间零点差，解决了以前国内外一直没有解决的技术难题。 【EN】The invention belongs to the field of space launching and the field of space measurement and control, and discloses a real-time estimation method for time zero difference of a carrier rocket navigation calculation and external measurement system. The method comprises the steps of converting a telemetering ballistic sequence of a takeoff section of a carrier rocket into a ballistic sequence of a launching coordinate system, and calculating the ballistic sequence of the carrier rocket in the measuring coordinate system; calculating a slope distance change rate sequence of the speed measuring main station and distance and change rate sequences of other secondary stations by utilizing a ballistic sequence of the carrier rocket in a measuring coordinate system; then constructing a remote and external zero difference estimation model, and estimating remote and external zero differences; and finally calibrating the zero difference between the remote measurement and the external measurement. The method utilizes the characteristics that the high-precision speed measuring radar in the space launching field has high radial speed measuring precision and the remote measuring trajectory precision of the takeoff section of the carrier rocket is also high to construct a remote and external measurement zero point difference estimation model, eliminates the time zero point difference between the remote measuring ballistic data and the external measurement data in real time, and solves the technical problem which is not solved at home and abroad in the past.