Evaluation on difference of therapeutic efficacy of Jiawei Xiaoyao Granules and Pills in treatment of emotional disorder during perimenopause based on Greene Climacteric Scale

目的:在前期加味逍遥丸治疗围绝经期情绪障碍具有比较优势的基础上,基于grEEnE量表探讨其颗粒剂和丸剂不同剂型间疗效差异。方法:经筛选后患有情绪障碍的围绝经期女性75例随机等分为A、b、C3组,分别对应采用帕罗西汀、加味逍遥丸和加味逍遥颗粒剂治疗8周。所有患者在治疗前后各进行1次grEEnE及其子因子评定,并在观察期结束时进行TESS评定。结果:grEEnE总分差及其焦虑、抑郁因子分差:3种治疗方法均能改善,且相互间无显著差异;grEEnE性因子和血管因子分差:后二组均优于A组(P<0.01);TESS评分:与A组比较,b、C组均有统计学意义(P<0.01),评分均小于A组,且后二组间无显著差异。结论:加味逍遥的2种剂型间疗效无显著差异,考虑到帕罗西汀的不良反应,治疗该病加味逍遥的2种剂型都值得推荐。Objective: To investigate the difference in therapeutic efficacy between Jiawei Xiaoyao Granules and pills based on the preliminary research of treating emotional disorder during perimenopause with Jiawei Xiaoyao Pills and Greene Climacteric Scale.Methods: 75 female patients with emotional disorder during perimenopause were slected and randomly divided into 3 groups as group A, B and C.Patients in the 3 groups were treated with paroxetine, Jiawei Xiaoyao Pills and Jiawei Xiaoyao Granules respectively for 8 weeks.Greene and Greene factors assessment were carried out in all the patients before and after treatment, and the TESS assessment was carried out at the end of the observation period.Results: The three therapies all could improve the gap in total score of Greene and its factors as anxiety and depressed, and the difference among these three groups was no significant.The factors of Greene and gap in score of vascular factors of group B and C was better than that of group A(P<0.01).The difference in TESS score between group A and group B and C was significant(P<0.01), while the difference between group B and group C was not significant.Conclusion: The difference in curative effect between the two formulations was not significant.Because of the adverse reactions of paroxetine, in the treatment of emotional disorder during perimenopause, the two formulations of Jiawei Xiaoyao Powder were worth to be recommended.国家自然科学青年基金项目(No.81302960)~

气相爆轰波DDT过程的物理模型

气相爆轰波的爆燃转爆轰过程(deflagration to detonation transition, DDT)所需的起爆能量比直接起爆小几个数量级,是一种经济有效的起爆方式。DDT过程涉及激波动力学、湍流燃烧、化学反应动力学等多种效应,包含丰富的物理机制,这些机制的相互作用规律仍不明确,是一项具有挑战性的前沿课题。本研究根据DDT的数值模拟结果和相关实验规律,提出了一个DDT的物理模型,该模型的核心思想是:在实验室坐标系下,爆轰波面和火焰面是跨声速的,火焰面的超声速和亚声速流动会产生不同的流动行为,直接影响爆轰波的DDT过程,爆轰波面的跨声速流动是产生DDT过程的关键机制。通过提出的物理模型和一维数值模拟,采用总包一步反应模型和详细反应模型,均得到了DDT的物理过程,利用该物理模型解释了两种计算结果的差异以及和DDT有关的各种实验现象

Formation of stabilized oblique detonation waves in a combustor

Initiation and stabilization of oblique detonation waves (ODWs) are important to the successful application of oblique detonation engines (ODEs), which, however, have been rarely studied under realistic combustor conditions. In this study, the flow structures, stabilization characteristics and potential thrust performance (under different combustor's geometries with different ODW reflection locations) in a typical hydrogen-fueled ODE combustor are numerically studied by solving the two-dimensional multi-species Reynolds-averaged conservation equations with a detailed hydrogen combustion mechanism. Results suggest that all the detonation waves/shock waves can be stabilized in the space-confined combustor, and the boundary layer separation induced by the ODW-boundary layer interaction is found crucial to determining the types of combustion mode in the combustor. Except for the expected ODW-induced combustion, fast combustion induced by a stabilized overdriven normal detonation wave (NDW) may exist in the combustor simultaneously (even up to a large extent, > 73.7%). It is demonstrated that the stabilization of the overdriven NDW in the combustor can be attributed to the formation of an effective aerodynamic convergent-divergent nozzle that quickly accelerates the subsonic flow behind the NDW to supersonic, preventing downstream disturbances from propagating upstream. Benefiting from the chemical equilibrium shift caused by the expansion effect of the flow, more heat is released to compensate for the compression loss and the simulated thrust performance is shown not deteriorate significantly even with a large percentage of NDW-induced combustion existing in the ODE combustor. This work would be beneficial to the future developments of the ODEs. (C) 2020 The Combustion Institute. Published by Elsevier Inc. All rights reserved

鼓包诱导斜爆震波的数值研究

为实现低马赫数条件下斜爆震波的快速起爆，以及提高斜爆震波对来流扰动的抗干扰能力，提出了通过在诱导区内设置一个小鼓包来控制斜爆震波起爆的方案，并通过数值求解二维多组分欧拉方程研究了楔面和鼓包诱导的斜爆震波。结果表明：通过在诱导区内设置鼓包可实现斜爆震波的提前起爆；且在较宽马赫数范围内，其起爆位置相对固定。鼓包诱导的斜爆震波主要有强耦合和弱耦合两种起爆形式，起爆形式与鼓包和斜激波的相对位置有关。此外，来流扰动会使楔面诱导的斜爆震波剧烈振荡，不利于斜爆震发动机的稳定工作；鼓包的存在对来流扰动所引发的斜爆震波振荡具有一定的抑制作用

提高高马赫数超燃冲压发动机推力的理论方法

斜爆轰发动机和激波诱导燃烧冲压发动机在高马赫数吸气式发动机中具有重要应用前景,但是斜爆轰发动机是否具有足够大的净推力,还是一个未知的问题,因此需要对高马赫数冲压发动机的推进性能以及提高推力的方法进行理论研究.本文主要分为3部分.第1部分理论研究了超燃冲压发动机中的爆燃波和爆轰波的传播特性.保证发动机稳定燃烧是提高推力的前提.通过对爆燃波和爆轰波传播特性研究,得到了影响发动机燃烧稳定性的关键参数和物理规律.第2部分研究了发动机处于热壅塞临界状态下的燃烧规律和推力特性.在临界状态下,燃烧室入口气流速度正好等于爆轰波传播速度,二者处于平衡状态,这是发动机推进性能的理论上限.第3部分研究了提高高马赫数超燃冲压发动机推力的理论方法.对于高马赫数冲压发动机,燃烧室入口气流速度远远大于爆轰波的传播速度,这部分速度差就是提高推力的理论空间.对于马赫数Ma≥12的超燃冲压发动机,理论上燃烧产生的爆燃波或激波不会引起发动机不起动,因此可以通过进一步添加燃料和氧化剂的方法来提高其推力.理论分析结果表明,对于高马赫数超燃冲压发动机,不但燃烧流场是容易稳定的,而且可以有很多方法来进一步提高推力

一种深海探测设备运行作业管理方法

本发明涉及一种深海探测设备运行作业管理方法。包括以下步骤：配置运行作业，用于配置运行作业类型，同时配置每种作业类型的关键数据以进行分析；配置运行作业任务，用于配置深海探测设备具体的运行作业任务，同时需要配置运行作业任务的关键数据以进行分析；运维任务自动生成，根据配置完成的运行作业以及运行作业任务，时间点自动生成运行作业任务，对运行作业任务进行详细记录，同时获取此运行作业的关键数据信息。本发明可配置性极强，可根据不通深海探测设备运行作业的类型生成相对应的运行作业内容，同时本发明具有强大的分析功能，根据深海探测设备的运行作业数据进行潜水器优良状况分析，同时进行预警，提高深海探测设备运行效率

一维与二维爆轰传播的时空关联特性数值研究

一维爆轰传播的理论完备、计算准确,二维斜爆轰传播由于壁面与黏性效应,大尺度、高精度预测还有一定难度.利用Euler方程和H_2-Air基元反应模型,对二维有限长楔面诱导的斜爆轰和活塞驱动一维非定常正爆轰进行计算比较研究,从时空两个维度方面,分析了两者在起爆过程、稀疏波传播、爆轰波面演化中的关联特性.研究结果表明:在过驱动度相同的条件下,经过时空变换的活塞驱动一维爆轰传播与二维驻定斜爆轰在起爆区波系结构、波面演化特征和主要参数分布规律方面无论定性或者定量对比均符合较好,所以,一维非定常爆轰和二维驻定斜爆轰具有时空相关性.两者的差异主要体现在过驱动斜爆轰受稀疏波影响过渡到近Chapman-Jouguet (C-J)爆轰状态所需的弛豫时间不同,原因可能是起源于活塞和壁面稀疏波强度的差异.本文提出的一维与二维爆轰传播的时空关联方法不仅有助于认知斜爆轰起爆、过驱爆轰产生、胞格爆轰演化的三阶段规律,还可以对比揭示壁面、边界层和黏性效应的影响,应用在斜爆轰发动机燃烧室设计中能够有效节约计算时间和成本,并降低复杂度

A theoretical method for solving shock relations coupled with chemical equilibrium and its applications

In this study, a theoretical method is proposed to solve shock relations coupled with chemical equilibrium. Not only shock waves in dissociated flows but also detonation waves in com-bustive mixtures can be solved. The global iterative solving process is specially designed to mimic the physical and chemical process in reactive shock waves to ensure good stability and fast conver-gence in the proposed method. Within each global step, the single-variable equations of normal and oblique shock relations are derived and solved with the Newton iteration method to reduce the com-plexity of the problems, and the minimization of free energy method of NASA (National Aeronau-tics and Space Administration) is adopted to solve equilibrium compositions. It is demonstrated that the convergent process is stable and very close to the real chemical-kinetic process, and high accuracy is achieved in the solutions of normal and oblique reactive shock waves. Moreover, the proposed theoretical method has also been applied to many problems associated with reactive shocks, including the stability of oblique detonation wave, bow detonation over a sphere, and shock reflection in dissociated air. The great importance of using chemical equilibrium to theoretically pre-dict the theoretical range of the wedge angle for a standing oblique detonation wave (the standing window of the oblique detonation wave), the stand-off distance of bow detonation wave and the transition criterion of shock reflection in dissociated air with high accuracy have been addressed.(c) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)

Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection

In this study, the performances of a Mach 9 oblique detonation engine fueled by hydrogen are numerically investigated by solving the multi-species reactive Reynolds-averaged Navier-Stokes (RANS) equations with a detailed combustion mechanism. The fuel is perpendicularly pre-injected into the core airflow in the engine inlet by three parallel strut-injectors. It is demonstrated that mixing can be enhanced by the baroclinic effect of oblique shock waves, the incipient expansion of fuel jets and the intensive momentum exchange of vertical jets into the crossflow, resulting in a well-mixed fuel-air core flow before entering the combustor. Analyses of the two most dangerous zones that bear potential of pre-ignition suggest that no pre-combustion occurs in the inlet. Benefiting from the floor bleed structure, the upstream movement of the shock waves stops at the combustor's entrance and they remain stabilized in the combustor thereafter. Finally, the combustor is proved to work under the stable detonation mode of combustion, and the supersonic fuel-air mixture is fast burnt through the steady detonation waves generated in the combustor. The concept of the pre-injection oblique detonation engine has been numerically demonstrated, which provides a significant reference to further experimental studies and future engineering applications. (C) 2020 Elsevier Masson SAS. All rights reserved

斜爆轰发动机燃烧机理试验研究

为了研究斜爆轰发动机的稳定燃烧机理,开展了飞行马赫数9的斜爆轰发动机的数值模拟研究和试验研究。设计了全尺度斜爆轰发动机模型,发动机的总长度为2.8m。采用两级进气道压缩,每级压缩角度均为15°。利用三个小支板在进气道前缘主流核心区中进行氢气的喷射和混合。采用带化学反应的雷诺平均N-S方程、SST k-ω模型以及9组分19步反应的基元反应模型,对氢气混合过程和发动机燃烧过程进行了数值模拟研究。结果表明,氢气在进气道内混合得比较均匀,在燃烧室内获得了稳定的斜爆轰流场和正爆轰流场。在激波风洞中开展了马赫数9状态下的斜爆轰发动机稳定燃烧机理试验研究,在50ms的风洞有效试验时间内获得了持续稳定的斜爆轰流场,试验结果与数值模拟结果吻合较好,表明在试验中形成了斜爆轰波。研究结果证明了斜爆轰发动机的技术可行性