摘要：Personalized drugs,as well as disease-specific and condition-dependent drug release,have been highly desired in drug delivery systems for effective and safe ***-dimensional(4 D)printing,as a newly emerging technique to develop drug capsules,displays unique advantages that can autonomously control drug release according to the actual physiological ***,core-shell structured hydrogel capsules were developed using a multimaterial extrusion-based 4 D printing method,which consists of a model drug as the core and UV cross-linked poly(N-isopropylacrylamide)(PNIPAM)hydrogel as the *** to the lower critical solution temperature(LCST)-induced shrinking/swelling properties,the prepared PNIPAM hydrogel capsules showed temperature-responsive drug release along with the topography changes in the cross-linked PNIPAM *** in vitro drug release test confirmed that the PNIPAM hydrogel capsules can autonomously control their drug release behaviors according to changes in ambient ***,the increased shell thickness of these capsules causes an obvious reduction in drug release rate,distinctly indicating that the drug release behavior can be well adjusted by setting the shell thickness of the *** proposed 4 D printing strategy pioneers the paradigm of smart drug release by showing great potential in the smart controlled release of drugs and macromolecular active agents.

摘要：The multidisciplinary design optimization(MDO)approach is very crucial for the conceptual design of the aircraft,and this is due to the complex interaction between different disciplines, especially for the hypersonic vehicle. In the hypersonic vehicle, the airframe and the engine are highly integrated. In the current survey, the research progress in the MDO approach has been reviewed comprehensively from four primary techniques, namely the design of experiments, the surrogate modeling, the optimization method and the MDO framework, and its application to the aerospace engineering has been summarized from its category as well. The concurrent subspace optimization approach is the most popular method in the aerospace engineering for its easy implementation, and following is the collaborative optimization approach. The multi-level optimization approach has attracted a growing attention due to its high efficiency. In conclusion, some promising research recommendations have been put forward, namely the combination of the low- and high-fidelity optimization approaches, the consideration of the uncertainty analysis and the MDO approach coupled with the data mining techniques.

摘要：Numerical simulations and experiments showed that bump inlet had a remarkable effect on boundary layer diversion of supersonic ***,the design and analysis of bump in hypersonic flow was still *** this paper,the mechanism of a supersonic bump inlet is introduced to the design of hypersonic forebody.A hypersonic inlet with an integrated bump/forebody is obtained by the Method Of Characteristics(MOC)based on a chin *** simulations show that the modified inlet achieves diversion of low-speed ***,the integrated bump/-forebody is also beneficial to inlet *** the starting process,the shape of the separation zone is rebuilt by the modified forebody surface which makes spillage much *** new design leads to a reduction of the self-start Mach number by 0.95.

摘要：人类活动干扰下荒野空间不断被压缩,导致生物多样性受到严重威胁。中国创新划定并严守的生态保护红线(ECR)在生态文明建设和生态环境保护方面发挥了巨大作用。然而,荒野地概念起源较晚,以往划定ECR时,几乎都未考虑荒野地保护这一因素。本研究以经济较为发达的浙江省为案例,基于改进的荒野识别模型将荒野地与现有ECR进行叠加分析,评估了ECR对荒野保护的贡献。同时,考虑荒野地经济效益与生态效益的平衡及空间分布差异,提出现有ECR的潜在优化路径。结果表明:2010—2020年间,浙江省荒野地分布呈现西多东少的分布格局,荒野地面积减少20.8%,荒野地质量整体呈明显降低趋势;研究期间,红线内荒野地丧失较少,且27.2%的荒野地质量有所提升,红线外荒野地丧失严重且整体质量下降;现有ECR对荒野地保护覆盖率仅为29.8%,存在明显的保护空缺,整合优化后的ECR面积增加40.2%,受保护的荒野面积增加135.8%。本研究模式为提高ECR保护效率、制定关键荒野保护途径、促进城镇可持续发展与生物多样性的维持提供了理论依据。

摘要：为实现高超声速二元进气道前体激波的压缩能力、压缩效率、流量捕获特性和结构长度可控,提出了平面曲线激波逆向设计方法。采用B-Spline曲线控制激波形状。利用有旋特征线法,求解激波的影响域及决定激波的壁面。设计了一凹激波,并对波后流场进行CFD无黏数值模拟,CFD结果和设计结果一致,验证了设计方法的可行性。此外,还设计了直激波、凹激波和凸激波3种激波,并对其在设计点和非设计点处的性能开展了数值研究。在设计点处,分析了激波的压缩比、激波的总压恢复系数、激波压缩区的压升、激波压缩区出口马赫数和流动角随激波控制角的变化规律。在非设计点处,分析了激波压缩区的流量系数和总压恢复系数随攻角和马赫数的变化规律。

摘要：为研究时滞忆阻神经网络的全局指数镇定性,并克服忆阻突触连接权矩阵突然跳变所带来的困难,借助非光滑分析和微分包含理论给出了系统Filippov解的定义.根据Lyapunov稳定性理论,通过设计时滞依赖的反馈控制律,实现了所考虑忆阻网络模型的指数镇定.所设计的反馈控制律,使用于多数已存在的忆阻网络模型的镇定性控制.所设计的镇定性算法简单,容易实现,结论描述了忆阻器件的基本电力学规律.

摘要：提出了基于B-Spline曲线和特征线方法的超声速型面可控喷管设计方法,通过设置喷管轴向马赫数分布可以灵活地调整喷管的型面形状。数值验证结果表明,该方法不仅可以设计出高品质的喷管出口流场,而且能够实现喷管型面的灵活调整,可以获得长度与最短长度喷管一致,但流场品质更优的喷管。

摘要：固体运载火箭传统耗尽关机制导方法姿态角调整次数过多,不利于控制系统设计。提出了姿态角单次调整的耗尽关机能量管理策略:以火箭的待增视速度方向为基准,通过计算火箭所需耗费的视速度,优化选取火箭的初、末姿态角;火箭以恒定角速率从初姿态角变为末姿态角,达到末姿态角时保持恒定,直至耗尽关机。仿真结果表明,新方法在满足火箭的终端速度约束条件下,视速度模量耗费百分比超过30%,且姿态角单向调整,有利于控制系统的工程设计。

摘要：介绍了一种宇航用的利用产生燃气做功并通过提升机构完成提升动作的微型燃气发生器的设计。建立了描述燃气发生器内部流场的数学物理方程。通过数值方法模拟了燃气发生器内部的燃烧和流动以及提升机构的运动过程。由模拟结果及理论分析来指导药柱的设计，

摘要：以二维轴对称高超声速进气道为研究对象,研究唇口角对进气道总压恢复性能、阻力性能和起动性能的影响,开展多目标考虑下唇口角设计。首先,采用三阶准均匀B样条对唇罩进行参数化设计,获得具有不同唇口角的进气道构型。然后基于数值仿真方法研究唇口角对进气道总压恢复性能、阻力性能和起动性能的影响。结果表明,存在一个最佳唇口角使进气道总压恢复性能最佳。分析发现唇口角过小时入口处会形成强烈唇口激波,唇口角过大时内收缩段会形成汇聚激波,二者均会造成严重总压损失。在阻力性能研究中发现通过减小唇口角,可有效减小内外唇罩阻力,但压缩侧壁面阻力因唇口激波强度增加而增大,在三者共同作用下进气道总阻力随唇口角增大表现出先减小后增大的规律。在唇口角对起动性能的影响研究中同样发现存在一个最佳唇口角使进气道起动性能最佳。唇口角过小时大尺度分离区难以被吞入,唇口角过大时分离区在内收缩段形成稳定驻留,两者均不利于进气道起动。最后,分析了不同内收缩比下进气道唇口角对总压恢复性能、阻力性能和起动性能的影响,并对多目标考虑下最优唇口角设计展开研究。结果表明使总压恢复性能、阻力性能和起动性能分别最佳的唇口角并不重合,但总体而言三者相差不大,通过唇口角设计可使进气道同时达到较好的总压恢复性能、阻力特性和起动性能。