炮风洞中进行高温喷流底部热流、压力测量试验

本文介绍了在北京空气动力研究所炮风洞 M 数为6、7、8的气流中进行具有高温喷流的模型底部热流和压力测量试验的有关试验技术。试验结果表明底部对流热流和压力测量值随外流 M 数增大而减小,他们都大于无外流时的测值。辐射热流不受外流影响。     

确定风洞模型压力中心的变距测力试验

本文提出了采用变换模型相对天平校准中心位置来测得同一状态下的不同俯仰力矩值,再通过数学处理或作图获得小攻角下的精确压力中心位置的试验方法。某型号用本方法试验得到了令人满意的结果。     

超声速流中激波/湍流附面层干扰数值模拟

采用修正的B／L湍流模型以及多块结构化网格求解了二维N-S方程。分别对超声速流和高超声速流中的激波／湍流附面层干扰进行了数值研究。本文首先研究了进口马赫数为2．96的超声速流。计算结果准确预测了入射斜激波在平直壁面引起湍流附面层分离的流动特征：分离点的反射激波、分离包引起的膨胀扇以及再附点的反射激波。计算的壁面压力分布与实验值吻合较好，计算的分离区长度与实验值比较有一定误差。本文还对进口马赫数为9．22的高超声速流中压缩角引起的激波／湍流附面层干扰进行了数值研究。计算结果与实验结果吻合较好。     

The characteristics of sharp (small-scale) boundaries of solar wind plasma and magnetic field structures

We investigate properties of large (>20%) and sharp (<10 min) solar wind ion flux changes using INTERBALL-1 and WIND plasma and magnetic field measurements from 1996 to 1999. These ion flux changes are the boundaries of small-scale and middle-scale solar wind structures. We describe the behavior of the solar wind velocity, temperature and interplanetary magnetic field (IMF) during these sudden flux changes. Many of the largest ion flux changes occur during periods when the solar wind velocity is nearly constant, so these are mainly plasma density changes. The IMF magnitude and direction changes at these events can be either large or small. For about 55% of the ion flux changes, the sum of the thermal and magnetic pressure are in balance across the boundary. In many of the other cases, the thermal pressure change is significantly more than the magnetic pressure change. We also attempted to classify the types of discontinuities observed.     

环路热管内工质流动特性的研究

由于环路热管（LHP）具有高传热性能、远距离传输热量、优良的控温特性和管路的可任意弯曲、安装方便等特点，使LHP在航天热控领域有着广泛的应用前景。文章对LHP内工质的流动压力降进行了分析和计算；对毛细芯所能提供的最大蒸发传热能力进行了预测，并结合实验研究综合分析了毛细芯结构对LHP性能的影响。     

微结构谐振传感器

阐述了频率输出的新型谐振传感器的发展方向之一——微型化。评价性地论述了热激励硅谐振压力传感器和热激励谐振膜质量流量传感器。重点讨论了热激励的原理,特点等。指出我国应对传感器的这一发展趋势给予足够的重视。     

大厚度比零件（外侧）和波纹管（内侧）的缝焊研究

某重点型号波纹管组合件的设计要求是缝焊，对照以往产品的结构，比较明显的情况是波纹管在零件的内侧。零件的厚度是3mm，波纹管的厚度是0.1mm，零件与波纹管的厚度比比较大。波纹管在零件的内侧会产生一个问题：波纹管在焊接过程中会逐渐收缩，到最后与零件之间产生间隙，导致局部形不成焊缝。研究通过减小车配间隙,增加冷却手段、滚轮厚度和压力等措施来实现大厚度比的零件和波纹管之间的缝焊。     

Effects of Mach numbers on Magnus induced surface pressure

Experimental and numerical methods were used to investigate the Magnus phenomena over a spinning projectile. The pressure force acting on the surface of a spinning projectile was measured for various cases by employing a relatively novel experimental technique. A set of miniature pressure sensors along with a data acquisition board, battery and storage memory were placed inside a spinning model and the surface pressure were obtained through a remotely controlled system. Circumferential pressures of the model for both rotational and static conditions were obtained at two different free stream Mach numbers of 0.4 and 0.8 and at different angles of attack. The results showed the ability of this new test method to measure the very small Magnus force via surface pressures over the projectile. The results provide a deep insight into the flow structure and illustrate changes in the cross-flow separation locations as a result of rotation. Similar results were obtained by the numerical simulations and were compared with the experimental data.     

Fast spacecraft solar radiation pressure modeling by ray tracing on graphics processing unit

A novel method is presented to evaluate on the graphics processing unit (GPU) the force and torque on a spacecraft due to solar radiation pressure. The method employs efficient ray tracing techniques, developed in the graphics rendering discipline, to resolve spacecraft self-shadowing and reflections at faster than real-time computation speed. The primary algorithmic components of the ray tracing process which contribute to the method’s computational efficiency are described. These components include two-level bounding volume hierarchy acceleration data structures, fast ray to bounding box intersection testing using the slab intersection algorithm and fast triangle intersection testing using the Möller-Trumbore algorithm. Spacecraft material optical properties are represented as a combination of Lambertian diffuse and ideal specular reflections. Both diffuse and specular ray-surface interactions are modeled. The approach is implemented using C++ and OpenCL and executed on a consumer grade GPU. Model validation is presented comparing ray traced force and torque values to the same quantities produce by a faceted analytic model. Numerical results illustrate the impact of self-shadowing on the force and torque calculation, and demonstrate the fast computational speed that is enabled with this implementation.     

Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator

Numerical simulation and theoretical analysis were conducted to study the hysteresis inside scramjet isolator during the reciprocating process of back pressure variation. It is revealed that only a regular reflection is theoretically possible for two leading shocks when the inflow Mach number is greater than 2.0, and no hysteresis can occur in the transition between shock reflection types. Nevertheless, wall suction, gas injection, and background waves cause non-uniformity of the incoming flow and would make hysteresis possible. Besides the classical hysteresis in the transition between shock reflection, new kinds of hysteresis were found in both the deflection angle of separated boundary layer and the location of the shock train. Moreover, the occurrence of hysteresis in the deflection angle of the separated boundary layer is accompanied with the shock reflection hysteresis. In the case with background waves or gas injection, hysteresis in the starting position of leading shock was observed too. As back pressure decreases, the leading shock does not follow the same path as that as the back pressure increases, and it is anchored at the location where the background shock or the injection interacts with the leading shock. It is inferred that, if two strong adverse pressure gradient regions move towards and interact with each other, hysteresis will take place when they start to separate.