Study on Compressive Properties of Z-pinned Laminates in RTD and Hygrothermal Environment

Compressive tests of [0] 12 and [90] 12 unidirectional laminates and [45/0/-45/90] 2S quasi-isotropic laminates are accomplished in both room-temperature and dry (RTD) and hygrothermal environment. And simulation studies on the compressive strength of Z-pinned laminates of [0] 12 and [45/0/-45/90] 2S are conducted by using finite element analysis (FEA). A microstructural unit cell for FEA is created to simulate a representative laminates unit with one pin. Within the unit cell, the first directions of the elements’ material coordinate systems are changed to simulate the fibres’ deflecting around the pin. The hygrothermal effect is simulated by the material properties’ adjustments which are determined by the compressive tests of non-pined laminates. The experimental results indicate that the percentage of reduction in the compressive modulus of Z-pinned laminates caused by Z-pin becomes smaller with the percentage of 0° fibres decreasing in the laminates; the compressive strength of quasi-isotropic laminates reduces and the percentage of the reduction in the compressive strength declines with Z-pin volume content increasing, and the moisture absorption ratio of the Z-pinned specimens is greater than that of the non-pinned specimens, because the cracks around Z-pin increase the moisture absorption. In addition, the simulations show that the deflection of fibres around Z-pin is the main factor for the reduction in the compressive strength of Z-pinned unidirectional laminates, the dilution of fibre volume content caused by resin-rich pocket is the principal factor for the decline in the compressive strength of Z-pinned quasi-istropic laminates, and the compressive strength of Z-pinned specimens in hygrothermal environment reduces as the result of superimposition of some factors, including the changes in material properties caused by hygrothermal environment, the deflection of fibres and the resin-rich pocket caused by Z-pin.     

Low-frequency Periodic Error Identification and Compensation for Star Tracker Attitude Measurement

The low-frequency periodic error of star tracker is one of the most critical problems for high-accuracy satellite attitude determination.In this paper an approach is proposed to identify and compensate the low-frequency periodic error for star tracker in attitude measurement.The analytical expression between the estimated gyro drift and the low-frequency periodic error of star tracker is derived firstly.And then the low-frequency periodic error,which can be expressed by Fourier series,is identified by the frequency spectrum of the estimated gyro drift according to the solution of the first step.Furthermore,the compensated model of the low-frequency periodic error is established based on the identified parameters to improve the attitude determination accuracy.Finally,promising simulated experimental results demonstrate the validity and effectiveness of the proposed method.The periodic error for attitude determination is eliminated basically and the estimation precision is improved greatly.     

Cycle-slip Detection of GPS Carrier Phase with Methodology of SA4 Multi-wavelet Transform

That cycle-slips remain undetected will significantly degrade the accuracy of the navigation solution when using carrier phase measurements in global positioning system (GPS). In this paper, an algorithm based on length-4 symmetric/anti-symmetric (SA4) orthogonal multi-wavelet is presented to detect and identify cycle-slips in the context of the feature of the GPS zero-differential carrier phase measurements. Associated with the local singularity detection principle, cycle-slips can be detected and located precisely through the modulus maxima of the coefficients achieved by the multi-wavelet transform. Firstly, studies are focused on the feasibility of the algorithm employing the orthogonal multi-wavelet system such as Geronimo-Hardin-Massopust (GHM), Chui-Lian (CL) and SA4. Moreover, the mathematical characterization of singularities with Lipschitz exponents is explained, the modulus maxima from wavelet to multi-wavelet domain is extended and a localization formula is provided from the modulus maxima of the coefficients to the original observation. Finally, field experiments with real receiver are presented to demonstrate the effectiveness of the proposed algorithm. Because SA4 possesses the specific nature of good multi-filter properties (GMPs), it is superior to scalar wavelet and other orthogonal multi-wavelet candidates distinctly, and for the half-cycle slip, it also remains better detection, location ability and the equal complexity of wavelet transform.     

Safety Analysis of Flow Parameters in a Rotor-stator Cavity

In order to ensure the safety of engine life limited parts (ELLP) according to airworthiness regulations, a numerical approach integrating one-way fluid structure interaction (FSI) and probabilistic risk assessment (PRA) is developed, by which the variation of flow parameters in a rotor-stator cavity on the safety of gas turbine disks is investigated. The results indicate that the flow parameters affect the probability of fracture of a gas turbine disk since they can change the distribution of stress and temperature of the disk. The failure probability of the disk rises with increasing rotation Reynolds number and Chebyshev number, but descends with increasing inlet Reynolds number. In addition, a sampling based sensitivity analysis with finite difference method is conducted to determine the sensitivities of the safety with respect to the flow parameters. The sensitivity estimates show that the rotation Reynolds number is the dominant variable in safety analysis of a rotor-stator cavity among the flow parameters.     

卫星在轨故障全数字仿真平台设计

以通信卫星为例,分析卫星已经发生的和可能出现的在轨故障信息,利用数据库与面向对象技术对在轨故障现象与故障排除过程的仿真进行建模,设计了一种通过遥测信息显示故障仿真过程的全数字仿真平台,可为卫星在轨故障的辅助分析与定位、故障解决预案的制定提供验证手段。     

Recent Progresses of Magnetospheric Physics in China: 2010-2011

In the past two years, many progresses are made in magnetospheric physics by using either the data of Double Star Program, Cluster and THEMIS missions, or by computer simulations. This paper briefly reviews these works based on papers selected from the 80 publications from April 2010 to April 2011. The subjects covered various sub-branches of magnetospheric physics, including geomagnetic storm, magnetospheric substorm, etc.      

惯性平台的实时自校准

为了鉴定导弹的精度和提高导弹的精度,都需要准确地适时地测得惯性平台的各项工具误差,即进行平台的校准。平台利用自身的硬件条件进行发射前实时、自主的校准,具有许多特有的优点。采用卡尔曼滤波方法实现这一校准过程可以在精度和速度上同时取得较满意的效果。本文针对一个具体的三轴平台设计了一种用卡尔曼滤波估计各主要误差的过程。仿真计算表明了方法的可行性。在给定现实条件的基础上,所得估计精度能满足系统的要求。     

固体火箭发动机喷管集成设计分析技术研究

固体火箭发动机喷管不仅结构形式多样,而且工作条件恶劣,长期以来难以找到一种通用的设计计算和分析的一体化方法。文中在大量研究喷管的结构形式、流动模型及传热模型基础上,利用先进的计算机辅助设计技术、有限元技术和两相流分析技术,研制出了喷管一体化设计、分析和计算软件。它可为喷管的热结构分析和发动机工作过程数值模拟提供参考。     

AP-CMDB推进剂燃速压强指数的变化分析与辨识

采用燃烧模型分析了AP-CMDB推进剂的燃速压强指数与推进剂配方组成和火箭发动机燃烧室压强之间的耦合关系．指出了该推进剂的燃速压强指数随AP颗粒和双基母体的燃速差而变化,对于确定配方组成的AP-CMDB推进剂,则该指数将主要随压强而变化,且近似呈对数关系。采用C-K法对特定配方进行了压强指数辨识,辨识结果能够较准确地预示脉冲推力器的内弹道性能。     

非壅塞固体火箭冲压发动机二次燃烧室进气方案研究

用k-ε湍流模型以及EBU燃烧模型。对固体火箭冲压发动机二次燃烧三维反应流场进行了数值计算,研究了空气射流与富燃燃气射流动量之比、射流速度和燃气发生器喷管数量对二次燃烧的影响。研究结果表明,当空燃动量比在一定范围内时。若空燃动量比变大,则二次燃烧效率升高;降低空气和燃气射流的速度有利于二次燃烧效率的提高;并且增加燃气发生器喷管数量能增强燃气与空气在头部的掺混效果,为燃烧创造良好的条件。