先进钣金成形技术在航天制造领域应用分析

针对航天产品对先进钣金成形技术的需求,介绍了板材充液成形技术、管材内高压成形技术、超塑成形/扩散连接技术(SPF/DB)、旋压成形技术、橡皮囊成形技术等钣金成形技术的成形原理、技术特点及其在国内外航天制造领域的典型应用情况。在此基础之上简要分析了先进钣金成形技术在未来航天领域的应用前景。     

光谱红移自主导航新方法

提出了一种基于太阳系天体光谱红移测量的自主导航新方法.以太阳系天体作为光源和信息源,由实时光谱红移测量值获得航天器在惯性坐标系中的飞行速度,实现航天器的自主导航.与现有自主导航方法相比,该法不依赖地面无线电信息,无需引入航天器轨道动力学,具有高度自主、简单易行、无时延等优势,在深空探测领域有广阔的应用前景,并可为近地卫星的自主导航提供参考与借鉴.     

3D打印技术在航天复合材料制造中的应用

复合材料作为新一代结构材料已大量应用在航天遥感器结构中,如相机支架、承力框、遮光罩等。低成本、高效率的制造技术是进一步推进复合材料应用的重要途径,三维(Three dimension,3D)打印技术的出现为复合材料的低成本快速制造提供了可能,随着技术的发展,复合材料的3D打印技术逐渐成为该技术的一个新兴领域。文章介绍了以纤维增强树脂基复合材料为打印材料的3D打印技术的研究情况,结合航天遥感器用复合材料产品的特点对3D打印技术在航天复合材料产品制造上的应用进行了分析。     

适合临近空间通信的Ka/V双频口径耦合天线设计

为了减缓飞行器在临近空间高速飞行时产生的等离子体鞘套“黑障”对其通信影响,根据ITU分配的临近空间3区业务频段,设计了一种在Ka/V双频段工作的口径耦合微带天线。该天线在中间缝隙开一圆孔,通过改变圆孔大小实现双频工作,并组成1×4的天线阵列,实现了在Ka和V两个频段的通信。设计结果表明：在Ka频段的-10dB带宽达到11.33%,V频段带宽达到2.52%,满足其在临近空间3区业务的通信频段。该天线易于实现,结构简单,可为临近空间通信飞行器天线设计提供参考。     

J─133室温固化耐100℃结构胶工艺试验

本文就J－133等室温固化胶的实验条件、实验结果以及J—133胶的应用情况作一简单介绍。所得结果可作为产品设计和拟定工艺规范使用。     

飞行过载对固体火箭发动机不稳定燃烧的影响

针对某固体发动机飞行试验中出现的压强振荡现象,开展压强振荡特性分析、机理分析及声模态数值仿真,提出该非线性不稳定燃烧故障的两种可能的触发模式。通过建立脉冲激励试验方法及火箭橇过载模拟试验方法对故障发动机开展试验研究,并验证了导弹飞行过载是引起发动机不稳定燃烧的最主要原因。     

Effective Thermal Conductivity for 3D Five-Directional Braided Composites Based on Microstructural Analysis

A method for predicting effective thermal conductivities(ETCs) of three-dimensional five-directional(3D5D) braided composites is presented. The effective thermal conductivity prediction method contains a digital image processing technology. Multiple scanning electron microscopy(SEM)images of composites are analyzed to obtain actual microstructural features. These actual microstructural features of 3D5D braided composites are introduced into representative volume element(RVE) modeling. Apart from applying actual microstructural features,compression effects between yarns are considered in the modeling of RVE,making the RVE more realistic. Therefore,the ETC prediction method establishes a representative unit cell model that better reflects the true microstructural characteristics of the 3D5D braided composites. The ETCs are predicted with the finite element method. Then thermal conductivity measurements are carried out for a 3D5D braided composite sample.By comparing the predicted ETC with the measured thermal conductivity, the whole process of the ETC prediction method is proved to be effective and accurate,where a relative error of only 2.9 % is obtained.Furthermore,the effects of microstructural features are investigated,indicating that increasing interior braiding angles and fiber fill factor can lead to higher transverse ETCs. Longitudinal ETCs decrease with increasing interior braiding angles,but increase with increasing fiber fill factor. Finally,the influence of variations of microstructure parameters observed in digital image processing are investigated. To explore the influence of variations in microstructural features on variations in predicted ETCs,the actual probability distributions of microstructural features obtained from the 3D5D braided composite sample are introduced into the ETC investigation. The results show that,compared with the interior braiding angle,variations in the fiber fill factor exhibit more significant effects on variations in ETCs.     

An active damping vibration control system for wind tunnel models

In wind tunnels, long cantilever sting support systems with low structural damping encounter flow separation and turbulence during wind tunnel tests, which results in destructive low-frequency and big-amplitude resonance, leading to data quality degradation and test envelope limitation. To ensure planed test envelope and obtain high-quality data, an active damping vibration control system independent of balance signal based on stackable piezoelectric actuators and velocity feedback using accelerometer, is proposed to improve the support stability and wind tunnel testing safety in transonic wind tunnel. Meanwhile, a design of powerful sting-root embedded active damping device is given and an active vibration control method is presented based on the mechanism analysis of aircraft model vibration. Furthermore, a self-adaptive fuzzy Proportion Differentiation(PD) control model is proposed to realize control parameters adjustment automatically for various testing conditions. Besides, verification tests are performed in laboratory and a continuous transonic wind tunnel. Experimental results indicate that the aircraft model does not vibrate obviously from -4° to 11° at Ma = 0.6, the number of useable angle-of-attack has increased by 7° at Ma = 0.6 and 5° at Ma = 0.7 respectively, satisfying the requirements of practical wind tunnel tests.     

应用非线性高阶谐波衰减和尾波干涉监测高温作用后水泥制品的损伤演化

非线性高阶谐波和尾波波速变化均能够反映水泥材料内部微结构的应力变化。利用高阶谐波和尾波干涉实验测量系统,对引入高温作用后的3类不同粒径共6块水泥试样进行单轴加载的损伤演化实验,并与无高温作用的完整试样的实验结果进行对比。结果表明,从初始状态到25%抗压强度的过程中,高温作用后的试样的谐波幅值和尾波波速变化出现明显增强的现象(谐波幅值最大增幅约20%),而无高温作用的完整试样的谐波幅值和尾波波速变化较为平稳(谐波幅值最大增幅约5%);在达到65%抗压强度的过程中,高温作用后的试样的谐波幅值和尾波波速变化急剧增大(谐波幅值最大增幅约100%),且粒径较大的试样的增幅高于粒径较小的试样,而无高温作用的完整试样的谐波幅值和尾波波速变化的增幅较小(谐波幅值最大增幅约10%);当抗压强度超过75%以后,高温作用后的试样的谐波幅值和尾波波速变化急剧衰减(谐波幅值最大衰减幅度约140%),而无高温作用的完整试样的谐波幅值和尾波波速的最大衰减幅值在40%以内。基于以上观测结果对高温作用后水泥制品损伤演化的物理机制以及这两类监测方法的适用性进行了讨论。     

一种模块化微小型卫星对接机构建模仿真

面向微小卫星在轨服务的连接分离技术的需求,针对一种模块化微小型卫星对接机构,分析其机构原理,推导了机构的运动方程,并利用MATLAB验证机构的运动学模型的正确性,结合仿真定量分析机构可能出现的干涉问题,给出了不干涉条件。为研制用于模块化微小型卫星的对接机构提供一种运动学建模和仿真分析的 思路 。