飞行载荷参数识别方法研究

介绍了飞行载荷参数识别方法的基本原理。基于飞行载荷与飞行参数之间存在着相关性,通过专门的飞行试验实测载荷和参数,利用回归技术建立载荷与参数之间的经验关系,将飞行测量的参数转换成飞机结构部件上的载荷。还介绍了把该方法使用于Ｆ－７尾翼载荷和Ｆ－６操纵面铰链力矩导数的参数识别的研究实例,并对其进行了相应的评述。研究结果表明了这种方法的可行性、可靠性及实用价值。     

高超声速1 MHz 高频脉动压力测试技术及其应用

为了研究高超声速边界层内的高频脉动结构,特别是第二模态不稳定波,在 FD-07风洞中搭建了一套1MHz 量级高频脉动压力采集系统。风洞背景噪声和电磁噪声是影响高频脉动结构测量的主要原因。在风洞流场品质无法改变的前提下,对高频脉动压力采集系统的信号传输进行了改进,包括工频电源隔离、传输电缆屏蔽和采集设备接地等。通过改进措施,采集系统的抗电磁干扰和信号衰减的能力得到改善,其信噪比得以显著提升。结果表明,改进前后各频段噪声的能谱密度大幅降低(在频率400 kHz 以下,噪声能谱密度降低了一个量级以上)。最后,利用该测试技术成功地在 FD-07高超声速风洞中进行了边界层稳定性实验,捕捉到了第二模态不稳定波,其主导频率范围与线性稳定性理论预测结果吻合。     

多孔材料夹层结构声辐射特性的两尺度拓扑优化设计

基于均匀化计算理论结合结构构型设计和材料构型设计,建立以声辐射功率为目标的两尺度材料/结构协同优化模型,针对夹层结构声学设计问题,开展了声辐射特性拓扑优化研究。分别给出了声辐射功率对宏观和微观设计变量的灵敏度,结合移动渐近线法(MMA)实现了材料/结构两尺度设计。结果表明,声辐射功率两尺度优化改变了夹层结构各阶主振型的形状和顺序,同时也改变了被激发的振型。此外,算例研究了激励频率和约束对优化结果的影响以及声辐射功率目标优化的特殊现象。     

湍流边界层相干结构空间拓扑形态的 层析TRPIV测量

用层析TRPIV(time-resolved paticle image velocimetry)技术精细测量了水洞中平板湍流边界层三分量速度的时空序列信号,提出了空间局部平均多尺度速度结构函数的新概念描述湍流多尺度涡结构的空间拉伸、压缩、剪切变形和旋转.用空间局部平均多尺度速度结构函数对湍流脉动速度进行了空间多尺度分解.用空间局部平均多尺度速度结构函数的新概念,根据湍流多尺度涡结构在空间流向的拉伸和压缩特征,提出了新的湍流相干结构条件采样方法,检测并提取了层析TRPIV数据中相干结构的“喷射”和“扫掠”事件中的速度、涡量等物理量的空间拓扑形态.发现在喷射和扫掠事件中均存在一对反向旋转的准流向“马蹄形”涡结构.      

DECENTRALIZED ROBUST CONTROL FOR UNCERTAIN FLEXIBLE SPACE STATION

ＤＥＣＥＮＴＲＡＬＩＺＥＤＲＯＢＵＳＴＣＯＮＴＲＯＬＦＯＲＵＮＣＥＲＴＡＩＮＦＬＥＸＩＢＬＥＳＰＡＣＥＳＴＡＴＩＯＮＷａｎｇＱｉｎｇ；ＣｈｅｎＸｉｎｈａｉ（ＣｏｌｌｅｇｅｏｆＡｓｔｒｏｎａｕｔｉｃｓ，ＮｏｒｔｈｔｖｅｓｔｅｒｎＰｃｌｙｔｅｃｈｎｉｃａ...     

直8金属桨叶升级换代的几个设计关键分析

本文概要地介绍了国内自行设计研制的直8金属桨叶升级换代的必要性,并结合复合材料桨叶设计实际,对气动设计、桨叶结构相似性设计、全机动力学匹配分析、重量控制等几个设计关键进行较为详细的分析,给出了具体的处理措施。     

一次二阶矩可靠度方法及其软件

开发了利用一次二阶矩方法计算正态分布、对数正态分布、极值分布和截断正态分布随机变量非线性极限状态方程可靠度的软件,并利用相关系数考虑了机械产品随机变量相关的情况.在增加相应简单模块的基础上,可用于计算包含其它分布类型随机变量极限状态方程的可靠度.软件运行表明这种方法迭代格式简单,收敛快,可用于计算机械零件、结构和机构可靠度.      

太阳微波双峰事件的初步分析

本文对1989年1月-1990年6月期间的11个微波双峰事件进行了初步的分析,发现大部分双峰事件的两个峰随频率的演化呈现出竟争的趋势。这一观测特征,可由不同的非热电子分布、或相同非热电子分布,但在相同频率上不同光厚导致谱相交特征得到合理的解释,井可得到双峰事件中两个峰产生在不同源区的推论。     

Very large space structures: Non-linear control and robustness to structural uncertainties

Very Large Space Structures (VLSS) are challenging systems to be controlled, due to their high flexibility. In particular, rapid attitude maneuvers can determine great oscillations on the flexible elements of a spacecraft (solar wings, antennas, booms). On account of this, in the last decades many researchers have developed different strategies to effectively damp the elastic vibrations by means of active vibration devices (such as piezo-electric patches) or by means of robust control algorithms. The approach suggested in this paper is different, since neither additional devices nor complex control laws are introduced. In fact, the complete model of the system (including rigid, elastic and orbital dynamics, coupled with control actions) is controlled by the non-linear attitude controller named state dependent Riccati equation, which will be based on a simplified version of the spacecraft model. The task to reduce the mutual interaction between rigid attitude and flexible dynamics is entirely transferred to a modification of the desired trajectory that must be tracked. This command shaping technique is based on the knowledge of the parameters (inertial and elastics) of the VLSS. Unfortunately these parameters are not always exactly known and, however, they may change over the time. On account of this a Monte Carlo analysis has been also performed, showing the robustness of the proposed control strategy to the structural uncertainties. The numerical simulations prove that this strategy, based on the joint application of two well-known yet simple techniques, produces accurate and robust results.     

Lagrangian coherent structures in various map representations for application to multi-body gravitational regimes

The Finite-Time Lyapunov Exponent (FTLE) has been demonstrated as an effective metric for revealing distinct, bounded regions within a flow. The dynamical differential equations derived in multi-body gravitational environments model a flow that governs the motion of a spacecraft. Specific features emerge in an FTLE map, denoted Lagrangian Coherent Structures (LCS), that define the extent of regions that bound qualitatively different types of behavior. Consequently, LCS supply effective barriers to transport in a generic system, similar to the notion of invariant manifolds in autonomous systems. Unlike traditional invariant manifolds associated with solutions in an autonomous system, LCS evolve with the flow in time-dependent systems while continuing to bound distinct regions of behavior. Moreover, in general, FTLE values supply information describing the relative sensitivity in the neighborhood of a trajectory. Here, different models and variable representations are used to generate maps of FTLE, and the resulting structures are applied to design and analysis within an astrodynamical context. Application of FTLE and LCS to transfers from LEO to the L₁ region in the Earth–Moon system are presented and discussed. In an additional example, an FTLE analysis is offered of a few stationkeeping maneuvers from the Earth–Moon mission ARTEMIS (Acceleration, Reconnection, Turbulence and Electrodynamics of the Moon's Interaction with the Sun).