Performance of a small and low-cost chamber to simulate lunar surface environment

The performance of a small and low-cost metal chamber built to simulate the pressure and temperature conditions of lunar surface was assessed and the results are presented. This chamber is intended for studying the physical properties of lunar surface and subsurface (using soil simulants) and also to validate the technology readiness of certain newly developed payloads planned for future lunar surface missions (Lander/Rover). It is possible to reach down to ∼10⁻⁷ Pa under specific conditions and maintain the temperature of the sample under investigation to lunar day and night temperatures. The designed system has been subjected to various tests to evaluate its performance and suitability for carrying out experiments in a simulated lunar environment.     

复杂结构的非线性检测

由于非线性系统的复杂性，现有的各种非线性检测方法都有局限性。从频域、幅域和时域三方面综合考察复杂结构的非线性表现，采用六种方法进行非线性检测，给出一个综合描述系统非线性程度的指标－非线性因子。鉴于非线性系统表现出的非线性强弱与系统所受的激励有直接的关系，将非线性因子定义为与激励的幅值特性和频率特性相关的系数指标。对几种典型非线性系统的仿真模型进行了检测，以验证非线性因子的有效性。     

蒙特卡洛方法在降落伞-返回舱系统中的应用

文章简要介绍了蒙特卡洛方法的起源和基本思想，随机数和随机抽样的产生方法，同时，基于蒙特卡洛方法的基本思想提出了用数值方法计算飞船返回舱着陆姿态参数的初步设想。对于此问题的研究，将有助于节约试验经费，分析返回舱缓冲结构的设计合理性及可靠性。     

A systematic approach to nonlinear rotorcraft model identification

The development of a powerful parameter estimation routine and its integration into the simulation environment HOST is described. With this tool approaches are being made towards new strategies of mathematical modeling, aimed at providing highly accurate and nevertheless run-time efficient simulation models. The identification routine is capable of optimizing parameterized models in both dynamic time domain simulation and static (e.g. trim state variation) conditions. Examples of both cases are presented to emphasize the improvement in the system response prediction and to demonstrate the abilities of the identification techniques in combination with the nonlinear simulation platform. This article reviews the activities and achievements accomplished by the DLR Institute of Flight Research and the ONERA Systems Control and Flight Dynamics Department during the last few years in the research on rotorcraft flight dynamics modeling and model identification. Future activities that require extensive high fidelity modeling are in the scope of the current and coming modeling activities that include the use of the presented methods and software technologies.     

槽对超声速混压式进气道性能及附面层的影响

为了提高定几何超 声速混压式轴对称进气道的性能，应用在进气道不同位置开槽的方法 ，研究了在各级锥体上、锥体的折角处开槽时锥体上的附面层变化；研究了多工况下开槽对进气道的总压恢复系数、流量系数、冲压比和起动性能产生的影响。结果表明开槽将改变超声速进气道头锥上的波系分布，使槽后附面层厚度增加。折角处开槽槽后附面层厚度比原型进气道增加16.7%，锥体上开槽比原型进气道增加33.3%。开槽使高马赫数下的总压恢复系数有所增加，其增加量随来流马赫数的变化而变化。在马赫数为4.0的设计状态下，折角处开槽可使进气道的总压恢复系数提高1.8%，锥体上开槽可以提高4.3%。之外，锥体折角处开槽对流量系数影响不大，还可以改善进气道的起动性能，降低起动马赫数。     

通用机实时仿真软件平台

仿真软件平台是介于操作系统和用户仿真试验程序之间的一层系统软件。在本文中作了介绍。一个通用实时仿真工作站的软件平台，包括体系结构、功能、语言特性等和主控程序。     

反坦克导弹飞行仿真关键技术探讨

有关反坦克导弹的特点、飞行仿真的特性以及关键技术在本文中作了探讨，对我国发展反坦克导弹的飞行仿真和开展仿真软件的研制提出了一些设想。     

姿态控制系统冗余设计方法与半实物仿真试验

从系统冗余的角度研究了提高运载火箭姿态控制系统可米住的途径，论述了捷联／捷联，平台／捷联冗余姿态控制系统的组成和工作原理，介绍了用姿态角判别故障和用姿态角速度判别故障的两种故障诊断、切换和重构的模式。对捷联／捷联冗余方案进行了半实物仿真试验。     

正态-复合非时齐Poisson过程模型结构可靠性当量正态设计

讨论强度R～N（μ_R，_R），应力｛S（t），t∈［0，T］｝为非时齐Poisson过程模型结构可靠性当量正态设计。获得应力在设计基准期［0，T］内的最大值概率分布及统计参数估计；正态－复合非时齐Poisson过程模型结构可靠度及结构可靠性当量正态设计表达式。