航空军工产品实验室环境鉴定试验工作情况分析（1）

文章分为两部分。此为第一部分,主要阐述了军工产品定型试验分类和目的,特别是航空军工产品地面鉴定试验的基本内容;着重分析了实验室环境鉴定试验的地位和作用,指出在其实施和管理过程中的复杂性。这部分还介绍了承试实验室资质、试验设备使用和管理、试验大纲和试验报告等文件编写和质量控制方面存在的问题,进行分析并提出改进建议。     

Fourier变换的基本格式与PSD非参数估计

以传统Fourier变换为基础的非参数估计方法是振动工程研究中PSD估计的重要方法。文章以周期图法为例,研究Fourier变换基本格式的不同对PSD非参数估计结果的影响。首先介绍了Fourier变换常见的几种基本格式及其对应的PSD非参数估计计算公式;然后基于PSD的物理内涵,分析、证明多种不同形式的PSD估计公式的同时存在是一种人为误解,只有惟一的一种PSD估计结果才是具有典型物理意义的;最后给出了Fourier变换的一种通用格式及其PSD估计计算公式。     

航天器用高性能塑封器件的板级鉴定方法

由于技术进步和设计需要,航天应用中不可避免地会遇到选用低质量等级塑封器件的情况。随着器件功能的日益复杂和封装的多样化,实现器件级的鉴定越来越困难。文章提出了基于板级系统对塑封器件进行鉴定的方法,包括几个标准的评估方面,如器件级筛选、破坏性物理分析、特殊的设计评估等;并介绍了一种基于局部加热技术,能够考核器件热温度特性的板级评估方法。     

一种用于条带模式SAR成像的自聚焦算法

 针对现有条带模式合成孔径雷达（SAR）成像的自聚焦算法中,相位的拼接会引起误差的严重积累,本文结合相位梯度自聚焦（PGA）算法和子孔径偏移（MD）算法,提出了一种新的用于条带模式SAR成像的自聚焦算法（PGA-MD）。该算法先利用PGA算法有效估计各子孔径相位误差函数,再利用相邻子图间方位向偏移量和线性相位之间的关系,通过MD算法精确估计相邻子图间方位向偏移量,然后计算线性相位差,并基于—阶导数实现子孔径相位误差函数拼接。理论分析以及实测数据处理结果对比均表明PGA-MD算法可以有效提高对条带SAR图像的自聚焦效果。     

Inner Attitude Integration Algorithm Based on Fault Detection for Strapdown Inertial Attitude and Heading Reference System

This article proposes a new inner attitude integration algorithm to improve attitude accuracy of the strapdown inertial attitude and heading reference system(SIAHRS), which, by means of a Kalman filter, integrates the calculated attitude from the accelerometers in inertial measuring unit(IMU), called damping attitudes, with those from the conventional IMU. As vehicle's acceleration could produce damping attitude errors, the horizontal outputs from accelerometers are firstly used to judge the vehicle's motion so as to determine whether the damping attitudes could be reasonably applied. This article also analyzes the limitation of this approach. Furthermore, it suggests a residual chi-square test to judge the validity of damping attitude measurement in real time, and accordingly puts forward proper information fusion strategy. Finally, the effectiveness of the proposed algorithm is proved through the experiments on a real system in dynamic and static states.     

Dynamics of Rotor Drop on New Type Catcher Bearing

In an active magnetic bearing(AMB)system,the catcher bearings(CBs)are indispensable to protect the rotor and stator in case the magnetic bearings fail or overload.A new CB structure composed of two ball bearings is introduced.Detailed simulation models containing contact model between rotor and inner race,double-decker catcher bearing(DDCB)model as well as single-decker catcher bearing(SDCB)model are established using multibody dynamics simulation software MSC.ADAMS.Then,using those established models,the rotor orbits and the contact forces between rotor and inner race are simulated respectively after rotor drop on DDCBs and SDCBs.The simulation result shows that the rotor vibration range using DDCBs is significantly smaller than that using SDCBs;the maximum contact forces drop about 15%—27% compared with the contact forces using SDCBs.Finally,the test bench for the rotor drop experiments is built and the rotor drop experiments for different types of CBs are carried out.Labview data acquisition system is utilized to collect the displacement of rotor and the rotating frequencies of both inner race and intermediate races after rotor drop.The experimental results are comparatively analyzed,and the conclusion that DDCB can help to reduce vibration amplitude and collision force is obtained.The studies can provide certain theoretical and experimental references for the application of DDCBs in AMB system.     

Trajectory Planning Algorithm Based on Quaternion for 6-DOF Aircraft Wing Automatic Position and Pose Adjustment Method

 A 6-degree of freedom (6-DOF) aircraft wing position and pose automatic adjustment method is presented to improve ARJ21 wing-fuselage connection precision and efficiency. Wing position and pose are adjusted by three pillars which are driven by six high-precision servo motors. During the adjustment process, wing is tracked and positioned by laser tracker. Wing initial posi-tion and pose are calibrated by using the measurement coordinates of assembly reference points. Wing target position and pose are calculated according to wing initial, fuselage position and pose, and relative position and pose requirements between wing and fuselage for the connection. Combining Newton-Euler method with quaternion position and pose analyzing method, the inverse kinematics of servo motors, together with the adjustment system dynamics is obtained. Wing quintic polynomial trajec-tory planning algorithm based on quaternion is proposed; the initial, target position and pose need to be solved and the inter-mediate moving path is uncertain. Simulation results show that the adjustment method has good dynamic characteristics and satisfies engineering requirements. Preliminary engineering application indicates that ARJ21 wing adjustment efficiency and precision are improved by using the proposed method.     

基于CAN总线的等效器的设计与实现CSCD

为了方便配合测量系统中某类部件的检测与监控,设计了基于CAN总线接口电路的等效器,增加了总线的监视功能和数据通信功能,从而实现了相关接口和功能电路的故障诊断功能。阐述了等效设备的CAN总线、数据采集测量以及数字IO功能。在实现全部功能的前提下,尽可能做到器件少、体积小,性能稳定可靠,并有效地实现测量系统综合检查的目的。     

按GJB/Z 9001A-2001建立质量管理体系的做法及成效

介绍中国航天标准化研究所按照GJB/Z 9001A,在规范管理、解决相关管理问题、提高质量意识等方面建立质量管理体系的做法.