查询词典 maximum error

On a grating type gear integrated error measuring equipm ent, this technique employs the three-point method error separation technique fo r separation of the systematic error of the measuring chain of equipment spindle system including measuring worm error, grating transducer error, bearing rota ry error etc.

在一台光栅式齿轮整体误差测量仪上，它用三点法误差分离技术能分离开仪器轴系测量链的系统误差(包括测量蜗杆误差、光栅传感器误差、轴承回转误差等)和被测齿轮的全谐波误差。

Regarding the general industrial dust aluminite powder, the firing delay time and the most tremendous pressure rise speed influence is very obvious to its maximum explosion pressure; Its maximum explosion pressure and the maximum pressure rise speed reduces along with the dust granularity increases: And increases the tendency to be obvious; Has a best dust loading, causes its maximum explosion pressure and the maximum pressure rise speed maximizing.

对于一般工业粉尘铝粉来说，点火延迟时间对其最大爆炸压力和最大压力上升速率的影响十分明显；其最大爆炸压力和最大压力上升速率随着粉尘粒度的减小而增加：且增加趋势明显；存在一个最佳粉尘浓度，使其最大爆炸压力和最大压力上升速率达到最大值。

RELIABILITY MTBF 600,000 hours Unrecoverable read errors 1 in 10^14 POWER Average idle current 5.0 watts Average seek power 7.30 watts Standby power 1.4 watts Sleep power 1.07 watts Maximum start current, DC 2.0 amps ENVIRONMENT Ambient Temperature Operating 0 to 60 degrees C Nonoperating -40 to 70 degrees C Maximum operating temperature change 20 degrees C per hour Maximum nonoperating temperature change 30 degrees C per hour Maximum operating case temperature 69 degrees C Relative Humidity Operating 5 to 90 Nonoperating 5 to 95 Maximum allowable humidity change 30 per hour Altitude Operating altitude -60.96 meters (-200 feet) Operating altitude 3,048 meters (10,000 feet) Nonoperating altitude -60.96 meters (-200 feet) Nonoperating altitude 12,192 meters (40,000 feet) Shock Operating vibration 0.50 Gs Operating Shock 63 Gs at 2 msec Nonoperating Shock 350 Gs at 2 msec Vibration Operating vibration 0.5 Gs at22-350 Hz Nonoperating vibration 5.0 Gs at 22-350 Hz ACOUSTICS Acoustics 2.6 bels Acoustics 2.7 bels

可靠性 平均无故障工作时间六十点○万小时不可恢复读错误1 10 ^ 14 电力平均闲置电流五点○瓦特平均寻求权力7.30瓦特待机功耗一点四瓦特睡眠电力1.07瓦特最大启动电流，直流二点〇安培环境常温经营0至60摄氏度非经营性-40 ℃至70摄氏度最大运行温度变化20摄氏度，每小时非经营性最大温度变化30摄氏度，每小时最大运行外壳温度69摄氏度相对湿度操作5至90 非经营性5日至95 最大允许湿度变化每小时30 高原高空作业-60.96米（-200米）操作高度三〇四八米（ 10000英尺）非经营性高度-60.96米（-200米）非经营性高度一二一九二米休克操作振动0.50亚基操作震动 63亚基在2毫秒非经营性休克 350亚基在2毫秒振动操作振动0.5气孔at22 - 350赫兹非经营性振动5.0亚基在22-350赫兹声学声学 2.6分贝声学仅有2.7分贝

The maximum error of regional anomaly separation is 3.101×10^(-6)m/s^2 the mean square error is 0.989×10^(-6)m/s^2 and the maximum percentage error is 7.76% for several data on the boundary and is lower than 4.1% for the other points.

分离出的区域异常最大误差为3.101×10^(-6)m/s^2，均方差为0.989×10^(-6)m/s^2，最大百分比误差仅在边部的几个数据上，为7.76%，其余各点的误差均小于4.1%。

The error is described by weighted average variance-covariance of root mean square error in curve normal direction, and error in the direction with maximum error respectively.

曲线上任意点的误差由端点及距离误差传播导出的误差之加权平均值的协方差表示。

The common method, that all strong-correlation terms of the model are eliminated, can bring the loss in the engineering application, so the new method is proposed that the identified model reserves some correlation. The augmented matrix A is constructed by the outputΔW and the matrix S. The"determinating order based on ratio of determinant"is brought out to screen the strong-correlation terms in the structure identification. The latent root estimation is improved in screening the eigenvalues and eigenvectors. Thus the estimation precision is improved greatly.The consistence check of guidance instrument error coefficients of flight test and ground test is the purpose of flight experiment. The causes of inconsistency of the two models are analyzed. The hypothesis test of linear regression model based on F statistics is proposed to check the consistence.Finally, the instability of error coefficients is probably caused by the change of the flight environments, therefore, the relation between the error coefficients and flight environment is analyzed. The approach is presented to identify SINS guidance instrument error models and compensate the error in the segmented sections corresponding to the change of vertical acceleration of aircraft.

在结构辨识中，常用的方法由于将模型中的强相关项全部剔除而给工程应用带来损失，因此，本文提出了新的有益思想，即在保留一定相关性的基础上进行辨识：将输出向量ΔW与环境函数矩阵S构成增广矩阵A，然后采用"比定阶行列式"来剔除相关向量的方法，这样既可以尽可能多地保留了对落点影响大的强相关参数，又可以对落点影响小的强相关参数给予剔除；在参数估计中，改进了特征根估计中特征根和特征向量的筛选方法，提出"近零"准则，从而大大提高了参数估计的精度；再者，鉴于天地模型"一致性"检验是飞行试验和SINS制导工具误差系数分离的主要目的，因此，本文又深入分析了造成天地模型不一致的原因，提出了采用基于F统计的线性回归模型假设检验方法来进行捷联制导工具误差模型的天地"一致性"检验；最后，鉴于飞行环境剧烈变化可能会对惯性仪表误差系数稳定性带来一定的影响，因此本文深入地分析了SINS制导工具误差系数与外界环境的关系，提出了基于过载变化大小的分段辨识和分段实时补偿的算法。

The adaptive program is calculated by T-B stress recovery scheme and z-z error estimation, the error is estimated by energy norm of difference of recovery stress and meshless stress. If the local relative error exceeds the limit relative error, then new nodes will be generated at the high error area.

本研究的自适应方法采用TB应力平滑技术和Z-Z误差估计，利用平滑应力和无网格法所得应力解差值的能量范数来估算误差，如果局部相对误差超过了允许误差，则在高误差域插入新的离散点进行加密。

Besides, we have studied deeply error of two kinds which appeared frequently in the hypothesis testing (error of the first kind and error of the second kind), including the relations to error of two kinds and its effect to the result of hypothesis testing and the effective control of error of two kinds so as to be satisfying and etc.

另外，对假设检验中经常出现的两类错误（第一类错误和第二类错误）也作了深入的探讨，其中涉及到了两类错误之间的关系，两类错误对假设检验结果的影响以及如何有效的控制两类错误使之达到令人满意的程度等。

In this paper the effects of scanning truncation error, scanning position error, random amplitude and phase error, and multiple-reflection error in near-field antenna measurement are analyzed; error equations and the uncertainty of measurement are obtained through computer simulation; compensated techniques for reducing the effects of measurement errors in near-field antenna measurement are presented and the formula and arithmetic of phaseless near-field techniques are derived.

本文从解析法和数值仿真两个角度深入分析口面天线近场测量中扫描面截断误差、扫描面位置误差、随机幅相误差、多次反射误差等误差源对天线远场特性测量精度的影响，一方面从理论上给出相应的误差方程，另一方面建立误差分析模型，通过计算机模拟，得到不同误差条件下测量结果的不确定度，并介绍了减小这些误差的修正方法，推导无相位近场测量的公式和算法。

The new method is given to design the optimum profile modification curve design The effects of optimum profile gear in improving the dynamic performance of gear transmission are verified in the Gear Dynamic Performance Test Rig In this dissertation, the main study contents and creative results are shown as following: The influences on the gear transmission system caused by the gear's accumulated error (periodic error and harmonic error) are theoretically studied. A new method is developed to simulate the gear's harmonic error by using the 2-order MARKOV process A simulated model of the dynamic performance which is excited by the gear's accumulated error is obtained.

本文在前人大量研究的基础上，结合作者承担的国家自然科学基金项目"齿轮传动动态系统辨识与三维修形研究"和山东省自然科学基金项目"齿轮传动动态性能仿真及结构参数、齿形的优化修形"，采用理论和试验相结合的新思路，系统地研究了齿轮传动的动态性能，建立了能正确描述齿轮传动系统动态性能的仿真模型和系统辨识模型，给出了确定齿轮传动轮齿修形曲线的优化设计方法，利用自行研制的齿轮传动动态性能试验装置，验证了优化修形齿轮对提高齿轮传动动态性能的突出作用。

Objective:To explore the feasibility of laparoscopy in diagnosing and treating of abdominal diseases.

目的：探讨腹腔镜用以诊断腹部外科疾病及选择治疗方案的可行性。

The lifetime of nylon 1010 and nylon 1010/POSS composites decreased with increasing temperature.

热重-红外联用分析表明尼龙1010在氮气气氛下的降解产物主要为小分子的低聚物，POSS并不改变尼龙1010降解产物的组成。