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数据相容性
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  data compatibility
     Flight Test Data Compatibility Check for SAM Based on Recursive Minimum Model Error Estimation
     基于最小误差模型估计的地空导弹飞行试验数据相容性检验
短句来源
     Discrete-time model of aircraft motion used for decreasing modeling errors. Finally, this new approach has been compared with the conventional method by digital simulation and actual flight test data compatibility check.
     为了得到数据相容性检验的准确结果,本文采用直接离散化的飞机运动模型,以减小模型误差。
短句来源
     A method for flight test data compatibility check for SAM based on RMMEE is proposed. By means of measuring the missile postition and the angular displacement of missile body, not only can the method make an on line reconstruction of six degree of freedom trajectory,but also estimate the dynamic error of the strapdown INS(SINS). It completely eliminates the constraint of the Klein model.
     提出了基于递推最小模型误差估计 (RMMEE)的地空导弹飞行试验数据相容性检验的方法 ,该方法采用导弹位置和弹体角位移测量 ,不仅能在线重构六自由度弹道参数 ,而且能估计捷联惯导的动态误差 ,从根本上克服了Klein模型的局限性。
短句来源
     Checkout methods for compatibility of pre test data and locale test data are given, which include parameter methods for static test data compatibility checkout and direct statistic methods for dynamic test data compatibility checkout .
     给出试验数据处理中验前试验数据与现场试验数据相容性检验的方法 ,包括静态试验数据相容性检验的参数法和动态试验数据相容性检验的直接统计法 ;
短句来源
     This paper studies the data compatibility and business operation flow co-operation among different departments in the area of e-government catalog system and exchange system. A solution framework that consists of service pattern,technical frame,information resources and management mechanism is proposed.
     针对电子政务目录体系和交换体系的跨部门共享数据相容性、业务流程协同性等问题,提出一种由服务模式、技术架构、信息资源和管理机制组成的可行解决总体框架;
短句来源
  “数据相容性”译为未确定词的双语例句
     Checkout Methods for Compatibility of Pre-test Data and Locale Test Data
     验前试验数据与现场试验数据相容性检验方法
短句来源
     A NEW THREE-STEP METHOD FOR COMPATIBILITY CHECK OF REAL FLIGHT TEST DATA
     飞行实测数据相容性检验的三步法
短句来源
     In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft.
     本文采用飞行器六自由度运动方程组,建立了飞行试验数据相容性检验的数学模型.
短句来源
  相似匹配句对
     DATA
     数据
短句来源
     DATA & INFORMATION
     数据
短句来源
     The Triangulation Algorithm of Scattered Data Based on the Compatibility of NURBS
     基于NURBS相容性的散乱数据三角剖分算法
短句来源
     COMPATIBILITY CHECK OF THE FLIGHT TEST DATA AND RECONSTRUCTION OF THE DATA
     飞行试验数据相容性检验和数据重建
短句来源
     Compatibility of Polymer Blends
     高分子共混物的相容性
短句来源
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  data compatibility
An interoperable building model would assure data compatibility across applications and platforms.
      
For nationwide data compatibility, a common standard for accuracy and database must be maintained.
      
However, obtaining information from many different sources compounds the data compatibility problem in an effort such as this one.
      
However, transformation rules are implemented in the CARE database in order to increase data compatibility.
      
In general, the data compatibility of our estimations is good.
      
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In order to determine aircraft performance stability and contrdl characteristics from test data, flight stale estimation is needed.Usually, extended, Kalman filter and fixed-interval smoother are used for handling the nonlinear estimation problems of both the state and parameter.However, practical experience and theoretical studies show that this augmented algorithm, in fact, is not satisfactory for parameter estimation.In order to provide a more accurate and practical method for flight state estimation, this...

In order to determine aircraft performance stability and contrdl characteristics from test data, flight stale estimation is needed.Usually, extended, Kalman filter and fixed-interval smoother are used for handling the nonlinear estimation problems of both the state and parameter.However, practical experience and theoretical studies show that this augmented algorithm, in fact, is not satisfactory for parameter estimation.In order to provide a more accurate and practical method for flight state estimation, this paper presents a new separated bias identification and state estimation algorithm which is used for both the flight state estimation and instrumentation errors identification.In order to get high accuracy, U-D factorization methods are applied to improving the computational stability and efficiency. Discrete-time model of aircraft motion used for decreasing modeling errors.Finally, this new approach has been compared with the conventional method by digital simulation and actual flight test data compatibility check.The results calculated show that the new method can give more consistent results than the usual one for a different initial values and the noise statistics.Moreover, this approach can be used for the compatibility check of lower sampled flight test data.

本文根据最小方差估计和分离算法原理,提出一种新的非线性状态估计和偏差辨识的分离算法。并用此算法确定飞行状态和测试仪器的误差,同时U-D分解保证计算效率和数值稳定性。为了得到数据相容性检验的准确结果,本文采用直接离散化的飞机运动模型,以减小模型误差。通过仿真并在我国两种歼击机上实际应用,结果表明本文所给的算法对不同的初值和噪声统计特性都能得到飞行数据相容性检验的一致结果,并能用于低采样率下的数据相容性检验。

In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft. By using the maximum likelihood method the system error of the measurement data can be obtained and the flight data can be reconstructed. The feasibility of the method and the correctness of the program have been checked using the simulation data calculated by six freedom kinematic equations in consideration of the measurement noice. Finally various flight...

In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft. By using the maximum likelihood method the system error of the measurement data can be obtained and the flight data can be reconstructed. The feasibility of the method and the correctness of the program have been checked using the simulation data calculated by six freedom kinematic equations in consideration of the measurement noice. Finally various flight test data are processed and the results are quite satisfactory.

本文采用飞行器六自由度运动方程组,建立了飞行试验数据相容性检验的数学模型.应用最大似然估计求得测量数据的系统误差并进行数据重建。利用计入测量噪音的六自由度动力学方程组的仿真数据检查了方法的可行性和程序的正确性,最后处理各种飞行器的飞行试验数据,得到了满意的结果.

The extended Kalman Filter and fixed-interval Smoother (EKF/S) and Square-Root Information Filter and Smoother (SRIF/S) for flight data compatibility check of two kinds of supersonic aircraft are presented. In order to get high accuracy and computation efficiency, the modified SRIF/S is proposed by exploiting some features of model. The results of simulation and actural flight data computation show that these two methods can give satisfactory result and the modified SRIF/S not only imprives the numerical stability,...

The extended Kalman Filter and fixed-interval Smoother (EKF/S) and Square-Root Information Filter and Smoother (SRIF/S) for flight data compatibility check of two kinds of supersonic aircraft are presented. In order to get high accuracy and computation efficiency, the modified SRIF/S is proposed by exploiting some features of model. The results of simulation and actural flight data computation show that these two methods can give satisfactory result and the modified SRIF/S not only imprives the numerical stability, but also reduces significantly the computation and storage requirement and is more efficient than EKF/S.

飞行数据相容性检验在飞行试验数据分析中是很重要的。由于飞行试验测量数据中存在着各种过程噪声(如大气紊流)和测量噪声(如尺度因子偏差、常值系统偏差等),这些误差将会导致飞行数据各通道之间不相容。利用估计理论进行飞行状态估计,同时估计出未知的尺度因子,系统偏差,即进行飞行轨迹重构被认为是飞行数据相容性(一致性)检验的强有力的工具。本文利用推广卡尔曼滤波和信息平方根滤波及平滑进行高速飞机飞行数据的相容性检验,提出了飞机纵向运动和全面运动的新模型,通过仿真和实际计算得出满意的结果。

 
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