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   aircraft parameter 的翻译结果: 查询用时:0.006秒
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aircraft parameter
相关语句
  飞机参数
     Nonlinear Maximum Likelihood Method and Its Application to Aircraft Parameter Identification
     非线性极大似然法及其在飞机参数辨识中的应用
短句来源
     And then, design the loop-shapingcontroller with great robustness on the basis of H_∞ theory since dynamic inversioncontroller can't satisfy control requirement when aircraft parameter is perturbed.
     接下来根据动态逆控制器在飞机参数摄动的情况下不能满足控制要求的事实,基于H_∞理论设计了回路成形控制器,使得系统具有良好的鲁棒性。
短句来源
  “aircraft parameter”译为未确定词的双语例句
     Maximum likelihood method dased on interior point algorithm for aircraft parameter identification
     用于飞行器参数辨识的基于内点算法的极大似然法
     MUTI-STEP SIGNAL DESIGN FOR AIRCRAFT PARAMETER IDENTIFICATION
     飞行器参数辨识的最优方波形输入信号设计
短句来源
     An evolutionary computation method for aircraft parameter identification
     飞行器参数辨识的一种演化计算方法
短句来源
  相似匹配句对
     Research on Aircraft Flutter Modal Parameter Identification
     飞机颤振模态参数识别方法研究
短句来源
     Parameter Optimization in Aircraft Skin Stretch Forming Process
     飞机蒙皮拉伸成形工艺参数优化
短句来源
     Magnetization of aircraft
     飞机的磁化
短句来源
     estimation of its parameter;
     评定运动模糊的参数;
短句来源
     B.W. to the aircraft performances.
     电传飞控 /主动控制对飞机性能的影响。
短句来源
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  aircraft parameter
This paper briefly presents aircraft parameter estimation methods for both stable and unstable aircraft, highlighting the developmental work at the DLR Institute of Flight Mechanics.
      
Aircraft parameter estimation - A tool for development of aerodynamic databases
      


The modeling and parameter estimation of the DORNIER DO 28 research aircraft is a part of the special research program 212 of West Germany "airtraffic safety" (SFB 212" Sicherheit im Luftve-rkehr"). In this paper a nonlinear multi-point mathematical model with six-degree-of-freedom for DO 28 parameter estimation is presented. The model considers not only the high nonlinearity of aircraft motions, the characteristics of the propller of the wings and of the horizontal stabilizer, but also the wind disturbance...

The modeling and parameter estimation of the DORNIER DO 28 research aircraft is a part of the special research program 212 of West Germany "airtraffic safety" (SFB 212" Sicherheit im Luftve-rkehr"). In this paper a nonlinear multi-point mathematical model with six-degree-of-freedom for DO 28 parameter estimation is presented. The model considers not only the high nonlinearity of aircraft motions, the characteristics of the propller of the wings and of the horizontal stabilizer, but also the wind disturbance by reconstruction of a quasi-stationary windfield, the improved algorithm for thrust calculation and the necessary corrections of the measured input/output signals through flight-test-data-compatibility-check. Nonlinear Maximum-Likelihood method and modified Newton-Raphson optimization algorithm are applied to the estimation of the stability and control derivatives of the DO 28 aircraft. Compared with one-point model of aircraft motion it is shown that Multi-point model can more accurately describe the aircraft motion and is more suitable for aircraft parameter estimation.

本文建立了DO 28试验机的非线性六自由度多点数学模型。该模型考虑了飞机运动的高度非线性,螺旋桨、机翼、尾翼空气动力特性,改进的推力计算,风场干扰以及飞行试验数据一致性检验和校正。与一点模型相比,该模型能更准确地描述飞机的运动,更适合飞机的参数估计。

The concept and basic requirement of computer aided design, the charac-ters and requirements of computer aided aircraft conceptual design system are describedin this paper. The first thing in developing a design system is to create the models. A de-sign model and a design process model are estabhshed according to the design theory.The design object model is applied to integrating the design tools, and the design pro-cess model is applied to describing design process and design activities. The correctnessand...

The concept and basic requirement of computer aided design, the charac-ters and requirements of computer aided aircraft conceptual design system are describedin this paper. The first thing in developing a design system is to create the models. A de-sign model and a design process model are estabhshed according to the design theory.The design object model is applied to integrating the design tools, and the design pro-cess model is applied to describing design process and design activities. The correctnessand effectiveness of the established models have been testified through the developmentof an aircraft parameter selecting system. Further work is still going on, and the abovemodels will continue to be testified in it.

DESIGNOBJECTMODELANDDESIGNPROCESSMODELOFCOMPUTERAIDEDAIRCRAFTCONCEPTUALDESIGNSYSTEMShenZhang(AircraftCADResearchCenter,Beijin...

This paper provides an adaptive fast sampling control law to compensate for changing aircraft parameters by the parameter adaptive control techniques.This control law recursively using a technique which does not need special “test”signals and which automatically discounts old data depending on the input excitation detected,the step response matrix required for implementation is identified.By the simulation experiments,it can be shown that the use of this parameter adaptive control technique...

This paper provides an adaptive fast sampling control law to compensate for changing aircraft parameters by the parameter adaptive control techniques.This control law recursively using a technique which does not need special “test”signals and which automatically discounts old data depending on the input excitation detected,the step response matrix required for implementation is identified.By the simulation experiments,it can be shown that the use of this parameter adaptive control technique can highly effective maintaining a specified level of tracing performance by adaptive compensating for the host aircraft parameter variations,despite parameter changes which occur either abruptly or slowly.This increased fidelity for in flight simulation.

利用参数自适应控制技术,提出了一种能够自适应补偿飞机参数变化的快速采样控制律。这种控制律可使用迭代技术在不需要特殊“试验”信号又能自动折算依据检测输入激励而获得的原有数据下,对所需要的阶跃响应矩阵进行在线辨识。仿真结果表明,在空中飞行模拟中采用这种参数自适应控制技术,尽管飞机参数突然或缓慢变化,但通过对本机参数变化的自适应补偿,仍可有效地保持其跟踪性能,从而提高了空中飞行模拟的逼真度。

 
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