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 描述函数 在 航空航天科学与工程 分类中 的翻译结果: 查询用时：1.323秒
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 描述函数
 describing function
 Describing Function Theory and Its application in Aerospace 描述函数理论及其在航天中的应用 短句来源 Using the describing function method, this paper gives emphasis to analyse the conditional feedback correction effect on restrain self-sustaining oscillation. 本文利用描述函数法,重点分析了条件反馈校正对自持振荡的抑制作用。 短句来源 As a classical frequency method,Describing Function(DF)has numerous advantages when it is applied in analysis nonlinear systems. 在分析非线性系统时，描述函数作为一种古典的频域方法，具有许多优点。 短句来源 A pilot vehicle system (PVS) mathematical model containing nonlinear control elements of the flight control system is established by the describing function method; the limit cycle of PVS is determined; the relation between the limit cycle and pilot induced oscillation (PIO) and the influence of nonlinear control elements on PIO are explored. 采用描述函数法建立了含有非线性控制系统的人机系统数学模型,确定了系统的极限特性,探讨了极限环与驾驶员诱发振荡(PIO)之间关系和操纵系统非线性因素对PIO影响等。 短句来源 With the rate limiting element in man machine closed loop system, we analyse the PIO using the method of describing function. 然后将速率限制环节置于人机闭环系统中 ,利用描述函数法对驾驶员诱发振荡 ( PIO)机理进行了研究。 短句来源 更多
 describe function
 This paper analyses and studies helicopter stability and limit loop oscillation under nonlinear condition by establishing describe function, the computation formula for longitudinal control displacement and stability store have been derived with limit loop oscillation, the computation and error analyses have been made from Z-8 flight test data. 建立了直升机的描述函数,分析和研究了非线性条件下直升机稳定性和极限环振荡情况,导出了极限环振荡情况下纵向操纵位移计算公式和稳定裕度计算公式,并根据Z—8飞机飞行试验数据进行了验证计算和误差分折。 短句来源
 the describing function
 Using the describing function method, this paper gives emphasis to analyse the conditional feedback correction effect on restrain self-sustaining oscillation. 本文利用描述函数法,重点分析了条件反馈校正对自持振荡的抑制作用。 短句来源 A pilot vehicle system (PVS) mathematical model containing nonlinear control elements of the flight control system is established by the describing function method; the limit cycle of PVS is determined; the relation between the limit cycle and pilot induced oscillation (PIO) and the influence of nonlinear control elements on PIO are explored. 采用描述函数法建立了含有非线性控制系统的人机系统数学模型,确定了系统的极限特性,探讨了极限环与驾驶员诱发振荡(PIO)之间关系和操纵系统非线性因素对PIO影响等。 短句来源 In the equations of motion of the aeroservoelastic system,the nonlinear structural stiffness was transformed to the quasi-linear equivalent stiffness by using the describing function method. The stability and stable margin of the aeroservoelastic system were analyzed by Nyquist method in linear control theory. 在气动伺服弹性运动方程中,非线性的结构刚度通过描述函数法转化为准线性的等效刚度,然后采用线性控制理论中的Nyquist方法来判断气动伺服弹性系统的稳定性并计算稳定裕度. 短句来源
 “描述函数”译为未确定词的双语例句
 Text presents several principles of the gyro system's design. 研究陀螺跟踪的描述函数和干扰误差的描述函数。 同时还提出了陀螺稳定系统设计的几个原则。 短句来源 The nonlinear equations are transferred into the state space. The amplitude of limit cycle, frequency and the critical parameter curves are determined by optimizing the real part of complex eigenvalues. Meanwhile, this method can extricate designers from the tedious algebraical derivation in the early shimmy stability analysis. 文中假设前起落架支柱上端固支,并且给出了用以描述五自由度的前轮摆振运动的非线性微分方程组,使用描述函数法研究了上述三个非线性项对前轮摆振稳定区域的影响,将准线性化的方程组代入状态空间内,利用优化特征值实部的方法确定摆振系统的极限环幅值、摆振频率以及临界参数曲线,这种方法可以免去以往摆振稳定性分析时冗长的代数推导. 短句来源 So the study makes an easy way for launching research of MLRS and prepares for applying some mathematics methods (such as CADET)in the statistic field of MLRS. 也为采用某些数学方法（如协方差描述函数法）进一步研究火箭发射系统的统计性能作了必备的前提工作。 短句来源 This thesis makes an efficient analysis on missile intercepting error based on CADET method. 本文通过采用协方差分析描述函数法,对弹道误差变化规律进行了有效分析。 短句来源

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 describing function
 The describing function of a gamma peak is derived. The steady-state analysis of constant (fixed) frequency, parallel resonant dc/dc converters operating under pulse-width modulation control is set forth based on the concepts of harmonic balance analysis and describing function. A dual-input describing function analysis supports the complementary model; vestibular cues dominate sensation at higher frequencies. The describing function model is extended by the proposal of a non-linear cue conflict model, in which cue weighting depends on the level of agreement between visual and vestibular cues. For frequencies whereN/M is a simple ratio a describing function for the membrane is computed. 更多
 describe function
 This model can be used to describe function in terms of mathematical equations and to make predictions from these equations. Here we focus on function definition and describe function invocation later. The framework is based on a metamodel language that can be used to describe function, architecture, and mapping. We describe Function Annotator implementation and its usage scenario in section 5.
 the describing function
 The describing function of a gamma peak is derived. The describing function model is extended by the proposal of a non-linear cue conflict model, in which cue weighting depends on the level of agreement between visual and vestibular cues. Application of the describing function to the Danziger-Elmegreen equations The describing function method is used as a guide to the behaviour of the solutions of the equations of Danziger and Elmergreen, proposed as a model of periodic catatonia. This paper analyzes the dynamical properties of systems with backlashand impact phenomena based on the describing function method. 更多
 descriptive function
 In such cases the descriptive function of echocardiography is of considerable importance. The so-called humanistic orientation and the descriptive function have predominated over empirical studies and the explanatory function in these areas. A characterization theorem for normal integrands with applications to descriptive function theory, functional analysis and nonco Applications are given to descriptive function theory, functional analysis, and nonconvex optimization. For reasons mentioned below, it was useful to have a descriptive function fitted through the points of the N function.
 This paper researches mainly for differential equation and schematic diagram of the motions of the gas-dynamic free-rotor gyroscope which is linked by intersection feedback, researches also for equivalent transfer functions of the gyro system, description functions of the gyro tracking and disturbance errors. Text presents several principles of the gyro system's design. According to above-mentioned analytical result and actual parameter of the gyroscope was made design of the stabilization system. Finally was... This paper researches mainly for differential equation and schematic diagram of the motions of the gas-dynamic free-rotor gyroscope which is linked by intersection feedback, researches also for equivalent transfer functions of the gyro system, description functions of the gyro tracking and disturbance errors. Text presents several principles of the gyro system's design. According to above-mentioned analytical result and actual parameter of the gyroscope was made design of the stabilization system. Finally was made test of the actual gyro system and enclosed actual result of the test in the last part of the paper. Actual design and experimental result showed that the mathematical model of the intersection feedback system of the gasdynamic free-rotor gyroscope, achieved in this paper was correspondnig with the practical situation. As the gas-dynamic free-rotor gyroscope is linked by intersection feedback, the two channel of the gyro (x channel and y channel) are symmetric, thence in the paper only was discussed the derivation and research for the x channel of the gyros, these results of the x channel sufficiently can applied to the y channel of the gyro. 本文着重研究动压陀螺交叉反馈连接时陀螺运动的微分方程和结构图;研究接入反馈时陀螺系统的等效传递函数;研究陀螺跟踪的描述函数和干扰误差的描述函数。同时还提出了陀螺稳定系统设计的几个原则。根据上述分析的结果,结合实际的陀螺参数进行了稳定系统的设计。最后对实际的陀螺系统进行测试,并附有实际结果。通过实际的设计和实验结果说明文中推导的动压陀螺交叉反馈系统数学模型是符合实际的。因为动压陀螺交叉反馈时,陀螺的两个通道(X通道和Y通道)是对称的。所以在文中只用X通道进行推导和听究,而Y通道的各项结果与X通道是一一对应的。 This paper presents the dynamic equations of three axis stabilized satellite during apogee maneuver in transfer orbit. The dynamic interaction between satellite, solar arrays and propellant has been taken into account. A control loop design, computer simulation and stability analysis using root locus and description function has been performed. A priliminary conclusion has been obtained. 本文建立了在转移轨道远地点机动期间,包括液体晃动和太阳帆板挠性在内的三轴稳定卫星姿态动力学方程,进行了姿态控制系统的设计和仿真,分别用根轨迹方法和描述函数方法对系统的稳定性进行了分析,得出了初步结论。 In order to restrain effectively and to eliminate the self-sustaining oscillation caused by nonlinearity in longitudinal DFBW of an aircraft, adopted several methods in design of control law:reduced open loop gain, adding phase lead filter, conditional feedback correction and limited amplitude of oscillation. Using the describing function method, this paper gives emphasis to analyse the conditional feedback correction effect on restrain self-sustaining oscillation. 为了有效地抑制和消除某飞机纵向DBW中非线性引起的自持振荡,在控制律设计中采取了降低系统开环增益、引入相位超前滤波、设置条件反馈校正和限制振荡幅值等措施。本文利用描述函数法,重点分析了条件反馈校正对自持振荡的抑制作用。 << 更多相关文摘
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