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性能寻优
相关语句
  performance seeking
     Research of Hybrid Optimization Method for Aeroengine Performance Seeking Control
     航空发动机性能寻优控制混合优化算法
短句来源
     Study of MAPS Methods for Turbofan Engine Performance Seeking Control
     MAPS方法在航空发动机性能寻优控制中的应用
短句来源
     Based on generalized reduced gradient method for aero-engine performance seeking control
     基于广义既约梯度法的航空发动机性能寻优控制
短句来源
     Performance Seeking Control (PSC) is the vital technology of IFPC.
     航空发动机性能寻优控制是飞行/推进系统综合控制的关键技术。
短句来源
     Model-Assisted Pattern Search method (MAPS) was applied to the study of performance seeking control using an aircraft engine nonlinear component level model.
     利用模型辅助模式搜索方法(MAPS方法),研究了某型涡扇发动机基于部件级非线性实时数学模型的性能寻优控制。
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  “性能寻优”译为未确定词的双语例句
     Performance Optimization of Turbofan Engine Non-Augmented Maximum Thrust Mode Based on Genetic Algorithm
     基于遗传算法的涡扇发动机最大状态性能寻优
短句来源
     Firstly, the engine models including the nonlinear model and adaptive model are studied, and then the linear model is established.
     首先研究了发动机非线性数学模型和适应发动机性能寻优控制使用的自适应实时模型的设计思路,并在此基础上建立发动机线性模型。
短句来源
     PERFORMANCE OPTIMIZATION OF HIGH THRUST-WEIGHT RATIO TURBOFAN ENGINE
     高推重比涡扇发动机性能寻优分析研究
短句来源
     Dynamic Characteristics Optimization Design for Crank and Rocker Mechanisms of Knowing Link Positions
     以动力性能寻优设计铰链四杆机构
短句来源
     The nonlinear component level engine mathematical model was analyzed and supplied with the performance optimization part and the practical constraints part.
     对该涡扇发动机在最大非加力状态和巡航状态下的性能寻优问题进行研究分析,将之转化为带约束的非线性数学规划问题。
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  相似匹配句对
     Its performance is proved by simulation experiments.
     仿真实验结果表明了它的寻优性能 .
短句来源
     Optimization for Multi- Mood Engine Experiment
     发动机性能试验多工况综合寻优
短句来源
     Plant Performance
     设备性能
短句来源
     application forecast;
     性能预测;
短句来源
     AN ORTHOGONAL OPTIMIZATION METHOD
     正交寻优
短句来源
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The optimization of installation performance was completed by the comprehensive optimal method for the high thrust-weight ratio turbofan engine.The propulsion system performance model of the variable geometry turbofan engine served as the base,and the maximum of install thrust,minimum of install SFC and minimum of the inlet temperature of turbine were taken as the optimization modules respectively.The calculation and the following analysis showed that the propulsion system performance can be improved significantly...

The optimization of installation performance was completed by the comprehensive optimal method for the high thrust-weight ratio turbofan engine.The propulsion system performance model of the variable geometry turbofan engine served as the base,and the maximum of install thrust,minimum of install SFC and minimum of the inlet temperature of turbine were taken as the optimization modules respectively.The calculation and the following analysis showed that the propulsion system performance can be improved significantly by multiple parameter performance seeking control for the turbofan engine with afterburner.The improvements are as follows:(1)the supersonic cruise install thrust can be increased by about 8% on the module of maximum thrust;(2)the subsonic cruise install SFC can be decreased by 2% on the module of minimum SFC;and (3) the turbine inlet temperature can be lowered by about 25 K at the constant install thrust on the module of minimum temperature.

本文在变几何涡扇发动机推进系统性能模型基础上,采用综合优化方法,分别以安装推力最大、安装耗油率最低和涡轮前温度最低为推进系统性能寻优的目标,针对某高推重比加力涡扇发动机进行了稳态安装性能最优化计算。分析结果表明,对于包含多个可调节几何参数的军用加力涡扇发动机而言,在基准调节规律的基础上对发动机进行性能寻优控制,可以明显改善推进系统的性能,从而大幅度提高飞机的综合作战能力。

The constraints of engine military regime is analized,and a whole range performace optimizing method is given.The engine perfomance at high altitude and high mach number is greatly improved by suitabily choosing high pressure rotor speed matching to the throttle ratio and using the “cold overrunning”and “gas temperature storage utilizing”techniques

对发动机最大状态进行了约束分析,提出了全范围性能寻优算法。通过改进设计点高压物理转速和节流比的配置,以及“冷超转”和“燃气储备利用”技术的采用,大大提高了发动机高空高速的推力特性。

In order to improve the non augmented supersonic cruise performance of the 4th generation engine,an idea for designing is proposed,which consists in rational matching of the high pressure rotor physical speed to the throttle ratio at ground design point and utilization of the "cold overrun" and "gas temperature storage" techniques for performance optimization.A realization of the ides is carried out.It is proven that the velocity characteristics of the engine is improved to a great extent and the optimal thrust...

In order to improve the non augmented supersonic cruise performance of the 4th generation engine,an idea for designing is proposed,which consists in rational matching of the high pressure rotor physical speed to the throttle ratio at ground design point and utilization of the "cold overrun" and "gas temperature storage" techniques for performance optimization.A realization of the ides is carried out.It is proven that the velocity characteristics of the engine is improved to a great extent and the optimal thrust characteristics of the engine are provided in a broad range of the flight Mach numbers.

本文基于改善第四代发动机不加力超声巡航性能这一目标 ,提出了合理配置发动机地面设计点高压物理转速和节流比的设计思想 ,并结合冷超转和燃气储备利用技术进行性能寻优 ,大大提高了发动机的高空速度特性。

 
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