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a variable thrust
相关语句
  变推力
     The Design and Implementation of a Variable Thrust Liquid Propellant Rocket Engine Control System
     一种大范围变推力液体火箭发动机控制器的设计及实现
短句来源
     A RESEARCH ON THE SIMULATION SOFTWARE OF A VARIABLE THRUST LIQUID PROPELLANT ROCKET ENGINE SYSTEM
     变推力液体火箭发机系统仿真软件的研究
短句来源
     THE ANALYSIS FOR REGULATION PERFORMANCE OF A VARIABLE THRUST ROCKET ENGINE CONTROL SYSTEM
     变推力火箭发动机控制系统调节性能分析
短句来源
     FAULT DIAGNOSIS OF A VARIABLE THRUST LIQUID ROCKET ENGINE
     变推力液体火箭发动机的故障识别
短句来源
     A method for calculating dynamic and static characteristics of direct-acting regulator of a variable thrust engine is suggested in this paper.
     本文以变推力发动机混合比调节器为例,给出了直接作用式调节器动静特性的计算方法.
短句来源
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  相似匹配句对
     A TEST STUDY OF THE VARIABLE-THRUST LIQUID ROCKET ENGINE
     变推力液体火箭发动机试验研究
短句来源
     A DESIGN ON INJECTOR OF BIPROPELLANT THRUST-VARIABLE ROCKET ENGINES
     双组元变推力火箭发动机喷注器改进设计
短句来源
     A.
     拟糙叶黄耆 A.
短句来源
     and A.
     和展毛大渡乌头A .
短句来源
     On Selection of the Variable
     关于自变量的选择
短句来源
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  a variable thrust
The interceptor vehicle has propulsive jet systems which can produce a variable thrust, positive or negative, independently in three perpendicular directions.
      
In support of this conclusion, experience on the developmental studies of a variable thrust 100 kg engine is presented.
      


A preliminary analysis for the dynamic Characteristics of a variable-thrust rocket engine control-loop system under investigation is presented.Employing the testing results and with the aid of equivalent approach,the mathematical descriptions for the main links of such a system are introduced,and then the analytical models and impulse transfer functions of this system are given. According to the calculation results,the effect of design parameters on the stability, the static error and the time response...

A preliminary analysis for the dynamic Characteristics of a variable-thrust rocket engine control-loop system under investigation is presented.Employing the testing results and with the aid of equivalent approach,the mathematical descriptions for the main links of such a system are introduced,and then the analytical models and impulse transfer functions of this system are given. According to the calculation results,the effect of design parameters on the stability, the static error and the time response is analysed.In order that the analysis is based on the reliable initial data,the experimental method for obtaining these data is illustrated briefly in the last section.

本文对研究中的变推力火箭发动机控制回路系统现行方案的动特性进行了初步分析。为此,文中利用试验结果和运用等效处理方法建立了该系统各主要环节的数学描述,进而给出整个系统的分析模型和脉冲传递函数。并通过计算分析了系统中诸设计参数对稳定性、静差和时间响应的影响。为了使分析建立在可靠的初始数据的基础上,文章最后对获得这些数据的试验方法作了简略说明。

This paper states the application of state-space method to the analysis ofthe dynamic characteristics of a variable thrust liquid propellant rocket engineand presents a set of state equations for describing the dynamic process of theengine. An efficient numerical method for solving these system equations isdeveloped. The theoretical solutions agree well with the experimental data.The analysis leads to the following conclusion: the set coefficient of theimpulse width, the working frequency of the solenoid...

This paper states the application of state-space method to the analysis ofthe dynamic characteristics of a variable thrust liquid propellant rocket engineand presents a set of state equations for describing the dynamic process of theengine. An efficient numerical method for solving these system equations isdeveloped. The theoretical solutions agree well with the experimental data.The analysis leads to the following conclusion: the set coefficient of theimpulse width, the working frequency of the solenoid valves and the deviationof the critical working points of these valves are important parameters fordetermining the dynamic response time and the control precision of this engi-ne. The methods developed in this paper may be used effectively in the ana-lysis of dynamic characteristics of variable thrust liquid propellant rocketengines.

本文将状态空间分析方法运用于变推力液体火箭发动机系统的动态特性分析,导出了一组描述所述变推力液体火箭发动机动态过程的状态方程。文中提出了求解该系统方程的一种有效的数值方法,理论解与实验数据得到了满意的符合。做为变推力液体火箭发动机系统分析的初步结果,在文中分析了几个重要的工作参数对所述发动机系统动态特性的影响。

This paper introduces a Variable thrust rocket engine controlled bythe hydraulic pressure control system with variable gain and high speedresponse solenvid values. In this article, we discuss theoretical analysisand experimental study of dynamic thrust rocket engine. Test resultshave been also given in this paper.

本文介绍了以可变增益的快速响应电磁阀液压控制系统控制的变推力火箭发动机系统。文中重点对变推力火箭发动机的动态响应特性进行了理论分析和实验研究,并给出了满意的试验结果。

 
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