建立了带推力矢量的涡扇发动机数学模型。
A mathematical model of turbofan engine with thrust vector control was established.
建立带矢量喷管的涡扇发动机动态数学模型。
The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
本论文建立了一个新的涡扇发动机起动过程模拟的模型。
This paper build up a new model of turbofan engine's starting process.
该方法在某型涡扇发动机风车特性试验中得到了成功应用。
The method was satisfactorily applied to the windmilling characteristics test of a turbofan engine.
本文给出了涡扇发动机可靠性增长分析与评估的流程与方法。
In this paper, the flow and methods of reliability growth and assessment for a type of turbofan engine are presented.
研究了矢量喷管偏转角和偏转角速度对涡扇发动机工作的影响。
The effects of thrust vectoring angle and angular velocity of vectoring on turbofan engine operation were investigated.
起动模型可以应用到其它涡扇发动机的起动过程模拟和设计中。
The new starting model can be applied to other turbofan engine's starting processes' numerical simulation and design.
研究了在外场更换和修理某型涡扇发动机各级风扇叶片的技术。
The field replacing and repairing technologies of various stages fan blades for an turbofan engine were studied.
提出了一种基于FSQP算法的涡扇发动机多变量最优加速控制方法。
FSQP algorithm based multivariable optimal control method for the acceleration process of turbofan engine is developed.
建立了一体化弹用小涡扇发动机系统含粘性力项的准三维欧拉流动模型。
A quasi three dimensional flow Euler model with viscous force terms was constructed for integrated small turbofan engine systems.
可以把这个起动模型应用到其它涡扇发动机的起动过程的模拟和设计中。
The new starting model can be applied to other turbofan engine "s starting processes" numerical simulation and design.
喷管中的气流由主流燃气和次流空气组成，用以模拟涡扇发动机的喷管。
The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.
某涡扇发动机数百小时的各飞行状态高空模拟试验证实，改造成功有效。
Following hundreds hours of altitude test of a turbofan engine at different conditions, it has proved that the reconstruct ion is effective.
本文采用基于LQR的PID控制算法，设计某型号涡扇发动机控制系统。
In this paper, the optimal PID control system for aero-engine was designed using LQR (Linear-Quadratic Regulator) approach.
将此设计方法应用于某型涡扇发动机的LTR控制，取得了良好的控制效果。
Simulation results of LTR control for a turbofan engine show the effectiveness of the approach.
结果证明所提出的两种途径对于涡扇发动机的性能和多任务适应性有很大改善。
The results validate the feasibility of the two methods. They are also very useful in improving the performance of the turbofan engine.
简述了飞航导弹任务剖面、约束条件的给定、导弹的重量组成以及涡扇发动机模型。
The mission section, the constrain conditions, the weight composition of the maneuverable missile, and the model of used in turbofan engine maneuverable missile were presented.
通过一个高涵道比涡扇发动机故障诊断的实例分析，验证了三层逆传播网络的可行性。
The case study of a high bypass ratio turbofan engine has verified the feasibility of a three-layer back propagation network.
提出了一种带模糊补偿的神经网络辨识器，并应用在某型涡扇发动机转速控制系统中。
A new neural network algorithm with fuzzy logic compensation was proposed and applied to an aero-engine rotating speed control system.
本文将此方法成功应用于某涡扇发动机，取得了良好的效果，验证了本方法的可行性。
This method has been successfully applied to a turbofan engine and the simulation results show the feasibility and effectiveness of the proposed method.
提出了一种加入线性不等式约束的卡尔曼滤波方法，并用于涡扇发动机的健康状况估计。
A method for incorporating linear state inequality constraints in a Kalman filter is proposed and applied to turbofan engine health estimation.
基于各部件特性进行涡扇发动机小偏差模型研究时，需用到风扇和压气机的通用特性图。
The general characteristic maps of fan and Compressor is necessary for turbofan engine little deviation modeling which based on component characteristics.
采用实验方法对某型弹用涡扇发动机涡轮低压导向器原型和改型进行了详细的低速风洞实验。
Detailed flow field measurements were conducted in a low speed wind tunnel for both original and modified LGV's which are used in turbofan engines.
经过十年努力，部分分析家相信，中国终于开始用上了自己的涡扇发动机，这一先进战机不可缺少的技术。
After decades of effort, some analysts believe, China is finally beginning to use its own turbofan engines, an essential technology for advanced fighters.
涡扇发动机作为现代战斗机的心脏，其性能和稳定性对战斗机的性能和稳定性能有很大的影响。
Modern low bypass ratio turbofan engine is the heart of the new fighter, whose performance and aerodynamic stability greatly affect the characteristics of the new fighter.
在涡扇发动机基础上，以脉冲爆震燃烧室代替普通加力燃烧室构成涡扇-脉冲爆震组合发动机。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
基于双轴涡扇发动机热力学模型，采用高低压涡轮间补燃的方法，实现了对发动机性能的改善。
On the basis of the thermodynamics model of two-spool turbofan engine, performance of two-spool turbofan engine was improved by after-burning between high and low turbines.
这些经验对于我们今后设计大函道比涡扇发动机和螺浆风扇发动机试车台时，将是十分有用的。
This experience will be very helpful in the design of test for high by-pass ratio turbofan engine and propeller-fan engine.
这些经验对于我们今后设计大函道比涡扇发动机和螺浆风扇发动机试车台时，将是十分有用的。
This experience will be very helpful in the design of test for high by-pass ratio turbofan engine and propeller-fan engine.
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