A multivariable neural network adaptive control is provided for a turbofan engine.
提出了一种发动机多变量神经网络控制方法。
A mathematical model of turbofan engine with thrust vector control was established.
建立了带推力矢量的涡扇发动机数学模型。
Simulation results of LTR control for a turbofan engine show the effectiveness of the 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。
The method was satisfactorily applied to the windmilling characteristics test of a turbofan engine.
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。
Mirage 2000 uses a SNECMA M53-P2 turbofan engine which provides 64 kN thrust and 98 kN with afterburn.
幻影2000的动力装置为一个SNECMA公司的M53-P2涡扇发动机，推力64千牛，加力推力98千牛。
The mathematical model of turbofan engine transient process with thrust vectoring nozzle was established.
建立带矢量喷管的涡扇发动机动态数学模型。
The field replacing and repairing technologies of various stages fan blades for an turbofan engine were studied.
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。
In this paper, the flow and methods of reliability growth and assessment for a type of turbofan engine are presented.
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。
The new starting model can be applied to other turbofan engine "s starting processes" numerical simulation and design.
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 content of this article for follow-up of micro-components turbofan engine research laid the foundation for design.
本文的内容为后续的微涡扇发动机部件设计研究奠定了基础。
FSQP algorithm based multivariable optimal control method for the acceleration process of turbofan engine is developed.
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。
The effects of thrust vectoring angle and angular velocity of vectoring on turbofan engine operation were investigated.
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。
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。
The case study of a high bypass ratio turbofan engine has verified the feasibility of a three-layer back propagation network.
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。
An artificial neural network based expert system has been developed and is applied to aircraft turbofan engine fault diagnosis.
介绍了人工神经网络专家系统在航空涡轮风扇发动机故障诊断上的应用。
A quasi three dimensional flow Euler model with viscous force terms was constructed for integrated small turbofan engine systems.
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。
The digital turbofan engine model contains 10 state variables, 12 measurements, 6 control inputs and 8 component health parameters.
涡扇发动机数字模型包含10个状态变量、12个量测量、6个控制输入量以及8个健康状况参数。
The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.
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。
As the bypass ratio of turbofan engine is more and more high, fan noise is a more important part to the overall turbofan engine noise.
随着飞机广泛使用的涡轮风扇发动机涵道比的不断提高，风扇噪声在飞机总噪声中占有越来越突出的地位。
A fault diagnosis equation for the twin-spool mixed flow turbofan engine was established based on the simulation and gas path analysis.
并以此为基础运用气路分析原理，选取表征发动机性能参数变化的症兆变量和测量参数，建立了发动机故障诊断小偏差方程。
The results validate the feasibility of the two methods. They are also very useful in improving the performance of the turbofan engine.
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。
A method, "gross thrust model", is developed to determine gross thrust of jet engine and afterburning turbofan engine in flight testing.
提出了一种飞机飞行中发动机推力测定的总推力模型。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
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。
Eventually given a 40 kg thrust class, low-pressurized than 3.0 single-turbofan engine micro-impeller rich data and characteristic curves.
最终给出了一台40公斤推力级、低增压比为3.0的单叶轮微涡扇发动机的丰富数据和特性曲线。
Following hundreds hours of altitude test of a turbofan engine at different conditions, it has proved that the reconstruct ion is effective.
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。
A method for incorporating linear state inequality constraints in a Kalman filter is proposed and applied to turbofan engine health estimation.
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 model of optimizing the turbofan engine performance by adjusting the key sections of components and the program based on the model were developed.
为了解决工程研制中某型涡扇发动机性能调整与优化问题，建立了关键截面调整对发动机特性影响的数学模型并开发了相应的程序。
This method has been successfully applied to a turbofan engine and the simulation results show the feasibility and effectiveness of the proposed method.
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.
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。
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