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。
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。
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。
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。
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。
The above experimental result is of value for the mechanism and suppression of low frequency combustion oscillation in an afterburner of a turbofan engine.
上述结果对研究低频振荡燃烧机理和抑制技术有一定的参考价值。
Using the available data from 3 starts in simulated altitude tests, the windmilling start ignition characteristic of a turbofan engine was analyzed in this paper.
本文利用某型涡扇发动机高空模拟试车台的试验结果，选取其中3次左边界起动试验的数据，着重对该发动机的风车起动点火特性进行了分析。
One is the geared turbofan (GTF), a new type of jet engine from Pratt &Whitney, part of America’s United Technologies group.
一款是来自普惠公司的新型喷气发动机GTF，普惠隶属于美国联合技术公司。
One is the geared turbofan (GTF), a new type of jet engine from Pratt & Whitney, part of America's United Technologies group.
一款是来自普惠公司的新型喷气发动机GTF，普惠隶属于美国联合技术公司。
Both BA and KLM, after all, had direct experience of what flying through volcanic ash can do to a high-bypass turbofan jet engine.
毕竟，英航和荷航都有用高旁路涡轮风扇喷气式飞机引擎穿越火山灰的经验。
The solution devised by Pratt & Whitney (P&W), a division of United Technologies, is a “geared turbofan” engine called the PurePower PW1000G.
由普惠提供的解决方案，是名为PurePower PW1000G的齿轮传动涡扇发动机。 普惠是联合科技集团的一个分公司。
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 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。
United Technologies has suffered a few setbacks this year, including a fire in the prototype for the geared turbofan on the Bombardier C-Series and an engine blowout on the F-35 Joint Strike Fighter.
联合技术公司在今年曾遭遇过多次打击，包括庞巴迪c系列的齿轮传动式涡轮风扇发动机原型起火，还有F - 35联合攻击战斗机的引擎爆炸。
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。
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。
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。
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。
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。
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。
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。
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。
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。
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