turbofan engine

Preliminary analysis of thermodynamic cycle of an intercooled recuperated turbofan engine

中冷回热航空涡扇发动机热力循环初步分析

The optimal control for turbofan engine acceleration control has been investigated. The optimal method used in this paper is Sequential Quadratic Programming ( SQP), one of the most successful methods for solving nonlinear constrained problem.

本文研究了采用非线性规划方法中的序列二次规划最优化方法解决涡轮风扇发动机加速过程的最优控制问题。

Aerodynamic design characteristic of test cell for-high. by-pass ratio turbofan engine

大函道比涡扇发动机试车台气动力设计的特点

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。

The results show that a turbofan engine with a small bypass ratio must be installed, and a suitable turbine entry temperature is obtained by optimization with life cycle cost.

结果表明宜采用小涵道比涡扇发动机，而且不考虑费用时涡轮前温度取值越高越好，考虑费用时则有最大值；

Application of SQP to Multi-Object Optimization of Turbofan Engine Acceleration Control

利用SQP控制涡扇发动机加速过程的多目标最优化研究

Based on these two real time models, the real time mathematical model of the turbofan engine with thrust vectoring nozzle was acquired.

在以上两个模型的基础上建立了带轴对称矢量喷管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 effects 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.

Research of Turbofan Engine Transient Process with Thrust Vectoring Nozzle

带矢量喷管的涡扇发动机动态过程研究

Key Technology of Modern High Bypass Ratio Turbofan Engine

现代高涵道比涡扇发动机关键技术

Application of SQP to acceleration control of turbofan engine

SQP方法在航空发动机加速过程控制中的应用研究

An Investigation on Performance of Variable Vane Control Channel for a Turbofan Engine LPC

某涡扇发动机低压压气机叶片角度控制通道性能研究

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 Effect of Thrust Vector Control on the Performance of Turbofan Engine

矢量喷管控制对发动机性能的影响

The Strength Design System of the Turbojet and Turbofan Engine

航空涡喷、涡扇发动机强度设计系统

Stability Assessment Test Technology of a Turbofan Engine Inlet Temperature Distortion

某型涡扇发动机进口温度畸变的稳定性评定试验技术研究

A design method of QFT robust controller for the turbofan engine based on the Diagonal Dominance Precompensation using the theory of linear matrix inequalities ( LMI) is presented in this thesis.

论文提出了一种基于LMI对角占优预补偿的航空发动机多变量控制系统QFT鲁棒控制器设计方法。

Abnormal vibration has been found on rear installation plane in a turbofan engine durability test.

在某民用涡轮风扇发动机的持久试车过程中,出现了发动机后安装面振动异常的现象.

And identification arithmetic of the Volterra progression model for aero engines was proposed. It was applied to a certain turbofan engine by imitating the dynamic respondence.

利用某型涡扇发动机的动态仿真，进行了发动机Volterra模型辨识及验证。

Chinese large aircraft turbofan engine must be verified through inclusive to obtain airworthiness certificate.

航空大国在民用和军用航空发动机规范中都有专门条文对包容性做出严格规定，我国自行研制的大飞机涡扇发动机，要取得适航证，就必须通过包容性验证。

Aerothermodynamic Model of Turbofan Engine With Matlab Description

涡扇发动机气动热力模型的Matlab表达

The Temperature Distortion Generator ( TDG) design specifications, design technique and the technology of its fabrication were presented. The TDG was tested and calibrated using a turbojet engine and a turbofan engine.

介绍了航空发动机温度畸变试验装置设计技术与研制方法，主要设备及设计技术指标，以及用A型涡轮喷气发动机B型涡轮风扇发动机调试和对比试验结果。

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

Intermediate case is an important part of the turbofan engine components.

中介机匣是涡轮风扇发动机的重要承力部件.

The method is applied to a turbofan engine control system, and is demonstrated to be feasibility.

应用于某型航空涡扇发动机控制系统设计, 仿真结果表明了其可行性.