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transport aircraft
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  运输机
     Future Development of Helicopter and Transport Aircraft in China
     中国直升机 运输机的未来发展
短句来源
     Design and Realization of Digital Flight Support Systerm of Transport Aircraft
     运输机数字化飞行保障系统的设计与实现
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     The helicopter in production such as Z-11, Z-9, Z-8, and the transport aircraft in production such as Y-5, Y-7,Y-8, Y-12 and N-5 are reviewed.
     介绍了中国在产的直升机、运输机 ,在产的直升机有直 11(2吨级 )、直 9(4吨级 )、直 8(13吨级 )系列 ,在产的运输机有运 5、运 7、运 8、运 12和农 5系列 ;
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     Design of longitudinal automatic landing control law of transport aircraft with μ synthesis
     基于μ综合方法的运输机纵向自动着陆控制律
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     The control system to be beaten coal installation may be divided into the leather belt transport aircraft (Consising of shifters fragmentary installation , Except for iron ,Except for timber ,Dust exclusion installation and measure installation )Control , Unload coal installation control , Coal yard machine control and giving distributes coal the dominateeing four sections of system device.
     输煤设备的控制系统可分为皮带运输机(包括筛碎设备、除铁、除木、除尘设备和计量设备)的控制、卸煤设备的控制、煤场机械的控制和给配煤系统设备的控制四个部分。
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  运输类飞机
     Y7-200A aircraft is a transport aircraft which is certificated fully based on China civil aircraft regulation (CCAR-25) for the first time by our country.
     Y7-200A型飞机是我国第一次全面按照中国民用航空规章第25部(CCAR-25)进行型号合格审定的运输类飞机
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     The Calculation on Balanced Field Length for Transport Aircraft
     运输类飞机平衡场长的计算
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     Study on certification performance flight test methods of civil transport aircraft
     民用运输类飞机合格审定性能试飞方法研究
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     Analysis of Airframe/Propulsion Integration for Complex Transport Aircraft
     运输类飞机/发动机干扰流场纵、横向一体化数值分析
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     This paper can be used as a reference for natural icing flight test of transport aircraft.
     可供运输类飞机自然结冰飞行试验时参考。
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  “transport aircraft”译为未确定词的双语例句
     Aerodynamics Design Problems of Special Transport Aircraft
     特殊运输平台的气动设计问题
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     Combining dynamic design of wing flutter model for a giant transport aircraft, a numerical example of engineering application is presented.
     结合某大型飞机机翼颤振吹风模型的动力设计 ,本文给出了工程应用的具体数值例子。
短句来源
     NUMERICAL SIMULATION OF TRANSONIC FLOW OVER AN ADVANCED TWIN ENGINE TRANSPORT AIRCRAFT
     先进双发民用飞机跨音速绕流数值模拟
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     Finally, a typical TECS is designed for a Boeing- 707 transport aircraft model, and satisfactory simulation results are obtained.
     最后以波音(Boeing)707飞机为对象,进行了具体的系统设计。
短句来源
     The transonic flowfield and aerodynamic characteristics of the advanced twin engine transport aircraft are also simulated numerically by using finite volume methods to solve the Euler equations with high efficiency, and the viscous effect of wing boundary layer is considered.
     应用有限体积法高效求解欧拉方程,模拟先进双发民用飞机的跨音速绕流,并计入机翼边界层的粘性效应,获得存在短舱、挂架干扰的翼身组合体气动特性。
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  transport aircraft
As a substitute to the NASA GA(W)-2 airfoil, that is envisaged for a Light Transport Aircraft (LTA), a new airfoil NAL-MSNLF-136 is designed at NAL.
      
Design of a natural laminar flow airfoil for the light transport aircraft
      
Development of a semiautomatic fatigue-evaluation system for transport aircraft
      
Some problems of flight mechanics encountered in creating transport aircraft designed by O.
      
Resolving applied-mechanics problems in creating Antonov transport aircraft
      
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In this paper an algorithm is developed, which is based on Levine-Athans work, by using functional optimization, This approach requires considerably less computation than for the algorithm of Levine- Athans and ensures the convergence of solution.Derivation of the gradient matrix is important in this algorithm. A more simple and explicit derivation is presented here.The conjugate gradient technique is here generalized and applied to the problem of matrix function-A program is produced to make this algorithm...

In this paper an algorithm is developed, which is based on Levine-Athans work, by using functional optimization, This approach requires considerably less computation than for the algorithm of Levine- Athans and ensures the convergence of solution.Derivation of the gradient matrix is important in this algorithm. A more simple and explicit derivation is presented here.The conjugate gradient technique is here generalized and applied to the problem of matrix function-A program is produced to make this algorithm viable on CDC-6500.As a numerical example, a stability augmentation system of M-2.7 flight condition of a supersonic transport aircraft is computed.

本文在Levine-Athans方法基础上提出了一种输出反馈最优化设计的算法。这一算法采用了函数最优化技术,比Levine-Athans算法在计算上大为简化,收敛性也得到了保证。 求梯度矩阵是这一算法的关键。文中给出了一种求梯度矩阵的方法,较其它方法更为直观和简单。 将共轭斜量法及Armijo法则推广运用到矩阵函数最优化问题。采用符号函数法求解矩阵Lyapunov方程。从而实现了这一算法的各主要步骤。 在CDC—6500上编制了实现这个算法的程序。 作为例子,文中对M=2.7超音速运输机的侧向增稳控制系统进行了设计。

This paper introduces the general methods of calculating the optimal flight trajectories of vertical navigation,including the selection of motion equations,control variables,cost functions and the optimal calculation by the variational method. The paper recommends a simplified algorithm and trajectory synthesis supplied by FMC Software and developed by DELCO which is currently used on transport aircraft.It then describes how the POA Software is being used to formulate the flight plan and implement the...

This paper introduces the general methods of calculating the optimal flight trajectories of vertical navigation,including the selection of motion equations,control variables,cost functions and the optimal calculation by the variational method. The paper recommends a simplified algorithm and trajectory synthesis supplied by FMC Software and developed by DELCO which is currently used on transport aircraft.It then describes how the POA Software is being used to formulate the flight plan and implement the real-time data updating and the guided flight.

本文首先叙述垂直剖面内优化飞行轨迹的一般计算方法,从确定飞行运动方程、选择控制变量、建立成本函数到变分法优化运算。然后以目前运输机和某些客机机载飞行(性能)管理计算机的软件为例(由DELCO公司开发,首先应用于C-130、C-135、C-141运输机,并在此基础上发展到用于DC-9-80客机上),说明一种简化的计算方法、轨迹综合。特别说明了性能优化运算POA软件如何制订出飞行计划表格,及在实时飞行中的数据更新和制导飞行。

Total energy control is a new concept for the integrated flight / propulsion control of aircraft. Based on controlling the amount of aircraft total energy and its distribution, it decouples the vertical flight path and speed control, and further establishes a unified flight control system. This paper studies this control technique with the decoupling control principle of multi-variable system. First, the basic concept and principle of total energy control system (TECS) is analyzed, and the aircraft point-mass...

Total energy control is a new concept for the integrated flight / propulsion control of aircraft. Based on controlling the amount of aircraft total energy and its distribution, it decouples the vertical flight path and speed control, and further establishes a unified flight control system. This paper studies this control technique with the decoupling control principle of multi-variable system. First, the basic concept and principle of total energy control system (TECS) is analyzed, and the aircraft point-mass energy movement model is established based on its inner longitudinal attitude control loop and engine thrust control loop. Then, with output feedback control and fore-feed V-canonical decoupling structure, the TECS is analyzed, the control law which can decouple the vertical flight path and speed control of aircraft is designed, and the system design criteria are determined. Finally, a typical TECS is designed for a Boeing- 707 transport aircraft model, and satisfactory simulation results are obtained.

飞机总能量控制是一种全新的综合飞行/推力控制技术,从控制飞机总能量的变化与分配出发,全面解决纵向飞行轨迹控制与速度控制之间的耦合问题;进而建立起一体化的综合飞行控制系统。用多变量系统解耦控制理论研究了这种控制系统,首先分析了总能量控制的基本思想,建立起包含飞机纵向姿态控制回路和发动机推力控制回路的飞机质点能量运动模型,然后利用输出反馈和V规范型前馈解耦策略,对此系统进行解耦分析,设计出能实现飞行轨迹与速度间解耦控制的总能量控制律,并确定出系统的设计条件;最后以波音(Boeing)707飞机为对象,进行了具体的系统设计。

 
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