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maneuvering aircraft
相关语句
  机动飞行器
     A new mathematical model of a rotor with initial bending and stiffness asymmetry in a maneuvering aircraft is presented.
     建立在机动飞行器内具有初始弯曲和不对称刚度的单盘转子的动力学模型 ,研究重力方向与转子轴间夹角变化对等速运行转子幅频特性曲线和等变速运行转子瞬态响应的影响。
短句来源
  机动飞机
     NONLINEAR DYNAMIC INVERSION CONTROL FOR SUPER MANEUVERING AIRCRAFT
     超机动飞机的非线性动态逆控制
短句来源
  “maneuvering aircraft”译为未确定词的双语例句
     Identification of Nonlinear Aerodynamic Model for Maneuvering Aircraft at High Angle of Attack
     飞机大迎角机动非线性气动力模型的辨识
短句来源
     Nonlinear Dynamics of a Cracked Rotor in a Maneuvering Aircraft
     飞行器内裂纹转子系统的非线性动力学特性研究
短句来源
     Aerodynamic Modeling of Spatial Maneuvering Aircraft at High Angle of Attac
     飞机大攻角空间机动气动力建模研究
短句来源
  相似匹配句对
     NONLINEAR DYNAMIC INVERSION CONTROL FOR SUPER MANEUVERING AIRCRAFT
     超机动飞机的非线性动态逆控制
短句来源
     NONLINEAR DECOUPLING CONTROL STUDY FOR AIRCRAFT MANEUVERING FLIGHT
     飞机机动飞行的非线性解耦控制研究
短句来源
     Magnetization of aircraft
     飞机的磁化
短句来源
     B.W. to the aircraft performances.
     电传飞控 /主动控制对飞机性能的影响。
短句来源
     The Orbital Maneuvering Vehicle
     NASA的轨道机动飞行器
短句来源
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  maneuvering aircraft
The MHFS characterizations of the unsteady boundary layers are useful in the study of unsteady separated flowfields generated by rapidly maneuvering aircraft, helicopter rotor blades, and wing energy machines.
      
Nonlinear dynamics of a cracked rotor in a maneuvering aircraft
      
The guidance laws are tested against non-maneuvering and maneuvering aircraft targets and against a simulation of a cruise missile threat.
      
Pictured with the Dayton area landmark avionics tower facility is a maneuvering aircraft--replicating this transformation theme.
      
Finally, maneuvering aircraft can suffer high trim drag at high lift coefficients, severely limiting sustained turn performance.
      


A new mathematical model of a rotor with initial bending and stiffness asymmetry in a maneuvering aircraft is presented. In the model, the influence of the gravity direction on the response amplitude is considered. The dynamical characteristics of a rotor were studied when the angle between the gravity direction and rotor axis direction changes. The response amplitude is obviously different if the angle between the gravity direction and rotor axis direction changes when a rotor runs in a steady state or...

A new mathematical model of a rotor with initial bending and stiffness asymmetry in a maneuvering aircraft is presented. In the model, the influence of the gravity direction on the response amplitude is considered. The dynamical characteristics of a rotor were studied when the angle between the gravity direction and rotor axis direction changes. The response amplitude is obviously different if the angle between the gravity direction and rotor axis direction changes when a rotor runs in a steady state or at a constant acceleration or deceleration. Moreover, the angle between the initial bending and the unbalance and the value of the initial bending affect significantly the response amplitude. With the rotating speed increasing, the amplitude may decrease then increase when the angle is near 180°. The influence of the gravity parameter on the trend of the response amplitude is little. A new method to diagnose both the initial bending and the angle between the initial bending and the unbalance is proposed.

建立在机动飞行器内具有初始弯曲和不对称刚度的单盘转子的动力学模型 ,研究重力方向与转子轴间夹角变化对等速运行转子幅频特性曲线和等变速运行转子瞬态响应的影响。结果表明 :( 1)重力方向与转子轴间夹角变化将导致等速运行转子的幅频特性曲线发生变化 ,振幅差别明显 ,特别是在临界转速之前振幅区别较大。如果其他转子参数相同 ,当重力方向与转子轴间夹角从 0°~ 36 0°变化时 ,部分夹角对应的振幅曲线会重合。 ( 2 )如果重力方向与转子轴间夹角变化 ,则等变速运行转子的瞬态响应振幅也明显不同 ,特别是等变速初期的振幅差别很大。不同夹角所对应的响应曲线可能在临界附近及之后重合。 ( 3)当初始弯曲方向与不平衡方向夹角大到一定程度时 ,等速转子的幅频曲线或等变速转子的瞬态响应曲线的走势发生根本的变化。随着转速的升高或降低 ,转子振幅可能会下降然后再上升 ,或者在临界前保持不变 ,之后则振荡并衰减。 ( 4 )初始弯曲值的大小对转子振幅曲线趋势变化影响很大 ,而重力参数的变化只影响振幅的大小 ,而不影响幅频曲线的趋势。由上述结论可以得到一种新的诊断初始弯曲及判断初始弯曲方向与不平衡夹角大小的方法

This paper describes a neural network based direct adaptive control approach to the problem of reconfigurable flight control of a super-maneuvering aircraft. The base control law is designed in nonlinear dynamic inversion, and neural networks are used to cancel the inversion error induced by many reasons, especially by actuator failures. Simulation of two types of actuator failures show that through adaptively canceling the inversion error, neural networks can reconfigure the control instantly when there...

This paper describes a neural network based direct adaptive control approach to the problem of reconfigurable flight control of a super-maneuvering aircraft. The base control law is designed in nonlinear dynamic inversion, and neural networks are used to cancel the inversion error induced by many reasons, especially by actuator failures. Simulation of two types of actuator failures show that through adaptively canceling the inversion error, neural networks can reconfigure the control instantly when there should be actuator failures. The system will keep steady and maintain certain handling qualities.

讨论了一种基于神经网络的超机动飞机直接自适应重构控制方法。飞机的基本控制律采用非线性动态逆方法设计 ,对于模型不准确和舵面故障等因素导致的逆误差采用神经网络进行在线补偿。通过仿真表明 ,在飞机发生舵面故障时 ,神经网络通过自适应地补偿逆误差 ,可以快速在线重构控制律 ,保持飞机稳定和一定的操纵品质

An adaptive controller with a neural network compensator is designed and applied in the control of a super-maneuvering aircraft. The base control law is designed by nonlinear dynamic inversion method, and single hidden layer (SHL) neural networks are used to compensate the inversion error induced by the inaccuracy of the system model. Simulational results show that the limitation of the accurate mathematical model used in dynamic inversion method can be released through adaptively canceling inversion error...

An adaptive controller with a neural network compensator is designed and applied in the control of a super-maneuvering aircraft. The base control law is designed by nonlinear dynamic inversion method, and single hidden layer (SHL) neural networks are used to compensate the inversion error induced by the inaccuracy of the system model. Simulational results show that the limitation of the accurate mathematical model used in dynamic inversion method can be released through adaptively canceling inversion error in neural networks and the robustness of the control system is improved. Besides, the design of dynamic inversion control law can be simplified by the online neural networks.

讨论了一种基于神经网络动态逆的直接自适应控制方法 ,并应用于超机动飞机的飞行控制中。基本控制律采用非线性动态逆方法进行设计 ,对由于模型不准确导致的逆误差采用单隐层神经网络进行在线补偿。仿真结果表明 ,神经网络通过补偿由于模型不准确引起的逆误差 ,弥补了非线性动态逆要求精确数学模型的缺点 ,提高了整个控制系统的鲁棒性 ,而且可以大大简化动态逆控制律的设计。

 
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