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aircraft maneuvers
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  “aircraft maneuvers”译为未确定词的双语例句
     CONTROL LAW STUDY OF AIRCRAFT MANEUVERS AT HIGH ATTACK ANGLE
     飞机大迎角机动飞行控制律研究
短句来源
     NONLINEAR DECOUPLING CONTROL OF AIRCRAFT MANEUVERS
     机动飞行非线性解耦控制
短句来源
     Three modes of decoupling controls for aircraft maneuvers are studied with the decoupling control theory based on the differential geometry control theory. Two types of agility maneuvers and three basic modes \%A\-n,α\-1 \%and\% α\-2\% of direct lift control are realized by the three nonlinear decoupling control modes.
     用微分几何控制理论研究了飞机非线性运动的 3种解耦运动模式 ,并用这 3种模式实现了 3种形式的敏捷性机动和直接升力控制的 3种基本模式 ,即 An,α1和α2 模式。
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  相似匹配句对
     NONLINEAR DECOUPLING CONTROL OF AIRCRAFT MANEUVERS
     机动飞行非线性解耦控制
短句来源
     NONLINEAR DECOUPLING CONTROL AND AIRCRAFT AGILITY MANEUVERS
     非线性解耦控制与飞机敏捷性机动
短句来源
     Magnetization of aircraft
     飞机的磁化
短句来源
     AIRCRAFT MAINTENANCE
     飞机维修
短句来源
     HELICOPTER AEROBATIC CHARACTERISTICS AND MANEUVERS
     直升机空战特征及机动科目
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  aircraft maneuvers
Dendritic solidification experiments during multiple parabolic aircraft maneuvers for iron-carbon type alloys and superalloys show increased dendritic spacing in low-gravity periods.
      
Nonlinear loop simulations of real time kinematic (RTK) tracking during high-g aircraft maneuvers with vehicle-induced blockages are used to illustrate the filtering method and it s robustness.
      
Instructors train pilots to fly the full range of aircraft maneuvers or capabilities necessary to accomplish the unit's flying mission.
      


It is well known that an Inertial Navigation System(INS) can proyide accurate continuous navigation information in a short period of time, but its errors increase with time. On the other hand, the velocity errors of a Doppler Radar(DR) do not accumulate with time, but the velocity accuracy is poor due to outer disturbances and inherent uncertainties. A Doppler-Aided Inertial Navigation System (DINS) incorporates the advantages of both INS and DR to give a system which can provide accurate navigation information...

It is well known that an Inertial Navigation System(INS) can proyide accurate continuous navigation information in a short period of time, but its errors increase with time. On the other hand, the velocity errors of a Doppler Radar(DR) do not accumulate with time, but the velocity accuracy is poor due to outer disturbances and inherent uncertainties. A Doppler-Aided Inertial Navigation System (DINS) incorporates the advantages of both INS and DR to give a system which can provide accurate navigation information for a long period of time. An optimum incorporation of the two systems can be accomplished by means of a Kalman filter. From the system point of view, the crux of improving the navigation performance of DINS is to increase the estimating ability of the Kalman filter, that is, to enhance the observability of the state variables. The common me- thod applied to analyze the performance of a Kalman filter is the covariance analysis, which can get the estimation effects of the Kalman filter. But it proves to be very difficult for us to employ covariance analysis to make clear the relation between the state estimation and aircraft maneuvers and to make clear the connections among the state variables themselves. This paper, however, chooses an intuitive method, which directly inves- tigates the relations between state variables and measurement values. By using this method, the observabilities of both a Doppler-Aided Strapdown Inertial Navigation System(DSINS) and a Doppler-Aided Platform Inertial Navigation System(DPINS) are studied. The effects of different types of maneuvers on the system observability are discussed in detail, and major sim- ilarities and differences between the characteristics of DSINS and those of DPINS in maneuvers are pointed out particularly. Finally, a sample system, with all its numerical values included, is given.

多卜勒/惯性组合导航系统(DINS)是较复杂的卡尔曼滤波系统。提高DINS的导航性能的关键在于提高卡尔曼滤波器对误差状态的可观测性[1]、[2]。若用通常的可观测性分析法对DINS的可观测性进行研究,不但分析过程复杂,并且难以具体判定不同的飞行动作对于提高各个误差状态的可观测性的作用[3]。本文采取直接从误差状态与量测值的关系入手来分析系统可观测性的方法,详细研究了增强DINS误差状态可观测性的条件和如何利用飞机的机动飞行来实现这些条件;不仅分析了在不同的飞行动作时各个误差状态是否可观测,而且还比较出它们的可观测性程度以及相互之间的联系。最后,通过计算机仿真给出在飞机做弯道飞行时,误差状态可观测性提高的效果。

Based on Bifurcation Analysis and catastrophe theory, a novel theoretical method to forecast jump bifurcation phenomena in the control space is established with nonlinear mathematical models. The jump bifurcation is a type of phenomenon which often occurs in the aircraft maneuvers, such as rapid-roll divergence departure, entry into stall and then into spin from steady, straight flight, or recovery into the state of low angle of attack from high angle of attack. Apparently prediction of these phenomena...

Based on Bifurcation Analysis and catastrophe theory, a novel theoretical method to forecast jump bifurcation phenomena in the control space is established with nonlinear mathematical models. The jump bifurcation is a type of phenomenon which often occurs in the aircraft maneuvers, such as rapid-roll divergence departure, entry into stall and then into spin from steady, straight flight, or recovery into the state of low angle of attack from high angle of attack. Apparently prediction of these phenomena in the control space will be of much help in the design of control law. By means of studying singular lines in the bifurcation surfaces, we get the critical values of control surfaces avoiding rapid-roll divergence and provide the guide to extend rapid-toll maneuver scope. According to the change of numbers and stability of equilibrium solutions in the bifurcation surfaces, the thesis works out the control law of bringing planes entry into stall, spin, then returning to stable and controllable state at low angle of attack. The calculation of time history proves the conclusion.

本文以分歧突变理论为基础,采用非线性数学模型,建立了求解分歧面的理论方法。文中通过对分歧面的分析研究,得到了避免飞机出现急滚发散的舵面极限值;通过分析分歧面上平衡解的个数和稳定性的变化情况,设计了使飞机进入或退出失速尾旋的操纵规律。经时间历程验证,所得结论正确可靠。

Integration of a Strapdown Inertial Navigation System (SINS) with a Glo-bal Positioning System (GPS) receiver presents many advantages. With thisintegrated design approach, the authors overcome some of the recognized limi-tations of an INS such as: (1) unbounded position error and pilot initialization,(2) stand-alone GPS limitations such as poor satellite geometry and dynamicnoise. This paper discusses the synergistic effect obtainable with such an approach,and emphasizes Kalman filter design, system configurations...

Integration of a Strapdown Inertial Navigation System (SINS) with a Glo-bal Positioning System (GPS) receiver presents many advantages. With thisintegrated design approach, the authors overcome some of the recognized limi-tations of an INS such as: (1) unbounded position error and pilot initialization,(2) stand-alone GPS limitations such as poor satellite geometry and dynamicnoise. This paper discusses the synergistic effect obtainable with such an approach,and emphasizes Kalman filter design, system configurations and performanceevaluation. This paper analyzes a specific example and the key features of suchan analysis are: (1) A comprehensive digital computer simulation is developed. (2) Covariance analysis results are presented to demonstrate the impro-ved performance of the proposed integrated system composed of medium accu-racy strapdown instrument package and C/A Code GPS receiver under diffe-rent flight scenarios. In the covariance analysis just mentioned, the authors show that beforeloss of the GPS signal, the navigation errors are bounded by the GPS solutionaccuracy. North, East and vertical velocity errors are 0.07, 0.1 and 0.08m/s(1σ), respectively. North and East positions and altitude errors are 11, 15 and20m (1σ) for precise position locating. During the 180sec GPS signal outagedue to aircraft maneuvers and/or radio noise jamming, the position error inc-reases from 18m to 80m, the horizontal velocity error goes from 0.1m/s to0.7m/s. As a result of inertial velocity aiding, fast reacquiring of the jammedor masked satellite signal can be realized, the navigation error quickly returnsto its full operational values. Accurate and rapid INS in-flight alignment canbe accomplished in aircraft straight flight and turns by using GPS measure-ments. Initial rms azimuth alignment errors are reduced from about 35 arcminto about 2, 5 arcmin in less than 3 minutes. In this paper the authors show that the present integrated system approachallows the error estimation filter design to be less dependent on strict modellingof error dynamics, and that the system can be implemented with a modulardesign approach and is cost-effective and reliable.

采用卡尔曼滤波器进行最优组合的GPS/捷联惯性组合导航系统是一种精度高、成本效益好、功能可靠的导航系统。它既能增强GPS接收机的抗干扰能力又能抑制惯导的积累误差。机动飞行和干扰环境下所进行的模拟计算表明,采用C/A码GPS接收机和低精度(0.1°/h陀螺,1×10~(-3)加速度计)捷联惯导所组成的系统,定位精度可达20m(1σ),速度精度约为0.1m/s(1σ)。与纯惯导相比,性能精度约提高2个数量级。系统具有对惯性元件进行测漂补偿,对GPS用户钟差进行估计校正和实现惯性平台空中对准的功能,能缩短地面准备时间,提高飞行器的快速反应能力,是一种在航空、航天等领域中有着广阔应用前景的导航定位系统。

 
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