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双语推荐：操纵特性

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由于倾转旋翼机飞行模式多，各部件气动干扰复杂且操纵面冗余，特别是倾转过渡模式，短舱带动旋翼系统倾转，结构布局发生改变，从理论上确定气动与操纵特性难度大。为了研究倾转旋翼机的气动与操纵特性，对某小型无人倾转旋翼机展开全尺寸、全模式吹风试验，其中不带动力试验主要用于研究倾转旋翼机在不同迎角、短舱倾角、前飞速度等飞行状态下的气动特性；带动力试验主要用于研究倾转旋翼机不同飞行模式带机翼与不带机翼时，旋翼／机翼／襟副翼相互干扰作用，以及总距、副翼、升降舵的操纵功效。根据试验数据推导出小型无人倾转旋翼机全包线飞行的操纵特性方法，对进一步完善倾转旋翼机设计以及试飞试验的成功提供了参考。
It is very difficult to determine the aerodynamics and control characteristics theo-retically for tiltrotor aircraft because of multi-flight modes,complexity of aerodynamic interac-tions,and redundancy of control surfaces.Especially for the tilting flight mode,the layout of the aircraft is transformed between the helicopter mode and the fixed-wing airplane mode with the na-celle driven rotor system tilting.In order to investigate the aerodynamics and control characteris-tics,the full-span and full-envelop flight modes of a small unmanned tilt rotor are tested in wind-tunnel prior to flight.The un-powered test is mainly determining the flight characteristics with different attack angles,nacelle angles and forward speeds.The powered test is focused on the aerodynamic interactions among rotor,wing and flaperon wing,with and without wings,as well as the efficacy manipulation of the collective aileron and elevator.According to the experimental data,the full-envelop flight control

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滚装船是近几十年才出现的新型船种，其操纵性有其自身特点。分析滚装船的船型特点和操纵特性。阐述了滚装船在天津港主航道航行和靠离泊时的操纵经验，可供参考。
Roll-on roll-offship is a new kind of ship, it has appeared for several decades. Manipulation of it has its characteristics. The ship feature of both navigating in the main channel of Tianjin Port and berthing and leaving manipulating are stated, which could be referenced.

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无尾飞翼飞机通常使用开裂式阻力方向舵或者嵌入式操纵面来解决其航向控制问题。开裂式阻力方向舵对飞机的航向控制机理与传统方向舵不同，其舵效随舵偏角的变化呈非线性特性，且在较大迎角时会产生操纵反效现象，诱发航向振荡，产生飞行事故。针对此问题，利用CFD方法分析了某小型无尾飞翼飞机开裂式阻力方向舵的操纵特性，提出一种基于迎角反馈的开裂式阻力方向舵预偏差动控制方法，并进行了非线性数值仿真和试飞验证。结果表明：该方法可以改善开裂式阻力方向舵的非线性特性，解决操纵反效问题，增强无尾飞翼飞机低速飞行时的航向控制性能。
The yaw of a tailless flying wing aircraft ( TFWA) is usually controlled with a split drag rudder or spoiler slot deflector.The yaw control mechanism of the split drag rudder is different from that of the traditional rudder in that the former''s rudder effect is nonlinear as the deflection varies.The split drag rudder may produce control rever-sal when the TFWA has large angle of attack, causing directional oscillation and a flight accident.Therefore we use the CFD method to analyze the control characteristics of the split drag rudder of a certain miniature TFWA and pro-pose a method for dynamically controlling the biased deflection of the split drag rudder based on the angle of attack feedback, which is then verified through nonlinear numerical simulations and flight tests.The simulation and test re-sults and their analysis show preliminarily that our method can reduce the nonlinearity and control reversal of the split drag rudder and enhance the yaw control performance of t

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为研究某型飞机操纵系统国产钢索滑轮组与进口钢索滑轮组动摩擦特性的差异，在参考国内外相关文献资料和工程实践的基础上，就该操纵系统中拟采用的进口钢索滑轮组进行动摩擦特性的研究。运用经典力学理论的基本原理，通过与系统中正在使用的国产钢索滑轮组动摩擦特性的对比分析，并对试验中取得的数据运用Labview 软件和频谱分析软件进行处理。结果表明：该进口钢索滑轮组的动摩擦力较小、刚度较大，符合工程设计的需要。研究结果为该型飞机操纵系统钢索滑轮组的设计改进提供工程依据。
In order to study the differences of dynamic friction characteristics between domestic rope pulley and imported rope pulley in certain aircraft control system ,and provide data support and engineering reference for the improvement of rope pulley design in the control system ,based on relevant domestic and abroad paper mate-rials and engineering practice ,the dynamic friction characteristics of imported rope pulley is analyzed ,which will be adopted in this control system .Applying basic principles of classical mechanics theory ,comparative a-nalysis of dynamic friction characteristics is made for the domestic rope pulley being used ,and using Labview software and spectral analysis software the test data is processed .Result shows that the dynamic friction of im-ported rope pulley is small ,and the stiffness is large ,which meets the requirements of engineering design .It provides the reference for improvement of the control system .

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汽车操纵稳定性试验和评价方法不能完全适用于多轴车辆，制定和完善多轴车辆的操纵稳定性试验方法具有现实意义。针对某前四轮转向四轴车辆，制定了操纵稳定性试验方案，进行了定半径稳态回转试验、蛇行试验和转向盘转角脉冲输入试验，对该车稳态与瞬态转向特性进行了评价，为多轴车辆操纵稳定性试验与评价的科学化与规范化奠定了基础。
Test and evaluation methods of automobile handling stability can not be fully applicable to multi -ax-le wheeled vehicle ,so establishing and improving handling stability testing methods of multi -axle vehicle are of practical significance .According to one four -axle vehicle , the testing methods of handling stability were made,the given radius steady -state circular test,pylon course slalom test and steering wheel angle pulse input test were carried out.Steady -state and transient steering characteristics of the vehicle were evaluated ,which laid the scientific and standardized foundation for multi -axle vehicle handling stability test and evaluation .

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车辆在高速行驶时，驾驶员和道路环境对车辆的操纵稳定性会有很大影响。考虑驾驶员特性和道路特性的人—车—路闭环系统更能评价车辆的操纵稳定性，采用“单点预瞄最优曲率”驾驶员模型和蛇行道路模型，在类菱形车二自由度模型的基础上构建了类菱形车闭环系统并进行了仿真分析。通过蛇行试验验证了类菱形车良好的操纵稳定性，并将试验结果与仿真结果进行了对比分析，分析表明，模型仿真结果与试验结果具有很好的一致性。
The driver and road environment had most influence on vehicle handling and stability,when vehicle was of high speed.The evaluation model of lateral dynamics with driver model of single point preview optimal curvature and road model of slalom based on driver-vehicle -road closed -loop system was built.It considered the influence of driver’s response.The slalom test suggested the rhombic vehicle has good handling and stability,and the comparison between the simulation of the driver-vehicle-road closed-loop model and the slalom test proved that the result has good consistency.

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建立了电动舵机的理想模型和详细模型,对舵机在正、反操纵力矩作用下的频率特性进行了理论分析与仿真研究,并对某型舵机在反操纵力矩作用下的性能进行了试验验证。结果表明:随着反操纵力矩负载的增大,电动舵机系统的谐振峰值增大,带宽变窄,稳定性和快速性均呈下降趋势。
The ideal model and particular model of an electromechanical actuator are established . The frequency performances of electromechanical actuator under the positive operating torque and reverse operating torque are studied on theoretical analysis and simulation .The performance validity test of an ac-tuator under the reverse operating is done .The result shows that with the increase of reverse operating torque , the resonance peak of electromechanical actuators enlarges , bandwidth becomes narrow , and so the stability and the speediness of electromechanical actuators become worse .

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为了研究高空远程滑翔UUV气动参数特性,运用计算流体动力学(computational fluid dynamics,CFD)理论,采用结构和非结构分域混合网格方案,确定计算域、边界条件、求解Navier-Stokes方程对亚音速下高空远程滑翔UUV三维绕流流场进行数值模拟。仿真数据与估算数据进行对比,分析UUV的纵向气动特性、横向气动特性和操纵导数特性,结果显示,仿真数据与计算数据吻合较好,并且其气动特性满足航行器的低阻特性和静稳定性的要求,两种计算方法的准确性进行了相互验证,不仅利于下一步进行航行器的操纵性、稳定性和弹道特性研究,而且为进一步完善设计和模型加工试验提供重要依据。
In order to study the pneumatic parameter characteristics of the high-altitude long-distance gliding UUV with computational fluid dynamics theory, we use the hybrid grid strategy, determine the computational domain and boundary conditions, solve the Navier-Stokes computation, and complete the three-dimensional subsonic flow field numerical simulation of the UUV. Comparing simulation results with estimation results ones, we analyze the longitu-dinal aerodynamic parameters, the lateral aerodynamic parameters and the manipulation derivatives. The results and their analysis show preliminarily that: ( 1 ) the calculated and simulated results are consistent; ( 2 ) aerodynamic characteristics meet the requirements of the low draft characteristic and the static stability of the UUV. The two methods give consistent results;they not only facilitate studying the maneuverability, stability and ballistic charac-teristics of the UUV, but also provide an important basis for improving the designs and

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为提高某型直升机飞行模拟器操纵系统操纵力感逼真度，将直升机操纵系统分布参数分段集中化处理，利用最小二乘参数估计法得到其线性模型，并以纵向通道为例建立了杆力．位移模型和电动力伺服加载系统模型。将模型应用于某型直升机飞行模拟器并进行力感试验，试验结果表明，所建立的杆力．位移模型与实装飞机力感特性相吻合，充分证明了杆力．位移模型的有效性，该模型已成功地应用于某型直升机飞行模拟器操纵负荷系统。
To improve the force-sense fidelity of control loading system for a certain type of helicopter flight simulator, the heli-copter distributed system parameters are centralized, and the linear model is built with the Least-Square estimation method (LS). Taking longitudinal channel as an example, the pole force-displacement mathematical model and electro-servo loading system model are built. The model is applied to a type of helicopter and it makes force-sense experimental flight, the results show that force-displacement model meets with the real flight force-sense characteristics and its validity is proved, the model is successfully applied to a type of flight simulator control loading system.

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为了解决翼伞空投系统在实际工程中航迹跟踪操纵频繁问题，提出一种基于模糊逻辑的航迹跟踪控制算法。首先，建立翼伞系统的运动模型，根据操纵特性设计飞行控制方案，控制信号操纵翼伞左右伞绳的下拉、保持和回复操作，实现系统对指定航迹的跟踪。其次，仿真了相关因素对控制性能的影响。仿真结果表明：该模糊控制方法简单有效，易于实现，解决了翼伞航迹跟踪时操纵频繁问题，完全满足航迹跟踪的要求。
In order to solve the problem of frequent manipulation when parafoil airdrop system is tracking a trajectory in actual engineering, presents a fuzzy logic-based tracking control algorithm. First, the motion model of parafoil system was established, flight control scheme was developed based on the handling characteristic, and the control signals manipulate the left and right sides suspension line of parafoil into the drop-down, maintain and/or reset operation. As a result, system can track the authorized path. Secondly, the influence of the interrelated factors to control performance were simulated. Simulation results show that: the fuzzy control method is simple and effective, easy to implement, solves the problem of frequent manipulation of suspension line during path tracking, fully meetting the requirements of path tracking.

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